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
1997020600181	19970206	00181	EU  	1997	2	6	19735            	1	19970115	G	2510	Z00N6068707220	BELT FITTING    			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										CREW SEATS	CORRODED        	B		A	VDNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	113J	900  				606				FOUND BOTH CREW SEAT BELTS' ALUMINUM FITTINGS (ATTACHED TO SEAT BELT WEB) COMPLETELY CORRODED THROUGH.  FITTINGS ARE MAD	E OF ALUMINUM, AND ARE ATTACHED TO AIRFRAME.  (X)					1	L	7	1 	30			NT	A51EU   					 
2001041700092	20010417	00092	CE  	2001	4	17	20010417AP001    	1	19970525	G	3411		KNOB            			CESSNA	182   	182Q        	2072732	CE  										COCKPIT	BACKED OUT      	C				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	4673N	1100 				18266848				CLIMBING VFR OUT OF KLAS, NOTED VVI AND AIRSPEED INDICATING ZERO, AND ALTIMITER FROZEN.  PULLED ALTERNATE STATIC KNOB AN	D INDICATIONS RETURNED TO NORMAL.  AFTER LANDING, FOUND RUBBER TRIM PIECE AROUND ALTERNATE STATIC KNOB HAD COME UNGLUED 	FROM METAL MOUNTING BRACKET.  THIS TRIM HUNG ON THE KNOB UNTIL IT VIBRATED THE KNOB OUT TO AN INTERMEDIATE POSITION THAT	 BLOCKED BOTH STATIC SOURCES.  THE LOOSE TRIM DID NOT INTERFERE WITH ALTERNATE STATIC USE, BUT IF THE KNOB WAS PUSHED BA	CK IN, THE TRIM WOULD VIBRATE THE KNOB BACK OUT.  HAD MECHANIC SECURE TRIM PIECE.		1	H	7	1 	3O			NT	3A13    					 
2001103100122	20011031	00122	GL  	2001	10	31	2001FA0000435    	3	19971024	G	6114	1A103	HUB             													MCAULY	1A103	1A103TCM    	GL  	PROPELLER ASSY	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								R774521		UPON INSPECTION PROPELLER HUB WAS FOUND TO BE CRACKED AT MOUNTING BOLT HOLD.  PROPELLER HAS BEEN SCRAPPED.																5	N	P50GL	 
2001103100123	20011031	00123	GL  	2001	10	31	2001FA0000436    	3	19970909	G	6114	D6603C88	HUB             													MCAULY	3A32C	D3A32C88    	GL  	PROPELLER ASSY	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								772394		UPON INSPECTION HUB WAS FOUND TO BE CRACKED IN BLADE SOCKET NR 2.  HUB HAS BEEN SCRAPPED.																5	C	P21EA	 
1997061900459	19970619	00459	GL  	1997	6	19	97031300148      	1	19970221	G	6100		BLADE           			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  										PROPELLER	SEPARATION      	H				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	11	29TM					729				WHILE IN STABLE FLIGHT AT 7,500 FEET MSL IN SMOOTH AIR, PART OF THE WOODEN PROPELLER CAME APART.  THE SEPARATION OCCURRE	D LENGTHWISE DOWN ONE BLADE OF THE TWO-BLADED PROPELLER.  THERE WERE NO SIGNS OF BIRDS PRIOR TO THE SEPARATION NOR WERE 	THERE ANY SIGNS OF AN OBJECT STRIKING THE PROPELLER.  THE BREAKAGE OCCURRED LENGTHWISE DOWN THE BLADE MIDWAY BETWEEN THE	 LEADING AND TRAILING EDGES.  THE BREAK DID NOT FOLLOW ALONG ANY LAMINATED PIECES OF WOOD.  (X)			1	M	7	1 	3O			RT	EXPA1M71					 
1997061900460	19970619	00460	SO  	1997	6	19	97031300233      	2	19970219	G	8550	CH48109	FILTER          	CHAMPION    		AMTR  	STRDST	STARDUSTR300		GL  	CONT  	E225  	E225*       	17015	SO  					ENGINE OIL	BURST           	H				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			WP	27	7989					476	2582D			OIL FILTER BURST AT START-UP.  GASKET FORCED FROM GROOVE.  ENGINE LOST ALL OIL.  FILTER 'DOMED OUT' AT BOTH ENDS.  ALL O	IL PASSAGEWAYS IN ENGINE AND OIL COOLER OK.  PRESSURE RELIEF VALVE IN ENGINE OK.  SUSPECT FILTER BYPASS.					1	Q	7	1 	3O	3	O		EXPA1Q71	E267				 
1997041000432	19970410	00432	NE  	1997	4	10	970326           	2	19970313	G	7230	384347	AIR SEAL        								PWA   	JFTD12	JFTD12A5A   	52047	NE  					7TH STAGE REAR	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09			1537 				677775			ON MARCH 13, 1997, COMPRESSOR ASSY S/N 677775 WAS SCHEDULED FOR AN OVERHAUL, W.O. NR 25419.  TEAR DOWN WAS COMPLETED ON 	MARCH 14, 1997, WITH NO PROBLEMS.  THE AIR SEAL ON THE REAR OF THE 7TH STAGE DISK WAS NOTED TO  HAVE A CRACK COMPLETELY 	THROUGH IT AND ANOTHER CRACK HALF-WAY THROUGH APPROXIMATELY 130 DEGREES FROM THE FIRST CRACK.  SIGNS OF AIR SEAL RUBBING	 WERE NOTED OVER A 2 INCH LONG AREA ON THE ADJACENT PART.  THE AIR SEAL EXHIBITED OVERHEAT DAMAGE FROM RUBBING 360 DEGRE	ES AROUND ITS EDGE.  (X)							4	U			E15EA				 
1997042400898	19970424	00898	NE  	1997	4	24	970401           	2	19970414	G	7230	536210	TAB LOCK        								PWA   	JFTD12	JFTD12A4A   	52047	NE  					COMP BLADE	MISSING         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2FOR	2998 					672538			TAB LOCK FOUND MISSING WHEN ENGINE DISASSEMBLED.  NO CONTACT NOTED BETWEEN BLADE AND 3RD STAGE STATOR.  BROKEN PIECES OF	 THE TAB LOCK CONTACTED BLADES AND STATORS AFT OF THE 3RD STAGE CAUSING IMPACT DAMAGE.  ENGINE WAS LAST OVERHAULED BY PR	ATT AND WHITNEY.  (X)									4	U			E15EA				 
1998040800080	19980408	00080	NM  	1998	4	8	97UAL900850      	1	19971202	G	2820	343T00123	TUBE ASSY       			BOEING	767   	767222      	1385122	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					RIB 3	DAMAGED         	A				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	29	610UA					21871				CENTER  TANK WENT FROM 300 INDICATED TO 1200 IN IST 1.5 HOURS OF FLIGHT.  WHEN MAINS BELOW HALF, SCAVENGED BACK TO ZERO.	  *S/D*  THIS PROBLEM WAS CAUSED BY TWO MINOR LEAKS TO THE CENTER FUEL TANKS.  ONE WAS A LEAKY COUPLING ON THE FUEL SCAV	ENGE PLUMBING IN THE CENTER TANK.  THE O-RING WAS REPLACED AND THE COUPLING WAS RESECURED AND SAFETIED.  THE SECOND WAS 	CAUSED BY A DAMAGED RT SURGE TANK DRAIN LINE.  THE DAMAGE WAS LOCATED ON TUBE ASSY PN 343T0012-3 LOCATED JUST OUTBOARD O	F RIB 3.  THE DAMAGE TO THE TUBE WAS CAUSED FROM CONTACT WITH A HI-LOK COLLAR ON AN ADJACENT STRINGER.  THE TUBE WAS REP	AIRED PER GN/MM7-0-4-9.	2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
1997092500423	19970925	00423	NE  	1997	9	25	97ZZZM968        	2	19970809	G	7250	3040911	TURBINE         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	FAILED          	A		A	AMWA	J	E			DUMP FUEL               	ENGINE SHUTDOWN         			O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	07	182YV					UE182	114401			IN MCI, THE RIGHT ENGINE HAD A CONTAINED ENGINE FAILURE DURING START.  REMOVED AND REPLACED RIGHT ENGINE GAS GENERATOR A	ND POWER SECTION.  TEAR DOWN INSP REVEALED THE COMPRESSOR TURBINE CENTER BOLT AND KEY WASHER WAS NOT SUFFICIENTLY LUBRIC	ATED AT INSTALLATION.  AS A RESULT, WHEN THE CT BOLT WAS TORQUED A FALSE TORQUE READING WAS INDICATED.  THIS ALLOWED THE	 COMPRESSOR TURBINE TO COME LOOSE AND PULL FORWARD INTO THE POWER TURBINE VANE RING.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1997092500432	19970925	00432	CE  	1997	9	25	97ZZZM977        	1	19970628	G	5753	3516505030	BRACKET         			BEECH 	1900  	1900D       	1154162	CE  										LT TE FLAP	WORN            	A			AMWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	182YV	4100 				UE182				AT ICT OVERNIGHT MAINTENANCE INSPECTION PER BEECH TEMP REV 5-6, FOUND LHOB FLAP.  INBOARD ATTACH BRACKET WORN.  REMOVED 	AND REPLACED ATTACH BRACKET IAW SRM 57-00 AND 51-40.					2	L	7	2 	4T			RT	A24CE   					 
1997031300147	19970313	00147		1997	3	13	97ZZZX1009       	1	19970219	G	3411	1J47	FILTER          																	PNEU AIR	BLOCKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11										PRIOR TO INSTALLATION ON AIRCRAFT, BLEW THROUGH FILTER TO CHECK FOR OBSTRUCTIONS AND FREEDOM OF AIR MOVEMENT.  FILTER AP	PEARED TO BE BLOCKED.  DISASSEMBLED FILTER AND FOUND MATERIAL THAT IS USED TO GLUE ELEMENT IN FILTER BLOCKING HOLE.																		 
1997031300148	19970313	00148	GL  	1997	3	13	97ZZZX1010       	1	19970221	G	6100		BLADE           			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  										PROPELLER	SPLIT           	H				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	11	29TM					729				WHILE IN STABLE FLIGHT AT 7,500 FEET MSL IN SMOOTH AIR, PART OF THE WOODEN PROPELLER CAME APART.  THE SEPARATION OCCURRE	D LENGTHWISE DOWN ONE BLADE OF THE TWO-BLADED PROPELLER.  THERE WERE NO SIGNS OF BIRDS PRIOR TO THE SEPARATION NOR WERE 	THERE ANY SIGNS OF AN OBJECT STRIKING THE PROPELLER.  THE BREAKAGE OCCURRED LENGTHWISE DOWN THE BLADE MIDWAY BETWEEN THE	 LEADING AND TRAILING EDGES.  THE BREAK DID NOT FOLLOW ALONG ANY LAMINATED PIECES OF WOOD.			1	M	7	1 	3O			RT	EXPA1M71					 
1997031300149	19970313	00149	SO  	1997	3	13	97ZZZX1011       	1	19970215	G	3234		SELECTOR        			PIPER 	PA31  	PA31310     	7103103	SO  										GEAR HANDLE	MISRIGGED       	D		A		O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			NM	11	27518					317812038				UPON LANDING, NOSE GEAR COLLAPSED DOING SUBSTANTIAL DAMAGE TO THE AIRCRAFT.  INSPECTION OF THE GEAR SELECTOR HANDLE FOUN	D INSTRUMENT PANEL SHOCK MOUNT SCREW HITTING GEAR SELECTOR HANDLE WHEN SELECTING GEAR DOWN POSITION.  ALSO, FOUND CABLE 	HAD BEEN MISRIGGED.  AFTER REMOVING SCREW FROM PANEL AND RE-RIGGING CABLE GEAR, SELECTOR OPERATED FLAWLESSLY.				1	L	7	1 	3O			RT	A20SO   					 
1997031300150	19970313	00150	CE  	1997	3	13	97ZZZX1012       	1	19970126	G	3260	16936002547	BRACKET         		M24R        	BEECH 	23    	B24R        	1151253	CE  										NLG LIMIT SWITCH	DEFECTIVE       	G		A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	03	6570R	1302 				MC298				DURING TAXI AFTER LANDING, THE NOSE GEAR COLLAPSED.  INVESTIGATION DISCLOSED THE BRACKET WHICH HOLDS THE NOSE GEAR DOWN,	 LIMIT SWITCH WAS ELONGATED AT THE POINT WHERE THE BRACKET MOUNTS TO THE NOSE GEAR ASSEMBLY.  THIS CONDITION ALLOWED THE	 LIMIT SWITCH TO GIVE A FALSE DOWN AND LOCKED INDICATION.  IT IS RECOMMENDED A SECURITY CHECK IN ADDITION TO A VISUAL AN	D OPERATIONAL CHECK BE MADE OF ALL LIMIT SWITCHES.			1	L	7	1 	3O				A1CE    					 
1997031300151	19970313	00151	SO  	1997	3	13	97ZZZX1013       	1	19970217	G	3230	454656	BREAKER         			PIPER 	PA31  	PA31350     	7103110	SO  										GEAR SAFETY	INTERMITTENT    	B			IGXR	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			NE	05	771A					317852027				LANDNG GEAR HANDLE DID NOT RETURN TO 'DOWN NEUTRAL' AFTER GEAR EXTENSION.  TROUBLE WAS TRACED TO A CIRCUIT BREAKER LABEL	ED 'GEAR SAFETY SOLENOID'.  THIS BREAKER SUPPLIES THE SAFETY SYSTEM AS WELL AS THE INDICATION LIGHTS AND THE DOOR SOLENO	ID ON THE POWER PACK.  THE BREAKER WAS FOUND WITH INTERNAL RESISTANCE CAUSING IT TO BE INTERMITTENT.  AIRFRAME TT 5,662.	00 HOURS.  PART TT UNKNOWN.			1	L	7	2 	3O				A20SO   					 
1997031300153	19970313	00153	NE  	1997	3	13	97ZZZX1015       	2	19970207	G	7200		ENGINE          			AMD   	FALC20	FALCON20F5  	2730105	EU  	GE    	CF700 	CF7002D2    	30010	NE  					NR 2	POWER LOSS      	B		A	YL1R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	11	108BG		2730 			403	E304495B			PILOT NOTES:  AFTER RE-FUEL, THE ACFT LOST PWR ON T/O APPROX 200 FEET AGL.  NR 2 ENG EGT WENT RED LINE APPROX 780 DEGREE	S FAHRENHEIT AND RPM HAD ROLL BACK.  A POP WAS HEARD IN THE CABIN BY PASSENGERS.  (POSSIBLE COMPRESSOR STALL).  PILOT WE	NT TO FLT IDLE WITH NR 2 THROTTLE.  THE ENG CONTINUED TO TURN AND PARAMETERS FOR ENGINE READINGS RETURNED TO NORMAL FOR 	FLT IDLE.  THE AIRCRAFT RETURNED TO AIRPORT FOR SAFE LDG.  EXTERIOR VISUAL AND INTERIOR BORESCOPE ON THE ENG DID NOT SHO	W ANY MAJOR DAMAGE THAT WOULD CAUSE LOSS OF PWR, ADDITIONAL GROUND RUNS, LOW PWR, HIGH PWR, AND RAPID ACC TEST WERE NORM	AL.  CAUSE FOR PWR LOSS UNK.  FUEL FILTERS CK OK.  PART TOTAL CYCLES, 6518.	2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
1997031300159	19970313	00159	CE  	1997	3	13	97ZZZX1021       	1	19970201	G	5240		DOOR            			LEAR  	60    	60LEAR      	5170707	CE  										FUEL SERVICE	WATER LEAK      	B		A	TR1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	5003X					039				THE DESIGN OF THE FUEL SERVICE PANEL AND DOOR DOES NOT PREVENT WATER FROM ENTERING THE DOOR AND COLLECTING AT THE BOTTOM	 OF THE PANEL.  THERE IS NO DRAIN HOLE.  THIS IS A POTENTIAL CORROSION PROBLEM. THREE MODEL 60'S WERE LOOKED AT.  ALL TH	REE ARE THE SAME DESIGN.				2	L	7	2 	4F			RT	A10CE   					 
1997031300160	19970313	00160	CE  	1997	3	13	97ZZZX1022       	1	19970220	G	2840		INDICATOR ASSY  			BEECH 	100   	B100        	1152919	CE  										FUEL QUANTITY	BRACKET CORRODED	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	4004C	9007 				BE12				PILOTS STATED FUEL INDICATION WAS SOME TIMES UNRELIABLE.  REMOVED FUEL INDICATOR PANEL AND FOUND CORROSION ON BRACKET TH	AT SERVES AS MOUNT FOR FUEL INDICATOR DIODES.  SUSPECT THAT CORROSION ALLOWED A GROUND TO DIODES.  (DIODES ARE NORMALLY 	INSULATED FROM BRACKET). THIS BRACKET IS DIRECTLY UNDER THE PILOTS VENT WINDOW.  SUSPECT MOISTURE FROM LEAKING WINDOW SE	AL CAUSED CORROSION.  CORROSION WAS CLEANED FROM BRACKET.  NEW INSULATORS INSTALLED.  SYSTEM FUNCTIONS NORMALLY.			1	L	7	2 	4T				A14CE   					 
1997031300161	19970313	00161	NM  	1997	3	13	97ZZZX1023       	1	19970129	G	5753	69207737	FITTING         		65216329    	BOEING	727   	72730C      	1384009	NM  										WS 144-204 TE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					374					FOUR EACH FITTINGS, P/N 69-20773-7, LOCATED BETWEEN THE CENTER TWO AFT FLAP TRACKS ARE CRACKED AT THE LOWER FLANGE OF TH	E FITTINGS.  CRACKS RANGE FROM 1 INCH TO 6 INCHES DOWN THE LOWER FLANGE.  SUSPECT CAUSE WOULD BE EXCESSIVE BOWING OF THE	 MID-FLAP.				2	L	7	3 	4F				A3WE    					 
1997031300162	19970313	00162	GL  	1997	3	13	97ZZZX1024       	2	19970217	G	7261	6871311	TUBE            								ALLSN 	250C  	250C20      	03013	GL  					BEARING OIL	CRACKED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										DURING OVERHAUL OF THE TURBINE, FOUND THE BEARING OIL TUBE TO HAVE A CRACK IN THE FLARE.											3	U			E4CE				 
1997031300163	19970313	00163	EU  	1997	3	13	97ZZZX1025       	1	19970212	G	2520		PANEL           			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										INTERIOR	CORRODED        	B		A	VDNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	113J	898  				606				DURING ROUTINE INSPECTION, FOUND INTERIOR ALUMINUM TRIM PANELS CORRODED AT ALL AREAS WHERE ANY STEEL PARTS, I.E., SCREWS	, BOLTS, ETC., OR ADJACENT ALUMINUM STRUCTURE WAS MAKING CONTACT WITH THE TRIM PANELS.  SUSPECT THAT THE FABRIC ATTACHED	 TO THE TRIM PANELS HAD BEEN FIREPROOFED WITH 'SALT BRINE SOLUTION' OR EQUIVALENT; CAUSING THE REPEATED HEAVY CORROSION 	FOUND ON ALL TRIM PANELS.			1	L	7	1 	30			NT	A51EU   					 
1997031300164	19970313	00164	CE  	1997	3	13	97ZZZX1026       	1	19970211	G	2133		VALVE           			BEECH 	200   	200BEECH    	1152920	CE  										OUTFLOW SAFETY	CLAMP DEFECTIVE 	B			VDNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	122RF	3406 				BB122				PILOT REPORTED THAT CABIN PRESSURIZED ON GROUND.  FOUND VACUUM HOSES TO OUTFLOW AND SAFETY VALVES HAD DEFECTIVE HOSE CLA	MPS.  REPLACED CLAMPS, OPS CHECK SATISFACTORY.					1	L	7	2 	4T				A24CE   					 
1997031300165	19970313	00165	CE  	1997	3	13	97ZZZX1027       	1	19970224	G	7830	45122704	BEAM            		660828110   	LEAR  	55    	55LEAR      	5170702	CE  										THRUST REV LT	CORRODED        	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	2FOR	4437 			0518	022				DURING 600-HOUR INSPECTION, FOUND INTERGRANULAR CORROSION OF BEAM AROUND NAS1154C5 ATTACH SCREW.  BOTH OUTBOARD BEAMS OF	 THRUST REVERSERS HAD THIS CORROSION.  BEAM IS EXTRUDED ALUMINUM.  LEARJET RECOMMENDS BEAM REPLACEMENT.  PART TOTAL CYCL	ES, 2,933.				2	L	7	2 	4F				A10CE   					 
1997031300166	19970313	00166	CE  	1997	3	13	97ZZZX1028       	1	19970224	G	7830	45122703	BEAM            		660828119   	LEAR  	55    	55LEAR      	5170702	CE  										THRUST REV RT	CORRODED        	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	VRBOL	4437 			0519	022				DURING 600-HOUR INSPECTION, FOUND INTERGRANULAR CORRROSION OF BEAM AROUND NAS1154C5 ATTACH SCREW.  BOTH OUTBOARD BEAMS O	F THRUST REVERSERS HAD THIS CORROSION.  BEAM IS EXTRUDED ALUMINUM.  LEARJET RECOMMENDS BEAM REPLACEMENT.  PART TOTAL CYC	LES, 2,933.				2	L	7	2 	4F				A10CE   					 
1997031300167	19970313	00167	CE  	1997	3	13	97ZZZX1029       	1	19970211	G	3233	1153800025	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  										MLG GEARBOX	DEFECTIVE       	B			VDNR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	09	122RF	3406 	200  		2073	BB122				PILOT REPORTED HE HAD GEAR UNSAFE LIGHT AND GEAR WOULD NOT RETRACT OR EXTEND.  FOUND GEAR GEARBOX MOTOR DEFECTIVE.  REPL	ACED WITH NEW, RETRACT CHECKED SEVERAL TIMES IN NORMAL AND EMERGENCY MODES, SATISFACTORY.					1	L	7	2 	4T				A24CE   					 
1997031300168	19970313	00168	EA  	1997	3	13	97ZZZX1030       	1	19970211	G	3234	600509677	CONTROL         			CNDAIR	CL600 	CL6002B16   	1900305	EA  										MLG	BINDING         	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	25	1812C	4494 			206	5010				IN-FLIGHT EXPERIENCED:  UNABLE TO RAISE LANDING GEAR HANDLE TO UP POSITION.  TELESCOPING FUNCTION BINDING.						2	L	7	2 	4F			RT	A21EA   					 
1997031300169	19970313	00169	CE  	1997	3	13	97ZZZX1031       	1	19970220	G	3340	90033	BEACON          	WHELEN      		BEECH 	B300  	B300        	1159232	CE  										STROBE	NOISY           	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	202PV					FL50				THE FLASHING BEACON INSTALLATION IS CAUSING ELECTRONIC 'NOISE' IN THE STORMSCOPE EVEN AFTER FOLLOWING 3M INSTRUCTIONS FO	R INSTALLATION.  BEACON NEEDS A SB FOR AN APROVED ALTERATION TO ELIMINATE THE 'NOISE'.					2	L	7	2 	4T			RT	A24CE   					 
1997031300170	19970313	00170	CE  	1997	3	13	97ZZZX1032       	1	19970220	G	3340	90033	BEACON          	WHELEN      		BEECH 	90    	C90A        	1152911	CE  										STROBE	NOISY           	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	3242L					LJ1413				THE FLASHING BEACON INSTALLATION IS CAUSING ELECTRONIC 'NOISE' IN THE STORMSCOPE EVEN AFTER FOLLOWING 3M INSTRUCTIONS FO	R INSTALLATION.  BEACON NEEDS A SB FOR AN APPROVED ALTERATION TO ELIMINATE THE 'NOISE'.					1	L	7	2 	3T			RT	3A20    					 
1997031300171	19970313	00171	CE  	1997	3	13	97ZZZX1033       	1	19970225	G	5751		AILERON         			CESSNA	500   	560CESSNA   	2076750	CE  										WING TO AILERON	CHAFING         	B		A	CNQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	344QS					5600344				AFTER A CONTINUOUS INSPECTION PHASE 1-5 WAS C/W, THE AIRCRAFT WAS RELEASED FOR A MAINTENANCE CHECK FLIGHT.  A POST-FLIGH	T SQUAWK WAS WRITTEN 'ON TEST FLIGHT, AILERONS FEEL LIKE THEY HAVE A CATCH GOING FROM LEFT BANK TO RIGHT BANK'.  ON POST	 INSPECTION FOUND A MS27039-807 SCREW WAS CHAFING BETWEEN AILERON AND THE WING.  SUBMITTER SUGGESTS ADDING TO MAINTENANC	E RELEASE SHEET TO CHECK AILERON AIR CAP SEALS FOR FOREIGN OBJECTS PRIOR TO RELEASE.			2	L	7	2 	4F			RT	A22CE   					 
1997031300172	19970313	00172	SO  	1997	3	13	97ZZZX1034       	1	19970211	G	2434	1159SCAV373103	ALTERNATOR      			GULSTM	G1159 	GIV         	3980115	SO  										LT ENGINE	FAILED          	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	25	399CC		366  		456	1051				IN-FLIGHT EXPERIENCED LT AD/DC POWER FAILURE AND RETURNED TO KEWR.  REMOVED AND REPLACED DEFECTIVE LT ALTERNATOR.						2	L	7	2 	4F			RT	A12EA   					 
1997031300173	19970313	00173	SO  	1997	3	13	97ZZZX1035       	1	19970211	G	2420	1159SCAV373509	CONVERTER       			GULSTM	G1159 	GIV         	3980115	SO  										LT AC/DC	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	399CC		209  		269	1051				IN-FLIGHT EXPERIENCED LT AC/DC POWER FAILURE AND RETURNED TO KEWR.  REMOVED AND REPLACED DEFECTIVE LT CONVERTER.						2	L	7	2 	4F			RT	A12EA   					 
1997031300174	19970313	00174	EA  	1997	3	13	97ZZZX1036       	1	19970224	G	2820	6006286151	LINE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  										AUX TANK XSFER	LEAK            	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	733CF	2134 				5057				DRY ROTTING OF FUEL TRANSFER LINE FROM FORWARD FUSELAGE FUEL TANK TO WING AUXILIARY TANK.  FUEL LEAK INTO THE SHROUDS AN	D INTO AIRSPACE OF DOUBLE WALL TANK IN CABIN.  (LOWER FUSELAGE).					2	L	7	2 	4F			RT	A21EA   					 
1997031300175	19970313	00175	CE  	1997	3	13	97ZZZX1037       	1	19970205	G	3234	1013841379	SELECTOR        			BEECH 	200   	B200        	1152922	CE  										MLG	INTERMITTENT    	B			HBKR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	11	77HD					BB1397				LANDING GEAR DID NOT EXTEND WHEN GEAR HANDLE WAS SELECTED DOWN.  FOUND GEAR SELECTOR ASSEMBLY INTERMITTENT.  INSTALLED N	EW GEAR SELECTOR ASSEMBLY; GEAR SYSTEM OPERATIONAL CHECK OK.					1	L	7	2 	4T				A24CE   					 
1997031300176	19970313	00176	NE  	1997	3	13	97ZZZX1038       	2	19970219	G	7230	817401	HUB             								PWA   	JT8   	JT8D9A      	52048	NE  					FRONT COMPRESSOR	DAMAGED         	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		10797			P243242					FRONT COMPRESSOR FRONT HUBS WERE RECEIVED FOR SCHEDULED OVERHAUL.  HUBS WERE INSPECTED PER INSP 01, JT8D ENGINE MANUAL 4	81672, SECTION 72-33-31.  MINOR DAMAGE OBSERVED ON BLADE SLOT PRESSURE FACES.  NO DAMAGE OR BLENDING ALLOWED IN THIS ARE	A.									4	F			E2EA				 
1997031300177	19970313	00177	NE  	1997	3	13	97ZZZX1039       	2	19970219	G	7230	817401	HUB             								PWA   	JT8   	JT8D9A      	52048	NE  					FRONT COMPRESSOR	DAMAGED         	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		9991 			R12135					FRONT COMPRESSOR FRONT HUBS WERE RECEIVED FOR SCHEDULED OVERHAUL.  HUBS WERE INSPECTED PER INSP 01, JT8D ENGINE MANUAL 4	81672, SECTION 72-33-31.  MINOR DAMAGE OBSERVED ON BLADE SLOT PRESSURE FACES.  NO DAMAGE OR BLENDING ALLOWED IN THIS ARE	A.									4	F			E2EA				 
1997031300178	19970313	00178	NE  	1997	3	13	97ZZZX1040       	2	19970219	G	7230	817401	HUB             								PWA   	JT8   	JT8D9A      	52048	NE  					FRONT COMPRESSOR	DAMAGED         	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		17861			M07042					FRONT COMPRESSOR FRONT HUBS WERE RECEIVED FOR SCHEDULED OVERHAUL.  HUBS WERE INSPECTED PER INSP 01, JT8D ENGINE MANUAL 4	81672, SECTION 72-33-31.  MINOR DAMAGE OBSERVED ON BLADE SLOT PRESSURE FACES.  NO DAMAGE OR BLENDING ALLOWED IN THIS ARE	A.									4	F			E2EA				 
1997031300179	19970313	00179	NE  	1997	3	13	97ZZZX1041       	2	19970219	G	7230	817401	HUB             								PWA   	JT8   	JT8D9A      	52048	NE  					FRONT COMPRESSOR	DAMAGED         	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		10878			P24455					FRONT COMPRESSOR FRONT HUBS WERE RECEIVED FOR SCHEDULED OVERHAUL.  HUBS WERE INSPECTED PER INSP 01, JT8D ENGINE MANUAL 4	81672, SECTION 72-33-31.  MINOR DAMAGE OBSERVED ON BLADE SLOT PRESSURE FACES.  NO DAMAGE OR BLENDING ALLOWED IN THIS ARE	A.									4	F			E2EA				 
1997031300180	19970313	00180	NE  	1997	3	13	97ZZZX1042       	2	19970219	G	7230	817401	HUB             								PWA   	JT8   	JT8D9A      	52048	NE  					FRONT COMPRESSOR	DAMAGED         	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		6382 			S13547					FRONT COMPRESSOR FRONT HUBS WERE RECEIVED FOR SCHEDULED OVERHAUL.  HUBS WERE INSPECTED PER INSP 01, JT8D ENGINE MANUAL 4	81672, SECTION 72-33-31.  MINOR DAMAGE OBSERVED ON BLADE SLOT PRESSURE FACES.  NO DAMAGE OR BLENDING ALLOWED IN THIS ARE	A.									4	F			E2EA				 
1997031300181	19970313	00181	NE  	1997	3	13	97ZZZX1043       	2	19970219	G	7230	817401	HUB             								PWA   	JT8   	JT8D9A      	52048	NE  					FRONT COMPRESSOR	DAMAGED         	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		22446			M98582					FRONT COMPRESSOR FRONT HUBS WERE RECEIVED FOR SCHEDULED OVERHAUL.  HUBS WERE INSPECTED PER INSP 01, JT8D ENGINE MANUAL 4	81672, SECTION 72-33-31.  MINOR DAMAGE OBSERVED ON BLADE SLOT PRESSURE FACES.  NO DAMAGE OR BLENDING ALLOWED IN THIS ARE	A.									4	F			E2EA				 
1997031300182	19970313	00182	NM  	1997	3	13	97ZZZX1044       	1	19970211	G	2720	591005017	PCU             	PARKER      	591005017   	BOEING	727   	727222      	1384073	NM  										RUDDER	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3408					PLASTIC BLAST MEDIA WAS FOUND THROUGHOUT THE UNIT.  THE MAJORITY WAS FOUND IN THE PRESSURE AND RETURN FILTERS AND THE HY	DRAULIC SOLENOID VALVE, P/N 59600-5003, S/N G194.					2	L	7	3 	4F				A3WE    					 
1997031300227	19970313	00227	CE  	1997	3	13	97ZZZX1047       	1	19970225	G	3246	4040A	WHEEL           	PARKERHANFIN		CESSNA	335   	335         	2075601	CE  										RT MLG	BROKEN          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CE	09	2704N	4630 				3350003				ON LANDING ROLL OUT, PILOT NOTICED JERKING ACTION ON THE RT MLG.  AFTER PARKING AND FURTHER INVESTIGATION, REVEALED A 5 	TO 6 INCH CHUNK OF WHEEL GONE, AND TIRE RUBBING ON BRAKE ASSEMBLY.  SUSPECT HEAT FROM BRAKES HAS TRANSFERRED ENOUGH HEAT	 TO WEAKEN WHEEL TO POINT OF FAILURE.  SUBMITTER RECOMMENDED RUNNING WHEELS UNDER TIME LIMITS OF SOME SORT.				1	L	7	2 	3O				3A25    					 
1997031300229	19970313	00229	SO  	1997	3	13	97ZZZX1049       	2	19970127	G	8540	653583A	STARTER DRIVE   		646209TMD   	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					RT ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	411MZ	700  				421C1002	277166R			STARTER DRIVE GEAR WEAR UNACCEPTABLE IAW TELEDYNE CONTINENTAL CSB 94-4 EVEN THOUGH THE SERVICE KIT REQUIRED BY TCM CSB 9	4-4 HAD BEEN PREVIOUSLY INSTALLED AT ENGINE OVERHAUL.  SUBMITTER SUGGESTED CSB 94-4 MAY NOT BE SUFFICIENT.  RECOMMENDED 	FLEET DATA BE EXAMINATED TO DETERMINE NUMBER AND FREQUENCY OF OCCURRENCES.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997031300230	19970313	00230	CE  	1997	3	13	97ZZZX1050       	1	19970127	G	2750	500000862	CONTROL CABLE   			CESSNA	414   	414A        	2075907	CE  										FLAP EXTEND	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58H	5000 				414A0314				EXTREME CABLE WEAR (FLAP EXTEND) AT PULLEY ASSY JUST OUTBOARD OF THE FLAP MOTOR AND TRANSMISSION ASSY.  PULLEYS MUST BE 	REMOVED IN ORDER TO SEE THIS TYPE OF WEAR.  SUBMITTER RECOMMENDED 100 PERCENT INSPECTION OF FLAP CABLES (BY REMOVAL AND 	REPLACEMENT) AT 4,000 HOURS ACTT, AND 100 PERCENT INSPECTION AT EVERY 600 HOUR/1 YEAR THEREAFTER.				1	L	7	2 	3O			 	A7CE    					 
1997031300231	19970313	00231	SO  	1997	3	13	97ZZZX1051       	1	19970217	G	2824	4600	VALVE FITTING   			PIPER 	PA23  	PA23250     	7102308	SO  										FUEL CROSSFEED	CRACKED         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	63851	2700 				277854003				DURING ROUTINE MAINTENANCE, FOUND FUEL STAINS ON BELLY PAN.  REMOVED, FOUND FUEL CROSSFEED FITTING CRACKED AND LEAKING. 	 REMOVED AND DISASSEMBLED VALVE AND REDUCER, CRACKED AT CORNER OF HEX ALL THE WAY THROUGH AND OTHER CRACKS JUST ON INSID	E OF THREADS NOT ON OUTSIDE OF HEX.  THIS IS THE SAME ONE AS DESCRIBED IN AL43-16, ALERT 222, JANUARY, 1997.				1	L	7	2 	3O				1A10    					 
1997031300232	19970313	00232	CE  	1997	3	13	97ZZZX1052       	1	19970127	G	2750	500000862	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										FLAP EXTEND	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	746CA	4000 				421C1049				EXTREME CABLE WEAR (FLAP EXTEND) AT PULLEY JUST OUTBOARD OF THE FLAP MOTOR AND TRANSMISSION ASSY.  PULLEYS MUST BE REMOV	ED IN ORDER TO SEE THIS TYPE OF WEAR.  SUBMITTER RECOMMENDED 100 PERCENT INSPECTION OF FLAP CABLES (BY REMOVAL AND REPLA	CEMENT) AT 4,000 HOURS PLUS TT, AND 100 PERCENT INSPECTION AT 600-HOUR/1-YEAR CESSNA SPECIAL INSPECTION INTERVALS.				1	L	7	2 	3O			 	A7CE    					 
1997031300233	19970313	00233	SO  	1997	3	13	97ZZZX1053       	2	19970219	G	8550	CH48109	FILTER          	CHAMPION    		AMTR  	STRDST	STARDUSTR300		GL  	CONT  	E225  	E225*       	17015	SO  					ENGINE OIL	BURST           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	7989					476	2582D			OIL FILTER BURST AT START-UP.  GASKET FORCED FROM GROOVE.  ENGINE LOST ALL OIL.  FILTER 'DOMED OUT' AT BOTH ENDS.  ALL O	IL PASSAGEWAYS IN ENGINE AND OIL COOLER OK.  PRESSURE RELIEF VALVE IN ENGINE OK.  SUSPECT FILTER BYPASS.					1	Q	7	1 	3O	3	O		EXPA1Q71	E267				 
1997031300234	19970313	00234	NM  	1997	3	13	97ZZZX1054       	1	19970214	G	6230	A2035	YOKE            			ROBSIN	R22   	R22BETA     		NM  										SWASHPLATE	CRACKED         	B			WG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	8066U	1804 				1273				ON PRE-FLIGHT, ONE-HALF OF YOKE WAS FOUND CRACKED THROUGH.  LOW TIME, PILOT DID NOT REPORT ANY SUBSTANTIAL VIBRATION DUR	ING PREVIOUS FLIGHT.  SURROUNDING AREA HAS CORROSION.  DAMAGE DID NOT APPEAR TO HAVE BEEN CAUSED BY CORROSION.					1	G	7	1 	3O				H10WE   					 
1997031300237	19970313	00237	CE  	1997	3	13	97ZZZX1057       	1	19970227	G	3230	3581512545	RETRACT ROD     			BEECH 	58    	58TC        	1152746	CE  										LT RETRACT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	97R	2331 				TK45				DURING ANNUAL INSPECTION PERFORMING EMERGENCY EXTENSION, LOUD BANG HEARD.  UPON FURTHER INVESTIGATION, FOUND LEFT RETRAC	T ROD ASSY CRACKED ABOUT 8 INCHES OUTBOARD OF ACTUATOR.  ROD ASSY COMPLETELY FAILED ON NEXT RETRACTION NOT ALLOWING LEFT	 GEAR TO EXTEND OR RETRACT.  FAILURE PROBABLY DUE TO IMPROPER GEAR UPLOCK TENSION.				1	L	7	2 	3O				A23CE   					 
1997031300238	19970313	00238	SW  	1997	3	13	97ZZZX1058       	1	19970224	G	2822	14990019	PUMP            	DUKES       		MOONEY	M20   	M20F        	5870214	SW  										FUEL BOOST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	9339M				5280	670253				OPERATOR REPORTED THAT EMERGENCY ELECTRIC FUEL PUMP NO LONGER WORKED.  UPON REMOVAL AND REPLACMENT OF PUMP, DISCOVERED T	HE FAILED PUMP HAD BEEN IN SERVICE ON THE AIRCRAFT FOR 23 YEARS.  THESE PUMPS ARE STAMPED ON THE PUMP HOUSING TO REPLACE	 EVERY TEN YEARS.  TOTAL TIME ON THE PUMP IS UNKNOWN, HOWEVER, ACFT TT IS 2,665.0 HOURS.  SUBMITTER RECOMMENDED THIS SHO	ULD BE AN ITEM OF PARTICULAR ATTENTION DURING ANNUAL INSPECTIONS.			1	L	7	1 	3O				2A3     					 
1997031300239	19970313	00239	NE  	1997	3	13	97ZZZX1059       	2	19970218	G	7230	1B4790	STATOR VANE     			BOEING	757   	757*        		NM  	PWA   	2037  	PW2040      		NE  					HPC MODULE	FAILED          	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		16952					P726634			ENGINE WAS IN-FLIGHT, SHUT DOWN.  DISASSEMBLY INSPECTION REVEALED ONE LIBERATED 10TH STAGE STATOR VANE AT THE CONVEX END	 OF ONE QUADRANT AT 9:00.  THREE ADDITIONAL VANES IN THE SAME CLUSTER OF FIVE ARE FRACTURED THROUGH AT THE OUTSIDE DIAME	TER SHROUD VANE BRAZE FILLET.  METALLURIGCAL ANALYSIS OF THE 10TH STATOR AND 11TH BLADES IS BEING CONDUCTED BY PRATT AND	 WHITNEY MERL TO VERIFY FAILURE.			2	L	7	2 	4F	4	F	RT	A2NM    	E17NE				 
1997031300240	19970313	00240	NE  	1997	3	13	97ZZZX1060       	2	19970213	G	7230	AS3209011	O-RING          								PWA   	2037  	PW2037      		NE  					HPC MODULE	MISSING         	B			WA2D	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03		3992 	3992 				P727149			DISASSEMBLY INSPECTION OF HPC MODULE REVEALED O-RINGS, P/N AS3209-011, TO BE MISSING FROM THE 9TH STAGE VARI-VANE TRUNNI	ONS (ALL VANES).  THIS CONDITION WAS AN ORIGINAL MANUFACTURING ERROR.  MANUFACTURING ADVISED OF CONDITION.  NOTE:  THE A	BOVE CONDITION HAD NO BEARING ON ENGINE REMOVAL CAUSE.									4	F			E17NE				 
1997031300242	19970313	00242	CE  	1997	3	13	97ZZZX1061       	1	19970130	G	3260		SWITCH          			LEAR  	24    	24A         	5170304	CE  										MLG SQUAT	ICE PACKED      	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	63CK					119				LANDING GEAR WOULD NOT RETRACT AFTER DEPARTURE.  FOUND GEAR SQUAT SWITCHES FROZEN AND PACKED WITH ICE.  CLEANED GEAR OF 	ALL SNOW AND ICE, LUBED, AND PERFORMED SATISFACTORY OPERATIONAL CHECK.					2	L	7	2 	4J				A10CE   					 
1997031300244	19970313	00244	CE  	1997	3	13	97ZZZX1062       	1	19970220	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	B		A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	835MA	2963 				4410343				DURING A PHASE INSPECTION, FOUND A CRACK IN THE RT WING CANTED RIB TOP CAP.  CRACK STARTS AT AFT SIDE OF FORWARD WING SP	AR AND RUNS AFT PARALLEL TO THE BEND RADIUS, APPROXIMATELY 1 INCH IN LENGTH.  STOP-DRILLED ENDS OF CRACK PER CESSNA INST	RUCTIONS.				1	L	7	2 	3T			RT	A28CE   					 
1997031300245	19970313	00245	EA  	1997	3	13	97ZZZX1063       	2	19970224	G	8530	05K21103	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					EXHAUST VALVES	DETERIORATED    	B			RH6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4635L	50   				15284201				INSTALLED 4 NEW CYLINDERS ON OVERHAULED ENGINE.  COMPRESSION LOSS STARTED AT ABOUT 300 HOURS THROUGH RINGS AND EXHAUST V	ALVE SEAT.  PULLED CYLINDERS, FOUND BADLY HEATED EXHAUST STEM AND EXHAUST SEAT.  EXHAUST VALVES ERODED AND BADLY PITTED.	  INSTALLED ADDITIONAL 4 NEW CYLINDERS ON 1-20-97 APPRXOIMATELY ONE MONTH AND 50 HOURS AND SAME PROBLEM.  OIL TEMP OK AN	D BAFFLES INSTALLED.  SUBMITTER STATED EXHAUST VALVE FAILURE IMMINENT.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997031300247	19970313	00247	EA  	1997	3	13	97ZZZX1065       	2	19970204	G	7414	ES103827901	COIL            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE MAGNETO	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	1401E	489  				17270986	L597976T			BENDIX MAGNETO OVERHAULED BY ELECTRO SYSTEMS, REPAIR STATION UT2R22GL.  MAGNETO WAS FURNISHED WITH LYCOMING FACTORY OVER	HAULED ENGINE IN 1995.  MAGNETO WAS REMOVED FOR 500-HOUR INSPECTION AND C/W AD 96-12-07 AT 489.3 SMOH FOR THE FIRST TIME	.  FOUND ONE EACH COIL P/N ES 10-382790-1 WITH MFG DATE 2/01/95 CRACKED IN 10 PLACES WITH CRACKS RADIATING OUTWARD FROM 	CENTER SUPPORTS AND BRUSH CONTACT TANG.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997031300248	19970313	00248	EA  	1997	3	13	97ZZZX1066       	2	19970130	G	7414	D4RN2021	MAGNETO         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					DISTRIBUTOR GEAR	TEETH MISSING   	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	1401E		489  			17270986	L597976T			BENDIX/TCM DUAL MAGNETO REMOVEDF FROM LYCOMING.  FACTORY OVERHAULED ENGINE AT SMOH 489.3 FOR 500-HOUR INSPECTION AND C/W	 AD 96-12-07.  FOUND MAGENTO DISTRIBUTOR GEARS WITH THREE TEETH MISSING FROM ONE GEAR AND ONE-HALF TOOTH MISSING FROM OT	HER GEAR.  CONTINUED OPERATION WOULD HAVE CAUSED CATASTROPHIC FAILURE.  THIS MAGNETO WAS OVERHAULED BY ELECTRO SYSTEMS I	N 1995 AND HAD AN ELECTRO SYSTEMS DATA PLATE AFFIXED TO MAGNETO.  THIS MAGNETO WAS INSTALLED AT LYCOMING OVERHAUL AND NE	VER REMOVED UNTIL SMOH 489.3.  RECOMMEND ALL MAGNETOS OVERHAULED BY ELECTRO SYSTEMS BE REMOVED AND INSPECTED IAW BENDIX 	OVERHAUL MANUAL.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997031300328	19970313	00328	GL  	1997	3	13	97ZZZX1078       	3	19970206	G	6114		HUB             													MCAULY	D3A34	D3A34C403   	GL  	PROPELLER	CORRODED        	B			TX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			398  					890579		PROPELLER WAS DUE RESEAL.  FOUND FACE OF HUB TO BE SEVERELY CORRODED OVER 60 PERCENT AT A DEPTH OF .008 INCH DEEP AND DE	EPER.  LAST OVERHAUL WAS 9-16-96 BY PRESCISION PROPELLER OUT OF TUSCALOOSA, AL.  DURING OVERHAUL, CORROSION WAS PROBABLY	 NOT REWORKED ALL THE WAY.														5	C	P47GL	 
1997031300329	19970313	00329	CE  	1997	3	13	97ZZZX1079       	1	19970129	G	2810	B1001421	CAP VENT        			CESSNA	150   	152         	2071835	CE  										FUEL TANK	FROZE           	G		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NE	03	67898					15282084				PREVIOUS DAY, ACCIDENT AIRCRAFT TIED DOWN ON OUTSIDE RAMP.  RAIN AND SNOW WITH ABOVE FREEZING TEMPS.  ICE NOT REMOVED FR	OM CAPS DURING FREEZING CONDITION THE NEXT DAY.  ICE FORMED IN VENT HOLES.  FUEL STARVATION DUE TO VACUUM AS FUEL CONSUM	ED CAUSED ENGINE FAILURE.  NEED BETTER METHOD TO KEEP STANDING WATER FROM FREEZING CLOGGING VENTS.				1	H	7	1 	3O			NT	3A19    					 
1997031300330	19970313	00330	SO  	1997	3	13	97ZZZX1080       	1	19970224	G	2910	AE7007422	LINE            			GULSTM	G1159 	G1159A      	3970109	SO  										LT ENG COWL	CHAFED          	B	P	A	RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7906G					497				AFTER THE LT ENGINE WAS REMOVED A VISUAL INSPECTION OF THE FIXED COWLING AREA, IT WAS NOTICED THAT A FIRE EXTINGUISHING 	DISCHARGE TUBE P/N 1159P20438-15 HAD A .75 INCH BY .25 INCH HOLE CHAFED INTO IT BY THE LT ENGINE HYDRAULIC LINE P/N AE70	0742-2.  THE LINE WAS ALSO CHAFED AND HAD FRAYED BRAIDS.  LOOKED AT A 2ND AIRCRAFT (S/N 389) AND FOUND SIMILAR CHAFE MAR	KS ON THE FIRE EXTINGUISHING TUBE AND ON THE SAME HYDRAULIC LINE, BUT, ALSO, FOUND SIMILAR CHAFE MARKS ON THE RETURN HYD	RAULIC AND BYPASS LINES THAT GO TO THE ENGINE HYDRAULIC PUMP.  THESE LINES WERE MISSING CLAMPS OR WERE IMPROPERLY CLAMPE	D TO PREVENT CHAFING ON THE EXTINGUISHER LINE.  REMOVED AND REPLACED LINES AND PROPERLY CLAMPED TO PREVENT CHAFING.	2	L	7	2 	4F				A12EA   					 
1997031300331	19970313	00331	SO  	1997	3	13	97ZZZX1081       	1	19970224	G	2620	1159P2043815	TUBE            			GULSTM	G1159 	G1159A      	3970109	SO  										LT ENG FIRE EXT	CHAFED          	B	P	A	RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7906G					497				AFTER THE LT ENGINE WAS REMOVED A VISUAL INSPECTION OF THE FIXED COWLING AREA, IT WAS NOTICED THAT A FIRE EXTINGUISHING 	DISCHARGE TUBE P/N 1159P20438-15 HAD A .75 INCH BY .25 INCH HOLE CHAFED INTO IT BY THE LT ENGINE HYDRAULIC LINE P/N AE70	0742-2.  THE LINE WAS ALSO CHAFED AND HAD FRAYED BRAIDS.  LOOKED AT A 2ND AIRCRAFT (S/N 389) AND FOUND SIMILAR CHAFE MAR	KS ON THE FIRE EXTINGUISHING TUBE AND ON THE SAME HYDRAULIC LINE, BUT, ALSO, FOUND SIMILAR CHAFE MARKS ON THE RETURN HYD	RAULIC AND BYPASS LINES THAT GO TO THE ENGINE HYDRAULIC PUMP.  THESE LINES WERE MISSING CLAMPS OR WERE IMPROPERLY CLAMPE	D TO PREVENT CHAFING ON THE EXTINGUISHER LINE.  REMOVED AND REPLACED LINES AND PROPERLY CLAMPED TO PREVENT CHAFING.	2	L	7	2 	4F				A12EA   					 
1997031300332	19970313	00332	CE  	1997	3	13	97ZZZX1082       	1	19970226	G	7820	075016161	MUFFLER         			CESSNA	185   	A185F       	2072821	CE  										BAFFLE CONE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7239E	2900 				18502642				MUFFLER REMOVED TO FACILITATE OTHER MAINTENANCE.  UPON REMOVAL, A VISUAL INSPECTION REVEALED A BAFFLE CONE WAS BROKEN AN	D A LARGE PORTION OF THE BAFFLE WAS MISSING.  SUBMITTER RECOMMENDED 100-HOUR INSPECTION INCLUDE THE USE OF A STRONG FLAS	HLIGHT AND A MIRROR BE USED IN THE LARGE EXHAUST STACK TO EXAMINE BAFFLE INTEGRITY.				1	H	7	1 	3O				3A24    					 
1997031300333	19970313	00333	CE  	1997	3	13	97ZZZX1083       	1	19970227	G	5553	04311489	FITTING         			CESSNA	150   	152         	2071835	CE  										VERT STAB	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	89301	5158 				15282706				INSPECTION FOUND VERTICAL STABILIZER ATTACH FITTING CRACKED ON LEFT SIDE OF ROOT AREA.  POSSIBLE CAUSE:  ATTEMPTING SNAP	 ROLLS IN A C-152.					1	H	7	1 	3O			NT	3A19    					 
1997031300334	19970313	00334	NM  	1997	3	13	97ZZZX1084       	1	19970225	G	5320	50534511	FITTING         			BOEING	707   	7073D3C     		NM  										BS 600K	CRACKED         	B	S		UGMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2FOR					20495				SEVEN INCH LONG CRACK LT TERMINAL FITTING LOWER FORWARD CARGO AREA BS 600K, WL 170, LBL 50, INTERIOR P/N 50-5345-11.  RE	F DWG. 50-2529 5H.3A ZNC2.  THE FOLLOWING A/C HAS THE SAME CRACKS IN THE SAME AREA FROM 3.8 INCHES LONG TO 8 INCHES LONG	.  BOEING 707-338C S/N 19296 N6546L 65,300 HRS.  BOEING 707-338C S/N 19293 N2178F 59,473 HRS.  BOEING 707-321C S/N 20016	 N870PA 52,582.24 HRS.			2	L	7	4 	4F				4A26    					 
1997031300335	19970313	00335	NM  	1997	3	13	97ZZZX1085       	1	19970225	G	5320	50534511	FITTING         			BOEING	707   	707338C     	138367N	NM  										BS 600K	CRACKED         	B	S		UGMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2178F					19293				3.8 INCH LONG CRACK LT TERMINAL FITTING, 8 INCH LONG CRACK, RT TERMINAL FITTING.  LOWER FWD CARGO AREA BS 600K, WL 170, 	LBL 50, RBL 50, INTERIOR P/N 50-5345-11.  REF DWG 50-2529 5H.3A ZNC2.  THE FOLLOWING A/C HAS THE SAME CRACKS IN THE SAME	 AREA FROM 3.8 INCHES LONG TO 8 INCHES LONG.  BOEING 707-338C S/N 19296 N6546L 65,300 HRS.  BOEING 707-3D3C S/N 20495 JY	-ADP 45,498.6 HRS.  BOEING 707-321C S/N 20016 N870PA 52,582.24 HRS.			2	L	7	4 	4F				4A26    					 
1997031300336	19970313	00336	NM  	1997	3	13	97ZZZX1086       	1	19970225	G	5320	50534511	FITTING         			BOEING	707   	707338C     	138367N	NM  										BS 600K	CRACKED         	B	S		UGMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6546L									EIGHT INCH LONG CRACK LT TERMINAL FITTING LOWER FWD CARGO AREA BS 600K, WL 170, LBL 50, INTERIOR P/N 50-5345-11.  REF DW	G 50-2529 SH.3A ZNC2.  THE FOLLOWING A/C HAS THE SAME CRACKS IN THE SAME AREA.  FROM 3.8 INCHES LONG TO 8 INCHES LONG. B	OEING 707-338C S/N 19293 N2178F 59,473 HRS.  BOEING 707-3D3C S/N 20495 JY-ADP 45,498.6 HRS.  BOEING 707-321C S/N 20016 N	870PA 52,582.24.			2	L	7	4 	4F				4A26    					 
1997031300337	19970313	00337	NM  	1997	3	13	97ZZZX1087       	1	19970225	G	5320	50534511	FITTING         			BOEING	707   	707321C     	138367B	NM  										BS 600K	CRACKED         	B	S		UGMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	870PA					20016				4.5 INCH LONG CRACK LT TERMINAL FITTING LOWER FWD CARGO AREA BS 600K, WL 170, LBL 50, INTERIOR P/N 50-5345-11.  REF DWG 	50-2529 SH.3A ZNC2.  THE FOLLIWNG A/C HAS THE SAME CRACKS IN THE SAME AREA FROM 3.8 INCHES LONG TO 8 INCHES LONG.  BOEIN	G 707-338C S/N 19296 N6546L 65,300 HRS.  BOEING 707-338C S/N 19293 N2178F 59,473 HRS.  BOEING 707-3D3C S/N 20495 JY-ADP 	45,498.6 HRS.			2	L	7	4 	4F				4A26    					 
1997031300338	19970313	00338	GL  	1997	3	13	97ZZZX1088       	3	19970226	G	6111	V8433N4	BLADE           			GULSTM	500   	500B        	0141106	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	SHANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	444CA	10026	1946 			1458162		BJ165		INSPECTION FOUND RPOPELLER BLADE SHANK CRACKED.						1	H	7	2 	3O				6A1     		5	C	P6EA	 
1997031300339	19970313	00339	CE  	1997	3	13	97ZZZX1089       	1	19970127	G	3231	12838002141	RELEASE CABLE   			MTSBSI	MU300 	MU300       	5780602	CE  										MLG DOOR EMRG	BROKEN          	B	L	A	RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	482DM	1655 				A088SA				DURING A POST-FLIGHT INSP DAMAGE WAS NOTICED ON THE LT FUSELAGE MLG DOOR, THE AFT SIDE COVER ASSEMBLY, AND THE MIDDLE FU	SELAGE SKIN ASSY.  AFTER FURTHER INSP THE LT EMERG MLG DOOR UPLOCK RELEASE CABLE WS FOUND BROKEN AT THE ROD END ADJACENT	 TO THE DOOR UPLOCK RELEASE.  AFTER LOWERING THE DOOR MANUALLY IT WAS DETERMINED THAT THE ROD END FROM THE BROKEN CABLE 	HAD JAMMED THE MLG DOOR UPLOCK RELEASE DURING A GEAR EXT.  THIS ALLOWED THE UPLOCK RELEASE HOOK TO ONLY OPEN SLIGHTLY BU	T NOT ENOUGH TO RELEASE THE MLG DOOR.  AT THIS POINT THE LEFT MLG DOOR ACTUATOR BEGAN TO EXTEND THE UNRELEASED DOOR.  AT	 THIS POINT THE LEFT MLG DOOR ACTUATOR BEGAN TO EXTEND THE UNRELEASED DAMAGE TO THE LT FUSELAGE MLG DOOR.	2	H	7	2 	4F			RT	A14SW   					 
1997032000267	19970320	00267	NE  	1997	3	20	97ZZZX1091       	3	19970130	G	6111		ABRASION STRIP  			DIAMON	DA20A1	DA20A1      	05626UX	GL  						HOFMAN	HOV352	HOV352F     	NE  	PROPELLER	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	179DA	124  				10179		H493		INSPECTION FOUND ABRASION STRIP CRACKED FROM TIP OF PROPELLER TO APPROXIMATELY 5 INCHES FROM TIP.  PROPELLER WAS NOT KNO	WN TO HAVE HAD ANY STRIKES.  CRACK WAS FOUND DURING PRE-FLIGHT INSPECTION.					1	L	7	1 	3O			NT	TA4CH   		5	C	TP5BO	 
1997032000268	19970320	00268	GL  	1997	3	20	97ZZZX1092       	2	19970303	G	7230	23057142	CASE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	LINER LOOSE     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	18FH		1612 		13642	2599	CAE833451			COMPRESSOR CASE PLASTIC LINER CAME LOOSE IN THE BLEED VALVE AIR FLOW BAND OF COMPRESSOR CASE.  ONE PIECE APPROXIMATELY 2	 SQUARE INCHES IN SIZE LODGED IN BLEED VALVE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997032000269	19970320	00269	SW  	1997	3	20	97ZZZX1093       	1	19970225	G	3340	1402R	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	250  				LN001				BASE OF LENS CRACKED FROM MOUNT RING CLAMP DUE TO VIBRATION.  FOUND ON INSPECTION, APPROXIMATELY 250 HOURS.						1	G	7	1 	3U			NC	H3WE    					 
1997032000270	19970320	00270	SW  	1997	3	20	97ZZZX1094       	1	19970227	G	3340		LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	527FB	35   				LN007				BASE OF LENS CRACKED  WOULD HAVE FALLEN OFF.  FOUND ON INSPECTION.  TT:  35 HOURS.						1	G	7	1 	3U			NC	H3WE    					 
1997032000271	19970320	00271	CE  	1997	3	20	97ZZZX1095       	1	19970221	G	3340	MS25306222	SWITCH          			CESSNA	208   	208B        	2073701	CE  										LANDING LIGHT	FAILED          	B			BJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	1293E	422  				208B0537				AIRCRAFT LEFT LANDING LIGHT WOULD NOT SHUT OFF.  PILOT REPORTED FAINT SMOKE SMELL IN COCKPIT.  IINVESTIGATION REVEALED L	ANDING LIGHT SWITCH HAD SHORTED AND SHOWED SIGNS OF OVERHEATING.  THE SWITCH WAS REPLACED AND SYSTEM OPERATED NORMALLY.					1	H	7	1 	3T				A37CE   					 
1997032000272	19970320	00272	SO  	1997	3	20	97ZZZX1096       	1	19970210	G	3260		SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	FAULTY          	D				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			EA	23	161SA	531  				318082029				PILOT REPORTS LEFT GEAR WILL NOT COME DOWN.  C/W GEAR SWINGS WITH HYDRAULIC CART, COULD NOT DUPLICATE PROBLEM.  LUBED GE	AR, CHECKED RIGGING, REPLACED UPLOCK ROLLERS.  FLEW AGAIN, SAME PROBLEM EXISTS.  CHANGED LEFT GEAR ACTUATOR AND HYDRAULI	C PACK, GEAR CHECK GOOD AGAIN IN HANGAR.  FLEW AGAIN, SAME PROBLEMS.  LAST RESORT, CHANGED DOWNLOCK SWITCH, FIXED PROBLE	M.			1	L	7	2 	3O				A20SO   					 
1997032000273	19970320	00273		1997	3	20	97ZZZX1097       	4	19970213	G	6122	F848L	GOVERNOR        	HARTZL      		PIPER 	PA31  	PA31350     	7103110	SO  										PROPELLER	FAILED          	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NE	05	344T	1088 			B9590	317952013				GOVERNOR FAILED ON CLIMB-OUT CAUSING ENGINE TO FEATHER PROP NECESSITATING AN EMERGENCY LANDING.  OIL PLUG WITHIN GOVERNO	R CAME LOOSE CAUSING IT TO JAM OIL PUMP GEARS AND SHEAR SHAFT ON GOVERNOR.  1,088 HRS SMOH OF GOVERNOR.					1	L	7	2 	3O				A20SO   					 
1997032000274	19970320	00274	CE  	1997	3	20	97ZZZX1098       	1	19970110	G	3260	1SE18	SWITCH          			CESSNA	310   	310R        	2074245	CE  										NLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	07	3700G					310R0899				DSM - TOOK SEVERAL CYCLES TO GET NOSE GEAR DOWN LIGHT.  REMOVED AND REPAIRED NOSE GEAR DOWN AND LOCK SWITCH ASSY.  CHECK	ED GEAR SEVERAL TIMES, OPS CHECK GOOD.					1	L	7	2 	3O				3A10    					 
1997032000275	19970320	00275	SO  	1997	3	20	97ZZZX1099       	1	19970113	G	2140	461731	VALVE           	JANITROL    		PIPER 	PA31  	PA31350     	7103110	SO  										FUEL PRESS REG	FAILS           	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	04	4091D					318152154				SUBMITTER STATED HAVE HAD 5 FAILURES OF THIS VALVE OVER 24 MONTH PERIOD.  DIAPHRAGM FAILS AND FUEL LEAKS OVERBOARD.  TIM	E RANGES FROM 101 HOURS TO 600 HOURS.  PIPER P/N 461-731.  ELECTRO SYSTEMS, P/N A 23 D0407.5, NEW VALVES OR OVERHAULED V	ALVES, MAKES NO DIFFERENCE.				1	L	7	2 	3O				A20SO   					 
1997032000276	19970320	00276	CE  	1997	3	20	97ZZZX1100       	1	19970205	G	5730		SKIN            			CESSNA	441   	441         	2076020	CE  										RT WING LE	CORRODED        	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	410MA	4960 				4410254				RIGHT WING DEICE BOOT WAS REMOVED FOR REPLACEMENT.  WING SKIN WAS FOUND TO HAVE EXCESSIVE CORROSION PITS ON MUCH OF THE 	SKIN.  DAMAGE ALLOWANCE IS ONLY 15 PERCENT OF .032 INCH SKIN THICKNESS.  LEADING EDGE ASSEMBLY HAS TO BE REPAIRED.  THIS	 COULD POSSIBLY BE FOUND BY FEELING SURFACE OF DEICE BOOTS FOR LUMPS UNDERNEATH.  DEICE BOOT INSTALLATION DATE AND TIME 	UNKNOWN.			1	L	7	2 	3T			RT	A28CE   					 
1997032000277	19970320	00277	SO  	1997	3	20	97ZZZX1101       	2	19970122	G	8550	12509225	ADAPTER         			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					OIL FILTER	LEAK            	D				K				NONE                    				J	K		WARNING INDICATION        	FLUID LOSS                		NR	NOT REPORTED   	1			EA	23	4853N					18267420				PILOT REPORTED LOW OIL PRESSURE IN-FLIGHT.  UPON INSPECTION, FOUND OIL LEAKING FROM OIL FILTER ADAPTER.  REMOVED ADAPTER	, INSTALLED NEW O-RING AND REINSTALLED.  NO FURTHER LEAKS FOUND.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997032000278	19970320	00278	SO  	1997	3	20	97ZZZX1102       	2	19970303	G	8530	A50222	CYLINDER        			CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4 CYL ROCKER	FAILED          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			EA	05	150J	1694 	305  			15069500	2045149A			ENGINE RAN ROUGH ON START.  REMOVED COWLING.  RESTARTED ENGINE.  SHAKING VIOLENTLY.  REMOVED  ROCKER COVER.  ENTIRE ROCK	ER ARMS, PINS, AND BOSSES FELL IN COVER.  SUSPECT VALVE STUCK.					1	H	7	1 	3O	3	O		3A19    	E252				 
1997032000279	19970320	00279	CE  	1997	3	20	97ZZZX1103       	1	19970226	G	3230	50452112	FORK BOLT       		08421043    	CESSNA	402   	402B        	207590P	CE  										NLG	BROKEN          	D	S	A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	09	7162K	9243 				402B1208				DURING APPROACH TO LAND, PILOT SELECTED GEAR DOWN.  NOSE GEAR SHOWED UNSAFE.  A FLY-BY WAS DONE AND PERSONNEL ON THE GRO	UND VERIFIED THE NOSE LANDING GEAR WAS TRAILING AT 45 DEGREES.  THE AIRCRAFT RETURNED TO HOME BASE AND A NOSE GEAR UP LA	NDING WAS MADE.  INSPECTION REVEALED THE NOSE LANDING GEAR FORK BOLT HAD BROKEN.  METAL FATIGUE IS SUSPECTED DUE TO THE 	HIGH TIME ON PART.			1	L	7	2 	3O				A7CE    					 
1997032000280	19970320	00280	CE  	1997	3	20	97ZZZX1104       	1	19970129	G	2750	500000862	CONTROL CABLE   			CESSNA	414   	414A        	2075907	CE  										FLAP	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	717BD	4992 				414A0337				BASED ON PREVIOUS INSPECTIONS, REMOVED FLAP CABLES FOR CLOSE INSPECTION BY TWISTING AND BENDING.  FOUND MANY INTERNAL ST	RANDS BROKEN.  SUBMITTER STATED MAY NEED TO HAVE LIFE LIMIT.  THIS IS THE THIRD OCCURRENCE OUT OF FOUR, 400 SERIES INSPE	CTED IN PAST SIX MONTHS.				1	L	7	2 	3O			 	A7CE    					 
1997032000281	19970320	00281	CE  	1997	3	20	97ZZZX1105       	1	19970128	G	3230		MAIN GEAR       			BEECH 	58    	58          	1152740	CE  										LT MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	07	9044V					TH216				LEFT LANDING GEAR FROZEN IN WHEELWELL, GEAR SELECTED DOWN, ROD BENT, AND GEAR STAYED IN WELL.  REMOVED AND REPLACED BENT	 ROD AND MOTOR AND GEARBOX ASSY, LEFT PROPELLER AND LEFT ENGINE FOR PROPELLER STRIKE INSPECTION.					1	L	7	2 	3O				3A16    					 
1997032000282	19970320	00282	SW  	1997	3	20	97ZZZX1106       	1	19970203	G	7603	660226007	CABLE SWAGE     			MOONEY	M20   	M20K        	5870220	SW  										THROTTLE	LOOSE           	B	S		DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	98968					250542				WHILE ATTEMPTING TO ADJUST THROTTLE WARNING HORN, SOME MAJOR INCONSISTENT SETTINGS WOULD OCCUR.  INVESTIGATION REVEALED 	A DEFECTIVE OR FAILED SWAGE JOINT WHERE FLEXIBLE CABLE TRANSITIONS AND CONNECTS AT AFT HOUSING ASSEMBLY.  DEFECT LOCATED	 ONLY INCHES FORWARD OF WARNING HORN MICROSWITCH ATTACH.  OPERATING THROTTLE WOULD MOVE HOUSING IN AND OUT INSTEAD OF CO	NTROLLING ENGINE.			1	L	7	1 	3O				2A3     					 
1997032000283	19970320	00283	CE  	1997	3	20	97ZZZX1107       	1	19970228	G	3234	98810202	SELECTOR        			CESSNA	182   	R182        	2072734	CE  										GEAR	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CE	09	6122S	7800 				R18201619				AFTER GEAR 'DOWN' SELECTION PRIOR TO LANDING, PILOT NOTICED HYD FLUID DRIPPING ONTO THE FLOOR.  ACFT LANDED WITHOUT INCI	DENT.  LANDING GEAR POSITION SELECTOR V ALVE WAS REMOVED AND CHECKED.  IT WAS DETERMINED THAT THE LEAK WAS CAUSED BY A D	ETERIORATED 'PACKING' FOR THE 'DOWN' LINE UNION FITTING.  THE REMAINING 3 LINE UNION FITTINGS WERE REMOVED AND IT WAS FO	UND THAT THE UNION PACKINGS WERE ALSO DETERIORATED.  THE AGE OF THESE PACKINGS CAUSED THEM TO BECOME HARD AND BRITTLE AN	D HAD TAKEN A PERMANENT SET.  NEW MS PACKINGS WERE INSTALLED UNDER THE UNION NUT FITTINGS AND SELECTOR VALVE.  OPS CHECK	ED GOOD.	1	H	7	1 	3O			RT	3A13    					 
1997032000284	19970320	00284	SO  	1997	3	20	97ZZZX1108       	1	19970228	G	2820	484297	REDUCER         			PIPER 	PA31  	PA31310     	7103103	SO  										CROSSFEED	CRACKED         	B			BXSR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	09	272HJ					317712055				PILOT REPORTED FUEL SMELL IN THE CABIN.  FOUND THE CROSSFEED LINE DRAIN REDUCER FLARE CRACKED AND SEEPING FUEL.						1	L	7	1 	3O			RT	A20SO   					 
1997032000285	19970320	00285	SO  	1997	3	20	97ZZZX1109       	1	19970228	G	2820	601	HOSE            			PIPER 	PA31  	PA31310     	7103103	SO  										LT WING ROOT	LEAK            	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ					317712055				PILOT REPORTED FUEL SMELL IN THE CABIN.  FOUND AEROQUIP TYPE 601 HOSE INSTALLED IN THE LT WING ROOT DRIPPING FUEL.  THES	E HOSES ARE AFFECTED BY AEROQUIP BULLETIN NR AA135 WHICH LIMITED THEIR LIFE TO TWO YEARS.					1	L	7	1 	3O			RT	A20SO   					 
1997032000288	19970320	00288		1997	3	20	97ZZZX1112       	4	19970228	G	3418	4219F010301	SWITCH          			AMD   	FALC50	FALCON50MYST	2730106	EU  										STALL VANE	FAILED          	B			UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	4350M					142				AIRCRAFT FAILED CAMP CARD CHECK OF NR 2 STALL VANE.  FOUND AIRSPEED SWITCH 66F FAILED TO THE PLUS 270 KNOT POSITION.  OR	DERED AND INSTALLED REPLACEMENT AIRSPEED SWITCH.  AIRCRAFT AGAIN FAILED CHECK, BUT A DIFFERENT PART OF THE CHECK.  FOUND	 REPLACEMENT AIRSPEED SWITCH FAILED TO THE BELOW 270 KNOT POSITION.  SWITCH HAD BEEN OVERHAULED TO ZERO TIME ON 1-16-97.				2	L	7	3 	4F				A46EU   					 
1997032000289	19970320	00289	EU  	1997	3	20	97ZZZX1113       	1	19970228	G	2820	D97C00215	ACTUATOR        			AMD   	FALC50	FALCON50MYST	2730106	EU  										TRANSFER	MALFUNCTIONED   	B		A	UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	4350M				763	142				TRANSFER INTERCONNECT VALVES WERE REMOVED AND SENT TO MIDWAY TO C/W DASSAULT SB F50-186.  VALVES WERE RETURNED TO US, OV	ERHAULED TO ZERO TIME.  AFTER INSTALLATION AND TEST IN THE AIRCRAFT, THE TEST SHOWED ONE VALVE WORKING BACKWARDS (CLOSED	 WHEN SELECTED OPEN AND OPEN WHEN SELECTED CLOSED).  REMOVED AND BENCH CHECKED VALVE PER CMM 28-15-28.  VALVE FAILED FUN	CTIONAL TEST.  REPAIR TAG SAYS IT WAS TESTED PER CMM 28-15-28 AND PASSED.			2	L	7	3 	4F				A46EU   					 
1997032000290	19970320	00290	CE  	1997	3	20	97ZZZX1114       	1	19970224	G	2910	2407003467	LINE            			LEAR  	25    	25D         	5170514	CE  										HELL HOLE	CRACKED         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			GL	23	900WA	10616				248				AIRCRAFT LOST HYDRAULIC PRESSURE DURING LANDING GEAR EXTENSION CYCLES.  REPLACED CRACKED HYDRAULIC LINE IN HELL HOLE.  S	ERVICED RESERVOIR, BLED SYSTEM, LEAK AND FUNCTIONALLY CHECKED GOOD.					2	L	7	2 	4J				A10CE   					 
1997032000386	19970320	00386	WP  	1997	3	20	97ZZZX1117       	1	19970122	G	6320	369D2512711	RING GEAR       		369D25100   	HUGHES	369   	369D        	4470706	WP  										M/R XMSN	SPALLED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	447  			1810	1151D				OPENED TRANSMISSION TO INSPECT FOR WEAR AND FOUND M/R OUTPUT SHAFT RING GEAR 369D25127-11, S/N 005570-1089, AND PINION 3	69D25125-13, S/N 005570-0437, SPALLED IN SEVERAL PLACES.  REPLACED TRANSMISSION.  SENT THIS ONE IN FOR OVERHAUL.					1	G	7	1 	3U				H3WE    					 
1997032000387	19970320	00387	GL  	1997	3	20	97ZZZX1118       	2	19970307	G	7250	6898735	TURBINE         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					EXH COLLECTOR	SMOKING         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	7015 	543  			1151D	CAE832750			19.4 HOURS AFTER A REPAIR TO THE TURBINE PT SUPPORT, THE TURBINE STARTED SMOKING HEAVILY ON SHUT DOWN.  AFTER THE ENGINE	 COOLED, A VISUAL INSPECTION FOUND OIL PUDDLING IN THE TURBINE EXHAUST COLLECTOR.  UNIT SENT BACK FOR REPAIR.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997032000388	19970320	00388	WP  	1997	3	20	97ZZZX1119       	1	19970303	G	5347	15080811	SEAT TRACK      			DOUG  	DC9   	DC981       	3022081	WP  										BS 200-237	CORRODED        	B			S5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	818SJ					48058				CORRODED SEAT TRACKS UNDER GALLEYS.  FOUND DURING CPCP INSPECTION.  SEAT TRACK SECTION REPLACED.  SUBMITTER STATED SPECI	AL ATTENTION TO SEALING AREA, UNDER GALLEY AND MAINTAINING ENVIRONMENTAL SEAL BETWEEN C-CHECKS.					2	L	7	2 	4F				A6WE    					 
1997032000389	19970320	00389	WP  	1997	3	20	97ZZZX1120       	1	19970303	G	5347	15080721	SEAT TRACK      			DOUG  	DC9   	DC981       	3022081	WP  										BS 200-237	CORRODED        	B			S5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	818SJ					48058				CORRODED SEAT TRACKS UNDER GALLEYS.  FOUND DURING CPCP INSPECTION.  SEAT TRACK SECTION REPLACED.  SUBMITTER STATED SPECI	AL ATTENTION TO SEALING AREA, UNDER GALLEY AND MAINTAINING ENVIRONMENTAL SEAL BETWEEN C-CHECKS.					2	L	7	2 	4F				A6WE    					 
1997032000696	19970320	00696	WP  	1997	3	20	97ZZZX1124       	2	19970212	G	7200		ENGINE          			BEECH 	18    	C45H        	1151018	CE  	GARRTT	TPE331	TPE331101B  	01514	WP  					RT ENGINE	FAILED          	D				K				NONE                    				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			GL	23	4209V	7782 	6310 			AF884	P93010			RIGHT ENGINE QUIT RUNNING ON APPROACH TO YIP.  UNEVENTFUL LANDING CARRIED OUT.  ENGINE EXPERIENCED INTERNAL FAILURE, CAU	SE AT THIS TIME UNKNOWN.  ENGINE REPLACED WITH SERVICEABLE UNIT.  AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3R	3	T		A765    	E3WE				 
1997032000697	19970320	00697	CE  	1997	3	20	97ZZZX1125       	1	19970221	G	3020	10091000239	LINE            			BEECH 	100   	B100        	1152919	CE  										ENG ANTI ICE	FAILED          	B	L	A	CW7R	A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CL	CLIMB          	1			GL	25	771CW					BE52				CREW WAS PERFORMING A MISSED APPROACH PROCEDURE.  DURING CLIMB-OUT, THE RT ENG WAS RETARDED TO FLIGHT IDLE TO SIMULATE E	NG OUT CONDITION.  DURING THIS ENTIRE TIME THE ACFT WAS IN LIGHT ICING CONDITIONS WITH ALL ANTI-ICE SYSTEMS OPERATING NO	RMALLY.  AFTER COMPLETION OF THE ENG OUT EXERCISE THE RT ENG THROTTLE WAS ADVANCED TO NORMAL CRUISE SETTING.  THE PILOT 	NOTICED VERY LITTLE TO NO RESPONSE IN PERFORMANCE AND THEN SHORTLY AFTER THE RT ENG FLAMED OUT.  THE ACFT RETURNED TO TH	E AIRPORT WITHOUT FURTHER INCIDENT.  DURING MAINT TROUBLESHOOTING, THE MECH FOUND THAT THE RT ENG INLET ANTI-ICE LINE 'B	' NUT HAD BACKED OFF AND SUBSEQUENT VIBRATION CAUSED THE LINE TO FATIGUE CRACK AND FAIL.  AIRCRAFT TT 4,118.8 HOURS.	1	L	7	2 	4T				A14CE   					 
1997032000698	19970320	00698	EU  	1997	3	20	97ZZZX1126       	1	19970228	G	2750		FLAP            			AIRBUS	320   	A320321     	3930325	EU  										WING	LOCK OUT        	C		A		O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	03	E1TLH					247				ORD - FLT 4326 - FLAPS HAD ISOMETRIC FAULT AND LOCK-OUT ON APPROACH.  AN EMERGENCY WAS DECLARED AND A NO-FLAP LANDING WA	S MADE.  AIRCRAFT LANDED AND TAXIED TO GATE WITH NO INCIDENT.  WING TIP BRAKES RESET ON GROUND.  BITE TEST WAS PERFORMED	 ON LGCIU IAW MM 32-69-00, 740-001.  NO FAULT DETECTED.  FLAPS OPERATE NORMALLY ON GROUND.				2	L	7	2 	RT			4T	A28NM   					 
1997032000699	19970320	00699	SO  	1997	3	20	97ZZZX1127       	1	19970303	G	7120	6711949	MOUNT           			PIPER 	PA28  	PA28R180    	7102809	SO  										ENGINE	CRACKED         	B			BCBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	3811T	2001 				28R30126				FOUND UPPER RT ENGINE MOUNT TUBE BROKEN.  REF:  PIPER S/L 568 PERTAINS TO THIS SUBJECT AND HAS A FACTORY APPROVED REPAIR	 PROCEDURE.  TACH WAS AT 2001.  LOGS NOT AVAILABLE TO CHECK IF THIS IS TOTAL TIME.					1	L	7	1 	3O				2A13    					 
1997032000700	19970320	00700	CE  	1997	3	20	97ZZZX1128       	1	19970226	G	8010	J4A18N	GROUND WIRE     			BEECH 	23    	23          	1151202	CE  										MAG SWITCH	BURNED          	D	P	A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	13	2368L	2350 				M209				THIS GROUND WIRE GROUNDS THE STARTER/VIBRATOR CIRCUIT.  IT WAS GROUNDED VIA A COPPER CLAMP TO THE MAG.  P-LEAD SHIELDING	.  THE P-LEAD SHIELDING WAS GROUNDED ONLY AT THE MAGNETO.  THE GROUND WIRE, J4A18N, COULD NOT HANDLE THE LOAD DURING STA	RT, AND, OVER TIME, DETERIORATED TO THE POINT WHERE THE WIRE J4A18N BURNED THROUGH CAUSING SMOKE IN THE COCKPIT AND DURI	NG START.  NEW WIRE WAS FABRICATED AND GROUNDED ELSEWHERE AS WERE THE P-LEAD SHIELDINGS.			1	L	7	1 	3O				A1CE    					 
1997032000702	19970320	00702	NM  	1997	3	20	97ZZZX1130       	1	19970304	G	5320	50534511	FITTING         			BOEING	707   	707338C     	138367N	NM  										LT 600K BLKHEAD	CRACKED         	B			VGMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	VHEBU	47677				19294				3 INCH LONG CRACK LT AND RT TERMINAL FITTING LOWER FWD CARGO AREA BS 600K WL 170 LBL 50 RBL 50 INTERIOR P/N 50-5345-11. 	 REF DWG 50-2529 SH 3A ZN02.					2	L	7	4 	4F				4A26    					 
1997032000703	19970320	00703	CE  	1997	3	20	97ZZZX1131       	1	19970201	G	3250	MISLSH19C	CONNECTOR       			LEAR  	35    	36A         	5170603	CE  										NLG STEERING	CORRODED        	B			L4JD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	978E					024				INTERMITTENT CONNECTION OF PLUG CAUSES INTERMITTENT AVAILABILITY OF VARIABLE AUTHORITY OF NOSE WHEEL STEERING.  THE PLUG	 IS TOO SUSCEPTIBLE TO MOISTURE AND CORROSION.  THIS SITUATION THE PLUG OPERATED INTERMITTENTLY CAUSING LOSS OF CONTROL 	OF NOSE WHEEL STEERING AND CONTROL OF THE AIRCRAFT WHICH WENT OFF THE RUNWAY.				2	L	7	2 	4F				A10CE   					 
1997032000704	19970320	00704	NM  	1997	3	20	97ZZZX1132       	1	19970303	G	2730	59118	SPRING          		680005003   	BOEING	727   	727225      	1384077	NM  										ELEV PCU	MISSING         	B			DM4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										UPON DISASSEMBLY OF ELEVATOR POWER CONTROL UNIT, IT WAS NOTED THAT THE CENTERING SPRING WAS MISSING.  (NOT INSTALLED AT 	LAST REPAIR.)  CUSTOMER REPORTED 'AIRPLANE PORPOISES IN A AND B MODE".					2	L	7	3 	4F				A3WE    					 
1997032000705	19970320	00705	EA  	1997	3	20	97ZZZX1133       	2	19970225	G	8530		CYLINDER        			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					FLANGE	NOT TO SPEC     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	36MV					5060	L254243			DURING ASSEMBLY OF ENGINE, MEASURED DRY TAPPET CLEARANCE FROM .107 INCH TO .187 INCH.  LYC OHM REQUIRES .028 INCH TO .08	0 INCH.  RETURNED 6 CYLINDERS TO EC/SW WHERE THEY CUT/REMOVED MATERIAL FROM THE CYL FLANGE.  CYLINDERS WERE RE-INSTALLED	.  THESE CYLINDERS JUST MADE THE .080 INCH DTC USING THE LONGEST PUSH ROD AND NEW ROCKER ARMS.				1	G	7	1 	3O	3	O		4H11    	E304				 
1997032000706	19970320	00706	GL  	1997	3	20	97ZZZX1134       	2	19970305	G	7260	6854857A	GEARSHAFT       								ALLSN 	250C  	250C20B     	03013	GL  					TACH DRIVE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		4889 			UPI342		CAG37227			TACH DRIVE END WORN ABOUT .040 INCH.  SUBMITTER STATED FOUND ABOUT 50 PERCENT OF ALL THE GEARS ARE FOUND WORN WHEN INSPE	CTED.										3	U			E4CE				 
1997032000707	19970320	00707	SW  	1997	3	20	97ZZZX1135       	1	19970217	G	5260	212075418105	ACTUATOR        			BELL  	412   	412EP       	1182205	SW  										STEP	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	1207W	17   			P86908	36149				STEP ACTUATOR FAILED.  REPLACED WITH NEW LINEAR ACTUATOR.						1	G	7	2 	4U				H4SW    					 
1997032000708	19970320	00708		1997	3	20	97ZZZX1136       	4	19970212	G	3425	1113034	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										ROLL COMMAND	STICKS          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	12070	16   			93041	36147				INDICATOR ROLL COMMAND BAR STICKS.  REPLACED WITH NEW INDICATOR.						1	G	7	2 	4U				H4SW    					 
1997032000709	19970320	00709	EU  	1997	3	20	97ZZZX1137       	1	19970306	G	6310		FREEWHEEL SHAFT 			SNIAS 	350   	AS350B      	8680801	EU  										ENG POWER SHAFT	EXTRA O RING    	B			RC0R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	4035W	199  				2912				DURING REPLACEMENT OF MODULE I MAG ASSEMBLY, DISCOVERED AN O-RING ON POWER SHAFT BETWEEN FREEWHEEL UNIT AND MAG SEALING 	RING HOLDER.  THIS PARTICULAR MODEL ENGINE DOES NOT USE AN O-RING IN THIS LOCATION.  THE PRESENCE OF THIS O-RING COULD R	ESTRICT SOME FLOW OF OIL TO THE FREEWHEEL UNIT.  THIS COMPONENT WAS NEVER WORKED ON BEFORE THIS SEAL REPLACEMENT.  DEFEC	T WAS PROBABLY DONE DURING ASSEMBLY BY MANUFACTURER.			1	G	7	1 	3U				H9EU    					 
1997032000710	19970320	00710	SW  	1997	3	20	97ZZZX1138       	1	19970220	G	6320	206040272101	SEAL ASSY       		206040015015	BELL  	206   	206L1       	1182107	SW  										MAIN DRIVE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	531KH	5441 				45581				DURING PRE-FLIGHT INSPECTION, MAIN DRIVESHAFT GREASE WAS FOUND ON FORWARD FIREWALL.  AFTER FURTHER INVESTIGATION WHEN TH	E DRIVESHAFT WAS REMOVED, THE AFT SEAL ASSEMBLY HAD BECOME DEBONDED FROM THE ALUMINUM CUP.  THE ROTOR BRAKE HAD ALSO STA	YED ENGAGED WITH A VERY SLIGHT CLEARANCE BETWEEN THE PUCKS AND DISC.  IT APPEARS THAT THE ROTOR DISC HAD GOTTEN HOT ENOU	GH TO MELT THE SEAL; THUS, ALLOWING GREASE TO SLING OUT.			1	G	7	1 	3U				H2SW    					 
1997032000711	19970320	00711	GL  	1997	3	20	97ZZZX1139       	2	19970225	G	7210	6875776	NOZZLE          		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	GOUGED          	B	S		EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 			CAG36146	1280431D	CAE832846			DURING DISASSEMBLY OF ENGINE GEARBOX, NR 4 BEARING WAS FOUND NOT TO BE SEATED ALL THE WAY ON THE JOURNAL ON THE HELICAL 	GEAR DUE TO IMPROPER INSTALLATION.  SUBSEQUENT INSPECTION FOUND THE 6875776 OIL NOZZLE GOUGED ON THE BOTTOM FLANGE BY TH	E BEARING.  REPLACED NOZZLE.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997032000712	19970320	00712	GL  	1997	3	20	97ZZZX1140       	2	19970226	G	7210	6876925	OIL TUBE        		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	TOO SHORT       	B			EOOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		CAG36146	1280431D	CAE832846			INSPECTED OIL TUBE PER CEB1307 AND IS TOO SHORT PER REQUIREMENTS OF THE BULLETIN.  PART WAS REPLACED.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997032000713	19970320	00713	NE  	1997	3	20	97ZZZX1141       	1	19970213	G	2435	230321586	V BAND CLAMP    	LUCAS       	23081042    	SKRSKY	S76   	S76C        	8143008	NE  										START GEN	CRACKED         	B	P		KS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	986AH	223  			94039	760438				DURING ENGINE CHANGE, DISCOVERED STARTER/GENERATOR V-BAND CLAMP T-BOLT CRACKED AT WELD.  REPLACED CLAMP ASSEMBLY.						1	G	7	2 	3U			NC	H1NE    					 
1997032700061	19970327	00061	EU  	1997	3	27	97ZZZX1143       	1	19970218	G	6510	350A34015003	SHAFT           			SNIAS 	350   	AS350B2     	8680813	EU  										T/R DRIVE	CHAFED          	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6095U	1103 			M2869	2699				DURING AN ANNUAL INSPECTION, A RUB SPOT WAS FOUND ON THE SHORT SHAFT JUST AFT OF THE ENGINE.  THIS IS A HARD AREA TO INS	PECT WITH BOTH PIECES OF DRIVE SHAFT COVER IN PLACE.  A CLOSE LOOK AT THIS AREA AT ANNUAL SHOULD BE DONE AS IT IS HARD T	O SEE.  THE REAR ENGINE MOUNTS WERE CHANGED AND THE PROBLEM WAS CORRECTED.				1	G	7	1 	3U				H9EU    					 
1997032700062	19970327	00062	WP  	1997	3	27	97ZZZX1144       	1	19970304	G	7820	A1698	MUFFLER         			ROBSIN	R22   	R22ALPHA    	7640104	WP  										FLAME TUBE	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	8561V	831  				0484				FOUND ON ANNUAL INSPECTION, FLAME TUBES BROKEN LOOSE INSIDE OF THE MUFFLER AND SEVERAL PIECES BLOCKING SOME OF THE EXHAU	ST STACK OPENING.					1	G	7	1 	3O				H10WE   					 
1997032700063	19970327	00063		1997	3	27	97ZZZX1145       	1	19970114	G	3510	80321301	REGULATOR       	SCOTTAVATION																OXY SYS	MISOVERHAULED   	H	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99					1964					INVESTIGATION FOR AN OXYGEN REGULATOR MALFUNCTION, FOUND SOMEONE ATTEMPTED TO REMOVE THE VALVE FROM THE ASSEMBLY.  THE U	PPER HOUSING BROKE OFF LEAVING THE BROKEN SCREWS EMBEDDED IN THE LOWER HOUSING.  SOMEONE REMOVED THE LOWER HOUSING, HYDR	OSTATIC TESTED THE CYLINDER AND INSTALLED THE UPPER HOUSING INTO THE LOWER HOUSING WITHOUT REMOVING THE BROKEN SCREWS. T	HE UPPER HOUSING WAS INSTALLED INTO THE LOWER HOUSING 60 DEGREES OUT OF ALIGNMENT BY USING THE REMAINING THREE MACHINED 	SCREW HOLES IN THE LOWER HOUSING.  ASSEMBLING THE REGULATOR 60 DEGREES OUT OF ALIGNMENT WILL CAUSE A PROBLEM ON THE AIRC	RAFT DURING INSTALLATION AND IN THE ACTIVATION OF THE CYLINDER ASSEMBLY.														 
1997032700064	19970327	00064	EA  	1997	3	27	97ZZZX1146       	2	19970210	G	8530	SL14995	SPRING          			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG CYL	BROKEN          	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	25	100PD					17257902	L7598927A			RECEIVING INSPECTION OF A NEWLY OVERHAULED ENGINE FOUND PUSH ROD HOUSING COULD BE POPPED OUT OF SEAT.  REMOVED ROCKER CO	VER AND FOUND HOLD-DOWN SPRING BROKEN.  FURTHER INVESTIGATION FOUND 3 OF 4 PUSH ROD SPRINGS BROKEN.  SUBMITTER SUSPECTS 	SPRINGS MISMANUFACTURED AND ARE BRITTLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997032700065	19970327	00065	GL  	1997	3	27	97ZZZX1147       	1	19970206	G	3230	5533525	LOCK PIN        			NAMER 	T6    	SNJ5        	6400418	GL  										LT MLG	DEFECTIVE       	C	L	A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	11	6900C					84867				AFTER A ROUTINE FLIGHT AFTER LANDING, STOPPED ON THE TAXIWAY AND RETRACTED THE FLAPS THEN TAXIED ON WHILE S-TURNING.  AC	FT WAS APPROXIMATELY TWO-THIRDS THE WAY DOWN THE TAXIWAY WHEN THE LEFT GEAR COLLAPSED PUTTING THE WING TIP AND PROPELLER	 INTO THE GROUND.  INSPECTED THE LOCK-PIN ON THE LEFT SIDE, IT WAS RETRACTED, THEN INSP THE RIGHT GEAR AND FOUND THE LOC	K-PIN OUT AND LOCKED.  WHILE LOOKING AT THE LEFT GEAR LOCK-PIN NOTICED IT WAS SLOWLY WORKING ITS WAY OUT INTO THE LOCKED	 POSITION.  ON LATER INSPECTION, PUTTING THE AIRCRAFT ON JACKS THE GEAR-LOCK MECHANISM FUNCTIONED PROPERLY.  UPON REMOVI	NG THE LOCK-PIN AND SPRING, SMALL FLAKES OF HARD CHROME WERE DETECTED FROM AROUND THE AFT OF HOUSING-BORE AND LOCK-PIN.	1	L	7	1 	3R				A2575   					 
1997032700066	19970327	00066	SO  	1997	3	27	97ZZZX1148       	1	19970226	G	5720	CH20391	RIB REINFORCMENT		7400906     	PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	HANGS GEAR      	G	L	A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			AL	01	792FC	1    	1    			317552108				UPON RETRACTION OF THE GEAR, THE BRAKE CALIPER FITTING P/N 754-857 OVERCENTERED INTO THE RIB CUT OUT AND THE GEAR WOULD 	NOT COME DOWN UPON EXTENSION.  THE PILOT HAD TO 'G' LOAD THE AIRCRAFT AND EXTEND THE GEAR SIMULTANEOUSLY TO GET THE LEFT	 GEAR TO EXTEND.  BOUNDRY LAYER RESEARCH ENGINEERING HAS APPROVED A CLEARANCE MODIFICATION TO PRECLUDE ANY FURTHER PROBL	EMS WITH THE SUPER CHIEF II WING RIB REINFORCEMENT.  STC SA002025E.			1	L	7	2 	3O				A20SO   					 
1997032700067	19970327	00067	SO  	1997	3	27	97ZZZX1149       	1	19970228	G	3230	4027909	DRAG BRACE      			PIPER 	PA31  	PA31310     	7103103	SO  										RT MLG	BROKEN          	B			B2ER	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			EA	23	100RT	5029 				31808				AD 96-10-14 APPLIES TO THIS SUBJECT DRAG BRACE.  AIRCRAFT TOOK OFF ON GUSTY/WINDY DAY, GEAR WAS SEEN TO BEGIN TO RETRACT	, RT MAIN DROPPED BACK OUT.  FWD SIDE BRACE IN AREA SUBJECT TO PENETRANT INSP.  PART WAS INSPECTED 84.0 HOURS EARLIER. S	UBMITTER RECOMMENDED 5000 HOUR TIME RETIREMENT ALONG WITH 1200 HOUR IN SERVICE AFTER DATE OF AD.				1	L	7	1 	3O			RT	A20SO   					 
1997032700068	19970327	00068	SO  	1997	3	27	97ZZZX1150       	2	19970207	G	7414		DISTRIBUTOR GEAR	BENDIX      		BEECH 	58    	58TC        	1152746	CE  	CONT  	O520  	TSIO520L    	17040	SO  					MAG	BROKE           	B			BIOR	A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	23	117HS	3695 			A156805	TK21	508213			DISTRIBUTION GEAR BROKE AND CONTACT STUCK ON NR 2 CYL LEAD.  MAG CONTINUED TO ROTATE CAUSING ONLY NR 2 CYL TO FIRE EACH 	TIME POINTS OPENED.  THIS CAUSED SEVERE DETONATION IN NR 2 CYL BURNING A HOLE THROUGH PISTON.  THIS RESULTED IN AN INFLI	GHT SHUT DOWN.  ENGINE INSP, AND FOUND TO BE CONTAMINATED WITH METAL.  ENGINE REPLACED.  SUBMITTER STATED IMPROPER MAINT	 AND OVERHAUL TIME OF MAG NOT C/W.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1997032700072	19970327	00072	CE  	1997	3	27	97ZZZX1154       	1	19970225	G	3230	08421211	TUBE ASSY       			CESSNA	310   	310L        	2074230	CE  										NLG LINKAGE	BROKEN          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	3285X					310L0135				TUBE MAY BECOME BENT DUE TO HIGH AIR SPEED WHEN GEAR IS EXTENDED.  AFTER INITIAL BENDING, TUBE WILL FLEX WITH EACH CYCLE	 EVENTUALLY BREAKING.  THIS TUBE IS HARD TO INSPECT DUE TO THE LOCATION IN THE A/C.  SUBMITTER SUGGESTED TUBE BE REMOVED	 AND INSPECTED EACH 2000 HOURS.				1	L	7	2 	3O				3A10    					 
1997032700073	19970327	00073	CE  	1997	3	27	97ZZZX1155       	1	19970303	G	2823	13341511	VALVE           	WHITTAKER   		MTSBSI	MU2   	MU2B60      	5780460	CE  										MAIN FUEL SOV	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	350RG	2946 				773SA				FOUND LEFT MAIN FUEL SHUT-OFF VALVE STUCK IN CLOSED POSITION.  MANUALLY OPERATED VALVE AFTER REMOVAL AND VALVE BEGAN TO 	WORK PROPERLY.  REINSTALLED AND VALVE OPERATED GOOD.  SUGGEST OPERATION OF VALVE PERIODICALLY TO PREVENT STICKING.					1	H	7	2 	3T			RT	A10SW   					 
1997032700074	19970327	00074	CE  	1997	3	27	97ZZZX1156       	1	19970217	G	7120	50980002521	PLATE           			BEECH 	90    	E90         	1152914	CE  										ENG MT	CORRODED        	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	50EB	7946 				LW128				ENGINE MOUNT PLATE AND SHIM WERE FOUND CORRODED UNDER THE AREA OF THE LEFT AND RIGHT ENGINE MOUNT TO FIREWALL ATTACHMENT	.  THE SHIMS WERE FLAKING AWAY SEVERELY AND IF LEFT UNREPAIRED, WOULD CAUSE THE MOUNT TO FIREWALL BOLT TORQUE TO DROP. T	HESE PARTS SHOULD BE MADE OF STAINLESS STEEL.				1	L	7	2 	3T				3A20    					 
1997032700075	19970327	00075	CE  	1997	3	27	97ZZZX1157       	1	19970217	G	7120	50980002523	SHIM            			BEECH 	90    	E90         	1152914	CE  										ENG MT	CORRODED        	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	50EB	7946 				LW128				ENGINE MOUNT PLATE AND SHIM WERE FOUND CORRODED UNDER THE AREA OF THE LEFT AND RIGHT ENGINE MOUNT TO FIREWALL ATTACHMENT	.  THE SHIMS WERE FLAKING AWAY SEVERELY AND IF LEFT UNREPAIRED, WOULD CAUSE THE MOUNT TO FIREWALL BOLT TORQUE TO DROP. T	HESE PARTS SHOULD BE MADE OF STAINLESS STEEL.				1	L	7	2 	3T				3A20    					 
1997032700076	19970327	00076	SO  	1997	3	27	97ZZZX1158       	1	19970303	G	2810	48603	TANK            			LUSCOM	8     	8A          	8190104	SO  										FUSELAGE	WELD WORN       	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	71231	1838 				2678				TANK WORN FROM INTERIOR UPHOLSTERY PANEL VIBRATING AGAINST WELD.  COULD BE CATASTROPHIC, DUMPING 14 GALS FUEL INTO CABIN	 AND AFT FUSELAGE.  SUBMITTER STATED HAVE FOUND THIS IN NUMEROUS LUSCOMBES WITH FUS TANKS.  RECOMMEND INSPECTING FOR DAM	AGE TO EDGE WELD.  IF STILL AIRWORTHY PUT FELT SPACERS ON PANEL TO KEEP PANEL AWAY FROM TANK.  OTHERWISE, PURGE TANK AND	 RE-WELD OR REPLACE WITH AIRWORTHY TANK.			1	H	7	1 	3O				A694    					 
1997032700077	19970327	00077	SO  	1997	3	27	97ZZZX1159       	2	19970227	G	8530	631475	PISTON          			BEECH 	33    	35C33A      	1151410	CE  	CONT  	O520  	IO520BA     	17032	SO  					1ST-2ND RING	BROKEN          	B			IQ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	9480S					CE6	1208025B			INSTALL NEW TCM CYLINDER AND VALVE ASSY USED SA 631475 PISTON DUE TO WEIGHT DIFFERENCE (TO BALANCE PISTON SET).  INSTALL	 TCM RING SET.  FLEW 228.1 HOURS.  REMOVE CYL DUE TO ENG MISSING.  FOUND TOP OF PISTON AND 1ST RING GLAND BROKEN. TOP 2 	RINGS BROKEN.  REASON UNKNOWN.				1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997032700078	19970327	00078	SW  	1997	3	27	97ZZZX1160       	1	19970214	G	2410	646655	HUB             		649304      	MOONEY	M20   	M20R        	5870225	SW  										ALT DRIVE	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NM	09	97ST	62   			L1595020	290101				ALTERNATOR FAILURE IN-FLIGHT.  INVESTIGATION REVEALED ALT DRIVE HUB HAD FAILED.						1	L	7	1 	3O			RT	2A3     					 
1997032700079	19970327	00079	CE  	1997	3	27	97ZZZX1161       	1	19970221	G	2612		FIRE LOOP       			CESSNA	500   	500CESSNA   	2076602	CE  										LT ENGINE	CHAFED          	B			FJTR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			SO	03	38MH					5000265				LEFT ENGINE FIRE LIGHT.  INVESTIGATION FOUND LEFT FIRE LOOP WAS CHAFING ON ENGINE CASE.  REPOSTIONED FIRE LOOP.						1	L	7	2 	4F				A22CE   					 
1997032700080	19970327	00080	CE  	1997	3	27	97ZZZX1162       	1	19970312	G	2150	1179100609	PIVOT           			BEECH 	B300  	B300        	1159232	CE  										AIR COND MOUNT	BROKEN          	D		A		E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SO	05	507EB	1505 				FL81				THIS PIVOT P/N 117-910060-9, (I.P.B. KINGAIR 350 MODEL B300 AND B300C) BOOK P/N 130-590031-9A7 CHAPTER 21-50-20, PAGE 4,	 FIG 50-20, HAS BEEN FOUND BROKEN ON THE LAST TWO KINGAIR 350'S THAT INSPECTIONS WERE PERFORMED ON.  BOTH AIRCRAFT HAD L	ESS THAN 2,000 HOURS OPERATING TIME.  WHEN THE PIVOT BREAKS AT ONE END, IT ALLOWS THE AIR CONDITIONING COMPRESSOR TO MOV	E AND STARTS A VIBRATION THAT CAN BE MISTAKEN FOR AN ENGINE VIBRATION, RESULTING IN AN ENGINE SHUT DOWN.  IT APPEARS THI	S PIVOT IS NOT MADE TO WITHSTAND THE STRESS FROM THE AIR CONDITIONER COMPRESSOR WHEN ENGAGED AND SHUT DOWN.  RECOMMEND A	LL THESE PIVOTS BE REMOVED FROM AIRCRAFT AND NEW DESIGNED STRONGER PIVOTS INSTALLED.	2	L	7	2 	4T			RT	A24CE   					 
1997032700081	19970327	00081		1997	3	27	97ZZZX1163       	4	19970210	G	2562	E01	ELT             			BEECH 	23    	C23         	1151242	CE  										FUSEAGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9793L				014104	M1398				AKC EMERGENCY LOCATOR TRANSMITTER INSTALLED 12-05-94 WITH DURACELL MN 1300 BATTERIES WITH AN EXPIRATION DATE OF JANUARY 	1999.  WHILE INSPECTING IAW FAR 91.207(D), FOUND ONE OF THE BATTERIES HAD BEEN LEAKING.  SOME OF THE FLUID LEAKED OUT OF	 THE CASE AND CAUSED A SMALL AMOUNT OF CORROSION ON THE MOUNTING TRAY.  THERE WAS SOME CORROSION ON THE BOTTOM SPRING IN	 THE CASE.  REPLACED THE BATTERIES WITH NEW MN 1300 BATTERIES AND FOUND THE ELT DID NOT OPERATE PROPERLY.  RETURNED THE 	ELT TO THE MANUFACTURER FOR REPAIR.		1	L	7	1 	3O				A1CE    					 
1997032700234	19970327	00234	WP  	1997	3	27	97ZZZX1164       	1	19970310	G	2921	4365082	DIAPHRAGM       			DOUG  	DC8   	DC8*        		WP  										AUX HYD ACCUM	TORN            	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					JW2897					AUXILIARY HYD POWER SURGE DAMPER ACCUMULATOR TANK HAD NEW DIAPHRAGM INSTALLED AT OVERHAUL.  DIAPHRAGM FAILED (TORN) AFTE	R 5 MONTHS TIME IN SERVICE.  2ND REPORT.  THIS PART WAS OBTAINED FROM THE MANUFACTURER.					2	L	7	4 	4J			F	4A25    					 
1997032700235	19970327	00235	WP  	1997	3	27	97ZZZX1165       	1	19970310	G	2921	4365082	DIAPHRAGM       		43442795002 	DOUG  	DC8   	DC8*        		WP  										AUX HYD ACCUM	TORN            	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1620					AUXILIARY HYD POWER SURGE DAMPER ACCUMULATOR TANK HAD NEW DIAPHRAGM INSTALLED AT OVERHAUL.  DIAPHRAGM FAILED (TORN) AFTE	R 2 MONTHS TIME IN SERVICE.  DIAPHRAGM SEPARATES HYD FLUID AND AIR.  THIS PART WAS OBTAINED FROM THE MANUFACTURER.					2	L	7	4 	4J			F	4A25    					 
1997032700236	19970327	00236	NE  	1997	3	27	97ZZZX1166       	3	19970305	G	6111	8022581	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  						HAMSTD	14RF	14RF19      	NE  	SHANK FILLET	CRACKED         	B			H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		4770 								DURING DYE CHECK OF THE BLADE SHANK, CRACK INDICATION IN THE BEARING RACE FILLET RADIUS WAS OBSERVED.  THE INDICATION IS	 LOCATED APPROXIMATELY 170 DEGREES FROM THE BLADE PIN, CLOCKWISE, AS VIEWED FROM THE BUTT END.  THE INDICATION IS APPROX	IMATELY .300 INCH LONG, AND IS ORIENTED CIRCUMFERENTIALLY IN THE RADIUS.				2	L	7	2 	4T			RT	A52EU   		6	C	P11NE	 
1997032700240	19970327	00240	CE  	1997	3	27	97ZZZX1170       	1	19970305	G	2435	23085001	ALTERNATOR      	LUCAS       		BEECH 	300   	300BEECH    	1152930	CE  										LT START/GEN	SEIZED          	D				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	13	3237S		92   		96055	FA163				THE PILOT REPORTED THE LEFT GENERATOR INOPERATIVE.  UPON INVESTIGATION, THE GENERATOR WAS FOUND TO BE MECHANICALLY SEIZE	D DUE TO APPARENT FAILURE OF THE ARMATURE RETAINING RING.					2	L	7	2 	4T				A24CE   					 
1997032700241	19970327	00241	CE  	1997	3	27	97ZZZX1171       	1	19970211	G	3340	900336	LIGHT           	WHELEN      		BEECH 	MU300 	400BEECH    		CE  										ANTI COLL	HARDWARE LOOSE  	B		A	JEMR	K				NONE                    				G			MULTIPLE FAILURE          			NR	NOT REPORTED   	1			CE	01	402FB	594  			10600122	RJ2				FOUND CAPACITOR IN UNIT LOOSE, AND SIDE COVER MOUNTING HARDWARE LOOSE AND ARCING TO DC BUSS OF AIRCRAFT.  CAUSED BULB FI	LAMENT TO BECOME FUSED TO UPRIGHTS OF FILAMENT.  THIS WAS PRODUCING A 5 VAC PULSE AT 50 MICROSEC ON THE DC BUSS OF AIRCR	AFT WHICH SHUT DOWN BOTH AC INVERTERS.  CAUSED TAIL DE-ICE CONTROL BOX TO LOCK UP IN A STATE OF FAILURE AND LANDING FLAP	 DELAY.  FIRST FAILURE, 216 TT 7-2-95, 2ND FAILURE 2-11-97.  RECOMMEND DIFFERENT STYLE OF SIDE COVERS ON ANTI-COLLISION 	LIGHT.		2	H	7	2 	4F			RT	A16SW   					 
1997032700243	19970327	00243	CE  	1997	3	27	97ZZZX1173       	1	19970115	G	3710	442CW4	PUMP            			BEECH 	58    	58P         	1152744	CE  										LT-RT VAC	INOPERATIVE     	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	6371V					TJ417				PILOT REPORTED GYRO WAS OUT.  (IFR) A/C DIVERTED TO RFD.  BOTH INSTRUMENT VACUUM PUMPS FAILED, LT AND RT.  NO FAULT COUL	D BE FOUND THAT WOULD CAUSE BOTH PUMPS TO FAIL SIMULTANEOUSLY.  TOTAL TIME OF PUMPS UNKNOWN.  RECOMMEND LOG BOOK ENTRIES	 BE MADE WHEN VACUUM ADJUSTMENTS ARE MADE.  LOGS SHOULD BE EXAMINED DURING INSPECTIONS TO DETERMINE IF REGULATORS HAVE B	EEN ADJUSTED TO COMPENSATE FOR FAILING PUMPS.			1	L	7	2 	3O				A23CE   					 
1997032700244	19970327	00244	EA  	1997	3	27	97ZZZX1174       	2	19970218	G	7261	3034393A	FILTER          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENG OIL	SCREEN FAILED   	B			DX4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	711MB	665  				BB437	80969			THE INNER CONE SHAPED SCREEN HAD SEPARATED ON OIL FILTER.  SEPARATION APPEARED TO BE AT A SEAM ON THE SCREEN.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997032700245	19970327	00245	CE  	1997	3	27	97ZZZX1175       	1	19970225	G	3243	45AS38401012	CYLINDER ASSY   			BEECH 	MU300 	400A        	1155402	CE  										RT BRAKE	NUT DETACHED    	B	L	A	UJDR	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	05	10J	2545 				RK31				CLIMBING OUT AT FL 300 AT APPROX 120 MILES FROM THE AIRPORT, THE HYD FLUID LOW ANNUNCIATOR ILLUMINATED.  THE PILOTS DECI	DED TO RETURN TO THE AIRPORT TO HAVE THE ACFT CHECKED.  THE EMER GEAR EXT SYS WAS EMPLOYED TO LOWER THE GEAR AND THE EME	R BRAKING WAS USED AFTER LANDING.  UPON INSP OF THE ACFT, IT WAS NOTED THAT HYD FLUID WAS DRIPPING FROM THE FUSELAGE AND	 THAT THE HYD FLUID RESERVOIR WAS EMPTY.  FURTHER INSP DISCLOSED THAT THE CAUSE OF THE HYD LEAK WAS A FAILED PILOT'S RT 	BRAKE MASTER.  THE PISTON ROD HAD BECOME DISCONNECTED FROM THE CYL BARREL ASSEMBLY. UPON DISASSEMBLY OF THE CYL, IT WAS 	DISCOVERED THAT THE PISTON RETAINING NUT P/N NAS 679C08W HAD BECOME UNTHREADED FROM THE PISTON ROD.	2	H	7	2 	4F			RT	A16SW   					 
1997032700246	19970327	00246	EU  	1997	3	27	97ZZZX1176       	1	19970210	G	5610	7256100502	WINDSHIELD      			SAAB  	SF340 	SF340A      	7850100	EU  										COCKPIT	DEFECTIVE       	B			P9AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	05										THIS WINDOW  WAS RECENTLY OVERHAULED FOR COMAIR.  COMAIR SENT THE WINDOW FOR EVALUATION DUE TO VARIOUS DEFECTS.  WINDSHI	ELD HAS MAJOR DISTORTION.  PHOTO REVEALS DISTORTION OF 1:3 IN CRITICAL OPTICAL AREAS.  ACCEPTABLE DISTORTION IS 1:10.  O	UTSIDE WEATHER SEAL SHOWS SEAL TO BE .860 INCH TO 1.10 INCH; SEAL SHOULD BE .820 INCH PLUS OR MINUS .030 INCH.  VARIOUS 	FRACTURES.			2	L	7	2 	4T			RT	A52EU   					 
1997032700247	19970327	00247	CE  	1997	3	27	97ZZZX1177       	1	19970219	G	2720	040010749	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										RUDDER	FRAYED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	47962	5025 				15283264				RUDDER CABLES ARE FRAYING IN AFT BULKHEAD ON TOP OF PULLEYS.  YOU MUST MOVE RUDDER IN OPPOSITE DIRECTION AND FEEL FWD AN	D AFT OF PULLEY TO DETERMINE IF CABLE IS FRAYED.  IN SOME CASES, THIS IS NOT A GUARANTEE THAT IT IS NOT FRAYED.					1	H	7	1 	3O			NT	3A19    					 
1997032700248	19970327	00248	CE  	1997	3	27	97ZZZX1178       	1	19970219	G	2710	040010758	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										RT WING	FRAYED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	47962	5025 				15283264				REMOVED PANEL AT FLAP OUTBOARD HINGE AREA.  INSPECTED AFT CABLE FOR WEAR WHERE IT GOES OVER ANTI-CHAFE BOX.  THIS IS SEC	OND AIRCRAFT THAT AILERON CABLE WAS FOUND FRAYED AT THIS POINT.					1	H	7	1 	3O			NT	3A19    					 
1997032700249	19970327	00249	CE  	1997	3	27	97ZZZX1179       	1	19970117	G	2434	ALV8402	ALTERNATOR      			CESSNA	310   	310Q        	2074242	CE  										DC SYSTEM	FAILED          	G				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	03	6248Q					310Q0746				PILOT LOST RADIO CONTACT AND DIVERTED TO ALTERNATE AIRPORT.  INVESTIGATION REVEALED ELECTRICAL POWER LOSS DUE TO ALTERNA	TOR, ALTERNATOR SENSOR, AND ALTERNATOR BELT FAILURE.					1	L	7	2 	3O				3A10    					 
1997032700250	19970327	00250	CE  	1997	3	27	97ZZZX1180       	1	19970117	G	2430	99100943	SENSOR          			CESSNA	310   	310Q        	2074242	CE  										ALTERNATOR	FAILED          	G				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	03	6248Q					310Q0746				PILOT LOST RADIO CONTACT AND DIVERTED TO ALTERNATE AIRPORT.  INVESTIGATION REVEALED ELECTRICAL POWER LOSS DUE TO ALTERNA	TOR, ALTERNATOR SENSOR, AND ALTERNATOR BELT FAILURE.					1	L	7	2 	3O				3A10    					 
1997032700251	19970327	00251	CE  	1997	3	27	97ZZZX1181       	1	19970117	G	2410	5395473500	BELT            			CESSNA	310   	310Q        	2074242	CE  										ALT DRIVE	FAILED          	G				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	03	6248Q					310Q0746				PILOT LOST RADIO CONTACT AND DIVERTED TO ALTERNATE AIRPORT.  INVESTIGATION REVEALED ELECTRICAL POWER LOSS DUE TO ALTERNA	TOR, ALTERNATOR SENSOR, AND ALTERNATOR BELT FAILURE.					1	L	7	2 	3O				3A10    					 
1997032700252	19970327	00252	CE  	1997	3	27	97ZZZX1182       	1	19970219	G	2720	040010750	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										RUDDER	FRAYED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	67376	3060 				15281792				RUDDER CABLES ARE FRAYING IN AFT REAR BULKHEAD ON TOP OF PULLEYS.  SUBMITTER STATED YOU MUST MOVE RUDDER IN OPPOSITE DIR	ECTION AND FEEL FWD AND AFT OF PULLEYS TO DETERMINE IF CABLE IS FRAYED.					1	H	7	1 	3O			NT	3A19    					 
1997032700253	19970327	00253	CE  	1997	3	27	97ZZZX1183       	1	19970303	G	7160	646020	HOSE ELBOW      			CESSNA	414   	414A        	2075907	CE  										ENG INDUCTION	BLOWN           	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	10	6624C					414A0034				ENG INDUCTION HOSE BLOWN OUT CAUSING INDUCTION LEAKAGE AND ENG PERFORMANCE DEGRADATION IN ALL PWR MODES.  RECOMMEND CHAN	GING THE MATERIAL HOSES ARE MADE FROM.  THIS IS THE THIRD OCCURENCE IN LESS THAN 600 HRS.					1	L	7	2 	3O				A7CE    					 
1997032700254	19970327	00254	SO  	1997	3	27	97ZZZX1184       	1	19970202	G	2434		ALTERNATOR      			PIPER 	PA23  	PA23250     	7102308	SO  										DC SYS	FAILED          	G				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			GL	03	6943A					277954117				BOTH ELECTRICAL SYSTEMS FAILED IN-FLIGHT.  RIGHT ALTERNATOR FAILED IN-FLIGHT.  LEFT ALTERNATOR INOP LIGHT WAS NOT ILLUMI	NATED DUE TO A BROKEN WIRE ON THE LIGHT CONCEALING A FAILED LEFT ALTERNATOR.  SUBMITTER RECOMMENDATION:  ADD INSPECTION 	OF ALTERNATOR INOP INDICATORS TO NORMAL INSPECTION PROGRAM.				1	L	7	2 	3O				1A10    					 
1997032700255	19970327	00255	CE  	1997	3	27	97ZZZX1185       	1	19970303	G	3230	574122218	HOOK ASSY       			CESSNA	414   	414A        	2075907	CE  										RT MLG	MALFUNCTION     	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	13	4686N					414A0075				PILOT REPORTED THAT AFTER GEAR RETRACTION ON TAKEOFF, THE GEAR UNLOCK RED LIGHT AND THE HYDRAULIC PRESSURE MASTER CAUTIO	N LIGHT REMAINED ILLUMINATED.  ACFT LANDED WITHOUT INCIDENT.  AIRCRAFT PLACED ON JACKS AND GEAR OPERATIONAL CHECK ACCOMP	LISHED.  DISCREPANCY DUPLICATED.  IT WAS DISCOVERED THAT THE RT MLG UPLOCK HOOK ASSEMBLY WAS NOT ENGAGING THE UPLOCK ROL	LER P/N 5141206-1.  THE HOOK ASSEMBLY, ATTACHING BOLT P/N NAS464P6-8, BUSHING P/N NAS75-6-117 AND BEARING BLOCK P/N 5T14	1203-3 WERE REMOVED, CLEANED, LUBRICATED AND REINSTALLED.  GEAR CYCLED SIX (6) TIMES WITH NO DISCREPANCIES.  SUBMITTER S	TATED THESE AREAS BE LUBRICATED AFTER WASHING.  ACFT RETURNED TO SERVICE.	1	L	7	2 	3O				A7CE    					 
1997032700256	19970327	00256	GL  	1997	3	27	97ZZZX1186       	2	19970225	G	7210	6875035	BEARING         		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GRBOX	PITTED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		CAG36146	1280431D	CAE832846			DURING INSPECTION OF ENGINE GEARBOX, BEARING WAS FOUND TO BE PITTED ON SEVE RAL ROLLERS.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997032700257	19970327	00257	GL  	1997	3	27	97ZZZX1187       	2	19970225	G	7210	6851505	PICOLLO TUBE    		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GRBOX	BURRS           	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		CAG36146	1280431D	CAE832846			INSPECTED PICOLLO TUBE PER CEB 1177 (S/N BN16959) AND FOUND BURRS - SCRAPPED PER CEB.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997032700258	19970327	00258	CE  	1997	3	27	97ZZZX1188       	1	19970227	G	7160	11111	ELBOW           			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 2 INDUCTION	TORN            	D		A		O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	13	6604C					414A0030	519399			PILOT REPORTED THAT THE RIGHT ENGINE WOULD NOT MAINTAIN POWER.  MANIFOLD PRESSURE DECREASED DURING FLIGHT.  TAKEOFF POWE	R OKAY ON BOTH ENGINES.  DURING CLIMB, THE RIGHT ENGINE ONLY DEVELOPED 27 IN HG.  IT WAS DISCOVERED THAT THE INBOARD IND	UCTION ELBOW RAM P/N 1111-1, LOCATED BETWEEN THE INTERCOOLER ASSEMBLY P/N 635921 AND NR 2 INTAKE MANIFOLD ELBOW P/N 6425	90 HAD TORN.  INDUCTION ELBOW REPLACED.  ENGINE RUN UP OKAY.  AIRCRAFT RETURNED TO SERVICE.  SUBMITTER STATED IT IS NOT 	UNCOMMON FOR THE RAM P/N 1111-1 OR TCM P/N 646020 INDUCTION TO TEAR.		1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997032700259	19970327	00259	GL  	1997	3	27	97ZZZX1189       	3	19970226	G	6111	A971	BEARING         			GULSTM	500   	500A        	0141104	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	PROP BLADE	CRACKED         	B			CBCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	9382R				131	500A8998		BJ146		BLADE BEARING RACE, P/N A971, FOUND CRACKED.  PROP CAME IN FOR TBO (135 OP.).  HAD NO PROBLEMS ON AIRCRAFT.						1	H	7	2 	3O				6A1     		5	C	P6EA	 
1997032700260	19970327	00260	GL  	1997	3	27	97ZZZX1190       	3	19970226	G	6111	A971	BEARING         			GULSTM	500   	500A        	0141104	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	PROP BLADE	CRACKED         	B	S		CBCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	9382R				141	500A8998		BJ146		BLADE BEARING RACE, P/N A971, FOUND CRACKED.  CAME IN FOR TBO (135 OP.).  HAD NO PROBLEMS ON AIRCRAFT.						1	H	7	2 	3O				6A1     		5	C	P6EA	 
1997032700261	19970327	00261	CE  	1997	3	27	97ZZZX1191       	1	19970201	G	3211	23221971	BUSHING         			LEAR  	60    	60LEAR      	5170707	CE  										MLG AFT TRUNNION	MISALIGNED      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	227N					049				AFT MAIN GEAR TRUNNION BUSHING NOT LINED UP WITH FORWARD BEARING.  CORRECTED BY FOLLOWING PROCEDURES IN SRM 51-71-05.  I	NSTALLED NEW BUSHING, THEN LINE REAMED TO FORWARD BEARING LOCATION.					2	L	7	2 	4F			RT	A10CE   					 
1997032700262	19970327	00262	CE  	1997	3	27	97ZZZX1192       	1	19970201	G	3211	23221981	BUSHING         			LEAR  	60    	60LEAR      	5170707	CE  										MLG AFT TRUNNION	MISALIGNED      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	227N					049				AFT MAIN GEAR TRUNNION BUSHING NOT LINED UP WITH FORWARD BEARING.  CORRECTED BY FOLLOWING PROCEDURES IN SRM 51-71-05.  I	NSTALLED NEW BUSHING, THEN LINE REAMED TO FORWARD BEARING LOCATION.					2	L	7	2 	4F			RT	A10CE   					 
1997032700277	19970327	00277	CE  	1997	3	27	97ZZZX1193       	1	19970101	G	8120	4810B49001	WASTEGATE       			CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENG TURBO	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		1361 								DURING AN OIL AND FILTER CHANGE, THE WASTEGATE CRACK DEFECT WAS FOUND.  DEFECT NOT PRESENT AT 50 HOUR CHECK 50 HOURS PRE	VIOUS.					1	L	7	2 	3O	3	O	RT	A7CE    	E7CE				 
1997032700278	19970327	00278	EA  	1997	3	27	97ZZZX1194       	2	19970304	G	8550		LINE            			SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					TURBO OIL	FAILED          	D	P	A		A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	23	20NB	1738 				557				INFLIGHT FAILURE OF THE TURBOCHARGER OIL RETURN LINE BETWEEN THE TURBOCHARGER HOUSING AND A SMALL RESERVOIR CAN LOCATED 	UNDER THE ENGINE.  THE AIRCRAFT LOST 9 QUARTS OF OIL INFLIGHT AND WAS LANDED WITHOUT INCIDENT.  THE OIL RETURN LINE WAS 	FOUND WITH A CRACK RUNNING AROUND 300 DEGREES OF THE TUBE'S CIRCUMFERENCE WHERE IT MADE A SWEEPING 90 DEGREE BEND BELOW 	THE MOUNTING FLANGE.  MATERIAL FATIGUE FAILURE IN THE 90 DEGREE RADIUS BEND OF THE OIL RETURN LINE TUBE BETWEEN THE 2 BO	LT MOUNTING FLANGE TO THE TURBOCHARGER HOUSING AND OIL RESERVOIR CAN.  VISUAL INSPECTION INDICATES THAT THE OUTER RADIUS	 WALL THICKNESS WAS MUCH THINNER THAN THE INNER RADIUS WALL THICKNESS WHERE THE CRACK OCCURRED.	1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
1997032700279	19970327	00279	EA  	1997	3	27	97ZZZX1195       	2	19970217	G	8530	S14995	SPRING          			CESSNA	182   	T182        	2072736	CE  	LYC   	O540  	O540L3C5    	41532	EA  					CYL SHROUD TUBE	BROKEN          	B	L	A	WTXR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	201SP					18268313	L2385040A			AFTER AN INITIAL TEST FLIGHT OF 1.1 HOURS, IT WAS NOTED THAT A LARGE AMOUNT OF OIL HAD COLLECTED ON THE RT SIDE OF THE E	NG.  FURTHER INSP REVEALED THAT THE PUSHROD HOUSING ON THE INTAKE SIDE OF THE NR 1 CYL RETAINING SPRING WAS FOUND TO BE 	BROKEN.  WHEN THE REMAINING ROCKER COVERS WERE REMOVED, THE PUSHROD RETAINING SPRING FROM THE NR 5 CYLINDER WAS FOUND TO	 BE CRACKED.  THESE PARTS WERE INSTALLED FROM A SUPERIOR AIR PARTS GASKET SET SL 13377 PURCHASED FROM SUPERIOR JAN. 1997	.  SUPERIOR SL 94-002 AND LYCOMING SB 519 ADDRESSED THE PROBLEM OF CERTAIN SHROUD TUBE RETAINING SPRINGS THAT WERE BREAK	ING IN SERVICE.  HOWEVER, THOSE SPRINGS WERE MADE AND SOLD IN 1994.  THESE SPRINGS WERE SOLD IN 1997.	1	L	7	1 	3O	3	O		3A13    	E295				 
1997032700280	19970327	00280	CE  	1997	3	27	97ZZZX1196       	1	19970301	G	3340	S21604	SWITCH          			CESSNA	172   	172M        	2072418	CE  										LANDING LIGHT	CORRODED        	D				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			NM	01	9730H					17266338				DURING ANNUAL INSPECTION, DISCOVERED WIRE TERMINAL AT LANDING LIGHT SWITCH PARTIALLY MELTED CAUSED BY INCREASED RESISTAN	CE DUE TO CORRODED WIRES AT TERMINAL.  REPLACED TERMINALS.  FOUND SIMILAR CONDITION ON 1 OTHER TYPE A/C.					1	H	7	1 	3O			NT	3A12    					 
1997032700281	19970327	00281	CE  	1997	3	27	97ZZZX1197       	1	19970311	G	3246		HUB             			CESSNA	172   	172M        	2072418	CE  										WHEEL HALF	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9730H					17266338				WHEN NOSE WHEEL WAS REMOVED TO GREASE BEARINGS, DISCOVERED THAT BEARING CUP (KOYO MFG) WAS LOOSE IN WHEEL HUB. WHEEL HUB	 WAS WORN WHERE CUP HAD BEEN SPINNING IN HUB.  THE CUP IS NORMALLY A PRESS FIT INTO THE WHEEL.  A/C HAD NOSE WHEEL SHIMM	Y COMPLAINT PRIOR TO DISCOVERY.  REPLACED RACE AND WHEEL HALF.				1	H	7	1 	3O			NT	3A12    					 
1997032700282	19970327	00282	CE  	1997	3	27	97ZZZX1198       	1	19970223	G	3222	1243009201	FORK            			CESSNA	210   	P210N       	2073454	CE  										NLG	FAILED          	G	S			K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	27	323DC					P21000384				ON PROBABLE HARD LANDING, THE NOSE LANDING GEAR BROKE, WHERE THE FORKS ATTACH TO THE PISTON.  NO RECOMMENDATIONS.						1	H	7	1 	3O				3A21    					 
1997032700283	19970327	00283	CE  	1997	3	27	97ZZZX1199       	1	19970304	G	2140	75D80	MOTOR           	JANITROL    	B4050       	BEECH 	58    	58          	1152740	CE  										COMBUSTION AIR	RUNS BACKWARD   	E		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	401SB	163  			3751454	TH641				FOUND HEATER RUNS RICH, AFTER A LONG TROUBLESHOOTING TIME DISCOVERED COMBUSTION AIR FAN MOTOR RAN BACKWARDS.						1	L	7	2 	3O				3A16    					 
1997032700284	19970327	00284	CE  	1997	3	27	97ZZZX1200       	1	19970305	G	3710	4502003	SHUTTLE VALVE   			BEECH 	33    	35C33       	1151408	CE  										VAC PUMP	FAILED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4887J	1000 			68888233	CD1076				CHECK VALVE FAILED ON ENGINE DRIVEN VACUUM PUMP.  SIDE RIVET HEAD SEPARATED FROM VALVE ASSEMBLY.  RENDERED VALVE INOP.						1	L	7	1 	3O				3A15    					 
1997032700285	19970327	00285	CE  	1997	3	27	97ZZZX1201       	1	19970310	G	3211		LANDING GEAR    			CESSNA	150   	150         	2071802	CE  										MLG BOX	RIVET SHEARED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	5960E					17460				BOX THAT HOLDS SPRING STEEL LANDING GEAR HAD TWO RIVETS WITH THE FACTORY HEADS SHEARED OFF.  SKIN ON THE OUTSIDE AFT OF 	LANDING GEAR WAS WRINKLED.  SUSPECT CAUSED BY A HARD LANDING.  AIRFRAME TOTAL TIME 4580 HRS.					1	H	7	1 	3O			NT	3A19    					 
1997032700286	19970327	00286	EU  	1997	3	27	97ZZZX1202       	1	19970306	G	2820	190620	COUPLING        			HOACAU	DV20  	DV20        	4170001	EU  										FUEL LINE	DISCONNECTED    	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99	194DV	916  				20094				AIRCRAFT MAIN FUEL LINE BECAME DISCONNECTED AT INLINE ELECTRIC FUEL PUMP QUICK DISCONNECT FITTING.  QUICK DISCONNECT IS 	INSTALLED TO FACILITATE FUEL PUMP FILTER MAINTENANCE.  FUEL SYSTEM SHOULD BE MODIFIED TO SYSTEM INSTALLED ON LATE MODEL 	DA-20 KATANAS.				1	L	7	1 	3O				A74EU   					 
1997032700288	19970327	00288		1997	3	27	97ZZZX1204       	1	19970310	G	2434	649093	HUB ASSY        								CONT  	O550  	IO550*      		SO  					ALTERNATOR	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11							281690P			ALTERNATOR KEY (633342-10) FAILED CAUSING HUB ASSY TO SPIN ON ALTERNATOR SHAFT.  THE RESULTS WERE EXCESSIVE WEAR TO ALTE	RNATOR SHAFT AND HUB ASSEMBLY.  THERE WAS ALSO WEAR ON THE TEETH OF THE ALTERNATOR FACE GEAR.										3	O			E3SO				 
1997032700289	19970327	00289		1997	3	27	97ZZZX1205       	1	19970313	G	3350	EMSE299A	BATTERY PACK    	GULTON      	EMBS1392    															FWD GALLEY	MELTED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1297TM					BATTERY PACK MELTED AND DETERIORATED.  BATTERY PACK WAS REPLACED NEW FROM MANUFACTURER 1-29-97. APPROXIMATELY 30 DAYS IN	 SERVICE.																		 
1997032700291	19970327	00291	EU  	1997	3	27	97ZZZX1206       	1	19970307	G	5240	F50B281043	DOOR            			AMD   	FALC50	FALCON50MYST	2730106	EU  										DOOR 170A	MISSING         	B		A	JZBR	K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			EA	25	134AP					048				DURING CLIMB, CREW NOTED A VIBRATION FOR APPROXIMATELY 5 SECONDS.  DURING PRE-FLIGHT THE NEXT DAY, DOOR 170A WAS DISCOVE	RED TO BE MISSING.  TEMPORARY REPAIRS WERE MADE AND THE A/C WAS FLOWN TO A REPAIR FACILITY FOR REPLACEMENT OF DOOR 170A.					2	L	7	3 	4F				A46EU   					 
1997032700292	19970327	00292	SO  	1997	3	27	97ZZZX1207       	1	19970228	G	2740	688237	SWITCH          			PIPER 	PA42  	PA42720     	7104212	SO  										TRIM MASTER	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	2247R					425501005				FOUND TRIM MASTER SWITCH PREVIOUSLY REPAIRED WITH GLUE.  REPLACED SWITCH, NEW SWITCH FELL APART AT FWD SEAM AT FIRST OPS	 CHECK.  SECOND NEW SWITCH DID THE SAME.  BACK PART OF SWITCH FELL INTO CENTER CONSOLE, SHORTED OUT ON A/F STRUCTURE AND	 COULD NOT BE RETRIEVED TO SELECT TRIM OFF.  POOR DESIGN OF SWITCH ASSEMBLY AND POOR CONSTRUCTION OF SWITCH.  REPLACED S	WITCH WITH ONE OF HIGHER QUALITY AND MADE BY A DIFFERENT MANUFACTURER.  FAA FORM 337 AND FIELD APPROVAL GRANTED FOR CHAN	GE.		1	L	7	2 	4T				A23SO   					 
1997032700294	19970327	00294	SO  	1997	3	27	97ZZZX1208       	1	19970214	G	2822	RR12040F	PUMP            			LKHEED	1329  	1329        	5263102	SO  	GARRTT	TFE731	TFE7313     	01518	WP  					NR 2	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	817BD		466  			5083				FUEL PUMP WAS OVERHAULED BY CRS NR ZK3R027M ON 10-5-93.  OVERHAUL REQUIREMENT IS 2000 HOURS. TIME SINCE OVERHAUL ON PART	 WAS 466 HOURS.  PUMP WOULD NOT MAINTAIN PRESSURE WITH COLD FUEL.  SUBMITTER STATED SEVERAL OPERATORS HAVE COMPLAINED AB	OUT SIMILAR PROBLEMS WITH PUMPS FROM THE SAME CRS.				2	L	7	4 	4J	4	F		2A15    	E6WE				 
1997032700295	19970327	00295	CE  	1997	3	27	97ZZZX1209       	1	19970310	G	3610	10138417313	VALVE           			BEECH 	90    	C90         	1152913	CE  										BLEED SYSTEM	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	6280E	7471 				LJ1015				DURING ROUTINE PRIMARY INSPECTION, FLAPPER VALVE TEST WAS PERFORMED IAW BEECH MODEL 90 MM.  VALVE FAILED TEST AND WHEN R	EMOVED, IT WAS DISCOVERED THAT THE RUBBER DIAPHRAGM INSIDE THE VALVE HAD SEPARATED FROM ITS HINGE AND WAS CARRIED INTO T	HE BLEED AIR DISTRIBUTION SYSTEM.  PART WAS REPLACED AND SYSTEM RETURNED TO NORMAL OPERATION.  RECOMMEND VISUAL INSPECTI	ON AT 600 HOURS RATHER THAN A FUNCTIONAL CHECK.			1	L	7	2 	3T				3A20    					 
1997032700296	19970327	00296	CE  	1997	3	27	97ZZZX1210       	1	19970307	G	3210	10581002369	A FRAME         			BEECH 	76    	76          	1153005	CE  										RT MLG	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6002C	4864 				ME120				WHEN INSPECTING LANDING GEAR A-FRAMES PER AD 91-14-14 AND BEECH SB 2361, THE RIGHT AND LEFT A-FRAMES WERE REMOVED FROM T	HE AIRCRAFT FOR FURTHER INSPECTION.  A MAGNAFLUX INSPECTION OF THESE PARTS WAS PERFORMED AND THE A-FRAMES WERE FOUND CRA	CKED.  THE MAGNAFLUX INSPECTION IS NOT CALLED OUT FOR IN SB 2361, BUT THE CRACKS THAT WERE FOUND DID NOT SHOW UP WITH TH	E DYE PENETRANT INSPECTION AS REQUIRED BY SB 2361.  RECOMMEND REPLACING THE OLD STYLE A-FRAMES WITH THE NEW STYLE A-FRAM	ES LISTED IN SB 2361 REV 111.		1	L	7	2 	3O				A29CE   					 
1997032700297	19970327	00297	CE  	1997	3	27	97ZZZX1211       	1	19970307	G	3210	10581002370	A FRAME         			BEECH 	76    	76          	1153005	CE  										LT MLG	CRACKED         	B		A	UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6002C	4864 				ME120				WHEN INSPECTING LANDING GEAR A-FRAMES PER AD 91-14-14 AND BEECH SB 2361, THE RIGHT AND LEFT A-FRAMES WERE REMOVED FROM T	HE AIRCRAFT FOR FURTHER INSPECTION.  A MAGNAFLUX INSPECTION OF THESE PARTS WAS PERFORMED AND THE A-FRAMES WERE FOUND CRA	CKED.  THE MAGNAFLUX INSPECTION IS NOT CALLED OUT FOR IN SB 2361, BUT THE CRACKS THAT WERE FOUND DID NOT SHOW UP WITH TH	E DYE PENETRANT INSPECTION AS REQUIRED BY SB 2361.  RECOMMEND REPLACING THE OLD STYLE A-FRAMES WITH THE NEW STYLE A-FRAM	ES LISTED IN SB 2361 REV 111.		1	L	7	2 	3O				A29CE   					 
1997040300001	19970403	00001	SO  	1997	4	3	97ZZZX1217       	1	19970312	G	8011	MHB4005	STARTER         	PRESTOLITE  		PIPER 	PA31  	PA31P       	7103120	SO  										ENGINE	SHORTED         	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	18MC		341  		A105041	31P7300143				STARTER INOPERABLE.  FOUND SHORTED OUT.  TIME 341.1 HOURS SMOH.  ONE YEAR IN SERVICE.						1	L	7	2 	3O				A8EA    					 
1997040300002	19970403	00002	SO  	1997	4	3	97ZZZX1218       	1	19970312	G	2434	ALV9510	ALTERNATOR      			PIPER 	PA31  	PA31P       	7103120	SO  										ROTOR	SHAFT FAILED    	B		A	EKIR	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			WP	07	18MC		10   			31P7300143				ALTERNATOR QUIT WORKING.  REMOVED, FOUND SHAFT THROUGH ROTOR ASSY WOULD TURN WITHOUT TURNING ROTOR.  UNIT OVERHAULED 1-1	3-97.					1	L	7	2 	3O				A8EA    					 
1997040300003	19970403	00003	CE  	1997	4	3	97ZZZX1219       	1	19970319	G	3230	51001116	LINE            			CESSNA	414   	414A        	2075907	CE  										GEAR BOTTLE	CORRODED        	B		A	NT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	442CC	5086 				414A0483				ALUMINUM LINE THAT ATTACHES TO GEAR BLOW-DOWN BOTTLE HAS A HOLE CORRODED IN TUBE 7.5 INCHES DOWN FROM BLOW-DOWN BOTTLE W	HERE IT LAYED AGAINST THE CROSS-OVER HEAT DUCT INSULATION.  SUBMITTER SUGGESTED LINE BE BENT OUT ENOUGH TO RELIEVE PRESS	URE AND CHAFING PROBLEM.				1	L	7	2 	3O				A7CE    					 
1997040300004	19970403	00004	CE  	1997	4	3	97ZZZX1220       	1	19970314	G	5553	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  										V FIN ATTACH	CRACKED         	B		A	AJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	49169	7700 				15281177				FOUND VERTICAL/HORIZONTAL STABILIZER REAR ATTACH FITTING CRACKED DURING ROUTINE MAINTENANCE.  REMOVED FIN AND RUDDER.  R	EMOVED ELEVATORS TO REMOVE BRACKET ASSY, P/N 0432004-9.  FOUND REINFORCEMENT, P/N 0432001-15, AND SPARS, P/N 0432001-56,	 ALSO CRACKED IN SAME LOCATION STARTING AT CENTERLINE OF FUSELAGE PROPAGATING TO THE RIGHT SIDE OF STABILIZER APPROXIMAT	ELY 3.0 INCHES.  MOST OF THIS AIRPLANE'S TIME HAS BEEN SPENT IN A FLIGHT SCHOOL.			1	H	7	1 	3O			NT	3A19    					 
1997040300005	19970403	00005	CE  	1997	4	3	97ZZZX1221       	1	19970314	G	5511	043200115	REINFORCEMENT   			CESSNA	150   	152         	2071835	CE  										HORIZ STAB	CRACKED         	B			AJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	49169	7700 				15281177				FOUND VERTICAL/HORIZONTAL STABILIZER REAR ATTACH FITTING CRACKED DURING ROUTINE MAINTENANCE.  REMOVED FIN AND RUDDER.  R	EMOVED ELEVATORS TO REMOVE BRACKET ASSY, P/N 0432004-9.  FOUND REINFORCEMENT, P/N 0432001-15, AND SPARS, P/N 0432001-56,	 ALSO CRACKED IN SAME LOCATION STARTING AT CENTERLINE OF FUSELAGE PROPAGATING TO THE RIGHT SIDE OF STABILIZER APPROXIMAT	ELY 3.0 INCHES.  MOST OF THIS AIRPLANE'S TIME HAS BEEN SPENT IN A FLIGHT SCHOOL.			1	H	7	1 	3O			NT	3A19    					 
1997040300006	19970403	00006	CE  	1997	4	3	97ZZZX1222       	1	19970314	G	5511	043200156	SPAR            			CESSNA	150   	152         	2071835	CE  										HORIZ STAB	CRACKED         	B			AJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	49169	7700 				15281177				FOUND VERTICAL/HORIZONTAL STABILIZER REAR ATTACH FITTING CRACKED DURING ROUTINE MAINTENANCE.  REMOVED FIN AND RUDDER.  R	EMOVED ELEVATORS TO REMOVE BRACKET ASSY, P/N 0432004-9.  FOUND REINFORCEMENT, P/N 0432001-15, AND SPARS, P/N 0432001-56,	 ALSO CRACKED IN SAME LOCATION STARTING AT CENTERLINE OF FUSELAGE PROPAGATING TO THE RIGHT SIDE OF STABILIZER APPROXIMAT	ELY 3.0 INCHES.  MOST OF THIS AIRPLANE'S TIME HAS BEEN SPENT IN A FLIGHT SCHOOL.			1	H	7	1 	3O			NT	3A19    					 
1997040300007	19970403	00007	CE  	1997	4	3	97ZZZX1223       	1	19970226	G	7810	075016167	STACK           			CESSNA	185   	A185F       	2072821	CE  										EXHAUST RISER	CRACKED         	B		A	ILIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7239E	105  				18502642				THREE INTERSECTING CRACKS, EACH ABOUT AN INCH LONG, RADIATING ON THE AFT SIDE OF THE CENTER EXHAUST TUBE (BOTH STACKS). 	 FOUND DURING 100-HOUR INSPECTION.  RECOMMEND THAT THE EXHAUST SYSTEM BE INSPECTED DURING THE 50-HOUR INSPECTION.					1	H	7	1 	3O				3A24    					 
1997040300008	19970403	00008	EA  	1997	4	3	97ZZZX1224       	2	19970318	G	8520		CRANKSHAFT      			SOCATA	TB9   	TB9         	8680694	EU  	LYC   	O320  	O320D2A     	41508	EA  					FLANGE	CRACKED         	B	P	A	NI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	508PC					1477	L1754339A			THIS AIRCRAFT IS USED EXCLUSIVELY FOR FLIGHT TRAINING.  ON PRE-FLIGHT, STUDENT AND INSTRUCTOR FOUND OIL ON THE COWLING. 	 UPON INSPECTION, TWO CRACKS WERE FOUND ON THE CRANKSHAFT COVERGING AT THE RADIUS OF THE CRANKSHAFT AND CRANKSHAFT FLANG	E.  THIS ENGINE AND PROPELLER HAVE NO HISTORY OF PROPELLER STRIKE OR SUDDEN STOPPAGE.  IN SERVICE DATE FOR THIS ENGINE A	ND PROPELLER 4/92.  TOTAL TIME SINCE NEW, ENGINE AND PROPELLER, 1,809 HOURS.			1	L	7	1 	3O	3	O	NT	AS1EU   	E274				 
1997040300009	19970403	00009		1997	4	3	97ZZZX1225       	2	19970204	G	7414		CAM ASSY        	BENDIX      	D4LH2021    															IMPULSE COUPLING	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08		779  			R14992K					INSPECTION IAW AD 96-12-7 FOUND NEW SNAP RING STYLE CAM ASSY WORN BEYOND LIMITS.  THIS IS ONE OF SEVERAL THAT DID NOT MA	KE 1,000 HOURS.  FIRST INSPECTION AT 500 HOURS SHOWED WEAR, BUT WITHIN ACCEPTABLE LIMITS.  WEAR WAS WELL BEYOND LIMITS B	EFORE SECOND 500-HOUR INSPECTION WAS DUE.  THESE CAM ASSEMBLIES SEEM TO BE MORE PRONE TO WEAR THAN THE OLD STYLE RIVETED	 ASSEMBLIES.																 
1997040300010	19970403	00010	CE  	1997	4	3	97ZZZX1226       	1	19970217	G	2430	C5930010101	SWITCH          			CESSNA	172   	172M        	2072418	CE  										OVERVOLTAGE	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NE	03	13593	3662 				17262866				PILOT OBSERVED HIGH DISCHARGE RATE ON AMMETER APPROXIMATELY 45 MINUTES INTO FLIGHT.  NO HIGH VOLTAGE LIGHT INDICATION. P	ILOT MADE PRECAUTIONARY LANDING.  REPLACED OVERVOLTAGE LIGHT ASSEMBLY AND OVERVOLTAGE SWITCH.  ALL OTHER COMPONENTS BENC	H CHECKED WITH NO DISCREPANCIES.  OPERATIONAL CHECK WAS SATISFACTORY AND AIRCRAFT WAS RETURNED TO SERVICE.  SUBMITTER SU	GGESTED INSPECTION CHECKLIST REVISION TO INCLUDE TEST OF HIGH VOLTAGE INDICATING SYSTEM.			1	H	7	1 	3O			NT	3A12    					 
1997040300011	19970403	00011	CE  	1997	4	3	97ZZZX1227       	1	19970304	G	3040	T2513	DIODE           		99102222    	CESSNA	402   	402C        	207590R	CE  										WINDSHIELD HEAT	BURNT           	D	S			K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NE	01	1376G					402C0271				PILOT REPORTED ARCING AND SMOKE FROM ELECTRIC HEATED WINDSHIELD.  ELECTRICAL CONNECTION OR LEFT SIDE OF HEATED WINDSHIEL	D HAS DIODE THAT MELTED AND ARCED.					1	L	7	2 	3O				A7CE    					 
1997040300012	19970403	00012	EA  	1997	4	3	97ZZZX1228       	2	19970311	G	7414	1038256013	DISTRIBUTOR GEAR	ELECTROSYS  		PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE MAGNETO	TEETH BROKE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	1392H	655  			6021788R	32R7780156	L1642048A			MAGNETO DISTRIBUTOR TEETH BROKE DURING RUN-UP.  RECOMMEND BETTER QC DURING MANUFACTURE.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997040300013	19970403	00013	CE  	1997	4	3	97ZZZX1229       	1	19970225	G	5751	512400075	AILERON         			CESSNA	402   	402C        	207590R	CE  										BALANCE WEIGHT	WEIGHT BROKEN   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	258PB	12000			119	402C0336				AILERON HAS A 4 FOOT LEAD WEIGHT INSTALLED FOR BALANCING.  LEAD WEIGHT HAD BROKEN AWAY FROM MOUNT AND WAS LOOSE IN LEADI	NG EDGE OF AILERON.  LEADING EDGE WAS REMOVED AND BALANCE WEIGHT WAS RE-ATTACHED TO AILERON.  FLIGHT CONTROL WAS RE-BALA	NCED AND RETURNED TO SERVICE.				1	L	7	2 	3O				A7CE    					 
1997040300014	19970403	00014	SO  	1997	4	3	97ZZZX1230       	1	19970219	G	3213	6531904	CYLINDER        		3564405     	PIPER 	PA28  	PA28181     	7102807	SO  										GEAR LEG	EARS BROKEN     	B			QWLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	8198P	3703 				288090295				TORQUE LINK MOUNTING GEARS BROKE ON LANDING GEAR.  ONE LINK MOUNT HAD EVIDENCE OF PRIOR CRACKS.  BROKEN TAB HAD A DARK A	REA.					1	L	7	1 	3O				2A13    					 
1997040300015	19970403	00015	CE  	1997	4	3	97ZZZX1231       	1	19970311	G	5511	053200198	SPAR            		0532001202  	CESSNA	172   	172N        	2072434	CE  										HORIZONTAL STAB	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	737YY	9200 				17269789				CRACKS FROM FORWARD CENTER LIGHTNING HOLE UP AND DOWN THROUGH SPAR, DOUBLER, UPPER AND LOWER ANGLES AND UPPER-LOWER HORI	ZONTAL SKINS RUNNING AFT.  SUBMITTER SUGGESTED CAUSE AS MOVING AIRCRAFT USING HORIZONTAL AND, ALSO, FATIGUE DUE TO NUMBE	R OF HOURS.  PRIOR TO REMOVAL, HORIZONTAL TIP DEFLECTION 2 INCHES UP - 2 INCHES DOWN.				1	H	7	1 	3O			NT	3A12    					 
1997040300016	19970403	00016	SO  	1997	4	3	97ZZZX1232       	2	19970306	G	8530	653446A5	CYLINDER        			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 3	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	962CC	1101 				21064986	294563R			NR 3 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION.  THE CYLINDER WAS SENT FOR INSPECTION.  THE CYLINDER INSPECTION REVEAL	ED A CRACK WHICH BEGAN AT THE SPARK PLUG HOLE AND TERMINATED AT THE INTAKE VALVE SEAT.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE				 
1997040300017	19970403	00017	SO  	1997	4	3	97ZZZX1233       	2	19970306	G	8530	653446A5	CYLINDER        			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 2	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	962CC	1297 				21064986	294563R			WHILE PERFORMING TCM SB 96-12, CONTINUED AIRWORTHINESS INSTRUCTIONS FOR TCM CYLINDERS, BUBBLES WERE FOUND ACCUMULATING A	ROUND THE NR 2 CYLINDER UPPER SPARK PLUG HOLE.  INSPECTION REVEALED A CRACK AT THE SPARK PLUG HOLE.  THE CRACK ORIGINATE	D AT THE 3 O'CLOCK POSITION AND EXTENDED AFT TOWARD THE FUEL NOZZLE HOLE.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE				 
1997040300018	19970403	00018	SO  	1997	4	3	97ZZZX1234       	2	19970312	G	8520	641931075	THROUGH BOLT    			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 2 CYLINDER	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	17	977GF	781  				TH175	287057R			UPON INSPECTION OF LT ENGINE, FOUND NR 2 CYLINDER SEPARATED FROM CASE BY 2-3 INCHES.  UPPER THROUGH-BOLT APPEARS TO BE B	ROKEN INTERNALLY AS WELL AS LOWER THROUGH-BOLT, ALL UPPER AND LOWER CASE STUDS TO CYLINDER HOLD-DOWN APPEAR TO BE BROKEN	 AT THREAD AREA OR AFT OF THREAD AREA.  PISTON STILL CONNECTED TO CONNECTING ROD TO CRANKSHAFT.  EVIDENCE OF PISTON SKIR	T AND RING MATERIAL IN CASE.  AIRCRAFT IN NORMAL CRUISE SETTING WITH TEMPS AND PRESSURES NORMAL.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997040300019	19970403	00019	CE  	1997	4	3	97ZZZX1235       	1	19970315	G	2436	GCSG5023	CONTROL UNIT    			CESSNA	210   	P210N       	2073454	CE  										GENERATOR	FAILED          	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CE	07	93LC	24   			1030B	P21000741				THE GENERATOR CONTROL UNIT FAILED DURING FLIGHT (IFR).  PLANE MADE AN EMERGENCY LANDING.  NEW GENERATOR CONTROL UNIT INS	TALLED.  CHECKED OK.					1	H	7	1 	3O				3A21    					 
1997040300020	19970403	00020	SO  	1997	4	3	97ZZZX1236       	1	19970201	G	3030	9937726	SWITCH          			PIPER 	PA34  	PA34200T    	7103406	SO  										PITOT HEAT	FAILED          	B			F3NR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	04	633TC					348070314				PILOT REPORTED STRONG ELECTRICAL SMELL FROM LEFT SIDEWALL ELECTRIC SWITCH PANEL WITH ALL ANTI-ICE PROTECTION ON.  INVEST	IGATION REVEALED PITOT HEAT SWITCH HAD ARCED AND BURNED INTERNALLY.  TOTAL TIME ON SWITCH 3,109.7 HOURS SINCE INSTALLED.					1	L	7	2 	3O				A7SO    					 
1997040300294	19970403	00294	EA  	1997	4	3	97ZZZX1237       	2	19970307	G	8530	LW12987C2	CYLINDER        			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 1	DEFECTIVE       	B			FW7R	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			EA	07	2044F		162  			S1722	L2674451A			AFTER THIS CYLINDER WAS INSTALLED, THE ENGINE OIL CONSUMPTION INCREASED.  EVEN AFTER A SUFFICIENT BREAK-IN PERIOD, THE C	ONSUMPTION DID NOT DROP.  AFTER APPROXIMATELY 162 HOURS, THE ENGINE RAN EXTREMELY ROUGH EVEN WITHOUT THE MAIN ROTOR ENGA	GED.  THE SPARK PLUGS WERE REMOVED, AND THE LOWER NR 1 PLUG WAS FOUND COMPLETELY OIL FOULED.  THE CYLINDER WAS REPLACED 	WITH A FACTORY NEW UNIT.			1	G	7	1 	3O	3	O		4H12    	1E10				 
1997040300295	19970403	00295	NE  	1997	4	3	97ZZZX1238       	1	19970227	G	6310	7636104008103	COUPLING        			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE DRIVE	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	22BF					760216				INSPECTION FOUND ENGINE DRIVE COUPLING CRACKED.						1	G	7	2 	3U				H1NE    					 
1997040300296	19970403	00296	GL  	1997	4	3	97ZZZX1239       	2	19970317	G	7230	23052270	COMPRESSOR      			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SCROLL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	5748H	8342 	6506 		CAC90373	45490	CAC890611			DURING DAILY INSPECTION OF ENGINE ASSY, A CRACK WAS DISCOVERED ON THE RIGHT UPPER SIDE OF THE SCROLL, 1.50 INCHES IN LEN	GTH.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997040300297	19970403	00297	CE  	1997	4	3	97ZZZX1240       	1	19970214	G	2823		VALVE           			CESSNA	177   	177         	2073704	CE  										FUEL SELECTOR	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	23	29530	1975 				17700944				DURING ANNUAL INSPECTION  IT WAS DETECTED THAT WHEN TESTING OR OPS CHECKING, THE FUEL SELECTOR VALVE TO DETERMINE DETENT	 OPERATION, MOVEMENT OF THE VALVE CAUSED FUEL TO LEAK OUT THE TOP OF VALVE AROUND THE SHAFT.  THIS HAD BEEN IN PROCESS F	OR SOME TIME BECAUSE THE BELLY WAS FUEL STAINED ALSO.				1	H	7	1 	3O			NT	A13CE   					 
1997040300298	19970403	00298	CE  	1997	4	3	97ZZZX1241       	1	19970301	G	3230	0840125	PUSH PULL ROD   			CESSNA	320   	320E        	2074514	CE  										NLG	BENT            	D	P			O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	11	3425Q					320E0025				AIRCRAFT WAS ON A PART 91 CROSS-COUNTRY FLIGHT.  ON RETURN, THE NOSE GEAR FAILED TO EXTEND.  THE AIRCRAFT WAS LANDED AND	 THE NOSE GEAR COLLAPSED DAMAGING BOTH PROPELLERS, THE NOSE GEAR DOORS, THE NOSE CONE, AND THE PITOT TUBE.  THE AIRCRAFT	 WAS RAISED UP ON THE RUNWAY AND NOSE GEAR WAS LOWERED BY HAND AND TOWED TO THE HANGAR.  ON INSPECTION, FOUND NOSE GEAR 	PUSH-PULL ROD BENT, CRACKED, AND JAMMING ON THE BULKHEAD AT FS 0.00.  THIS IS USUALLY CAUSED BY THE LANDING GEAR BEING E	XTENDED AT TOO HIGH AN AIR SPEED.  RECOMMEND THAT ALL PILOTS BE MADE AWARE OF THIS PROBLEM.  TOTAL TIME ON PART IS 1,556	 HOURS.	1	L	7	2 	3O				3A25    					 
1997040300299	19970403	00299	SW  	1997	4	3	97ZZZX1242       	1	19970201	G	5753	21005000X	BRACKET         			MOONEY	M20   	M20G        	5870316	SW  										FLAP HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	3862N	2900 				680056				FOUND AIRFRAME SIDE OF FLAP HINGE UNAIRWORTHY DUE TO SEVERE INTERGRANULAR EXFOLIATION.  DEFECT WAS FOUND DURING AN ANNUA	L INSPECTION.  AIRCRAFT WAS EQUIPPED WITH A 'SPEED KIT' STC NR SA4023WE, WHICH INCLUDED FLAP HINGE FAIRINGS WITH THE FLA	P HINGE FAIRINGS INSTALLED.  INSPECTION OF THE HINGES IS LIMITED.  THE FAIRINGS ON THIS AIRCRAFT WERE ATTACHED WITH BLIN	D RIVETS.  RECOMMEND REMOVING FAIRINGS AT EACH INSPECTION.			1	L	7	1 	3O				2A3     					 
1997040300300	19970403	00300	SW  	1997	4	3	97ZZZX1243       	1	19970201	G	5753	21004800X	BRACKET         			MOONEY	M20   	M20G        	5870316	SW  										FLAP HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	3862N	2900 				680056				FOUND AIRFRAME SIDE OF FLAP HINGE UNAIRWORTHY DUE TO SEVERE INTERGRANULAR EXFOLIATION.  DEFECT WAS FOUND DURING AN ANNUA	L INSPECTION.  AIRCRAFT WAS EQUIPPED WITH A 'SPEED KIT' STC NR SA4023WE, WHICH INCLUDED FLAP HINGE FAIRINGS WITH THE FLA	P HINGE FAIRINGS INSTALLED.  INSPECTION OF THE HINGES IS LIMITED.  THE FAIRINGS ON THIS AIRCRAFT WERE ATTACHED WITH BLIN	D RIVETS.  RECOMMEND REMOVING FAIRINGS AT EACH INSPECTION.			1	L	7	1 	3O				2A3     					 
1997040300301	19970403	00301	SO  	1997	4	3	97ZZZX1244       	2	19970311	G	7314	6462123A1	PUMP            			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  					RT ENG FUEL	SHAFT SHEARED   	B	L		CSLR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CE	01	7872Q	1230 	1230 			310Q0653	170980R			RIGHT ENGINE FUEL PUMP FAILED DURING FLIGHT.  BOOST PUMP WOULD NOT RUN AND ENGINE STOPPED, UNEVENTFUL LANDING WAS MADE. 	 FOUND FUEL PUMP DRIVESHAFT SHEARED.  FOUND BOOST PUMPS WOLD PRIME ENGINE AND ALLOW ENGINE TO RUN, BUT WOULD NOT RUN IN 	HIGH OR LOW BOOST PUMP POSITION.  FOUND OIL PRESSURE SWITCHES IN NACELLE TO BE DIRTY AND NOT ALLOWING BOOST PUMP TO RUN.	  CLEAN AND ADJUST SWITCHES PER CESSNA 3100 MM, CHAPTER 11.  NOTE:  MEB 88-3 WAS C/W.			1	L	7	2 	3O	3	O		3A10    	3E1				 
1997040300302	19970403	00302	CE  	1997	4	3	97ZZZX1245       	1	19970311	G	2822		SWITCH          			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  					BOOST PUMP	DIRTY           	B			CSLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	7872Q	1230 				310Q0653	170980R			RIGHT ENGINE FUEL PUMP FAILED DURING FLIGHT.  BOOST PUMP WOULD NOT RUN AND ENGINE STOPPED, UNEVENTFUL LANDING WAS MADE. 	 FOUND FUEL PUMP DRIVESHAFT SHEARED.  FOUND BOOST PUMPS WOLD PRIME ENGINE AND ALLOW ENGINE TO RUN, BUT WOULD NOT RUN IN 	HIGH OR LOW BOOST PUMP POSITION.  FOUND OIL PRESSURE SWITCHES IN NACELLE TO BE DIRTY AND NOT ALLOWING BOOST PUMP TO RUN.	  CLEAN AND ADJUST SWITCHES PER CESSNA 3100 MM, CHAPTER 11.  NOTE:  MEB 88-3 WAS C/W.			1	L	7	2 	3O	3	O		3A10    	3E1				 
1997040300303	19970403	00303	CE  	1997	4	3	97ZZZX1246       	1	19970201	G	3221		BRACKET         			CESSNA	170   	170A        	2072304	CE  										TAIL WHEEL	BOLT BROKE      	D	L	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9032A	5714 				18787				TAIL WHEEL SEPARATED FROM AIRCRAFT.  INVESTIGATION FOUND ASSY HAD SEPARATED DUE TO BROKEN BOLT.  BOLT HAD BEEN DYE CHECK	ED AT LAST ANNUAL DUE TO REPORT OF ANOTHER AIRCRAFT WITH BROKEN BOLT.  THE BOLT CRACK DID NOT SHOW UP ON A DYE CHECK.  S	UBMITTER RECOMMENDED TO NDT X-RAY OR EDDY CURRENT CHECK.				1	H	7	1 	3O				A799    					 
1997040300304	19970403	00304	CE  	1997	4	3	97ZZZX1247       	1	19970321	G	5700		STRUT           			CESSNA	140   	140         	2071602	CE  										WING LIFT STRUT	CORRODED        	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	3728V	2300 				15005				REMOVED WING LIFT STRUT VERTICAL BRACES TO FACILITATE REPAINT OF STRUTS AND BRACES.  FOUND CORROSION ON STRUT AT BRACE C	LAMP AREA.  PTTING HAD OCCURRED CIRCUMFERENTIALLY AROUND THE LIFT STRUT.  ALTHOUGH PITTING WAS NOT EXCESSIVE IN THIS CAS	E, FURTHER DAMAGE COULD SERIOUSLY COMPROMISE STRUT INTEGRITY WHICH COULD RESULT IN A 'WING FOLD' IN-FLIGHT.  PITTING OCC	URRED IN A STRAIGHT LINE AROUND THE STRUT REDUCING WALL THICKNESS OF THE TUBING.  NON-HYDROSCOPIC TAPE HAD BEEN USED AS 	A CHAFE STRIP UNDER BRACE CLAMP.  RECOMMEND REMOVAL OF VERTICAL BRACE DURING REFINISHING OR WHENEVER CORROSION IS DETECT	ED.	1	H	7	1 	3O			NC	A768    					 
1997040300305	19970403	00305	SO  	1997	4	3	97ZZZX1248       	2	19970320	G	8520		CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 6 CYL STUD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	999AN					TH924	561912			DURING OIL CHANGE, FOUND 1 INCH CRACK EXTENDING FROM CYLINDER NR 6 UPPER REAR STUD.  AD 77-13-22 PARA(A) ADDRESSES THIS 	SUBJECT, BUT IS NOT INCLUDED IN THE SERIAL NUMBER REQUIREMENT LIST.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997040300307	19970403	00307	CE  	1997	4	3	97ZZZX1250       	1	19970307	G	3233		ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  										NLG	SLIPPING        	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	42TD	600  				BB968				ACTUATOR WAS INSTALLED NEW 14 MONTHS AGO.  HAD TO MAKE ADJUSTMENTS TWICE SI NCE INSTALLED FOR RED INSTRANSIT LIGHT STAYI	NG ON .  ON THIRD TIME, FOUND END PLAY EXCESSIVE AND SPRING TENSION TOO TIGHT, NOSE GEAR NOT UP ALL THE WAY.  CONSULTED 	BEECH REP AND WAS TOLD PINION GEAR IS SLIPPING IN ACTUATOR.  ALSO, FOUND R12ZZ BEARING BAD TO NOSE GEAR ACTUATOR DRIVE A	SSY, P/N 90820014-1.			1	L	7	2 	4T				A24CE   					 
1997040300309	19970403	00309	NE  	1997	4	3	97ZZZX1251       	2	19970305	G	7313		NOZZLE          			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					STAGE 1	REQUIRED ADJ    	D				K				NONE                    				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			GL	23	50CK	10399	7232 			157	241033			LEFT ENGINE FLAMED OUT.  ADJUSTED STAGE 1 AIR NOZZLE.  GROUND RUN AND PERFORMANCE CHECK GOOD.  C/W ALTITUDE ACCELERATION	 TEST FLIGHT.  OPS CHECK GOOD.					2	L	7	2 	4J	4	J		A10CE   	1E16				 
1997040300310	19970403	00310	NE  	1997	4	3	97ZZZX1252       	2	19970309	G	7200		ENGINE          			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					LEFT ENGINE	FAIL CHECK      	E				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	23	50CK	10405	7233 			157	241033			LEFT ENGINE FLAME OUT.  RE-ADJUSTED STAGE 1 AIR NOZZLE.  INSPECTED COMBUSTION LINER AND INSTALLED OVERHAULED FUEL CONTRO	L UNIT.  GROUND RUN LEAK AND PERFORMANCE CHECK GOOD.  LEFT ENGINE FAILED ACCELERATION CHECK AT FL 410.  REPLACED ENGINE 	WITH S/N 251-095A.  GROUND RUN AND LEAK CHECK GOOD.				2	L	7	2 	4J	4	J		A10CE   	1E16				 
1997040300311	19970403	00311	NE  	1997	4	3	97ZZZX1253       	2	19970312	G	7320	C2995150202	CONTROL CABLE   			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					EMERGENCY POWER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	762FE	2774 				208B0255	19131			EMERGENCY POWER CABLE AND ATTACH BRACKETS WORN.  THE BRACKETS WORN WITHIN .0625 INCH OF BEING COMPLETELY THROUGH MATERIA	L.  EMERGENCY POWER CABLE WORN THROUGH ATTACH POINT ON CABLE.  SUGGEST WEAR IS NORMAL, CABLE AND ATTACH BRACKETS NEED TO	 BE OF HEAVIER MATERIAL.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
1997040300312	19970403	00312	NE  	1997	4	3	97ZZZX1254       	2	19970312	G	7320	24510022	BRACKET         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					EMERGENCY POWER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	762FE	2774 				208B0255	19131			EMERGENCY POWER CABLE AND ATTACH BRACKETS WORN.  THE BRACKETS WORN WITHIN .0625 INCH OF BEING COMPLETELY THROUGH MATERIA	L.  EMERGENCY POWER CABLE WORN THROUGH ATTACH POINT ON CABLE.  SUGGEST WEAR IS NORMAL, CABLE AND ATTACH BRACKETS NEED TO	 BE OF HEAVIER MATERIAL.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
1997040300313	19970403	00313	NE  	1997	4	3	97ZZZX1255       	2	19970312	G	7320	24510021	BRACKET         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					EMERGENCY POWER	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	762FE	2774 				208B0255	19131			EMERGENCY POWER CABLE AND ATTACH BRACKETS WORN.  THE BRACKETS WORN WITHIN .0625 INCH OF BEING COMPLETELY THROUGH MATERIA	L.  EMERGENCY POWER CABLE WORN THROUGH ATTACH POINT ON CABLE.  SUGGEST WEAR IS NORMAL, CABLE AND ATTACH BRACKETS NEED TO	 BE OF HEAVIER MATERIAL.				1	H	7	1 	3T	3	T		A37CE   	E4EA				 
1997040300314	19970403	00314	GL  	1997	4	3	97ZZZX1256       	2	19970312	G	7260	6854857	GEARSHAFT       								ALLSN 	250C  	250C20B     	03013	GL  					TACH DRIVE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11					UPI314					TACHOMETER DRIVE END WORN ABOUT .040 INCH.											3	U			E4CE				 
1997040300315	19970403	00315	CE  	1997	4	3	97ZZZX1257       	1	19970303	G	3244	184F102	TIRE            	GOODYEARAERO		LEAR  	55    	55LEAR      	5170702	CE  										BALANCE PATCH	DEFECTIVE       	H				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			GL	17	1125M		662  			065				THE BALANCE PATCH THAT IS GLUED TO THE INSIDE OF NOSE TIRE, CAME OFF.  THIS CAUSED THE NOSE WHEEL TO BECOME OUT OF BALAN	CE CREATING A SHIMMY DURING GROUND OPERATION.  LANDINGS, 135.					2	L	7	2 	4F				A10CE   					 
1997040300318	19970403	00318	SO  	1997	4	3	97ZZZX1260       	1	19970315	G	7600	452557	ROD END         			PIPER 	PA34  	PA34*       		SO  										ENGINE CONTROL	BEARING FROZE   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										DURING INSTALLATION OF PIPER ENGINE CONTROL MODIFICATION KIT NR 79509, NOTICED THAT KIT ROD END BEARINGS WERE UNUSUALLY 	STIFF.  AFTER 100 HOURS TIS, CONTROL ROD END BEARINGS, 4 EACH, WERE ALL FROZEN.  SUBMITTER STATED THAT THE BEARINGS, P/N	 452 557 (PS 10020-4-1R) ARE DEFECTIVE.				1	L	7	2 	3O			RT	A7SO    					 
1997040300638	19970403	00638	WP  	1997	4	3	97ZZZX1262       	1	19970220	G	5751		FINGER DOUBLER  			DOUG  	DC10  	DC1010      	3022110	WP  										RT OTBD AIL SKIN	DISBONDED       	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1813U					46612				DURING C-CHECK INSPECTION, FOUND RIB CAP FINGER DOUBLER DISBONDED ON RIGHT OTBD AILERON, TWO AREAS, LOWER SKIN, 1 EACH A	T INBD END, AND 1 EACH AT CENTER HINGE.					2	L	7	3 	4F				A22WE   					 
1997040300639	19970403	00639	WP  	1997	4	3	97ZZZX1263       	1	19970220	G	5751		FINGER DOUBLER  			DOUG  	DC10  	DC1010      	3022110	WP  										RT AIL OTBD	DISBONDED       	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1849U					46939				DURING C-CHECK INSPECTION, FOUND RIB CAP FINGER DOUBLER DISBONDED, RT OTBD AILERON, LOWER SKIN.						2	L	7	3 	4F				A22WE   					 
1997040300640	19970403	00640	WP  	1997	4	3	97ZZZX1264       	1	19970219	G	5751		FINGER DOUBLER  			DOUG  	DC10  	DC1010      	3022110	WP  										RT AIL XORS 1013	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1849U					46939				DURING C-CHECK INSPECTION, FOUND RIB CAP FINGER DOUBLER DISBONDED RT OTBD AILERON UPPER SKIN.  SUSPECT CAUSE, UNKNOWN.						2	L	7	3 	4F				A22WE   					 
1997040300651	19970403	00651	SW  	1997	4	3	97ZZZX1270       	1	19970213	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3185P	1664 			A1666	45775				DURING DAILY INSPECTION FOUND SKIN CORRODED AND SEPARATED AT TIP.  CORROSION AT WEAR PADS OR ROOT END.						1	G	7	1 	3U				H2SW    					 
1997040300652	19970403	00652	SW  	1997	4	3	97ZZZX1271       	1	19970206	G	6320	2040401321	INNER RACE      		206040004111	BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3186P		2842 		BMC00271	45776				METAL CHIPPING AWAY FROM THE INNER RACE OF ONE BEARING SET FROM PLANETARY GEAR SET OF THE MAIN ROTOR TRANSMISSION.  DETE	CTED BY THE CHIP DETECTOR.					1	G	7	1 	3U				H2SW    					 
1997040300653	19970403	00653	SW  	1997	4	3	97ZZZX1272       	1	19970218	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3195P	828  			A1311	45789				DISCOVERED DURING DAILY INSPECTION, CORROSION AND SKIN SEPARATION AT SPAR TIP. CORROSION AT ROOT END WEAR PADS.						1	G	7	1 	3U				H2SW    					 
1997040300654	19970403	00654	SW  	1997	4	3	97ZZZX1273       	1	19970121	G	6320	206040030003	BEARING         		206040004107	BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	FAILED          	B			ALGR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	351AL	1442 			J0358	51431				TRANSMISSION MADE CHIP LIGHTS,  FOUND BEARING BALLS BREAKING DOWN.						1	G	7	1 	3U				H2SW    					 
1997040300655	19970403	00655	SW  	1997	4	3	97ZZZX1274       	1	19970128	G	5530	206023126101	VERTICAL FIN    			BELL  	206   	206L3       	1182108	SW  										LT AUXILIARY	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	355AL	4975 			BP00002190C0	51444				DAILY INSPECTION FOUND CRACK ON LEFT AUXILIARY VERTICAL FIN AT ATTACH POINT (4 INCH) SPIDER.  THIS IS A PROBLEM THAT WAS	 CORRECTED MANY YEARS AGO ON 206L-1 SERIES.					1	G	7	1 	3U				H2SW    					 
1997040300656	19970403	00656	SW  	1997	4	3	97ZZZX1275       	1	19970213	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										M/R	SEPARATED       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	366AL	1693 			A1673	51470				DURING DAILY INSPECTION, FOUND UPPER SKIN SEPARATED AT SPAR TIP.  CORROSION OR ROOT END AT WEAR PADS.						1	G	7	1 	3U				H2SW    					 
1997040300658	19970403	00658	SW  	1997	4	3	97ZZZX1277       	1	19970206	G	6510	406090340101	DISC PACK       		407040302101	BELL  	407   	407         		SW  										NR 6 T/R SHAFT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	309  	309  			53044				DURING A 50-HOUR INSPECTION, FOUND T/R COUPLING DISC PACK, P/N 406-090-340-101, TO HAVE A CRACK ON ONE OUTER LAMINATE EX	TENDING THREE-FOURTHS OF THE WAY THROUGH THE LAMINATE.  THE DESIGN OF THIS AIRCRAFT DOES NOT ALLOW THE NR 4 THROUGH THE 	NR 7 (ALL OF THEM ON THE TAILBOOM) T/R DRIVESHAFTS TO FLOAT.  IT IS GOING TO BE HARDER ON DISC PACS THAN A 206L.  THIS I	S THE THIRD OCCURRENCE OF THIS PROBLEM ON A FLEET OF TWO A/C WITH 550 HOURS FLIGHT TIME COMBINED.			1	G	7	1 	3U			O	H2SW    					 
1997040300659	19970403	00659	SW  	1997	4	3	97ZZZX1278       	1	19970106	G	6510		HANGER SUPPORT  		407040302101	BELL  	407   	407         		SW  										NR 4 T/R BRG	LOOSE           	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	407AL					53044				DURING A 50-HOUR INSPECTION, THE NR 4 T/R BEARING HANGER SUPPORT WAS FOUND LOOSE FLOATING UP AND DOWN ON THE ATTACH BOLT	.  NR 7 HANGER SUPPORT WAS FOUND TO BE MAKING MUD AT CONTACT AREA WITH TAILBOOM BRACKET.  FOUND ATTACH BOLT P/N NAS6604D	65 WORN AND STEPPED ON NR 4 SHAFT AND ONLY SLIGHTLY WORN ON NR 7 SHAFT.  THE 407 MM REQUIRES TORQUE OF 50-70 INCHES/POUN	DS.  NEITHER CHAPTER 65 OR PARAGRAPHS 1-13 TORQUES STATE WHETHER OR NOT NUT DRAG SHOULD BE FACTORED IN.  ALSO, DRAWING I	N THE TAILBOOM BRACKET WILL EFFECT THE FINAL TORQUE.		1	G	7	1 	3U			O	H2SW    					 
1997040300660	19970403	00660	SW  	1997	4	3	97ZZZX1279       	1	19970114	G	6220	407010111101	CENTER CONE SET 			BELL  	407   	407         		SW  										M/R	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	263  				53044				AFTER SITTING OFFSHORE IN MODERATE WINDS, THE PILOT NOTICED AN INCREASE IN VIBRATION LEVEL OF THE MAIN ROTOR ON THE NEXT	 FLIGHT.  THE MAIN ROTOR CENTER CONE SET P/N 407-010-111-101 HAS A THICK TEFLON COATING ON THE INSIDE OF CONES.  THIS CO	ATING WAS DAMAGED ALLOWING THE HUB TO SHIFT.  NOTE:  BEFORE THE MAIN ROTOR HEAD WAS REMOVED, A MAST NUT RE-TORQUE WAS PE	RFORMED.  NO LOSS OF TORQUE WAS FOUND.			1	G	7	1 	3U			O	H2SW    					 
1997040300661	19970403	00661	SW  	1997	4	3	97ZZZX1280       	1	19970224	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R SHAFT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	394  	394  			53044				DURING ROUTINE INSPECTION, FOUND ONE DISC OF DISC PAC CRACKED IN THREE PLACES.  TWO CRACKS WERE RUNNING PARALLEL WITH TH	E GRAIN METAL EXTENDING APPROXIMATELY 75 PERCENT OF THE WIDTH OF THE DISC.  THE THIRD CRACK RUNNING PERPENDICULAR TO THE	 GRAIN APPROXIMATELY 75 PERCENT OF THE WIDTH OF THE DISC.				1	G	7	1 	3U			O	H2SW    					 
1997040300662	19970403	00662	GL  	1997	4	3	97ZZZX1281       	2	19970109	G	7320	G851430	REAR SUPPORT    		G890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE COMP	CRACKED         	B			ALGR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	4572V	37119	770  		ER38066	S665	CAE836143			COMPRESSOR WAS REMOVED FOR LOW POWER AND UPON PRELIMINARY INSPECTION, FOUND CRACKING OF REAR SUPPORT.  AT APPROXIMATELY 	1-5 INCHES OUT FROM BEARING BORE, FOUND CRACKING FROM 220 DEGREES - 260 DEGREES AROUND ON REAR SUPPORT.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997040300664	19970403	00664	SW  	1997	4	3	97ZZZX1283       	1	19970115	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	SEPARATED       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5750Y	3303 			A1242	45517				DISCOVERED DURING ROUTINE MAINTENANCE, SKIN SEPARATED FORM SPAR AT BLADE TIP.						1	G	7	1 	3U				H2SW    					 
1997040300665	19970403	00665	SW  	1997	4	3	97ZZZX1284       	1	19970213	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	SEPARATION      	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5760A	1876 			A1358	45538				DURING DAILY INSPECTION FOUND SKIN SEPARATED OVER SPAR AND BLADE TIP.						1	G	7	1 	3U				H2SW    					 
1997040300666	19970403	00666	SW  	1997	4	3	97ZZZX1285       	1	19970213	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	SEPARATION      	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5760A	1876 			A1361	45538				DURING DAILY INSPECTION FOUND SKIN SEPARATED AND CORRODED OVER SPAR AT TIP.						1	G	7	1 	3U				H2SW    					 
1997040300667	19970403	00667	NE  	1997	4	3	97ZZZX1286       	1	19970120	G	6210	7615009100050	BLADE RIB       			SKRSKY	S76   	S76         	8143010	NE  										M/R	DEDBONDED       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	702AL	6257 			A08600880	760243				DISCOVERED DURING 500 HOUR INSPECTION THAT BLADE TIP RIB WAS DEBONDED.						1	G	7	2 	3U				H1NE    					 
1997040300668	19970403	00668	SW  	1997	4	3	97ZZZX1287       	1	19970212	G	6230	206010443001	DUPLEX BEARING  			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	PITTED          	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618	244  				45503				SWASHPLATE REMOVED DUE TO BEARING ROUGHNESS.  FOUND DUPLEX BEARING RACE PITTED DURING DISASSEMBLY AND INSPECTION.						1	G	7	1 	3U				H2SW    					 
1997040300826	19970403	00826	NM  	1997	4	3	97ZZZX1307       	1	19970311	G	2720	69356021	LEVER ASSY      		65C370527   	BOEING	737   	7373G7      	1384595	NM  										RUDDER PCU	BEARING DEFECT  	B		A	IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			43783		1026ASP					TESTING, RUDDER PCU WAS WORKING FOR ABOUT 5 COMPLETE CYCLES SECONDARY STROKE/FLOW TEST PASSED IN BOTH RETRACT AND EXTEND	 POSITION.  IN NEUTRAL TO FULL EXTEND, UNIT WAS BYPASSING AND WANTING TO GO IN THE RETRACT POSITION.  IT REQUIRED AN EXC	ESSIVE AMOUNT OF FORCE TO KEEP IN NEUTRAL OR EXTEND.  UNIT WAS PUT IN THE ELECTRICAL POSITION MODE, UNIT WOULD NOT RESPO	ND.  IT WOULD HAVE A 5 TO 10 SECOND DELAY AND THEN WOULD OSCILLATE.  COULD NOT CONTROL UNIT WITH THE POSITION KNOB.  UNI	T WAS OUT IN THE TOGGLE POSITION.  IT WAS SHUDDERING IN BOTH DIRECTIONS.  BEARING ON LEVER ASSY (18-1106) WAS NOT PROPER	LY SECURED CAUSING BEARING TO POP UP ENOUGH TO CAUSE THE PRIMARY SLIDE TO BIND UP CAUSING AN UNWANTED RUDDER INPUT.	2	L	7	2 	4F			RT	A16WE   					 
1997040300829	19970403	00829	SO  	1997	4	3	97ZZZX1310       	1	19970319	G	2750	454657	BREAKER         			PIPER 	PA31  	PA31350     	7103110	SO  										FLAP	FAILED          	B			DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	23TL	3295 				318152172				DURING OUTGOING RUN-UP AFTER ANNUAL INSPECTION, FOUND BOTH COWL FLAPS INOPERABLE.  TROUBLESHOT AND FOUND 10-AMP CIRCUIT 	BREAKER, P/N 454-657, FAILED TO OPEN.  REPLACED BREAKER WITH NEW AND OPERATIONAL CHECKED GOOD.  CUT OPEN OLD BREAKER AND	 FOUND CORROSION ON CONTACTS AND ALL INTERNAL PARTS.				1	L	7	2 	3O				A20SO   					 
1997040300830	19970403	00830	CE  	1997	4	3	97ZZZX1311       	1	19970315	G	2432	RG35	BATTERY         	CONCORDEBATT		CESSNA	182   	182K        	2072724	CE  										NEG POST	POST MELTED     	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	2624R	29   			CBC293615	18258324				THE AIRPLANE HAS A CONCORDE RG35 (RECOMBINANT GAS) SEALED BATTERY INSTALLED.  THE NEGATIVE BATTERY POST-POTTING SOLDER M	ELTED (TWO TIMES, TWO DIFFERENT BATTERIES) JUST ENOUGH TO LEAVE THE TERMINAL GROUND STRAP CONNECTION LOOSE.  I BELIEVE I	T HAPPENS ON CHARGE-UP AFTER A LOW BATTERY.  BOTH OF THE DAMAGED BATTERIES WERE REPLACED UNDER WARRANTY.  CONCORDE SAYS 	THAT THEY ARE AWARE OF THE PROBLEM AND ARE WORKING ON A FIX.  THIS ARIPLANE WAS USED IN FREQUENT IFR CONDITIONS AND WAS 	JUST A MOMENT AWAY FROM TOTAL ELECTRICAL FAILURE ON TWO SEPARATE OCCASIONS.		1	H	7	1 	3O			NT	3A13    					 
1997040300831	19970403	00831	CE  	1997	4	3	97ZZZX1312       	1	19970219	G	5210	354104565	LATCH           			BEECH 	58    	58          	1152740	CE  										FORWARD COCKPIT	REQUIRED ADJ    	C	S	A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SW	03	3012W					TH364				SHORTLY AFTER TAKEOFF, COPILOT'S DOOR POPPED OPEN.  AIRCRAFT RETURNED TO AIRPORT AND LANDED SAFELY.  READJUSTED UPPER LA	TCH.  SUBMITTER SUGGESTION:  EXTRA CARE BE TAKEN DURING 100-HOUR INSPECTION TO ENSURE PROPER LATCH RIGGING.					1	L	7	2 	3O				3A16    					 
1997040300832	19970403	00832	SO  	1997	4	3	97ZZZX1313       	2	19970226	G	8550		ENGINE          								CONT  	O470  	IO470C      	17026	SO  					ENGINE OIL	LOW PRESSURE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05		2842 	7    				711617C			AT ANNUAL INSPECTION, ENGINE OIL PRESSURE WAS BELOW SPECIFIED LIMITS.  CAUSE UNKNOWN.											3	O			E273				 
1997040300834	19970403	00834	SO  	1997	4	3	97ZZZX1315       	1	19970318	G	5730		SKIN            			PIPER 	PA46  	PA46350P    		SO  										LT WING MLG DOOR	CRACKED         	B			AIHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	61FL	1294 				4622037				DURING THE ANNUAL INSPECTION, A CRACK WAS FOUND IN THE BOTTOM SKIN OF THE LEFT WING.  THE CRACK WAS .75 INCH LONG AND ST	ARTED AT THE FRONT CORNER OF THE LEFT MAIN GEAR DOOR.  THE CRACK WAS LOCATED .1250 INCH AFT OF THE S.B. REINFORCEMENT KI	T.  THE CRACK RAN PARALLEL TO THE SPAR REINFORCEMENT PATCH.				1	L	7	1 	3O			RT	A25SO   					 
1997040300836	19970403	00836	SO  	1997	4	3	97ZZZX1317       	1	19970307	G	5510	452394	BEARING         			PIPER 	PA28  	PA28161     	7102803	SO  										STABILATOR	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	PA281					288016285				PIVOT BEARINGS WERE WORN TO POINT WHERE OUTBOARD END OF STABILATOR HAD 2 INCHES PLAY UP AND DOWN.						1	L	7	1 	3O				2A13    					 
1997040300837	19970403	00837	SO  	1997	4	3	97ZZZX1318       	1	19970304	G	2840	55000092	FUEL LINE       			GULSTM	AA5   	AA5B        	3960105	SO  										COCKPIT	BROKEN          	G		A		A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			GL	03	81182					AA5B0450				REPORTED FUEL IN COCKPIT AND LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED BROKEN FUEL LINE.						1	L	7	1 	3O				A16EA   					 
1997040300838	19970403	00838	EA  	1997	4	3	97ZZZX1319       	2	19970307	G	8530	SL14995	SPRING          			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  					SHROUD TUBE	BROKE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	8677L					255427	L1480540			DURING ASSEMBLY OF THIS ENGINE, 6 SHROUD TUBE SPRINGS WERE INSTALLED, 3 BROKE WHEN THE NUT WAS TIGHTENED.  THESE SPRINGS	 WERE SUPPLIED AS PART OF A PACKET SET FROM SUPERIOR AIR PARTS.					1	L	7	1 	3O	3	O		2A10    	E295				 
1997040300839	19970403	00839	EA  	1997	4	3	97ZZZX1320       	1	19970301	G	7713		GAUGE           			SCWZER	G164  	G164A       	3952704	EA  										MANIFOLD PRESS	READS LOW       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	84PG					1536				INVESTIGATION FOR CONTINUING CYLINDER PROBLEMS, CRACKS, ETC., FOUND MANIFOLD PRESSURE GAUGE READING LOW.  VERIFIED INCOR	RECT READING PER BARO PRESSURE.  SUSPECT OVERBOOST OF CYLINDERS DUE TO INCORRECT MP GAUGE READING.					1	Q	7	1 	3R				1A16    					 
1997040300840	19970403	00840	EU  	1997	4	3	97ZZZX1321       	1	19970305	G	2730		LEVER ARM       			BRAERO	1000  	BAE1251000  	1500287	EU  										ELEVATOR	GOUGED          	B	L	A	LEGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	514QS	3312 				NAS1005				DURING A ROUTINE INSPECTION, FOUND ELEVATOR LEVER ARM (IPC 55-20-05-01, ITEM 370) GOUGED ON THE OUTBOARD SIDE APPROXIMAT	ELY .5 INCH ABOVE ELEVATOR ROD ATTACHEMENT BOLT.  DURING REMOVAL AND INSTALLATION OF THE TAIL ASSEMBLY BULLET FAIRING, (	IPC 55-30-10-01, PAGE 0) SCREWS (ITEM 10) FOR THE LEFT AND RIGHT INSPECTION PANELS (ITEMS 25 AND 30) CAN CONTACT THE ELE	VATOR ACTUATING LEVER ESPECIALLY IF LONGER SCREWS ARE INSTALLED.  FOUND LONGER SCREWS HAD BEEN INSTALLED IN SEVERAL LOCA	TIONS ON THIS PANEL.		2	L	7	2 	4F			RT	A3EU    					 
1997040300841	19970403	00841	CE  	1997	4	3	97ZZZX1322       	1	19970319	G	7333	3035737	LINE            			BEECH 	2000  	2000        	1152000	CE  										FUEL FLOW XDUCER	CHAFED          	B		A	ERYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	999RF	1194 				NC9				DURING ROUTINE INSPECTION, FOUND THE STAINLESS STEEL FUEL LINE FROM THE FUEL FLOW TRANSDUCER TO FLOW DIVIDER IN CONTACT 	WITH AND CHAFED INTO BY POWER LEVER BRACKET, P/N 122-940028-1.  CHAFE AREA IS AT THE APEX OF THE FIRST BEND OF THIS LINE	 AS IT LEAVES THE FUEL FLOW TRANSDUCER.  INSPECTED TWO OTHER AIRCRAFT AND FOUND SIMILAR CONTACT IN 4 OUT OF 6 POSSIBLE L	OCATIONS.			1	L	7	2 	4T			RT	A38ACE  					 
1997040300842	19970403	00842	GL  	1997	4	3	97ZZZX1323       	2	19970321	G	7210	6889700	PINION GEAR     		6886442     						ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		4889 			2229076					INTERNAL SPLINES WORN OR AT LEAST BEYOND MAXIMUM LIMITS.  NO WEAR STEP.  BOTH BEARINGS JOURNALS .0002 INCH BELOW MINIMUM	 DIAMETER.										3	U			E4CE				 
1997040300843	19970403	00843		1997	4	3	97ZZZX1324       	1	19970321	G	3350	EMSE299A	BATTERY PACK    	GULTON      	EMBS1392    															GALLEY	SHORTED         	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1155TM					BATTERY PACK HAS SEVERAL SHORTED CELLS.  BATTERY PACK WAS REPLACED NEW FROM MANUFACTURER ON 1-30-97.  EMERGENCY LIGHTS C	AME ON WITH SWITCH OFF.																		 
1997040300844	19970403	00844	CE  	1997	4	3	97ZZZX1325       	1	19970320	G	3010	260106712	LINE            			CESSNA	208   	208B        	2073701	CE  										DEICE	HOLED           	B		A	P3NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	7580B	5013 				208B0051				DURING A SCHEDULED INSPECTION, NOTED THE SECOND CYCLE OF THREE WAS NOT HOLDING ENOUGH PRESSURE IN THE SURFACE DEICE SYST	EM.  INSPECTION REVEALED A HOLE IN AN ALUMINUM LINE CAUSED BY A SCREW IN AN INSPECTION COVER MAKING CONTACT.  SUGGEST MA	KING SURE ADEQUATE CLEARANCE EXISTS AROUND INSPECTION COVERS AND PLUMBING.				1	H	7	1 	3T				A37CE   					 
1997040300845	19970403	00845	CE  	1997	4	3	97ZZZX1326       	1	19970312	G	8010	2T4687	RELAY           		241804331   	LEAR  	35    	35A         	5170602	CE  										START CUTOUT	DEFECTIVE       	B			DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	258G	3929 				443				HAD INTERMITTENT STARTER OPERATION ON NR 2 ENGINE.  'DELAYED' OR NO ROTATION WHEN STARTER SWITCH WAS MOVED TO THE START 	POSITION.  FOUND POOR ELECTRICAL CONNECTION THROUGH THE CONTACTS OF THE K68 START CUT-OUT RELAY, P/N 2T-4687, LOCATED IN	 THE FUEL CONTROL RELAY PANEL,  P/N 2418043-31.  REPLACED RELAYS K68, K7A, K7B, AND K5.  ALL LIKE PART NUMBERS WITH NEW 	STYLE RELAYS P/N E210-1655 AND OPERATIONAL CHCKED GOOD.			2	L	7	2 	4F				A10CE   					 
1997040300846	19970403	00846	EU  	1997	4	3	97ZZZX1327       	1	19970318	G	5522	54630122	ELEVATOR        			ISRAEL	1123  	1123        	4500101	EU  										LT-RT ELEV	CORRODED        	H			GQFG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	44PR					169				MAJOR CORROSION ON TRAILING EDGE RIVET LINE.  MISSING AND WORKING RIVETS AS A RESULT.						2	M	7	2 	4J				A2SW    					 
1997040300847	19970403	00847	EA  	1997	4	3	97ZZZX1328       	2	19970310	G	7314	02532330003	PUMP            	PESCO       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE FUEL	SEIZED          	D				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			GL	23	942CE	6295 	3459 			BB494	PCE81782			LEFT ENGINE ROLLED BACK TO IDLE CUT-OFF IN FLIGHT.  (FLAME OUT.)  MAIN ENGINE FUEL PUMP SEIZED CAUSING ROUNDING OFF OF S	PLINE ON PUMP AND DRIVE COUPLING.  SUBMITTER SUGGESTED TO INCREASE FREQUENCY OF INSPECTION FOR THIS COMPONENT.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997041000036	19970410	00036	CE  	1997	4	10	97ZZZX1329       	1	19970127	G	3710	3H647	REGULATOR       			CESSNA	500   	S550        	2076607	CE  										GYRO AIR	DEFECTIVE       	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	211QS	8128 				S5500011				DURING POST-INSPECTION RUN UP, NOTICED CO-PILOT'S ATTITUDE GYRO AIR PRESSURE LOW AND GYRO UNSTABLE.  FOUND FIRST STAGE A	IR PRESSURE REGULATOR LOWER THAN NORMAL AND UNADJUSTABLE. REPLACED REGULATOR.  FOUND CORROSION, DIRT, AND WATER INSIDE R	EGULATOR.  AIR FILTER AND WATER SEPARATOR NOT REMOVING WATER.				1	L	7	2 	4F			RT	A22CE   					 
1997041000037	19970410	00037	CE  	1997	4	10	97ZZZX1330       	1	19970113	G	7720		TERMINAL LUG    			CESSNA	500   	S550        	2076607	CE  										T1 PROBE	WRONG PART      	B			CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	93QS					S5500093				DURING ENGINE INSPECTION, FOUND IMPROPER TERMINAL LUG ON RIGHT ENGINE T1 PROBE.  THE TERMINAL APPEARS TO BE THE PROPER M	ATERIAL (AL), BUT IS NOT A 1-322338-0 TERMINAL.  IT APPEARS THAT THIS TERMINAL LUG WAS INSTALLED WHEN THE PROPER ONE WAS	 UNAVAILABLE.				1	L	7	2 	4F			RT	A22CE   					 
1997041000038	19970410	00038	NE  	1997	4	10	97ZZZX1331       	3	19970220	G	6111	A2202	BEARING RACE    			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	INBD BLADE	SPLIT           	G	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	94UX	6635 	2882 		6	UE94		HJ211		BLADE, S/N 930, PROPELLER WAS REMOVED FOR LOOSE BLADES AND SLINGING GREASE.  WHEN DISASSEMBLED FOUND BLADE BEARING (SPLI	T BEARING).  ONE-HALF OF IT SPLIT IN TWO, OTHER ONE-HALF HAS ONE SIDE SPLIT AND BROKEN OFF, 2 INCH PIECE, AND OTHER SIDE	 SPLIT .50 INCH.				2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997041000039	19970410	00039	NE  	1997	4	10	97ZZZX1332       	3	19970220	G	6111	A2202	BEARING RACE    			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	INBD BLADE	SPLIT           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	94UX	6635 	2882 		34	UE94		HJ211		BLADE, S/N 982, PROPELLER WAS REMOVED FOR LOOSE BLADES AND SLINGING GREASE.  WHEN DISASSEMBLED, FOUND ONE-HALF OF SPLIT 	BEARING TO BE CRACKED UP CENTER APPROXIMATELY 2 INCHES.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997041000040	19970410	00040	NM  	1997	4	10	97ZZZX1333       	1	19970304	G	2731	600035507	CONTROL CABLE   		600014503   	PIPER 	PA60  	PA60600     	7106001	NM  										ELEVATOR TRIM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	8234J	8600 				600638796120				DURING INSPECTION, MAINTENANCE NOTICED THAT THERE WAS 'SPRING' IN THE ELEVATOR TRIM CABLE ASSY.  MECHANIC APPLIED SLIGHT	 PRESSURE TO TRIM TABS AT WHICH POINT THE CABLE SNAPPED.  INVESTIGATION REVEALED THE CABLE WAS BROKEN .25 INCH FROM THE 	SWAGED END.  SUGGEST PERIODIC REPLACEMENT OF CABLE AS IT IS NOT POSSIBLE TO INSPECT IT.				1	M	7	2 	3O			RT	A17WE   					 
1997041000046	19970410	00046		1997	4	10	97ZZZX1339       	4	19970123	G	2211	7008138903	COMPUTER        		FZ710       	BOLKMS	BK117 	BK117C1     	5626025	EU  										NR 1 AUTOPILOT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				89080110	7505				NR 1 AUTOPILOT WOULD NOT COME ON LINE.						1	G	7	2 	3U			NC	H13EU   					 
1997041000047	19970410	00047		1997	4	10	97ZZZX1340       	4	19970102	G	3421	4021541671	GYRO HORIZON    			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	B			TI1R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	05	911MZ	1    			88071674	7098				HORIZON STARTED SPINNING AND TUMBLING IN-FLIGHT.						1	G	7	2 	3U				H13EU   					 
1997041000049	19970410	00049		1997	4	10	97ZZZX1342       	4	19970117	G	3421	4021541671	GYRO HORIZON    			BOLKMS	117   	BK117A3     	5626015	EU  										CSAS PITCH ROLL	INOPERABLE      	B			TI1R	K				NONE                    				I			FLT. ATTITUDE INST.       			IN	INSP/MAINT     	1			SW	05	911MZ				86081357	7098				GYRO HORIZ PITCH AND ROLL CSAS INOPERABLE.						1	G	7	2 	3U				H13EU   					 
1997041000050	19970410	00050		1997	4	10	97ZZZX1343       	4	19970104	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										YAW CSAS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ					7098				YAW COMPUTER HAD EHA FAILED IN FULL RETRACT POSITION.						1	G	7	2 	3U				H13EU   					 
1997041000055	19970410	00055	EU  	1997	4	10	97ZZZX1348       	1	19970120	G	2822	1176415103	PUMP            			BOLKMS	117   	BK117A3     	5626015	EU  										FUEL TRANSFER	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	1140H				169726	7078				LEAKING AT CASE DRAIN WHEN PUMP IS SHUT OFF.  NEW PUMP, LASTED ONLY 15 MINUTES IN OPERATION.						1	G	7	2 	3U				H13EU   					 
1997041000057	19970410	00057	EU  	1997	4	10	97ZZZX1350       	1	19970209	G	3411	PR6123	PITOT TUBE      			BOLKMS	117   	BK117B1     	5626012	EU  										PITOT SYSTEM	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117LU				5030057	7144				PITOT TUBE DEFORMED AND CRACKED.  PREMATURE FAILURE ONLY INSTALLED FOR 205.8 HOURS.						1	G	7	2 	3U				H13EU   					 
1997041000063	19970410	00063		1997	4	10	97ZZZX1356       	4	19970102	G	2211	117884141	COMPUTER        			BOLKMS	117   	BK117A4     	5626017	EU  										YAW CSAS	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	313LF	107  			5034	7138				YAW CSAS OSCILLATES IN-FLIGHT.  SAME DISCREPANCY WAS REPAIRED  ON LAST REPAIR.  (COMPUTER MALFUNCTION.)						1	G	7	2 	3U				H13EU   					 
1997041000064	19970410	00064	EU  	1997	4	10	97ZZZX1357       	1	19970111	G	2822	1176415103	BOOST PUMP      			BOLKMS	117   	BK117A4     	5626017	EU  										FUEL SYSTEM	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	313LF	6    			140485	7138				PUMP LEAKING FROM DRAIN.  ONLY 5.6 HOURS IN A/C BEFORE FAILURE.						1	G	7	2 	3U				H13EU   					 
1997041000065	19970410	00065	WP  	1997	4	10	97ZZZX1358       	2	19970310	G	7210	31016051	TRANSFER TUBE   			STBROS	SC7   	SC7SERIES3  	8100512	EU  	GARRTT	TPE331	TPE3312201A 		WP  					GEARBOX OIL	FRACTURED       	B			ILIR	E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	07	101UV	467  				SH1842	P90255			PILOT REPORTED A LOSS OF POWER AND GEARBOX NOISE AND SHUT THE ENGINE DOWN.  AFTER DISASSEMBLY OF THE GEARBOX, DISCOVERED	 THE OIL TUBE 3101605-1 HAD FRACTURED AND A 3 INCH PIECE OF THE TUBE WAS FOUND IN THE GEARBOX NEXT TO THE OIL SCAVENGE P	UMP PICK-UP TUBE.  THIS TUBE FEEDS OIL PRESSURE TO THE HIGH SPEED PINION WHICH FAILED AFTER OIL PRESSURE WAS LOST.  AD 7	6-16-01 COVERS THIS PROBLEM, BUT AFTER CHECKING THE AD AND ITS MANUFACTURER'S SB, IT WAS DETERMINED THAT TUBE 3101605-1 	IS THE TUBE CALLED FOR DURING C/W THE AD AND SB.  C/W THE AD WAS PERFORMED 19 YEARS PRIOR TO THE TUBE FAILURE.		1	H	7	2 	3T	4	T	NT	A15EU   	E3WE				 
1997041000066	19970410	00066	NE  	1997	4	10	97ZZZX1359       	1	19970220	G	5530		WEB             			SKRSKY	S76   	S76         	8143010	NE  										AFT PYLON	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										UPON RECEIVING PART (NEW) FROM SIKORSKY, FOUND PYLON WEB MADE OF WRONG ALLOY OR NOT HEAT TREATED CORRECTLY.  METAL TOO S	OFT.					1	G	7	2 	3U				H1NE    					 
1997041000067	19970410	00067	SW  	1997	4	10	97ZZZX1360       	1	19970214	G	6230	206010336005	LINK ASSY       			BELL  	206   	206L        	1181522	SW  										PYLON	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DRIVE LINK ASSY HAS EXCESS PLAY AT TWO PLACES.  SEE BELL MM L-3 FIG 62.21.  AT TEAR DOWN, FOUND BEARINGS AND SPACERS WOR	N BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACEMENT.  REPLACED 4 EACH.					1	G	7	1 	3U				H2SW    					 
1997041000068	19970410	00068	SW  	1997	4	10	97ZZZX1361       	1	19970317	G	7603	660190003	CONTROL CABLE   			MOONEY	M20   	M20C        	5870208	SW  										THROTTLE	DEFECTIVE       	B			FC6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	101T					2887				CABLE WAS MANUFACTURED AND DELIVERED WITHOUT THE FRICTION LOCK COLLAR.						1	L	7	1 	3O			 	2A3     					 
1997041000069	19970410	00069	CE  	1997	4	10	97ZZZX1362       	1	19970105	G	5270	P18M30	SWITCH          			CESSNA	500   	560CESSNA   	2076750	CE  										CABIN DOOR	FAILED          	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	350RD	1797 			341	5600026				CREW REPORTED THAT DOOR SEAL CAUTION LIGHT DOES NOT COME ON WHEN SEAL DEFLATED.  FOUND DOOR SEAL PRESSURE SWITCH STUCK O	PEN.  SUSPECT CAUSE IS CORROSION/CONTAMINATION, AND/OR POSITION OF SWITCH.  SUBMITTER SUGGESTS A MORE RESISTENT SWITCH O	R A BETTER POSITION TO MINIMIZE CONTAMINATION.				2	L	7	2 	4F			RT	A22CE   					 
1997041000070	19970410	00070	CE  	1997	4	10	97ZZZX1363       	1	19970318	G	3610	NAS130413	BOLT            			LEAR  	55    	55LEAR      	5170702	CE  										NR 2 ENG BLEED	FAILED          	B	S	A	DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	127GT	4006 				067				FOUND EVIDENCE OF A BLEED AIR LEAK ON THE INBOARD UPPER COWL OF THE NR 2 ENGINE.  REMOVED COWL AND FOUND BLEED AIR FLANG	E (ITEM NR 159C REF PAGE 2) SEPARATED APPROXIMATELY .1250 INCH.  BOTH BOLTS (ITEM NR 160) HAD THEIR HEADS SHEARED OR POP	PED OFF.  THE GASKET (ITEM NR 163P) WAS COMPLETELY MISSING.  REPLACED ALL GASKETS AND HARDWARE WITH NEW.				2	L	7	2 	4F				A10CE   					 
1997041000071	19970410	00071	CE  	1997	4	10	97ZZZX1364       	1	19970301	G	5540	65310181	BRACKET         			CESSNA	172   	172P        	2072436	CE  										RUDDER ATTACH	LOOSE RIVETS    	B	S		AHVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	92SP	6500 				17268830				INSPECTTION FOUND BOTTOM ATTACHMENT BRACKET FOR RUDDER BOLT TO HAVE LOOSE RIVETS.  SUBMITTER STATES THIS WAS SECOND ONE 	FOUND THIS YEAR.					1	H	7	1 	3O			NT	3A12    					 
1997041000072	19970410	00072	CE  	1997	4	10	97ZZZX1365       	1	19970301	G	5540	05310181	BRACKET         			CESSNA	172   	172D        	2072410	CE  										RUDDER ATTACH	LOOSE RIVETS    	B		A	AHVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	2061Y	4250 				17249561				INSPECTION FOUND BOTTOM ATTACHMENT BRACKET FOR RUDDER BOLTS TO HAVE LOOSE RIVETS.  SUBMITTER STATED THIS WAS THIRD ONE T	HIS YEAR.					1	H	7	1 	3O			NT	3A12    					 
1997041000073	19970410	00073	CE  	1997	4	10	97ZZZX1366       	1	19970301	G	5540	05310181	BRACKET         			CESSNA	172   	172I        	2072426	CE  										BOT RUD ATTACH	LOOSE RIVETS    	B			AHVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	44BL					17256854				DURING SHOP INSPECTION FOUND ATTACH BRACKET FOR RUDDER BOLT TO HAVE LOOSE RIVETS.  PART NUMBER FOR BRACKET BOTTOM ATTACH	 IS 0531018-1 AND FOR TOP ATTACH 0531018-2.					1	H	7	1 	3O			NT	3A12    					 
1997041000075	19970410	00075	NM  	1997	4	10	97ZZZX1368       	1	19970119	G	5311	65B01709	FRAME           			BOEING	747   	747228F     	1384895	NM  										BS 300-320	CRACKED         	B			CISY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	809MC	79993	17434			20887				AD 96-26-04.  INSPECTION OF LEFT FRAME BS 300 AND BS 320.  BS 300, STR 39 - STR 40, LEFT, CRACKED.  BS 320, STR 41 - STR	 42, LEFT, CRACKED.  REPAIRED IAW ATLAS E.O. 4753A031.					2	L	7	4 	4F				A20WE   					 
1997041000076	19970410	00076	NM  	1997	4	10	97ZZZX1369       	1	19970224	G	5311	65B01709	FRAME           			BOEING	747   	747228F     	1384895	NM  										BS 320 STR 39	CRACKED         	B			CISY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	809MC					20887				AD 96-26-04.  INSPECTION OF FRAME, RIGHT BS 320, STR 39R, CRACK FOUND.  INTERIM REPAIR CARRIED OUT IAW SRM 53-10-04, FIG	URE 85.					2	L	7	4 	4F				A20WE   					 
1997041000077	19970410	00077	CE  	1997	4	10	97ZZZX1370       	1	19970301	G	3246	C30482	HUB             			CESSNA	177   	177RG       	2073709	CE  										NLG WHEEL	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	1571H					177RG0745				CIRCUMSTANCE UNKNOWN.  FOUND DURING ANNUAL INSPECTION.  HUB THREAD CRACKS LOOK LIKE OVERTORQUE ON A VERY THIN BOSS.  1,0	70 HOURS ON AIRCRAFT AND DEFECTIVE PART.					1	H	7	1 	3O				A20CE   					 
1997041000079	19970410	00079	EU  	1997	4	10	97ZZZX1372       	2	19970331	G	7210	837280	SHAFT SPLINES   			DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					PROP GEARBOX	MISSING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	608F	1161 				10033	4380627			FOUND METAL IN CHIP DETECTORS.  PULLED GEARBOX FOUND MISSING SPLINES ON PROPELLER SHAFT, P/N 837-280.						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
1997041000080	19970410	00080	EU  	1997	4	10	97ZZZX1373       	2	19970331	G	7210	837280	SHAFT SPLINE    			DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					PROP GEARBOX	MISSING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	607F	1024 				10027	4380622			FOUND METAL IN CHIP DETECTOR.  PULLED GEARBOX, FOUND MISSING SPLINES.						1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
1997041000085	19970410	00085	GL  	1997	4	10	97ZZZX1378       	2	19970217	G	7250	6875491	MATING RING     								ALLSN 	250C  	250C28B     	03013	GL  					TURBINE	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05		24   			QL61430					MATING RING LEAKING AFTER ONLY 23.5 HOURS.											3	U			E1GL				 
1997041000086	19970410	00086		1997	4	10	97ZZZX1379       	4	19970213	G	2562	ELT10	ELT             	NARCO       																COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					C48466					NO AUDIO DURING FUNCTIONAL CHECK BEFORE INSTALLATION.																			 
1997041000087	19970410	00087	EU  	1997	4	10	97ZZZX1380       	1	19970212	G	6520	4639310012	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DAMAGED         	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					1982					SCORING ON BEARING ROLLERS, BEARING WAS RECEIVED NEW FROM AEC.						1	G	7	2 	3U			NC	H13EU   					 
1997041000088	19970410	00088	EU  	1997	4	10	97ZZZX1381       	1	19970204	G	6520	4639310012	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DAMAGED         	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					1793					DAMAGE ON ROLLERS.  RECEIVED AS NEW PART FROM AMERICAN EUROCOPTER.						1	G	7	2 	3U			NC	H13EU   					 
1997041000089	19970410	00089		1997	4	10	97ZZZX1382       	1	19970203	G	6520	469310012	BEARING         																	T/R GEARBOX	DAMAGED         	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					1913					DAMAGE ON ROLLERS.  BEARING WAS RECEIVED AS NEW, SERVICEABLE FROM AMERICAN EUROCOPTER.																			 
1997041000090	19970410	00090	EU  	1997	4	10	97ZZZX1383       	1	19970203	G	6520	4639306006	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DAMAGED         	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					2046					FOUND DAMAGE ON ROLLER.  BEARING WAS RECEIVED NEW, SERVICEABLE FROM AMERICAN EUROCOPTER.						1	G	7	2 	3U			NC	H13EU   					 
1997041000091	19970410	00091	GL  	1997	4	10	97ZZZX1384       	2	19970217	G	7250	6898764	BELLOWS SEAL    								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05		24   			95859					CARBON BELLOWS SEAL LEAKING AFTER ONLY 23.5 HOURS.											3	U			E4CE				 
1997041000092	19970410	00092	EU  	1997	4	10	97ZZZX1385       	1	19970219	G	6520	4639311001	BEVEL GEAR      			BOLKMS	117   	BK117A1     	5626010	EU  										T/R GEARBOX	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					949					COULD NOT GET A GOOD BACKLASH AND CONTACT PATTERN TOGETHER AS REQUIRED BY CURRENT BK117REM305 MANUAL.  PART CAME WITHOUT	 MANUFACTURER'S CONTACT PRINTS MADE AT MANUFACTURING.					1	G	7	2 	3U				H13EU   					 
1997041000093	19970410	00093	EU  	1997	4	10	97ZZZX1386       	1	19970219	G	6520	4639311043	BEVEL GEARSHAFT 			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					893					COULD NOT GET A GOOD BACKLASH ON CONTACT PATTERN TOGETHER AS REQUIRED BY CURRENT BK117REM305 MANUAL.  PART CAME WITHOUT 	MANUFACTURER'S CONTACT PRINTS MADE AT MANUFACTURING.					1	G	7	2 	3U			NC	H13EU   					 
1997041000094	19970410	00094	EU  	1997	4	10	97ZZZX1387       	1	19970219	G	6520	4639310012	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DAMAGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					1824					BEARING WAS INSTALLED ON GEARSHAFT, P/N 4639311043 MMIR FORM NR 78853B, AND GEAR WAS FOUND BAD.  BEARING WAS DAMAGED DUR	ING REMOVING IAW BK117REM305 AND MUST BE REPLACED.					1	G	7	2 	3U			NC	H13EU   					 
1997041000095	19970410	00095		1997	4	10	97ZZZX1388       	4	19970217	G	3424	9551BN541	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										TURN SLIP	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		4    			4760					INOPERABLE TURN AND SLIP INDICATOR.						1	G	7	2 	3U				H13EU   					 
1997041000097	19970410	00097	EU  	1997	4	10	97ZZZX1390       	1	19970108	G	6330	1171282101	SUPPORT ASSY    			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRANSMISSION	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					13					TRANSMISSION SUPPORT WITH MFG DEFECT.  TOP PAD TOO THIN.						1	G	7	2 	3U			NC	H13EU   					 
1997041000103	19970410	00103	SW  	1997	4	10	97ZZZX1396       	1	19970109	G	2432	RG222	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	721SP	362  			CBC261759	45486				BATTERY WOULD NOT HOLD CHARGE.						1	G	7	1 	3U				H2SW    					 
1997041000116	19970410	00116	CE  	1997	4	10	97ZZZX1406       	1	19970304	G	3010	621441323	SUPPLY TUBE     			CESSNA	650   	650         	2076802	CE  										WING LE	CRACKED         	B			BQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	900FL	1016 				6507049				DURING AN INSPECTION REQUIRING WING LEADING EDGE PANEL REMOVAL, THE OUTBOARD CENTER LEADING EDGE SECTION ANTI-ICING SUPP	LY TUBE WAS FOUND CRACKED AND NOT CONNECTED.  THIS WAS DUE TO MISALIGNMENT WHEN INSTALLED NEW AT THE FACTORY.					2	L	7	2 	4F				A9NM    					 
1997041000118	19970410	00118	SW  	1997	4	10	97ZZZX1407       	1	19970120	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										SHAFT	DISC CRACKED    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	131  				53054				INSPECTION FOUND TWO OUTER DISCS CRACKED.  ONE CRACKED INTO 2 PIECES, ONE CRACKED FROM MIDDLE OF DISC TO INNER EDGE.						1	G	7	1 	3U			O	H2SW    					 
1997041000119	19970410	00119	EU  	1997	4	10	97ZZZX1408       	1	19970121	G	6210	355A11002009	BLADE           			AEROSP	AS355 	AS355E      	8680805	EU  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	372E	3615 			3841	5208				DURING DAILY INSPECTION, FOUND SKIN CRACKED AT STA 1000 MM.						1	G	7	2 	3U				H11EU   					 
1997041000317	19970410	00317	GL  	1997	4	10	97ZZZX1409       	2	19970317	G	7210	6899402	PTO GEAR SPLINE 			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	WORN            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		CG80352	1280431D	CAE832846			DURING INSPECTION OF GEARBOX GEARS, FOUND THE PTO GEAR INTERNAL DRIVE SPLINES WORN BEYOND LIMITS.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997041000318	19970410	00318	GL  	1997	4	10	97ZZZX1410       	2	19970317	G	7210	6896437	SPUR GEAR       		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	SPALLED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		60509	1280431D	CAE832846			DURING INSPECTION OF GEARBOX GEARS, THE TEETH WERE FOUND SPALLED.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997041000319	19970410	00319	GL  	1997	4	10	97ZZZX1411       	2	19970317	G	7210	6876529	SPUR GEAR       		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	SPALLED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F				UP1341	1280431D	CAE832846			INSPECTION FOUND GEAR TEETH SPALLED.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997041000320	19970410	00320	GL  	1997	4	10	97ZZZX1412       	2	19970317	G	7260	6854857	GEARSHAFT       		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TACH DRIVE	WORN            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F		3420 		UP1341	1280431D	CAE832846			INSPECTION FOUND TACHOMETER DRIVE WORN BEYOND LIMITS.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997041000321	19970410	00321	GL  	1997	4	10	97ZZZX1413       	2	19970317	G	7260	689701	GEAR            		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TORQUE METER	WORN            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		NN60045	1280431D	CAE832846			DURING INSPECTION OF GEARBOX GEARS, FOUND THE TORQUE METER GEAR DAMPER RING GROOVE WORN BEYOND LIMITS.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997041000322	19970410	00322	NM  	1997	4	10	97ZZZX1414       	1	19970320	G	5330	6545775	SKIN            			BOEING	737   	737242      	1384477	NM  										BS 822-908	WRINKLED        	B			S5WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	159PL	52863				21186				DURING C-CHECK INSPECTION, FOUND SKIN AFT OF AFT CARGO DOOR WRINKLED.  CONDITION OF SKIN AN PREVIOUS REPAIRS NECESSITATE	 REPLACEMENT OF SKIN SECTION IAW BOEING TELEXES SOHR970319 AND SOHR970314.					2	L	7	2 	4F				A16WE   					 
1997041000323	19970410	00323	GL  	1997	4	10	97ZZZX1415       	2	19970324	G	7261	6840532	FILTER ASSY     								ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		4889 			UPI342					GEARBOX FILTER ASSY EPOXY IS CRACKED.											3	U			E4CE				 
1997041000427	19970410	00427		1997	4	10	97ZZZX1449       	1	19970227	G	2121	1143800287	BLOWER          																	VENT	MALFUNCTION     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03					428					MOTOR TURNS OPPOSITE DIRECTION WHEN POWER IS APPLIED WITH CORRECT POLARITY.  RAYTHEON P/N 114-380028-7.  ADVANCED IND P/	N BC80A-3.																		 
1997041000428	19970410	00428	NM  	1997	4	10	97ZZZX1450       	1	19970112	G	3221	162N11427	SUPPORT PLATE   			BOEING	757   	757*        		NM  										NLG SHOCK STRUT	WRONG COATING   	B			OBJY	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	35										SUPPORT PLATE SUB-CONTRACTED FOR APPLICATION OF 'KARON' COATING IAW BOEING 757 CMM 32-21-49.  PART RETURNED WITH C OF C 	AS HAVING C/W ORDER, HOWEVER, PROCESS APPLIED IS NOT KARON COATING.  BOEING ADVISED NO OTHER APPROVED PROCESS AND THAT O	NLY APPROVED VENDOR IS KAMATICS.				2	L	7	2 	4F			RT	A2NM    					 
1997041000429	19970410	00429	SO  	1997	4	10	97ZZZX1451       	2	19970317	G	8510	634503	BEARING         								CONT  	O520  	GTSIO520*   	17032	SO  					PROP DRV GEAR	MISPACKAGED     	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19										P/N 630571 (BEARING FOR PROP DRIVER GEAR IN ENGINE CRANKCASE) MARKED ON PACKAGING AS P/N 630571.  BEARING ITSELF MARKED 	AS P/N 634503.  P/N 634503 IS CRANKSHAFT MAIN BEARING.  PURCHASED NEW FROM TELEDYNE CONTINENTAL MOTORS.  BEARINGS WILL F	IT IN CRANKCASE SADDLES WHEN SWITCHED, BUT OIL HOLES DO NOT LINE UP AND BEARING OIL GROOVES ARE DIFFERENT WIDTHS.  COULD	 CAUSE BEARING FAILURE/OIL STARVATION.								3	O			E7CE				 
1997041000430	19970410	00430		1997	4	10	97ZZZX1452       	4	19970325	G	2564		SAFETY VALVE    	EAAEROMARINE																INFLATE CYLINDER	MISASSEMBLED    	B			RC0R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										DURING ANNUAL INSPECTION SERVICE OF A 6-MAN LIFE RAFT, THE CYLINDER SAFETY VALVE DISK WAS INSPECTED.  AN EXTRA SAFETY DI	SK RO508-RA AND AN EXTRA O-RING 514-05B WERE FOUND INSTALLED ON TOP OF THE ORIGINAL O-RING AND DISK.  THESE WERE REMOVED	 AND THE SYSTEM RE-ASSEMBLED.  THESE EXTRA COMPONENTS COULD HAVE CAUSED THE SAFETY VALVE NOT TO FUNCTION.																	 
1997041000431	19970410	00431	CE  	1997	4	10	97ZZZX1453       	1	19970325	G	2701	169420028129	COVER           			BEECH 	23    	B24R        	1151253	CE  										CONTROL COLUMN	CORRODED        	B	S		CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	104DB	3216 				MC309				DURING ANNUAL INSPECTION, DISCOVERED SEVERE CORROSION ALONG SEAMS OF CONTROL COLUMN COVER.						1	L	7	1 	3O				A1CE    					 
1997041000433	19970410	00433	CE  	1997	4	10	97ZZZX1454       	1	19970301	G	3240	45226	ADJUSTER TUBE   	BFGOODRICH  		CESSNA	500   	560CESSNA   	2076750	CE  										BRAKE	LOOSE           	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	348QS		429  		215297	5600348				DURING PRE-FLIGHT INSPECTION, THE BRAKE ASSEMBLY ADJUSTER GUIDE TUBE WAS FOUND PROTRUDING ON S/N 2314 AND S/N 2362. THE 	ADJUSTER ASSEMBLY WAS LOOSE.  REMOVED BOTH ASSEMBLIES AND SENT OUT FOR OVERHAUL.					2	L	7	2 	4F			RT	A22CE   					 
1997041000447	19970410	00447	CE  	1997	4	10	97ZZZX1468       	1	19970318	G	3244	650T661	TIRE            	GOODYEARAERO		BEECH 	90    	C90         	1152913	CE  										NLG	DEFECTIVE       	B			DFKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	4774M				41200939	LJ771				GOODYEAR FLIGHT CUSTOM 6.50X10-6PR TUBELESS.  REMOVED TIRE FROM NOSE OF AIRCRAFT.  TIRE WAS BULGING IN TREAD AREA NEAR S	IDEWALL.  AFTER TIRE REMOVAL FROM WHEEL, FOUND 'SOFT' AREA INSIDE TIRE AT BULGED AREA.					1	L	7	2 	3T				3A20    					 
1997041000450	19970410	00450	EU  	1997	4	10	97ZZZX1471       	2	19970401	G	7314	996592	PUMP            			DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					OUTPUT TUBE	CRACKED         	D		A		O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			WP	07	671DA	164  			960157	10180	4412507			DURING FLIGHT, THE FUEL PUMP HOUSING CRACKED AT THE OUTPUT TUBE CAUSING THE AVAILABLE FUEL TO BE PUMPED INTO THE ENGINE 	COMPARTMENT.  ONE-QUARTER TO ONE-HALF OF THE FUEL TANK WAS LOST IN APPROX 15 MINUTES.  CAUSE OF THE FAILURE IS BELIEVED 	TO BE RELATIVE MOVEMENT OF THE RIDGED FUEL LINE OF ITS ATTACH POINT ON THE BALANCE TUBE.  THE BALANCE TUBE WAS FOUND CHA	FED.  THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM ON THIS AIRCRAFT.  SUBMITTER RECOMMENDS AIRCRAFT INSPECTION AND RETU	RN TO AN EARLIER DESIGN USING SOFT LINES.		1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
1997041000451	19970410	00451	GL  	1997	4	10	97ZZZX1472       	3	19970314	G	6114	7015C87	HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 3 HOLE	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	69374	7979 	946  		788094	402B0520		788094		INSPECTION FOUND HUB CRACK LOCATED IN NR 3 HOLE, 2ND THREAD FROM OUTSIDE EDGE.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997041000452	19970410	00452	GL  	1997	4	10	97ZZZX1473       	3	19970314	G	6111	7636D	BLADE           			PIPER 	PA23  	PA23160     	7102304	SO  						HARTZL	HC82	HC82VL2     	GL  	V GROOVE	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	3403P				A8600	231367		K3045		INSPECTION FOUND PROPELLER BLADE CRACKED IN RETENTION V-GROOVE OF BLADE.						1	L	7	2 	3O				1A10    		5	C	P23EA	 
1997041000453	19970410	00453	NM  	1997	4	10	97ZZZX1474       	1	19970327	G	2722	680105005	SERVO VALVE     		65C370529   	BOEING	737   	7373G7      	1384595	NM  										RUDDER PCU	FAIL TEST       	B	L	A	AU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		20624			524X					BRAZILIAN AIR LINES SENT RUDDER PCU TO REPAIR STATION AU4R FOR EVALUATION FOLLOWING FAILURE ON PRE-FLIGHT TEST PER BAC S	B 7371202.  FOUND UNIT FAIL TEST 12C SECONDARY STROKE/FLOW OF BAC CMM 27-20-01 AND CAUSE WAS IMPROPER ASSY OF SERVO CONT	ROL VALVE AD 94-01-07 AND 95-06-53 APPLICABLE.				2	L	7	2 	4F			RT	A16WE   					 
1997041000458	19970410	00458	SW  	1997	4	10	97ZZZX1479       	1	19970327	G	3230		ACTUATOR        			GULSTM	690TP 	690B        	7630516	SW  										EMERGENCY EXT	LEAK            	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	22CK					11524				N2 SYSTEM SHOWED HIGH PRESSURE.  FOUND HYDRAULIC FLUID IN N2 SYSTEM.  DRAINED SYSTEM AND RESERVICED WITH N2.  SUSPECT CA	USE IS MAIN LANDING GEAR EMERGENCY EXTEND ACTUATOR HAS LEAKING SEAL.					1	H	7	2 	3T				2A4     					 
1997041000459	19970410	00459	SW  	1997	4	10	97ZZZX1480       	1	19970309	G	2841		INDICATOR       			GULSTM	560   	560A        	0141404	SW  										FUEL QUANTITY	FAILED          	G		A		A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	2751B					251				DURING INVESTIGATION OF OFF-AIRPORT LANDING, IT WAS FOUND THAT THE FUEL QUANTITY INDICATOR WAS SHOWING 45 GALLONS OF FUE	L ON BOARD.  IN REALITY, ALL TANKS WERE EMPTY.					1	H	7	2 	3O				6A1     					 
1997041000460	19970410	00460	NM  	1997	4	10	97ZZZX1481       	1	19970301	G	5753		SPAR            			BOEING	727   	727276      	138408R	NM  										MID FLAP	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				DURING C-CHECK INSPECTION, INTERGRANULAR CORROSION WAS NOTED IN THE RIGHT WING OUTBOARD MID-FLAP LOWER FRONT SPAR.						2	L	7	3 	4F			RT	A3WE    					 
1997041000461	19970410	00461	CE  	1997	4	10	97ZZZX1482       	1	19970327	G	3244	301361311	TIRE            			BEECH 	B300  	B300        	1159232	CE  										SIDEWALL	LEAKS           	B			EKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	96KA					FL36				BOTH TIRES WERE PUT ON THE SAME DAY.  BOTH LEAKED DOWN AND WERE FOUND TO HAVE PIN HOLES IN THE SIDEWALLS.  SERIAL NUMBER	S ON THE TIRES WERE 60691499 AND 60691500.					2	L	7	2 	4T			RT	A24CE   					 
1997041000462	19970410	00462	SW  	1997	4	10	97ZZZX1483       	1	19970301	G	5753		FLAP            			GULSTM	690TP 	695A        	7630519	SW  										INBD LT FLAPL	MISINSTALLED    	B			XMJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19	2267U					96007				WHILE AIRCRAFT WAS UNDERGOING MAINTENANCE, THE INBOARD LEFT FLAP WAS REMOVED.  UPON INSTALLATION OF THE FLAP THE ATTACH 	BOLT MISSED THE ROD END THAT WAS COMING FROM THE PULLEY; THUS, WEDGING THE ROD END BETWEEN BOLT AND THE FLAP SKIN.  THIS	 GAVE THE FALSE APPEARANCE THAT THE ROD END WAS INSTALLED CORRECTELY.  IN THIS CONFIGURATION THE FLAP OPERATED NORMALLY.	  THE AREA OF THE CUT-OUT  TOP OF THE FLAP IS NOT ENOUGH TO SEE THE ROD END TO BOLT ATTACHMENT CLEARLY.  SUBMITTER STATE	D THAT WHENEVER THE FLAPS ARE REMOVED, THAT THE TOP CUT-OUT BE EXTENDED BY .50 INCHES.  THIS WOULD PROVIDE POSITIVE VISU	AL CONFORMATION OF THE BOLT INSTALLATION.	1	H	7	2 	4T				2A4     					 
1997041000463	19970410	00463	CE  	1997	4	10	97ZZZX1484       	1	19970312	G	5610	1014200811	WINDOW          			BEECH 	90    	C90         	1152913	CE  										PILOT SIDE D	CRACKED         	D				A	I			UNSCHED LANDING         	CABIN DEPRESSURIZATION  			O			OTHER                     			CR	CRUISE         	1			GL	15	851KA					LJ851				WHILE IN CRUISE FLIGHT, PILOT HEARD A LOUD BANG.  WHEN HE TURNED TO LOOK, THE 'D' WINDOW ON HIS SIDE HAD CRACKED FROM FO	RWARD END TO AFT END.  PILOT DE-PRESSURIZED CABIN AND RETURNED TO HOME BASE WITH NO INCIDENT.					1	L	7	2 	3T				3A20    					 
1997041000464	19970410	00464		1997	4	10	97ZZZX1485       	4	19970317	G	2215	06500760012	PITCH SERVO     	ALIDSIGNAL  	KSA470      	LEAR  	35    	31A         	5170531	CE  										AUTOPILOT	DEFECTIVE       	B	L		NVIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	293SA				2547	101				AUTOPILOT PORPOISES DEFECT.  FOUND WEAK SERVO, REPLACED SWITCH REPAIRED UNIT.  CONTINUED MALFUNCTION WITH AUTOPILOT.  LE	NGTHY TROUBLESHOOTING FOUND REPAIRED SERVO FAULT HAD BLOWN FUSE IN MODE SELECTOR DUE TO AP ELECTRICAL BOX FEEDBACK TO AP	.  ALL DEFECTIVE COMPONENTS REPLACED WHICH CORRECTED PROBLEM.				2	L	7	2 	4F			RT	A10CE   					 
1997041000465	19970410	00465	CE  	1997	4	10	97ZZZX1486       	1	19970301	G	3246	101800145	WHEEL           			BEECH 	200   	B200        	1152922	CE  										NR 3 MLG	BEARING FAILED  	G		A		O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			EA	17	992TJ	125  				BB992				NR 3 MAIN OUTER WHEEL BEARING FAILED.  WHEEL DEPARTED AIRCRAFT ON TAKEOFF.  WHEEL SLID OVER AXLE NUT AND COTTER PIN.  BE	ARING CONE SEIZED ON AXLE.  AXLE WAS GALLED.  BRAKE LINE FITTING SNAPPED OFF.					1	L	7	2 	4T				A24CE   					 
1997041000466	19970410	00466	CE  	1997	4	10	97ZZZX1487       	1	19970301	G	3246	13600LA	BEARING         	BFGOODRICH  	101800145   	BEECH 	200   	B200        	1152922	CE  										NR 2 MLG WHEEL	FAILED          	C	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6812A	350  			1267	BB1484				FAILURE OF THE NR 2 MAIN GEAR OUTER WHEEL BEARING WAS FOUND DURING A GEAR LUBRICATION FOLLOWING A GEAR WASH.  PREVIOUS T	AXIING AND TOWING OF ACFT APPEARED NORMAL.  BEARING CAGE ASSY APPEARS TO HAVE FAILED, AND RACE WAS SCORED AS A RESULT OF	 CAGE DISINTEGRATION.  THE SEAL WAS TORN.  THE FAILURE DOES NOT APPEAR TO BE LUBRICATION RELATED AND NO SIGNS OF HEAT DA	MAGE.  THE AXLE SHOWED NO SIGNS OF DAMAGE OR TEMPERATURE.  THE FAILED WHEEL BEARING (TIMKEN P/N 13600-LA BEECH P/N 13600	LA3685) WAS CLEANED AND REPLACED 60 HRS PRIOR TO FAILURE.  THE FAILED BEARING HAD 350 HOURS TIME IN USE.		1	L	7	2 	4T				A24CE   					 
1997041000516	19970410	00516	SW  	1997	4	10	97ZZZX1488       	1	19970331	G	2730	530534501	ARM             			GULSTM	690TP 	695B        	3970610	SW  										ELEV WEIGHT	CRACKED         	B	S		XMJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	81432	3407 				96206				DURING THE 100-HOUR INSPECTION, BOTH ARMS ON THE ELEVATOR CONTROL BOBWEIGHT ASSEMBLY WERE FOUND CRACKED AT THE WEIGHT AT	TACH POINTS.  SUBMITTER RECOMMENDS BEEFING-UP THE AREA OF THE WEIGHT ATTACH POINTS.					1	H	7	2 	4T			RT	2A4     					 
1997041700006	19970417	00006	WP  	1997	4	17	97ZZZX1533       	1	19970127	G	5512		SKIN            			CVAC  	440   	440         	2422902	WP  										LT HORIZ STAB	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LEFT HORIZONTAL STABILIZER LEADING SKIN CRACKED.						2	L	7	2 	4R				6A6     					 
1997041700007	19970417	00007	WP  	1997	4	17	97ZZZX1534       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 76 STR 10R	TORN            	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE UPPER SKIN STA 76, STR 10R, TORN.						2	L	7	2 	4R				6A6     					 
1997041700008	19970417	00008	WP  	1997	4	17	97ZZZX1535       	1	19970127	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 413.3	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				STR 24R LAP SEAM CORRODED AFT OF BELT FRAME STA 413.30.						2	L	7	2 	4R				6A6     					 
1997041700009	19970417	00009	WP  	1997	4	17	97ZZZX1536       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										FWD FUSELAGE	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FORWARD LOWER FUSELAGE SKIN CRACKED.						2	L	7	2 	4R				6A6     					 
1997041700010	19970417	00010	WP  	1997	4	17	97ZZZX1537       	1	19970127	G	5320		INTERCOSTAL     			CVAC  	440   	440         	2422902	WP  										BS 140 R1 DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				INTERCOSTAL AND STRINGER AT R1 DOOR LOWER SECTION STA 140 CORRODED.						2	L	7	2 	4R				6A6     					 
1997041700011	19970417	00011	WP  	1997	4	17	97ZZZX1538       	1	19970127	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 730-760	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				STRINGERS 4, 5, AND 6, STA 730 - STA 760, CORRODED.  LAP SEAM STR 6L STA 681 - STA 730 CORRODED.						2	L	7	2 	4R				6A6     					 
1997041700012	19970417	00012	WP  	1997	4	17	97ZZZX1539       	1	19970127	G	5320		ANGLE           			CVAC  	440   	440         	2422902	WP  										AFT BULKHEAD	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				AFT BULKHEAD L-ANGLE CORRODED AT FLOOR LEVEL.						2	L	7	2 	4R				6A6     					 
1997041700013	19970417	00013	WP  	1997	4	17	97ZZZX1540       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 730-745	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				CROWN SKIN CRACKED STA 730 TO STR 745.						2	L	7	2 	4R				6A6     					 
1997041700014	19970417	00014	WP  	1997	4	17	97ZZZX1541       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 760	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				CROWN SKIN CRACKED STA 760.						2	L	7	2 	4R				6A6     					 
1997041700015	19970417	00015	WP  	1997	4	17	97ZZZX1542       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 509 STR 21R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LAP SEAM CORRODED AT 21R STA 509 TO STA 526.						2	L	7	2 	4R				6A6     					 
1997041700016	19970417	00016	WP  	1997	4	17	97ZZZX1543       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 435.23 S21R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LAP SEAM CORRODED AT STA 435.23, STR 21R.						2	L	7	2 	4R				6A6     					 
1997041700017	19970417	00017	WP  	1997	4	17	97ZZZX1544       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 413-435	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				STR 21L LAP SEAM CORRODED STA 413 TO STA 435.						2	L	7	2 	4R				6A6     					 
1997041700018	19970417	00018	WP  	1997	4	17	97ZZZX1545       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 836 STR 4L	DENTED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				SKIN DENTED STA 937 STR 4L.						2	L	7	2 	4R				6A6     					 
1997041700019	19970417	00019	WP  	1997	4	17	97ZZZX1546       	1	19970127	G	5320		INTERCOSTAL     			CVAC  	440   	440         	2422902	WP  										BS 210-227	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				INTERCOSTAL GOUGED AT BELT FRAME FLANGE STA 210 TO STA 227.						2	L	7	2 	4R				6A6     					 
1997041700020	19970417	00020	WP  	1997	4	17	97ZZZX1547       	1	19970127	G	5320		ANGLE           			CVAC  	440   	440         	2422902	WP  										COCKPIT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				ANGLE FORWARD OF CAPTAIN'S INSTRUMENT PANEL CORRODED						2	L	7	2 	4R				6A6     					 
1997041700021	19970417	00021	WP  	1997	4	17	97ZZZX1548       	1	19970127	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 92 STR 13R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				STR 13R CRACKED AND DISTORTED STA 92.						2	L	7	2 	4R				6A6     					 
1997041700022	19970417	00022	WP  	1997	4	17	97ZZZX1549       	1	19970127	G	5320		INTERCOSTAL     			CVAC  	440   	440         	2422902	WP  										BS 210	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				INTERCOSTAL AT STA 210 GOUGED.						2	L	7	2 	4R				6A6     					 
1997041700023	19970417	00023	WP  	1997	4	17	97ZZZX1550       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 730 STR 29R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				SKIN AT STR 29R CRACKED BETWEEN STA 730 TO STA 745.						2	L	7	2 	4R				6A6     					 
1997041700024	19970417	00024	WP  	1997	4	17	97ZZZX1551       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 420 STR 13R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE INNER SKIN CRACKED STA 420 STR'S 13 AND 14R						2	L	7	2 	4R				6A6     					 
1997041700025	19970417	00025	WP  	1997	4	17	97ZZZX1552       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 420 STR 13L	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE SKIN INNER SURFACE CRACKED STA 420, STR'S 13, 14L.						2	L	7	2 	4R				6A6     					 
1997041700026	19970417	00026	WP  	1997	4	17	97ZZZX1553       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 344 STR 13	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE INNER SKIN CRACKED STA 344 BETWEEN STR 13 AND 14R.						2	L	7	2 	4R				6A6     					 
1997041700027	19970417	00027	WP  	1997	4	17	97ZZZX1554       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 798 STR 29R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				SKIN CRACKED STR 29R, STA 798.						2	L	7	2 	4R				6A6     					 
1997041700028	19970417	00028	WP  	1997	4	17	97ZZZX1555       	1	19970127	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 760 STR 29R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				STRINGER 29R CRACKED STA 760.						2	L	7	2 	4R				6A6     					 
1997041700029	19970417	00029	WP  	1997	4	17	97ZZZX1556       	1	19970127	G	5311		BELT FRAME      			CVAC  	440   	440         	2422902	WP  										BS 698	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				BELT FRAME AT STA 698 CORRODED RT SIDE.						2	L	7	2 	4R				6A6     					 
1997041700030	19970417	00030	WP  	1997	4	17	97ZZZX1557       	1	19970127	G	5311		FRAME           			CVAC  	440   	440         	2422902	WP  										BS 641 S25L	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FRAME FLANGE CRACKED STA 641 OUTBOARD AT STR 25L.						2	L	7	2 	4R				6A6     					 
1997041700031	19970417	00031	WP  	1997	4	17	97ZZZX1558       	1	19970128	G	3211		FITTING         			CVAC  	440   	440         	2422902	WP  										LT MLG TRUNNION	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LEFT MLG INBOARD TRUNNION FITTING CRACKED.						2	L	7	2 	4R				6A6     					 
1997041700032	19970417	00032	WP  	1997	4	17	97ZZZX1559       	1	19970128	G	5551		FITTING         			CVAC  	440   	440         	2422902	WP  										H. STAB ATTACH	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				RIGHT UPPER FORWARD HORIZONTAL STABILIZER ATTACH FITTING ATTACHED.						2	L	7	2 	4R				6A6     					 
1997041700033	19970417	00033	WP  	1997	4	17	97ZZZX1560       	1	19970127	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 140 STR 11R	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				SKIN CRACKED STA 140 STR 11R.						2	L	7	2 	4R				6A6     					 
1997041700034	19970417	00034	WP  	1997	4	17	97ZZZX1561       	1	19970128	G	5315		FLOOR BEAM      			CVAC  	440   	440         	2422902	WP  										BS 681	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FLOOR BEAM STA 681 CORRODED						2	L	7	2 	4R				6A6     					 
1997041700035	19970417	00035	WP  	1997	4	17	97ZZZX1562       	1	19970128	G	5730		SKIN            			CVAC  	440   	440         	2422902	WP  										LT WING	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				WING SKIN, STRINGERS (4 EACH), FORWARD SPAR WEB, AND AFT SPAR WEB CORRODED FROM WET BAY TO WING TIP.						2	L	7	2 	4R				6A6     					 
1997041700036	19970417	00036	WP  	1997	4	17	97ZZZX1563       	1	19970128	G	5730		SKIN            			CVAC  	440   	440         	2422902	WP  										WS 23	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				SURFACE CORROSION RIGHT WING BAY WING PLANK STA 23 TO STA 29.						2	L	7	2 	4R				6A6     					 
1997041700037	19970417	00037	WP  	1997	4	17	97ZZZX1564       	1	19970128	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										ADF ANT CUT-OUT	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				AFT ADF ANTENNA SKIN CUT-OUT CRACKED.						2	L	7	2 	4R				6A6     					 
1997041700038	19970417	00038	WP  	1997	4	17	97ZZZX1565       	1	19970128	G	5720		SHROUD          			CVAC  	440   	440         	2422902	WP  										LE WS 290	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				CRACK IN INNER SHROUD RT OTBD L/E STA 290.						2	L	7	2 	4R				6A6     					 
1997041700039	19970417	00039	WP  	1997	4	17	97ZZZX1566       	1	19970128	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										BS 193	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				SKIN CORRODED IN FORWARD CARGO BAY AROUND BELT FRAME 193/210.						2	L	7	2 	4R				6A6     					 
1997041700040	19970417	00040	WP  	1997	4	17	97ZZZX1567       	1	19970128	G	5330		SKIN            			CVAC  	440   	440         	2422902	WP  										FS 344 STR 13L	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE INNER SKIN SURFACE CRACKED STA 344, STR'S 13L-14L.						2	L	7	2 	4R				6A6     					 
1997041700041	19970417	00041	WP  	1997	4	17	97ZZZX1568       	1	19970128	G	5730		SKIN            			CVAC  	440   	440         	2422902	WP  										WS 23.5	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LEFT WING UPPER SURFACE HAS CORROSION ON PLANK AND STRINGER BULKHEAD, STA 235 TO 28.5						2	L	7	2 	4R				6A6     					 
1997041700042	19970417	00042	WP  	1997	4	17	97ZZZX1569       	1	19970128	G	5753		BEAVER TAIL RIB 			CVAC  	440   	440         	2422902	WP  										RT WING	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				RIGHT WING BEAVER TAIL, NUMEROUS RIBS HAVE EXFOLIATION.						2	L	7	2 	4R				6A6     					 
1997041700043	19970417	00043	WP  	1997	4	17	97ZZZX1570       	1	19970128	G	5720		FRAME           			CVAC  	440   	440         	2422902	WP  										LT WING STA 25	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LEFT WING STA 25 FRAME CRACKED UPPER 'Z'.						2	L	7	2 	4R				6A6     					 
1997041700044	19970417	00044	WP  	1997	4	17	97ZZZX1571       	1	19970127	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 712 S10R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE STRINGER 10 RIGHT, CORRODED STA 712.						2	L	7	2 	4R				6A6     					 
1997041700045	19970417	00045	WP  	1997	4	17	97ZZZX1572       	1	19970127	G	5313		STRINGER        			CVAC  	440   	440         	2422902	WP  										BS 698 S9R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE STRINGER CORRODED, STA 698 RT.						2	L	7	2 	4R				6A6     					 
1997041700046	19970417	00046	WP  	1997	4	17	97ZZZX1573       	1	19970127	G	5320		HAT SECTION     			CVAC  	440   	440         	2422902	WP  										BS 681 RT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FUSELAGE HAT SECTION CORRODED STA 681, RT SIDE.						2	L	7	2 	4R				6A6     					 
1997041700047	19970417	00047	WP  	1997	4	17	97ZZZX1574       	1	19970127	G	5320		FLOOR SUPPORT   			CVAC  	440   	440         	2422902	WP  										BS 681 RT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FLOOR SUPPORT CORRODED BETWEEN STA 681-712 RT.						2	L	7	2 	4R				6A6     					 
1997041700048	19970417	00048	WP  	1997	4	17	97ZZZX1575       	1	19970127	G	5315		FLOOR BEAM      			CVAC  	440   	440         	2422902	WP  										BS 712 RT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FLOOR BEAM CORRODED AT STA 712 RT.						2	L	7	2 	4R				6A6     					 
1997041700049	19970417	00049	WP  	1997	4	17	97ZZZX1576       	1	19970127	G	5321		STRUCTURE       			CVAC  	440   	440         	2422902	WP  										COCKPIT FLOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				COCKPIT FLOOR STRUCTURE CORRODED STA 109 CENTER AREA.						2	L	7	2 	4R				6A6     					 
1997041700050	19970417	00050	WP  	1997	4	17	97ZZZX1577       	1	19970127	G	5730		SKIN            			CVAC  	440   	440         	2422902	WP  										LT MLG WELL	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				LEFT MLG WHEELWELL AFT LOWER SKIN CRACKED.						2	L	7	2 	4R				6A6     					 
1997041700051	19970417	00051	WP  	1997	4	17	97ZZZX1578       	1	19970127	G	5400		DOUBLER         			CVAC  	440   	440         	2422902	WP  										RT PIPE ACCESS	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				DOUBLER CRACKED RT INBD NR 2 ENGINE TAILPIPE ACCESS.						2	L	7	2 	4R				6A6     					 
1997041700052	19970417	00052	WP  	1997	4	17	97ZZZX1579       	1	19970127	G	5315		FLOOR BEAM      			CVAC  	440   	440         	2422902	WP  										BS 718 RBL 8	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				FLOOR BEAM CRACKED STA 718 RBL 8 AND 12.						2	L	7	2 	4R				6A6     					 
1997041700053	19970417	00053	WP  	1997	4	17	97ZZZX1580       	1	19970127	G	5551		FITTING         			CVAC  	440   	440         	2422902	WP  										HORIZ STAB	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	582P					475				RT UPPER FORWARD HORIZ STAB FITTING CRACKED.						2	L	7	2 	4R				6A6     					 
1997041700054	19970417	00054	CE  	1997	4	17	97ZZZX1581       	1	19970303	G	2823	13341511	VALVE           	WHITTAKER   		MTSBSI	MU2   	MU2B60      	5780460	CE  										MAIN FUEL SOV	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25					1297					THE SHUT-OFF VALVE FAILED IN CLOSED POSITION.  ORDERED AN OVERHAULED VALVE AND IT TRIPPED THE CIRCUIT BREAKER.  THIS WAS	 A NEWLY OVERHAULED VALVE WITH ZERO TIME.  VALVE WAS RETURNED TO VENDOR.					1	H	7	2 	3T			RT	A10SW   					 
1997041700055	19970417	00055	SO  	1997	4	17	97ZZZX1582       	2	19970310	G	8530	637836	SPRING          								CONT  	O520  	GTSIO520M   	17032	SO  					VALVE	BROKEN          	B	L	A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07		1014 					276111R			ENGINE WAS RECEIVED AT FACILITY FOR INSPECTION DUE TO METAL CONTAMINATION.  UPON DISASSEMBLY OF THE CYLINDERS, NOTED THE	RE WAS ONE BROKEN VALVE SPRING ON EACH CYLINDER IN THE INTAKE POSITION.  CYLINDERS NR 1, NR 3, AND NR 4 HAD BROKEN INNER	 VALVE SPRINGS AND CYLINDERS NR 2, NR 5, AND NR 6 HAD BROKEN OUTER VALVE SPRINGS.  THE SPRING ON NR 3 CYLINDER APPEARED 	TO HAVE BEEN BROKEN FOR SOME TIME AND WAS THE SOURCE OF THE METAL CONTAMINATION IN THE ENGINE.								3	O			E7CE				 
1997041700056	19970417	00056	SO  	1997	4	17	97ZZZX1583       	2	19970310	G	8530	637837	SPRING          								CONT  	O520  	GTSIO520M   	17032	SO  					VALVE	BROKEN          	B	L	A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07		1014 					276111R			ENGINE WAS RECEIVED AT FACILITY FOR INSPECTION DUE TO METAL CONTAMINATION.  UPON DISASSEMBLY OF THE CYLINDERS, NOTED THE	RE WAS ONE BROKEN VALVE SPRING ON EACH CYLINDER IN THE INTAKE POSITION.  CYLINDERS NR 1, NR 3, AND NR 4 HAD BROKEN INNER	 VALVE SPRINGS AND CYLINDERS NR 2, NR 5, AND NR 6 HAD BROKEN OUTER VALVE SPRINGS.  THE SPRING ON NR 3 CYLINDER APPEARED 	TO HAVE BEEN BROKEN FOR SOME TIME AND WAS THE SOURCE OF THE METAL CONTAMINATION IN THE ENGINE.								3	O			E7CE				 
1997041700057	19970417	00057	SO  	1997	4	17	97ZZZX1584       	1	19970301	G	5711		SPAR            			GULSTM	AA5   	AA5         	0631410	SO  										LT WING ROOT	CORRODED        	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	5507L					AA50627				AIRCRAFT WAS BEING DISASSEMBLED FOR PAINTING.  UPON REMOVAL OF LEFT WING ROOT, AN AREA OF INTERGRANULAR CORROSION WAS FO	UND ON THE TOP SURFACE OF THE INBOARD SPAR.  EXFOLIATION HAD PENETRATED TO A DEPTH OF .0625 INCH OVER AN AREA APPROXIMAT	ELY 3 INCHES BY 1.50 INCHES.  THIS PORTION OF SPAR IS TOTALLY INACCESSIBLE UNLESS WING AND WING ROOT ARE REMOVED.  SUSPE	CT MOISTURE IS TRAPPED BETWEEN SPAR AND INSIDE SURFACE OF WING ROOT.			1	L	7	1 	3O				A16EA   					 
1997041700058	19970417	00058	CE  	1997	4	17	97ZZZX1585       	1	19970327	G	3710	RAIJ47	FILTER          	RAPCO       		BEECH 	33    	F33A        	1151425	CE  										AUX AIR SYSTEM	MELTED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5530A	50   				CE1342				IN-LINE AIR FILTER FOR AUXILIARY AIR SYSTEM MOUNTED SIX INCHES FROM LEFT EXHAUST STACK.  THIS ITEM WAS MOUNTED FOR 50 HO	URS IN WHICH TIME PART OF THE HOUSING MELTED, AND THE REST BROKE APART FROM HEAT DAMAGE.  HOUSING IS MADE OF PLASTIC.  M	ANUFACTURER NEEDS TO RETURN TO USE OF METAL HOUSING.				1	L	7	1 	3O				3A15    					 
1997041700059	19970417	00059	SO  	1997	4	17	97ZZZX1586       	1	19970131	G	3230	3807802	HOOK            			PIPER 	PA32  	PA32R301T   	7103220	SO  										NLG DOWNLOCK	WORN            	D	L			O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			SW	09	8292G					32R8129004				PILOT REPORTED THE NOSE GEAR DOWN INDICATOR LIGHT WOULD 'FLICKER' AND THE GEAR PUMP RUN INTERMITTENTLY DURING TAXI.  INV	ESTIGATION REVEALED THE NOSE GEAR DOWNLOCK HOOK WAS SEVERELY WORN WHERE THE ARM OF THE DOWNLOCK SWITCH CONTACTED IT.  TH	IS ALLOWED THE SWITCH TO CLOSE AS THE DRAG LINK/DOWNLOCK ASSY FLEXED UNDER TAXI LOADS.				1	L	7	1 	3O				A3SO    					 
1997041700060	19970417	00060		1997	4	17	97ZZZX1587       	4	19970313	G	2562	AK450	ELT             	AMERIKING   																G SWITCH	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	05					4504652					OUT OF BOX FAILURE:  G-SWITCH.  NEW ELT FUNCTION CHECKS NORMALLY ON TEST CIRCUIT, BUT WHEN G-SWITCH IS ACTIVATED THE TON	E DOES NOT SWEEP.  SUSPECT DEFECTIVE (HIGH RESISTANCE) G-SWITCH.																		 
1997041700061	19970417	00061	CE  	1997	4	17	97ZZZX1588       	1	19970319	G	5751	0523816	HINGE           			CESSNA	172   	172G        	2072420	CE  										AILERON	DAMAGED         	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										HINGE AS DELIVERED FROM MFG SHOWS WHAT APPEARS TO BE A TOOL MARK.  SUBMITTER STATED MAKE SURE PART IS INSPECTED BEFORE U	SE.					1	H	7	1 	3O			NT	3A12    					 
1997041700062	19970417	00062	SO  	1997	4	17	97ZZZX1589       	2	19970321	G	8530	TM641370	CYLINDER        								CONT  	O360  	TSIO360F    	17025	SO  					NR 2	HEAD SEPARATED  	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15							305385			DURING ANNUAL INSPECTION, FOUND NR 2 CYLINDER HEAD SEPARATING FROM BARREL.  THE HEAD WAS TURNED COUNTERCLOCKWISE 4 DEGRE	ES AND WAS .0625 INCH FARTHER FROM FIRST CYLINDER FIN THAN OTHER CYLINDERS.  LEAK CHECK (PARAGRAPH C TCM SB 96-12) REVEA	LED LEAK.  COMPRESSION WAS 69/80.									3	O			E9CE				 
1997041700063	19970417	00063		1997	4	17	97ZZZX1590       	1	19970320	G	2432	G35	BATTERY         	GILLBATT    																VENT CAP	DEFECTIVE       	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										WHEN SERVICING NEW BATTERY PRIOR TO INSTALLATION, FOUND VENT CAPS DEFECTIVE.  LUG ON INSIDE OF CAP FELL OUT OF 4 OF 6 CA	PS.																		 
1997041700064	19970417	00064		1997	4	17	97ZZZX1591       	4	19970321	G	3197		WIRE            			PIPER 	PA31T 	PA31T1      	7103126	SO  										GLARESHIELD	CHAFED          	D		A		O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	11										WIRE BUNDLE FROM GLARESHIELD CHAFED THROUGH 'A+' WIRE FOR ANNUNCIATORS CAUSING ARCING AND SMOKE FROM UNDER GLARESHIELD. 	 FOUND WIRES UNPROTECTED AT FEED-THROUGHS.  ALSO, NO GROMMETS INSTALLED IN INSTRUMENT PANEL.  THE SHORT ALSO CAUSED THE 	ANNUNCIATOR CONTROL BOX TO SMOKE AND BECOME INOPERATIVE LOSING ALL THE WARNING SYSTEMS.  NOTE:  NO CURRENT PROTECTION IS	 BETWEEN THE BOX AND PANEL.			1	L	7	2 	3T			 	A8EA    					 
1997041700065	19970417	00065	CE  	1997	4	17	97ZZZX1592       	1	19970313	G	7160	125083920	HINGE PIN       			CESSNA	207   	T207A       	2073614	CE  										ALT AIR DOOR	FAILED          	D		A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			WP	11	1783U	9400 				20700383				PILOT REPORTED LOSS OF MANIFOLD PRESSURE AFTER TAKEOFF.  MADE OFF-AIRPORT LANDING.  NO INJURY, NO DAMAGE TO AIRCRAFT.  M	AINTENANCE INSPECTION FOUND ALTERNATE AIR DOOR HINGE PIN MISSING WHICH ALLOWED THE DOOR TO FALL INTO THE CONNECTING ELBO	W TO THE TURBOCHARGER RESTRICTING AIR FLOW.				1	H	7	1 	3O				A16CE   					 
1997041700066	19970417	00066	SO  	1997	4	17	97ZZZX1593       	1	19970320	G	3246	4086B	WHEEL           			PIPER 	PA28  	PA28161     	7102803	SO  										LT MLG AXLE	BEARING FROZE   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2115P					287916274				WHEN REMOVING WHEEL TO REPLACE BRAKE DISK (DUE TO NORMAL WEAR), WHEEL BEARINGS WERE FOUND FROZEN ON AXLE.  WHEN WHEEL WA	S FINALLY FREED FROM AXLE INSIDE, FOUND WHEEL FILLED WITH CORROSION RESIDUE.  AXLE HAD SOME MINOR PITTING, BUT WAS DETER	MINED TO BE IN SERVICEABLE CONDITION.				1	L	7	1 	3O				2A13    					 
1997041700067	19970417	00067	SO  	1997	4	17	97ZZZX1594       	1	19970320	G	7160	37328802	AIR BOX         			PIPER 	PA28  	PA28161     	7102803	SO  										CARBURETOR AIR	CRACKED         	D		A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	2115P					287916274				WHEN TROUBLESHOOTING POWER LOSS, FOUND CARBURETOR AIR BOX CRACKED IN SEVERAL PLACES, 1 OF 2 GROMMETS FOR FLAP PIVOT MISS	ING, BOTH SCAT HOSE ATTACHMENT FLANGES LOOSE.  THIS CONDITION ALLOWED HEAT TO CARBURETOR AT ALL TIMES.					1	L	7	1 	3O				2A13    					 
1997041700068	19970417	00068	SO  	1997	4	17	97ZZZX1595       	1	19970301	G	3030	464357	ELEMENT         			PIPER 	PA34  	PA34200T    	7103406	SO  										REAR PITOT HEAT	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	24CT					347670248				LOSS OF AIRSPEED - TRACED TO OPEN ELEMENT IN PITOT HEAT.   REPLACED REAR ELEMENT.						1	L	7	2 	3O				A7SO    					 
1997041700214	19970417	00214	SW  	1997	4	17	97ZZZX1620       	1	19970319	G	2430		HARNESS         			SWRNGN	SA226 	SA226TC     	8780404	SW  										LT GCU	CHAFED          	B			ATZR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	62Z					TC237				LEFT GCU WIRE HARNESS CHAFED IN NACELLE THROUGH LIGHTNING HOLE.  CAUSED CIRCUIT BREAKER FOR GENERATOR TO TRIP.  SUSPECT 	WIRE BUNDLE BROKE LOOSE FROM CLAMP DURING PROPELLER STRIKE 9.5 HRS BEFORE.  ENGINES AND PROPELLERS CHANGED OUT 9.5 HRS B	EFORE THIS PROBLEM.				2	L	7	2 	4T			RT	A8SW    					 
1997041700215	19970417	00215	CE  	1997	4	17	97ZZZX1621       	1	19970131	G	5610	991206415	WINDSHEILD      			CESSNA	500   	550         	2076604	CE  										COCKPIT	DEFECTIVE       	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	801JP				4097	5500043				OWNER REQUESTED INSTALLATION OF A SET OF WINDSHEILDS DELIVERED BY THE CUSTOMER.  INQUIRIES WERE MADE FROM THE SUPPLIER A	S TO THE TRACEABILITY OF THE WINDSHIELDS.  NO TRACABILITY COULD BE PROVIDED AND NEW WINDSHIELDS WERE ORDERED FROM CESSNA	 AND INSTALLED.  THIS MATTER WAS TURNED OVER TO CESSNA QUALITY AND ENGINEERING FOR FINAL DISPOSITION WITH THEIR SUPPLIER	 AND HAS BEEN RESOLVED.			1	L	7	2 	4F				A22CE   					 
1997041700216	19970417	00216	CE  	1997	4	17	97ZZZX1622       	1	19970131	G	5610	991206416	WINDSHEILD      			CESSNA	500   	550         	2076604	CE  										COCKPIT	DEFECTIVE       	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	801JP				3720	5500043				OWNER REQUESTED INSTALLATION OF A SET OF WINDSHEILDS DELIVERED BY THE CUSTOMER.  INQUIRIES WERE MADE FROM THE SUPPLIER A	S TO THE TRACEABILITY OF THE WINDSHIELDS.  NO TRACABILITY COULD BE PROVIDED AND NEW WINDSHIELDS WERE ORDERED FROM CESSNA	 AND INSTALLED.  THIS MATTER WAS TURNED OVER TO CESSNA QUALITY AND ENGINEERING FOR FINAL DISPOSITION WITH THEIR SUPPLIER	 AND HAS BEEN RESOLVED.			1	L	7	2 	4F				A22CE   					 
1997041700217	19970417	00217	CE  	1997	4	17	97ZZZX1623       	1	19970321	G	2460	99143871	OVERLAY         			CESSNA	650   	650         	2076802	CE  										PILOT CB PANEL	SHORTED         	B	S	A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	805GT	2988 				6500212				UPON REINSTALLATION OF THE PILOT'S SIDE MAIN CIRCUIT BREAKER PANEL OVERLAY, THE ATTACHING SCREW INSTALLED IN THE AFT CEN	TER MOUNT HOLE CONTACTED THE VERTICAL LEG OF A BUSS BAR.  THE BUSS BAR IS LOCATED DIRECTLY BEHIND (OUTBOARD OF THE MOUNT	ING NUTPLATE.  THE SCREW BEING INSTALLED WAS ONLY SLIGHTLY LONGER, APROXIMATELY .0625 INCH, THAN THE ONE ORIGINALLY INST	ALLED.  WHEN THE AIRCRAFT WAS POWERED UP, AN ELECTRICAL SHORT CIRCUIT TO GROUND OCCURRED RESULTING IN DAMAGE TO THE CIRC	UIT BREAKER PANEL, PANEL OVERLAY, SCREW, NUTPLATE, AND WIRING.		2	L	7	2 	4F				A9NM    					 
1997041700219	19970417	00219	NM  	1997	4	17	97ZZZX1625       	1	19970323	G	2752	MS9391130ZE	MOTOR           			BOEING	737   	737222      	1384473	NM  										FLAP DRIVE	LEAKING         	B			JR2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	9066U				MX190398D	19947				DURING FUNCTIONAL CHECK FLIGHT, A-SYSTEM HYDRAULICS WAS LOST.  UPON LANDING, FOUND THE FLAP DRIVE MOTOR LEAKING AT MOUNT	 SURFACE.  UPON REMOVAL OF FLAP DRIVE MOTOR, FOUND THE SEAL PLATE P/N 176002 S/N 569341 SHEARED AWAY FROM MOTOR DUE TO C	ORROSION OF INTERNAL WRENCHING RETAINING BOLTS P/N MS24-667-8L.  THIS HYDRAULIC MOTOR MANUFACTURED BY MICKERS.				2	L	7	2 	4F				A16WE   					 
1997041700221	19970417	00221	NE  	1997	4	17	97ZZZX1627       	3	19970319	G	6111	213E	BEARING RACE    													ROTOL	R389	R3894123F25 	NE  	BALL TRACK	BROKEN          	B	S		MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		19721	7380 					DRG151286		DURING TEAR DOWN FOR OVERHAUL OF PROPELLER, NOTED THAT 2 EACH SMALL BEARING RACES WERE BROKEN IN BALL TRACK.  ALSO, ALL 	4 BLADE BEARING ASSEMBLIES OF PROPELLER HAVE HEAVY/SEVERE CORROSION.  PROPELLER HAD BEEN REMOVED FOR ROUTINE OVERHAUL. A	/C REG NR UNKNOWN.														6	C	P30NE	 
1997041700222	19970417	00222	SO  	1997	4	17	97ZZZX1628       	1	19970320	G	7810	3563100	SHROUD ASSY     			PIPER 	PA28  	PA28161     	7102803	SO  										EXHAUST SYSTEM	DAMAGED         	D		A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	2115P					287916274				WHEN TROUBLESHOOTING POWER LOSS, FOUND PIECE OF FOREIGN MATTER (PROBABLY PIECE OF SPIRAL WRAP) IN CARBUREATOR THROAT.  A	LSO, FOUND MUFFLER TAKEOFF SHROUD ASSEMBLY BADLY DAMAGED AND SCREEN MISSING.  PRESUMABLY PIECE OF SPIRAL WRAP FELL OFF O	F STARTER CABLE AND INTO CARB HEAT DUCT (DUE TO MISSING SCREEN) AND WAS INJESTED INTO CARBURETOR.				1	L	7	1 	3O				2A13    					 
1997041700223	19970417	00223	SO  	1997	4	17	97ZZZX1629       	1	19970301	G	3030	464356	ELEMENT         			PIPER 	PA34  	PA34200T    	7103406	SO  										FWD PITOT HEAT	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	24CT					347670248				LOSS OF AIRSPEED TRACED TO OPEN PITOT TUBE ELEMENTS.						1	L	7	2 	3O				A7SO    					 
1997041700224	19970417	00224	SO  	1997	4	17	97ZZZX1630       	1	19970301	G	3030	464357	ELEMENT         			PIPER 	PA34  	PA34200T    	7103406	SO  										REAR PITOT HEAT	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	24CT					347670248				LOSS OF AIRSPEED TRACED TO OPEN PITOT TUBE ELEMENTS.						1	L	7	2 	3O				A7SO    					 
1997041700225	19970417	00225	CE  	1997	4	17	97ZZZX1631       	1	19970207	G	3231		DOOR            			CESSNA	210   	210L        	2073448	CE  										NLG	JAMMED          	D	L			O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NM	03	29209					21059832				AIRCRAFT TOOK OFF FOLLOWING RUN-UP AND TAXI IN 4-5 INCHES OF SNOW.  GEAR RETRACT OK.  RETURNED FOR LANDING AND GEAR DOOR	 WOULD NOT OPEN.  GEAR UP LANDING WITH DAMAGE.  RAISED NOSE, PRIED DOORS OPEN, GEAR FELL OUT.  APPARENTLY, ICE CAUSED DO	ORS TO RETRACT PAST SEAL AND JAM AFTER CLOSURE.				1	H	7	1 	3O				3A21    					 
1997041700226	19970417	00226	CE  	1997	4	17	97ZZZX1632       	1	19970402	G	3231	08411065	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  										LT MLG DOOR	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	310FH					310R1887				LEFT INBOARD GEAR DOOR WOULD NOT CLOSE.  FOUND BROKEN BELLCRANK.  DOOR ACTUATOR ARM FOUND BROKEN FROM CASTING.  DOOR FOU	ND TO BE RIGGED PER CESSNA MANUAL.					1	L	7	2 	3O				3A10    					 
1997041700227	19970417	00227	SO  	1997	4	17	97ZZZX1633       	1	19970301	G	3030	464356	ELEMENT         			PIPER 	PA34  	PA34200T    	7103406	SO  										FWD PITOT HEAT	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	47537					347770413				LOSS OF AIRSPEED TRACED TO OPEN PITOT HEAT ELEMENTS.						1	L	7	2 	3O				A7SO    					 
1997041700228	19970417	00228	SO  	1997	4	17	97ZZZX1634       	1	19970301	G	3030	464357	ELEMENT         			PIPER 	PA34  	PA34200T    	7103406	SO  										REAR PITOT HEAT	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	47537					347770413				LOSS OF AIRSPEED TRACED TO OPEN PITOT HEAT ELEMENTS.						1	L	7	2 	3O				A7SO    					 
1997041700229	19970417	00229	CE  	1997	4	17	97ZZZX1635       	1	19970311	G	7714	D11125025	TACHOMETER      	MITCH       		CESSNA	150   	152         	2071835	CE  										ENGINE	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	68792	57   			6446	15285338				TACHOMETER NEEDLE MOVEMENT HESITATES WITH CHANGES IN THROTTLE MOVEMENT.  THIRD TACHOMETER OF SAME MAKE AND MODEL INSTALL	ED IN SAME AIRCRAFT.					1	H	7	1 	3O			NT	3A19    					 
1997041700230	19970417	00230	CE  	1997	4	17	97ZZZX1636       	1	19970318	G	3230	50410012	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  										RT MLG	BROKEN          	D	S	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	01	7598Q	4135 				310Q0098				DISCOVERED BELLCRANK BROKEN AFTER RIGHT MAIN LANDING GEAR COLLAPSED ON LANDING ROLL OUT.						1	L	7	2 	3O				3A10    					 
1997041700231	19970417	00231	CE  	1997	4	17	97ZZZX1637       	1	19970317	G	2700		CONTROL CABLE   			CESSNA	206   	TU206F      	2073353	CE  										FLIGHT CONT	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7485Q					U20602220				AIRCRAFT TOTAL TIME 3,075 HRS.  AIRCRAFT BUILT AS LAND PLANE AND MODIFIED FOR FLOATS INSTALLATION IAW WIPAIRE STL SA1483	GL.  POH SUPPLEMENT REQUIRES 'OPERATION IN FRESH WATER ONLY' PLACARD DUE TO NO STAINLES STEEL CONTROL CABLES OR FUSELAGE	 INTERIOR PRIMER.  CONTROL CABLES FOUND BADLY RUSTED IN BELLY UNDER BAGGAGE DECK AREA.  BAGGAGE DECK STRUCTURE BADLY COR	RODED.  'FRESH WATER ONLY' PLACARD MISSING.  AIRCRAFT HAD BEEN OPERATED IN SALT WATER FOR THREE YEARS.			1	H	7	1 	3O			 	A4CE    					 
1997041700232	19970417	00232	CE  	1997	4	17	97ZZZX1638       	1	19970317	G	5320		STRUCTURE       			CESSNA	206   	TU206F      	2073353	CE  										BAG DECK	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7485Q					U20602220				AIRCRAFT TOTAL TIME 3,075 HRS.  AIRCRAFT BUILT AS LAND PLANE AND MODIFIED FOR FLOATS INSTALLATION IAW WIPAIRE STL SA1483	GL.  POH SUPPLEMENT REQUIRES 'OPERATION IN FRESH WATER ONLY' PLACARD DUE TO NO STAINLES STEEL CONTROL CABLES OR FUSELAGE	 INTERIOR PRIMER.  CONTROL CABLES FOUND BADLY RUSTED IN BELLY UNDER BAGGAGE DECK AREA.  BAGGAGE DECK STRUCTURE BADLY COR	RODED.  'FRESH WATER ONLY' PLACARD MISSING.  AIRCRAFT HAD BEEN OPERATED IN SALT WATER FOR THREE YEARS.			1	H	7	1 	3O				A4CE    					 
1997041700233	19970417	00233	CE  	1997	4	17	97ZZZX1639       	1	19970321	G	7120	J151981	MOUNT           	LORD        		CESSNA	188   	A188B       	2073005	CE  										ENGINE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	9086R					18802107T				WHILE REMOVING ENGINE FOR MAJOR OVERHAUL, FOUND BOLTS OF THE REAR LORD MOUNTS NOT INSTALLED THROUGH THE INTERNAL SPACERS	.  APPARENTLY, BOLTS HAD BEEN REMOVED AND THE SPACERS FELL OUT OF POSITION AND THEN THE BOLTS WERE REINSTALLED.					1	L	7	1 	3O				A9CE    					 
1997041700234	19970417	00234	SO  	1997	4	17	97ZZZX1640       	1	19970308	G	5711	SP17	SPAR            			LUSCOM	8     	8A          	8190104	SO  										WING REAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1057K					3784				INTERGRANULAR CORROSION FOUND ON LEFT WING REAR SPAR WHILE INSPECTING AS REQUIRED BY AD 96-24-17.  REPLACED WITH NEW SPA	R.					1	H	7	1 	3O				A694    					 
1997041700235	19970417	00235	SO  	1997	4	17	97ZZZX1641       	2	19970228	G	8530	635448CN	CYLINDER        			BEECH 	36    	36BEECH     	1151602	CE  	CONT  	O520  	IO520B      	17032	SO  					NR 2	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	1194A		1400 			E159				CYLINDER HEAD CAME OFF IN-FLIGHT 2-28-97.  NO DAMAGE OR OIL LEAK OCCURRED.  REPLACED CYLINDER.						1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997041700236	19970417	00236	EA  	1997	4	17	97ZZZX1642       	2	19970325	G	7320	3030523	SUPPORT BRACKET 			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					P3 FILTER	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	23407	4021 				31T7920055	51979			INSPECTION FOUND P3 FILTER HOUSING SUPPORT BRACKET CRACKED.  IF UNIT FAILED COULD AFFECT FCU.						1	L	7	2 	3T	4	T		A8EA    	E4EA				 
1997041700237	19970417	00237	CE  	1997	4	17	97ZZZX1643       	1	19970314	G	2750	051015259	CONTROL CABLE   			CESSNA	206   	U206F       	2073333	CE  										LT FLAP DIRECT	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1523U	6558 				U20602234				DURING A 200-HOUR INSPECTION, LEFT FLAP DIRECT CABLE WAS FOUND FRAYED WHERE IT PASSES OVER PULLEY NEXT TO BELLCRANK.  FR	AYED AREA COULD NOT BE SEEN WITH FLAPS DOWN.  SUBMITTER STATED AGE AND INACCESSABILITY WERE PROBABLY THE CAUSES OF THIS 	PART FAILURE.  RECOMMEND AREA BE INSPECTED WITH BOTH FLAPS UP AND DOWN.				1	H	7	1 	3O			 	A4CE    					 
1997041700238	19970417	00238	CE  	1997	4	17	97ZZZX1644       	1	19970314	G	7120	075100331	MOUNT           			CESSNA	185   	A185F       	2072821	CE  										ENG RT FRONT	CRACKED         	B			CF4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	6705H	3362 				18503337				DURING ENGINE CHANGE, BEADBLASTED AND MAGNAFLUX INSPECTED ENGINE MOUNT.  FOUND CRACK AT WELD OF RIGHT FRONT CROSS MEMBER	 TO HORIZONTAL TUBE.  THIS AREA HAD BEEN PREVIOUSLY WELDED AND THIS CRACK WAS AT THIS WELD AREA.  THIS IS UNDER THE RIGH	T FRONT MOUNT BED.				1	H	7	1 	3O				3A24    					 
1997041700239	19970417	00239	NE  	1997	4	17	97ZZZX1645       	2	19970228	G	7250	3029241	GAS GENERATOR   			CESSNA	501   	501         	2076603	CE  	PWA   	JT15  	JT15D1      	52060	NE  					DIFFUSER TUBE	CORROSION HOLE  	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1AT	4730 	1533 			5010159	77405			WHILE TROUBLESHOOTING AN EXISTING PROBLEM WITH ONE ENGINE, THE DIFFUSER TUBES WERE FOUND TO HAVE HEAVY CORROSION WITH SE	VERAL HOLES CORRODED THROUGH.  SUBSEQUENT INSPECTION OF THE OTHER ENGINE RESULTED IN FINDING THE SAME PROBLEM.  BOTH ENG	INES WERE REMOVED AND SENT TO THE MANUFACTURER.				1	L	7	2 	4F	4	F		A27CE   	E1NE				 
1997041700240	19970417	00240	NE  	1997	4	17	97ZZZX1646       	2	19970228	G	7250	3029241	GAS GENERATOR   			CESSNA	501   	501         	2076603	CE  	PWA   	JT15  	JT15D1      	52060	NE  					DIFFUSER TUBE	CORROSION HOLE  	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1AT	4730 	1533 			5010159	77402			WHILE TROUBLESHOOTING AN EXISTING PROBLEM WITH ONE ENGINE, THE DIFFUSER TUBES WERE FOUND TO HAVE HEAVY CORROSION WITH SE	VERAL HOLES CORRODED THROUGH.  SUBSEQUENT INSPECTION OF THE OTHER ENGINE RESULTED IN FINDING THE SAME PROBLEM.  BOTH ENG	INES WERE REMOVED AND SENT TO THE MANUFACTURER.				1	L	7	2 	4F	4	F		A27CE   	E1NE				 
1997041700241	19970417	00241	NE  	1997	4	17	97ZZZX1647       	3	19970325	G	6111	SK112315	PIN ASSY        	HAMSTD      	7922221     											HAMSTD	14SF	14SF7       	NE  	BLADE	CRACKED         	B			H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		7052 								DURING DYE CHECK OF BLADE SHANK, AN INDICATION IN THE BEARING RACE FILLET RADIUS WAS OBSERVED.  THE INDICATION IS LOCATE	D APPROXIMATELY 90 DEGREES FROM THE BLADE PIN, CLOCKWISE, AS VIEWED FROM THE BUTT END.  THE INDICATION IS APPROXIMATELY 	.600 INCH LONG, AND IS ORIENTED CIRCUMFERENTIALLY IN THE RADIUS.														6	C	P7NE	 
1997041700242	19970417	00242	CE  	1997	4	17	97ZZZX1648       	1	19970327	G	2121	591224	MOTOR           		725652B     	CESSNA	650   	650         	2076802	CE  										HYD FAN ASSY	LEAKAGE         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	67SF		2498 		166	6500045				ACFT PARKING BRAKE WAS SET AND BOTH ENGINES WERE STARTED, ACFT STARTED DRIFTING FWD.  THE PILOT RESET PARKING BRAKE, THE	N NOTICED BOTH HYD FLUID LEVEL AND HYD PRESSURE GAUGES FALLING RAPIDLY.  ENG WERE SHUT DOWN IMMEIDATELY.  HYD FLUID WAS 	FOUND RUNNING DOWN THE RT SIDE AND OUT OF THE BELLY DRAINS OF THE FUSELAGE.  THE LOCATION OF LEAK WAS FOUND TO BE THE EN	VIRONMENTAL CONTROL UNIT RAM AIR HYD FAN.  THE FAN ASSEMBLY WAS REPLACED AND SYSTEM BLED.  JUST PRIOR TO THIS OCCURRENCE	, PILOTS HAD NOTICED A SLIGHTLY MORE THAN NORMAL PRESSURE DROP WHEN THE FAN WAS RUNNING AND THE ENGINES WERE AT IDLE.  T	HE FAN IS ONLY RUNNING WITH THE AIRCRAFT IS ON THE GROUND AND THE ECU'S ARE TURNED ON.	2	L	7	2 	4F				A9NM    					 
1997041700502	19970417	00502	SW  	1997	4	17	97ZZZX1654       	1	19970212	G	2430	1820300150	SHUNT           			BELL  	230   	230         	1182149	SW  										DC SYSTEM	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	706  				23019				SHUNT DISCOLORED, CAUSING INTERMITTENT LOAD BREAKDOWN.  REPLACED 2 EACH.						1	G	7	2 	3U			NC	H9SW    					 
1997041700504	19970417	00504	SW  	1997	4	17	97ZZZX1656       	1	19970122	G	6720	230312001101	PITCH LINK      			BELL  	230   	230         	1182149	SW  										BEARING	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	674  				23019				BEARINGS WORN.  REPLACED 2 EACH PITCH LINKS.						1	G	7	2 	3U			NC	H9SW    					 
1997041700549	19970417	00549	EA  	1997	4	17	97ZZZX1666       	2	19970331	G	8520		CRANKCASE       			ENSTRM	F28   	280F        	3300550	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					CRANKCASE	MISALIGNED      	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	199TV					1510	L2313251A			A FACTORY OVERHAULED ENGINE WAS INSTALLED.  ENGINE STARTED TO MAKE METAL.  WHEN OIL WAS DRAINED, IT LOOKED LIKE ALUMINUM	 PAINT.  AN OIL SAMPLE AND FILTER ELEMENT WERE SENT TO FACTORY.  FACTORY REQUESTED THAT ENGINE BE REMOVED AND SENT IN FO	R REPAIR.  TIME ON ENGINE 63.5 HRS SMOH.  SUSPECT CAUSE WAS MISALIGNED CRANKCASE.  THIS CAUSED PISTON PINS TO SHIFT.				1	G	7	1 	3O	3	O		H1CE    	1E10				 
1997042200005	19970422	00005	WP  	1997	4	22	97ZZZX1669       	1	19970324	G	6720	369A18079	BEARING         			HUGHES	369   	369HS       	4470728	WP  										T/R PITCH LINK	FAILED          	D		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SO	09	8388F		132  			760838S				TAIL ROTOR PITCH CHANGE LINKS WERE INSTALLED AT 13,300.8 AIRCRAFT HOURS.  AT 13,432 AIRCRAFT HOURS, ONE PITCH CHANGE LIN	K FAILED AT ONE END.  THE BEARING APPEARS TO HAVE BEEN EXCESSIVELY OVER ROLL STAKED UPON INSTALLATION INTO THE LINK BEAR	ING HOUSING.  FAILURE OF THE LINK ASSY CAUSED LOSS OF TAIL ROTOR CONTROL OF THE AIRCRAFT.  PILOT LANDED SAFELY WITHOUT F	URTHER DAMAGE.  RECOMMEND MANDATORY NDI INSPECTION AFTER A BEARING IS INSTALLED IN THESE LINKS.			1	G	7	1 	3U				H3WE    					 
1997041700552	19970417	00552	SW  	1997	4	17	97ZZZX1670       	1	19970321	G	6320	206040076009	SCREEN          			BELL  	206   	206B        	1181511	SW  										XMSN SUMP	UNBONDED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67960	598  				5232				TRANSMISSION SUMP INBOARD SLEEVE UNBONDED FROM SCREEN ASSY, 2 EACH REPLACED IN LAST 4 MONTHS FOR SAME REASON.						1	G	7	1 	3U				H2SW    					 
1997041700553	19970417	00553	NE  	1997	4	17	97ZZZX1671       	1	19970319	G	5320	7620103501101	SUPPORT BEAM    			SKRSKY	S76   	S76B        	8143007	NE  										CABIN OVERHEAD	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	388GS	1608 				760410				WHILE DOING CABIN INSPECTION, THE OVERHEAD LATERAL VIBRATION SUPPORT BEAM WAS FOUND CRACKED IN THE LOWER LEFT AND RIGHT 	CORNERS.  THE SUPPORT BEAM WAS REPLACED WITH A NEW SUPPORT BEAM AND WAS MODIFIED IAW SIKORSKY INSTRUCTIONS AND 8110 INFO	RMATION.				1	G	7	2 	4U				H1NE    					 
1997041700554	19970417	00554	NE  	1997	4	17	97ZZZX1672       	1	19970319	G	5320	7620103501103	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										CABIN OVERHEAD	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	388GS	1608 				760410				WHILE DOING CABIN INSPECTION, ANGLE WAS FOUND CRACKED.  THE ANGLE WAS REPLACED WITH A NEW ANGLE AND REINFORCED IAW SIKOR	SY SRM.					1	G	7	2 	4U				H1NE    					 
1997041700555	19970417	00555	NE  	1997	4	17	97ZZZX1673       	1	19970319	G	5320	7620103501115	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										CABIN OVERHEAD	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	388GS	1608 				760410				WHILE DOING CABIN INSPECTION, ANGLE WAS FOUND CRACKED IN THE RIGHT CORNER.  THE ANGLE WAS REPLACED WITH A NEW ANGLE FROM	 SIKORSKY.					1	G	7	2 	4U				H1NE    					 
1997041700558	19970417	00558	SW  	1997	4	17	97ZZZX1675       	1	19970312	G	3213	206324004	SKID TUBE       			BELL  	206   	206L1       	1182107	SW  										SKID PLATE	CRACKED         	B		A	HEER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y				AUG1495	45192				FOUND 8 CRACKS ON RT SKID TUBE RADIATING FROM SKIP-PLATE MOUNTING HOLES.  THIS TUBE WAS MFG 8-14-95.  HAVE FOUND 3 SKID 	TUBES CRACKED IN THIS MANNER.  ALL TUBES WERE MFG IN AUG '95.  REPLACED TUBES WITH SERVICEABLE TUBES.					1	G	7	1 	3U				H2SW    					 
1997041700559	19970417	00559	SW  	1997	4	17	97ZZZX1676       	1	19970312	G	3213	206324003	SKID TUBE       			BELL  	206   	206L1       	1182107	SW  										SKID PLATE	CRACKED         	B			HEER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y				AUG95	45192				FOUND 3 CRACKS ON RT SKID TUBE RADIATING FROM SKID PLATE AND FRONT MOUNTING HOLES.  HAVE FOUND 3 SKID TUBES CRACKED IN T	HIS MANNER.  ALL MFG AUG '95.  REPLACED TUBES WITH SERVICEABLE TUBES.					1	G	7	1 	3U				H2SW    					 
1997041700561	19970417	00561	EU  	1997	4	17	97ZZZX1678       	1	19970301	G	6240	350A08386100	WARN HORN       			SNIAS 	350   	AS350B2     	8680813	EU  										ROTOR RPM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	6098U					2718				THERE ARE TWO TYPES OF WARNING HORNS.  ONE MANUFACTURER IS KLAXON, THE OTHER IS VOXBELL.  BOTH OF THE HORNS ARE FAILING 	DUE TO POOR WORKMANSHIP.  ITEMS CAUSING FAILURE ARE POOR SOLDERING POINTS AND RIVETS NOT FULLY SQUEEZED WHICH SHOULD MAK	E CONTACT TO ACTIVATE THE HORN WHEN ROTOR RPM FALLS BELOW MINIMUM.  HAVE HAD TO ORDER FOUR HORNS IN SIXTY-DAY PERIOD.				1	G	7	1 	3U				H9EU    					 
1997041700562	19970417	00562	WP  	1997	4	17	97ZZZX1679       	1	19970326	G	6410	36124	CUFF            		3612319     	HILLER	UH12  	UH12E       	4360122	WP  										CONTROL BLADE	CRACKED         	B			OUGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	62392	3806 	381  		6526	1591				IAW AD 77-07-05(S) AND HILLER SB 36-1 REV 3, PARA 2(G).  FOUND CRACK AT CONTROL BLADE CUFF INBOARD BOLT HOLE DURING 100-	HOUR REPETATIVE DYE-PENETRANT INSPECTION.  NOTE:  6,860 HOUR LIFE-LIMIT.					1	G	7	1 	3O				4H11    					 
1997041700563	19970417	00563	WP  	1997	4	17	97ZZZX1680       	1	19970326	G	6410	36124	CUFF            		3612319     	HILLER	UH12  	UH12E       	4360122	WP  										CONTROL BLADE	CRACKED         	B			OUGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	62392	4402 	381  		5599	1591				IAW AD 77-07-05(S) AND HILLER SB 36-1 REV 3, PARA 2(G).  FOUND CRACK AT CONTROL BLADE CUFF INBOARD BOLT HOLE DURING 100-	HOUR REPETATIVE DYE-PENETRANT INSPECTION.  NOTE:  6,860 HOUR LIFE-LIMIT.					1	G	7	1 	3O				4H11    					 
1997041700565	19970417	00565	GL  	1997	4	17	97ZZZX1682       	2	19970318	G	7210	6871064	DAMPER RING     		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F	6734 	3420 		CAG36146	1280431D	CAE832846			FOUND DAMPER RING CRACKED AND A SMALL CHIP MISSING ON THE OUTSIDE DIAMETER OF THE RING.  THIS DEFECT BEING ON THE GEAR S	IDE OF THE RING, FITS ALL THE WAY IN THE GROOVE, AND WAS ONLY FOUND AFTER REMOVAL.  CRACK WAS 2 INCHES FROM THE END OF T	HE RING.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997041700566	19970417	00566	SW  	1997	4	17	97ZZZX1683       	1	19970306	G	6410	206010765001	BEARING         			BELL  	206   	206L3       	1182108	SW  										T/R FEATHER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	728H					51553				CRACKED FEATHERING BEARING ON TAIL ROTOR BLADE P/N 206-016-201-127.  OCCURRED DURING NORMAL OPERATION, FOUND DURING ROUT	INE INSPECTION.  SUSPECTED GAP BETWEEN BEARING AND BLADE.  RECOMMENDED AD OR ASB BE ISSUED TO REPLACE FEATHERING BEARING	 INSTEAD OF T.B. 206L-984-172.  SUBMITTER STATEDTHIS PROBLEM HAS OCCURRED MANY TIMES.				1	G	7	1 	3U				H2SW    					 
1997041700567	19970417	00567	SW  	1997	4	17	97ZZZX1684       	1	19970306	G	6410	206010765001	BEARING         			BELL  	206   	206L3       	1182108	SW  										T/R FEATHER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	727H					51550				CRACKED FEATHERING BEARING ON TAIL ROTOR BLADE P/N 206-016-201-127.  OCCURRED DURING NORMAL OEPRATION, FOUND DURING ROUT	INE INSPECTION.  SUSPECTED GAP BETWEEN BEARING AND BLADE.  RECOMMENDED AD OR ASB BE ISSUED TO REPLACE FEATHERING BEARING	 INSTEAD OF T.B. 206L-94-172.  SUBMITTER STATED PROBLEM HAS OCCURRED MANY TIMES.				1	G	7	1 	3U				H2SW    					 
1997041700568	19970417	00568	SW  	1997	4	17	97ZZZX1685       	1	19970306	G	6410	206010765001	BEARING         			BELL  	206   	206L3       	1182108	SW  										T/R FEATHER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	722H					51452				CRACKED FEATHERING BEARING ON TAIL ROTOR BLADE P/N 206-016-201-127.  OCCURRED DURING NORMAL OEPRATION, FOUND DURING ROUT	INE INSPECTION.  SUSPECTED GAP BETWEEN BEARING AND BLADE.  RECOMMENDED AD OR ASB BE ISSUED TO REPLACE FEATHERING BEARING	 INSTEAD OF T.B. 206L-94-172.  SUBMITTER STATED PROBLEM HAS OCCURRED MANY TIMES.				1	G	7	1 	3U				H2SW    					 
1997041700570	19970417	00570	NE  	1997	4	17	97ZZZX1687       	1	19970319	G	5313	7620204001146	LONGERON        			SKRSKY	S76   	S76B        	8143007	NE  										TAIL BOOM	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5NJ	2855 				760346				WHILE REPAIRING CRACK IN AFT SHEAR DECK WEB, FOUND A CRACK IN THE RIGHT TAIL BOOM LONGERON.  THE LONGERON WAS REPAIRED I	AW SIKORSKY SRM.  THE NESTED ANGLE, P/N 76202-04001-106, WAS REPLACED WITH NEW STYLE NESTED ANGLE P/N 76202-24001-104 IA	W SRM AT THE SAME TIME.				1	G	7	2 	4U				H1NE    					 
1997042400001	19970424	00001	WP  	1997	4	24	97ZZZX1690       	1	19970304	G	6310	234005	SHAFT           			HILLER	UH12  	H23B        	4360114	WP  										INTERMED DRIVE	SHEARED         	D		A		R				AUTOROTATION            				J			WARNING INDICATION        			HO	HOVERING       	1			NM	01	6055		262  		2776	598				WHILE PERFORMING HOVER TRACK AND BALANCE OF THE M/R BLADE ASSEMBLIES, A LOUD BANG WAS HEARD AND ROTOR RPM DECAYED.  A HO	VERING AUTOROTATION WAS SUCCESSFULLY COMPLETED.  UPON TEAR-DOWN, EXCESSIVE WEAR WAS FOUND ON THE INTERMEDIATE SHAFT LOWE	R GEAR TEETH OF .030 INCH.  THIS SHAFT HAD SHEARED IN TWO CAUSING THE DISENGAGEMENT OF THE ENGINE AND ROTOR DRIVE TRAIN.	  THE MATING GEAR LOCATED INSIDE OF THE MERCURY CLUTCH HOUSING HAD A WEAR OF APPROXIMATELY .037 INCH.			1	G	7	1 	3O				6H2     					 
1997042400002	19970424	00002	EU  	1997	4	24	97ZZZX1691       	1	19970327	G	6320	4638001004	TRANSMISSION    			BOLKMS	105   	BO105S      	5626006	EU  										SWASH PLATE	PIN MISSING     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	19	70EG				1234	S458				OPERATOR PURCHASED AN 'EXCHANGE' MAIN ROTOR TRANSMISSION FROM AMERICAN EUROCOPTER.  UNIT RECEIVED WITH HISTORICAL RECORD	 CARDS, A 'SERVICABLE' TAG, AND A FAA FORM ONE CERTIFICATE.  TRANSMISISON WAS OVERHAULED 2-4-97, FAA REPAIR STATION ZF6Y	043N.  AFTER INSTALLATION AND DURING GROUND MAINTENANCE RUNS AND PREPARATION FOR MAIN ROTOR SYSTEM TRACK AND BALANCE CHE	CKS, DISCOVERED THE TRANSMISSION HAD BEEN ASSEMBLED WITHOUT THE INSTALLATION OF P/N 105-41901.19, BALANCING SYSTEM MAGNE	TIC PICK-UP 'TARGET'/INTERRUPTOR.  SUBMITTER STATED ALTHOUGH NOT A HAZARDOUS SITUATION IN ITSELF, 'WHAT ELSE WAS NOT INS	TALLED OR INSTALLED INCORRECTLY?'	1	G	7	2 	3U				H3EU    					 
1997042400003	19970424	00003	NM  	1997	4	24	97ZZZX1692       	1	19970327	G	6320	A0061	GEARBOX         			ROBSIN	R22   	R22BETA     		NM  										M/R GEARBOX	SLUDGED         	B			GJOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	222YP	3799 	726  		1135	1057				WHILE PERFORMING A 100-HR INSPECTION, MAIN GEARBOX CHIP DETECTOR WAS REMOVED.  CHIP DETECTOR FOUND WITH EXCESSIVE AMOUNT	S OF SLUDGE BUILD-UP.  A FUNCTIONAL CHECK VERIFIED A CHIP WOULD NOT COMPLETE THE CIRCUIT.  AFTER CLEANING CHIP DETECTOR,	 NO FURTHER DISCREPANCIES NOTED.  TT 190.0 HRS SINCE LAST CLEANING AND FUNCTIONAL CHECK ON CHIP DETECTOR.  SUBMITTER REC	OMMENDS A 100-HR CLEANING AND FUNCTIONAL CHECK ON CHIP DETECTOR ALONG WITH ANNUAL GEARBOX OIL CHANGE.  THE ROBINSON R22 	MAIN TRANSMISSION CHIP DETECTOR IS NOT EASILY ACCESSED.  MOST AIRCRAFT AND ROTORCRAFT CHIP DETECTORS ARE OF A QUICK DISC	ONNECT TYPE.  SUBMITTER WOULD REQUEST A CHANGE IN DESIGN TO THE R22 TO INSTALL THE QUICK DISCONNECT TYPE CHIP DETECTOR.	1	G	7	1 	3O				H10WE   					 
1997042400006	19970424	00006		1997	4	24	97ZZZX1695       	1	19970318	G	3242	16430388	BRAKE DISC      	PARKERHANFIN																WHEEL FLANGE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07										INSPECTION FOUND BRAKE DISC MISMANUFACTURED. UNIT MEASURES 2.375 INCH OVERALL.  CORRECT DIMENSION IS 2.335 INCHES TO 2.3	45 INCHES OVERALL.  NUMBER STAMPED ON FLANGE IS 30388624.																		 
1997042400007	19970424	00007		1997	4	24	97ZZZX1696       	4	19970328	G	2562	BP1025	BATTERY PACK    	MERL        		CESSNA	170   	170A        	2072304	CE  										ELT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	1314D					19890				DURING ANNUAL INSPECTION FOUND HEAVY RUST ON ENDS OF BATTERY PACK WHERE TERMINALS AND CONNECTING BUSS BARS ARE SOLDERED.	  CORROSION WAS NOT VISIBLE UNTIL PACK WAS DISASSEMBLED (RENDERING IT NOT USABLE) BECAUSE CARDBOARD WAS GLUED OVER ENDS 	THEN WHOLE BATTERY PACK WAS SHRINK WRAPPED IN PLASTIC.  THIS PACK WAS CHANGED 6 MONTHS BEFORE DUE DATE FOR CONVENIENCE. 	 BATTERY DID MAKE NORMAL VOLTAGE.			1	H	7	1 	3O				A799    					 
1997042400008	19970424	00008	SO  	1997	4	24	97ZZZX1697       	1	19970327	G	5741	6244802	FITTING         			PIPER 	PA28  	PA28R200    	7102811	SO  										LT WING AFT	CORRODED        	B		A	BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	15597	3251 				28R7335072				DURING ANNUAL INSPECTION, FOUND AFT WING FITTINGS AND ADJACENT STRUCTURE CORRODED.  PIPER SB977 ADDRESSES THIS PROBLEM. 	 CAUSE DUE TO WINDOW SEALS FAILING AND MOISTURE REMAINING IN THE INSULATION.					1	L	7	1 	3O				2A13    					 
1997042400009	19970424	00009	SO  	1997	4	24	97ZZZX1698       	1	19970327	G	5741	6244803	FITTING         			PIPER 	PA28  	PA28R200    	7102811	SO  										RT WING AFT	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	15597	3251 				28R7335072				DURING ANNUAL INSPECTION, FOUND AFT WING FITTINGS AND ADJACENT STRUCTURE CORRODED.  PIPER SB977 ADDRESSES THIS PROBLEM. 	 CAUSE DUE TO WINDOW SEALS FAILING AND MOISTURE REMAINING IN THE INSULATION.					1	L	7	1 	3O				2A13    					 
1997042400010	19970424	00010	SO  	1997	4	24	97ZZZX1699       	1	19970327	G	2810	6358500	FILLER NECK     			PIPER 	PA28  	PA28R200    	7102811	SO  										FUEL TANK	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	15597	3251 				28R7335072				DURING ANNUAL INSPECTION, FOUND AFT WING FITTINGS AND ADJACENT STRUCTURE CORRODED.  PIPER SB977 ADDRESSES THIS PROBLEM. 	 CAUSE DUE TO WINDOW SEALS FAILING AND MOISTURE REMAINING IN THE INSULATION. FOUND THE FUEL TANK FILLER NECK CORRODED TH	ROUGH INTO THE FUEL STORAGE AREA.  THE PILOT REMARKED, 'AH!  I WAS WONDERING WHY MY FUEL ALWAYS HAD WATER IN IT!'.  THE 	CORROSION WAS PLAINLY VISIBLE, BUT COULD ONLY SEE THE PENETRATION WHEN THE RUST BUILD-UP WAS CLEANED AWAY.  SUBMITTER ST	ATED LACK OF SEAL MAINT AND BASED IN A CORROSIVE ENVIRONMENT CAUSED THIS PROBLEM.		1	L	7	1 	3O				2A13    					 
1997042400011	19970424	00011	SO  	1997	4	24	97ZZZX1700       	1	19970326	G	2410	452541	BELT            			PIPER 	PA28  	PA28R200    	7102811	SO  										ALT DRIVE	FAILED          	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09	15597	3251 				28R7335072				A COMMON PROBLEM THAT SUBMITTER HAS FOUND OVER THE YEARS, WITH PIPER PRODUCTS ESPECIALLY, IS THE USE OF AUTOMOTIVE OR UN	APPROVED ALTERNATOR DRIVE BELTS.  IN THIS CASE, A NAPA AUTOMOTIVE BELT WAS INSTALLED.					1	L	7	1 	3O				2A13    					 
1997042400012	19970424	00012	SO  	1997	4	24	97ZZZX1701       	1	19970326	G	3411	69041005	PITOT HEAD      			PIPER 	PA28  	PA28R200    	7102811	SO  										AIR INLET	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	15597	3251 				28R7335072				THE PITOT MAST WAS SO CORRODED THE AIR INLET HOLES WERE CLOSED APPROXIMATELY ONE-FOURTH DUE TO THE BUILD-UP OF THE CORRO	SION.  SUBMITTER STATED THE AIRCRAFT HAD BEEN BASED IN A CORROSIVE ENVIRONMENT (FLORIDA).					1	L	7	1 	3O				2A13    					 
1997042400013	19970424	00013	SO  	1997	4	24	97ZZZX1702       	1	19970326	G	7120	6711949	MOUNT           			PIPER 	PA28  	PA28R200    	7102811	SO  										ENG/MLG MT	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	15597	3251 			F2079	28R7335072				MOST OF THE TUBES ON THIS ENGINE/LANDING GEAR MOUNT HAD TO BE REPLACED DUE TO CORROSION, CRACKS, OR CHAFING.  THE CHAFIN	G WAS FROM OLD LOOP-TYPE (ADEL) CLAMPS THAT HAD NOT BEEN REPLACED WHEN THE RUBBER CUSHIONS DRIED OUT.  THE AIRCRAFT HAD 	BEEN IN AN ACCIDENT WHERE ONE GEAR COLLAPSED WHICH MAY ACCOUNT FOR THE TWO CRACKED TUBES.  THE CORROSION WAS JUST FROM L	ACK OF PREVENTATIVE MAINTENANCE IN A CORROSIVE ENVIRONMENT (FLORIDA).			1	L	7	1 	3O				2A13    					 
1997042400014	19970424	00014	CE  	1997	4	24	97ZZZX1703       	1	19970226	G	7120	07516001	MOUNT           			CESSNA	182   	182P        	2075816	CE  										ENG LT SIDE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	344K		1750 		K2772	18263709				THE ENGINE MOUNT WAS FOUND CRACKED ON THE LEFT HAND SIDE.  THE LEFT HAND HORIZONTAL TUBE WAS FOUND CRACKED ABOUT THREE-F	OURTHS OF THE WAY AROUND WITH THE CRACK STARTING AT THE AFT GUSSET WELD AND WORKING ITS WAY AROUND THE CIRCUMFERENCE OF 	THE TUBE.				1	H	7	1 	3O			NT	TA13    					 
1997042400015	19970424	00015	CE  	1997	4	24	97ZZZX1704       	1	19970321	G	5320	0024100113	COVER           			BEECH 	33    	F33A        	1151425	CE  										NLG WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	856KS	303  				CE1753				AT 100-HOUR INSPECTION, CRACK ABOUT 3 INCHES LONG WAS FOUND IN NOSE GEAR WHEELWELL COVER JUST BEHIND NOSE GEAR STRUT.  C	AUSE OF CRACK IS UNKNOWN.  PATCHED CRACK WITH SECTION OF A NEW COVER IAW 43.13.					1	L	7	1 	3O				3A15    					 
1997042400016	19970424	00016	CE  	1997	4	24	97ZZZX1705       	1	19970321	G	5320	0024100113	COVER           			BEECH 	33    	F33A        	1151425	CE  										NLG WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	854KS					CE1764				AT 100-HOUR INSPECTION, CRACK ABOUT 5 INCES LONG WAS FOUND IN NOSE GEAR WHEELWELL COVER JUST BEHIND NOSE GEAR STRUT.  CA	USE OF CRACK IS UNKNOWN.  SPLICED IN NEW SECTION OF A NEW COVER IAW 43.13.  SUBITTER SUGGESTS KEEPING CLOSE INSPECTION O	F THIS AREA FOR CRACKS.				1	L	7	1 	3O				3A15    					 
1997042400017	19970424	00017	SO  	1997	4	24	97ZZZX1706       	1	19970325	G	5347		MOUNT BRACKET   			PIPER 	PA42  	PA42        	7104202	SO  										PAX SEAT FRAME	BROKEN          	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	158TJ	3090 				428001057				DURING SCHEDULED MAINTENANCE, PASSENGER SEAT AFT FACING BEHIND COPILOT, WRITTEN UP AS 'LOOSE IN TRACK'.  DISCOVERED FRON	T FLOOR MOUNTED BRACKET CRACKED AND TORN FROM SEAT FRAME.  SUSPECT CAUSE, SEAT BACK USED AS LEVERAGE INTO COCKPIT:  ALSO	, AIRCRAFT TYPE CERTIFICATE DOES NOT ALLOW FOR VARIATIONS IN CONFIGURATION OF SEATS.  AIRCRAFT IS AOG.				1	L	7	2 	4T				A23SO   					 
1997042400018	19970424	00018		1997	4	24	97ZZZX1707       	4	19970401	G	6113	04500401	BULKHEAD        			CESSNA	150   	150G        	2071816	CE  										SPINNER REAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	4044J					15065344				SPINNER BULKHEAD CRACKED.  SUSPECT FROM PUSHING ON SPINNER WHEN MOVING A/C AND OR PUTTING TOO MANY SHIMS ON FORWARD BULK	HEAD; THUS, HAVING TO PUSH TOO HARD TO GET SCREW IN.  SECOND TIME THIS BULKHEAD WAS REPLACED.					1	H	7	1 	3O				3A19    					 
1997042400019	19970424	00019	SO  	1997	4	24	97ZZZX1708       	1	19970324	G	7922	75944	VALVE           			PIPER 	PA32  	PA32R301T   	7103220	SO  										THERMO BYPASS	DEFECTIVE       	B			G9CR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4386B					32R85269001				AT ENGINE OVERHAUL, THE THERMOSTATIC VALVE WAS REMOVED AND FOUND WITH AN EXTREMELY ROUGH SEAT.  THE SPRING WAS ALSO FOUN	D COMING LOOSE.  THE VALVE IS SUSPECT TO LYC SI 1423, BUT WAS NOT A FACTOR BECAUSE THE RETAINING NUT IS OK.					1	L	7	1 	3O				A3SO    					 
1997042400020	19970424	00020	CE  	1997	4	24	97ZZZX1709       	1	19970319	G	5553	04311481	FITTING         			CESSNA	150   	152         	2071835	CE  										V FIN AFT ATTACH	BROKEN          	B			AJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	49169	7660 				15281177				FOUND LEFT, REAR, VERTICAL FIN ATTACH FITTING BROKEN ON OUTBOARD LEG.  THIS MDR IS RELATED TO AN EARLIER MDR REPORT ON A	 BROKEN HORIZONTAL/VERTICAL FIN ATTACH FITTING AND CRACKED SPAR/REINFORCEMENT STRUCTURE.  AIRPLANE IS USED IN A FLIGHT S	CHOOL				1	H	7	1 	3O			NT	3A19    					 
1997042400021	19970424	00021	SO  	1997	4	24	97ZZZX1710       	1	19970402	G	8120		RETAIN RING     			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					TURBO SCAV PUMP	DISLODGED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	54830	3440 				277554128				EXTERNAL RETAINING RING THAT HOLDS THE TURBO SCAVENGE PUMP DRIVEN GEAR IN PLACE DISLODGED ALLOWING GEAR TO DISENGAGE WIT	H SUBSEQUENT PUMP FAILURE.  WITH SCAVENGE PUMP INOPERABLE, OIL WAS FORCED BY TURBO SEAL AT A RAPID RATE AND BURNED IN TH	E EXHAUST UNNOTICED BY PILOT UNTIL TAXIING IN.  MINUTES MORE IN FLIGHT COULD HAVE RESULTED IN IMMINENT ENGINE FAILURE. S	UBMITTER SUSPECT CAUSE WAS FAILURE TO C/W LYC SI NR 1338 DATED 7-2-76, AT ENGINE OVERHAUL WHICH WOULD HAVE REPLACED RETA	INING RING WITH A ROLL PIN.  POTENTIAL CONSEQUENCES OF THIS MALFUNCTION SHOULD HAVE WARRANTED MORE ATTENTION THAN JUST A	 SERVICE INSTRUCTION.	1	L	7	2 	3O	3	O		1A10    	E14EA				 
1997042400022	19970424	00022	GL  	1997	4	24	97ZZZX1711       	3	19970402	G	6114	D4883C55	HUB             			BEECH 	55    	95C55       	1152708	CE  						MCAULY	2AF34C	2AF34C55    	GL  	SOCKET NR 2	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	9313Y				694015	TC9		694015		DURING INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 2.  HUB HAS BEEN SCRAPPED.						1	L	7	2 	3O				3A16    		5	C	P5EA	 
1997042400023	19970424	00023	SO  	1997	4	24	97ZZZX1712       	2	19970404	G	8540	635050A1	ADAPTER GEAR    			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					STARTER	FAILED          	B			UG1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	999VE	1067 				421C0629	272357R			ENGINE FAILED TO START.  INSPECTION REVEALED FAILED STARTER ADAPTER.  REMOVED ADAPTER AND FOUND DRIVE GEAR AND CRANKSHAF	T GEAR DEFECTIVE.  INSPECTION OF OIL FILTER REVEALED METAL CONTAMINATION OF ENGINE OIL SYSTEM.  ENGINE TSOH:  1,067 HOUR	S.  SUBMITTER RECOMMENDS C/W MANUFACTURER'S SB CSB94-4.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997042400025	19970424	00025	SO  	1997	4	24	97ZZZX1713       	1	19970331	G	3230	7642603	LINK ASSY       			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG ASSY	CRACKED         	B	S		UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	47227	5611 				28R7737158				FOUND THE LINK ASSY CRACKED IN RADIUS JUST FORWARD OF THE ATTACH POINT FOR THE DOWNLOCK ASSY.  THIS IS THE SECOND ONE FO	UND IN FLEET.  THE AREA WHERE THE CRACK OCCURRED IS ONE OF THE ITEMS CALLED OUT FOR IN SB 724A, PART II, ITEM NR 3, SKET	CH 3, TO BE CHECKED FOR CRACKING.  SUBMITTER SUGGESTS CHECKING THIS AREA FOR CRACKS EVERY 10 HOURS BY USING DYE PENETRAN	T METHODS.			1	L	7	1 	3O				2A13    					 
1997042400026	19970424	00026	SO  	1997	4	24	97ZZZX1714       	1	19970403	G	3222	4533303	FORK ASSY       			PIPER 	PA31T 	PA31T2      	7103127	SO  										NLG	CRACKED         	B	S		LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	107PC	3831 				31T8166046				DURING A COMBINATION EVENT 1 AND 2 INSPECTION, NOTED THE LEFT SIDE OF THE NLG FORK ASSY WAS CRACKED AT THE LOWER SURFACE	 OF THE AXLE OPENING.  PILOT REPORTED NO HARD LANDINGS.  NO OTHER DAMAGE NOTED.					1	L	7	2 	3T			RT	A8EA    					 
1997042400027	19970424	00027	CE  	1997	4	24	97ZZZX1715       	1	19970301	G	3710	RAIJ47	AIR FILTER      	RAPCO       		BEECH 	33    	F33A        	1151425	CE  										INLINE AIR	MELTED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5530A	26   			02797	CE1342				DURING A ROUTINE INSP OF THE AIRCRAFT, FOUND THE IN-LINE AIR FILTER TO THE SECONDARY PRESSURE SYSTEM HAD BEEN HEATED BY 	THE EXHAUST SYSTEM ON THE LEFT EXHAUST.  THE CLEAR PLASTIC MELTED THEN SHATTERED IN PIECES.  SUBMITTER STATED THIS COULD	 CAUSE SMALL PIECES TO GET INTO THE INSTRUMENT AIR SYSTEM.  AIRBORNE PRODUCTS MAKES AN IN-LINE AIR FILTER MADE OUT OF A 	METAL CANISTER.  THIS FILTER WAS USED PREVIOUSLY ON THE AIRCRAFT WITHOUT HAVING ANY DISCREPANCIES.			1	L	7	1 	3O				3A15    					 
1997042400028	19970424	00028	NE  	1997	4	24	97ZZZX1716       	2	19970327	G	7230	745704	C4 DISK         								PWA   	JT8   	JT8D1       	52044	NE  					WINDAGE TAB	CORRODED        	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		25321			K52635					C4 DISK WAS RETURNED DUE TO CORROSION.  DISK WAS RECEIVED  WITH 3 BROKEN AND 6 BENT WINDAGE TABS.  PER ENGINE MANUAL 481	672 SECTION 72-33-35, INSP 01. THIS PART IS SCRAP.  PART WAS TAGGED SCRAP AND RETURNED.										4	F			E2EA				 
1997042400029	19970424	00029	SO  	1997	4	24	97ZZZX1717       	1	19970404	G	3230	1742001	DRAG LINK       			PIPER 	PA23  	PA23250     	7102308	SO  										MLG FITTING	CRACKED         	B		A	HEWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405MC	4122 				277405314				DURING AN ANNUAL INSPECTION, CRACKS WERE FOUND ON THE MLG DRAG LINK FITTING SUPPORT TUBE ASSEMBLIES LOCATED ON THE RT IN	BD P/N 17420-01, RT OTBD, P/N 17420-02, AND LT OTBD P/N 17420-03 AFT MOUNTING BOLT HOLES.  TWO TUBE ASSEMBLIES REQUIRED 	REPLACEMENT AND ONE WAS REPAIRABLE.  SUBMITTER SPECULATED THAT THE AFT MOUNTING BOLTS WERE NOT CHECKED FOR TORQUE DURING	 INSPECTIONS.			1	L	7	2 	3O				1A10    					 
1997042400030	19970424	00030	SO  	1997	4	24	97ZZZX1718       	1	19970404	G	3230	1742002	DRAG LINK       			PIPER 	PA23  	PA23250     	7102308	SO  										MLG FITTING	CRACKED         	B		A	HEWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405MC	4122 				277405314				DURING AN ANNUAL INSPECTION, CRACKS WERE FOUND ON THE MLG DRAG LINK FITTING SUPPORT TUBE ASSEMBLIES LOCATED ON THE RT IN	BD P/N 17420-01, RT OTBD, P/N 17420-02, AND LT OTBD P/N 17420-03 AFT MOUNTING BOLT HOLES.  TWO TUBE ASSEMBLIES REQUIRED 	REPLACEMENT AND ONE WAS REPAIRABLE.  SUBMITTER SPECULATED THAT THE AFT MOUNTING BOLTS WERE NOT CHECKED FOR TORQUE DURING	 INSPECTIONS.			1	L	7	2 	3O				1A10    					 
1997042400031	19970424	00031	SO  	1997	4	24	97ZZZX1719       	1	19970404	G	3230	1742003	DRAG LINK       			PIPER 	PA23  	PA23250     	7102308	SO  										MLG FITTING	CRACKED         	B		A	HEWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405MC	4122 				277405314				DURING AN ANNUAL INSPECTION, CRACKS WERE FOUND ON THE MLG DRAG LINK FITTING SUPPORT TUBE ASSEMBLIES LOCATED ON THE RT IN	BD P/N 17420-01, RT OTBD, P/N 17420-02, AND LT OTBD P/N 17420-03 AFT MOUNTING BOLT HOLES.  TWO TUBE ASSEMBLIES REQUIRED 	REPLACEMENT AND ONE WAS REPAIRABLE.  SUBMITTER SPECULATED THAT THE AFT MOUNTING BOLTS WERE NOT CHECKED FOR TORQUE DURING	 INSPECTIONS.			1	L	7	2 	3O				1A10    					 
1997042400032	19970424	00032	GL  	1997	4	24	97ZZZX1720       	3	19970401	G	6111	A14966	PILOT TUBE      													HARTZL	HCA2V	HCA2VK2     	GL  	HUB	CRACKED         	B			LU4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17										NEW PILOT TUBE NEVER INSTALLED.  HAD RELEVANT INDICATION FROM MAG PARTICLE TESTING APPROXIMATELY 2.5 INCHES RUNNING APPR	OXIMATELY 15 DEGREES OF THE CENTERLINE OF THE PILOT TUBE.															5	C	P24EA	 
1997042400033	19970424	00033	GL  	1997	4	24	97ZZZX1721       	1	19970325	G	2720		HORN            			AMTR  	SKYBLT	SKYBOLT     		GL  										RUDDER	BROKEN WELDS    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		420  								THE WELDS ATTACHING THE RUDDER HORN TO THE RUDDER VERTICAL POST BROKE CAUSING AN IN-FLIGHT LOSS OF RUDDER CONTROL.  ONLY	 ONE TAC WELD EXISTED AROUND THE VERTICAL TUBE.  THIS FAILURE CAUSED BY INSUFFICIENT WELD AREA AROUND THE VERTICAL RUDDE	R POST.  THIS AREA IS COVERED WITH FABRIC AND IMPOSSIBLE TO INSPECT.  WELDS APPEAR TO HAVE FAILED OVER A LONG PERIOD OF 	TIME.  (SOME RUST FOUND IN BROKEN WELD AREA.)  THE AIRCRAFT WAS LANDED WITHOUT FURTHER DAMAGE USING BRAKES FOR DIRECTION	AL CONTROL ON GROUND.		1	Q	7	1 	3O				EXPA1Q71					 
1997042400034	19970424	00034	SW  	1997	4	24	97ZZZX1722       	1	19970204	G	3340	A402A	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER AFT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										N NR 521FB THROUGH N NR 527FB.  P/N A402A 'R AND R/N' STROBE LENS, APPROXIMATELY 60 LENS COVERS HAVE BROKEN OR CRACKED O	N OUR HELICOPTERS.  DIFFERENT DESIGNS HAVE BEEN TRIED.  SAME RESULTS.  MOST BREAKAGE IS ON LOWER AFT STROBE.					1	G	7	1 	3U			NC	H3WE    					 
1997042400035	19970424	00035	SW  	1997	4	24	97ZZZX1723       	1	19970204	G	3340	7052101	LIGHT           			HUGHES	500N  	500N        	3027374	SW  										UPPER AFT	FAIL            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										N NR 521FB  THROUGH N NR 527FB.  P/N 70521-01.  APPROXIMATELY 30 UNITS HAVE GONE BAD IN THE A996 SEASON.  ALMOST ALL HAV	E LESS THAN 500 HOURS ON THEM.  MOST OF THE TIME IT IS THE UPPER AFT LOCATION.					1	G	7	1 	3U			NC	H3WE    					 
1997042400036	19970424	00036	SW  	1997	4	24	97ZZZX1724       	1	19970318	G	3340	A402ARN	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	526FB	8    				LN006				NEW LENS FROM WHELEN.  FAILED BY CRACKING IN HALF AT SEAM.  PARTS FOUND ON 100 HOUR INSPECTION .  ALL 3 PIECES AT SHOP F	OR INSPECTION.					1	G	7	1 	3U			NC	H3WE    					 
1997042400037	19970424	00037	SW  	1997	4	24	97ZZZX1725       	1	19970327	G	3340		LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER STROBE	SEAM CRACKED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	6    				LN004				LOWER STROBE LENS SEAM CRACKED.  FOUND ON PRE-FLIGHT.  PART SENT TO WHELEN.						1	G	7	1 	3U			NC	H3WE    					 
1997042400038	19970424	00038	SW  	1997	4	24	97ZZZX1726       	1	19970317	G	3340	A402ARN	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER AFT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	21   				LN004				LENS CRACKED RADIALLY .50 INCH - 1 INCH FROM TOP OR BOTTOM.  NEW CLAMP WORKS GOOD.  LENS IS NEW STYLE FROM WHELEN.  PART	 SENT TO WHELEN.					1	G	7	1 	3U			NC	H3WE    					 
1997042400039	19970424	00039	SW  	1997	4	24	97ZZZX1727       	1	19970327	G	3340		LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER AFT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	525FB	31   				LN005				LOWER AFT LENS CRACKED ON SEAM.  ALSO, STAR CRACK ON FWD LIP.  PART SENT TO WHELEN.						1	G	7	1 	3U			NC	H3WE    					 
1997042400040	19970424	00040	SW  	1997	4	24	97ZZZX1728       	1	19970204	G	3340	A470DRSU	LIGHT           	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										UPPER TAIL	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	205  				LN001				P/N 70521-01.  STROBE GOES INTO 'GLOW' SELF-IONIZATION.  PART CAUSES STROBES TO STOP OPERATION.  SUBMITTER STATED MAY CA	USE HAZARD DURING NIGHT OPERATION.					1	G	7	1 	3U			NC	H3WE    					 
1997042400041	19970424	00041	SW  	1997	4	24	97ZZZX1729       	1	19970204	G	3340	A470DRSU	LIGHT           	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										UPPER TAIL	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	527FB	165  				LN007				STOBE ASSY GOES INTO 'GLOW' SELF-IONIZATION.  PART CAUSES STROBES TO STOP OPERATION.  SUBMITTER STATED CAN CAUSE HAZARD 	WHEN FLYING AT NIGHT.  P/N 70521-01.					1	G	7	1 	3U			NC	H3WE    					 
1997042400042	19970424	00042	SW  	1997	4	24	97ZZZX1730       	1	19970207	G	3340	A470DRSU	LIGHT           			HUGHES	500N  	500N        	3027374	SW  										LOWER TAIL AFT	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	527FB	165  				LN007				STROBE LIGHT GOES INTO 'GLOW' SELF-IONIZATION.  PART CAUSES STROBES TO STOP OPERATION.  MAY CAUSE HAZARD DURING NIGHT FL	IGHT.  P/N 70521-01.					1	G	7	1 	3U			NC	H3WE    					 
1997042400043	19970424	00043	SW  	1997	4	24	97ZZZX1731       	1	19970328	G	3340		LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER AFT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	526FB	24   				LN006				LENS CRACKED ALONG SEAM.  FOUND ON MORNING WALK-AROUND.  PART SENT TO WHELEN.						1	G	7	1 	3U			NC	H3WE    					 
1997042400044	19970424	00044	SW  	1997	4	24	97ZZZX1732       	1	19970402	G	3340		LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER STOBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	45   				LN004				LOWER AFT STROBE LENS FAILED BY CRACKING ALONG SEAM OF LENS.  FOUND ON MORNING WALK-AROUND.  PART SENT TO WHELEN.						1	G	7	1 	3U			NC	H3WE    					 
1997042400045	19970424	00045	SW  	1997	4	24	97ZZZX1733       	1	19970328	G	3340		LENS            			HUGHES	500N  	500N        	3027374	SW  										STROBE LIGHT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	7    				LN001				LOWER AFT LENSE CRACKED.  NEW STYLE, AND NEW STYLE PLASTIC CLAMP.  LENS SENT TO WHELEN.						1	G	7	1 	3U			NC	H3WE    					 
1997042400277	19970424	00277	NM  	1997	4	24	97ZZZX1734       	1	19970301	G	5320		STIFFENER       			BOEING	727   	7272J4      	1384006	NM  										NLG BOX BS 312	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2FOR					20764				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON TOP NOSE GEARBOX HORIZONTAL STIFFENER AT STA 312 (AS VIEWED FR	OM THE E/E BAY).					2	L	7	3 	4F			RT	A3WE    					 
1997042400278	19970424	00278	NM  	1997	4	24	97ZZZX1735       	1	19970301	G	5320		STIFFENER       			BOEING	727   	7272J4      	1384006	NM  										NLG BOX HORIZ	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2FOR					20764				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON TOP NOSE GEARBOX HORIZONTAL SITFFENER, FROM END TO END, AT STA	 294.5 (AS VIEW FROMT HE E/E BAY).					2	L	7	3 	4F			RT	A3WE    					 
1997042400279	19970424	00279	NM  	1997	4	24	97ZZZX1736       	1	19970328	G	5311		FRAME           			BOEING	727   	7272J4      	1384006	NM  										FR 950A S19L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2FOR					20764				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS  FOUND ON FUSELAGE FRAME 950A BETWEEN S19L AND S20L.						2	L	7	3 	4F			RT	A3WE    					 
1997042400280	19970424	00280	NM  	1997	4	24	97ZZZX1737       	1	19970301	G	5711		SPAR CAP        			BOEING	727   	7272J4      	1384006	NM  										RT WS 560	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2FOR					20764				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON LOWER FWD SPAR CAP AT RT WING STA 560 AT ATTACH POINT FOR LOWE	R LEADING EDGE ACCESS PANEL.  APPARENTLY CAUSED BY INADEQUATE PREVENTIVE TREATMENT.					2	L	7	3 	4F			RT	A3WE    					 
1997042400281	19970424	00281	NM  	1997	4	24	97ZZZX1738       	1	19970301	G	5313		STRINGER        			BOEING	727   	7272J4      	1384006	NM  										BS 277 S33L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2FOR					20764				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S23L FROM STA 277 TO STA 294.5.						2	L	7	3 	4F			RT	A3WE    					 
1997042400282	19970424	00282	WP  	1997	4	24	97ZZZX1739       	2	19970328	G	7210		ENGINE          			GULSTM	690TP 	695         	7630518	SW  	GARRTT	TPE331	TPE33110    	01514	WP  					GEARBOX	FAILED          	D				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	23	3U	3451 	17   			95041	P38096			LEFT ENGINE SHUT DOWN IN-FLIGHT DUE TORQUE PRESSURE DROP (40 PSI).  SPEED INCREASE TO 103+ .  ON INSPECTION, NO OUTWARD 	SIGN OF DAMAGE, BUT COULD NOT ROTATE PROPELLER.  ENGINE OIL FILTER REMOVED, METAL IN FILTER.  METAL ON CHIP DETECTOR (NO	 LIGHT).  OIL BLACK AND MILKEY.  S.O.A.P. OBTAINED.  SUSPECT GEARBOX PROBLEM.  ENGINE REMOVED AND SHIPPED TO REPAIR AGEN	T FOR INVESTIGATION.			1	H	7	2 	3T	4	T		2A4     	E4WE				 
1997042400284	19970424	00284	WP  	1997	4	24	97ZZZX1741       	1	19970401	G	5753	5614374503	FITTING         			DOUG  	DC8   	DC8F54      	3021926	WP  										LT FLAP STA 20	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	56FA					45663				TAT:  66,105:12 HOURS.  TAC:  23,119.  DURING ROUTINE MAINTENANCE, FOUND A 2 INCH CRACK ON LEFT WING FLAP FITTING STA 22	0, INBOARD SIDE.  REMOVED AND REPLACED FLAP SUPPORT FITTING IAW DOUGLAS MM CHAP 27-27-7 AND ACCOMPLISHED FLAP RIG CHECK 	IAW CHAP 27-30-0.				2	L	7	4 	4F				4A25    					 
1997042400285	19970424	00285	WP  	1997	4	24	97ZZZX1742       	1	19970331	G	5751	NRC60411K	AILERON         			DOUG  	DC10  	DC1010      	3022110	WP  										WING RT OTBD	DEBONDED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1837U					47969				DURING ROUTINE C-CHECK, FOUND RT OTBD AILERON DISBONDED FROM INTERNAL DOUBLER.  REPLACED BOTH LOWER SKINS.						2	L	7	3 	4F				A22WE   					 
1997042400286	19970424	00286	WP  	1997	4	24	97ZZZX1743       	1	19970327	G	5751	NRC6041502	AILERON         			DOUG  	DC10  	DC1010      	3022110	WP  										STA XRS 885	DEBONDED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1816U					46615				DURING ROUTINE C-CHECK, RT OTBD AILERON LOWER SKIN WAS FOUND BULGED IN SEVERAL AREAS STA XRS 885 TO XRS 1013.  LOWER SKI	N REMOVED AND FOUND DISBONDED FROM INTERNAL DOUBLER.   FABRICATED NEW SKIN AND INSTALLED IAW UAL GN/MM1-0-8-2.  A/C TOTA	L TIME:  67,314.55 HOURS.  A/C TOTAL CYCLES, 26,462.				2	L	7	3 	4F				A22WE   					 
1997042400287	19970424	00287	WP  	1997	4	24	97ZZZX1744       	1	19970327	G	5751	NRC6041502L	AILERON         			DOUG  	DC10  	DC1010      	3022110	WP  										STA XRS 1013	DISBONDED       	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1830U				MAC213	46629				DURING ROUTINE C-CHECK, RT OTBD AILERON LOWER SKIN WAS FOUND BULGED IN SEVERAL PLACES STA XRS 1013 TO SRX 1042.  LOWER S	KIN REMOVED AND FOUND DISBONDED WITH INTERNAL DOUBLER.  FABRICATED NEW SKIN AND INSTALLED IAW UAL GN/MM 1-9-8-2.  A/C TO	TAL TIME:  60,225.58 HOURS.  A/C TOTAL CYCLES, 24,014.				2	L	7	3 	4F				A22WE   					 
1997042400288	19970424	00288	EA  	1997	4	24	97ZZZX1745       	2	19970408	G	7314	02532330003	PUMP            	PESCO       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENG FUEL	SHAFT FAILED    	D				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			GL	23	942CE				7476	BB494	PCE817782			ENGINE WENT TO IDLE CUT OFF IN-FLIGHT.  (FLAME OUT.)  MAIN ENGINE PUMP SEIZED.  ENGINE SHAFT BECAME WORN AND ROUNDED OFF	 SPLINES.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997042400289	19970424	00289	SW  	1997	4	24	97ZZZX1746       	1	19970328	G	2434		CLAMP           			SWRNGN	SA227 	SA227AT     	8780610	SW  										GENERATOR	BROKEN          	D				E				ENGINE SHUTDOWN         				N	A		FALSE WARNING             	FLAME/FIRE                		TX	TAXI/GRND HDL  	1			WP	23	9UA					AT495				ENGINE SHUT DOWN BY CREW (RT) DUE FIRE WARNING AND FLAME FROM JET PIPE.  CREW ON TRAINING/CHK RIDE.  A/C TAXI.  ENG INSP	 NIL DAMAGE OBSERVED.  BROKEN CLAMP NOTICED ON GENERATOR.  THIS CLAMP SECURES FIRE THERMAL S/W AT FWD RT POSITION.  S/W 	P/N 17343-61-350F.  SUSPECT S/W HAD 'SHORTED' AGAINST GENERATOR CLAMP CAUSING FIRE LIGHT TO COME ON.  S/W SECURED.  FIRE	 EXT RE-CHARGED.  GROUND RUNS CHK GOOD.  SUSPECT FLAME CAUSED BY REMAINING FUEL AFTER SHUT DOWN AND HOT ENGINE.			2	L	7	2 	4T			RT	A5SW    					 
1997042400290	19970424	00290	CE  	1997	4	24	97ZZZX1747       	3	19970324	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		5543 	919  							FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF TWO PITCH PIN ENGAGEMENT SLOTS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997042400291	19970424	00291	CE  	1997	4	24	97ZZZX1748       	3	19970326	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		3568 			2790NR					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	 
1997042400292	19970424	00292	CE  	1997	4	24	97ZZZX1749       	3	19970321	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		12310	4556 							FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF ONE PITCH PIN ENGAGEMENT SLOT.  PART SENT TO HARTZELL FOR 	EVALUATION.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997042400293	19970424	00293	CE  	1997	4	24	97ZZZX1750       	1	19970129	G	3260	840508	SWITCH          			RKWELL	NA265 	NA26565     	7630107	CE  										LT MLG UPLOCK	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	03	2N					46563				ON 1-29-97, PILOT REPORTED RED FLASHING LIGHT IN GEAR HANDLE WITH HYDRAULIC PUMP RUN LIGHT.  LANDING GEAR SEEMED TO RETR	ACT OR TRY TO AFTER IT WAS RAISED.  AFTER RETURN TO MDW, JACKED AIRCRAFT AND FUNCTIONAL CHECKED.  LANDING GEAR CHECKED N	ORMAL.  AFTER 2 HOURS ON JACKS, A/C DUPLICATED ORIGINAL PROBLEM.  TROUBLESHOT FAULT TO LT MLG UPLOCK SWITCH.  REPLACED A	ND RETURNED TO SERVICE.			2	L	7	2 	4J				A2WE    					 
1997042400294	19970424	00294		1997	4	24	97ZZZX1751       	4	19970127	G	2312	686804	CONTROL HEAD    	GABLES      		BRAERO	DH125 	BAE125800A  	1500285	EU  										NR 1 COMM	DIODE BURNED    	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			GL	05	8186	1596 			57	258186				AFTER TAKEOFF, THE COCKPIT BEGAN TO FILL WITH SMOKE.  THE AIRCRAFT WAS RETURNED TO THE DEPARTURE AIRPORT WITH NO DAMAGE 	TO THE AIRCRAFT.  THE CAUSE OF THE SMOKE WAS DETERMINED TO BE THE NR 1 COMM. RADIO HEAD, PC BOARD, P/N 701-314-01, REV 3	, WAS FOUND WITH 9 BURNED DIODES.				2	L	7	2 	4F			RT	A3EU    					 
1997042400295	19970424	00295	CE  	1997	4	24	97ZZZX1752       	1	19970401	G	3610	45AA0304001	DUCT            			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR DUCT	RUPTURED        	B			BUER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	80KM	2354 				RK50				FOUND ENGINE BLEED AIR LINE STAINLESS STEEL OUTER BRAIDING AND BELLOWS ASSEMBLY RUPTURED NEAR NACELLE CONNECTION.						2	H	7	2 	4F			RT	A16SW   					 
1997042400296	19970424	00296	WP  	1997	4	24	97ZZZX1753       	1	19970314	G	5751	NRC60411K	AILERON         			DOUG  	DC10  	DC1010      	3022110	WP  										LT WS XORS 855	DELAMINATED     	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	1812U				MAC38	46611				LEFT WING OUTBOARD AILERON HAS DELAMINATION.  REMOVED AND REPLACED DAMAGED SKIN IAW UNITED AIRLINES GN/MM 1-0-8-2.  ACFT	 TT:  69,132.00 HOURS.  ACFT TOTAL CYCLES:  27,585.  ACFT TSO:  13,720.39 HOURS.  ACFT CYCLES SINCE OVERHAUL:  5,698.					2	L	7	3 	4F				A22WE   					 
1997042400297	19970424	00297	CE  	1997	4	24	97ZZZX1754       	1	19970301	G	5230		CARGO DOOR      			BEECH 	200   	B200        	1152922	CE  										SUPPORT	MISMODIFIED     	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	3258P					BB1526				AFT CARGO DOOR MOD/INSTALLATION PERFORMED ON ACFT IS UNAIRWORTHY.  E.M.S. MODIFICATIONS WERE BEING DONE WHEN PROBLEMS IN	 THE DOOR AND ADDED STRUCTURE WAS NOTICED.  AN UNBUCKED RIVET, DRILLED HOLES NOT FILLED WITH RIVETS, AND OVER BUCKED RIV	ETS IN ADDED FORMER FOR CARGO DOOR SUPPORT.  METAL SHAVINGS AND LOOSE RIVETS WERE FOUND UNDER FLOOR PANEL LYING ON AND C	LOSE TO PULLEYS.  FLIGHT TRIM CONTROL CABLES TOUCHING FORMER IN TWO PLACES OF NEW SUPPORT INSTALL.  STRINGERS TOUCHING S	UPPORTS IN FLOOR OF AIRCRAFT.		1	L	7	2 	4T				A24CE   					 
1997042400298	19970424	00298	SO  	1997	4	24	97ZZZX1755       	1	19970310	G	2121	X702278A	FAN             			LKHEED	188   	188C        	5262604	SO  										BEARING	FAILED          	B			FF3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27					AA57871					DURING OVERHAUL, UNAPPROVED BEARINGS WERE INSTALLED CAUSING PREMATURE FAILURE.  BEARING, P/N 377416-5, REPLACED WITH P/N	 60042ZJ, BEARING P/N 377416-6, REPLACED WITH P/N 77200.					2	L	7	4 	4T				4A22    					 
1997042400301	19970424	00301	CE  	1997	4	24	97ZZZX1758       	1	19970404	G	7810	1019500191	EXHAUST         			BEECH 	200   	200BEECH    	1152920	CE  										EXHAUST FLANGE	CRACKED         	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	30XY	356  				BB305				STACK CRACKED AT FLANGE APPROXIMATELY 6 INCHES IN LENGTH.  DEFECT FOUND ON PRE-FLIGHT INSPECTION.  SUBMITTER SUGGESTS EN	GINE EXHAUST STACKS BE LOOKED AT CLOSELY ON POST-FLIGHT INSPECTIONS.  NEW EXHAUST STACKS P/N 101-950022-1 SEEM TO HOLD U	P BETTER BECAUSE OF REINFORCEMENTS INSTALLED DURING MANUFACTURE.				1	L	7	2 	4T				A24CE   					 
1997042400303	19970424	00303	NE  	1997	4	24	97ZZZX1760       	2	19970219	G	7240		LINER           			CESSNA	501   	501         	2076603	CE  	PWA   	JT15  	JT15D1      	52060	NE  					ENGINE COMB	BURNED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	25	501AF	6024 	2522 			500139	79128			PILOT REPORTED TEMP SPLIT BETWEEN ENGINES.  MECHANIC PERFORMED GROUND PERFORMANCE RUN AND NOTED THE RIGHT ENGINE'S OUTPU	T LOW.  A BORESCOPE INSPECTION OF ENGINE HOT SECTION THROUGH THE INBD IGNITER HOLE WAS MADE AND FOUND THE COMBUSTION LIN	ER BURNED AT THE OTBD IGNITER HOLE BY THE IGNITER.  THE ENGINE HOT SECTION WAS REMOVED AND ALL COMPONENTS SENT TO P&WC F	OR INSPECTION AND REPAIR.			1	L	7	2 	4F	4	F		A27CE   	E1NE				 
1997042400329	19970424	00329	GL  	1997	4	24	97ZZZX1786       	2	19970318	G	7260	6889094	GEAR            		6894171     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	TEETH PITTED    	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8639F				UPI341	1280431D	CAE832846			FOUND PTTING AND NICKS ON TEETH OF AIR OIL SEPARATOR GEAR.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997042400814	19970424	00814	SO  	1997	4	24	97ZZZX1818       	1	19970224	G	2434		BRUSH           	BENDIX      	30E20111B   	GULSTM	G1159 	G1159       	3953505	SO  										DC GENERATOR	WORN            	B			BQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	900DH		15   		1280	111				BLACK STREAKS WERE NOTICED ON THE ENGINE COWLING BY MAINTENANCE PERSONNEL.  FOUND THE DC GENERATOR TO HAVE PREMATURE BRU	SH WEAR, WORN BEYOND LIMITS (NO WEAR MARK REMAINING - 100 PERCENT WORN).					2	L	7	2 	4F			RT	A12EA   					 
1997042400816	19970424	00816	EU  	1997	4	24	97ZZZX1819       	1	19970123	G	4930	25VF3627	FUEL  HOSE      	DUNLOP      	FLEXIMET    	BRAERO	DH125 	BAE125800A  	1500285	EU  										APU	FAILED          	B	S		COZR	H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	415PT	2471 				258016				DURING TROUBLESHOOTING IN THE TAIL COMPARTMENT, THE FUEL LINE SUPPLY HOSE FOR THE GARRETT 30-92 APU STARTED SPRAYING FUE	L.  THERE WAS ENOUGH FUEL COMING FROM THE LINE THAT THE TECHNICIAN'S CLOTHES WERE SOAKED.  THE LINE THAT FAILED WAS A PR	EMOD 253141B (THIS MOD INTRODUCES AN ALTERNATE HIGH PRESSURE HOSE).  SEE HAWKER IPC 49-10-05-05, ITEM 255.				2	L	7	2 	4F			RT	A3EU    					 
1997042400869	19970424	00869	SO  	1997	4	24	97ZZZX1820       	1	19970328	G	3242	755950	SNAP RING       		6335300     	PIPER 	PA28  	PA28140     	7102802	SO  										HAND BRAKE CYL	DISLODGED       	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	5926U	3900 				2826739				ON 2 OUT OF 15 LAST PRE-FLIGHTS, FOUND BRAKE RESERVOIR EMPTY.  REFILLED AND LEVEL STAYED UP FOR 6 FLIGHTS, THEN WENT TOT	ALLY EMPTY ON NEXT FLIGHT.  DISCOVERED HAND BRAKE ACTUATING CYLINDER (PIPER P/N 63353-00/CLEVELAND 10-22) HAD DISLODGED 	ITS SNAP RING (P/N 755 950); THUS, CAUSING SHAFT AND INNER PISTON TO EXIT CYLINDER ANYTIME HAND BRAKE HANDLE WAS PUSHED 	FORWARD.  THIS, IN TURN, WOULD 'QUICK' DUMP ALL RESERVOIR FLUID OUT THROUGH ACTUATOR END AND DIRECTLY DOWN CONTROL COLUM	N OPENING IN CONSOLE.		1	L	7	1 	3O				2A13    					 
1997042400870	19970424	00870	SO  	1997	4	24	97ZZZX1821       	2	19970404	G	8550	653491	FILTER ADAPTER  			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					ENGINE OIL	PLUG LOOSE      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	8294M	239  				E2761	296844R			WHEN THE OIL FILTER WAS REMOVED DURING AN ENGINE INSPECTION, DISCOVERED A PLUG THAT WAS PRESSED INTO AN UNUSED OIL PASSA	GE IN THE OIL FILTER ADAPTER HAD COME LOOSE.  THIS ALLOWED THE OIL FILTER TO BE BYPASSED AND FOR UNFILTERED OIL TO BE PU	MPED IN THE OIL SYSTEM.  THIS WAS A FACTORY REBUILT ENGINE WITH 239 HRS SINCE INSTALL.  IT IS RECOMMENDED THE OIL FILTER	 ADAPTERS THAT HAVE THIS FEATURE BE INSPECTED TO CONFIRM THE SECURITY OF THE BLOCK-OFF PLUG INSTALLATION.			1	L	7	1 	3O	3	O		3A15    	E3SO				 
1997042400871	19970424	00871	CE  	1997	4	24	97ZZZX1822       	1	19970314	G	3213	05430181	CAP             			CESSNA	172   	172F        	2072414	CE  										NLG STRUT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	8484U	1986 				17252384				DURING ANNUAL INSPECTION, FOUND LOWER NOSE GEAR STRUT SECURING CAP CRACKED IN HALF AT RT ATTACH POINT.  SUSPECT CAUSE IG	NORING NOSE GEAR SHIMMY PROBLEMS/LOOSE TORQUE LINKS, AND NOT SERVICING DAMPENER AT SPECIFIED INTERVALS.  SUBMITTER STATE	D ADDRESS SHIMMY PROBLEMS ASAP AND FOLLOW MFG RECOMMENDED SERVICING INTERVALS AND PAY CLOSE ATTENTION TO SECURING POINTS	 DURING CORRECTION.			1	H	7	1 	3O			NT	3A12    					 
1997042400874	19970424	00874	EA  	1997	4	24	97ZZZX1825       	2	19970407	G	8530	AEL12949	VALVE           		75137CN     	HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					NR 2 CYLINDER	FAILED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	36MV	167  			06	5060	L256043			THE HELICOPTER WAS RUNNING ROUGH SO A COMPRESSION CHECK WAS RUN.  THE NR 2 CYLINDER HELD NO COMPRESSION AND WAS REMOVED 	FOR INSPECTION.  NOTED A .1250 INCH BY .25 INCH SECTION OF THE VALVE FACE WAS MISSING.  THE MISSING SECTION WAS IRREGULA	R IN SHAPE AND APPEARED TO HAVE  MANUFACTURING VOIDS WITHIN THE BASE METAL.  SMALL CRATER LIKE HOLES WERE FOUND ALONG TH	E EDGE OF THE BROKEN SECTION.  THE VALVE STEM SHOWED HIGH WEAR ADJACENT TO THE VALVE KEEPERS UNDER THE HAT SECTION AT TH	E TOP OF THE VALVE.  IT APPEARED AS THOUGH THE VALVE WAS MANUFACTURED WITH SOFT MATERIAL.		1	G	7	1 	3O	3	O		4H11    	E304				 
1997042400875	19970424	00875	SO  	1997	4	24	97ZZZX1826       	2	19970206	G	8540	631871	CRANK GEAR      			CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					CRANKSHAFT	SCREWS LOOSE    	B	L		CY4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	4584L					4210784	21015370H			UPON ENGINE DISASSEMBLY  FOUND ALL 6 CRANK GEAR RETAINING SCREWS 'GANG WIRED'.  IN ADDITION TO NOT BEING LOCK WIRED CORR	ECTLY, THE CRANK GEAR SCREWS WERE ALL LOOSE.  SEE TELEDYNE CONTINENTAL MOTORS SIL 93-15 FOR CORRECT USE OF SAFETY WIRE, 	KEYS, AND LOCK TABS.  FURTHER INSP REVEALED THE STARTER SHAFT NEEDLE BEARING, P/N 537721 (SEE GTSIO-520 PARTS BOOK NR X3	0046A, FIG 1, ITEM NR 3), WAS MISSING AND APPEARED THAT IT WAS NEVER RE-INSTALLED AT OVERHAUL, DATED 7-20-95.  ALSO, LOG	 ENTRIES OF 2-16-96, TSO NOT NOTED, REVEALED CONTINUAL REPORTS OF STARTER/STARTER DRIVE SEAL LEAKS AND REPAIR WHICH IN '	HINDSIGHT' ARE UNDERSTANDABLE KNOWING STARTER DRIVE WAS NOT PROPERLY SUPPORTED ON THE LOWER OF 'CRANKCASE END' OF THE SH	1	L	7	2 	3O	3	O	RT	A7CE    	E7CE				 
1997042400876	19970424	00876	CE  	1997	4	24	97ZZZX1827       	1	19970206	G	2410		GEAR            		976J4171    	CESSNA	421   	421         	2076010	CE  										ALTERNATOR DRIVE	DETACHED        	B	L		CY4R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AL	03	4584L				A5990179	4210184				PILOT LOST POWER FROM THE ALTERNATOR.  UPON INVESTIGATING THE PROBLEM, DISCOVERED THE ALTERNATOR DRIVE GEAR HAD FALLEN O	FF THE ALTERNATOR, INSIDE THE ENGINE, CAUSING SUBSTANTIAL DAMAGE IN THE FORWARD RIGHT-HAND HALF OF THE CRANKCASE.  UPON 	DISASSEMBLY OF THE ENGINE, THE CAMSHAFT CLUSTER GEARS, P/N 537432 AND P/N 535662, WERE FOUND LOOSE.  THE CAMSHAFT GEAR R	ETAINING SCREWS WERE 'FINGER LOOSE', BUT LOCK WIRED.  THE ALTERNATOR HAD APPROXIMATELY 130 HOURS SINCE OVERHAUL, BUT THE	 ENGINE LOG IS UNCLEAR AS TO THE ACTUAL INSTALLMENT DATE.  THE ENGINE HAS APPROXIMATELY 150 HOURS SINCE MAJOR OVERHAUL A	ND APPROXIMATELY 43.5 HOURS SINCE A COMPLETE DISASSEMBLY AND REASSEMBLY.	1	L	7	2 	3O			RT	A7CE    					 
1997042400878	19970424	00878	EU  	1997	4	24	97ZZZX1828       	1	19970408	G	7810	LW14004	EXHAUST         			PARTEN	P68   	P68TCOBS    	6780108	EU  										NR 4 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737	132  				40004OTC				FOUND EXHAUST SYSTEM DEFORMED AND CRACKED ALONG WELDS WITH ONLY 132.1 HOURS ON NEW EXHAUST.  SLIP JOINTS NOT ALLOWING EX	HAUST TO MOVE PROPERLY.					1	H	7	2 	30				A31EU   					 
1997042400879	19970424	00879	EU  	1997	4	24	97ZZZX1829       	1	19970408	G	7810	LW14001	EXHAUST         			PARTEN	P68   	P68TCOBS    	6780108	EU  										NR 1 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737	275  				40004OTC				FOUND EXHAUST SYSTEM DEFORMED AND CRACKED ALONG WELDS WITH ONLY 275.1 HOURS ON NEW EXHAUST.						1	H	7	2 	30				A31EU   					 
1997042400880	19970424	00880	EU  	1997	4	24	97ZZZX1830       	1	19970408	G	7810	LW14002	EXHAUST         			PARTEN	P68   	P68TCOBS    	6780108	EU  										NR 2 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737	132  				40004OTC				FOUND EXHAUST SYSTEM DEFORMED AND CRACKED ALONG WELDS WITH ONLY 132.1 HOURS ON NEW EXHAUST.						1	H	7	2 	30				A31EU   					 
1997042400881	19970424	00881	EU  	1997	4	24	97ZZZX1831       	1	19970408	G	7810	LW15689	EXHAUST         			PARTEN	P68   	P68TCOBS    	6780108	EU  										NR 3 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737	275  				40004OTC				FOUND EXHAUST SYSTEM DEFORMED AND CRACKED ALONG WELDS WITH ONLY 275.1 HOURS ON NEW EXHAUST.						1	H	7	2 	30				A31EU   					 
1997042400882	19970424	00882	GL  	1997	4	24	97ZZZX1832       	3	19970402	G	6114	D6097C30	HUB             													MCAULY	2A34C	D2AF34C30   	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					701309			701309		DURING INSPECTION, HUB FOUND CRACKED IN BLADE SOCKET NR 2.  HUB HAS BEEN SCRAPPED.																5	C	P5EA	 
1997042400883	19970424	00883	GL  	1997	4	24	97ZZZX1833       	3	19970416	G	6111	C52702	BEARING         													MCAULY	2A34C	2A34C201    	GL  	BLADE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								739671		UPON DISASSEMBLY, FOUND BLADE BUTT HAD SMALL SCRATCHES THAT CAUSED THE PROPELLER TO LEAK.  APPARENTLY CAUSED BY SHARP ED	GES ON OUTER BEARING INNER RADIUS.															5	C	P3EA	 
1997042400884	19970424	00884	EA  	1997	4	24	97ZZZX1834       	2	19970401	G	7414	M3548	ROTOR SHAFT     	SLICK       	4370        	CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  					MAGNETO	BROKEN          	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5361K		260  		94100187	74080	L3350536A			MAGNETO ROTOR SHAFT SHEARED .25 INCH BELOW CAM.  SUBMITTER RECOMMENDS VISUAL INSPECTION OF SHAFT AT DISASSEMBLY.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1997042400885	19970424	00885	CE  	1997	4	24	97ZZZX1835       	1	19970413	G	3230	08421022	BELLCRANK       			CESSNA	320   	320F        	2074516	CE  										NLG IDLER	FAILED          	G		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	01	6173Q	665  				320F0023				BELLCRANK FAILED ON TAKEOFF DURING RETRACTION.  NOSE GEAR WOULD NOT EXTEND TO LOCKED POSITION.  ACCORDING TO AIRCRAFT RE	CORDS, THE NOSE GEAR FAILED IN THE SAME MANNER IN DECEMBER, 1988.					1	L	7	2 	3O				3A25    					 
1997042400886	19970424	00886	SO  	1997	4	24	97ZZZX1836       	1	19970327	G	5513	6358701	RIB             		6358600     	PIPER 	PA32  	PA32300     	7103212	SO  										RT STAB TRIM TAB	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	681AT	4500 				327740038				FIGHT TRIM TAB SKIN AND INBOARD SUPPORT RIB CRACKED AT ACTUATOR ATTACHMENT UNDER FLANGE FOOTPRINT.						1	L	7	1 	3O				A3SO    					 
1997042400887	19970424	00887		1997	4	24	97ZZZX1837       	4	19970331	G	2312	KX165	TRANSCEIVER     			PIPER 	PA60  	PA60601P    	7106012	NM  										NAV COMM	EXCESS INTERF   	B			LN7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	66CG				P10800	61P0277061				UPON IFR CERTIFICATION UPGRADE OF APOLLO 2001GPS, C/W RFI TESTS.  FOUND NAV COMM RADIO TO INDUCE EXCESSIVE RFI INTO GPS 	SYSTEM.  CAUSE BEING NAV RADIO; OTHER NAV/COMM OF SAME TYPE OK IN EITHER NR 1 OR NR 2 SLOT.  APPLICATION OF 'NOTCH' FILT	ERS HAD NO AFFECT ON SITUATION.  RADIO SENT TO FACTORY FOR REPAIR.				1	M	7	2 	3O			RT	A17WE   					 
1997042400888	19970424	00888	SO  	1997	4	24	97ZZZX1838       	2	19970301	G	8530		CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					ALL CYLS	EXCESS WORN     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	72291	850  				E2247				REMOVED ALL CYLINDERS FROM AN 850-HOUR FACTORY REMANUFACTURED (ZERO TIME) ENGINE DUE TO LOW COMPRESSION.  FOUND ALL CYLI	NDERS WORN .009 INCH - .011 INCH OVER NEW SPECS.  OPERATOR KEEPS OIL SAMPLES WITH NO INDICATIONS.  NORMAL OIL CHANGES AN	D GOOD PILOT OPERATION.				1	L	7	1 	3O	3	O		3A15    	E3SO				 
1997042400890	19970424	00890	SO  	1997	4	24	97ZZZX1840       	1	19970301	G	3230	4546600	BREAKER         			PIPER 	PA24  	PA24250     	7102404	SO  										MLG	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	05	8236P	2404 				243490				LANDING GEAR FAILED TO RETRACT DUE TO INOPERATIVE CIRCUIT BREAKER.						1	L	7	1 	3O				1A15    					 
1997042400891	19970424	00891	SO  	1997	4	24	97ZZZX1841       	2	19970408	G	8550		OIL PAN         			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300A       	17022	SO  					PLUG BOSS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8591B					36291	16036			CORROSION FOUND INSIDE OF THE BOTTOM OF THE OIL PAN AROUND THE PLUG BOSS.  THIS WAS DUE TO MOISTURE CONDENSING AND COLLE	CTING AT THE BOTTOM OF PAN.  IF THE AIRCRAFT IS GOING TO SIT FOR WEEKS ON END;SUBMITTER SUGGESTS ONE-QUARTER OF THE OIL 	BE DRAINED AS THIS WILL FACILITATE REMOVAL OF THE COLLECTED MOISTURE.				1	H	7	1 	3O	3	O		3A12    	E253				 
1997042400893	19970424	00893	CE  	1997	4	24	97ZZZX1843       	1	19970405	G	7110	075205712	STIFFENER       			CESSNA	182   	182Q        	2072732	CE  										COWL	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	97852					18267222				STIFFENER HAS BEEN REPLACED 4 TIMES IN APPROXIMATELY 90 HOURS.  EACH TIME IT CRACKS IN THE SAME AREA IN THE SAME WAY.  A	LL OTHER ATTACHING PARTS ARE NEW.  IT APPEARS METAL IS TOO LIGHT OF A GAUGE OR IT IS BEING IMPROPERLY HEAT TREATED OR BO	TH.  CESSNA OFFERS CREDIT ON TWO OF THESE BUT HAS NOT IMPROVED PART OR OFFERRED A SOLUTION.  ALL COWL MOUNTS ARE NEW AND	 ENGINE SHOWS NO SIGN OF VIBRATION TO CAUSE THIS CRACKING OF PART.  THE ONE ON THE LEFT HAS OVER 90 HRS WITH NO SIGN OF 	CRACKING.		1	H	7	1 	3O			NT	3A13    					 
1997042400895	19970424	00895	SO  	1997	4	24	97ZZZX1845       	1	19970403	G	2421	1159SCAV373105	GENERATOR       	GARRTT      	GTCP36100G  	GULSTM	G1159 	GIV         	3980115	SO  										APU	SHAFT DECOUPLED 	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2WL	1825 			857	1118				DURING APU MAINTENANCE, THE AC GENERATOR WAS REMOVED.  THE INPUT DRIVESHAFT WAS FOUND DECOUPLED FROM AC GENERATOR.  THIS	 SHAFT IS HELD IN PLACE BY A SINGLE SCREW.  IF THE SCREW SHEARS OFF OR BACKS OUT, IT CAN CAUSE INTERNAL DAMAGE OR FAILUR	E TO THE AC GENERATOR.				2	L	7	2 	4F			RT	A12EA   					 
1997042400897	19970424	00897	NM  	1997	4	24	97ZZZX1847       	1	19970317	G	2710	25W530014509	CONTROL ROD     			ISRAEL	1125  	1125        		NM  										AILERON	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	500AJ					074				FOUND PART TO HAVE A LOT OF PLAY SIDEWAYS TO ROD MOVEMENT.  ALSO, PART DID NOT PASS THE AILERON LINEAR BALL BEARING INSP	ECTION/CHECK PER ASTRA MM 2710-02, PAGE 601.  MEASURED OUTSIDE DIAMETER OF ROD OF REJECTED PART .618 INCH.  MEASURED AGA	INST ANOTHER KNOWN NEW ROD .625 INCH.  NO CHROME NOTED ON REJECTED ROD ASSY.				2	L	7	2 	4F			RT	A16NM   					 
1997050100103	19970501	00103	GL  	1997	5	1	97ZZZX1848       	3	19970328	G	6114	D32612	HUB             			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	MT FLANGE	CRACKED         	B			FG6R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			NM	11		256  			DJ9234A			DJ9234A		PILOT NOTED VIBRATION IN LEFT ENGINE WHEN POWER REDUCED FOR LANDING.  FOUND 3 OF 6 MOUNTING STUDS ON PROPELLER FRACTURED	.  REMOVAL OF PROPELLER REVEALED O-RING PINCHED BETWEEN PROPELLER HUB AND STARTER RING GEAR.  PROPER LOCATION OF O-RING 	IS INSIDE PROPELLER FLANGE.  AS O-RING EXTRUDED OUT, BOLT TORQUE REDUCED ALLOWING PROPELLER TO WORK AND MOVE FRACTURING 	BOLTS.  PROPELLER HAD RECENTLY BEEN REMOVED AND REPLACED FOR SPINNER ASSEMBLY REPLACEMENT.  FURTHER INVESTIGATION REVEAL	ED STARTER RING GEAR CRACKED AND HUB CRACKED AT ONE MOUNTING STUD HOLE.  RING GEAR AND HUB REPLACED.  SUSPECT CAUSE:  FA	ILURE TO FOLLOW MANUFACTURER'S INSTALLATION INSTRUCTIONS.	1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997050100104	19970501	00104	SW  	1997	5	1	97ZZZX1849       	1	19970201	G	3230	B10006	COUPLING        	DUKES       	950158503   	MOONEY	M20   	M20C        	5870208	SW  										MLG ACTUATOR	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	25	111JP	500  				690078				DUKES LANDING GEAR ACTUATOR RUBBER DRIVE COUPLING CONNECTS TRANSMISSION TO ACTUATOR.  COUPLING SPLIT IT IN TWO PLACES  D	ISCONNECTING TRANSMISSION TO ACTUATOR; THUS, PREVENTING ELECTRICAL OR MECHANICAL GEAR EXTENSION, A GEAR UP LANDING FOLLO	WED.				1	L	7	1 	3O				2A3     					 
1997050100105	19970501	00105	SO  	1997	5	1	97ZZZX1850       	1	19970318	G	2140	10E212	HEATER          	JANITROL    		PIPER 	PA31T 	PA31T       	7103124	SO  										FUEL DRAIN	MALFUNCTION     	D		A		K				NONE                    				A			FLAME/FIRE                			NR	NOT REPORTED   	1			WP	19	111KV		23   			7920035				HEATER VENTING FUEL OVERBOARD FROM COMBUSTION CHAMBER DRAIN CAUSING FLAME STREAK THE LENGTH OF THE LOWER FUSELAGE.  FUEL	 DRAIN IS LOCATED IN LINE AND 3 INCHES AHEAD OF HEATER EXHAUST.  RECOMMEND AIR CREWS LOOK FOR THIS CONDITION DURING PRE-	FLIGHT.				1	L	7	2 	3T				A8EA    					 
1997050100106	19970501	00106	SO  	1997	5	1	97ZZZX1851       	1	19970415	G	5743	486291	SCREW           		9564306     	PIPER 	PA32  	PA32RT300T  	7103216	SO  										MLG TRUSS BKT	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	3034A	1600 				32R7987020				INSPECTION FOUND ONE OF THE COUNTERSINK SCREWS ATTACHING MAIN GEAR TRUSS BRACKET TO WING SPAR IS LOOSE.  NUT IS TIGHT ON	 SCREW, BUT SCREW CAN BE EASILY TURNED WITH FINGERS.					1	L	7	1 	3O				A3SO    					 
1997050100107	19970501	00107	SO  	1997	5	1	97ZZZX1852       	1	19970410	G	5542	7892802	SKIN            			PIPER 	PA32  	PA32RT300T  	7103216	SO  										RUD LT SIDE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	3034A	1600 				32R7987020				INSPECTION FOUND RUDDER SKIN LT SIDE AT TRAILING EDGE, APPROXIMATELY 18 INCHES FROM TOP AT AFT END OF STIFFENING DIMPLE,	 TO HAVE ABOUT 6 SPIDER WEB CRACKS ALL ABOUT 1 INCH IN LENGTH.  PIPER SL 882A WAS INCORPORATED.					1	L	7	1 	3O				A3SO    					 
1997050100108	19970501	00108	SO  	1997	5	1	97ZZZX1853       	1	19970319	G	7160		DUCT            			PIPER 	PA28  	PA28140     	7102802	SO  										ENGINE INTAKE	ICE DEBRIS      	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NE	01	3DP					287325252				PILOT PERFORMED PRE-FLIGHT INSPECTION OF AIRCRAFT.  FOUND NO DISCREPANCIES, STARTED AIRCRAFT AND TAXIED TO RUN-UP AREA. 	 PERFORMED GROUND RUN-UP, NO DISCREPANCIES NOTED.  RECEIVED CLEARANCE FOR TAKEOFF, SHORTLY AFTER TAKEOFF, THE PILOT EXPE	RIENCED POWER LOSS AND NOTIFIED ATC OF HIS SITUATION.  PILOT LANDED UNEVENTFULLY AND ROLLED OFF THE RUNWAY WHERE THE ENG	INE STOPPED.  ON INSPECTION, WATER WAS SEEN DRIPPING OUT OF CARBURETOR HEAT BOX.  INSPECTED DUCTING BETWEEN INDUCTION FI	LTER AND CARBURETOR HEAT BOX AND FOUND A CHUNK OF ICE (APPROXIMATELY 1.5 INCHES BY 2 INCHES) LOOSE IN THE DUCTING.  GROU	ND RUN-UP PROVED ALL FUNCTIONS SATISFACTORY AFTER CLEARING DUCTING OF DEBRIS.	1	L	7	1 	3O				2A13    					 
1997050100112	19970501	00112	CE  	1997	5	1	97ZZZX1857       	1	19970328	G	2720	0024100341	TUBE            			BEECH 	58    	58          	1152740	CE  										RUDDER PEDAL	SCORED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	3270J	265  				TH1770				THE RUDDER PEDAL BELLCRANK INTERCONNECT TUBE WAS SCORED ENTIRELY THROUGH THE TUBE WALL BY A 1 INCH LONG PK TYPE UPHOLSTE	RY SCREW USED TO SECURE THE PILOT'S KICKPLATE TO THE FLOOR BOARD.  REPLACED TUBE.  NEW SCREW INSTALLED NO LONGER THAN .7	5 INCH.  SUBMITTER STATED BE SURE TO USE SCREWS .75 INCH LONG OR SHORTER.				1	L	7	2 	3O				3A16    					 
1997050100113	19970501	00113	SO  	1997	5	1	97ZZZX1858       	1	19970403	G	5711	6207400	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	3713K					2823702				DURING MAINTENANCE TO CHANGE THE WING FUEL TANK FLEXIBLE HOSES, FOUND INTERGRANULAR CORROSION IN THE AREA WHERE THE HOSE	S PASS THROUGH THE SPARS, AND THE TOP AND BOTTOM OF THE RIGHT SPAR STRUCTURE.					1	L	7	1 	3O				2A13    					 
1997050100114	19970501	00114	SO  	1997	5	1	97ZZZX1859       	1	19970403	G	5711	6207401	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  										WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	3713K					2823702				DURING MAINTENANCE TO CHANGE THE WING FUEL TANK FLEXIBLE HOSES, FOUND INTERGRANULAR CORROSION IN THE AREA WHERE THE HOSE	S PASS THROUGH THE SPARS, AND THE TOP AND BOTTOM OF THE RIGHT SPAR STRUCTURE.					1	L	7	1 	3O				2A13    					 
1997050100115	19970501	00115	CE  	1997	5	1	97ZZZX1860       	1	19970301	G	3213	07416011	GEAR LEG        			CESSNA	182   	182G        	2072716	CE  										LT MLG	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	3791U					18255191				DURING ANNUAL INSPECTION, RUST WAS NOTICED ON THE LANDING GEAR LEGS (MAIN GEAR) MOST SEVERE RUST WAS FOUND UNDER STOP. M	ETAL WAS RUSTED TO THE POINT OF 'DELAMINATION'.  THE RUST APPEARED TO HAVE BEEN CAUSED BY THE GLUE THAT WAS USED BY CESS	NA TO HELP ATTACH THE STEP TO THE LANDING GEAR.  SUBMITTER SUGGESTS THESE AIRCRAFT IN THIS SERIAL NUMBER RANGE BE CLEANE	D AND INSPECTED IN THIS AREA.  THE AIRCRAFT LISTED IN THIS REPORT REQUIRED REPLACEMENT OF BOTH GEAR LEGS.			1	H	7	1 	3O			NT	3A13    					 
1997050100116	19970501	00116	CE  	1997	5	1	97ZZZX1861       	1	19970301	G	3213	07416012	GEAR LEG        			CESSNA	182   	182G        	2072716	CE  										RT MLG	RUSTED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	3791U					18255191				DURING ANNUAL INSPECTION, RUST WAS NOTICED ON THE LANDING GEAR LEGS (MAIN GEAR) MOST SEVERE RUST WAS FOUND UNDER STOP. M	ETAL WAS RUSTED TO THE POINT OF 'DELAMINATION'.  THE RUST APPEARED TO HAVE BEEN CAUSED BY THE GLUE THAT WAS USED BY CESS	NA TO HELP ATTACH THE STEP TO THE LANDING GEAR.  SUBMITTER SUGGESTS THESE AIRCRAFT IN THIS SERIAL NUMBER RANGE BE CLEANE	D AND INSPECTED IN THIS AREA.  THE AIRCRAFT LISTED IN THIS REPORT REQUIRED REPLACEMENT OF BOTH GEAR LEGS.			1	H	7	1 	3O			NT	3A13    					 
1997050100117	19970501	00117	SO  	1997	5	1	97ZZZX1862       	1	19970306	G	5741	66762000	STRAP           			PIPER 	PA28  	PA28R201T   	7102813	SO  										AFT WING STRAP	CORRODED        	G	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	38557	3276 				28R7703242				REAR WING ATTACH STRAP FOUND CORRODED BEHIND FLAP.  STRAP DIFFICULT TO SEE THROUGH SPAR CAP.  SUBMITTER SUGGESTED LOWERI	NG FLAP AND LOOK ABOVE FLAP UNDER TRAILING EDGE OF WING WHERE IT ATTACHED TO FUSELAGE FOR STRAP CORROSION.					1	L	7	1 	3O				2A13    					 
1997050100118	19970501	00118	CE  	1997	5	1	97ZZZX1863       	1	19970403	G	2434	ALV9510	ALTERNATOR      	PRESTOLITE  		CESSNA	421   	421B        	2076014	CE  										DC SYSTEM	FAILED          	B			EKIR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			WP	07	4050Q	252  			6010789	421B0274				LEFT ALTERNATOR BECAME INTERMITTENT THEN DROPPED OFF LINE.  RETURNED FLIGHT TO YUMA.  UNIT HAD BEEN OVERHAULED 1-25-96.						1	L	7	2 	3O				A7CE    					 
1997050100122	19970501	00122	EA  	1997	5	1	97ZZZX1867       	2	19970225	G	8500		ENGINE          			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE REAR	FIRE            	B			KG4R	K				NONE                    				A			FLAME/FIRE                			NR	NOT REPORTED   	1			SO	19	43733	4154 	667  			288416122	L1131939A			ENGINE COMPARTMENT ON FIRE AT REAR OF ENGINE.  INSPECTION OF ENGINE REVEALS NO APPARENT CAUSE FOR START-UP OF FIRE.  CAR	BURETOR SENT TO SOUTHEAST FUEL SYSTEM, CRS TW4R559M FOR INSPECTION.  REFER TO CEU INV NR 27646/2878 FOR DETAILS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997050100123	19970501	00123	EA  	1997	5	1	97ZZZX1868       	2	19970404	G	7414	M3975	COIL            	SLICK       	4371        	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					MAG	SHORTED         	B			EEAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	65875	218  				17275910	RL1835339A			RIGHT MAGNETO ON ENGINE INOPERATIVE.  NO ELECTRICAL OUTPUT.  FOUND COIL AND SECONDARY COIL OHMS READING TO BE OUT OF TOL	ERANCE.  REMOVED COIL FOUND BURNED OUT SPOT ON BOTTOM OF COIL SHORTED OUT TO CASE.  INSTALL NEW COIL.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997050100125	19970501	00125	NE  	1997	5	1	97ZZZX1870       	1	19970301	G	7120		MOUNT           			CONAER	LA4   	LA4         	5110302	NE  										ENGINE	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6653L	712  				416				ENGINE MOUNT CRACKS WERE DISCOVERED DURING REMOVAL OF BRACKETT AIR FILTER COWLING.  CRACKED SUPPORT IS APPROXIMATELY 4 I	NCHES LONG, 2 INCHES HIGH, .1250 INCH THICK AND MADE OF STEEL, AND IS WELDED HORIZONTALLY TO THE ENGINE MOUNT STRUCTURE.	  THE SUPPORT ACTS AS A RIVETED CONNECTION FOR THE FORWARD RIB, P/N 2-5250, 2-5200, AND AFT RIBS 2-5253-27 AND 28.				1	H	7	1 	3O				1A13    					 
1997050100126	19970501	00126	CE  	1997	5	1	97ZZZX1871       	1	19970317	G	3213		AXLE            			CESSNA	206   	TU206F      	2073353	CE  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7485Q					U20602220				AIRCRAFT TOTAL TIME 3,075.0 HOURS.  AIRCRAFT HAD BEEN CONVERTED TO SEAPLANE BY STC 1483GL IN 1991 AND OPERATED IN SALT W	ATER FOR 3 YEARS PRIOR TO ANNUAL INSPECTION IN 1997.  ON DISASSEMBLY FOR MAINTENANCE AND INSPECTION, THE MLG AXLES WERE 	REMOVED FROM THE GEAR SWING-ARMS.  AFTER ACCUMULATED GREASE WAS REMOVED, NOTED ALL FOUR AXLES HAD SEVERE INTERGRANULAR C	ORROSION AT THE UPPER MOUNTING BOSS LOCATION.  AXLES WERE REPLACED WITH NEW PARTS.  SUBMITTER SUGGESTED CLEANING GREASE 	FROM AXLES AND INSPECTING EACH ANNUAL.  PARTS TOTAL TIME:  APPROX 1,500 HOURS.		1	H	7	1 	3O				A4CE    					 
1997050100127	19970501	00127	SO  	1997	5	1	97ZZZX1872       	2	19970401	G	8550	12509221	ADAPTER         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520L      	17032	SO  					OIL FILTER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	756HK	4271 				U20604102	567375			DURING ENGINE CHANGE, THE OIL FILTER ADAPTER WAS REMOVED AND THE THREADS WERE FOUND DAMAGED AS DEPICTED IN AD 96-12-22. 	 THERE WERE NO SIGNS OF LEAKAGE, BUT THE BREAKAWAY TORQUE APPEARED TO BE LOW.  SUBMITTER STATED THIS IS THE THIRD ADAPTE	R OF THIS TYPE FOUND WITH THREAD DAMAGE.  DIFFICULTY IN TORQUING WHILE MAINTAINING PROPER ALIGNMENT MAY BE A POSSIBLE CA	USE.			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1997050100128	19970501	00128	SO  	1997	5	1	97ZZZX1873       	1	19970105	G	3230		TRANSMISSION    			PIPER 	PA30  	PA30        	7103002	SO  										MLG	BOLTS BACKED OUT	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	7745Y	4300 				30836				LANDING GEAR COLLAPSE DUE TO MOUNTING BOLTS ON GEAR TRANSMISSION AND MOTOR BACKING OUT (NO SAFETY WIRE).  GEAR LINKAGE D	ISRUPTED AND BECAME MISALIGNED.  THIS PREVENTED NOSE GEAR FROM LOCKING.  GEAR ALSO FAILED TO RETRACT.  NOSE GEAR FAILED 	COMPLETELY DUE TO GEAR MOTOR SHEARING RIVETS AND RIPPING THE GEAR MOTOR FROM THE BULKHEAD.  GEAR MOTOR MOUNTING BRACKET 	IS .1250 INCH T6 ALUMINUM MOUNTING BRACKET IS ATTACHED TO .32 INCH BULKHEAD AND SUPPORTS (FLIMSY).  THIS AREA MUST BE BU	TTRESSED BY .1250 INCH T6 SO THAT EVEN IF THE NOSE GEAR FAILS TO DESCEND OVER CENTER THE GEAR MOTOR ASSEMBLY WILL STILL 	SUPPORT THE GEAR.  GEAR MOUNT BOLTS AT GEAR MOTOR BACKED OUT.  NO SAFETY WIRE.  DATE OF INCIDENT 1-5-97.	1	L	7	2 	3O				A1EA    					 
1997050100129	19970501	00129	SO  	1997	5	1	97ZZZX1874       	1	19970105	G	3230	2176000	ATTACHMENT      			PIPER 	PA30  	PA30        	7103002	SO  										XMSN ATTACH	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	7745Y	4300 				30836				LANDING GEAR COLLAPSE DUE TO MOUNTING BOLTS ON GEAR TRANSMISSION AND MOTOR BACKING OUT (NO SAFETY WIRE).  GEAR LINKAGE D	ISRUPTED AND BECAME MISALIGNED.  THIS PREVENTED NOSE GEAR FROM LOCKING.  GEAR ALSO FAILED TO RETRACT.  NOSE GEAR FAILED 	COMPLETELY DUE TO GEAR MOTOR SHEARING RIVETS AND RIPPING THE GEAR MOTOR FROM THE BULKHEAD.  GEAR MOTOR MOUNTING BRACKET 	IS .1250 INCH T6 ALUMINUM MOUNTING BRACKET IS ATTACHED TO .32 INCH BULKHEAD AND SUPPORTS (FLIMSY).  THIS AREA MUST BE BU	TTRESSED BY .1250 INCH T6 SO THAT EVEN IF THE NOSE GEAR FAILS TO DESCEND OVER CENTER THE GEAR MOTOR ASSEMBLY WILL STILL 	SUPPORT THE GEAR.  GEAR MOUNT BOLTS AT GEAR MOTOR BACKED OUT.  NO SAFETY WIRE.  DATE OF INCIDENT 1-5-97.	1	L	7	2 	3O				A1EA    					 
1997050100130	19970501	00130	SO  	1997	5	1	97ZZZX1875       	1	19970105	G	5320	2095400	CHANNEL ASSY    			PIPER 	PA30  	PA30        	7103002	SO  										BS 87	FAILED          	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	7745Y	4300 				30836				LANDING GEAR COLLAPSE DUE TO MOUNTING BOLTS ON GEAR TRANSMISSION AND MOTOR BACKING OUT (NO SAFETY WIRE).  GEAR LINKAGE D	ISRUPTED AND BECAME MISALIGNED.  THIS PREVENTED NOSE GEAR FROM LOCKING.  GEAR ALSO FAILED TO RETRACT.  NOSE GEAR FAILED 	COMPLETELY DUE TO GEAR MOTOR SHEARING RIVETS AND RIPPING THE GEAR MOTOR FROM THE BULKHEAD.  GEAR MOTOR MOUNTING BRACKET 	IS .1250 INCH T6 ALUMINUM MOUNTING BRACKET IS ATTACHED TO .32 INCH BULKHEAD AND SUPPORTS (FLIMSY).  THIS AREA MUST BE BU	TTRESSED BY .1250 INCH T6 SO THAT EVEN IF THE NOSE GEAR FAILS TO DESCEND OVER CENTER THE GEAR MOTOR ASSEMBLY WILL STILL 	SUPPORT THE GEAR.  GEAR MOUNT BOLTS AT GEAR MOTOR BACKED OUT.  NO SAFETY WIRE.  DATE OF INCIDENT 1-5-97.	1	L	7	2 	3O				A1EA    					 
1997050100131	19970501	00131	SO  	1997	5	1	97ZZZX1876       	1	19970404	G	3250	9539400	CHANNEL         			PIPER 	PA34  	PA34200     	7103405	SO  										NLG STEERING	DAMAGED         	G		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	15	94PG					347450064				NOSE LANDING GEAR TURN LIMITS EXCEEDED DURING GROUND HANDLING OF THE AIRCRAFT WITH TOW VEHICLE.  THE NLG STRUT, UPPER TI	LLER ROLLER (PN 78535-00) WAS DISPLACED OUTSIDE OF STEERING TRACK CHANNEL (PN 95394-00).  PILOT DID NOT EXPERIENCE ANY A	BNORMAL STEERING DURING TAXI/TAKEOFF.  WHEN GEAR WAS RETRACTED, UNSAFE NLG LIGHT WAS EXPERIENCED.  PILOT EXTENDED GEAR, 	LANDED AND NLG COLLAPSED DURING ROLL-OUT!			1	L	7	2 	3O				A7SO    					 
1997050100132	19970501	00132	CE  	1997	5	1	97ZZZX1877       	1	19970401	G	3246	10322300	BOLT            			CESSNA	208   	208B        	2073701	CE  										MLG WHEEL	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										A NEW OPERATOR HAS FOUND ONE OR TWO BOLTS BROKEN APART AND MISSING FROM MAIN WHEELS DURING INTRANSIT INSPECTION OF AIRCR	AFT. THIS HAPPENED QUITE OFTEN ON FLEET AIRCRAFT.  THEY WERE USING 53-57 PSI TIRE PRESSURE IAW CESSNA PHASE CHECK TACK C	ARD 321004.  PROBLEM STARTED AT APPROX 150 TSN AIRCRAFT TIME.  CHAPTER 12 OF MM SHOWS A TABLE WITH THE REQUIRED PRESSURE	 FOR THIS OPERATOR'S TIRES WAS 35-45 PSI.  TIRE PRESSURE WAS ADJUSTED IAW MM AND PROBLEM DISAPPEARED.  SUBMITTER STATED 	MECHANICS SHOULD BE ADVISED TO FOLLOW THE MM INSTRUCTIONS OVER ANY OTHER DOCUMENT.		1	H	7	1 	3T				A37CE   					 
1997050100133	19970501	00133	SO  	1997	5	1	97ZZZX1878       	1	19970331	G	2460	475109	SHOCK MOUNT     			PIPER 	PA31T 	PA31T1      	7103126	SO  										RELAY PANEL	BROKEN          	B	L		CPNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	114JR					31T8004037				PILOT REPORTED WHEN DEICE TURNED ON, PANEL LIGHTS WOULD FLICKER OR GO OUT.  VARIOUS OTHER CKTS ENERGIZED (HEATER FUEL, B	OOT DEICE, ETC).  FOUND RELAY PANEL SHOCK MOUNT BROKEN CAUSING PANEL TO BE HOT WITH 24V DC, WHICH TURNED CIRCUITS ON.					1	L	7	2 	3T				A8EA    					 
1997050100134	19970501	00134	EA  	1997	5	1	97ZZZX1879       	2	19970403	G	8520	SL13521	ROD BEARING     			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					NR 3	FAILED          	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	13FC	661  				M2017	L2620936A			METAL WAS FOUND IN THE SCREEN AND OIL FILTER AT THE 100-HOUR INSPECTION.  THE CYLINDERS WERE REMOVED AND NO EVIDENCE OF 	METAL WEAR COULD BE FOUND.  THE AIRCRAFT WAS PUT BACK INTO SERVICE AND FLOWN FOR APPROXIMATELY 50 HOURS.  THE SCREENS AN	D FILTERS WERE AGAIN CHECKED FOR METAL.  MORE METAL WAS FOUND AND THE ENGINE WAS REMOVED AND DISASSEMBLED FOR FURTHER IN	SPECTION.  THE NR 3 ROD BEARING WAS FOUND TO HAVE THE TOP LAYER OF MATERIAL (BABBIT) STARTING TO SEPARATE AND FLAKE OFF.			1	L	7	1 	3O	3	O		A1CE    	E286				 
1997050100136	19970501	00136	CE  	1997	5	1	97ZZZX1881       	1	19970409	G	2510	071402539	SEAT FRAME      			CESSNA	210   	210N        	2073453	CE  										PILOT SEAT	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	9309Y					21064469				PILOT SEAT FRAME BROKEN WHERE BELLCRANK ATTACHES.  SEAT P/N 0714025-39.						1	H	7	1 	3O				3A21    					 
1997050100137	19970501	00137	CE  	1997	5	1	97ZZZX1882       	1	19970409	G	2510	071402539	SEAT FRAME      			CESSNA	185   	A185F       	2072821	CE  										PILOT SEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	9434N	2625 				18504355				PILOT SEAT FRAME BROKEN WHERE BELLCRANK ATTACHES.						1	H	7	1 	3O				3A24    					 
1997050100138	19970501	00138	SO  	1997	5	1	97ZZZX1883       	2	19970317	G	8540	536421	CRANK GEAR      			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  					ASSY CASE	TEETH BROKEN OFF	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3129D		1656 			31927	469748JR			NOISE HEARD AT IDLE POWER AFTER LANDING THAT SOUNDED LIKE A ROD KNOCK (OR A WELL RUNNING RADIAL ENG).  DECIDED TO DISASS	EMBLE ENGINE FOR OVERHAUL.  FOUND TWO TEETH MISSING FROM CRANK GEAR P/N 536421 AND ONE TOOTH MISSING AND ANOTHER TOOTH C	RACKED ON CAM GEAR P/N 535660.  TEETH WERE FOUND IN OIL PAN.  SUSPECT GEARS WERE STRESSED FROM SUDDEN STOPPAGE IN 1972. 	 ENG TT SINCE CONT REMAN:  2,615 HRS.			1	H	7	1 	3O	3	O	NC	5A6     	E273				 
1997050100139	19970501	00139	SO  	1997	5	1	97ZZZX1884       	2	19970317	G	8540	535660	CAM GEAR        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  					ASSY CASE	TEETH BROKEN OFF	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3129D		1656 			31927	469748JR			NOISE HEARD AT IDLE POWER AFTER LANDING THAT SOUNDED LIKE A ROD KNOCK (OR A WELL RUNNING RADIAL ENG).  DECIDED TO DISASS	EMBLE ENGINE FOR OVERHAUL.  FOUND TWO TEETH MISSING FROM CRANK GEAR P/N 536421 AND ONE TOOTH MISSING AND ANOTHER TOOTH C	RACKED ON CAM GEAR P/N 535660.  TEETH WERE FOUND IN OIL PAN.  SUSPECT GEARS WERE STRESSED FROM SUDDEN STOPPAGE IN 1972. 	 ENG TT SINCE CONT REMAN:  2,615 HRS.			1	H	7	1 	3O	3	O	NC	5A6     	E273				 
1997050100140	19970501	00140	CE  	1997	5	1	97ZZZX1885       	1	19970409	G	2434	ALT9422R	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  										DC SYSTEM	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SO	11	6671X	552  				TH1077				AFTER AN IN-FLIGHT ALTERNATOR FAILURE, FOUND THAT THE SHAFT HAD NO SUPPORT AND WOBBLED FREELY, THAT THE ALT GEAR P/N 640	932 WAS CHEWED UP AND SO WAS THE DRIVE GEAR FROM THE CRANKSHAFT P/N 632018.  ALSO, ONE EACH LOCKPLATE P/N 641909 WAS MIS	SING AS WELL AS THE TWO EACH P/N 634080 BOLTS THAT RETAIN IT.  CUT OPEN THE OIL FILTER AND DISCOVERED LARGE AMOUNTS OF M	ETAL.  THE ENGINE WAS REMOVED FOR INSPECTION.			1	L	7	2 	3O				3A16    					 
1997050100141	19970501	00141	CE  	1997	5	1	97ZZZX1886       	1	19970403	G	3040	66001413	THERMOSTAT      			LEAR  	35    	35A         	5170602	CE  										WINDSHIELD SW	FAILED          	B			JKIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17	2FOR					161				REMOVED FAILED SWITCHES, PURCHASED NEW FROM LEAR, TESTED AND FOUND FAILED, HAD SWITCHES TESTED BY LAB AND FAILED.  REPLA	CEMENTS FROM LEAR FAILED, ONE OUT OF TWO, 2 TIMES.  RECOMMEND LEAR RE-INITIATE TEST PROGRAM ON THEIR SWITCHES LIKE THEY 	USED TO DO.				2	L	7	2 	4F				A10CE   					 
1997050100142	19970501	00142	CE  	1997	5	1	97ZZZX1887       	1	19970408	G	3020	101910026	SHAFT           			BEECH 	200   	B200        	1152922	CE  										RT ICE DOOR	SHEARED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6182A	905  				BB1484				CREW REPORTED RIGHT ICE DEFLECTION DOOR IS INOPERATIVE.  FOUND RIGHT ICE DOOR SHAFT ASSY SHEARED AT BOLT HOLE FOR ACTUAT	OR ATTACHMENT ARM.  NO BINDING NOTED ON DOOR ASSY.  REMOVED AND REPLACED SHAFT ASSY WITH A NEW UNIT.  GROUND OPS CHECKED	 OK.  REFERENCE BEECHCRAFT MM CHAPTER 30-20-00 AND BEECHCRAFT PARTS CATALOG CHAPTER 30-22-01, PAGE 6 ITEM NR 53.				1	L	7	2 	4T				A24CE   					 
1997050100144	19970501	00144	NE  	1997	5	1	97ZZZX1889       	2	19970109	G	7260	3013883H	IDLER GEAR      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ACCESSORY CASE	FAILED          	G	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6606R	2368 				BB1122				PILOT REPORTED AIR COND INOP.  MAINT SUSPECTED 'QUILL SHAFT' HAD SHEARED.  REMOVED AND FOUND SHAFT IN SERVICEABLE CONDIT	ION.  REMOVAL OF ACCESSORY CASE FOUND IDLER GEAR HAD FAILED RESULTING IN LOSS OF DRIVE FOR AIR/COND COMP.  NO REASON FOR	 FAILURE HAS BEEN DETERMINED AT THIS TIME.  PART HAS BEEN SENT TO PRATT AND WHITNEY FOR EVAL.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997050100145	19970501	00145	CE  	1997	5	1	97ZZZX1890       	1	19970401	G	3240	07308500	PRESSURE PLATE  	PARKERHANFIN	30182       	CESSNA	208   	208B        	2073701	CE  										RT BRAKE	MISINSTALLED    	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										DURING INSP, RT BRAKE PRESSURE PLATE FOUND INSTALLED IN WRONG POSITION.  LINING SIDE WAS FACING THE PISTON HOUSING.  ACF	T BRAKING METAL-TO-METAL CAUSING VERY HIGH BRAKE TEMPERATURES AND SUSPECTED SPARKS CAME OUT ON EVERY BRAKE APPLICATION. 	 PRESSURE PLATE AND LININGS DAMAGED BEYOND LIMITS.  ACFT TT:  525 HRS.				1	H	7	1 	3T				A37CE   					 
1997050100146	19970501	00146	SO  	1997	5	1	97ZZZX1891       	1	19970328	G	5320	1022914	WEB             			GULSTM	AA5   	AA5A        	3960106	SO  										FUSELAGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9920U					AA50320				INSPECTION FOUND FUSELAGE COMPONENT P/N 102291-4 CRACKED BOTH SIDES IN THE 90 DEGREE ANGLE UNDER RIVETS THAT ATTACH TO B	ULKHEAD.  ACTION DRILLED STOP HOLES AND INSTALLED REINFORCEMENT WITH NEW.					1	L	7	1 	3O				A16EA   					 
1997050100147	19970501	00147	CE  	1997	5	1	97ZZZX1892       	1	19970408	G	5341	2050411129	BLOCK           			CESSNA	172   	172         	2072402	CE  										LT/RT WING SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8591B	2363 				36291				FRONT AND AFT BLOCKS (RIGHT AND LEFT SIDES) FOR WING SPAR ATTACHMENT SHOW  HEAVY EXFOLIATION BETWEEN MAIN BOLT SPAR ATTA	CHMENT AND HOLD-DOWN BOLTS FOR BLOCK, MAY BE UNDETECTABLE WITH WINGS ATTACHED, EVEN WITH SKIRTING REMOVED.  MIGHT POSSIB	LY DO A MIRROR INSPECTION; IF NOT, WOULD NEED TO MAKE SOME FORM OF PERIODIC INSPECTION SCHEUDLE TO PULL WINGS TO INSPECT	 INNER BLOCK AREA AND BOLTS FOR CORROSION AND/OR WHEN APPROPRIATE, PULL BLOCK TO INSPECT BACK PORTION AND BOLTS.  SHOULD	 BE NOTED THAT AIRCRAFT SAT IN AN OPEN FIELD FOR APPROXIMATELY TEN YEARS.		1	H	7	1 	3O			NT	3A12    					 
1997050100148	19970501	00148	CE  	1997	5	1	97ZZZX1893       	1	19970408	G	5341	2870512122	BEARING ATTACH  			CESSNA	172   	172         	2072402	CE  										LT/RT WING SPAR	CORRODED        	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8591B	2363 				36291				FRONT AND AFT BLOCKS (RIGHT AND LEFT SIDES) FOR WING SPAR ATTACHMENT SHOW  HEAVY EXFOLIATION BETWEEN MAIN BOLT SPAR ATTA	CHMENT AND HOLD-DOWN BOLTS FOR BLOCK, MAY BE UNDETECTABLE WITH WINGS ATTACHED, EVEN WITH SKIRTING REMOVED.  MIGHT POSSIB	LY DO A MIRROR INSPECTION; IF NOT, WOULD NEED TO MAKE SOME FORM OF PERIODIC INSPECTION SCHEUDLE TO PULL WINGS TO INSPECT	 INNER BLOCK AREA AND BOLTS FOR CORROSION AND/OR WHEN APPROPRIATE, PULL BLOCK TO INSPECT BACK PORTION AND BOLTS.  SHOULD	 BE NOTED THAT AIRCRAFT SAT IN AN OPEN FIELD FOR APPROXIMATELY TEN YEARS.		1	H	7	1 	3O			NT	3A12    					 
1997050100342	19970501	00342	NM  	1997	5	1	97ZZZX1899       	1	19970221	G	2710	69356881	PCU FILTER CAP  			BOEING	737   	737*        		NM  										AILERON SYSTEM	BURST           	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			1800 		3064SS					THE FILTER CAP BURST UNDER WORKING CONDITIONS FOR THE AILERON PCU.  THE ALUMINUM FILTER CAPS ARE WEAKER THAN THE STEEL O	NES.  IT IS RECOMMENDED THAT ALUMINUM CAPS BE REPLACED COMPLETELY BY STEEL FILTER CAPS.					2	L	7	2 	4F			RT	A16WE   					 
1997050100343	19970501	00343	EU  	1997	5	1	97ZZZX1900       	1	19970327	G	3610	HTE460009009	NON RETURN VALVE			AIRBUS	320   	A320321     	3930325	EU  										APU AIR	CRACKED         	B		A	F5HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03					M174VNR274					VALVE FLAPPERS DEVELOP CRACKS.  FLAPPER TO BODY HINGE HAS PREMATURE WEAR CAUSING HINGE TO SEPARATE FROM BODY.  SUBMITTER	 STATED COMPONENT CONSTRUCTION IS ALUMINUM ALLOY.  TIME CONTROL OF COMPONENT MAY ELIMINATE EXCESSIVE WEAR CONDITIONS ELI	MINATING OPERATOR DIFFICULTY REPORTS AND DISCREPANCIES.				2	L	7	2 	RT			4T	A28NM   					 
1997050100344	19970501	00344	EA  	1997	5	1	97ZZZX1901       	2	19970325	G	7414	1068291018	MAGNETO         	ELECTROSYS  	D6RN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					BASE FLANGE	LOOSE           	B			V0AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	2QC	400  			4052388	317752124				INSPECTION FOUND MAG COULD BE MOVED DUE TO BASE METAL FROM FLANGE MISSING TOP AND BOTTOM ABOUT .0625 INCH.  MAG P/N 10-6	8291018, TYPE D6RN3200.  SUBMITTER STATED THIS IS 2ND MAG 2000/3000 SERIES FOUND LOOSE WITH FLANGE METAL MISSING.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997050100345	19970501	00345	CE  	1997	5	1	97ZZZX1902       	1	19970324	G	3246	50300010109	WHEEL           			BEECH 	90    	65A90       	1152908	CE  										LT MLG	FAILED          	B	P	A	EFAR	K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	21	88SP	8291 			B1884	LJ116				THE LEFT MLG OUTER WHEEL HALF FAILED AFTER LANDING ROLL-OUT AT THE RUNWAY TURN OFF.  THE WHEEL HALF BLEW OFF, HIT THE AS	PHALT AND BOUNCED UP INTO THE RT NACELLE CAUSING MINOR DAMAGE.  CAUSE OF FAILURE SEEMS TO BE CRACKS STARTING AT THE VALV	E STEM HOLE, BOTH SIDES, ABOUT THE CIRCUMFERENCE OF THE WHEEL OR POSSIBLY FROM A DENT ON THE OUTSIDE RIM.  THE MFG DATE 	IS 1-68.  SUBMMITTER RECOMMENDED STRIPPING PAINT AND DYE CHECK FOR EDDY CURRENT CHECK FOR CRACKS.  CYCLES, 8,394.			1	L	7	2 	3T				3A20    					 
1997050100346	19970501	00346	NE  	1997	5	1	97ZZZX1903       	2	19970301	G	7323	1412654	BEARING         	WOODWARD    	8210        						PWA   	PT6   	PT6A25      	52043	NE  					GOVERNOR	MISASSEMBLY     	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03										NEW WOODWARD BEARING P/N 1412-654.  RECEIVING IN INSPECTION REVEALED THAT INNER BEARING RACE, ROLLER BALLS, AND BALL CAG	E WERE NOT SEATED CORRECTLY INTO THE OUTER RACE.  BEARING WOULD SPIN, HOWEVER, THE OUTER RACE WOULD 'WOBBLE' WHEN ROTATE	D.									3	T			E4EA				 
1997050100347	19970501	00347	SO  	1997	5	1	97ZZZX1904       	1	19970312	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										RT ENGINE	CRACKED         	B	S		OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	192ND	4422 				4495004				FOUND RIGHT ENGINE MOUNT CRACKED.  CRACK WAS ON TOP RIGHT MOUNT RING WHERE MOUNT RING AND TUBE FROM FIREWALL ARE WELDED 	TOGETHER.  CRACK RUNS ALONG EDGE OF WELD.  INSPECTION FREQUENCY INCREASED BY OPERATION.					1	L	7	2 	3O				A19S0   					 
1997050100348	19970501	00348	GL  	1997	5	1	97ZZZX1905       	3	19970324	G	6114	C93	HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 2 SOCKET	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	2666J		1689 			340A0718		791048		DURING PROPELLER INSPECTION A CRACK WAS FOUND IN THE THREADS OF BLADE SOCKET NR 2 ON THE ENGINE SIDE.						1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997050100349	19970501	00349	CE  	1997	5	1	97ZZZX1906       	1	19970403	G	5412	051310929	DOUBLER         			CESSNA	172   	172P        	2072436	CE  										FIREWALL LT	CORRODED        	B	P		R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	62258	7458 				17275236				DURING ANNUAL INSPECTION, CORROSION NOTED AT UPPER LT ENG MOUNT TO FIREWALL ATTACH POINT.  FIREWALL DOUBLER BADLY CORROD	ED.  DOUBLER REMOVED AND SEVERE CORROSION FOUND ON REVERSE SIDE.  FIREWALL WAS SALVAGED AND NEW DOUBLER WAS INSTALLED. D	OUBLER WAS INSTALLED AT FACTORY WITH STEEL TUBULAR MS 20450C8 RIVETS AND CANNOT BE SUBSTITUTED PER CESSNA FACTORY REP.  	INFORMATION ON REPLACING DOUBLER NOT IN CESSNA MM.  CESSNA FIELD SERVICE MUST BE CONTACTED.  AREA OF CORROSION ADJACENT 	TO LEAD ACID BATTERY.  SUBMITTER SUGGESTED INSPECTION OF THIS AREA AND REMOVE DOUBLER IF ANY EXTERNAL CORROSION FOUND.		1	H	7	1 	3O			NT	3A12    					 
1997050100350	19970501	00350	SO  	1997	5	1	97ZZZX1907       	1	19970307	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										LT ENGINE	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	851ND	4290 				4495005				DURING SCHEUDLED INSPECTION, FOUND LEFT ENGINE MOUNT BROKEN.  CRACK/BREAK IS AT 5 O'CLOCK LOWER DIAGONAL TUBE ON TOP RIG	HT MOUNT.  CRACK/BREAK IS ALONG WELD WHERE DIAGONAL TUBE IS WELDED TO MOUNT RING.  NEW PART ON ORDER.					1	L	7	2 	3O				A19S0   					 
1997050100351	19970501	00351	SO  	1997	5	1	97ZZZX1908       	1	19970312	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										LT ENGINE	CRACKED         	B	S		OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	854ND	4099 				4495008				LEFT ENGINE MOUNT WAS FOUND CRACKED.  CRACK WAS ON TOP RIGHT MOUNT RING AT WELD WHERE TUBE FROM FIREWALL MEETS MOUNT RIN	G.  C/W PIPER SB 937 PREVIOUSLY.  CRACK WAS DETECTED WITHOUT REMOVING PAINT FROM MOUNT.  INSPECTION FREQUENCY INCREASED 	BY OPERATOR.				1	L	7	2 	3O				A19S0   					 
1997050100352	19970501	00352	SO  	1997	5	1	97ZZZX1909       	1	19970312	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										LT/RT ENGINES	CRACKED         	B	S		OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	855ND	3951 				4495009				FOUND LEFT AND RIGHT ENGINE MOUNTS CRACKED.  CRACKS WERE LOCATED ON TOP RIGHT MOUNT WHERE MOUNT RING AND TUBE FROM FIREW	ALL ARE WELDED.  CRACK WAS ALONG EDGE OF WELD.  CRACKS WERE NOT DETECTABLE UNTIL PAINT WAS REMOVED AND INSPECTION AIDS W	ERE USED.  OPERATOR HAS INCREASED INSPECTION FREQUENCY.				1	L	7	2 	3O				A19S0   					 
1997050100353	19970501	00353	SO  	1997	5	1	97ZZZX1910       	1	19970310	G	7120	8936102	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										LT ENGINE	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	852ND	4714 				4495006				FOUND LEFT ENGINE UPPER RIGHT MOUNT CRACKED WHERE TUBE WELDS TO MOUNT RING AT 5 O'CLOCK POSITION.  CRACK RUNS ALONG EDGE	 OF WELD.  MOUNT WAS PREVIOUSLY MODIFIED PER PIPER SB 937.					1	L	7	2 	3O				A19S0   					 
1997050100401	19970501	00401	GL  	1997	5	1	97ZZZX1911       	1	19970301	G	5610	28011302212	WINDSHIELD      			ENSTRM	F28   	280C        	3300505	GL  										RT COCKPIT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	122TV					1049				OUTSIDE AIR TEMP (27 DEGREES FAHRENHEIT).  ON ENGI\EEN START-UP, WINDHSIELD CRACKED HORIZONTALLY APROXIMATELY 14 INCHES 	ONE-THIRD OF THE WAY UP FROM BOTTOM.  CRACK ORIGINATED AT CENTER WINDSHIELD ATTACH RIVET.					1	G	7	1 	3O				H1CE    					 
1997050100402	19970501	00402	CE  	1997	5	1	97ZZZX1912       	1	19970411	G	7830	2250012511	THRUST REVERSER 			BEECH 	MU300 	400A        	1155402	CE  										FORMER RING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	200BL	2512 			2465	RK23				AFT FAN DUCT FORMER RING CRACKED IN VICINITY OF SUPPORT BEAM MOUNT.  SUSPECT CAUSE FATIGUE.						2	H	7	2 	4F			RT	A16SW   					 
1997050100403	19970501	00403		1997	5	1	97ZZZX1913       	2	19970410	G	7414	M3827	ROTOR GEAR      	SLICK       	4371        															MAGNETO	LOOSE           	B			KC2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	03					91100139					THE ROTOR GEAR LOOSENED ON ROTOR SHAFT DUE TO NORMAL WEAR AND THERMAL CYCLING.  THE GEAR THEN RUBBED THE DISTRIBUTOR BLO	CK GENERATING NYLON PARTICLES THAT CONTAMINATED THE CONTACTS.  THIS RENDERED THE MAGNETO INOPERATIVE.  THIS ROTOR GEAR I	S A PRESS FIT ON THE ROTOR AND NO MECHANICAL RETENSION IS USED.																	 
1997050100404	19970501	00404		1997	5	1	97ZZZX1914       	2	19970407	G	7414	N3525	COIL            	SLICK       	4271        															MAGNETO	FAILED          	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		382  			88100154					FOUND COIL IN MAGNETO HAS OPEN SECONDARY CIRCUIT.  THIS PART NUMBER COIL IS USED IN  MANY MAGNETO MODELS.  SUBMITTER STA	TED SEEING THIS PROBLEM IN MANY COILS MANUFACTURED IN THIS SAME TIME FRAME.																		 
1997050100405	19970501	00405		1997	5	1	97ZZZX1915       	4	19970411	G	3416	3431	CASTING         		5934P1      	CESSNA	177   	177B        	2073708	CE  										ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	17142				G4042	17702507				INCOMING INSPECTION CHECKS ON ALTIMETER REVEALED JUMPS IN THE OPERATION OF 100 FEET TO 200 FEET. THE END-SHAKES ON THE M	ECHANISM SHAFTS WERE MEASURED.  ONE END-SHAKE MEASURED ZERO.  THE OH MANUAL CALLS OUT A MINIMUM END-SHAKE OF .0020 INCH 	ON ALL THREE CRITICAL ROTATING SHAFTS.  BECAUSE OF THIS ZERO END-SHAKE CONDITION, FOUND THE JUMPY CONDITION AT ROOM TEMP	, AND THE INSTRUMENT WOULD HANG UP THE POINTERS WHEN OPERATED IN A COLD ENVIRONMENT.  THE MANUFACTURER  INDICATED THAT A	 SHAFT END-SHAKE OF .0004 INCH OR LESS WILL CAUSE AN INSTRUMENT HANG-UP UNDER COLD OPERATING CONDITIONS ACCORDING TO THE	IR TESTING.	1	H	7	1 	3O				A13CE   					 
1997050100407	19970501	00407	EA  	1997	5	1	97ZZZX1917       	2	19970417	G	8520	LW18639	LOCKPLATE       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CRANKSHAFT GEAR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	4863H	1551 				15283989	L2045515			SEE LYCOMING O-235 SERIES PARTS CATALOG PC-302, FIGURE 3, INDEX 9.  WHILE TROUBLESHOOTING EXCESSIVE MAGNETO DROP AND INS	UFFICIENT STATIC RPM, DISCOVERED SCREW (STD 2213) HAD BACKED OUT OF CRANKSHAFT. THE LOCKPLATE EARS WERE FOUND IN THE OIL	 SUMP; THE CRANKSHAFT GEAR (13S19646) AND DOWEL (STD 1065) WERE WORN BEYOND LIMITS.  THE ENGINE HAD BEEN OVERHAULED SEVE	N YEARS PRIOR TO THIS EVENT; THE LOGBOOK ENTRY STATES, 'ASSEMBLED CRANKSHAFT GEAR ON CRANKSHAFT IAW LYCOMING SB NR 475. 	 USED A NEW BOLT AND LOCKPLATE, FINAL TORQUES TO 204 INCH/POUND.....'.		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997050100408	19970501	00408		1997	5	1	97ZZZX1918       	4	19970411	G	3416	3431	CASTING         		5934P1      	CESSNA	172   	172L        	2072432	CE  										ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	59PG				H4059	17260347				THE END-SHAKES, (BACK AND FORTH MOVEMENT) OF THE THREE CRITICAL ROTATING SHAFTS OF THE MECHANISM OF THIS ALTIMETER WERE 	CHECKED.  THE OH MANUAL CALLS OUT .0020 INCH MINIMUM END-SHAKE.  ONE END-SHAKE MEASURED .00020 INCH.  THIS IS TEN TIMES 	SMALLER THAN THE SPECIFICATION.  WITH THIS CONDITION, THE INSTRUMENT COULD HANG UP THE POINTERS OF THE ALTIMETER UNDER A	 COLD TEMPERATURE OPERATING CONDITION.  THE MANUFACTURER HAS INDICATED THAT AN END-SHAKE OF .0004 INCH OR LESS COULD CAU	SE A POINTER HANG UP UNDER COLD OPERATING CONDITIONS.		1	H	7	1 	3O			NT	3A12    					 
1997050100409	19970501	00409	SO  	1997	5	1	97ZZZX1919       	2	19970422	G	8520	653580	GEAR            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					CRANKSHAFT	FAILED          	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	6867L	400  				421C1087	608068			NEW CRANKSHAFT GEAR P/N 653580 INSTALLED AT TIME OF ENGINE OVERHAUL IN CONJUNCTION WITH TCM SB CSB 94-4 IN KIT EQ6642. E	NGINE FAILED APROXIMATELY 400.0 HOURS LATER.  ENGINE DISASSEMBLY REVEALED THE POSSIBILITY THE GEAR BROKE FIRST CAUSING D	AMAGE TO VALVE TRAIN, STARTER ADAPTER GEAR, AND IDLER GEAR.				1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997050100410	19970501	00410	SO  	1997	5	1	97ZZZX1920       	2	19970415	G	8520		CRANKCASE       			BEECH 	35    	S35         	1151532	CE  	CONT  	O520  	IO520B      	17032	SO  					NR 2 CYL BASE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	8604Q	2078 	940  			D7635	1219368B			DURING ANNUAL INSPECTION, CRANKCASE AT NR 2 CYLINDER BASE STUD FOUND CRACKED FOUR INCHES LONG.  THIS IS A LIGHT CASE ENG	INE.					1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997050100411	19970501	00411	SO  	1997	5	1	97ZZZX1921       	1	19970409	G	2721	419938	SCREW           			PIPER 	PA46  	PA46350P    		SO  										RUD TRIM WHEEL	DETACHED        	B	S	A	LF1R	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			EA	07	88846	308  				4622150				PILOT REPORTED COMPLETE CONTROL LOSS OF RUDDER TRIM SYSTEM:  AN INSPECTION, REVEALED THE THREE MOUNTING SCREWS HOLDING T	HE TRIM WHEEL TO THE SPROCKET HAD FALLEN OUT ALLOWING THE TRIM WHEEL TO SPIN FREE.  THE SCREWS WERE LOCATED ON THE FLOOR	 PANELS UNDER THE CONTROL QUADRANT.  SUBMITTER SUGGESTED TO ISSUE SB FOR INSPECTION.  ALSO, NEED TO CHANGE SCREW TYPE TO	 MACHINE SCREW.  ACFT TT:  308.1 HOURS.			1	L	7	1 	3O			RT	A25SO   					 
1997050800001	19970508	00001	EU  	1997	5	8	97ZZZX1923       	1	19970401	G	5310		STRUCTURE       			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										INTERIOR	CORRODED        	B			FG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										REPORT RECEIVED WHICH INDICATES THE EXTENSIVE USE OF FIRE RETARDANT CHEMICALS (BROMIDES AND SALINES) ON ACFT FABRICS, IS	 A MAJOR CAUSE OF STRUCTURAL CORROSION.					1	L	7	1 	30			NT	A51EU   					 
1997050800002	19970508	00002	SO  	1997	5	8	97ZZZX1924       	1	19970402	G	3230	6720000	SPRING          			PIPER 	PA34  	PA34200T    	7103406	SO  										LT  MLG	WEAK            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	19TP	4000 				347870383				LANDING GEAR DOWN LIGHT SLOW COMING ON.  LEFT GEAR FELT LOOSE ON LANDING.  WEAK SPRINGS ON BOTH GEAR.  SUBMITTER STATED 	DOWNLOCK SPRINGS SHOULD BE REPLACED EVERY 2,000 HOURS OR 2,000 CYCLES.					1	L	7	2 	3O				A7SO    					 
1997050800003	19970508	00003	CE  	1997	5	8	97ZZZX1925       	1	19970408	G	7921	8406J	COOLER          			CESSNA	177   	177RG       	2073709	CE  										ENGINE OIL	FAILED          	D				K				NONE                    				K			FLUID LOSS                			AP	APPROACH       	1			NM	01	1958Q		99   			177RG0358				AIRCRAFT WAS IN DOWN WIND FOR LANDING WHEN STUDENT NOTICED 'WET' GEAR LEG AND WHEEL.  UPON EXAMINATION, FOUND OIL COOLER	 SUFFERED INTERNAL FAILURE, LOSS OF SUBSTANTIAL OIL.  SUBMITTER STATED ENGINE FAILURE WOULD HAVE BEEN IMMINANT.  OUTSIDE	 TEMP 58 DEGREES.				1	H	7	1 	3O				A20CE   					 
1997050800004	19970508	00004	SO  	1997	5	8	97ZZZX1926       	1	19970217	G	7160	3551506	HEAT VALVE      			PIPER 	PA28  	PA28161     	7102803	SO  										CARBURETOR HEAT	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3858M	1650 				287816628				DURING ANNUAL INSPECTION, FOUND CARBURETOR HEAT VALVE MISSING SEAL MATERIAL.  ALSO, WHERE ASSY ATTACHED TO ALUMINUM PLAT	E, RIVETS WERE LOOSE AND WORKING.  REPLACED WITH NEW SEAL AND LARGER RIVETS.  SUBMITTER RECOMMENDED TO WATCH CLOSELY DUR	ING INSPECTIONS.  SUSPECT CAUSE IS HEAVY STEEL VALVE ASSEMBLY ATTACHED TO ALUMINUM PLATE WITH AN470-3 RIVETS.  NOT SUFFI	CIENT TO PREVENT VIBRATION AND LOOSENING OF RIVETS.			1	L	7	1 	3O				2A13    					 
1997050800005	19970508	00005	CE  	1997	5	8	97ZZZX1927       	1	19970310	G	2510	1414115	CAM             			CESSNA	185   	A185F       	2072821	CE  										SEAT BACK	CRACKED         	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	3868Q					18502205				ORDERED NEW SEAT BACK CAM FROM FACTORY.  UNIT RECEIVED HAD CRACK ON ONE-HALF OF ASSY NEXT TO ATTACH RIVET.  RETURNED TO 	FACTORY.					1	H	7	1 	3O				3A24    					 
1997050800007	19970508	00007		1997	5	8	97ZZZX1929       	4	19970228	G	6113	C22831	BULKHEAD        			PIPER 	PA34  	PA34200T    	7103406	SO  										PROP SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4516F					347670340				RECEIVED PROPELLER AND BULKHEAD FROM OVERHAUL FACILITY.  DURING INSTALLATION, DISCOVERED BULKHEAD CRACKED FROM ANCHOR NU	T ON FLANGE TO BULKHEAD DOUBLER.  IT HAD BEEN PREVIOUSLY STOP DRILLED.  REPLACED BULKHEAD WITH SERVICABLE UNIT.  OVERHAU	L FACILITY STATED THEY WERE AWARE OF IT, BUT DID NOTHING.				1	L	7	2 	3O				A7SO    					 
1997050800008	19970508	00008	CE  	1997	5	8	97ZZZX1930       	1	19970405	G	3230	35815109	UPLOCK CABLE    			BEECH 	35    	V35         	1151538	CE  										LT MLG	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	7586L					D8289				DURING INSTALLATION OF OXYGEN SYSTEM, OBSERVED INBD END OF LEFT LANDING GEAR UPLOCK CABLE SEVERELY FRAYED AT THE TERMINA	L END WHERE IT EXITS THE HOUSING:  SUBMITTER SUSPECTS OLD AGE AND LACK OF LUBRICATION.  SUBMITTER RECOMMENDS FREQUENT IN	SPECTION OF BOTH MLG UPLOCK CABLES AND PREVENTATIVE LUBRICATION EACH 100 HOURS.				1	L	7	1 	3O				3A15    					 
1997050800010	19970508	00010	CE  	1997	5	8	97ZZZX1932       	1	19970402	G	2750	500000862	CONTROL CABLE   			CESSNA	425   	425         	2076018	CE  										RT FLAP EXTEND	FAILED          	B		A	PRIR	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	03	67726	3049 				0030				PILOT REPORATED WHILE ON APPROACH, FULL FLAPS WERE SELECTED.  AT THAT TIME, A LOUD NOISE WAS HEARD AND THE A/C VIOLENTLY	 ROLLED TO THE RIGHT.  THE PILOT REGAINED CONTROL OF THE A/C BY RAISING THE FLAPS AND MADE A SAFE LANDING.  UPON INSP FO	UND RT FLAP HANGING DOWN AND LOOSE.  FURTHER INVESTIGATION DISCLOSED RT FLAP EXT CABLE BROKE AT PRESELECT CABLE ATTACH P	OINT.  THE FLAP GEARBOX WAS SEVERELY DAMAGED AND LIMIT SWITCH ARM SHAFT WAS BROKEN OFF.  ALL FLAP PUSH RODS WERE FOUND B	ENT FROM THE RETRACTION.  IT IS BELIEVED THE EXTEND CABLE BROKE AT THE PRESELECT CABLE LEAVING FLAPS UNCONTROLLABLE.  GE	ARBOX REPLACED AND ALL PUSH RODS REPLACED AND ALL CABLES RERIGGED.	1	L	7	2 	3T			RT	A7CE    					 
1997050800012	19970508	00012	EA  	1997	5	8	97ZZZX1934       	2	19970401	G	8530	75838	VALVE GUIDE     			ENSTRM	F28   	F28C        	3300407	GL  	LYC   	O360  	HIO360E1BD  	41514	EA  					NR 4 CYLINDER	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	17	5691Y	566  				4792	L1981551A			EXHAUST VALVE GUIDE BROKE UP LETTING THE EXHAUST VALVE LOOSEN IN THE CYLINDER.  EXHAUST VALVE DID NOT FAIL.  PIECES FROM	 THE GUIDE JAMMED THE TURBOCHARGER TURBINE WHEEL DESTROYING THE TURBOCHARGER AND CAUSING LOSS OF POWER.					1	G	7	1 	3O	3	O		H1CE    	1E10				 
1997050800013	19970508	00013		1997	5	8	97ZZZX1935       	1	19970401	G	5741	6862102	ATTACH FITTING  																	AFT WING ATTACH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										A COMMON WATER CORROSION PROBLEM HAS BEEN FOUND WITH THESE SERIES OF AIRCAFT.  ALMOST WITHOUT EXCEPTION, WATER HAS BEEN 	ENTERING THE INTERIOR OF THE CABIN AT FS 187.84 AND FS 138.63.  THEN WATER IS ABSORBED BY THE INSULATION AND CARPET.  TH	IS CREATES A POTENTIALLY SERIOUS CORROSION PROBLEM WITH THE REAR WING ATTACH FITTINGS AND THE ANGLE AT STA 128.  IT APPE	ARS THAT WATER IS ABLE TO ENTER THROUGH THE OUTER SKIN LAP JOINTS.  SEALING OF THESE JOINTS MAY HELP PREVENT FUTURE WATE	R INTRUSION.															 
1997050800014	19970508	00014		1997	5	8	97ZZZX1936       	1	19970401	G	5741	6862103	ATTACH FITTING  																	AFT WING ATTACH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										A COMMON WATER CORROSION PROBLEM HAS BEEN FOUND WITH THESE SERIES OF AIRCAFT.  ALMOST WITHOUT EXCEPTION, WATER HAS BEEN 	ENTERING THE INTERIOR OF THE CABIN AT FS 187.84 AND FS 138.63.  THEN WATER IS ABSORBED BY THE INSULATION AND CARPET.  TH	IS CREATES A POTENTIALLY SERIOUS CORROSION PROBLEM WITH THE REAR WING ATTACH FITTINGS AND THE ANGLE AT STA 128.  IT APPE	ARS THAT WATER IS ABLE TO ENTER THROUGH THE OUTER SKIN LAP JOINTS.  SEALING OF THESE JOINTS MAY HELP PREVENT FUTURE WATE	R INTRUSION.															 
1997050800015	19970508	00015		1997	5	8	97ZZZX1937       	1	19970401	G	5320	6864400	ANGLE           																	BS 128	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										A COMMON WATER CORROSION PROBLEM HAS BEEN FOUND WITH THESE SERIES OF AIRCAFT.  ALMOST WITHOUT EXCEPTION, WATER HAS BEEN 	ENTERING THE INTERIOR OF THE CABIN AT FS 187.84 AND FS 138.63.  THEN WATER IS ABSORBED BY THE INSULATION AND CARPET.  TH	IS CREATES A POTENTIALLY SERIOUS CORROSION PROBLEM WITH THE REAR WING ATTACH FITTINGS AND THE ANGLE AT STA 128.  IT APPE	ARS THAT WATER IS ABLE TO ENTER THROUGH THE OUTER SKIN LAP JOINTS.  SEALING OF THESE JOINTS MAY HELP PREVENT FUTURE WATE	R INTRUSION.															 
1997050800402	19970508	00402	NE  	1997	5	8	97ZZZX1938       	2	19970416	G	7250	657803	T3 DISK         			BELL  	206   	206B        	1181511	SW  	PWA   	JT3D  	JT3D3B      	52039	NE  					TIE ROD HOLES	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	30VA	12935				3229	P645748			DURING ROUTINE DISASSEMBLY AND ENGINE BUILD-UP, AD 82-14-02 WAS C/W ON T-3 DISK.  DURING EDDY CURRENT INSPECTION, FOUND 	2 TIE ROD HOLES HAD CRACKS RADIATING FROM HOLES INTO DISK.  DISK WAS REMOVED FROM SERVICE AND SCRAPPED.  CYCLES, 6,623.					1	G	7	1 	3U	4	F		H2SW    	1E8				 
1997050800403	19970508	00403	SW  	1997	5	8	97ZZZX1939       	1	19970313	G	6320	2040401431	BEARING         		204040016005	BELL  	204   	UH1B        	1181410	SW  										TRANSMISSION	SPALLED         	B			QJ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	600MA		976  		2202A	6413970				SPALLING ON BALLS AND OUTER RACE OF BEARING.  THIS BEARING IS USED IN SEVERAL DIFFERENT APPLICATIONS IN THE DRIVE TRAIN 	OF BELL HELICOPTERS.					1	G	7	1 	4U				EXPA1G71					 
1997050800404	19970508	00404	SW  	1997	5	8	97ZZZX1940       	1	19970212	G	6310	214040841101	SEAL            		406040500113	BELL  	206   	206L4       	1182110	SW  										FREEWHEEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	696BA	130  			A2944	52166				REPLACED FREEWHEELING UNIT TAIL ROTOR OUTPUT DRIVE SEAL DUE TO LEAKING OIL.  ACFT TT: 317.6 HOURS.						1	G	7	1 	3U			NC	H2SW    					 
1997050800405	19970508	00405	SW  	1997	5	8	97ZZZX1941       	1	19970412	G	6310	214040841101	SEAL            		406040500113	BELL  	206   	206L4       	1182110	SW  										FREEWHEEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	696BA	67   			A2944	52166				REPLACED FREEWHEELING UNIT TAIL ROTOR OUTPUT DRIVE SEAL DUE TO LEAKING OIL.  ACFT TT:  384.2 HOURS.						1	G	7	1 	3U			NC	H2SW    					 
1997050800406	19970508	00406		1997	5	8	97ZZZX1942       	4	19970418	G	2561	KS9	LIFE VEST       	EAAEROMARINE																INFLATE SEC	FAIL TEST       	B			GP4R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	13					C21391					LIFE VEST FAILED MANUFACTURER'S 2 PSI INFLATION TEST.																			 
1997050800407	19970508	00407	NE  	1997	5	8	97ZZZX1943       	3	19970113	G	6111	792221	BLADE           		SFA13M10A   											HAMSTD	14SF	14SF7       	NE  	SHANK	CRACKED         	B			H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		14911	8935 		855906					DURING A MAJOR INSPECTION DYE CHECK, AN INDICATION WAS DETECTED IN THE BLADE SHANK FILLET RADIUS.  THE INDICATION IS CIR	CUMFERENTIALLY LOCATED APPROXIMATELY 135 DEGREES FROM THE BLADE PIN, ON THE FACE SIDE.  THE SHAPE OF THE INDICATION IS R	ECTANGULAR, WITH HALF OF IT LOCATED IN THE FILLET RADIUS, AND HALF ON THE SHANK OUTSIDE DIAMETERS, WITH BOTH HALVES CONN	ECTED AT EACH END.													6	C	P7NE	 
1997050800408	19970508	00408	GL  	1997	5	8	97ZZZX1944       	3	19970324	G	6111	FC84686R	BLADE           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	BLADE SHANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		4029 	935  					C20315		UPON INSPECTION OF PROPELLER BLADE DURING OVERHAUL, FOUND 1 INCH LONG CRACK IN BLADE SHANK FILLET.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997050800409	19970508	00409	SO  	1997	5	8	97ZZZX1945       	1	19970422	G	2434	ALU9510	ALTERNATOR      	PRESTOLITE  		PIPER 	PA31  	PA31P       	7103120	SO  										DC SYSTEM	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	26556	185  			A113559	31P7400184				ALTERNATOR FAILED AT 5-1/2 MONTHS AND 185.3 HRS TT.  WAS OVERHAULED 9-19-96.  CONTINUE TO HAVE VERY SHORT SERVICE LIFE O	F THESE UNITS.					1	L	7	2 	3O				A8EA    					 
1997050800410	19970508	00410	EA  	1997	5	8	97ZZZX1946       	2	19970402	G	7314	RG17980J	PUMP            	ROMEC       		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					ENGINE FUEL	LEAK            	D		A		O				OTHER                   				K	A		FLUID LOSS                	FLAME/FIRE                		TO	TAKEOFF        	1			SO	03	27FM	1100 	1100 		B8608	277654087	L416961A			PUMP LEAKAGE AT SEAM CASE TO PUMP.  PUMP LEAKAGE OCCURRED AT TAKEOFF.  SPRAYED FUEL DIRECTLY ON HOT TURBOCHARGER CAUSING	 FIRE IN ENGINE COMPARTMENT.  APPEARED TO LEAK AT GASKET FLANGE.					1	L	7	2 	3O	3	O		1A10    	E14EA				 
1997050800413	19970508	00413	EA  	1997	5	8	97ZZZX1949       	2	19970324	G	8530		CYLINDER        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  					NR 2 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	55777	3993 	1762 			347350244	L71467A			NR 2 CYLINDER FOUND CRACKED AT THE MOLD LINE THROUGH THE SPARKPLUG HOLE OUT ONTO THE TOP OF THE CYLINDER, THE INTAKE SID	E, RIGHT ENGINE.					1	L	7	2 	3O	3	O		A7SO    	1E10				 
1997050800414	19970508	00414	EA  	1997	5	8	97ZZZX1950       	2	19970414	G	8520	SL13212M03	BEARING         			BEECH 	B80   	B80         	1153010	CE  	LYC   	O540  	IGSO540A1D  	41532	EA  					CONNECT ROD	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	65RW	775  				LD404	L240950			SECTIONS FROM THE CENTER OF THE BEARING APPEARED TO DETERIORATE OR DISSOLVE WITH NO APPARENT REASON.  QUALITY OF BEARING	 IS IN QUESTION.					1	L	7	2 	3O	3	O	RT	3A20    	1E7				 
1997050800415	19970508	00415	CE  	1997	5	8	97ZZZX1951       	1	19970429	G	3230	50120202143	ANGLE           			BEECH 	90    	F90         	1152909	CE  										MLG SUPPORT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	66BS	500  				LA40				LANDING GEAR SUPPORT BRACKET PART CRACKED VARIOUS PLACES.  PART REPLACED AT INSPECTION AND PROBLEM OCCURRED SAME PART 50	0 HOURS LATER IN SAME LOCATION.  EXACT PART LOCATION, LEFT AND RIGHT GEAR ANGLES.					1	L	7	2 	4T				A31CE   					 
1997050800416	19970508	00416	CE  	1997	5	8	97ZZZX1952       	1	19970416	G	2720	51152604	TORQUE TUBE     			CESSNA	401   	401A        	207590D	CE  										LT RUDDER PEDAL	FAILED          	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	671AW					401A0080				RUDDER SYSTEM CEASED TO OPERATE.  FOUND LEFT RUDDER TORQUE TUBE ASSY ARM BROKEN FREE OF TORQUE TUBE.  THIS ARM IS CONNEC	TED TO RUDDER CABLE.  REPLACED TORQUE TUBE WITH NEW PART.					1	L	7	2 	3O				A7CE    					 
1997050800417	19970508	00417	EA  	1997	5	8	97ZZZX1953       	2	19970304	G	8520	LW15949	GEAR TOOTH      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CRANKSHAFT	FAILED          	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	01	734JD	3050 	350  			17268882	RL323376T			ENGINE STARTED TO MAKE A KNOCKING NOISE WHILE IN-FLIGHT.  AS THE ENGINE WAS THROTTLED, BACK NOISE BECAME MORE PRONOUNCED	.  AIRCRAFT WAS LANDED AT NEAREST AIRPORT.  INVESTIGATION OF KNOCKING NOISE REVEALED THAT ONE TOOTH WAS MISSING FROM THE	 CRANKSHAFT GEAR.  ENGINE TIME SINCE FACTORY REMANUFACTURE APPROXIMATELY 3,050 HOURS.  TIME SINCE MAJOR OVERHAUL, APPROX	IMATELY 350 HOURS.  CRANKSHAFT GEAR WAS MAGNAFLUXED AT MAJOR OVERHAUL.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997050800418	19970508	00418	EA  	1997	5	8	97ZZZX1954       	2	19970401	G	7322	MA3	CARBURETOR      	FACET       		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					POWER JET	FOD PLUG        	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	68148					15282150	L1511415			AIRCRAFT LOST POWER DURING LOCAL FLIGHT.  STUDENT PILOT COULD ONLY GET 1200/1400 RPM'S, BUT MADE IT BACK TO AIRPORT.  AF	TER CHECKING FUEL STRAINERS, PROBLEM APPEARED TO BE IN CARBURETOR.  DISASSEMBLY REVEALED A SMALL INSECT IN THE NOZZLE PO	WER JET ASSEMBLY.  THE INSECT THE SIZE OF A PENCIL POINT COULD NOT HAVE PASSED THROUGH THE FUEL STRAINERS.  SUSPECT IT E	NTERED WHILE ACFT WAS PARKED , THROUGH AIR BOX, AND INTO NOZZLE.  TOTAL TIME ON CARBURETOR SINCE OVERHAUL, 836.0 HOURS.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997050800420	19970508	00420	CE  	1997	5	8	97ZZZX1956       	1	19970328	G	3230	CB2320A	BREAKER         			BEECH 	36    	A36         	1151604	CE  										MLG MOTOR	FAILED          	B			DC1R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	07	88ES	6219 				E758				LANDING GEAR MOTOR CIRCUIT BREAKER, WHEN RESET, NO LOAD WILL GO THROUGH BREAKER TO OPERATE MOTOR.  PILOT MANUALLY CRANKE	D LANDING GEAR DOWN.					1	L	7	1 	3O				3A15    					 
1997050800421	19970508	00421	SW  	1997	5	8	97ZZZX1957       	1	19970331	G	2430	PA10A06	WIRE            			MOONEY	M20   	M20J        	5870219	SW  										FIREWALL	SHORTED         	B		A	DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	195ER	5769 				243256				WHILE TROUBLESHOOTING AN INTERMITTENT/UNCOMMANDED, ON OR OFF, OF THE AVIONICS MASTER RELAY - ELECTRICAL ARCING WAS HEARD	.  INVESTIGATION REVEALED ALTERNATOR OUTPUT 'A+' SHIELDED WIRE NR PA10A06 (BETWEEN FIRE WALL AND FORWARD END OF RF FILTE	R) HAD RUBBED THROUGH INSULATION OF WIRE NR PB11A06 (AT UNSHIELDED WIRE BETWEEN AMPMETER SHUNT AND HOT SIDE OF START REL	AY).  THIS SHORT CIRCUIT BYPASSES ALL CIRCUIT BREAKER PROTECTION.			1	L	7	1 	3O			 	2A3     					 
1997050800422	19970508	00422	SO  	1997	5	8	97ZZZX1958       	1	19970221	G	7920	111F4176S0120	HOSE            	STRATOFLEX  	1116        	AMRGEN	AG5B  	AG5B        	3990100	SO  										OIL COOLER	OBSTRUCTED      	B	S		PF2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	128VU					10067				HOSE PURCHASED NEW FROM AVIALL, NOVEMBER, 1996.  DURING TEST FLIGHT, OIL TEMP NOTED EXCESSIVE.  RESULTS OF INVESTIGATION	, OIL COOLER RETURN FLOW LINE FOUND OBSTRUCTED.  APPEARS LINE MAY HAVE MFG DEFECT.					1	L	7	1 	3O			NT	1L71    					 
1997050800423	19970508	00423	GL  	1997	5	8	97ZZZX1959       	3	19970421	G	6114		HUB             			CESSNA	206   	U206G       	2073356	CE  						MCAULY	3A32C	D3A32C90    	GL  	NR 2 SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2FOR					U2063807		773447		DURING EDDY CURRENT INSPECTION, TWO CRACKS FOUND IN NR 2 HOLE, 3RD AND 4TH THREADS IN AT 6 O'CLOCK.						1	H	7	1 	3O				A4CE    		5	C	P21EA	 
1997050800424	19970508	00424	CE  	1997	5	8	97ZZZX1960       	1	19970412	G	3230	353800943	MOTOR           			BEECH 	35    	H35         	1151520	CE  										MLG	BRUSHES WORN    	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			EA	21	5414D				1668	D4921				THE LANDING GEAR WAS EXTENDED DURING AN APPROACH INTO THE LYH AIRPORT.  PILOT REPORTED AN UNSAFE INDICATION (NO GREEN DO	WN/LOCKED LIGHT).  IT IS UNCLEAR IF THE EMERGENCY EXTENSION CYCLE WAS COMPLETED.  THE PILOT STATES HE NEVER GOT A GREEN,	 GEAR DOWN INDICATION.  UPON THE LANDING ROLL-OUT, LANDING GEAR COLLAPSED PARTIALLY.  DAMAGE WAS MINIMAL DUE TO THE INNE	R GEAR DOORS AND NOSE GEAR DOORS SUPPORTING MOST OF THE AIRCRAFT'S WEIGHT.  SUBMITTER RECOMMENDS GEAR MOTOR BRUSHES AND 	EMERGENCY EXTENSION SYSTEM BE CHECKED AND OPERATED EVERY ANNUAL OR 100 HOURS.		1	L	7	1 	3O				3A15    					 
1997050800425	19970508	00425	CE  	1997	5	8	97ZZZX1961       	1	19970401	G	3110	S2501	HOSE            			CESSNA	172   	172P        	2072436	CE  										INSTRUMENTS	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	62258	7458 				17275236				DURING ANNUAL INSPECTION, INSTRUMENT HOSE UNDER INSTRUMENT PANEL CRUMBLED WHEN TOUCHED.  HOSE IDENTIFIED AS THE SAME TYP	E HOSE MENTIONED IN CESSNA BULLETIN SEB 96-10.  THE REST OF THE SYSTEM INSPECTED AND ALL S2501 HOSES REPLACED.  HOSE COM	ING APART COULD CAUSE DEBRIS THAT CAUSES EARLY INSTRUMENT FAILURE.  HOSE FAILURES COULD CAUSE COMPLETE SYSTEM FAILURE. S	UBMITTER SUGGESTS MANDATORY COMPLIANCE OF CESSNA BULLETIN SEB 96-10, DATED 6-7-96.			1	H	7	1 	3O			NT	3A12    					 
1997050800426	19970508	00426	EU  	1997	5	8	97ZZZX1962       	2	19970215	G	7230	EU58621A	BLADE           			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					5TH STG COMP	BROKEN          	E				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	99	17ND		3041 			63	8552			CREW REPORTED HIGH ENGINE VIBRATION ON THE RIGHT ENGINE.  A BORESCOPE INSPECTION OF THE L.P. COMPRESSOR REVEALED A FIFTH	 STAGE L.P. COMPRESSOR BLADE DAMAGED (APPROXIMATELY THREE INCHES OF THE BLADE WAS BROKEN OFF).					2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
1997050800427	19970508	00427	CE  	1997	5	8	97ZZZX1963       	1	19970401	G	7110	40S459B	CAMLOC          			CESSNA	425   	425         	2076018	CE  										ENGINE COWL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5PP					4250198				DURING REMOVAL OF ENGINE COWL, ONE CAMLOC  DIFFICULT TO REMOVE.  CAMLOC FINALLY CAME OUT WHEN CROSS PIN FELL OUT.  THE C	ROSS PIN FELL INTO ENGINE INTAKE AIR PLENUM.  THE PIN WAS RECOVERED.  CAMLOC RECEPTACLE IS OF AN OPEN BACK TYPE AND LOCA	TED INSIDE INTAKE AIR PLENUM OF THE ENGINE.  IF PIN CAME OUT OR THE CAMLOC BROKE, THE PIECE WOULD LIKELY BE INGESTED BY 	ENGINE.  THIS CAMLOC ALSO SHOWED EVIDENCE OF POST MANUFACTURE STAKING TO RETAIN PIN.  CHANGE CAMLOC RECEPTACLES IN ENG I	NTAKE AIR PLENUM TO CLOSE BACK TYPE.  DO NOT TRY TO 'REPAIR' LOOSE PINS IN CAMLOCS, CHANGE CAMLOC INSTEAD.		1	L	7	2 	3T			RT	A7CE    					 
1997050800428	19970508	00428	WP  	1997	5	8	97ZZZX1964       	2	19970401	G	7250	8965841	SUPPORT ASSY    								GARRTT	TPE331	TPE3316252B 	01514	WP  					STG 1 TURBINE	MISOVERHAULED   	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										AFTER INSTALLATION OF SUPPORT ASSY, ENGINE MADE CHATTERING NOISE WHEN ROTATED.  DISASSEMBLY SHOWED IMPROPER MACHINING OF	 SUPPORT ALLOWING SEGMENTS TO CONTACT TURBINE WHEEL BLADES.  CAUSE:  IMPROPER REPAIR.  SUBMITTER SUGGESTS BETTER QUALITY	 CONTROL DURING REPAIR.									4	T			E2WE				 
1997051500001	19970515	00001	NM  	1997	5	15	97ZZZX1970       	1	19970428	G	3240	MIL5606	HYD FLUID       			UNIVAC	GC1   	GC1B        	9230104	NM  										BRAKE SYSTEM	CONGEALED       	D	L			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	03	3312K					1305				INVESTIGATION FOR GROUND HANDLING DIRECTIONAL CONTROL (GROUND LOOP) FOUND BRAKES AT FAULT.  WHEN THE BRAKE LINE WAS DISC	ONNECTED AT THE WHEEL CYLINDER AND BRAKE PRESSURE WAS APPLIED, A GOOEY SUBSTANCE WAS EXCRETED FROM THE BRAKE LINE.  THIS	 WAS ORIGINALLY 5606 'RED JUICE' THAT HAD CONGEALED.  ACFT HAS A RETRACTABLE, NON-STEERABLE TAIL WHEEL THAT REQUIRES SOM	E BRAKING FOR DIRECTIONAL CONTROL.  THE CONGEALED FLUID CAUSED A DELAY IN THE ACTION OF THE BRAKES, AND ANOTHER DELAY IN	 THE REMOVAL OF BRAKE APPLICATION.  NOT A GOOD SITUATION.		1	L	7	1 	3O				A766    					 
1997051500002	19970515	00002	NM  	1997	5	15	97ZZZX1971       	1	19970428	G	3240	MIL5606	HYD FLUID       			UNIVAC	GC1   	GC1B        	9230104	NM  										BRAKE SYSTEM	CONGEALED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	80772					172				MECH STARTED OVERHAUL ON AIRCRAFT HYDRAULICS.  FLAP ACTUATOR LOOKED GOOD, NO LEAKS.  ALL O-RINGS LOOKED GOOD, THAT IS NO	T SQUARED OFF, AND STILL PLIABLE.  FLUID CLEAN WITH A SLIGHT FILM RESIDUE ON THE BOTTOM OF ACTUATOR END PIECES.  REMOVAL	 OF THE BRAKE LINES AT THE WHEEL CYL INDICATED THE SAME CONGEALED PROBLEM THAT N NR 3312K HAD, BUT PROBABLY NOT QUITE AS	 CONGEALED.  THE 5606 BRAKE FLUID TOOK ABOUT TEN MINUTES FOR THE FIRST DROP TO COME OUT.  A COUPLE OF TABLESPOONS OF THI	S 'GOO' SLOWLY DRIPPED OUT BEFORE NORMAL FLUID FLOW STARTED.  THE LINE WAS A 601 AEROQUIP AND IS SUPPLYING FLUID TO CLEV	ELAND 30-79B BRAKE ASSEMBLIES, AND HAD BEEN INSTALLED FOR MORE THAN 10 YEARS WITHOUT THE NEED TO BLEED THE SYSTEM.	1	L	7	1 	3O				A766    					 
1997051500003	19970515	00003	CE  	1997	5	15	97ZZZX1972       	1	19970416	G	2140	719843	COIL            			CESSNA	310   	310R        	2074245	CE  										HEATER	EXPLODED        	B		A	BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	123RA		526  		8259HR2	310R0221				HEATER FOUND INOPERABLE.  FOUND THE IGNITION COIL HAD EXPLODED.  THE END CAP HAD COME OFF WITH ENOUGH FORCE THAT IT BENT	 THE IGNITER OVER; THE OPPOSITE REACTION CAUSED THE COIL CAN TO GO AFT AND BREAK WIRES OFF MISCELLANEOUS PARTS IN THE CO	IL COVER.  THE MOST SIGNIFICANT POINT WAS THAT FUEL WAS STILL BEING PUMPED INTO THE HEATER, BUT NOT BEING IGNITED.				1	L	7	2 	3O				3A10    					 
1997051500004	19970515	00004	SW  	1997	5	15	97ZZZX1973       	1	19970331	G	2497		WIRE            			MOONEY	M20   	M20J        	5870219	SW  										FIREWALL	BURNED          	B			DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	195ER	5769 				243256				WHILE TROUBLESHOOTING AND REPAIRING INOPERABLE PANEL LIGHTS, DISCOVERED NUMEROUS ELECTRICAL WIRES BURNED AND SHORTED.  T	HE PANEL LIGHTS FAULT WAS WORN THROUGH INSULATION BY ADJACENT LIKE TYPE WIRES IN MID-HARNESS, WORN AND BURNED SEVERAL PL	ACES WITHIN THE HARNESS.  ALSO DISCOVERED WORN, CUT, AND BURNED WIRES IN SAME HARNESS TO OTHER SYSTEMS CONTAINED IN THE 	BUNDLE.			1	L	7	1 	3O			 	2A3     					 
1997051500005	19970515	00005	EA  	1997	5	15	97ZZZX1974       	2	19970417	G	7414	LW68504611085	MAGNETO         	ELECTROSYS  	D6RN320     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENGINE	GEAR FAILED     	E				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	3536B		660  		6080503	317952205	RL191768A			INTERNAL DRIVE GEARS FAILED ON BOTH THE LEFT AND RIGHT SIDES OF THIS 'DUAL STYLE' MAGNETO ASSEMBLY, MODEL NR D6RN-3200. 	 AIR CREW WAS TAXIING AIRCRAFT WHEN RIGHT POWERPLANT STOPPED RUNNING.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997051500007	19970515	00007	CE  	1997	5	15	97ZZZX1976       	1	19970417	G	5311		FRAME           			CESSNA	172   	172M        	2072418	CE  										DOOR POST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4574V	5338 				17266358				FOUND BOTH AFT LOWER DOOR POST FRAMES CRACKED WHILE C/W SEB 97-1.  INSTALLED SK172-149-1 AND SK172-149-2 TO REPAIR.  INS	TRUCTIONS CALL FOR THIS TO BE A 1,000 HOUR REPETITION INSPECTION.  SUBMITTER STATED THAT IS MUCH TOO LONG.  SHOULD BE IN	CLUDED ON EACH ANNUAL AT LEAST.				1	H	7	1 	3O			NT	3A12    					 
1997051500008	19970515	00008	CE  	1997	5	15	97ZZZX1977       	1	19970401	G	2810	F39172	VALVE           			CESSNA	172   	172N        	2072434	CE  										FUEL TANK	LEAK            	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	6317F					17273189				NEW FUEL TANK DRAIN VALVES START DRIPPING APPROXIMATELY TWO AND THREE DAYS AFTER INSTALLATION.  NO DEBRIS OR PARTICLES D	RAIN FROM FUEL TANK.  HOLDING VALVE UNSEATED.  O-RINGS LOOKED GOOD.  EACH PART HAD 8130-3 FORM ATTACHED.  ALL MANUFACTUR	ED 1993 OR LATER.  SUBMITTER STATES HAVE REPLACED ABOUT SIX VALVES IN 18 MONTHS.				1	H	7	1 	3O			NT	3A12    					 
1997051500009	19970515	00009	CE  	1997	5	15	97ZZZX1978       	1	19970401	G	2810	S21062	VALVE           			CESSNA	172   	172N        	2072434	CE  										FUEL TANK	LEAK            	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	6317F					17273189				NEW FUEL TANK DRAIN VALVES START DRIPPING APPROXIMATELY TWO AND THREE DAYS AFTER INSTALLATION.  NO DEBRIS OR PARTICLES D	RAIN FROM FUEL TANK.  HOLDING VALVE UNSEATED.  O-RINGS LOOKED GOOD.  EACH PART HAD 8130-3 FORM ATTACHED.  ALL MANUFACTUR	ED 1993 OR LATER.  SUBMITTER STATES HAVE REPLACED ABOUT SIX VALVES IN 18 MONTHS.				1	H	7	1 	3O			NT	3A12    					 
1997051500010	19970515	00010	EA  	1997	5	15	97ZZZX1979       	2	19970227	G	7322	105135	CARBURETOR SCREW			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	LOOSE           	D				O				OTHER                   				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	05	7729G	199  			CK13350	17259429	L1753927A			IDLE ADJUSTMENT SCREW BACKED OUT OF CARBURETOR IN-FLIGHT.  ENGINE FAILED TO RUN WITH POWER SETTING BELOW 2300 RPM'S.  IN	STALLED NEW SPRING AND SCREW.  CARBURETOR THREADS APPEAR TO BE LOOSE.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997051500011	19970515	00011	SO  	1997	5	15	97ZZZX1980       	1	19970325	G	2720	6342008	BAR ASSY        			PIPER 	PA28  	PA28181     	7102807	SO  										LT RUDDER	CRACKED         	D	P	A		O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			SW	09	8367T	3445 				28190209				WHILE MAKING A RIGHT CROSS-WIND LANDING, RUDDER FELT MUSHY AND WOULD ONLY MOVE THE 5 DEGREES LEFT.  INSPECTION REVEALED 	THE LEFT RUDDER BAR HAD CRACKED ALMOST COMPLETELY AT THE POINT WHERE THE STRAIGHT TUBING IS WELDED TO THE CURVED TUBING 	AND REINFORCED WITH A WELDED BRACE.  THREE CRACKS EMANATED FROM AN OILING HOLE, RADIALLY, THEN LONGITUDINALLY TO THE LEF	T .3750 INCH, THEN CRACKED AROUND THE CIRCUMFERENCE OF THE TUBE.  TO PREVENT RECURRENCE IF EVIDENCE OF HARD LANDING DAMA	GE EXISTS, THE RUDDER BARS SHOULD BE REMOVED AND CHECKED FOR BENDS.		1	L	7	1 	3O				2A13    					 
1997051500012	19970515	00012	SO  	1997	5	15	97ZZZX1981       	1	19970415	G	3230	6718900	SPRING          			PIPER 	PA28  	PA28RT201T  	7102817	SO  										NLG DOWNLOCK	FAILED          	B	S		CS3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17										NEW SPRING WITHDRAWN FROM STOCK.  INSTALLED ON NOSE LANDING GEAR DOWNLOCK ASSY.  SPRING SNAPPED FIRST CYCLE OF RETRACTIO	N CHECK.					1	L	7	1 	3O				2A13    					 
1997051500013	19970515	00013	CE  	1997	5	15	97ZZZX1982       	1	19970422	G	2913	99101372	PUMP            			CESSNA	414   	414A        	2075907	CE  										RT ENGINE HYD	LEAKING         	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	13	5614C	277  			831	414A0203				PILOT REPORTED BOTH LEFT AND RIGHT HYDRAULIC FLOW LIGHTS ON THE CAUTION PANEL WERE ILLUMINATED.  LANDING GEAR WAS EXTEND	ED USING THE EMERGENCY EXTENSION PROCEDURE.  AIRPLANE LANDING WITHOUT INCIDENT.  FLUID DISCOVERED LEAKING FROM RIGHT ENG	INE NACELLE DRAIN.  DISCOVERED THE RIGHT HYDRAULIC PUMP SHAFT SEAL HAD FAILED ALLOWING HYDRAULIC FLUID TO BE PUMPED OVER	BOARD.  HYDRAULIC PUMP WAS REPLACED.  LANDING GEAR EMERGENCY BLOW-DOWN SYSTEM SERVICED AND THE LANDING GEAR OPERATIONAL 	CHECK C/W IAW CESSNA SM.  AIRPLANE RETURNED TO SERVICE.  PUMP P/N 9910137-2, S/N 831, HAD 227.1 HOURS TOTAL TIME SINCE N	EW.	1	L	7	2 	3O				A7CE    					 
1997051500014	19970515	00014	EA  	1997	5	15	97ZZZX1983       	2	19970415	G	7322	30628	FLOAT           	PRECISION   	MA3A        	CESSNA	120   	120         	2071402	CE  	LYC   	O235  	O235C1      	41505	EA  					CARBURETOR	FAILED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	76381	1100 			Y7FG2092	10802	L868215			AFTER OPENING UP CARBURETOR TO REPLACE TWO-PIECE VENTURI, NOTICED FLOAT WAS BRO KEN, ONE-HALF OF IT LAYING IN BOWL.  REP	LACED WITH NEW METAL TYPE.					1	H	7	1 	3O	3	O		A768    	E223				 
1997051500015	19970515	00015	SO  	1997	5	15	97ZZZX1984       	1	19970401	G	2410	635796	COUPLING        			PIPER 	PA28  	PA28RT201T  	7102817	SO  										ALTERNATOR DRIVE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	83047	268  				28R8131038				ALTERNATOR DRIVE COUPLING IS VIBRATION DAMPED BY RUBBER BONDED TO SHAFT AND OUTER HOUSING.  RUBBER SEPARATED FROM OUTER 	HOUSING.  SECOND FAILURE ON THIS TYPE AIRCRAFT SERVICED BY THIS AGENCY IN LAST 12 MONTHS.  PART IS ALSO VERY EXPENSIVE. 	 SUGGEST GOING BACK TO PREVIOUS DESIGN USING DRIVE BLOCKS LIKE MAGNETO DRIVES.				1	L	7	1 	3O				2A13    					 
1997051500016	19970515	00016		1997	5	15	97ZZZX1985       	4	19970423	G	3421	500E1	GYRO            	SIGMATEK    		PIPER 	PA34  	PA34200     	7103405	SO  										COCKPIT ATTITUDE	MISOVERHAULED   	B			IP6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	56730		50   		21712H	347450027				POOR OPERATION OF AUTOPILOT GYRO.  FOUND LAST OVERHAUL WAS NOT PROPER.  ROTOR BEARINGS HAVE EXCESSIVE PRELOAD.  PENDULUM	S HAVE BEEN ALTERED.  ADDITIONAL CERAMIC PENDULUM STOPS ADDED BY ALTERING BOTTOM PLATE.  HORIZON ARM RUBBING AT LEVEL FL	IGHT POSITION AGAINST PIN CASTING.				1	L	7	2 	3O				A7SO    					 
1997051500017	19970515	00017	NM  	1997	5	15	97ZZZX1986       	1	19970221	G	2700	126344171	PNEU DRIVE UNIT 	ALIDSIGNAL  		BOEING	747   	747*        		NM  										DIAPHRAGM ASSY	FAIL TEST       	B			UN7R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	19					10P928					UNIT FAILED FUNCTIONAL TEST.  FOUND DIAPHRAGM ASSY 886083-5 MISSING SPACER/SLEEVE P/N 113842-146.  SPRING RETAINER P/N 3	166820-1 MISSING.  WRONG SPRING IN VALVE, SPRING P/N 3160871-1 IS NOT USED WITH VALVE 3290402-1.  SB 27-1014 NOT C/W.  S	B 27-1042 PARTIALLY C/W.				2	L	7	4 	4F			RT	A20WE   					 
1997051500018	19970515	00018	CE  	1997	5	15	97ZZZX1987       	1	19970113	G	2140	0800400239	FUEL LINE       	STWARNER    	8259JR2     	CESSNA	310   	310R        	2074245	CE  										HEATER	LEAK            	G	L	A		O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			SO	15	6107X	2665 				310R1276				FUEL LINE ON HEATER FAILED DUE TO CORROSION ALLOWING AVGAS TO SPRAY INTO NOSE BAGGAGE COMPARTMENT AND IGNITE.  HEATER AS	SY ITSELF IS IN GOOD CONDITION.  AD 81-09-09 PROVIDES FOR INSPECTION OF THAT AREA BY HEATER OPERATION TIME, BUT, NO CALE	NDAR TIME.  PART HAD 19 HRS SINCE AD, HOWEVER, SEVERAL YEARS HAD PASSED.  ACFT LOCATED IN FLORIDA WHICH HAS A CORROSIVE 	ENVIRONMENT.  SUBMMITTER RECOMMENDATION - ADD CALENDAR TIME TO AD.			1	L	7	2 	3O				3A10    					 
1997051500019	19970515	00019	EA  	1997	5	15	97ZZZX1988       	2	19970401	G	8530	73806P	PUSH ROD        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	95693					15285959	L2454815			PUSH ROD CRACKED BOTH ENDS.  CRACKS APPROXIMATELY .50 INCH LONG.  AD'S 80-25-02K2 AND 95-03-10 DO NOT APPLY.  ENGINE FAC	TORY REMANUFACTURED APPROXIMATELY 3300 HOURS AGO.  FIELD OVERHAUL APPROXIMATELY 900 HOURS AGO.  RECORDS WOULD INDICATE 3	300 HOURS ON PUSH ROD!				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997051500020	19970515	00020	EU  	1997	5	15	97ZZZX1989       	1	19970408	G	2710		BELLCRANK       			RHNFLU	EA300 	EA300S      	1130864	EU  										RT WING AILERON	MOUNT DEBONDED  	D		A		O				OTHER                   				F			FLT CONT AFFECTED         			AB	AEROBATIC      	1			CE	03	9K	664  				022				ACFT HAD UNDERGONE A 50 HOUR INSP.  NO DISCREPANCIES WERE NOTED IN THE AIL SYS WHEN THE BELLCRANKS WERE INSP NOR WAS ANY	 SLACK NOTED IN THE AIL SYS AT THE CONTROL STICK OR THE PUSH/PULL TUBES AT EACH AIL.  DURING THE FIRST FLIGHT AFTER THE 	INSP WHILE PRACTICING SNAP ROLLS TO THE RT, THE AIL CONT STARTED TO BIND NEAR THE NEUTRAL POSITION.  INITIAL INSP FOUND 	THE RT AIL PUSH/PULL TUBE WAS BINDING AGAINST THE OTBD EDGE OF THE BOTTOM SKIN CUT-OUT JUST FORWARD OF THE AIL.  FURTHER	 INSP REVEALED OTBD AIL BELLCRANK ASSEMBLY WAS LOOSE IN THE WING.  THE BOND JOINT ON THE MOUNT BLOCK TO BOTH THE UPPER A	ND LOWER WING SKIN HAD FAILED.  ALL OF THE BONDING MATERIAL WAS STILL ADHERED TO THE MOUNT BLOCK.	1	M	7	1 	3O			NC	A67EU   					 
1997051500021	19970515	00021	SO  	1997	5	15	97ZZZX1990       	1	19970415	G	3230		ROD             			PIPER 	PA44  	PA44180     	7104402	SO  										NLG FOLLOW UP	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			WP	03										PA44-180 PIPER SEMINOLE MADE A LANDING WITH THE NOSE GEAR RETRACTED.  THE INSTRUCTOR-PILOT CLAIMED THAT, AFTER EXTENDING	 THE LANDING GEAR HANDLE, HAD A 'NOSE GEAR UNSAFE' INDICATION....'.  AFTER SEVERAL ATTEMPTS TO NORMALLY AND MANUALLY EXT	END THE NOSE GEAR, THE AIRCRAFT LANDED WITH THE NOSE GEAR RETRACTED.  THE STUDENT/PILOT STATED THAT THE '..GEAR DOOR LIN	KAGE FELL OUT WHEN (THE) NOSE WAS LIFTED'.  THE OWNER/OPERATOR STATED THAT THE NOSE GEAR FOLLOW-UP ROD FAILED JAMMING TH	E NOSE GEAR IN THE WHEELWELL.  REPORTEDLY, THE PART HAD OVER 5,000 HOURS OF TIME IN SERVICE, AND THERE IS NO LIMITING TI	ME PUBLISHED FOR THE PART.	1	L	7	2 	3O				A19S0   					 
1997051500022	19970515	00022	SW  	1997	5	15	97ZZZX1991       	1	19970313	G	6720	205011711101	GRIP            		20401180117 	BELL  	204   	UH1B        	1181410	SW  										T/R	DEFECTIVE       	B	P	A	QJ5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	05	22753	1143 			IMPT4654	6413985				BUSHING FOR PITCH LINK DOES NOT PROTRUDE FLUSH ON BACK SIDE OF GRIP EAR.  THEREFORE, SINGLE STEEL WASHER UNDER NUT OF PC	 LINK BOLT SITS OVER RECESS AND CAN 'DISH' INTO RECESS CAUSING BOLT TO LOOSE TORQUE.  PC LINK CONTACTED GRIP EAR AS LOOS	E BOLT MOVED.				1	G	7	1 	4U				EXPA1G71					 
1997051500023	19970515	00023	NE  	1997	5	15	97ZZZX1992       	1	19970408	G	5280	7620902019045	FITTING         			SKRSKY	S76   	S76B        	8143007	NE  										LT MLG DOOR	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	22CP	1313 				760425				LEFT MAIN LANDING GEAR DOOR FITTING FOUND FAILED ON DAILY POST-FLIGHT INSPECTION.  FITTING WAS REPLACED BY A SUPERSEDED 	(-048) PART NUMBERED FITTING WHICH IS DIMENSIONALLY LARGER IN SUPPORT AREA.  NOTE:  SEE ALERT NR 217, AUGUST 1996, PAGE 	12, FOR SAME PROBLEM.  DOOR P/N 76207-02002-011.				1	G	7	2 	4U				H1NE    					 
1997051500024	19970515	00024	SW  	1997	5	15	97ZZZX1993       	1	19970326	G	6510	AN1746A	BOLT            			BELL  	206   	206L1       	1182107	SW  										T/R DRIVE	WORN            	B			QEVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	400EA					45544				DURING PHASE INSPECTION, FOUND THOMAS COUPLING BOLTS ON SEGMENTED DRIVE SHAFTS FOR TAIL ROTOR TO HAVE WORN THREADS CAUSI	NG NEW MS21042-L4 NUTS TO NOT HAVE PROPER LOCKING FRICTON AT THESE LOCATIONS, FORWARD SHORT SHAFT TO ENGINE, NR 3 SHORT 	SHAFT AND SHORT SHAFT AT TAIL ROTOR GEARBOX AREAS WHICH ARE REMOVED FREQUENTLY.  SUBMITTER RECOMMENDS CHANGING BOLTS AT 	600 OR 1200 HOUR INTERVALS OR EVEN MORE FREQUENTLY, IF WEAR IS NOTICED.			1	G	7	1 	3U				H2SW    					 
1997051500025	19970515	00025	SW  	1997	5	15	97ZZZX1994       	1	19970326	G	6510	AN1747A	BOLT            			BELL  	206   	206L1       	1182107	SW  										T/R DRIVE	WORN            	B		A	QEVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	400EA					45544				DURING PHASE INSPECTION, FOUND THOMAS COUPLING BOLTS ON SEGMENTED DRIVE SHAFTS FOR TAIL ROTOR TO HAVE WORN THREADS CAUSI	NG NEW MS21042-L4 NUTS TO NOT HAVE PROPER LOCKING FRICTON AT THESE LOCATIONS, FORWARD SHORT SHAFT TO ENGINE, NR 3 SHORT 	SHAFT AND SHORT SHAFT AT TAIL ROTOR GEARBOX AREAS WHICH ARE REMOVED FREQUENTLY.  SUBMITTER RECOMMENDS CHANGING BOLTS AT 	600 OR 1200 HOUR INTERVALS OR EVEN MORE FREQUENTLY, IF WEAR IS NOTICED.			1	G	7	1 	3U				H2SW    					 
1997051500028	19970515	00028	CE  	1997	5	15	97ZZZX1997       	1	19970127	G	3150		ANNUNCIATOR     			BEECH 	B300  	B300        	1159232	CE  										AUTOFEATHER	MISWIRED        	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	3269W	18   				FL147				PERFORMED AUTOFEATHER SYSTEM TEST AND ARM PROCEDURE PER B300 MM 61-20-00 AND CONFIRMED CONFLICTING LEFT/RIGHT ANNUNCIATI	ON. VERIFIED WIRING PER B300 WIRING DIAGRAM 61-21-02 PAGE 4 AND SUBSEQUENT SECTIONS.  CORRECTED MIS-WIRING AT ANNUNCIATO	R LIGHT CONNECTORS TO CONFORM TO WIRING DIAGRAGM AND ANNUNCIATE CORRECTLY.  PEFORMED AUTOFEATHER SYSTEM TEST AND ARM PRO	CEDURE PER B300 MM 61-20-00 AND PASSED.			2	L	7	2 	4T			RT	A24CE   					 
1997051500029	19970515	00029	SW  	1997	5	15	97ZZZX1998       	1	19970429	G	5330	2730018023	SKIN            			SWRNGN	SA226 	SA226TB     	8780406	SW  										BS 228.0	CRACKED         	B			VH2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	626PS					TB329				FUSELAGE SKIN WAS FOUND TO BE CRACKED IN PRESSURIZED, STRUCTURAL CLOSE OUT SKIN AREA.  CRACK LOCATIONS WERE FS 228.0 AT 	BL 6.0 LT AND RT SIDES.  BASED ON PREVIOUS EXPERIENCE WITH MODELS SA226-T, AT, AND TC, THE MOST PROBABLE CAUSE APPEARS T	O BE THE BELLY FAIRING STRINGERS CHAFING AGAINST THE FUSELAGE SKIN.  FAIRCHILD AIRCRAFT HAS ISSUED SB 226-53-006 WHICH A	DDRESSES THIS PROBLEM FOR MODELS SA 226 T, AT, AND TC.  SUBMITTER WOULD RECOMMEND FAIRCHILD SB 226-53-006 BE INCLUSIVE O	F MODEL SA 226T(B).		2	L	7	2 	4T			RT	A5SW    					 
1997051500030	19970515	00030	CE  	1997	5	15	97ZZZX1999       	1	19970422	G	3241	302EX	MOTOR ASSY      	ELECTROMECH 		CESSNA	500   	550         	2076604	CE  										ANTISKID	MALFUNCTION     	B			R8RR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	2663Y				1833	5500602				AFTER REPLACING THE ANTI-SKID BRAKE MOTOR ASSY WITH THE GREEN AND BLACK WIRES CONNECTED PROPERLY, THE MOTOR ASSY RUNS IN	 A COUNTER CLOCKWISE DIRECTION, OPPOSITE OF THE NORM.  REMOVED AND REPLACED ANTI-SKID MOTOR ASSY.  SUBMITTER SUSPECTS IM	PROPER WIRING WITHIN MOTOR AND IMPROPER BENCH TESTS PERFORMED.				1	L	7	2 	4F				A22CE   					 
1997051500031	19970515	00031	CE  	1997	5	15	97ZZZX2000       	1	19970422	G	3241	302EX	MOTOR ASSY      			CESSNA	500   	550         	2076604	CE  										ANTI SKID	INTERMITTENT    	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2663Y				00341	5500602				REMOVED AND REPLACED ANTI-SKID HYDRAULIC POWER PACK ASSY.  AFTER 29.8 HRS OF USAGE, THE MOTOR BECAME INTERMITTENT.  SUSP	ECT A LOOSE CONNECTION WITHIN THE MOTOR ASSY.  THIS WAS A REPAIRED ANTI-SKID HYDRAULIC POWER PACK PROVIDED BY THE MANUFA	CTURER.  REMOVED AND REPLACED THE ANTI-SKID MOTOR P/N 30-2.				1	L	7	2 	4F				A22CE   					 
1997051500033	19970515	00033	NE  	1997	5	15	97ZZZX2001       	2	19970421	G	8530		CYLINDER        			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 9 HEAD	SEPARATED       	D	L			A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	08	4397S					3010057	51132			AIRCRAFT EXPERIENCED A SUDDEN LOSS OF POWER.  EMERGENCY LANDING MADE AT MOUNTAIN HOME AIR FORCE BASE.  NR 9 CYLINDER HEA	D HAD SEPARATED JUST ABOVE THE TOP OF PISTON TRAVEL.  FATIGUE FRACTURE APPEARS TO ORIGINATE AT THE EXHAUST VALVE SEAT. 6	75 SMOH.				1	L	7	1 	3R	3	R		A9SW    	5E2				 
1997051500035	19970515	00035	SW  	1997	5	15	97ZZZX2002       	1	19970414	G	3222		SNAP RING       			GULSTM	690TP 	690B        	7630516	SW  										NLG STRUT	FAILED          	B		A	WD4R	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	17	137BW					11446				WHILE ATTEMPTING TO LAND, THE PILOT PUT THE GEAR HANDLE DOWN AND CONFIRMED THE NOSE GEAR DID NOT GO DOWN AND LOCKED.  TH	IS AIRCRAFT WAS LANDED WITH THE NOSE GEAR UP WITH DAMAGE TO THE FUSELAGE STRUCTURE.  UPON INSPECTION, IT WAS FOUND THE N	OSE GEAR LOWER STRUT SNAP RING CAME OUT OF THE STRUT WHICH ALLOW THE NOSE STRUT TO EXTEND WHILE STILL IN THE WHEELWELL. 	 THE SNAP RING AND STRUT GROOVE WERE NOT DAMAGED.  SUBMITTER STATED IT APPEARS THE SNAP RING WAS NEVER PROPERLY INSTALLE	D.		1	H	7	2 	3T				2A4     					 
1997051500036	19970515	00036	WP  	1997	5	15	97ZZZX2003       	2	19970409	G	7314	8974001	PUMP            			STBROS	SC7   	SC73        	8100512	EU  	GARRTT	TPE331	TPE3312201A 		WP  					DRIVESHAFT	LEAKAGE         	B	L	A	ILIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1846	4060 				SH1846	P90094			INVESIGATION FOR EXCESS OIL USAGE, FOUND THE OIL WAS ENTERING THE FUEL SYS VIA THE OIL WET SPLINE MOD TO THE DRIVESHAFT 	THAT DRIVES THE FUEL PUMP ON THE ENG GEARBOX.  ALLIED SIGNAL SB TPE 331-72-0104 IS THE WET SPLINE MOD.					1	H	7	2 	3T	4	T		A15EU   	E3WE				 
1997051500037	19970515	00037	EA  	1997	5	15	97ZZZX2004       	1	19970418	G	6123	8190026	SWITCH          			DHAV  	DHC6  	DHC6300     		EA  										AUTOFEATHER	FAILED          	D		A		E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	235SA	105  			3703	772				TORQUE PRESS SWITCH IN AUTOFEATHER SYSTEM FAILED CAUSING PROP TO FEATHER IN-FLIGHT.						1	H	7	2 	3T				A9EA    					 
1997051500039	19970515	00039	EA  	1997	5	15	97ZZZX2005       	2	19970425	G	7250	PCE84114	GAS GENERATOR   			STBROS	SD3   	SD330       	8100602	EU  	PWA   	PT6   	PT6A45      	52043	EA  					RT ENGINE	SEAL FAILED     	D				E	A	H		ENGINE SHUTDOWN         	UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS		B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	13	936MA					SH3036	84114			PILOTS REPORTED SMOKE IN COCKPIT AND CLOSED PRSOV VALVE STOPPING THE SMOKE.  SEVERAL MINUTES LATER, THE PILOTS NOTICED T	ORQUE AND OIL PRESSURE FLUCTUATING.  FEATHERED AND SHUT DOWN ENGINE AND LANDED WITHOUT INCIDENCE.  ENGINE WAS LEAKING OI	L FROM THE COMPRESSOR SEAL.				2	H	7	2 	4T	4	T		A41EU   	E4EA				 
1997051500040	19970515	00040	WP  	1997	5	15	97ZZZX2006       	1	19970425	G	5312		BULKHEAD WEB    			DOUG  	DC8   	DC861F      	3021953	WP  										AFT PRESSURE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	27UA					45942				DURING 'C' CK INSPECTION ACCOMPLISHED VISUAL AND DYE PENETRANT INSPECTION OF THE AFT PRESS BULKHEAD WEB IAW SB 53-73 REV	 1.  FOUND A CRACK AT RT FWD SIDE OF THE APB WEB AT I/B SIDE OF VERTICAL STIFFENER ABOVE FASTENER ROW.  ACCOMPLISHED TER	MINATING ACTION BY REMOVING CRACK SECTION AND INSTALLED A DOUBLER IAW DOUGLAS DWG SR08530007.  ALSO DURING INSPECTION FO	UND A CRACK AT LT FWD SIDE OF THE APB WEB AT BOTH SIDES OF THE STIFFENERS ABOVE FASTENERS.  ACCOMPLISHED TERM. ACTION BY	 REMOVING CRACK SECTIONS AND INSTALLED DOUBLER IAW DACO DWG SR08530007.		2	L	7	4 	4F				4A25    					 
1997051500387	19970515	00387	CE  	1997	5	15	97ZZZX2015       	1	19970428	G	2435	230890002	GENERATOR       	LEARSIEGLER 		RKWELL	NA265 	NA26565     	7630107	CE  										LT START/GEN	BEARING FAILED  	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	13	265A	540  			695	46547				ON 4-28-97, THE AIRCRAFT EXPERIENCED A VERY NOTICEABLE VIBRATION AND NOISE AFTER DEPARTURE.  CREW WAS ABLE TO DETERMINE 	THAT IT CHANGED WITH THROTTLE MOVEMENT.  ACFT RETURNED TO BASE, THE LEFT STARTER/GENERATOR WAS PULLED AND CHECKED.  UPON	 INSPECTION IT WAS NOTED THERE WAS A LOT OF PLAY IN THE AFT BEARING.  THE STARTER/GENERATOR WAS REPLACED.				2	L	7	2 	4J				A2WE    					 
1997051500388	19970515	00388	CE  	1997	5	15	97ZZZX2016       	1	19970428	G	2820	57001133	FUEL LINE       			CESSNA	441   	441         	2076020	CE  										RT WING CWS 88.0	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	40FJ	3141 				4410359				MAIN FUEL LINE FROM BOOST PUMP TEE TO FUEL CROSSFEED SHUTOFF VALVE WAS CHAFED BEYOND LIMITS BY WING RIB ASSY, AT WS 88.0	 INCH, RIB P/N 572225-33.  SUBMITTER RECOMMEND ALL CONQUEST II SHOULD BE INSPECTED IN THIS AREA - SHOULD THIS LINE OPEN 	UP DUE TO CHAFING, COULD RESULT IN COMPLETE LOSS OF AIRCRAFT.  THIS IS A HIGH PRESSURE LINE THAT IS BEHIND FUEL SHUTOFF 	VALVE, SO WITH BOOST PUMPS IN, CANNOT SHUT FUEL OFF.  FUEL COULD THEN BE IGNITED BY BLEED AIR LINE THAT RUNS IN SAME LEA	DING EDGE COMPARTMENT.  SUBMITTER RECOMMENDS LINE BE RESHAPED OVER THIS AREA AND SOME SORT OF CHAFING PREVENTION LIKE SP	IRAL WRAP INSTALLED ON FUEL LINE.  SUBMITTER STATED NOTE:  THIS IS NOT THE FIRST TIME HAVE SEEN THIS PROBLEM IN THIS ARE	1	L	7	2 	3T			RT	A28CE   					 
1997051500389	19970515	00389	CE  	1997	5	15	97ZZZX2017       	1	19970429	G	2711	NAS35860900	TUBE            			LEAR  	35    	35A         	5170602	CE  										AIL TAB PUSH ROD	RUSTED          	B	L	A	DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	258G	3951 				443				DURING POST FLIGHT INSP A SMALL PAINT BLISTER NOTED ON ONE OF THE LT HAND AIL BALANCE TAB PUSH RODS AT BOTTOM DEAD CENTE	R APPROXIMATELY 3.50 INCHES FWD OF THE AFT ROD END BOLT CENTER.  WHEN PROBED THE BLISTER OPENED UP TO A HOLE APPROXIMATE	LY .25 INCH LONG BY .1250 INCH WIDE.  FLAKED RUST WAS NOTED INSIDE THE TUBE AND COULD BE SHAKEN OUT THROUGH THE HOLE.  B	OTH DRIVE-IN RIVETS, USED FOR CORROSION TREATMENT, ARE STILL IN PLACE AND SECURE.  IT SEEMS OBVIOUS MOISTURE ENTERED THE	 TUBE BY SOME MEANS AND OVER TIME RUSTED A HOLE THROUGH IT.		2	L	7	2 	4F				A10CE   					 
1997051500390	19970515	00390	CE  	1997	5	15	97ZZZX2018       	1	19970422	G	3221	NAS464P61A	BOLT            			CESSNA	182   	R182        	2072734	CE  										NLG ATTACH	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	07	202CT	3935 			24	R18200060				PILOT REPORTED NOSE GEAR NOT RETRACTING ALL THE WAY INTO GEAR WELL.  INSPECTION FOUND LT NOSE GEAR MAIN ATTACH BOLT MISS	ING.  NOSE GEAR WAS HELD IN PLACE BY REMAINING BOLT (RT).  BOLT WAS FOUND BELOW LT EXHAUST PIPE WITH THREAD END SHEARED 	OFF, NUT AND PART OF BOLT WAS NOT FOUND, REPLACED BOTH ATTACH BOLTS AND NUTS/WASHERS.				1	H	7	1 	3O			RT	3A13    					 
1997051500391	19970515	00391	CE  	1997	5	15	97ZZZX2019       	1	19970416	G	7160	BA5710	AIR FILTER      	BRACKETT    		CESSNA	177   	177RG       	2073709	CE  										INDUCT AIR	DETERIORATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	217AF	777  				177RG1011				AIR FILTER GASKET HAS TURNED TO MUSH FROM THE OIL THEY USE IN THE AIR FILTER, MAYBE A NEW TYPE OF GASKET IS CALLED FOR. 	 PART HAS BEEN REPLACED.					1	H	7	1 	3O				A20CE   					 
1997051500392	19970515	00392	SO  	1997	5	15	97ZZZX2020       	2	19970401	G	7414		CAM ASSY        			BEECH 	35    	K35         	1151524	CE  	CONT  	O470  	IO470C      	17026	SO  					SNAP RING	RIVET FAILED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	5008					D5865				DURING ACCOMPLISHING SB MSB645, NR 639, AND AD 96-12-07, FOUND MAG SNAP RING CAM ASSY HAD RIVET FAILURE.						1	L	7	1 	3O	3	O		3A15    	E273				 
1997051500393	19970515	00393	SO  	1997	5	15	97ZZZX2021       	2	19970428	G	7414	M3006	BEARING         	SLICK       	6310        	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      		SO  					MAG DRIVE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	877CA	1385 			94020912	TH1727	676761			PILOT REPORTED LEFT ENGINE LEFT MAGNETO WAS 'DEAD' ON RUN-UP.  REMOVED MAGNETO AND OPENED UP FOR INSPECTION.  FOUND INTE	RNAL DAMAGE - MATERIAL BEING WORN AWAY BY ROTATING MAGNET.  FURTHER DISASSEMBLY REVEALED DRIVE END BEARING P/N M3006 BAL	L RETAINER CAGE AND GREASE SEAL GONE - BEARING WAS DRY WHICH MAY HAVE LEAD TO FAILURE.  NEW MAGNETO INSTALLED ON AIRCRAF	T AND RETURNED TO SERVICE.			1	L	7	2 	3O	3	O		3A16    	E3SO				 
1997051500394	19970515	00394	SO  	1997	5	15	97ZZZX2022       	1	19970428	G	5512		SKIN            			PIPER 	PA24  	PA24250     	7102404	SO  										RT STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	8200P	2200 				243452				ANNUAL INSP FOUND RT STAB SKIN WRINKLED AND BENT AT THE END OF TORQUE FITTING P/N 16809-03.						1	L	7	1 	3O				1A15    					 
1997051500395	19970515	00395	SO  	1997	5	15	97ZZZX2023       	1	19970428	G	5510	452363	BEARING         			PIPER 	PA24  	PA24250     	7102404	SO  										STAB	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	8200P	2200 				243452				ANNUAL INSP FOUND STAB BEARING WAS WORN.  INSP IN AREA COVERED IN AD 97-13-10 NOTE 1 PARA (A2) AND SB 411A INST PARA (1-	4).					1	L	7	1 	3O				1A15    					 
1997051500396	19970515	00396	SO  	1997	5	15	97ZZZX2024       	1	19970401	G	3211	39486803	TRUNNION ASSY   			PIPER 	PA34  	PA34220T    	7103420	SO  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8287U					348333027				DURING INSPECTION NOTICED PART CRACKED ON AFT WEBBING OF RT MAIN GEAR TRUNNION.  STRIPPED PAINT, DYE  PENETRANT INSPECTI	ON REVEALED A CRACK LOCATED 4.5 INCHES FROM BASE STRETCHING HORIZONTALLY ACROSS SEAM APPROXIMATELY .50 INCH IN LENGTH. T	HIS AREA HAD A FEW MANUFACTURING GRIND MARKS.				1	L	7	2 	3O				A7SO    					 
1997051500397	19970515	00397	SO  	1997	5	15	97ZZZX2025       	1	19970422	G	5311	1056236	TUBE            			PIPER 	PA18  	PA18        	7101802	SO  										FUSELAGE FRAME	CORRODED        	B	L	A	QK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05										FAA APPROVED REPAIR STATION, THAT REBUILDS AND REPAIRS PA-18 FUSELAGE FRAMES, HAS EXPERIENCED A PROBLEM, IN FINDING SEVE	RE CORROSION ON APPROX 35 PERCENT OF THE FUSELAGES IN WORK.  ONE PROBLEM CENTERS ON THE .6250 INCH VERTICAL TUBE, P/N 10	562-36, FROM THE TOP LONGERON, UP TO THE REAR WING ATTACH FITTING, ON THE RT SIDE AND LOCATED AT THE AFT UPPER DOOR.  TH	E CHANNEL, P/N 12205-5, THAT IS TACK WELDED TO THIS TUBE, IS SET TO PROVIDE PROPER CLEARANCE TO THE REAR UPPER DOOR.  FI	NDING TRAPPED MOISTURE IS RETAINED BEHIND THE CHANNEL AND RUSTS OUT THE .6250 INCH TUBE.  IMPOSSIBLE AREA TO INSPECT, UN	LESS THE CHANNEL IS REMOVED.  THE AREA, NOT COVERED BY THE CHANNEL, IS RELATIVELY FREE OF CORROSION.	1	H	7	1 	3O				1A2     					 
1997051500398	19970515	00398	EA  	1997	5	15	97ZZZX2026       	2	19970501	G	7322	105217	CARBURETOR      		MA4SPA      	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O320  	O320D3G     	41508	EA  					BOWL DRAIN	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	15050					287225569	L2262227A			TWO BOWL SCREWS LEAKING.  FUEL BOWL DRAIN LEAKING.  BOTTOM OF CARBURETOR SMALL HOUSING OF ACCELERATOR PUMP LEAKING.  VER	Y POOR QUALITY ASSURANCE.  SUBMITTER STATED ALSO SAME PROBLEM ON AN OVERHAULED MODEL - SAME P/N, 10-5217.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997051500400	19970515	00400	CE  	1997	5	15	97ZZZX2028       	1	19970317	G	2130		HOSE            			CESSNA	501   	501         	2076603	CE  										CABIN PRESS	FAILED          	C	L	A		B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			J			WARNING INDICATION        			CR	CRUISE         	1			EU	01	501CF					5010128				DURING CRUISE AT FL 370,  PRESSURIZATION SET FOR FL 380 WITH CABIN AT APPROX 7,000 FEET.  CREW HEARD A DULL NOISE, CABIN	 OXY MASK DEPLOYED, MASTER WARN RED LIGHTS AND CABIN ALTITUDE INCREASING.  ACFT DIVERTED FOR REPAIR.  FOUND FAILED BLEED	 SYS HOSE AND A NON-RETURN VALVE OUT OF LIMITS AT .75 INCH OPEN.				1	L	7	2 	4F				A27CE   					 
1997051500402	19970515	00402	SO  	1997	5	15	97ZZZX2030       	2	19970401	G	8540	643110	SPRING          		643259A28   	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					START ADAPTER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	234CN		342  			421C0404	292152R			RIGHT ENGINE WOULD NOT TURN OVER TO START.  FOUND CLUTCH SPRING INSIDE THE STARTER ADAPTER BROKEN.  REPLACED STARTER ADA	PTER.  NOTE:  THIS ENGINE AND STARTER ADAPTER IS NOT REQUIRED TO BE INSPECTED BY TCM BULLETIN CSB94-4A.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997051500403	19970515	00403	EU  	1997	5	15	97ZZZX2031       	1	19970312	G	3230	TB2061032003	SWITCH          		TB204207200 	SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										NLG LEG	WIRE BROKEN     	D		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	25	72BM					466				NOSE GEAR DID NOT FULLY EXTEND AND LOCK DUE TO A NOSE GEAR END OF TRAVEL LIMIT SWITCH.  THE SWITCH IS MOUNTED ON THE FOR	WARD LEG OF THE OVER-CENTER LINK AND DOWNLOCK.  THE WIRE IS TY-WRAPPED TO THE LINK.  THE SWITCH HAD 1736.08 HOURS TOTAL 	TIME.  THE SWITCH SHOULD BE REPLACED ANY TIME THE OUTER COVER SHOWS SIGNS OF DETERIORATION OR CRACKING.				1	L	7	1 	3O			RT	A51EU   					 
1997051500404	19970515	00404	EA  	1997	5	15	97ZZZX2032       	2	19970416	G	7322	MA3A	CARBURETOR      	FACET       		PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR MAIN	JET BLOCKED     	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	15	2585B	3195 			CR15849	3879A0132	L1768215			AIRCRAFT ENGINE LOST POWER FROM PARTIAL OBSTRUCTION OF MAIN JET WHICH FEEDS DISCHARGE NOZZLE.  MATERIAL APPEARS TO HAVE 	BUILD-UP OF SEDIMENT SCALE.  RECOMMEND INTERNAL BOWL INSPECTION OF CONDITION AT EACH 2,000-HOUR OPERATION.					1	L	7	1 	3O	3	O		A18SO   	E223				 
1997051500405	19970515	00405		1997	5	15	97ZZZX2033       	3	19970228	G	6112	RA19833	CLAMP           			PIPER 	PA31T 	PA31T       	7103124	SO  										PROP BLADE	FAILED          	B	L		EBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	23407					31T7920055				RAPCO P/N RA1983-3 CLAMP (DE-ICE BOOT AND HARNESS LEADS ATTACH AT THIS POINT ON PART) FAILED (CRACKED INTO PIECES) ALLOW	ING WEIGHT OF PIECES TO PULL LEAD WIRES FROM SPINNER BULKHEAD TERMINAL STRIP.  TERMINAL STRIP ON SPINNER BULKHEAD THEN F	AILED AND PULLED WIRES FROM PROP DE-ICE SLIP RING.  PILOT FOUND WIRES HANGING OUT OF SPINNER ON PRE-FLIGHT.				1	L	7	2 	3T				A8EA    					 
1997051500406	19970515	00406	SW  	1997	5	15	97ZZZX2034       	1	19970421	G	6510	206040365001	SHAFT           			BELL  	206   	206L3       	1182108	SW  										T/R DRIVE	PITTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	937S	1237 				51258				DURING INSPECTION OF THE TAILBOOM, MECHANIC NOTICED A VERY FAINT DISCOLORED LINE ADJACENT TO THE GLUE LINE OF ONE FLANGE	 ON THE TAIL ROTOR DRIVESHAFT.  FURTHER INSPECTION WITH 10X MAG GLASS REVEALED PITTING INTO THE ALUMINUM SHAFT APPROXIMA	TELY 30 DEGREES OF THE CIRCUMFERENCE WITH EVIDENCE OF MORE BEGINNING THE REMAINDER OF THE WAY AROUND THE SHAFT.  SUSPECT	 A CORROSIVE REACTION TO THE GLUE OR PREPARATION FOR GLUE AT MANUFACTURE AS THIS HELICOPTER HAS NEVER BEEN OPERATED IN A	 HIGH CORROSIVE ENVIRONMENT.  THE PART WAS INSTALLED NEW 3 YEARS EARLIER AND HAS ACCUMULATED 1237.1 HOURS.		1	G	7	1 	3U				H2SW    					 
1997051500407	19970515	00407	NE  	1997	5	15	97ZZZX2035       	2	19970409	G	7230	204322017	VANE ASSY       								LYC   	LF507 	LF5071F     		NE  					3RD STAGE COMP	FOD DAMAGE      	B			SW5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							LF07338			SEVERE FOD DAMAGE TO 1ST, 2ND, AND EXIT VANE ROWS.  TRAMP MATERIAL LODGED BETWEEN VANES.  OUTER SHROUD DAMAGED FROM FOD 	IMPACTS.										4	F			E6NE				 
1997051500408	19970515	00408	NM  	1997	5	15	97ZZZX2036       	2	19970429	G	7261		ENGINE          			GULSTM	690TP 	690C        	7630517	SW  	GARRTT	TPE331	TPE3315251K 		NM  					LT ENGINE	LOW OIL PRESS   	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			NM	04	3XY	1970 				11638	P40341			UPON REACHING FL 26,000 FEET, PILOT OBSERVED OIL PRESSURE DECREASING SLOWLY.  THE OIL PRESSURE HAD REACHED A LOW END RED	 LINE.  THE PILOT ELECTED TO SHUT DOWN NR 1 ENGINE AND RETURN TO THE AIRPORT.  AFTER LANDING, INVESTIGATION WAS MADE INT	O OIL PRESSURE.  PRESSURES WERE ALL GOOD ON THE GROUND.  SOAP SAMPLES PROVED GOOD.  PREVIOUS ENGINE WORK SUGGESTS SOME P	OSSIBLE NICKED O-RINGS ON OIL TRANSFER TUBES INTERNALLY IN ENGINE.  THE ENGINE WAS REMOVED AND SENT BACK TO ALLIED SIGNA	L FOR INSPECTION.		1	H	7	2 	3T	4	T		2A4     	E2WE				 
1997051500409	19970515	00409	EA  	1997	5	15	97ZZZX2037       	2	19970424	G	8530	LW14077	PISTON PIN      			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					ENGINE	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	62392	161  				1591	L150943			AD 97-01-03 AND LYC SB 527B DO NOT REFERENCE VO540 ENGINES IN MODELS AFFECTED, BUT 4 OF 6 PISTON PINS IN ENGINE HAD TO B	E REPLACED IN C/W THE SB REQUIRED ACTION.  NOTE:  6-CYLINDER HELICOPTER ENGINES ARE LISTED IN WARRANTY LABOR ALLOWANCE A	ND A VO540 ENGINE IS LISTED IN MODEL AND S/N ATTACHMENT TO THE SB.				1	G	7	1 	3O	3	O		4H11    	E304				 
1997051500410	19970515	00410	WP  	1997	5	15	97ZZZX2038       	1	19970305	G	6710	A21810064603	SWITCH          			HUGHES	369   	369E        	4470707	WP  										CYCLIC TRIM	FAILED          	D		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	07	504MP	381  				O523E				DURING NORMAL OPERATIONS, THE TRIM SYSTEM CONTINUED TO DRIVE TO THE LEFT LATERAL CYCLIC STOP.  ATTEMPTS TO BRING THE TRI	M BACK TO THE NEUTRAL POSITION WERE UNSUCCESSFUL FROM BOTH THE PILOTS AND COPILOTS POSITION (STICK).  TRIM SYSTEM CIRCUI	T BREAKER WAS PULLED TO PREVENT ANY FURTHER PROBLEMS, AND THE AIRCRAFT WAS FLOWN BACK TO FACILITY WHILE GREAT FORCE WAS 	EXERTED TO OVERCOME THE TRIM-SPRING CAPSULE.  AFTER SHUT DOWN, THE STICK WAS RELAXED.  AFTER REPLACING PILOT'S TRIM SWIT	CH AND RESETTING CIRCUIT BREAKER, ALL GROUND AND FLIGHT TESTS CHECKED GOOD.		1	G	7	1 	3U				H3WE    					 
1997051500411	19970515	00411	EU  	1997	5	15	97ZZZX2039       	1	19970418	G	2435	150SG122Q	GENERATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	FAILED          	B		A	R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9084W					2672				AFTER INSTALLATION OF OVERHAULED STARTER/GENERATOR ON INITIAL START-OPERATIONAL CHECK, THE STARTER/GENERATOR DID NOT COM	E ON-LINE, IT WAS RESET WITH NO RESULTS.  IT WAS AGAIN RESET AND FUNCTIONED PROPERLY.  LATER, ACFT WAS DISPATCHED WITH N	O DISCREPANCIES.  THE NEXT DAY, A MAINTENANCE RUN WAS PERFORMED TO VERIFY AN OIL SEEP ON THE TAIL GEARBOX.  ACFT STARTED	 NORMAL, BUT GENERATOR DID NOT COME ON-LINE.  AFTER SEVERAL ATTEMPTS TO RESET FAILED, STARTER/GENERATOR WAS REMOVED AND 	REPLACED.  SUBMITTER SUSPECTS INTERNAL FAILURE, INADEQUATE OVERHAUL, OR BENCH TESTING PROCEDURES.		1	G	7	1 	3U				H9EU    					 
1997051500413	19970515	00413	SO  	1997	5	15	97ZZZX2041       	2	19970401	G	8530	625393	RETAINER        								CONT  	O520  	GTSIO520H   	17032	SO  					NR 5 CYL INT VLV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							267116R			NR 5 CYLINDER VALVE RETAINER DEFECT.  CHECKED TWO CYLINDERS ON THIS RUN-OUT CORE.  ONE GOOD AND NR 5 WAS NOT DUE TO INTA	KE VALVE SPRING RETAINER CRACKED.										3	O			E7CE				 
1997051500414	19970515	00414	EA  	1997	5	15	97ZZZX2042       	2	19970401	G	8530	SL798606	PUSHROD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	LOOSE END       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03			2400 				L1453615			RUN-OUT CORE ENGINE THAT WAS DISASSEMBLED FOR PUSHRODS FOR C/W AD 95-3-10.  THIS ENGINE HAD ONE SUPERIOR AIR PARTS PUSHR	OD WITH LOOSE END.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997051500415	19970515	00415	SO  	1997	5	15	97ZZZX2043       	2	19970401	G	8530	625393	RETAINER        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 3/4 EXH VLV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	1562G	673  				421B0801	267147R			NR 3 AND NR 4 CYLINDER EXHAUST VALVE RETAINER CRACKED.  1 EACH CYLINDER.  INSPECTED ALL OTHER CYLINDERS.  NONE FOUND DEF	ECTIVE.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997051500416	19970515	00416	SO  	1997	5	15	97ZZZX2044       	2	19970422	G	8530	542343CN	CYLINDER        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					LT NR 5	SEPARATED       	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SW	11	421FC		618  			421C0442	604119			ACFT LOST NR 5 CYLINDER IN CRUISE FLIGHT TO JBR.  CYLINDER SEPARATED ABOUT 1 INCH INBOARD OF THREADED AREA IN STEEL SLEE	VE.  AREA CRACKED IS 360 DEGREES AND EXPOSED TOP RINGS ON PISTON CAUSING METAL CONTAMINATION IN ENGINE.  OIL PRESSURE WA	S LOST 4 MINUTES BEFORE LANDING AT BVX.  THE NR 5 CYLINDER THAT FAILED IS LOCATED ON THE LEFT ENGINE.  CAUSE FOR THE CYL	INDER FALURE HAS NOT BEEN DETERMINED.  THE STEEL PORTION OF THIS CYLINDER HAD NO SIGN OF CRACKING OR LEAKING AT THE LAST	 INSPECTION WHICH WAS 15.9 HOURS AGO AT SCHEDULED OIL CHANGE ON 2-6-97.		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997051500417	19970515	00417	SO  	1997	5	15	97ZZZX2045       	2	19970326	G	8520	530196A1	CRANKSHAFT      			PIPER 	PA17  	PA17        	7101702	SO  	CONT  	A65   	A658        	17003	SO  					NR 2 THROW	FRACTURED       	G				K				NONE                    				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SW	11	4820H	109  			4F98	17118	T024483			CRANKSHAFT FRACTURED IN AFT CHEEK OF NR 2 THROW CAUSING ENGINE TO STOP.  THE CRANKSHAFT WAS IN THE 0.010 INCH UNDER COND	ITION.  THE ORIGIN OF THE FRACTURE MAY HAVE BEEN THE AFT RADIUS OF THE NR 2 CRANK PIN.  THE CRANKSHAFT WAS MAGNAFLUXED A	T OVERHAUL.  SUBMITTER RECOMMENDS MAKING ULTRASONIC INSPECTION AN OVERHAUL REQUIREMENT ON AGING ENGINES.				1	H	7	1 	3O	3	O		A805    	E205				 
1997051500418	19970515	00418		1997	5	15	97ZZZX2046       	4	19970505	G	3416	D120P2T	ENCODER         			CESSNA	172   	172P        	2072436	CE  										INST PANEL	ERRORS          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	5394K				66694	17274093				ON STATIC TEST, ENCODER FOUND INOPERATIVE AT 4600 FEET.  BETWEEN 5050 TO 5500 UNIT INDICATED 5200, AT 6050 TO 6500, UNIT	 INDICATED 6200.  SAME AT 7050, 8050, TESTS TERMINATED AND UNIT WAS REPLACED.					1	H	7	1 	3O			NT	3A12    					 
1997051500419	19970515	00419	SO  	1997	5	15	97ZZZX2047       	2	19970401	G	8550	625393	RETAINER        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 4 CYL INT VLV	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	5451J	280  				421B0909	267346R			NR 4 CYLINDER INTAKE VALVE RETAINER FAILED.  INSPECTED ALL OTHER CYLINDERS, FOUND NO OTHER DEFECTS.						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997051500420	19970515	00420		1997	5	15	97ZZZX2048       	4	19970408	G	2562	ELT10	ELT             	NARCO       		PIPER 	PA28  	PA28140     	7102802	SO  										ANTENNA	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	6475W	1000 			53461	2820549				INSPECTION REVEALED POSSIBLE SHORTING OF PORTABLE ANTENNA.  ANTENNA MAY BECOME DISLODGED FROM ITS HOLD AND SHORTING TO T	HE BASE THROUGH THE LATCH.  SUBMITTER STATED REMOVE PLASTIC PULL AND INSULATOR FROM THE OUTSIDE OF ANTENNA AND PLACE ON 	INSIDE TO INSULATE THE ANTENNA FROM THE CLIP.				1	L	7	1 	3O				2A13    					 
1997051500421	19970515	00421	SO  	1997	5	15	97ZZZX2049       	2	19970421	G	8530	648045	PISTON          		646657C     	CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	6480N					21063054	245650R			UPON DISASSEMBLY OF ENGINE, FOUND WRONG PISTONS INSTALLED.  RECORDS INDICATE PISTONS SOLD AS PART OF A TOP OVERHAUL KIT 	WITH CHROME CYLINDERS (4/1994).  CYLINDERS REMOVED FOR GLAZING AND 3 PISTONS WERE SCORED ENOUGH TO REQUIRE REPLACEMENT. 	 REPLACED ALL 6 WITH CORRECT SET OF BALANCED PISTONS.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997051500422	19970515	00422	EA  	1997	5	15	97ZZZX2050       	2	19970422	G	8530	LW13561	CYLINDER        			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					INTAKE PORT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	82606		81   			31P7730011	L55762			DURING MAINTENANCE WITH INTAKE PIPE REMOVED, INTAKE GUIDE WAS FOUND MOVING WITH THE VALVE.  CYLINDER REPLACED, TEAR DOWN	 REPORT REQUESTED FROM ENGINE OVERHAULER.  REPORT STATED A CRACK HAD CAUSED THE PROBLEM.  OUT OF 4 ENGINES OF THIS TYPE 	MAINTAINED BY THIS FACILITY, THIS WAS THE 6TH CYLINDER WITH CRACKS IN INTAKE PORT AREA.  ALL CYLINDERS WERE OVERHAULED A	ND CHROMED.  TIMES VARIED 81 AND 900 HOURS.			1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997051500423	19970515	00423	EA  	1997	5	15	97ZZZX2051       	2	19970422	G	8530	LW13561	CYLINDER        			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 1	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	82606		81   			31P7730011	RL36662			DURING ROUTINE MAINTENANCE, NR 1 AND NR 3 CYLINDERS WERE FOUND CRACKED IN THE INTAKE PORT AREA.  CRACKS WERE BETWEEN FIR	ST AND SECOND COOLING FINS FROM THE TOP AND PROGRESSED TO THE THINNER AREA OF THE PORT.  CRACKS NOTED BY A GREENISH TO B	LACK STAIN LOOKING FROM THE BOTTOM OF THE ENGINE.  OF FOUR ENGINES OF THIS TYPE MAINTAINED BY THIS FACILITY, THESE ARE T	HE 4TH AND 5TH WITH SIMILAR CRACKS.  ALL CYLINDERS WERE OVERHAULED AND CHROMED.  TIMES WERE 80 HRS AND APPROX 900 HRS SI	NCE OVERHAUL.		1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997051500424	19970515	00424	EA  	1997	5	15	97ZZZX2052       	2	19970422	G	8530	LW13561	CYLINDER        			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 3	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	82606		81   			31P7730011	RL36662			DURING ROUTINE MAINTENANCE, NR 1 AND NR 3 CYLINDERS WERE FOUND CRACKED IN THE INTAKE PORT AREA.  CRACKS WERE BETWEEN FIR	ST AND SECOND COOLING FINS FROM THE TOP AND PROGRESSED TO THE THINNER AREA OF THE PORT.  CRACKS NOTED BY A GREENISH TO B	LACK STAIN LOOKING FROM THE BOTTOM OF THE ENGINE.  OF FOUR ENGINES OF THIS TYPE MAINTAINED BY THIS FACILITY, THESE ARE T	HE 4TH AND 5TH WITH SIMILAR CRACKS.  ALL CYLINDERS WERE OVERHAULED AND CHROMED.  TIMES WERE 80 HRS AND APPROX 900 HRS SI	NCE OVERHAUL.		1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997051500425	19970515	00425	SO  	1997	5	15	97ZZZX2053       	2	19970428	G	7414	1051324	SPRING          			BLANCA	1419  	14193       	1220406	GL  	CONT  	O470  	IO470F      	17026	SO  					LT MAG	BROKEN          	B			QKKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	8838R	26   			446018	4192				BOTH MAGNETOS OVERHAULED APRIL 1995.  NEW SPRINGS INSTALLED.  BOTH SPRINGS FOUND BROKEN INTO 3 PARTS.  CAUSE APPEARED TO	 BE FROM CORROSION PITS LEADING TO STRESS POINTS.  THE REPORT WAS THAT MOST HOURS WERE FLOWN SHORTLY AFTER OVERHAUL AND 	THEN AIRCRAFT SAT.  THE SPRINGS WERE PURCHASED BY THIS CRS DURING JANUARY 10 TO MARCH 21, 1995 RECORDS.				1	L	7	1 	3O	3	O		1A3     	3E1				 
1997051500426	19970515	00426	SO  	1997	5	15	97ZZZX2054       	2	19970428	G	7414	1051324	SPRING          			BLANCA	1419  	14193       	1220406	GL  	CONT  	O470  	IO470F      	17026	SO  					RT MAG	BROKEN          	B			QKKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	8838R	26   			441258	4192				BOTH MAGNETOS OVERHAULED APRIL 1995.  NEW SPRINGS INSTALLED.  BOTH SPRINGS FOUND BROKEN INTO 3 PARTS.  CAUSE APPEARED TO	 BE FROM CORROSION PITS LEADING TO STRESS POINTS.  THE REPORT WAS THAT MOST HOURS WERE FLOWN SHORTLY AFTER OVERHAUL AND 	THEN AIRCRAFT SAT.  THE SPRINGS WERE PURCHASED BY THIS CRS DURING JANUARY 10 TO MARCH 21, 1995 RECORDS.				1	L	7	1 	3O	3	O		1A3     	3E1				 
1997052200056	19970522	00056	CE  	1997	5	22	97ZZZX2059       	1	19970414	G	5751	21992	BRACKET         		5180        	BBAVIA	8     	8KCAB       	2110612	CE  										LT/RT AILERON	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1126E	1169 				30677				UPON INSPECTION FOR RECOVER PROCESS, FOUND BRACKET P/N 2-1992 AND RIB P/N 3-446 WERE CRACKED AT SPAR ATTACH.  SL 404 COV	ERS THIS SUBJECT FOR '7' SERIES AIRCRAFT WITH 1,000 'PLUS' HOURS, BUT DOES NOT INCLUDE '8' SERIES AIRPLANES.  THIS CONDI	TION FOUND ON BOTH AILERONS.  AIRCRAFT HAS AILERON SPADES INSTALLED.				1	H	7	1 	3O				A21CE   					 
1997052200057	19970522	00057	NE  	1997	5	22	97ZZZX2060       	2	19970415	G	8500		ENGINE          			BEECH 	18    	H18         	1151012	CE  	PWA   	R985  	R985AN14B   	52008	NE  					MAIN BEARING	SEIZED          	G				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	11	117ME		420  			BA638	16729			WHILE IN CRUSE FLIGHT, PILOT NOTICED OIL PRESSURE STARTING TO DECREASE AND OIL TEMP STARTING TO RISE.  ENGINE WAS SECURE	D, PROP WAS FEATHERED, AND A PRECAUTIONARY LANDING MADE.  UPON LANDING, PILOT FOUND HE COULD NOT TURN PROP BY HAND.  SUS	PECT THAT THE MAIN BEARING FAILED.  ENGINE HAD APPROXIMATELY 420 HOURS SINCE OVERHAUL.				1	L	7	2 	3R	3	R		A765    	5E1				 
1997052200058	19970522	00058	EA  	1997	5	22	97ZZZX2061       	2	19970320	G	7314	154739506	FUEL PUMP       			BEECH 	23    	B19         	1151215	CE  	LYC   	O320  	O320E3D     	41508	EA  					PART NUMBER	MISIDENTIFIED   	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	02	2048A					MB904	L4828827A			NEW FUEL PUMP INSTALLED ON OVERHAULED ENGINE.  DURING INITIAL RUN-UP, FUEL STREAMED OUT OF CARBURETOR.  CARB RPLD WITH R	E-MFG'D ONE AND PERFORMED IN LIKE MANNER.  WHILE T/S, FOUND FUEL PUMP ONE OF A WRONG P/N,  AND CAME FROM 'A' SUPPLIER IN	 ORIG TEXTRON LYC CONTAINER MARKED FUEL PUMP P/N LW-15472 WHICH IS NUMBER ENGINE REQUIRES (4-6 PSI).  ACTUAL PART INSTAL	LED SHOWED P/N 154739506 (25-35 PSI).   FOUND FLOAT CRUSHED ON BOTH REMFG'D CARBS INSTALLED.  CHECKING STOCK REVEALED ON	E P/N 154739506 INSTALLED IN ORIG SEALED CONTAINER MARKED LW15472.  SUBMITTER SUSPECTED HIGHER PRESSURE FUEL PUMPS CAUSE	D FLOAT TO BE CRUSHED.  RECOMMEND WHEN RECEIVING PARTS FOR STOCK, ENSURE EXTERIOR MARKED P/N IS SAME AS INTERIOR PART.	1	L	7	1 	3O	3	O		A1CE    	E274				 
1997052200059	19970522	00059	CE  	1997	5	22	97ZZZX2062       	1	19970501	G	5700		STRUCTURE       			BEECH 	18    	H18         	1151012	CE  										WS 111-102	CRACKED         	B			NI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	26035					BA754				AD 75-27-09 PERFORMED ON OUTBOARD WING AT WS 111 AND WS 102.  X-RAYS REVEALED LINEAR INDICATIONS AT WS 111 AND CORROSION	 AT WS 102.  FILMS SENT TO BEECHCRAFT FOR FURTHER EVALUATION.  THIS WING NOT YET ATTACHED TO AN AIRCRAFT.  IT WAS PURCHA	SED AS A SERVICEABLE SPARE. THE ACFT IDENTIFICATION ON THIS FORM IS FOR THE ACFT THE WING MAY BE USED ON.				1	L	7	2 	3R				A765    					 
1997052200060	19970522	00060	SO  	1997	5	22	97ZZZX2063       	1	19970429	G	3240	A8504	VALVE           	GERDES      		PIPER 	PA22  	PA22        	7102202	SO  										PARKING BRAKE	CABLE MISRIG    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3461A					221735				AFTER REPAIRS TO BELLY, LANDING GEAR, AND ENGINE, THE FIRST GROUND RUN WAS PERFORMED.  THE LEFT BRAKE LOCKED UP AND WOUL	D NOT RELEASE.  THE INVESTIGATION REVEALED THE PARK BRAKE RELEASED THE RIGHT BRAKE, BUT WOULD NOT FULLY RELEASE THE LEFT	 BRAKE.  THE REMEDY WAS TO SECURE THE PARK BRAKE CABLE END CLOSER TO THE BRAKE VALVE CONTROL ARM MAKING THE ACTUATION OF	 THE PARK BRAKE VALVE MUCH MORE POSITIVE ALL THE WAY TO THE STOPS.			1	H	7	1 	3O				1A6     					 
1997052200061	19970522	00061		1997	5	22	97ZZZX2064       	4	19970419	G	2210	0655011	ACCELEROMETER   	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTION     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4082T	593  			1109	318152089				AUTOPILOT WOULD KICK OFF IN STRAIGHT AND LEVEL FLIGHT WITH NO TURBULENCE.  ALSO, THE ACCELEROMETER WOULD NOT TEST PROPER	LY IN THE UP POSITION.					1	L	7	2 	3O				A20SO   					 
1997052200062	19970522	00062	CE  	1997	5	22	97ZZZX2065       	1	19970429	G	3213	25410835	METERING TUBE   		25411001    	CESSNA	303   	T303        	2073820	CE  										LT STRUT	BROKEN          	D		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	04	4095V	10142				T30300275				AFTER TAKEOFF, PILOT ELECTED GEAR UP.  GEAR CYCLED UP  NORMALLY .  AT END OF CYCLE, AUDIBLE 'BANG' HEARD.  PILOT SELECTE	D DOWN AND GEAR EXTENDED WITH ONLY RT MAIN AND NOSE GEAR GREEN LIGHTS .  LT  MAIN GEAR STUCK UP IN WHEELWELL.  NUMEROUS 	ATTEMPTS MADE TO EXTEND LT MLG.  PILOT RETRACTED LANDING GEAR, FEATHERED, AND CAGED BOTH ENGINES, BELLIED ACFT ON NORMAL	 RUNWAY.  INVESTIGATION REVEALED METERING TUBE INSIDE LT STRUT BROKE AT A MACHINED HOLE IN SHAFT.  THIS ALLOWED LOWER PO	RTION OF SHOCK STRUT BARREL TO OVEREXTEND AND COME OUT OF UPPER BARREL DUE TO CHARGE INSIDE STRUT.  RECOMMENDATION:  NDT	 OF METERING TUBE INSIDE SHOCK STRUT AT SOME GIVEN INTERVAL UPON ACCUMULATION OF 'X' AMOUNT OF HOURS.	1	L	7	2 	3O				A34CE   					 
1997052200063	19970522	00063	CE  	1997	5	22	97ZZZX2066       	1	19970411	G	2710	05117862	CABLE CLAMP     			CESSNA	185   	A185F       	2072821	CE  										AILERON	BOLT DETACHED   	D		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	11	61423	2180 				18504180				BOLT AND NUT WHICH HOLD CLAMP ON AILERON CABLE SWEGE TO PULLEY FELL OUT ON COCKPIT FLOOR ALLOWING AILERON CONTROL CABLE 	TO SLIP AROUND CONTROL COLUMN CENTER PULLEY.  THIS CAUSED PARTIAL LOSS OF AILERON CONTROL.					1	H	7	1 	3O				3A24    					 
1997052200064	19970522	00064	CE  	1997	5	22	97ZZZX2067       	1	19970401	G	3211	24411001	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  										MAIN GEAR	CRACKED         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	03	64332	4263 				172RG0694				PIVOT ASSY CRACKED BETWEEN THE SPLINED END AND THE INTERNAL PASSAGE WAY THAT SUPPLIES THE BRAKE WITH FLUID.  PART WOULD 	ONLY LEAK DURING GEAR EXTENSION AND WHEN APPLYING BRAKES ON ROLL-OUT.					1	H	7	1 	3O				3A17    					 
1997052200066	19970522	00066	CE  	1997	5	22	97ZZZX2069       	1	19970507	G	3230	12700341	SWITCH          			CESSNA	210   	T210F       	2073422	CE  										NLG SAFETY	INTERMITTENT    	G		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	10GM	4600 				T2100151				WIRES TO SAFETY SWITCH CHAFED AND WORN INTERNALLY; ALLOWED GEAR TO RETRACT WITHOUT SWITCH BEING OPERATED.  CAUSED NOSE G	EAR TO RETRACT WITH INSUFFICIENT STRUT CHARGE.  GEAR WOULD NOT EXTEND FOR LANDING.					1	H	7	1 	3O				3A21    					 
1997052200067	19970522	00067	CE  	1997	5	22	97ZZZX2070       	1	19970414	G	5712	3446	RIB             		5180L       	BBAVIA	8     	8KCAB       	2110612	CE  										LT/RT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1126E	1169 				30677				UPON INSPECTION FOR RECOVER PROCESS, FOUND BRACKET P/N 2-1992 AND RIB P/N 3-446 CRACKED AT SPAR ATTACH.  SL 404 COVERS T	HIS SUBJECT FOR '7' SERIES AIRCRAFT WITH 1,000 'PLUS' HOURS, BUT DOES NOT INCLUDE '8' SERIES AIRCRAFT, THIS CONDITION FO	UND ON BOTH AILERONS.  AIRCRAFT HAS AILERON SPADES INSTALLED.				1	H	7	1 	3O				A21CE   					 
1997052200069	19970522	00069	CE  	1997	5	22	97ZZZX2072       	1	19970422	G	5311	1054200111	FRAME           			BEECH 	76    	76          	1153005	CE  										BS 94 RT	CRACKED         	B			BF8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3812C	6835 				ME390				FORWARD SPAR ATTACH BRACKET AT STA 94.0 LEFT AND RIGHT SIDES.  DURING ROUTINE INSPECTION, A CRACK WAS FOUND IN THE LOWER	 PORTION OF THE UPPER RADIUS FOR THE FORWARD SPAR SLOT CUT-OUT.  LEFT FRAME WAS CRACKED .3750 INCH LONG, RT FRAME FOUND 	CRACKED .0625 INCH LONG.  CAUSE:  APPEARED TO BE STRESS RELEASE CRACK.  ACT:  6,835.2 HOURS.				1	L	7	2 	3O				A29CE   					 
1997052200070	19970522	00070	CE  	1997	5	22	97ZZZX2073       	1	19970422	G	5311	1054200111	FRAME           			BEECH 	76    	76          	1153005	CE  										BS 94 LT	CRACKED         	B	S		BF8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3812C	6835 				ME390				FORWARD SPAR ATTACH BRACKET AT STA 94.0 LEFT AND RIGHT SIDES.  DURING ROUTINE INSPECTION, A CRACK WAS FOUND IN THE LOWER	 PORTION OF THE UPPER RADIUS FOR THE FORWARD SPAR SLOT CUT-OUT.  LEFT FRAME WAS CRACKED .3750 INCH LONG, RT FRAME FOUND 	CRACKED .0625 INCH LONG.  CAUSE:  APPEARED TO BE STRESS RELEASE CRACK.  ACT:  6,835.2 HOURS.				1	L	7	2 	3O				A29CE   					 
1997052200072	19970522	00072	SO  	1997	5	22	97ZZZX2075       	1	19970502	G	8120	LW31S444	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										TURBO MOUNT	SHEARED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	59829					317685081				TURBO MOUNT BOLT LOWER INBOARD AND OUTBOARD AND GETS LOOSE USUALLY AFTER 100 HOURS FLYING TIME.  SUBMITTER RECOMMENDS TH	E BOLT BE CHANGED FROM COURSE THREAD TO FINE THREAD WITH LOCKNUT.					1	L	7	2 	3O				A20SO   					 
1997052200074	19970522	00074	CE  	1997	5	22	97ZZZX2077       	1	19970422	G	5311	1054200111	FRAME           			BEECH 	76    	76          	1153005	CE  										BS 94 RT	CRACKED         	B	S		BF8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6636Z					ME253				FORWARD SPAR ATTACH BRACKET AT STA 94.0, RT SIDE.  DURING A ROUTINE INSPECTION, A CRACK WAS FOUND IN THE LOWER PORTION O	F THE UPPER RADIUS FOR THE FORWARD SPAR SLOT CUT-OUT (APPROXIMATELY .25 INCH LONG).  CAUSE:  APPEARED TO BE STRESS RELEA	SE CRACK.  ACT:  7,538 HOURS.				1	L	7	2 	3O				A29CE   					 
1997052200075	19970522	00075	CE  	1997	5	22	97ZZZX2078       	1	19970421	G	5730		SKIN            			CESSNA	340   	340A        	2076405	CE  										LT WING LE	CORRODED        	B		A	DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	6826Y					340A1216				LUMPS OBSERVED UNDER WING DE-ICE BOOT AND BOOT COMING UNGLUED.  DE-ICE BOOT WAS REMOVED AND SEVERE CORROSION FOUND.  COR	ROSION WAS REMOVED AND TREATED.  WING SKIN REPAIRED WITH AN EXTERNAL DOUBLER BONDED INTO PLACE.  SUGGEST BOOT REMOVAL FO	R INSPECTION ANY TIME LUMPS ARE FOUND UNDER DE-ICE BOOT OR WHEN BOOT HAS COME UNGLUED AND MOISTURE HAS ENTERED BETWEEN W	ING AND BOOT.			1	L	7	2 	3O				3A25    					 
1997052200077	19970522	00077	CE  	1997	5	22	97ZZZX2080       	1	19970401	G	5311	1054200111	FRAME           			BEECH 	76    	76          	1153005	CE  										BS 94 LT	CRACKED         	B			BF8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	92ER					ME425				FORWARD SPAR ATTACH BRACKET AT STA 94.0, LEFT SIDE.  DURING A ROUTINE INSPECTION, A CRACK WAS FOUND IN THE LOWER PORTION	 OF THE UPPER RADIUS FOR THE FORWARD SPAR SLOT CUT-OUT (APPROXIMATELY .1250 INCH LONG).  CAUSE:  APPEARED TO BE STRESS R	ELEASE CRACK.  ACTT:  4,396.0 HOURS.				1	L	7	2 	3O				A29CE   					 
1997052200078	19970522	00078	CE  	1997	5	22	97ZZZX2081       	1	19970408	G	2720	50150068	TORQUE TUBE     			CESSNA	401   	401A        	207590D	CE  										RUDDER	BROKEN          	G	L	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	09	671AW					401A0080				PILOT EXPERIENCED LANDING DIFFICULTIES.  UPON INSPECTION OF FLIGHT CONTROLS, TECHNICIAN DISCOVERED RUDDER CABLE ATTACH F	ITTING BROKEN OFF OF THE LT CONTROL TORQUE TUBE ASSY.  MAGNAFLUX INSPECTION OF THE RT TORQUE TUBE ASSY REVEALED IT CRACK	ED AT THE EDGE OF THE WELD IN SAME LOCATION.  PROBLEM BELIEVED TO BE CAUSED BY USE OF THE INSIDE RUDDER LOCK ASSY, P/N S	Z15027-1-11 OR DASH 13, PUTTING UNDUE STRESS ON TORQUE TUBE ASSY.  RECOMMEND USE OF AN OUTSIDE RUDDER LOCK AND A ONE-TIM	E INSPECTION OF TORQUE TUBE ASSY.  ACFT REF:  PAGE 2-406, FIG 116, INDEX -3 RT, -13 LT.		1	L	7	2 	3O				A7CE    					 
1997052200079	19970522	00079	CE  	1997	5	22	97ZZZX2082       	1	19970409	G	2710	35524664	BUNGEE SPRING   			BEECH 	33    	F33A        	1151425	CE  										AILERON	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T					CE1547				PILOT REPORTED A LOUD POPPING SOUND AND A BIND IN THE RUDDER PEDALS.  A MECHANIC PERFORMED ROUTINE INSPECTION AND FOUND 	UPPER FORWARD RUDDER AILERON BUNGEE SPRING HAD BROKEN IN HALF ON THE CLIP END SIDE.  SUBMITTER SUGGESTED DURING ROUTINE 	100-HOUR ANNUAL PROGRESSIVE INSPECTION, TO PAY CLOSE ATTENTION TO THIS AREA.				1	L	7	1 	3O				3A15    					 
1997052200471	19970522	00471	CE  	1997	5	22	97ZZZX2085       	1	19970430	G	5280	508201837	HINGE           			BEECH 	200   	B200        	1152922	CE  										NLG DOOR	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	575T					BB1384				NOSE GEAR DOOR HINGE CRACKED AT RIVET HOLE ON INBOARD SIDE.  SUSPECT CAUSE IS THAT THE HINGE IS .75 INCH THICK WITH AN O	VERSIZE -4 CHERRY MAX RIVET HOLDING IT TOGETHER.  ALL THE RIVET HOLES ON THE HINGE DECREASE THE AMOUNT OF METAL LEFT ON 	THE HINGE AT THE RIVET HOLES.  THE HINGE NEEDS TO BE REDESIGNED WITH THICKER EARS.				1	L	7	2 	4T				A24CE   					 
1997052200474	19970522	00474	CE  	1997	5	22	97ZZZX2088       	1	19970422	G	3240	1206P27	SWITCH          			CESSNA	500   	550         	2076604	CE  										PWR BRAKE PUMP	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2737K				2430	5500595				THIS SWITCH IS THE CONTROL FOR THE POWER BRAKE PUMP.  IT FAILS IN THE ELECTRICALLY 'OPEN' POSITION AND THE PUMP FAILS TO	 RUN CREATING A NO BRAKES CONDITION.  SUBMITTER STATED IN LOOKING AT PAST RECORDS FOR THE LAST 5 YEARS, HAVE CHANGED THI	S P/N SWITCH 5 TIMES IN FLEET OF 4 C-550'S.  (CESSNA P/N 38-581-501).				1	L	7	2 	4F				A22CE   					 
1997052200479	19970522	00479	NE  	1997	5	22	97ZZZX2093       	2	19970429	G	7314	GB3173CE	FUEL PUMP       			FOKKER	F27   	F27MK500    	4990629	EU  	RROYCE	DART  	DART5327R   	54509	NE  					LEFT ENGINE	SHAFT SHEARED   	C		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SO	33	709FE		4839 			10375	14206			ON CLIMB-OUT OF LCK, THE LEFT ENGINE AUTOFEATHERED.  THE CREW DECLARED AN EMERGENCY AND RETURNED TO LCK WITH NO FURTHER 	PROBLEMS.  THE MECHANIC FOUND A SHEARED SHAFT ON THE FUEL PUMP.  THE ENGINE CHECKED GOOD IAW THE FOKKER MM AFTER THE FUE	L PUMP WAS REPLACED.				2	H	7	2 	4T	4	T		A817    	E297				 
1997052200480	19970522	00480	NE  	1997	5	22	97ZZZX2094       	2	19970206	G	7250		ENGINE          			FOKKER	F27   	F27MK500    	4990629	EU  	RROYCE	DART  	DART5327R   	54509	NE  					LT ENG TURB	DAMAGED         	C		A		E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SO	33	721FE	18430	3054 			10460	14727			EWR/YMX - EN ROUTE, THE LEFT ENGINE STARTED TO AUTOFEATHER.  THE LEFT ENGINE TEMP STARTED TO RISE, THE FLIGHT CREW THEN 	MANUALLY FEATHERED THE PROP.  THE CREW DECLARED AN EMERGENCY AND WAS CLEARED TO LAND IN ALB. THE PILOT TRIED TO RESTART 	THE ENGINE, BUT IT WOULD NOT START.  THE AIRCRAFT LANDED WITHOUT ANY OTHER PROBLEMS.  A MAINTENANCE CREW WAS DISPATCHED 	TO ALB FOR THE ENGINE CHANGE.			2	H	7	2 	4T	4	T		A817    	E297				 
1997052200482	19970522	00482		1997	5	22	97ZZZX2096       	4	19970429	G	3422	1426200314	GYRO            	SIGMATEK    	46981E      															DIRECTIONAL GYRO	SHORTED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	01										EXCITATION WIRE SHORTED TO CHASIS GROUND CAUSING THE HEADING OUTPUT TO BE INOPERABLE.  SUBMITTER SUGGESTS TO INSULATE WI	RE BUNDLE FROM CHASIS DURING THE ROUTING OF THE BUNDLE.																		 
1997052200483	19970522	00483	EA  	1997	5	22	97ZZZX2097       	2	19970502	G	8530	SL139973	RETAINER KEY    								LYC   	O360  	O360*       	41514	EA  					CYLINDER KIT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15										KEY NOT CUT ON ONE SIDE.  PART IS IN A COMPLETE POWER SECTION.  NEW CYLINDER KIT S/N 97-2806.											3	O			E286				 
1997052200485	19970522	00485	SO  	1997	5	22	97ZZZX2098       	2	19970401	G	7322	63255424	LEVER           		649052A2    	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL CONTROL	MISINSTALLED    	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										DURING ROUTINE MAINTENANCE, FUEL INJECTION ASSY FOUND LOOSE.  OF THE 3 BOLTS THAT ATTACH THIS TO THE THROTTLE CONTROL AS	SY, 2 BOLTS MISSING, 1 LOOSE.  ASSY ABOUT TO BREAK LOOSE.  ALSO, SHROUD P/N 646673 BROKEN AND LOOSE, AND CHAFING ON FUEL	 LINE FITTINGS.  FITTINGS WERE CHAFED OVER 50  PERCENT THROUGH SIDE WALL THICKNESS.  APPEARS TO BE CAUSED BY THROTTLE LE	VER BEING INSTALLED INCORRECTLY AND HITTING ASSY AND SHROUD CAUSING PRESSURE AND SHEARING OF THE BOLTS.  ALSO, FULL TRAV	EL OF THE THROTTLE WAS IMPAIRED.		1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997052200486	19970522	00486	CE  	1997	5	22	97ZZZX2099       	1	19970430	G	5312	05121593	BULKHEAD        			CESSNA	172   	172M        	2072418	CE  										V FIN ATTACH	MISINSTALLED    	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	29501	8042 				17264117				VERTICAL FIN AFT SPAR TO BULKHEAD CLEARANCE EXCESSIVE.  MAXIMUM CLEARANCE .070 INCH PER CESSNA 172 SM.  P/N 0512159-3 IN	STALLED INCORRECTLY OR MACHINED INCORRECTLY BY FACTORY AT LOWER HOLE MACHINE FACE.  MISSING .090 INCH OF MATERIAL.  FIXE	D BY INSTALLING .090 INCH 204T3 SHIM ON BULKHEAD 0512159-3 AFT FACE.				1	H	7	1 	3O			NT	3A12    					 
1997052200487	19970522	00487	SO  	1997	5	22	97ZZZX2100       	1	19970429	G	7160		VALVE           			MAULE 	MX7   	MX7180      	5460185	SO  										CARBURETOR HEAT	SCREWS SHEARED  	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	3110Y	423  				20024C				DURING AN ANNUAL INSPECTION, THE CARBURETOR HEAT DIVERTER VALVE WAS FOUND SHEARED FROM THE CONTROL SHAFT.  TWO 8-32 SCRE	WS WITH SELF-LOCKING NUTS SECURE THE VALVE TO THE CONTROL SHAFT IN THE CARB AIR INTAKE BOX.					1	H	7	1 	3O			NC	3A23    					 
1997052200488	19970522	00488	SW  	1997	5	22	97ZZZX2101       	1	19970429	G	2810		DRAIN           			BBAVIA	8     	8GCBC       	1220803	SW  										FUEL TANK	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	106EB	36   				38497				ALL FOUR FUEL TANK QUICK DRAINS WERE FOUND LEAKING.  INVESTIGATION REVEALED ALL OF THE DRAIN SEALS HAD BECOME CLOGGED WI	TH ALUMINUM SHAVINGS BELIEVED TO BE FROM THE TANK MANUFACTURING PROCESS.  ALSO NOTED THE ALUMINUM DEBRIS HAD BEGUN TO BU	ILD UP IN THE MAIN FUEL STRAINER.  SUBMITTER RECOMMENDS DRAIN AND FLUSH OF FUEL SYSTEM AND REVIEW OF MANUFACTURING PROCE	SS QUALITY CONTROL.			1	H	7	1 	3O				A21CE   					 
1997052200489	19970522	00489	CE  	1997	5	22	97ZZZX2102       	1	19970427	G	3230	42104	CONTROL CABLE   		5972730     	CESSNA	185   	185D        	2072812	CE  										GEAR RETRACT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	285BG				120	1850798				BROKEN CABLE P/N 42104 ON GEAR RETRACT.  CABLE BROKE AT AFT END.  SUSPECT CAUSE FROM RUST.						1	H	7	1 	3O			 	3A24    					 
1997052200490	19970522	00490	CE  	1997	5	22	97ZZZX2103       	1	19970428	G	7110	J74444	MOUNT           	LORD        		CESSNA	172   	172N        	2072434	CE  										COWL MOUNT	SEPARATION      	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	3056E	12   				17271423				AIRCRAFT WAS TEST FLOWN AFTER ANNUAL INSPECTION.  DURING FLIGHT AT AIRSPEED 10 KNOTS LESS THAN REDLINE, THE 6 LOWER COWL	 MOUNTS FAILED AT THE BONDED AREA TO THEIR BACKING PLATE.  THE COWL CONTACTED THE SPINNER BULKHEAD WITH MINOR DAMAGE.  S	TILL HAVE 2 NEW MOUNTS PURCHASED AT THE SAME TIME AS THE ONES THAT FAILED.  THEY ARE STAMPED WITH THE PROPER NUMBERS AND	 CURE DATE, HOWEVER, THE LAST 2 DIGITS OF P/N ARE OF A LARGER SIZE NUMBER THAN THE REST OF THE P/N'S.			1	H	7	1 	3O			NT	3A12    					 
1997052200496	19970522	00496	CE  	1997	5	22	97ZZZX2109       	1	19970422	G	2730	0510105350	CONTROL CABLE   			CESSNA	182   	R182        	2072734	CE  										ELEVATOR UP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5131T	3314 				R18201821				DURING ANNUAL INSPECTION, 'UP' ELEVATOR CABLE, P/N 0510105-350, FOUND SEVERELY WORN, MANY STRANDS WORN THROUGH AT PULLEY	, FS 156.00.  CABLE 'BUZZES' ON THIS PULLEY DURING FLIGHT.  PULLEY ACTS AS FAIRLEAD; CABLE DEFLECTION ONLY A FEW DEGREES	.  PULLEY COULD BE DELETED, CABLE WOULD RUN STRAIGHT AND TRUE WITHOUT BEING DAMAGED.				1	H	7	1 	3O			RT	3A13    					 
1997052200497	19970522	00497	EA  	1997	5	22	97ZZZX2110       	2	19970428	G	8520		CONNECTING ROD  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 3 CYLINDER	DETACHED        	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SW	07	757CH	700  				15279629	L1736815			PILOT EXPERIENCED RPM DROP, LOSS OF OIL PRESSURE, AND ROUGHNESS.  LANDED ON CITY STREET.  NO AIRCRAFT DAMAGE.  FOUND OIL	 APPARENTLY EXHAUSTED THROUGH CRANKCASE BREATHER.  NR 4 CYLINDER PISTON BURNED THROUGH AFT SIDE UNDER RINGS .3750 INCH H	OLE.  NR 3 CYLINDER CONNECTING ROD BROKEN LOOSE AT END CAP.  PUNCTURED BOTTOM OF CRANKCASE.  NOTE:  APPROX 8 FLIGHT HOUR	S PREVIOUSLY, CYLINDER COMPRESSION CHECKS WERE ALL IN THE MID 70'S, OVER 80.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997052200498	19970522	00498	EA  	1997	5	22	97ZZZX2111       	2	19970428	G	8530		PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 4 CYLINDER	BURNED          	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SW	07	757CH	700  				15279629	L1736815			PILOT EXPERIENCED RPM DROP, LOSS OF OIL PRESSURE, AND ROUGHNESS.  LANDED ON CITY STREET.  NO AIRCRAFT DAMAGE.  FOUND OIL	 APPARENTLY EXHAUSTED THROUGH CRANKCASE BREATHER.  NR 4 CYLINDER PISTON BURNED THROUGH AFT SIDE UNDER RINGS .3750 INCH H	OLE.  NR 3 CYLINDER CONNECTING ROD BROKEN LOOSE AT END CAP.  PUNCTURED BOTTOM OF CRANKCASE.  NOTE:  APPROX 8 FLIGHT HOUR	S PREVIOUSLY, CYLINDER COMPRESSION CHECKS WERE ALL IN THE MID 70'S, OVER 80.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997052200505	19970522	00505	CE  	1997	5	22	97ZZZX2118       	1	19970428	G	2730	MD4615M	ROD END         	HEIM        		BEECH 	35    	S35         	1151532	CE  										RUDDERVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	8604Q	2100 				D7635				WHILE PERFORMING AD 97-06-11, ALL 4 RUDDERVATOR ROD ENDS WERE FOUND WORN AND ONE WITH CORROSION.  SB NR 2668 PERTAINS TO	 THIS SUBJECT.					1	L	7	1 	3O				3A15    					 
1997052200506	19970522	00506	CE  	1997	5	22	97ZZZX2119       	1	19970430	G	5312	07125281	BULKHEAD        			CESSNA	182   	182N        	2072730	CE  										BS 230.187	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	92391	3993 				18260184				DURING ROUTINE INSPECTION, CRACKS DETECTED IN UPPER LEFT BULKHEAD FLANGE RADIUS ABOVE RUDDER STOP.  SUBJECT IS COVERED B	Y CESSNA SL 72-3 AND AD 72-07-09.  SUSPECT CAUSE IS YEARS OF RUDDER STOP CONTACT.  SUBMITTER STATED THIS TYPE OF CRACK M	AY BE ELIMINATED BY THE USE OF EXTERNAL CONTROL LOCKS.				1	H	7	1 	3O			NT	3A13    					 
1997052200507	19970522	00507	SO  	1997	5	22	97ZZZX2120       	2	19970423	G	7414	M917	SPRING          	SLICK       	662         	CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  					IMPULSE COUPLING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	93377				7110441	21060381				TROUBLESHOOTING OF 400 RPM MAG DROP FOUND LEFT MAGNETO TIMING AT 7 DEGREES BTC.  REMOVED MAG AND FOUND IMPULSE COUPLING 	SPRING BROKEN TWO INCHES FROM OUTER END.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997052200527	19970522	00527	GL  	1997	5	22	97ZZZX2123       	2	19970401	G	7230	23005250	COMPRESSOR      			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SCROLL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	255EV		6506 			51488	89550			DURING ROUTINE VISUAL INSPECTION FOUND COMPRESSOR SCROLL CRACKED AT 7:00 O'CLOCK POSITION LOOKING FORWARD.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997052900186	19970529	00186	SW  	1997	5	29	97ZZZX2293       	1	19970416	G	6310	206050222005	SHAFT           			BELL  	206   	206B        	1181511	SW  										FREEWHEEL.	WORN            	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	206SB	442  				4214				INSPECTION FOUND FREEWHEEL SHAFT INNER RACE SEAL AREA WORN.  REPLACED WITH NEW SHAFT.						1	G	7	1 	3U				H2SW    					 
1997052900187	19970529	00187	SW  	1997	5	29	97ZZZX2294       	1	19970304	G	6720	206010795101	PITCH LINK      			BELL  	206   	206L1       	1182107	SW  										T/R	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	73MM					45180				DURING PRE-FLIGHT INSPECTION, A CRACK WAS FOUND ON THE TAIL ROTOR PITCH CHANGE LINK ADJACENT TO THE BEARING.  SUSPECT CA	USE MAY HAVE BEEN DUE TO OUT OF BALANCE TAIL ROTOR ASSEMBLY.					1	G	7	1 	3U				H2SW    					 
1997052900188	19970529	00188	EU  	1997	5	29	97ZZZX2295       	1	19970425	G	3233	1090500103	ACTUATOR        			AGUSTA	A109  	A109A       	0260109	EU  										NLG	DEFECTIVE       	D				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	03	613AC	2458 				7205				PILOT NOTICED UTILITY HYDRAULIC POWER CYCLING EXCESSIVELY.  GROUND RETRACT TEST SHOWED PROBLEM ONLY ON UPSIDE, ISOLATING	 THE PROBLEM TO NOSE GEAR ACTUATOR.  RESEALED THE PISTON O-RING.  SUBSEQUENT RETRACTION TESTS AND FLIGHT, OK.  SUBMITTER	 NOTE:  A60STA TB 109.62 - LUBRICATION OF NOSE GEAR ACTUATOR C/W EVERY 900 HRS OR 3 YEARS DOES NOT ADDRESS THIS AREA.  I	T WOULD BE ADVISEABLE TO RESEAL THIS PISTON SEAL AT THIS TIME.			1	G	7	2 	3U				H7EU    					 
1997052900189	19970529	00189	SW  	1997	5	29	97ZZZX2296       	1	19970402	G	6720	500N71123	LINK            			HUGHES	500N  	500N        	3027374	SW  										PEDAL CONTROL	BEARING LOCK UP 	G				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	07										OPERATOR REPORTS LINK BEARING ASSY HAS LIMITED LIFE DUE TO LOCKING UP OF BEARINGS CAUSES PILOT TO HAVE ERRATIC PEDAL CON	TROL HARD PEDALS, CAM, OVERSCARRING OF CLEVIS AT GEARING.  AT PRESENT, NO GREASING PER MDHC.  S/N'S NOTED LN001 THROUGH 	LN007.				1	G	7	1 	3U			NC	H3WE    					 
1997052900190	19970529	00190	SW  	1997	5	29	97ZZZX2297       	1	19970506	G	3340	A402A	LENS            			HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										OPERATOR HAS EXPERIENCED 5 EACH STROBE LENSES CRACKED AT SEAM LINE.  ALL OCCURRED ON S/N'S LN001 THROUGH LN007.						1	G	7	1 	3U			NC	H3WE    					 
1997052900191	19970529	00191	SW  	1997	5	29	97ZZZX2298       	1	19970423	G	5312	369H2532	RING ASSY       			HUGHES	500N  	500N        	3027374	SW  										FS 137.50	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	5700 				LN001				RIGHT LOWER 137.50 BULKHEAD RING ASSY CRACKED 1 INCH UP AND COMPLETELY THROUGH SKIN ATTACH TURN-BACK.  THIS CRACK IS REL	ATED TO FLOAT LIGHT INSTALLATION.					1	G	7	1 	3U			NC	H3WE    					 
1997052900192	19970529	00192	SW  	1997	5	29	97ZZZX2299       	1	19970423	G	5313	369A250015	STRINGER        			HUGHES	500N  	500N        	3027374	SW  										AFT ENG BAY	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	5700 				LN001				FIRST STRINGER LEFT OF CENTER KEEL CRACKED AT AFT END 1.50 INCHES.  THIS CRACKING APPEARS TO BE RELATED TO FLOAT LIGHT M	OUNTING PROCEDURES.					1	G	7	1 	3U			NC	H3WE    					 
1997052900193	19970529	00193	SW  	1997	5	29	97ZZZX2300       	1	19970423	G	5313	369A250016	STRINGER        			HUGHES	500N  	500N        	3027374	SW  										AFT END ENG BAY	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	5700 				LN001				STRINGER CRACKED APPROXIMATELY 1.50 INCHES LONG AT AFT END.  FIRST STRINGER TO RIGHT OF KEEL AT CENTER.  THIS CRACKING A	PPEARS TO BE RELATED TO FLOAT LIGHT MOUNTING PROCEDURE.					1	G	7	1 	3U			NC	H3WE    					 
1997052900194	19970529	00194	SW  	1997	5	29	97ZZZX2301       	1	19970407	G	5302	500N31307	BRACE           			HUGHES	500N  	500N        	3027374	SW  										NOTAR STA 137	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	522FB	5252 				LN002				UPON CHANGING FAN DRIVESHAFT, FOUND NOTAR DIAGONAL BRACE LOOSE.  WORKING RIVETS BETWEEN FITTING 500N3130-3 AND TUBE 500N	3122 AT STA 137.5.					1	G	7	1 	3U			NC	H3WE    					 
1997052900195	19970529	00195	SW  	1997	5	29	97ZZZX2302       	1	19970402	G	7810	369A8230519	EXHAUST         			HUGHES	500N  	500N        	3027374	SW  										RT EXHAUST STACK	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	522FB	400  				LN002				LOWER END AFT OF RT STACK CRACKED APPROXIMATELY 2 INCHES ON BOTTOM STARTING AT END TRAVELING THROUGH REINFORCEMENT RIDGE	 THEN CURVING TOWARD OUTBOARD SIDE OF MAIN BODY OF STACK.					1	G	7	1 	3U			NC	H3WE    					 
1997060300001	19970603	00001	SW  	1997	6	3	97ZZZX2303       	1	19970423	G	3340	A402A	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										LOWER STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	73   				LN004				LOWER AFT STROBE LENS CRACKED AND SEPARATED AT SEAM.						1	G	7	1 	3U			NC	H3WE    					 
1997052900196	19970529	00196	SW  	1997	5	29	97ZZZX2304       	1	19970423	G	3340	A402A	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	525FB	18   				LN005				LOWER STROBE LENS CRACKED ON SEAM.  FOUND ON MORNING WALK-AROUND POST-FLIGHT INSPECTION.  ACFT HRS 4,727.6.						1	G	7	1 	3U			NC	H3WE    					 
1997052900197	19970529	00197	SW  	1997	5	29	97ZZZX2305       	1	19970414	G	6322	500N711311	TUBE ASSY       			HUGHES	500N  	500N        	3027374	SW  										FAN TRANSMISSION	BINDING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	526FB	7347 				LN006				INSPECTION FOUND SPLINES WORN AT SPIDER END.  ROD BENT AT SPLINES.						1	G	7	1 	3U			NC	H3WE    					 
1997052900198	19970529	00198	SW  	1997	5	29	97ZZZX2306       	1	19970414	G	3340	A402A	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	525FB	85   				LN005				FOUND LOWER AFT STROBE LENS CRACKED AT SEAM.						1	G	7	1 	3U			NC	H3WE    					 
1997052900199	19970529	00199	SW  	1997	5	29	97ZZZX2307       	1	19970411	G	6322	500N71163	SUPPORT         			HUGHES	500N  	500N        	3027374	SW  										FAN TRANSMISSION	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	526FB	4748 				LN006				FOUND FAN TUBE SUPPORT WORN BY FAN POSITION PUSH ROD.  SPLINED TEETH IN SUPPORT GUIDE WORN EXCESSIVELY.						1	G	7	1 	3U			NC	H3WE    					 
1997052900200	19970529	00200	SW  	1997	5	29	97ZZZX2308       	1	19970506	G	6710	A21810064603	SWITCH          			HUGHES	500N  	500N        	3027374	SW  										PILOT TRIM	FAILURE         	G		A		O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	07	526FB	216  				LN006				RUNAWAY TRIM TO THE RIGHT FOUND DURING FLIGHT.						1	G	7	1 	3U			NC	H3WE    					 
1997052900201	19970529	00201	SW  	1997	5	29	97ZZZX2309       	1	19970410	G	6230	206010336005	BEARING         			BELL  	206   	206L1       	1182107	SW  										M/R	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FOUND EXCESSIVE PLAY AT TWO PLACES, SEE BELL MM L-3 FIG 62.21.  AT TEAR DOWN FOUND BEARINGS AND SPACERS WORN BEYOND LIMI	TS.  TOTAL TIME OF PARTS LESS THAN 1,000 HRS/1 YEAR SINCE REPLACEMENT.  REPLACED 5 EACH.					1	G	7	1 	3U				H2SW    					 
1997052900249	19970529	00249	SW  	1997	5	29	97ZZZX2310       	1	19970414	G	2140	20608516	SILENCER ASSY   			BELL  	206   	206L3       	1182108	SW  										HEATER	CORRODED        	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17592	4689 				51535				HEATER SILENCER HAS CORROSION AT INLET AREA AND OUTER SHIELD WHERE BLEED AIR TUBE SUPPORT PLATE IS ATTACHED.						1	G	7	1 	3U				H2SW    					 
1997052900250	19970529	00250	SW  	1997	5	29	97ZZZX2311       	1	19970422	G	5302	2060313291035	FITTING         			BELL  	206   	206L3       	1182108	SW  										TAIL BOOM LT	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17592	4689 				51535				TAIL BOOM LT ATTACH FITTING FOUND CRACKED ON PHASE B (320 HR) INSPECTION.  REPLACED FITTING.						1	G	7	1 	3U				H2SW    					 
1997052900251	19970529	00251	SW  	1997	5	29	97ZZZX2312       	1	19970401	G	6220	206310005101	BOLT            			BELL  	206   	206L3       	1182108	SW  										M/R HEAD	MISSING         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53702	8117 				51249				ROTOR HEAD BOLT THAT HOLDS THE PILLOW BLOCK IN PLACE FOUND MISSING.  FOUND DURING PMI ON 3-22-97.  REPLACED BOLT AND TOR	QUED ON MAIN ROTOR PILLOW BLOCK.					1	G	7	1 	3U				H2SW    					 
1997052900252	19970529	00252	NE  	1997	5	29	97ZZZX2313       	1	19970416	G	6210	761509100043A	BLADE           			SKRSKY	S76   	S76         	8143010	NE  										M/R	DISBONDED       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T	11432				760140				MAIN ROTOR BLADE S/N AC86-00479 HAS AREAS OF DISBOND ON LOWER SIDE SKIN JUST AFT OF TITANIUM LEADING EDGE.  FIRST AREA I	S 47.50 INCHES OUTBOARD OF ROOT END AND IS APPROXIMATELY 13 INCHES BY 1 INCH.  SECOND AREA IS 201 INCHES OUTBOARD OF ROO	T END AND APPROXIMATELY 8 INCHES BY 1 INCH.				1	G	7	2 	3U				H1NE    					 
1997052900253	19970529	00253	NE  	1997	5	29	97ZZZX2314       	1	19970416	G	6210	7615009100042A	BLADE           			SKRSKY	S76   	S76         	8143010	NE  										M/R	DISBONDED       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T	10584			A08600655	760140				MAIN ROTOR BLADE S/N A086-00655 HAS AREA OF DISBOND ON UPPER SIDE SKIN JUST OUTBOARD OF THE ROOT END LAMINATE APPROXIMAT	ELY 6 INCHES BY 6 INCHES AT A PREVIOUS REPAIR C/W BY SIKORSKEY 20.50 INCHES OUTBOARD FROM ROOT END APPROXIMATELY 2 INCHE	S FORWARD OF TRAILING EDGE.				1	G	7	2 	3U				H1NE    					 
1997052900270	19970529	00270	SW  	1997	5	29	97ZZZX2331       	1	19970414	G	6220	369A10053	DAMPER PIN      			HUGHES	500N  	500N        	3027374	SW  										M/R HEAD	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	523FB	5100 				LN003				M/R DAMPER PINS LOST EXPANSION CLAMP UP.  WILL NOT ADJUST TO HOLD DURING FLIGHT.						1	G	7	1 	3U			NC	H3WE    					 
1997052900271	19970529	00271	SW  	1997	5	29	97ZZZX2332       	1	19970411	G	6322	500N71163	SUPPORT         			HUGHES	500N  	500N        	3027374	SW  										FAN TRANSMISSION	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	523FB					LN003				FOUND FAN TUBE SUPPORT WORN.  GUIDE TEETH WORN FROM FAN PUSH ROD.						1	G	7	1 	3U			NC	H3WE    					 
1997052900296	19970529	00296	SO  	1997	5	29	97ZZZX2333       	2	19970429	G	7322	104894	CARBURETOR      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					MIX NEEDLE	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	1413Q				4021425	15072713				INSTALLED OVERHAULED CARBURETOR.  WOULD NOT MEET MINIMUM STATIC RPM OF 2,500 RPM.  ANOTHER NEW CARBURETOR MET RPM.  OLD 	UNIT OBSERVED IDLE MIXTURE NEEDLE AS TOO SHORT.  VENTURI NUT CENTERED.  SAFETY WIRE SLOPPY.					1	H	7	1 	3O	3	O		3A19    	E252				 
1997052900297	19970529	00297	SO  	1997	5	29	97ZZZX2334       	2	19970510	G	8520		CRANKSHAFT      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					JOURNAL 3-4	BROKE           	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	05	1890W	4500 	1421 			CE447	122913R			CRANKSHAFT FAILED IN FLIGHT.  BROKE THROUGH SHORT CHECK AREA BETWEEN ROD JOURNALS 3 AND 4.  ENGINE FROZE IN FLIGHT.						1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997052900298	19970529	00298	CE  	1997	5	29	97ZZZX2335       	1	19970502	G	5553	04310082	FITTING         			CESSNA	150   	150H        	2071818	CE  										V FIN ATTACH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	22172	3802 				15068115				INSPECTION FOUND VERTICAL FIN ATTACH FITTING WITH INTERGRANULAR CORROSION.  SUBMITTER STATED SINCE THIS DEFECT IS CAUSED	 BY IMPROPER QUENCHING, THERE MAY BE MORE IN SERVICE THAT WERE HEAT TREATED IN THAT BATCH.					1	H	7	1 	3O				3A19    					 
1997052900299	19970529	00299	CE  	1997	5	29	97ZZZX2336       	1	19970502	G	5553	04310081	FITTING         			CESSNA	150   	150H        	2071818	CE  										V FIN ATTACH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	22172	3802 				15068115				INSPECTION FOUND VERTICAL FIN ATTACH FITTING WITH INTERGRANULAR CORROSION.  SUBMITTER STATED SINCE THIS DEFECT IS CAUSED	 BY IMPROPER QUENCHING, THERE MAY BE MORE IN SERVICE THAT WERE HEAT TREATED IN THAT BATCH.					1	H	7	1 	3O				3A19    					 
1997052900300	19970529	00300	EA  	1997	5	29	97ZZZX2337       	2	19970429	G	7310	76292	DIAPHRAGM VALVE 		LW13889     	PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					FUEL PRESS	LOOSE           	B		A	EKIR	K				NONE                    				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	07	252MA	3433 	297  			31P33	RL48862			SCREW THAT SECURES NEEDLE VALVE TO DIAPHRAGM IN FUEL PRESSURIZATION VALVE CAME LOOSE ALLOWING NEEDLE VALVE TO COME LOOSE	 WHICH SHUT ENGINE DOWN.  SCREW STILL HAD EVIDENCE OF LOC-TITE ON THREADS.  SUSPECT THAT FUEL MAY HAVE SOFTENED LOC-TITE	 WHICH ALLOWED SCREW TO BACK OUT.				1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997052900301	19970529	00301	SO  	1997	5	29	97ZZZX2338       	1	19970401	G	7120		MOUNT           			PIPER 	PA46  	PA46310P    	7104605	SO  										ENGINE	CRACKED         	B	S		MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	286CM	1626 				468608043				FOUND ENGINE MOUNT CRACKED IN 3 SPOTS.  NOTE:  SL 1001 HAD BEEN C/W PREVIOUSLY.						1	L	7	1 	3O				A25SO   					 
1997052900302	19970529	00302	EA  	1997	5	29	97ZZZX2339       	2	19970429	G	7322	MA4SPA	CARBURETOR      	FACET       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					THROTTLE	SHAFT FROZE     	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	47717					287816126	L3589927A			THROTTLE SHAFT FROZE IN BUSHINGS.  POSSIBLE RESULT OF PREVIOUS INSTALLATION OF THROTTLE SHAFT KIT.  UNABLE TO DETERMINE 	EXACT CAUSE.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997052900303	19970529	00303	CE  	1997	5	29	97ZZZX2340       	1	19970505	G	3222	12430097	TRUNNION        			CESSNA	210   	T210N       	2073456	CE  										NLG STRUT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5154A	3894 				21063289				DURING ANNUAL INSPECTION, THE NOSE GEAR STRUT LOWER TRUNNION WAS FOUND CRACKED AT BOTH EARS WHERE THE VERTICAL BRACES AR	E ATTACHED.  THE CRACKS STARTED AT THE FWD END AND TRAVELED AFT .250 INCH ON THE RIGHT AND .125 INCH ON THE LEFT EAR.  N	OSE STEERING TURN LIMIT DOWEL PIN WAS ALSO FOUND BROKEN OFF.  CESSNA SINGLE ENGINE SB SEB 94-19 DETAILS INSPECTION REQUI	REMENTS AND REPLACEMENT PROCEDURES FOR THE LOWER TRUNNION WITH A NEW (PN 1243402-15) STRENGTHENED TRUNNION.  AS IS NOTED	 IN THE SB, AGGRESSIVE TOWING AND THE NOSE WHEEL BEING TURNED BEYOND ITS LIMITS CAN BE THE CAUSES OF THIS DAMAGE.  THE L	OWER TRUNNION WAS REPLACED AND TOW LIMIT INDICATORS APPLIED PER SEB 94-19 INSTRUCTIONS.	1	H	7	1 	3O				3A21    					 
1997052900304	19970529	00304	EA  	1997	5	29	97ZZZX2341       	2	19970501	G	8520	LW13885	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					FRONT MAIN	DETERIORATED    	B			PAWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	521WA	86   				317752103	L227268A			AT INSPECTION, AN OIL CHANGE WAS BEING STARTED AND FOUND METAL SHAVINGS IN SUMP SCREEN AND FILTER.  ENGINE WAS REMOVED A	ND SENT TO OVERHAUL FACILITY FOR TEAR DOWN AND INSPECTION.  PRELIMINARY INSPECTION REPORT REVEALED FRONT MAIN CRANKSHAFT	 BEARING FAILURE.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997052900305	19970529	00305	SO  	1997	5	29	97ZZZX2342       	1	19970430	G	5347	62557004	SEAT RAIL       			PIPER 	PA28  	PA28140     	7102802	SO  										RT OUTBOARD	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	6072W	3298 				2820085				RIGHT OUTBOARD SEAT TRACK SEVERELY CORRODED UNDER LIP OF TRACK.  SUSPECT CAUSE OF CORROSION WAS TRAPPED WATER IN THE CAR	PET FROM ENTRY INTO AIRCRAFT.  ALSO, CARPET WAS NOT OF AIRCRAFT QUALITY OR TYPE (HOME SHAG CARPET).  TO PREVENT RECURREN	CE OF CORROSION, INSPECT CARPET AND REPLACE IF NOT AIRCRAFT QUALITY AND CAREFULLY INSPECT SEAT RAIL MORE FREQUENTLY AND 	REMOVE AND TARGET ANY CORROSION FOUND.			1	L	7	1 	3O				2A13    					 
1997052900306	19970529	00306	SO  	1997	5	29	97ZZZX2343       	2	19970511	G	8530	639222	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 1 CYLINDER	HEAD SEPARATED  	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	05	727NE		511  			U20605152	570521			CYLINDER HEAD SEPARATED FROM BARREL IN FLIGHT.  PILOT NOTICED ROUGH ENGINE AND MADE PRECAUTIONARY LANDING.  FAILED CYLIN	DER WAS 'LIGHT' CASTING WHILE OTHER FIVE WERE 'HEAVY' CASTING.  HEAD SEPARATION ALSO CAUSED FUEL LINE SEPARATION AND EXH	AUST Y-PIPE DAMAGE. ENGINE HAD 511 HOURS SINCE OVERHAUL BY SHOP IN CANADA.  POSSIBLE CAUSE OF FAILURE, INTERNAL CORROSIO	N BETWEEN BARREL AND HEAD THREADS.			1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1997052900307	19970529	00307	SO  	1997	5	29	97ZZZX2344       	1	19970419	G	2821	2245800	STRAINER GASKET 			PIPER 	PA24  	PA24250     	7102404	SO  										FUEL STRAINER	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	8209P	46   				243461				REPLACED FUEL STRAINER SCREEN/GASKET IN MARCH, 1996 WITH PN 22458-00 PURCHASED FROM PIPER.  DURING ANUAL INSPECTION, FOU	ND FUEL STRAINER SEEPING AROUND CLAMP.  UNABLE TO STOP SEEP WITH NEW CLAMP.  THE DISTANCE BETWEEN BOWL ASSY AND COVER IN	 THE GASKET AREA IS .040 INCH.  THE 22458-00 SCREEN/GASKET ALSO MEASURED .040 INCH.  THIS DID NOT LET THE CLAMP PULL THE	 COVER AND BOWL TOGETHER ON THE GASKET TIGHT ENOUGH TO PREVENT LEAKING.  A NEW FAA/PMA SCREEN/GASKET FROM WEBCO AIRCRAFT	, PN W22458-000, MEASURED .068 INCH AND SEALED THE FUEL STRAINER WITH NO LEAKS.  PIPER AIRCRAFT REP STATED REQUIRED DIME	NSIONS FOR THIS GASKET WERE NOT AVAILABLE FROM PIPER AS IT IS PROPRIETARY.	1	L	7	1 	3O				1A15    					 
1997052900308	19970529	00308	CE  	1997	5	29	97ZZZX2345       	1	19970205	G	3260		GEAR WARN       			CESSNA	340   	340A        	2076405	CE  										RT MLG	MALFUNCTION     	D				K				NONE                    				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			SW	99	8618G					340A0708				RIGHT GEAR LIGHT MALFUNCTION DUE TO SUSPECTED MICROSWITCH STICKING ON RIGHT GEAR (GEAR WAS FULLY DOWN AND LOCKED WHEN RT	 GEAR LIGHT STILL NOT OPERATING).  ACFT WAS JACKED UP/GEAR CYCLED.  FAULT COULD NOT BE REPLICATED, BUT MICROSWITCH AND G	EAR RE-OILED AND LUBRICATED.				1	L	7	2 	3O				3A25    					 
1997052900309	19970529	00309	CE  	1997	5	29	97ZZZX2346       	1	19970509	G	2730	081400010	BRACKET         			CESSNA	310   	310R        	2074245	CE  										ELEV BELLCRANK	ELONGATED HOLES 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	98870	5640 				310R0626				DURING 100 HOUR INSPECTION, NOTED EXCESSIVE PLAY/SLOPE OF ELEVATOR,  FURTHER INSPECTION REVEALED ELONGATED BOLT HOLES AT	 LOCATION WHERE ELEVATOR BELLCRANK PIVOT BOLT IS SECURED AT THE BELLCRANK SUPPORT BRACKETS, BOLT HOLES LOCATED ON SUPPOR	T BRACKETS WERE ELONGATED APPROX .75 INCH.  THESE SUPPORT BRACKETS ARE LOCATED AT THE MOST AFT BULKHEAD OF TAIL ASSY.  S	USPECT CAUSE MAY BE IMPROPER RIGGING OF ELEVATOR CONTROL CABLES (TOO TIGHT).  MAYBE THESE BRACKETS CAN BE REINFORCED AT 	BOLT HOLES BY CESSNA.		1	L	7	2 	3O				3A10    					 
1997052900310	19970529	00310	CE  	1997	5	29	97ZZZX2347       	1	19970509	G	2730	081400011	BRACKET         			CESSNA	310   	310R        	2074245	CE  										ELEV BELLCRANK	ELONGATED HOLES 	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	98870	5640 				310R0626				DURING 100 HOUR INSPECTION, NOTED EXCESSIVE PLAY/SLOP OF ELEVATOR, FURTHER INS PECTION REVEALED ELONGATED BOLT HOLES AT 	LOCATION WHERE ELEVATOR BELLCRANK PIVOT BOLT IS SECURED AT THE BELLCRANK SUPPORT BRACKETS, BOLT HOLES LOCATED ON SUPPORT	 BRACKETS WERE ELONGATED APPROX .75 INCH.  THESE SUPPORT BRACKETS ARE LOCATED AT THE MOST AFT BULKHEAD OF TAIL ASSY.  SU	SPECT CAUSE MAY BE IMPROPER RIGGING OF ELEVATOR CONTROL CABLES (TOO TIGHT).  MAYBE THESE BRACKETS CAN BE REINFORCED AT B	OLT HOLES BY CESSNA.		1	L	7	2 	3O				3A10    					 
1997052900312	19970529	00312	CE  	1997	5	29	97ZZZX2349       	1	19970328	G	5711		SPAR            			BEECH 	18    	AT11        	1150202	CE  										RT WING	CORRODED        	B			UF7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05						1214				HEAVY CORROSION FOUND DURING ROUTINE INSPECTION OF MAIN SPAR.  ALSO, 2 CRACKS .1250 INCH LONG IN THE WELD AT RIGHT WS 64	.					1	L	7	2 	3R				A2582   					 
1997052900317	19970529	00317	CE  	1997	5	29	97ZZZX2353       	1	19970523	G	3230		TRANSMISSION    			PIPER 	PA24  	PA24180     	7102402	CE  										MLG	COVER FAILED    	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	7678P	2315 				242889				TRANSMISSION COVER (AS REFERENCED IN PIPER PA-24-180 SM SECTION 6, FIG 6-13, ITEM 7), FAILED BY CRACKING AROUND ATTACHME	NT LUG.  LUG BECAME LIBERATED FROM REMAINING PORTION OF COVER.  FAILURE CAUSED LANDING GEAR TO NOT LOCK IN DOWN POSITION	.  SUBMITTER RECOMMENDS PAYING PARTICULAR ATTENTION TO THIS AREA DURING INSPECTION OR REPAIR.  FAILURE COULD BE INDUCED 	BY HARD LANDING OR IMPROPER GEAR RIGGING.			1	L	7	1 	3O			NT	1A15    					 
1997052900318	19970529	00318		1997	5	29	97ZZZX2354       	1	19970207	G	2410	696233B	CSD             																	GOVERNOR SUPPORT	WRONG BOLT      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17										FOUND INCORRECT HARDWARE INSTALLED IN GOVERNOR BEARING SUPPORT.  BOLTS INSTALLED ARE P/N MS 948925.  THIS IS CONTRARY TO	 THE OEM MANUAL.  OEM APPROVED HARDWARE FOR THIS INSTALLATION IS P/N 0645-1024-28UDK.																		 
1997052900319	19970529	00319		1997	5	29	97ZZZX2355       	1	19970506	G	3241	1400252	TRANSDUCER      																	WHEEL SPEED	DEFECTIVE       	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EU	01		15494			08688					DEFECTIVE CRIMPING FOUND ON WHEEL SPEED TRANSDUCER DURING WORKSHOP INVESTIGATION.  UNIT REMOVED FROM AIRCRAFT G-CIVC ON 	MAY 6  1997.  FOR AN 'ANTI-SKID ADVISORY', MESSAGE ON AIRCRAFT'S CENTRAL MAINTENANCE COMPUTER.  FIRST VISIT OF UNIT TO W	ORKSHOPS DEFECTIVE CRIMP POSSIBLY OCCURRED DURING MANUFACTURE.  ADDITIONAL CHECK ADDED TO CHECK CRIMP INTEGRITY.																	 
1997052900272	19970529	00272	CE  	1997	5	29	97ZZZX2356       	1	19970502	G	3222	10180211P	STRUT           			BEECH 	100   	B100        	1152919	CE  										NLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	187J					BE24				NOSE LANDING GEAR STRUT UPPER BODY CASTING HAS A CRACK FROM THE LEFT LOWER GREASE FITTING TO THE BOTTOM OF THE BODY CAST	ING.  A DISTANCE OF .3125 INCH LONG.  SUBMITTER ADVISES OTHERS TO CHECK THIS AREA.					1	L	7	2 	4T				A14CE   					 
1997052900273	19970529	00273	NE  	1997	5	29	97ZZZX2357       	2	19970520	G	7260	R1309P140	O RING          		2CM82JIB    						GE    	CF700 	CF7002D     	30010	NE  					START/GEN DRIVE	LEAK            	G				A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	05							304220B			THE PILOT RETURNED AFTER 30 MINUTES DUE TO OIL PRESSURE AND OIL  QUANTITY LOSS ON NR 2 ENGINE.  AN INVESTIGATION REVEALE	D THE O-RING SEAL (ACCESS 'C') ON THE DRIVE END OF THE STARTER/GENERATOR HAD APPARENTLY BECOME DAMAGED DURING INSTALLATI	ON 3 HOURS PREVIOUSLY.  SPECIAL CARE SHOULD BE TAKEN DURING INSTALLATION OF THE SEAL AND A THOROUGH LEAK CHECK (ENGINE R	UN) AFTER INSTALLATION OF THE STARTER/GENERATOR.								4	F			E7EA				 
1997052900275	19970529	00275	SO  	1997	5	29	97ZZZX2359       	1	19970305	G	5414	1159P20504	FAIRING         			GULSTM	G1159 	G1159       	3953505	SO  										LT PYLON	DELAMINATED     	D				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			WP	01	21AM					110				LOWER LEFT PYLON SKIN MISSING.  SKIN DELAMINATED FROM HONEYCOMB AND APPARENTLY CAME OFF IN FLIGHT.  APPROXIMATE SIZE OF 	SKIN IS 12 INCHES BY 36 INCHES.  LOWER RIGHT PYLON SKIN INSPECTED AND FOUND PARTIALLY DELAMINATED.  LEFT SKIN REPLACED, 	RIGHT SKIN REPAIRED.  IF THIS IS NOT AN ISOLATED INCIDENT, THE MANUFACTRER NEEDS TO IMPROVE LAMINATING PROCESS CONTROL A	ND REQUIRE MORE FREQUENT INSPECTIONS OF THIS AREA.			2	L	7	2 	4F			RT	A12EA   					 
1997052900277	19970529	00277	EU  	1997	5	29	97ZZZX2360       	1	19970404	G	3213	200463301	UPPER MEMBER    			FOKKER	F27   	F27MK500    	4990629	EU  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	724FE					10677				INSPECTION FOUND MLG UPPER MEMBER CRACKED.  PART TOTAL CYCLES, 56,096.  PART TSO CYCLES, 6,712.  (X)						2	H	7	2 	4T				A817    					 
1997052900279	19970529	00279	CE  	1997	5	29	97ZZZX2361       	1	19970501	G	5210	511151515	HINGE           			CESSNA	441   	441         	2076020	CE  										CABIN DOOR	CRACKED         	B	S	A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	800YM	4781 				4410266				WHILE AIRCRAFT WAS IN HANGAR FOR MAINTENANCE, LOWER CABIN DOOR, AFT HINGE BROKE IN TWO.  BREAK WAS ALIGNED WITH THREE RI	VETS THAT WERE ADDED TO C/W SB PJ 81-21.  EVIDENCE OF PREVIOUS CRACKING WAS VISIBLE.  NEW HINGE WAS INSTALLED.					1	L	7	2 	3T			RT	A28CE   					 
1997052900280	19970529	00280	CE  	1997	5	29	97ZZZX2362       	1	19970502	G	2120	651532627	VALVE ASSY      			CESSNA	500   	S550        	2076607	CE  										PRESS DUCT	WORN            	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	07	92QS	9435 				S5500092				WHEN CLIMBING OUT OF 31,000 FEET, A LOUD BOOM WAS HEARD IN THE REAR OF AIRCRAFT.  CABIN ALTITUDE ROSE AT 5,000 FPM.  EME	RGENCY DESCENT INITIATED AND AIRCRAFT LANDED AT PIT.  TAIL CONE PRESSURIZATION DUCT BLOWN OFF AT CONNECTOR TO WATER SEPA	RATOR.  BEADING ON FLOOD COOLING VALVE WORN.  CONNECTOR P/N SS4-300 AND SLEEVE P/N U50-300SS ALSO WORN.  RECOMMEND PERIO	DIC CHECKS FOR SECURITY AND SERVICEABILITY OF VALVE AND CLAMP/CONNECTOR SLEEVE ASSEMBLY.			1	L	7	2 	4F			RT	A22CE   					 
1997052900281	19970529	00281	EU  	1997	5	29	97ZZZX2363       	1	19970418	G	2150	12501605BSC	COMPRESSOR      			BRAERO	DH125 	BAE125800A  	1500285	EU  										AUX AIR COND SYS	EXPLODED        	B		A	UA2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	98	4026 				258156				DURING INITIAL START-UP OF AIR CONDITIONER TO ACCOMPLISH SERVICING THE COMPRESSOR EXPLODED.  THIS DESTROYED THE HONEYCOM	B COVER, DAMAGED THREE STRINGERS AND PUNCTURED HOLE IN FUSELAGE.					2	L	7	2 	4F			RT	A3EU    					 
1997052900282	19970529	00282	SW  	1997	5	29	97ZZZX2364       	1	19970501	G	5730		SKIN            			SWRNGN	SA227 	SA227TT     		SW  										LT WING	CHAFED          	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	99JW	4836 				TT450				DURING AN ENGINE EXHAUST PIPE FAIRING CHANGE, DISCOVERED A STEEL BRAIDED FUEL VENT LINE HAD CHAFED INTO THE TOP SKIN OF 	THE LEFT WING NEAR THE EXHAUST PIPE.  THE CHAFED AREA WAS 1.25 INCHES LONG, .4375 INCH WIDE BY .017 INCH DEEP.  FAIRCHIL	D ENGINEERING DETERMINED THIS WAS STILL SERVICEABLE.  RECOMMEND THIS AREA BE INSPECTED ASAP.				2	L	7	2 	4T			RT	A5SW    					 
1997052900283	19970529	00283	NM  	1997	5	29	97ZZZX2365       	1	19970507	G	2150	758073102	HOUSING         		R72EC53A    	DHAV  	DHC8  	DHC8*       		NM  										ACM TURBINE	MISMODIFIED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	05					880416					REF.  FR26481.  AIR LEAKING AROUND FORWARD CASE.  AFTER EVALUATION AND ANALYSIS, DETERMINED ACM HOUSING HAD UNAUTHORIZED	 MODIFICATION DONE OUTSIDE OF HAMILTON STANDARD.  IT WAS MODIFIED FROM A R72/EC53A HOUSING (MILITARY APPLICATION ONLY) T	O ACCOMODATE R80/EC35A PARTS AND COMPONENTS.				2	H	7	2 	4T			RT	A13NM   					 
1997052900284	19970529	00284	CE  	1997	5	29	97ZZZX2366       	1	19970502	G	7120	909100141	MOUNT           			BEECH 	100   	B100        	1152919	CE  										ENGINE TRUSS	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	187J	3894 				BE24				DURING ROUTINE INSPECTION, DISCOVERED THE RIGHT ENGINE MOUNT TRUSS HAD BEEN CHAFED BEYOND ALLOWABLE LIMITS IN TWO PLACES	 BY A NR 8 STAINLESS STEEL HARD OIL SCAVAGE RETURN LINE.  SUBMITTER ADVISES OTHERS WITH KA-B-100'S TO CHECK THIS AREA OF	 MOUNT TRUSS.  THE CHAFED AREA WAS IN THE FORWARD BOTTOM AND OUTBOARD PORTION OF THE U-SHAPED PART.				1	L	7	2 	4T				A14CE   					 
1997052900285	19970529	00285	SW  	1997	5	29	97ZZZX2367       	1	19970501	G	5620		WINDOW          			GULSTM	690TP 	690A        	0141722	SW  										CABIN	DAMAGED         	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	80TB	5676 				11300				DURING A ROUTINE 100-HOUR INSPECTION, DISCOVERED FIVE OF THE CABIN AND COCKPIT PLASTIC SIDE OUTER WINDOW PANELS HAD MELT	ED AND DETERIORATED DEPRESSIONS ALONG THE BOTTOM HORIZONTAL EDGES WHERE THE WINDOW MEETS THE AIRFRAME.  THE SUSPECTED CA	USE IS FROM PAINT STRIPPER CONTACTING THE PLASTIC WINDOWS.				1	H	7	2 	3T				2A4     					 
1997052900286	19970529	00286	CE  	1997	5	29	97ZZZX2368       	1	19970502	G	2612		FIRE LOOP       			BEECH 	200   	200BEECH    	1152920	CE  										ENGINE	CONTAMINATED    	B	L		ABOR	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			GL	15	83GA					BB518				INTERMITTENT FIRE WARNING ON START-UP.  TROUBLESHOOTING REVEALED THAT SUSPECT CAUSE IS MOISTURE CONTAMINATION OF FIRE LO	OP DETECTORS.					1	L	7	2 	4T				A24CE   					 
1997052900287	19970529	00287		1997	5	29	97ZZZX2369       	4	19970501	G	2210		SWITCH          			SWRNGN	SA227 	SA227TT     		SW  										YAW DAMPENER	MISWIRED        	B		A	W6NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	99JW	4836 				TT450				DURING THE PROCESS OF TROUBLESHOOTING A YAW DAMPENER PROBLEM, DISCOVERED THE POSITION OF THE SWITCH (RIGHT OR LEFT),INDI	CATING FROM WHICH BUS IT RECEIVED POWER, WAS REVERSED.  CORRECTED THIS CONDITION AND ASSUMED THE AIRCAFT HAS BEEN WIRED 	THIS WAY SINCE IT WAS MANUFACTURED.				2	L	7	2 	4T			RT	A5SW    					 
1997052900288	19970529	00288	SW  	1997	5	29	97ZZZX2370       	1	19970501	G	5414	2735166905	FAIRING         			SWRNGN	SA227 	SA227TT     		SW  										RT EXHAUST	CHAFED          	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	99JW	4836 				TT450				BOTH LEFT AND RIGHT ENGINE EXHAUST PIPE FAIRINGS WERE FOUND CHAFED COMPLETELY THROUGH THE LOWER PORTION OF THE SEAL AND 	INNER FLANGE OF THE FAIRINGS.  THIS WAS DISCOVERED DURING THE NORMAL A AND B LETTER CHECK INSPECTION.					2	L	7	2 	4T			RT	A5SW    					 
1997052900289	19970529	00289	SW  	1997	5	29	97ZZZX2371       	1	19970501	G	5414	2735166906	FAIRING         			SWRNGN	SA227 	SA227TT     		SW  										LT EXHAUST	CHAFED          	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	99JW	4836 				TT450				BOTH LEFT AND RIGHT ENGINE EXHAUST PIPE FAIRINGS WERE FOUND CHAFED COMPLETELY THROUGH THE LOWER PORTION OF THE SEAL AND 	INNER FLANGE OF THE FAIRINGS.  THIS WAS DISCOVERED DURING THE NORMAL A AND B LETTER CHECK INSPECTION.					2	L	7	2 	4T			RT	A5SW    					 
1997052900290	19970529	00290	SW  	1997	5	29	97ZZZX2372       	1	19970501	G	3243	VI151125	MASTER CYLINDER 			SWRNGN	SA227 	SA227TT     		SW  										BRAKE	LEAKING         	B			W6NR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	99JW					TT450				DURING A ROUTINE AND B LETTER CHECK, FOUND BOTH PILOTS' LEFT AND RIGHT MASTER CYLINDERS LEAKING.  BOTH CYLINDERS WERE RE	PLACED.					2	L	7	2 	4T			RT	A5SW    					 
1997052900291	19970529	00291	GL  	1997	5	29	97ZZZX2373       	3	19970420	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	BOLT HOLE	CRACKED         	H			CB9T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6199Q	9361 	5106 			15288191		R775205		WHEN C/W AD 95-21-01, VISUAL INSPECTION OF PROPELLER HUB, A CRACK WAS FOUND FROM BOLT HOLE TO THE EDGE OF THE HUB APPROX	IMATELY 1 INCH IN DEPTH.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997052900294	19970529	00294	SW  	1997	5	29	97ZZZX2376       	1	19970312	G	6310	212040687001	COUPLING        			BELL  	412   	412         	1182202	SW  										MAIN DRIVE	PITTED          	B			VE3D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	412WP	91   			A4136	33170				ACFT TT 2,225.8 HOURS.  ON A 6-MONTH (180 DAY) INSPECTION, M/D/SHAFT WAS REMOVED FOR INSPECTION AND REPACK OF GREASE COU	PLINGS.  BOTH INNER GEARS AND BOTH OUTER COUPLINGS WERE FOUND WITH CORROSION AND PITTING.  TOTAL TIME ON M/D/SHAFT WAS 9	1.3 HOURS SINCE NEW AND 6 MONTHS SINCE INSTALLATION.  BELL HELICOPTER WAS NOTIFIED AND NEW PARTS INSTALLED.				1	G	7	2 	4U				H4SW    					 
1997060300003	19970603	00003	SW  	1997	6	3	97ZZZX2377       	1	19970503	G	2810	369A81205	CAP             			HUGHES	500N  	500N        	3027374	SW  										RT SIDE FUEL	NO LOCK         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB					LN001				ACFT S/N LN001 THROUGH LN007 REPORTED 30 EACH FUEL CAPS HAVE WORN LOCK TABS AND REQUIRED REPLACEMENT.  FUEL CAP WILL NOT	 LOCK PROPERLY.  NO REPAIR CAP HAS TO BE CHANGED.					1	G	7	1 	3U			NC	H3WE    					 
1997052900295	19970529	00295	SW  	1997	5	29	97ZZZX2378       	1	19970503	G	2810	369A81205	CAP             			HUGHES	500N  	500N        	3027374	SW  										FUEL TANK	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB					LN001				LOCK TAB ON FUEL CAP WORN AT CAM END.  FUEL CAP WILL NOT LOCK PROPERLY.  NO REPAIR.  CAP MUST BE REPLACED.						1	G	7	1 	3U			NC	H3WE    					 
1997060500001	19970605	00001	NM  	1997	6	5	97ZZZX2379       	1	19970401	G	5311		FRAME           			BOEING	727   	727230      	1384080	NM  										BS 1090 S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FORWARD FACE OF FRAME 1090 AND ON TOP OF THE FRAME EXTENDING F	ROM S21L TO S22L.					2	L	7	3 	4F				A3WE    					 
1997060500002	19970605	00002	NM  	1997	6	5	97ZZZX2380       	1	19970401	G	5311		FRAME           			BOEING	727   	727230      	1384080	NM  										BS 990 S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION NOTED ON TOP CAP OF FRAME STA 990 AT S22L.						2	L	7	3 	4F				A3WE    					 
1997060500003	19970605	00003	NM  	1997	6	5	97ZZZX2381       	1	19970401	G	5313		SRINGER         			BOEING	727   	727230      	1384080	NM  										BS 1030 S29R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION NOTED ON S29R EXTENDING FROM STA 1030 TO STA 1050.						2	L	7	3 	4F				A3WE    					 
1997060500004	19970605	00004	NM  	1997	6	5	97ZZZX2382       	1	19970401	G	5330		SKIN            			BOEING	727   	727230      	1384080	NM  										BS 950B-950C	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION NOTED ON INNER SKIN BETWEEN FS 950B AND STA 950C, AND BETWEEN S22L AND S23L	.					2	L	7	3 	4F				A3WE    					 
1997060500005	19970605	00005	NM  	1997	6	5	97ZZZX2383       	1	19970401	G	5313		STRINGER        			BOEING	727   	727230      	1384080	NM  										BS 950D S22L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION NOTED ON S22L AT STA 950D.						2	L	7	3 	4F				A3WE    					 
1997060500006	19970605	00006	NM  	1997	6	5	97ZZZX2384       	1	19970401	G	5311		FRAME           			BOEING	727   	727230      	1384080	NM  										BS 1010	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION NOTED ON FRAME 1010 BETWEEN S27R TO S26R.						2	L	7	3 	4F				A3WE    					 
1997060500007	19970605	00007	NM  	1997	6	5	97ZZZX2385       	1	19970401	G	5311		FRAME           			BOEING	727   	727230      	1384080	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION NOTED ON FRAME 1166 BETWEEN S23L AND S22L.						2	L	7	3 	4F				A3WE    					 
1997060500008	19970605	00008	NM  	1997	6	5	97ZZZX2386       	1	19970401	G	5311		FRAME           			BOEING	727   	727230      	1384080	NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION NOTED ON FRAME 1130 EXTENDING FROM S21L TO S22L.						2	L	7	3 	4F				A3WE    					 
1997060500009	19970605	00009	SW  	1997	6	5	97ZZZX2387       	1	19970502	G	6220	206011118001	BEARING         		206011100147	BELL  	206   	206L3       	1182108	SW  										M/R HUB	FAILED          	B		A	LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	721LL	1168 			A499	51164				AT DISASSEMBLY, FOUND BEARING BREAKING UP.  ROLLERS WERE BROKEN AND GRINDING UP.  THIS BEARING IS ONE OF TWO BETWEEN YOK	E AND GRIP.					1	G	7	1 	3U				H2SW    					 
1997060500294	19970605	00294	NE  	1997	6	5	97ZZZX2476       	1	19970209	G	6320	643520536101	MAIN SHAFT      		643520500048	SKRSKY	S64   	S64F        		NE  										MGB SPLINES	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	158AC	2969 	2199 		55	64081				DURING O/H OF MGB, THE MAIN SHAFT WAS SUBJECTED TO A FMPI.  ONE SPLINE FOUND CRACKED ACROSS THE SPLINE WIDTH ON UPPER EN	D OF LOWER SPLINE.  THE CRACK DID NOT APPEAR TO ORIGINATE WHERE THE LOWER PLANETARY SPLINE CONTACTS THE SHAFT, BUT WAS L	OCATED APPROX 0.100 INCH ABOVE PLANETARY PLATE SPLINE CONTACT ZONE.  THE CRACK EXTENDED FROM ROOF OF ONE SPLINE TOOTH TO	 THE ROOT OF ADJACENT SPLINE.  APPROX 30 ADDITIONAL SPLINES HAD UNUSUAL CRACK-LIKE INDICATIONS IN ROOT RADIUS OF THE SPL	INES.  THESE INDICATIONS COULD NOT BE VERIFIED TO BE THE START OF CRACK.  THE S HAFT IS BEING SENT TO A LAB FOR DESTRUCT	IVE ANALYSIS OF THE CRACK AND ALL INDIC ATIONS.  NOTE: THIS MDR PREVIOUSLY SUBMITTED, BUT INFO HAS BEEN CORRECTED.	2	G	7	2 	4U				H6EA    					 
1997060500295	19970605	00295	NE  	1997	6	5	97ZZZX2477       	1	19970304	G	6320	643520536101	MAIN SHAFT      		643520500048	SKRSKY	S64   	S64F        		NE  										MGB SPLINES	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC	3428 	2436 		01	64084				MGB MAIN SHAFT INSPECTION.  TWO SPLINES FOUND CONTAINING ONE INDICATION EACH.  INDICATIONS LOCATED ON THE LOAD SIDE OF T	HE SPLINE AND IN THE ROOT AREA.  LENGTH OF INDICATIONS WERE APPROXIMATELY 0.100 INCH LONG.  INDICATION DID NOT EXTEND ON	TO THE TOOTH FACE OF SPLINE.  INDICATIONS WERE FOUND DURING MPI INSPECTION.				2	G	7	2 	4U				H6EA    					 
1997060500296	19970605	00296	NE  	1997	6	5	97ZZZX2478       	1	19970317	G	6320	643520536101	MAIN SHAFT      		643520500048	SKRSKY	S64   	S64F        		NE  										MGB SPLINES	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	163AC	3473 	338  		65	64093				MGB MAIN SHAFT INSPECTION, CRACKS FOUND IN LOWER SPLINES.  CRACKS APPEAR TO START IN SPLINE RADIUS AND TRAVEL AT 45 DEGR	EES TOWARD THE SPLINE TOOTH.  INDICATIONS ARE ON THE LOAD SIDE JUST AT OR BELOW ENGAGEMENT AREA.  ELEVEN SPLINES WITH IN	DICATIONS.  LONGEST INDICATION IS 0.150 INCH LONG AND IS APPROXIMATELY 0.6 INCH BELOW THE TOP OF THE LOWER SPLINE.  NOTE	:  THIS MDR PREVIOUSLY SUBMITTED, BUT INFORMATION HAS BEEN CORRECTED.			2	G	7	2 	4U				H6EA    					 
1997060500298	19970605	00298	SW  	1997	6	5	97ZZZX2480       	1	19970430	G	6310	214040841101	SEAL            			BELL  	206   	206L4       	1182110	SW  										FREEWHEEL	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	696BA	23   				52166				REPLACED FREEWHEELING UNIT TAIL ROTOR OUTPUT DRIVE SEAL DUE TO LEAKING OIL.  ACFT TT, 407.4 HOURS.						1	G	7	1 	3U			NC	H2SW    					 
1997060500300	19970605	00300	SW  	1997	6	5	97ZZZX2481       	1	19970416	G	6520	99199	SLEEVE          			BELL  	206   	206B        	1181511	SW  										T/R GRBOX SHAFT	LEAKING         	B			GS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	206SB	442  				4214				INSPECTION FOUND T/R GEARBOX INPUT SHAFT SLEEVE LEAKING.  REPLACED WITH NEW SLEEVE.						1	G	7	1 	3U				H2SW    					 
1997060500302	19970605	00302	EU  	1997	6	5	97ZZZX2483       	1	19970307	G	5240	F50B281043	DOOR            			AMD   	FALC50	FALCON50MYST	2730106	EU  										DOOR 170A	DEPARTED        	B		A	JZBR	O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			EA	25	96UH					55				REPORTED BELLY DOOR 170A P/N F50B281043 DEPARTED AIRCRAFT DURING CLIMB AND DAMAGED RT MLG DOOR.  SUBMITTER BELIEVES THE 	LAV SERVICE DOOR MOUNTED IN DOOR 170A IS LIFTING INTO AIR STREAM AND CAUSING DOOR 170A TO DEPART ACFT.  SUBMITTER STATES	 MFG'R BELIEVES LAV SERVICE DOOR LIFTS INTO AIR STREAM DUE TO WEAR OR OTHER REASONS.				2	L	7	3 	4F				A46EU   					 
1997060500303	19970605	00303	EU  	1997	6	5	97ZZZX2484       	1	19970307	G	5240	F50B281043	DOOR            			AMD   	FALC50	FALCON50MYST	2730106	EU  										DOOR 170A	DEPARTED        	B		A	JZBR	O				OTHER                   				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			EA	25	99JD					129				REPORTED BELLY DOOR 170A P/N F50B281043 DEPARTED AIRCRAFT DURING CLIMB AND DAMAGED RT MLG DOOR.  SUBMITTER BELIEVES THE 	LAV SERVICE DOOR MOUNTED IN DOOR 170A IS LIFTING INTO AIR STREAM AND CAUSING DOOR 170A TO DEPART ACFT.  SUBMITTER STATES	 MFG'R BELIEVES LAV SERVICE DOOR LIFTS INTO AIR STREAM DUE TO WEAR OR OTHER REASONS.				2	L	7	3 	4F				A46EU   					 
1997060500304	19970605	00304	NE  	1997	6	5	97ZZZX2485       	2	19970501	G	7310	F2MA521501100AZ	LINE            			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   		CFE73811B   		NE  					FUEL DIST	CRACKED         	B			CW1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	790M	766  				019				MAINTENANCE PERSONNEL NOTICED FUEL ON BOTTOM OF ENGINE COWL.  FURTHER INVESTIGATION REVEALED A CRACKED WELD IN THE MAIN 	FUEL SUPPLY LINE WHERE THE FUEL PRESSURE SENDER IS LOCATED.  LOCATION OF THE SENDER MAY IMPOSE UNDUE STRESS ON THE WELD.					2	K	7	3 	4F	4	F	RT	A50NM   	E44NE				 
1997060500305	19970605	00305	NM  	1997	6	5	97ZZZX2486       	1	19970422	G	2620	1032894	SELECTOR VALVE  			BOEING	707   	707153B     		NM  										NR 1 ENGINE	FAILED          	H		A		E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	15	2MIL					17926				IN FLT FIRE WARNING LIGHT INDICATING A FIRE ON NR 1 ENG.  CREW C/W EMERG PROCEDURES, SECURED ENG AND FIRED EXT.  ACFT LA	NDED OK.  FOUND FALSE FIRE WARN CAUSED BY OIL SOAKED HARNESS.  DURING REPLACEMENT OF DISCHARGED FIRE BOTTLE, FOUND SHUTO	FF VALVE FAILED AND PLUMBING UNDER PRESSURE.  BOTTLE HAD FIRED, BUT VALVE FAILURE CAUSED AGENT TO NOT REACH ENG.  THE EV	ENT CAUSED USAF TO CK ALL C-137B/C ACFT FOR PROPER OPER OF FIRE SELECTOR VALVE P/N 10-3289-4 (MFG MAROTTA P/N 215343-4).	  SB 3326 ISSUED IN 1977 REF:  FIRE EXT VALVES P/N 10-3289-1 AND -3.  SUBMITTER STATED AFTER INSPECTING 77 ACFT, 10 SELE	CTOR VALVES HAVE BEEN FOUND THAT DID NOT PASS THE FUNCTIONAL TEST.	2	L	7	4 	4J			F	4A21    					 
1997060500306	19970605	00306	NM  	1997	6	5	97ZZZX2487       	1	19970508	G	5330		SKIN            			BOEING	727   	7272J4      	1384006	NM  										BS 277L STR 17L	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC									GOUGE IN SKIN STA 277L STR 17L.  GOUGE IS BEYOND LIMITS.  REPAIR IAW SRM 53-30-3 FIG 1.						2	L	7	3 	4F			RT	A3WE    					 
1997060500307	19970605	00307	NM  	1997	6	5	97ZZZX2488       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										BS 1070-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON TRANSITION PANEL FS 1070 - FS 1130.  FABBED NEW PANEL IAW 727 SRM 51-20-1 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500308	19970605	00308	NM  	1997	6	5	97ZZZX2489       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 1166 LBL 3	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON FLOOR BEAM FS 1166 AND LBL 3.  REMOVED AND REPLACED DAMAGED SECTION IAW 727 SRM 53-10-5 FIG 6 AND SRM 51-30	-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500309	19970605	00309	NM  	1997	6	5	97ZZZX2490       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 1166 LBL 6	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON FLOOR BEAM FS 1166 AND LBL 6.  REMOVED AND REPLACED DAMAGED SECTION FS 1166 - IAW 727 SRM 53-10-5 FIG 6 AND	 SRM 51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500310	19970605	00310	NM  	1997	6	5	97ZZZX2491       	1	19970508	G	5347		TRACK           			BOEING	727   	7272J4      	1384006	NM  										FWD GALLEY	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FWD GALLEY NR 1 INBD SEAT TRACK CORRODED.  INSTALLED SEAT TRACK IAW 727 SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500311	19970605	00311	NM  	1997	6	5	97ZZZX2492       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 1166 RBL 12	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON FLOOR BEAM FS 1166 RBL 12.  REPLACED FLOOR BEAM SECTION IAW SRM 51-30-2 AND SRM 53-10-5 FIG 6.						2	L	7	3 	4F			RT	A3WE    					 
1997060500312	19970605	00312	NM  	1997	6	5	97ZZZX2493       	1	19970508	G	5320		DOUBLER         			BOEING	727   	7272J4      	1384006	NM  										SERVICE DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				DOUBLER AT SERVICE DOOR PAN FOUND CORRODED OUT OF LIMITS IAW 727 SRM 53-30-01.  REPAIRED IAW 727 SRM 51-20-1 AND SRM 51-	30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500313	19970605	00313	NM  	1997	6	5	97ZZZX2494       	1	19970508	G	5320		ANGLE           			BOEING	727   	7272J4      	1384006	NM  										L2 DOOR FLOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FLOOR ANGLE CORRODED AT L-2 DOOR.  REPAIRED ANGLE IAW BAE 727 SRM 51-20-1.						2	L	7	3 	4F			RT	A3WE    					 
1997060500314	19970605	00314	NM  	1997	6	5	97ZZZX2495       	1	19970508	G	5320		ANGLE           			BOEING	727   	7272J4      	1384006	NM  										AFT GALLEY FLOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				AFT GALLEY FLOOR 'L' ANGLE CORRODED.  REPAIRED IAW BAC 727 SRM 51-10-6 AND SRM 51-10-1.						2	L	7	3 	4F			RT	A3WE    					 
1997060500315	19970605	00315	NM  	1997	6	5	97ZZZX2496       	1	19970508	G	5313		STRINGER        			BOEING	727   	7272J4      	1384006	NM  										BS 700-720 26L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON STR 26L BETWEEN FS 700 - FS 720.  REPAIRED IAW BAC727 SRM 53-10-3 DETAIL I.						2	L	7	3 	4F			RT	A3WE    					 
1997060500316	19970605	00316	NM  	1997	6	5	97ZZZX2497       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										FWD PIT FS 620	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FORWARD PIT, CORROSION UNDER  TRANSITION PANEL AT FS 620 RBL 18.  REPAIRED IAW BAC 727 SRM'S 53-10-1, 53-10-2, 51-20-1, 	51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500317	19970605	00317	NM  	1997	6	5	97ZZZX2498       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										BS 560 RBL 18	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FWD PIT CORROSION UNDER TRANSITION PANEL AT FS 650 RBL 18.  REPAIRED IAW BAC 727 SRM'S 51-10-6, 51-20-1, 51-10-2, AND 51	-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500318	19970605	00318	NM  	1997	6	5	97ZZZX2499       	1	19970508	G	5313		STRINGER        			BOEING	727   	7272J4      	1384006	NM  										BS 481 STR 8L	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CRACK IN STRINGER AT BS 481 STR 8L.  REPAIRED IAW BAC 727 SRM'S 53-30-3, 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500319	19970605	00319	NM  	1997	6	5	97ZZZX2500       	1	19970508	G	5347		SEAT TRACK      			BOEING	727   	7272J4      	1384006	NM  										BS 1090 RBL 24	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				SEAT TRACK CORRODED BS 1090 - BS 1140 RBL 24.  REPLACED SEAT TRACK IAW BAC 727 SRM 53-10-5.						2	L	7	3 	4F			RT	A3WE    					 
1997060500320	19970605	00320	NM  	1997	6	5	97ZZZX2501       	1	19970508	G	5320		SUPPORT         			BOEING	727   	7272J4      	1384006	NM  										FWD LAVATORY	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FWD LAVATORY SUPPORT CORRODED.  REPLACED SUPPORT IAW BAC 727 SRM'S 51-30-5, 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500321	19970605	00321	NM  	1997	6	5	97ZZZX2502       	1	19970508	G	5347		SEAT TRACK      			BOEING	727   	7272J4      	1384006	NM  										FWD GALLEY	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FWD GALLEY SEAT TRACK CORRODED.  REPLACED SEAT TRACK IAW BAC 727 SRM'S 51-40-4, 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500322	19970605	00322	NM  	1997	6	5	97ZZZX2503       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										PNL 9501	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				PANEL 9501 CORRODED BEYOND LIMITS AT FASTENER HOLES.  FABBED AND INSTALLED NEW REPAIR PARTS PER 727 SRM'S 55-30-7 AND 51	-30-02.					2	L	7	3 	4F			RT	A3WE    					 
1997060500323	19970605	00323	NM  	1997	6	5	97ZZZX2504       	1	19970508	G	5320		Z CHANNEL       			BOEING	727   	7272J4      	1384006	NM  										RT BS 320	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON Z-CHANNEL AT FS 320 RT NOSE GEARBOX.  REAPAIRED EXTRUSION IAW BAC 727 SRM 51-40-4 PG 5.						2	L	7	3 	4F			RT	A3WE    					 
1997060500324	19970605	00324	NM  	1997	6	5	97ZZZX2505       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										PNL 3458	CORROSION       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				BLOW OUT PANEL 3458 HAS CORROSION AT BONDING WIRE ATTACH.  FABBED AND INSTALLED NEW PANEL 3458 IAW 727 SRM'S 51-40-3 AND	 51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500325	19970605	00325	NM  	1997	6	5	97ZZZX2506       	1	19970508	G	5320		ANGLE           			BOEING	727   	7272J4      	1384006	NM  										BS 351.2 RT SIDE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION AT FS 351.2 RIGHT SIDE OF NOSE GEARBOX ON ANGLE BELOW FLOOR LEVEL.  REPAIRED ANGLE IAW BAC SRM 727-51-40-03.						2	L	7	3 	4F			RT	A3WE    					 
1997060500326	19970605	00326	NM  	1997	6	5	97ZZZX2507       	1	19970508	G	2730		PCU             			BOEING	727   	7272J4      	1384006	NM  										LT ELEVATOR	LEAKING         	B			KT3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	290SC					20764				LEFT ELEVATOR PCU LEAKING.  REMOVED AND REPLACED PCU IAW BAC 727 MM 27-30-81.						2	L	7	3 	4F			RT	A3WE    					 
1997060500327	19970605	00327	NM  	1997	6	5	97ZZZX2508       	1	19970508	G	5755		SUPPORT STRUT   			BOEING	727   	7272J4      	1384006	NM  										NR 6 SPOILER	DENTED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				DENT IN SUPPORT STRUT FOR NR 6 SPOILER.  REPLACED SUPPORT STRUT WITH NEW BAC PART.						2	L	7	3 	4F			RT	A3WE    					 
1997060500328	19970605	00328	NM  	1997	6	5	97ZZZX2509       	1	19970508	G	5523		TAB             			BOEING	727   	7272J4      	1384006	NM  										LT ELEVATOR	DELAMINATED     	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				ELEVATOR TAB DELAMINATED.  REPAIRED IAW BAC 727 SRM 51-40-6 PARA 3 AND FIG 13.						2	L	7	3 	4F			RT	A3WE    					 
1997060500329	19970605	00329	NM  	1997	6	5	97ZZZX2510       	1	19970508	G	5330		SKIN            			BOEING	727   	7272J4      	1384006	NM  										BS 351.2	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION AT FS 351.2 BELOW FLOOR.  REPAIRED IAW BAC 727 SRM 51-40-03 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500330	19970605	00330	NM  	1997	6	5	97ZZZX2511       	1	19970508	G	5730		PANEL           			BOEING	727   	7272J4      	1384006	NM  										RT WING 8612	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				RIGHT WING ACCESS PANEL 8612 CORRODED.  REPAIRED IAW BAC SRM 727 51-40-6 PAR 3 E, F, 2C, J, AND K.						2	L	7	3 	4F			RT	A3WE    					 
1997060500331	19970605	00331	NM  	1997	6	5	97ZZZX2512       	1	19970508	G	5320		SUPPORT         			BOEING	727   	7272J4      	1384006	NM  										L2 SERVICE DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				GALLEY FLOOR AND SUPPORT CORRODED AT L-2 SERVICE DOOR.  REPAIRED IAW BAC 727 SRM 51-20-1 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500332	19970605	00332	NM  	1997	6	5	97ZZZX2513       	1	19970508	G	5520		FITTING         			BOEING	727   	7272J4      	1384006	NM  										NR 4 ELEV HINGE	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				NR 4 ELEVATOR HINGE FITTING CRACKED AT T-E BEAM.  REPAIRED IAW BAC 727 SRM 55-10-4 FIG 5.						2	L	7	3 	4F			RT	A3WE    					 
1997060500333	19970605	00333	NM  	1997	6	5	97ZZZX2514       	1	19970508	G	7110		NOSE COWL       			BOEING	727   	7272J4      	1384006	NM  										NR 3 ENGINE	DENTED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				NR 3 ENGINE NOSE COWL DENTED.  REPAIRED NOSE COWL IAW DAC SRM 54-04A PAGE 3.  NOTE:  VALSAN MOD.						2	L	7	3 	4F			RT	A3WE    					 
1997060500334	19970605	00334	NM  	1997	6	5	97ZZZX2515       	1	19970508	G	5520		FITTING         			BOEING	727   	7272J4      	1384006	NM  										RT ELEV NR 4	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				RIGHT NR 4 ELEVATOR HINGE ATTACH FITTING CRACKED.  REPAIRED IAW BAC SRM 727-5T5-10-04 FIG 5.						2	L	7	3 	4F			RT	A3WE    					 
1997060500335	19970605	00335	NM  	1997	6	5	97ZZZX2516       	1	19970508	G	5520		FITTING         			BOEING	727   	7272J4      	1384006	NM  										RT ELEV NR 5	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				RIGHT NR 5 ELEVATOR HINGE ATTACH FITTING CRACKED.  REPAIRED IAW BAC 727 SRM 55-10-04 FIG 6.						2	L	7	3 	4F			RT	A3WE    					 
1997060500336	19970605	00336	NM  	1997	6	5	97ZZZX2517       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 1166 RBL 15	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON FLOOR BEAM FS 1166 AND RBL 15.  FABBED AND INSTALLED REPAIR PARTS IAW 727 SRM'S 51-30-2, 53-10-5 FIG 6.						2	L	7	3 	4F			RT	A3WE    					 
1997060500337	19970605	00337	NM  	1997	6	5	97ZZZX2518       	1	19970508	G	5520		FITTING         			BOEING	727   	7272J4      	1384006	NM  										LT ELEV NR 5	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				LEFT NR 5 ELEVATOR HINGE ATTACH FITTING CRACKED.  REPAIRED IAW BAC 727 SRM 55-10-04 FIG 6.						2	L	7	3 	4F			RT	A3WE    					 
1997060500338	19970605	00338	NM  	1997	6	5	97ZZZX2519       	1	19970508	G	5730		SKIN            			BOEING	727   	7272J4      	1384006	NM  										RT WS 825	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				WING LOWER SURFACE AT FS 825 RBL 15 HAS CORROSION.  REMOVED CORROSION IAW SRM 51-10-6.  THICKNESS CHECKED WITHIN LIMITS 	IAW BAC 727 SRM 57-30-01 FIG 4.					2	L	7	3 	4F			RT	A3WE    					 
1997060500339	19970605	00339	NM  	1997	6	5	97ZZZX2520       	1	19970508	G	2560		MOUNT BRACKET   			BOEING	727   	7272J4      	1384006	NM  										L2 DOOR SLIDE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON L-2 DOOR SLIDE MOUNT BRACKET.  REPAIRED IAW BAC 727 SRM 51-20-1.						2	L	7	3 	4F			RT	A3WE    					 
1997060500340	19970605	00340	NM  	1997	6	5	97ZZZX2521       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 540 RBL 8	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FWD PIT CORROSION UNDER NUTPLATES ON FLOOR BEAM AT FS 540 RBL 8.  REPAIRED IAW BAC 727 SRM 53-10-5 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500341	19970605	00341	NM  	1997	6	5	97ZZZX2522       	1	19970508	G	2530		ANGLE           			BOEING	727   	7272J4      	1384006	NM  										NR 4 GALLEY	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				GALLEY SERVING CART COMPT ANGLE CORRODED.  REMOVED AND REPLACED ANGLE IAW BAC 727 SRM 51-10-6 AND SRM 51-20-04.						2	L	7	3 	4F			RT	A3WE    					 
1997060500342	19970605	00342	NM  	1997	6	5	97ZZZX2523       	1	19970508	G	5312		ANGLE           			BOEING	727   	7272J4      	1384006	NM  										BS 178 BLKHEAD	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				L-ANGLE CRACKED FORWARD BULKHEAD FS 178.  INSTALLED NEW ANGLE IAW 727 SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500343	19970605	00343	NM  	1997	6	5	97ZZZX2524       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 1166 RBL 9	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON FLOOR BEAM FS 1166 AND RBL 9  REMOVED AND REPLACED BEAM SECTION IAW 727 SRM 53-10-5 FIG 6 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500344	19970605	00344	NM  	1997	6	5	97ZZZX2525       	1	19970508	G	5320		SUPPORT         			BOEING	727   	7272J4      	1384006	NM  										BS 1130 RBL 3	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON SUPPORT FOR CARGO NET FRAME 1130 RBL 3.  FABBED NEW TOP PLATE IAW SRM 51-30-02.						2	L	7	3 	4F			RT	A3WE    					 
1997060500345	19970605	00345	NM  	1997	6	5	97ZZZX2526       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										C3 DOOR FR 1090	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				PANEL FWD OF C3 DOOR AND FRAME 1090 IS CRACKED.  REPAIRED PANEL IAW 727 SRM 51-90-2 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500346	19970605	00346	NM  	1997	6	5	97ZZZX2527       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 1030 STR 29R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION FLOOR BEAM AT FLOOR BOARD SUPPORT FS 1030 AND S29R.  FABBED AND INSTALLED NEW BEAM SECTION IAW 727 SRM 51-40-3	 AND SRM 51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500347	19970605	00347	NM  	1997	6	5	97ZZZX2528       	1	19970508	G	5320		ATTACH ANGLE    			BOEING	727   	7272J4      	1384006	NM  										BS 219.8 STR 25R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON ATTACH ANGLE FS 219.8 APPROXIMATELY S25R.  FABBED NEW PART PER 51-10-01 AND INSTALLED PER 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500348	19970605	00348	NM  	1997	6	5	97ZZZX2529       	1	19970508	G	5330		PANEL           			BOEING	727   	7272J4      	1384006	NM  										BS 1030-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON LEFT TRANSITION PANEL FROM BS 1030 TO BS 1166.  FABBED AND INSTALLED NEW TRANSITION PANEL IAW 727 SRM 51-20	-1 AND SRM 51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500349	19970605	00349	NM  	1997	6	5	97ZZZX2530       	1	19970508	G	5320		FLOOR SUPPORT   			BOEING	727   	7272J4      	1384006	NM  										BS 360 RBL 12	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CABIN FLOOR BOARD SUPPORT CRACKED STA 370 RBL 12.  FABBED AND INSTALLED NEW SUPPORT IAW 727 SRM 51-20-1 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500350	19970605	00350	NM  	1997	6	5	97ZZZX2531       	1	19970508	G	5320		SUPPORT ANGLE   			BOEING	727   	7272J4      	1384006	NM  										COCKPIT STA 243	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				TWO EACH COCKPIT SUPPORT ANGLES CRACKED APPROXIMATELY STA 243.  FABBLED AND INSTALLED TWO NEW SUPPORT ANGLES IAW 727 SRM	 51-20-1 AND SRM 51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500351	19970605	00351	NM  	1997	6	5	97ZZZX2532       	1	19970508	G	5347		SEAT TRACK      			BOEING	727   	7272J4      	1384006	NM  										RT OTBD BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				RIGHT OUTBOARD SEAT TRACK CORRODED STA 420 TO STA 460.  FABBED NEW SEAT TRACK AND INSTALLED IAW 727 SRM 53-10-5 AND SRM 	51-30-2.					2	L	7	3 	4F			RT	A3WE    					 
1997060500352	19970605	00352	NM  	1997	6	5	97ZZZX2533       	1	19970508	G	5320	651841713	STIFFENER       			BOEING	727   	7272J4      	1384006	NM  										BS 294.5	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				INTERGRANULAR CORROSION ON NOSE GEARBOX HORIZONTAL STIFFENER STA 294.5. INSTALLED NEW STIFFENER IAW 727 SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500353	19970605	00353	NM  	1997	6	5	97ZZZX2534       	1	19970508	G	5330		SKIN            			BOEING	727   	7272J4      	1384006	NM  										BS 312L STR 17L	DENTED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				DENTS IN SKIN STA 312L STR 17L - STR 18L.  INSTALLED REPAIR DOUBLER IAW SRM 50-30-3.						2	L	7	3 	4F			RT	A3WE    					 
1997060500354	19970605	00354	NM  	1997	6	5	97ZZZX2535       	1	19970508	G	5320	65184175	STIFFENER       			BOEING	727   	7272J4      	1384006	NM  										BS 312	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON NOSE GEARBOX HORIZONTAL STIFFENER STA 312.  INSTALLED NEW STIFFENER IAW 727 SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500355	19970605	00355	NM  	1997	6	5	97ZZZX2536       	1	19970508	G	5320		BRACE           			BOEING	727   	7272J4      	1384006	NM  										FR 420 STR 27L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON BRACE BACK SIDE FRAME 420 S27L.  FABBED AND INSTALLED NEW PART IAW 51-20-1 AND 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500356	19970605	00356	NM  	1997	6	5	97ZZZX2537       	1	19970508	G	5320		ANGLE           			BOEING	727   	7272J4      	1384006	NM  										BS 760 BL 7R-7L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON ANGLE BETWEEN FS 760 AND PANEL 3217 BL 7R-7L.  FABBED AND INSTALLED ANGLE IAW 51-20-1 AND SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500357	19970605	00357	NM  	1997	6	5	97ZZZX2538       	1	19970508	G	5320		T ANGLE         			BOEING	727   	7272J4      	1384006	NM  										ADF ANT RT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON T-ANGLE TO RIGHT OF ADF ANT AFT OF PNEUMATIC GROUND CONNECTION.  REPLACED T-ANGLE IAW 727 SRM 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500358	19970605	00358	NM  	1997	6	5	97ZZZX2539       	1	19970508	G	5315		FLOOR BEAM      			BOEING	727   	7272J4      	1384006	NM  										BS 342 RBL 12	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				FLOOR BEAM STA 342 APPROXIMATELY RBL 12 CORRODED.  INSTALLED REPAIR IAW 727 SRM 53-10-8 FIG 9.						2	L	7	3 	4F			RT	A3WE    					 
1997060500359	19970605	00359	NM  	1997	6	5	97ZZZX2540       	1	19970508	G	5311		FRAME           			BOEING	727   	7272J4      	1384006	NM  										PNL 3217 LBL 5	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION AFT OF PANEL 3217 ON FRAME ABOVE IT APPROXIMATELY LBL 5 A/C BAY. INSTALLED NEW PART 69-46628-4.						2	L	7	3 	4F			RT	A3WE    					 
1997060500360	19970605	00360	NM  	1997	6	5	97ZZZX2541       	1	19970508	G	2730		PCU             			BOEING	727   	7272J4      	1384006	NM  										RT ELEVATOR	LEAKING         	B			KT3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	290SC					20764				RIGHT ELEVATOR PCU LEAKING.  REMOVED AND REPLACED PCU IAW BAC 727 MM 27-30-81.						2	L	7	3 	4F			RT	A3WE    					 
1997060500361	19970605	00361	NM  	1997	6	5	97ZZZX2542       	1	19970508	G	5320		SHEAR TIE       			BOEING	727   	7272J4      	1384006	NM  										BS 350 STR 26L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				CORROSION ON SHEAR TIE AT STA 350 STR 26L.  REPAIRED IAW BAC 727 SRM'S 53-10-2, 51-40-3, 51-30-2.						2	L	7	3 	4F			RT	A3WE    					 
1997060500362	19970605	00362	NM  	1997	6	5	97ZZZX2543       	1	19970508	G	5730		PANEL           			BOEING	727   	7272J4      	1384006	NM  										RT WING 8613	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	290SC					20764				RIGHT WING PANEL 8613 CORRODED.  REPAIRED IAW BAC 727 SRM 51-40-6 PAR 3(E)(I).						2	L	7	3 	4F			RT	A3WE    					 
1997060500363	19970605	00363	CE  	1997	6	5	97ZZZX2544       	1	19970429	G	2121	591224	HYDRAULIC MOTOR 	SUNDSTRANDEM	725652B     	CESSNA	650   	650         	2076802	CE  										RAM HYD FAN	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	67SF		57   		143	6500045				PILOT REPORTED LOW HYDRAULIC PRESSURE WITH ONE ENGINE RUNNING AND AT IDLE.  DISCOVERED THE HYDRAULIC FLUID FLOW RATE THR	OUGH THE RAM AIR HYDRAULIC FAN TO BE EXCESSIVE.  REPLACED ASSEMBLY WITH REPAIRED UNIT AND RETESTED FLOW RATE AND FOUND T	O BE WITHIN TOLERANCE LEVELS.  DUE TO THE NORMALLY HIGH FLOW RATE OF THE FAN MOTOR AND THE SUBSEQUENT LOSS OF PRESSURE W	HEN THIS UNIT BEGINS TO FAIL, IT IS SUGGESTED THAT AN ELECTRIC MOTOR/FAN ASSEMBLY BE DESIGNED AS A REPLACEMENT TO THIS E	XISTING ASSEMBLY.		2	L	7	2 	4F				A9NM    					 
1997060500365	19970605	00365		1997	6	5	97ZZZX2546       	4	19970308	G	2562		PARACHUTE       	TANDEM      																MAIN	MALFUNCTION     	H	L	A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25										TANDEM RESERVE CHUTE DEPLOYMENT OCCURRED DUE TO MAIN CHUTE CLOSING LOOP BROKE JUST BELOW FINGER TRAP ENTRY POINT FOLLOWI	NG EXIT FROM AIRCRAFT.																		 
1997060500366	19970605	00366	NM  	1997	6	5	97ZZZX2547       	1	19970501	G	2720	664483621	MANIFOLD        		654486121   	BOEING	737   	737*        		NM  										FILTER BOWL	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					6609A					RUDDER PCU MANIFOLD IS CRACKED INSIDE FILTER BOWL AT PRESSURE PORT PASSAGEWAY.						2	L	7	2 	4F			RT	A16WE   					 
1997060500367	19970605	00367	NM  	1997	6	5	97ZZZX2548       	1	19970501	G	2720	664483617	MANIFOLD        		654486121   	BOEING	737   	737*        		NM  										FILTER BOWL	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					6603A					RUDDER PCU MANIFOLD IS CRACKED INSIDE FILTER BOWL AT PRESSURE PORT PASSAGEWAY.						2	L	7	2 	4F			RT	A16WE   					 
1997060500368	19970605	00368	NM  	1997	6	5	97ZZZX2549       	1	19970501	G	2720	664483615	MANIFOLD        		654486114   	BOEING	737   	737*        		NM  										FILTER BOWL	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4008					RUDDER PCU MANIFOLD IS CRACKED INSIDE FILTER BOWL AT PRESSURE PORT PASSAGEWAY.						2	L	7	2 	4F			RT	A16WE   					 
1997060500369	19970605	00369		1997	6	5	97ZZZX2550       	4	19970519	G	6122	210738	GOVERNOR        	WOODWARD    		BEECH 	100   	B100        	1152919	CE  										LT PROP	WRONG PART      	B			W6NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	500KD				1998547E	BE79				UPON INSPECTING AIRCRAFT FOR PART 135 OPERATION, THE LEFT PROP GOV WAS FOUND TO BE A PART NUMBER NOT AUTHORIZED FOR B-10	0'S.  THIS WAS CONFIRMED THROUGH WOODWARD GOVERNOR.  THERE WERE NO OPERATING PROBLEMS AT THE TIME.  GOVERNOR WAS REPLACE	D WITH PROPER PART NUMBER OF 210939.  THE GOVERNOR WAS BEING REPLACED ALSO DUE TO 6-YEAR OVERHAUL REQUIREMENT PER WOODWA	RD SB 33580E.			1	L	7	2 	4T				A14CE   					 
1997060500370	19970605	00370	SW  	1997	6	5	97ZZZX2551       	1	19970425	G	5610	407030114125	WINDSHIELD      			BELL  	407   	407         		SW  										COCKPIT	DISTORTED       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6932Z	8    				53124				INSPECTION FOUND WINDSHIELD DISTORTED.  REPLACED WITH NEW WINDSHIELD.						1	G	7	1 	3U			O	H2SW    					 
1997060500457	19970605	00457	EU  	1997	6	5	97ZZZX2552       	1	19970510	G	6520		GEARBOX         			SNIAS 	350   	AS350B      	8680801	EU  										T/R GEARBOX	CHIP  LIGHT     	D				K				NONE                    				J			WARNING INDICATION        			AP	APPROACH       	1			WP	07	91GT	3140 	102  		M1916	1289				ON FINAL APPROACH, T/R CHIP LIGHT ILLUMINATED.  FOUND EXCESSIVE CHIPS IN OIL.  REMOVED GEARBOX FROM SERVICE.						1	G	7	1 	3U				H9EU    					 
1997060500458	19970605	00458	EU  	1997	6	5	97ZZZX2553       	1	19970512	G	6520		HUB             			SNIAS 	350   	AS350B      	8680801	EU  										T/R GEARBOX	BOLT SEIZED     	D				K				NONE                    				W			INADEQUATE Q C            			AP	APPROACH       	1			WP	07	91GT	3140 	102  		M1916	1289				DURING REMOVAL OF T/R HUB, HUB RETAINING BOLT WAS VERY HARD TO REMOVE.  UPON INSPECTION OF BOLT, FOUND SIGNS THAT BOLT W	AS INSTALLED WITH (RED) LOCTITE INSTEAD OF LOCTITE 242 (BLUE).  MWC 65.20.00.401 PARA 4 STATES TO APPLY LOCTITE 242 (BLU	E) TO THREADS.  AFTER TALKING TO ANOTHER REPAIR STATION ABOUT THIS PROBLEM, THEY STATED THAT 80 PERCENT OF THE GEARBOXES	 THEY OVERHAUL/REPAIR GET RED LOCTITE; THUS, GOING AGAINST THE AIRCRAFT MANUFACTURER'S OVERHAUL/REPAIR PROCEDURES.			1	G	7	1 	3U				H9EU    					 
1997060500461	19970605	00461	GL  	1997	6	5	97ZZZX2556       	1	19970513	G	6230	28161191	UNIVERSAL HSNG  			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPLATE	CRACKED         	C			PP0M	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			WP	01	8624B	641  			13100991H	752				MOUNTING WEBS FOR CONTORL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION.  THIS IS A P	RIMARY FLIGHT CONTROL PART.  THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS.  PART NON-REPAIRABLE.  REPLACED WITH NEW P	ART 28-16119-1.				1	G	7	1 	3O				H1CE    					 
1997060500462	19970605	00462	GL  	1997	6	5	97ZZZX2557       	1	19970514	G	6230	28161191	UNIVERSAL HSNG  			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPLATE	CRACKED         	C			PP0M	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			WP	01	8626S	6672 			1085185H	786				MOUNTING WEBS FOR CONTORL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION.  THIS IS A P	RIMARY FLIGHT CONTROL PART.  THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS.  PART NON-REPAIRABLE.  REPLACED WITH NEW P	ART 28-16119-1.				1	G	7	1 	3O				H1CE    					 
1997060500479	19970605	00479	NE  	1997	6	5	97ZZZX2575       	1	19970207	G	6320	643520500048	SHAFT           		643520536101	SKRSKY	S64   	S64F        		NE  										MGB	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			NM	09	179AC	2725 			61	64091				MAIN GEARBOX INSPECTION.  TWO INDICATIONS FOUND IN THE RADIUS OF ONE SPLINE DURING MPI INSPECTION.  BOTH INDICATIONS WER	E APPROXIMATELY 0.050 INCH IN LENGTH AND EXTENDING TOWARDS THE TOOTH FACE.  NO OTHER INDICATIONS WERE FOUND.					2	G	7	2 	4U				H6EA    					 
1997060500480	19970605	00480	CE  	1997	6	5	97ZZZX2576       	1	19970510	G	3230	08421201	DRIVE TUBE      			CESSNA	320   	320D        	2074512	CE  										NLG	BENT            	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	15DS	4150 				320D0079				ROUTINE INSPECTION FOUND FWD END OF PUSHROD BENT.  REMOVED AND DETERMINED SPACERS (ITEM 7) WERE NOT INSTALLED ABOVE AND 	BELOW END BEARING WHICH ALLOWED ACTUATOR ROD TO WORK UP AND DOWN.  FURTHER INSP REVEALED IDLER BELLCRANK (ITEM 11) WAS I	NSTALLED WITHOUT THE MAIN .25 INCH TO .4375 INCH BUSHING (ITEM 14) INSTALLED WHICH CAUSED BELLCRANK TO FLOAT ON THE .25 	INCH BOLT (ALLOW .200 INCH PLAY).  THIS AREA WAS REPAIRED AFTER A NOSE GEAR COLLAPSE APPROX 350 HRS EARLIER AT WHICH TIM	E THE IDLER BELLCRANK APPEARED TO HAVE BEEN REPLACED.  THERE WAS NO LOG ENTRY OF ANY OF THIS REPAIR.		1	L	7	2 	3O				3A25    					 
1997060500481	19970605	00481	SO  	1997	6	5	97ZZZX2577       	1	19970501	G	2701	62716	SHAFT           			PIPER 	PA32  	PA32300     	7103212	SO  										CONTROL COLUMN	MISDRILLED      	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05	2884M	6000 				327840058				YOKE CONTROL SHAFT FITTED AND DRILLED IMPROPERLY.  WAS CHANGING OUT CONTROL U-JOINT, FOUND THIS DEFECTIVE CONTROL SHAFT.	  HAVE HAD ACFT FOR 4,500 HOURS AND PRIOR TO THAT, NO RECORD OF CONTROL COLUMN BEING APART.  ASSUME IT WAS DRILLED IMPRO	PERLY AT FACTORY.  SUBMITTER STATED TO PREVENT BY CHECKING WORK.  FIND BY FEEL:  SHAFT SHOULD BE FLUSH IN SPROCKET HOLE.				1	L	7	1 	3O				A3SO    					 
1997060500482	19970605	00482	SO  	1997	6	5	97ZZZX2578       	2	19970501	G	8520		CRANKCASE       			UNIVAC	GC1   	GC1B        	9230104	NM  	CONT  	O360  	IO360C      	17025	SO  					OVER NR 2 CYL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	2403B					3703	R55320SD			THIRTY HOURS AFTER REPAIR AND OVERHAUL OF ENGINE, CRANKCASE WAS FOUND TO HAVE A CRACK ON UPPER AREA ABOVE NR 2 CYLINDER 	(NOT A STUD HOLE CRACK) EXTENDING 1 INCH FORE AND AFT APPROX 1 INCH INBOARD OF CYLINDER MOUNT AREA.  CYLINDERS ALSO FOUN	D NOT TO HAVE BEEN OVERHAULED.  ENGINE DISASSEMBLED AND FOUND NUMEROUS OTHER DISCREPANCIES.  ( NO COTTER PIN, ETC.).  SB	 96-13 NOT SIGNED OFF.  AD 92-04-09 NOT C/W.			1	L	7	1 	3O	3	O		A766    	E1CE				 
1997060500483	19970605	00483	NM  	1997	6	5	97ZZZX2579       	1	19970501	G	3230	1153230542	CONTROL CABLE   			UNIVAC	GC1   	GC1*        	       	NM  										GEAR EXTENSION	JAMMED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	2403B					3703				DURING ANNUAL GEAR RETRACTION TEST, SHORT EXTENSION CABLE KINKED AND JAMMED LT GEAR 1/2 TRAVEL BETWEEN UP AND DOWN POSIT	ION.  CABLE WAS FOUND RUSTED AND STIFF.  REMOVED CABLE AND INSTALLED NEW CABLE AND ADJUSTED TENSION.  SUBMITTER SUGGESTE	D OLDER AIRCRAFT BE LOOKED AT CLOSER DURING ANNUAL INSPECTIONS.  PART IS APPROXIMATELY 50 YEARS OLD.				1	L	7	1 	3O			 	A766    					 
1997060500484	19970605	00484	SO  	1997	6	5	97ZZZX2580       	1	19970501	G	2430	9937713	SWITCH          			PIPER 	PA34  	PA34200T    	7103406	SO  										MASTER SWITCH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	36345					347870321				INTERNAL CORROSION ON ALL CONTACTS OF SWITCH.  POSSIBLE WATER ENTRAPMENT, SOURCE MOST LIKELY PILOT SIDE WINDOW.  REPLACE	D SWITCH ASSY WITH OEM REPLACEMENT.  SEALED SWITCH WITH FUEL TANK SEALANT.					1	L	7	2 	3O				A7SO    					 
1997060500485	19970605	00485	CE  	1997	6	5	97ZZZX2581       	1	19970515	G	5542	553300054	SKIN            			CESSNA	500   	560CESSNA   	2076750	CE  										RUDDER RT SIDE	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	393QS	649  				5600393				FOUND 3 INCH CRACK ON RIGHT SIDE OF RUDDER ALONG AFT RIB - WL 158.00.  CRACK IS THROUGH 3 EACH RIVETS.  SUBMITTER STATED	 THIS IS THE 8TH OCCURRENCE ON FLEET.					2	L	7	2 	4F			RT	A22CE   					 
1997060500487	19970605	00487	EA  	1997	6	5	97ZZZX2583       	2	19970422	G	7414		ROTOR           	BENDIX      	S4LN203     	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					RT MAG	SHAFT SHEARED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5224T	1857 			A39663	287205248	L1661236A			ROTOR SHAFT SHEARED OFF JUST AFT OF SEAL RUNNER BUSHING.  THE BREAK IN THE SHAFT APPEARS TO HAVE BEEN CRACKED FOR SOME T	IME.  THIS ENGINE HAD MAJOR OVERHAUL 441 HOURS AGO FOR PROP STRIKE.  THE RIGHT MAGNETO IS DIRECT DRIVE (NO IMPULSE), AND	 SUSPECT THE SHAFT FAILURE WAS DUE TO SUDDEN STOP OR TORSIONAL SHOCK TO MAGNETO ROTORSHAFT.  THE ENGINE HAD SUDDEN STOPP	AGE PREVIOUSLY, AND PROP WAS SEVERELY CURLED THE FIRST STRIKE.  LOGS SHOW  LEFT MAG TO BE ORIGINAL EQUIPMENT.			1	L	7	1 	3O	3	O		2A13    	E286				 
1997060500488	19970605	00488	GL  	1997	6	5	97ZZZX2584       	3	19970514	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	NR 1 BLADE	CRACKED         	B			EK2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	5238H					15284071		R776219		PROPELLER INSPECTION FOUND CRACK APPROXIMATELY .820 INCH LONG, .040 INCH DEEP, TRAILING EDGE SIDE OF HUB OF NR 1 BLADE. 	 AD 97-21-01 AND MCAULEY SB 221B ADDRESSES THE HUB FRONT FACE AND BOLT HOLES.  NO RE-WORK IS ALLOWED ON SIDE OF HUB.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997060500489	19970605	00489	SO  	1997	6	5	97ZZZX2585       	1	19970520	G	7810	K3342005	PIPE            			PIPER 	PA23  	PA23250     	7102308	SO  										RT ENG EXH	HOLED           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	6776A					277954088				EXHAUST PIPE HAD LARGE HOLE IN PIPE INSIDE HEAT MUFFLER.  THIS ALLOWED RAW EXHAUST GAS TO ENTER ENGINE THROUGH FUEL SERV	O.  P/N RSA-5AD1.					1	L	7	2 	3O				1A10    					 
1997060500492	19970605	00492	SO  	1997	6	5	97ZZZX2588       	1	19970505	G	2913	ESQ12S	BRUSH           	PRESTOLITE  	9667102     	PIPER 	PA32  	PA32R300    	7103213	SO  										HYD PUMP ASSY	WORN            	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6925J	2268 				32R7680388				INSPECTED HYDRAULIC PUMP MOTOR FOLLOWING ACFT LANDING WITH NOSE GEAR UNLOCKED.  FOUND BRUSHES WORN OUT AND COMMUTATOR UN	DERCUT.  COMMUTATOR WAS TURNED AND NEW BRUSHES INSTALLED 368 HRS PREVIOUSLY, 1-3-95.  BRUSHES WERE REMOVED AND INSPECTED	 296 HRS PRIOR TO FAILURE AND FOUND NO EVIDENCE OF WEAR SINCE INSTALLED 72 HRS PREVIOUSLY.  BRUSHES AND COMMUTATOR LOOK 	AS IF MOTOR RAN FOR MANY HOURS.			1	L	7	1 	3O				A3SO    					 
1997060500494	19970605	00494	CE  	1997	6	5	97ZZZX2590       	1	19970501	G	7160	96919100609	INDUCT AIR BOX  			BEECH 	95    	95B55       	1152729	CE  										AIR DOOR	MISMANUFACTURED 	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11										NEW AIR BOX ASSEMBLIES LISTED WERE RECEIVED DEFECTIVE.  'NEW PARTS FROM BEECH'.  THE AIR FILTER SLOT IS NOT WIDE ENOUGH 	TO ACCOMODATE THE SUPPLIED AIR FILTER.  SECOND, THE ALTERNATE AIR DOOR DOES NOT CLOSE COMPLETELY.  SUBMITTER STATED POOR	 QC ON BOTH ASSEMBLIES.				1	L	7	2 	3O			RT	3A16    					 
1997060500495	19970605	00495	CE  	1997	6	5	97ZZZX2591       	1	19970501	G	7160	96919100615	AIR BOX         			BEECH 	95    	95B55       	1152729	CE  										AIR FILTER	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11										NEW AIR BOX ASSEMBLIES LISTED WERE RECEIVED DEFECTIVE.  'NEW PARTS FROM BEECH'.  THE AIR FILTER SLOT IS NOT WIDE ENOUGH 	TO ACCOMODATE THE SUPPLIED AIR FILTER.  SECOND, THE ALTERNATE AIR DOOR DOES NOT CLOSE COMPLETELY.  SUBMITTER STATED POOR	 QC ON BOTH ASSEMBLIES.				1	L	7	2 	3O			RT	3A16    					 
1997060500497	19970605	00497	SO  	1997	6	5	97ZZZX2593       	2	19970520	G	7414	S6RN1225	MAGNETO         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					IMPULSE COUPLING	CRACKED         	D	P			K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			SW	05	2038X	860  			H21595	CE819	569620			WHEN CHECKING MAGNETOS DURING ENGINE RUN-UP PRIOR TO TAKEOFF, RIGHT MAGNETO GAVE A 350 FOOT RPM DROP ACCOMPANIED BY A VE	RY ROUGH RUNNING ENGINE.  AFTER RIGHT MAGNETO WAS REMOVED FOR TROUBLESHOOTING, CRACKS WERE DISCOVERED ON THE TOP AND BOT	TOM OF THE HOUSING EXTENDING FORWARD APPROXIMATELY 1.50 INCHES FROM THE FLANGE OF THE IMPULSE COUPLING.				1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997060500498	19970605	00498	NE  	1997	6	5	97ZZZX2594       	1	19970520	G	3230	18000045	HOSE ASSY       			CONAER	LA4   	LA4200      	5110310	NE  										GEAR RETRACT	MISASSEMBLY     	D				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			NM	08	3060P	6    				971				HYDRAULIC HOSE KIT ORDERED FROM LAKE FACTORY INSTALLED ON AIRCRAFT.  TWO OUT OF SIX LANDING GEAR RETRACT HOSES LEAKED AT	 THE FITTINGS.  UPON DISASSEMBLY OF HOSES, FOUND THE ENDS WERE IMPROPERLY INSTALLED.  THE FERRULES WERE SCREWED ONTO THE	 HOSE ONLY ONE THREAD, SHOULD BE THREE THREADS.  THE INSIDE PART OF THE FITTING WAS APPARENTLY INSTALLED WITHOUT THE PRO	PER TOOL CAUSING IT TO CUT THE INSIDE OF THE HOSE.  HOSE IS AEROQUIP 303-4.  FITTINGS ARE MS24590-4.			1	H	7	1 	3O				1A13    					 
1997060500500	19970605	00500	EA  	1997	6	5	97ZZZX2595       	2	19970522	G	8530	73806	PUSHROD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 2 EXH VLV	MUSHROOMED      	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			NE	01	69232		1897 			15282575	L1709915			PILOT REPORTED ENGINE RUNS ROUGH.  CHECKED VALVE CLEARANCE AND FOUND NR 2 EXHAUST TO BE .083 INCH.  REMOVED NR 2 EXHAUST	 PUSHROD.  PUSHROD FOUND MUSHROOMED AND BALL END WAS LOOSE.  SUBMITTER SUGGESTS INSPECTING PUSHRODS FOR LOOSE BALL ENDS 	ANYTIME THE 100-HOUR VALVE TAPPET CLEARANCE INSPECTION DISCLOSES A LARGER THAN ACCEPTABLE VALUE OR WHEN LOW POWER IS NOT	ED.  REFERENCE LYCOMING SI 1388C AND SI 1068A.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997060500501	19970605	00501	EA  	1997	6	5	97ZZZX2596       	3	19970518	G	6111		BLADE           			PIPER 	PA28  	PA28180     	7102808	SO  						SNSNCH	76E	76EM8S5     	EA  	PROPELLER	TIP SEPARATED   	D				A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CR	CRUISE         	1			EA	13	7863W	3271 				281884		8697K		FOUR INCHES OF BLADE TIP SEPARATED IN-FLIGHT.  AIRCRAFT RETURNED TO BASE IN REDUCED POWER SETTING.  NO DAMAGE OR INJURIE	S.					1	L	7	1 	3O				2A13    		5	N	P4EA	 
1997060500502	19970605	00502	CE  	1997	6	5	97ZZZX2597       	1	19970429	G	2821	HE15262	GASKET          			BEECH 	33    	F33A        	1151425	CE  										FUEL SELECT	MISINSTALLED    	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	99MK				HE763	CE742				PILOT REPORTED LOW FUEL FLOW AND HIGH EGT'S.  AFTER EXTENSIVE T/S AND BENCH CHECK OF ENGINE FUEL INJECTION SYSTEM COMPON	ENTS, DISCOVERED THE AIRFRAME FUEL SELECTOR VALVE SCREEN ASSY IMPROPERLY ASSEMBLED.  ACFT EQUIPPED WITH STC'D TIP TANKS 	WHICH UTILIZED A NON-STANDARD FUEL SELECTOR VALVE.  DUE TO DATE OF ISSUANCE OF STC, INSTRUCTIONS FOR CONTINUED AIRWORTHI	NESS (MANDATED BY PAR 21.50) WERE NOT ISSUED BY THE STC HOLDER.  BY NOT HAVING INSTRUCTIONS AVAILABE, IT IS POSSIBLE TO 	INCORRECTLY ASSEMBLE THE FUEL SCREEN WHICH CAN RESULT IN RESTRICTED FUEL FLOW AT HIGH POWER SETTINGS.  THIS CAN RESULT I	N EXCESSIVELY LEAN MIXTURES WITH EXCESSIVELY HIGH EGT'S WHICH CAN CAUSE CYLINDER DAMAGE AND POSSIBLE ENGINE FAILURE.	1	L	7	1 	3O				3A15    					 
1997060500503	19970605	00503	SO  	1997	6	5	97ZZZX2598       	2	19970519	G	8530	535666	SCREW           		654761A1    	BEECH 	35    	E35         	1151512	CE  	CONT  	E225  	E2258       	17015	SO  					ROCKER SHAFT	STRIPPED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	3251C					D3916	30350D48			DURING CYLINDER INSTALLATION ATTEMPTING TO TORQUE ROCKER SHAFT HOLD-DOWN SCREWS RESULTED IN 2 SCREWS STRIPPING BEFORE TH	E MINIMUM TORQUE OF 180 INCH/POUND WAS REACHED.  THIS IS THE 2ND OCCURRENCE ON THIS ENGINE.  BOTH TIMES THE CORRECTIVE A	CTION WAS REPLACING SCREWS AND CLEANING THREADS IN ROCKER SHAFT. COULD NOT DETERMINE IF THREADS IN SHAFT ARE STRIPPING O	R IF SCREWS ARE DEFECTIVE.			1	L	7	1 	3O	3	O		A777    	E267				 
1997060500724	19970605	00724		1997	6	5	97ZZZX2606       	1	19970506	G	7920	3038	HOSE            	AEROQUIP    																	PLUGGED         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15										AFTER INSTALLING FITTINGS ON A PIECE OF AEROQUIP 303-8 HOSE, FOUND HOSE CLOGGED.  INVESTIGATION REVEALED APPROX 1 FOOT O	F THE HOSE WAS SOLID RUBBER INSIDE. HOSE PURCHASED FROM AVSCO ON 4-28-97.  BATCH NR MIL-H-8794-8-3096-248-06827.  IF HOS	E HAD NOT BEEN CHECKED AFTER INSTALLING FITTINGS, ENGINE OIL FLOW WOULD HAVE STOPPED AT OIL COOLER WITH DISASTROUS RESUL	TS.  HOSE SENT TO NTSB, MIA.																 
1997060500725	19970605	00725	SO  	1997	6	5	97ZZZX2607       	2	19970514	G	8530	SA10200A20P	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					BARREL	FAILED          	D				A				UNSCHED LANDING         				E	Y	B	VIBRATION/BUFFET          	ENGINE STOPPAGE           	SMOKE/FUMES/ODORS/SPARKS  	CR	CRUISE         	1			SW	17	148EL	1024 				15077412	253635A48			ON A TRAINING FLIGHT, THE ENGINE STARTED RUNNING ROUGH.  INSTRUCTOR REQUESTED DIRECT RETURN.  WHITE SMOKE CAME FROM ENGI	NE, A LOUD BANG, FOLLOWED BY VERY ROUGH ENGINE AND PARTIAL POWER LOSS.  ENGINE STOPPED, SAFE LANDING, CYLINDER HEAD AND 	TOP ONE-THIRD OF BARREL SEPARATED FROM LOWER ONE-THIRD OF CYLINDER.  PISTON DESTROYED, PUSH ROD BENT,  SUBMITTER STATED 	CAUSE WAS DEFECTIVE CYLINDER BARREL, PREVENT BY USING NEW CONTINENTAL CYLINDERS.			1	H	7	1 	3O	3	O		3A19    	E252				 
1997060500726	19970605	00726	CE  	1997	6	5	97ZZZX2608       	1	19970324	G	3240		BRAKE LINE      			ZINAIR	CH2000	CH2000      	9950100	CE  										RT MLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	25ZA	86   				200025				DURING TAXI INSTRUCTION, RT MLG BRAKE ASSY FAILED.  INSPECTION OF BRAKE PRESSURE DETERMINED THE .25 INCH NYLON TUBING (C	LEAR) HAD A BUBBLE FORMED IN THE LINE AND HAD RUPTURED AT THAT POINT.  DURING TAXI INST, IT IS BELIEVED THE STUDENT MAIN	TAINED PRESSURE ON THE RT BRAKE CAUSING BRAKE DISK TO BUILD UP EXCESSIVE HEAT WHICH WAS TRANSFERRED TO THE NYLON LINE WH	ICH IS ROUTED CLOSE TO THE DISK.  ACFT HAS WHEEL FAIRINGS INSTALLED MAKING PRE-FLIGHT INSPECTION OF THIS AREA VERY DIFFI	CULT.		1	L	7	1 	3O			NT	TA5CH   					 
1997060500727	19970605	00727	SO  	1997	6	5	97ZZZX2609       	1	19970428	G	7603	472606	ROD END         		455359      	PIPER 	PA32  	PA32300     	7103212	SO  										THROTTLE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	32641					327540054				LOST THROTTLE CONTROL. INSPECTION FOUND BALL AND BEARING HAD COME OUT OF ROD END, P/N 472-606.  CAN REPLACE WITH P/N 317	47-00, JOINT ASSY.  IF NEW PART FOR ROD END USED, P/N 472-606, USE AN 'AN' 970-3 WASHER UNDER BOLT HEAD SO HOUSING CANNO	T SLIP OFF.				1	L	7	1 	3O				A3SO    					 
1997060500728	19970605	00728	CE  	1997	6	5	97ZZZX2610       	1	19970515	G	3230	NAS505SJ	BEARING         			BEECH 	36    	A36         	1151604	CE  										RT MLG UPLOCK	FROZEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	37CH					E1460				RIGHT LANDING GEAR UPLOCK ROLLER BEARING FROZEN CAUSING RT LANDING GEAR NOT TO RELEASE FROM ROLLER.  SUBMITTER SUGGESTS 	MAY HAVE BEEN CAUSED BY NOT LUBING AT LAST INSPECTION.					1	L	7	1 	3O				3A15    					 
1997060500732	19970605	00732	CE  	1997	6	5	97ZZZX2614       	1	19970514	G	5730		SKIN            			CESSNA	402   	402B        	207590P	CE  										RT WING	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5040Q					402B0347				DURING A 50-HOUR INSPECTION, MECHANIC NOTICED CRACK IN WING SKIN IN THE MOST AFT OTBD SECTION OF RT WING.  ALSO, TWO RIV	ETS WERE SHEARED THAT ATTACH THE OTBD HINGE BRACKET ASSY (CESSNA PN 5021002-13) WHICH ARE THE SAME RIVETS THAT ATTACH TI	P TANK SUPPORT BRACKETS (CESSNA PN 0822600-29 AND 30) TO THE WING.  THE MOST OTBD WING RIB CRACKED IN MOST AFT LOWER SEC	TION (CESSNA PN 0822040-18).  SUSPECT CAUSES:  TIP TANK STRINGER (MOST AFT POINT) HAS SLIGHT DAMAGE AS THOUGH IT HAS STR	UCK A SOLID OBJECT.  AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUT	ING FACTOR.	1	L	7	2 	3O				A7CE    					 
1997060500733	19970605	00733	CE  	1997	6	5	97ZZZX2615       	1	19970514	G	5720	502100213	SUPPORT BRACKET 			CESSNA	402   	402B        	207590P	CE  										RT WING	RIVETS SHEARED  	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5040Q					402B0347				DURING A 50-HOUR INSPECTION, MECHANIC NOTICED CRACK IN WING SKIN IN THE MOST AFT OTBD SECTION OF RT WING.  ALSO, TWO RIV	ETS WERE SHEARED THAT ATTACH THE OTBD HINGE BRACKET ASSY (CESSNA PN 5021002-13) WHICH ARE THE SAME RIVETS THAT ATTACH TI	P TANK SUPPORT BRACKETS (CESSNA PN 0822600-29 AND 30) TO THE WING.  THE MOST OTBD WING RIB CRACKED IN MOST AFT LOWER SEC	TION (CESSNA PN 0822040-18).  SUSPECT CAUSES:  TIP TANK STRINGER (MOST AFT POINT) HAS SLIGHT DAMAGE AS THOUGH IT HAS STR	UCK A SOLID OBJECT.  AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUT	ING FACTOR.	1	L	7	2 	3O				A7CE    					 
1997060500734	19970605	00734	CE  	1997	6	5	97ZZZX2616       	1	19970514	G	5712	082204018	RIB             			CESSNA	402   	402B        	207590P	CE  										RT WING OTBD	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5040Q					402B0347				DURING A 50-HOUR INSPECTION, MECHANIC NOTICED CRACK IN WING SKIN IN THE MOST AFT OTBD SECTION OF RT WING.  ALSO, TWO RIV	ETS WERE SHEARED THAT ATTACH THE OTBD HINGE BRACKET ASSY (CESSNA PN 5021002-13) WHICH ARE THE SAME RIVETS THAT ATTACH TI	P TANK SUPPORT BRACKETS (CESSNA PN 0822600-29 AND 30) TO THE WING.  THE MOST OTBD WING RIB CRACKED IN MOST AFT LOWER SEC	TION (CESSNA PN 0822040-18).  SUSPECT CAUSES:  TIP TANK STRINGER (MOST AFT POINT) HAS SLIGHT DAMAGE AS THOUGH IT HAS STR	UCK A SOLID OBJECT.  AMOUNT OF WEIGHT WITH A FULL TANK OF FUEL BOUNCING ON THE TIP OF THE WING COULD ALSO BE A CONTRIBUT	ING FACTOR.	1	L	7	2 	3O				A7CE    					 
1997060500735	19970605	00735	CE  	1997	6	5	97ZZZX2617       	1	19970520	G	5330		SKIN            			CESSNA	210   	T210N       	2073456	CE  										SERVO MT BS 166	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	5144U	2230 				21064851				UPON INVESTIGATION OF SKIN CRACK AT FS 166.4 IN THE TOP AREA OF EMPENNAGE, DETERMINED CESSNA FACTORY INSTALLED AUTOPILOT	 PITCH SERVO ATTACHED TO STA 166.4 BULKHEAD AND AREA SKIN FAILED.  A TEAR-LIKE CRACK OCCURRED ON SKIN AND TWO CRACKS FOU	ND ON LOCATION BULKHEAD IN AREA OF SERVO MOUNT ATTACH.  INVESTIGATION DISCLOSED SERVO  MOUNT DID NOT INCLUDE ANY DOUBLER	 OR STIFFENER TO SKIN OR BULKHEAD.  CESSNA AUTOPILOT SM ALSO DID NOT INCLUDE DOUBLER OR STIFFENER TO SUPPORT SERVO MOUNT	.		1	H	7	1 	3O				3A21    					 
1997060500736	19970605	00736	CE  	1997	6	5	97ZZZX2618       	1	19970421	G	5313	2611201	LONGERON        			CESSNA	208   	208B        	2073701	CE  										BELLY SKIN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	5187B	3828 				208B0270				ON INSPECTION, CORROSION WAS FOUND ON LONGERONS BETWEEN FS 188.70 AND FS 214.40 AND ON THE BELLY SKIN FLANGE WHERE THE N	UTPLATES ARE INSTALLED FOR THE MLG FORWARD STRAPS TO BOLT ONTO.  THIS ACFT CAME FROM A SALT WATER CLIMATE.  WATER RUNS I	NTO WING ATTACH AREA DOWN TO FUEL RESERVOIR TANK AREA.  THE TANK AREA IS SEALED.  CESSNA DID HAVE A DRAIN IN THE BAY JUS	T OUTBOARD OF THE AREA OF CORROSION, HOWEVER, DRAIN WAS PLUGGED UP WHEN POD INSTALLED WHICH GAVE NO MEANS TO DRAIN THIS 	AREA.  CESSNA HAS BEEN CONTACTED FOR A SOLUTION.		1	H	7	1 	3T				A37CE   					 
1997060500737	19970605	00737	CE  	1997	6	5	97ZZZX2619       	1	19970421	G	5313	2611202	LONGERON        			CESSNA	208   	208B        	2073701	CE  										BELLY SKIN	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	5187B	3828 				208B0270				ON INSPECTION, CORROSION WAS FOUND ON LONGERONS BETWEEN FS 188.70 AND FS 214.40 AND ON THE BELLY SKIN FLANGE WHERE THE N	UTPLATES ARE INSTALLED FOR THE MLG FORWARD STRAPS TO BOLT ONTO.  THIS ACFT CAME FROM A SALT WATER CLIMATE.  WATER RUNS I	NTO WING ATTACH AREA DOWN TO FUEL RESERVOIR TANK AREA.  THE TANK AREA IS SEALED.  CESSNA DID HAVE A DRAIN IN THE BAY JUS	T OUTBOARD OF THE AREA OF CORROSION, HOWEVER, DRAIN WAS PLUGGED UP WHEN POD INSTALLED WHICH GAVE NO MEANS TO DRAIN THIS 	AREA.  CESSNA HAS BEEN CONTACTED FOR A SOLUTION.		1	H	7	1 	3T				A37CE   					 
1997060500738	19970605	00738	SO  	1997	6	5	97ZZZX2620       	2	19970501	G	8530		CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 4	STUDS FAIL      	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AL	05	5246E	779  				18503943	281256R			PILOT HEARD AND FELT ABRUPT CHANGE IN ENGINE 10 MINUTES INTO FLIGHT.  UNEVENTFUL RETURN TO BASE WITH ENGINE INSTRUMENTS 	NORMAL.  NR 4 CYLINDER HAD SHEARED ALL 8 STUDS AND HAD SEPARATED .50 INCH FROM CASE.  ENGINE HAD HISTORY OF PROP STRIKE 	TEAR-DOWN 460 HRS PRIOR TO FAILURE.				1	H	7	1 	3O	3	O		3A24    	E5CE				 
1997060500741	19970605	00741	CE  	1997	6	5	97ZZZX2623       	1	19970517	G	7160	BA5110A	AIR FILTER      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					AIR INDUCT	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	64154	7    				17265049	L4166627A			DURING ANNUAL INSPECTION, BRACKETT AIR FILTER ASSY WAS FOUND LOOSE ON THE AIRBOX.  UPON REMOVAL, IT WAS FOUND TO BE THE 	INCORRECT ASSEMBLY FOR THE AIRCRAFT MODEL.  THE MODEL 172M USES ASSEMBLY NR BA 5110, A BA 5710A WAS INSTALLED.  THE CAML	OCK STUDS ON THE BA 5110A ARE TOO LONG.  THE BASE GASKET WOULD NOT CONTACT THE AIRBOX LEAVING IT LOOSE AND FLOPPING.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997060500742	19970605	00742	EA  	1997	6	5	97ZZZX2624       	2	19970521	G	7310		HOSE            	AEROQUIP    		PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A5    	41532	EA  					ENGINE COMPT	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	8174P	2884 				243430				FUEL HOSES IN ENGINE COMPARTMENT.  ORIGNAL HOSES DATED 1962.  HOSES WERE VERY STIFF, BUT NOT LEAKING.  SHOULD HAVE BEEN 	CHANGED BEFORE THEY LOSE FLEXABILITY.					1	L	7	1 	3O	3	O		1A15    	E295				 
1997060500743	19970605	00743	SO  	1997	6	5	97ZZZX2625       	1	19970516	G	7922	75944	VALVE           			PIPER 	PA32  	PA32R301T   	7103220	SO  										THERMO BYPASS	LOOSE CRIMP NUT 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8387D				63736	32R8129072				VERNATHERM VALVE INSPECTED PER LYCOMING SB 518C.  NUT LOOSE.  SUBMITTER STATED VALVES CONTINUE TO BE A PROBLEM.  THIS BU	LLETIN SHOULD BE MADE INTO AN AIRWORTHINESS DIRECTIVE.					1	L	7	1 	3O				A3SO    					 
1997060500744	19970605	00744	SO  	1997	6	5	97ZZZX2626       	1	19970428	G	7922	53E19600	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  										THERMO BYPASS	NUT LOOSE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	89PA	872  				317952110				FOUND NUT LOOSE.  LYC SB 518C DOES NOT APPLY.  THIS VALVE ABOVE S/N LIST IN SB 518C.  USE VALVE MADE BY SUPERIOR.  IT HA	S ROLL PIN TO HOLD NUT ON VALVE.					1	L	7	2 	3O				A20SO   					 
1997060500745	19970605	00745	CE  	1997	6	5	97ZZZX2627       	1	19970501	G	3222		BRACE           			BEECH 	35    	K35         	1151524	CE  										UPPER NLG	CORRODED        	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	9520R					D6154				ABOVE THE LOWER BEARING IN THIS CASTING, THERE IS CORROSION ALL THE WAY THROUGH THE NOSE WHEEL BRACE ASSY.  THE CORROSIO	N IS ON THE INSIDE AND HARD TO SEE WITHOUT DISASSEMBLING.  TOTAL TIME ON THIS AIRCRAFT IS 3,315 HRS.					1	L	7	1 	3O				3A15    					 
1997060500746	19970605	00746	WP  	1997	6	5	97ZZZX2628       	2	19970227	G	7320		APR SYSTEM      			LEAR  	55    	55LEAR      	5170702	CE  	GARRTT	TFE731	TFE7313A    	01518	WP  					ENGINE	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	646G	763  			108291	016				AUXILIARY PERFORMANCE RESERVE (APR).  WHEN SYSTEM IS 'ARMED' SYSTEM GOES STRAIGHT TO 'ON' WHEN N2'S ARE MATCHED.						2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1997060500747	19970605	00747	NM  	1997	6	5	97ZZZX2629       	1	19970512	G	2782	654476015	ACTUATOR        			BOEING	737   	737*        		NM  										LE SLAT	MISMODIFIED     	H	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03										SLAT ACTUATOR FAILED TO OPERATE PROPERLY UPON INSTALLATION.  INITIAL INSPECTION AND TESTING REVEALED COMPONENT TO BE THE	 DASH 12 CONFIGURATION RATHER THAN DASH 15 CONFIGURATION.  THE CURRENT CONFIGURATION WAS DETERMINED BY THE LENGTH OF STR	OKE AND A BEARING PART NUMBER.  CUSTOMER STATES THIS UNIT HAS NOT BEEN OPERATED SINCE OVERHAUL.				2	L	7	2 	4F			RT	A16WE   					 
1997060500748	19970605	00748		1997	6	5	97ZZZX2630       	4	19970508	G	6122	1355780REVA	PACKING         	WOODWARD    	8210212D    	BEECH 	300   	300BEECH    	1152930	CE  										BETA VLV SHAFT	DEFECTIVE       	C			W0VM	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			EA	09	1WV		63   		2137236	FA62				WHEN POWER WAS REDUCED DURING LANDING FLARE, RT PROP WENT TO A FLATTER PITCH THAN LEFT.  BELIEVE O-RING TO BE TIGHT IN B	ORE OF BETA VALVE.  REPLACED O-RING.  MADE NO CHANGES IN RIGGING.  NEW O-RING PERFORMED SATISFACTORY.					2	L	7	2 	4T				A24CE   					 
1997060500749	19970605	00749	WP  	1997	6	5	97ZZZX2631       	2	19970513	G	7261	31081381	GASKET          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					TURB SCAV PUMP	FAILED          	B			ATZR	K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CE	09	19WP	3154 				TC390	P54286			SCAVENGE PUMP GASKET WENT BAD CAUSING SLOW LOSS OF ENGINE OIL.  ALSO, THIS CAUSED VIBRATION TO BREAK OIL JET AT PUMP ASS	Y.  NEW STYLE GASKET NOW INSTALLED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997060500750	19970605	00750	WP  	1997	6	5	97ZZZX2632       	2	19970407	G	7250	8682721	ROTOR           			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE3313U    	01514	WP  					2ND STAGE TURB	CRACKED         	B			S2WR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	264B	2842 			80134510069	T221	P03074C			SECOND STAGE TURBINE ROTOR EXHIBITS RIVET HOLE CRACKS 0.020 INCH TO 0.050 INCH DEEP.  DEFECT DISCOVERED 200 HOURS AFTER 	HOT SECTION INSPECTION AT UNSCHEDULED ENGINE REMOVAL.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
1997060500751	19970605	00751	EU  	1997	6	5	97ZZZX2633       	1	19970522	G	2130	25VF3323309	CONTROL LINE    			BRAERO	DH125 	BAE125800A  	1500285	EU  										PRESS VENTURI	CHAFED          	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	300GN	3315 				258057				REMOVED CABIN FLOOR PANEL F61A AT FRAME 9 RT SIDE FOR UNRELATED MAINTENANCE WORK.  FOUND PRESSURIZATION VENTURI CONTROL 	LINE CUT APPROXIMATELY ONE-HALF WAY THROUGH FROM LOWER AILERON CABLE CONTACTING LINE WHENEVER AILERON CONTROL WHEEL MOVE	D.  AFTER FURTHER INSPECTION, IT APPEARS LINE WAS NOT INSTALLED WITH SUFFICIENT CLEARANCE FROM CABLE. INSPECTED CABLE, F	OUND NOT TO BE WORN.  INSTALLED NEW LINE AND PROVIDED PROPER CLEARANCE.			2	L	7	2 	4F			RT	A3EU    					 
1997060500752	19970605	00752	SW  	1997	6	5	97ZZZX2634       	1	19970404	G	3240	111672BD090S0000	BRAKE LINE      			SWRNGN	SA226 	SA226T      	8780122	SW  										OTBD BRAKE ASSY	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	39MS					T257				WHILE REMOVING BRAKE ASSY, NORMAL FLEXING OF OTBD BRAKE LINE CAUSED LINE TO BREAK OFF AT METAL FERRULE. FURTHER INVESTIG	ATION REVEALED LINE WAS SO BRITTLE, IT LITERALLY SNAPPED OFF RIGHT THROUGH THE FABRIC AND METAL BRAIDING.  RESEARCH OF L	OG BOOKS SHOWED THE BRAKE LINES ARE ORIGINAL AND ALL HAVE A MANUFACTURE DATE OF 1974.  NO TIME LIFE REQUIREMENTS, SB'S, 	SL'S, OR AD'S WERE FOUND THAT ADDRESSES THE CHANGE OF THESE BRAKE LINES.  SUBMITTER RECOMMENDED OPERATOR OF THESE AIRCRA	FT CHECK MANUFACTURE DATE AND INSPECT BRAKE LINES AND REPLACE, AS NEEDED, BEFORE A FAILURE OCCURS.		2	L	7	2 	4T			RT	A5SW    					 
1997061200124	19970612	00124	CE  	1997	6	12	97ZZZX2636       	1	19970402	G	3244	850T061	TIRE            	GOODYEARAERO		MTSBSI	MU2   	MU2B36      	5780412	CE  										RT MLG	SEPARATION      	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	09	500PJ	284  			51710805	668				RIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE COMPLETELY AROUND CIRCUMFERENCE.  OCCURRED ON L	ANDING.  TIRE REMAINED INFLATED.  TREAD STAYED ATTACHED AROUND OUTBOARD EDGE CIRCUMFERENCE.  THIS WAS ONE OF THREE SIMIL	AR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT AIRCRAFT (BOTH MU-2'S).  TIRE RETURNED TO MFG FOR EVALUATION.				1	H	7	2 	3T			RT	A10SW   					 
1997061200125	19970612	00125	CE  	1997	6	12	97ZZZX2637       	1	19970430	G	3244	850T061	TIRE            	GOODYEARAERO		MTSBSI	MU2   	MU2B36      	5780412	CE  										LT MLG	SEPARATION      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	500PJ	228  			51582304	668				LEFT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE FOR APPROXIMATELY 10 INCHES.  OCCURRED ON LANDIN	G.  TIRE REMAINED INFLATED.  THIS WAS ONE OF 3 SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT MU-2'S.  TIRE WAS RET	URNED TO MFG FOR EVALUATION.				1	H	7	2 	3T			RT	A10SW   					 
1997061200126	19970612	00126	CE  	1997	6	12	97ZZZX2638       	1	19970421	G	3260	1CH16	SWITCH          			LEAR  	35    	35A         	5170602	CE  										NLG ACTUATOR	INTERMITTENT    	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	425AS					281				DURING LANDING GEAR RETRACTION FOR MAINTENANCE, NOSE GEAR DOWNLOCK LIGHT BECAME INTERMITTENT.  TROUBLESHOT TO NOSE GEAR 	ACTUATOR DOWNLOCK SWITCH.  REMOVED SWITCH AND FOUND WIRE POTTING COMPOUND CRACKED AT SWITCH CASE.  WHEN WIRES WERE FLEXE	D AT CRACK, CONNECTION WAS INTERMITTENT.  THE NEW SWITCH HAD A MUCH MORE FLEXIBLE POTTING COMPOUND.  SUGGEST CLOSE ATTEN	TION TO POTTING COMPOUND AREA OF SWITCH WHERE WIRES FLEX.			2	L	7	2 	4F				A10CE   					 
1997061200127	19970612	00127	EU  	1997	6	12	97ZZZX2639       	1	19970430	G	2752	1181	MOTOR           		AVIAC60144  	AMD   	FALC10	FALCON10    	2730101	EU  										FLAP GEARBOX	SCREW LOOSE     	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	654PC		1107 		190	131				PILOTS REPORTED FLAP CIRCUIT BREAKER TRIPPED ON SELECTION, RESET AND WORKED FINE.  OPS CHECKED ON GROUND, COULD NOT DUPL	ICATE.  APPROXIMATELY 20 DAYS LATER, HAPPENED AGAIN.  REMOVED FLAP REDUCTION GEAR MOTOR, DISASSEMBLED, FOUND SET SCREW, 	PN ATQ1ED040005UL, AND NUT, PN 936-003, LAYING LOOSE IN HOUSING.  THERE WAS DAMAGE TO CLUTCH SPRINGS AND OTHER SIGNS OF 	CONTACT IN GEARBOX.			2	L	7	2 	4F				A33EU   					 
1997061200128	19970612	00128	CE  	1997	6	12	97ZZZX2640       	1	19970506	G	2430	60884082	GCU             			LEAR  	60    	60LEAR      	5170707	CE  										NR 2 BATTERY	STUD LOOSE      	D	P			K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			EA	25	660AH	1356 				017				STUD THAT CONNECTS NR 2 BATTERY TO BATTERY BUSS IS LOOSE.  DISCREPANCY FOUND DURING 300-HOUR  INSPECTION.  STUD LOCATED 	IN THE GENERATOR CONTROL PANEL.  EVIDENCE OF OVERHEAT CONDITION.					2	L	7	2 	4F			RT	A10CE   					 
1997061200129	19970612	00129	EU  	1997	6	12	97ZZZX2641       	1	19970513	G	5610		WINDSHIELD      			AMD   	FALC50	FALCON50MYST	2730106	EU  										COPILOT OUTER	CRACKED         	B			JGVR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	09	747Y					50				OUTER WINDSHIELD CRACKED WHILE AIRCRAFT WAS IN CRUISE FLIGHT.  AIRCRAFT WAS VISUALLY INSPECTED AND DETERMINED IN AIRWORT	HY CONDITION.  SUSPECT CAUSE OF CRACK WAS A DEFECT IN THE OUTER PANEL OF THE WINDSHIELD.					2	L	7	3 	4F				A46EU   					 
1997061200130	19970612	00130		1997	6	12	97ZZZX2642       	4	19970514	G	3425	727421	CIRCUIT BREAKER 			BRAERO	DH125 	BAE125800A  	1500285	EU  										EFIS PWR SUPPLY	SHORTED         	B	S		JGVR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CE	09	800N	6739 				258003				WHILE PERFORMING 1,200 HOUR CHECK (CODE 340009 ON PAGE 4 OF CHAPTER 5) OF EFIS POWER SUPPLIES, FOUND EFIS TUBES TO BLANK	 OUT WITH RT GENERATOR OFF AND BUS TIE OPEN.  FURTHER INVESTIGATION FOUND 35 AMP CIRCUIT BREAKER B5 (TO FEED PS1B BUS FR	OM PS1 BUS) ON PANEL ZK TRIPPED.  THIS C/B WAS CHANGED.  ANOTHER ENGINE RUN TO FUNCTION TEST THIS SYSTEM SHOWED (WITH RT	 GENERATOR OFF AND BUS TIE OPEN) EFIS TUBES TO REMAIN ON FOR ABOUT 10 SECONDS AND THEN 35 AMP B5 BREAKER WOULD TRIP WITH	 22 VOLTS SHOWING ON PS2 BUS (SHOULD READ ZERO).  WHILE ISOLATING VOLTAGE SOURCE, FOUND SMOKE COMING FROM SUBPANEL 'C' O	F DA PANEL.  FOUND LOWER TERMINAL OF 1 AMP BREAKER (PN 7274-2-1) FOR 'EFIS EQUIP NR 1' ABRADED INTO A WIRE BUNDLE.	2	L	7	2 	4F			RT	A3EU    					 
1997061200131	19970612	00131	CE  	1997	6	12	97ZZZX2643       	1	19970417	G	3244	850T061	TIRE            	GOODYEARAERO		MTSBSI	MU2   	MU2B36      	5780412	CE  										RT MLG	SEPARATION      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	869P	300  			51701608	692				RIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE FOR APPROXIMATELY 1 INCH.  SEPARATION NOTICED D	URING A POST-FLIGHT WALK AROUND INSPECTION.  THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT M	U-2'S. TIRE WAS RETURNED TO MFG FOR EVALUATION.				1	H	7	2 	3T			RT	A10SW   					 
1997061200132	19970612	00132		1997	6	12	97ZZZX2644       	4	19970426	G	2563	400	PARACHUTE       	RELATIVE    	3253        															STEERING LINES	MALFUNCTION     	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15										RESERVE PARACHUTE ACTIVATED DUE TO MAIN CHUTE MALFUNCTION FOLLOWING DROGUE RELEASE.  THE SLIDE HUNG UP THREE-FOURTHS OF 	THE WAY BY TENSION KNOTS ON BOTH STEERING LINES.  RESERVE EMERGENCY PROCEDURES EXECUTED NORMALLY.																		 
1997061200133	19970612	00133		1997	6	12	97ZZZX2645       	4	19970414	G	2561	KS9	LIFE VEST       	EAAEROMARINE																CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					BB1482					LIFE VEST FAILED THE MANUFACTURER'S 2 PSI INFLATION TEST.																			 
1997061200134	19970612	00134		1997	6	12	97ZZZX2646       	4	19970417	G	2561	KS9	LIFE VEST       	EAAEROMARINE																CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					B18664					LIFE VEST FAILED THE MANUFACTURER'S 2 PSI INFLATION TEST.																			 
1997061200135	19970612	00135		1997	6	12	97ZZZX2647       	4	19970528	G	2561	KS9	LIFE VEST       	EAAEROMARINE																CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					C77644					LIFE VEST FAILED 2 PSI TEST.																			 
1997061200136	19970612	00136		1997	6	12	97ZZZX2648       	4	19970414	G	2561	GA12	LIFE VEST       	EAAEROMARINE																CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					A76108					LIFE VEST FAILED THE MANUFACTURER'S 2 PSI INFLATION TEST.																			 
1997061200137	19970612	00137		1997	6	12	97ZZZX2649       	4	19970414	G	2561	KS9	LIFE VEST       	EAAEROMARINE																CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					B18454					LIFE VEST FAILED THE MANUFACTURER'S 2 PSI INFLATION TEST.																			 
1997061200138	19970612	00138	SO  	1997	6	12	97ZZZX2650       	1	19970524	G	2750	451813	TRANSMISSION    			PIPER 	PA31T 	PA31T       	7103124	SO  										FLAP	EXCESS WEAR     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	111KV				97020016	31T7920035				FLAP TRANSMISSION INSTALLED ON PIPER PA31T.  EXCESSIVE JACK SCREW WEAR EXCEEDED LIMITS IN 60-DAY PERIOD.  PART WAS ORIGI	NALLY REBUILT BY MANUFACTURER.  PART RETURNED TO MANUFACTURER FOR EVALUATION.  TOTAL TIME ON PART, 99.6 HOURS, APPROXIMA	TELY 70 CYCLES.				1	L	7	2 	3T				A8EA    					 
1997061200139	19970612	00139	EU  	1997	6	12	97ZZZX2651       	1	19970514	G	3221	TB1042010005	MOUNT           			SOCATA	TB9   	TB9         	8680694	EU  										NLG	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	142ER	4304 				1337				NOSE GEAR MOUNT TUBE RUSTED FROM INSIDE OUT.  SUBMITTER STATED RUSTED AREA 2ND ONE FOUND IN FLEET.						1	L	7	1 	3O			NT	AS1EU   					 
1997061200140	19970612	00140	EA  	1997	6	12	97ZZZX2652       	2	19970520	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					POWER SECTION	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AL	01	3582P	7799 	1391 			318052103	L655361A			DURING DESCENT TO LANDING, PILOT NOTICED MANIFOLD PRESSURE STARTING TO DECREASE, FUEL FLOW INCREASE AND CYLINDER HEAD TE	MP DECREASE AND THE EXHAUST GAS TEMP DECREASE.  AFTER LANDING AND ON THE GROUND, THE ENGINE WOULD ONLY PRODUCE 2,200 RPM	 AND 28 INCHES OF MANIFOLD PRESSURE.  THE OIL SCREENS WERE CHECKED WITH AN EXCESIVE AMOUNT OF STEEL AND ALUMINUM SHAVING	S FOUND.  THE ENGINE WAS REMOVED FROM SERVICE FOR A TEAR DOWN INSPECTION.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997061200141	19970612	00141	SO  	1997	6	12	97ZZZX2653       	1	19970501	G	5711	6707002	SPAR            			PIPER 	PA28  	PA28R180    	7102809	SO  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3760T	4500 				28R30069				DURING ANNUAL INSPECTION, FOUND LT WING MAIN SPAR UPPER CAP SEVERELY CORRODED ON FWD FLANGE.  ONLY WAY TO DETECT IS WITH	 A MIRROR THROUGH FWD WHEELWELL INSPECTION PANEL.  WING REMOVED AND SPAR REPLACED. SUBMITTER STATED INTERGRANULAR CORROS	ION IS THE CAUSE.				1	L	7	1 	3O				2A13    					 
1997061200142	19970612	00142	SO  	1997	6	12	97ZZZX2654       	1	19970501	G	5753	6232840	RIB             		6232000     	PIPER 	PA28  	PA28R180    	7102809	SO  										LT FLAP	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3760T	4500 				28R30069				DURING ANNUAL INSPECTION, FOUND BOTH LT AND RT FLAP OTBD HINGE BRACKETS ATTACHED TO FLAPS WORKING WERE FREE DUE TO CORRO	SION ON END CAPS.  REMOVED AND REPLACED CAPS AND REATTACHED BRACKETS.  CAUSE OF FAILURE APPEARS TO BE DISSIMILAR METAL C	ORROSION.				1	L	7	1 	3O				2A13    					 
1997061200143	19970612	00143	SO  	1997	6	12	97ZZZX2655       	1	19970501	G	5753	6232901	RIB             		6232002     	PIPER 	PA28  	PA28R180    	7102809	SO  										RT FLAP	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3760T	4500 				28R30069				DURING ANNUAL INSPECTION, FOUND BOTH LT AND RT FLAP OTBD HINGE BRACKETS ATTACHED TO FLAPS WERE WORKING FREE DUE TO CORRO	SION ON END CAPS.  REMOVED AND REPLACED CAPS AND REATTACHED BRACKETS.  CAUSE OF FAILURE APPEARS TO BE DISSIMILAR METAL C	ORROSION.				1	L	7	1 	3O				2A13    					 
1997061200144	19970612	00144	SO  	1997	6	12	97ZZZX2656       	2	19970404	G	8530	J92KBW	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					SLEEVE	CRACKED         	B			BUPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	45511				653426	15076955	1994529A			WHILE CHANGING PUSHROD SEALS, A CRACK WAS FOUND IN THE CYLINDER SLEEVE, THE CRACK IS ABOUT 1.5 INCHES LONG AND TRAVELED 	RADIALLY.  THE CRACK IS ABOUT 2 INCHES UP FROM THE BASE FLANGE.					1	H	7	1 	3O	3	O		3A19    	E252				 
1997061200146	19970612	00146	CE  	1997	6	12	97ZZZX2658       	1	19970506	G	5753	052323113	FLAP TRACK      			CESSNA	172   	172M        	2072418	CE  										LT FLAP WELL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	64134	7052 				17265039				SEVERE CORROSION AND WEAR FOUND ON TRACK DURING ANNUAL INSPECTION.  TRACK AND ROLLERS SHOWED NO SIGNS OF RECENT LUBRICAT	ION.  TRACK IS AVAILABLE FOR INSPECTION.					1	H	7	1 	3O			NT	3A12    					 
1997061200147	19970612	00147	EA  	1997	6	12	97ZZZX2659       	2	19970514	G	8530	SL15345	PUSHROD         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE CYLINDER	FAILED          	B			QX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	738QZ	312  				17270167	L577876T			BALL END OF PUSHROD BROKEN OFF.  SUBITTER STATED A POSSIBLE MANUFACTURE MACHINING DEFECT.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997061200148	19970612	00148	SO  	1997	6	12	97ZZZX2660       	2	19970505	G	8530	641916	CYLINDER        			CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300D       	17022	SO  					HEAD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8220X	3518 	705  			17248720	24677010			DURING AN INSPECTION, CYLINDER WAS FOUND WITH LOW COMPRESSION/EXHAUST VALVE LEAKAGE.  CYLINDER WAS REMOVED FOR REPAIR AN	D SENT TO ENGINE SHOP.  AFTER CLEANING, NOTED THE HEAD WAS CRACKED FROM THE ROCKER COVER FLANGE THROUGH THE EXHAUST PORT	 AND ACROSS TO THE UPPER SPARKPLUG HOLE.  CYLINDER WAS REPLACED WITH A NEW ASSEMBLY.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997061200149	19970612	00149	SO  	1997	6	12	97ZZZX2661       	2	19970331	G	8530	SA10200A20P	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 3	FAILED          	B			BUPR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			EA	23	8898U		145  			15078019	264405A48			WHILE PERFORMING A POWER OFF STALL TO FULL POWER RECOVERY, PILOT FELT ENGINE BEGIN TO RUN ROUGH.  WHILE RETURNING TO AIR	PORT, IT STARTED TO GET WORSE.  PILOT SUCCESSFULLY LANDED AIRCRAFT.  UPON INSPECTION, FOUND NR 3 CYLINDER SPLIT IN HALF 	ABOUT 2 INCHES UP FROM BASE FLANGE.  VISUAL INSPECTION OF BREAK SHOWED 90 PERCENT SMOOTH AND 10 PERCENT JAGGED EDGE.  PI	STON AND CONNECTING ROD WERE BOTH DESTROYED.			1	H	7	1 	3O	3	O		3A19    	E252				 
1997061200150	19970612	00150	EA  	1997	6	12	97ZZZX2662       	2	19970526	G	7322	RSA5AD1	SERVO           			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540D4A5   	41532	EA  					FUEL INJ	SEAL LEAK       	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	16	991K				6543	244055	L138248			ENGINE ROUGHNESS DUE TO EXCESS RIGH MIXTURE.  FOUND RECENT OVERHAULED SERVO TO BE AT FAULT DUE TO SEAL LEAKING FUEL INTO	 AIR CHAMBER.  SERVO TSO SERVICE 30 HOURS.  SEAL, S/N 2539561.					1	L	7	1 	3O	3	O		1A15    	1E4				 
1997061200151	19970612	00151	SO  	1997	6	12	97ZZZX2663       	1	19970501	G	3211	6704013	TRUNNION PLATE  			PIPER 	PA34  	PA34200T    	7103406	SO  										MLG	BOLTS LOOSE     	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2855U	4090 				347970294				RIGHT SIDE FORWARD LANDING GEAR TRUNNION PLATE BOLTS WERE BACKED OUT AND HOLES IN PLATE HAD ELONGATED AS A RESULT.  THIS	 PLATE HAD BEEN PREVIOUSLY MODIFIED IAW PIPER SB 956, PART TWO, WHICH HAD ENLARGED BOLT HOLES AS OUTLINED IN SB.  LARGER	 BOLTS AN5-10A5 ARE INSTALLED AT TIME OF PERFORMANCE OF SB ALONG WITH NUTPLATES OR NUTS AS REQUIRED.				1	L	7	2 	3O				A7SO    					 
1997061200152	19970612	00152	CE  	1997	6	12	97ZZZX2664       	1	19970429	G	5711	052340014	SPAR            			CESSNA	172   	172B        	2072406	CE  										STIFFENER	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	6978X	3344 				17247878				DURING HIDDEN DAMAGE INSPECTION OF WINGS AFTER HAIL AND WIND DAMAGE, FORWARD LEFT WING SPAR, EXTRUDED STIFFENER WAS FOUN	D TO HAVE SEVERAL SPOTS OF INTERGRANULAR CORROSION.  SUBMITTER STATED THIS IS A COMMON PROBLEM ON CESSNAS THAT DID NOT H	AVE ANY WING PARTS PRIMERED PREVIOUSLY AT THE FACTORY.				1	H	7	1 	3O			NT	3A12    					 
1997061200153	19970612	00153	CE  	1997	6	12	97ZZZX2665       	1	19970429	G	5311	05230201	ANGLE CAP       			CESSNA	172   	172B        	2072406	CE  										LT WING SPAR	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	6978X	3344 				17247878				DURING HIDDEN DAMAGE INSPECTION OF WINGS AFTER HAIL AND WIND DAMAGE, THE FORWARD LT WING SPAR CAP WAS FOUND TO HAVE EXTE	NSIVE INTERGRANULAR CORROSION.  SUBMITTER STATED THIS IS A COMMON PROBLEM ON CESSNAS THAT DID NOT HAVE WING PARTS PRIMED	 AT THE FACTORY.				1	H	7	1 	3O			NT	3A12    					 
1997061200154	19970612	00154	CE  	1997	6	12	97ZZZX2666       	1	19970501	G	5320	521304011	TRUNNION TEE    			CESSNA	404   	404CESSNA   	2075901	CE  										NLG	BROKEN          	D				K				NONE                    				E			VIBRATION/BUFFET          			LD	LANDING        	1			NM	01	41SA					4040023				PILOT REPORTED SEVERE NOSE SHIMMY ON LANDING.  AIRCRAFT NOSE GEAR WAS JACKED UP AND FOUND BOTH TEE EXTRUSIONS BROKEN WHI	CH ARE PART OF THE PRIMARY STRUCTURAL SUPPORT FOR THE NOSE LANDING GEAR TRUNNION.					1	L	7	2 	3O				A25CE   					 
1997061200155	19970612	00155	CE  	1997	6	12	97ZZZX2667       	1	19970501	G	5343	521304012	TRUNNION TEE    			CESSNA	404   	404CESSNA   	2075901	CE  										NLG	BROKEN          	D	S	A		K				NONE                    				E			VIBRATION/BUFFET          			LD	LANDING        	1			NM	01	41SA					4040023				PILOT REPORTED SEVERE NOSE SHIMMY ON LANDING.  AIRCRAFT NOSE GEAR WAS JACKED UP AND FOUND BOTH TEE EXTRUSIONS BROKEN WHI	CH ARE PART OF THE PRIMARY STRUCTURAL SUPPORT FOR THE NOSE LANDING GEAR TRUNNION.					1	L	7	2 	3O				A25CE   					 
1997061200156	19970612	00156	CE  	1997	6	12	97ZZZX2668       	1	19970501	G	5320		HILOKS          			CESSNA	404   	404CESSNA   	2075901	CE  										NLG STRUCTURE	LOOSE           	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	48SA					4040417				DURING A RECENT MDL 404 GEAR INSPECTION, NOTED THE NOSE GEAR ACTUATOR ATTACH STRUCTURE HAD NUMEROUS LOOSE HI-LOKS.						1	L	7	2 	3O				A25CE   					 
1997061200157	19970612	00157	CE  	1997	6	12	97ZZZX2669       	1	19970527	G	3230	5741100203	GEAR PIN        			CESSNA	404   	404CESSNA   	2075901	CE  										MLG LINK PIVOT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	48SA					4040417				DURING A RECENT 404 TITAN GEAR INSPECTION ON THE MAIN LANDING GEAR, FOUND TRAILING LINK PIVOT PINS WORN EXCESSIVELY.  TH	E PHENOLIC-LINED BUSHINGS WERE WITHIN MANUFACTUER'S SPECS.  NEW PINS WERE INSTALLED.					1	L	7	2 	3O				A25CE   					 
1997061200158	19970612	00158	CE  	1997	6	12	97ZZZX2670       	1	19970527	G	3230	5741100204	GEAR PIN        			CESSNA	404   	404CESSNA   	2075901	CE  										MLG LINK PIVOT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	48SA					4040417				DURING A RECENT 404 TITAN GEAR INSPECTION ON THE MAIN LANDING GEAR, FOUND TRAILING LINK PIVOT PINS WORN EXCESSIVELY.  TH	E PHENOLIC-LINED BUSHINGS WERE SITHIN MANUFACTUER'S SPECS.  NEW PINS WERE INSTALLED.					1	L	7	2 	3O				A25CE   					 
1997061200161	19970612	00161	CE  	1997	6	12	97ZZZX2673       	3	19970418	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER PITCH	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4643 			2446NR					FORWARD EAR OF PROPELLER PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOT.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997061200162	19970612	00162	CE  	1997	6	12	97ZZZX2674       	3	19970521	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER PITCH	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					1791NR					FORWARD EAR OF PROPELLER PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997061200163	19970612	00163	CE  	1997	6	12	97ZZZX2675       	3	19970418	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER PITCH	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4541 			2313NR					FORWARD EAR OF PROPELLER PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOT.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997061200164	19970612	00164	NE  	1997	6	12	97ZZZX2676       	3	19970429	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER PITCH	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2996 			2740NP					FORWARD EAR OF PROPELLER PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997061200166	19970612	00166	NM  	1997	6	12	97ZZZX2677       	1	19970527	G	3230	35210400000	SWITCH HOUSING  		D25W252004  	ISRAEL	1125  	1125        		NM  										DWNLOCK ACTUATOR	LEAKING         	B			AN3R	O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			WP	23	49MW				019	019				AIRCRAFT LOST NORMAL HYDRAULIC SYSTEM PRESSURE.  AUXILIARY PUMP AND LANDING GEAR BLOW DOWN BOTTLE WERE USED FOR LANDING.	  FOUND LEFT MAIN LANDING GEAR ACTUATOR DOWNLOCK SWITCH HOUSING ALLOWING FLUID TO BYPASS PLUNGER SEALS, TRAVEL AROUND AN	D THROUGH DOWNLOCK SWITCH, AND LEAK FROM SWITCH HARNESS BEFORE SPRAYING INTO WHEELWELL.				2	L	7	2 	4F			RT	A16NM   					 
1997061200167	19970612	00167	CE  	1997	6	12	97ZZZX2678       	1	19970506	G	5610	10138402517	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  										HEAT TERMINAL	SMOKED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			GL	03	6PW	3670 			95271H5974	FA32				PILOT REPORTED SMOKE IN COCKPIT DURING DESCENT.  RAN AIRCRAFT AND FOUND PILOT'S WINDSHIELD SMOKING AT LOW HEAT TERMINAL.						2	L	7	2 	4T				A24CE   					 
1997061200168	19970612	00168	CE  	1997	6	12	97ZZZX2679       	1	19970501	G	3213	66413301	STRUT ASSY      			CESSNA	500   	560CESSNA   	2076750	CE  										SCISSOR PIN BOSS	WORN            	B	P	A	HAXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	615AT					5600245				LOWER SCISSOR PIN AND BOSS ASSEMBLY WORN EXCESSIVELY.  TOTAL TIME 1,071 HOURS. TOTAL CYCLES, 839.  THIS WAS FOUND DURING	 A ROUTINE INSPECTION.  THERE WAS A SMALL AMOUNT OF UP AND DOWN PLAY IN THE ASSEMBLY.					2	L	7	2 	4F			RT	A22CE   					 
1997061200170	19970612	00170	NE  	1997	6	12	97ZZZX2681       	2	19970520	G	7220	F2MA581100801	INLET           			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   		CFE73811B   		NE  					ENGINE	BOLTS LOOSE     	B		A	CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	790M	798  			FA037LN40	P105134	P105134			AFTER ENGINE FAILURE, MORE THAN HALF THE BOLTS SECURING THE ENGINE INLET HA D UNSCREWED THEMSELVES.  THE REMAINING WERE 	LOOSE.  SUBMITTER SUSPECTS UNUSUAL ENGINE VIBRATION CAUSED THE BOLTS TO BACK OUT.  THE INLET COULD POSSIBLY FALL OFF THE	 AIRCRAFT IN-FLIGHT.				2	K	7	3 	4F	4	F	RT	A50NM   	E44NE				 
1997061200171	19970612	00171	NE  	1997	6	12	97ZZZX2682       	2	19970520	G	7250		ENGINE          			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   		CFE73811B   		NE  					TURBINE	FAILED          	B		A	CW1R	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			EA	25	790M					19	P105134			RIGHT ENGINE COMPLETELY FAILED AFTER TAKEOFF AT APPROXIMATELY 200 FEET AGL.  AFTER A SUCCESSFUL LANDING, ENGINE WAS EXAM	INED AND FOUND THE FAN SEIZED; THE TURBINE BADLY DAMAGED.  NO EVIDENCE OF FOD WAS FOUND.  AWAITING EVALUATION FROM THE M	ANUFACTURER TO DETERMINE CAUSE.				2	K	7	3 	4F	4	F	RT	A50NM   	E44NE				 
1997061200172	19970612	00172	CE  	1997	6	12	97ZZZX2683       	1	19970523	G	3240	MS252531	SWITCH          			CESSNA	500   	560CESSNA   	2076750	CE  										GEAR CONTROL	FAILED          	D				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			EA	03	81SH	560  				5600357				FAILURE OF SWITCH RESULTED IN BRAKE PEDAL GOING TO FLOOR AND NO ANNUNCIATOR WARNING.  THIS SWITCH SUPPLIES A GROUND FOR 	THE POWER BRAKE PUMP AND THE LOW BRAKE PRESSURE ANNUNCIATOR LIGHT.  EXTENDED TR USE STOPPED AIRCRAFT WITHOUT INCIDENT.					2	L	7	2 	4F			RT	A22CE   					 
1997061200173	19970612	00173	EU  	1997	6	12	97ZZZX2684       	1	19970320	G	2620		CONNECTOR       			BRAERO	DH125 	BAE125800A  	1500285	EU  										FIRE EXT SYSTEM	MISINSTALLED    	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	935H					NA0475				DURING FUNCTIONAL TEST OF ENGINE FIRE EXTINGUISHER SYSTEM CIRCUIT CAMP CODE 262085, FOUND AFT FIRE BOTTLE CONNECTORS GH 	HEAD 'A' AND HEAD 'B' WERE INSTALLED REVERSED.  THE LABELING ON THE CONNECTORS READ 'AFT FIRE BOTTLE, AFT SQUIB' WHICH S	HOULD HAVE BEEN INSTALLED ON FWD SQUIB HAD THE ENGINE FIRE EXTINGUISHER NR 2 ENGINE SHOT 1 BEEN ACTIVATED, THE BOTTLE WO	ULD HAVE BEEN DISCHARGED TO THE NR 1 ENGINE.			2	L	7	2 	4F			RT	A3EU    					 
1997061200174	19970612	00174	EU  	1997	6	12	97ZZZX2685       	1	19970320	G	2150	20388022	COOLING TURBINE 			BRAERO	DH125 	BAE125800A  	1500285	EU  										BEARINGS	MAKING METAL    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	935H	1273 			79939	NA0475				AFTER ROTATION, CREW SELECTED MAIN AIR VALVES ON.  A RUMBLE AND VIBRATION WERE NOTED BY CREW LASTING APPROX 2 MINS INTO 	FLT.  REMAINDER OF TRIP WAS UNEVENTFUL.  AIRCRAFT TURNED OVER TO MAINTENANCE.  WITH APPLICATION OF BLEED AIR FROM THE AP	U, MAINTENANCE FOUND RUMBLE TO INCREASE WHEN SELECTING COOLER TEMPS.  A CHECK OF THE COOLING TURBINE OIL LEVEL WAS SATIS	FACTORY.  UPON REMOVAL OF THE MAG CHIP DETECTOR, EXCESSIVE AMOUNTS OF METAL AND BEARING PARTS WERE FOUND.  UNIT WAS REMO	VED AND REPLACED WITH THE UPGRADED/MODIFIED 203880-30-1 UNIT.  PART TT 1272.3 HOURS, 48 MONTHS FROM BUILD.		2	L	7	2 	4F			RT	A3EU    					 
1997061200175	19970612	00175		1997	6	12	97ZZZX2686       	4	19970412	G	3445	CAS67A	TCAS UNIT       			CESSNA	500   	550         	2076604	CE  										COCKPIT	MALFUNCTION     	G		A		B				EMER. DESCENT           				N			FALSE WARNING             			CR	CRUISE         	1			WP	17	960CP					5500313				PILOT DEVIATED FROM ASSIGNED ALTITUDE OF FL 330 AFTER HE APPARENTLY RECEIVED A SECOND RA VERBAL ALERT TO DESCEND WHILE A	PPROACHING ANOTHER AIRCRAFT AT ASSIGNED ALTITUDE OF FL 310.  PILOT SAID HE HAD TCAS II UNIT CHECKED AT A REPAIR STATION 	AND UNIT CHECKED GOOD.  AN ALLIED SIGNAL REPRESENTATIVE COULD FIND NO DEFECTS AFTER INSPECTING THE AIRCRAFT AND TCAS II 	UNIT.  PILOT OF THE OTHER AIRCRAFT DID NOT HAVE A TCAS RA ALERT.  ALLIED SIGNAL REPRESENTATIVE AT OLATHE, KS AND RESPECT	IVE FAA MIDO OFFICE HAS BEEN CONTACTED ABOUT THIS INCIDENT.  ATC DOCUMENTATION IS BEING FORWARDED TO THE RESPONSIBLE MID	O OFFICE.	1	L	7	2 	4F				A22CE   					 
1997061200780	19970612	00780	EA  	1997	6	12	97ZZZX2708       	2	19970514	G	8530	SL134441	PISTON PIN      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE CYLINDER	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			WP	11	739ZL		700  			17270936	L473076			CATASTROPHIC FAILURE AFTER TAKEOFF FROM CLEAR LAKE, CA ON 5-14-97.  PILOT TURNED BACK AND MADE UNPOWERED LANDING AT AIRP	ORT.  FOUND CYLINDER BROKEN OFF ENGINE.  PISTON BROKEN, CRANKSHAFT BROKEN.  PISTON PIN BROKEN IN HALF.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997061200781	19970612	00781	CE  	1997	6	12	97ZZZX2709       	1	19970522	G	3240	20701900	HOSE            	PARKERHANFIN	199101      	MTSBSI	MU2   	MU2B36A     	5780413	CE  	GARRTT	TPE331	TPE3315     	01514	WP  					BRAKE KIT	WRONG PART      	B			RG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	105WM	109  				709SA				FOUND, CLEVELAND BRAKE KIT 199-101 STC SA648GL BRAKE HOSES U/A HOSE LISTED SAE DOAS SAE DOT 3000 PSI AIR BRAKE HOSE, FIT	TING CONNECTORS WERE 45 DEGREE ANGLE AND HOSE FITTINGS WERE 45 DEGREES.  CONICAL SEAL WAS FOUND IN ONE HOSE FOR SEALINGS	.				1	H	7	2 	3T	4	T		A10SW   	E4WE				 
1997061200782	19970612	00782	CE  	1997	6	12	97ZZZX2710       	1	19970522	G	3240	20701900	HOSE            	PARKERHANFIN	19901       	MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					BRAKE KIT	WRONG PART      	B			RG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	223JS	770  				1544SA				FOUND CLEVELAND BRAKE KIT 199-101 STC 648GL BRAKE HOSES WERE SAE DOT 3000 PSI AIR BRAKE HOSES.  FITTINGS WERE 45 DEGREES	.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
1997061200783	19970612	00783	NE  	1997	6	12	97ZZZX2711       	3	19970516	G	6114	7943021	BEARING RACE    	HAMSTD      	7827014     											HAMSTD	14SF	14SF7       	NE  	NR 1 BORE	CRACKED         	B		A	BN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					804					REFERENCE:  FR28191 AND FW0508.  PROPELLER REMOVED DUE TO BURNED ELEMENT ON BLADE HEATER.  UPON BLADE REMOVAL, NR 1 BORE	 OUTER BEARING RACE FOUND CRACKED.  SUBMITTER'S RECOMMENDATIONS:  HUB ASSEMBLY AND NR 1 BLADE RETURNED TO HAMILTON STAND	ARD FOR INVESTIGATION.														6	C	P7NE	 
1997061200784	19970612	00784	NM  	1997	6	12	97ZZZX2712       	1	19970508	G	3250	1692R1	PRESSURE PORTS  		1692RA12    	BOEING	737   	737*        		NM  										STEERING VALVE	PITTED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					334					STEERING VALVE PRESSURE PORTS ARE CONTINUOUSLY FOUND PITTED AND SCORED FROM CONTAMINATION.  RECOMMEND SEALING ALL MATING	 POINTS WITH RTV SEALANT.					2	L	7	2 	4F			RT	A16WE   					 
1997061200785	19970612	00785	NM  	1997	6	12	97ZZZX2713       	1	19970521	G	2782	108010	ACTUATOR        		1U1110      	BOEING	727   	727         	1384001	NM  										LE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					296					DURING NDI, THE FLAP ACTUATOR BODY ASSEMBLIES WERE FOUND CRACKED IN THE EXTENSION TRUNNION PORT.						2	L	7	3 	4F				A3WE    					 
1997061200788	19970612	00788	CE  	1997	6	12	97ZZZX2716       	1	19970529	G	5711	5262	SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  										STRUT ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	2606G	2158 				51				INSPECTED SPAR IAW SL 406.  FOUND RIGHT FORWARD SPAR CRACKED OUTBOARD, AFT SIDE OF STRUT ATTACH DOUBLER.  CRACK VERY DIF	FICULT TO SEE WITHOUT BENDING LEADING EDGE ALUMINUM UP TO GET A CLEAR VIEW OF TOP OF SPAR. THIS CRACK COULD NOT BE SEEN 	FROM BOTTOM OF WING USING MIRRORS AND LIGHTS.  WING HAD BEEN DAMAGED IN A GROUND LOOP PREVIOUSLY.				1	H	7	1 	3O				A759    					 
1997061200789	19970612	00789	CE  	1997	6	12	97ZZZX2717       	1	19970526	G	4940	15700431	DIODE BOARD     			CESSNA	210   	T210L       	2073449	CE  										APU	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	732AJ	4220 				21061360				HOOKED UP APU AND STARTER IMMEDIATELY CRANKED ENGINE.  INVESTIGATION FOUND BOARD CONTAINING  DIODES IN CABIN NEXT TO POW	ER RELAY TO HAVE BOTH DIODES INOPERATIVE.  PART IS IN DIFFICULT LOCATION TO TEST INDIVIDUAL DIODES.  REPLACED DIODE BOAR	D P/N 1570043-1 AND TESTED GOOD.  RECOMMEND TESTING APU AT EACH ANNUAL.  NOTE:  PARTS MANUAL DOES NOT SHOW PART ON THIS 	SERIAL NUMBERED ACFT; HOWEVER, MAINTENANCE SCHEMATIC IS NOT SERIAL SPECIFIC.			1	H	7	1 	3O				3A21    					 
1997061200790	19970612	00790	GL  	1997	6	12	97ZZZX2718       	1	19970503	G	6310		CLUTCH          			AMTR  	500   	MINI500     	13015HW	GL  										ENGINE	VIBRATION       	D				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	07	5455K					0090				THIS IS AN AMATEUR-BUILT AIRCRAFT FROM REVOLUTION HELICOPTERS.  AT 100 PERCENT ENGINE RPM, PILOT REPORTED A VERY HIGH VI	BRATION IN THE AIRFRAME.  TROUBLESHOOTING REVEALED AN 8.0 IPS VIBRATION AT 6,500 RPM AT THE ENGINE CLUTCH ASSY.  THE CLU	TCH WAS SENT BACK TO REVOLUTION WHO RE-BALANCED THE ASSEMBLY.  AFTER RE-BALANCING AND RE-INSTALLATION, THE VIBRATION WAS	 STILL PRESENT.			1	G	7	1 	3I			NC	EXPA1G71					 
1997061200791	19970612	00791	NM  	1997	6	12	97ZZZX2719       	1	19970227	G	7921	20008A	OIL COOLER      			ROBSIN	R22   	R22BETA     		NM  										ENGINE OIL	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	444PH	1492 				1578				ALTERNATOR BELT P/N 3VX375 BROKE DAMAGING THE OIL COOLER P/N 20008A CAUSING A LOSS IN OIL PRESSURE.						1	G	7	1 	3O				H10WE   					 
1997061200792	19970612	00792	NM  	1997	6	12	97ZZZX2720       	1	19970227	G	2410	3VX375	BELT            			ROBSIN	R22   	R22BETA     		NM  										ALTERNATOR	BROKE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	444PH	1492 				1578				ALTERNATOR BELT P/N 3VX375 BROKE DAMAGING THE OIL COOLER P/N 20008A CAUSING A LOSS IN OIL PRESSURE.						1	G	7	1 	3O				H10WE   					 
1997061200793	19970612	00793	SW  	1997	6	12	97ZZZX2721       	1	19970512	G	5512	222035250109	SKIN            			BELL  	222   	222U        	1182140	SW  										HORIZ STABILIZER	TORN            	B			BUBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	911EC	1371 				47505				A TEAR IN THE HORIZONTAL STABILIZER SKIN WAS FOUND DURING INSPECTION.  THE DAMAGE WAS LOCATED ON THE RT INBOARD LEADING 	EDGE. THE DAMAGE MAY HAVE BEEN CAUSED DURING IMPROPER OR ROUGH INSTALLATION.  THE DAMAGE WAS REPAIRED UNDER MANUFACTURER	'S INSTRUCTIONS AND FAA FORM 337 FOR THIS AIRCRAFT DATED 5-12-97 HAS BEEN SUBMITTED.   A 'NOTE' IN THE INSTALLATION INST	RUCTIONS OF THE MM COULD HELP OTHERS FROM DAMAGING THIS PART.			1	G	7	2 	3U				H9SW    					 
1997061200794	19970612	00794	SW  	1997	6	12	97ZZZX2722       	1	19970522	G	5302	222035150105	TAILBOOM        			BELL  	222   	222U        	1182140	SW  										T/B RT SIDE	CRACKED         	B			BUBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	911EC	1371 				47505				A CRACK OF OVER 2 INCHES WAS FOUND ON RT SIDE OF TAILBOOM DURING PILOT POST-FLIGHT CHECK.  OTHER OPERATORS HAVE EXPERIEN	CED CRACKS IN THE SAME AREA.  BELL HAS ISSUED A TECHNICAL BULLETIN (TB 222U-94-65) TO ADDRESS THE PROBLEM.  SUBMITTER RE	COMMENDATION, HAVE BELL CHANGE THE TB TO AN ASB.				1	G	7	2 	3U				H9SW    					 
1997061200795	19970612	00795	NE  	1997	6	12	97ZZZX2723       	2	19970527	G	7230		COMPRESSOR      			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENGINE	DAMAGE          	D				O				OTHER                   				E	C		VIBRATION/BUFFET          	F.O.D.                    		HO	HOVERING       	1			WP	07	91GT	3497 	500  			1289	4078			PICKED UP HIGH FREQUENCY VIBRATION WHILE HOVERING TO MAINTENANCE HANGAR.  UPON INSPECTION, FOUND FOD DAMAGE TO COMPRESSO	R.  SUSPECTED CAUSE IS ROTOR WASH KICKED UP FOD.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
1997061200796	19970612	00796	SW  	1997	6	12	97ZZZX2724       	1	19970514	G	6710	A21810064603	SWITCH          			HUGHES	500N  	500N        	3027374	SW  										PILOT CYCLIC	STICKS          	G		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	99	524FB	336  				LN004				TRIM SWITCH STICKS TO RIGHT MAKING MOTOR RUN UNTIL BREAKING.						1	G	7	1 	3U			NC	H3WE    					 
1997061200827	19970612	00827	GL  	1997	6	12	97ZZZX2753       	2	19970506	G	7323	23057869	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50588		194  		86220668	S780				NR 1 ENGINE WOULD NOT BEEP PAST 95 PERCENT N2.  REPLACED GOVERNOR, CURED PROBLEM.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997061200828	19970612	00828	GL  	1997	6	12	97ZZZX2754       	2	19970502	G	7323	23057869	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5352Y		814  		85590222	S781				18 PERCENT TORQUE SPLIT.  REPLACED GOVERNOR CURED PROBLEM.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997061200829	19970612	00829	NE  	1997	6	12	97ZZZX2755       	1	19970508	G	5210	7620902019043	HINGE           			SKRSKY	S76   	S76         	8143010	NE  										DOOR	CORRODED        	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5401G	13674				760137				CORROSION WHERE BUSHINGS GO THROUGH HINGE.  REPLACED DOOR HINGE.						1	G	7	2 	3U				H1NE    					 
1997061200830	19970612	00830	GL  	1997	6	12	97ZZZX2756       	2	19970507	G	7323	23004836	GOVERNOR        			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTION     	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T		1331 		25705	760140				UNRESPONSIVE AT HIGH TORQUE RANGES.  SHAFT RATCHETY AND STIFF.  REPLACED GOVERNOR.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997061200831	19970612	00831	NE  	1997	6	12	97ZZZX2757       	2	19970312	G	7320	2525013	AFCU            		324473513   	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					DIAPHRAGM	TORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2071S	833  				33046				DURING REPAIR OF AFCU, FOUND DIAPHRAGM TORN AND ABOUT TO RUPTURE.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1997061900379	19970619	00379	SW  	1997	6	19	97ZZZX2758       	1	19970402	G	6320	206040032011	BEARING         		206040004107	BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	FAILED          	B			ALGR	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	350AL				J0972	51429				FIELD CHIP LIGHT.  FOUND BEARING BALLS, INNER AND OUTER RACE,  PITTED (BREAKING DOWN).						1	G	7	1 	3U				H2SW    					 
1997061900380	19970619	00380	SW  	1997	6	19	97ZZZX2761       	1	19970327	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	407AL	309  				53044				DURING 50-HOUR PREVENTIVE MAINTENANCE INSPECTION, FOUND T/R DRIVE SHAFT DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997061200834	19970612	00834	SW  	1997	6	12	97ZZZX2762       	1	19970327	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	407AL	394  				53044				DURING A 50-HOUR PREVENTIVE MAINTENANCE INSPECTION, FOUND DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997061200835	19970612	00835	SW  	1997	6	12	97ZZZX2763       	1	19970327	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	305  				53054				DURING 50-HOUR PREVENTIVE MAINTENANCE INSPECTION, FOUND T/R DRIVE SHAFT DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997061200836	19970612	00836	SW  	1997	6	12	97ZZZX2764       	1	19970327	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	351  			RNFS4667	53054				DURING 50-HOUR PREVENTIVE MAINTENANCE INSPECTION, FOUND T/R DRIVE SHAFT DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997061200837	19970612	00837	SW  	1997	6	12	97ZZZX2765       	1	19970327	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	131  				53054				DURING 50-HOUR PREVENTIVE MAINTENANCE INSPECTION, FOUND T/R DRIVE SHAFT DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997061200838	19970612	00838	SW  	1997	6	12	97ZZZX2766       	1	19970304	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										FWD END	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL				RNFS4887	53054				DURING 50-HOUR PMI, FOUND FORWARD DISC PACK CRACKED ON NR 7 T/R DRIVESHAFT.						1	G	7	1 	3U			O	H2SW    					 
1997061200842	19970612	00842	GL  	1997	6	12	97ZZZX2769       	1	19970518	G	6230	28161191	UNIVERSAL HSNG  			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPALTE	CRACKED         	C		A	PP0M	K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			WP	01	8624B	641  			13100991H	752				MOUNTING WEBS FOR CONTROL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION.  THIS IS A P	RIMARY FLIGHT CONTROL PART. THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS.  PART NON-REPAIRABLE.  REPLACED WITH NEW PA	RT 28-16119-1.				1	G	7	1 	3O				H1CE    					 
1997061200844	19970612	00844	GL  	1997	6	12	97ZZZX2771       	1	19970514	G	6230	28161191	UNIVERSAL HSNG  			ENSTRM	F28   	F28F        	3300412	GL  										SWASHPLATE	CRACKED         	C		A	PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8626S	6672 			1085185H	786				MOUNTING WEBS FOR CONTROL ROD BEARINGS AND UNIVERSAL JOINT OF LOWER SWASHPLATE FOUND CRACKED AT INSPECTION.  THIS IS A P	RIMARY FLIGHT CONTROL PART. THIS PART HAS A RETIREMENT LIFE OF 17,700 HOURS.  PART NON-REPAIRABLE.  REPLACED WITH NEW PA	RT 28-16119-1.				1	G	7	1 	3O				H1CE    					 
1997061200846	19970612	00846	GL  	1997	6	12	97ZZZX2773       	1	19970519	G	6720	0169104	ROD END BEARING 			ENSTRM	F28   	F28F        	3300412	GL  										T/R CONTROL	WORN            	C		A	PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	890JR	6387 				764				ACCELERATED LATERAL BEARING WEAR.  EXCEEDED LIMITS WITHIN 304 HOURS.  THIS ROD END NORMALLY LASTS UP TO 1,000 HOURS IN S	ERVICE.  INSTALLED 2 NEW 01-691-04 BEARINGS.					1	G	7	1 	3O				H1CE    					 
1997061200876	19970612	00876	EA  	1997	6	12	97ZZZX2775       	2	19970303	G	7320	2525013	DIAPHRAGM       	BENDIX      	32447218    	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					AFCU	RUPTURED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2FOR				A20325	30932	61073			DURING DISASSEMBLY OF AFCU, FOUND DIAPHRAGM RUPTURED, P/N 2525013.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997061200877	19970612	00877	SW  	1997	6	12	97ZZZX2776       	1	19970527	G	5531	2050308465	FIN SPAR        		UH1514471   	BELL  	204   	UH1B        	1181410	SW  										TAILBOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	99478				BBBE0596	638636				DURING ROUTINE VISUAL INSPECTION WHILE REFUELING, CRACK IN TAILBOOM SPAR CAP WAS DETECTED.  MECHANIC STATED NO CRACK WAS	 NOTED DURING PRE-FLIGHT INDICATING IT FORMED WITHIN AN HOUR OF OPERATION.  NO FRETTING NOTED TO SUPPORT THIS.  GARLICK 	HELICOPTERS ALERT SB NR UH1-96-04 WAS C/W BY REMOVAL OF RIVET AT FIN STA 70.3.  THIS TAILBOOM HAD ACCUMULATED APPROXIMAT	ELY 2,500 HRS OF CIVILIAN SERVICE PERFORMING LOGGING OPERATIONS UNDER PART 133.			1	G	7	1 	4U				EXPA1G71					 
1997061900202	19970619	00202	EU  	1997	6	19	97ZZZX2780       	3	19970529	G	6114	601022294	HUB             													ROTOL	R4304	R2124304    	EU  	DRIVE SNOUT	CRACKED         	B	S		MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		24811	5993 		R212			SE4582		UPON DISASSEMBLY OF PROPELLER FOR ROUTINE OVERHAUL, NOTED FRONT FACE OF HUB ASSEMBLY WAS CRACKED ALL THE WAY AROUND HUB 	CENTER DRIVE SNOUT RADIUS.  HUB ASSY REJECTED FROM FURTHER SERVICE.  REFERENCE AD 75-15-04.															6	C	P899	 
1997061900203	19970619	00203	EA  	1997	6	19	97ZZZX2781       	2	19970522	G	7322	MA4SPA	CARBURETOR      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					THROTTLE BODY	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03			900  							THROTTLE BODY LOOSE AT PARTING SURFACE TO FUEL BOWL DUE TO LOOSENING OF LOCKING TABS ' NOT THE RETAINING BOLTS'.  SUBMIT	TER RECOMMENDS SAFETY WIRE IN PLACE OF TABS.  THIRD INCIDENT NOTED WITH LOCKING TABS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997061900204	19970619	00204	SO  	1997	6	19	97ZZZX2782       	1	19970501	G	2710	40092	BELLCRANK       			PIPER 	PA14  	PA14        	7101402	SO  										LT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND LT AILERON BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				A797    					 
1997061900205	19970619	00205	SO  	1997	6	19	97ZZZX2783       	1	19970501	G	2750	4009210	BELLCRANK       			PIPER 	PA12  	PA12        	7101202	SO  										LT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND LT FLAP BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				A780    					 
1997061900206	19970619	00206	SO  	1997	6	19	97ZZZX2784       	1	19970501	G	2450	4009210	BELLCRANK       			PIPER 	PA14  	PA14        	7101402	SO  										LT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND LT FLAP BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				A797    					 
1997061900207	19970619	00207	SO  	1997	6	19	97ZZZX2785       	1	19970501	G	2750	4009210	BELLCRANK       			PIPER 	PA18  	PA18        	7101802	SO  										RT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND RT FLAP BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				1A2     					 
1997061900208	19970619	00208	SO  	1997	6	19	97ZZZX2786       	1	19970501	G	2750	400929	BELLCRANK       			PIPER 	PA22  	PA22        	7102202	SO  										RT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND RT FLAP BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				1A6     					 
1997061900209	19970619	00209	SO  	1997	6	19	97ZZZX2787       	1	19970501	G	2750	4009210	BELLCRANK       			PIPER 	PA20  	PA20        	7102002	SO  										LT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND LT FLAP BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				1A4     					 
1997061900210	19970619	00210	SO  	1997	6	19	97ZZZX2788       	1	19970501	G	2710	40092	BELLCRANK       			PIPER 	PA12  	PA12        	7101202	SO  										LT AILERON	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INSPECTION FOUND LT AILERON BELLCRANK CRACKED.  REF:  PIPER SB 109.						1	H	7	1 	3O				A780    					 
1997061900211	19970619	00211	SO  	1997	6	19	97ZZZX2789       	2	19970516	G	8550	12504221	ADAPTER         								CONT  	O520  	IO520A      	17032	SO  					OIL FILTER	THREADS BROKEN  	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01		775  					1116706A			CESSNA OIL FILTER TOWER INSPECTED IAW AD 96-12-22.  FOUND ONE THREAD BROKEN AWAY .6250 INCH LONG.  NO DAMAGE TO INTERNAL	 THREADS OF OIL PUMP HOUSING.										3	O			E5CE				 
1997061900212	19970619	00212	SO  	1997	6	19	97ZZZX2790       	1	19970603	G	2730	1374500	CONTROL CABLE   			PIPER 	PA18  	PA18125     	7101812	SO  										ELEVATOR CONTROL	BROKEN          	G	S	A		O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AL	03	1169A					18767				LOWER ELEVATOR CABLE SEPARATED IN-FLIGHT.  CAUSE OF SEPARATION WAS USE OF NON-FLEXIBLE CABLE IN A REPAIR SPLICE.  CABLE 	WORK HARDENED AND BROKE WHERE IT WENT AROUND THE PULLEY.  THIS IS A KNOWN HIGH WEAR POINT ON PA-18-150.  AN INSPECTION H	OLE SHOULD BE INSTALLED OVER THIS POSITION FOR EASE OF INSPECTION.				1	H	7	1 	3O			 	1A2     					 
1997061900213	19970619	00213	EA  	1997	6	19	97ZZZX2791       	2	19970527	G	8530	LW15322	CYLINDER        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ROCKER ARM	LOOSE STUD      	B			R2JR	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	21	142CK	1269 				447995252	RL20677T			ENGINE LOST POWER DURING FLIGHT.  SAFE LANDING C/W.  MAINT FOUND NR 2 CYLINDER PUSH ROD BENT.  FURTHER INSPECTION REVEAL	ED ROCKER ARMS ON THAT CYLINDER VERY LOOSE, ALMOST FELL OFF WHEN ROCKER COVER REMOVED.  ROCKER SHAFT STUDS FOUND BACKED 	OUT. THERE ARE NO SAFTIES TO PREVENT THIS FROM HAPPENING.  DAMAGED CYLINDER HAD TO BE CHANGED.  SUBMITTER SUGGESTS C/W F	ACTORY RECOMMENDED 400-HOUR VALVE TRAIN INSPECTION PROCEDURES.  ALSO, SUGGESTS MANUFACTURER RE-DESIGN ROCKER ARM ATTACHM	ENT OR INSTALL SAFETY ON STUDS.		1	L	7	2 	3O	3	O		A19S0   	E286				 
1997061900214	19970619	00214	EU  	1997	6	19	97ZZZX2792       	1	19970507	G	3221		MOUNT           			SOCATA	TB9   	TB9         	8680694	EU  										NLG	CORRODED        	B	S	A	DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	144ER	4933 				1339				NOSE GEAR MOUNT CORRODED COMPLETELY THROUGH FROM INSIDE OUT.  SMALL CRACK IN PAINT FOUND DURING INSPECTION.  TUBE BROKE 	OFF DURING REMOVAL.  CRACKED AREA.					1	L	7	1 	3O			NT	AS1EU   					 
1997061900215	19970619	00215	CE  	1997	6	19	97ZZZX2793       	1	19970524	G	2822		BREAKER         			BEECH 	80    	65B80       	1152812	CE  										LT BOOST PUMP	SMOKED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	15	138BA	7467 				LD361				SMOKE COMING FROM CIRCUIT BREAKER PANEL.  LEFT BOOST PUMP DID NOT WORK.  PILOT TURNED MASTER OFF.  SUBMITTER STATED CYCL	E CIRCUIT BREAKER ONCE EACH YEAR.					1	L	7	2 	3O				3A20    					 
1997061900216	19970619	00216	SW  	1997	6	19	97ZZZX2794       	1	19970528	G	8011	MZ4222R	STARTER         	ELECTROSYS  		MOONEY	M20   	M20J        	5870219	SW  										MOTOR BODY	BOLTS LOOSE     	B			DY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	201YE				6061149	240513				THE .3125 INCH HEAD MACHINE HARDWARE HOLDING THE STARTER MOTOR FORWARD CASE TO THE BODY HAS COME LOOSE LEAVING THE MOTOR	 ARMATURE IN FAILURE.  THE LOC-TITE APPLIED TO THE THREADED HARDWARE SEEMS INAPPROPRIATE.  SUBMITTER STATED SAFETY WIRE 	THE STARTER BODY HARDWARE.  FACTORY TO PROVIDE THE IMPROVED DRILLED  MACHINE HARDWARE.				1	L	7	1 	3O				2A3     					 
1997061900217	19970619	00217	CE  	1997	6	19	97ZZZX2795       	1	19970515	G	5347	05112435	SEAT RAIL       			CESSNA	172   	172M        	2072418	CE  										COCKPIT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	20582	529  				17261414				REPLACED ALL SEAT RAILS AND ROLLERS ON SEATS.  529.4 HOURS LATER OF OPERATION, THE FOURTH HOLE AFT WAS FOUND OUT OF LIMI	TS PER AD 87-20-03R2.  AD 87-20-03R2 STATES FIRST INSPECTION DUE 1,000 HOURS AFTER NEW RAILS INSTALLED.  RECOMMEND REDUC	ING FIRST INSPECTION TO 500 HOURS FOR FAR 135 OPERATORS DOING SHORT HAUL.				1	H	7	1 	3O			NT	3A12    					 
1997062400001	19970624	00001	EA  	1997	6	24	97ZZZX2797       	2	19970528	G	8520		CRANKCASE       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ALT MT LUG	BROKEN          	D		A		O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CE	07	2885D	1969 				287990520	L2678036A			RIGHT CRANKCASE LOWER FRONT ALTLERNATOR SUPPORT MOUNT LUG BROKE OUT OF CRANKCASE AND LEFT A HOLE 1.50 INCHES IN DIAMETER	.  CAUSE UNKNOWN.  CREATED OIL LEAK WITH OIL ON WINDSHIELD DURING FLIGHT.  REMOVED ENGINE AND INSTALLED LYCOMING REBUILT	.				1	L	7	1 	3O	3	O		2A13    	E286				 
1997061900219	19970619	00219	EA  	1997	6	19	97ZZZX2798       	2	19970530	G	7414	1051659	BUSHING         		S4LN1227    	CESSNA	177   	177A        	2073706	CE  	LYC   	O360  	O360A2F     	41514	EA  					ENG LT MAG	WRONG PART      	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	30567				85020127	17701332				ROUGH ENGINE, LEFT MAG DEAD ON RUN-UP.  REMOVED LEFT MAG AND FOUND SHOULDERED MAGNETO DRIVESHAFT BUSHING WITH SHOULDER M	ISSING.  UPON EXAMINATION OF BUSHING, DETERMINED IT WAS THE OLD STYLE, SINTERED IRON PN 10-51659.  IT SHOULD HAVE HAD A 	MACHINED STEEL BUSHING PN 10-163049 INSTALLED.  REF:  TCM SB 556C OR AD 74-26-09.				1	H	7	1 	3O	3	O		A13CE   	E286				 
1997061900220	19970619	00220	CE  	1997	6	19	97ZZZX2799       	1	19970603	G	7931		LINE            			CESSNA	150   	150J        	2071820	CE  										OIL PRESS IND	CHAFED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	3829J					15065129				OIL PRESSURE INDICATOR LINE (COPPER) BETWEEN FIREWALL AND INDICATOR WORE THROUGH AND LEAKED DUE TO IMPROPER SECURING OF 	LINE BY PLASTIC TY-RAP BANDS.  PLASIC TY-RAP IS HARDER THAN COPPER .1250 INCH LINE.  LINES SHOULD BE SECURED BY PROPER S	IZE ADEL CLAMPS.				1	H	7	1 	3O				3A19    					 
1997061900221	19970619	00221	GL  	1997	6	19	97ZZZX2800       	1	19970402	G	5340		ATTACH ANGLE    			NAMER 	T6    	AT6C        	6400412	GL  										TAILCONE ATTACH	EXCESS WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	417AS	7000 				847648				LOWER RT TAILCONE TO STEEL TUBE FUSELAGE ATTACH BOLTS WORN SEVERELY IN ALUM ATTACH ANGLES.  INSTALLED AN5 BOLTS GROOVED.	  WASHER NEXT TO NUT CHAFED AROUND COUNTERBORE APPROXIMATELY .060 INCH INTO A .090 INCH THICK ALUM ANGLE.  .3125 INCH BO	LT HOLES ELONGATED APPROX .250 INCH BY .4375 INCH.  REPLACED ALUM ANGLES.  SUSPECT CAUSE, TOO LONG OF LENGTH HARDWARE IN	STALLED.  NUT BOTTOMED ON THREADS.			1	L	7	1 	3R				A2575   					 
1997061900222	19970619	00222	SO  	1997	6	19	97ZZZX2801       	1	19970527	G	5551		FITTING         			PIPER 	PA28  	PA28236     	7102815	SO  										STAB ATTACH	CORRODED        	B	S		R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	43595	2436 				288411018				WHILE COMPLETING ANNUAL/100 HR INSPECTION, STABILATOR ATTACH BRACKETS WERE INSPECTED PER PIPER SB 856.  CORROSION FOUND 	UNDER TWO ATTACHMENTS.  BRACKETS ARE STEEL AND ATTACHED TO ALUMINUM SKIN.  REMOVED, CLEANED, AND PAINTED.  EPOXY PRIMER 	INSTALLED ON SKIN.  SB 856 CALLS FOR INSPECTION EACH 12 MOS.  THIS AIRCRAFT WAS INSPECTED 8 MOS EARLIER.  NO CORROSION. 	 ALSO, SUGGEST PIPER COME UP WITH A PERMANENT FIX.			1	L	7	1 	3O				2A13    					 
1997061900223	19970619	00223		1997	6	19	97ZZZX2802       	4	19970501	G	6113	D3586	BULKHEAD        			BEECH 	36    	A36         	1151604	CE  										PROP SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4612M	500  				E1244				INSPECTION FOUND AFT SIDE PROPELLER SPINNER REAR BULKHEAD CRACKED.						1	L	7	1 	3O				3A15    					 
1997061900224	19970619	00224	EA  	1997	6	19	97ZZZX2803       	2	19970508	G	8530	LW12427	CYLINDER        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					EXH PORT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4749L		298  			284077	L1118436A			DURING AN ANNUAL INSPECTION OF ENGINE, CRACKS WERE FOUND IN THE TWO REAR CYLINDERS IN EXHAUST PORTS.  ONE HAD CRACKS IN 	THE INNER (TOWARD CENTER OF HEAD) AND AFT.  OTHER IN INNER ONLY.  BOTH WERE INSTALLED DEC, '91 AND HAD ACCUMULATED APPRO	XIMATELY 300 HOURS.				1	L	7	1 	3O	3	O		2A13    	E286				 
1997061900225	19970619	00225	EA  	1997	6	19	97ZZZX2804       	2	19970507	G	7322		CARBURETOR      	PRECISION   		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					BOWL	CRACKED         	D				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CE	01	4749L				K105073	284077	L1118436A			DURING ANNUAL INSPECTION, FUEL FOUND SEEPING FROM LOWER AREA OF CARBURETOR.  FURTHER INVESTIGATION FOUND A BOLT USED TO 	MOUNT THE AIRBOX TO THE CARBURETOR WAS TOO LONG AND HAD BROKEN THE CARBURETOR BOWL.  SUBMITTER STATED MAINTENANCE PERSON	NEL SHOULD BE REMINDED TO CHECK, IN THIS CASE, BOLTS TO ASSURE THEY ARE THE CORRECT LENGTH/PART NUMBER.				1	L	7	1 	3O	3	O		2A13    	E286				 
1997061900226	19970619	00226	SO  	1997	6	19	97ZZZX2805       	2	19970519	G	8540	643259A	ADAPTER         			CESSNA	310   	310N        	2074234	CE  	CONT  	O520  	IO520E      	17032	SO  					STARTER	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	488SP		90   			310N0029	215853R			WHILE PERFORMING COMPRESSION TEST, DISCOVERED ENGINE WOULD LOCK-UP WHEN ROTATED BACKWARDS.  TROUBLESHOOTING REVEALED STA	RTER ADAPTER WAS CAUSE OF PROBLEM.  FURTHER INSPECTION OF ADAPTER SHOWED ACCUMULATION OF RUST AT STARTER MOUNTING PAD. T	HIS WAS SECOND NEWLY OVERHAULED ENGINE FOUND WITH THIS PROBLEM.  ADAPTER WAS REPLACED WITH NO FURTHER PROBLEMS.				1	L	7	2 	3O	3	O		3A10    	E5CE				 
1997061900228	19970619	00228	CE  	1997	6	19	97ZZZX2807       	1	19970530	G	3231		ROD END         		S2321L3     	CESSNA	210   	P210R       	2073455	CE  										NLG DOOR	STUD DEFECTIVE  	B	S	A	FC6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	5293A	1178 				P21000845				THREADED STUD STAKED IN ROD END PULLS THROUGH WHICH WOULD ALLOW NOSE GEAR DOOR TO JAM OR FLAP IN THE AIRFLOW.  THIS WAS 	FOUND DURING AN INSPECTION.					1	H	7	1 	3O			RT	3A21    					 
1997061900229	19970619	00229	CE  	1997	6	19	97ZZZX2808       	1	19970602	G	7160		INLET TUBE      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARB HEAT BOX	DETACHED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	5550L					15284352	L2275715			FOUND THAT WARM AIR INLET TUBE ROLLER FLANGE ON LT SIDE OF CARBURETOR AIRBOX BECOMES WORN AND DISCONNECTED.   THIS RENDE	RS CARBURETOR HEAT AIR SUPPLY INEFFECTIVE.  SUBMITTER SUGGESTS ATTACHING TUBE WITH SPOT WELDS.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997061900230	19970619	00230	CE  	1997	6	19	97ZZZX2809       	1	19970317	G	3530	1780001	BRACKET         			BEECH 	100   	B100        	1152919	CE  										OXYGEN BOTTLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	55FR	2322 				BE123				FOUND OXYGEN BOTTLE RT SUPPORT BRACKET CRACKED.  CRACK LOCATED AT THE CORNER OF THE CUT-OUT FOR THE BAND CLAMP.						1	L	7	2 	4T				A14CE   					 
1997061900231	19970619	00231	EA  	1997	6	19	97ZZZX2810       	2	19970505	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					OIL SYSTEM	MAKING METAL    	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	600EE		715  			317952158	L21468A			DURING SCHEDULED INSPECTION, ENGINE OIL FILTER WAS CUT OPEN AND INSPECTED.  FILTER WAS FOUND CONTAMINATED WITH METAL PAR	TICLES.  INSPECTION OF PROPELLER AND ALL OTHER ENGINE ACCESSORIES WAS SATISFACTORY.  ENGINE WAS REMOVED FROM SERVICE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997061900232	19970619	00232	EA  	1997	6	19	97ZZZX2811       	2	19970607	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					POWER SECTION	FAILED          	E				K				NONE                    				Y			ENGINE STOPPAGE           			IN	INSP/MAINT     	1			WP	07	600EE					317952158	L150268A			DURING COMPLIANCE OF LYCOMING SI 1427B, 'GROUND TEST PROCEDURES', ENGINE STOPPED RUNNING DURING 3 TO 5 SECONDS OF 'FULL 	STATIC POWER CHECK'.  ALL ENGINE OPERATING PARAMETERS WERE NORMAL BEFORE FAILURE.  PROPELLER COULD NOT BE MOVED BY HAND 	AFTER FAILURE.  PROPELLER AND ALL ACCESSORIES WERE REMOVED AND INSPECTED.  NO DEFECTS IN ACCESSORIES OR PROP WERE FOUND.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997061900233	19970619	00233	GL  	1997	6	19	97ZZZX2812       	3	19970417	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	NR 2 BLADE	CRACKED         	B			EK2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6155Q					15285175		RBF183		FOUND CRACK APPROXIMATELY .626 INCH LONG, .025 INCH DEEP, TRAILING EDGE SIDE OF HUB OF NR 2 BLADE.  AD 95-21-01 AND MCCA	ULEY SB 221B ADDRESSES THE HUB FRONT FACE AND BOLT HOLES.  NO RE-WORK IS ALLOWED ON SIDE OF HUB.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997061900234	19970619	00234	CE  	1997	6	19	97ZZZX2813       	1	19970606	G	5711		SPAR            			CESSNA	150   	150M        	2071830	CE  										RT WING	ERODED          	H	S	A	CZ9T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	66667	4988 				15076195				AFTER DISASSEMBLING AIRCRAFT FOR REFURBISHMENT, RT WING MAIN SPAR ATTACH FITTING WAS FOUND ERODED.  ADDITIONAL SIGNS OF 	FRETTING AND EROSION WERE DETECTED AT THE LOWER END OF THE LIFT STRUT.  ALL WEAR WAS INDICATIVE OF A LIMITED FORE AND AF	T 'SWING' OF THE ENTIRE WING STRUCTURE, AS OPPOSED TO GENERAL FRETTING IN THE CONTACT AREAS.				1	H	7	1 	3O				3A19    					 
1997061900235	19970619	00235	CE  	1997	6	19	97ZZZX2814       	1	19970605	G	2510	S22373	RETAINER BUSHING			CESSNA	150   	152         	2071835	CE  										LAP BELT	MISSING         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	68473	3851 				15282309				BOTH SHOULDER HARNESS RETAINERS PN S2237-3 MISSING.  CONDITION NOTICE ISSUED.  ALERT  NR 210 DATED JAN 96 PAGE 11 COVERS	 THIS SUBJECT.					1	H	7	1 	3O			NT	3A19    					 
1997061900236	19970619	00236	CE  	1997	6	19	97ZZZX2815       	1	19970521	G	2520	12005041	HANDLE          			CESSNA	172   	172K        	2072430	CE  										PAX SEAT LATCH	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	7203G	4999 				17258903				HANDLE BROKE AT PIVOT POINT.  ALLOWED THE ARM TO FALL FROM PIVOT POINT CAUSING THE SEAT LATCH DROP PIN TO NOT ENGAGE THE	 SEAT RAIL ALLOWING THE PASSENGER SEAT TO SLIDE BACK WHEN POWER TO THE AIRCRAFT IS APPLIED.  INDIVIDUALS SHOULD LOOK AT 	THIS AREA ON 100 HOUR AND ANNUAL INSPECTIONS.				1	H	7	1 	3O			NT	3A12    					 
1997061900237	19970619	00237	SO  	1997	6	19	97ZZZX2816       	2	19970517	G	8530	646612	EXHAUST VALVE   		653426A13   	CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512       	17008	SO  					ENGINE	LEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	72742	40   				9921	22960612			FORTY HOURS AFTER CYLINDER ASSY REPLACED, ALLL EXHAUST VALVES WERE LEAKING ON COMPRESSION CHECK ON ALL 4 CYLINDERS.						1	H	7	1 	3O	3	O	NC	A768    	E233				 
1997061900238	19970619	00238	CE  	1997	6	19	97ZZZX2817       	1	19970605	G	3710	131823H12A0030	LINE            			BEECH 	33    	F33A        	1151425	CE  										AUXILIARY VAC	DETERIORATED    	B		A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	8004V	1055 				CE1649				THE AUXILIARY INSTRUMENT VACUUM SYSTEM LINE PASSES CLOSE TO THE LT EXHAUST STACK.  COMING OUT OF THE AFT SIDE OF THE IN-	LINE FILTER IS A PLASTIC HOSE THAT CONNECTS THE FILTER TO THE HARD LINE.  THIS HARD PLASTIC HOSE CANNOT TAKE THE HEAT FR	OM THE EXHAUST AND HAS A TENDENCY TO GET BRITTLE AND SPLIT OR BREAK.  SOLUTION TO THIS PROBLEM WAS TO INSTALL  A HIGH QU	ALITY, HIGH TEMPERATURE SILICONE HOSE IN PLACE OF THE CHEAPER FACTORY HOSE.			1	L	7	1 	3O				3A15    					 
1997061900239	19970619	00239	CE  	1997	6	19	97ZZZX2818       	1	19970526	G	3230	2VA20	SWITCH          			CESSNA	402   	402B        	207590P	CE  										GEAR SAFETY	MALFUNCTION     	E		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	814CF	2644 				402B0335				LANDING GEAR SWITCH FOUND TO BE INTERMITTENT.  FLIGHT CREW TOOK AIRCRAFT FOR A FLIGHT JUST AFTER WASHING.  GEARS WOULD N	OT RETRACT.  ON INSPECTION, FOUND MOISTURE IN SIDE OF MLG SAFETY SWITCH.					1	L	7	2 	3O				A7CE    					 
1997061900240	19970619	00240	SO  	1997	6	19	97ZZZX2819       	1	19970605	G	2510		RETAINER BUSHING			PIPER 	PA34  	PA34220T    	7103420	SO  										LAP BELT	MISSING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	8393Y	1984 				348133108				PILOT'S NYLON SHOULDER HARNESS RETAINER MISSING.  THIS SUBJECT WAS COVERED IN ALERT NR 210, JAN '96.  SUBMITTER STATED H	AVE FOUND SEVERAL AIRCRAFT WITHOUT TY-RAPS, BUT WITH THE NYLON SHOULDER HARNESS RETAINER MISSING.  MAINTENANCE PERSONNEL	 NEED TO INSPECT THIS AREA CLOSER.  SEVERAL OTHER AIRCRAFT FOUND MISSING NYLON:  CESSNA AND PIPER.  NOTE:  UNABLE TO FIN	D PIPER PART NUMBER.			1	L	7	2 	3O				A7SO    					 
1997061900241	19970619	00241	SO  	1997	6	19	97ZZZX2820       	2	19970524	G	8530	639614	ROCKER ARM      			UNIVAR	415   	415G        	0420310	NM  	CONT  	O200  	O200A       	17020	SO  					NR 2 CYL EXHAUST	FAILED          	G	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	94415	3600 	1225 			5050	2045979A			NR 2 CYLINDER HAD INTAKE AND EXHAUST ROCKER ARM ASSEMBLIES SWITCHED.  NR 2 EXHAUST VALVE MIGHT HAVE STUCK DUE TO NO LUBR	ICATION OR COOLING FROM THE DRILLED PASSAGEWAY BECAUSE THE EXHAUST ROCKER ARM WAS IN THE INTAKE VALVE POSITION.  INTAKE 	ROCKER FAILED.				1	L	7	1 	3O	3	O		A787    	E252				 
1997061900242	19970619	00242	GL  	1997	6	19	97ZZZX2821       	1	19970501	G	3230		LANDING GEAR    			AMTR  	GAIR  	GLASAIRIII  	05691HK	GL  										MLG-NLG	MALFUNCTION     	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	99	957DJ					3084				PILOT REPORTED LANDING GEAR WOULD NOT RETRACT AFTER HE DEPARTED AIRPORT EN ROUTE TO TORRANCE AIRPORT, CA.  HE STATED HE 	HAD THREE GREEN LIGHTS DURING THE FLIGHT TO COMPTON.  PILOT DECIDED TO LAND AT COMPTON AIRPORT TO CHECK OUT GEAR PROBLEM	.  WHILE LANDING AT COMPTON, THE LEFT GEAR COLLAPSED, THEN THE RIGHT, THEN THE NOSE GEAR, IN THAT ORDER.  CAUSE NOT KNOW	N.  LANDING GEAR CHECK FOUND NO DISCREPANCIES.			1	L	7	1 	3O			RT	EXPA1L71					 
1997061900243	19970619	00243	SO  	1997	6	19	97ZZZX2822       	1	19970605	G	5330	99470	SKIN            			PIPER 	PA34  	PA34200T    	7103406	SO  										FUSELAGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	9798C					347870222				FUSELAGE SKIN CRACKED AT REAR BULKHEAD HORIZONTAL STABILIZER ATTACH BRACKETS.  CRACK IS LOCATED IN FORMED FUSELAGE SKIN.						1	L	7	2 	3O				A7SO    					 
1997061900244	19970619	00244	SO  	1997	6	19	97ZZZX2823       	1	19970605	G	5330	99471	SKIN            			PIPER 	PA34  	PA34200T    	7103406	SO  										FUSELAGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	9798C					347870222				FUSELAGE SKIN CRACKED AT REAR BULKHEAD HORIZONTAL STABILIZER ATTACH BRACKETS.  CRACK IS LOCATED IN FORMED FUSELAGE SKIN.						1	L	7	2 	3O				A7SO    					 
1997061900381	19970619	00381	GL  	1997	6	19	97ZZZX2824       	2	19970429	G	7323	23057870	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B		A	AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5059C	1031 			BR32500	S779				GOVERNOR FAILED TO MAINTAIN N2 ROTOR SPEED.  HAVING ALOT OF PROBLEMS WITH THESE GOVERNORS FAILING AT ABOUT THIS TIME. TH	E COUPLINGS ON THESE GOVERNORS DO NOT HOLD UP.  REPLACED GOVERNOR WITH SERVICEABLE ITEM.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997061900382	19970619	00382	NE  	1997	6	19	97ZZZX2825       	1	19970501	G	6210	7615009100041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R BLUE	SKIN MISSING    	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7266F	9754 			A08600648	760273				BLUE M/R BLADE MISSING A SECTION OF OUTER SKIN ON BOTTOM OF BLADE.  MISSING SECTION STARTS JUST AFT OF LEADING EDGE STRI	P EXTENDING TO TRAILING EDGE BETWEEN APPROXIMATELY BLADE STA 204 THROUGH STA 216 (APPROX 12 INCHES LONG).  REMOVED AND R	EPLACED BLUE M/R BLADE, BALANCED AND TRACKED M/R SYSTEM.				1	G	7	2 	3U				H1NE    					 
1997061900384	19970619	00384	EU  	1997	6	19	97ZZZX2827       	1	19970515	G	6520	350A33215300	LAMINATE HINGE  			SNIAS 	350   	AS350B      	8680801	EU  										T/R	CRACKED         	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	911NT	62   				1556				RUBBER LAMINATE IS CRACKED 180 DEGREES AROUND PART.						1	G	7	1 	3U				H9EU    					 
1997061900454	19970619	00454	CE  	1997	6	19	97ZZZX2828       	1	19970514	G	5542	553300054	SKIN            			CESSNA	500   	560CESSNA   	2076750	CE  										RUD RT LOWER	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	315QS	1343 				5600315				FOUND CRACK ON RIGHT SIDE LOWER RUDDER SKIN.  THIS IS THE 2ND TIME A CRACK HAS BEEN FOUND IN THIS AREA ON THIS PARTICULA	R RUDDER.  THE FIRST WAS AT 718.2 HOURS TOTAL TIME.  THE SKIN WAS REPLACED AT THAT TIME AND WAS CHANGED AGAIN THIS TIME.	  SUBMITTER STATED IT SEEMS THERE MAY BE AN ENGINEERING AND/OR A PRODUCTION DEFECT.  NINTH OCCURRENCE IN FLEET.				2	L	7	2 	4F			RT	A22CE   					 
1997061900455	19970619	00455	CE  	1997	6	19	97ZZZX2829       	1	19970516	G	3510	1780001	BRACKET         			BEECH 	100   	B100        	1152919	CE  										OXYGEN BOTTLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	55FR	3000 				BE123				FOUND OXYGEN BOTTLE LEFT SUPPORT BRACKET CRACKED.  CRACK LOCATED AT THE CORNER OF THE CUT OUT FOR THE BAND CLAMP.  BRACK	ET MANUFACTURED BY PURITAN BENNETT.					1	L	7	2 	4T				A14CE   					 
1997061900456	19970619	00456	CE  	1997	6	19	97ZZZX2830       	1	19970530	G	5320	251127162	FRAME           			LEAR  	35    	35A         	5170602	CE  										ENTRY DOOR FWD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	58MM					261				THE LOWER ENTRY DOOR FORWARD STEP FRAME WAS CRACKED IN THE RADIUS OF THE EXTERNAL SKIN FLANGE AT THE HINGE.  CAUSE OF CR	ACK WAS DUE TO IMPROPER RIGGING OF THE ASSEMBLY.					2	L	7	2 	4F				A10CE   					 
1997061900457	19970619	00457	EU  	1997	6	19	97ZZZX2831       	1	19970528	G	3310	RH00252350JBS	DIMMER SWITCH   			AMD   	FALC50	FALCON900   	2700160	EU  										CREW LIGHT	SHORTED         	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	730SA	322  			9550	155				THE THIRD CREW MEMBER'S READING LIGHT RHEOSTAT ELECTRICALLY SHORTED TO THE ADJACENT OXYGEN MASK CONTAINER.  THE READING 	LIGHT CIRCUIT BREAKER TRIPPED.  THIS COULD HAVE BEEN A POTENTIAL SERIOUS INCIDENT.  THE OPERATOR SUGGESTED TO DASSAULT N	OT TO USE RHEOSTATS WITH OPEN CONTACTS.  AIRCRAFT TOTAL TIME:  322.4 HOURS.  LANDINGS, 215.				2	L	7	3 	4F			RT	A46EU   					 
1997061900458	19970619	00458	EA  	1997	6	19	97ZZZX2832       	1	19970527	G	5320	60035031201	SUPPORT ANGLE   			CNDAIR	CL600 	CL6002A12   	1900304	EA  										FLOOR SUPPORT	CRACKED         	B	S		R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	999JR	4627 				3061				WHILE PERFORMING 4,800 HOUR/120 MONTH INSPECTION, FOUND FLOOR SUPPORT ANGLE CRACKED AT FS 621 (AFT PRESSURE BULKHEAD). A	REA INSPECTED WAS UNDER THE FLOOR IN AFT BAGGAGE COMPARTMENT.  SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA.  SRM AT	A 53-15-08 HAS A RIVETED ANGLE DOUBLER REPAIR FOR THIS CRACKING.  THIS AREA PRONE TO CRACKING IS MAJOR STRUCTURE FOR PRE	SSURE BULKHEAD AND BAGGAGE FLOOR.			2	L	7	2 	4F			RT	A21EA   					 
1997061900462	19970619	00462	SO  	1997	6	19	97ZZZX2834       	1	19970522	G	3320	BR9800005	LAMP            			GULSTM	G1159 	GIV         	3980115	SO  										RT CABIN AFT	BURNED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	401JL	527  				1283				RIGHT SIDE AFT CABIN LOWER FLUORESCENT LAMP WAS FOUND INOPERABLE.  THE ACCESS COVER WAS REMOVED TO CHECK THE LAMP AND FO	UND TO BE BURNED COMPLETELY IN HALF .50 INCH FROM END OF TUBE.  EVIDENCE OF A SMALL FIRE IN THAT AREA WAS FOUND.  SMOKE 	AND FIRE STAINS ON WALL BEHIND BULB WERE 4 INCHES HIGH TOWARD THE CEILING.  PARTS WERE SENT TO GULFSTREAM IMMEDIATELY FO	R EVALUATION.  BRUCE INDUSTRIES INC, PN BR 98000-005; SYLVANIA, P/N 5108WW.			2	L	7	2 	4F			RT	A12EA   					 
1997061900463	19970619	00463	WP  	1997	6	19	97ZZZX2835       	1	19970502	G	6310	369A532	BEARING         			HUGHES	369   	369HS       	4470728	WP  										OVERRUN CLUTCH	CRACKED         	B			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										OVERRUNNING CLUTCH BEARING OUTER RACE IS CRACKED.						1	G	7	1 	3U				H3WE    					 
1997061900464	19970619	00464	GL  	1997	6	19	97ZZZX2836       	1	19970501	G	5610	28011302212	WINDSHIELD      			ENSTRM	F28   	280C        	3300505	GL  										COCKPIT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	122TV					1049				DURING ENGINE START ON A COLD MORNING, RT WINDSHIELD CRACKED APPROXIMATELY 14 INCHES FROM CENTER WINDSHIELD ANCHORING ST	RIP TOWARD OUTBOARD OF AIRCRAFT.  POSSIBLY HAD A PREVIOUS CRACK AT RIVET LOCATION THAT WAS HIDDEN UNDER CENTER STRIP.					1	G	7	1 	3O				H1CE    					 
1997061900465	19970619	00465	GL  	1997	6	19	97ZZZX2837       	2	19970508	G	7320	6893073	AIR LINE        			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GOV PC TO FCU	BROKEN          	B		A	ZV1R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	03	202SR					760236	CAE890251S			IN CRUISE FLIGHT, NR 2 ENGINE SPOOLED DOWN TO 30 PERCENT AND THEN DOWN TO 10 PERCENT.  ENGINE WAS SECURED AND AIRCRAFT W	AS FLOWN TO AIRPORT FOR LANDING.  FOUND PC AIR LINE, PN 6893073, BROKEN AT FERRULE ON FUEL CONTROL.  THIS LINE COMES FRO	M GOVERNOR TO FUEL CONTROL.  REPLACED LINE.  OPS CHECK AND FLIGHT OK.  RAN VIB CHECK ON ENGINE.  FOUND 1.25 IPS.  REPLAC	ED ENGINE ASSY DUE TO HIGH VIB LEVEL.  RECOMMEND VIB CHECK AT LEAST EVERY 300 HOURS.			1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997061900466	19970619	00466	EA  	1997	6	19	97ZZZX2838       	2	19970407	G	8530	AEL12949	INTAKE VALVE    			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					STEM AND FACE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	36MV	160  			75137CN	5060	L256043			THE VALVE STEM UNDER THE KEEPER'S WAS HEAVILY WORN.  THIS CONDITION WAS ALSO FOUND ON 4 OTHER VALVES (INTAKE) ALL HAVING	 THE SAME TOTAL TIME AND PART NUMBER.  THE 6TH VALVE WAS A LYCOMING WITH THE SAME TIME AND INSTALLATION DATE.  NO PROBLE	M FOUND.				1	G	7	1 	3O	3	O		4H11    	E304				 
1997061900467	19970619	00467	SW  	1997	6	19	97ZZZX2839       	1	19970512	G	6330	222031605109	FLEXTURE        			BELL  	222   	222B        	1182124	SW  										M/R XMSN MT	DELAMINATED     	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	510W	838  			LK00131	47133				INSPECTION FOUND FLEXTURES DELAMINATED.  REPLACED WITH NEW FLEXTURES.						1	G	7	2 	3U				H9SW    					 
1997061900468	19970619	00468	SW  	1997	6	19	97ZZZX2840       	1	19970512	G	6330	222031605109	FLEXTURE        			BELL  	222   	222B        	1182124	SW  										M/R XMSN MT	DELAMINATED     	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	510W	1016 			LK0124	47133				INSPECTION FOUND FLEXTURES DELAMINATED.  REPLACED WITH NEW FLEXTURES.						1	G	7	2 	3U				H9SW    					 
1997061900469	19970619	00469		1997	6	19	97ZZZX2841       	4	19970512	G	2210	412074030101	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										AUTOFLIGHT	BURNT           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	82628	510  				36106				INSPECTION FOUND AMPLIFIER BURNT.  REPLACED WITH NEW AMPLIFIER.						1	G	7	2 	4U				H4SW    					 
1997061900470	19970619	00470	WP  	1997	6	19	97ZZZX2842       	1	19970528	G	6710	B2923	ROD END         			ROBSIN	R22   	R22HP       		WP  										COLLECTIVE	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	9077Q		1200 		A0387	0273				DURING PRE-FLIGHT FOR A TRAINING FLIGHT WHILE LIFTING COLLECTIVE STICK, A LOUD BANG WAS HEARD.  CYCLING COLLECTIVE STICK	 UP AND DOWN, TWO MORE SOFTER BANGS AND RATCHETING FEELING IN STICK.  MAINTENANCE WAS CALLED AND COLLECTIVE STICK WAS SM	OOTH AND NO NOISE WAS HEARD.  FURTHER INVESTIGATION REVEALED SPRING ASSY A429-8 WAS LAYING FREE UNDER COPILOT'S COLLECTI	VE STICK, UPPER ROD END, LT THREAD, BENT AND BROKE OFF AT BASE OF PLATE CAUSING UNIT TO COCK TO ONE SIDE RESULTING IN TH	E BREAKAGE OF THREE A28-1 RODS AND COMPLETE SEPARATION OF SPRING ASSY.  FLIGHT IN THIS CONDITION WOULD BE VERY DIFFICULT	 BECAUSE OF NO SPRING HELP, HEAVY COLLECTIVE CONTROLS.  SUBMITTER STATED INSPECTION AT 100 HRS FOR BENT ROD ENDS.	1	G	7	1 	3O			O	H10WE   					 
1997061900471	19970619	00471	NM  	1997	6	19	97ZZZX2843       	1	19970523	G	2761	656952210	HOUSING         		65449616    	BOEING	737   	7372M8      	1384483	NM  										SPOILER	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					149AW80BD					SPOILER ACTUATOR HAS A HOLE IN HOUSING.  FOUND DURING PROOF PRESSURE TESTING FOR REPAIR.						2	L	7	2 	4F				A16WE   					 
1997061900472	19970619	00472		1997	6	19	97ZZZX2844       	4	19970203	G	6113	AN526C1032R8	SCREW           			BEECH 	36    	36BEECH     	1151602	CE  										SPINNER	CRACKED         	B	S	A	OYSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09										RECEIVED SHIPMENT OF 400 EACH AN526C-1032R8 SPINNER SCREWS.  UPON RECEIVING, INSPECTED, NOTED ALL SCREWS HAD CRACKS OR F	ISSURES ALL THE WAY THROUGH SCREW HEAD RADIATING FROM PHILLIPS RECESS.  THIS COULD RESULT IN PROPELLER SPINNER DEPARTING	 AIRCRAFT IN-FLIGHT.  SUBMITTER RECOMMENDS TRACING TO MANUFACTURER (NOT LISTED ON PARTS BAG) AND RECALL ALL SCREWS ON TH	IS LOT NUMBER.			1	L	7	1 	3O				3A15    					 
1997061900473	19970619	00473	NE  	1997	6	19	97ZZZX2845       	2	19970602	G	8500		ENGINE          			BEECH 	18    	H18         	1151012	CE  	PWA   	R985  	R985AN14B   	52008	NE  					LT ENGINE	MAKING METAL    	G				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			SW	11	117ME		1266 			BA638	P225009			WHILE IN CRUISE FLIGHT, PILOT NOTICED OIL LEAK ON LEFT ENGINE.  ENGINE WAS SECURED, PROPELLER FEATHERED, AND AN UNEVENTF	UL LANDING MADE.  MAINTENANCE FOUND PROPELLER TO BE LEAKING, BUT THE ENGINE OIL SCREEN WAS FULL OF METAL.  SUSPECT INTER	NAL FAILURE.  ENGINE TO BE REMOVED AND REPLACED.				1	L	7	2 	3R	3	R		A765    	5E1				 
1997061900474	19970619	00474	SO  	1997	6	19	97ZZZX2846       	1	19970527	G	2910		TUBE            			PIPER 	PA28  	PA28RT201T  	7102817	SO  										NLG ACTUATOR	LEAK            	B			SL5R	O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			NE	03	3071N					28R7931060				LANDING GEAR WOULD NOT EXTEND.  EMERGENCY EXTENSION PERFORMED AND AIRCRAFT LANDED SAFELY.  FOUND HYDRAULIC POWER PACK RE	SERVOIR VERY LOW ON FLUID.  SERVICED RESERVOIR AND GEAR RETRACTION AND EXTENSION OPS CHECKED GOOD WHILE AIRCRAFT WAS ON 	JACKS.  FOUND INSULATION WAS SOAKED WITH HYDRAULIC LEAK FROM PIN HOLE IN NOSE LANDING GEAR ACTUATOR LOWER HYD TUBE.  FAB	RICATED NEW TUBE, NO FURTHER LEAKS NOTED.			1	L	7	1 	3O				2A13    					 
1997061900475	19970619	00475	GL  	1997	6	19	97ZZZX2847       	1	19970501	G	5311		FRAME           			DHAV  	DHC1  	DHC1B2S3    	2801738	GL  										BS 190	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	33BR					166				THE FUSELAGE FRAMES AT STA 190 ARE CRACKED.  THE CRACKS FOUND DURING INSPECTIONS ARE LOCATED AT THE POINT WHERE THE LOWE	R SPAR CAP IS SANDWICHED.  THE CRACKS RUN VERTICALLY FROM TOP TO BOTTOM AND THE DEPTH IS COMPLETELY THROUGH FRAME MATERI	AL.  THE CRACKS ARE LOCATED 6 INCHES INBD FROM FUSELAGE SIDES WHERE THE STEEL DOUBLERS END ON LOWER SPAR CAP.  BOTH FRAM	ES FRONT AND REAR SHOULD BE INSPECTED.  IF ANY CRACKS ARE FOUND, ADVISE SUSPENDING ANY AEROBATIC FLYING AND HAVING REPAI	RS ACCOMPLISHED AS SOON AS POSSIBLE.		1	L	7	1 	3O				EXPA1L71					 
1997061900476	19970619	00476	CE  	1997	6	19	97ZZZX2848       	1	19970121	G	3213	MS9048180	PIN             		16981001215 	BEECH 	23    	C24R        	1151254	CE  										NLG COMPRESSOR	SHEARED         	D	L	A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	11	3343L					MC466				ACFT WAS NOT ABLE TO LOWER NOSE GEAR IN-FLIGHT.  MADE A NOSE GEAR UP LANDING WITH DAMAGE TO THE PROPELLER AND ENGINE COW	LING.  NOSE GEAR FOUND STUCK IN THE UP POSITION WITH DOWN MOVEMENT BEING PREVENTED BY THE TIRE HITTING THE ACFT SKIN IN 	NOSE WHEELWELL.  FURTHER INSPECTION REVEALED ROLL PIN P/N MS9048-180 HAD SHEARED IN THE COMPRESSOR ASSY, P/N 169-810012-	15.  THIS ROLL PIN HOLDS THE ROD, P/N 169-810000-111, IN THE COMPRESSOR ASSY.			1	L	7	1 	3O				A1CE    					 
1997061900477	19970619	00477	CE  	1997	6	19	97ZZZX2849       	1	19970501	G	3230	504501019	TORQUE TUBE     			CESSNA	402   	402B        	207590P	CE  										LT MLG	CRACKED         	D	P	A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	99	403PA	8    				402B0917				PILOT REPORTED 'AFTER DEPARTURE, ADVISED BY ANOTHER AIRCRAFT THAT THE LEFT GEAR WAS DOWN AND LOCKED'.  AFTER VERIFYING T	HIS IN MIRROR, HE CONTINUED TO DESTINATION AND EXTENDED GEARS AND A SAFE LANDING WAS MADE.  THE PART WAS SUPERCEDED TO A	 DIFFERENT NUMBER WHEN ORDERED.				1	L	7	2 	3O				A7CE    					 
1997061900478	19970619	00478	CE  	1997	6	19	97ZZZX2850       	1	19970528	G	8120	4066109005	TURBOCHARGER    	GARRTT      		CESSNA	210   	T210G       	2073432	CE  	CONT  	O520  	TSIO520C    	17040	SO  					EXH HOUSING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	6843R				FDR0152	T2100243	1408179C			TURBOCHARGER EXHAUST HOUSING CRACKED AROUND AUXILIARY MOUNTING LUG.						1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997061900479	19970619	00479	CE  	1997	6	19	97ZZZX2851       	1	19970526	G	3230	12806005	ACTUATOR        		12805147    	CESSNA	210   	T210L       	2073449	CE  										NLG DOWNLOCK	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	732AJ					T21061360				DURING ANNUAL INSPECTION, FOUND A CRACK IN THE BEARING END OF THE NOSE GEAR ACTUATOR.  THE CRACK ORIGINATES AT THE DOWNL	OCK PIN LOCATION AND EXTENDS FORWARD LONGITUDINALLY AROUND THE CASTING.  (NO PLAY WAS NOTED IN PIN WHEN C/W SEB 95-20). 	 POTENTIAL OF NOSE GEAR DOWNLOCK FAILURE IN NEAR FUTURE.				1	H	7	1 	3O				3A21    					 
1997061900480	19970619	00480	SO  	1997	6	19	97ZZZX2852       	1	19970605	G	3222	6705408	TRUNNION ASSY   			PIPER 	PA32  	PA32R301    	7103218	SO  										NLG SPRING ARM	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9274Q	156  				3246038				NLG TRUNNION ASSY CRACKED AT THE AREA THAT THE SPRING ATTACHES.  P/N 6716800.						1	L	7	1 	3O				A3SO    					 
1997061900481	19970619	00481	SO  	1997	6	19	97ZZZX2853       	1	19970530	G	5553		STABILIZER      			PIPER 	PA34  	PA34200T    	7103406	SO  										V STAB ATTACH	RIVETS POPPED   	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4377X					347670035				INSPECTION OF RUDDER AND VERTICAL STABILZIER AREA REVEALED RIVETS WITH POPPED HEADS ON ATTACHMENT FITTING FOR AFT SPAR O	N VERTICAL STABILIZER-TO-EMPENNAGE ATTACH POINT.  (SIX OUT OF EIGHT RIVETS WERE SHEARED).  THOROUGH INSPECTION OF EMPENN	AGE REVEALED NO OTHER PROBLEMS.				1	L	7	2 	3O				A7SO    					 
1997061900482	19970619	00482	EA  	1997	6	19	97ZZZX2854       	2	19970412	G	8530	75068	VALVE           			GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					NR 1 CYL EXHAUST	FAILED          	G	S			O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			NM	03	38X	2011 				AA5B0889	L2699236A			VALVE MALFUNCTION OCCURRED DURING TAKEOFF AT APPROXIMATELY 2,450 RPM.  (AIRPORT AT 5,100 FEET). OAT 20 DEGREES FAHRENHEI	T.					1	L	7	1 	3O	3	O		A16EA   	E286				 
1997061900661	19970619	00661	NE  	1997	6	19	97ZZZX2855       	1	19970508	G	5210	7620902019043	HINGE           			SKRSKY	S76   	S76         	8143010	NE  										DOOR	BROKE           	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5414X					760152				DOOR HINGE BROKE WHILE MECHANIC WAS STANDING ON DOOR.  REPLACED HINGE.						1	G	7	2 	3U				H1NE    					 
1997061900662	19970619	00662	NE  	1997	6	19	97ZZZX2856       	1	19970501	G	3212	7625101110106	EXPLOSIVE LINK  			SKRSKY	S76   	S76         	8143010	NE  										FLOATS	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5447C	12925			0517	760180				EXPLOSIVE LINK DID NOT ACTIVATE WHEN FLOATS WERE DEPLOYED.  HARNESS TEST OK.  REPLACED LINK.						1	G	7	2 	3U				H1NE    					 
1997061900664	19970619	00664	SW  	1997	6	19	97ZZZX2857       	1	19970310	G	3212	8226003	FUSIBLE PLUG    		206073847103	BELL  	407   	407         		SW  										RT FLOAT BOTTLE	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	15   				53107				WHILE AIRCRAFT WAS SITTING ON MAINTENANCE RAMP, NITROGEN CAME OUT OF FUSIBLE PLUG.  THE INTERNAL PLUNGER CAME LOOSE OR S	HEARED.					1	G	7	1 	3U			O	H2SW    					 
1997061900665	19970619	00665	NE  	1997	6	19	97ZZZX2858       	1	19970430	G	6210	7615009100051	BLADE RIB       			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	164AG	6245 	446  		A08601424	760290				DISCOVERED DURING 500-HOUR INSPECTION, MAIN ROTOR BLADE TIP RIB DEBONDED.						1	G	7	2 	3U				H1NE    					 
1997061900668	19970619	00668	NE  	1997	6	19	97ZZZX2859       	1	19970501	G	3212	PM225681	SWITCH          			SKRSKY	S76   	S76         	8143010	NE  										FLOAT	SHORTED         	B			AC2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5447C	12925				760180				FLOAT INFLATED PREMATURELY.  FOUND SWITCH ROTATING IN CYCLIC, LOOSE INSTALLATION, WIRE FRAYED.  NO SHIELDING OVER SOLDER	 JOINT, CAUSING SHORT.  UNSOLDERED CONNECTION, INSTALLED SHIELDING OVER WIRES, RESOLDERED, AND INSTALLED SWITCH SECURELY	 TO PREVENT TURNING.				1	G	7	2 	3U				H1NE    					 
1997062600098	19970626	00098	NE  	1997	6	26	97ZZZX2861       	3	19970603	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		8863 	4615 		2761NR			HJ473		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	 
1997062600099	19970626	00099	NE  	1997	6	26	97ZZZX2862       	3	19970606	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		4621 	4621 		2488NR			HJ380		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	 
1997062600100	19970626	00100	CE  	1997	6	26	97ZZZX2863       	1	19970528	G	2121	99123232	BLOWER          			CESSNA	500   	550         	2076604	CE  										AFT CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	11	10EG		344  		1250	5500055				INSTALLED A CESSNA CITATION FACTORY SUPPLIED 'NEWLY OVERHAULED' EXCHANGE OVERHEAD BLOWER ASSEMBLY PN 9912323-2, MANUFACT	URER'S PN BC61A901-2EX ON 5-7-96.  NORMAL USE IS FOR THIS BLOWER TO BE TURNED 'ON' TO SUPPLY AIR TO THE OVERHEAD WEMAC V	ENT SYSTEM.  APPARENTLY, THE CENTRIFUGAL FAN END BEARINGS HAVE FAILED IN SERVICE AFTER ONLY 343.8 HOURS OF INSTALLED TIM	E. THIS IS A TBO PART AS LISTED IN THE CITATION MM CHAPTER 5-11-00 WITH A TIME BETWEEN OVERHAUL OR REPLACEMENT OF 1,200 	HOURS.  THE 'SQUIRREL CAGE' CENTRIFUGAL BLOWER WAS NOT DAMAGED OR SEVERELY DIRTY.  THE MOTOR COOLING VENT TUBE AND ADAPT	ER WERE ATTACHED AND UN-RESTRICTED.  CAUSE OF BEARING FAILURE IS NOT OBVIOUS OR KNOWN AT THIS TIME.	1	L	7	2 	4F				A22CE   					 
1997062600102	19970626	00102	SW  	1997	6	26	97ZZZX2864       	1	19970610	G	6123	57B4026	PITCH CHANGE ROD		573083150   	AIRTRC	AT802 	AT802       	0390305	SW  										PROPELLER	FAILED          	B			EK2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	1546H	2257 				802A0003				AIRCRAFT PARKED IN FIELD.  DURING RUN-UP, LOUD BANG WHEN PROPELLER WAS REVERSED.  ENGINE WAS SHUT DOWN AND PROPELLER WAS	 REMOVED FOR INSPECTION.  ALL DAMAGE WAS CONTAINED TO THE FEATHER SPRING ASSEMBLY.					1	L	7	1 	3T			NC	A19SW   					 
1997062600103	19970626	00103	CE  	1997	6	26	97ZZZX2865       	1	19970501	G	2720	265313461013	SUPPORT WEB     			RKWELL	NA265 	NA26565     	7630107	CE  										RUD TORQ TUBE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	58HT	5980 				46570				WHILE VISUALLY INSPECTING THE RUDDER SUPPORT ASSY DURING A 150-HOUR INSPECTION, TWO CRACKS WERE FOUND ON THE RUDDER TORQ	UE TUBE LOWER SUPPORT WEB.  THE CRACKS WERE DEVELOPED AS A RESULT OF PART STRESS DURING MANUFACTURE.					2	L	7	2 	4J				A2WE    					 
1997062600105	19970626	00105	CE  	1997	6	26	97ZZZX2866       	1	19970528	G	2612	473275	DETECTOR        			BEECH 	200   	200BEECH    	1152920	CE  										ENGINE	FAILED          	B			BXSR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			EA	09	200BE				1265	BB832				FLAME DETECTOR FAILED WITHIN 71 HOURS AND WOULD INTERMITTENTLY CAUSE THE ENGINE FIRE ANNUNCIATOR TO ILLUMINATE.						1	L	7	2 	4T				A24CE   					 
1997062600106	19970626	00106	EU  	1997	6	26	97ZZZX2867       	1	19970502	G	2710	10306233	SERVO           	AMD         		AMD   	FALC20	FALCON20F5  	2730105	EU  										LT AILERON	LEAKS           	C				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	347HS				497	347				LEFT AILERON SERVO LEAKING EXCESSIVELY WITH NO SYSTEM PRESSURE APPLIED OTHER THAN 21 PSI ON HYDRAULIC TANK (HEAD PRESSUR	E).  BELIEVE PISTON O-RING SEALS SPLIT OR ROLLED.  NOT SURE UNTIL AERO PRECISION REPAIR AND OVERHAUL, INC., FL, HAS HAD 	AN OPPORTUNITY TO INVESTIGATE CAUSE.				2	L	7	2 	4F			RT	A7EU    					 
1997062600107	19970626	00107	EU  	1997	6	26	97ZZZX2868       	1	19970609	G	2710	10306233	SERVO           	AMD         		AMD   	FALC20	FALCON20F5  	2730105	EU  										LT AILERON SYST	LEAKS           	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	25	347HS				1913	347				LEFT AILERON SERVO LEAKED EXCESSIVELY IN-FLIGHT, CAUSED LOSS OF NR 1 HYDRAULIC SYSTEM.  SUBMITTER BELIEVES PISTON O-RING	 SEALS RUPTURED OR ROLLED.  NOT SURE UNTIL INVESTIGATED.					2	L	7	2 	4F			RT	A7EU    					 
1997062600108	19970626	00108	CE  	1997	6	26	97ZZZX2869       	1	19970603	G	3244	265F864	TIRE            	GOODYEARAERO		BEECH 	200   	B200        	1152922	CE  										NLG	DEFECTIVE       	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	700WR				51171106	BB1313				TWO INCH KNOT RAISED ON EDGE OF TIRE TREAD ADJACENT TO SIDEWALL.  NO OTHER APPARENT TIRE DAMAGE.  .2187 TREAD DEPTH.  TI	RE TIME IN SERVICE, 348.4 HOURS.  TOTAL LANDINGS, 404.					1	L	7	2 	4T				A24CE   					 
1997062600109	19970626	00109	CE  	1997	6	26	97ZZZX2870       	1	19970506	G	2121	239	FAN             			CESSNA	500   	500CESSNA   	2076602	CE  										CABIN	FAILED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	96FB	7708 			926	5000094				THE CABIN BLOWER MOTOR FAN CAME APART CAUSING THE MOTOR TO OVERHEAT AND ULTIMATELY BURN THE BLOWER MOTOR UP.  INSTALL SB	 500-21-20.					1	L	7	2 	4F				A22CE   					 
1997062600275	19970626	00275	SO  	1997	6	26	97ZZZX2871       	2	19970528	G	7414	1052948	BEARING         		S6RSC25     						CONT  	O360  	LTSIO360EB  	17025	SO  					DRIVE END	LOOSE           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21		361  			D099634DR		807336R			DRIVE END BEARING INNER RACE BECAME LOOSE ON SHAFT CAUSING OIL TO LEAK THOUGH SEAL.  MAG HAD AN EXTREME AMOUNT OF OIL IN	TERNALLY AND STILL RAN NORMALLY.										3	O			E9CE				 
1997062600277	19970626	00277		1997	6	26	97ZZZX2872       	1	19970602	G	2460	1648009060	BREAKER         	CESSNA      																ELECTRIC SYSTEM	MISMARKED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										CIRCUIT BREAKER FROM CESSNA IMPROPERLY MARKED.  THE BODY OF THE CIRCUIT BREAKER IS MARKED 60A AND THE RESET BUTTON IS MA	RKED 20.																		 
1997062600278	19970626	00278	SO  	1997	6	26	97ZZZX2873       	1	19970530	G	5720	4042313	STIFFENER       			PIPER 	PA31  	PA31350     	7103110	SO  										WS 49 RT	CRACKED         	D				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SO	25	124AG					317852103				FOUND .50 INCH CRACK IN STIFFENER ON RIB, PIPER PN 40423-13.  REPAIRED IAW AC43.13.  CRACK IS LOCATED ADJACENT TO WHEEL 	BUMPER IN UPPER WHEELWELL AND SUSPECT WAS CAUSED BY FATIGUE FROM GEAR RETRACTION.					1	L	7	2 	3O				A20SO   					 
1997062600279	19970626	00279	EA  	1997	6	26	97ZZZX2874       	2	19970605	G	7314	RG9080J4A	FUEL PUMP       	ROMEC       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					VALVE BODY	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	300ED		510  			317852008	RL267268A			UPON PULLING AIRCRAFT IN HANGAR FOR A SCHEDULED INSPECTION, FOUND THE ENGINE DRIVEN FUEL PUMP LEAKING FUEL FROM THE VALV	E BODY PARTING FLANGES.  PUMP WAS REMOVED FROM SERVICE.  SUSPECT CAUSE, THE PARTING HALF FLANGE SCREWS FOR THE VALVE BOD	Y MAY BE IMPROPERLY TORQUED.  GASKET MAY BE PINCHED.  THIS HAS BEEN A PROBLEM WITH OTHER PUMPS IN THE PAST.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997062600280	19970626	00280	SO  	1997	6	26	97ZZZX2875       	1	19970606	G	5521	4007514	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										LT ELEVATOR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	3527U	14480				317952141				AIRCRAFT ELEVATORS WERE OPENED UP IN C/W PIPER MANDATORY SB 998.  THE LEFT ELEVATOR SPAR WAS FOUND CRACKED AT THE TIP AN	D FOUND CRACKED HALF WAY THROUGH THE SPAR JUST INBOARD OF THE VERY OUTBOARD ATTACH POINT.  ELEVATOR SPARS NEED TO BE STR	ENGTHENED UP AT THESE POINTS AND THE ELEVATOR LEADING EDGE ABRASION (RUBBER BOOT) NEEDS TO BE CHANGED TO SOMETHING SOLID	 THAT DOESN'T VIBRATE IN THE AIRFLOW.			1	L	7	2 	3O				A20SO   					 
1997062600281	19970626	00281	SO  	1997	6	26	97ZZZX2876       	1	19970503	G	5412	337505	FIREWALL        			PIPER 	PA28  	PA28R201T   	7102813	SO  										TURBOCHARGER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	48427					28R7803056				UPON ENGINE REMOVAL, FOUND GALVANIZED PORTION OF FIREWALL DETERIORATED AND CORROSION SET IN FROM THE OUTSIDE IN.  SUSPEC	T HIGH HEAT AREA DIRECTLY BEHIND TURBOCHARGER.  RECOMMEND HEAT SHIELD MADE OF STAINLESS STEEL - BEHIND TURBOCHARGER (INS	ULATING COVER WAS IN PLACE AROUND THE TURBOCHARGER).				1	L	7	1 	3O				2A13    					 
1997062600282	19970626	00282	SO  	1997	6	26	97ZZZX2877       	2	19970602	G	7322	P16160	FULCRUM PIN     	BENDIX      	NAS3A1      	CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512       	17008	SO  					CARBURETOR FLOAT	SPALLED         	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CE	05	76122					10519	24177612			ENGINE QUIT ON TAKEOFF JUST AFTER ROTATION RESULTING IN DAMAGE TO THE AIRCRAFT.  ENGINE WAS CHECKED FOR FUEL, COMPRESSIO	N, AND IGNITION.  ENGINE WAS STARTED AND RUN-UP.  OPERATION APPEARED TO BE NORMAL.  DISASSEMBLED CARBURETOR AND BENCH CH	ECKED.  FLOAT LEVEL WAS WITHIN SPECS.  ALL PASSAGES CLEAN AND OPEN.  DID FIND THE FLOAT FULCRUM PIN SPALLED.  EXPERIENCE	 HAS SHOWN ANY WEAR ON THIS PIN CAN CAUSE THIS TYPE OF PROBLEM.  BECAUSE OF THE VERY LIMITED MOVEMENT OF THE FLOAT LEVEL	, IT IS HARD TO SAY WHAT THE FIX SHOULD BE.  PERHAPS IT NEEDS SOME ENGINEERING STUDY.  NTSB ACCIDENT NR CHI-97LA143.		1	H	7	1 	3O	3	O	NC	A768    	E233				 
1997062600283	19970626	00283	SO  	1997	6	26	97ZZZX2878       	1	19970604	G	3222	6705408	TRUNNION        			PIPER 	PA32  	PA32R301    	7103218	SO  										NLG	EAR BROKEN      	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9274Q	158  				3246038				AFTER LANIDNG AIRCRAFT, PILOT NOTICED SPRING HANGING FROM NOSE GEAR ARM.  UPON INVESTIGATING, FOUND EAR ON RT FORWARD UP	PER SIDE OF TRUNNION BROKEN.  GEAR OPERATIONS ARE NORMAL, NO BINDING OR INTERFERENCE WAS NOTED WITH AIRCRAFT ON JACKS. S	USPECT A DEFECT IN MANUFACTURING THAT EXISTED SINCE NEW.  AIRCRAFT 6 MONTHS OLD.  REPLACED TRUNNION WITH NEW UNIT.				1	L	7	1 	3O				A3SO    					 
1997062600284	19970626	00284	GL  	1997	6	26	97ZZZX2879       	1	19970529	G	3230	KHP1CAL	RELAY           			BLANCA	17    	1730A       	1220433	GL  										GEAR SYSTEM	DETACHED        	B		A	IU2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	93603	1332 				7330610				RELAY CAME LOOSE FROM SOCKET.  RELAY IS MOUNTED UPSIDE DOWN IN AIRCRAFT.  NO WAY TO ATTACH IN HOLDER.  NEEDS SOME TYPE O	F POSITIVE LOCKING.  IF SWITCH COMES LOOSE ON ONE SIDE, GEAR WILL NOT GO UP.  IF SWITCH COMES LOOSE ON THE OTHER SIDE, G	EAR WILL NOT GO DOWN.  FACTORY ADVISED TO INSTALL AND WRAP TAPE AROUND IT.  NEEDS A BETTER POSITIVE LOCKING DEVICE.				1	L	7	1 	3O				A18CE   					 
1997062600285	19970626	00285	SO  	1997	6	26	97ZZZX2880       	1	19970609	G	2510	FD56673	BUSHING         		FDC59001205 	PIPER 	PA28  	PA28RT201T  	7102817	SO  										SEAT BOLT	MISSING         	G	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	8392T	2267 				28R8131140				NYLON SHOULDER HARNESS RETAINING BUSHING WAS FOUND MISSING FROM BOTH FRONT SEAT LAP BELTS.  MANUFACTURER INDICATED NO FI	ELD REPAIRS.  MANUFACTURER STATED THEY ARE DOING A N/C REPLACEMENT.  SUBMITTER STATED LIKE CONDITION FOUND ON VARIOUS OT	HER SEAT BELTS.				1	L	7	1 	3O				2A13    					 
1997062600286	19970626	00286	CE  	1997	6	26	97ZZZX2881       	1	19970523	G	7120	085112132	MOUNT BEAM      			CESSNA	340   	340A        	2076405	CE  										RT OTBD NACELLE	CORRODED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	111SC	5031 				340A0335				DURING 100-HOUR INSPECTION, SEVERE CORROSION WAS FOUND ON RIGHT OUTBOARD ENGINE MOUNT BEAM ASSY, AFT CANTED BULKHEAD, AN	D RT AND LT DOUBLERS.  FOUND PARTS TO BE EXTREMELY SCARCE FOR THIS TYPE OF REPAIR.  CORROSION CAUSED BY HEAT FROM EXHAUS	T TAILPIPE AND EXHAUST ELBOW.  SUBMITTER SUGGESTS HEAT SHIELD.				1	L	7	2 	3O				3A25    					 
1997062600287	19970626	00287	CE  	1997	6	26	97ZZZX2882       	1	19970604	G	2430		GROUND WIRE     			CESSNA	425   	425         	2076018	CE  										RT GENERATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	12214	1650 				4250194				RIGHT GENERATOR CONTINUOUSLY DROPPED OFF-LINE, BUT WOULD RESET.  FOUND GENERATOR GROUNDING ATTACHED TO SPAR WEB JUST AFT	 OF ENGINE.  THE GROUND WIRE WAS LOOSE AND HAD BEEN ARCING TO SPAR WEB. ORIGINAL HOLE IS ORIGINALLY .375 INCH DIAMETER A	ND HAD BEEN ARCED OUT TO ALMOST 1 INCH IN DIAMETER.				1	L	7	2 	3T			RT	A7CE    					 
1997062600288	19970626	00288	CE  	1997	6	26	97ZZZX2883       	1	19970529	G	2140	719843	COIL            		8259HR2     	CESSNA	310   	310R        	2074245	CE  										HEATER IGNITOR	SHORTED         	B		A	BXSR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	09	123RA	5    				310R0221				THE FIRST COIL EXPLODED BREAKING OFF THE TOP OF THE IGNITOR AND BREAKING WIRES IN THE IGNITION UNIT SPEWING 'OIL' FROM I	NSIDE THE COIL THROUGHOUT THE HEATER BAY.  THE REPLACEMENT COIL SHORTED OUT, LEAKED OIL, AND THE COVER CAME LOOSE.					1	L	7	2 	3O				3A10    					 
1997062600289	19970626	00289	SO  	1997	6	26	97ZZZX2884       	1	19970611	G	2720	2151	CONNECTOR SPRING			LUSCOM	8     	8E          	8190112	SO  										RUD TAIL WHEEL	BROKEN          	D				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SW	17	2070B					6497				PILOT AT TAKEOFF NOTICED AIRCRAFT FELT STRANGE IN THE TAIL SECTION/TAIL WHEEL.  TAIL WAS OFF THE GROUND, PILOT SET TAIL 	BACK ON GROUND, AIRCRAFT TOOK HARD SHARP TURN TO THE LEFT AND ENDED UP IN A FENCE.  AFTER INVESTIGATION, NOTED THE CONNE	CTOR SPRING AND CHAIN WAS BROKEN ON THE RIGHT SIDE OF AIRCRAFT.  PART NR 2151.  RECOMMEND THAT CONNECTOR SPRING AND CHAI	N BE REINFORCED OR UPGRADED TO A STRONGER CHAIN SYSTEM.			1	H	7	1 	3O				A694    					 
1997062600290	19970626	00290	EA  	1997	6	26	97ZZZX2885       	2	19970613	G	8550	LW13901	SUMP            			SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					ENGINE OIL	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	3188R	538  				2205	L2551348A			AFTER A PHASE INSPECTION AND AFTER ENGINE RUN-UP, THE ENGINE WAS CHECKED FOR OIL LEAKS BEFORE COWLING INSTALLED.  A LEAK	 WAS NOTED BEHIND THE RIGHT REAR ENGINE MOUNT BRACKET.  A CLOSER LOOK WAS MADE AND A CRACK WAS FOUND (ABOUT 2.50 INCHES 	LONG).  OIL SUMP WAS REMOVED AND REPLACED WITH A SERVICEABLE PART.  CAUSE UNKNOWN.				1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1997062600291	19970626	00291	EA  	1997	6	26	97ZZZX2886       	2	19970529	G	8520	LW13831	CRANKCASE       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LT CASE HALF	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	46SD	1656 				278054040	RL1583748A			FOUND A CRACK IN THE LEFT CASE HALF BETWEEN NR 4 AND NR 6 CYLINDERS.						1	L	7	2 	3O	3	O		1A10    	1E4				 
1997062600292	19970626	00292	CE  	1997	6	26	97ZZZX2887       	1	19970529	G	5510	07321014	REINFORCEMENT   		123260031   	CESSNA	182   	R182        	2072734	CE  										LT HORZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	52442	9561 				R18201646				THE LEFT HAND REINFORCEMENT ON THE HORIZONTAL STABILIZER WAS FOUND CRACKED.  THIS REINFORCEMENT IS ONE OF THE AFT ATTACH	 POINTS OF THE HORIZONTAL STABILIZER.					1	H	7	1 	3O			RT	3A13    					 
1997062600293	19970626	00293	EA  	1997	6	26	97ZZZX2888       	2	19970606	G	7310		HOSE            			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A5    	41532	EA  					ENGINE FUEL	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6159P	5170 				24412				HOSES HAVE NO IDENTIFICATION MARKINGS BECAUSE THEY ARE SO OLD.  SEVERELY CHAFED, HARDENED WITH FOSSILIZED EMBRITTLEMENT.	  OUTER COVERING ON ONE HOSE HAS DISSENTEGRATED TO THE INNER CORE.  SUBMITTER RECOMMENDED THAT ALL GENERAL AVIATION FLEX	IBLE HOSES LOCATED IN THE ENGINE COMPARMENT HAVE A MANDATORY LIFE LIMIT ESTABLISHED BY AN AIRWORTHINESS DIRECTIVE.				1	L	7	1 	3O	3	O		1A15    	E295				 
1997062600294	19970626	00294	EA  	1997	6	26	97ZZZX2889       	2	19970605	G	8530	74925	CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NR 2	FAILED          	D				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			GL	15	6881Y					274230	L99348			PILOT NOTICED LEFT ENGINE COWLING BECOMING COVERED WITH OIL.  ENGINE WAS UNCOWLED FOR INVESTIGATION AND FOUND NR  2 CYLI	NDER HEAD CRACKED COMPLETELY OFF THE CYLINDER BARREL.  THE ONLY THING HOLDING THE CYLINDER HEAD IN PLACE WAS THE EXHAUST	, INDUCTION TUBE, AND ENGINE BAFFLING.  TOTAL TIME ON CYLINDER UNKNOWN.  TIME ON CYLINDER SMOH, 1,905 HOURS.  CAUSE UNKN	OWN.			1	L	7	2 	3O	3	O		1A10    	1E4				 
1997062600295	19970626	00295	CE  	1997	6	26	97ZZZX2890       	1	19970523	G	7120	085112132	MOUNT BEAM      			CESSNA	340   	340CESSNA   	2076404	CE  										RT OTBD NACELLE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	69558	5163 				3400504				DURING ANNUAL INSPECTION, SEVERE CORROSION FOUND ON RT OUTBOARD ENGINE MOUNT BEAM ASSY, AFT CANTED BULKHEAD AND RT AND L	T DOUBLERS.  PROBE WAS USED TO TEST CORROSION AND PUSHED COMPLETELY THROUGH MOUNT BEAM.  PARTS ARE EXTREMELY SCARCE FOR 	THIS REPAIR.  CORROSION WAS CAUSED BY HEAT EXHAUST TAILPIPE AND ELBOW.  SUGGEST HEAT SHIELD.				1	L	7	2 	3O				3A25    					 
1997062600296	19970626	00296		1997	6	26	97ZZZX2891       	4	19970528	G	2562	12630423	G SWITCH        	DORNEMARGLN 		SLNSBY	T67   	T67M260     	8323006	EU  										ELT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	7020D	1067 				2109				WHILE PERFORMING AN ANNUAL ELT INSPECTION, ELT SENSOR DID NOT COME ON.  DORNE AND MARGOLIN, ELT NR TSOC91.						1	L	7	1 	3O			NT	A73EU   					 
1997062600360	19970626	00360	EU  	1997	6	26	97ZZZX2893       	2	19970509	G	7321	1310526	SOLENOID        	WOODWARD    	8063215     						CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL CONTROL	MALFUNCTION     	B	L		UU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					94318					WOODWARD RECENTLY BECAME AWARE OF A POTENTIAL NON-CONFORMANCE OF THE CFM56-3 IDLE RESET SOLENOID.  THE NON-CONFORMANCE I	S DIRECTLY RELATED TO A SPECIFICATION CHANGE FOR THE SOLENOID.  SPECIFICALLY, THE SPEC WAS ALTERED TO REQUIRE DROP-OUT A	T EXTREME RATHER THAN NORMAL PRESSURIZATION CONDITIONS.  THE PRESSURIZATION CHARACTERISTICS AFFECT BOTH PULL-IN AND DROP	-OUT OF THE SOLENOID, SO THE SUPPLIER ALTERED THE CALIBRATION OF THE UNIT ACCORDINGLY.  AS A RESULT OF THE ALTERED CALIB	RATION, IT HAS BEEN DETERMINED THAT IN SOME CASES THE SOLENOID WILL NOT DROP OUT WITH NORMAL PRESSURIZATION.							4	F			E21EU				 
1997062600362	19970626	00362	CE  	1997	6	26	97ZZZX2894       	1	19970514	G	2497		WIRE            			CESSNA	206   	U206F       	2073333	CE  										FIREWALL	SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	27	1523U	6662 				U20602234				THE PILOT NOTED SMOKE COMING FROM UNDER THE INSTRUMENT PANEL UPON ACTIVATING THE MASTER ELECTRICAL SWITCH.  UPON INVESTI	GATION, FOUND THE WIRING COMING THROUGH THE UPPER LEFT FIREWALL WAS BURNED AT THE FIREWALL ONLY.  IT APPEARS THAT DUE TO	 AGE, THE INSULATOR GROMMET HAD WORN THROUGH ALLOWING ONE WIRE TO CONTACT GROUND AND BURN THROUGH WHICH STARTED THE OTHE	RS IN THE BUNDLE ALLOWING THEM TO SHORT TO THE SHIELDING.  THE AREA WAS COVERED BY A THICK GLOB OF SEALANT MAKING IT IMP	OSSIBLE TO INSPECT.  AFTER REPLACING OR REPAIRING THE WIRES AS NECESSARY, A FUNCTIONAL CHECK OF THE CIRCUIT PROTECTORS W	AS DONE AND FOUND NORMAL.	1	H	7	1 	3O			 	A4CE    					 
1997062600363	19970626	00363	SO  	1997	6	26	97ZZZX2895       	1	19970618	G	3213	58383	GEAR LEG        		08311       	LUSCOM	8     	8E          	8190112	SO  										LT MLG	FAILED          	G	S			K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	21	1750K	2840 				4477				PRIVATE PILOT REPORTED DURING LANDING ROLL,  20 TO 25 KNOTS,  APPLIED LIGHT BRAKING.  ACFT THEN VEERED TO THE RT INTO A 	GROUND LOOP.  LT MAIN GEAR COLLAPSED.  EXAMINATION OF MLG REVEALED HEAVY CORROSION WITHIN THE INNER BORE OF LOWER LEG ST	RUT WHERE IT JOINS THE AXLE.  SUBMITTER STATED CORROSION MAY HAVE REDUCED STRENGTH OF THE MLG STRUT BY 70 PERCENT.  MOIS	TURE INTRODUCED INTO THE INNER CORE OF THE STRUT THROUGH THE MLG FAIRING ATTACH POINT BOLT HOLES.  AREA DIFFICULT TO INS	PECT DUE TO  POSITION OF THE GEAR FAIRING AND ROD CLEVIS.  RECOMMENDATION:  STRIP AREA AND PERFORM DYE PENETRANT INSP CH	ECK FOR CRACKS AND PITTING, FILLING STRUT WITH LINSEED OIL, DRAIN, AND PROVIDE SEAL FOR MLG FAIRING TO STRUT BOLT HOLES.	1	H	7	1 	3O				A694    					 
1997062600364	19970626	00364	EA  	1997	6	26	97ZZZX2896       	1	19970602	G	2622	892480	EXTINGUISHER    	KIDDE       		CNDAIR	CL600 	CL6002A12   	1900304	EA  										AGENT	DEFECTIVE       	B		A	JG1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	1824T				18380	3029				FIRE EXTINGUISHER RECEIVED FOR OVERHAUL.  WHEN A FUNCTIONAL TEST WAS PERFORMED PRIOR TO OVERHAUL, A STRANGE VIBRATION OR	 THUMP WAS FELT WHEN THE CO2 CARTRIDGE WAS DISCARDED INTO THE EXTINGUISHER.  WHEN THE DISCHARGE LEVER WAS PUSHED, NO EXT	INGUISHING AGENT WAS DISCHARGED, ONLY CO2.  UPON EXAMINATION, THE EXTINGUISHER WAS FOUND CONTAMINATED WITH WHAT SMELLED 	LIKE LACQUER THINNER.  THE SIPHON TUBE WAS FOUND COILED INSIDE THE CYLINDER.  THIS PROBABLY WAS THE NOISE HEARD ON DISCH	ARGING THE CO2.  THE BOTTOM OF THE CYLINDER ALSO IS CORRODED AND THE PLATING IS FLAKING.  THE EXTINGUISHER FLUID WAS POU	RED INTO A CONTAINER AND THERE WAS A LAYER OF FLAMMABLE LIQUID ON TOP OF THE ANTIFREEZE.	2	L	7	2 	4F			RT	A21EA   					 
1997062600365	19970626	00365	CE  	1997	6	26	97ZZZX2897       	1	19970609	G	5510	3541050416	STAB CUFF       			BEECH 	35    	C35BEECH    	1151508	CE  										RT HORIZ STAB	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	656D	71   				D2924				DURING ANNUAL INSPECTION AND AD 94-20-04 PARA (B) COMPLIANCE FOUND BEECH KIT 35-4016-3 (STAB REINFORCEMENT) LEADING EDGE	 CUFF ATTACH RIVETS FAULTY.  FOUND LT CUFF ON THE RT SIDE AND RT CUFF ON LT SIDE.  REVERSAL CAUSED A MISFIT OF CONTOUR A	ND INADQUATE RIVETING.				1	L	7	1 	3O				A777    					 
1997062600366	19970626	00366	CE  	1997	6	26	97ZZZX2898       	1	19970609	G	5510	3541050415	STAB CUFF       			BEECH 	35    	C35BEECH    	1151508	CE  										LT HORIZ STAB	MISINSTALLED    	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	656D	71   				D2924				DURING ANNUAL INSPECTION AND AD 94-20-04 PARA (B) COMPLIANCE FOUND BEECH KIT 35-4016-3 (STAB REINFORCEMENT) LEADING EDGE	 CUFF ATTACH RIVETS FAULTY.  FOUND LT CUFF ON THE RT SIDE AND RT CUFF ON LT SIDE.  REVERSAL CAUSED A MISFIT OF CONTOUR A	ND INADQUATE RIVETING.				1	L	7	1 	3O				A777    					 
1997062600367	19970626	00367	EA  	1997	6	26	97ZZZX2899       	2	19970517	G	8530		SEAL            			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					NR 3 CYL PUSHROD	LEAK            	D				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			GL	13	666AW					317312061	L415661A			AFTER TAKEOFF DURING CLIMB-OUT, PILOT NOTICED FINE SPRAY OF OIL MIST FROM RT ENGINE OUTBOARD SIDE AND TRACE OF OIL LEAK 	BEGIN TO FORM.  PILOT MADE AN UNEVENTFUL LANDING AND ENGINEERING INVESTIGATION WAS CARRIED OUT.  NR 3 CYLINDER EXHAUST P	USHROD LOCKING CLIP HAD UNLOCKED ALLOWING SEAL TO LEAK OIL DUE TO A LOOSE SHROUD TUBE.  SUBMITTER RECOMMENDATION:  TO WI	RE LOCK WITH SAFETY WIRE IN PAIRS THE LOCKING CLIPS OF THE INDIVIDUAL SHROUD TUBES FOR EVERY CYLINDER.			1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
1997062600368	19970626	00368	EA  	1997	6	26	97ZZZX2900       	2	19970425	G	7322	14190	THROTTLE VALVE  		MA4SPA      	CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARBURETOR	OUT OF ADJUST   	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	78512				CK815294	17257646	L4478727A			OVERHAULED CARBURETOR FURNISHED WITH LYCOMING OVERHAULED ENGINE WOULD NOT IDLE BELOW 1,000 RPM AFTER BUILD-UP AND INSTAL	LATION.  CARUBURETOR WAS NEWLY OVERHAULED.  REMOVAL AND INSPECTION REVEALED THE THROTTLE PLATE WAS NOT ALIGNED CORRECTLY	 AND WAS BINDING ON THROAT OF CARBURETOR WHEN CLOSED AND WOULD NOT HIT IDLE STOP WITH SCREW FULLY BACKED OUT.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997062600369	19970626	00369	SW  	1997	6	26	97ZZZX2901       	1	19970612	G	5711		SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  										RT WING	CRACKED         	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	88083	700  				71974				WHILE C/W AMERICAN CHAMPION SL 406 RE:  CRACKED SPARS.  BOTH MAIN SPARS FOUND TO HAVE HAIRLINE CRACKS OPPOSITE THE UPPER	 INBOARD ATTACH BOLT FOLLOWING THE SPAR GRAIN.  BOTH WINGS TO BE REPLACED WITH FACTORY NEW WINGS.  1974 CITABRIA 7GCBC 7	00 HRS TTSN.  NEVER USED FOR AEROBATIC TRAINING.  WAS USED BRIEFLY WHEN NEW FOR GLIDER TOWING.				1	H	7	1 	3O			NC	A759    					 
1997062600370	19970626	00370	SW  	1997	6	26	97ZZZX2902       	1	19970612	G	5711		SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  										LT WING	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	88083	700  				71974				WHILE C/W AMERICAN CHAMPION SL 406 RE:  CRACKED SPARS.  BOTH MAIN SPARS FOUND TO HAVE HAIRLINE CRACKS OPPOSITE THE UPPER	 INBOARD ATTACH BOLT FOLLOWING THE SPAR GRAIN.  BOTH WINGS TO BE REPLACED WITH FACTORY NEW WINGS.  1974 CITABRIA 7GCBC 7	00 HRS TTSN.  NEVER USED FOR AEROBATIC TRAINING.  WAS USED BRIEFLY WHEN NEW FOR GLIDER TOWING.				1	H	7	1 	3O			NC	A759    					 
1997062600371	19970626	00371	CE  	1997	6	26	97ZZZX2903       	1	19970602	G	2750		BELLCRANK       			CESSNA	500   	S550        	2076607	CE  										LT WING FLAP	CORRODED        	B		A	CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	134QS	8994 				S5500134				DURING INSPECTION, FOUND LT INBOARD FLAP OUTBOARD BELLCRANK WITH EXCESSVIE SIDE-TO-SIDE PLAY.  UPON REMOVAL, FOUND UPPER	 AND LOWER BEARINGS FROZEN AND/OR CORRODED.  A LARGE QUANTITY OF RUSTY WATER FLOWED OUT OF THE BELLCRANK TUBE.  IT APPEA	RS THE TUBE WAS FILLED WITH WATER AS THE BEARINGS, SPACER, AND MOUNTING BOLTS WERE FOUND CORRODED.  SUBMITTER STATED PER	HAPS A DRAIN HOLE IN BELLCRANK TUBE WOULD HELP.			1	L	7	2 	4F			RT	A22CE   					 
1997062600372	19970626	00372	GL  	1997	6	26	97ZZZX2904       	2	19970602	G	7210	6894171	GEARBOX         			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	16917	7850 			834952	2303	834952			FOUND ENGINE GEARBOX CRACKED AT TOP MOUNTING LOCATION FOR COMPRESSOR.  NO ABNORMAL VIBRATIONS OR CIRCUMSTANCES LED TO FI	NDING CRACK.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997062600373	19970626	00373	SO  	1997	6	26	97ZZZX2905       	1	19970608	G	7333	3006614	CLAMP           			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL FLOW XMIT	MISSING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	242RA					428001003	PCE80883			FUEL FLOW TRANSMITTER IS MOUNTED TO ENGINE WITH 2 STAINLESS LINES PN 3032010 AND PN 3026779 B1; AND, IF SUPPORT CLAMP PN	 30006614 IS NOT INSTALLED, LINES WILL CRACK AT WELDS CREATING A HEAVY FUEL LEAKING ENGINE COMPARTMENT AND ONTO WING.					1	L	7	2 	4T	4	T		A23SO   	E4EA				 
1997062600374	19970626	00374	CE  	1997	6	26	97ZZZX2906       	1	19970602	G	2435	300SG1064	ARMATURE        		300SG118Q   	CESSNA	441   	441         	2076020	CE  										START/GENERATOR	DAMAGED         	E				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		AP	APPROACH       	1			WP	07	445AE		982  		1682	4410043				WHILE APPROACHING TO LAND AT 'LAS', PILOT LOST LT GENERATOR INDICATION.  TWO MINUTES LATER PILOT GOT A FIRE WARNING INDI	CATION AND SECURED THE ENGINE AND FIRED THE LT FIRE BOTTLE.  LANDED WITH NO FURTHER PROBLEMS.  EXAMINATION FOUND THE GEN	ERATOR SHAFT SHEARED AND ARMATURE DAMAGED.  BEARINGS WERE INTACT AND CASE OF GENERATOR SHOWED SIGNS OF OVERHEATING.  NO 	OTHER DAMAGE FOUND.  INSTALLED SERVICEABLE GENERATOR AND FIRE BOTTLE.  SYSTEMS CHECKED GOOD.			1	L	7	2 	3T			RT	A28CE   					 
1997062600375	19970626	00375	CE  	1997	6	26	97ZZZX2907       	1	19970523	G	5720	65220516	CAP ANGLE       			CESSNA	500   	560CESSNA   	2076750	CE  										RT WHEELWELL	CRACKED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	561EJ	3400 				5600035				DURING PHASE 1-4 INSPECTION, FOUND RT WHEELWELL CAP ANGLE CRACKED AT AFT END.  HARD TO TELL WHAT CAUSED CRACK OTHER THAN	 INSTALLATION OR NORMAL USE.					2	L	7	2 	4F			RT	A22CE   					 
1997062600376	19970626	00376	CE  	1997	6	26	97ZZZX2908       	1	19970523	G	5542	553300053	SKIN            			CESSNA	500   	560CESSNA   	2076750	CE  										RUDDER LT LOWER	CRACKED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	561EJ	3460 				5600035				DURING PHASE 1-4 INSPECTION, FOUND LT LOWER RUDDER SKIN CRACKED ALONG A ROW OF RIVETS.  LIKELY CAUSE IS VIBRATION.  THIS	 IS A COMMON PROBLEM ON S550 AND 560 AIRCRAFT.  HEAVIER SKIN AND/OR INTERNAL BEEF-UP NEEDED.					2	L	7	2 	4F			RT	A22CE   					 
1997062600377	19970626	00377	EA  	1997	6	26	97ZZZX2909       	3	19970515	G	6111		BLADE           			LUSCOM	8     	8A          	8190104	SO  						SNSNCH	W72	W72GK       	EA  	TIP	SEPARATED       	G				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			WP	07	5896X	55   				2553				TIP AND CENTER SECTION (LAMINATE) SEPARATED IN-FLIGHT UNBALANCING ENGINE.  MADE UNSCHEDULED STOP AT NEARBY AIRPORT AFTER	 SHUT DOWN.					1	H	7	1 	3O				A694    		5	N	P170	 
1997062600717	19970626	00717	CE  	1997	6	26	97ZZZX2910       	1	19970501	G	5511	0530015	SPAR            			CESSNA	172   	172         	2072402	CE  										HORIZ STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		3853 								INSPECTION FOUND HORIZONTAL STABILIZER FRONT SPAR CRACKED.						1	H	7	1 	3O			NT	3A12    					 
1997062600718	19970626	00718	CE  	1997	6	26	97ZZZX2911       	1	19970611	G	3411		LINE            			CESSNA	320   	320         	2074502	CE  										PITOT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11										FOUND PITOT LINE FROM PITOT TUBE TO FORWARD BULKHEAD CORRODED THROUGH IN NUMEROUS LOCATIONS.						1	L	7	2 	3O				3A25    					 
1997062600719	19970626	00719	CE  	1997	6	26	97ZZZX2912       	1	19970606	G	2510		HARNESS         			CESSNA	150   	152         	2071835	CE  										COCKPIT	UNLATCHES       	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13										THE SHOULDER HARNESS CLIP THAT ATTACHES THE SHOULDER STRAP TO THE LAP (SEAT) BELT IS DEFECTIVE.  THE SHOULDER STRAP WILL	 DISCONNECT FROM THE LAP BELT UNLESS TENSION IS KEPT ON THE SHOULDER STRAP.					1	H	7	1 	3O			NT	3A19    					 
1997062600720	19970626	00720	CE  	1997	6	26	97ZZZX2913       	1	19970528	G	3230	AHM6NMB	ROD END         			BEECH 	36    	A36         	1151604	CE  										NLG RETRACT	FAILED          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	1849W	5343 				E428				THIS ROD END IS PART OF THE AFT EXTENSION/RETRACTION TUBE FOR THE NOSE GEAR RETRACT SYSTEM.  THE TUBE WAS FOUND INSTALLE	D BACKWARDS RESULTING IN THE INCORRECT ROD END STYLE BEING ATTACHED TO THE GEARBOX ARM.  THIS ROD END SHOULD HAVE BEEN A	TTACHED TO THE IDLER ARM.  THE DESIGN OF THIS ROD END IS FOR FORE AND AFT MOVEMENT (IDLER ARM) NOT ROTATIONAL MOVEMENT (	GEARBOX).  THE RESULT WAS THAT SIDE PRESSURE CRACKED THE ROD END BEARING CASE, STRETCHED THE CASE TO A 'C' SHAPE DURING 	GEAR OPERATION, AND, FINALLY, ALLOWED THE BEARING TO SEPARATE FROM THE CASE RESULTING IN THE NOSE GEAR FAILING TO EXTEND	.  SUBMITTER BELIEVES THIS TO BE AN ORIGINAL FACTORY INSTALLATION.	1	L	7	1 	3O				3A15    					 
1997062600722	19970626	00722	CE  	1997	6	26	97ZZZX2915       	1	19970616	G	7810	82269	EXHAUST WYE     			CESSNA	340   	340A        	2076405	CE  										TURBOCHARGER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	5174J	2000 				340A0009				THE EXHAUST TO TURBOCHARGER WYE AND BYPASS ELBOW PN 8226-9 AND PN K9910299-5 WERE FOUND CRACKED AT THEIR COUPLING FLANGE	S.					1	L	7	2 	3O				3A25    					 
1997062600723	19970626	00723	EU  	1997	6	26	97ZZZX2916       	1	19970212	G	2432	RG390E	BATTERY         			BRAERO	DH125 	HS125700A   	4230170	EU  										DC SYSTEM	SPLIT           	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	571CH	503  			CBC273171	NA0256				NR 1 BATTERY SHOWS CRACK.  CRACK IS ON A SEAM.  NR 2 BATTERY SHOWS RETAINER SLEEVE VIBRATED DOWN TO BOTTOM OF BATTERY. P	ART TOTAL CYCLES, 436.					2	L	7	2 	4F				A3EU    					 
1997062600724	19970626	00724	EA  	1997	6	26	97ZZZX2917       	2	19970616	G	7322	12856	LEVER           		MA45        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					THROTTLE	SEPARATED       	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			GL	25	5955V	53   			G519232	287790516	L2727336A			WHILE ON APPROACH TO CAK, PILOT LOST THROTTLE CONTROL, AND , SUBSEQUENTLY, LANDED IN AN OPEN FARM FIELD.  INVESTIGATION 	REVEALED THAT THE THROTTLE CONTROL LEVER WAS LOOSE EVEN THOUGH THE CASTLE NUT AND COTTER PIN WERE FAIRLY TIGHT AND INTAC	T.  SUSPECT IMPROPER INSTALLATION PROCEDURE AND IMPROPER TORQUE OF NUT SECURING ARM.				1	L	7	1 	3O	3	O		2A13    	E286				 
1997062600725	19970626	00725	CE  	1997	6	26	97ZZZX2918       	1	19970609	G	5741	05233091	ANGLE           			CESSNA	150   	150M        	2071830	CE  										RT WING SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	66221					15075929				DURING ANNUAL INSPECTION, INTERGRANULAR CORROSION WAS FOUND IN ANGLE REINFORCEMENT AT RT WING SPAR BUTT WHERE SPAR BOLTS	 TO FUSELAGE SPAR CARRY-THROUGH.  DIFFICULT AREA TO INSPECT WITHOUT REMOVAL OF COCKPIT HEADLINER.  SUBMITTER STATED IMPR	OPER HEAT TREATMENT WHEN MANUFACTURED.  RECOMMENDATION:  AGING AIRCRAFT REQUIRE MORE DETAILED INSPECTION IN DIFFICULT TO	 SEE AREAS.  SIDE NOTE:  A PAIR OF PLIERS WERE FOUND INSIDE A VOID IN THE RIGHT WING.  RUST OF PLIERS INDICATE IT HAD BE	EN THERE A LONG TIME.		1	H	7	1 	3O				3A19    					 
1997062600726	19970626	00726	CE  	1997	6	26	97ZZZX2919       	1	19970423	G	3230	12802091	PIN             			CESSNA	210   	T210M       	2073451	CE  										NLG DOWNLOCK	SHEARED         	B	S		CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6798M	2314 				21061992				SEE FIGURE 126A OF PART MANUAL 1970 TO 1980 CESSNA 210.  PIN PN 1280209-1 IS PRESSED INTO BEARING END PN 1280600-5 AND L	OCKED IN PLACE WITH A ROLL PIN.  THIS PIN IS USED FOR NOSE GEAR DOWNLOCK.  PINS WERE BEING REPLACED AS PART OF REPAIR TO	 REMOVE PLAY IN NLG.  DOWNLOCK ASSY PINS DID NOT SHOW EXCESSIVE WEAR AND WERE TIGHT IN BEARING END.  UPON REMOVAL, FOUND	 BOTH PINS SHEARED AT GROOVE FOR ROLL PIN.			1	H	7	1 	3O				3A21    					 
1997062600727	19970626	00727	CE  	1997	6	26	97ZZZX2920       	1	19970612	G	2434	ALT9422	ALTERNATOR      			CESSNA	401   	401A        	207590D	CE  										RT ENGINE	LUG CRACKED     	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	25	711SN	197  			512260	401A0054				ALTERNATOR MOUNT LUG FOUND CRACKED, AND OIL LEAKING AT GASKET.  ALTERNATOR HAS ONLY 197 HRS SINCE OVERHAUL.  ON DISASSEM	BLY, ONE LUG FOUND CRACKED AND ONE LUG FELL OFF COMPLETELY.					1	L	7	2 	3O				A7CE    					 
1997062600728	19970626	00728	EA  	1997	6	26	97ZZZX2921       	2	19970524	G	8530	LYC16T19468	VALVE SEAT      		05K21108CKP 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENG EXHAUST	LOOSE           	E				D				RETURN TO BLOCK         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TX	TAXI/GRND HDL  	1			AL	03	493SC	1585 				317652048	L184368A			DURING TAXI FOR TAKEOFF, PILOT REPORTED ENGINE RUNNING ROUGH.  RIGHT ENGINE MANIFOLD PRESSURE HIGHER THAN NORMAL.  COMPR	ESSION CHECK FOUND NR 1 CYLINDER LOW, 10/80.  DISASSEMBLY OF CYLINDER FOUND LOOSE EXHAUST VALVE SEAT.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997062600729	19970626	00729	GL  	1997	6	26	97ZZZX2922       	3	19970612	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROP BOLTS	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	49951	5451 				15281411		R772521		PROPELLER HAS 2 CRACKS APPROXIMATELY .4375 INCH LONG AT BOLT HOLES.  FOUND DURING INSPECTION REQUIRED BY AD 97-06-18 AND	 SB 221B.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997062600730	19970626	00730	CE  	1997	6	26	97ZZZX2923       	1	19970508	G	5412		FIREWALL        			CESSNA	172   	172P        	2072436	CE  										COWL MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	53051	3407 				17274673				FOUND FIREWALL CRACKED AT COWL MOUNT NEXT TO BATTERY BOX BRACKET AND EXTERNAL POWER RECEPTACLE.  AFTER REMOVING COWL MOU	NT AND STIFFENER, FOUND CRACK UNDER STIFFENER WHICH COULD NOT BE SEEN WITH STIFFENER INSTALLED ON AIRCRAFT.  SUSPECT CAU	SE OF CRACK IS COMBINATION OF NORMAL ENGINE MOUNT VIBRATION AND WEIGHT OF BATTERY BOX AND EXT POWER RELAY MOUNTED ON FIR	EWALL.  RECOMMENDATION TO PREVENT RECURRENCE IS TO FABRICATE STIFFENER TO EXTEND FROM COWL MOUNT TO UNDER BATTERY BOX BR	ACKET.		1	H	7	1 	3O			NT	3A12    					 
1997062600731	19970626	00731	CE  	1997	6	26	97ZZZX2924       	1	19970617	G	5541	04310043	RUDDER          			CESSNA	150   	150M        	2071830	CE  										FORWARD RIB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	6122K	4900 				15077536				AT ANNUAL INSPECTION, CRACKS WERE FOUND IN THE FORWARD RIB OF THE RUDDER AROUND THE TOP LIGHTNING HOLE.  PART WAS REMOVE	D AND REPLACED.  ANNUAL INSPECTIONS OF THIS AREA ARE RECOMMENDED.					1	H	7	1 	3O				3A19    					 
1997062600732	19970626	00732	GL  	1997	6	26	97ZZZX2925       	3	19970612	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER BOLTS	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	6529M	5646 	1750 			15284763		R77918		PROPELLER HAS CRACK APPROXIMATELY .50 INCH LONG AT BOLT HOLE.  FOUND DURING INSPECTION REQUIRED BY AD 97-06-16 AND SB 22	1B.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997062600733	19970626	00733	SW  	1997	6	26	97ZZZX2926       	1	19970520	G	2434	ALU8421	ALTERNATOR      			MOONEY	M20   	M20J        	5870219	SW  	CONT  	O360  	IO360A      	17025	SO  					HOUSING	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	658FT		190  		5081285	243270	L1170451A			FOUND ALTERNATOR HOUSING CRACKED AT THE FRONT MOUNTING ARM.  AFTER INSPECTING LIKE AIRCRAFT, FOUND A SECOND ALTERNATOR C	RACKED IN THE SAME LOCATION.  THE SUSPECT CAUSE FOR THE CRACK IS INCORRECT SHIMMING OF THE ALTERNATOR TO THE MOUNT.  SUB	MITTER STATED CLOSE ATTENTION NEEDS TO BE GIVEN TO THE CORRECT SHIMMING OF THE ALTERNATOR WHEN IT IS INSTALLED.				1	L	7	1 	3O	3	O		2A3     	E1CE				 
1997062600734	19970626	00734	CE  	1997	6	26	97ZZZX2927       	1	19970618	G	3260		SWITCH          			CESSNA	340   	340CESSNA   	2076404	CE  										RT MLG DOWNLOCK	WIRE BROKEN     	B			NVIR	L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			SW	05	69507					3400344				UPON GEAR EXTENSION, RT MAIN GEAR UNSAFE DOWN AND LOCK INDICATION WAS SHOWN.  GEAR APPEARED TO BE DOWN AND LOCKED AFTER 	A LOW FLY-BY OVER THE CONTROL TOWER.  AIRCRAFT LANDED WITH NO FURTHER INCIDENT.  FOUND BAD WIRE CONNECTIONS AT RT DOWN A	ND LOCK SWITCH.  RE-SOLDERED CONNECTIONS.  GEAR INDICATION AND OPERATIONAL CHECKS WERE GOOD.				1	L	7	2 	3O				3A25    					 
1997062600735	19970626	00735	CE  	1997	6	26	97ZZZX2928       	1	19970612	G	8120	085071239	HEADER ASSY     	GARRTT      	4066109025  	CESSNA	310   	T310R       	2074246	CE  										TURBO	HOLE BURNED     	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	777V	1200 				310R0267				SPECIAL INSPECTION OF EXHAUST SYSTEMS IAW AD 75-23-08-R5 AND CESSNA PILOTS ASSOCIATION LETTER 4-28-97 (URGENT LETTER TO 	OWNERS OF TURBOCHARGED TWIN CESSNAS).  THE HEADER HAD A HOLE BLOWN IN V-BAND CLAMP AREA.  THE BAFFLE IN HEADER WAS WARPE	D FROM HEAT AND CRACKED APPROXIMATELY 1 INCH AT THE BOTTOM.  THE TURBO WAS ALSO UNSERVICEABLE DUE TO MATING FLANGE BETWE	EN EXHAUST AND AIR SIDE BEING BLOWN.  SUBMITTER STATED SIMPLIFY OR MAKE CLEAR THE REQUIREMENTS.			1	L	7	2 	3O				3A10    					 
1997062600736	19970626	00736	CE  	1997	6	26	97ZZZX2929       	1	19970601	G	5540	12310349	RUDDER          			CESSNA	206   	U206F       	2073333	CE  										EMPENNAGE	MISRIGGED       	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	02	8146Q	1665 				U20603097				DURING AN ANNUAL INSPECTION, NOTICED THE SEAPLANE-TYPE RUDDER WOULD CONTACT THE ELEVATOR ASSEMBLY WHEN BOTH SURFACES WER	E POSITIONED APPROXIMATELY HALF THEIR TRAVEL.  ELEVATOR TRAVEL WAS DETERMINED TO BE CORRECT.  BECAUSE A SEAPLANE-TYPE RU	DDER WAS INSTALLED, RIGGING OF THE RUDDER WAS REFERENCED THROUGH THE CESSNA 206 SM.  THE SM MAKES ABSOLUTELY NO DISTINCT	ION BETWEEN RIGGING A STANDARD RUDDER AS OPPOSED TO A SEAPLANE RUDDER.			1	H	7	1 	3O				A4CE    					 
1997062600737	19970626	00737	SO  	1997	6	26	97ZZZX2930       	2	19970608	G	8530		CYLINDER        			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 5 AND NR 2	DEFECTIVE       	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4915R		1250 			18802432T				FOLLOWING TOP OVERHAUL, NOTED A KNOCK FROM CYLINDERS 5 AND 2.  FOUND NEW PISTONS WERE HITTING ON THE CYLINDER HEADS.  FO	UND THE CYLINDER HEAD TO BARREL DISTANCE IS SMALLER THAN OTHER CYLINDERS.					1	L	7	1 	3O	3	O		A9CE    	E5CE				 
1997062600738	19970626	00738	CE  	1997	6	26	97ZZZX2931       	1	19970501	G	3246	D3C259	HUB             			CESSNA	185   	A185F       	2072821	CE  										MLG WHEEL	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	1708R	2117 				18502430				AT TIRE CHANGE, WHEEL COMPONENTS WERE INSPECTED.  FOUND CENTER HUB CRACKED IN THREE PLACES.  RECOMMEND CAREFUL INSPECTIO	N.  MECHANIC/PILOT MADE NO HARD LANDINGS OR ROUGH FIELDS.					1	H	7	1 	3O				3A24    					 
1997062600739	19970626	00739	EA  	1997	6	26	97ZZZX2932       	1	19970601	G	3211	MS20009138	BOLT            			SCWZER	G164  	G164B       	3952802	EA  										LT MLG ATTACH	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	8097K	1016 				562B				PILOT WAS MAKING A TURN FOR TAKEOFF WITH A LOAD OF FERTILIZER WHEN LEFT GEAR COLLAPSED CAUSING DAMAGE TO PROPELLER AND L	ANDING GEAR BEAM, BRACKET ASSY, PN A1322-001, AND STUD ASSY, PN A1518-111.  CAUSE WAS SUSPECT DUE TO THE HEAD OF THE REA	R BOLT, PN MS20009-138 HAD BROKEN OFF CAUSING THE UPPER ATTACH POINT OF THE GEAR LEG TO FAIL.				1	Q	7	1 	3R				1A16    					 
1997070300132	19970703	00132	NE  	1997	7	3	97ZZZX2936       	1	19970609	G	2150	451400016	DRIVE BELT      			SKRSKY	S76   	S76         	8143010	NE  										AIR COND COMP	FAILED          	E				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NE	03	176SH	1851 				760182				BELT SPLIT CAUSING LOSS OF TENSION AND ALLOWING BELT TO JUMP OFF PULLEY DRIVE AND WEDGING BETWEEN MOTOR AND PULLEY; THUS	, CAUSING RUBBER SMELL AND SMOKE IN CABIN.  BELT WAS LAST INSPECTED FOR CONDITION 33.2 HRS AGO.  DATE OF LAST REPLACEMEN	T 8-11-92.  ITEM IS ON CONDITION.				1	G	7	2 	3U				H1NE    					 
1997070300134	19970703	00134	SW  	1997	7	3	97ZZZX2938       	1	19970515	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										FUEL QUANTITY	MALFUNCTION     	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407FC				0054	53050				FUEL QUANTITY INDICATOR STAYS IN TEST MODE FOR LONG PERIODS OF TIME.  REPLACED WITH NEW INDICATOR.						1	G	7	1 	3U			O	H2SW    					 
1997070300136	19970703	00136	CE  	1997	7	3	97ZZZX2939       	1	19970605	G	2910	306588003039	LINE ASSY       			RKWELL	NA265 	NA26540     	6402608	CE  										FS 367	CHAFED          	B	S		JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	316NT	11055				28260				DURING PYLON MATCHING ANGLES AND FUSELAGE SKIN INSPECTION, NOTED AN ADEL CLAMP, PN MS21919DG6, WAS BROKEN ON THE RIGHT H	AND SIDE FS 367.  FURTHER INSPECTION REVEALED THE THRUST REVERSER STOW HYDRAULIC PRESSURE LINE ASSY, PN 306-588003-039, 	HAD WORN THROUGH APPROXIMATELY HALF OF THE .035 INCH  WALL THICKNESS CAUSED BY THE BROKEN ADEL CLAMP AND RUBBING AGAINST	 THE ATTACH BRACKET.  RECOMMEND A ONE-TIME INSPECTION OF CLAMPS AND LINE ASSEMBLIES AND REINSPECTION EVERY 150 HOURS MAI	NTENANCE CHECK.		2	L	7	2 	4J				A2WE    					 
1997070300137	19970703	00137	SO  	1997	7	3	97ZZZX2940       	1	19970604	G	2820	3999710	HOSE ASSY       			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYSTEM	LEAKS           	B			WWKR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	4105D	5750 				318252027				HOSE ASSY LEAKS.  NOT AT FITTINGS, BUT IN MIDDLE OF HOSE.  HOSE HAS STAINLESS BRAID ON OUTSIDE WHICH LOOKS FINE, BUT RUB	BER IS DETERIORATED.					1	L	7	2 	3O				A20SO   					 
1997070300138	19970703	00138	EA  	1997	7	3	97ZZZX2941       	2	19970428	G	8530		VALVE           			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR2  CYL EXH	DEFORMED        	B			BJFR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	23	4182H					240656	L1938951A			AT 308 HRS SMOH, ANNUAL INSPECTION REVEALED NR 2 CYLINDER HAD NO COMPRESSION.  CYLINDERS WERE ECI CERMINIL CYLINDERS.  U	PON REMOVAL, FOUND EXHAUST VALVE AND SEAT DEFORMED.  NEW CYLINDER INSTALLED ALL OPS CHECK GOOD.  314 HRS SMOH, PILOT REP	ORTS AIRCRAFT SEEMS TO BE LOSING POWER.  COMPRESSION TEST REVEALED NR 3 CYLINDER COMPRESSON FAILING.  REMOVED NR 3 CYLIN	DER AND FOUND DAMAGE SIMILAR TO NR 2.  REMOVED NR 4 CYLINDER AND FOUND IRREGULAR WEAR MARKS.  LOG BOOK RESEARCH REVEALED	 NR 1 CYLINDER REMOVED AT 208 HRS DUE TO EXHAUST VALVE FAILURE.		1	L	7	1 	3O	3	O		2A3     	1E10				 
1997070300140	19970703	00140	EU  	1997	7	3	97ZZZX2943       	2	19970601	G	8520		ENGINE          			AMTR  	KITFOX	KITFOX      	05613LZ	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					REAR CYLINDER	SEIZED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NM	03	950AW					950	3971294			ENGINE SEIZED AFTER 2 HOURS OF FLIGHT OPERATION ON INITIAL FLIGHT.  ENGINE WAS STORED FOR 4 YEARS AND UNCRATED FOR 2 YEA	RS.  ENIGNE SHOWED SIGNS OF CORROSION ON OUTPUT SHAFT OF GEARBOX.  MANUFACTURER OF THE KIT SUPPLIED NO INFORMATION FOR L	ONG TERM STORAGE OF THE ENGINE.  THE REAR CYLINDER ROD LOST LUBRICATION, MADE METAL, AND SEIZED THE ENGINE.  LOWER ROD B	EARING COMPLETELY GONE AND ROD WAS HEAT DISCOLORED.  SUBMITTER SUGGESTED KIT MANUFACTURER BE REQUIRED TO SUPPLY ENGINE S	TORAGE AND PREPARATION INFORMATION.		1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1997070300195	19970703	00195	NM  	1997	7	3	97ZZZX2944       	1	19970606	G	5751	65464542	SKIN            			BOEING	737   	737*        		NM  										RT AILERON	DISBONDED       	B			HN6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			26300		BN206					AILERON SKIN DISBOND, 3-4 YEARS AFTER BOND REPAIR PERFORMED.  SUSPECT CAUSE:  BREAKDOWN OF BOND DUE TO REPORTED ENTRANCE	 OF WATER FROM LEADING AND TRAILING EDGES.  BOND FAILURE POSSIBLY DUE TO IMPROPER CLEANING PRIOR TO LAY-UP AND INSTALLAT	ION OF FIBERGLASS REPAIRS.  SUBMITTER RECOMMENDATIONS TO PREVENT RECURRENCE:  PERFORM REMEDIAL AND RECURRENT TRAINING OF	 TECHNICIANS ON PROPER/CORRECT FIBERGLASS BOND PRACTICES.  OPERATOR:  SOUTH AFRICAN AIRWAYS.			2	L	7	2 	4F			RT	A16WE   					 
1997070300196	19970703	00196	EU  	1997	7	3	97ZZZX2945       	1	19970609	G	5751	258WG2	AILERON         			BRAERO	DH125 	BAE125800A  	1500285	EU  										LEADING EDGE	WATER CONTAM    	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	354WG					NA0436				FOUND STAINS ON THE LT AND RT AILERON LEADING EDGES.  INVESTIGATED AND FOUND WATER SEEPING FROM AILERON LEADING EDGE FAS	TENER HOLES.  REMOVED NECESSARY FASTENERS TO DRAIN AND PURGED THE AILERON LEADING EDGE.  RE-INSTALLED BLIND FASTENERS WI	TH SEALANT PER FAA FROM J37 DATED 5-18-97.  SUBMITTER STATED IT IS VERY DIFFICULT TO DO A THOROUGH INSPECTION OF THE INT	ERNAL STRUCTURE OF THE LEADING EDGE TO LOOK FOR EVIDENCE OF CORROSION.  SUBMITTER STATED TO PREVENT THIS FROM HAPPENING,	 THOROUGHLY INSPECT THE AILERON LEADING EDGE GAP SEAL TO LOOK FOR VOIDS IN THE SEALANT AND ALSO TO INSPECT FASTENER HEAD	 CONDITION.	2	L	7	2 	4F			RT	A3EU    					 
1997070300197	19970703	00197	EU  	1997	7	3	97ZZZX2946       	1	19970609	G	5751	258WG1	AILERON         			BRAERO	DH125 	BAE125800A  	1500285	EU  										LEADING EDGE	WATER CONTAM    	B		A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	354WG					NA0436				FOUND STAINS ON THE LT AND RT AILERON LEADING EDGES.  INVESTIGATED AND FOUND WATER SEEPING FROM AILERON LEADING EDGE FAS	TENER HOLES.  REMOVED NECESSARY FASTENERS TO DRAIN AND PURGED THE AILERON LEADING EDGE.  RE-INSTALLED BLIND FASTENERS WI	TH SEALANT PER FAA FROM J37 DATED 5-18-97.  SUBMITTER STATED IT IS VERY DIFFICULT TO DO A THOROUGH INSPECTION OF THE INT	ERNAL STRUCTURE OF THE LEADING EDGE TO LOOK FOR EVIDENCE OF CORROSION.  SUBMITTER STATED TO PREVENT THIS FROM HAPPENING,	 THOROUGHLY INSPECT THE AILERON LEADING EDGE GAP SEAL TO LOOK FOR VOIDS IN THE SEALANT AND ALSO TO INSPECT FASTENER HEAD	 CONDITION.	2	L	7	2 	4F			RT	A3EU    					 
1997070300198	19970703	00198	NM  	1997	7	3	97ZZZX2947       	1	19970601	G	5330		SKIN            			BOEING	727   	727287      	1384020	NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	920PG					21688				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON INTERIOR SKIN AT STA 1030 (L-2 DOOR CUT-OUT) AT S10L.						2	L	7	3 	4F			RT	A3WE    					 
1997070300199	19970703	00199	NM  	1997	7	3	97ZZZX2948       	1	19970601	G	5311		FRAME CAP       			BOEING	727   	727287      	1384020	NM  										BS 1183 RT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	920PG					21688				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON 1183 BULKHEAD FRAME CAP RT SIDE AT S17R.						2	L	7	3 	4F			RT	A3WE    					 
1997070300200	19970703	00200	NM  	1997	7	3	97ZZZX2949       	1	19970601	G	5210		HINGE CAVITY    			BOEING	727   	727287      	1384020	NM  										R2 DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	920PG					21688				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON INSIDE OF UPPER HINGE CAVITY.						2	L	7	3 	4F			RT	A3WE    					 
1997070300201	19970703	00201	NM  	1997	7	3	97ZZZX2950       	1	19970616	G	2761	656952212	HOUSING         		65449617    	BOEING	737   	7372B7      	1384560	NM  										ACTUATOR	CRACKED         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		1054 	13315							CRACK WAS FOUND DURING INCOMING INSPECTION OF DRAG CONTROL ACTUATOR.						2	L	7	2 	4F				A16WE   					 
1997070300202	19970703	00202	CE  	1997	7	3	97ZZZX2951       	1	19970515	G	7722	8972052	RESISTOR        			CESSNA	441   	441         	2076020	CE  										NR 1 ENG EGT	FAULT           	D		A		E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	01	711GE	1487 			1510N	4410209				DURING ROUTINE CLIMB THROUGH 12,000 FEET, LOST POWER IN LT ENG, OBSERVED TORQUE AT 300 POUNDS AND EGT OVER RED LINE.  SH	UT DOWN NR 1 ENG AND SECURED.  DURING TROUBLESHOOTING, ISOLATED PROBLEM TO INTERMITTENT FAULT IN EGT COMPENSATING RESIST	OR.  A FAULT IN THIS SYS CAUSED ENG COMPUTER TO SENSE AN ERRONEOUS OVERTEMP CONDITION AND THE AUTOTEMP AND TORQUE FUNCTI	ON OF COMPUTER TAKES CONTROL OVER THE POWER LEVER.  HAD THIS OCCURRED AT TAKEOFF DURING ROTATION, CONTROL OF ACFT WOULD 	BE DIFFICULT AS NTS SYS WILL NOT SENSE A FAILURE WITH 300 POUNDS TORQUE AND THE ENG IS PRODUCING MORE DRAG THAN THRUST A	ND WILL NOT AUTOFEATHER.  THIS SITUATION CAN BE ISOLATED BY TURNING OFF AUTO TORQUE AND EGT FUNCTIONS OF THE COMPUTER.	1	L	7	2 	3T			RT	A28CE   					 
1997070300389	19970703	00389	NM  	1997	7	3	97ZZZX2952       	1	19970525	G	5730		SKIN            			BOEING	727   	72722       	1384002	NM  										BS 259.5-295	CORROSION       	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	400RG	38277				19149				DURING C-CHECK INSPECTION, DISCOVERED CORROSION COMMON TO THE LAP SEAM BETWEEN STA 259.5 AND STA 295 AND STR 24R.  REPAI	RED BY CLEANING OUT CORROSION PER SB 53-0072.  DUE TO EXTENT OF DAMAGE, THE LAP SEAM WAS REPAIRED USING REPAIR DOUBLERS 	AND FILLERS.  REPAIRED IAW EVERGREEN AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHORIZATION NR N400RG-53-04-EAC.				2	L	7	3 	4F				A3WE    					 
1997070300644	19970703	00644	CE  	1997	7	3	97ZZZX2955       	1	19970611	G	3710		PUMP            	SIGMATEK    		CESSNA	210   	P210N       	2073454	CE  										VAC SYSTEM	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	11	40RP		1700 			P21000041				DURING VFR FLIGHT, LOST AIR OPERATED INSTRUMENTS.  LANDED WITHOUT INCIDENT.  ENGINE TT, 1,700 HRS.						1	H	7	1 	3O				3A21    					 
1997070300645	19970703	00645	SO  	1997	7	3	97ZZZX2956       	1	19970605	G	3340	8517402	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										LANDING LIGHT	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	6072W					2820085				DURING A 100-HOUR INSPECTION, THE LANDING LIGHT SUPPORT WAS FOUND INSTALLED UPSIDE-DOWN PREVENTING THE CASE FROM DRAININ	G.  SUBMITTER SUGGESTS INATTENTION DURING RE-ASSEMBLY.  PLACARD THE PART 'THIS SIDE UP'.   ALIGN PROPERLY AND RIVET TO A	IR FILTER RETAINER.				1	L	7	1 	3O				2A13    					 
1997070300647	19970703	00647	CE  	1997	7	3	97ZZZX2958       	1	19970623	G	2820		FITTING         			BBAVIA	8     	8KCAB       	2110612	CE  										HEADER TANK	SEEP            	D	L	A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	8SC	1720 				58480				OWNER COMPLAINED OF FUEL SMELL IN THE COCKPIT.  FOUND A SEEP ON  THE EXIT FITTING, TOP OF HEADER TANK, UNDER DASH GOING 	TO THE FIREWALL SOV.  THIS TANK IS SUPPLIED BY BOTH WING TANKS.   FITTING IS A COMPRESSION TYPE, NOT AN AN-FLARE.  MECHA	NIC WENT TO SNUG IT UP AND FOUND THAT FUEL HAD SATURATED CARPET AND WAS DRIPPING OUT THE TAIL.  WHEN MECHANIC PUT A WREN	CH ON THE FITTING,  LINE BROKE CLEAN OFF SPRAYING FUEL AND FURTHER SOAKING COCKPIT.  WITH THE HEAD PRESSURE AT THIS POIN	T, IT SPRAYED UP AND BEHIND THE INSTR PANEL WHERE SEVERAL ELECTRICAL SWITCHES AND RADIOS ARE LOCATED.  SUBMITTER BELIEVE	S IF THE FLIGHT HAD STARTED, A FIRE WAS IMMINENT, EITHER AT START-UP OR DURING AEROBATICS, BOTH WITH THE SAME OUTCOME.	1	H	7	1 	3O				A21CE   					 
1997071000248	19970710	00248	NE  	1997	7	10	97ZZZX3013       	1	19970613	G	6210	641520601045	BLADE           			SKRSKY	S64   	S64F        		NE  										MAIN ROTOR	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC	1153 			64M65385921	64084				BLADE OPERATED BY ERICKSON FOR APPROXIMATELY 350.0 HOURS AND WAS REMOVED FOR A BLACK BIM INDICATION.  A NITROGEN LEAK WA	S DETECTED BETWEEN BLADE POCKETS NR 24 AND NR 25 ON THE LOWER SPAR SURFACE.  IT APPEARED TO ORIGINATE UNDER AN APPROVED 	MILITARY APPLIED PATCH.  THE PATCH WAS REMOVED AND ALSO POCKETS NR 24 AND NR 25.  A SEVERE GOUGE WAS NOTED AT THE AREA B	ETWEEN THE POCKETS.  IT APPEARS TO BE THE RESULT OF POOR WORKMANSHIP WHEN THE BLADE WAS REWORKED TO APPLY THE PATCH.  A 	CHORDWISE CRACK WAS FOUND AT THE BOTTOM OF THE GOUGED AREA APPROXIMATELY 1.75 INCHES IN LENGTH IN THE SPAR.  PART HAS BE	EN SCRAPPED.	2	G	7	2 	4U				H6EA    					 
1997071000249	19970710	00249		1997	7	10	97ZZZX3014       	4	19970130	G	6122	592444	IOC             			DHAV  	DHC4  	DHC4A       	2800304	EA  										RT ENG PROP GOV	FAILED          	G	L	A		E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			AL	03	702SC				538	126				INVESIGATION FOR PROPELLER OVERSPEED AND ENGINE FEATHER WHICH LED TO TERRAIN COLLISION, FOUND THE INDEPENDENT OIL CONTRO	L FAILURE.  RT ENGINE COWL COVERED WITH H-5606 FLUID.  LAST OVERHAUL 6-10-96.					2	H	7	2 	4R				1A19    					 
1997071000250	19970710	00250	NE  	1997	7	10	97ZZZX3015       	3	19970625	G	6111	SFA13M10A	BLADE           													HAMSTD	14SF	14SF7       	NE  	ZONE 3 STA 45	CRACKED         	B		A	PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05		21112	2746 		853671					RECEIVED PROPELLER BLADE ONLY.  REMOVED DEICER BOOT, FOUND FIBERGLASS CRACKED IN THE DEICER AREA ON THE LEADING EDGE NEX	T TO NICKEL SHEATH.  THE CRACK EXTENDED 2.50 INCHES FROM THE LEADING EDGE TOWARD THE TRAILING EDGE.  THE BLADE IS SHOWIN	G SIGNS OF TWISTING IN THIS AREA.														6	C	P7NE	 
1997071000251	19970710	00251		1997	7	10	97ZZZX3016       	2	19970625	G	7421	RHB32S	SPARK PLUG      	CHAMPION    																ELECTRODE	SPLIT           	B	S		CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17										CHAMPION SPARK PLUG RHB325S SIDE ELECTRODE HAS APPEARANCE OF DELAMINATION, USAGE IN LYCOMING OR CONTINENTAL NO DIFFERENC	E:  30 PLUS PLUGS THIS YEAR.																		 
1997071000252	19970710	00252	SO  	1997	7	10	97ZZZX3017       	2	19970624	G	7414	1051324	SPRING          			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  					MAG IMPULSE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										CUSTOMER COMPLAINED THAT UPON PERFORMING REAR ENGINE MAGNETO CHECK, ONE MAGNETO PRODUCED NO DROP, THE OTHER MAGNETO WOUL	D CAUSE ENGINE DECELERATE TO THE POINT OF STOPPING.  MAGNETO'S WERE REMOVED AND INSPECTED.  FOUND IMPULSE COUPLING SPRIN	G BROKEN.  THIS IS THE THIRD SUCH SPRING FOUND BROKEN IN ONE MONTH.				1	H	7	2 	3O	3	O		A6CE    	E1CE				 
1997071600004	19970716	00004	CE  	1997	7	16	97ZZZX3018       	1	19970619	G	3230	57412026	HOOK            			CESSNA	414   	414A        	2075907	CE  										LT MLG UPLOCK	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	135BG	5749 				414A0419				OLD UPLOCK HOOK CRACKED IN HOOK AREA.  NEW UNPLOCK HOOK ASSY PN 5141312-10 IS MUCH HEAVIER.  SUSPECT CAUSE WAS TIME AND 	NUMBER OF GEAR CYCLES.					1	L	7	2 	3O				A7CE    					 
1997071000253	19970710	00253	SO  	1997	7	10	97ZZZX3019       	1	19970520	G	3230	400111	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										RT MLG DOWNLOCK	FAILED          	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	25	333FS					274456				RIGHT LANDING GEAR COLLAPSED ON LANDING.  FOUND A BROKEN DOWNLOCK DRAG LINK BOLT.						1	L	7	2 	3O				1A10    					 
1997071000254	19970710	00254	CE  	1997	7	10	97ZZZX3020       	1	19970530	G	3231	08411066	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  										RT INBD DOOR	BROKE           	D	P	A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	05	391DJ	2187 				340A1250				RIGHT INBOARD DOOR BELLCRANK BROKE ON LANDING.  FURTHER INSPECTION FOR CAUSE FOUND RT MLG ROD PN 5045009-16 HAD A LOOSE 	JAMNUT AT INBOARD IDLER BELLCRANK.  POSSIBLE STRETCHING OF ROD END THREAD AND LENGTHENING OF ROD PLACED EXCESS TENSION O	N BELLCRANK.				1	L	7	2 	3O				3A25    					 
1997071000255	19970710	00255	CE  	1997	7	10	97ZZZX3021       	1	19970422	G	7931	070009937	LINE ASSY       			CESSNA	182   	TR182       	2072735	CE  										OIL PRESS GAUGE	LEAK            	D	L			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	4700S	1325 				R18201388				OIL LINE BETWEEN FIREWALL AND OIL PRESSURE GAUGE LEAKING OIL THROUGH TWO CORRODED PIN HOLES ONTO CARPET ON COPILOT SIDE.	  LOST APPROXIMATELY 3-4 QUARTS OF OIL.					1	H	7	1 	3O				3A13    					 
1997071000256	19970710	00256	EA  	1997	7	10	97ZZZX3022       	2	19970624	G	7322	30800	FLOAT           		HA6         	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					CARBURETOR	DEFECTIVE       	D		A		K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	6303V	19   			DL0198	172RG0615				PILOTS REPORT EXCESS MAGNETO DROPS OF GREATER THAN 300 RPM'S AND SEVERE ENGINE ROUGHNESS.  THE FLOAT IN THE CARBURETOR W	AS REMOVED AND FOUND THAT THE REAR-MOST CHAMBER WAS FILLED WITH FUEL.  FLOAT IS A PLASTIC DESIGN WITH 3 VISABLE CHAMBERS	.  THE CHAMBER THAT WAS FULL OF FUEL WAS THE ONE CLOSEST TO THE NEEDLE VALVE.  UPON INSTALLING A SERVICEABLE FLOAT, ENGI	NE OPERATED NORMALLY.			1	H	7	1 	3O	3	O		3A17    	E286				 
1997071000257	19970710	00257	SO  	1997	7	10	97ZZZX3023       	1	19970606	G	3250	3945902	MOUNT ASSY      			PIPER 	PA34  	PA34220T    	7103420	SO  										NLG STEERING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8287U	7325 				348333027				LOWER TAB OF MOUNT BRACKET PN 39459-02 FOR STEERING ARM ASSY OF NOSE GEAR WAS FOUND BROKEN AWAY FROM BRACKET ASSY.  THIS	 DEFECT WAS DISCOVERED DURING AN INSPECTION AS A RESULT OF NOSE STEERING PROBLEM.  THIS DEFECT IS A RESULT OF AGE/METAL 	FATIGUE AND/OR OVERSTEERING USING TUG FROM ANOTHER AIRPORT LOCATION. SUBMITTER SUGGESTS CLOSE LOOK AT EVERY OPPORTUNITY 	IF ANY NOTABLE STEERING PROBLEM.			1	L	7	2 	3O				A7SO    					 
1997071000258	19970710	00258	SO  	1997	7	10	97ZZZX3024       	1	19970527	G	3710	212CW	PUMP            	AIRBORNE    		PIPER 	PA34  	PA34220T    	7103420	SO  										VACUUM SYSTEM	SHAFT FAILED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8404X		98   		9AM2818	348133146				INSTALLED NEW VACUUM PUMP: WITHIN 98 HOURS, PUMP WAS INOPERABLE.  CAUSE WAS BROKEN PUMP TO GEAR DRIVESHAFT TWISTED OFF. 	 CHECKED AND FOUND NO ENGINE STOPPAGE OR INTERNAL PROBLEM WITH ENGINE TO CAUSE BROKEN SHAFT.  SUSPECT CAUSE - VANE IN PU	MP STOPPED PUMP ROTATION.				1	L	7	2 	3O				A7SO    					 
1997071000259	19970710	00259	SO  	1997	7	10	97ZZZX3025       	2	19970407	G	8520		CRANKSHAFT      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360KB  	17025	SO  					NR 1 ROD CHEEK	BROKE           	B			MW2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	83878					348133097	233941H			CRANKSHAFT BROKE AT NR 1 ROD CHEEK RESULTING IN ENGINE FAILURE.  ENGINE HAD A VAR CRANKSHAFT INSTALLED SN J159203.  TT 3	,295 HOURS.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1997071000260	19970710	00260	SO  	1997	7	10	97ZZZX3026       	1	19970606	G	3250	3945902	MOUNT ASSY      			PIPER 	PA34  	PA34220T    	7103420	SO  										NLG STEERING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8449T	5863 				348133272				THE LOWER MOUNTING TAB FOR PN 95061-28 BUSHING AND PN 95395-00 STEERING ARM ASSY WAS FOUND COMPLETELY CRACKED AND HAD SE	PARATED FROM THE ENTIRE ASSY (PN 39459-02) CAUSING LOSS OF NOSE WHEEL STEERING.  SUBMITTER SUGGESTED CAUSE DUE TO METAL 	FATIGUE.  RECOMMENDATION FOR PREVENTION WOULD BE CLOSE INSPECTION OF THE ENTIRE MOUNT ASSY AND DYE PENETRANT TEST AT REG	ULAR INSPECTIONS OR STRENGTHEN STRUCTURE.			1	L	7	2 	3O				A7SO    					 
1997071000261	19970710	00261	NM  	1997	7	10	97ZZZX3027       	1	19970619	G	3213	65221125	STRUT           			BOEING	707   	707320C     	1383668	NM  										MLG	CRACKED         	B			VQ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1871					THE TWO 707 MLG INNER CYLINDERS WERE RECEIVED FOR EVALUATION IN SERVICEABLE CONDITION.  DURING MAGNETIC PARTICLE INSPECT	ION, NUMEROUS REGIONS OF UNTEMPERED AND OVERTEMPERED MARTENSITE WITH LADDER CRACKS WERE FOUND UNDER THE CHROME PLATING. 	 PN 65-22112-1, SN 1871.  PN 65-22112-5, SN 2624.  NORTHROP RUMM AN W/O:  314848 AND W/O 314847.				2	L	7	4 	4F				4A26    					 
1997071000262	19970710	00262	NM  	1997	7	10	97ZZZX3028       	1	19970619	G	3213	65221125	STRUT           			BOEING	707   	707320C     	1383668	NM  										MLG	CRACKED         	B			VQ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					2624					THE TWO 707 MLG INNER CYLINDERS WERE RECEIVED FOR EVALUATION IN SERVICEABLE CONDITION.  DURING MAGNETIC PARTICLE INSPECT	ION, NUMEROUS REGIONS OF UNTEMPERED AND OVERTEMPERED MARTENSITE WITH LADDER CRACKS WERE FOUND UNDER THE CHROME PLATING. 	 PN 65-22112-1, SN 1871.  PN 65-22112-5, SN 2624.  NORTHROP RUMM AN W/O:  314848 AND W/O 314847.				2	L	7	4 	4F				4A26    					 
1997071000263	19970710	00263	NM  	1997	7	10	97ZZZX3029       	1	19970619	G	3230	65588324	BEAM            			BOEING	707   	707320C     	1383668	NM  										MLG ACTUATOR	CRACKED         	B			VQ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										THE 707 MLG ACTUATOR BEAM WAS RECEIVED FOR OVERHAUL.  VISUAL INSPECTION REVEALED A LARGE CRACK AT THE SUPPORT LINK ATTAC	H LUG.  THE CRACK WAS DETECTED THROUGH THE PAINT.  NORTHROP GRUMMAN W/O:  314846					2	L	7	4 	4F				4A26    					 
1997071000264	19970710	00264	NM  	1997	7	10	97ZZZX3030       	1	19970619	G	3230	6552361	SUPPORT LINK    			BOEING	707   	707320C     	1383668	NM  										ACTUATOR BEAM	CRACKED         	B			VQ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										THE 707 SUPPORT LINK WAS RECEIVED FOR OVERHAUL WITH 2 CRACKS AT THE HANGER ATTA CH REGION.  THE CRACKS WERE FOUND DURING	 PENETRANT INSPECTION AFTER THE REMOVAL OF THE BUSHINGS AND PAINT.  NORTHOP GRUMMAN W/O: 314847.					2	L	7	4 	4F				4A26    					 
1997071000265	19970710	00265	NM  	1997	7	10	97ZZZX3031       	1	19970619	G	3213	6532855	SIDE STRUT      			BOEING	707   	707320C     	1383668	NM  										MLG	CRACKED         	B			VQ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										THE 707 MLG SIDE STRUT WAS RECEIVED FOR OVERHAUL.  AFTER BUSHING REMOVAL AND PAINT REMOVAL, PEENTRANT INSPECTION DETECTE	D TWO 3-INCH CRACKS AT THE CENTER SECTION (WEB REGION).					2	L	7	4 	4F				4A26    					 
1997071000266	19970710	00266	NE  	1997	7	10	97ZZZX3032       	2	19970620	G	7322	7923801	FLAPPER NOZZLE  		7863927     						PWA   	120   	PW120       		NE  					FCU	CLOGGED         	B			BN4R	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	05		139  			F21454					REFERENCE:  FW05670.  ENGINE SHUT-DOWN IN FLIGHT.  SUSPECT TBD - SCREEN ON POSITIVE FLAPPER NOZZLE BECAME CLOGGED WITH C	ONTAMINATION.  SUBMITTER RECOMMENDS FUEL CONTROL BE OVERHAULED.  OPERATOR OF AIRCRAFT HAS BEEN NOTIFIED OF FUEL SYSTEM C	ONTAMINATION.  CUSTOMER:  MAYA AIRLINES THROUGH PWC SERVICE CENTER (MONTREAL).									4	T			E20NE				 
1997071000267	19970710	00267	EU  	1997	7	10	97ZZZX3033       	1	19970620	G	3250	632010	SWITCH          		EA18D12     	ISRAEL	1124  	1124        	4500102	EU  										STEERING VALVE	FAILED          	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	1124F	20   			IL153	281				INSTALLED OVERHAULED STEERING VALVE ASSY.  20 HOURS LATER, STEERING VALVE FAILED.  TROUBLESHOT, FOUND BAD PRESSURE SWITC	H.  INSTALLED NEW PRESSURE SWITCH AND STEERING WAS STILL INOPERABLE.  FOUND SWITCH WAS LOOSING CONTACT WHEN SWITCH WAS D	EPRESSED ALL THE WAY.  INSTALLED ANOTHER PRESSURE SWITCH FOR STEERING VALVE ASSY.  PERFORMED OPERATIONAL AND CHECKED SAT	ISFACTORY.			2	M	7	2 	4F				A2SW    					 
1997071000269	19970710	00269	EA  	1997	7	10	97ZZZX3035       	2	19970605	G	7200		ENGINE          			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					RT ENGINE	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SW	01	35062		2750 			429	PCE40881			RIGHT ENGINE QUIT WHEN POWER WAS REDUCED TO IDLE.  ENGINE WAS REMOVED AND REPLACED, AIRCRAFT RETURNED TO SERVICE.  AWAIT	ING TEAR-DOWN REPORT.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997071000270	19970710	00270	CE  	1997	7	10	97ZZZX3036       	1	19970623	G	3213	508102903	STRUT           			BEECH 	90    	B90         	1152912	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	48A		629  			LJ381				A CRACK WAS FOUND IN THE FILLET AREA ABOVE THE PIVOT OF THE TOP SCISSOR ARM.						1	L	7	2 	3T				3A20    					 
1997071000271	19970710	00271	CE  	1997	7	10	97ZZZX3037       	1	19970601	G	5260	551124411	BRACKET         			CESSNA	500   	500CESSNA   	2076602	CE  										STEP STOP	BENT            	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	58TC					5000261				THE BRACKET WAS BENT DOWN FROM STEP BEING PUSHED UP TOO FAR AND ANCHOR NUTPLATES HAVE CRACKS IN SKIN BETWEEN RIVETS.						1	L	7	2 	4F				A22CE   					 
1997071000272	19970710	00272	CE  	1997	7	10	97ZZZX3038       	1	19970623	G	2150	11791006013	BRACKET         			BEECH 	B300  	B300        	1159232	CE  										AIR CONDITIONER	CRACKED         	B	S		KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	65CR					FL60				AIR CONDITIONER BRACKET CRACKED.  THIS IS THE UPDATED BRACKET MADE OUT OF STEEL.  WHEN BRACKET WAS MADE OUT OF ALUMINUM,	 HAD ALOT OF FAILURES ALL IN THE SAME AREA.					2	L	7	2 	4T			RT	A24CE   					 
1997071000273	19970710	00273	EU  	1997	7	10	97ZZZX3039       	1	19970425	G	3241	9542653	DETECTOR        			AMD   	FALC10	FALCON10    	2730101	EU  										ANTI SKID	SHORTED         	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	908RF	2500 				46				UPON LANDING, ACFT PULLED RIGHT AND DEPARTED RUNWAY.  MAINTENANCE FOUND NR 2 DETECTOR (TACH GEN) FOR THE ANTI-SKID SYSTE	M HAD 'SHORTED OUT' WHERE THE WIRES ENTER THE CONNECTOR.   THE DEAD SHORT APPARENTLY CAUSED THE CONTROL BOX TO READ A SK	ID SITUATION AND PREVENTED BRAKE PRESSURE FROM BEING APPLIED TO THE LEFT BRAKE.  SUBMITTER RECOMMENDS THAT SPECIAL ATTEN	TION BE GIVEN TO THIS AREA DURING INSP DUE TO THE ENVIRONMENT, ETC.  SUBMITTER ALSO SUSPECTED THE PROBLEM WAS LIKELY DUE	 TO POOR MAINTENANCE PRACTICES WHEN THIS CONNECTOR WAS PREVIOUSLY REPAIRED.  APPARENTLY THE WIRE INSULATION WAS STRIPPED	 BACK TOO FAR EXPOSING WIRES.	2	L	7	2 	4F				A33EU   					 
1997071000276	19970710	00276	WP  	1997	7	10	97ZZZX3040       	2	19970611	G	7230	8945283	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										INSPECTION FOUND 1 EACH VANE AIR PASSAGE CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET ME	TAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS, I	T IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000277	19970710	00277	WP  	1997	7	10	97ZZZX3041       	2	19970612	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					7E081					INSPECTION FOUND 2 EACH VANE AIR PASSAGES CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET M	ETAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS I	T IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000278	19970710	00278	WP  	1997	7	10	97ZZZX3042       	2	19970616	G	7230	89452810	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										INSPECTION FOUND 14 EACH VANE AIR PASSAGES CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET 	METAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS,	 IT IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  REJECT.									3	T			E2WE				 
1997071000279	19970710	00279	WP  	1997	7	10	97ZZZX3043       	2	19970611	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					7E048					INSPECTION FOUND 2 EACH VANE AIR PASSAGES CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET M	ETAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS, 	IT IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000280	19970710	00280	WP  	1997	7	10	97ZZZX3044       	2	19970611	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					4083782597					INSPECTION FOUND 1 EACH VANE AIR PASSAGE CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET ME	TAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS, I	T IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000281	19970710	00281	WP  	1997	7	10	97ZZZX3045       	2	19970611	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					6C090					INSPECTION FOUND 1 EACH VANE AIR PASSAGE CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET ME	TAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS, I	T IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000282	19970710	00282	WP  	1997	7	10	97ZZZX3046       	2	19970611	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					7C098					INSPECTION FOUND 5 EACH VANE AIR PASSAGES CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET M	ETAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS, 	IT IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000283	19970710	00283	WP  	1997	7	10	97ZZZX3047       	2	19970616	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					4083782083					INSPECTION FOUND 12 EACH VANE AIR PASSAGES CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET 	METAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS,	 IT IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  REJECT.									3	T			E2WE				 
1997071000284	19970710	00284	WP  	1997	7	10	97ZZZX3048       	2	19970611	G	7230	8945286	STATOR VANE     								GARRTT	TPE331	TPE331*     	01514	WP  					2ND STAGE	CLOGGED         	B	S		XWMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					7D084					INSPECTION FOUND 5 EACH VANE AIR PASSAGES CLOGGED.  CLOGGED VANE AIR PASSAGES CAN RESTRICT COOLING AIR TO CENTER SHEET M	ETAL SEAL SUPPORT.  THIS COULD BE A CONTRIBUTING FACTOR IN THE FAILURE OF THE SEAL SUPPORT.  IF THE SEAL SUPPORT FAILS, 	IT IS LIKELY THAT A CATASTROPHIC FAILURE WILL OCCUR.  SUBMITTER RECOMMENDATION:  MODIFICATION TO -10.									3	T			E2WE				 
1997071000285	19970710	00285	NE  	1997	7	10	97ZZZX3049       	2	19970624	G	7261	30722311	HOUSING         			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7313B    	01518	NE  					OIL FILTER	CRACKED         	D	S	A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	2606	2885 				650194	P87488			AFTER LANDING DURING THE CREWS TRANSIENT WALK-AROUND, FOUND THE LT ENGINE OIL QUANTITY ONE AND ONE-HALF QUARTS LOW.  THE	 OIL WAS FULL BEFORE THE 2-1/2 HOUR FLIGHT.  FURTHER INVESTIGATION REVEALED A CRACKED OIL FILTER HOUSING PN 3072231-1. A	LSO, FOUND A CRACKED ATTACH BRACKET PN 3071943-1.  MPI'S WERE JUST COMPLETED 87 HOURS AGO.  THE CREW NOTED NO ABNORMAL O	IL RPESSURE OR VIBRATION INDICATIONS.  THE OIL FILTER HOUSING WAS REPLACED AND A VIBRATION SURVEY WAS COMPLETED WITH NO 	ABNORMAL FINDINGS.		2	L	7	2 	4F	4	F		A9NM    	E6WE				 
1997071700103	19970717	00103	NM  	1997	7	17	97ZZZX3066       	1	19970601	G	5320	65198618	T CHORD         			BOEING	727   	72730       	1384008	NM  										BS 320 S26R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	357KP					20675				DURING C-CHECK INSPECTION, CORROSION NOTED ON T-CHORD BETWEEN STA 320 AND STA 350 AT S26R.						2	L	7	3 	4F				A3WE    					 
1997071700104	19970717	00104	NM  	1997	7	17	97ZZZX3067       	1	19970616	G	2913	42086	PUMP            	ABEX        		DORNER	DO32  	DO328100    	2996000	NM  										HYDRA SYSTEM	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	09	653PC	1570 			4476	3027				INBOUND, MAIN HYDRA PUMP FAILED.  MADE NORMAL LANDING WITH BACK-UP AUXILIARY PUMP.  INSPECTED MOTOR PUMP ASSY, FOUND POW	ER BREAKERS TRIPPED.  RESET AND OPS CHECKED SYSTEM, BREAKERS TRIPPED, UNIT REMOVED.  INSTALLED REPAIRED UNIT.  OPS CHECK	 WAS GOOD.  AIRCRAFT RETURNED TO SERVICE.  NOTE:  MAIN HYDRA SYSTEM IS 115 VAC MOTOR PUMP ASSY DRIVEN BY ENGINE ALTERNAT	ORS.			2	H	7	2 	4T			RT	A45NM   					 
1997071700107	19970717	00107		1997	7	17	97ZZZX3070       	4	19970106	G	6122	C290D3KT12	PROP GOVERNOR   			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	MISINSTALLED    	D	S			A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	07	52945				840366	177RG1316	L185651A			THE CESSNA SM AND LYC ENGINE OVERHAUL DO NOT CONTAIN THE REQUIREMENT TO USE A PROPELLER GOV PAD PLATE, PN LW-12347, WHEN	 INSTALLING A MCCAULEY GOVERNOR ON LYC 4 OR 6 CYLINDER ENGINE WITH REAR MOUNTED DUEL MAG INSTALLATIONS. THIS PLATE WAS L	EFT OUT DURING REINSTALLATION OF THE ENGINE AND THE ACFT MADE A FORCED LANDING DUE TO LOSS OF ENGINE OIL THROUGH THE GOV	ERNOR ADAPTER PLATE SCREW.			1	H	7	1 	3O	3	O		A20CE   	1E10				 
1997071700108	19970717	00108	SO  	1997	7	17	97ZZZX3071       	2	19970609	G	8520		CONNECT ROD     			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					2 AFT CYLINDERS	FAILED          	G				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			GL	23	30AW					18502369	559733			THE TWO REAR OPPOSING CYLINDERS FAILED; THUS, PUNCHING HOLES INTO THE ENGINE BLOCK.  THIS CAUSED SMOKE IN COCKPIT (CASE)	 FOLLOWED BY EMERGENCY LANDING.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
1997071700109	19970717	00109	CE  	1997	7	17	97ZZZX3072       	1	19970625	G	7921	629116	GASKET          			CESSNA	421   	421C        	2076016	CE  										OIL COOLER	TORN            	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	321FL	242  				421C0207				AIRCRAFT CAME IN WITH RIGHT ENGINE LEAKING OIL.  FOUND LEAK BETWEEN OIL COOLER AND CASE.  WHEN COOLER PULLED AWAY FROM C	ASE, GASKET HAD A STRAIGHT LINE TEAR AND PART 'OF 1 SIDE OF GASKET ON CASE, OTHER ON COOLER.  THE REST OF THE GASKET HAD	 UNEVEN MARKS LIKE BEING TORN'  WHEN COOLER WAS REMOVED.				1	L	7	2 	3O				A7CE    					 
1997071700110	19970717	00110	NM  	1997	7	17	97ZZZX3073       	1	19970618	G	7120	300022501AF	MOUNT           			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					ENG MOUNT 'V'	CHAFED THROUGH  	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	6894G	34488				600905816125	L2097248A			LOWER MOTOR MOUNT 'V' AT MIDDLE ATTACH FITTING WAS FOUND CHAFED COMPLETELY THROUGH THE WALL OF TUBING (APPROXIMATELY 20 	PERCENT OF DIAMETER OF TUBE) BY P/N 920029-01 FLEX DUCT.  SUBMITTER STATED THIS PROBLEM IS REPEATEDLY SEEN ON ALL MODEL 	AEROSTAR.  RECOMMEND THOROUGH INSPECTION OF AREA.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997071700111	19970717	00111	SO  	1997	7	17	97ZZZX3074       	1	19970618	G	7112		BAFFLE          			PIPER 	PA32  	PA32R300    	7103213	SO  										ENG FWD LT	CHAFED          	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9253N	272  				3213100				DURING ANNUAL INSPECTION, FOUND PROPELLER CONTROL ATTACH BOLT AT GOVERNOR RUBBING ON ENGINE BAFFLE.  IF LEFT ALONE, BAFF	LE COULD WEAR THROUGH CAUSING PROPELLER CONTROL TO JAM AT A SELECTION OTHER THAN FULL RPM.  A BRACKET WAS MANUFACTURED T	O KEEP BAFFLE CLEAR.  SUBMITTER STATED PIPER SHOULD RE-DESIGN OR PUT OUT SB TO RECTIFY PROBLEM.  SUBMITTER STATED THIS I	S 4TH AIRCRAFT WITH THIS CONDITION.			1	L	7	1 	3O				A3SO    					 
1997071700112	19970717	00112	SO  	1997	7	17	97ZZZX3075       	1	19970607	G	2750	6270600	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP LEVER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	9500W	5848 				PA2822921				WHILE C/W WITH PIPER SB NR 965, FOUND FLAP HANDLE MOUNTING BRACKET CRACKED IN 4 PLACES.  NOTE:  THERE WAS NO MECHANICAL 	REASON FOUND FOR SB NR 965.					1	L	7	1 	3O				2A13    					 
1997071700113	19970717	00113	SO  	1997	7	17	97ZZZX3076       	1	19970625	G	5521	4007516	SPAR            			PIPER 	PA31  	PA31325     	7103105	SO  										ELEVATOR	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	979SD	4089 				317812015				WHILE DOING REPETATIVE INSPECTION OF PIPER SB 998 WITH BORESCOPE, FOUND .75 INCH LONG CRACK IN TOP OUTBOARD SPAR.  CRACK	 WAS NOT THERE 100 HRS AGO.  100 HOURS AGO HOLES WERE CUT PER SB 998.					1	L	7	2 	3O				A20SO   					 
1997071700114	19970717	00114	SO  	1997	7	17	97ZZZX3077       	1	19970619	G	7920	6240008D0290	HOSE            			PIPER 	PA36  	PA36285     	7103610	SO  										ENGINE OIL	LEAK            	B			CKYR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03	9986P					367560101				FOUND MASSIVE OIL LEAK REAR OF ENGINE.  RAN ENGINE AFTER CLEANING AND OIL SPRAYING OUT OF HOSE.  HOSE HAD A FIRE SLEEVE 	INSTALLED OR A FIRE WOULD HAVE STARTED IN THE ENGINE COMPARTMENT.  AD 95-26-13 SHOULD BE REVISED TO INCLUDE PA-36 IN ITS	 APPLICATION, ALSO, PA-25.  HOSE REPLACED.				1	L	7	1 	3O				A10SO   					 
1997071700116	19970717	00116		1997	7	17	97ZZZX3078       	4	19970502	G	3418	66082639	STALL COMPUTER  			LEAR  	35    	35A         	5170602	CE  										STALL WARNING	INTERMITTENT    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	152TJ				01520	243				RECEIVED REPAIRED STALL WARNING COMPUTER PN 6608263-9 FROM LEARJET PARTS.  INSTALLED IN AIRCRAFT, UNIT WAS INTERMITTENT 	ON SEVERAL SETTINGS.  UNABLE TO CALIBRATE SYSTEM, REMOVED, REPLACED WITH SECOND REPAIRED UNIT SAME PART NUMBER.  SECOND 	UNIT FUNCTIONED PROPERLY.  RETURNED FIRST UNIT FOR WARRANTY.				2	L	7	2 	4F				A10CE   					 
1997071700117	19970717	00117	CE  	1997	7	17	97ZZZX3079       	1	19970624	G	2722	4006719	SERVO           	HONEYWELL   		CESSNA	650   	650         	2076802	CE  										RUDDER	FAILED          	D		A		O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	21	2605		1597 		87103491	6500144				DURING APPROACH, CREW NOTICED RUDDER OPERATION WAS EXTREMELY STIFF IN BOTH DIRECTIONS.  MAINT INVESTIGATION VERIFIED RUD	DER TRAVEL WAS FULL, BUT VERY STIFF WITH OR WITHOUT ELECTRIC POWER.  OCCASIONALLY, STIFFNESS WOULD BREAK FREE, THEN RE-E	NGAGE.  THE RUDDER SERVO WAS DISCONNECTED AND FREE MOVEMENT RESTORED.  THE RUDDER SERVO DRIVE OUTPUT CLUTCH WAS FULLY EN	GAGED.  THE RUDDER SERVO DRIVE WAS REPLACED.  SUBMITTER STATED THIS CONDITION COULD HAVE BEEN A DANGEROUS SITUATION HAD 	THERE BEEN A CROSSWIND OR WHERE RUDDER INPUT WAS REQUIRED.		2	L	7	2 	4F				A9NM    					 
1997071700118	19970717	00118	NE  	1997	7	17	97ZZZX3080       	2	19970618	G	7200		ENGINE          			LEAR  	24    	24D         	5170311	CE  	GE    	CJ610 	CJ6106      	30006	NE  					POWER SECTION	FLAME OUT       	G				O	B			OTHER                   	EMER. DESCENT           			X			ENGINE FLAMEOUT           			CR	CRUISE         	1			GL	15	295NW					295	251712A			IN-FLIGHT FLAME OUT AT 45,000 FEET.  DESCENDED TO 23,000 FEET, RESTARTED, CLIMBED TO 43,000 FEET.  SUBMITTER STATED THIS	 OCCURRENCE IS COMMON TO LEAR 24 DXR'S.  NO DEFECT NOTED.					2	L	7	2 	4J	4	J		A10CE   	1E16				 
1997071700119	19970717	00119	CE  	1997	7	17	97ZZZX3081       	1	19970627	G	5320	551124914	FRAME           			CESSNA	500   	500CESSNA   	2076602	CE  										THRESHOLD OTBD	CRACKED         	G	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	58TC	6319 				5000261				DURING INSPECTION, A  REPAIR STATION DISCOVERED A CRACK IN THE LOWER DOOR FRAME.   CLOSER INSP NOTED CRACK EMANATED FROM	 THE HOLES DRILLED FOR INSTALLATION OF A NUTPLATE (FOR THE DOOR STEP INSTALLATION, AFT ATTACH POINT).  NOTED NUMEROUS CR	ACKS THROUGHOUT THIS AND SEVERAL OTHER PIECES OF THE LOWER DOOR FRAME ASSY.  THERE WERE A NUMBER OF HOLES DRILLED THAT D	ID NOT HAVE PROPER EDGE DISTANCE SOME OF WHICH WERE AROUND THE 2 HOLES FOR THE MAIN CABIN DOOR BOTTOM RETAINING PINS.  S	UBMITTER STATED IT APPEARS THESE DEFICIENCIES WERE CAUSED DURING ORIG MANUFACTURE AS THERE IS NO EVIDENCE THIS AREA HAS 	BEEN REWORKED.  THESE  AREAS ARE NOW MANIFESTING THEMSELVES AS CRACKS.  ACFT HAS 6,319 HRS TIME IN SERVICE AS OF 6-24-97	1	L	7	2 	4F				A22CE   					 
1997071700120	19970717	00120	CE  	1997	7	17	97ZZZX3082       	1	19970627	G	5320	55112493	FRAME           			CESSNA	500   	500CESSNA   	2076602	CE  										THRESHOLD INBD	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	58TC	6319 				5000261				DURING INSPECTION, A  REPAIR STATION DISCOVERED A CRACK IN THE LOWER DOOR FRAME.   CLOSER INSP NOTED CRACK EMANATED FROM	 THE HOLES DRILLED FOR INSTALLATION OF A NUTPLATE (FOR THE DOOR STEP INSTALLATION, AFT ATTACH POINT).  NOTED NUMEROUS CR	ACKS THROUGHOUT THIS AND SEVERAL OTHER PIECES OF THE LOWER DOOR FRAME ASSY.  THERE WERE A NUMBER OF HOLES DRILLED THAT D	ID NOT HAVE PROPER EDGE DISTANCE SOME OF WHICH WERE AROUND THE 2 HOLES FOR THE MAIN CABIN DOOR BOTTOM RETAINING PINS.  S	UBMITTER STATED IT APPEARS THESE DEFICIENCIES WERE CAUSED DURING ORIG MANUFACTURE AS THERE IS NO EVIDENCE THIS AREA HAS 	BEEN REWORKED.  THESE  AREAS ARE NOW MANIFESTING THEMSELVES AS CRACKS. ACFT HAS 6,319 HRS TIME IN SERVICE AS OF 6-24-97.	1	L	7	2 	4F				A22CE   					 
1997071700121	19970717	00121	CE  	1997	7	17	97ZZZX3083       	1	19970627	G	5320	551123937	CHANNEL         			CESSNA	500   	500CESSNA   	2076602	CE  										LOWER FRAME	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	58TC	6319 				5000261				DURING INSPECTION, A  REPAIR STATION DISCOVERED A CRACK IN THE LOWER DOOR FRAME.   CLOSER INSP NOTED CRACK EMANATED FROM	 THE HOLES DRILLED FOR INSTALLATION OF A NUTPLATE (FOR THE DOOR STEP INSTALLATION, AFT ATTACH POINT).  NOTED NUMEROUS CR	ACKS THROUGHOUT THIS AND SEVERAL OTHER PIECES OF THE LOWER DOOR FRAME ASSY.  THERE WERE A NUMBER OF HOLES DRILLED THAT D	ID NOT HAVE PROPER EDGE DISTANCE SOME OF WHICH WERE AROUND THE 2 HOLES FOR THE MAIN CABIN DOOR BOTTOM RETAINING PINS.  S	UBMITTER STATED IT APPEARS THESE DEFICIENCIES WERE CAUSED DURING ORIG MANUFACTURE AS THERE IS NO EVIDENCE THIS AREA HAS 	BEEN REWORKED.  THESE  AREAS ARE NOW MANIFESTING THEMSELVES AS CRACKS. ACFT HAS 6,319 HRS TIME IN SERVICE AS OF 6-24-97.	1	L	7	2 	4F				A22CE   					 
1997071700122	19970717	00122	CE  	1997	7	17	97ZZZX3084       	1	19970627	G	5320	551124913	STIFFENER       			CESSNA	500   	500CESSNA   	2076602	CE  										DOOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	58TC	6319 				5000261				DURING INSPECTION, A  REPAIR STATION DISCOVERED A CRACK IN THE LOWER DOOR FRAME.   CLOSER INSP NOTED CRACK EMANATED FROM	 THE HOLES DRILLED FOR INSTALLATION OF A NUTPLATE (FOR THE DOOR STEP INSTALLATION, AFT ATTACH POINT).  NOTED NUMEROUS CR	ACKS THROUGHOUT THIS AND SEVERAL OTHER PIECES OF THE LOWER DOOR FRAME ASSY.  THERE WERE A NUMBER OF HOLES DRILLED THAT D	ID NOT HAVE PROPER EDGE DISTANCE SOME OF WHICH WERE AROUND THE 2 HOLES FOR THE MAIN CABIN DOOR BOTTOM RETAINING PINS.  S	UBMITTER STATED IT APPEARS THESE DEFICIENCIES WERE CAUSED DURING ORIG MANUFACTURE AS THERE IS NO EVIDENCE THIS AREA HAS 	BEEN REWORKED.  THESE  AREAS ARE NOW MANIFESTING THEMSELVES AS CRACKS. ACFT HAS 6,319 HRS TIME IN SERVICE AS OF 6-24-97.	1	L	7	2 	4F				A22CE   					 
1997071700123	19970717	00123	CE  	1997	7	17	97ZZZX3085       	1	19970604	G	2810		TUBE            			LEAR  	35    	35A         	5170602	CE  										TIP TANK	MISINSTALLED    	B		A	NVIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	71E	7598 				306				WHILE PERFORMING INSPECTION OF TIP TANK FLAPPER VALVES PER AD 95-25-03, FOUND AFT INTERCONNECT TUBE SCARFED AT AN ANGLE 	NOT ALLOWING FLAPPER VALVE TO BE MOUNTED IN REQUIRED PERPENDICULAR POSITION.  REMOVED TIP TANK, RE-PROFILED TUBE END TO 	ALLOW FOR PROPER ALIGNMENT OF FLAPPER.  RE-INSTALLED TIP TANK, LEAK CHECKED, OPS CHECKED FLAPPER.  RECORDS RESEARCHED BA	CK TO THE 12-YEAR INSPECTION.  NO RECORD FOUND OF TIP TANK REPAIR.  SUBMITTER STATED POSSIBLY THIS SITUATION HAD EXISTED	 SINCE AIRCRAFT WAS NEW.		2	L	7	2 	4F				A10CE   					 
1997071700124	19970717	00124	WP  	1997	7	17	97ZZZX3086       	2	19970224	G	7210		FITTING         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313U    	01514	WP  					ENGINE GEARBOX	STRIPPED        	E				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			SW	11	509SS	4021 				TC206	P03297			WHILE IN CRUISE FLIGHT, PILOT NOTICED OIL LEAK ON RIGHT ENGINE.  ENGINE SECURED AND UNEVENTFUL LANDING MADE.  FURTHER IN	VESTIGATION FOUND SCAVANGE OIL PUMP FITTING THREADS STRIPPED.  ENGINE REMOVED AND SENT TO OUTSIDE MAINTENANCE FACILITY F	OR REPAIR.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997071700126	19970717	00126	CE  	1997	7	17	97ZZZX3088       	2	19970521	G	7414	104001676	IMPULSE CAM     			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					MAG	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	252ZA	328  				251072	279241R			HEARD LOUD POP WHEN INSTALLING IMPULSE ASSEMBLY WHEN 15 POUNDS/FOOT OF TORQUE WAS REACHED.  REMOVED AND FOUND INNER HUB 	OF IMPULSE CRACKED IN THREE PLACES.					1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997071700127	19970717	00127	EA  	1997	7	17	97ZZZX3089       	2	19970603	G	7322		THROTLE BODY    			GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					ENGINE	STUCK OPEN      	B			NVIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	28339					AA5B0870				THROTTLE STUCK OPEN.  GAINED ACCESS TO AIRCRAFT ENGINE THROTTLE BODY BY REMOVING RT AND LT TOP ENGINE COWLINGS AND LOWER	 ENGINE COWL. RAN THROTTLE THROUGH AND SAW THROTTLE ARM LOOSE AND SLIPPING ON CARBURETOR.  REMOVED AND INSPECTED ARM SER	RATIONS AND CARBURETOR SERRATIONS, NOTED NO DEFECTS.  RE-INSTALLED ARM.  DISCONNECTED THROTTLE CABLE ROD END AND LUBED T	HROTTLE CABLE.  RE-INSTALLED ROD END ON CABLE.			1	L	7	1 	3O	3	O		A16EA   	E286				 
1997071700128	19970717	00128	CE  	1997	7	17	97ZZZX3090       	1	19970617	G	2760	20544470	FILTER          			CESSNA	650   	650         	2076802	CE  										SPOILER VALVE	FAILED          	B		A	GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	39WP	6024 				650039				DURING SMIP INSPECTION OPERATION 10, ITEM 27-20, INSPECTION REVEALED FILTER SEPARATED FROM MOUNTING FLANGE IN THE END OF	 THE ELBOW FITTING PERMITTING FILTER TO SLIDE BACK AND FORTH WITHIN THE FITTING.  SUBMITTER STATED THIS NEGATES FILTERIN	G CAPABILITY.  REPLACED ELBOW FILTER FITTING. THIS IS 3RD FITTING FOUND BROKEN OR FAILED DURING THE 1200-HOUR REMOVAL IN	SPECTION.  SUBMITTER RECOMMENDS IMPROVED FILTER ASSY OR A REPLACEMENT INTERVAL.			2	L	7	2 	4F				A9NM    					 
1997071700129	19970717	00129	CE  	1997	7	17	97ZZZX3091       	1	19970625	G	2150	73838416	ACM             			CESSNA	441   	441         	2076020	CE  										FAN BLADES	DAMAGED         	B			HUNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	477B					4410055				ACTT 4,328.25 HOURS.  BLADES FOUND DAMAGED, SOURCE UNKNOWN.  APPLIANCE TTSN UNKNOWN.  REPLACED ACM.						1	L	7	2 	3T			RT	A28CE   					 
1997071700130	19970717	00130	EA  	1997	7	17	97ZZZX3092       	2	19970625	G	7322	25244405	FUEL CONTROL    	BENDIX      		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					LT ENGINE	FAILED          	D		A		E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			EA	21	707ML	2048 			A41149	7520017	PS0761			ON THE 23RD OF JUNE, 1997 IN CRUISE FLIGHT, LEFT ENGINE WENT TO MAX POWER EXCEEDING TORQUE, TEMP, AND SPEED LIMITS.  ENG	INE WAS SHUT DOWN WITH THE FIREWALL SHUT OFF, PROPELLER FEATHERED, AND A DECLARED EMERGENCY LANDING MADE AT PHF WITHOUT 	ANY FURTHER PROBLEMS.  UPON FURTHER INVESTIGATION, FOUND BEARINGS IN FUEL CONTROLLER INPUT SHAFT DETERIORATED CAUSING TH	E SHAFT TO DISENGAGE CAUSING AN OUT OF CONTROL ENGINE RUNAWAY.			1	L	7	2 	3T	4	T		A8EA    	E4EA				 
1997071700131	19970717	00131	SO  	1997	7	17	97ZZZX3093       	2	19970613	G	7310	11141745032D	HOSE            	STRATOFLEX  		AYRES 	S2    	600S2DRESTD 	0143012	SO  	CONT  	O520  	IO520A      	17032	SO  					ENGINE FUEL	DEFECTIVE       	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	11	898LF					323	1113886A			DURING A POST-ACCIDENT INSPECTION/DISASSEMBLY, A TSO'D HOSE ASSY FROM 'STRATOFLEX' WAS REMOVED FROM THE FUEL CONTROL TO 	THE FUEL INJECTION MANIFOLD.  THIS HOSE WAS FOUND TO HAVE A SLIVER OF THE INNER WALL PROTRUDING BETWEEN THE INNER FERRUL	E AND THE NUT AT THE MANIFOLD ORIFICE.  THIS IS STRONGLY SUSPECTED AS THE CAUSE FOR LOSS OF ENGINE POWER IN-FLIGHT.  THI	S SEEMED TO BE AN INTERMITTENT PROBLEM IN THAT THE PILOT REPORTED THAT FUEL PRESSURE WAS ERRATIC DURING FLIGHT.  HOSE IN	FO:  CD3Q92, OP3000 PSI, TSO C532, A1193, OT 250 DEGREES FAHRENHEIT.		1	L	7	1 	3R	3	O		A4SW    	E5CE				 
1997071700132	19970717	00132	CE  	1997	7	17	97ZZZX3094       	1	19970614	G	2120		DUCT            			CESSNA	182   	TR182       	2072735	CE  										AVIONICS COOLING	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	5153R					R18200637				DURING AVIONICS INSTALLATION, AVIONICS COOLING DUCT FROM AIR INLET ON SIDE OF AIRCRAFT TO COOLING PANS ON LEFT AND RIGHT	 SIDE OF RADIOS WAS FOUND COMPLETELY DETERIORATED. THE BLACK FABRIC OF THE HOSE HAD ROTTED LEAVING STRIPS OF FABRIC HANG	ING BEHIND PANEL.  IT APPEARS THE AIRCRAFT WAS OPERATED NEAR SALT WATER CAUSING THE INTERIOR WIRE SUPPORTING THE HOSE TO	 RUST COMPLETELY THROUGH IN SEVERAL PLACES.  THE RUSTED SPRING WIRE WAS FOUND RUBBING ON ELECTRICAL WIRES AND HOSES CAUS	ING A HAZARD.		1	H	7	1 	3O				3A13    					 
1997071700133	19970717	00133	SO  	1997	7	17	97ZZZX3095       	2	19970612	G	8530		CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BB     	17032	SO  					NR 4	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	361BC		1466 		5498388	E1331	282253R			INSPECTION FOUND NR 4 CYLINDER CRACKED.  CRACK RUNS FROM EXHAUST.						1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997071700134	19970717	00134	SO  	1997	7	17	97ZZZX3096       	1	19970625	G	8120	301E10	TURBOCHARGER    	ROTOMASTER  		PIPER 	PA34  	PA34200     	7103405	SO  										ENGINE	BEARING FAILED  	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	42752		2950 		129	347450172				A MINOR OIL LEAK WAS DISCOVERED COMING FROM THE TURBOCHARGER HOUSING.  UPON INSPECTION, FOUND THE TURBO'S MAIN BEARINGS 	HAD GONE OUT CAUSING SLIGHT DAMAGE TO THE OIL SEAL.  TURBO HAS BEEN REMOVED AND IS BEING REPLACED WITH A SERVICEABLE PAR	T.				1	L	7	2 	3O				A7SO    					 
1997071700135	19970717	00135	CE  	1997	7	17	97ZZZX3097       	1	19970622	G	2436	DGR3	CONTROL UNIT    			CESSNA	150   	152         	2071835	CE  										ALTERNATOR	DEFECTIVE       	D				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			WP	23	5447P					15284948				CESSNA/LAMAR PN DGR3 IS SUPPOSED TO BE A SUITABLE SUBSTITUTE FOR C611005-0101.  HOWEVER, WHEN INSTALLED, ENGINE OFF, BAT	TERY/ALT SWITCH ON - LOW VOLTAGE LIGHT DOES NOT COME ON.  SUSPECT DGR3 IS A SUBSTITUTE FOR ANOTHER CESSNA PN, NOT C61100	5-0101.				1	H	7	1 	3O			NT	3A19    					 
1997071700136	19970717	00136	SO  	1997	7	17	97ZZZX3098       	1	19970624	G	2823	5226303	FUEL SELECTOR   			PIPER 	PA31  	PA31350     	7103110	SO  										CONTROL PANEL	SHAFT BROKE     	D	P	A		E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			AL	01	59829	14956				317652081				TOP END OF FUEL CONTROL ARM BROKE OFF WHERE HANDLE ATTACHES WITH ROLL PIN.  HANDLE BROKE OFF DURING TANK SELECTION IN TH	E OFF POSITION.  RIGHT ENGINE QUIT AND WAS FEATHERED.  TOP OF CONTROL ARM SHAFT HAD BEEN REPAIRED AND RE-DRILLED FOR ROL	L PIN.  FUEL CONTROL ARM SHOULD BE REPLACED ANY TIME THERE IS PLAY BETWEEN OPERATING HANDLE AND SHAFT.  STEEL ROLL PIN W	HICH ATTACHES HANDLE TO SHAFT WILL ELONGATE HOLE IN SHAFT.			1	L	7	2 	3O				A20SO   					 
1997071700137	19970717	00137	EA  	1997	7	17	97ZZZX3099       	2	19970625	G	7322		THROTTLE ARM    			CESSNA	172   	172L        	2072432	CE  	LYC   	O360  	O360A4M     	41514	EA  					CARBURETOR	JAMMED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	7031Q					17260331				MISALIGNMENT OF THE RIGGING OF THE THROTTLE ARM TO THE CARBURETOR (IN 1994) CAUSED THE THROTTLE ARM TO JAM PREVENTING TH	E ENGINE FROM ACCELERATING.					1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1997071700138	19970717	00138	CE  	1997	7	17	97ZZZX3100       	1	19970625	G	3246	201302561	WHEEL           			CESSNA	172   	172N        	2072434	CE  										RT MLG	CRACKED         	B			CBCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	73764	3231 				17267661				DURING A 100-HOUR INSPECTION, THE RT MAIN TIRE WAS BEING ROTATED.  DURING INSPECTION OF MAIN WHEEL CENTER HUB, CRACKS WE	RE DISCOVERED AT EACH BOLT HOLE (6) ON THE OUTBOARD SIDE OF WHEEL.  ALSO, ON THE INBOARD SIDE 3 OF THE 6 HOLES SHOWED CR	ACKS TOO.  THIS AIRCRAFT IS USED FOR TRAINING PURPOSES.  POSSIBLE CAUSE, REPEATED HARD LANDINGS.				1	H	7	1 	3O			NT	3A12    					 
1997071700139	19970717	00139	CE  	1997	7	17	97ZZZX3101       	1	19970610	G	5210	05170194	HINGE           			CESSNA	172   	172N        	2072434	CE  										RT CABIN DOOR	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	739NY					17270685				CABIN DOOR HINGE MANUFACTURED WITH DEFECT IN PIN BOSS.  LOOKS AS IF WHEN DRILLING HOLE, BIT WAS ON A SLANT AND DID NOT D	RILL THROUGH CENTER OF MATERIAL.  DEFECT WAS NOT CAUGHT BY INSPECTION PERSONNEL.					1	H	7	1 	3O			NT	3A12    					 
1997071700140	19970717	00140	NE  	1997	7	17	97ZZZX3102       	2	19970612	G	8520		CONNECT ROD     			DHAV  	DHC4  	DHC4A       	2800304	EA  	PWA   	R2000 	R20007M2    	52023	NE  					ENGINE	FAILED          	H				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	99	800NC	96   				98	P106788			ENGINE BROKE A CONNECTING ROD IN-FLIGHT.  RETURNED TO BASE WITH 25 INCHES MANIFOLD PRESSURE.  LANDED WITHOUT INCIDENT. E	NGINE STILL RAN WITH BROKEN ROD AND DID NOT DESTROY ITSELF.					2	H	7	2 	4R	4	R		1A19    	5E5				 
1997071700141	19970717	00141	SW  	1997	7	17	97ZZZX3103       	1	19970625	G	5280		DOOR HINGE      			MOONEY	M20   	M20M        	5870222	SW  										MLG	RIVET SHEARED   	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	72FG					270118				THE RIVETS HOLDING THE INNER STBD MAIN LANDING GEAR DOOR HINGE SHEARED CAUSING THE DOOR TO JAM AND PREVENTING FULL GEAR 	RETRACTION.  GEAR EXTENSION WAS NOT AFFECTED.  THE RIVETS WERE REPLACED AND THE BENT OPERATING RODS AND BELLCRANK.  GEAR	 RETRACTION TESTS WERE CARRIED OUT. SUBMITTER RECOMMENDS CLOSE INSPECTION OF GEAR DOOR HINGE RIVETS AT ROUTINE MAINTENAN	CE CHECKS.  AIRCRAFT TOTAL TIME 714.6 HOURS.			1	L	7	1 	30			RT	2A3     					 
1997071700142	19970717	00142	WP  	1997	7	17	97ZZZX3104       	1	19970624	G	7922	53E19600	VALVE           			ROBSIN	R22   	R22ALPHA    	7640104	WP  										THERMO BYPASS	CRIMP NUT LOOSE 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	8497Y	520  			5998A	0408				DURING A00-HOUR INSPECTION OF OIL SCREEN, FOUND NUT ON END OF VERNATHERM THERMOSTATIC VALVE WAS LOOSE.  ACCORDING TO LYC	OMING SB 518C, THIS PART NUMBER AND SERIAL NUMBER ARE NOT REQUIRED TO HAVE THE INSPECTIONS LISTED TO DETERMINE IF THE NU	T IS LOOSE.  VALVE WAS RE-WORKED IAW LYC SI NR 1423 AND RE-INSTALLED IN ENGINE ON 6-24-97.				1	G	7	1 	3O				H10WE   					 
1997071700631	19970717	00631	CE  	1997	7	17	97ZZZX3148       	1	19970626	G	2150	12502327	SWITCH          			CESSNA	208   	208B        	2073701	CE  										AIR CONDITIONER	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01					171					AIR CONDITIONER PRESSURE SWITCH NOT MACHINED ADEQUATELY TO ACCEPT THE SEALING O-RING.						1	H	7	1 	3T				A37CE   					 
1997071700632	19970717	00632	GL  	1997	7	17	97ZZZX3149       	3	19970607	G	6114	D4035C30	HUB             													MCAULY	2A34C	D2AF34C30   	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1314 						701310		PROPELLER WAS RECEIVED FOR ROUTINE OVERHAUL.  AFTER DISASSEMBLY, HUB WAS FOUND CRACKED IN NR 2 BLADE SOCKET, 2 THREADS I	N AT THE 6 O'CLOCK POSITION ABOUT 1.5 INCHES LONG.  CRACK DISCOVERED USING A 10X POWER MICROSCOPE.															5	C	P5EA	 
1997071700633	19970717	00633	CE  	1997	7	17	97ZZZX3150       	1	19970703	G	2822	1016	PUMP            	AIRBORNE    		BEECH 	58    	58P         	1152744	CE  										BOOST LT ENGINE	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	01	133Z				12E360	TJ367				INSPECTION OF LEFT FUEL BOOST PUMP REVEALED FUEL LEAKING FROM B PLUS INSULATOR.   REF:  BSL 1255 R1.  PUMP WAS OVERHAULE	D 3-91.					1	L	7	2 	3O				A23CE   					 
1997071700636	19970717	00636	CE  	1997	7	17	97ZZZX3153       	1	19970613	G	2434	ALV9510	ALTERNATOR      	PRESTOLITE  		CESSNA	421   	421         	2076010	CE  										DC SYSTEM	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	421Z		137  		A11378L	4210077				ALTERNATOR FAILED AFTER 136.6 HOURS OF OPERATION.  OVERHAULED 10-3-96.  SUBMITTER STATED CONTINUE TO HAVE SHORT SERVICE 	LIFE ON THESE UNITS.					1	L	7	2 	3O			RT	A7CE    					 
1997071700637	19970717	00637	GL  	1997	7	17	97ZZZX3154       	3	19970702	G	6114	C6447C23	HUB             			BEECH 	33    	35C33       	1151408	CE  						MCAULY	2A36C	2A36C23     	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19	5908S		238  			CD1026		7710546		PROPELLER RECEIVED FOR INSPECTION OF RED DYE OIL LEAK (SMALL).  DISASSEMBLED PROPELLER, INSPECTED HUB WITH 10X POWER MIC	ROSCOPE, FOUND CRACK IN NR 2 BLADE SOCKET, LAST THREAD IN 8 O'CLOCK POSITION, 1.50 INCHES TO 2 INCHES LONG.  NOTE:  THIS	 PROPELLER HAS TTSN UNKNOWN.  TSO:  238.1 HOURS WITH 32 MONTHS SINCE LAST OVERHAUL.  AD NOTE 89-26-08, OIL FILLING THIS 	PROPELLER PREVENTED A CATASTROPHIC FAILURE.			1	L	7	1 	3O				3A15    		5	C	P880	 
1997071700638	19970717	00638	SO  	1997	7	17	97ZZZX3155       	1	19970630	G	5347	62557004	SEAT TRACK      			PIPER 	PA28  	PA28150     	7102804	SO  										CABIN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5071W					2880				ON AN ANNUAL INSPECTION, POWDER CORROSION WAS NOTED ON PASSENGER SIDE INBOARD SEAT TRACK, ON PEELING CARPET OFF, FOUND T	HE SEAT TRACK WAS CORRODED TO REPLACEMENT.  THREE OTHER SEAT TRACKS WERE ALSO BADLY CORRODED.  IT WOULD BE WELL TO PEEL 	THE CARPET OFF SEAT TRACKS AND TREAT.				1	L	7	1 	3O				2A13    					 
1997071700639	19970717	00639	SO  	1997	7	17	97ZZZX3156       	1	19970419	G	3230	17SF41014	SPRING          			STOLAM	RC3   	RC3         	3080202	SO  										GEAR DOWNLOCK	DETACHED        	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	21	6505K					771				OVERCENTER LOCKING SPRINGS, 2 EACH, ON INTERNAL LANDING GEAR CAME OFF ALLOWING OR CAUSING OVERCENTER LOCKING MECHANISM T	O RELEASE ALLOWING LANDING GEAR TO ROTATE REARWARD TO UP POSITION.  THIS OCCURRED DURING ROLLOUT FOLLOWING NORMAL LANDIN	G.  NO APPRECIABLE DAMAGE TO AIRCRAFT.  SPRINGS SLIGHTLY DEFORMED.  NEW SPRINGS INSTALLED, TESTED, AND ALL OK NOW.				1	H	7	1 	3O				A769    					 
1997071700642	19970717	00642	SO  	1997	7	17	97ZZZX3159       	1	19970424	G	7820	66894003	MUFFLER         			PIPER 	PA28  	PA28161     	7102803	SO  										BAFFLES	FAILED          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	8234D	1017 				288216027				FOLLOWING A REPORT THAT AIRCRAFT SOUNDED 'FUNNY' DURING APPROACH, INSPECTION FOUND EXHAUST FLAME TUBE FAILED AND WAS BLO	CKING MUFFLER OUTLET.  AIRCRAFT USED FOR FLIGHT SCHOOL RENTAL.					1	L	7	1 	3O				2A13    					 
1997071700643	19970717	00643	SW  	1997	7	17	97ZZZX3160       	1	19970617	G	7920	AN626410D16	OIL LINE        			TMPSON	NAVION	NAVION*     	6150130	SW  										ENGINE OIL	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8551H					NAV4535				OIL LINE FAILED AFTER ENGINE CHANGE.  THE OIL COOLER LINES WERE NOT CHANGED.  THE LINE APPEARED TO BE ORIGINAL, 50 YEARS	 OLD.					1	L	7	1 	3O				A782    					 
1997071700644	19970717	00644	CE  	1997	7	17	97ZZZX3161       	1	19970703	G	2720	0025240205	PEDAL           			BEECH 	95    	95B55       	1152729	CE  										PILOT LEFT	WORN            	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	213CH	4378 				TC2298				WHILE INSPECTING THE PILOT'S RUDDER PEDALS AT THE ANNUAL INSPECTION, THE PILOT'S PEDAL ARMS WERE FOUND WORN AT THE PEDAL	 TO ARM ATTACH PIVOT HOLES; .0625 INCH OF ARM WAS LEFT IN THE AREA AROUND THE BUSHING AT THE PIVOT POINT.  SUBMITTER STA	TED TIME ON AIRCRAFT, AND BOLTS NOT TIGHT ENOUGH, CONTRIBUTED TO THIS PROBLEM.  CHECK FOR PLAY AT INSPECTIONS.				1	L	7	2 	3O			RT	3A16    					 
1997071700645	19970717	00645	CE  	1997	7	17	97ZZZX3162       	1	19970703	G	2720	0025240206	PEDAL           			BEECH 	95    	95B55       	1152729	CE  										PILOT RIGHT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	213CH	4378 				TC2298				WHILE INSPECTING THE PILOT'S RUDDER PEDALS AT THE ANNUAL INSPECTION, THE PILOT'S PEDAL ARMS WERE FOUND WORN AT THE PEDAL	 TO ARM ATTACH PIVOT HOLES; .0625 INCH OF ARM WAS LEFT IN THE AREA AROUND THE BUSHING AT THE PIVOT POINT.  SUBMITTER STA	TED TIME ON AIRCRAFT, AND BOLTS NOT TIGHT ENOUGH CONTRIBUTED TO THIS PROBLEM.  CHECK FOR PLAY AT INSPECTIONS.				1	L	7	2 	3O			RT	3A16    					 
1997071700646	19970717	00646	EA  	1997	7	17	97ZZZX3163       	2	19970630	G	8520		STUD            			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 3 CYLINDER	FAILED          	B			EKIR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	252MA		697  			31P33	RL12762			FOUR CYLINDER ATTACH STUDS ON NR 3 CYLINDER FOUND BROKEN FOLLOWING ENGINE RUNNING ROUGH.  FOUND NO EVIDENCE OF DETONATIO	N ON TEAR DOWN.					1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997072200007	19970722	00007	SO  	1997	7	22	97ZZZX3165       	1	19970424	G	2913		PUMP            			PIPER 	PA31  	PA31325     	7103105	SO  										HYDRAULICS	FAILED          	D	L	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	4039L					318112013				INVESTIGATION FOR DUAL HYDRAULIC PUMP FAILURE FOUND PUMPS RAN DRY DUE TO NO HYDRAULIC FLUID.  SIGHT GAUGE USED FOR FLUID	 CHECK.  IT IS BELIEVED FLUID CHECK WAS ERRONEOUS DUE TO STAIN ON GAUGE.  GAVE INDICATION OF ADEQUATE FLUID WHEN ACTUALL	Y FLUID WAS DEPLETED.  150 FLIGHT HOURS SINCE RESERVOIR SERVICED.				1	L	7	2 	3O				A20SO   					 
1997071700649	19970717	00649	CE  	1997	7	17	97ZZZX3166       	1	19970708	G	7120		MOUNT           			BEECH 	55    	E55         	1152732	CE  										ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	48CM					TE985				THIS REPORT INVOLVES METAL FATIGUE AND SEVERE CRACKING ON BOTH ENGINE MOUNTS ON AN E-55 BEECHCRAFT BARON.  LEFT ENGINE W	AS REMOVED FOR REPLACEMENT WITH A FACTORY REMANUFACTURED IO520.  LEFT MOUNT WAS FOUND CRACKED IN FOUR PLACES.  SAME COND	ITION EXPERIENCED ON RIGHT ENGINE EXCEPT CRACKS WERE MORE EXTENSIVE.  BOTH MOUNTS WERE OVERHAULED WITH AN APPROVED KIT W	ELDING PROCEDURE.  THIS ACFT WAS INSPECTED BY THREE DIFFERENT INSPECTORS DURING THE PRE-PURCHASE INSPECTION AND WAS SUBS	EQUENTLY INSPECTED DURING TWO ANNUAL INSPECTIONS AND NONE OF THE CRACKS WERE FOUND UNTIL THE ENGINES WERE REMOVED.  TT A	CFT AND ENGINES, 1,675 HOURS.	1	L	7	2 	3O				3A16    					 
1997071700650	19970717	00650	SO  	1997	7	17	97ZZZX3167       	1	19970627	G	8120	646396	TURBOCHARGER    			PIPER 	PA34  	PA34200T    	7103406	SO  										LT ENGINE	SEAL FAILED     	B			RG4R	K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		IN	INSP/MAINT     	1			SO	03	5423F		33   			347770018				TURBOCHARGER OIL SEAL FAILED BETWEEN FLIGHTS.  ACFT PARKED, AND WAS RESTARTED 15 MINUTES AFTER SHUT DOWN.  LEFT ENGINE W	AS BLOWING BLUE SMOKE AND OIL WAS RUNNING OUT OF COWL. TURBOCHARGER SEAL FAILURE OCCURRED DURING START ON THE GROUND.					1	L	7	2 	3O				A7SO    					 
1997071700651	19970717	00651	CE  	1997	7	17	97ZZZX3168       	1	19970326	G	3230	0842107497	DRAG BRACE      			CESSNA	310   	310I        	2074224	CE  										NLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			WP	21	8133M					310I0133				NOSE GEAR DRAG BRACE FAILED ON LANDING ROLL OUT.						1	L	7	2 	3O				3A10    					 
1997071700652	19970717	00652	SO  	1997	7	17	97ZZZX3169       	1	19970626	G	2434	ALX9425ECH	ALTERNATOR      	PRESTOLITE  		PIPER 	PA34  	PA34200T    	7103406	SO  										SLIP RING	DEFECTIVE       	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8407C		109  		A119339	347670137				AFTER ONLY 109 HOURS ON THE OVERHAULED ALTERNATOR, IT WOULD NOT FUNCTION PROPERLY (I.E., PARALLEL, SHARE THE LOAD, REMAI	N ON-LINE).  UPON REMOVAL OF THE BRUSHES, FOUND BURNED SLIP RINGS.  UNIT REMOVED FOR WARRANTY CONSIDERATION AND 'NEW' EX	HANGE UNIT INSTALLED.				1	L	7	2 	3O				A7SO    					 
1997071700653	19970717	00653	EA  	1997	7	17	97ZZZX3170       	2	19970601	G	8550	S19515	DRAIN PLUG      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					SEAL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	924ER					4496011				FOUND SEAL ON OIL SIDE OF DRAIN SWOLLEN CAUSING THE QUICK DRAIN TO OOZE AND NOT DRAIN PROPERLY.						1	L	7	2 	3O	3	O		A19S0   	E286				 
1997071700654	19970717	00654	EA  	1997	7	17	97ZZZX3171       	2	19970601	G	8550	BJ1000AH4	DRAIN PLUG      			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					ENGINE OIL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	923ER					4496010	L3504136A			DURING ROUTINE INSPECTION, FOUND OIL DRAIN O-RING NOT SEATED PROPERLY.						1	L	7	2 	3O	3	O		A19S0   	E286				 
1997071700655	19970717	00655	CE  	1997	7	17	97ZZZX3172       	1	19970624	G	2913	73303	PUMP ADAPTER    			BEECH 	80    	65A80       	1152808	CE  										HYDRAULIC PUMP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	95LL					LD235				THE HYDRAULIC PUMP ADAPTER CRACKS AND EVENTUALLY BREAKS AT THE ATTACH POINT TO ACCESSORY CASE.						1	L	7	2 	3O				3A20    					 
1997071700624	19970717	00624		1997	7	17	97ZZZX3173       	2	19970618	G	7200	9125M65G07	LEVER ASSY      			BOEING	747   	74745E      	1384947	NM  										VSV STATOR STG 5	FAILED          	C		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	407EV	17865				27899				CAPTAIN REPORTED NR 3 ENGINE FAILURE ON INITIAL CLIMB AT 1,500 FEET AGL.  POWER HAD JUST GONE FROM TAKEOFF THRUST TO CLI	MB THRUST.  LOUD EXPLOSIVE NOISE HEARD ACCOMPANIED BY HEAVY VIOLENT 'JOLT'.  NO FURTHER VIBRATION AFTER ENGINE FAILURE. 	 METAL CHIPS ARE NOTICED AT TAIL PIPE AREA.  SEVERAL STAGE 5 VSV LEVER ARMS BROKEN.  NO OBVIOUS SIGN OF FOD NOTICED.  SU	SPECT CAUSE MAY BE THE STAGE 5 LEVER ARMS.  A FLEET WIDE ONE TIME INSPECTION WILL BE CARRIED OUT AS A RECOMMENDATION, AN	D NOTICE AND REQUEST G.E. DOES FORMAL INVESTIGATION.  ENGINE CYCLES:  1,202 (SINCE INSTALLED), 2,666 (TOTAL).		2	L	7	4 	4F			RT	A20WE   					 
1997071700627	19970717	00627	CE  	1997	7	17	97ZZZX3174       	1	19970624	G	3230		SUPPORT BRACKET 			CESSNA	650   	650         	2076802	CE  										NLG ACTUATOR	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	07	652JM	4449 				6500113				NOSE GEAR REMAINED IN UP POSITION WHEN GEAR SELECTED TO DOWN POSITION.  EMERGENCY EXTENSION PERFORMED AND GEAR EXTENDED 	AND SHOWED GEAR SAFE LIGHTS.  UNEVENTFUL LANDING AND TAXI TO RAMP.  INSPECTION FOUND DAMAGED UPLOCK SUPPORT BRACKET.  CI	TATION 650 SB 650-53-15 REV 1 IS RECOMMENDED FOR ACFT SN'S 0001-0124.  THIS INSTALLS IMPROVED SUPPORT BRACKET ASSY AND A	LONG WITH SB 650-32-22 REV 2, AND SB 650-32-29 REV 2 IMPROVEMENTS TO UPLOCK HOOK ASSY AND UPLOCK SPRING.  SUBMITTER STAT	ED EACH AIRCRAFT IN THIS S/N RANGE SHOULD BE INSPECTED FOR ANY DEFECTS IN THIS AREA.		2	L	7	2 	4F				A9NM    					 
1997071700628	19970717	00628	CE  	1997	7	17	97ZZZX3175       	1	19970608	G	2800		FUEL SYSTEM     			HELIO 	H295  	HT295       	4300803	CE  										ENGINE	WATER CONTAM    	G		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			WP	09	68874					1707				WATER CONTAMINATION OF FUEL SYSTEM RESULTED IN ENGINE STOPPAGE SHORTLY AFTER TAKEOFF RESULTING IN SUBSTANTIAL DAMAGE TO 	AIRCRAFT, IN OFF-FIELD LANDING LESS FAVORABLE TERRAIN MAY HAVE RESULTED IN SERIOUS OR FATAL INJURIES.  DETERMINED THAT D	UE TO NO MAIN FUEL TANK DRAINS OR ADEQUATE SUMP OR GASCOLATOR VOLUME, UNDRAINABLE WATER OR CONTAMINATION MAY EXIST IN AL	L HELIO MODELS ESPECIALLY TRI-GEAR VERSIONS.  SUBMITTER RECOMMENDS ADDING MAIN TANK DRAINS AND COLLECTOR SUMP OF ONE-HAL	F GALLON OR MORE.  THIS ALTERATION HAS BEEN COMPLETED ON THIS AIRCRAFT AND HAS PROVEN SUCCESSFUL.		1	H	7	1 	3O				1A8     					 
1997071700629	19970717	00629	WP  	1997	7	17	97ZZZX3176       	1	19970701	G	6322	29227	HUB             		369D25630   	HUGHES	369   	369D        	4470706	WP  										COOLER BLOWER	SEPARATED       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										DURING BUILD-UP, LOWER BEARING SLINGER RING LOCKED UP.  USING TOOL TO PRESS OUT LOWER BEARINGS, THE ENTIRE RACE PRESSED 	OUT OF HUB.					1	G	7	1 	3U				H3WE    					 
1997072400069	19970724	00069	NE  	1997	7	24	97ZZZX3186       	3	19970701	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		3613 			2922NR			HJ537		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	 
1997072400070	19970724	00070	SO  	1997	7	24	97ZZZX3187       	2	19970630	G	8520	653136	CRANKSHAFT      								CONT  	O360  	LTSIO360KB  	17025	SO  					FILLET AREA	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		3523 	1786 		B022MI		314329			THIS COMPONENT CAME OUT OF AN IN STOCK ENGINE.  CRANKSHAFT FAILED UT INSPECTION PER TCM MHS-200.  ALL 4 FILLET AREAS HAD	 INDICATIONS IN EXCESS OF 40 PERCENT FSH.										3	O			E9CE				 
1997072400071	19970724	00071	NE  	1997	7	24	97ZZZX3188       	3	19970601	G	6111	AG100	BLADE           													HAMSTD	12D	12D40       	NE  	PROP LE/TE	MISREPAIR       	B			NWOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					732033					UNAUTHORIZED REPAIR TO LEADING AND TRAILING EDGES OF BLADES BY WELDING TO INCREASE CHORD.  BLADE SN 732033 ALSO INCORPOR	ATES STC'D BEARING MODIFICATION.  BLADE REPAIR INDICATED BY NON-DESTRUCTIVE TESTING AND ANODIZATION PROCEDURE.															5	C	P257	 
1997072400072	19970724	00072	NE  	1997	7	24	97ZZZX3189       	3	19970601	G	6111	AG100	BLADE           													HAMSTD	12D	12D40       	NE  	PROP LE/TE	MISREPAIR       	B			NWOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					764957					UNAUTHORIZED REPAIR TO LEADING AND TRAILING EDGES OF BLADES BY WELDING TO INCREASE CHORD.  BLADE SN 732033 ALSO INCORPOR	ATES STC'D BEARING MODIFICATION.  BLADE REPAIR INDICATED BY NON-DESTRUCTIVE TESTING AND ANODIZATION PROCEDURE.															5	C	P257	 
1997072400073	19970724	00073	GL  	1997	7	24	97ZZZX3190       	3	19970601	G	6114		HUB             													HARTZL	HCC2Y	HCC2YR4     	GL  	NR 2 SOCKET	CRACKED         	B	S		NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05								DN1378		TOP HALF HUB, BLADE SOCKET NR 2 CRACKED AND SEPARATED FROM HUB EAR DIAGONALLY ACROSS CORNER OF HUB.  DISCOVERED DUE TO G	REASE LEAK, DISASSEMBLY.															5	C	P920	 
1997072400074	19970724	00074	EA  	1997	7	24	97ZZZX3191       	2	19970623	G	7414	1052947	ROTOR           		S6LN200     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MAGNETO	WORN            	B			B2ER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	510WA		720  		C139602ER	277405436	RL676840			REMOVED MAGNETO FOR INSPECTION.  FOUND ROTOR CRACKED NEAR MAGNET.  HOUSING WALLS FOUND TO BE WORN.  THERE ALSO WAS NO BE	ARING, THE METAL FROM THE BEARING WAS INSIDE THE MAGNETO.					1	L	7	2 	3O	3	O		1A10    	1E4				 
1997072400075	19970724	00075	NE  	1997	7	24	97ZZZX3192       	2	19970706	G	8520	10992	LINK ROD        			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R134053     	52016	NE  					NR 9 CYLINDER	FAILED          	G				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	AG	AGRICULTURE    	1			GL	15	6633K		637  			400B	21637			DURING AERIAL APPLICATION OPERATIONS, NR 9 CYLINDER CONNECTING ROD FAILED AT MASTER ROD CONNECTION PIN.  SEVERE IMPACT D	AMAGE TO ROD.  PISTON CONTACTED CYLINDER HEAD WHICH BROKE INTO 3 PIECES.  CAUSE OF FAILURE UNKNOWN AT THIS TIME.					1	Q	7	1 	3R	3	R		1A16    	5E2				 
1997072400076	19970724	00076	EU  	1997	7	24	97ZZZX3193       	2	19970604	G	8520	887051	CRANKSHAFT      			AMTR  	KITFOX	KITFOX      	05613LZ	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					PTO SIDE	ROD FAILED      	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	85TA	110  				HCU085	4171942			CRANKSHAFT CONNECTING ROD BEARING FAILED CAUSING PISTON CONNECTING ROD TO FAIL WHICH LOCKED ENGINE.  ENGINE COOLANT AND 	EXHAUST TEMPERATURE NORMAL PRIOR TO FAILURE.  OIL INJECTION PUMP CHECKED OUT SATISFACTORILY.					1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1997072400077	19970724	00077	NE  	1997	7	24	97ZZZX3194       	3	19970702	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		4582 			2422NR			HJ377		PROPELLER 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	 
1997072400078	19970724	00078	CE  	1997	7	24	97ZZZX3195       	1	19970616	G	2730	50524410601	BELLCRANK       			BEECH 	200   	B200        	1152922	CE  										ELEVATOR	MISDRILLED      	B			XE9R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	1114K					BB1559				FIRST PHASE INSPECTION FOUND SLACK IN HORIZONTAL CONTROL.  LOCATED PLACE OF LOOSE CONNECTION FORWARD ELEVATOR BELLCRANK 	TO PUSH/PULL TUBE WAS MISDRILLED TO .3125 INCH; SUPPOSED TO BE .25 INCH.					1	L	7	2 	4T				A24CE   					 
1997072400079	19970724	00079	NM  	1997	7	24	97ZZZX3196       	1	19970227	G	6322	B1741	FAN             		O320B2C     	ROBSIN	R22   	R22BETA     		NM  										ENGINE BLOWER	CRACKED         	B			BJDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2311X	834  				1972				ENGINE COOLING FAN HAD TOTAL TIME OF 833.7 HOURS.  ROBINSON HAD NO REPAIR OR OVERHAUL FOR THIS PART.  SUBMITTER STATED P	ART SHOULD LAST AT LEAST 2,000 HOURS, THEN BE OVERHAULED.					1	G	7	1 	3O				H10WE   					 
1997072400080	19970724	00080	EU  	1997	7	24	97ZZZX3197       	1	19970701	G	6500	22208BC060012L	SCREW           			SNIAS 	350   	AS350B2     	8680813	EU  										T/R DRIVE SHAFT	DEFECTIVE       	B		A	RC0R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	4035W	400  				2912				DURING C/W SB 05.08 PARA 1C(2A) WHEN REINSTALLING SCREW INTO BEARING SUPPORT MOUNT BRACKET, MECHANIC STATED THAT TORQUE 	DID NOT FEEL STABLE.  REMOVED AND INSPECTED, FOUND NO OBVIOUS DEFECTS.  REINSTALLED TORQUED NUT AND, AGAIN, DID NOT FEEL	 LIKE TORQUE STABILIZED.  ATTEMPTED TO TORQUE TO MAXIMUM, TORQUE BOLT FAILED.  EUROCOPTER AS350B2 PARTS MANUAL,  SCREW, 	PN 22208BC060012C, ITEM 230, FIGURE 65.10.10, PG 3.			1	G	7	1 	3U				H9EU    					 
1997072400081	19970724	00081		1997	7	24	97ZZZX3198       	4	19970611	G	2312	RT5000	TRANSCEIVER     			SNIAS 	350   	AS350B2     	8680813	EU  										SQUELCH CKT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	4055L				1360	2916				AIRCRAFT TRANSCEIVER RT 5000 RECEIVED WITH BROKEN SQUELCH EVERY 4 SECONDS, NEVER RECEIVED.  SN 1360 RT 5000 RECEIVED WIT	H CONSTANT SQUELCH.  BOTH ITEMS WERE SENT IN PRIOR FOR THESE DISCREPANCIES TO GLOBAL WOLFSBURG/BENDIX KING.					1	G	7	1 	3U				H9EU    					 
1997072400082	19970724	00082		1997	7	24	97ZZZX3199       	4	19970611	G	2312	RT5000	TRANSCEIVER     			SNIAS 	350   	AS350B2     	8680813	EU  										SQUELCH CKT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	4055L				1367	2916				AIRCRAFT TRANSCEIVER RT 5000 RECEIVED WITH BROKEN SQUELCH EVERY 4 SECONDS, NEVER RECEIVED.  SN 1360 RT 5000 RECEIVED WIT	H CONSTANT SQUELCH.  BOTH ITEMS WERE SENT IN PRIOR FOR THESE DISCREPANCIES TO GLOBAL WOLFSBURG/BENDIX KING.					1	G	7	1 	3U				H9EU    					 
1997072400083	19970724	00083	SW  	1997	7	24	97ZZZX3200       	1	19970701	G	3340	A402RW	LENS            			HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	197  				LN004				DURING MORNING WALK-AROUND, FORWARD LOWER STROBE LENS FOUND TO BE CRACKED ON SEAM.  SECOND CRACK 2 INCHES DOWN PROCEEDIN	G TO CLAMP AREA.					1	G	7	1 	3U			NC	H3WE    					 
1997072400084	19970724	00084	SW  	1997	7	24	97ZZZX3201       	1	19970403	G	6720	500N3139	MOUNT           			HUGHES	500N  	500N        	3027374	SW  										NOTAR FAN XMSN	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	522FB	5253 				LN002				AFT TRANSMISSION  MOUNT CRACKED FROM RIVET, OUTWARD THROUGH EXTRUSION WEB AT UPPER LEFT MOUNT, PN 500N3139, STA 137.50 B	ULKHEAD.					1	G	7	1 	3U			NC	H3WE    					 
1997072400085	19970724	00085	SW  	1997	7	24	97ZZZX3202       	1	19970701	G	3340	A402RW	LENS            	WHELEN      		HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	526FB	185  				LN006				DURING DAILY WALK-AROUND, STROBE LENS FOUND CRACKED ALONG SEAM.						1	G	7	1 	3U			NC	H3WE    					 
1997072400086	19970724	00086	SW  	1997	7	24	97ZZZX3203       	1	19970531	G	2510	369H6512501	SEAT BELT       			HUGHES	500N  	500N        	3027374	SW  										COPILOT	FAILED          	G				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			WP	07	527FB		211  			LN007				SEAT BELT LOOSENS DURING FLIGHT.  DOES NOT HOLD WHEN TIGHTENED.						1	G	7	1 	3U			NC	H3WE    					 
1997072400087	19970724	00087	SW  	1997	7	24	97ZZZX3204       	1	19970531	G	3340	A402RW	LENS            			HUGHES	500N  	500N        	3027374	SW  										STROBE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	527FB	50   				LN007				FOUND AFT LOWER STROBE LENS CRACKED AND SEPARATED AT SEAM.						1	G	7	1 	3U			NC	H3WE    					 
1997072400088	19970724	00088	SW  	1997	7	24	97ZZZX3205       	1	19970531	G	2510	369H6512501	SEAT BELT       			HUGHES	500N  	500N        	3027374	SW  										PILOT	FAULTY          	G				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			WP	07	527FB		211  			LN007				SEAT BELT DOES NOT HOLD IN TIGHTEN MODE.  ALLOWS BELT TO SLIDE LOOSE DURING FLIGHT.						1	G	7	1 	3U			NC	H3WE    					 
1997072400089	19970724	00089	NM  	1997	7	24	97ZZZX3206       	1	19970601	G	6210	A1561	BOOT            		A0162       	ROBSIN	R22   	R22BETA     		NM  										M/R BLADE	LEAK            	B		A	BJDR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	8350M	31   			9717C	2665				SHIP HAD A TOTAL TIME OF 30.5 HOURS.  THE INNER BOOT CLAMP PN A165-1 DID NOT HAVE ENOUGH TORQUE TO PREVENT LEAKAGE OF TH	E FLUID.  THE MM DOES NOT HAVE A TORQUE FOR THIS CLAMP.  A LOSS OF ENOUGH FLUID COULD CAUSE SERIOUS PROBLEMS (M/R OUT OF	 BALANCE, LACK OF LUBRICATION).				1	G	7	1 	3O				H10WE   					 
1997072400091	19970724	00091	GL  	1997	7	24	97ZZZX3208       	1	19970516	G	6710	28161861	SOCKET          			ENSTRM	F28   	F28C        	3300407	GL  										COLLECTIVE	CRACKED         	D		A		A				UNSCHED LANDING         				O			OTHER                     			HO	HOVERING       	1			EA	25	15SA	3093 				469				AFTER GROUND RUN AND HOVER TO CHECK ENGINE PERFORMANCE, AIRCRAFT WAS LANDED AND COLLECTIVE WAS LOWERED TO SECURE FRICTIO	N.  MODERATE PRESSURE WAS APPLIED AND BEFORE FRICTION COULD BE SET, A BANG WAS HEARD.  THE PILOT'S COLLECTIVE STICK DROP	PED APPROXIMATELY 1 INCH.  FURTHER INSPECTION, FOUND PILOT'S COLLECTIVE SOCKET HAD CRACKED ON AFT SIDE ABOVE BOLTS SECUR	ING TO TORQUE TUBE.			1	G	7	1 	3O				H1CE    					 
1997072400092	19970724	00092	SW  	1997	7	24	97ZZZX3209       	1	19970619	G	6720	22006B161416	BUSHING         			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	173P	3129 				51370				BUSHING CRACKED, THREE PLACES IN FLANGE.  BUSHING IS LOCATED IN BELLCRANK SUPPORT AT THE AFT END OF THE TAILBOOM, AND IS	 PART OF THE TAIL ROTOR CONTROL SYSTEM.  FAILED BUSHING IS THE UPPER OF TWO BUSHINGS LOCATED IN THE BELLCRANK SUPPORT. N	O DAMAGE WAS FOUND IN THE SUPPORT ASSEMBLY.  CRACK MAY HAVE BEEN CAUSED BY OVERTORQUING OF BELLCRANK BOLTS.  AIRCRAFT WA	S PREVIOUSLY INVOLVED IN INCIDENT IN WHICH TAILBOOM WAS DAMAGED, AND REBUILT.			1	G	7	1 	3U				H2SW    					 
1997072400093	19970724	00093	WP  	1997	7	24	97ZZZX3210       	1	19970410	G	6710	C0561	SPRING ASSY     			ROBSIN	R44   	R44         	7640120	WP  										CYCLIC TRIM	WORN            	B		A	BJDR	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	15	244BF	288  			C5811	0250				ARM C581-1 WAS BINDING AND WEARING INTO SHAFT.  THIS CAUSED THE LATERAL SPRING ASSEMBLY TO LOCK MOMENTARILY.  EXCESSIVE 	WEAR ON THE SPRING SHAFT COULD AFFECT THE FLIGHT CONTROLS AND AIRCRAFT CONTROL ABILITY.					1	G	7	1 	3O				H11NM   					 
1997072400094	19970724	00094	WP  	1997	7	24	97ZZZX3211       	1	19970410	G	6320	C0455	SWITCH          			ROBSIN	R44   	R44         	7640120	WP  										M/R GEARBOX	FAILED          	B			BJDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	244BF	288  				0250				TEMPERATURE SWITCH MALFUNCTIONED FOR NO OBVIOUS REASON.  CAUSED INTERMITTENT OVERTEMP LIGHT OF M/R GEARBOX.						1	G	7	1 	3O				H11NM   					 
1997072400095	19970724	00095	NM  	1997	7	24	97ZZZX3212       	1	19970314	G	6322	B1741	FAN VANE        			ROBSIN	R22   	R22BETA     		NM  										ENGINE COOLING	CRACKED         	B			BJDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	40725	1085 				1830				COOLING FAN HAD TOTAL TIME OF 1085.1 HOURS.  VANES CRACKED AT WELDS.  ROBINSON HAS NO REPAIR OR OVERHAUL FOR THIS PART. 	 SUBMITTER STATES PART SHOULD BE REPAIRA BLE AND SHOULD LAST 2,000 HOURS AND THEN BE OVERHAULED.					1	G	7	1 	3O				H10WE   					 
1997072400097	19970724	00097	NE  	1997	7	24	97ZZZX3214       	1	19970516	G	5511	7608020063051	SPAR            			SKRSKY	S76   	S76B        	8143007	NE  										HORIZ STABILIZER	DAMAGED         	B			S8GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	76UT	533  			A25300155	760443				INVESTIGATION REVEALED ARCING PIT (.1562 INCH BY .3437 INCH) DEPTH .041 INCH IN UPPER HORIZONTAL STABILIZER SPAR ON LEFT	 SIDE OF SPAR SUPPORT FITTING KEVLAR WRAP.  LEFT UPPER HORIZONTAL SUPPORT FITTING SHIM REVEALED ARCING HOLE, SUPPORT FIT	TING REVEALED NO APPRECIABLE DAMAGE FROM ARCING.  ARCING WAS DUE TO POSITION LIGHTS POWER (28VDC) WIRE ATTACHED TO HORIZ	ONTAL STABILIZER CONDUCTING THROUGH GRAPHITE AND WIRE MESH WRAPPING THROUGH THIN LAYER OF KEVLAR WRAPPING.  MOISTURE INT	RUSION OR SMALL IMPERFECTION IN KEVLAR WRAPPING ALLOWED CURRENT FLOW TO HORIZONTAL STABILIZER SUPPORT FITTING.		1	G	7	2 	4U				H1NE    					 
1997072400098	19970724	00098	NE  	1997	7	24	97ZZZX3215       	1	19970507	G	3397		WIRE            			SKRSKY	S76   	S76B        	8143007	NE  										POSITION LIGHT	MISINSTALLED    	B			S8GR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	76UT	532  				760443				POSITION LIGHT CIRCUIT BREAKER TRIPPED. INVESTIGATION REVEALED LT POSITION LIGHT POSITIVE WIRE (WIRE NR 15201J22) WAS CO	NNECTED TO POSITION LIGHT GROUND WIRE SPLICE, AND GROUND WIRE (WIRE NR L5204B20) WAS CONNECTED TO POSITION LIGHT GROUND 	WIRE SPLICE, AND GROUND WIRE (WIRE NR L5202B20) WAS CONNECTED TO POSITION LIGHT POSITIVE WIRE SPLICE.  POSITION LIGHT WI	RES WERE RE-CORRECTED PER SIKORSKY WIRE PRINT NR 76552-1056.  NO FURTHER WIRING PROBLEM EXISTS IN POSITION LIGHT SYSTEM.			1	G	7	2 	4U			 	H1NE    					 
1997073100031	19970731	00031	WP  	1997	7	31	97ZZZX3320       	1	19970310	G	6310	V31001	SWITCH          		C0511       	ROBSIN	R44   	R44         	7640120	WP  										DRV BELT TENSION	BROKE           	B			BJDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	244BF	188  				0250				ENGINE/TRANSMISSION COUPLING, VIBRATION OF ACTUATOR CAUSED ACTUATOR SPRINGS TO VIBRATE ON BOTH SWITCHES AND, THEREFORE, 	ONE BELT TENSION SWITCH TO BREAK.  SWITCH BROKE IN CLOSED POSITION.  SPRINGS TOO WEAK TO WITHSTAND VIBRATION.					1	G	7	1 	3O				H11NM   					 
1997073100032	19970731	00032	WP  	1997	7	31	97ZZZX3321       	1	19970310	G	6310	B1151	BEARING         			ROBSIN	R44   	R44         	7640120	WP  										ENG/XMSN ACTUATE	WORN            	B			BJDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	244BF	188  				0250				ENG/TRANSMISSION COUPLING, LOWER BEARING OF ACTUATOR WHICH IS CONNECTED TO LOWER SHAFT AND BEARING ASSEMBLY WORE OUT.  T	HIS CAUSED THE ACTUATOR ASSEMBLY TO VIBRATE AND, THEREFORE, ONE BELT TENSION SWITCH TO BREAK.  BEARING TOO WEAK TO HOLD 	UP TO THE PRESSURE AND VIBRATIONS.				1	G	7	1 	3O				H11NM   					 
1997073100033	19970731	00033	CE  	1997	7	31	97ZZZX3322       	1	19970424	G	5711	169110000605	SPAR            	BENDIX      		BEECH 	23    	A23         	1151204	CE  										WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3579R	1950 				M769				WING SPAR CORROSION DUE TO BONDING MATERIAL AND OUTDOOR ELEMENTS.  TIED DOWN OUTSIDE FOR SEVERAL YEARS WITHOUT USE.						1	L	7	1 	3O				A1CE    					 
1997073100034	19970731	00034	SO  	1997	7	31	97ZZZX3323       	1	19970626	G	2410	07A21443	BRACKET         	FORD        	DOFF10300J  	GULSTM	AA5   	AA5B        	3960105	SO  										ALERNATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	36ER	1428 				AA5B0897				INSPECTION FOUND CRACKS AT AFT HOLE IN WHICH THE ALTERNATOR BRACKET MOUNTS TO ENGINE AND WHERE THE THROUGH-BOLT HOLDS AL	TERNATOR TO ENGINE.  SUBMITTER SUSPECTS CAUSE, INFERIOR DESIGN OR METAL TYPE.					1	L	7	1 	3O				A16EA   					 
1997073100035	19970731	00035	CE  	1997	7	31	97ZZZX3324       	1	19970708	G	3710	242	PUMP            	AIRBORNE    		BEECH 	36    	A36         	1151604	CE  										VACUUM SYSTEM	FAILED          	E				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	361BC		270  		13826	E1331				VACUUM PUMP FAILED.  BOTH FILTERS CHANGED.  REASON FOR FAILURE, UNKNOWN AT THIS TIME.						1	L	7	1 	3O				3A15    					 
1997073100036	19970731	00036	SO  	1997	7	31	97ZZZX3325       	1	19970626	G	2410	07A21443	BRACKET         	FORD        	DOFF10300J  	GULSTM	AA5   	AA5B        	3960105	SO  											CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	3773N	1907 			A80507	AA5B1229				INSPECTION FOUND ALTERNATOR BRACKET HAD CRACKS THAT WENT THROUGH THE THICKNESS OF THE BRACKET.  SUSPECT CAUSE COULD BE H	OW PROCESS OF BRACKET IS MADE OR THE TYPE OF METAL BEING USED.					1	L	7	1 	3O				A16EA   					 
1997073100037	19970731	00037	SO  	1997	7	31	97ZZZX3326       	1	19970625	G	7110		COWLING         			PIPER 	PA32  	PA32R300    	7103213	SO  										ENG TOP COWL	DEPARTED        	D		A		O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	99	4BR	4008 				32R7780140				INSTRUCTED FLIGHT RETURNED TO HOME BASE WITH FRONT RIGHT CORNER OF COWL DISLODGED AT THE PIN LOCATION AND RAISED UP .50 	INCH.  UNIT WAS INSPECTED AND FIT OK.  SIDE LATCHES WERE ADJUSTED TO TIGHTEN UP ATTACHMENT ON PINS.  AIRCRAFT WAS FLOWN 	250 MILES WITHOUT INCIDENT.  UPON DEPARTURE FOR RETURN TRIP, COWLING PIN FAILED ALLOWING TOP COWL TO LEAVE AIRCRAFT.  SU	BSEQUENT DAMAGE WAS DONE TO RIGHT ELEVATOR.  LEFT ONE-THIRD OF COWL WAS STILL ATTACHED TO AIRCRAFT BY SIDE LATCHES.  LAN	DING WAS SAFELY MADE AT AIRPORT WITHOUT FURTHER INCIDENT.		1	L	7	1 	3O				A3SO    					 
1997073100038	19970731	00038		1997	7	31	97ZZZX3327       	4	19970710	G	6113	075263717	BULKHEAD        			CESSNA	182   	182R        	2072731	CE  										SPINNER MOUNT	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	5535N	1355 				18267777				SPINNER BULKHEAD CRACKED BEWEEN BOLT HOLES AND SEPARATED CAUSING SPINNER TO WOBBLE.  ACTION OF SPINNER CAUSED DAMAGE TO 	BOTH PROPELLER BLADES AT THE ROOTS, AND DAMAGE TO PROPELLER HUB, SPINNER AND BULKHEAD.  SUBMITTER STATED CLOSE INSPECTIO	N OF SPINNER BULKHEAD MOUNTING BOLT HOLES AT REGULAR INTERVALS MAY PREVENT SEPARATION AND FURTHER DAMAGE.				1	L	7	1 	3O			NT	3A13    					 
1997073100040	19970731	00040	CE  	1997	7	31	97ZZZX3329       	1	19970421	G	3340	HDACF1428	POWER SUPPLY    		WHELEN      	BEECH 	45    	T34A        	1152008	CE  										STROBE	CONNECTOR FAULTY	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	655K					5812093				DURING INSTALLATION OF WHELEN POWER SUPPLY PN HDA-CF-14/28 WHILE ATTEMPTING TO CONNECT STROBE HARNESS SOCKET AND JUMPER 	SOCKET, POWER SUPPLY SOCKET DISCONNECTED AND PUSHED INTO SUPPLY BOX.  THIS OCCURRED TWICE WITH VERY MINIMUM FORCE BEING 	USED TO INSTALL CONNECTOR. THIS REQUIRES REMOVING COVER TO RE-ENGAGE POWER SUPPLY CONNECTOR.  SUBMITTER SUGGESTS MANUFAC	TURER WHELEN IMPROVE METHOD OF SECURING CONNECTOR SOCKET IN POWER SUPPLY UNIT.			1	L	7	1 	3O				5A3     					 
1997073100042	19970731	00042	SO  	1997	7	31	97ZZZX3331       	1	19970628	G	5711	082202	SPAR            			LUSCOM	8     	8A          	8190104	SO  										WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	71599	1511 				3026				2.5 INCH BY 2.5 INCH AREA OF INTERGRANULAR CORROSION ON WING SPAR FOUND WHILE INSTALLING DLAHF S.R. NR 2 PRIOR TO ISSUAN	CE OF AD 96-24-17.  AD 96-24-17 ADEQUATELY DESCRIBED PROBLEM AND SOLUTION.  SPAR REPLACED 6/97.					1	H	7	1 	3O				A694    					 
1997073100043	19970731	00043	SW  	1997	7	31	97ZZZX3332       	1	19970601	G	5500	3500617	FITTING         			MOONEY	M20   	M20C        	5870208	SW  										EMPENNAGE	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	73DX					2868				SUPPORTING STRUCTURES AND ATTACHING RIVETS FOR EMPENNAGE ATTACH FITTINGS PN 350061-7, AND DASH 8, WITH SEVERE CORROSION.	  CORROSION IN THIS AREA DIFFICULT TO DETECT UNTIL EXTREMELY ADVANCED.  NINETY PERCENT OF ATTACHING RIVETS FAILED DUE TO	 CORROSION.  SUSPECT CAUSE:  AIRCRAFT BASED IN PUERTO RICO FOR 22 YEARS.				1	L	7	1 	3O				2A3     					 
1997073100045	19970731	00045	SO  	1997	7	31	97ZZZX3334       	2	19970702	G	8530	643619	PISTON          			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NR 1	ERODED          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	17	761FM	790  				21062222	245658R			SHORTLY AFTER TAKEOFF, PILOT LOST ENGINE POWER AND CRASH LANDED SHORT OF RUNWAY.  POST-ACCIDENT INVESTIGATION REVEALED C	YL NR 1 SHOWED SIGNS OF EXCESSIVE HEAT.  UPON REMOVAL OF CYL ASSY, THE PISTON WAS FOUND SEVERELY ERODED AROUND MUCH OF T	HE UPPER PERIMETER.  THIS EROSION COMPETELY DESTROYED A SIGNIFICANT PORTION OF THE TOP AND SECOND PISTON RING GROOVES. T	HE TOP OF THE PISTON AND THE COMBUSTION SIDE OF THE CYL HEAD SHOWED SIGNS OF SEVERE PITTING WHICH MAY HAVE BEEN CAUSED B	Y PISTON AND PISTON RING FRAGMENTS.  ADDITIONALLY, THE INTAKE VALVE WAS FOUND SEIZED IN THE OPEN POSITION.  THIS FAILURE	 MAY HAVE BEEN CAUSED BY DETONATION.  THE PISTON AND CYL WERE SENT TO THE MFG FOR FURTHER EVALUATION.	1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997073100046	19970731	00046	CE  	1997	7	31	97ZZZX3335       	1	19970616	G	2721	26131013	TRIM SHAFT      			CESSNA	208   	208B        	2073701	CE  										RUD PEDAL BAR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	771FE					208B0267				INSPECTION FINDING RUDDER TRIM NUT (SHAFT) WEARS OUT.  VIBRATION AND PRESSURE ARE CONCENTRATED ON A SMALL AREA OF THIS P	ARTICULAR PART AND THE PART BEING MADE OF SOFTER METAL WEARS OUT.					1	H	7	1 	3T				A37CE   					 
1997073100047	19970731	00047	SO  	1997	7	31	97ZZZX3336       	1	19970702	G	2750	6267900	BRACKET         			PIPER 	PA32  	PA32301     	7103207	SO  										FLAP HANDLE	FAILED          	D		A		K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SW	11	82723	1946 				328306002				FOUND AILERON CABLES HANGING UP.  DISCOVERED RIGHT AILERON-RUDDER INTERCONNECT CLAMP CATCHING ON BROKEN BRACKET.  SUSPEC	T CAUSE, STEPPING ON FLAP HANDLE AND/OR EXCESSIVE FORCE APPLIED ON RETRACTION AND EXTENSION.  LOCATION IS FORWARD ATTACH	 POINT FOR FLAP HANDLE.				1	L	7	1 	3O				A3SO    					 
1997073100048	19970731	00048	EA  	1997	7	31	97ZZZX3337       	2	19970601	G	7310	LW120980100	LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 2 CYL INJ	CRACKED         	E	L			E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SO	09	760SC					317785074	L827461A			FUEL INJECTOR LINE LEAKING, CRACKED DURING CRUISE.  CAUSE UNKNOWN, POSSIBLE VIBRATION.  RECOMMENDATION:  SUBMITTER SUGGE	STED TO REVISE SB 342B PAGE 24 TO DELETE THE OPTIONAL CONSTRUCTION AND TO REQUIRE THAT THE LINE BE CLAMPED PER ITEMS 35,	 36, 50, 58 OR INSTALLED AS THE PARTS MANUAL PC-315-5.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997073100049	19970731	00049	SW  	1997	7	31	97ZZZX3338       	1	19970701	G	5730		SKIN            		160010      	GULSTM	690TP 	695A        	7630519	SW  										LT WING STA 39L	CORRODED        	B	L		VE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	79PH		4976 			96029				ACFT RETURNED FOR FUSELAGE INSP AND FINAL REPAIRS OF THE RT WING.  DURING INSP, CORROSION FND IN THE LT WING IN SAME ARE	A, WS 39, BOTTOM SIDE, FWD OF THE MAIN SPAR.  EFFECTED PARTS, THE L/E SKIN, STR NR 6 INBD, AND 2 ANGLES FWD.  EXTENT OF 	CORROSION REQUIRED THESE PARTS TO BE REPLACED.  BOTH AREAS CONTAIN FUEL BLADDERS AND NO PROVISIONS FOR WEEP HOLES TO ALL	OW TRAPPED MOISTURE TO ESCAPE.  AFTER REMOVAL OF RT L/E SKIN, FURTHER INSP FOUND CORROSION ON RT WING, UPPER MAIN SPAR C	AP, UPPER FACE OF FWD FLANGE.  PREVIOUS MODELS HAVE CUSTOMER BULLETINS ADDRESSING CORROSION ON THE LOWER SPAR CAP.  CORR	OSION REMOVED AND REMAINING THICKNESS MEASURED BY NDT AND RESULTS WERE SUBMITTED TO GTEC, INC., FOR DISPOSTION.	1	H	7	2 	4T				2A4     					 
1997073100050	19970731	00050	SW  	1997	7	31	97ZZZX3339       	1	19970701	G	5730		SKIN            			GULSTM	690TP 	695A        	7630519	SW  										RT WING STA 39R	CORRODED        	B	L		VE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	79PH		4976 			96029				ACFT RETURNED FOR FUSELAGE INSP AND FINAL REPAIRS OF THE RT WING.  DURING INSP, CORROSION FND IN THE LT WING IN SAME ARE	A, WS 39, BOTTOM SIDE, FWD OF THE MAIN SPAR.  EFFECTED PARTS, THE L/E SKIN, STR NR 6 INBD, AND 2 ANGLES FWD.  EXTENT OF 	CORROSION REQUIRED THESE PARTS TO BE REPLACED.  BOTH AREAS CONTAIN FUEL BLADDERS AND NO PROVISIONS FOR WEEP HOLES TO ALL	OW TRAPPED MOISTURE TO ESCAPE.  AFTER REMOVAL OF RT L/E SKIN, FURTHER INSP FOUND CORROSION ON RT WING, UPPER MAIN SPAR C	AP, UPPER FACE OF FWD FLANGE.  PREVIOUS MODELS HAVE CUSTOMER BULLETINS ADDRESSING CORROSION ON THE LOWER SPAR CAP.  CORR	OSION REMOVED AND REMAINING THICKNESS MEASURED BY NDT AND RESULTS WERE SUBMITTED TO GTEC, INC., FOR DISPOSTION.	1	H	7	2 	4T				2A4     					 
1997073100127	19970731	00127	NM  	1997	7	31	97ZZZX3346       	1	19970707	G	3213	65650303	BOGIE BEAM      			BOEING	707   	707320C     	1383668	NM  										MLG	CRACKED         	B			VQ4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19					2648					THE MLG BOGIE BEAM WAS RECEIVED IN OVERHAULED CONDITION WITH TWO LARGE CRACKS AT THE TOW LUG.  THE BEAM WAS SUBMITTED TO	 BOEING FOR A REPAIR PROCEDURE AAG-MIA-97-0133TR.					2	L	7	4 	4F				4A26    					 
1997073100128	19970731	00128	CE  	1997	7	31	97ZZZX3347       	1	19970702	G	2720	101630000601	TORQUE TUBE     			BEECH 	200   	200BEECH    	1152920	CE  										RUDDER	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	206P				BB469					UPON REMOVAL OF THE RUDDER, A BIRD NEST AND WATER WAS FOUND INSIDE THE TORQUE TUBE CREATING A CORROSION PROBLEM INSIDE A	T TORQUE TUBE.  THERE IS NO DRAIN HOLE IN THE BELLCRANK OR TORQUE TUBE TO ALLOW WATER TO DRAIN FROM THE TUBE.					1	L	7	2 	4T				A24CE   					 
1997073100129	19970731	00129	NM  	1997	7	31	97ZZZX3348       	1	19970703	G	5312		BULKHEAD        			BOEING	727   	727251      	138408H	NM  										BS 1183 LBL 37	BEAM CRACKED    	B	S		EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	259US	64341	2962 			19978				THE CRACK WAS FOUND IN THE AFT BULKHEAD VERTICAL BEAM LBL 36.83 (LT/RT).  THE SUSPECT CAUSE WAS THE RESULT OF FATIGUE TH	AT WAS CAUSED BY PRESSURIZED FLIGHTS.  SUBMITTER RECOMMENDATION:  THERE SHOULD BE A LIMITED TIME TO INSTALL THE PREVENTI	VE MODIFICATION PER SB B727-53-0192.				2	L	7	3 	4F				A3WE    					 
1997073100130	19970731	00130	NM  	1997	7	31	97ZZZX3349       	1	19970703	G	5312		BULKHEAD        			BOEING	727   	727251      	138408H	NM  										BS 1183 RBL 37	BEAM CRACKED    	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	259US	64341	2962 			19978				THE CRACK WAS FOUND IN THE AFT BULKHEAD VERTICAL BEAM LBL 36.83 (LT/RT).  THE SUSPECT CAUSE WAS THE RESULT OF FATIGUE TH	AT WAS CAUSED BY PRESSURIZED FLIGHTS.  SUBMITTER RECOMMENDATION:  THERE SHOULD BE A LIMITED TIME TO INSTALL THE PREVENTI	VE MODIFICATION PER SB B727-53-0192.				2	L	7	3 	4F				A3WE    					 
1997073100131	19970731	00131	NM  	1997	7	31	97ZZZX3350       	1	19970703	G	5312		BULKHEAD        			BOEING	727   	727251      	138408H	NM  										BS 1183 LBL 26	CRACKED         	B	S		EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	259US					19978				THE CRACK WAS FOUND IN THE AFT BULKHEAD VERTICAL BEAM LBL 26.83 WL 257.0.  THE CRACK IS ATTRIBUTED TO PRESSURIZATION CYC	LES.  RECOMMENDATION:  THE SB 53-0182 RECOMMENDED TO INSTALL THE PREVENTIVE MODIFICATION AT OR BEFORE 60,000 CYCLES.  SU	BMITTER RECOMMENDED THE PREVENTIVE MODIFICATION MUST BE INSTALLED AT OR BEFORE 45,000 CYCLES.				2	L	7	3 	4F				A3WE    					 
1997073100133	19970731	00133	NE  	1997	7	31	97ZZZX3352       	2	19970706	G	7311	10585F	EXCHANGER       			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					FUEL/OIL COOLER	CRACKED         	B	S		XE9R	E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		CL	CLIMB          	1			CE	07	642JL	6060 			884	FA30	PCE95067			ON TAKEOFF, ENGINE LOST OIL PRESSURE.  ENGINE SHUT DOWN AND NORMAL LANDING MADE.  PROBLEM FOUND TO BE ONE LONG CRACK AT 	WELD ON SIDE OF HEAT EXCHANGER.  SUSPECT FATIGUE OR AGE.					2	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997073100134	19970731	00134	EU  	1997	7	31	97ZZZX3353       	1	19970708	G	2422	501123501	INVERTER        			BRAERO	DH125 	BAE125800A  	1500285	EU  										NR 2	FAILED          	E				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			EA	25	801MB		1860 		1107	258067				AFTER TAKEOFF, PILOT REPORTED NR 2 INVERTER FAIL LIGHT WITH CORRESPONDING NR 2 SSU (SIGNAL SUMMING UNIT) FAIL LIGHT AND 	NR 2 SSU CIRCUIT BREAKER TRIPPED.  SUSPECT CAUSE:  NR 2 INVERTER SPIKED BEFORE COMPLETE FAILURE CAUSING IT TO DAMAGE CIR	CUITRY IN THE SSU UNIT.  NR 2 INVERTER WAS REPLACED.  NR 2 SSU UNIT WAS REPAIRED.				2	L	7	2 	4F			RT	A3EU    					 
1997073100135	19970731	00135	SO  	1997	7	31	97ZZZX3354       	1	19970623	G	2750	1159SCH2105	VALVE           			GULSTM	G1159 	G1159       	3953505	SO  										FLAP CONTROL	MISWIRED        	B		A	UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	902MP				454B	241				SOMETIMES FLAPS WOULD GO PAST THE DESIRED SETTING.  PROBLEM WAS TRACED TO A STICKING FLAP CONTROL VALVE.  ORDERED AND IN	STALLED OVERHAULED FLAP CONTROL VALVE.  WITH FLAP HANDLE 'UP', FLAPS EXTENDED.  USED POWER SUPPLY TO CONTROL NEW VALVE. 	 WHEN THE EXTEND COIL WAS POWERED, THE FLAPS RETRACTED.  WHEN THE RETRACT COIL WAS POWERED, THE FLAPS EXTENDED.  THE FLA	PS MANUAL CONTROL WORKED NORMALLY.  ORDERED AND INSTALLED ANOTHER FLAP CONTROL VALVE.  THIS ONE WORKED NORMALLY.			2	L	7	2 	4F			RT	A12EA   					 
1997073100136	19970731	00136	NM  	1997	7	31	97ZZZX3355       	1	19970601	G	5313		STRINGER        			BOEING	727   	727287      	1384020	NM  										BS 1166 S29R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	920PG					21688				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S29R AT FS 1166.						2	L	7	3 	4F			RT	A3WE    					 
1997073100137	19970731	00137	NM  	1997	7	31	97ZZZX3356       	1	19970601	G	5330		SKIN            			BOEING	727   	727287      	1384020	NM  										BS 1070 S18L	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	920PG					21688				DURING C-CHECK INSPECTION, SEVERAL GOUGES WERE NOTED ON AIRCRAFT SKIN PANEL AT FS 1070L AT S18L.						2	L	7	3 	4F			RT	A3WE    					 
1997073100138	19970731	00138	NM  	1997	7	31	97ZZZX3357       	1	19970601	G	5315		FLOOR BEAM      			BOEING	727   	727287      	1384020	NM  										FS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	920PG					21688				DURING C-CHECK INSPECTION, FOUND LEVEL 2 CORROSION ON FLOOR BEAM LOWER CHORD AT FS 1130.						2	L	7	3 	4F			RT	A3WE    					 
1997073100427	19970731	00427	EU  	1997	7	31	97ZZZX3376       	1	19970708	G	6710	109011057105	ROD END         		109011059105	AGUSTA	A109  	A109A2      	0260120	EU  										M/R BLUE	DISPLACED       	B			KUVR	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SO	19	8WH	707  			432	7256				PILOT NOTICED UNUSUAL VERTICAL VIBRATION AND PRECAUTIONARY LANDING WAS MADE.  FOUND BLUE M/R PITCH CHANGE LINK ROD END B	EARING POPPED OUT OF ITS HOUSING CAUSING EXCESSIVE RADIAL PLAY.  SUSPECT CAUSE, AGE AND/OR TIME ON PART.  UNUSUAL WEAR N	OT NOTICED ON PRE-FLIGHT INSPECTION.				1	G	7	2 	3U				H7EU    					 
1997073100428	19970731	00428	NE  	1997	7	31	97ZZZX3377       	1	19970710	G	6320	643520536101	MAIN SHAFT      		643520500048	SKRSKY	S64   	S64F        		NE  										MAIN GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC	2852 	984  		18	64084				PART WAS MPI'D AND FOUND TO HAVE ONE CRACK INDICATION LOCATED AT THE UPPER END OF THE LOWER SPLINES.  THE INDICATION EXT	ENDS FROM THE SPLINE RADIUS AND GOES TOWARD THE TOOTH FACE AT APPROXIMATELY A 45 DEGREE ANGLE.  LENGTH OF INDICATION IS 	APPROXIMATELY 0.050 INCH LONG.  NO OTHER INDICATIONS WERE FOUND.				2	G	7	2 	4U				H6EA    					 
1997073100429	19970731	00429		1997	7	31	97ZZZX3378       	1	19970707	G	2620	01876296	CARTRIDGE       	KIDDE       	89524001    															FIREX CONTAINER	MALFUNCTION     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05					AEN220					CARTRIDGE FAILED TO BURST FIREX CONTAINER DISC ONCE FIRED.  SUSPECT CAUSE:  DURING OVERHAUL AND SERVICE OF CONTAINER, OX	YGEN SYSTEMS OR THE AIRLINES (CANADIAN) REPLACED CARTRIDGE WITH ONE MANUFACTURED BY OVERLAND AVIATION.  ALTHOUGH OVERLAN	D AVIATION HAS FAA PMA, THEY DO NOT INCORPORATE LATEST DESIGN CHANGES BY CONTAINER DESIGNER AND MANUFACTURER, WALTER KID	DE AEROSPACE.  SUBMITTER RECOMMENDS ONLY MANUFACTURER'S APPROVED COMPONENTS SHOULD BE USED WHEN OVERHAULING OR SERVICING	 A FIREX CONTAINER.															 
1997073100430	19970731	00430	CE  	1997	7	31	97ZZZX3379       	1	19970703	G	3252	17430213	CYLINDER        		17430203    	CESSNA	177   	177B        	2073708	CE  										SHIMMY DAMPENER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	19974	2505 				17702617				SHIMMY DAMPENER HOUSING FAILED DURING FLIGHT.  UNIT FAILED AT THE OUTER PORTION OF OUTER RETAINING RING FLANGE.  FAILURE	 WAS ON DOWN-WIND LEG AFTER A NORMAL TOUCH AND GO.  SUBMITTER STATES OWNER MENTIONED SEVERAL YEARS AGO, TWO SEPARATE SEV	ERE SHIMMY INSTANCES THAT COULD HAVE CREATED CRACKS.  PRIOR TO FAILURE, UNIT WAS VISUALLY INSPECTED FOR LEAKS AND CHECKE	D FULL STROKE FOR AIR IN SYSTEM.			1	H	7	1 	3O				A13CE   					 
1997073100431	19970731	00431	EA  	1997	7	31	97ZZZX3380       	2	19970703	G	7310	38B0100006D0210	HOSE            	DEUTSCH     		CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F     	41514	EA  					FUEL PUMP	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	19974	141  				17702617	L2276836A			DURING ANNUAL INSPECTION, FUEL WAS SHUT OFF FOR CLEANING CARBURETOR, DRAIN, AND GASCULATOR.  UPON TURNING FUEL ON, FUEL 	LEAKED FROM HOSE IN A STEADY STREAM.  HOSE WAS LOCATED ON LOW PRESSURE SIDE FEEDING ENGINE DRIVEN PUMP.  HOSE WAS ALSO I	N A LOCATION WHERE IT WAS NOT AGITATED BY THE PREVENTATIVE MAINTENANCE.  SUBMITTER STATED THIS IS THE SECOND DEUTSCH HOS	E FAILURE ON THIS AIRCRAFT WITH LOW TIME.			1	H	7	1 	3O	3	O		A13CE   	E286				 
1997073100432	19970731	00432	SO  	1997	7	31	97ZZZX3381       	1	19970707	G	5541	40039003	RIB             			PIPER 	PA31T 	PA31T1      	7103126	SO  										RUDDER	CORRODED        	B		A	RC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	27BF	6432 				31T8104038				DURING A 100-HOUR INSPECTION, A RIVET WAS FOUND MISSING ON THE BOTTOM OF THE RUDDER WHERE THE TORQUE TUBE IS RIVETED TO 	THE BOTTOM RIB. CLOSER INSPECTION REVEALED HOLE WAS CORRODED.  DRILLED AND PEELED BACK SKIN.  FOUND STEEL TORQUE TUBE RU	STED AND BOTTOM RIB HEAVILY CORRODED.  REMOVED AND REPLACED AFFECTED PARTS WITH NEW.  SUBMITTER STATED PROBLEM COULD BE 	CAUSED BY PLUGGED DRAIN HOLES OR DISSIMILAR METALS.  RECOMMEND CLOSE INSPECTION OF THIS AREA AND TO ENSURE DRAIN HOLES A	RE CLEAR.		1	L	7	2 	3T				A8EA    					 
1997073100433	19970731	00433	SO  	1997	7	31	97ZZZX3382       	1	19970707	G	2720	40040007	TORQUE TUBE     			PIPER 	PA31T 	PA31T1      	7103126	SO  										RUDDER	RUSTED          	B			RC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	27BF	6432 				31T8104038				DURING A 100-HOUR INSPECTION, A RIVET WAS FOUND MISSING ON THE BOTTOM OF THE RUDDER WHERE THE TORQUE TUBE IS RIVETED TO 	THE BOTTOM RIB. CLOSER INSPECTION REVEALED HOLE WAS CORRODED.  DRILLED AND PEELED BACK SKIN.  FOUND STEEL TORQUE TUBE RU	STED AND BOTTOM RIB HEAVILY CORRODED.  REMOVED AND REPLACED AFFECTED PARTS WITH NEW.  SUBMITTER STATED PROBLEM COULD BE 	CAUSED BY PLUGGED DRAIN HOLES OR DISSIMILAR METALS.  RECOMMEND CLOSE INSPECTION OF THIS AREA AND TO ENSURE DRAIN HOLES A	RE CLEAR.		1	L	7	2 	3T				A8EA    					 
1997073100434	19970731	00434	CE  	1997	7	31	97ZZZX3383       	1	19970717	G	2571		VENT            			CESSNA	180   	180K        	2072624	CE  										BATTERY BOX	PLUGGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	2643K					1805023				AT ANNUAL INSPECTION, NOTICED CORROSION ON THE MAIN ELECTRICAL CONTACTOR AND THE STARTER RELAY.  SUSPECT THE BATTERY WAS	 VENTING OUT BY THE CABLES.  CHECKING THE BATERY BOX VENT, IT WAS FILLED WITH MUD DAUBER LARVA.  THIS AIRCRAFT HAD ACCUM	ULATED 36 HOURS SINCE THE LAST OVERHAUL.				1	H	7	1 	3O				5A6     					 
1997073100435	19970731	00435	CE  	1997	7	31	97ZZZX3384       	1	19970630	G	3243	MS2877132	O-RING          	PARKERHANFIN	30100       	CESSNA	421   	421B        	2076014	CE  										LT BRAKE	WORN            	D				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			GL	05	41019					421B0401				LEFT BRAKE INOPERABLE CAUSING PILOT TO LOSE CONTROL AND STRIKE ANOTHER AIRCRAFT.  INVESTIGATION FOUND NO FLUID IN BRAKE,	 CAUSED BY O-RINGS BEING OLD, WORN, AND HARD AND LEAKING.  REPLACED O-RINGS AND SERVICED BRAKE SYSTEM.  OPERATION WAS NO	RMAL.				1	L	7	2 	3O				A7CE    					 
1997073100436	19970731	00436	EU  	1997	7	31	97ZZZX3385       	1	19970711	G	2820	645471037842	SAFETY VALVE    			PILATS	PC12  	PC12        	7090550	EU  										DIFF CONTROL	DEFECTIVE       	B			LF1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	62JT	1074 			83B0013	107				PILATUS PN 959-90-91-131 SAFETY VALVE.  DURING NORMAL CLEANING, NOTED THAT JET FUEL WAS COMING OUT OF THE DIFFERENTIAL C	ONTROL VALVE ASSY PORTION OF THE SAFETY VALVE.  CLOSER INVESTIGATION SHOWED SMALL BELLOWS AND POPPET VALVE UNSERVICEABLE	.  CAUSE - THE STATIC ATMOSPHERIC PRESSURE LINE IS OPEN TO ATMOSPHERE IN THE FUEL FILTER BAY, AND FUEL LEAKING OR REMAIN	ING WOULD OR COULD END UP IN THE VALVE.			1	L	7	1 	3T			RT	A78EU   					 
1997073100438	19970731	00438	CE  	1997	7	31	97ZZZX3387       	1	19970718	G	2810	603890215	FUEL CELL       			BEECH 	60    	60          	1153602	CE  										FUEL SYSTEM	DETERIORATED    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	713V				7714757	P16				FUEL CELL BEGAN LEAKING IN MARCH, 1994; WAS REMOVED AND SENT TO A/C FUEL CELLS WORLDWIDE, INC., FOR REPAIR.  A/C CONDEMN	ED CELL AND REBUILT CELL WAS PURCHASED FOR REPLACEMENT (WORK ORDER NR 9938, INSPECTED 4-18-94) IN APRIL, 1994.  JUNE, 19	97, REPLACEMENT CELL REMOVED FOR LEAKS AND RETURNED TO A/C FUEL CELLS FOR WARRANTY REPAIR. WARRANTY REPAIR REFUSED, A/C 	CONDEMNED REPLACEMENT CELL.  AIRCRAFT FUEL SYSTEM KEPT FULL AT ALL TIMES.  REASON FOR DETERIORATION NOT KNOWN.			1	L	7	2 	3O				A12CE   					 
1997073100439	19970731	00439	CE  	1997	7	31	97ZZZX3388       	1	19970718	G	2810	603890223	FUEL CELL       			BEECH 	60    	60          	1153602	CE  										FUEL SYSTEM	DETERIORATED    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	713V				7862689N	P16				FUEL CELL BEGAN LEAKING IN MARCH, 1994; WAS REMOVED AND SENT TO A/C FUEL CELLS WORLDWIDE, INC., FOR REPAIR.  A/C CONDEMN	ED CELL AND REBUILT CELL WAS PURCHASED FOR REPLACEMENT (WORK ORDER NR 9681, INSPECTED 4-12-94) IN APRIL, 1994.  OCTOBER,	 1996, REPLACEMENT CELL REMOVED FOR LEAKS AND RETURNED TO A/C FUEL CELLS FOR WARRANTY REPAIR.  WARRANTY REPAIR REFUSED, 	A/C CONDEMNED REPLACEMENT CELL.  AIRCRAFT FUEL SYSTEM KEPT FULL AT ALL TIMES.  REASON FOR DETERIORATION NOT KNOWN.			1	L	7	2 	3O				A12CE   					 
1997073100440	19970731	00440	SO  	1997	7	31	97ZZZX3389       	1	19970717	G	7820	FL099005705	MUFFLER         			GULSTM	GA7   	GA7         	3960401	SO  										TAIL PIPE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	779GA	4300 				GA7066				DURING ANNUAL INSPECTION, RIGHT EXHAUST MUFFLER WAS PRESSURIZED AND FOUND CRACKED AT TAIL PIPE OUTLET.  A LARGE QUANTITY	 OF SOOT (EXHAUST GAS RESIDUE) WAS SEEN FLOWING OUT OF THE CRACK AND INTO THE DUCTING TO THE CABIN HEAT SYSTEM.  THIS DE	FECT HAD BEEN LEAKING FOR SOME TIME AND VERY DIFFICULT TO SEE DUE TO THE LOCATION, THE LT MUFFLER SHOWED SIMILAR DEFECTS	.			1	L	7	2 	3O				A17SO   					 
1997073100441	19970731	00441	CE  	1997	7	31	97ZZZX3390       	1	19970613	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										MLG	SHEARED         	G				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	03	9851B					172RG				PILOT NOTICED GEAR ON RIGHT SIDE HANGING DOWN DURING APPROACH TO LAND AIRCRAFT.  AFTER SEVERAL TRIES, PLOT DECIDED TO LA	ND GEAR UP.  THERE WERE NO INJURIES, AND MINOR DAMAGE TO THE PROP AND BELLY OF AIRCRAFT.  INSPECTION OF THE MAIN GEAR RE	VEALED THE GEAR INSIDE THE PIVOT ASSEMBLY HAD SHEARED.  THIS WAS SUSPECTED TO BE CAUSED BY HARD LANDINGS OR AIRCRAFT MIS	USE.  THIS IS A FLIGHT SCHOOL AIRCRAFT.			1	H	7	1 	3O				3A17    					 
1997080700252	19970807	00252	CE  	1997	8	7	97ZZZX3399       	1	19970717	G	2720	0024100343	TUBE            			BEECH 	58    	58          	1152740	CE  										RUD INTERCONNECT	CHAFED          	B		A	EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1093G	207  				TH1793				DURING 100-HOUR INSPECTION, FOUND RUDDER INTERCONNECT TUBE CHAFED THROUGH BY A FLOOR ATTACHMENT SCREW - TOO LONG OR WRON	G LOCATION.  SUBMITTER STATED HAVE FOUND SIMILAR DAMAGE ON OTHER AIRCRAFT.  THIS TUBE HAS A THICK SIDE WALL AND HAS A 1.	50 INCH LONG ARCING CHAFE MARK WHICH CUTS THROUGH TUBE SIDE WALL.				1	L	7	2 	3O				3A16    					 
1997080700253	19970807	00253	EA  	1997	8	7	97ZZZX3400       	2	19970701	G	8540	STD2167	BOLT            		LW13797     	BEECH 	23    	19A         	1151214	CE  	LYC   	O320  	O320E2C     	41508	EA  					IDLER GEARSHAFT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	16BD	5570 	1613 			MB456	L2612927A			DURING ROUTINE INSPECTION TO C/W AD 96-09-10C (OIL PUMP IMPELLER INSP), THE ACCESSORY CASE WAS REMOVED FROM THE ENGINE. 	 UPON INSP OF THE CRANKSHAFT IDLER GEARS, THE LT SIDE GEAR WOBBLED SIGNIFICANTLY.  UPON REMOVAL OF THE IDLER GEAR, DETER	MINED THE LOWER BOLT SECURING IDLER GEAR SHAFT MOUNT (PN LW-13797), HAD BROKEN AT THE INTERFACE BETWEEN THE SHAFT MOUNT 	AND THE CRANKCASE.  THE THREADED PORTION OF THE BOLT WAS STILL IN THE CRANKCASE.  THE BOLT HEAD AND SHANK COULD NOT BE L	OCATED.  THIS CAUSED THE IDLER GEARSHAFT TO MOVE AND WORK ON THE ALUMINUM CRANKCASE CREATING AN ENLARGED OPENING THROUGH	 WHICH OIL PASSES TO LUBRICATE THE IDLER GEAR.  SUBMITTER STATED CAUSE OF FAILURE MAY BE IMPROPER TORQUE OF THE BOLT.	1	L	7	1 	3O	3	O		A1CE    	E274				 
1997080700254	19970807	00254	CE  	1997	8	7	97ZZZX3401       	1	19970714	G	2750	50250052	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  										RT FLAP	BROKEN          	B	S		EIYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	20SS					310Q0521				PILOT REPORTED LOOSENESS IN RIGHT, INBOARD FLAP DURING PRE-FLIGHT.  INSPECTION REVEALED INBOARD BELLCRANK ARMS, 2 EACH, 	BROKEN LOOSE FROM ASSY.  SUBMITTER RECOMMENDS THOROUGH INSPECTION OF FLAP CONTROL SYSTEM DURING ANNUAL INSPECTION.					1	L	7	2 	3O				3A10    					 
1997080700255	19970807	00255	CE  	1997	8	7	97ZZZX3402       	1	19970601	G	2823	HE7805	SELECTOR VALVE  			BEECH 	95    	95B55       	1152729	CE  										FUEL SYSTEM	LEAK            	B			H8AR	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			EA	05	2018Q					TC2165				FUEL VALVE BEGAN LEAKING 24 HOURS AFTER INSTALLATION FROM NEW.						1	L	7	2 	3O			RT	3A16    					 
1997080700256	19970807	00256	CE  	1997	8	7	97ZZZX3403       	1	19970601	G	2823	HE7805	SELECTOR VALVE  			BEECH 	95    	95B55       	1152729	CE  										FUEL SYSTEM	LEAK            	B			H8AR	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			EA	05	2018Q				A97060097	TC2165				THIS VALVE INSTALLED TO REPLACE 2 OTHER PREVIOUS VALVES INSTALLED AS NEW THAT FAILED A SHORT TIME AFTER INSTALLATION.						1	L	7	2 	3O			RT	3A16    					 
1997080700257	19970807	00257	CE  	1997	8	7	97ZZZX3404       	1	19970601	G	2823	HE7805	SELECTOR VALVE  			BEECH 	95    	95B55       	1152729	CE  										FUEL SYSTEM	LEAK            	B		A	H8AR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	05	2018Q	3    			A97040073	TC2165				FUEL VALVE INSTALLED TO REPLACE DEFECTIVE NEW FUEL VALVE WITH ONLY 24 HOURS TIME.  THIS VALVE BEGAN TO LEAK WITH 25 HOUR	S TIME IN SERVICE.					1	L	7	2 	3O			RT	3A16    					 
1997080700258	19970807	00258	CE  	1997	8	7	97ZZZX3405       	1	19970601	G	5711	17107036	SPAR            			CESSNA	177   	177B        	2073708	CE  										CARRY THROUGH	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	35090	2897 				17702201				FOUND ON ANNUAL INSPECTION, INTERGRANULAR CORROSION ON CARRY-THROUGH SPAR.  SOME SPOTS 2 INCHES AND .0625 INCH DEEP, PLU	S OTHER CORROSION.  SUBMITTER STATED THIS IS HARD TO SEE WITHOUT REMOVING HEADLINER.					1	H	7	1 	3O				A13CE   					 
1997080700259	19970807	00259	CE  	1997	8	7	97ZZZX3406       	1	19970624	G	3230	ADNE4JW	ROD END         			CESSNA	402   	402C        	207590R	CE  										NLG	BEARING FAILED  	A		A	GULC	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	01	401BK	3500 				402C0297				NOSE GEAR COLLAPSED UPON LANDING.  THE NOSE GEAR ROD END BEARING SEPARATED FROM HOUSING ALLOWING NOSE GEAR TO BECOME SEP	ARATED FROM NOSE GEAR ACTUATOR.  THIS ALLOWED ACTUATOR TO FULLY EXTEND AND GIVE THE PILOT THE APPEARANCE OF 3 GREEN, DOW	N, AND LOCKED, BUT, ACTUALLY, THE NOSE GEAR WAS NO LONGER CONNECTED TO THE NOSE GEAR ACTUATOR.  THE BEARING ITSELF WAS S	TILL CONNECTED TO THE NOSE GEAR.  SUSPECT CAUSE, NO REQUIREMENT TO 'TIME CHANGE' THESE ITEMS.  SUBMITTER STATED THESE AR	E OPERATED TO 'FAILURE' ITEMS.  THEY SHOULD BE TIME CHANGED OR ROUTINELY DYE PENETRANT INSPECTED.  HAVE CONTACTED THE AC	O IN WICHITA.  AC E-117W.  SEE AD 84-20-02.	1	L	7	2 	3O				A7CE    					 
1997080700261	19970807	00261	NE  	1997	8	7	97ZZZX3408       	2	19970717	G	7310	AE7010000H1700	HOSE            	AEROQUIP    		CNDAIR	CL600 	CL6002A12   	1900304	EA  	GE    	CF34  	CF341A      		NE  					LT PYLON	RUPTURED        	D		A		K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	05	601TX					3005				THE MOTIVE FLOW FUEL LINE THAT RUNS FROM THE LEFT WHEELWELL TO THE LEFT PYLON RUPTURED CAUSING FUEL TO VENT OVERBOARD. T	HE FUEL THAT VENTED OVERBOARD THEN MIGRATED AFT INTO THE TAIL CONE AREA CREATING A POTENTIAL HAZARD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997080700262	19970807	00262	CE  	1997	8	7	97ZZZX3409       	1	19970709	G	7120	05131324	MOUNT           			CESSNA	175   	175         	2072502	CE  										UPPER RT	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	7151M					55451				ACFT OWNER REPORTED THE COWL DID NOT FIT RIGHT.  UPON EXAMINATION, DETERMINED THE RT STRINGER ASSY, ENGINE MOUNT UPPER, 	HAD FAILED AT THE POINT WHERE THE UPPER RT ENGINE MOUNT BOLT PASSES THROUGH THE MOUNTING BRACKET.  THE FIREWALL ATTACH R	IVETS HAD RIPPED OUT FOR ABOUT 3 INCHES IN EACH DIRECTION ALLOWING WEIGHT OF ENGINE TO PULLTHE FIREWALL OUT ABOUT O.50 I	NCH DISPLACING THE COWL WHICH IS ATTACHED TO THE ENGINE MOUNT.  EXAMINATION OF THE LT STRINGER ASSY, ENG MOUNT UPPER, RE	VEALED THAT THAT PART HAD CRACKED AND WAS AT NEAR FAILURE.  THE ENGINE MOUNTING WAS VERY NEAR FAILURE.  NEW PARTS WILL B	E INSTALLED AND ACFT RETURNED TO SERVICE.	1	H	7	1 	3O			NT	3A17    					 
1997080700263	19970807	00263	CE  	1997	8	7	97ZZZX3410       	1	19970709	G	7120	05131323	MOUNT           			CESSNA	175   	175         	2072502	CE  										LT UPPER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	7151M					55451				ACFT OWNER REPORTED THE COWL DID NOT FIT RIGHT.  UPON EXAMINATION, DETERMINED THE RT STRINGER ASSY, ENGINE MOUNT UPPER, 	HAD FAILED AT THE POINT WHERE THE UPPER RT ENGINE MOUNT BOLT PASSES THROUGH THE MOUNTING BRACKET.  THE FIREWALL ATTACH R	IVETS HAD RIPPED OUT FOR ABOUT 3 INCHES IN EACH DIRECTION ALLOWING WEIGHT OF ENGINE TO PULLTHE FIREWALL OUT ABOUT O.50 I	NCH DISPLACING THE COWL WHICH IS ATTACHED TO THE ENGINE MOUNT.  EXAMINATION OF THE LT STRINGER ASSY, ENG MOUNT UPPER, RE	VEALED THAT THAT PART HAD CRACKED AND WAS AT NEAR FAILURE.  THE ENGINE MOUNTING WAS VERY NEAR FAILURE.  NEW PARTS WILL B	E INSTALLED AND ACFT RETURNED TO SERVICE.	1	H	7	1 	3O			NT	3A17    					 
1997080700264	19970807	00264	NE  	1997	8	7	97ZZZX3411       	2	19970716	G	8550	CH48103	FILTER          	CHAMPION    		MAULE 	M6    	M6235       	5460160	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					ENGINE OIL	LEAKS           	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	91AR		35   			7446C	L2226848A			OIL FILTER WAS INSTALLED ON 6-28-97.  NOTED AT THE TIME THAT THE LOCKING TAB WAS NEARLY FLAT AGAINST THE BOWL OF THE CAN	NISTER, SUCH THAT THE TAB HAD TO BE BENT SLIGHTLY TO ADMIT .032 INCH SAFETY WIRE.  NO LEAKS WERE FOUND AFTER A GROUND RU	N-UP.  AFTER 3 HOURS OF SERVICE, THE FILTER DEVELOPED A LEAK AROUND THE BASE OF THE LOCKING TABS CAUSING A LOSS OF 1 QUA	RT IN A  20 MINUTE FLIGHT ON 7-14-97.  INSPECTION OF THE FILTER CASE REVEALS CRACKS AT THE SITE OF EACH OF THE 4 SPOT WE	LDS WHICH ATTACH THE LOCKING TABS.		1	H	7	1 	3O	3	O		3A23    	1E4				 
1997080700265	19970807	00265	GL  	1997	8	7	97ZZZX3412       	3	19970717	G	6111	M10083K	BLADE           			CESSNA	208   	208         	2073702	CE  						HARTZL	H3B3M	HCB3M       	GL  	STA 24	DAMAGED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	192AV				9281A	20800215		G13137		PROPELLER DE-ICE BOOT BURNED OUT AND DAMAGED PROPELLER BLADE AT STA 24.  SUBMITTER STATES A POSSIBLE CAUSE, ROCK NICK ON	 BOOT.					1	H	7	1 	3T			NT	A37CE   		5	C	P9NE	 
1997080700266	19970807	00266	GL  	1997	8	7	97ZZZX3413       	3	19970724	G	6114		HUB             			PIPER 	PA46  	PA46310P    	7104605	SO  						HARTZL	HCC2Y	BHCC2YF1    	GL  	BLADE CLAMP	CRACKED         	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	2604X							AM2737		PROPELLER WAS OVERHAULED DURING ANNUAL AND WAS FOUND TO HAVE A CRACK IN HUB.  CRACK WAS LOCATED AROUND BLADE CLAMP AREA 	OF HUB AT BOLT HOLE.  PROPELLER HAD NOT BEEN OVERHAULED SINCE 1989 (993.0 TSOH).  SUBMITTER HIGHLY RECOMMENDS THE PROPEL	LER BE OVERHAULED EVERY 5 YEARS PER MANUFACTURER.  HARTZELL AD 77-12-06 COMPLIANCE IS NOW 12,000 HOURS WHICH MOST PROPS 	WILL NEVER REACH.			1	L	7	1 	3O				A25SO   		5	C	P920	 
1997080700267	19970807	00267	GL  	1997	8	7	97ZZZX3414       	3	19970715	G	6111		BLADE           			SLNSBY	T67   	T67M260     	8323006	EU  						HOFMAN	HOV123	HOV123KV    	GL  	PROPELLER	LOOSE           	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			AB	AEROBATIC      	1			SW	17	3037C	871  				2134		B696		AFTER AEROBATICS, EXCESSIVE NOSE/PROPELLER VIBRATION WAS FELT, VERY ROUGH AND LOW AIRSPEED.  ACFT LANDED SAFELY.  FOUND 	NR 1 PROPELLER BLADE HAD EXCESSIVE PLAY.  REMOVED AND REPLACED THE PROPELLER.  PROPELLER WAS SENT TO MANUFACTURER FOR IN	SPECTION AND REPAIR.				1	L	7	1 	3O			NT	A73EU   		5	C	P5EU2	 
1997080700268	19970807	00268	EA  	1997	8	7	97ZZZX3415       	2	19970623	G	8530	7224Z	ROCKER BOX TAB  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					COVER	WORN            	B			APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3582X		180  			318052105	L421361A			ROCKER PIN RETAINING TAB ON COVER WORN EXCESSIVELY.  THIS ENGINE HAS 180 HOURS TSOH!						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997080700269	19970807	00269	SO  	1997	8	7	97ZZZX3416       	1	19970722	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG DOOR	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			AL	01	45052					318152063				GEAR WOULD NOT EXTEND, GREEN LIGHTS FOR LT MLG AND NLG.  RED INTRANSIT LIGHT STAYED ON.  CYCLED GEAR UNTIL 3 GREEN.  LAN	DED, FOUND FORWARD HINGE ON RT INNER GEAR DOOR BROKEN.  PART NUMBER IS IMPROVED VERSION THAT TERMINATES REPETITIVE AD.					1	L	7	2 	3O				A20SO   					 
1997080700270	19970807	00270	SO  	1997	8	7	97ZZZX3417       	1	19970721	G	2913	HYC5005	POWER PACK      	PRESTOLITE  		PIPER 	PA32  	PA32R300    	7103213	SO  										MLG HYD	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	09	47423	3521 				32R7880006				LANDING GEAR ONLY PARTIALLY EXTENDED WITH NOSE AND RT MAIN LOCKED, BUT LT MAIN UNLOCKED, CIRCUIT BREAKER KEPT TRIPPING N	OT ALLOWING LT MAIN TO EXTEND FULLY.  EMERGENCY EXTENSION WAS ATTEMPTED (FREEFALL), BUT NO HELP.  LANDING WAS MADE ON GR	ASS STRIP WITH MINIMAL DAMAGE.  POWER PACK REMOVED FOR OVERHAUL AND REINSTALLED.  GEAR OPERATION WAS GOOD IN NORMAL AND 	EMERGENCY MODES.			1	L	7	1 	3O				A3SO    					 
1997080700271	19970807	00271	GL  	1997	8	7	97ZZZX3418       	3	19970623	G	6111		BLADE           			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	BOLT HOLE	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	5139B	6964 	3464 			15283771		R773437		CRACKED ON NR 1 BLADE SIDE AT TOP, NEXT TO HOLE, APPROXIMATELY .50 INCH LONG.  FOUND DURING INSPECTION REQUIRED BY AD 97	-06-16 AND SB 221B,					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997080700272	19970807	00272	SO  	1997	8	7	97ZZZX3419       	2	19970721	G	8530	532129	VALVE           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					ENGINE INTAKE	WRONG PART      	B	L		XA14	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	68BB		177  			TJ317	274344R			DURING AN ANNUAL INSPECTION, FOUND LEAKING EXHAUST VALVES ON NR 2, NR 4, AND NR 6 CYLINDERS, ON LT ENGINE.  SINCE TOTAL 	TIME OF THIS ENGINE WAS ONLY 177.3 HOURS SINCE REBUILT, THE CUSTOMER DECIDED TO REMOVE ALL CYL'S FOR INSP AND/OR REPAIR.	  CYL'S DISASSEMBLED, 2 INTAKE VALVES WERE TCM PN 532129.  ACCORDING TO RESEARCH, THESE INTAKE VALVES ARE NOT PROPER P/N	 FOR THIS MODEL ENGINE.  OTHER 4 INTAKE VALVES WERE PROPER P/N, HOWEVER, INTAKE VALVE SEATS APPEAR TO HAVE BEEN CUT TOO 	WIDE.  ALL 6 EXHAUST VALVES WERE REJECTED DUE TO EXCESSIVE STEM WEAR AND THE VALVE FACES WERE BURNED.  ALSO, FOUND A RIN	G STEP IN EACH CYL AND MAY REQUIRE BORING OF EACH OF THE CYLINDERS.  ENGINE REBUILT BY TCM, MOBILE, ALA, 4-3-96.	1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1997080700273	19970807	00273	CE  	1997	8	7	97ZZZX3420       	1	19970717	G	2822	41400015	PUMP            	DUKES       		CESSNA	182   	TR182       	2072735	CE  										FUEL BOOST	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	736YQ				18704	R18200790				DUKES ELECTRIC FUEL PUMP RELIEF VALVE ASSEMBLY HAD BEEN CROSS-THREADED ON ORIGINAL ASSEMBLY.  OVER TIME, STRESS CAUSED P	UMP BODY TO CRACK.  IF NOT FOUND, PROBLEM COULD HAVE ALLOWED RELIEF VALVE TO BE EJECTED FROM PUMP BODY CAUSING COMPLETE 	FAILURE AND MASSIVE FUEL LEAK AND ENGINE FAILURE.				1	H	7	1 	3O				3A13    					 
1997080700274	19970807	00274	CE  	1997	8	7	97ZZZX3421       	1	19970721	G	2434	DOFF10300G	ALTERNATOR      	FORD        		CESSNA	172   	R172K       	2072431	CE  										FWD HOUSING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	758BZ		370  		2060285	R1722977				TOTAL AIRCRAFT TIME 3,176.9 HOURS.  DURING AN ANNUAL INSPECTION, THE ALTERNATOR FORWARD HOUSING WAS FOUND CRACKED AT THE	 WEB SUPPORTS.  SUBMITTER SUGGESTS ALTERNATOR BE INSPECTED IN MORE DETAIL.					1	H	7	1 	3O				3A17    					 
1997080700275	19970807	00275	EA  	1997	8	7	97ZZZX3422       	2	19970520	G	8530	75068	VALVE           								LYC   	O320  	O320E3D     	41508	EA  					NR 3 CYL EXH	BROKEN          	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			NM	05										PILOT EXPERIENCED LOSS OF POWER DURING CRUISE FLIGHT.  EXCESSIVE VIBRATION AND POWER LOSS LED HIM TO  MAKE A PRECAUTIONA	RY/EMERG LANDING IN WHICH AIRCRAFT WAS HEAVILY DAMAGED.  FAA/NTSB INSPECTED ENGINE, FOUND NR 3 CYLINDER EXHAUST VALVE BR	OKEN OFF AT BASE OF VALVE, AND VALVE HEAD BLOCKING EXHAUST IN STACK FROM NR 4 CYLINDER.									3	O			E274				 
1997080700276	19970807	00276		1997	8	7	97ZZZX3423       	4	19970722	G	2561	KS9	LIFE VEST       	EAAEROMARINE																VEST CELL	FAIL TEST       	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					B51720					LIFE VEST FAILED THE MANUFACTURER'S 2-POUND P.S.I. INFLATION TEST.																			 
1997080700277	19970807	00277		1997	8	7	97ZZZX3424       	4	19970701	G	2561	KS9	LIFE VEST       	EAAEROMARINE																VEST CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					B31112					LIFE VEST FAILED THE MANUFACTURER'S 2-POUND P.S.I. TEST.																			 
1997080700278	19970807	00278	GL  	1997	8	7	97ZZZX3425       	2	19970703	G	7323	2526146	SPOOL BEARING   	BENDIX      	252466713   						ALLSN 	250C  	250C20      	03013	GL  					GOVERNOR	WRONG PART      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21			2117 		9658					PER AD 82-24-05, INSPECTION REQUIRED TO DETERMINE IF SPOOL BEARING IS CORRECT TYPE. PREVIOUS REPAIR STATION INSPECTED IT	 AND STATED ON REPAIR TAG THAT SPOOL BEARING WAS CORRECT, WHEN, IN FACT, IT WAS NOT.										3	U			E4CE				 
1997080700279	19970807	00279	EA  	1997	8	7	97ZZZX3426       	2	19970712	G	7310	6390102	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FIREWALL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	9779W					2823267				INSPECTION FOUND AIRCRAFT FUEL HOSES DETERIORATED AND LEAKING.  HOSES FROM FIREWALL FORWARD NEED FIRE SLEEVE REMOVED AND	 CHECKED FOR CORROSION.  P/N AFFECTED 639017, 6390102, 6390114, AND P/N 6390118.  ACFT TT:  600 - 1200 HOURS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997080700280	19970807	00280	EA  	1997	8	7	97ZZZX3427       	2	19970712	G	7310	639017	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FIREWALL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	56055					287325563				INSPECTION FOUND AIRCRAFT FUEL HOSES DETERIORATED AND LEAKING.  HOSES FROM FIREWALL FORWARD NEED FIRE SLEEVE REMOVED AND	 CHECKED FOR CORROSION.  P/N AFFECTED 639017, 6390102, 6390114, AND P/N 6390118.  ACFT TT:  600 - 2400 HOURS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997080700281	19970807	00281	EA  	1997	8	7	97ZZZX3428       	2	19970712	G	7310	63901114	HOSE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FIREWALL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	05	7167R					2821876				INSPECTION FOUND AIRCRAFT FUEL HOSES DETERIORATED AND LEAKING.  HOSES FROM FIREWALL FORWARD NEED FIRE SLEEVE REMOVED AND	 CHECKED FOR CORROSION.  P/N AFFECTED 639017, 6390102, 6390114, AND P/N 6390118.  ACFT TT:  600 - 2400 HOURS.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997080700282	19970807	00282	EU  	1997	8	7	97ZZZX3429       	1	19970723	G	5330	7253501712	PANEL           			SAAB  	SF340 	340B        	7860101	EU  										BELLY	FAILED          	B	L	A	YTQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	250AE					340B250				OPERATOR FORWARDED ACFT SAAB 340 BELLY PANEL PN 7253501-712 TO BE REPAIRED.  PANELS OUTER FIBERGLASS LAYER USED AS A SEA	L PLY OVER ANTI-STATIC MATERIAL IS FAILING.  PANEL HAD BEEN PREVIOUSLY REPAIRED USING SAAB APPROVED PROCEDURE.  SUBMITTE	R STATES PROCEDURE IS UNRELIABLE.				2	L	7	2 	4T			RT	A52EU   					 
1997080700283	19970807	00283	GL  	1997	8	7	97ZZZX3430       	2	19970722	G	7250	23031478	BEARING         								ALLSN 	250C  	250C30P     	03013	GL  					TURBINE NR 8	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	11		327  			MP00460		CAE895526			BEARING FAILED IN-FLIGHT, CAUSED CHIP LIGHT.  OIL FLOWED ALL NOZZLES AND OIL LINES AT DISASSEMBLY.  ALL CLEAR.  ALL OTHE	R BEARINGS, VISUAL OK.										3	U			E1GL				 
1997080700284	19970807	00284	CE  	1997	8	7	97ZZZX3431       	1	19970717	G	5540	1155240599	HINGE CASTING   			BEECH 	90    	C90A        	1152911	CE  										RUDDER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	478JA	4846 				LJ1163				MULTIPLE CRACKS ON THE BASE OF RUDDER HINGE CASTING WHERE IT ATTACHES TO VERTICAL FIN.  NORMAL TORQUE ON REMOVAL.  INSPE	CTION REQUIREMENT FOR CASTINGS IS 12,000 HOURS.					1	L	7	2 	3T			RT	3A20    					 
1997080700286	19970807	00286		1997	8	7	97ZZZX3433       	4	19970701	G	2561	SMV2102	LIFE VEST       	JCRIND      																CELL	FAILED TEST     	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					00008					LIFE VEST FAILED THE MANUFACTURER'S 2 P.S.I. INFLATION TEST.																			 
1997080700287	19970807	00287		1997	8	7	97ZZZX3434       	4	19970701	G	2561	H2L8	LIFE VEST       	AMERICANSFTY																CELL	FAILED TEST     	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					190					LIFE VEST FAILED THE MANUFACTURER'S 2 P.S.I. INFLATION TEST.																			 
1997080700288	19970807	00288	NE  	1997	8	7	97ZZZX3435       	2	19970716	G	8530		ROCKER BOSS     			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					CYLINDER EXHAUST	SEPARATED       	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AL	03	17689	300  				431				CYLINDER HEAD EXHAUST ROCKER BOSS SEPARATED FROM HEAD.  OCCURRED DURING TAKEOFF CLIMB.  STUCK VALVE.  CORRECT LEAD CONTE	NT OF FUEL.					1	H	7	1 	3R	3	R		A815    	5E2				 
1997080700289	19970807	00289	SO  	1997	8	7	97ZZZX3436       	2	19970620	G	8530	538304	PUSH ROD        								CONT  	O520  	IO520F      	17032	SO  					NR 5 CYL INT	BROKEN          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			AL	03		1366 					553699			AFTER NORMAL FLIGHT AND ON TURN-AROUND, ENGINE ON POWER CHECK RAN VERY ROUGH AND WOULD NOT RESPOND NORMALLY TO THROTTLE 	ADVANCE.  FOUND NR 5 CYLINDER WITH ONE BROKEN (INTAKE) PUSH ROD AND EXHAUST PUSH ROD BENT.  ENGINE SHOP ADVISED VALVE ST	EMS STUCK.  15W50 AEROSHELL WAS IN USE AT THIS TIME.									3	O			E5CE				 
1997080700290	19970807	00290	NM  	1997	8	7	97ZZZX3437       	1	19970708	G	7830	122510	BODY            		1U1225      	BOEING	737   	737222      	1384473	NM  										ISOLATION VALVE	CRACKED         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			667  		1923					THE 1U1225'S ISOLATION BODY, PN 1225-10, IS SUSCEPTIBLE TO PINHOLES AND CRACKS ALONG THE BODY'S SEAMS AND WITHIN THE FIT	TING PORTS.  RONSON MIGHT CONSIDER MANUFACTURING A STRONGER BODY, PERHAPS A CHANGE OF MATERIAL.					2	L	7	2 	4F				A16WE   					 
1997080700291	19970807	00291	NM  	1997	8	7	97ZZZX3438       	1	19970710	G	2720	8816041	COIL            	PARKERHANFIN	8816001001  	BOEING	737   	737*        		NM  										RUDDER PCU	JOINT CRACKED   	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3017					JOINT WHERE THE CONNECTOR ATTACHES TO THE COIL IS CRACKED.  JOINT IS NARROW AND WEAK.  SUBMITTER STATES; CAN SEE RECURRI	NG PROBLEMS WITH CRACKING.  RECOMMEND MAKING JOINT STRONGER.					2	L	7	2 	4F			RT	A16WE   					 
1997080700292	19970807	00292	NM  	1997	8	7	97ZZZX3439       	1	19970708	G	2761	65C268634	HOUSING         		65C26864    	BOEING	737   	737*        		NM  										SPOILER ACTUATOR	CRACKED         	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			8898 		0499					IT HAS BEEN NOTED THAT THE 65-44960, 65C26864, AND 251A1510 SPOILER ACTUATORS HAVE BEEN EXPERIENCING CRACKING AT THE ROD	 END END OF THE HOUSING ASSEMBLIES, PN'S 65C26863-1, DASH 4 AND DASH 6.					2	L	7	2 	4F			RT	A16WE   					 
1997080700294	19970807	00294	NM  	1997	8	7	97ZZZX3441       	1	19970627	G	2520	608041	STANCHION       		AA99S3      	BOEING	767   	767         	1385102	NM  										LITTER	CORRODED        	B			TR1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										LITTER STANCHIONS SHOW SIGNS OF CORROSION AT ATTACH WELD.  IT APPEARS THE MATERIAL WAS EXPOSED TO MOISTURE DURING SHIPME	NT OR STORAGE.  CAUSE AND PREVENTION ARE UNDER INVESTIGATION BY RAYTHEON.  THE PARTS ARE BEING REPLACED BY KNOWN SERVICE	ABLE PARTS.  THIS MATERIAL PART OF THE CIVIL RESERVE AIR FLEET AEROMEDICAL EVACUATION SHIP SET SYSTEM ASSIGNED STC SA503	9SW-D WHICH INSTALLS ONTO A B767-200/300.			2	L	7	2 	4F				EXPA2L72					 
1997080700295	19970807	00295	NM  	1997	8	7	97ZZZX3442       	1	19970627	G	2520	608051	STANCHION       		05395       	BOEING	767   	767         	1385102	NM  										LITTER	CORRODED        	B			TR1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										LITTER STANCHIONS SHOW SIGNS OF CORROSION AT ATTACH WELD.  IT APPEARS THE MATERIAL WAS EXPOSED TO MOISTURE DURING SHIPME	NT OR STORAGE.  CAUSE AND PREVENTION ARE UNDER INVESTIGATION BY RAYTHEON.  THE PARTS ARE BEING REPLACED BY KNOWN SERVICE	ABLE PARTS.  THIS MATERIAL PART OF THE CIVIL RESERVE AIR FLEET AEROMEDICAL EVACUATION SHIP SET SYSTEM ASSIGNED STC SA503	9SW-D WHICH INSTALLS ONTO A B767-200/300.			2	L	7	2 	4F				EXPA2L72					 
1997080700297	19970807	00297	EU  	1997	8	7	97ZZZX3444       	1	19970718	G	6120	57A3044	FEEDBACK BLOCK  			SOCATA	TBM   	TBM700      	8682000	EU  										PROP BETA	WORN            	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	800GS					5				DURING ANNUAL INSPECTION, FOUND CARBON 'BETA' FEEDBACK BLOCK SEVERELY WORN.  THIS HAD CAUSED DAMAGE TO FEEDBACK RING AS 	WELL.  THIS OCCURRED DUE TO BLOCK NOT MOVING FREELY IN ARM.  (LACK OF LUBRICATION).  AIRCRAFT HAD NOT BEEN INSPECTED FOR	 160 HOURS.  NORMAL CYCLE IS 100, 200, AND 400 HOURS FOR THIS AIRCRAFT.  THIS DISCREPANCY MAY HAVE BEEN CAUGHT BEFORE DA	MAGE TO PROPELLER OCCURRED IF 100-HOUR INSPECTION HAD BEEN C/W.			1	L	7	1 	3T			RT	A60EU   					 
1997080700298	19970807	00298	EU  	1997	8	7	97ZZZX3445       	1	19970627	G	3246	AH42671	WHEEL HALF      			HWKSLY	DH125 	BH125400A   	4230138	EU  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	89SR				1693	NA778				WHEEL HALF WAS TESTED FOR MILLION AIR; SALT LAKE CITY, UTAH IAW DUNOP 32-40-2(4) 6-28-84, FOUND CRACKED.						2	L	7	2 	4J				A3EU    					 
1997080700300	19970807	00300	NE  	1997	8	7	97ZZZX3447       	2	19970717	G	7320		HOSE            			HAMFLU	HFB320	HFB320      	4071204	EU  	GE    	CJ610 	CJ6105      	30006	NE  					T2 SENSE	LOOSE           	H				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			GL	23	92045	3474 				1041	249020			RIGHT ENGINE FLAMED OUT AT FL 370.  ENGINE RE-STARTED IAW AFM AIR START PROCEDURES.  ENGINE INSPECTED AND NO DAMAGE NOTE	D.  TIGHTENED LOOSE T2 SENSE HOSE.  C/W ALTITUDE ACCELERATION TEST FLIGHT.  OPS CHECK GOOD.					2	L	7	2 	4J	4	J		A14EU   	1E16				 
1997080700301	19970807	00301	EU  	1997	8	7	97ZZZX3448       	1	19970714	G	6320	109040304105	INPUT QUILL     		109040002107	AGUSTA	A109  	A109C       	0260118	EU  										M/R TRANSMISSION	SPALLED         	H		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	15	911D	1178 				7637				APPROXIMATELY 5 MINUTES AFTER TAKEOFF, MAIN TRANSMISSION CHIP LIGHT CAME ON AND WOULD NOT ZAP OFF.  PILOT RETURNED.  TEC	HNICIAN REMOVED AND INSPECTED BOTH CHIP PLUGS.  TOP CHIP PLUG WAS CLEAN.  BOTTOM CHIP PLUG HAD 4 LARGE CHIPS ON IT.  TRA	NSMISSION FILTER WAS REMOVED AND FOUND TO CONTAIN AN EXCESSIVE AMOUNT OF METAL FILINGS.  TECHNICIANS WHO OPENED THE GEAR	BOX AND FOUND EXCESSIVE SPALLING ON THE INPUT QUILL AND GLEASON CROWN GEAR.  THEY ALSO FOUND A POSSIBLE CRACK IN ONE OF 	THE INPUT QUILL TEETH.		1	G	7	2 	3U				H7EU    					 
1997080700302	19970807	00302	WP  	1997	8	7	97ZZZX3449       	1	19970710	G	2510	269A40661	COVER ASSY      			HUGHES	269   	269C        	4470504	WP  										COCKPIT	JAMMED THROTTLE 	D		A		O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	27	61458					0008				FLIGHT AFTER ANNUAL INSP FOR M/R TRACK AND BALANCE, THROTTLE STUCK FULL ON IN CRUISE FLT NOT ALLOWING REDUCTION IN POWER	 WITHOUT OVERSPEED OF ENG AND ROTOR.  CAUSE FOUND IN-FLIGHT AND CORRECTED.  BETWEEN PILOT'S AND COPILOT'S SEAT IS A VERT	ICAL PANEL THAT WHEN INSTALLED, THE LIP THAT SHOULD TUCK IN NEXT TO THE PILOT'S SEAT GOT TUCKED BACK INTO THE FLT CONTRO	L AREA (ON OPPOSITE SIDE OF VERT RIB GUARD).  FREE THROTTLE MOVEMENT WAS STILL ALLOWED IN BOTH DIRECTIONS UNTIL FULL THR	OTTLE ACHIEVED.  AT THIS TIME, LIP OF PANEL KEPT THROTTLE BELLCRANK FROM ROTATING IN THE OFF DIRECTION.  AREA OF CONTACT	 IS THE PANEL-TO-BELLCRANK/OVERTRAVEL SPRING ASSY.  THIS WAS CORRECTED AND ACFT RETURNED TO SERVICE.	1	G	7	1 	3O				4H12    					 
1997080700303	19970807	00303	CE  	1997	8	7	97ZZZX3450       	1	19970701	G	2823	HE7805	SELECTOR VALVE  			BEECH 	95    	95B55       	1152729	CE  										FUEL SYSTEM	LEAK            	B			H8AR	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			EA	05	2018Q				A97050056	TC2165				THIS VALVE INSTALLED TO REPLACE 2 OTHER PREVIOUS VALVES INSTALLED AS NEW THAT FAILED A SHORT TIME AFTER INSTALLATION.						1	L	7	2 	3O			RT	3A16    					 
1997080700324	19970807	00324	NE  	1997	8	7	97ZZZX3451       	1	19970618	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76         	8143010	NE  										TAIL ROTOR	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T	6196 			A13700421	760140				TAIL ROTOR BLADE ASSY WAS REPAIRED BY SIKORSKY JUST 422.4 HOURS AGO.  PAINT AND EROSION STRIP NEEDS TO BE REWORKED.						1	G	7	2 	3U				H1NE    					 
1997080700325	19970807	00325	EU  	1997	8	7	97ZZZX3452       	1	19970701	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50588	648  			534	S780				TWO BLADES REPAIRED BY EUROCOPTERS ONLY 306.4 HOURS AGO.  LEAIDNG EDGE AND TIP CAP NEEDS REWORK AND PAINTING.						1	G	7	2 	3U				H3EU    					 
1997080700326	19970807	00326	EU  	1997	8	7	97ZZZX3453       	1	19970701	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50588	572  			534	S780				TWO BLADES REPAIRED BY EUROCOPTERS ONLY 306.4 HOURS AGO.  LEAIDNG EDGE AND TIP CAP NEEDS REWORK AND PAINTING.						1	G	7	2 	3U				H3EU    					 
1997080700327	19970807	00327	NE  	1997	8	7	97ZZZX3454       	1	19970709	G	6210	7615009000049	BLADE           			SKRSKY	S76   	S76         	8143010	NE  										MAIN ROTOR	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5403C	7191 			A08600213	760141				BLADE HAS A COMPLETE CHORD-WISE CRACK IN THE NICKEL LEADING EDGE ABRASION STRIP LOCATED 170 INCHES FROM THE ROOT END OF 	BLADE.  THE NICKEL STRIP IS SEPARATED OUTBOARD OF THE CRACK ON LOWER SIDE, 12 INCHES ALONG TRAILING EDGE OF STRIP AND IN	BOARD OF THE CRACK 2.50 INCHES.  THE DEPTH OF SEPARATION IS APPROXIMATELY OUT TO THE LEADING EDGE.  BLADE WAS REMOVED FR	OM SERVICE AND SENT TO SIKORSKY FOR REPAIR.			1	G	7	2 	3U				H1NE    					 
1997080700328	19970807	00328	NE  	1997	8	7	97ZZZX3455       	1	19970701	G	3340	A402	LENS            			SKRSKY	S76   	S76         	8143010	NE  										STROBE	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5414X	207  				760152				STROBE LENS IS CRACKED ALONG SEAM.						1	G	7	2 	3U				H1NE    					 
1997080700329	19970807	00329	EU  	1997	8	7	97ZZZX3456       	1	19970610	G	7714	9580111270	PICKUP          			AEROSP	SA365 	AS365N2     	8680815	EU  										ENGINE	MALFUNCTION     	B			KY1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	65MD	1383 			N3622	6464				OVERSPEED SENSOR LIGHT STAYS ON.						1	G	7	2 	3U			RT	H10EU   					 
1997080700330	19970807	00330	NE  	1997	8	7	97ZZZX3457       	1	19970602	G	3340	A402AR	LENS            			SKRSKY	S76   	S76A        	8143006	NE  										STROBE	SPLIT           	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72649					760292				BRAND NEW PART OUT OF STOCK, SPLIT ALONG GLUE LINE.  LENS HALVES NOT BONDED TOGETHER PROPERLY. THIS WAS TO REPLACE THE L	ENS INSTALLED THAT WAS REMOVED FOR THE SAME REASON.					1	G	7	2 	3U				H1NE    					 
1997080700331	19970807	00331	NE  	1997	8	7	97ZZZX3458       	1	19970601	G	3340	A402AR	LENS            			SKRSKY	S76   	S76A        	8143006	NE  										STROBE	SPLIT           	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72649					760292				STROBE LIGHT LENS SPLIT IN HALF, GLUE DOES NOT HOLD HALVES TOGETHER ALONG BOND LINE.						1	G	7	2 	3U				H1NE    					 
1997080700332	19970807	00332	NE  	1997	8	7	97ZZZX3459       	1	19970601	G	6210	7615009100052A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DISBOND         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72649	7304 			A0861577	760292				TWO AREAS OF DISBOND ON MAIN ROTOR BLADE.  (TOP SURFACE STARTS AT BLADE STA 232 AND EXTENDS SPANWISE APPROXIMATELY 4 INC	HES ALONG LEADING EDGE STRIP, EXTENDING AFT APPROXIMATELY 4 INCHES CHORDWISE).  LOWER SURFACE STARTING AT BLADE STA 237,	 APPROXIMATELY EXTENDING SPANWISE 4 INCHES, LOCATED AFT OF LEADING EDGE 3 INCHES APPROX .75 IN CHORDWISE.				1	G	7	2 	3U				H1NE    					 
1997080700333	19970807	00333		1997	8	7	97ZZZX3460       	4	19970623	G	3444	6222938001	INDICATOR       			AEROSP	SA365 	SA365N1     	8680668	EU  										RADAR ALT	FLAG STUCK      	B			KY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	79MD	2260 				6352				RADAR ALTIMETER FLAG 'STUCK' (WILL NOT MOVE).  DOES NOT TEST.						1	G	7	2 	3U				H10EU   					 
1997080700334	19970807	00334	EU  	1997	8	7	97ZZZX3461       	1	19970623	G	7714	H2901428	INDICATOR       			AEROSP	SA365 	SA365N1     	8680668	EU  										AUTOTAK NG	MALFUNCTION     	B			KY1R	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			EA	07	79MD					6352				'ERR' DISPLAYED AT ALL TIMES.						1	G	7	2 	3U				H10EU   					 
1997080700335	19970807	00335	EU  	1997	8	7	97ZZZX3462       	1	19970620	G	2436	026	REGULATOR       			AEROSP	SA365 	SA365N1     	8680668	EU  										DC SYSTEM	FAILED          	B			KY1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	95MD				4822	6320				VOLTAGE REGULATOR FAILED DUE TO CROSSED WIRING AND TERMINALS.						1	G	7	2 	3U				H10EU   					 
1997080700341	19970807	00341	NM  	1997	8	7	97ZZZX3467       	1	19970326	G	3246	10321700	BOLT            		40124       	PIPER 	PA60  	PA60601P    	7106012	NM  										WHEEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	14SP					61P0494202				DURING A ROUTINE TIRE CHANGE, ONE OF THE WHEEL BOLTS WAS FOUND CRACKED ALL THE WAY AROUND THE BOTTOM OF THE HEAD.						1	M	7	2 	3O			RT	A17WE   					 
1997080700343	19970807	00343	EU  	1997	8	7	97ZZZX3469       	2	19970526	G	8530		CARB SOCKET     			AMTR  	RANS  	RANSS12     	05618JF	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					INTAKE MANIFOLD	LOOSE           	H				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	13			100  							THE CARBURETOR SOCKET VIBRATED LOOSE FROM THE INTAKE MANIFOLD.  NO SAFETY WIRING OF THE CLAMPS AS RECOMMENDED BY ROTAX. 	 CARBS HAD FELT SECURE ON PRE-FLIGHT INSPECTION.					1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1997080700344	19970807	00344	SW  	1997	8	7	97ZZZX3470       	1	19970612	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DRIVE LINK ASSY HAS EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3 FIG 62:21.  AT TEAR DOWN FOUND BEARINGS AND SPACERS W	ORN BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS.  ONE YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW    					 
1997080700345	19970807	00345		1997	8	7	97ZZZX3471       	2	19970701	G	7322	661529	BEARING         	HAMSTD      	JFC564      															FUEL CONTGROL	WRONG PART      	B			JYDR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09										BOGUS BEARINGS PURCHASED NEW SURPLUS FROM CALIFORNIA PROPELLER UNDER EAC P.O. K4495.  PART  PACKAGED IN JUNE 1997.  WHEN	  INSTALLING IN FUEL CONTROL, BEARING CAME APART.  ONLY PART MARKING IS SBB 3 USA AND LOCATED ON INNER RACE.  PARTS PURC	HASED FROM HAMILTON STD (PN 561529) ARE MADE FROM 2 COMPONENTS:  INNER AND OUTER RACE AND HAVE P/N MARKED ON OD WITH HAM	ILTON STANDARD STAMP.  BOGUS  BEARING  DESIGNED FOR LOAD IN 1 DIRECTION AND CORRECT BEARING PN 561529 IS DESIGNED TO BE 	LOADED IN BOTH DIRECTIONS.  BEARING IS NOT SURPLUS, BUT SOLD AS SURPLUS.  MFG OF BOGUS BEARING CONTACTED AND VERIFIED TH	EY NEVER PRODUCED A BEARING WITH PN 561529 AND SOME ONE ILLEGALLY MIS-IDENTIFIED THEIR BEARING PN SBB 3 AS  PN 561529.														 
1997080700346	19970807	00346	EU  	1997	8	7	97ZZZX3472       	1	19970721	G	5711	33719912	SPAR            			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										RT WING	CORRODED        	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	2527E					878				DURING AN ANNUAL INSPECTION OF THIS AIRCRAFT, A CONSIDERABLE AMOUNT OF CORROSION OF THE RIGHT WING SPAR WAS FOUND WITH S	OME FORM OF DELAMINATION.  THE PRIMARY CORROSION WAS FOUND ON THE RIGHT WING SPAR NEAR THE RIB ONTO WHICH THE LANDING GE	AR IS ATTACHED.				1	L	7	1 	3O			RT	A51EU   					 
1997080700347	19970807	00347	GL  	1997	8	7	97ZZZX3473       	3	19970722	G	6111	V8433N4	BLADE           			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	SHANK	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15			373  		D51435			BJ527		BLADE CRACKED IN SHANK AREA.  REFER TO HARTZELL SB 61-217, REV 1.						1	H	7	2 	3O				6A1     		5	C	P6EA	 
1997080700348	19970807	00348	GL  	1997	8	7	97ZZZX3474       	3	19970724	G	6111	V8433N4	BLADE           			GULSTM	500   	500RKWELL   	0141102	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	SHANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		10385	1989 		D96215			BJ119		CRACK IN BLADE SHANK AREA.						1	H	7	2 	3O				6A1     		5	C	P6EA	 
1997080700349	19970807	00349	EA  	1997	8	7	97ZZZX3475       	2	19970608	G	8530	60828	PIN PLUG        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					NR 3 PISTON	FAILED          	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	27	520ST	1675 				287225337	L3424227A			THIS AIRPLANE MADE AN EMERGENCY LANDING ON A HIGHWAY AT NIGHT.  NO DAMAGES TO THE AIRCRAFT OR THE PASSENGERS.  A TEAR-DO	WN INSPECTION OF THE ENGINE WAS COMPLETED WITH THE FOLLOWING RESULTS.  NR 3 CYLINDER PISTON PIN PLUG SEVERELY WORN.  ALU	MINUM FROM THE PLUG AND ASSOCIATED PISTON HAD PLUGGED THE OIL SYSTEM CAUSING CONNECTING ROD BEARING TO OVERHEAT AND FAIL	.  THIS PISTON PIN PLUG COULD HAVE BEEN INSTALLED WHEN THE ENGINE WAS OVERHAULED IN 1976.  SUBMITTER STATED LYCOMING HAS	 SINCE CHANGED THE DESIGN OF THIS PART TO PREVENT THIS FROM OCCURRING.		1	L	7	1 	3O	3	O		2A13    	E274				 
1997080700350	19970807	00350	CE  	1997	8	7	97ZZZX3476       	1	19970728	G	6120		SUPPORT         			CESSNA	172   	172D        	2072410	CE  										PROP GOV CONTROL	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	56EC					17249661				DURING REMOVAL FOR OIL PUMP AD COMPLIANCE, FOUND TWO OF THE THREE SUPPORT FINGERS CONNECTING THE PROPELLER GOVERNOR CONT	ROL CABLE CRACKED AT THE THREE-FINGER JUNCTION WELD, AND THE CABLE WAS SUPPORTED BY ONE FINGER.  FAILURE OF THAT FINGER 	WOULD CAUSE LOSS OF PROP PITCH CONTROL.  THIS CRACK WOULD BE DIFFICULT TO SEE DURING ROUTINE INSPECTIONS.  RE-WELDED AND	 RETURNED TO SERVICE.  FAILURE MODE UNKNOWN, SUSPECT INDUCED VIBRATION; TY-WRAPPED TO ADJACENT HOSE.  AVCON 180 CONVERSI	ON FOR CESSNA 172.		1	H	7	1 	3O			NT	3A12    					 
1997080700351	19970807	00351	GL  	1997	8	7	97ZZZX3477       	3	19970722	G	6110		PROPELLER       			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	BOLT HOLES	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	67402	7346 	3673 			15281817		R772947		TWO CRACKS FOUND AT EDGE OF BOLT HOLES, APPROXIMATELY .50 INCH LONG.  FOUND DURING INSPECTION REQUIRED BY SB 221 AND AD 	97-06-16.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997080700352	19970807	00352	SO  	1997	8	7	97ZZZX3478       	1	19970701	G	3211	6705400	TRUNNION        		6710004     	PIPER 	PA28  	PA28R200    	7102811	SO  										NLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	9350K					28R7635233				DURING ANNUAL INSPECTION, TWO FINE CRACKS WERE DISCOVERED IN THE UPPER RIGHT TRUNNION MOUNTING ARM, ON THE AFT SIDE, AND	 ONE ON THE FORWARD SIDE.  CRACKS VERIFIED BY DYE PENETRANT INSPECTION.  AFT CRACK APPROXIMATELY 1 INCH LONG EXTENDING F	ROM .33 INCH UNDER BRACE TO .33 INCH OVER TOP.  FORWARD CRACK APPROXIMATEY .75 INCH LONG, EXTENDING SLIGHTLY UNDER AND O	VER BRACE.  SUBMITTER SUSPECTS HARD LANDINGS AND/OR EXCEEDING TURN LIMITS ON TOW.			1	L	7	1 	3O				2A13    					 
1997080700353	19970807	00353	CE  	1997	8	7	97ZZZX3479       	1	19970701	G	2720		PEDAL           			CESSNA	170   	170A        	2072304	CE  										RUDDER	EXCESS WEAR     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9526A					190897				RUDDER PEDALS WERE REMOVED TO FACILITATE OTHER MAINTENANCE.  UPON REMOVAL, FOUND PEDAL ATTACH HOLES SEVERELY ELONGATED. 	 TO REPAIR, A .125 INCH DOUBLER OF 6061-T6 WAS USED ON EACH SIDE OF THE PEDAL AS THE PEDAL PIN WAS JUST LONG ENOUGH TO A	CCOMODATE THE EXTRA THICKNESS.  ALL 4 PEDALS WERE DAMAGED IN THIS WAY.  SUSPECT CAUSE, 48 YEARS OF FLIGHT.  RECOMMEND PE	RIODIC INSPECTION ON OLDER AIRCRAFT.			1	H	7	1 	3O				A799    					 
1997080700354	19970807	00354	EA  	1997	8	7	97ZZZX3480       	2	19970711	G	8550		OIL PUMP        			GRTLKS	2T1   	2T1A2       	3910101	NM  	LYC   	O360  	AEIO360B1G6 	41514	EA  					GEARS	DEFECTIVE       	B			PB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23							L1961951A			DURING AD RESEARCH, AD 96-09-10, ENGINE WAS SUBJECT TO VERIFICATION.  ENGINE MANUFACTURED (FIRST TEST FLIGHT) OCTOBER, 1	978, AND HAS 330 HOURS TOTAL TIME SINCE NEW.  THIS ENGINE WAS NOT LISTED IN BULLETIN 524 UNDER AEIO - SO LYCOMING WAS CO	NSULTED AND ADVISED THAT ENGINES ARE LISTED BY SUFFIX, NOT PREFIX, AS STATED IN BULLETIN; THEREFORE, ENGINE FALLS UNDER 	IO-360 AND HAS STEEL AND ALUMINUM GEARS.			1	Q	7	1 	3O	3	O		A18EA   	1E10				 
1997080700355	19970807	00355	SO  	1997	8	7	97ZZZX3481       	1	19970722	G	2821	2W072322	FUEL FILTER     	AIRMAZE     		PIPER 	PA46  	PA46350P    		SO  										THREADED POST	LOOSE           	B		A	WC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	113WB	108  			1Q90	4622193				WHILE SERVICING THE FUEL BOWL FILTER SEGMENTS, THE THREADED POST WHICH RETAINS AND SECURES THE FILTERS AND BOWL TO THE A	SSY BODY WAS FOUND LOOSE AND HELD IN BY ONLY ONE THREAD (1 FULL TURN).  POST AND BODY HAVE APPROXIMATELY 8 THREADS.  SUS	PECT CAUSE WAS THAT POST MAY NOT HAVE BEEN FULLY THREADED OR SECURED INTO ASSY BODY.				1	L	7	1 	3O			RT	A25SO   					 
1997080700356	19970807	00356	SO  	1997	8	7	97ZZZX3482       	2	19970618	G	8530	6461401	STUD            		643207      	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 1 CYLINDER	BROKEN          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			GL	17	25SC					414A0114	233993R			THE LEFT ENGINE NR 1 CYLINDER HAD 5 BROKEN HOLD-DOWN STUDS (ALL 3 ON THE BOTTOM AND 2 FORWARD ON TOP) WHICH CAUSED A VIB	RATION AND RPM REDUCTION AT FULL POWER.  ALL THE STUDS WERE BROKEN JUST UNDER THE HOLD-DOWN NUTS.  REPLACEMENT OF ALL ST	UDS ON THAT CYLINDER CORRECTED THE PROBLEM.  USUALLY, IT IS JUST ONE DEFECTIVE STUD AND THE REST FOLLOW UNDER THE EXTA L	OAD.  SUBMITTER RECOMMENDS REPLACEMENT OF ALL STUDS AT OVERHAUL.  ENGINE TSO:  1394.7 HOURS.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997080700357	19970807	00357	SO  	1997	8	7	97ZZZX3483       	1	19970722	G	7820	7105302	MUFFLER         			PIPER 	J3    	J3C65       	7100510	SO  										EXHAUST	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	3390N	2654 				22592				INSPECTION FOUND MUFFLER CRACKED.  WELDED WITH STAINLESS STEEL.						1	H	7	1 	3O				A691    					 
1997080700359	19970807	00359	CE  	1997	8	7	97ZZZX3485       	1	19970701	G	5320	0713643	BULKHEAD        			CESSNA	182   	182J        	2072722	CE  										STBD TUNNEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	2787F	2936 				182586887				PILOTS HAD COMMENTED ON A 'CLICKING' SOUND SOMEWHERE IN THE CABIN FOR SOME TIME.  DURING AN ANNUAL INSPECTION, THE STARB	OARD TUNNEL BULKHEAD WAS FOUND CRACKED IN AREA OF THE FUEL LINE (TO FIREWALL BULKHEAD FITTING).  POSSIBLE CAUSE OF DAMAG	E MAY BE FROM SEVERE NOSE WHEEL SHIMMY.  NOSE STRUT, TORQUE LINKS, SHIMMY DAMPENER, WERE REPAIRED AT ANNUAL.  SUBMITTER 	STATES THIS AIRCRAFT HAS NOT BEEN WELL MAINTAINED IN THE PAST.			1	H	7	1 	3O			NT	3A13    					 
1997080700360	19970807	00360	CE  	1997	8	7	97ZZZX3486       	1	19970612	G	3213	50411082	BEARING         			CESSNA	414   	414A        	2075907	CE  										LT/RT MLG	WRONG PART      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	30EE	3900 				414A0443				PULLED STRUTS TO RESEAL.  DISCOVERED UPPER BEARING BLOCKS, AD 90-02-13, REQUIRES MAGNAFLUX EACH 1,000 HOURS, BUT SERIAL 	NUMBER DOES NOT APPLY TO 414A AFTER 0340.  THESE WERE NOT BROKEN, BUT HAVE FOUND SEVERAL ON EARLIER AIRCRAFT COVERED BY 	THE AD BROKEN.				1	L	7	2 	3O				A7CE    					 
1997080700361	19970807	00361	CE  	1997	8	7	97ZZZX3487       	1	19970718	G	2822	S23271	SWITCH          			CESSNA	206   	U206F       	2073333	CE  										THROTTLE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	35854					20602759				P/N S-2327-1 FUEL PUMP THROTTLE SWITCH ACTIVATION ARM BREAKS INTERNALLY.  SUBMITTER STATED THIS IS THE 4TH SWITCH IN THE	 LAST 12 MONTHS.  THIS LAST SWITCH HAS 40 HOURS OPERATION TIME.					1	H	7	1 	3O				A4CE    					 
1997080700362	19970807	00362	EA  	1997	8	7	97ZZZX3488       	2	19970711	G	8550		SCREEN          			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					OIL SUCTION	REQUIRED CHANGE 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	3669W					32578	L1033140			REMOVED ENGINE FOR OVERHAUL WITH APPROXIMATELY 2,100 HOURS SINCE LAST OVERHAUL.  OIL SUCTION SCREEN SAFETY WIRE WAS PAIN	TED WITH ENGINE PAINT.  ENGINE LAST OVERHAUL WAS 10-71.  MANY ANNUALS AND OIL CHANGES WITHOUT THIS SCREEN BEING PULLED. 	 VERY POOR MAINTENANCE.				1	L	7	1 	3O	3	O		A3SO    	E295				 
1997080700363	19970807	00363	SO  	1997	8	7	97ZZZX3489       	1	19970701	G	5510		HORIZ STABILIZER			LUSCOM	8     	8B          	8190106	SO  										LOWER PORT INBD	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	37049	1431 				1710				AIRCRAFT DISMANTLED FOR RENOVATION.  UPON STRIPPING HORIZONTAL STABILIZER OF PAINT, CORROSION SPOTS WERE NOTICED ON LOWE	R INBOARD SKIN - PORT SIDE.  SKIN WAS DRILLED OFF AND A SUPER-HUGE MOUSE NEST WAS LYING IN THE AFT POSITION.  MOUSE URIN	E HAD CORRODED THE LOWER SKIN AND TWO RIBS TO THE POINT OF DESTRUCTION.  MOUSE ENTRANCE APPEARS TO BE IN CABLE EXIT IN C	ENTER OF STABILIZER AND AFT OF FRONT SPAR INTO RIB BAYS. THIS AREA CANNOT BE INSPECTED VISUALLY, OTHERWISE, THIS FIFTY-S	IX YEAR OLD AIRCRAFT ENJOYS A RELATIVELY SOUND STRUCTURE.		1	H	7	1 	3O				A694    					 
1997011600842	19970116	00842	CE  	1997	1	16	97ZZZX349        	1	19970106	G	3010	15323	DISTRIBUTOR     			MTSBSI	MU2   	MU2B60      	5780460	CE  										ANTI ICE BOOT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	175CA				42557U	736SA				DURING A 150 HR INSPECTION, IT WAS DISCOVERED THAT THE VERTICAL AND HORIZONTAL BOOTS WERE NOT INFLATING.  THIS AREA IS I	MPOSSIBLE FOR THE PILOT TO SEE DURING A FUNCTION CHECK AND MUST BE INSPECTED REGULARLY.					1	H	7	2 	3T			RT	A10SW   					 
1997080700364	19970807	00364	SO  	1997	8	7	97ZZZX3490       	1	19970623	G	5553		RIVETS          			PIPER 	PA34  	PA34200T    	7103406	SO  										VERT STAB LT	SHEARED         	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4490F					347670339				RIVETS ON LT SIDE (3 OUT OF 4) SHEARED WHERE AFT SPAR OF VERTICAL STABILIZER ATTACHES TO EMPENNAGE. THESE RIVETS HAVE BE	EN REPLACED BEFORE, BUT COULD NOT DETERMINE T.I.S. SINCE REPAIR.  SUBMITTER STATED THIS IS THE SECOND PA-34-200T IN FLEE	T FOUND WITH SHEARED RIVETS IN THIS AREA.				1	L	7	2 	3O				A7SO    					 
1997080700365	19970807	00365	EA  	1997	8	7	97ZZZX3491       	2	19970722	G	8550		DIP STICK       			GULSTM	112   	112TCA      	7630307	SW  	LYC   	O360  	TO360C1A6   	41514	EA  					ENGINE OIL	ERROR           	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17	4655W					13185	L31369A			THIS ENGINE AT OIL CHANGE REQUIRES TEN QUARTS OF OIL TO BRING DIPSTICK TO READ EIGHT QUARTS.						1	L	7	1 	3O	3	O		A12SO   	E26EA				 
1997080700366	19970807	00366	CE  	1997	8	7	97ZZZX3492       	1	19970723	G	7602	S17771	CONTROL         			CESSNA	150   	150J        	2071820	CE  										ENGINE MIXTURE	BROKE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	21	60001					15069997				MIXTURE CONTROL BROKE AT CARBURETOR APPROXIMATELY .1250 INCH FROM END OF CABLE.						1	H	7	1 	3O				3A19    					 
1997080700367	19970807	00367	EA  	1997	8	7	97ZZZX3493       	1	19970725	G	5540	AN36A	BOLT            			SCWZER	G164  	G164C       	3952803	EA  										RUDDER ATTACH	EXCESS WEAR     	B		A	MU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	6555K					4C				UPON REMOVAL OF RUDDER, THE UPPER ATTACH BOLT WAS FOUND SEVERELY WORN TO THE POINT FAILURE WAS INEVITABLE.  THIS PROBLEM	 HAS BEEN NOTED BEFORE ON A R-985 B-MODEL.  THE SUSPECT CAUSE FOR THIS DEFECT WAS LACK OF PROPER INSPECTION.  WITH PROPE	R INSPECTION AND PREVENTIVE MAINTENANCE, THIS DEFECT WOULD NOT BE A PROBLEM.  SUBMITTER RECOMMENDS THAT EVERY 2,000 HOUR	S THE RUDDER ATTACH BOLTS BE REMOVED AND VISUALLY INSPECTED.			1	Q	7	1 	3R				1A16    					 
1997080700368	19970807	00368	SO  	1997	8	7	97ZZZX3494       	1	19970715	G	3230	AN2319A	BOLT            			PIPER 	PA32  	PA32R301    	7103218	SO  										NLG DOWNLOCK	BROKEN          	B		A	MZER	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	15	69160					32R8513016				PILOT REPORTED COULD NOT GET NOSE GEAR DOWN LIGHT WHEN GEAR SELECTED DOWN IN-FLIGHT.  EMERGENCY EXTENSION UNSUCCESSFUL. 	 PILOT LANDED AIRPLANE UNEVENFULLY.  MAINTENANCE PERSONNEL FOUND BOLT BROKEN ON DOWNLOCK TO ACTUATOR.  BENT DOWNLOCK, AN	D ROD END SEIZED.  SEVERAL INSPECTIONS HAVE FOUND THE SAME BOLT BENT AND REQUIRED REPLACEMENT.  RECOMMEND A STRONGER BOL	T BE INSTALLED.			1	L	7	1 	3O				A3SO    					 
1997080700369	19970807	00369	SO  	1997	8	7	97ZZZX3495       	2	19970703	G	8530	637836	VALVE SPRING    		642343      	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 2 CYLINDER	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	17	85SC		717  			421C0026	R604049L			THE PILOT NOTICED A VIBRATION AT CRUISE POWER AFTER AN HOUR OF FLIGHT.  AFTER LANDING, INVESTIGATION REVEALED THE RIGHT 	ENGINE WOULD INCREASE IN VIBRATION WITH AN INCREASE IN RPM AND NOT DEVELOP FULL RPM.  TROUBLESHOOTING REVEALED THE NR 2 	CYLINDER HAD BOTH INNER VALVE SPRINGS BROKEN WHICH ALLOWED THE VALVES TO FLOAT AS RPM WAS INCREASED.  REPLACEMENT OF THE	 VALVE SPRINGS CORRECTED THE PROBLEM.  SUBMITTER STATED THIS IS THE SECOND INSTANCE TO ENCOUNTER A BROKEN INNER VALVE SP	RING ON THIS SAME TYPE OF ENGINE.		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997080700370	19970807	00370	SW  	1997	8	7	97ZZZX3496       	1	19970603	G	6310	SKCP2281103	DRIVESHAFT      			BELL  	204   	UH1H        	1181407	SW  										ENG TRANSMISSION	FAILED          	B			NTWR	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			EX	EXTERNAL LOAD  	1			NM	01	85NW	903  	497  		2553	6600792				DRIVESHAFT CAUSED HIGH FREQUENCY VIBRATION DURING EXTERNAL LOAD OPERATIONS.  DRIVESHAFT FAILED COMPLETELY AFTER APPROXIM	ATELY ONE MINUTE WHILE AIRCRAFT WAS RETURNING TO ITS LANDING AREA.  AIRCRAFT SUSTAINED HARD LANDING WITH NO PILOT INJURI	ES.				1	G	7	1 	4U				EXPA1G71					 
1997080700371	19970807	00371	WP  	1997	8	7	97ZZZX3497       	1	19970728	G	2921	4365082	DIAPHRAGM       		43442795002 	DOUG  	DC8   	DC8*        		WP  										ACCUMULATOR	TORN            	B			DM4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					JW2779A					NEW BLADDER DIAPHRAGM INSTALLED IN ACCUMULATOR JULY, 1996.  UNIT FAILED JULY, 1997.  BLADDER TORN AND LEAKING.  THIRD TY	PE FAILURE SEEN WITH THIS PART NUMBERED BLADDER.  BLADDER PMA PART FROM KAPCO (DOUGLAS LICENSEE).					2	L	7	4 	4J			F	4A25    					 
1997080700372	19970807	00372	EA  	1997	8	7	97ZZZX3498       	1	19970722	G	2434	VHP430KH3	CELL            	SAFT        	40783       	CNDAIR	CL600 	CL6001A11   	1900302	EA  										BATTERY	SHORTED         	B			WC7R	K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			GL	25	100LR	111  			083318	1064				AIRCRAFT BATTERY CHARGER DROPPING OFF-LINE.  REMOVED AND SHIPPED BATTERY TO INSPECTION AND SERVICE.  FOUND SHORTED CELL,	 STRAPS HAD BURNED SMALL HOLE THROUGH SIDE OF CELL. BATTERY WILL BE SHIPPED BACK TO MANUFACTURER DUE TO LOW TSN.					2	L	7	2 	4F			RT	A21EA   					 
1997080700373	19970807	00373	CE  	1997	8	7	97ZZZX3499       	1	19970724	G	5500	26120691	GUSSET          			CESSNA	208   	208B        	2073701	CE  										TAIL CONE	CHAFED          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	723FX					208B0456				WHILE REMOVING THE ELEVATOR TRIM ACTUATOR, DISCOVERED THE TRIM CONTROL CABLE WAS INCORRECTLY ROUTED BENEATH THE GUSSET I	N THE TAIL CONE RATHER THAN THROUGH THE GUSSET.  THIS CAUSED THE CABLES TO RIDE AGAINST THE AFT FLANGE OF THE GUSSET.  M	INIMAL DAMAGE WAS DONE TO THE GUSSET WITH LESS THAN .0312 INCH REMOVED FROM THE GUSSET FLANGE AND NO DAMAGE TO THE CONTR	OL CABLES.  THERE WAS NO INDICATION THAT THE CABLES HAD BEEN REMOVED OR RE-ROUTED SINCE THE AIRCRAFT WAS NEW.  RECOMMEND	 INSPECTING OTHER AIRCRAFT IN THIS RANGE OF SERIAL NUMBERS FOR INCORRECTLY ROUTED TRIM CABLES.		1	H	7	1 	3T				A37CE   					 
1997080700374	19970807	00374	EU  	1997	8	7	97ZZZX3500       	1	19970723	G	2430	Z00N7707115228	CONNECTOR       			SOCATA	TBM   	TBM700      	8682000	EU  										BATTERY	BURNED          	B		A	LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	800GS	801  				5				WHILE REMOVING BATTERY FOR MAINTENANCE, FOUND NEGATIVE TERMINAL ON CONNECTOR ARCED AND BURNED.  THE NEGATIVE POST IN BAT	TERY RECEPTACLE WAS ALSO DAMAGED AND POSSIBLY CAUSED BY WORN CONNECTOR (SOCKET ENLARGED) NOT PROVIDING GOOD CONTACT.  CO	NNECTOR SHOULD BE CHECKED WITH GO/NO-GO GAUGE ANYTIME BATTERY MAINTENANCE IS PERFORMED.  CONNECTOR AND RECEPTACLE REPLAC	ED.			1	L	7	1 	3T			RT	A60EU   					 
1997080700376	19970807	00376	NE  	1997	8	7	97ZZZX3502       	2	19970607	G	7250		ENGINE          			BOEING	747   	747SR46     		NM  	PWA   	JT9   	JT9D7       	52054	NE  					NR 3 LP TURBINE	FAILED          	B		A	GK4Y	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	03	478EV					21033				PPG/AKL - FLT EZ6987 - EN ROUTE, DIVERTED TO NAN DUE NR 3 ENGINE FAILURE DURING CLIMB.  NR 3 ENGINE INSPECTIONS CARRIED 	OUT AND SEVERAL LP TURBINE BLADES FOUND SEVERELY DAMAGED.  AOG EVERGREEN MECHANICS AND ATS ENGINEERS CARRIED OUT ENGINE 	CHANGE AND ENGINE POWER RUN SATISFACTORY.				2	L	7	4 	4F	4	F		A20WE   	E20EA				 
1997080700377	19970807	00377	NE  	1997	8	7	97ZZZX3503       	2	19970720	G	7200		ENGINE          			BOEING	747   	747SR46     		NM  	PWA   	JT9   	JT9D7       	52054	NE  					NR 2	FAILED          	B		A	GK4Y	A				UNSCHED LANDING         				O	M		OTHER                     	OVER TEMP                 		CL	CLIMB          	1			WP	03	478EV					21033				PPG/AKL - FLT EZ6987 - EN ROUTE, DIVERTED TO NAN DUE NR 2 ENGINE SHUT DOWN (OVER TEMP) DURING CLIMB.  DURING GROUND INSP	ECTION, MELTED METAL PIECES FOUND IN TAIL PIPE AREA, NR 2 ENGINE.  EVERGREEN DECIDED TO TRANSFER CARGO TO RELIEVING AIRC	RAFT AND FERRY N478EV ON 3 ENGINES TO HONG KONG.  A ONE-OFF APPROVAL TO PREPARE AIRCRAFT PER EZ INSTRUCTIONS GIVEN TO AT	S.  CERTIFICATION CARRIED OUT BY EZ MECHANIC.			2	L	7	4 	4F	4	F		A20WE   	E20EA				 
1997080700378	19970807	00378	CE  	1997	8	7	97ZZZX3504       	1	19970716	G	2820	W99106	COUPLING        			LEAR  	55    	55C         	5170706	CE  										LT FUEL SUPPLY	FAILED          	B		A	VIBR	A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	13	111US	3359 				147				CLAMP ON COUPLING OPENED AND FELL OFF.  COUPLING LOCATED IN FUEL SUPPLY LINE JUST BELOW LEFT FUEL FILTER IN TAIL CONE. A	IRCRAFT CREW NOTICED DECREASING FUEL QUANTITY AND DIVERTED TO BNA.  LEFT ENGINE THROTTLE SET TO IDLE WHEN PROBLEM NOTICE	D.  ENGINE FLAMED OUT ON FINAL APPROACH.  AIRCRAFT LANDED WITH 800 POUNDS FUEL ON BOARD.  LOST 3,650 POUNDS OF FUEL IN L	ESS THAN 30 MINUTES.  FUEL IN TAIL CONE AREA DRAINED OUT THROUGH DRAIN HOLES, BUT WAS A HAZARDOUS SITUATION DUE TO EQUIP	MENT LOCATED IN TAIL CONE.  COUPLING REMOVED AND REPLACED WITH NEW DESIGN COUPLING.		2	L	7	2 	4F			RT	A10CE   					 
1997080700416	19970807	00416	EU  	1997	8	7	97ZZZX3506       	1	19970718	G	6230	4619305032	ROTOR MAST      		4638001004  	BOLKMS	105   	BO105C      	5626005	EU  										TRANSMISSION	CRACKED         	B		A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501AL	7071 			1117	S58				DURING MAIN ROTOR HUB REMOVAL, NOTED THE MAIN ROTOR MAST FLANGE WAS CRACKED.  THE MAST FLANGE WAS FOUND CRACKED APPROXIM	ATELY THREE-FOURTHS AROUND. THE CRACK WAS NEAR THE RADIUS OF THE FLANGE AND THE STUD HOLES.					1	G	7	2 	3U				H3EU    					 
1997081400118	19970814	00118	EU  	1997	8	14	97ZZZX3537       	1	19970509	G	2820	S25CX315	BELLCRANK       			BRAERO	DH125 	BAE125800A  	1500285	EU  										FUEL SYS LP COCK	CORRODED        	B		A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	800N	6739 								DURING A ROUTINE 600-HOUR INSPECTION, THE FUEL SYSTEM LP COCK BELLCRANK AND CROSSFEED BELLCRANK WERE FOUND EXTENSIVELY C	ORRODED.  THIS AREA IS BETWEEN THE MAIN GEAR WHEELWELLS BELOW THE POTTY AREA.  EVIDENCE OF 'BLUE POTTY WATER' SATURATED 	THE AREA.  ACCESS TO THIS AREA IS THROUGH PANELS W511 AND W512 IN THE MAIN GEAR WHEELWELLS.  THE BELLCRANKS WERE CHANGED	 AND THE AREA CLEANED.  SPECIAL ATTENTION SHOULD BE GIVEN DURING INSPECTIONS TO THE POTTY AREA IN LIGHT OF THE CORROSIVE	 CONTENT OF LAV CONTAINERS.		2	L	7	2 	4F			RT	A3EU    					 
1997081400119	19970814	00119	GL  	1997	8	14	97ZZZX3538       	2	19970722	G	7250	6889069	COUPLING        		23035128    						ALLSN 	250C  	250C30P     	03013	GL  					TURBINE N2	FAILED TEST     	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	11		842  			58787		CAE895526			N2 COUPLING FAILED SPLINE TEST.											3	U			E1GL				 
1997081400120	19970814	00120	NM  	1997	8	14	97ZZZX3539       	1	19970723	G	2710	1293841	PISTON ASSY     		129307      	BOEING	747   	747*        		NM  										AIL ACTUATOR	BENT            	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					K135					INSPECTION OF AILERON ACTUATOR FOUND PISTON ATTACHMENT POINTS WHERE THE PISTON ATTACHES TO THE PISTON CONNECTOR, 15 ARE 	BENT OUTWARDS.  AREA OF PISTON BENT UNDER NORMAL OPERATION.					2	L	7	4 	4F			RT	A20WE   					 
1997081400121	19970814	00121	SO  	1997	8	14	97ZZZX3540       	2	19970729	G	7260	632018	DRIVE GEAR      			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					ALT DRIVE	DAMAGED         	H				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	25	111HR		807  			CE512	249272R			ALTERNATOR FAILED IN-FLIGHT.  NORMAL LANDING MADE.  ELECTRICALLY ALTERNATOR CHECKED OK.  SAW ROTOR NOT MOVING WITH PROPE	LLER.  REMOVED ALTERNATOR.  ALTERNATOR DRIVE GEAR AND ALTERNATOR FACE DRIVE GEAR TEETH WORN AWAY.  REMOVED DRIVE.  PIECE	S OF BUSHING FELL OUT OF ASSY. DISASSEMBLED ALTERNATOR.  DRIVE END BEARING SLOPPY.  ALTERNATOR SHAFT WORN UNEVENLY AT BE	ARING.  ROTOR HAD BEEN RUBBING ON STATOR.  FOUND METAL IN OIL FILTER.  ENGINE REMOVED FOR OVERHAUL.			1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997081400122	19970814	00122	CE  	1997	8	14	97ZZZX3541       	1	19970729	G	2410	640934	DRIVE ASSY      	PRESTOLITE  	ALX9424     	BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					ALT DRIVE	FAILED          	H				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	25	111HR		807  		5120624	CE512	249272R			ALTERNATOR FAILED IN-FLIGHT.  NORMAL LANDING MADE.  ELECTRICALLY ALTERNATOR CHECKED OK.  SAW ROTOR NOT MOVING WITH PROPE	LLER.  REMOVED ALTERNATOR.  ALTERNATOR DRIVE GEAR AND ALTERNATOR FACE DRIVE GEAR TEETH WORN AWAY.  REMOVED DRIVE.  PIECE	S OF BUSHING FELL OUT OF ASSY. DISASSEMBLED ALTERNATOR.  DRIVE END BEARING SLOPPY.  ALTERNATOR SHAFT WORN UNEVENLY AT BE	ARING.  ROTOR HAD BEEN RUBBING ON STATOR.  FOUND METAL IN OIL FILTER.  ENGINE REMOVED FOR OVERHAUL.			1	L	7	1 	3O	3	O		3A15    	E5CE				 
1997081400123	19970814	00123	CE  	1997	8	14	97ZZZX3542       	1	19970701	G	2720	0024100397	BELLCRANK       			BEECH 	95    	95B55       	1152729	CE  										RUDDER PEDAL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	6663C	2160 				TC2265				RUDDER PEDAL INTERCONNECT REARWARD PROTRUDING ARM BROKE COMPLETELY OFF APPROXIMATELY 1 INCH FORWARD OF INTERCONNECT ROD 	PIVOT.  BELLCRANK BROKE DURING GROUND OPERATIONS WHEN FLIGHT INSTRUCTOR APPLIED PRESSURE ON RUDDER PEDAL OPPOSITE OF THE	 STUDENT, IN ORDER TO PREVENT AN EXCESSIVELY SHARP TURN.  BROKEN CROSS-SECTION DOES REVEAL PREVIOUS EXISTING CRACK.				1	L	7	2 	3O			RT	3A16    					 
1997081400124	19970814	00124	CE  	1997	8	14	97ZZZX3543       	1	19970721	G	7602	5038901223	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  										RT ENG MIXTURE	FAILED          	B			FFKR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SO	05	1HW	1155 				TH271				RIGHT ENGINE FAILED APPROXIMATELY 5 MINUTES AFTER TAKEOFF.  ENGINE SECURED IAW ENGINE OUT CHECK LIST AND RETURNED TO AIR	PORT WITH NO FURTHER PROBLEMS.  CABLE FAILED .50 INCH FROM ROD-END ON ENGINE SIDE OF CABLE.  CABLE WAS INSTALLED CORRECT	LY, CLEANED, AND LUBED AT EACH 100-HOUR INSPECTION INTERNAL.  RECOMMEND LARGER CABLE.				1	L	7	2 	3O			 	3A16    					 
1997081400125	19970814	00125	WP  	1997	8	14	97ZZZX3544       	1	19970719	G	6520	HPPBR49	BEARING         			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					T/R GEARBOX	MISMANUFACTURED 	B		A	OUGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17					H03037					NEW REPLACEMENT BEARING RECEIVED WITH INSTRUCTIONS FROM MRC (BEARING MFG), AND HILLER SL UH12-25-1 DESCRIBING INSTALLATI	ON INSTRUCTIONS WITH REGARDS TO THE FILING NOTCHES AND BEARING MARKINGS ON THE OUTER RACE.  THESE INSTRUCTIONS ORIENT TH	E BEARING SO THE MAJOR THRUST LOAD IS ON THE RACES THAT DO NOT HAVE FILING NOTCHES.  THIS BEARING WAS RECEIVED WITH MARK	INGS OPPOSITE THE WRITTEN INSTRUCTIONS.  BEARING RETURNED TO HILLER.			1	G	7	1 	3O	3	O		4H11    	E304				 
1997081400127	19970814	00127	WP  	1997	8	14	97ZZZX3546       	1	19970718	G	7330	369H81443	BYPASS SWITCH   		38655       	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL PUMP	FAILED          	B		A	GHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1109P	301  			T1927	1100849D	CAE833681			SWITCH FAILED TO CLOSE AT PRESCRIBED LIMITS OF DN-41.1 DURING A 300-HOUR INSPECTION.  THIS IS THE 7TH SWITCH TO FAIL IN 	LESS THAN 500 HOURS OF OPERATION SINCE FIRST FAILURE REPORTED ON 12-10-96.  THAT FAILURE COULD HAVE PREVENTED AN ENGINE 	FAILURE DUE TO FUEL CONTAMINATION IF THE SWITCH WOULD HAVE WORKED PROPERLY.  SUBMITTER RECOMMENDS A MANDATORY 100-HOUR I	NSPECTION INTERVAL.  NOTE:  AC NR 43-16, FUEL NOZZLE FILTER, 'NO FUEL BYPASS INDICATION'. NR 7313, PAGE 13.			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997081400130	19970814	00130	GL  	1997	8	14	97ZZZX3549       	2	19970710	G	7250	223031938	NOZZLE          		6898735     	AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GP TURBINE	FAILED          	B		A	KUVR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	19	8WH	709  			CAT35469	7256	CAE832740			ENGINE PRODUCING LOW POWER.  INSPECTED 2ND STAGE TURBINE NOZZLE.  FOUND TURBINE WHEEL SHROUD FLAKING AND SEPARATING CAUS	ING EXCESSIVE TURBINE WHEEL TIP CLEARANCE.  FOUND OUTER BAND CRACKED RADIALLY CAUSING GAS PATH LEAKAGE.  THIS PART SHOUL	D MAKE 1,750 HRS AT LEAST.  THIS, ALONG WITH NR 2 TURBINE WHEEL EROSION, CAUSED HIGH N1, HIGH TEMPERATURE, AND LOW POWER	.			1	G	7	2 	3U	3	U		H7EU    	E4CE				 
1997081400131	19970814	00131	GL  	1997	8	14	97ZZZX3550       	2	19970710	G	7250	6886407	WHEEL           		6898735     	AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GP TURBINE	ERODED          	B			KUVR	O				OTHER                   				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SO	19	8WH	709  			X121765	7256	CAE832740			ENGINE PRODUCING LOW POWER.  REMOVED TURBINE ASSY AND SEPARATED GAS PRODUCER FROM POWER TURBINE.  FOUND NR 1 TURBINE WHE	EL SEVERELY CORRODED AFTER ONLY 708.5 HRS TT.  WHEEL LIFE IS 1775.0 HRS.  TIP CLEARANCE WAS ALSO EXCESSIVE.  NO EVIDENCE	 OF FOD.  LEADING EDGES WERE FLATTENED. THIS, ALONG WITH NOZZLE SEPARATION, CAUSED HIGH N1 WITH HIGH TEMPERATURE AND LOW	 POWER.			1	G	7	2 	3U	3	U		H7EU    	E4CE				 
1997081400132	19970814	00132	EA  	1997	8	14	97ZZZX3551       	2	19970625	G	8530		ROCKER SHAFT    			ENSTRM	F28   	F28F        	3300412	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					NR 2 CYLINDER	FAILED          	D		A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	23	99YC	48   				809	L27061514			LOOSE RETAINING NUTS WORKED OFF STUDS ALLOWING THE PORT COVER TO FALL OFF AND NR 2 CYLINDER INTAKE VALVE ROCKER ARM SHAF	T TO FALL OUT OF THE ENGINE RESULTING IN A CRASH LANDING. SUGGEST REVIEWING ENSTROM PRODUCTION CERTIFICATE AND TIGHTEN T	HE INSPECTION PROCEDURE TO REDUCE THE CHANCES THAT ANOTHER HELICOPTER WILL BE RELEASED WITH HIDDEN LOOSE PARTS.				1	G	7	1 	3O	3	O		H1CE    	1E10				 
1997081400133	19970814	00133	CE  	1997	8	14	97ZZZX3552       	1	19970620	G	3244	850X10X10PR	TIRE            	GOODYEARAERO		MTSBSI	MU2   	MU2B60      	5780460	CE  										RT MLG	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	01	360RA	201  				740SA				DURING A LANDING JUNE 20, 1997, THE RIGHT MAIN LANDING GEAR TIRE TREAD SEPARATED FROM APPROXIMATELY TWO-THIRDS OF THE CI	RCUMFERENCE OF THE TIRE.  A NEW TIRE AND SERVICEABLE WHEEL WERE INSTALLED IAW THE MANUFACTURER'S MM PROCEDURES AND THE L	ANDING GEAR AREA WAS VISUALLY INSPECTED FOR DAMAGE.  NO DEFECTS WERE APPARENT.  THE AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	2 	3T			RT	A10SW   					 
1997081400134	19970814	00134	CE  	1997	8	14	97ZZZX3553       	1	19970620	G	3230	030A3876012	GEARBOX         			MTSBSI	MU2   	MU2B60      	5780460	CE  										RT MLG ACTUATOR	FAILED          	D	L	A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	01	360RA	3405 				740SA				INVESTIGATION FOLLOWING LANDING WITH RT MLG RETRACTED FOUND THE RT MAIN TO LT MAIN DRIVE SHAFT (PN 030A-38610-21) DISCON	NECTED.  THE RT MAIN ACTUATOR WAS TURNED MANUALLY UNTIL THE RT LANDING GEAR WAS IN THE DOWN POSITION.  INSPECTIONS REVEA	LED THE LOWER AFT ATTACH BOLT FOR THE RT MLG ACTUATOR WAS LOOSE AND THAT THE NUT WAS NOT ON THE BOLT.  THE ACFT WAS PLAC	ED ON JACKS AND A VISUAL INSPECTION REVEALED THE RT MLG  ACTUATOR GEARBOX HOUSING HAD FAILED AND THE REMAINING THREE FAS	TENERS WERE LOOSE ALLOWING ENOUGH MOVEMENT BETWEEN THE GEARBOX AND THE ACFT STRUCTURE TO DISCONNECT THE INTERCONNECT DRI	VE SHAFT.  BOTH MLG ACTUATOR GEARBOXES WERE REMOVED AND ALL ATTACHING HARDWARE WAS REPLACED WITH NEW ITEMS.	1	H	7	2 	3T			RT	A10SW   					 
1997081400135	19970814	00135	CE  	1997	8	14	97ZZZX3554       	1	19970724	G	5210	504300431329	SUPPORT         			BEECH 	200   	B200        	1152922	CE  										DOOR HINGE	CRACKED         	B	S	A	VG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	770AE	3323 				BB1226				LOOSE AFT RIVETS IN CABIN DOOR HINGE LED TO FURTHER INVESTIGATION.  FOUND HINGE SUPPORT INSIDE DOOR ASSY CRACKED TO A LE	NGTH OF 4 INCHES THROUGH 4 EACH RIVET HOLES.  SUGGEST HINGE AFT RIVETS MAY HAVE BEEN IN A LOOSE CONDITION FOR AN EXCESSI	VE LENGTH OF TIME.				1	L	7	2 	4T				A24CE   					 
1997081400212	19970814	00212	NM  	1997	8	14	97ZZZX3555       	1	19970430	G	6322	B1741	FAN WHEEL       			ROBSIN	R22   	R22BETA     		NM  										COOLING FAN	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	4033S	100  				1501				CRACKS FOUND DURING 100-HOUR INSPECTION OF AIRCRAFT IN FAN WHEEL ASSEMBLY, SECOND FAN WHEEL INSTALLED SINCE AIRCRAFT REB	UILT BY FACTORY.  FAN WAS BALANCED AT EACH INSTALLATION YET CONTINUED TO CRACK.  TOTAL AIRCRAFT TIME SINCE REBUILT, 499.	0 HOURS.				1	G	7	1 	3O				H10WE   					 
1997081400526	19970814	00526	NM  	1997	8	14	97ZZZX3560       	1	19970805	G	5551	69144105	PIN             			BOEING	727   	727251      	138408H	NM  										RT H STAB ATTACH	BROKEN          	B		A	JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	279US					21158				DURING C-CHECK, REMOVAL OF HORIZONTAL STABILIZER REVEALED THAT RT STABILIZER ATTACHMENT PIN WAS SEVERELY RUSTED AND BROK	EN IN HALF.  ALSO, FOUND FAIL-SAFE BOLT INSIDE PIN SEVERELY RUSTED.  SUBMITTER STATED PART FAILURE DUE TO LACK OF LUBRIC	ATION.				2	L	7	3 	4F				A3WE    					 
1997081400527	19970814	00527	WP  	1997	8	14	97ZZZX3561       	2	19970110	G	7200		ENGINE          			CASA  	C212  	C212CC      	2410204	EU  	GARRTT	TPE331	TPE33110    	01514	WP  					NR 2	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AL	03	348CA		1996 			175	P37050			NR 2 ENGINE SHUT DOWN IN-FLIGHT DUE TO ZERO TORQUE AND DECREASING ENGINE RPM FUEL FLOW.  ENGINE OIL OVER-SERVICE SUSPECT	ED DUE TO OIL TANK VENT VALVE OPEN.					2	H	7	2 	4T	4	T		A43EU   	E4WE				 
1997081400529	19970814	00529	GL  	1997	8	14	97ZZZX3563       	1	19970622	G	7160		AIR CLEANER     			AMTR  	HORNET	HORNET      	05630FL	GL  										ENGINE INT	DEPARTED        	G		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	09	414R	96   				0008				AMATEUR-BUILT AIRCRAFT.  DURING FLIGHT, ENGINE PROPELLER FAILED.  AN OFF-AIRPORT LANDING WAS MADE.  AIRCRAFT SUSTAINED D	AMAGE TO LANDING GEAR.  INVESTIGATION DETERMINED THAT ONE ENGINE AIR CLEANER ASSY WAS  MISSING, BELIEVED TO HAVE STRUCK 	THE PROPELLER.  FILTER IS A K & N MODEL AIR CLEANER.  NO PART NUMBER AVAILABLE.  NOT KNOWN WHEN AIR CLEANERS LAST MAINTA	INED.			1	H	7	1 	3I			NT	EXPA1H71					 
1997081400530	19970814	00530		1997	8	14	97ZZZX3564       	4	19970604	G	3452	071015071301	TRANSPONDER     			BELL  	230   	230         	1182149	SW  										CONTROL PANEL	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				X1154	23019				CONTROL PANEL WILL NOT SQUAWK 1200 WHEN TURNED TO VFR POSITION.						1	G	7	2 	3U			NC	H9SW    					 
1997081400531	19970814	00531		1997	8	14	97ZZZX3565       	4	19970215	G	3454	071121627	CONTROL HEAD    			BELL  	230   	230         	1182149	SW  										NAV CONTROL	FAILS           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	716  			5960	23019				NAVIGATION CONTROL HEAD LOSES MEMORY.						1	G	7	2 	3U			NC	H9SW    					 
1997081400532	19970814	00532		1997	8	14	97ZZZX3566       	4	19970215	G	3422	5050031926	GYRO            			BELL  	230   	230         	1182149	SW  										COCKPIT DG	FLAG FAILED     	B			TI1R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	05	4UV				1476	23019				DIRECTIONAL GYRO FLAG WILL NOT RETRACT.						1	G	7	2 	3U			NC	H9SW    					 
1997081400533	19970814	00533		1997	8	14	97ZZZX3567       	4	19970131	G	3455	071121009	CONTROL         			BELL  	230   	230         	1182149	SW  										COCKPIT ADF	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	690  			5271	23019				ADF CONTROL HEAD WOULD NOT POWER UP.						1	G	7	2 	3U			NC	H9SW    					 
1997081400534	19970814	00534		1997	8	14	97ZZZX3568       	4	19970228	G	3160	066040211111	SYMBOL GENERATOR			BELL  	230   	230         	1182149	SW  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			SW	05	4UV				1945	23019				AIRCRAFT SWAYS WHEN ON GPS APPROACH.						1	G	7	2 	3U			NC	H9SW    					 
1997081400535	19970814	00535	SW  	1997	8	14	97ZZZX3569       	1	19970217	G	3340	7028502	STROBE          			BELL  	230   	230         	1182149	SW  										ANTI COLLISION	SHORTED         	B			TI1R	K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			SW	05	4UV					23019				BEACON SHORTED AND BURNED.  CIRCUIT BREAKER TRIPS WHEN POWER APPLIED.						1	G	7	2 	3U			NC	H9SW    					 
1997081400536	19970814	00536	SW  	1997	8	14	97ZZZX3570       	1	19970208	G	2430	A1077V	RELAY           			BELL  	230   	230         	1182149	SW  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	705  			CL23999	23019				A1 STUD BURNED THROUGH.  REMOVED TO CW TB 230-95-10.						1	G	7	2 	3U			NC	H9SW    					 
1997081400537	19970814	00537	SW  	1997	8	14	97ZZZX3571       	1	19970115	G	2430	A1077V	RELAY           			BELL  	230   	230         	1182149	SW  										DC SYSTEM	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	661  			TA03729	23019				RELAY INTERMITTENTLY STICKS - GENERATOR WILL NOT COME ON LINE (INTERMITTENT).						1	G	7	2 	3U			NC	H9SW    					 
1997081400538	19970814	00538	SW  	1997	8	14	97ZZZX3572       	1	19970414	G	2422	PC125123C	INVERTER        			BELL  	230   	230         	1182149	SW  										AC SYSTEM	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	853  			5494	23019				INTERMITTENT INVERTER.						1	G	7	2 	3U			NC	H9SW    					 
1997081400539	19970814	00539		1997	8	14	97ZZZX3573       	4	19970301	G	3421	222375033101	INDICATOR       			BELL  	222   	222U        	1182140	SW  										COCKPIT ATITUDE	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM	163  			0158	47573				ATTITUDE INDICATOR INOPERATIVE.						1	G	7	2 	3U				H9SW    					 
1997081400540	19970814	00540		1997	8	14	97ZZZX3574       	4	19970408	G	3455	071123400	ANTENNA         		KA44B       	BOLKMS	117   	BK117A4     	5626017	EU  										ADF	FAULTY          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG	61   			62593	7083				ADF WILL NOT TRACK RMI NEEDLE.						1	G	7	2 	3U				H13EU   					 
1997081400541	19970814	00541	EU  	1997	8	14	97ZZZX3575       	1	19970220	G	3340	6034745	POWER SUPPLY    			BOLKMS	117   	BK117A1     	5626010	EU  										ANTI COLLISION	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117LF				0853	7013				ANTI-COLLISION LIGHT POWER SUPPLY NOISY.  CAUSED RADIO INTERFERENCE AND SPIKES ON AMPMETER.						1	G	7	2 	3U				H13EU   					 
1997081400542	19970814	00542	SW  	1997	8	14	97ZZZX3576       	1	19970223	G	2435	23032048	GENERATOR       			BELL  	222   	222         	1182122	SW  										START GEN	FAILED          	B			TI1R	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SW	05	911LW	315  			7723	47520				GENERATOR CAME OFF-LINE AND WOULD NOT RESET.						1	G	7	2 	3U				H9SW    					 
1997081400543	19970814	00543		1997	8	14	97ZZZX3577       	2	19970710	G	7210	23055464	COVER           																	ENG GEARBOX	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										TOP STUD FOR TURBINE MOUNT WILL NOT TORQUE.  COVER ONLY HAS 50.1 HOURS SINCE OVERHAULED.  REMOVED AND REPLACED.																			 
1997081400544	19970814	00544		1997	8	14	97ZZZX3578       	4	19970625	G	3452	066106200	TRANSPONDER     	KING        	KT76        															COCKPIT	INOPERATIVE     	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					38776					TRANSPONDER UNIT INOPERATIVE WHEN INSTALLED.  REMOVED AND REPLACED.																			 
1997081400629	19970814	00629		1997	8	14	97ZZZX3579       	4	19970728	G	2312	4000103000	RECEIVER        		RT450       	BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	214AE				811	7206				TRANSCEIVER WILL NOT TRANSMIT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997081400630	19970814	00630		1997	8	14	97ZZZX3580       	4	19970619	G	3422	5050031926	DIRECTIONAL GYRO			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	317MC				25005	7505				TOTAL TIME INSTALLED 221.2 HOURS.  INTERMITTENT - GYRO SLOW TO SPOOL AND SPINS IN-FLIGHT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997081400631	19970814	00631		1997	8	14	97ZZZX3581       	4	19970625	G	3416	B4553110004	ALTIMETER       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				5341	7505				ALTIMETER FAILED LEAK CHECK.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997081400632	19970814	00632		1997	8	14	97ZZZX3582       	4	19970625	G	3416	1042011968E	ALTIMETER       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				151552	7505				ALTIMETER CODE OFF FLAG ALWAYS 'ON'.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997081400633	19970814	00633	EU  	1997	8	14	97ZZZX3583       	1	19970717	G	5210	1172427401	GUIDE ASSY      			BOLKMS	BK117 	BK117C1     	5626025	EU  										DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				DOOR TRACK LATCH WORN.  REF:  RMA NR R011538.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997081400634	19970814	00634	SW  	1997	8	14	97ZZZX3584       	1	19970621	G	7810	230063301101	EXHAUST DUCT    			BELL  	230   	230         	1182149	SW  										ENGINE EXHAUST	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	995  				23019				CRACKED EXHAUST DUCT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997081400635	19970814	00635	SW  	1997	8	14	97ZZZX3585       	1	19970702	G	6400	222012711107	LINK            			BELL  	230   	230         	1182149	SW  										T/R CTWT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				TAIL ROTOR COUNTERWEIGHT HAS WORN BEARINGS.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H9SW    					 
1997081400636	19970814	00636	SW  	1997	8	14	97ZZZX3586       	1	19970702	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				PITCH LINK HAS WORN BEARINGS.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997081400637	19970814	00637	SW  	1997	8	14	97ZZZX3587       	1	19970704	G	2430	1820300150	SHUNT           			BELL  	230   	230         	1182149	SW  										DC SYSTEM	BURNT           	B			TI1R	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	05	4UV					23019				SHUNT DISCOLORED CAUSING GENERATOR NOT TO COME ON LINE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997081400638	19970814	00638	SW  	1997	8	14	97ZZZX3588       	1	19970621	G	7810	230063301102	EXHAUST DUCT    			BELL  	230   	230         	1182149	SW  										ENGINE EXHAUST	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	995  				23019				CRACKED EXHAUST DUCT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997081400639	19970814	00639	EU  	1997	8	14	97ZZZX3589       	1	19970710	G	7714	1179405603	INDICATOR NG    			BOLKMS	117   	BK117B1     	5626012	EU  										ENGINE N1	FLUCTUATES      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	460H				227	7142				N1 GAUGE FLUCTUATING 70 PERCENT N1.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997081400640	19970814	00640	SW  	1997	8	14	97ZZZX3590       	1	19970619	G	3510	IDP5	OXY INDICATOR   			BELL  	206   	206L1       	1182107	SW  										OXYGEN SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	519EH				6250001	45429				OXYGEN INDICATOR WOULD NOT SAY SET.  READ-OUT WOULD HUNT UP AND DOWN SCALE.  REF:  AR NR 707-8312.  REMOVED AND REPLACED	.					1	G	7	1 	3U				H2SW    					 
1997081400641	19970814	00641		1997	8	14	97ZZZX3591       	4	19970617	G	2211	11788292	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT SPAS	FAILED          	B			TI1R	K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			SW	05	527MB				0489113	7103				SPAS COMPUTER CAUTION LIGHT ILLUMINATES INTERMITTENTLY IN-FLIGHT.  UNIT FAILED AFTER ONLY 178 HOURS.  REMOVED AND REPLAC	ED.  (X)					1	G	7	2 	3U				H13EU   					 
1997081400642	19970814	00642	SW  	1997	8	14	97ZZZX3592       	1	19970620	G	7810	2060643000005	EXHAUST STACK   			BELL  	206   	206L1       	1182107	SW  										ENGINE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	721SP	339  				45486				EXHAUST DUCT CRACKED.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW    					 
1997081400653	19970814	00653		1997	8	14	97ZZZX3594       	4	19970314	G	2211	11788292	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										SPAS	MALFUNCTION     	B			TI1R	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	05	1140H				0588089	7078				SPAS LIGHT WILL NOT EXTINGUISH ON ANNUNCIATOR PANEL.						1	G	7	2 	3U				H13EU   					 
1997081400654	19970814	00654	EU  	1997	8	14	97ZZZX3595       	1	19970331	G	2620	301011032	FIRE BOTTLE     			BOLKMS	117   	BK117A3     	5626015	EU  										FIRE EXT SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117LS				22706A2	7113				FIRE EXTINGUISHER BOTTLE LOST PRESSURE AND CONTENTS.						1	G	7	2 	3U				H13EU   					 
1997081400655	19970814	00655	EU  	1997	8	14	97ZZZX3596       	1	19970404	G	7712	G555674	TRANSDUCER      			BOLKMS	117   	BK117A4     	5626017	EU  										TORQUE	ERRATIC         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG	21   			928	7083				TORQUE INDICATION ERRATIC.						1	G	7	2 	3U				H13EU   					 
1997081400656	19970814	00656	EU  	1997	8	14	97ZZZX3597       	1	19970427	G	6730	391110002	ACTUATOR        			BOLKMS	117   	BK117B1     	5626012	EU  										SPAS	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	214AE	2523 			237	7206				PART RECEIVED DEFECTIVE. ACTUATOR WILL NOT SELF-TEST, AND MOVES TOO SLOWLY.						1	G	7	2 	3U				H13EU   					 
1997081400657	19970814	00657		1997	8	14	97ZZZX3598       	4	19970501	G	3424	10290	GYRO            			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT RATE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	214AE				0112	7206				RATE GYRO WILL NOT STABILIZE AND OUTPUT CONSTANTLY FLUCTUATES.						1	G	7	2 	3U				H13EU   					 
1997081400658	19970814	00658		1997	8	14	97ZZZX3599       	4	19970528	G	3421	2223750333101	INDICATOR       			BELL  	222   	222U        	1182140	SW  										COCKPIT ATTITUDE	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM	8    			0068	47573				ATTITUDE INDICATOR INOPERATIVE.  ONLY 7.6 HRS SINCE INSTALLED AFTER OVERHAUL.						1	G	7	2 	3U				H9SW    					 
1997081400659	19970814	00659	SW  	1997	8	14	97ZZZX3600       	1	19970612	G	6220	222031605109	FLEXURE         			BELL  	222   	222U        	1182140	SW  										M/R	DEBONDED        	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	219HM				LK0078	47573				INSPECTION PRIOR TO INSTALLATION REVEALED SHEAR PAD TO BE DEBONDED.  PART RECEIVED BAD FROM STOCK.						1	G	7	2 	3U				H9SW    					 
1997081400660	19970814	00660	EU  	1997	8	14	97ZZZX3601       	1	19970425	G	7712	117902131	VARTOM          			BOLKMS	BK117 	BK117C1     	5626025	EU  										RPM CONTROL	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FAILS TO REACH 108 PERCENT MODE.  TORQUE SPLITS AND HUNTING.						1	G	7	2 	3U			NC	H13EU   					 
1997081400661	19970814	00661	EU  	1997	8	14	97ZZZX3602       	1	19970424	G	7714	L211790	CONTROL BOX     			BOLKMS	BK117 	BK117C1     	5626025	EU  										N2 CONTROL	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				CONTROL BOX HAS INTERNAL WEAR FROM CABLE.  STIFF IN OPERATION.						1	G	7	2 	3U			NC	H13EU   					 
1997081400662	19970814	00662	EU  	1997	8	14	97ZZZX3603       	1	19970607	G	2822	1176415103	PUMP            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL BOOST	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				172109	7505				BOOST PUMP TRIPS CIRCUIT BREAKER.  WILL NOT ROTATE.						1	G	7	2 	3U			NC	H13EU   					 
1997081400663	19970814	00663	EU  	1997	8	14	97ZZZX3604       	1	19970611	G	2820	1176415503	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL DIST	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				RUBBER SWELLED ON SEAL.						1	G	7	2 	3U			NC	H13EU   					 
1997081400664	19970814	00664	EU  	1997	8	14	97ZZZX3605       	1	19970611	G	2822	1176415103	PUMP            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL BOOST	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				172111	7505				BOOST PUMP OPERATION INTERMITTENT, HARD TO TURN ON.  RUNS ROUGH.						1	G	7	2 	3U			NC	H13EU   					 
1997081400665	19970814	00665	NE  	1997	8	14	97ZZZX3606       	2	19970329	G	7261	0292105230	PUMP            			BOLKMS	BK117 	BK117C1     	5626025	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE OIL	LOW PRESSURE    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	109  			233SO	7505				DEFECTIVE OIL PUMP, LOW OIL.  PRESSURE AT FULL ENGINE RPM.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE				 
1997081400666	19970814	00666	EU  	1997	8	14	97ZZZX3607       	1	19970314	G	7714	L211790	CONTROL BOX     			BOLKMS	BK117 	BK117C1     	5626025	EU  										N2 CONTROL	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	05	317MC				39	7505				ROUGH RUNNING, N2 CONTROL.						1	G	7	2 	3U			NC	H13EU   					 
1997081400667	19970814	00667		1997	8	14	97ZZZX3608       	4	19970615	G	2210	060002600	GYRO            			BELL  	230   	230         	1182149	SW  										AUTOPILOT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				2677	23019				OSCILLATION FELT IN CYCLIC CONTROL WHEN AUTOPILOT ENGAGED.  REMOVED AND REPLACED AUTOPILOT GYRO.						1	G	7	2 	3U			NC	H9SW    					 
1997081400668	19970814	00668	SW  	1997	8	14	97ZZZX3609       	1	19970423	G	6330	222331618105	ISOLATION MOUNT 			BELL  	230   	230         	1182149	SW  										TRANSMMISSION	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	875  			1081	23019				BEARING WORN ON ISOLATION MOUNT.						1	G	7	2 	3U			NC	H9SW    					 
1997081400669	19970814	00669	SW  	1997	8	14	97ZZZX3610       	1	19970424	G	6220	222031613103	LIFT LINK       			BELL  	230   	230         	1182149	SW  										M/R	BEARING FAILED  	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	875  				23019				LIFT LINK LOWER BEARING SEPARATED FROM ELASTOMER.						1	G	7	2 	3U			NC	H9SW    					 
1997081400670	19970814	00670	SW  	1997	8	14	97ZZZX3611       	1	19970404	G	2436	222375060115	REGULATOR       			BELL  	230   	230         	1182149	SW  										DC SYSTEM	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	834  			93020	23019				GENERATOR LIGHT WOULD NOT GO OUT.  REGULATOR DEFECTIVE.						1	G	7	2 	3U			NC	H9SW    					 
1997081400671	19970814	00671	SW  	1997	8	14	97ZZZX3612       	1	19970404	G	6200	222012711107	BEARING         			BELL  	230   	230         	1182149	SW  										LIK ASSY	LOOSE           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	834  				23019				BEARING LOOSE IN COUNTERWEIGHT.						1	G	7	2 	3U			NC	H9SW    					 
1997081400672	19970814	00672		1997	8	14	97ZZZX3613       	4	19970603	G	2312	071121570	CONTROL HEAD    			BELL  	230   	230         	1182149	SW  										COCKPIT VHF	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				6951	23019				CONTROL HEAD MEMORY FOR STANDBY DOES NOT HOLD.						1	G	7	2 	3U			NC	H9SW    					 
1997081400673	19970814	00673		1997	8	14	97ZZZX3614       	4	19970514	G	3422	40205773	GYRO            			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT DG	DRIFTS          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	4493X	5    			80031622	S7038				DIRECTIONAL GYRO DRIFTS OFF HEADING.  FAILED AFTER ONLY 4.5 HOURS OPERATION.						1	G	7	2 	3U				H13EU   					 
1997081400674	19970814	00674	SW  	1997	8	14	97ZZZX3615       	1	19970506	G	5620		WINDOW          			BELL  	222   	222         	1182122	SW  										LT REAR	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	05	911LW					47520				LEFT REAR WINDOW SHATTERED INSIDE THE AIRCRAFT IN-FLIGHT.						1	G	7	2 	3U				H9SW    					 
1997081400675	19970814	00675	SW  	1997	8	14	97ZZZX3616       	1	19970110	G	6510	222044625105	DRIVE SHAFT     			BELL  	222   	222         	1182122	SW  										T/R	OUT OF LIMITS   	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	911MK				A776	47515				TAIL ROTOR DRIVE AFTER INSTALLATION, PART WAS DETERMINED TO BE DEFECTIVE FROM FACTORY.  END PLATE OUT OF LIMITS PER BHT 	222 OMM.					1	G	7	2 	3U				H9SW    					 
1997081400676	19970814	00676		1997	8	14	97ZZZX3617       	4	19970401	G	2211	7004206901	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										CSAS	MALFUNCTION     	B			TI1R	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	05	911MZ				90100300	7098				PITCH AND ROLL CSAS CAUTION LIGHT ILLUMINATED INTERMITTENTLY.						1	G	7	2 	3U				H13EU   					 
1997082100059	19970821	00059	SW  	1997	8	21	97ZZZX3619       	1	19970616	G	2510	222020656107	PAD             			BELL  	230   	230         	1182149	SW  										PILOT SEAT	TORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				PROTECTIVE PAD TORN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997082100060	19970821	00060	SW  	1997	8	21	97ZZZX3620       	1	19970226	G	7700	22206084101	SWITCH          			BELL  	230   	230         	1182149	SW  										ENGINE PRESSURE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	763  			0644	23019				SWITCH INOPERABLE.						1	G	7	2 	3U			NC	H9SW    					 
1997082100061	19970821	00061	EU  	1997	8	21	97ZZZX3621       	1	19970529	G	7120	11760101111	SUPPORT         			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE MOUNT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				LOWER MOUNT POINTS WORN AND WORMING OUT.						1	G	7	2 	3U			NC	H13EU   					 
1997082100062	19970821	00062	EU  	1997	8	21	97ZZZX3622       	1	19970513	G	7712	117940691	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										DUAL TORQUE	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					253					DUAL TORQUE INDICATOR RECEIVED BAD FROM STOCK. ON INSTALLING, INDICATOR WOULD NOT CALIBRATE (SLOPE NR 1).  NEEDLE 1 STUC	K AT 20 PERCENT, WITH POWER OFF, IT GOES TO ZERO.					1	G	7	2 	3U			NC	H13EU   					 
1997082100063	19970821	00063	EU  	1997	8	21	97ZZZX3623       	1	19970424	G	7714	L21176209	CABLE CASE      			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE N1 CONT	BINDING         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	2002 				7505				CABLE CASING ROUGH IN OPERATION.  CABLE BINDS.						1	G	7	2 	3U			NC	H13EU   					 
1997082100064	19970821	00064		1997	8	21	97ZZZX3624       	4	19970507	G	3421	222375033101	INDICATOR       			BELL  	222   	222U        	1182140	SW  										COCKPIT ATTITUDE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM				0158	47573				ATTITUDE INDICATOR, FLAG WILL NOT STAY PULLED.						1	G	7	2 	3U				H9SW    					 
1997082100065	19970821	00065		1997	8	21	97ZZZX3625       	4	19970404	G	3421	222375033101	INDICATOR       			BELL  	222   	222U        	1182140	SW  										COCKPIT ATTITUDE	FAILED          	B			TI1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	05	219HM	41   			0025	47573				PILOT SMELLED BURNING ODOR.  OFF FLAG PULLED.  ATTITUDE INDICATOR FAILED AFTER ONLY 40.9 HOURS INSTALLED.						1	G	7	2 	3U				H9SW    					 
1997082100066	19970821	00066	NE  	1997	8	21	97ZZZX3626       	2	19970620	G	8530		VALVE           			DOUG  	DC3   	DC3         	3021401	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 1 CYLINDER	FAILED          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	17	941AT		693  			4293040	431414			NR 1 CYLINDER VALVE HEAD CAME OFF AND SPLIT CYLINDER HEAD.  ALSO, DAMAGED PISTON.						2	L	7	2 	4R	4	R		A669    	5E4				 
1997082100067	19970821	00067	EA  	1997	8	21	97ZZZX3627       	1	19970802	G	2612	24403057	FIRE LOOP       			CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT ENGINE	SEPARATED       	E				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			WP	09	757MC	876  				5177				RIGHT ENGINE FIRE LIGHT ILLUMINATED DURING CLIMB-OUT.  EXTINGUISHED WITH THROTTLE RETARD, FOUND CORE FIRE LOOP BAD.  WIL	L REPLACE WITH NEW LOOP.					2	L	7	2 	4F			RT	A21EA   					 
1997082100068	19970821	00068	WP  	1997	8	21	97ZZZX3628       	2	19970720	G	7200		ENGINE          			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE73123B   		WP  					RIGHT ENGINE	FLAME OUT       	E		A		A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CL	CLIMB          	1			WP	09	108FX	1296 				104	P99319			RIGHT ENGINE ROLLED BACK AND FLAMED OUT CLIMBING FROM 44,000 FEET TO 45,000 FEET.  NO INDICATION OF PROBLEM UNTIL AIRCRA	FT YAWED.  CONDITIONS SPEED - .74 TO .75 MACH.  OAT = -61C.  POWER = MAX COUNTS.  AIRCRAFT DESCENDED TO 25,000 FEET, UNA	BLE TO WINDMILL START.  STARTER ENGAGED AND START SUCCESSFUL WITHIN PARAMETERS.  OTHER CONDITIONS, AIRCRAFT ON AUTOPILOT	 AND CREW HAD NOT TOUCHED THE THROTTLE.  GRAVITY FLOW OPEN, STANDBY PUMPS OFF.  AIRCRAFT DIVERTED.  ENGINE CYCLES, 957.			2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
1997082100069	19970821	00069	EA  	1997	8	21	97ZZZX3629       	2	19970722	G	7322		FLOAT           	FACET       	105199      	PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	COLLAPSED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2452T	1415 			CR01775	3878A0807	L1827815			AIRCRAFT CAME IN FOR ENGINE WORK.  REMOVED CARBURETOR, RE-INSTALLED CARBURETOR.  ATTACHED FUEL LINES.  TURNED ON FUEL. F	UEL BOWL NEEDLE JET FAILED TO STOP FUEL.  REMOVED CARBURETOR, REMOVED BOWL, FOUND FLOAT COLLAPSED ON BOTH SIDES.  NO EXP	LANATION FOR CAUSE.				1	L	7	1 	3O	3	O		A18SO   	E223				 
1997082100070	19970821	00070	SO  	1997	8	21	97ZZZX3630       	1	19970727	G	5751	35640010	RIB             			PIPER 	PA28  	PA28RT201   	7102818	SO  										AILERON CENTER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	8098R	4672 				28R8018003				WHILE REPLACING THE SKIN ON THE OUTBOARD SIDE OF THE LEFT AILERON, THE CENTER RIB WAS FOUND CRACKED IN THE FORWARD ATTAC	H FLANGE.  THIS AREA IS RIGHT BEHIND THE ACTUATING PUSH ROD.  BOLTS WERE TIGHT.  TOTALLY INACCESSIBLE TO VIEW.					1	L	7	1 	3O				2A13    					 
1997082100071	19970821	00071	EU  	1997	8	21	97ZZZX3631       	1	19970724	G	2910		LINE            			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										HYDRAULIC PUMP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	25SW	2061 				360				POOR PUMP MOUNTING BY OEM GIVES INSUFFICIENT VIBRATION ATTENUATION.  ALUMINUM HYDRAULIC LINES ON PUMP FITTINGS CRACKED A	T FLARES.  SUBMITTER STATED SHOULD USE FLEXIBLE LINES.					1	L	7	1 	3O			RT	A51EU   					 
1997082100072	19970821	00072	CE  	1997	8	21	97ZZZX3632       	1	19970716	G	3250	12606321	SPACER          		1260664411  	CESSNA	206   	U206F       	2073333	CE  										NLG STEERING	FAILED          	D	S	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	05	1523U	6804 				U20602234				PILOT REPORTED SQUEALING IN NOSE ON LANDING ROLL OUT, JUST BEFORE NOSE GEAR COLLAPSED DAMAGING PROPELLER AND NOSE OF AIR	CRAFT.  INVESTIGATION FOUND SPACER IN NOSE GEAR STEERING BUNGEE CRACKED OFF WHICH WOULD HAVE ALLOWED THE NOSE GEAR TO FR	EE SWIVEL WITH NO CONTROL.				1	H	7	1 	3O				A4CE    					 
1997082100538	19970821	00538	EU  	1997	8	21	97ZZZX3659       	1	19970626	G	6730	7004305901	ACTUATOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										CSAS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	8    			91080342	7509				CSAS ACTUATOR REMOVED DUE TO LACK OF TRAVEL.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997082100539	19970821	00539		1997	8	21	97ZZZX3660       	4	19970627	G	2312	064105430	TRANSCEIVER     		KY196A      	BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT VHF	FAILED          	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	117NC				22666	7509				TRANSCEIVER OUT OF BOX FAILURE.  NEW PART DEFECTIVE ON RECEIPT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997082100540	19970821	00540		1997	8	21	97ZZZX3661       	4	19970612	G	3421	4021541671	GYRO            			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT HORIZ	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	8    			92082228	7509				HORIZONTAL GYRO WILL NOT FULLY ALIGN.  (REF:   RMA NR R011312).  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997082100541	19970821	00541	EU  	1997	8	21	97ZZZX3662       	1	19970628	G	6320	IPT20RT1100080G	PRESS TRANSDUCER			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R GEARBOX	FAILED          	B			TI1R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	05	117NC				38555196	7509				TRANSDUCER DROPPED FROM 2.5 TO 1.0 BARS IN-FLIGHT.  REF:  RMA NR R011617.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997082100542	19970821	00542	EU  	1997	8	21	97ZZZX3663       	1	19970628	G	2422	PC250	STATIC INVERTER 			BOLKMS	BK117 	BK117C1     	5626025	EU  										AC SYSTEM	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117NC				5370	7509				INVERTER CAUSES INTERMITTENT FAILURES IN SYSTEMS IT PROVIDES BUSS FOR.  REMOVED AND REPLACED						1	G	7	2 	3U			NC	H13EU   					 
1997082100543	19970821	00543	GL  	1997	8	21	97ZZZX3664       	2	19970617	G	7322	23059933	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 1 ENGINE	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	206AZ	77   			BR55429	51007				DELAYED STARTS, FAST TOT RISE, NO MODULATE OR RE-LIGHT.  REMOVED AND REPLACED FCU.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997082100546	19970821	00546	SW  	1997	8	21	97ZZZX3666       	1	19970506	G	3340	4501283	LIGHT           			BELL  	222   	222U        	1182140	SW  										SEARCH	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	222HX				63487	47533				WILL NOT EXTEND OR ROTATE.  WAS REPAIRED FOR SAME DISCREPANCY ON LAST REPAIR AND WOULD NOT WORK WHEN ISSUED FROM STOCK.						1	G	7	2 	3U				H9SW    					 
1997082100584	19970821	00584	CE  	1997	8	21	97ZZZX3667       	1	19970808	G	7120	265102215	MOUNT RING      			CESSNA	208   	208         	2073702	CE  										ENGINE	CRACKED         	B	P		H7NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17					225					ENGINE MOUNT RING REPAIRED PER CESSNA MM CHAPTER 71-21-00, PAGE 801, APRIL, 1996.  ROUGHLY 100 HOURS AFTER INSTALLING DO	UBLER PER MANUAL SPECIFICATIONS, THE OPPOSITE SIDE AT THE MOUNT CRACKED IN THE WELD.					1	H	7	1 	3T			NT	A37CE   					 
1997082100585	19970821	00585	CE  	1997	8	21	97ZZZX3668       	1	19970808	G	7120	265102215	MOUNT RING      			CESSNA	208   	208         	2073702	CE  										ENGINE	CRACKED         	B			H7NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17					274					ENGINE MOUNT RING REPAIRED PER CESSNA MM, CHAPER 71-20-00, PAGE 801, APRIL, 1996.  ROUGHLY 100 TO 200 HOURS AFTER REPAIR	.  (TIME IS UNSURE.)  CRACK APPEARED ON THE OPPOSITE SIDE OF THE MOUNT RING FROM WHERE THE DOUBLER WAS INSTALLED.					1	H	7	1 	3T			NT	A37CE   					 
1997082100586	19970821	00586		1997	8	21	97ZZZX3669       	4	19970807	G	2561	P0723E105P	LIFE VEST       	EAAEROMARINE																CELL VALVE	FAIL TEST       	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					36607					FAILED THE MANUFACTURER'S RECOMMENDED 2 PSI CELL TEST.																			 
1997082100587	19970821	00587		1997	8	21	97ZZZX3670       	1	19970728	G	2821	07560052	STRAINER        	CESSNA      																FUEL SYSTEM	MISMANUFACTURED 	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13										TWO NEW PARTS RECEIVED FROM CESSNA.  INLET STANDPIPE NOT FULLY INSERTED BEFORE CRIMP ALLOWING STANDPIPE TO FALL OUT.  FU	EL WOULD BYPASS STAINER SCREEN.  DEFECT FOUND BY MECHANIC BEFORE INSTALLATION.																		 
1997082100588	19970821	00588	SO  	1997	8	21	97ZZZX3671       	2	19970731	G	8520	652541	NUT             			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  					CYL HOLD DOWN	BROKEN          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	4804	1800 				18268321				NUT WAS BROKEN THROUGH COMPLETELY.  ALL TORQUE WAS RELEASED.  THIS NUT WAS INSTALLED AT ENGINE OVERHAUL IAW CONT SB M92-	9.					1	L	7	1 	3O	3	O	NT	3A13    	E273				 
1997082100589	19970821	00589	SO  	1997	8	21	97ZZZX3672       	1	19970701	G	3211	1742000	FITTING SUPPORT 			PIPER 	PA23  	PA23250     	7102308	SO  										GEAR WELL RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	14005					274623				FITTING SUPPORT CRACKS WERE DISCOVERED AT 85 HOURS AFTER ANNUAL (SIX MONTHS AGO).  ALL BOLTS WERE LOOSE AND HOLES WERE E	GG-SHAPED.  CRACKS WERE FOUND AT BOTTOM AFT DRAG LINK SUPPORT.  ALL BOLTS WRE LOOSE IN TRUNNION SUPPORT PADS, AS WELL. A	LSO, THE AFT REINFORCEMENT CHANNEL BOLTS WERE LOOSE, BOTH SIDES.  SUBMITTER STATED IF BOLTS ARE FOUND LOOSE, A CLOSE INS	PECTION SHOULD BE MADE OF THE AFT SUPPORT MOUNTS.			1	L	7	2 	3O				1A10    					 
1997082100590	19970821	00590	SO  	1997	8	21	97ZZZX3673       	1	19970701	G	3211	1742001	FITTING SUPPORT 			PIPER 	PA23  	PA23250     	7102308	SO  										GEAR WELL RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	14005					274623				FITTING SUPPORT CRACKS WERE DISCOVERED AT 85 HOURS AFTER ANNUAL (SIX MONTHS AGO).  ALL BOLTS WERE LOOSE AND HOLES WERE E	GG-SHAPED.  CRACKS WERE FOUND AT BOTTOM AFT DRAG LINK SUPPORT.  ALL BOLTS WRE LOOSE IN TRUNNION SUPPORT PADS, AS WELL. A	LSO, THE AFT REINFORCEMENT CHANNEL BOLTS WERE LOOSE, BOTH SIDES.  SUBMITTER STATED IF BOLTS ARE FOUND LOOSE, A CLOSE INS	PECTION SHOULD BE MADE OF THE AFT SUPPORT MOUNTS.			1	L	7	2 	3O				1A10    					 
1997082100591	19970821	00591	SO  	1997	8	21	97ZZZX3674       	1	19970701	G	3211	1742002	FITTING SUPPORT 			PIPER 	PA23  	PA23250     	7102308	SO  										GEAR WELL LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	14005					274623				FITTING SUPPORT CRACKS WERE DISCOVERED AT 85 HOURS AFTER ANNUAL (SIX MONTHS AGO).  ALL BOLTS WERE LOOSE AND HOLES WERE E	GG-SHAPED.  CRACKS WERE FOUND AT BOTTOM AFT DRAG LINK SUPPORT.  ALL BOLTS WRE LOOSE IN TRUNNION SUPPORT PADS, AS WELL. A	LSO, THE AFT REINFORCEMENT CHANNEL BOLTS WERE LOOSE, BOTH SIDES.  SUBMITTER STATED IF BOLTS ARE FOUND LOOSE, A CLOSE INS	PECTION SHOULD BE MADE OF THE AFT SUPPORT MOUNTS.			1	L	7	2 	3O				1A10    					 
1997082100592	19970821	00592	SO  	1997	8	21	97ZZZX3675       	1	19970701	G	3211	1742003	FITTING SUPPORT 			PIPER 	PA23  	PA23250     	7102308	SO  										GEAR WELL LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	14005					274623				FITTING SUPPORT CRACKS WERE DISCOVERED AT 85 HOURS AFTER ANNUAL (SIX MONTHS AGO).  ALL BOLTS WERE LOOSE AND HOLES WERE E	GG-SHAPED.  CRACKS WERE FOUND AT BOTTOM AFT DRAG LINK SUPPORT.  ALL BOLTS WRE LOOSE IN TRUNNION SUPPORT PADS, AS WELL. A	LSO, THE AFT REINFORCEMENT CHANNEL BOLTS WERE LOOSE, BOTH SIDES.  SUBMITTER STATED IF BOLTS ARE FOUND LOOSE, A CLOSE INS	PECTION SHOULD BE MADE OF THE AFT SUPPORT MOUNTS.			1	L	7	2 	3O				1A10    					 
1997082100593	19970821	00593	CE  	1997	8	21	97ZZZX3676       	1	19970723	G	7120	9691001061	MOUNT           			BEECH 	58    	58          	1152740	CE  										RT ENGINE	CRACKED         	B			HE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	1814W	2907 	1010 			TH267				RIGHT ENGINE MOUNT CRACKED AT THE TOP OUTBOARD ISOLATOR ATTACH WELD JOINT.  THIS ENGINE HAD THE MODIFIED BRACKETS INSTAL	LED PREVIOUSLY WHICH RELIEVES THE AD INSPECTION.					1	L	7	2 	3O				3A16    					 
1997082100595	19970821	00595	CE  	1997	8	21	97ZZZX3678       	1	19970611	G	7603		ROD END         			CESSNA	170   	170B        	2072306	CE  										THROTTLE	WRONG BOLTS     	B			V2AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	2814C					26357				AIRCRAFT WAS IN MAINTENANCE FOR CARBURETOR HEAT PROBLEM AND MECHANIC NOTED THAT AD 86-24-07 WAS NOT C/W.  AIRCRAFT HAS B	EEN MODIFIED WITH INSTALLATION OF 180 HP LYCOMING ENGINE IAW STC SA421CE AND SA749CE.  AD 86-24-07 DOES NOT LIST 170B AS	 APPLICABLE.  SE 79-6 DOES NOT CALL OUT SPECIFIC MODELS, BUT DOES REQUIRE DRILLED BOLTS ON ALL BALL BEARING TYPE CONTROL	S.			1	H	7	1 	3O				A799    					 
1997082100596	19970821	00596	CE  	1997	8	21	97ZZZX3679       	1	19970801	G	5712	57222061	CANTED RIB      			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	B		A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	40KM	4450 				4410053				DURING A PHASE INSPECTION, FOUND BOTH RT AND LT CANTED RIBS TOP CAPS TO BE CRACKED.  CRACKS START AT AFT SIDE OF FORWARD	 WING SPAR AND RUN AFT, PARALLEL TO THE BEND RADIUS.  STOP DRILLED BOTH ENDS OF EACH CRACK PER CESSNA ENGINEERING INSTRU	CTIONS.				1	L	7	2 	3T			RT	A28CE   					 
1997082100597	19970821	00597	CE  	1997	8	21	97ZZZX3680       	1	19970801	G	5712	57222062	CANTED RIB      			CESSNA	441   	441         	2076020	CE  										LT WING	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	40KM	4450 				4410053				DURING A PHASE INSPECTION, FOUND BOTH RT AND LT CANTED RIBS TOP CAPS TO BE CRACKED.  CRACKS START AT AFT SIDE OF FORWARD	 WING SPAR AND RUN AFT, PARALLEL TO THE BEND RADIUS.  STOP DRILLED BOTH ENDS OF EACH CRACK PER CESSNA ENGINEERING INSTRU	CTIONS.				1	L	7	2 	3T			RT	A28CE   					 
1997082100599	19970821	00599	GL  	1997	8	21	97ZZZX3682       	3	19970716	G	6114		HUB             			CESSNA	185   	A185F       	2072821	CE  						HARTZL	HCC3Y	PHCC3YF1    	GL  	AFT SIDE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	61092	912  				18504107		EE2084A		PROPELLER WAS REMOVED TO REPAIR OIL LEAK.  A SIX INCH CRACK WAS FOUND ON THE AFT SIDE OF THE HUB.						1	H	7	1 	3O				3A24    		5	C	P25EA	 
1997082100600	19970821	00600	EA  	1997	8	21	97ZZZX3683       	2	19970707	G	7421	REM37BY	SPARK PLUG      	CHAMPION    		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FOULED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			WP	09	68452	200  				15282300	L2048215			PILOT REPORTED INTERMITTENT ROUGH ENGINE OPERATION EN ROUTE.  PILOT HAD FAILED TO LEAN THE ENGINE, CONSEQUENTLY, FOULING	 ALL 4 LOWER PLUGS.  AN OFF-AIRPORT LANDING WAS MADE.  NO DAMAGE TO AIRCRAFT.  REPLACED LOWER PLUGS AND FLEW AIRCAFT BAC	K TO AIRPORT WITHOUT INCIDENT.  NO OTHER FAULTS FOUND.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997082100601	19970821	00601	CE  	1997	8	21	97ZZZX3684       	1	19970729	G	7160	86245834	AIR BOX         			CESSNA	180   	180         	2072602	CE  										NR 4 CYL RISER	FAILS           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16										THE OPERATOR HAS A FLEET, SIX, OF THESE AIRCRAFT.  A PROBLEM HAD DEVELOPED CONCERNING THE CARBURETOR HEAT AIRBOX.  THE C	OVER IS ATTACHED WITH A PAIR OF SCREWS ON ONE SIDE AND A TONGUE AND SLOT ARRANGEMENT ON THE OTHER.  THE SLOTS WEAR OUT A	T AN ALARMING RATE CAUSING THAT PART OF THE BOX ASSY TO DEPART THE AIRCRAFT.  IN A SHORT TIME, THE CLAMPS HOLDING THE AI	RBOX BREAK AND AIR BOX FALLS TO BOTTOM OF COWL.  NEW PART BREAKS IN ABOUT 100 HOURS OR LESS.			1	H	7	1 	3O			NC	5A6     					 
1997082100602	19970821	00602	CE  	1997	8	21	97ZZZX3685       	1	19970731	G	5720	4520031	BATHTUB FITTING 			BEECH 	18    	H18         	1151012	CE  										SPAR STRAP	BROKEN          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW	3497 				BA716				WHILE JACKING UP AIRCRAFT DURING ANNUAL INSPECTION, A 'POPPING' NOISE WAS HEARD COMING FROM CENTER SECTION.  INSPECTION 	REVEALED RIGHT CENTER SPAR STRAP BATHTUB FITTING HAD ITS UPPER FORWARD EAR BROKEN OFF.  THIS STRAP HAD BEEN INSTALLED UN	DER HAMILTON STC NR SA2000WE ON 6-23-71.  MAINTENANCE RECORDS DO NOT REFLECT ANY MAINTENANCE ON STRAP SINCE INSTALL.  HA	MILTON DOES NOT PROVIDE ANY MAINTENANCE GUIDANCE.  SUBMITTER RECOMMENDS DYE-PENETRANT INSPECTION AT 500-HOUR INTERVALS.			1	L	7	2 	3R				A765    					 
1997082100606	19970821	00606	SO  	1997	8	21	97ZZZX3689       	1	19970728	G	7810		EXHAUST STACK   			PIPER 	J3    	J3C65       	7100510	SO  										RIGHT SIDE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	27	27145					4393				EXHAUST STACK CRACKED AT NR 1 CYLINDER.  CRACK WELDED WITH STAINLESS STEEL.						1	H	7	1 	3O				A691    					 
1997082100607	19970821	00607	SO  	1997	8	21	97ZZZX3690       	1	19970701	G	8120	4091701	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					SEAL	OIL LEAK        	D				K				NONE                    				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		IN	INSP/MAINT     	1			EA	01	30SC					318152098	RL22668A			OIL AND SMOKE NOTICED FROM EXHAUST.  FOUND OIL SEAL IN TURBO LEAKING.  REPLACED TURBO.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997082100608	19970821	00608	EA  	1997	8	21	97ZZZX3691       	2	19970703	G	7310		HOSE            			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					PUMP/FIREWALL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	33831					327500032				FUEL HOSE AT LEFT SIDE OF FIREWALL TO ENGINE DRIVEN FUEL PUMP DEVELOPS LOSS OF FUEL PRESSURE ON TAKEOFF.  HOSE SUCKS IN 	AIR WHICH DOES NOT LET FUEL FLOW.  SUBMITTER RECOMMENDS THESE FUEL HOSES BE PRESSURE CHECKED AT EVERY ANNUAL OR WHEN THI	S TYPE OF PROBLEM OCCURS.				1	L	7	1 	3O	3	O		A3SO    	E295				 
1997082100609	19970821	00609	SO  	1997	8	21	97ZZZX3692       	2	19970716	G	8500		ENGINE          			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RIGHT ENGINE	RPM LOSS        	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	414GB	1468 				414A0457	276791R			PILOT REPORTED RIGHT ENGINE FLUCTUATED IN-FLIGHT.  WHEN PROPELLER LEVER WAS MOVED, RPM DECREASED.  TROUBLESHOT SYSTEM. A	DJUSTED IDLE MIXTURE AND SPEED.  ADJUSTED FOR 30 RPM RISE AND 600 RPM IDLE PER MM.  GROUND CHECK OK.  UPON FURTHER INVES	TIGATION, FOUND LOW FUEL PRESSURE PUMPS IN OFF POSITION.  THIS MODEL REQUIRES PUMPS TO BE ON DURING FLIGHT.  TEST FLEW A	IRCRAFT FOR 2 HOURS WITH NO PROBLEMS.  AIRCRAFT RETURNED BACK TO SERVICE.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997082100610	19970821	00610	SO  	1997	8	21	97ZZZX3693       	2	19970721	G	8550		OIL TUBE        			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					CRANKSHAFT	DISLODGED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	5203A					21063306	511938			DISCOVERED AT MAJOR OVERHAUL.  NEW VAR CRANKSHAFT INSTALLED 1985, ACCUMULATED 1,550 HOURS.  FOUND NR 3 OIL TUBE (INSIDE 	SHAFT) HAD DISLODGED AND WORKED ITS WAY OUT AND HAD PRACTICALLY CUT THE BEARING IN HALF.  SUBMITTER BELIEVES THE VAR CRA	NKSHAFT HAS AS MANY OR MORE PROBLEMS IN THE FIELD AS ITS OLDER PREDECESSOR.  MANUFACTURING FLAW.  NEED BETTER QUALITY CO	NTROL.			1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997082100611	19970821	00611	SO  	1997	8	21	97ZZZX3694       	2	19970626	G	8530	646612	VALVE           		641917A12   	CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300D       	17022	SO  					NR 4 CYLINDER	FAILED          	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			NM	11	6844X	108  				47744				VALVE FAILED, CAUSED LOW POWER, AIRCRAFT HAD A FORCED LANDING.  VALVE PARTS AND SEAT SENT TO NTSB.						1	H	7	1 	3O	3	O		3A12    	E253				 
1997082100612	19970821	00612	EA  	1997	8	21	97ZZZX3695       	2	19970520	G	8530		VALVE           			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENG NR 4 EXHAUST	STUCK           	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			GL	03	6950V		1147 			221323	L164151A			ENGINE RAN ROUGH AT TAKEOFF, AIRCRAFT LOST POWER.  AIRCRAFT SUSTAINED SUBSTANTIAL DAMAGE DURING A FORCED LANDING.  EXAMI	NATION FOR THE ENGINE REVEALED AN OPEN EXHAUST VALVE, CYLINDER NR 4.  ENGINE HAD A CYLINDER, NR 4 EXHAUST VALVE STUCK.					1	L	7	1 	3O	3	O		2A3     	1E10				 
1997082100614	19970821	00614	SO  	1997	8	21	97ZZZX3697       	2	19970720	G	8530		CYLINDER        			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  					NR 2 CYLINDER	CRACKED         	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	13	8303S	4344 	1100 			18256403	1314455R4			CYLINDER CRACKED FROM TOP SPARK PLUG HOLE TO BOTTOM SPARK PLUG HOLE AROUND THE EXHAUST VALVE.  HEAD OPENED UP BY THE EXH	AUST VALVE AND BLEW OUT THE SIDE AND BURNED FINS OFF THE CYLINDER.  ENGINE SKIPPED AND RAN ON THE OTHER 5 CYLINDERS.  CY	LINDER BURNED PRETTY BAD BY THE TIME ACFT LANDED.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997082100615	19970821	00615	GL  	1997	8	21	97ZZZX3698       	3	19970722	G	6114	D42145	HUB             			BEECH 	76    	76          	1153005	CE  						HARTZL	HCM2Y	HCM2YR      	GL  	BLADE SOCKET	CRACKED         	B			PC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	803FC		706  		FB979	ME150		FB979		PROPELLER WAS DISASSEMBLED TO CHECK FOR GREASE LEAK.  HUB EDDY CURRENT INSPECTED PER INSTRUCTIONS SB 164, AND DEFECT NOT	ED IN ONE BLADE SOCKET.  PHOTOS TAKEN OF HUB AND EDDY CURRENT TEST OF HUB.  HUB RED TAG (REJECT) ALL OTHER PARTS GREEN (	SERVICEABLE).  HARTZELL SB NR 164 WARNS, 'UNEXPLAINED VIBRATION OR GREASE LEAKAGE INCIDENTS DEMAND IMMEDIATE INSPECTION 	FOR CRACKED HUB'.			1	L	7	2 	3O				A29CE   		5	C	P43GL	 
1997082100616	19970821	00616	CE  	1997	8	21	97ZZZX3699       	1	19970725	G	7810	NH100089750	CLAMP           		99103001    	CESSNA	421   	421C        	2076016	CE  										EXHAUST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	88604					421C0604				OVERBOARD EXHAUST PIPE CLAMP HAD 2 INCH CRACK AROUND CLAMP.  REMOVED CLAMP AND INSTALLED NEW ONE.						1	L	7	2 	3O				A7CE    					 
1997082100617	19970821	00617		1997	8	21	97ZZZX3700       	4	19970701	G	6113	D3830	BULKHEAD        			BEECH 	55    	D55         	1152730	CE  										SPINNER	CRACKED         	B			UW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	8491N					TE607				THIS SPINNER BULKHEAD WAS A NEW PART THAT HAD ONLY 57 HOURS WHEN IT CRACKED.  THE CRACK WAS LOCATED IN THE FRONT PLATE U	NDER THE SCREW HEADS THAT HOLD THE PLATES THAT MOUNT THE BULKHEAD TO THE CRANKSHAFT.  THE SPINNER WAS INSTALLED WITH THE	 PROPER AMOUNT OF SHIMS IN THE FRONT BULKHEAD.				1	L	7	2 	3O				3A16    					 
1997082100618	19970821	00618	EA  	1997	8	21	97ZZZX3701       	2	19970725	G	7314	RG17980D	PUMP            	ROMEC       		PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE FUEL	LEAK            	I				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	13	8969N		607  			3240769				ON 100-HOUR INSPECTION, FUEL PUMP WAS FOUND LEAKING AT RELIEF VALVE.  SUBMITTER STATED HAVE HAD APPROXIMATELY 6 PUMPS IN	 THE LAST YEAR WITH THIS PROBLEM WITH MOST HAVING LESS THAN 1,000 HOURS TSO.					1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997082100619	19970821	00619	NE  	1997	8	21	97ZZZX3702       	2	19970804	G	8530	399353	CYLINDER        			BEECH 	18    	H18         	1151012	CE  	PWA   	R985  	R985AN14B   	52008	NE  					BARREL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	954		181  			BA670	24865			WHILE C/W AD 78-08-07 (CYLINDER CRACKS), FOUND CYLINDER WALL HAS EXHAUST RESIDUE AFTER 181 HOURS IN SERVICE.  35 HOURS S	INCE LAST VISUAL INSPECTION 12 MONTHS PREVIOUSLY.  CYLINDER HAD ULTRA SONIC INSPECTION IN 1993.					1	L	7	2 	3R	3	R		A765    	5E1				 
1997082100620	19970821	00620	EA  	1997	8	21	97ZZZX3703       	2	19970714	G	8530	75874	CYLINDER        			PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  					EXHAUST PORT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4620J		1380 			28R30503	L469151A			DURING ANNUAL INSPECTION, THREE OF THE CYLINDERS WERE FOUND CRACKED IN THE EXHAUST PORTS.  RESEARCH OF LOG BOOKS INDICAT	E CYLINDERS WERE OVERHAULED BY CHROME PLATE IN 1979.					1	L	7	1 	3O	3	O		2A13    	1E10				 
1997082100622	19970821	00622	SO  	1997	8	21	97ZZZX3705       	1	19970701	G	2434	680500	ALTERNATOR      			PIPER 	PA28  	PA28181     	7102807	SO  										FORWARD PIVOT	BROKEN EAR      	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9277N					2843051				DURING ANNUAL INSPECTION, FOUND FORWARD ALTERNATOR HOUSING BROKEN AT PIVOT BOLT EAR. INSPECTED INSTALLATION AND DETERMIN	ED BELT TENSION TOO TIGHT.  LYCOMING SI 1129A PERTAINS TO THIS SUBJECT.  PROPER BELT TENSION IS PARTICULARLY CRITICAL ON	 LYCOMING ENGINES.				1	L	7	1 	3O				2A13    					 
1997082100623	19970821	00623		1997	8	21	97ZZZX3706       	1	19970731	G	2140	488636	HEAT EXCHANGER  	STWARNER    	940DB12     															COMB HEATER	PLATE FAILED    	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09					1332					HEAT EXCHANGER ENDPLATE CORROSION CAUSED THE END PLATE TO BURN OUT.  SUBMITTER STATED EXCESSIVE TIME AND LACK OF ATTENTI	ON TO AD'S ALLOWED THIS CONDITION TO EXIST.  RECOMMEND AD ON AIRCRAFT 940 SERIES HEATERS INSTALLED IN PIPER PA-23'S, PA-	30'S AND CESSNA 310, 310B, 310C, 310D, AND LAKE AMPHIBS.  A SLIGHT BUMP WAS ALL IT TOOK TO DISPLACE THE ENDPLATE ON THE 	HEAT EXHANGER.  THERE IS CURRENTLY AN AD ON 940'S INSTALLED IN PIPER AIRCRAFT, BUT NOT ON CESSNA AIRCRAFT.																 
1997082800001	19970828	00001	CE  	1997	8	28	97ZZZX3708       	1	19970601	G	5523		TRIM TAB        			CESSNA	206   	U206        	2073306	CE  										ELEVATOR	CORE SOAKED     	H	L	A		O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			EU	01	2FOR					U20601076				PARACHUTING FLIGHT - FL 100, AFTER JUMP IN DESCENT SPEED 100 MPH ELEVATOR FLUTTER, FAST AND HEAVY MOVEMENTS 2-3 SECONDS,	 DISAPPEARED WHEN SPEED 80 MPH.  TRIM ACTUATOR WAS LOOSE FROM BROKEN STABILIZER BRACKET, FREE MOVEMENT 2 INCHES.  NEARBY	 RIB WAS ALSO BROKEN.  FREE PLAY OF ACTUATOR ITSELF WAS IN ORDER.  TRIM TAB URETHANE CORE WAS WET, WHEN WEIGHED, THE TAB	 WAS TWICE AS HEAVY COMPARED WITH NEW SPARE.  ALSO, THE ELEVATOR TRAILING EDGE URETHANE CORE WAS WET AND ELEVATOR FAR OU	T OF MASS COMPENSATION VALUES BECAUSE OF WATER IN URETHANE.  TOT:  4,983 HOURS.		1	H	7	1 	3O				A4CE    					 
1997082800002	19970828	00002	CE  	1997	8	28	97ZZZX3709       	1	19970601	G	5523		TRIM TAB        			CESSNA	206   	U206        	2073306	CE  										ELEVATOR	OUT OF BALANCE  	H		A		O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			EU	01	2FOR					U20601076				PARACHUTING FLIGHT -  AFTER JUMP TRIMMED NOSE DOWN, IN DESCENT 150 MPH, ELEVATOR VIBRATION WHICH DISAPPEARED WHEN SPEED 	130 MPH.  TRIM TAB UNDERSIDE SKIN WAS DEFORMED UNDER BRACKET ASSEMBLY AND TRIM ACTUATOR WAS LOOSE FROM FASTENERS.  ELEVA	TOR MASS BALANCE WAS FAR OUT OF LIMITS.  ELEVATOR TRAILING EDGE AND TRIM TAB URETHANE CORE WERE WET WHICH WAS THE REASON	 FOR OUT OF BALANCE.  SEVERAL OTHER CASES OF TRIM TABS AND TRAILING EDGES HEAVILY CORRODED BECAUSE OF WATER IN URETHANE.	  TOT:  2,800 HOURS.		1	H	7	1 	3O				A4CE    					 
1997082800003	19970828	00003	CE  	1997	8	28	97ZZZX3710       	1	19970728	G	6120	2995060105	CONTROL CABLE   			CESSNA	177   	177         	2073704	CE  										PROPELLER GOV	MISCONNECTED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	29531					17700945				WHILE RELOCATING THIS AIRCRAFT FOLLOWING AN ANNUAL INSPECTION, THE AIRCRAFT WAS TAXIED TO THE RUN-UP AREA FOR A RUN-UP. 	 PILOT NOTICED PROPELLER CONTROL WAS VERY SENSITIVE AND COULD ONLY GET 1,900 RPM MAX FROM THE ENGINE.  AFTER SHUTTING DO	WN AND REMOVING ENGINE COWLING TO INVESTIGATE, MECHANIC NOTED THE PROPELLER GOVERNOR CABLE WAS CONNECTED TO THE PROPELLE	R GOVERNOR LEVER IN A HOLE THAT WOULD NOT ALLOW FULL TRAVEL.  THE CABLE WAS DISCONNECTED AND RECONNECTED IN THE PROPER H	OLE.  ENGINE PERFORMED WITHOUT FURTHER TROUBLE.  THIS AIRCRAFT HAD BEEN SIGNED OFF WITH A FRESH ANNUAL BY AN APPROPRIATE	LY RATED IA.  THE CABLE WAS DISCONNECTED TO REPLACE THE CONNECTING BOLT.  AIRCRAFT TOTAL TIME BEING 1,169.5 HOURS.	1	H	7	1 	3O			NT	A13CE   					 
1997082800004	19970828	00004	CE  	1997	8	28	97ZZZX3711       	1	19970326	G	3242	16425E	BRAKE DISC      			BEECH 	36    	A36         	1151604	CE  										RT MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	36VU	1232 				E2429				AFTER HEAVY BRAKING, PILOT REPORTED RT BRAKE FAILURE.  INSPECTION REVEALED RT BRAKE DISC HAD TORN AWAY FROM WHEEL ASSY. 	 THIS FAILURE IS IDENTICAL TO FAILURE LISTED A.M.T. MAGAZINE DATE MAY/JUNE 1997.					1	L	7	1 	3O				3A15    					 
1997082800005	19970828	00005	EA  	1997	8	28	97ZZZX3712       	1	19970807	G	5610	6003303019	WINDSHIELD      			CNDAIR	CL600 	CL6002B16   	1900305	EA  										PILOT SIDE	HEAT FAILED     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	43R	1095 			1515	5134				PILOT'S WINDSHIELD HEAT INOPERATIVE.  TROUBLESHOT TO OPEN HEATING ELEMENT.  REMOVED AND REPLACED WINDSHIELD HEAT THEN WO	RKED CORRECTLY.  SUBMITTER STATED WINDSHIELDS ONLY AVERAGE 2,500 HOURS FLEET WIDE.  SOME FOR HEAT PROBLEMS AND SOME FOR 	CRACKS.				2	L	7	2 	4F			RT	A21EA   					 
1997082800006	19970828	00006	SO  	1997	8	28	97ZZZX3713       	1	19970729	G	5553		STABILIZER      			PIPER 	PA34  	PA34200T    	7103406	SO  										V STAB ATTACH	RIVETS SHEARED  	B		A	APCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	8407C					347670137				EIGHT RIVETS WERE SHEARED ON BOTH SIDES OF VERTICAL STABILIZER (WHERE VERTICAL STABILIZER ATTACHED TO EMPENNAGE).  SUBMI	TTER STATED THIS MAKES SIX AIRPLANES IN FLEET THAT HAVE HAD SOME OR ALL OF THESE RIVETS IN THIS CONDITION.					1	L	7	2 	3O				A7SO    					 
1997082800007	19970828	00007	CE  	1997	8	28	97ZZZX3714       	1	19970808	G	2731	12600741	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										ELEV TRIM TAB	GEAR PIN FAILED 	B		A	DSBR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	25	9423D	4652 				172RG00285				DURING FLIGHT,  PILOT NOTICED TRIM NOT RESPONSIVE (ELEVATOR).  INSPECTION OF SYSTEM FOUND PINS FELL OUT OF ACTUATOR WHIC	H ATTACH GEAR TO SHAFT.  THE TRIM WHEEL MOVED NORMALLY, BUT TAB STAYED IN ONE POSITION.					1	H	7	1 	3O				3A17    					 
1997082800008	19970828	00008	NE  	1997	8	28	97ZZZX3715       	2	19970725	G	7210	358206	BEARING         		3101807X    						GARRTT	TPE331	TPE3316252M 	01514	NE  					START/GEN GEAR	MAKING METAL    	B	L	A	DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		332  					P20381			S.O.A.P. SAMPLE RETURNED MAJOR CARBON STEEL PLATELETS AND TRACE COPPER.  DISASSEMBLY OF ENGINE REVEALED BEARING SEPARATO	R OUTER DIAMETER TO OUTER RACE LAND CLEARANCE INSUFFICIENT RESULTING IN RUBBING.  BEARING OUTER RACE HAS HEAT DISCOLORAT	ION.  BEARING SERIAL NR 0184.  NOTE:  S.O.A.P. WITH CARBON STEEL PLATELETS AND COPPER WOULD BE EXCLUSIVELY RELATED TO TH	IS PART NUMBER PMA BEARING FOR THE TPE331.  BEARING CAN BE EASILY INSPECTED FOR DISCOLORATION BY REMOVING STARTER GENERA	TOR AND BEARING SEAL RETAINER.											E2WE				 
1997082800009	19970828	00009	NE  	1997	8	28	97ZZZX3716       	2	19970725	G	7210	358206	BEARING         								GARRTT	TPE331	TPE3316252M 	01514	NE  					START/GEN GEAR	MAKING METAL    	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		332  					P20381			S.O.A.P. SAMPLE RETURNED MAJOR CARBON STEEL PLATELETS AND TRACE COPPER.  DISASSEMBLY REVEALED BEARING SEPARATOR OUTSIDE 	DIAMETER TO OUTER RACE LAND CLEARANCE INSUFFICIENT RESULTING IN RUBBING.  BEARING OUTER RACE HAS HEAT DISCOLORATION.  BE	ARING S/N 0129.  NOTE:  S.O.A.P. SHOWING CARBON STEEL PLATELETS AND COPPER WOULD BE EXCLUSIVELY RELATED TO THIS PART NUM	BER PMA BEARING FOR THE TPE331.  BEARING OPPOSITE THIS BEARING (SAME P/N) CAN BE INSPECTED FOR SIGNS OF DISCOLORATION BY	 REMOVING STARTER/GENERATOR AND SEAL RETAINER.  ACCESSIBLE BEARING RECEIVES LESS LUBRICATION, THEREFORE, EXHIBITS DISCOL	ORATION AT LOWER TIME IN SERVICE.										E2WE				 
1997082800010	19970828	00010	CE  	1997	8	28	97ZZZX3717       	1	19970701	G	3241	1206P27	PRESSURE SWITCH 			CESSNA	500   	550         	2076604	CE  										ANTI SKID BRAKE	FAILED          	B	L		ZU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	26496	459  			2497	550607				DURING A DAILY INSPECTION, A/C POWER WAS TURNED ON.  THE ANTI-SKID BRAKE PUMP BEGAN TO RUN, BUT WOULD NOT SHUT OFF ONCE 	SYSTEM PRESSURE WAS MADE.  TROUBLESHOOTING REVEALED A BAD IN-LINE PRESSURE SWITCH.  SWITCH WAS INSTALLED 459.4 HOURS AGO	.  TAKING INTO CONSIDERATION THE ONLY TIME THE SWITCH FUNCTIONS IS BETWEEN 900 TO 1300 PSI, THE ACTUAL OPERATING TIME IS	 ACCUMULATED DURING GROUND OPERATION, WHICH IS MUCH LESS.			1	L	7	2 	4F				A22CE   					 
1997082800011	19970828	00011	EA  	1997	8	28	97ZZZX3718       	2	19970724	G	7210	3024765	SUNGEAR         			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					GEAR BOX	FATIGUE         	H				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	23	2FOR	6653 				766	PCE42155			ENGINE FAILED IN CRUISE.  INVESTIGATION REVEALED THE FRACTURE OF THE RGB 1ST STAGE SUN GEAR FAILED DUE TO FATIGUE.  THE 	ORIGINAL CAUSE OF THE FATIGUE COULD NOT BE DETERMINED.  THE RGB DECOUPLING WAS CAUSED BY AN OVERSPEED CONDITION OF PT RO	TOR RESULTING IN LIBERATION OF THE PT BLADES DUE TO TENSILE OVERLOAD.  THE ENGINE WAS OVERHAULED AND RELEASED ON THE AUG	UST 6, 1996 AND FAILED AT TSO 409 HOURS/1623 CSO.			1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997082800013	19970828	00013	CE  	1997	8	28	97ZZZX3719       	1	19970728	G	5540	MS244614	BEARING         			BEECH 	90    	C90A        	1152911	CE  										RUDDER	FROZEN          	B		A	NN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25										RUDDER BEARING HAS BEEN FOUND FROZEN ON 5 AIRCRAFT OUT OF 18.  IN CHAPTER 12, SERVICING, THERE IS NO LUBE CALLED OUT FOR	 THE RUDDER BEARINGS.  A.T.A. 12-20-00, PAGE 233.					1	L	7	2 	3T			RT	3A20    					 
1997082800014	19970828	00014	EA  	1997	8	28	97ZZZX3720       	2	19970718	G	7313	3014704	ADAPTER ASSY    								PWA   	PT6   	PT6*        	52043	EA  					FUEL NOZZLE	LEAKAGE         	B		A	UE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01										DURING LEAK TEST OF A PT6A FUEL NOZZLE ADAPTER ASSY, LEAKAGE WAS DETECTED COMING FROM A WELD ON TOP OF THE FUEL NOZZLE A	DAPTER ASSY.  THIS IS THE SECOND ADAPTER ASSY FOUND LEAKING IN THIS AREA.  SUGGEST THAT ALL WELDS BE CHECKED ADDITIONALL	Y DURING FUEL NOZZLE ADAPTER LEAK TEST.									3	T			E2NE				 
1997082800015	19970828	00015	EU  	1997	8	28	97ZZZX3721       	1	19970806	G	2621	A813625	SWITCH COVER    	KIDDE       	81360021    	AIRBUS	300   	A300*       		EU  										ENG FIRE BOTTLE	MISOVERHAULED   	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99					U861					DURING PRELIMINARY INSPECTION OF ENGINE FIRE BOTTLE ASSY, NOTICED THE ORIGINAL PRESSURE SWITCH COVER, PN A813625, HAD BE	EN RE-WELDED TO THE LEG STUMPS CONTRARY TO THE DIRECTIONS AS WRITTEN ON WALTER KIDDE SB 813600-26-01.  THIS SB SPECIFICA	LLY DIRECTS THE PERSON PERFORMING THE HYDROSTATIC TEST OF THIS SPHERE TO CUT THE SWITCH COVER LEGS, FILE DOWN THE LEG ST	UMPS, REMOVE THE PRESSURE SWITCH, PN 282141, DISCARD THE ORIGINAL SWITCH COVER, PN A813625, AND, AFTER HYDROTEST, TO REP	LACE THE ORIGINAL SWITCH COVER WITH A KIT, CONSISTING OF A COLLAR, PN A813635-1, COVER, PN A813636-1, AND ATTACHING SCRE	WS, PN MS167997-3, AND MS16995-3.	2	L	7	2 	4F			RT	A35EU   					 
1997090300001	19970903	00001	EU  	1997	9	3	97ZZZX3722       	1	19970806	G	2621	A813625	SWITCH COVER    	KIDDE       	81360021    	AIRBUS	300   	A300*       		EU  										ENG FIRE BOTTLE	MISOVERHAULED   	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99					90230EK					DURING PRELIMINARY INSPECTION OF ENGINE FIRE BOTTLE ASSY, NOTICED THE ORIGINAL PRESSURE SWITCH COVER, PN A813625, HAD BE	EN RE-WELDED TO THE LEG STUMPS CONTRARY TO THE DIRECTIONS AS WRITTEN ON WALTER KIDDE SB 813600-26-01.  THIS SB SPECIFICA	LLY DIRECTS THE PERSON PERFORMING THE HYDROSTATIC TEST OF THIS SPHERE TO CUT THE SWITCH COVER LEGS, FILE DOWN THE LEG ST	UMPS, REMOVE THE PRESSURE SWITCH, PN 282141, DISCARD THE ORIGINAL SWITCH COVER, PN A813625, AND, AFTER HYDROTEST, TO REP	LACE THE ORIGINAL SWITCH COVER WITH A KIT, CONSISTING OF A COLLAR, PN A813635-1, COVER, PN A813636-1, AND ATTACHING SCRE	WS, PN MS167997-3, AND MS16995-3.	2	L	7	2 	4F			RT	A35EU   					 
1997082800016	19970828	00016	NE  	1997	8	28	97ZZZX3723       	2	19970616	G	7240	BD5144	COMB CHAMBER    			BOEING	747   	747136      	1384883	NM  	PWA   	JT9   	JT9D7A      	52054	NE  					DIFFUSER CASE	CRACKED         	D				J	E	A		DUMP FUEL               	ENGINE SHUTDOWN         	UNSCHED LANDING         		M			OVER TEMP                 			CL	CLIMB          	1			SW	99		47362			729237		685964			ON INITIAL CLIMB, NR 2 ENGINE OVERTEMP LIGHT ILLUMINATED (970 DEGREE CELSIUS INDICATED).  PARAMETERS RAN DOWN AND ENGINE	 FIRE CHECK LIST CARRIED OUT.  A THREE-ENGINE APPROACH AND LANDING CARRIED OUT FOLLOWING FUEL DUMP PROCEDURE.  GROUND CH	ECKS REVEALED ENGINE COMBUSTION CHAMBER OUTER CASING (CCOC) CRACKED AT L-FLANGE LOCATION.  PART TOTAL CYCLES, 10,669.				2	L	7	4 	4F	4	F		A20WE   	E20EA				 
1997082800017	19970828	00017	CE  	1997	8	28	97ZZZX3724       	1	19970715	G	3234	660036118	SELECTOR VALVE  			LEAR  	55    	55LEAR      	5170702	CE  										MLG	INOPERATIVE     	B			DELR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CE	03	121US				565					LANDING GEAR WOULD NOT EXTEND.  GEAR HAD TO BE BLOWN DOWN WITH EMERGENCY SYSTEM.  REPLACED GEAR DOOR SELECTOR VALVE WITH	 AN OVERHAULED UNIT.  CYCLED GEAR NUMEROUS TIMES (45).  OPS AND LEAK CHECKED GOOD.  AIRCRAFT HOURS:  3,105.1.  AIRCRAFT 	LANDINGS (CYCLES):  2,138.				2	L	7	2 	4F				A10CE   					 
1997082800018	19970828	00018	CE  	1997	8	28	97ZZZX3725       	1	19970701	G	5280	45A3081	HINGE           		45A30304    	BEECH 	MU300 	400BEECH    		CE  										MLG DOOR	CRACKED         	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	1564B	3502 				RJ64				AT A 200-HOUR INSPECTION, FOUND THE UPPER CHANNEL ON BOTH GEAR DOORS JUST ABOVE THE FORWARD DOOR HINGE CRACKED.  AFTER R	EMOVING THE CHANNEL, FOUND THE FORWARD HINGE CRACKED ALSO.  THIS PROBLEM HAS BEEN ADDRESSED BY BEECH IN COMMUNIQUE NR 26	.				2	H	7	2 	4F			RT	A16SW   					 
1997082800019	19970828	00019	CE  	1997	8	28	97ZZZX3726       	1	19970701	G	5280		HINGE CHANNEL   		45A30304    	BEECH 	MU300 	400BEECH    		CE  										MLG DOOR	CRACKED         	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	1564B	3502 				RJ64				AT A 200-HOUR INSPECTION, FOUND THE UPPER CHANNEL ON BOTH GEAR DOORS JUST ABOVE THE FORWARD DOOR HINGE CRACKED.  AFTER R	EMOVING THE CHANNEL, FOUND THE FORWARD HINGE CRACKED ALSO.  THIS PROBLEM HAS BEEN ADDRESSED BY BEECH IN COMMUNIQUE NR 26	.				2	H	7	2 	4F			RT	A16SW   					 
1997082800021	19970828	00021	CE  	1997	8	28	97ZZZX3728       	1	19970728	G	3231	45A386713141	CONTROL CABLE   			BEECH 	MU300 	400BEECH    	       	CE  										LT MLG DOOR EXT	BROKEN          	B		A	AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	1564B	1103 				RJ64				WHEN PERFORMING AN EMERGENCY GEAR EXTENSION TEST, THE LEFT GEAR WOULD NOT COME DOWN.   FOUND THE LEFT DOOR OPEN (EMERGEN	CY) PULL CABLE BROKEN.  IF THIS HAD HAPPENED IN-FLIGHT, THE CREW WOULD NOT HAVE BEEN ABLE TO GET THE LEFT GEAR DOWN USIN	G THE EMERGENCY SYSTEM.				2	H	7	2 	4F			RT	A16SW   					 
1997082800022	19970828	00022	NE  	1997	8	28	97ZZZX3729       	2	19970721	G	7320		SENSE PROBE     			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7313B    	01518	NE  					NR 2 ENG PT2	PLUG LOOSE      	D		A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NM	01	39WP					6500039				NR 2 ENGINE SURGED TWICE DURING CLIMB-OUT.  INDICATIONS WERE OBSERVED ON BOTH FAN AND FUEL FLOW.  AIRCRAFT ALSO YAWED. F	OUND NR 2 ENGINE PT2 LENS PROBE PLUG LOOSE, ALSO, DIRTY WITH RUST-LIKE MATERIAL.  CLEANED PROBE AND PLUG.  SWAPPED PT2 P	ROBE LT TO RT PER INNOTECH REP'S ADVISE.  RAN ENGINE TO TAKEOFF (92 PERCENT FAN) NORMAL AND MANUAL.  NO FLUCTUATIONS OR 	SURGES NOTED.  OPS CHECKED OK.  (X)			2	L	7	2 	4F	4	F		A9NM    	E6WE				 
1997082800023	19970828	00023	WP  	1997	8	28	97ZZZX3730       	2	19970423	G	7260	30728692	SPLINED ADAPTER 	BENDIX      	8060300     	AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					START/GENERATOR	STRIPPED        	B			DELR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	900JB					59	P76321C			WHEN ATTEMPTING TO START NR 2 ENGINE, STARTER SPUN, BUT ENGINE DID NOT ROTATE.  FOUND THE SPLINED ADAPTER STRIPPED INSID	E OF GEARBOX.  REPLACED SPLINE ADAPTER.					2	L	7	3 	4F	4	F		A46EU   	E6WE				 
1997082800024	19970828	00024	SW  	1997	8	28	97ZZZX3731       	1	19970804	G	6230	206040576105	BEARING         			BELL  	206   	206L3       	1182108	SW  										M/R MAST	MAKING METAL    	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	111SP	494  			MB333	51325				MAIN ROTOR MAST BEARING MAKING METAL.  REPLACED WITH NEW MAST BEARING.						1	G	7	1 	3U				H2SW    					 
1997082800026	19970828	00026	EA  	1997	8	28	97ZZZX3733       	2	19970717	G	8520	LW12596	BOLT            		LW13422     	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 4 CYL CON ROD	FAILED          	B		A	FW7R	O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			EA	07	6129Q					S1629	L2476251A			AT 500.0 HOURS TSO, THE ENGINE FAILED IN-FLIGHT.  ENGINE TEAR DOWN REVEALED NR 4 CONNECTING ROD HAD FAILED, PUNCHING A H	OLE THROUGH THE CRANKCASE.  THE TWO CONNECTING ROD BOLTS HAD FAILED ALLOWING THE CONNECTING ROD TO COME LOOSE FROM THE C	RANKSHAFT.  THE BOLTS WENT TO THE NTSB FOR ANALYSIS.  THE ENGINE WAS OVERHAULED NOVEMBER, 1996, LYC SB 240N REQUIRES REP	LACEMENT OF THE CONNECTING ROD BOLTS AT OVERHAUL.  EXAMINING THE WORK ORDER FROM THE OVERHAUL, IT WAS UNCLEAR IF THOSE B	OLTS HAD BEEN REPLACED.		1	G	7	1 	3O	3	O		4H12    	1E10				 
1997082800027	19970828	00027	SW  	1997	8	28	97ZZZX3734       	1	19970724	G	6730	206076062107	ACTUATOR        			BELL  	407   	407         		SW  										SERVO PILOT VALV	LEAKING         	B			GS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	7249U	9    				53152				SERVO ACTUATOR LEAKING AT PILOT VALVE.  REPLACED WITH NEW SERVO ACTUATOR.						1	G	7	1 	3U			O	H2SW    					 
1997082800055	19970828	00055	SO  	1997	8	28	97ZZZX3735       	2	19970630	G	7414		MAGNETO         			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	MISTIMED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	07		145  								WHILE CHECKING MAGNETO TIMING DURING AN ANNUAL INSPECTION, DISCOVERED THE TIMING WAS SET AT TOP DEAD CENTER.  ENGINE WAS	 FACTORY OVERHAULED BY TCM 2 YEARS AGO.  IT NOW HAS 145 HOURS ON IT.  THE MECHANIC THAT ANNUALED THE AIRCRAFT LAST STATE	D IN THE LOG BOOK HE CHECKED THE TIMING.  THE TAMPERPROOF PAINT WAS STILL ON THE MAG AND ENGINE AND HAD NOT BEEN DISTURB	ED.			1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997082800056	19970828	00056	EA  	1997	8	28	97ZZZX3736       	2	19970716	G	8530	LW19001	VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 1 CYL EXH VLV	STICKING        	H				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	99	172HR	4528 	422  			17269272	L1173539A			DURING CRUISE FLIGHT, PILOT REPORTED ROUGH RUNNING ENGINE.  PILOT REDUCED POWER AND LANDED SAFELY WITHOUT INCIDENT.  MEC	HANICS INSPECTING THE ENGINE DISCOVERED A SEVERELY BENT PUSH ROD AND HOUSING ON NR 1 CYLINDER.  FURTHER INSPECTION REVEA	LED THE EXHAUST VALVE STEM CAP SEPARATED FROM THE VALVE STEM AND LODGED BETWEEN THE VALVE ROCKER AND VALVE STEM.  MECHAN	ICS DETERMINED THIS MALFUNCTION WAS APPARENTLY CAUSED BY THE EXHAUST VALVE STICKING FROM EXCESSVIE CARBON BUILD-UP.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997082800057	19970828	00057	SO  	1997	8	28	97ZZZX3737       	1	19970809	G	5711		SPAR            			LUSCOM	8     	8A          	8190104	SO  										WING	CORROSION       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2066K	921  				4793				COMPLIED WITH AD 96-24-17 IAW LUSCOMBE RECOMMENDATION NR 2.  INSTALLED O.L.A.H.F. KIT NR 2.  NO DAMAGING CORROSION WAS F	OUND.  SUBMITTER RECOMMENDED SPRAYING WING INTERIOR WITH CF 50 CORROSION PROOFING.					1	H	7	1 	3O				A694    					 
1997082800058	19970828	00058	SO  	1997	8	28	97ZZZX3738       	2	19970714	G	8520	649277	LIFTER          			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					CYL NR 1/2	SPALLED         	B			CBCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	27FV	352  				21063483	293828R			DURING ROUTINE INSPECTION ON TCM FACTORY REMANUFACTURED TSIO520R (TIME 352.1 HOURS), CYLINDERS NR 1 AND NR 2 HAVE EXHAUS	T VALVE LEAKING.  UPON CYLINDER REMOVAL AND HYDRAULIC LIFTER INSPECTION, REVEALED SPALLED LIFTERS IN NR 1 INTAKE AND EXH	AUST POSTION.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997082800060	19970828	00060	CE  	1997	8	28	97ZZZX3740       	1	19970731	G	2430	RSX1678	LIMITER POST    		66082052    	LEAR  	35    	35A         	5170602	CE  										GEN CONT PANEL	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	43TJ	6696 			X170	121				PILOT REPORTED AIR CONDITIONING AS INOPERATIVE. ALSO, THAT IT WAS NOT DRAWING ELECTRICAL CURRENT.  UPON INSPECTION, FOUN	D THE 150-AMP CURRENT LIMITER WAS NOT BLOWN, BUT THE END WAS BURNED OFF.  THE DAMAGE ALSO EXTENDED TO THE STUD USED TO A	TTACH THE A.C. CURRENT LIMITER TO THE GENERATOR CONTROL PANEL.  SUBMITTER STATED DEFECT COULD POSSIBLY BE LINKED TO IMPR	OPER TORQUE OF THE NUT USED TO FASTEN CURRENT LIMITER TO THE PANEL OR THE NUT MAY HAVE VIBRATED LOOSE RESULTING IN ELECT	RICAL ARCING FROM THE LIMITER TO THE POST.		2	L	7	2 	4F				A10CE   					 
1997082800061	19970828	00061	SO  	1997	8	28	97ZZZX3741       	1	19970806	G	2820	4123006	HOSE            			PIPER 	PA31  	PA31P350    	7103111	SO  										RT WING ROOT	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	4157E	747  				31P8414047				AEROQUIPT 601000-8D-0130 HOSE WAS FOUND LEAKING (FAST DRIP) ON INSPECTION.  SIMILAR HOSE ON OTHER SIDE OF AIRCRAFT SEEPI	NG.  PART LOCATION RT WING ROOT.  CURRENT DATES, A2Q91, CD3Q90, PT-4-91, 06827, RUBBER PSI-1000.  INSTALLED 4-25-91, 667	.1 HOURS.  TIME NOW, 1,414 HOURS.  SUBMITTER STATED PART LEAKS WHERE IT TOUCHES FUEL PUMP, PROBABLY GETS HOT.				1	L	7	2 	3O			RT	A8EA    					 
1997082800062	19970828	00062	SW  	1997	8	28	97ZZZX3742       	1	19970601	G	2820	75685	HOSE ASSY       	ADEL        	19372       	TMPSON	NAVION	NAVIONA     	6150104	SW  										FUEL PUMP	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	4339K	3481 			672	NAV41339				DURING AN ANNUAL INSPECTION, THE RUBBER HOSE ASSEMBLY PROVIDING FUEL TO THE ELECTRIC FUEL PUMP WAS REMOVED.  THE RUBBER 	HOSE STOCK WAS EXTREMELY FRAYED BY BOTH SOCKETS.  THE WIRE SUPPORT WINDING WAS UNWOUND AND PROTRUDING.  THE IDENTIFICATI	ON TAG SHOWED THE ASSEMBLY DATE AS 1/47.  THIS HOSE ASSEMBLY WAS ORIGINAL EQUIPMENT ON THIS AIRCRAFT AND SHOULD HAVE BEE	N REPLACED YEARS AGO. THE HOSE ASSEMBLY IS ALMOST IMPOSSIBLE TO SEE WHEN INSTALLED.  SEE NAVION PARTS CATALOG, 4TH RYAN 	EDITION, FIGURE 18, INDEX 50.  WHILE IT WAS NOT YET LEAKING, SUBMITTER STATED THE DANGEROUS SITUATION THIS HOSE ASSEMBLY	 CREATED UNDERSCORES THE IMPORTANCE OF INSPECTING AND REPLACING THOSE ASSEMBLIES.	1	L	7	1 	3O				A782    					 
1997082800063	19970828	00063	CE  	1997	8	28	97ZZZX3743       	1	19970811	G	7160	SCAT12	DUCT            	FACET       	NA6         	BEECH 	23    	23          	1151202	CE  										AIR INTAKE	COLLAPSED       	G				O				OTHER                   				Y	W		ENGINE STOPPAGE           	INADEQUATE Q C            		NR	NOT REPORTED   	1			EA	13	6083N					M1176				ENGINE LOST RPM AND STOPPED.  INSPECTION REVEALED AIR INTAKE DUCT COLLAPSED BETWEEN CARB AIRBOX AND CARB.  INCORRECT TYP	E AND PART NUMBER DUCT INSTALLED PREVIOUSLY.  SCAT 12 SHOULD BE SCEET 12 (DOUBLE WALL).  BOTH SCAT AND SCEET ARE SAME CO	LOR AND SIMILAR IN APPEARANCE WHEN VIEWED FROM OUTSIDE AFTER DUCT IS INSTALLED.  SCEET AND SCAT COULD BE MADE MORE EASIL	Y IDENTIFIABLE.			1	L	7	1 	3O				A1CE    					 
1997082800064	19970828	00064	CE  	1997	8	28	97ZZZX3744       	1	19970801	G	7120	04511201	MOUNT           			CESSNA	150   	150M        	2071830	CE  										ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	66728	5406 				15076237				ENGINE MOUNT SEPARATED FROM LOWER STRUT COLLAR.  WAS NOTICED DURING SCHEDULED INSPECTION. THE SEPARATION CAUSED THE STRU	T TO MOVE FORWARD WHICH CAUSED EXCESSIVE SLACK IN CABLES (RUDDER).  CABLES WERE RESTING ON THE FUSELAGE BOTTOM.  SUSPECT	ED NLG LANDING BY STUDENT PILOT.  NO RECOMMENDATION TO PREVENT ITS RECURRENCE.				1	H	7	1 	3O				3A19    					 
1997082800065	19970828	00065	SO  	1997	8	28	97ZZZX3745       	2	19970731	G	8550	10291004641	SEPARATOR TANK  			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					LT ENG AIR/OIL	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	17	6742X	3319 				TJ267	237557R			WHILE TROUBLESHOOTING AN OIL LEAK, SUBMITTER FOUND AIR OIL SEPARATOR TANK CRACKED AROUND THE INLET TUBE COMING FROM THE 	TURBOCHARGER.  TWO CRACKS WERE RUNNING PARALLEL ALMOST 350 DEGREES AROUND THE TUBE.  CRACKS HAD BEEN MASKED BECAUSE SOME	ONE PREVIOUSLY COVERED THEM WITH RTV.  INSPECTION OF THIS TANK SHOULD BE C/W AND ADDITIONAL SUPPORT THROUGH THE USE OF A	 CLAMP IS RECOMMENDED.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1997082800066	19970828	00066	CE  	1997	8	28	97ZZZX3746       	1	19970806	G	2410	5395473119	BELT            			CESSNA	182   	182H        	2072718	CE  										ALTERNATOR	DEBONDED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	8529S					18256629				AN ALTERNATOR DRIVE BELT PURCHASED FROM API PARTS INTERNATIONAL WAS RECEIVED IN A DE-BONDED CONDITION ALONG WITH A SECON	D BELT WHICH WAS NORMAL.  CURE DATE ON DEFECTIVE PART, 1Q96/3Q01.					1	H	7	1 	3O			NT	3A13    					 
1997082800067	19970828	00067		1997	8	28	97ZZZX3747       	4	19970804	G	3416	3431	CASTING         	UNITEDINST  	5934PAA58   	CESSNA	340   	340CESSNA   	2076404	CE  										ALTIMETER	CREEP           	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9KW				81605	3400227				THE END-SHAKES (BACK AND FORTH MOVEMENT) OF THE THREE CRITICAL ROTATING SHAFTS OF THE MECHANISM OF THIS ALTIMETER WERE C	HECKED.  THE OHM CALLS OUT .0020 INCH MINIMUM END-SHAKE.  ONE END- SHAKE MEASURED .00020 INCH.  THIS IS TEN TIMES SMALLE	R THAN THE SPECIFICATION.  WITH THIS CONDITION, THE INSTRUMENT COULD HANG UP THE POINTERS OF THE ALTIMETER UNDER A COLD 	TEMPERATURE OPERATING CONDITION. THE MANUFACTURER HAS INDICATED THAT AN END-SHAKE OF .0004 INCH OR LESS COULD CAUSE A PO	INTER HANG UP UNDER COLD OPERATING CONDITIONS.		1	L	7	2 	3O				3A25    					 
1997082800068	19970828	00068	GL  	1997	8	28	97ZZZX3748       	3	19970729	G	6114		HUB             			CESSNA	207   	T207A       	2073614	CE  						MCAULY	D3A34	D3A34C401   	GL  	NR 3 SOCKET	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9317M		1524 			T20700680		795451		PENETRANT INSPECTION DURING NORMAL OVERHAUL INDICATED A FINE LINEAR CRACK OR SCRATCH.  SUBSEQUENT EDDY CURRENT TESTING U	SING PHASE PLANE ANALYSIS INSTRUMENTATION REVEALED A CRACK APPROXIMATELY 1.5 INCHES LONG, ESTIMATED OVER .040 INCH DEEP 	ON THE EXTERIOR SURFACE OF NR 3 BLADE SOCKET ON THE LEADING EDGE SIDE SLIGHTLY ABOVE CENTERLINE OF THE HUB.  THIS CONDIT	ION IS NOT COMMONLY FOUND IN THE 'THREADLESS' STYLE OF MCAULY HUBS AND MAY BE OVERLOOKED WITHOUT EDDY CURRENT TEST.			1	H	7	1 	3O				A16CE   		5	C	P47GL	 
1997082800069	19970828	00069	EA  	1997	8	28	97ZZZX3749       	2	19970805	G	7414		GEAR            	ELECTROSYS  	1038256011  	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					MAG DISTRIBUTOR	TEETH MISSING   	A			E96R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	42GV		526  		5071348R	R18200219	L1881740A			DURING A 100-HOUR INSPECTION, REMOVED MAG FOR IMPULSE COUPLING AD.  FOUND SEVERAL TEETH MISSING FROM BOTH DISTRIBUTOR GE	ARS AND ONE GEAR CRACKED.  ALSO NOTED LARGE CRACKS ON THE TOPS OF BOTH COILS.  ENGINE AND MAG TIME SINCE FACTORY OVERHAU	L 526.4 HOURS.  CAUSE OF PROBLEM UNKNOWN.  ON PRE-INSPECTION RUN-UP, MAG DROP 150/150.				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
1997082800070	19970828	00070	CE  	1997	8	28	97ZZZX3750       	1	19970805	G	3230	AHML6NMB	ROD END         			BEECH 	36    	A36         	1151604	CE  										NLG RETRACT	FAILED          	G	L	A		K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	03	1849W					E428				THE ROD END BEARING CASE CRACKED CAUSING IT TO SPREAD OPEN; THUS, CAUSING EXTENSION OR RETRACTION OF NOSE GEAR TO BE IMP	OSSIBLE.  THIS ROD END WAS FOUND IN THE IMPROPER PLACE POSSIBLY NOT BEING MADE TO TAKE THAT RADIAL LOAD.  BEECH SI NR 07	60-010 SUGGESTS THE REPLACEMENT OF ANY BEARINGS WITH AN NMB SUFFIX SUGGEST FOLLOWING PARTS MANUAL VERY CLOSELY WHEN REPL	ACING PARTS.			1	L	7	1 	3O				3A15    					 
1997082800071	19970828	00071	SO  	1997	8	28	97ZZZX3751       	1	19970725	G	3213	9818000	GEAR LEG        			PIPER 	PA36  	PA36375     	7103620	SO  										LT MLG	BROKE           	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	3975E	2420 				367902013				AIRCRAFT WAS IN HANGAR.  PILOT WAS ON WING TO CHECK OIL AND LEFT MAIN LANDING GEAR BROKE WHERE THE GEAR ENTERS THE FUSEL	AGE.  CLEAN BREAK.  NO SIGN OF CRACKS.					1	L	7	1 	3O				A10SO   					 
1997082800073	19970828	00073	CE  	1997	8	28	97ZZZX3753       	1	19970730	G	5311	16940002561	FRAME           			BEECH 	23    	B24R        	1151253	CE  										BS 68	CORRODED        	B	S	A	ALN2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	4343W					MC264				ESTIMATE 10 - 15 INCHES OF MATERIAL ERODED AWAY FROM SEVERE CORROSION.  PART IS IN CONTACT WITH 'CAT' DUCTING PN 111728-	808-23 FRESH AIR INLET TO CABIN.  SUBMITTER SUGGESTS DETAILED INSPECTION OF AREA AT NEXT 100-HOUR ANNUAL.					1	L	7	1 	3O				A1CE    					 
1997082800074	19970828	00074	CE  	1997	8	28	97ZZZX3754       	1	19970801	G	3230	608100895	DOWNLOCK CABLE  			BEECH 	60    	B60         	1153605	CE  										DOWNLOCK RELEASE	FAILED          	G	P			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	541HR	2076 				P587				DOWNLOCK RELEASE CABLE FAILED AT TURNBUCKLE.  SAFETY WIRE WAS ALL THAT HELD TURNBUCKLE TOGETHER.						1	L	7	2 	3O			 	A12CE   					 
1997082800075	19970828	00075	CE  	1997	8	28	97ZZZX3755       	1	19970806	G	5320		STRUCTURE       			CESSNA	140   	140A        	2071604	CE  										CARRY THRU SPAR	CORRODED        	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	5629C					15582				FOLLOWING RIGHT HAND WING REMOVAL FOR PAINTING, INSPECTION OF THE FUSELAGE REAR SPAR CARRY-THROUGH STRUCTURE REVEALED MO	DERATE TO SEVERE CORROSION.  THE AREA OF CORROSION WAS BETWEEN THE FRONT FACE OF THE REAR SPAR AND THE BULKHEAD ATTACHME	NT TO THE SPAR.  IT IS LOCATED .50 INCH INBOARD OF THE REAR WING SPAR ATTACHMENT BLOCK THAT IS BOLTED TO THE SPAR CARRY-	THROUGH. THE CORROSION HAD EATEN THROUGH THE BULKHEAD 100 PERCENT.  FIVE OF THE TEN RIVETS THAT ATTACH THE BULKHEAD TO T	HE SPAR HAD RIVET HEADS MISSING DUE TO CORROSION.		1	H	7	1 	3O				5A2     					 
1997082800076	19970828	00076	CE  	1997	8	28	97ZZZX3756       	1	19970716	G	3213	AN547	BOLT            			CESSNA	172   	172RG       	2072438	CE  										NLG AXLE	BROKEN          	G	L	A		O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			WP	09	6273R					172RG0135				DURING INSTRUCTIONAL FLIGHT INVOLVING TAKEOFF AND LANDINGS, THE PILOT WAS INFORMED VIA RADIO FROM ANOTHER AIRCRAFT THAT 	THE ACFT NOSE WHEEL HAD FALLEN OFF.  HE PROCEEDED TO SEE WHERE HE MADE A SUCCESSFUL EMERGENCY LANDING.  INSPECTION OF TH	E ACFT NLG ASSY INDICATED THE NLG AXLE BOLT, AN 5-47, HAD FAILED.  NOTE:  THE REMAINS OF THIS BOLT WERE STILL IN THE RT 	HAND SIDE OF THE NLG FORK ASSY.  CLOSER INSPECTION OF THIS BOLT INDICATED IT HAD BEEN PREVIOUSLY FRACTURED/CRACKED.  TOT	AL TIME ON THIS BOLT IS UNKNOWN.		1	H	7	1 	3O				3A17    					 
1997082800077	19970828	00077	WP  	1997	8	28	97ZZZX3757       	1	19970813	G	2421	977J4123	STATOR HOUSING  	SUNDSTRANDEM	977J4132    	DOUG  	DC10  	DC10*       		WP  										AC GENERATOR	OVERSIZED       	B	L		MG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										DURING DISASSEMBLY OF BEARING LINER FROM THE HOUSING, A SHIM WAS FOUND AROUND THE HOUSING INSIDE DIAMETER WHERE THE BEAR	ING LINER SITS.  THE HOUSING I.D. WHERE BEARING LINER SITS IS OVERSIZED AND SHIM WAS INSTALLED BY UNKNOWN SHOP TO ACCOMM	ODATE THE NEW BEARING LINER.  THIS PRACTICE IS NOT ACCEPTABLE WITH THE MANUFACTURER'S SPECS.				2	L	7	3 	4F				A22WE   					 
1997082800078	19970828	00078	GL  	1997	8	28	97ZZZX3758       	1	19970625	G	2520		SEAT            			ENSTRM	F28   	F28F        	3300412	GL  										RT PAX SEAT	DEFORMED        	C	P			A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			WP	21	99YC	48   				809				THIN COMPOSIT BENCH SEAT ACROSS 15.50 INCH WIDE ALUMINUM SEAT STRUCTURE.  NOT ADEQUATE FOR TWO PASSENGERS.  LOSS OF ENGI	NE POWER WHEN A VALVE ROCKER ARM SHAFT FELL OUT OF THE ENGINE AND A DEFECTIVE LOW ROTOR RPM WARNING HORN RESULTED IN A C	RASH LANDING AND DAMAGE TO ALL MAJOR COMPONENTS OF THE HELICOPTER.  THE THIN COMPOSIT SEAT BOTTOM DEFORMED AND EACH PASS	ENGER'S PELVIS WAS TWISTED BY THE IMPACT CAUSING SEVERE DAMAGE TO THEIR VERTEBRA, AND A BROKEN RIB AND MANY BRUISES.			1	G	7	1 	3O				H1CE    					 
1997082800079	19970828	00079	GL  	1997	8	28	97ZZZX3759       	1	19970625	G	6240	726607	AMPLIFIER       	ELECTROCORP 		ENSTRM	F28   	F28F        	3300412	GL  										ROTOR RPM WARN	FAILED          	C	L			A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			WP	21	99YC	48   				809				DURING CLIMB-OUT AT 200 FEET AND 60 MPH, THE ENGINE LOST POWER DUE TO THE NR 2 CYLINDER INTAKE VALVE ROCKER ARM SHAFT FA	LLING OUT OF THE CYLINDER HEAD.  THE LOW ROTOR RPM WARNING HORN, A MAJOR SAFETY FEATURE IN MARKETING THE MODEL F28F, DID	 NOT SOUND OFF ALTHOUGH IT CHECKED OUT AT WARM-UP.  THE ENGINE SPEED DEGRADED RAPIDLY TO 2,300 RPM BEFORE TROUBLE WAS DE	TECTED AND AUTOROTATION BEGAN.  THE RESULTS WERE A VERY HARD CONTACT WITH THE GROUND AND DAMAGE TO THREE OCCUPANTS, AND 	DAMAGE TO ALL MAJOR COMPONENTS OF THE HELICOPTER.  AFTER THE DUST SETTLED, THE HORN STILL WAS NOT BLOWING.		1	G	7	1 	3O				H1CE    					 
1997082800080	19970828	00080	SW  	1997	8	28	97ZZZX3760       	1	19970808	G	6322	369D25623	BELT            			HUGHES	500N  	500N        	3027374	SW  										BLOWER	CRACKED         	H			PO7L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	900  				LN004				TWO EACH BLOWER BELTS WITH LOG B.04 HA1634, FOUND CRACKED VERTICALLY ON OUTSIDE LAYER OF BELT.  BOTH BELTS CRACKED AT SA	ME LOCATION IN RELATION TO PART NUMBER STAMP.					1	G	7	1 	3U			NC	H3WE    					 
1997082800081	19970828	00081	SW  	1997	8	28	97ZZZX3761       	1	19970729	G	6720	500N71123	LINK            			HUGHES	500N  	500N        	3027374	SW  										FAN PITCH	SEIZED          	H			PO7L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	300  				LN004				DURING 300-HOUR INSPECTION, FOUND BEARINGS LOCKED UP IN FAN PITCH CHANGE ARM AREA.						1	G	7	1 	3U			NC	H3WE    					 
1997082800185	19970828	00185	SW  	1997	8	28	97ZZZX3767       	1	19970724	G	6710	A21810064603	TRIM SWITCH     			HUGHES	500N  	500N        	3027374	SW  										CYCLIC STICK	FAILED          	H		A	PO7L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	523FB	276  				LN003				PILOT TRIM SWITCH STICKING IN ALL DIRECTIONS.						1	G	7	1 	3U			NC	H3WE    					 
1997082800186	19970828	00186	SW  	1997	8	28	97ZZZX3768       	1	19970808	G	6322	369D25623	BELT            			HUGHES	500N  	500N        	3027374	SW  										BLOWER	CRACKED         	H			PO7L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	523FB	600  				LN003				BELT WAS FOUND CRACKED VERTICALLY ON 300-HOUR INSPECTION.  CRACKED ON OUTSIDE LAYER.  BOTH BELTS CRACKED AT LOCATION IN 	RELATION TO PART NUMBER STAMP.					1	G	7	1 	3U			NC	H3WE    					 
1997082800187	19970828	00187	NE  	1997	8	28	97ZZZX3769       	2	19970625	G	7250		BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					TURBINE MO4	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	92LG	2193 			9441	2575	9198			15.9 AIRCRAFT FLIGHT HOURS AFTER CHANGING 2-3 MODULES.  ALL ENGINE CHIP PLUGS HAD METAL ON THEM.  ENGINE REPAIRED AND NO	TIFIED THAT FREE TURBINE BEARING HAD FAILED.  PART TOTAL CYCLES, 8,080.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997082800379	19970828	00379	CE  	1997	8	28	97ZZZX3778       	1	19970728	G	2436		REGULATOR       	BENDIX      	7           	RKWELL	NA265 	NA26540     	6402608	CE  										TERMINAL	CORRODED        	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09					614					PART RECEIVED FROM SUPPLY WITH CORROSION ON TERMINAL ENDS. THESE ARE NEWLY OVERHAULED UNITS.  SUBMITTER STATED THIS IS A	N ONGOING PROBLEM, APPARENTLY, THIS AREA IS NOT BEING LOOKED AT DURING OVERHAUL.					2	L	7	2 	4J				A2WE    					 
1997082800380	19970828	00380	CE  	1997	8	28	97ZZZX3779       	1	19970728	G	2436		REGULATOR       	BENDIX      	7           	RKWELL	NA265 	NA26540     	6402608	CE  										TERMINAL	CORRODED        	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09					704					PART RECEIVED FROM SUPPLY WITH CORROSION ON TERMINAL ENDS. THESE ARE NEWLY OVERHAULED UNITS.  SUBMITTER STATED THIS IS A	N ONGOING PROBLEM, APPARENTLY, THIS AREA IS NOT BEING LOOKED AT DURING OVERHAUL.					2	L	7	2 	4J				A2WE    					 
1997082800381	19970828	00381	GL  	1997	8	28	97ZZZX3780       	3	19970730	G	6111	83867	CLAMP           	HARTZL      		AIRTRC	AT500 	AT502       	0390303	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	BLADE	CRACKED         	B	S		PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07					EG7906			BU529		INSPECTION FOUND BLADE CLAMP CRACKED.						1	L	7	1 	3T			NC	A9SW    		6	C	P15EA	 
1997082800382	19970828	00382	SO  	1997	8	28	97ZZZX3781       	1	19970811	G	3246	1159SCL20343	WHEEL           			GULSTM	G1159 	GIV         	3980115	SO  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23M	2789 	224  		JUN8647	1022				AT TIRE CHANGE INSPECTION, THREE CRACKS WERE FOUND IN KEYWAY BOSSES.  THESE CRACKS ARE AT THE INBOARD END OF THE BOSSES.	  WE ARE WORKING WITH THE MANUFACTURER TO DETERMINE THE CAUSE OF THE CRACKS.  SUBMITTER RECOMMENDS THESE AREAS BE INSPEC	TED WITH AN EDDY CURRENT MACHINE AT EACH TIRE CHANGE.				2	L	7	2 	4F			RT	A12EA   					 
1997082800383	19970828	00383	CE  	1997	8	28	97ZZZX3782       	1	19970717	G	2913		PUMP            			RKWELL	NA265 	NA26540     	6402608	CE  										SHAFT	SEAL DAMAGED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	316NT		8    		MX193803A	282060				HYDRAULIC PUMP WAS REMOVED AFTER 7.9 HOURS TIME IN SERVICE DUE TO SHAFT SEAL FAILURE AND EXCESSIVE FLUID LEAKAGE. PUMP, 	SN MX193803A, REJECTED FOR INSTALLATION DUE TO SHAFT SEAL WAS DAMAGED AND STICKING OUT AROUND THE PUMP DRIVE SHAFT.  BOT	H PUMPS WERE OVERHAULED BY  REPAIR STATION.  PUMP, SN MX193803A, TSO:  0.0.  PUMP, SN MXW243463A, TSO:  7.9 HOURS.				2	L	7	2 	4J				A2WE    					 
1997082800384	19970828	00384	CE  	1997	8	28	97ZZZX3783       	1	19970717	G	2913	PF24390615BCE	PUMP            			RKWELL	NA265 	NA26540     	6402608	CE  										SHAFT	SEAL DAMAGED    	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	09	316NT		8    		MX243463A	282060				HYDRAULIC PUMP WAS REMOVED AFTER 7.9 HOURS TIME IN SERVICE DUE TO SHAFT SEAL FAILURE AND EXCESSIVE FLUID LEAKAGE. PUMP, 	SN MX193803A, REJECTED FOR INSTALLATION DUE TO SHAFT SEAL WAS DAMAGED AND STICKING OUT AROUND THE PUMP DRIVE SHAFT.  BOT	H PUMPS WERE OVERHAULED BY  REPAIR STATION.  PUMP, SN MX193803A, TSO:  0.0.  PUMP, SN MXW243463A, TSO:  7.9 HOURS.				2	L	7	2 	4J				A2WE    					 
1997082800385	19970828	00385	EA  	1997	8	28	97ZZZX3784       	1	19970808	G	5551	C2TP159A	BRACKET         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										LT HORIZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	67897	2119 				1045				DURING 100-HOUR INSPECTION AND C/W AD 90-02-22, FOUND 2 INCH CRACK ON OUTBOARD SIDE OF  THE LEFT HORIZONTAL STABILIZER (	TAIL PLANE) ATTACHMENT BRACKET, PN C2TP159A.  AD 90-02-22 CALLS FOR  INSPECTION OF THE FUSELAGE MOUNTED BRACKETS, P/N'S 	C2-FS-543A AND C2-FS-544A, AND NOT FOR INSPECTION OF BRACKETS MOUNTED ON THE HORIZONTAL STABILIZER P/N'S C2TP159A AND C2	TP160A.  THIS AIRCRAFT IS A FLOAT PLANE.  SUBMITTER BELIEVES CAUSE OF THIS DEFECT IS THE EXCESSIVE FORCE APPLIED TO THE 	HORIZONTAL STABILIZER (TAIL PLANE) DURING 'RAMPING' OR 'BEACHING' OF THE AIRCRAFT BY GROUND PERSONNEL AFTER FLIGHT.  AD 	90-02-22 SHOULD BE REVISED TO INCLUDE THE INSPECTION OF THE STABILIZER MOUNTED BRACKETS, P/N'S C2TP159A AND C2TP160A.	1	H	7	1 	3R				A806    					 
1997082800386	19970828	00386	CE  	1997	8	28	97ZZZX3785       	1	19970806	G	5210	MS3548941	SEAL GROMMET    			CESSNA	500   	S550        	2076607	CE  										MAIN DOOR	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	11	72AM					S5500004				PILOT REPORTED RAPID DE-PRESSURIZATION AT ALTITUDE AND NOTED DOOR SEAL AT MAIN ENTRANCE DOOR LEAK.  MAINTENANCE FOUND DO	OR SEAL GROMMET DRY-ROTTED AND CRACKED.  INSTALLED NEW GROMMET, P/N MS35489-41, AND PERFORMED OPERATIONAL CHECK, NO DEFE	CTS OF DOOR SEAL NOTED.  THIS GROMMET IS DIFFICULT TO INSPECT FOR CRACKS WHILE INSTALLED.  PROCEDURES FOR REMOVAL AND RE	PLACEMENT OF THIS GROMMET ARE FOUND IN CESSNA S550 MM, 52-10-01, PAGE 206.  AIRCRAFT TT:  3437.6 HOURS.			1	L	7	2 	4F			RT	A22CE   					 
1997082800387	19970828	00387	EA  	1997	8	28	97ZZZX3786       	3	19970716	G	6110	527	RETAIN NUT      			WACO  	YMF   	YMF         	9600412	EA  						SNSNCH	W96JB	W96JB       	EA  	PROPELLER SHAFT	FAILED          	D	L	A		A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	553T					F5C050		AC9806		AIRCRAFT ACCIDENT IN WHICH PROPELLER SEPARATED FROM AIRCRAFT.  SUSPECT CAUSE:  RETAINING NUT FAILURE.  SUBMITTER RECOMME	NDATION:  RETAINING NUT BE REPLACED AT SPECIFIC INTERVALS.  RETAINING NUT BE INSPECTED PRIOR TO EACH PROPELLER INSTALLAT	ION.				1	Q	7	1 	3R				ATC542  		5	N	P170	 
1997082800388	19970828	00388	CE  	1997	8	28	97ZZZX3787       	1	19970715	G	2810	08233435	BLADDER         			CESSNA	310   	310K        	2074228	CE  										LT AUX FUEL	MISMANUFACTURED 	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	09					F1375					UNABLE TO INSTALL LT WING AUXILIARY FUEL CELLS, DUE TO INCORRECT DIMENSIONS BETWEEN CENTER OF AUX FUEL GAUGE TRANSMITTER	 FLANGE OPENING AND FUEL DRAIN HOSE NIPPLE.  DISTANCE BTWN CENTERS OF AUX FUEL GAUGE XMITTER FLANGE OPENING AND ENG FUEL	 HOSE NIPPLE IS 6.312 INCHES FOR OEM BLADDER, 5.688 INCHES (SN F-1375) AND 5.812 INCHES (SN F-2341) FOR DURAFLEX BLADDER	S, A .624 INCH AND .50 INCH DIFFERENCE FROM OEM.  SUBMITTER RECOMMENDS QC AND MFG BE CHKD FOR SIGNS OF DEVIATION FROM EN	GINEERING PROCEDURES, PLANNING, AND PROCESS CONTROL.		1	L	7	2 	3O				3A10    					 
1997082800389	19970828	00389	CE  	1997	8	28	97ZZZX3788       	1	19970715	G	2810	08233435	BLADDER         			CESSNA	310   	310K        	2074228	CE  										LT AUX FUEL	MISMANUFACTURED 	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	09					F2341					UNABLE TO INSTALL LT WING AUXILIARY FUEL CELLS, DUE TO INCORRECT DIMENSIONS BETWEEN CENTER OF AUX FUEL GAUGE TRANSMITTER	 FLANGE OPENING AND FUEL DRAIN HOSE NIPPLE.  DISTANCE BTWN CENTERS OF AUX FUEL GAUGE XMITTER FLANGE OPENING AND ENG FUEL	 HOSE NIPPLE IS 6.312 INCHES FOR OEM BLADDER, 5.688 INCHES (SN F-1375) AND 5.812 INCHES (SN F-2341) FOR DURAFLEX BLADDER	S, A .624 INCH AND .50 INCH DIFFERENCE FROM OEM.  SUBMITTER RECOMMENDS QC AND MFG BE CHKD FOR SIGNS OF DEVIATION FROM EN	GINEERING PROCEDURES, PLANNING, AND PROCESS CONTROL.		1	L	7	2 	3O				3A10    					 
1997082800390	19970828	00390	EA  	1997	8	28	97ZZZX3789       	2	19970515	G	8550	10168500	WASHER          			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	TIO540U2A   	41532	EA  					OIL PUMP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	858CH	600  				608265006				DURING C/W SB 600-131, SUBSTANTIATED BOTH SCAVANGE OIL PUMPS WERE DUE IMMINENT FAILURE.  REPLACED PARTS REQUIRED.						1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
1997082800391	19970828	00391	CE  	1997	8	28	97ZZZX3790       	1	19970814	G	2820		FUEL LINE       			CESSNA	172   	172N        	2072434	CE  										FRAME HOLE	CHAFING         	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	05										FOLLOWING AIRCRAFT INTERIOR REMOVAL, FOUND FUEL DISTRIBUTION LINES CHAFING ON FUSELAGE FRAMES.  LINES WERE RIDING HARD O	N EDGE OF CUT-OUTS.  CHAFE WAS THROUGH RUBBER SLEEVE AND WAS METAL-TO-METAL ON THE LINE.					1	H	7	1 	3O			NT	3A12    					 
1997082800392	19970828	00392	NE  	1997	8	28	97ZZZX3791       	3	19970717	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		8685 	4536 					HJ76A		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	 
1997082800394	19970828	00394	EA  	1997	8	28	97ZZZX3793       	1	19970814	G	6220	114R205035	HUB             		414R20019   	BOEING	234   	234         	1385049	EA  										M/R HEAD	CRACKED         	B	S		CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2FOR	1157 	203  		A41453	MJ001				CRACK DISCOVERED DURING POST-FLIGHT INSPECTION.  CRACK ON TOP SURFACE OF CENTER SECTION BETWEEN RESERVOIR MOUNT HOLE AND	 TIE BAR BOLT ACCESS HOLE.  EXTENDS THROUGH RESERVOIR HOLE DOWN INTO WEB OF CENTER SECTION.  ROTOR HUB OPERATED ON MJ022	 IN 'LR' CONFIGURATION BY HELIKOPTER SERVICE NORWAY.  ONLY OPERATED 7 DAYS AND 55 HOURS IN 'UT' LOGGING ENVIRONMENT.  PA	RT NEW FROM BOEING APRIL 1994, INSTALLED BY HS AT COMPONENT TT 6,928.9 HOURS.  OVERHAULED BY HS JUNE 1995 AT COMPONENT T	T 7,883.5 HOURS.		2	G	7	2 	4U				H9EA    					 
1997082800395	19970828	00395	EA  	1997	8	28	97ZZZX3794       	2	19970526	G	7322	2539561	SEAL            		RSA5AD1     	PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540D4A5   	41532	EA  					INJECTOR SERVO	LEAK            	D		A		O				OTHER                   				K	E	R	FLUID LOSS                	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			SO	16	991K					244055	L138248			SERVO WAS OVERHAULED ON APPROXIMATELY 1-28-97.  COMPONENT OPERATED WITHOUT PROBLEM UNTIL 5-11-97 WHEN IT HAD ACCUMULATED	 30 HOURS IN SERVICE.  ON 5-11-97, EXPERIENCED IN-FLIGHT ENGINE ROUGHNESS WHICH ABATED SOMEWHAT WITH EXCESSIVELY LEANING	 OF THE MIXTURE.  UPON LANDING, ENGINE POWER COULD NOT BE SUSTAINED DUE TO EXCESSIVELY RICH MIXTURE.  UPON DISASSEMBLY, 	FOUND THAT SEAL PN 2539561 WAS LEAKING FUEL INTO THE AIR CHAMBER.			1	L	7	1 	3O	3	O		1A15    	1E4				 
1997090400259	19970904	00259	SO  	1997	9	4	97ZZZX3802       	1	19970810	G	3250	955100	MOUNT           			PIPER 	PA34  	PA34200     	7103405	SO  											BROKE           	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	17	1380T	4230 				347250302				SUPPORT WELD BROKE ON STEERING/RUDDER TAB DURING LANDING GEAR MALFUNCTION.  SUGGEST DYE CHECK EVERY 500 HOURS AND REPLAC	ED ALL NEW HARDWARE.					1	L	7	2 	3O				A7SO    					 
1997090400260	19970904	00260	CE  	1997	9	4	97ZZZX3803       	1	19970808	G	3260	99101366	ACTUATOR        			CESSNA	425   	425         	2076018	CE  										RT MLG DOWNLOCK	INTERMITTENT    	D				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			NM	09	146GW	266  			1	4250146				RIGHT MLG SHOWED UNSAFE INDICATION WHEN EXTENDED.  AFTER SEVERAL CYCLES, STILL NO DOWN AND LOCKED INDICATION.  TROUBLESH	OT SYSTEM AND FOUND DOWN AND LOCKED SWITCH WITHIN RT MLG ACTUATOR TO BE UNRELIABLE INTERMITTENTLY.  REPLACED RT MLG ACTU	ATOR ASSY.				1	L	7	2 	3T			RT	A7CE    					 
1997090400261	19970904	00261	CE  	1997	9	4	97ZZZX3804       	1	19970816	G	3233	22430022	FITTING         			CESSNA	182   	R182        	2072734	CE  										NLG ACTUATOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	182BG	2077 				R18200256				DURING NON-ROUTINE MAINTENANCE, FOUND NOSE GEAR ACTUATOR ATTACH FITTING UPPER RT LEG BROKEN AT ATTACH BOLT HOLE.  REPLAC	ED WITH NEW PART.  REVIEW OF LOG BOOKS INDICATE THIS AIRCRAFT HAD BEEN SEVERELY DAMAGED IN THE NOSE GEAR AREA (AS WELL A	S HAVING 3 GEAR UP LANDINGS) WITH NO MENTION OF THE FITTING BEING REPLACED DURING REPAIRS.  SUSPECT FITTING WAS DAMAGED 	DURING PREVIOUS ACCIDENT.  NOTE: AD 91-11-09 AND CESSNA MEB 88-4 APPLY TO CESSNA T303 AIRCRAFT WHICH USED A VERY SIMILAR	 FITTING.		1	H	7	1 	3O			RT	3A13    					 
1997090400262	19970904	00262	EA  	1997	9	4	97ZZZX3805       	2	19970805	G	7314	RG9080J7A	PUMP            	ROMEC       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	LEAKING         	D		A		A	E	F		UNSCHED LANDING         	ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      		J	K	A	WARNING INDICATION        	FLUID LOSS                	FLAME/FIRE                	CR	CRUISE         	1			SW	11	3533L		104  		C6509	317952181	L745861A			DURING NORMAL FLIGHT, PILOT NOTICED LEFT ENGINE WAS USING EXCESSIVE AMOUNT OF FUEL.  PILOT DEVIATED FROM INTENDED DESTIN	ATION TO NEAREST AIRPORT.  DURING LANDING, LEFT ENGINE CAUGHT FIRE.  LEFT ENGINE WAS SHUT DOWN AND FIREWALL SHUT-OFF WAS	 ACTUATED.  UPON INSPECTING WITH ELECTRIC FUEL BOOST TURNED ON, FUEL WAS FOUND LEAKING FROM SEAM OF ENGINE-DRIVEN FUEL P	UMP.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997090400263	19970904	00263	SO  	1997	9	4	97ZZZX3806       	1	19970613	G	8011	MZ4222	STARTER         			PIPER 	PA23  	PA23250     	7102308	SO  										RT ENGINE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	40259		797  		9M000004	277305069				RIGHT STARTER DRAGGING WHEN ENGAGED.  FOUND MOTOR HOUSING LOOSE.  ONE SCREW MISSING AND THREE OTHERS LOOSE.  THIS IS THE	 SECOND STARTER FOUND LIKE THIS.  THE SIXTH STARTER BY OUR OPERATION.  THESE STARTERS ARE OVERHAULED BY CRS NR MO6R900J.					1	L	7	2 	3O				1A10    					 
1997090400264	19970904	00264	CE  	1997	9	4	97ZZZX3807       	1	19970805	G	7810	99102998	HEADER          			CESSNA	340   	340A        	2076405	CE  										WASTEGATE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	6274X					340A0458				WHEN C/W AD 75-23-08 R5, FOUND HEADER CRACKED APPROXIMATELY TWO-THIRDS OF CIRCUMFERENCE ON THE WASTEGATE CONNECTOR PIPE.	  THIS AREA IS SUBJECT TO HEAT AND STRESSES WHEN IN OPERATION.					1	L	7	2 	3O				3A25    					 
1997090400265	19970904	00265	CE  	1997	9	4	97ZZZX3808       	1	19970814	G	5741		ATTACHMENT      			CESSNA	172   	172A        	2072404	CE  										WING ROOT	DAMAGED         	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7377T	6650 				46977				DAMAGED LEADING EDGE/MAIN SPAR/TRAILING EDGE AT WING CONNECTIONS TO FUSELAGE.  A NEED FOR REINFORCEMENT IN THESE AREAS A	ND IN  MAIN FUSELAGE SECTIONS NEED TO BE REINFORCED WITH ADDITIONAL BRACE AND HEAVY DUTY CONNECTION BRACING PLATES DUE T	O EXCESSIVE ICE AND SNOW ACCUMULATION ON AIRFRAME WHICH MAY HAVE EXCEEDED NEGATIVE LOAD FACTOR OF AIRFRAME.				1	H	7	1 	3O				3A12    					 
1997090400266	19970904	00266	CE  	1997	9	4	97ZZZX3809       	1	19970804	G	5312	00244002377	BULKHEAD        			BEECH 	58    	58          	1152740	CE  										BS 257.6	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	788CF	5084 				TH870				DURING PHASE 2 INSPECTION OF TAIL AREA, CRACKING AND STOP-DRILLING NOTICED ON STA 257.6 BULKHEAD AT HORIZONTAL SPARE ATT	ACH POINTS.  STOP-DRILLING IS NOT AN APPROVED REPAIR PER BEECH SI 990, REV 2 PART II.  A P/N 55-4030-5S REINFORCEMENT KI	T NEEDED TO BE INSTALLED.  KIT INSTALLED, AIRCRAFT RETURNED TO SERVICE.  SI 990, WHICH REQUIRES INSPECTION, MODIFICATION	, OR REPLACEMENT, SHOULD BE C/W EACH INSPECTION ON THESE BULKHEADS.  REFER TO BEECH SI 990 FOR DETAILS.			1	L	7	2 	3O				3A16    					 
1997090400267	19970904	00267	CE  	1997	9	4	97ZZZX3810       	1	19970818	G	5312	12128582	BULKHEAD        			CESSNA	206   	U206        	2073306	CE  										BS 230.187	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8030Z	4883 				U2060430				INSPECTION FOUND TAIL CONE BULKHEAD AT BS 230.187 CRACKED.  REPLACED WITH P/N 1212130-2.						1	H	7	1 	3O				A4CE    					 
1997090400269	19970904	00269	SO  	1997	9	4	97ZZZX3812       	1	19970818	G	2750	8290503	BELLCRANK       			PIPER 	PA46  	PA46350P    		SO  										RT FLAP DRIVE	BROKEN          	B	P	A	VA1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	91649	1233 				4622029				RIGHT HAND FLAP DRIVE BELLCRANK ASSY P/N 82905-3 CRACKED AND TWISTED APPROXIMATELY .33 INCH OF CIRCUMFERENCE ON .75 INCH	 TUBE (MAIN BACKBONE OF TUBE).					1	L	7	1 	3O			RT	A25SO   					 
1997090400270	19970904	00270	SO  	1997	9	4	97ZZZX3813       	2	19970803	G	8530	641793	VALVE SEAT      			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  					NR 2 INT VALVE	CARBONED UP     	B	L		B9CR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			EA	03	6674F					15063274	38263A			FOLLOWING TAKEOFF, ENGINE LOST POWER.  SAFE LANDING MADE.  INVESTIGATION FOUND NR 2 CYLINDER LOST POWER DUE TO VALVE SEA	T CARBON BUILD-UP CAUSING COMPRESSION LOSS AND BLOWBY TO OTHER CYLINDERS.					1	H	7	1 	3O	3	O		3A19    	E252				 
1997090400271	19970904	00271	SO  	1997	9	4	97ZZZX3814       	1	19970820	G	7810	LW15806	PIPE FLANGE     			PIPER 	PA32  	PA32301T    	7103209	SO  										UPPER RT EXHAUST	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	856RC					328024003				ROUTINE INSPECTION FOUND EXHAUST STAIN AT RT UPPER COWL AT FIRST CLAMP WAS SUSPECT.  FURTHER INSPECTION FOUND INTERMEDIA	TE EXHAUST PIPE FLANGE CRACKED.  FLANGE WAS STRESS CRACKED AROUND ENTIRE CIRCUMFERENCE.  PART TOTAL TIME .050 HRS.					1	L	7	1 	3O				A3SO    					 
1997090400274	19970904	00274	SW  	1997	9	4	97ZZZX3815       	1	19970819	G	7120	2762114003	TRUSS MOUNT     			SWRNGN	SA227 	SA227AC     	8780603	SW  										ENG NACELLE	CRACKED         	B		A	H7NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17					308007					MOUNT HAD BEEN INSPECTED AND SIGNED OFF ON SB 227-71-008.  HOWEVER, WHEN RECEIVED IN THE SHOP, THE REAR TRUSS MOUNT WAS 	NOT WELDED.  IT IS VERY DIFFICULT TO SEE IF THE MOUNT IS WELDED BY DOING SB 227-71-008 AS IT IS CALLED OUT.  CAN EASILY 	BE MISSED.  IF NOT REPAIRED, TRUSS CAN CRACK AT NON-WELDED AREA.				2	L	7	2 	4T			RT	A8SW    					 
1997090400275	19970904	00275	WP  	1997	9	4	97ZZZX3816       	2	19970806	G	7230	30770391	OUTER LINER     								GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	MISREPAIRED     	B		A	IY2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										RECEIVED FROM ALLIED SIGNAL REPAIR AND OVERHAUL SHOP.  ONE EACH LINER OUTER TRANSITION P/N 3077039-1.  THIS PART IS REWO	RKED FROM A P/N 3071611-1.  HOWEVER, THE PART RECEIVED WAS NOT AIRWORTHY.  THE INNER SURFACE SHOULD HAVE BEEN COATED WIT	H A THERMAL BARRIER COATING (TBC).  THIS STEP WAS OMITTED.  A SECOND AREA OF CONCERN IS THE SIGN-OFF IN THE REMARKS SECT	ION OF THE 8130-3.  THIS BLOCK STATES THE PART WAS WORKED AND INSPECTED PER MANUAL 72-02-71 (731 HEAVY MM).  THIS MANUAL	 DOES NOT FURNISH ANY DETAILS ON THE MODIFICATION OF THIS PART.  PART HAS BEEN RETURNED TO ALLIED SIGNAL, RMA NR 300133.							4	F			E6WE				 
1997090400276	19970904	00276	EU  	1997	9	4	97ZZZX3817       	1	19970820	G	2752	21007	ARMATURE        		D79         	FOKKER	F27   	F27MK400    	4990626	EU  										FLAP MOTOR	ARCING          	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	2MIL				1702	10652				INSPECTION FOUND FLAP MOTOR ARMATURE WINDINGS ARCING AT COMMUTATOR SEGMENT RISERS.  ARMATURE HAS OPEN CIRCUITED WINDINGS	.  CAUSED BY LATHE TURNING COMMUTATOR SEGMENTS TO CLEAN UP PREVIOUS COMPLAINT OF 'INSULATORS PROTRUDING FROM BETWEEN COM	MUTATOR SEGMENTS'.  LATHE TURNING REDUCED THICKNESS OF SEGMENTS BREAKING ELECTRICAL CONTACT BETWEEN ARMATURE WINDING AND	 COMMUTATOR SEGMENT BARS.  FLAP MOTOR FAILURE OCCURRED AFTER LANDING.  PART TOTAL CYCLES, 154.			2	H	7	2 	4T				A817    					 
1997090400278	19970904	00278	CE  	1997	9	4	97ZZZX3819       	1	19970815	G	3240	1206P27	SWITCH          			CESSNA	500   	550         	2076604	CE  										POWER BRAKE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26496	492  			2648	550607				MECHANIC NOTICED POWER BRAKE PUMP STOPPED CYCLING AFTER FLIGHT, IT NORMALLY CYCLES EVERY MINUTE OR SO TO RECHARGE PRESSU	RE ACCUMULATOR.  LACK OF CYCLING TRACED TO OPEN PRESSURE SWITCH WHICH WAS REPLACED AND OPS RETURNED TO NORMAL.  SUBMITTE	R HAS HAD TO CHANGE THESE SWITCHES 15 TIMES OVER THE LAST 7 YEARS ON FLEET OF FOUR C-550'S.				1	L	7	2 	4F				A22CE   					 
1997090400279	19970904	00279	CE  	1997	9	4	97ZZZX3820       	1	19970714	G	5610	50420066354	WINDOW          			BEECH 	100   	B100        	1152919	CE  										COPILOT D	DELAMINATED     	B	S		W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	500KD					BE79				FOUND COPILOT'S D-WINDOW STARTING TO DELAMINATE ON LOWER PORTION DUE TO OVERSIZED WINDOW WAS INSTALLED IN A NORMAL SIZE 	FUSELAGE OPENING.  WINDOW WAS RUBBING ON FUSELAGE SKIN AT THE RECESSED AREA OF THE WINDOW.  BEECHCRAFT IPC ONLY LISTS OV	ERSIZED WINDOWS.				1	L	7	2 	4T				A14CE   					 
1997090400280	19970904	00280	CE  	1997	9	4	97ZZZX3821       	1	19970806	G	2810	10192006711	PLATE ASSY      		1009200671  	BEECH 	90    	F90         	1152909	CE  										FUEL VENT FLOAT	LOOSE           	B	S		EHHR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	96TT	6100 				LA26				FUEL VENTING FROM RIGHT HEATED FUEL VENT.  FOUND FUEL LEAKING PAST AUXILIARY TANK FLAPPER VALVE.  LOOSE/WORN RIVETS ALLO	WED VALVE TO UNSEAT AND FUEL LEAKED BY GRAVITY FEED.  REPLACED RIVETS THAT HOLD HINGE HALF TO PLATE.					1	L	7	2 	4T				A31CE   					 
1997090400282	19970904	00282	CE  	1997	9	4	97ZZZX3822       	1	19970816	G	2720	504200337	BEAM            			BEECH 	99    	99          	1154002	CE  										RUD PEDAL BS 115	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	108BA	26664				U40				RUDDER PEDAL QUADRANT MOUNT BEAM CRACKED.  CRACK WAS FOUND ON THE BOTTOM BEND UNDER SUPPORT BRACKET (RUDDER) BOLT HOLES.	  SUSPECT POSSIBLE CAUSE, RUDDER CABLE TENSION TOO HIGH.					1	L	7	2 	3T				A14CE   					 
1997090400283	19970904	00283	NE  	1997	9	4	97ZZZX3823       	3	19970715	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	BLADE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4596 			2500NR			HJ382		INSPECTION OF PROPELLER 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	 
1997090400284	19970904	00284	CE  	1997	9	4	97ZZZX3824       	1	19970804	G	3244	028700	TIRE            			CESSNA	500   	560CESSNA   	2076750	CE  										LT MLG	FAILED          	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	92SS	258  			6003P00676	5600388				DURING MAINTENANCE TIRE SERVICING PRIOR TO FLIGHT, NOTICED LEFT MAIN TIRE TREAD WAS COMING OFF TIRE CASING.  TIRE HAD TO	 BE CHANGED BEFORE FLIGHT.  TIRE WAS AVIATOR 12-PLY AND TIRE PRESSURE AND TIRE TREAD LOOKED NORMAL.  TIRE PRESSURE WAS B	EING CHECKED AS PART OF NORMAL PRE-FLIGHT BY AN A & P MECHANIC.  LANDINGS, 263.				2	L	7	2 	4F			RT	A22CE   					 
1997090400285	19970904	00285	CE  	1997	9	4	97ZZZX3825       	1	19970714	G	2434	DOFF10300B	ALTERNATOR      	FORD        		CESSNA	150   	152         	2071835	CE  										DC SYSTEM	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	15	68175		33   		0082833	15285318				ALTERNATOR FAILED IN-FLIGHT 33.0 HOURS AFTER OVERHAUL.						1	H	7	1 	3O			NT	3A19    					 
1997090400286	19970904	00286	SO  	1997	9	4	97ZZZX3826       	1	19970826	G	5510		STABILATOR      			PIPER 	PA28  	PA28140     	7102802	SO  										RT/LT STABILATOR	CORRODED        	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	6747W	3014 				2820871				RIVET HEAD FOUND MISSING ON BOTTOM OF RT STABILATOR.  INSPECTION REVEALED THE AREA IN FRONT OF SPAR ON BOTH LT AND RT ST	ABILATOR WERE FILLED WITH MOUSE NESTING DEBRIS.  ACCESS COULD ONLY BE MADE BY REMOVING BOTH TIP RIBS.  CORROSION WAS LIG	HT, BUT ALL BOTTOM RIVETS ALONG SPAR ON RT SIDE WERE REPLACED.  THIS AIRCRAFT IS STORED IN A CLOSED HANGAR WITH A CONCRE	TE FLOOR.  THE POTENTIAL PROBLEMS FROM THIS CONDITION GOING UNNOTICED ARE SEVERE, SO LOOK SHARP!			1	L	7	1 	3O				2A13    					 
1997090400493	19970904	00493	SW  	1997	9	4	97ZZZX3827       	1	19970819	G	7120	2762114003	TRUSS MOUNT     			SWRNGN	SA227 	SA227AC     	8780603	SW  										ENG AFT MOUNT	CRACKED         	B		A	H7NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17										TRUSS MOUNT CRACKED AT TUBE THAT ATTACHES THE REAR UPPER ENGINE MOUNT.  THIS MOUNT WAS WELDED UNDER THE LUG POINT AND WA	S NOT EFFECTED BY THE CALL OUT OF SB 227-71-008.  FIRST WELDED ONE SUBMITTER HAS SEEN CRACKED.  PRIOR CRACKS HAD BEEN TH	OSE NOT WELDED.				2	L	7	2 	4T			RT	A8SW    					 
1997090400494	19970904	00494	NE  	1997	9	4	97ZZZX3828       	2	19970724	G	7210	8941191	COUPLER         								GARRTT	TPE331	TPE3316252M 	01514	NE  					RED GEARBOX	INSERT LOOSE    	B		A	RG4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03					W97190070					NEW PART RECEIVED WITH INTERNAL SPLINE INSERT LOOSE.  IF PART WAS INSTALLED IN ENGINE AND FAILED, ENGINE WOULD EITHER NT	S WHILE RUNNING, OR NOT NTS UPON ENGINE IN-FLIGHT FAILURE.														E2WE				 
1997090400495	19970904	00495		1997	9	4	97ZZZX3829       	1	19970725	G	2436	VR515G	CONTROL UNIT    	ELECTRODELTA	E3402A      															ALTERNATOR CONT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										THIS UNIT (ZERO TIME SINCE REPAIR) WAS REMOVED FROM SHELF STOCK AND INSTALLED IN PLACE OF AIRCRAFT'S FAULTY ACU.  DURING	 INSTALLATION, NOTED THERE WAS NO OUTPUT VOLTAGE TO ALTERNATOR FIELD.  UNIT WAS REMOVED WITH ZERO TIME IN SERVICE SINCE 	INSTALLATION.																	 
1997090400496	19970904	00496		1997	9	4	97ZZZX3830       	1	19970725	G	2436	VR55G	CONTROL UNIT    	ELECTRODELTA																ALTERNATOR	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15					0031243					THIS UNIT (NEWLY OVERHAULED) WAS REMOVED FROM SHELF STOCK AND INSTALLED IN PLACE OF AIRCRAFT'S FAULTY ALTERNATOR CONTROL	 UNIT.  DURING INSTALLATION, NOTED THERE WAS NO OUTPUT VOLTAGE TO ALTERNATOR FIELD.  UNIT WAS REMOVED WITH ZERO TIME IN 	SERVICE SINCE INSTALLATION.																	 
1997090400497	19970904	00497	CE  	1997	9	4	97ZZZX3831       	1	19970725	G	2436	VR515G	CONTROL UNIT    	ELECTRODELTA	2032601     	CESSNA	150   	152         	2071835	CE  										ALTERNATOR CONT	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	15	68725		101  			15282338				LOW VOLTAGE LIGHT ILLUMINATED IN-FLIGHT.  INSPECTION REVEALED NO VOLTAGE TO FIELD TERMINAL ON ALTERNATOR.  VERIFIED POWE	R SUPPLY TO ACU.  NO ACU OUTPUT.  INSTALLATION OF TWO ACU'S (ZERO TIME SINCE REPAIR/OVERHAUL) DID NOT RESTORE POWER.  IN	STALLATION OF ZEFTRONICS ACU P/N R25400 RESTORED POWER AND SYSTEM FUNCTIONED NORMALLY.				1	H	7	1 	3O			NT	3A19    					 
1997090400500	19970904	00500	SO  	1997	9	4	97ZZZX3834       	2	19970815	G	8530		CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					CYLINDER HEAD	CRACKED         	B	L		VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	105LY	807  				414A0060	L509474			THE TWO REPORTED ENGINES EXHIBITED FUEL STAINS ADJACENT TO THE ENGINE FUEL INJ ECTORS ON 9 OF A POSSIBLE 12 CYLINDERS. F	URTHER EXAMINATION REVEALED CYLINDER HEAD CRACKS UNDER CYLINDER FINS (AT THE INTAKE PORTS) AND THROUGH THE SPARK PLUG BO	SSES ON EACH OF THE CYLINDERS.  SUBMITTER STATED IF ALLOWED TO GO UNCHECKED, THE CRACKS COULD PROGRESS TO A POINT WHERE 	THE CYLINDER TO HEAD INTEGRITY WOULD BE LOST AND CYLINDER PERFORMANCE JEOPARDIZED.			1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997090400501	19970904	00501	GL  	1997	9	4	97ZZZX3835       	2	19970806	G	7240	23031260	COMBUSTION CASE 			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					RT ARM PIT SEAM	CRACKED         	B			B31R	K				NONE                    				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	17	163BH	2227 				3027	CAE270600			PILOT REPORTED HIGH TOT, LOW POWER.  INSPECTED COMBUSTION CASE, FOUND CRACK ALONG SEAM WHERE HALVES WERE WELDED TOGETHER	.  THIS AREA IS ALSO REINFORCED WITH WIRE MESH BRAZED FOR SUPPORT.  THE CRACK WAS BEHIND WIRE MESH.  A LARGER REINFORCEM	ENT PATCH MIGHT HELP.				1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997090400502	19970904	00502	EU  	1997	9	4	97ZZZX3836       	1	19970607	G	2822		BOOST PUMP      			SNIAS 	350   	AS350B2     	8680813	EU  										BELLY PANEL	WIRE CHAFED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	96LG	1160 				2817				RIGHT FUEL BOOST PUMP STOPPED.  TROUBLESHOT BOOST PUMP SYSTEM AND FOUND WIRE CHAFED THROUGH FROM BELLY PANEL RUBBING ON 	WIRE AND FUEL TANK.  EITHER THE BELLY PANEL WAS MIS-ALIGNED OR THE FUEL TANK WAS MIS-ALIGNED OR CUT OUT IN BELLY PANEL W	AS NOT LARGE ENOUGH.  SUBMITTER RECOMMENDS FACTORY VERIFY CLEARANCE AROUND FUEL TANK-SUMP-BOSS AREA.				1	G	7	1 	3U				H9EU    					 
1997090400503	19970904	00503	EU  	1997	9	4	97ZZZX3837       	1	19970625	G	2911	704A34240015	ACCUMULATOR     			SNIAS 	350   	AS350B2     	8680813	EU  										T/R CONTROL	LOST PRESSURE   	D				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	11	93LG					2654				TAIL ROTOR CONTROLS LOST ACCUMULATOR PRESSURE, FOUND VALVE STEM LOOSE.  SUBMITTER STATED THIS HAS HAPPENED SEVERAL TIMES	 WITH ALL ACCUMULATORS (INCLUDING M/R) ON 3 DIFFERENT AIRCRAFT.  SUBMITTER RECOMMENDS USING ACCUMULATOR WITH JAM NUT AND	 SHUT-OFF FOR VALVE STEM.				1	G	7	1 	3U				H9EU    					 
1997090400504	19970904	00504		1997	9	4	97ZZZX3838       	4	19970728	G	3414	206075725103	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT AIR SPD	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	7249U	10   				53152				AIR SPEED INDICATOR FAILED.  REPLACED WITH NEW AIRSPEED INDICATOR.						1	G	7	1 	3U			O	H2SW    					 
1997090400505	19970904	00505	EU  	1997	9	4	97ZZZX3839       	1	19970625	G	2916		RESERVOIR       			SNIAS 	350   	AS350B2     	8680813	EU  										HYDRAULIC SYSTEM	WATER CONTAM    	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	93LG	2654 				2654				ON SEVERAL OCCASIONS AND 3 DIFFERENT AIRCRAFT NOTICED WATER DROPLETS IN HYDRAULIC RESIDUE FILLER NECK SCREEN.  SUBMITTER	 SUSPECTS CAP DESIGN AS PROBLEM, OCCURS MAINLY AFTER SITTING OUT IN RAIN OR SNOW.  HYDRAULIC RESERVOIR IS POSITIONED WIT	H NO PROTECTION FROM WEATHER BY COWLINGS.  IT IS BELOW MAST OPENING IN COWLING.  RECOMMEND RE-DESIGN CAP.				1	G	7	1 	3U				H9EU    					 
1997090400506	19970904	00506	EU  	1997	9	4	97ZZZX3840       	1	19970714	G	6320	109040306105	INPUT QUILL     		A09040002107	AGUSTA	A109  	A109C       	0260118	EU  										MAIN GEARBOX	SPALLED         	D		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	15	911D	1178 			361	7637				APPROXIMATELY 5 MINUTES AFTER TAKEOFF, MAIN TRANSMISSION CHIP LIGHT CAME ON AND WOULD NOT ZAP OFF.  PILOT RETURNED TO MA	INT BASE.  TECHNICIAN REMOVED AND INSPECTED BOTH CHIP PLUGS.  TOP CHIP PLUG WAS CLEAN.  BOTTOM CHIP PLUG HAD 4 LARGE CHI	PS ON IT.  TRANSMISSION FILTER WAS REMOVED AND FOUND TO CONTAIN AN EXCESSIVE AMOUNT OF METAL FILINGS.  (200 HOUR OIL AND	 FILTER CHANGE HAD BEEN C/W APPROXIMATELY 23 HOURS PRIOR TO THIS WITH NOTHING ABNORMAL NOTED).  AGUSTA AEROSPACE TECHNIC	IANS OPENED THE GEARBOX AND FOUND EXCESSIVE SPALLING ON THE INPUT QUILL AND GLEASON CROWN GEAR.		1	G	7	2 	3U				H7EU    					 
1997090400507	19970904	00507	NE  	1997	9	4	97ZZZX3841       	1	19970811	G	6210	641520201048	BLADE           		64M47805074 	SKRSKY	S64   	S64E        	8142604	NE  										MAIN ROTOR	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2FOR	3473 				64065				SPAR IS CRACKED ON THE BOTTOM SIDE BACKWALL RADIUS APPROXIMATELY 112.1 INCHES FROM TIP END.  SPAR AT CRACK LOCATION SHOW	S NO OBVIOUS SIGNS OF DAMAGE ON THE EXTERIOR SURFACE.					2	G	7	2 	4U				H4EA    					 
1997090400509	19970904	00509	SO  	1997	9	4	97ZZZX3843       	2	19970812	G	8530		CYLINDER        			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					NR 1	SEPARATED       	B			KU1R	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	07	3838R		970  			17255338	34890D6D			AIRCRAFT WAS IN-FLIGHT WHEN NR 1 CYLINDER BARREL SEPARATED FROM HEAD CAUSING A FORCED LANDING.  NO FURTHER DAMAGE OCCURR	ED TO AIRCRAFT AND NO INJURIES OCCURRED DURING THIS INCIDENT.  SUSPECT CAUSE WAS ATTRIBUTED TO AGE AND TIME ON CYLINDER.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997090400510	19970904	00510	EU  	1997	9	4	97ZZZX3844       	2	19970730	G	8530		SEAL            			AMTR  	SEAREY	SEAREY      	05625X5	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					NR 3 CYL EXH VLV	FAILED          	G				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	23	7475Q	32   				1DK028	4400900			NUMEROUS PILOT LOG BOOK REPORTS OF A ROUGH RUNNING ENGINE.  ATTEMPTS TO CORRECT BY REPLACING SPARK PLUGS, LEADS, FUEL FI	LTER, ETC., DID NOT CORRECT PROBLEM.  INVESTIGATION DISCLOSED THAT BOTH SPARK PLUGS IN NR 3 CYLINDER WERE OIL SOAKED.  I	T APPEARED THE EXHAUST VALVE STEM SEAL ON NR 3 CYLINDER HAD FAILED.				1	H	7	1 	3I	3	I	RC	1H71EXPA	EXPE3I				 
1997091100100	19970911	00100	NE  	1997	9	11	97ZZZX3846       	2	19970707	G	7230	766962	CASE ASSY       								PWA   	JT8   	JT8D1       	52044	NE  					COMPRESSOR	CARBON BUILD UP 	B	L		CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					CD1239					INSPECTION OF COMPRESSOR CASE ASSY FOUND EXCESSIVE CARBON BUILD-UP.											4	F			E2EA				 
1997091100101	19970911	00101	NE  	1997	9	11	97ZZZX3847       	2	19970707	G	7230	766962	CASE ASSY       								PWA   	JT8   	JT8D1       	52044	NE  					COMPRESSOR	CARBON BUILD UP 	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					CK4178					INSPECTION OF COMPRESSOR CASE ASSY FOUND EXCESSIVE CARBON BUILD-UP.											4	F			E2EA				 
1997091100102	19970911	00102		1997	9	11	97ZZZX3848       	1	19970707	G	7500	634607	DIFFUSER DUCT   								PWA   	JT8   	JT8D1       	52044	NE  					P/D OF PORT AREA	CRACKED         	B	S		CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1970					INSPECTION FOUND DIFFUSER DUCT WITH LENGTHY CRACKING ON OUTSIDE DIAMETER ADJACENT TO PORT AREAS.											4	F			E2EA				 
1997091100103	19970911	00103		1997	9	11	97ZZZX3849       	1	19970707	G	7500	616288	DIFFUSER DUCT   								PWA   	JT8   	JT8D1       	52044	NE  					O/D OF PORT AREA	CRACKED         	B	S		CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					A45					DIFFUSER DUCT INSPECTION FOUND LENGTHY CRACKING ON OUTSIDE DIAMETER ADJACENT TO PORT AREAS.											4	F			E2EA				 
1997011600879	19970116	00879	WP  	1997	1	16	97ZZZX385        	1	19970116	G	5740		FITTING         			WTHRLY	620   	620         	9630602	WP  										WING ATTACH	RUSTED          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	2004G					1555				WHEN PERFORMING AN ANNUAL INSP, IT WAS NOTED THAT ALL THE WING TO CENTER SECTION FITTINGS WERE SEVERELY RUSTED, NO PITTI	NG HAS YET OCCURRED ON ANY OF THESE FITTINGS, BUT SOME POWDERY DEPOSITS CAN BE SEEN BETWEEN THE LOWER CAP FITTINGS AND T	HE SPAR WEB ON THE RT LOWER FRONT FITTING.  THESE ARE STEEL FITTINGS BOLTED TO AN ALUMINUM SPAR WEB.  THESE FITTINGS APP	EAR TO NOT HAVE ANY PRIMER OR PROTECTIVE COATING OF ANY KIND ON THEM.			1	L	7	1 	3R				A26WE   					 
1997091100104	19970911	00104	NE  	1997	9	11	97ZZZX3850       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					4873					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100105	19970911	00105	NE  	1997	9	11	97ZZZX3851       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					MM1101					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100106	19970911	00106	NE  	1997	9	11	97ZZZX3852       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					5358					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100107	19970911	00107	NE  	1997	9	11	97ZZZX3853       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					APM0100493					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100108	19970911	00108	NE  	1997	9	11	97ZZZX3854       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					3766					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100109	19970911	00109	NE  	1997	9	11	97ZZZX3855       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					APM010044					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100110	19970911	00110	NE  	1997	9	11	97ZZZX3856       	2	19970624	G	7240	748265	COMBUSTION CHAMB								PWA   	JT8   	JT8D1       	52044	NE  					INNER SEAM	CRACKED         	B			CD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					GK4968					INSPECTION OF COMBUSTION CHAMBER FOUND CRACKS IN FUSION WELD THIRD INNER SEAM.  ALL UNITS WERE REJECTED, 7 EACH.											4	F			E2EA				 
1997091100113	19970911	00113		1997	9	11	97ZZZX3859       	4	19970821	G	2562	ACKE01	ELT             	ACK         																BATTERY	CORRODED        	B			JVYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05										TWO TIMES WITHIN TWO WEEKS FOUND ACK TECHNOLOGIES ELT'S, MODEL ACK E01, INOPERABLE.  ON DISASSEMBLY, FOUND THE D-CELL BA	TTERIES, TERMINALS, AND  CIRCUIT BOARD CORRODED.  TERMINALS AND CIRCUIT BOARDS WERE CLEANED, NEW BATTERIES INSTALLED, BU	T THE ELT WAS STILL INOPERABLE.  CAUSE - BAD SEALING.																	 
1997091100114	19970911	00114		1997	9	11	97ZZZX3860       	4	19970821	G	2561	P0101	VEST            	EAAEROMARINE																	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					B31230					VEST FAILED THE MANUFACTURER'S 2-POUND PSI TEST.  BAD SEAM.																			 
1997091100115	19970911	00115	CE  	1997	9	11	97ZZZX3861       	1	19970725	G	7160	04500665	SEAL            			CESSNA	150   	152         	2071835	CE  										CARB AIR BOX	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	24870					15280426				CARBURETOR BOX SEAL CESSNA PART MADE FROM THIN PLASTIC, LESS THAN 200 HOURS, AND CRACKS OUT DUE TO VIBRATION.  ALL MODEL	 CESSNAS WITH CARBURETOR AIR BOX SEALS VIBRATE AND CRACK APART INTO ENGINE COMPARTMENT.  SUBMITTER STATED SHOULD BE CONS	TRUCTED OF MORE DURABLE MATERIAL.  REPLACEMENT REQUIRED ALMOST EVERY 100 HOURS.				1	H	7	1 	3O			NT	3A19    					 
1997091100116	19970911	00116	CE  	1997	9	11	97ZZZX3862       	1	19970731	G	5711		SPAR            			CESSNA	150   	150M        	2071830	CE  										RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	45434	3731 				15076917				RIGHT REAR SPAR, WS 40, BENT AND CRACKED.  LOG RESEARCH SHOWS INCIDENT 2 YEARS PRIOR.  WING CORROSION WAS VISABLE AT A G	LANCE.					1	H	7	1 	3O				3A19    					 
1997091100117	19970911	00117	CE  	1997	9	11	97ZZZX3863       	1	19970805	G	2434	653983	HUB             	FORD        	DOFF10300F  	CESSNA	150   	150M        	2071830	CE  										ALTERNATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	45434	3731 			0071253	15076917				ALTERNATOR HUB LOOSE ON WOODRUFF KEY AND WORE SHAFT TO .0312 INCH.  STEP WEAR WAS EVIDENT BY MOVING FAN A FULL WINDOW.						1	H	7	1 	3O				3A19    					 
1997091100118	19970911	00118	CE  	1997	9	11	97ZZZX3864       	1	19970728	G	2430	S199411	SWITCH          			CESSNA	150   	152         	2071835	CE  										ALTERNATOR CONT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	48858	282  				15281007				OWNER REPORTED DEAD BATTERY.  BATTERY FOUND TOO HOT TO TOUCH, AND DEVOID OF ELECTROLYTE.  TROUBLESHOOTING INDICATED SYST	EM VOLTAGE TO BE 1.6 VOLTS ABOVE NORMAL VALUES.  FOUND INTERMITTENT RESISTANCE IN ALTERNATOR CONTROL SWITCH.  RECOMMEND 	REGULAR SYSTEM VOLTAGE CHECKS.				1	H	7	1 	3O			NT	3A19    					 
1997091100120	19970911	00120	SW  	1997	9	11	97ZZZX3866       	1	19970731	G	6230	206040576103	BEARING         			BELL  	206   	206L3       	1182108	SW  										MAST	FAILED          	B			EOPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	360AL		1141 		ZV1265	51462				MAST BEARING, P/N 206-040-576-103, ONE BALL BROKE APART.  BEARING TT UNKNOWN.  TSO:  1,141.9 HOURS.  MAST WAS INSPECTED 	FOR SUSPECTED LIGHTNING STRIKE AT 430.3 HOURS TSO.  NO DEFECTS NOTED.  REPLACED BEARING.					1	G	7	1 	3U				H2SW    					 
1997091100121	19970911	00121	SO  	1997	9	11	97ZZZX3867       	1	19970818	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  										GEAR DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	141ME					318152117				INSPECTION FOUND GEAR DOOR HINGE WITH A CRACK IN INNER ASPECT OF RADIUS.  PART IS NEW STYLE TO C/W TERMINATING ACTION OF	 AD 802605.					1	L	7	2 	3O				A20SO   					 
1997091100122	19970911	00122	EA  	1997	9	11	97ZZZX3868       	2	19970813	G	7314	1C69	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					LT MAIN XSFER	INOPERATIVE     	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	110SK		419  			31P7630006	R71162			LEFT MAIN TRANSFER PUMP OVERHAULED BY 2-14-96, INSTALLED 7-8-96.  PUMP INOPERABLE.  SENDING TO RAPCO FOR DETERMINATION O	F PROBLEM.  SHORT SERVICE LIFE.					1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997091100123	19970911	00123	SO  	1997	9	11	97ZZZX3869       	1	19970812	G	5520	5423224	ELEVATOR        			PIPER 	PA31  	PA31350     	7103110	SO  										LT ELEV TIP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	27299	4082 				317752128				ELEVATOR TIP CORRODED.  FOUND AS A RESULT OF C/W SB 998A DATED 8-4-97.						1	L	7	2 	3O				A20SO   					 
1997091100124	19970911	00124	SO  	1997	9	11	97ZZZX3870       	1	19970812	G	5520	5423235	ELEVATOR        			PIPER 	PA31  	PA31350     	7103110	SO  										RT ELEV TIP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	27299	4082 				317752128				ELEVATOR TIP CORRODED.  FOUND AS A RESULT OF C/W SB 998A DATED 8-4-97.						1	L	7	2 	3O				A20SO   					 
1997091100125	19970911	00125	SO  	1997	9	11	97ZZZX3871       	1	19970820	G	3230	4033600	DRAG LINK       			PIPER 	PA31  	PA31350     	7103110	SO  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3235F					317952200				DURING INSPECTION NOSE GEAR RT DRAG LINK FOUND LINK CRACKED IN AREA WHERE IDLER LINK ROD ATTACHES.  SUBMITTER STATED HAV	E HAD SIMILAR CRACKS IN ONE OTHER LINK ASSY.  SUSPECT AGE, FATIGUE, AND HARD LANDING.					1	L	7	2 	3O				A20SO   					 
1997091100126	19970911	00126	SO  	1997	9	11	97ZZZX3872       	1	19970818	G	3233	WTC21151	ACTUATOR        	WIEBEL      		PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3535F				8279					FOUND RIGHT MAIN GEAR ACTUATOR CRACKED AND BROKEN IN THREADED AREA OF ROD ASSY.  CRACK LOCATED AT AREA WHERE THREADS STA	RT ON ROD.  AIRCRAFT HIGH TIME (+18,000 HOURS).  AGE FATIGUE A POSSIBILITY.					1	L	7	2 	3O				A20SO   					 
1997091100127	19970911	00127	EA  	1997	9	11	97ZZZX3873       	2	19970709	G	8520		CONNECT ROD     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 5 CYLINDER	FAILED          	E		A		E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			NM	01	36PB		1250 			317405128	L722561A			CLIMBING THROUGH 4,000 FEET OUT OF PDX, PILOT NOTED PROMINENT VIBRATION.  PILOT TRIED TO DETERMINE WHICH ENGINE WAS SOUR	CE OF VIBRATION, BUT WITHIN 30 SECONDS, THE LEFT ENGINE STOPPED PRODUCING POWER (DID NOT SEIZE).  PROPELLER WAS FEATHERE	D AND AIRCRAFT RETURNED TO PDX.  ENGINE TEAR-DOWN REVEALED THAT NR 5 CONNECTING ROD HAD COME LOOSE.  SUSPECT CAUSED BY T	HE BREAKING OF ONE OF THE CONNECTING ROD BOLTS.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997091100129	19970911	00129	EA  	1997	9	11	97ZZZX3875       	2	19970812	G	7414	6224	MAGNETO         	SLICK       		MOONEY	M20   	M20M        	5870222	SW  	LYC   	O540  	TIO540AF1A  	41532	EA  					LT MAGNETO	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	40JE	473  			91030020	270161	L943161A			DURING ANNUAL INSPECTION, BOTH MAGNETOS WERE REMOVED TO C/W SLICK RECOMMENDED 500-HOUR INTERNAL EXAMINATION.  RIGHT MAGN	ETO CHECKED OK, NEEDED ONLY MINOR INTERNAL CLEANING AND POINTS ADJUSTMENT.  LEFT MAG HAD A GOOD AMOUNT OF INTERNAL CONTA	MINATION FROM THE PRESSURIZATION PORT.  DISTRIBUTOR GEAR AND ROTOR GEAR WERE SOFT.  CLEANED MAGNETO, REPLACED NECESSARY 	PARTS AND RETURNED TO SERVICE.  THE LINES GOING TO THESE MAGNETOS SHOULD HAVE AN IN-LINE FILTER INSTALLED TO PREVENT THI	S KIND OF CONTAMINATION.  AT THIS TIME, BOTH MAGNETOS WERE STILL OPERATING CORRECTLY, BUT THE LEFT MAG WOULD HAVE FAILED	 OR MALFUNCTIONED SHORTLY.	1	L	7	1 	30	3	O	RT	2A3     	E14EA				 
1997091100130	19970911	00130	SO  	1997	9	11	97ZZZX3876       	1	19970816	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  										GEAR DOOR	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4112D					318353004				INSPECTION FOUND GEAR DOOR HINGE WITH A CRACK IN INNER ASPECT OR RADIUS.  PART IS NEW STYLE TO C/W TERMINATING ACTION OF	 AD 8026-05.					1	L	7	2 	3O				A20SO   					 
1997091100131	19970911	00131	CE  	1997	9	11	97ZZZX3877       	1	19970801	G	5260	LP389	WINDOW          			CESSNA	172   	172RG       	2072438	CE  										BAGGAGE COMPT	PLUG MISSING    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4723R					172R0018				PLUG ABOUT 8 INCHES IN DIAMETER MISSING IN REAR WINDOW.  REPLACED WINDOW ABOUT 2 YEARS AGO FOR SAME REASON.						1	H	7	1 	3O				3A17    					 
1997091100133	19970911	00133	EA  	1997	9	11	97ZZZX3879       	2	19970813	G	7414		DISTRIBUTOR GEAR	SLICK       	4373        	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					MAGNETO	WORN            	B			NX42	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	925ER	492  			96081211	4496012	L3521236A			MAGNETO WAS RECEIVED BY THIS REPAIR STATION FOR A MANUFACTURER'S RECOMMENDED 500-HOUR INSPECTION. INTERNAL INSPECTION RE	VEALED THE TEETH ON BOTH THE ROTOR AND DISTRIBUTOR GEARS WERE EXCESSIVELY WORN.  IT WAS FURTHER NOTED THAT MOISTURE CONT	AMINATION HAD RESULTED IN SUBSTANTIAL CORROSION OF THE BREAKER POINTS AND INTERNAL HARDWARE.				1	L	7	2 	3O	3	O		A19S0   	E286				 
1997091100134	19970911	00134	CE  	1997	9	11	97ZZZX3880       	1	19970710	G	2720	5052432625	PEDAL ARM       			BEECH 	200   	200BEECH    	1152920	CE  										RUDDER PEDAL	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	174PW	8858 				BB64				DURING PHASE 3 OF BEECH 200-HOUR INSPECTION PROGRAM, REQUIRED INSPECTION OF RUDDER PEDALS PER CHAPTER 27-20-00, PAGE 206	.  FOUND BOLT HOLES ON RUDDER PEDAL ARMS WORN BEYOND LIMITS.  PART IS MAGNESIUM, AND PART THAT REPLACES ARM IS ALUMINUM 	P/N 50-524326-33.				1	L	7	2 	4T				A24CE   					 
1997091100135	19970911	00135		1997	9	11	97ZZZX3881       	4	19970801	G	3440	HG1075AE03	IRU             	HONEYWELL   		CNDAIR	CL600 	CL6002B16   	1900305	EA  										COCKPIT	MALFUNCTION     	B			XJRR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	449ML				685					INERTIAL REF UNIT P/N HG1075AE03 S/W 685 WAS INSTALLED AFTER FACTORY BENCH CERTIFIED.  ON FIRST FLIGHT, IT WAS REPORTED 	TO HAVE EXCESSIVE DRIFT.  IT WAS REPLACED WITH ANOTHER UNIT AND SYSTEM OPERATED NORMALLY.  (X)					2	L	7	2 	4F			RT	A21EA   					 
1997091100136	19970911	00136	NE  	1997	9	11	97ZZZX3882       	2	19970515	G	7210	430101401	BEARING         								LYC   	LTS101	LTS101750B1 	41560	NE  					GEARBOX PTO	SPALLED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17		3016 			W89H011		LE45745			ENGINE WAS RECEIVED FOR MAKING METAL.  CHIP ANALYSIS INDICATED METAL WAS COMING FROM GEARBOX.  UPON DISASSEMBLY, FOUND T	HE PTO FORWARD BEARING TO HAVE SEVERE SPALLING OF BALLS AND RACES.  ALSO, FOUND SEVERAL WORN BEARING LINERS IN THE GEARB	OX CASE AND COVER.									3	U			E5NE10				 
1997091100137	19970911	00137	EA  	1997	9	11	97ZZZX3883       	2	19970728	G	8530	45433	VALVE SEAT      		45414       	TCRAFT	BL    	BL65        	8850350	EA  	LYC   	O145  	O145B2      	41502	EA  					CYL INTAKE	FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	07	36020	675  				2985	41822			INTAKE VALVE SEAT DROPPED OUT OF CYLINDER HEAD.  NO DAMAGE TO ENGINE.  PARTIAL LOSS OF POWER.						1	H	7	1 	3O	3	O		A700    	TC210				 
1997091100138	19970911	00138		1997	9	11	97ZZZX3884       	1	19970801	G	3246	AHA2063	WHEEL           	DUNLOP      																MLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					SH027					CRACKS FOUND USING MAGNAFLUX ED 530 EDDY CURRENT TESTER.  NEED TO REMOVE BOLT, KEY WAY, AND KEEPER TO SEE CRACKS ON S/N 	WHEEL SH027.  CRACKS WERE FOUND ON 6 OF THE BOLT HOLES AND ON S/N SB097.  CRACKS FOUND ON 4 OF THE BOLT HOLES.  APPROXIM	ATELY 190 LANDINGS.																	 
1997091100139	19970911	00139		1997	9	11	97ZZZX3885       	1	19970801	G	3246	AHA2063	WHEEL           	DUNLOP      																MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					SB097					CRACKS FOUND USING MAGNAFLUX ED 530 EDDY CURRENT TESTER.  NEED TO REMOVE BOLT, KEY WAY, AND KEEPER TO SEE CRACKS ON S/N 	WHEEL SH027.  CRACKS WERE FOUND ON 6 OF THE BOLT HOLES AND ON W/N SB097.  CRACKS FOUND ON 4 OF THE BOLT HOLES.  APPROXIM	ATELY 250 LANDINGS.																	 
1997091100278	19970911	00278	CE  	1997	9	11	97ZZZX3886       	1	19970814	G	5520	35660040607	ELEVATOR        			BEECH 	35    	C35BEECH    	1151508	CE  										LT ELEVATOR	OUT OF BALANCE  	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	656D	4692 				D2924				ANNUAL INSPECTION FOUND ELEVATOR AND AILERONS OUT OF BALANCE DUE TO RECENT PAINT JOB.  UNITS HAD NOT BEEN STRIPPED PRIOR	 TO PAINTING OR CHECKED FOR BALANCE.  NO REFERENCE TO AD 87-02-02 OR AD 94-20-04 WAS FOUND IN RECORDS.					1	L	7	1 	3O				A777    					 
1997091100279	19970911	00279	CE  	1997	9	11	97ZZZX3887       	1	19970814	G	5520	35660040608	ELEVATOR        			BEECH 	35    	C35BEECH    	1151508	CE  										RT ELEVATOR	OUT OF BALANCE  	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	656D	4692 				D2924				ANNUAL INSPECTION FOUND ELEVATOR AND AILERONS OUT OF BALANCE DUE TO RECENT PAINT JOB.  UNITS HAD NOT BEEN STRIPPED PRIOR	 TO PAINTING OR CHECKED FOR BALANCE.  NO REFERENCE TO AD 87-02-02 OR AD 94-20-04 WAS FOUND IN RECORDS.					1	L	7	1 	3O				A777    					 
1997091100280	19970911	00280	CE  	1997	9	11	97ZZZX3888       	1	19970814	G	5751	35135025	AILERON         			BEECH 	35    	C35BEECH    	1151508	CE  										LT/RT AILERON	OUT OF BALANCE  	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	656D	4692 				D2924				ANNUAL INSPECTION FOUND ELEVATOR AND AILERONS OUT OF BALANCE DUE TO RECENT PAINT JOB.  UNITS HAD NOT BEEN STRIPPED PRIOR	 TO PAINTING OR CHECKED FOR BALANCE.  NO REFERENCE TO AD 87-02-02 OR AD 94-20-04 WAS FOUND IN RECORDS.					1	L	7	1 	3O				A777    					 
1997091100281	19970911	00281	EA  	1997	9	11	97ZZZX3889       	1	19970801	G	3240		BRAKE ASSY      			SCWZER	G164  	G164A       	3952704	EA  										PARKING BRAKE	NOT MODIFIED    	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	941X					455				INSPECTION FINDING THAT AG CATS 'G164A' MANUFACTURED PRIOR TO FEBRUARY 15, 1967, HAVE NOT BEEN MODIFIED PER ENGINEERING 	CHANGE ORDER S164-1845.  CHANGE PREVENTS CHANCE OF ACCIDENTAL LOCKING OF RT BRAKE MASTER CYLINDER DURING FLIGHT MANEUVER	ING.				1	Q	7	1 	3R				1A16    					 
1997091100282	19970911	00282	SW  	1997	9	11	97ZZZX3890       	1	19970801	G	2720	12411	WRIST SHAFT     			BBAVIA	7     	7ECA        	21101NN	SW  										TOE BRAKE	PIN WORN        	H	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05		1400 								1974 AND LATER, 73CA CITABRIA AIRCRAFT WHICH UTILIZE TOE BRAKES.  AT APROXIMATELY 1,700 HOURS TT, FOUND WRIST PINS IN RU	DDER/BRAKE PEDAL WORN TO ALMOST FAILURE.  LOSS OF PIN WOULD INTERFERE WITH BRAKE OR RUDDER ACTION.					1	H	7	1 	3O				A759    					 
1997091100283	19970911	00283	EU  	1997	9	11	97ZZZX3891       	1	19970808	G	7810	1079	BRACKET         			GROB  	G115  	G115C       	1660303	EU  										RT EXHAUST	SEPARATED       	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	115FN	482  				82061C1				RIGHT SIDE EXHAUST/MUFFLER ASSY BRACKET CRACKED AND BECAME SEPARATED AT FIREWALL  MOUNT CONTACTING COWLING CAUSING HEAT 	DAMAGE TO LOWER COMPOSITE COWLING.  UPON REMOVAL, NOTED THE INTERNAL BAFFLE IN THE MUFFLER HAD ALSO RECEIVED HEAT DAMAGE	, BECAME CORRODED, AND SEPARATED FROM THE WALL OF MUFFLER IN SMALL SECTIONS, BECOMING LODGED IN EXIT PIPE OF EXHAUST ASS	Y PARTIALLY BLOCKING THE EXIT PORT.			1	L	7	1 	3O			NT	A57EU   					 
1997091100286	19970911	00286	EU  	1997	9	11	97ZZZX3894       	1	19970904	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH	WORN            	B	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				DURING A DAILY VISUAL INSPECTION, DISCOVERED THE BEARING IN THE OUTBOARD END OF THE TAIL ROTOR PITCH CHANGE ROD HAD ALMO	ST COMPLETELY SEPARATED FROM THE HOUSING.  THE PILOT OF THE PREVIOUS FLIGHT DID NOT NOTICE ANY ABNORMALITIES IN THE OPER	ATION OF THE AIRCRAFT OR THE TAIL ROTOR CONTROL SYSTEM.  IT APPEARS THE BEARING WAS ONE FLIGHT AWAY FROM A TOTAL FAILURE	 WHICH COULD HAVE RESULTED IN COMPLETE LOSS OF THE HELICOPTER AND ITS OCCUPANTS.  NOTE:  THIS IS THE SECOND SUCH FAILURE	 OF THIS PITCH CHANGE ROD BEARING EXPERIENCED BY THIS OPERATOR.  THE FIRST FAILURE RESULTED IN AN CATASTROPHIC AIRCRAFT 	ACCIDENT.	1	G	7	1 	3U				H9EU    					 
1997091100287	19970911	00287	SO  	1997	9	11	97ZZZX3895       	2	19970819	G	8530	654652A1	CYLINDER        			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					NR 2	SCORED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	138PB	20   				TJ273	274196R			DURING COMPLETION OF CONTINENTAL CRITICAL SB CSB 97-10A, FOUND NR 2 CYLINDER SEVERELY SCORED DURING A BORESCOPE INSPECTI	ON.  DAMAGE COVERS 50 PERCENT OF TOTAL CYLINDER WALL AND IS BEYOND PISTON PIN WEAR AREA.  HIGH AMOUNT OF ALUMINUM SHAVIN	GS FOUND IN OIL FILTER.  AD 97-15-01 DOES NOT APPLY TO THIS ENGINE, BUT SAME CYLINDER COATING PROCESS IS USED ON I0-520 	CYLINDERS.  THIS WAS A NEW CYLINDER FROM CONTINENTAL.  RECOMMEND AD REVISION.			1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1997091100288	19970911	00288	SO  	1997	9	11	97ZZZX3896       	1	19970801	G	7922	53E49600	VERNATHERM      			PIPER 	PA31  	PA31350     	7103110	SO  										ACCESSORY CASE	SEAT LOOSE      	D				K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			EA	13	3581X					318052096				ENGINE INDICATION OF HIGH OIL TEMPERATURE.  SEAT IN ACCESSORY CASE FOR VERNATHERM CAME LOOSE PREVENTING POSITIVE FLOW OF	 OIL TO COOLER.  WEAR PATTERN ON VERNATHERM AND SEAT INDICATE THE SEAT WAS INSTALLED COCKED AT AN ANGLE.  RECORDS INDICA	TE ENGINE WAS OVERHAULED AT LYCOMING FACTORY.				1	L	7	2 	3O				A20SO   					 
1997091100289	19970911	00289	SW  	1997	9	11	97ZZZX3897       	1	19970803	G	5300	7129012	TUBE            			BBAVIA	7     	7ECA        	21101NN	SW  										FUSELAGE	BROKE           	G		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	07	4178Y					118777				FOUND LEFT MAIN GEAR FOLDED ON LANDING.  7-1290-12 TUBE BROKE AT PREVIOUS WELD REPAIR WHERE LEFT MAIN GEAR ATTACHES.  NO	 ENTRY FOR REPAIR IN LOGS.  WELDS WERE NOT AIRWORTHY.  NO PENETRATION, SIGNS OF PREVIOUS CRACKING AND CORROSION INSIDE W	ELDS.				1	H	7	1 	3O				A759    					 
1997091100290	19970911	00290	GL  	1997	9	11	97ZZZX3898       	1	19970828	G	5300	STCSA1008WE	FABRIC          			BLANCA	17    	1730        	1220432	GL  										FUSELAGE	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	4855V					30109				AIRCRAFT RECOVERED 9/90.  HANGARED UNTIL 5/97.  HAIL STORM PUNCHED HOLES IN ALL FABRIC COVERED SURFACES.  SAME MODEL AIR	CRAFT WITH 23 YEAR OLD FABRIC HAD NO HOLES AND WAS PARKED ALONG SIDE.  FABRIC APPEARS TO BE WEAK, BUT PUNCH TEST INDICAT	ES GOOD CONDITION.  PAINT IS DARK IN COLOR.  RECOMMEND REVIEW BY STC HOLDER.				1	L	7	1 	3O				1A3     					 
1997091100291	19970911	00291	CE  	1997	9	11	97ZZZX3899       	1	19970821	G	2720	355241066	PUSHROD         			BEECH 	35    	K35         	1151524	CE  										LT RUDDERVATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5NB	5045 				D5956				WHILE C/W AD 97-06-11, LEFT PUSH ROD WAS FOUND FULL OF WATER.  UPON PAINT REMOVAL IN PREPARATION FOR DYE/PEN INSPECTION,	 AN APPROXIMATE .25 INCH HOLE WAS FOUND CORRODED THROUGH THE WALL THICKNESS AT THE LOWER FORWARD END OF THE ROD.  THIS A	REA WAS NOT VISIBLE DURING NORMAL INSPECTION AS IT HAD NOT YET PENETRATED THE PAINT COATING.  THERE WAS APPROXIMATELY 10	 PERCENT OF THE CROSS-SECTION AREA MISSING.			1	L	7	1 	3O				3A15    					 
1997091100292	19970911	00292	CE  	1997	9	11	97ZZZX3900       	1	19970818	G	5510	0531037	REINFORCEMENT   			CESSNA	172   	172P        	2072436	CE  										HORIZ STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	54381	3858 				17274968				UPON INSPECTION PER SB 94-8-A, THE SKIN WAS FOUND CRACKED.  THE SKIN AND REINFORCEMENT WERE REPLACED WITH NEW PARTS.  NO	 OTHER PROBLEMS FOUND.					1	H	7	1 	3O			NT	3A12    					 
1997091100293	19970911	00293	CE  	1997	9	11	97ZZZX3901       	1	19970818	G	5512	053200123	SKIN            			CESSNA	172   	172P        	2072436	CE  										HORIZ STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	54381	3858 				17274968				UPON INSPECTION PER SB 94-8-A, THE SKIN WAS FOUND CRACKED.  THE SKIN AND REINFORCEMENT WERE REPLACED WITH NEW PARTS.  NO	 OTHER PROBLEMS FOUND.					1	H	7	1 	3O			NT	3A12    					 
1997091100295	19970911	00295	SO  	1997	9	11	97ZZZX3902       	1	19970816	G	7810	653332	EXHAUST CLAMP   			PIPER 	PA28  	PA28R201T   	7102813	SO  										TURBO EXHAUST	FAILED          	C		A		O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	777JD	2752 				28R7703156				TURBOCHARGER EXHAUST CLAMP BOLT PARTED IN-FLIGHT.  LOST EGT AND LANDING GEAR STATUS LIGHTS DUE TO 7 WIRES BEING BURNED O	N FIREWALL.  WAS ABLE TO MAKE PRECAUTIONARY LANDING WITHIN 5 MINUTES AT AIRPORT.  SUBMITTER STATED PROBLEM LIKELY METAL 	FATIGUE DUE TO AGE AND HEAT CYCLING.  SUBMITTER RECOMMENDS THAT ALL SUCH CLAMPS IN SERVICE THIS LONG.  (20 YEARS) BE REP	LACED AS SOON AS POSSIBLE.			1	L	7	1 	3O				2A13    					 
1997091100296	19970911	00296	SO  	1997	9	11	97ZZZX3903       	2	19970821	G	7322	105284	CARBURETOR      	FACET       	MA45        	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					BUTTERFLY VALVE	STUCK           	D		A		O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	06	95868		877  			18266665	230582R			PILOT REPORTED AT CRUISE, PREPARED FOR DESCENT, THROTTLE STUCK FUEL OPEN.  AIRCRAFT LANDED AND SHUT OFF ENGINE WITH MIXT	URE.  UPON INSPECTION, DISCONNECTED THROTTLE, FOUND PROBLEM TO BE IN CARBURETOR.  BUTTERFLY VALVE STUCK FULL, WILL NOT C	LOSE.  CARBURETOR REPAIR SHOP RESULTS:  CARBURETOR FULL STOP EXCESSIVE WEAR ALLOWS BUTTERFLY VALVE TO TRAVEL FURTHER THA	N NORMAL JAMMING PIN INSIDE BODY; THUS, LOCKING IN FULL THROTTLE POSITION.			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997091100297	19970911	00297	CE  	1997	9	11	97ZZZX3904       	1	19970807	G	7602	5038901019	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  										MIX CONTROL	DEFECTIVE       	G				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			GL	03	8590R					TH645				DURING FLIGHT, PILOT COULD NOT GET PROPER MIXTURE CONTROL ON LEFT ENGINE.  P.I.C. SHUT ENGINE OFF AND LANDED AIRCRAFT WI	THOUT ANY FURTHER INCIDENT.  MECHANIC DISCOVERED DEFECTIVE MIXTURE CONTROL CABLE.  CABLE WAS REMOVED AND REPLACED.  AIRC	RAFT OPS CHECKED OK.				1	L	7	2 	3O			 	3A16    					 
1997091100298	19970911	00298	SO  	1997	9	11	97ZZZX3905       	1	19970818	G	3411	6391334	HOSE            			PIPER 	PA44  	PA44180     	7104402	SO  										PITOT/STATIC	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	921ER	940  				4496008				AIRSPEED INDICATION REPORTED READING LOW.  FOUND EACH FLEX HOSE RELATED TO SYSTEM CRACKED AND SPLIT.  REPLACED HOSES.  O	PERATION NORMAL ON LEAK CHECK.					1	L	7	2 	3O				A19S0   					 
1997091100299	19970911	00299	WP  	1997	9	11	97ZZZX3906       	1	19970827	G	2436	598711	RESISTOR        		707306A     	DOUG  	DC10  	DC10*       		WP  										CSD LOAD CONTROL	FAILED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		579  			1011					RESISTORS FAILED CAUSING CSD LOAD CONTROLLER TO FAIL AND MAINTAIN PROPER CYCLES.  THIS IS THE SECOND TYPE OF THIS FAILUR	E.  ORIGINAL PARTS CAME FROM MANUFACTURER.					2	L	7	3 	4F				A22WE   					 
1997091100300	19970911	00300	WP  	1997	9	11	97ZZZX3907       	1	19970827	G	2436	59046562	RESISTOR        		707306A     	DOUG  	DC10  	DC10*       		WP  										CSD LOAD CONTROL	FAILED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		579  			1011					RESISTORS FAILED CAUSING CSD LOAD CONTROLLER TO FAIL AND MAINTAIN PROPER CYCLES.  THIS IS THE SECOND TYPE OF THIS FAILUR	E.  ORIGINAL PARTS CAME FROM MANUFACTURER.					2	L	7	3 	4F				A22WE   					 
1997091100301	19970911	00301	WP  	1997	9	11	97ZZZX3908       	1	19970826	G	3242	2445902	DISC            	BFGOODRICH  	21565       	DOUG  	DC8   	DC8*        		WP  										BRAKE ASSY	BROKEN          	B			XC4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19		2197 			1476					ON RECEIPT OF BRAKE ASSEMBLY, DISC WAS FOUND BROKEN IN HALF.  HAVE WITNESSED NUMEROUS FAILURES AND DAMAGES.  DESIGN FLAW	 WHEN A PART BREAKS IN HALF.					2	L	7	4 	4J			F	4A25    					 
1997091100302	19970911	00302	NM  	1997	9	11	97ZZZX3909       	1	19970709	G	2820	25W653120692	FUEL LINE       			ISRAEL	1125  	1125        		NM  										FUEL SYSTEM	BURST           	B		A	JGVR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	09	166RM	3296 				047				WHILE PRESSURIZING THIS FUEL LINE WITH AIR TO FIND A LEAK IN A DIFFERENT AREA, THIS LINE BURST DUE TO IT CHAFING ON ANOT	HER LINE.  THIS LINE NORMALLY CARRIES ABOUT 300 PSI, AND HAD IT BURST IN-FLIGHT, IT WOULD HAVE SPRAYED THE TAILCONE WITH	 FUEL.  REPLACED THE LINE AND PROVIDED SEPARATION.  SUGGEST THAT THIS AREA SPECIFICALLY GETS LOOKED AT ON THE INSPECTION	 GUIDE.  ALSO, INFORMED GALAXY AEROSPACE TECHNICAL PEOPLE.			2	L	7	2 	4F			RT	A16NM   					 
1997091100303	19970911	00303	CE  	1997	9	11	97ZZZX3910       	1	19970710	G	5610	1014200807	WINDOW          			BEECH 	200   	200BEECH    	1152920	CE  										PILOT'S STORM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	174PW					BB64				ON AAIP INSPECTION, FOUND PILOT'S STORM WINDOW WITH MANY CRACKS AROUND LATCH ON WINDOW AND ONE CRACK FROM HOLE-TO-HOLE W	HERE TWO SCREWS SECURE LATCH.					1	L	7	2 	4T				A24CE   					 
1997091100304	19970911	00304	NE  	1997	9	11	97ZZZX3911       	3	19970822	G	6111	RFC11T	BLADE           		14RF9       	SAAB  	SF340 	340B        	7860101	EU  						HAMSTD	14RF	14RF19      	NE  	FILLET/SHANK	CRACKED         	B			BN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	282AE	11947			864106	340B282				AFTER DYE PENETRANT INSPECTION, TWO CRACKS WERE FOUND ON SHANK OUTSIDE DIAMETER OF BLADE.  DEFECT MEASURES AT .476 INCH 	LENGTH BY .143 INCH WIDE.					2	L	7	2 	4T			RT	A52EU   		6	C	P11NE	 
1997091700002	19970917	00002	SO  	1997	9	17	97ZZZX3912       	1	19970731	G	2430	38B934B	COVERTER        			GULSTM	G1159 	GIV         	3980115	SO  										RIGHT SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	200PM				N1197	1147				AFTER STARTING RIGHT ENGINE, THE RT A.C. MAIN BUSS WOULD DROP OFF LINE AND THE A.C. RESET LIGHT WOULD COME ON.  SELECTIN	G THE RT CONVERTER 'ON' WOULD POWER THE RT BUSS, BUT COULD NOT RESET A.C. RESET LIGHT.  A.C. WAS SHUT DOWN AND TROUBLESH	OT TO RT POWER CONVERTER.  AFTER REMOVING CONVERTER, FOUND BURN MARK ON OUTBOARD SIDE OF CONVERTER COVER.				2	L	7	2 	4F			RT	A12EA   					 
1997091100307	19970911	00307	CE  	1997	9	11	97ZZZX3915       	1	19970825	G	3240	AP6644	LINING          			BEECH 	58    	58          	1152740	CE  										BRAKE SHOE	MISDRILLED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	329H					TH219				THE ATTACHMENT HOLES OF BRAKE LININGS ARE IN DIFFERENT LOCATIONS FROM ONE BRAKE LINE TO ANOTHER.  ON CERTAIN LININGS, IT	 WILL NOT SIT FLUSH ON THE BRAKE SHOE.					1	L	7	2 	3O				3A16    					 
1997091100308	19970911	00308	CE  	1997	9	11	97ZZZX3916       	1	19970827	G	2810	S24851	VALVE           			CESSNA	150   	152         	2071835	CE  										FUEL DRAIN	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	4711H					15283968				FUEL DRAIN VALVE DELIVERED NEW FROM CESSNA WOULD NOT SEAT PROPERLY.  PART MANUFACTURERED BY AUTO VALVE INC, DAYTON, OHIO	 45427.  CURE DATE 1Q96.  ASSY DATE 1Q97.					1	H	7	1 	3O			NT	3A19    					 
1997091100309	19970911	00309	EA  	1997	9	11	97ZZZX3917       	2	19970821	G	7414	M3975	COIL            	SLICK       		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					LT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	68956	551  				15282415				INSPECTION FOUND BAD COIL IN MAGNETO.  MAGNETO IN LEFT POSITION.  AIRCRAFT ENGINE WOULD DIE WHEN LEFT MAG WAS SELECTED.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997091100310	19970911	00310	SO  	1997	9	11	97ZZZX3918       	1	19970818	G	5521	4007514	SPAR            			PIPER 	PA31  	PA31325     	7103105	SO  										LT ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	83PA	3244 				318112050				DURING INSPECTION PER PIPER SB 998A, FOUND CRACKED IN UPPER FLANGE RADIUS AS DESCRIBED.  NO CRACKS IN AREA OF OUTBOARD H	INGE ATTACH REINFORCEMENT.					1	L	7	2 	3O				A20SO   					 
1997091100311	19970911	00311	SO  	1997	9	11	97ZZZX3919       	1	19970818	G	5521	4007516	SPAR            			PIPER 	PA31  	PA31325     	7103105	SO  										RT ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	83PA	3244 				318112050				DURING INSPECTION PER PIPER SB 998A, FOUND CRACKS IN BOTH UPPER AND LOWER FLANGE RADIUS AS DESCRIBED.  NO CRACKS IN AREA	 OF OUTBOARD HINGE ATTACH REINFORCEMENT.					1	L	7	2 	3O				A20SO   					 
1997091100312	19970911	00312	EA  	1997	9	11	97ZZZX3920       	2	19970818	G	7322	CF30768	FLOAT           	FACET       	105253      	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					CARBURETOR	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			WP	07	9635B		581  		1096	172RG0933	L2982536A			PILOT REPORTED ENGINE QUIT ON FINAL APPROACH OVER RUNWAY.  DELIVERED TO MAINTEANCE, UNABLE TO GET GOOD RUN-UP.  DISCOVER	ED CARBURETOR FLOAT FULL OF FUEL.  REPLACED WITH SERVICEABLE FLOAT.  ENGINE OPS CHECK GOOD.					1	H	7	1 	3O	3	O		3A17    	E286				 
1997091100313	19970911	00313	CE  	1997	9	11	97ZZZX3921       	1	19970826	G	2730	5052447413	PUSH ROD        			BEECH 	90    	C90A        	1152911	CE  										LT ELEV TRIM	BROKEN          	B		A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	1NP	3489 				LJ1289				PILOT NOTICED LEFT ELEVATOR TRIM TAB LOOSE AND ROD BROKEN.  INVESTIGATION REVEALED BUSHING AT TAB ATTACH SEIZED AND APPL	IED SIDE LOAD ON PUSH ROD.  ROD BROKE AT BOTTOM OF THREADS OF ADJUSTMENT END.  FURTHER INVESTIGATION REVEALED ROD HAD EX	ISITNG CRACK APPROXIMATELY ONE-THIRD DIAMETER.  INSTALLED NEW ROD ASSY AND FUNCTION CHECKED OK.				1	L	7	2 	3T			RT	3A20    					 
1997091100314	19970911	00314	NE  	1997	9	11	97ZZZX3922       	2	19970815	G	8530	399359	CYLINDER        			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 1 CYL HEAD	CRACKED         	H			FYKG	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SO	11	4411S		1045 			3010071	519053			ENGINE LOST POWER AFTER TAKEOFF.  MADE FORCED LANDING INTO FIELD.  SUBSTANTIAL DAMAGE TO AIRCRAFT.  PILOT HAS MINOR INJU	RIES.  INVESTIGATION HAS REVEALED THAT NR 1 CYLINDER HEAD CRACKED INTO 2 PIECES.  SUBMITTER SUBMITTED SAFETY RECOMMENDAT	ION FOR EVALUATION AND ACTION.				1	L	7	1 	3R	3	R		A9SW    	5E2				 
1997091100315	19970911	00315	GL  	1997	9	11	97ZZZX3923       	1	19970807	G	5711		RIB             			AMTR  	EMRAUD	EMERAUDSUPER		GL  										WING SPAR	SEPARATION      	H	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	2FOR	1100 								INVESTIGATION FOR RIB SEPARATION FROM WING SPAR FOUND THE DESIGN OF LANDING GEARINSTALLATION TO BE A CAUSAL FACTOR.  THI	S INSTALLATION (EXTENDING FORWARD AND ATTACHED TO MAIN SPAR) INDUCES A TWISTING MOTION ON THE MAIN SPAR DURING LANDING. 	 A HARD 3-POINT OR OFF-FIELD LANDING ATTEMPTS TO TWIST THE SPAR.  THE TWISTING MOMENT IS ONLY RESTRAINED BY THE SECURITY	 OF THE GLUED RIBS.  FAILURE MODE IS SUBTLE SHOWING UP AS SQUEEKS IN THE WING WHEN ROCKING THE WING DURING THE PRE-FLIGH	T, BAGGINESS OR WRINKLES IN THE FABRIC, OR POSSIBLY WING LOW IF PROGRESSED FAIRLY FAR ALONG (NUMEROUS WING RIBS HAVING S	EPARATED FROM THE SPAR).	1	L	7	1 	3O				EXPA1L71					 
1997091100316	19970911	00316	EU  	1997	9	11	97ZZZX3924       	1	19970811	G	3250		STEERING COLLAR 			SLNSBY	T67   	T67M260     	8323006	EU  										NLG STRUT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		900  								DURING 100-HOUR INSPECTION, THE NOSE STEERING COLLAR ON NOSE STRUT WAS FOUND CRACKED.  A ONE-TIME INSPECTION WAS PERFORM	ED FOR THE REST OF THE FLEET (57).  EIGHTEEN AIRCRAFT WERE FOUND WITH NOSE WHEEL STEERING COLLAR CRACKED.  UNKNOWN CAUSE	 AND NO RECOMMENDATION AT THIS TIME.				1	L	7	1 	3O			NT	A73EU   					 
1997091100321	19970911	00321	WP  	1997	9	11	97ZZZX3927       	2	19970814	G	7250	8650821	MAIN SHAFT NUT  			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					AFT RETENTION	FAILED          	B		A	DSC2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	46KC					T332	P35090C			TURBINE (MAINSHAFT) RETENTION NUT FAILED (CRACKED IN HALF) DURING OPERATION OF ENGINE ON THE GROUND.  IT WAS OBSERVED TH	E PROPELLER WOULD NOT ROTATE FREELY AND THE ENGINE HAD SEIZED.  UPON DISASSEMBLY OF ENGINE, OBSERVED THAT ONE THREAD OF 	THE NUT (IN TWO PIECES) WAS COMPLETELY MISSING.  SUBMITTER STATED FAILURE OF THIS NUT DURING FLIGHT OPERATION WILL RESUL	T IN ENGINE FAILURE AND/OR UNCONTAINED FAILURE OF THE ENGINE.  ENGINE TSN:  3,012.0 HRS; CSN:  4,525 HRS; TSO:  179.1 HR	S.  CSO:  190.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
1997091100434	19970911	00434	CE  	1997	9	11	97ZZZX3934       	1	19970806	G	5711	0024300189	WEB             			BEECH 	33    	F33A        	1151425	CE  										CARRY THRU SPAR	CRACKED         	B		A	IYOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1568P					CE1298				INSPECTION FOUND FORWARD SPAR CARRY-THROUGH CRACKED.  A CRACK OF 1.3 INCHES IN LENGTH WAS DISCOVERED IN MID-SECTION OF L	OWER BEND RADIUS IN A VERTICAL DIRECTION FOLLOWING THE BEND.  THE CRACK SEEMS TO OCCUR IN THE AREA OF THE FORWARD SUPPOR	T (RT SIDE).  POSSIBLE CAUSE IS HARD LANDINGS.  SUBMITTER STATED POSSIBLE FIX, MANUFACTURE WEB WITH A MUCH THICKER/STRON	GER ALLOY.  CRACK WAS STOP-DRILLED AS SPECIFIED IN AD NR 95-04-03 WHICH DOES NOT APLY TO THIS SERIAL NUMBER.			1	L	7	1 	3O				3A15    					 
1997091100435	19970911	00435		1997	9	11	97ZZZX3935       	4	19970822	G	2561	PO201105	LIFE VEST       	EAAEROMARINE																SEAM	FAILED TEST     	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					J31311					LIFE VEST FAILED THE MANUFACTURER'S 2-POUND PSI TEST.																			 
1997091100436	19970911	00436		1997	9	11	97ZZZX3936       	4	19970822	G	2561	PO201105	VEST            	EAAEROMARINE																SEAM	FAILED TEST     	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					J31169					LIFE VEST FAILED THE MANUFACTURER'S 2-POUND PSI TEST.																			 
1997091100437	19970911	00437	EA  	1997	9	11	97ZZZX3937       	3	19970803	G	6110		PROPELLER       			PIPER 	J3    	J3C65       	7100510	SO  						SNSNCH	76AM	M76AM       	EA  	ENGINE	DEPARTED        	G				A				UNSCHED LANDING         				E	C		VIBRATION/BUFFET          	F.O.D.                    		CR	CRUISE         	1			NM	04	1477N	2732 	96   			23141		3595		THIRTY MINUTES AFTER TAKEOFF, PILOT REPORTS VIBRATION AND THEN PROPELLER SEPARATED FROM ENGINE.  PILOT SAYS NOT SURE IF 	BIRD STRIKE OR PART FAILURE.  AIRCRAFT LANDED WITHOUT INJURY TO PILOT OR FURTHER DAMAGE TO AIRCRAFT.					1	H	7	1 	3O				A691    		5	N	1P210	 
1997091100438	19970911	00438		1997	9	11	97ZZZX3938       	4	19970812	G	3430	1N6391	DIODE           			CESSNA	172   	172RG       	2072438	CE  										ALTERNATOR BUS	FAILED          	B			WIWR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			WP	07	361ES					172R80011				ALTERNATOR IN-FLIGHT FAILURE TOGETHER WITH FAILURE OF NAV 1 AND GPS.  ALTERNATOR FIELD BREAKER OPEN.  REPLACED TWO SHORT	ED DIODES WITH CESSNA P/N 1N6391.  AIRCRAFT WITH ONE HOUR TEST FLIGHT WAS UNEVENTFUL AND AIRWORTHY WITH ALL ELECTRICAL D	EVICES WORKING.				1	H	7	1 	3O				3A17    					 
1997091100439	19970911	00439	GL  	1997	9	11	97ZZZX3939       	1	19970803	G	3240	105	MASTER CYLINDER 			AMTR  	DESIGN	ONEDESIGN   	05616SA	GL  										BRAKE	MALFUNCTIONED   	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	15	62790	44   				940144				UPON LANDING, LEFT BRAKE LOCKED-UP.  UPON INSPECTION, FOUND PARKING BRAKE LEVER MOVED UP BLOCKING PRESSURE.  RELEASED LE	VER TO OFF POSITION, BRAKES RETURNED TO NORMAL.  SUBMITTER STATED PARKING BRAKE LEVERS WERE NOT USED AND SHOULD HAVE BEE	N SAFETIED TO OPEN POSITION OR HOOKED UP FOR USE.				1	L	7	1 	3O			NC	EXPA1L71					 
1997091100440	19970911	00440	SO  	1997	9	11	97ZZZX3940       	1	19970811	G	3230	701112245	RELAY           			PIPER 	PA32  	PA32R301    	7103218	SO  										MLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	09	96KC	30   				3246087				GEAR IN-TRANSIT LIGHT CAME ON IN-FLIGHT WHEN GEAR SELECTOR HANDLE IN UP POSITION.  GEAR CONTROL/LIGHT CIRCUIT BREAKER TR	IPPED AND COULD NOT BE RESET.  GEAR MANUALLY EXTENDED.  FOUND UP GEAR RELAY SHORTED.  LANDING GEAR MOTOR HAD STAYED ON C	AUSING NOSE GEAR ACTUATOR TO BLOW SEALS AND DUMP ALL FLUID FROM POWERPACK CAUSING PUMP TO FAIL.  PRESSURE SWITCH DID NOT	 SHUT MOTOR OFF.  FOUND 12-VOLT GEAR UP AND DOWN RELAYS IN A 24-VOLT SYSTEM.			1	L	7	1 	3O				A3SO    					 
1997091100441	19970911	00441	EU  	1997	9	11	97ZZZX3941       	1	19970828	G	3230		SWITCH          			AMD   	FALC20	FALCOND     	2720304	EU  										UPLOCK	OUT OF RIG      	B			RO5R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	2FOR					DA20				AIRCRAFT IS EGYPTIAN REGISTERED.  GEAR DOORS ON LANDING GEAR WOULD NOT RETRACT WHEN GEAR WAS RETRACTED.  CHECKED UPLOCK 	SWITCHES AND FOUND THE NOSE GEAR UPLOCK SWITCH WOULD NOT CLOSE TO ALLOW THE GEAR DOORS TO CLOSE.  ALSO, FOUND THE MECHAN	ICAL UNLOCK CONTROLS MOVED TOO HARD.  LUBED MECHANICAL UNLOCK AND MOVES OKAY.  COMPLETED A RETRACT TEST AND GEAR PERFORM	ED PROPERLY.			2	L	7	2 	4F				A7EU    					 
1997091100442	19970911	00442	EA  	1997	9	11	97ZZZX3942       	1	19970812	G	8110	12579	SUPERCHARGER    			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	BEARING FAILED  	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	48395	672  				1628	21888			PLASTIC BEARING CAGE FAILED.  CAUSED BEARING TO FAIL RESULTING IN TOTAL SUPERCHARGER FAILURE.						1	Q	7	1 	3R	3	R		1A16    	5E2				 
1997091100443	19970911	00443	CE  	1997	9	11	97ZZZX3943       	1	19970826	G	3250	358250522	IDLER ARM       			BEECH 	45    	A45         	1152006	CE  										STEERING ROD	FROZEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	34MR	5308 				G39				WHILE TAXIING, A SQUEAK WAS HEARD FROM THE NOSE WHEEL AREA.  WITH THE AIRCRAFT ON JACKS, THE NOISE WAS ISOLATED TO THE S	TEERING ROD IDLER ARM, P/N 35-825052-2.  THE ONLY WAY TO INSPECT THIS PART IS TO REMOVE THE ENTIRE COLLAR AND SHAFT.  TH	E IDLER ARM SHOULD BE FREELY MOVABLE ON THE SHAFT.  IN THIS CASE, IT WAS FOUND TO BE FROZEN.  ONLY AFTER SOAKING IN PENE	TRATING OIL FOR SEVERAL DAYS AND THEN USING CONSIDERABLE FORCE, WAS THE ARM SEPARATED FROM THE SHAFT.			1	L	7	1 	3O				5A3     					 
1997091100444	19970911	00444	CE  	1997	9	11	97ZZZX3944       	1	19970829	G	7120		MOUNT           			CESSNA	210   	T210N       	2073456	CE  										ENG LT REAR	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6621A	580  				21063559				NR 2 CYLINDER REMOVED FOR LOW COMPRESSION.  THIS EXPOSED LEFT REAR MOUNT.  IT WAS FOUND TO HAVE WEAR IN IT CAUSED BY PRO	PELLER CONTROL CABLE HOUSING CHAFING AGAINST IT.  THE DAMAGE WAS CLOSE TO THE CUT-OUT FOR THE BARREL NUT, SO TCM RECOMME	NDED CHANGING MOUNT.  SUBMITTER STATED THIS AREA IS VERY DIFFICULT TO SEE WHEN ENGINE INTAKE AND EXHAUST SYSTEM ARE INST	ALLED.  THERE WAS NO PROVISION FOR SUPPORT OF THE PROPELLER CONTROL IN THIS AREA.			1	H	7	1 	3O				3A21    					 
1997091100445	19970911	00445	CE  	1997	9	11	97ZZZX3945       	1	19970829	G	6120	643935	BRACKET         			CESSNA	210   	T210N       	2073456	CE  										ENG LT REAR	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6621A	580  				21063559				NR 2 CYLINDER REMOVED FOR LOW COMPRESSION.  THIS EXPOSED LEFT REAR MOUNT.  IT WAS FOUND TO HAVE WEAR IN IT CAUSED BY PRO	PELLER CONTROL CABLE HOUSING CHAFING AGAINST IT.  THE DAMAGE WAS CLOSE TO THE CUT-OUT FOR THE BARREL NUT, SO TCM RECOMME	NDED CHANGING MOUNT.  SUBMITTER STATED THIS AREA IS VERY DIFFICULT TO SEE WHEN ENGINE INTAKE AND EXHAUST SYSTEM ARE INST	ALLED.  THERE WAS NO PROVISION FOR SUPPORT OF THE PROPELLER CONTROL IN THIS AREA.			1	H	7	1 	3O				3A21    					 
1997091100447	19970911	00447	CE  	1997	9	11	97ZZZX3947       	1	19970801	G	2150	1155550259	SHAFT SPLINES   		115555020605	BEECH 	300   	300BEECH    	1152930	CE  										AIR COND COMP	WORN            	B	S		XE9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	642JL	255  				FA30				AFTER PILOT COMPLAINED OF NO AIR CONDITIONING, TROUBLESHOT AND FOUND QUILL SHAFT FOR COMPRESSOR DRIVE ON RT ENGINE HAD T	HE AFT SPLINES ON SHAFT WORN OFF AND SPLINES ON PULLEY WORN DOWN.  THERE WAS NO EVIDENCE OF BEARINGS AT PULLEY DRIVE SEI	ZING OR WORN OUT.  SPLINES AT ACCESSORY CASE END WERE GOOD.  THIS IS THE SECOND TIME IN 250 HOURS THAT THIS HAS HAPPENED	.			2	L	7	2 	4T				A24CE   					 
1997091100448	19970911	00448	SW  	1997	9	11	97ZZZX3948       	1	19970829	G	7160	BA81031	FILTER          			BBAVIA	8     	8GCBC       	1220803	SW  										ENGINE INDUCTION	DEFECTIVE       	B	L		KO2R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CE	01	5063W	1    				33L80				ENGINE AIR FILTER WAS CHANGED DURING ANNUAL.  EN ROUTE, AIRCRAFT ENGINE RAN ROUGH.  OWNER WAS ADVISED TO CHANGE AIR FILT	ER.  AFTER NEW FILTER INSTALLED, POWER RUN DOWN RUNWAY WAS MADE AND ENGINE PERFORMANCE NORMAL.   BRACKETT FILTERS BA 810	3-1 REMOVED AND WAS REPLACED WITH A P10-6150 FILTER.				1	H	7	1 	3O				A21CE   					 
1997091100449	19970911	00449	CE  	1997	9	11	97ZZZX3949       	1	19970829	G	7160	BA2510	FILTER          			CESSNA	182   	R182        	2072734	CE  										ENGINE INDUCTION	DEFECTIVE       	B			KO2R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CE	01	4773S	59   				R18201423				CRUISE AT 7,500 FEET AND ENGINE ROUGHNESS NOTED.  MAGNETO CHECK OK.  LEANING PROCEDURES DIFFERENT THAN NORMAL.  FOUND IN	DUCTION FILTER TO BE AT FAULT.  CHANGED BRACKETT P/N BA 2510 FOR A CESSNA P13-1E67 AND OPERATION NORMAL.					1	H	7	1 	3O			RT	3A13    					 
1997091800250	19970918	00250	WP  	1997	9	18	97ZZZX3968       	1	19970825	G	5511		RIB             			DOUG  	EA3B  	EA3B        	3026209	WP  										HORIZ STAB LE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	575HA					144865				DURING REPAIR TO THE LEADING EDGE OF THE HORIZONTAL STABILIZER, DISCOVERED THAT 13 OF 15 RIBS IN THE INBOARD SECTION (RT	 LEADING EDGE) HAD CRACKS AT THE TRAILING EDGE IN THE RADIUS OF THE BEND IN THE RIB.  SUBSEQUENT INSPECTION OF THE LT SI	DE REVEALED ONLY ONE CRACKED RIB.  REMOVAL AND INSPECTION OF SPARE UNIT SHOWED 12 OF THE 15 INBOARD RIBS CRACKED.				2	H	7	2 	4J			RT	EXPA2H72					 
1997091800251	19970918	00251	WP  	1997	9	18	97ZZZX3969       	1	19970828	G	5350		RADOME          			DOUG  	EA3B  	EA3B        	3026209	WP  										ACFT BELLY	DEPARTED        	D		A		O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			WP	01	575HA				001	144865				DURING THE FIRST TEST FLIGHT OF THE NEW BELLY RADOME FOR TIER II:  WHILE IN A HIGH SPEED DESCENT OUT OVER THE OCEAN, THE	 RADOME DEPARTED THE AIRCRAFT.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  INVESTIGATION INTO THE INCIDENT REVEALED THAT A S	HOCK WAVE FORMED ON THE RADOME WHICH CHANGED THE LOAD FACTORS BEYOND THE ORIGINAL ANALYSIS FINDINGS.  THE AFT SECTION OF	 THE RADOME WAS PULLED DOWN TEARING OUT THE MOUNTING FASTENERS RESULTING IN A BREAK-UP OF THE ENTIRE RADOME.			2	H	7	2 	4J			RT	EXPA2H72					 
1997091800252	19970918	00252	GL  	1997	9	18	97ZZZX3970       	1	19970629	G	2820		FILTER          			AMTR  	NIEUPO	NIEUPORT12  	0564041	GL  										LT CARBURETOR	PLUGGED         	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	23	169RD					005				FUEL LINE INADVERTENTLY LEFT OPEN FOR 2 MONTHS DURING OTHER REPAIRS.  LINE ASSEMBLED WITHOUT PROPER INSPECTION.  POST-AC	CIDENT INSPECTION REVEALED UNKNOWN CONTAMINATE IN FILTER OF LT CARBURETOR.  RECOMMEND ALWAYS PLUGGING LINES DURING DIS-A	SSEMBLY.  ALWAYS PURGE LINES AND CHECK FLOW PRIOR TO ASSEMBLY.  SUSPECT MUD/WASP NEST IN FUEL LINE.				1	Q	7	1 	3O			NC	EXP1Q71 					 
1997091800254	19970918	00254	CE  	1997	9	18	97ZZZX3971       	1	19970129	G	3211	24411009	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	172CM	3254 				172RG0787				DURING A MAINTENANCE RUN, DISCOVERED THE RIGHT BRAKES HAD FAILED.  INVESTIGATION REVEALED THE BELLY WAS COVERED IN HYDRA	ULIC FLUID.  INSPECTION OF RT MAIN GEAR PIVOT DISCLOSED HYDRAULIC FLUID LEAKING FROM THE SPLINES OF PIVOT.  PREVIOUS EXP	ERIENCE WITH CRACKS ON THE SPLINES INDICATES A COMPLETE FAILURE OF THE PIVOT ASSEMBLY WHICH WILL NOT ALLOW GEAR TO EXTEN	D.  SUBMITTER RECOMMENDS REMOVAL OF ACTUATOR AND INSPECTION FOR CRACKS FROM CESSNA SEB 90-1R2 AT LEAST FIRST 2,000 T.I.S	. AND EACH 250 HOURS THEREAFTER.		1	H	7	1 	3O				3A17    					 
1997091800255	19970918	00255		1997	9	18	97ZZZX3972       	4	19970829	G	2562		G SWITCH        	ACK         	E01         	CESSNA	182   	182P        	2075816	CE  										ELT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	182AP	291  			018504	18261843				G-SWITCH WAS FOUND INOPERATIVE DURING INSPECTION PER FAR 91.207.  ELT IS 2 YEARS OLD, ELT DID FUNCTION OK IN 'ON' POSITI	ON.					1	H	7	1 	3O			NT	TA13    					 
1997091800256	19970918	00256	EA  	1997	9	18	97ZZZX3973       	2	19970703	G	7414	M3525	COIL            	SLICK       	4281        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	2182B	600  			110289	287990124	L2565336A			SUBMITTER STATES IT IS COMMON FOR THE M3525 ORANGE MAGNETO COILS TO FAIL.  THE REPLACEMENT COILS ARE BLACK M3975 OR K397	5 AND HAVE BEEN AVAILABLE FOR A FEW YEARS.					1	L	7	1 	3O	3	O		2A13    	E286				 
1997091800257	19970918	00257	EA  	1997	9	18	97ZZZX3974       	2	19970904	G	7414		CAM             	SLICK       	4347        	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					MAGNETO	FRACTURED       	B			E96R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	09	444DJ	60   			9411	7000075				PILOT REPORTED ROUGH ENGINE OPS AND HIGH EGT.  INSPECTION REVEALED RIGHT MAGNETO CAMSHAFT FRACTURED AND SEPARATED BELOW 	CAM AT OUTER BUSHING.  FRACTURED SURFACE DISPLAYED EVIDENCE OF PREVIOUS FRACTURE.  SIXTY HOURS TIME SINCE NEW.  AIRCRAFT	 TOTAL TIME:  2,202.9 HOURS.  CORROSION WAS EVIDENT ON FRACTURE SURFACE.  FAILURE OCCURED 8-29-97.				1	L	7	1 	3O	3	O		2A3     	E286				 
1997091800258	19970918	00258	GL  	1997	9	18	97ZZZX3975       	1	19970802	G	5711		SPAR            			AMTR  	BG12A 	BG12A       	79001CG	GL  										RT WING ATTACH	BROKEN          	G		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	01	5516V	400  				1026				DURING TOW OPERATION, WING CENTER SECTION SPAR FAILED NEAR RIGHT FUSELAGE ATTACH POINT.  WOOD DETERIORATION DUE TO AGE A	ND WATER ACCUMULATION POSSIBLE.  HARDWARE FOUND RUSTY.  AIRCRAFT WAS BEING OPERATED OVER DESIGN GROSS WEIGHT WITH AN AFT	 C.G.  CONDITIONS OF AIRCRAFT USE AND STORAGE FOR PREVIOUS 12 YEARS UNKNOWN.  SUBMITTER RECOMMENDS THOROUGH CONDITION IN	SPECTIONS ON WOOD AIRCRAFT ESPECIALLY AFTER STORAGE.			1	L	0	0 	0 			0	EXPA1L00					 
1997091800259	19970918	00259	SO  	1997	9	18	97ZZZX3976       	1	19970813	G	7170	84029017	COLLECTOR TANK  			PIPER 	PA46  	PA46350P    		SO  										RT WHEEL	CRACKED         	B		A	SO5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	03	64TW	79   				4636054				TOP INBOARD EDGE WELD CRACKED APPROXIMATELY 2 INCHES ALLOWING FUEL TO LEAK INTO WHEEL AREA.  BRAKES DIRECTLY BEHIND COLL	ECTOR TANK WHEN GEAR RETRACTED.  SUBMITTER STATED POSSIBLE CAUSE:  OIL CANNING OF TANK OR EXCESSIVE HEAD PRESSURE WHEN W	ING TOPPED OFF.				1	L	7	1 	3O			RT	A25SO   					 
1997091800260	19970918	00260	SO  	1997	9	18	97ZZZX3977       	2	19970818	G	8520		CRANKSHAFT      			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					NR 4 JOURNAL	BROKE           	H				O				OTHER                   				Y	E		ENGINE STOPPAGE           	VIBRATION/BUFFET          		CR	CRUISE         	1			SW	99	6620Z	2138 	730  			U20606347	520431			PILOT REPORTED A STRONG VIBRATION FOLLOWED BY A LOUD MECHANICAL BANG IN THE ENGINE DURING FLIGHT.  SECONDS LATER THE ENG	INE ABRUPTLY STOPPED.  AN ENGINE 'TEAR DOWN' INSPECTION WAS PERFORMED AND REVEALED THE CRANKSHAFT BROKE AT THE NR 4 'CRA	NKSHAFT MAIN BEARING JOURNAL'.				1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1997091800261	19970918	00261	SO  	1997	9	18	97ZZZX3978       	2	19970725	G	8520	A830M1	CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 2 MAIN JRNL	FAILED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	9412Z	1383 				420606473	574416			CRANKSHAFT SEPARATED BETWEEN NR 2 ROD BEARING AND NR 2 MAIN BEARING JOURNALS.  FRETTING NOTED ON CASE MATING HALVES.  NR	 1 CYLINDER WAS PREVIOUSLY REMOVED AND REPLACED APPROXIMATELY 555 HOURS BEFORE FAILURE OF CRANK.  NR 2 MAIN BEARING HAD 	SHOWED SIGNS OF SPINNING.				1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1997091800263	19970918	00263	GL  	1997	9	18	97ZZZX3980       	2	19970801	G	7322	2526146	BUSHING         	BENDIX      							ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	FAULTY          	B			HEFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21					322442					AD 82-24-05 DESCRIBED METHOD OF IDENTIFICATION OF FAULTY PART.  UPON INSPECTION OF FUEL CONTROL, FOUND FAULTY PART INSTA	LLED THOUGH UNIT WAS OVERHAULED 4-23-92.  THIS IS THE FOURTH UNIT FOUND WITH PRE-AD BUSHING.  RECOMMEND SOURCE INSPECTIO	N AND/OR ONE TIME IN-SERVICE INSPECTION.									3	U			E4CE				 
1997091800264	19970918	00264	EU  	1997	9	18	97ZZZX3981       	1	19970905	G	2150	2055701	TURBINE         			FOKKER	F27   	F27MK400    	4990626	EU  										CABIN COOLING	SEIZED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SO	05	2MIL				92769	10652				FLIGHT CREW SMELLED A 'STRONG ELECTRICAL ODOR' IN THE COCKPIT AND CABIN.  THE ODOR WAS REMINISCENT OF BURNING ELECTRICAL	 INSULATION AND/OR SHORTED ELECTRICAL WIRING.  THE AIRPLANE CHIEF NOTED THE AIR CONDITIONING AND HEATING DUCT TEMPERATUR	E TO BE OVER 160 DEGREES FAHRENHEIT.  ALSO, THE ODOR WAS MOST NOTICEABLE NEAR THE VENT OUTLETS.  TROUBLESHOOTING REVEALE	D THE COOLING TURBINE SHAFT WAS SEIZED, IT COULD NOT BE TURNED WITH HAND PRESSURE.  THE COOLING TURBINE ASSEMBLY WAS REP	LACED AND THE AIRPLANE RETURNED TO SERVICE.		2	H	7	2 	4T				A817    					 
1997091800265	19970918	00265	GL  	1997	9	18	97ZZZX3982       	3	19970829	G	6111	22171	PIN BLOCK       													HARTZL	HCC2Y	HCC2YR2     	GL  	BLADE PIN	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13								BC512		BLADE PIN BLOCK WAS FOUND BROKEN AFTER DISASSEMBLY FOR INSPECTION.  SUSPECT CAUSE:  IMPROPER USE OF BLADE PADDLES.																5	C	P920	 
1997091800266	19970918	00266	SO  	1997	9	18	97ZZZX3983       	1	19970807	G	5520	764054	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR HINGE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	27478		71700			7852026				DURING INSPECTION, THE ELEVATOR BEARINGS WERE BEING INSPECTED AND UPON LIFTING UP ON ELEVATOR, A LOUD CLUNKING NOISE WAS	 HEARD.  UPON CLOSER INVESTIGATION, COULD SEE THE HEAD OR THE BOLT ROCKING UP AND DOWN IN THE BEARING.  ELEVATOR WAS REM	OVED AND BEARING FELL APART.  THIS IS THE SECOND ONE FOUND.				1	L	7	2 	3O				A20SO   					 
1997091800267	19970918	00267	NE  	1997	9	18	97ZZZX3984       	2	19970705	G	8530	45942	PUSH ROD        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985*       	52008	NE  					NR 1 CYL EXHAUST	BROKEN          	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AL	03	5164G		124  			506	MM2214			ENGINE BEGAN RUNNING ROUGH.  NR 1 CYLINDER EXHAUST ROCKER PUSH ROD BARREL PN 39288 WAS FOUND BROKEN JUST BELOW STEEL BAL	L FITTING PN 11473.   PART FATIGUE COULD HAVE PLAYED A PART.  TOTAL TIME ON PART UNKNOWN.  TOTAL TIME ON ENGINE WAS 6256	.3 HOURS. TIME SINCE OVERHAUL, 124.1 HOURS.				1	H	7	1 	3R	3	R		A806    	5E1				 
1997091800268	19970918	00268	GL  	1997	9	18	97ZZZX3985       	1	19970719	G	3213	194044	BOLT            			BLANCA	17    	1730        	1220432	GL  										LT MLG SCISSORS	FAILED          	B	S	A	OMKR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	6564V					30245				THE LEFT MAIN GEAR FAILED ON LANDING.  THE LOWER SCISSOR ATTACH BOLT, BELLANCA PN 19404-4, APPEARED TO HAVE FAILED ALLOW	ING THE LOWER GEAR SEGMENT TO ROTATE 180 DEGREES.					1	L	7	1 	3O				1A3     					 
1997091800269	19970918	00269	GL  	1997	9	18	97ZZZX3986       	1	19970801	G	3213	194096	GEAR LEG        			BLANCA	17    	1730        	1220432	GL  										RT MLG	FAILED          	B			OMKR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	6667V					30018				AIRCRAFT EXPERIENCED A FAILURE OF THE RIGHT MAIN GEAR LOWER GEAR SEGMENT.  THE LOWER TUBE FAILED AT THE SCISSOR ATTACH P	OINT CAUSING THE WHEEL TO ROTATE 180 DEGREES.					1	L	7	1 	3O				1A3     					 
1997091800270	19970918	00270	EA  	1997	9	18	97ZZZX3987       	1	19970810	G	7603	35N126144	CONTROL CABLE   			SCWZER	G164  	G164        	3952702	EA  										THROTTLE	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	634U					370				CABLE BROKE CAUSING LOSS OF POWER.  AIRCRAFT LANDED, FLIPPED OVER CAUSING FATAL INJURY TO PILOT.  THROTTLE CABLE WAS FOU	ND BROKEN BEHIND FIRE WALL WHERE CABLE MAKES A TURN TO THE LEFT SIDE OF THE AIR FRAME.  TIME ON AIR FRAME, 10,035 HOURS,	 AND NO RECORD OF CABLE BEING CHANGED.				1	Q	7	1 	3R			 	1A16    					 
1997091800271	19970918	00271	SO  	1997	9	18	97ZZZX3988       	2	19970825	G	8550	CHRISTEN802	OIL VALVE       			AMTR  	SKYBLT	SKYBOLT     		GL  	CONT  	O470  	IO470C      	17026	SO  					INVERTED OIL SYS	CORRODED        	D	L			A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	99	16HH	200  				001				DURING FLIGHT, OIL PRESS WAS INDICATING LOW (10-30 PSI) AND ERRATIC.  AFTER LANDING, DURING TAXI, OIL PRESS INDICATION W	AS 0-10 PSI.  PRESS XMITTER REMOVED AND A DIRECT READING GAUGE CONFIRMED THAT ON-BOARD INDICATIONS WERE CORRECT.  PRESS 	REGULATOR AND BYPASS VALVES WERE CHECKED, FOUND NORMAL AND UNOBSTRUCTED.    ENG IS EQUIPPED WITH A CHRISTEN 802  INVERTE	D OIL VALVE INSTALLED AT THE SUPPLY SIDE OF THE OIL PUMP.  UPON REMOVAL AND DISASSEMBLY OF SAME, THE UPPER OF THE TWO CH	ROME BALLS (1.1250  INCH DIAMETER) WAS FOUND CORRODED CAUSING OIL PUMP TO SUCK AIR WHILE IN THE UPRIGHT ATTITUDE AND ENA	BLING CAVITATION.  THE LOWER BALL, UNLIKE THE UPPER, IS CONTINUOUSLY BATHED IN OIL AND WAS FOUND IN LIKE-NEW CONDITION.	1	Q	7	1 	3O	3	O		EXPA1Q71	E273				 
1997091800272	19970918	00272	SW  	1997	9	18	97ZZZX3989       	1	19970908	G	6220	214010104121	ROTOR GRIP      		214010100207	BELL  	214   	214ST       	1182106	SW  										M/R HEAD	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	745H	1642 	875  		AL1229	28197				MAIN ROTOR GRIP, DRAG BRACE ATTACHMENT, LOWER LUG CRACKED, 1.25 INCHES LONG.  DEFECT IDENTIFIED VISUALLY DURING 5,000 HR	/5 YEAR E-CHECK.  DEFECT BECAME APPARENT DURING DISASSEMBLY.  DEFECTIVE PART BEING RETURNED TO BELL FOR INVESTIGATION.					2	G	7	2 	4U				H10SW   					 
1997091800273	19970918	00273	GL  	1997	9	18	97ZZZX3990       	2	19970112	G	7313	5233414	SCREEN          		6890917     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					FUEL NOZZLE	CONTAMINATED    	D	L	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	13	7012G					510981D				ON JANUARY 12, 1997, A HUGHES 369D WAS INVOLVED IN AN ACCIDENT DUE TO FUEL STARVATION (SEE ACCIDENT NR LAX97LA088).  THE	 STARVATION APPEARS TO HAVE BEEN CAUSED BY CONTAMINATION COLLECTING ON THE FUEL NOZZLE SCREEN RESTRICTING THE FLOW AND S	UBSEQUENTLY COLLAPSING THE FILTER SCREEN UNDER HIGH ENGINE POWER SETTINGS.  THESE POWER SETTINGS REQUIRE HIGHER FUEL PRE	SSURE AND VOLUME.  THE SCREEN WAS P/N 5233414 AND WAS OF A 104 MICRON MESH FILTER QUALITY.  THESE SCREENS ARE A SUB-PART	 OF THE FUEL NOZZLES, P/N 6890917, AND ARE INSTALLED IN THE ALLISON 250-C20 SERIES ENGINES.		1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997091800247	19970918	00247	GL  	1997	9	18	97ZZZX3992       	1	19970801	G	5751		SPADE           			AMTR  	LASER 	LASER200    	05626X5	GL  										RT AILERON	BROKE           	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	295L					002				RIGHT AILERON SPADE BENT AND BROKE JUST ABOVE TIG WELD.						1	L	7	1 	3I			NC	EXPA1L71					 
1997091800248	19970918	00248	WP  	1997	9	18	97ZZZX3993       	1	19970820	G	6410	369A1613507	BLADE           			HUGHES	369   	369HS       	4470728	WP  										T/R	CRACKED         	B		A	H8OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	33TM	3512 			8708	550746S				DURING POST-FLIGHT INSPECTION AFTER APPROXIMATELY A 2-HOUR FLIGHT, PILOT NOTICED PINHOLE IN T/R BLADE LEADING EDGE WITH 	APPROXIMATELY 1 INCH CRACKS DOWN BOTH SIDES OF BLADES.  THESE BLADES HAD NEW DESIGN ABRASION STRIPS INSTALLED IAW AD 95-	03-11 ON 1-2-96 AT PART TTSN 2,505.0 HOURS.  ORIGINAL SKIN INBOARD OF NEW STRIP APPARENTLY ERODED AND/OR CORRODED THROUG	H.  RECOMMEND X-RAY (OR OTHER INSPECTION) DURING 5,600 HOUR TIME LIFE.			1	G	7	1 	3U				H3WE    					 
1997091800249	19970918	00249	GL  	1997	9	18	97ZZZX3994       	1	19970626	G	3230		LANDING GEAR    			AMTR  	VENTUR	VENTURE     	05618V8	GL  										NLG & MLG	MALFUNCTIONED   	D	L			O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NE	05	60BP					51				LANDING GEAR WOULD NOT EXTEND UNTIL PILOT OPENED BYPASS VALVE TO USE EMERGENCY HAND PUMP.  GEAR FELL TO DOWN POSITION, B	UT WOULD NOT EXTEND AND LOCK.  A GEAR-UP LANDING WAS MADE WITH EXTENSIVE DAMAGE TO AIRCRAFT.					1	L	7	1 	3O			RT	EXPA1L71					 
1997091800399	19970918	00399	CE  	1997	9	18	97ZZZX3998       	1	19970819	G	5753	122101015	TRACK           			CESSNA	185   	A185F       	2072821	CE  										RT FLAP INB-FWD	RIVET SHEARED   	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	21	185ND	2249 				18504369				FLAPS WOULD NOT RETRACT FULLY.  FOUND RIGHT FLAP INBOARD TRACK FORWARD LOWER ATTACH POINT RIVETS SHEARED.  FLAP WELD SKI	N TO BRACKET ATTACH POINTS ALSO CRACKED.  LEFT FLAP INBOARD TRACK REPLACED PREVIOUS YEAR.  AIRCRAFT OPERATED FULL TIME O	N 3730 AMPHIBIAN FLOATS.				1	H	7	1 	3O				3A24    					 
1997091800400	19970918	00400	CE  	1997	9	18	97ZZZX3999       	1	19970707	G	3010		DEICE BOOT      	BFGOODRICH  		BEECH 	60    	B60         	1153605	CE  										WING-PROP	DEFECTIVE       	B	L		CNZ2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	21FH					P35G				WING AND PROPELLER DE-ICE BOOTS FAILED AFTER BEING TREATED BY A PROCESS CALLED 'NU-BOOTS' WHICH USED 'MEK' TO REFURBISH 	THE RUBBER.  BF GOODRICH DOES NOT APROVE THIS PROCESS.  THE OWNER HAS GROUNDed THE AIRCRAFT UNTIL ALL BOOTS ARE REPLACED	.				1	L	7	2 	3O				A12CE   					 
1997091800401	19970918	00401	GL  	1997	9	18	97ZZZX4000       	1	19970826	G	3220		SPRING          			AMTR  	EAGLE 	CHRISEAGLE2 		GL  										TAIL WHEEL	FAILED          	D		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	21	37BB	597  				BENNETT0001				TAIL WHEEL SPRING WAS MADE OF LAMINATED FIBERGLASS.  BOUNCED LANDING CAUSED SPRING TO BREAK IN HALF.  PARTS BOOK SHOWS S	TEEL LEAF SPRINGS AS ORIGINAL EQUIPMENT.  NO INDICATION OF WHEN OR WHY FIBERGLASS SPRING INSTALLED.					1	Q	7	1 	3O				EXPA1Q71					 
1997091800402	19970918	00402	SO  	1997	9	18	97ZZZX4001       	1	19970815	G	2810	649541	BLADDER         			PIPER 	PA25  	PA25235     	7102504	SO  										ATTACH SNAPS	FAILED          	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	21	4590Y	4263 				254271				PILOT MADE EMERGENCY LANDING DUE TO FUEL STARVATION.  FOUND FUEL BLADDER FAILED DUE TO ATTACHING SNAPS WERE UNSNAPPED.						1	L	7	1 	3O				2A10    					 
1997091800403	19970918	00403	SO  	1997	9	18	97ZZZX4002       	1	19970801	G	5610	6971200	WINDOW          			PIPER 	PA34  	PA34200     	7103405	SO  										PILOT LT SIDE	DEPARTED        	D				O				OTHER                   				C			F.O.D.                    			CR	CRUISE         	1			WP	23	41298					347450106				PILOT'S LEFT SIDE WINDOW DEPARTED AIRCRAFT DURING FLIGHT.  PILOTS REPORTED NO ADVERSE FLIGHT CHARACTERISTICS AFTER WINDO	W DEPARTED.  PILOT REPORTED THAT WINDOW WAS CRACKED AT WING WINDOW PRIOR TO FLIGHT.  SUSPECT CAUSE OF TOTAL FAILURE WAS 	WING WINDOW LEFT OPEN FOR COOLING AND BROKEN SECTION OF WINDOW WAS CAUGHT IN AIRFLOW CAUSING TOTAL FAILURE.  NO OTHER DA	MAGE TO AIRCRAFT.			1	L	7	2 	3O				A7SO    					 
1997091800404	19970918	00404	SO  	1997	9	18	97ZZZX4003       	2	19970825	G	8520	643207	CRANKCASE       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					CYL NR 2 STUD	CRACKED         	C	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	524CA	1328 				402C0522	290318R			CREW REPORTED OIL LEAK, RIGHT ENGINE.  UPON FURTHER INSPECTION, FOUND 1.25 INCH TO 1.5 INCH LONG CRACK IN CRANKCASE JUST	 AFT OF NR 2 CYLINDER, SEVENTH STUD, LOCATED IN WEB BETWEEN OIL COOLER MOUNTING AREA AND CYLINDER ATTACH AREA.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997091800407	19970918	00407	SO  	1997	9	18	97ZZZX4006       	1	19970827	G	2910	6390170	LINE            			PIPER 	PA34  	PA34200T    	7103406	SO  										GEAR RETRACT	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	75226	3825 				34670237				THERE IS A POSSIBILITY THE HYDRAULIC HOSE TO THE GEAR RETRACTION ACTUATOR MAY HAVE BEEN PICKED UP BY THE UPPER DRAG LINK	 BOLT WHEN THE GEAR WAS SELECTED DOWN.  COULD NOT DUPLICATE THE GEAR EXTENSION PROBLEM.					1	L	7	2 	3O				A7SO    					 
1997091800408	19970918	00408	SO  	1997	9	18	97ZZZX4007       	1	19970905	G	2150	424910	KEY             			PIPER 	PA31T 	PA31T       	7103124	SO  										AIR COND DRIVE	FAILED          	B			ISOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8CF					8020062				PILOT REPORTED AIR CONDITIONER INOPERATIVE.  INSPECTION REVEALED THAT AIR CONDITIONER QUILL SHAFT DRIVE PULLEY WAS LOOSE	 ON QUILL SHAFT.  RESULTING HEAT BUILD-UP DEFORMED QUILL SHAFT, PULLEYS, AND ATTACH HARDWARE, AND DESTROYED DRIVE BELTS.	  REPLACED QUILL SHAFT, BOTH BEARINGS, PULLEYS, BELTS, AND ASSOCIATED HARDWARE.  SYSTEM OPERATIONAL CHECKED NORMALLY.				1	L	7	2 	3T				A8EA    					 
1997091800409	19970918	00409	NE  	1997	9	18	97ZZZX4008       	2	19970827	G	8530	116733CP	CYLINDER        			DOUG  	DC3   	DC3AS1C3G   	3021440	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 11	FAILED          	G				E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SW	99	24320		1283 			20197	350920			AIRCRAFT WAS IN CRUISE FLIGHT WHEN ENGINE STARTED TO RUN ROUGH.  ENGINE WAS SECURED AND PROPELLER FEATHERED.  INVESTIGAT	ION SHOWED THAT ROCKER ARM OR CYLINDER HEAD FAILED.  CYLINDER TO BE REPLACED AND OPERATIONAL CHECK OF ENGINE DONE.					2	L	7	2 	4R	4	R		A669    	5E4				 
1997091800410	19970918	00410	NM  	1997	9	18	97ZZZX4009       	1	19970702	G	5230	C54667EA205	PISTON          		54C54667E01 	BOEING	727   	727         	1384001	NM  										CARGO DOOR ACT	ROD SEPARATED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			1510 		RH0039					PISTON ROD SEPARATED FROM PISTON BODY DURING PRE-DISASSEMBLY PROOF PRESSURE TEST.  SUSPECT CAUSE:  METAL FATIGUE AT CHRO	ME RUN-OUT, BASE OF PISTON ROD.					2	L	7	3 	4F				A3WE    					 
1997012300329	19970123	00329	GL  	1997	1	23	97ZZZX401        	3	19970106	G	6111	CDA334	CLAMP           			MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP BLADE	CRACKED         	D	S	A		K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	15	37AL		933  			752SA				DURING A 150 HOUR INSPECTION, A CLAMP WAS FOUND CRACKED ON THE LEFT PROP.  THE PILOT THAT DELIVERED THE AIRCRAFT FOR THE	 INSPECTION REPORTED VIBRATION FROM THE RIGHT ENGINE.  RECOMMENDED TO INSPECT PROPS IAW HC-SL-61-165 ANY TIME THERE IS G	REASE LEAKAGE OR VIBRATION.				1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
1997091800411	19970918	00411	SW  	1997	9	18	97ZZZX4010       	1	19970902	G	2710	500042293	CONTROL CABLE   			GULSTM	690TP 	695A        	7630519	SW  										LT AIL WS 142	FRAYED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	7896G	3116 				96070				WHILE PERFORMING SB 226, THE  LEFT AILERON CABLE WAS FOUND SEVERELY FRAYED AT WS 142.0. THE CABLE WAS PROPERLY ROUTED AN	D RUBBING ON THE FAIRLEAD AS IT WAS INTENDED TO DO.  SUBMITTER SUGGESTS INSPECTING ALL OF AILERON CABLES BEHIND WING TO 	FLAP FAIRINGS WHILE PERFORMING SB 226.				1	H	7	2 	4T			 	2A4     					 
1997091800412	19970918	00412	SW  	1997	9	18	97ZZZX4011       	1	19970825	G	2930	SS10127	SWITCH          			SWRNGN	SA226 	SA226TC     	8780404	SW  										HYDRAULIC PRESS	CRACKED         	E				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	11	71Z					TC245				HYDRAULIC WARN LIGHT (RT) ACTIVATED.  LIGHT WAS FALSE WARNING DUE TO PRESSURE SWITCH HAD A CRACKED WELD.						2	L	7	2 	4T			RT	A8SW    					 
1997091800415	19970918	00415	NE  	1997	9	18	97ZZZX4013       	2	19970827	G	7250		BLADE           			DOUG  	DC9   	DC983       	3022083	WP  	PWA   	JT8   	JT8D217C    	52053	NE  					HPT AND LPT	FAILED          	B	L	A	ASMF	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	07	2FOR	23744					718075			DURING TAKEOFF, ENGINE EXPERIENCED A CONTAINED FAILURE ON THE HPT AND LPT INCLUDING SEPARATION OF THE EXHAUST CONE.  DUR	ING INVESTIGATION, NUMEROUS PIECES OF THE TURBINE WERE FOUND IN THE ENGINE EXHAUST AREA AND RUNWAY.  A METALLURGICAL EXA	MINATION IS BEING ACCOMPLISHED BY PW FIELD REP.  AN ENGINE BORESCOPE WAS ACCOMPLISHED A WEEK PRIOR TO FAILURE, NO DAMAGE	 REPORTED DURING THIS INSPECTION.  ENGINE IS SCHEDULED FOR TEAR-DOWN AND CAUSE OF FAILURE WILL BE PROVIDED TO THE FAA.			2	L	7	2 	4F	4	F	RT	A6WE    	E9NE				 
1997091800416	19970918	00416	SW  	1997	9	18	97ZZZX4014       	1	19970520	G	5510	540011300009	STABILIZER BAR  			BELL  	204   	UH1E        	1181401	SW  										STAB ATTACH	BOLT FAILED     	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	121FC		278  		Q191167	151858				ON A DAILY INSPECTION OF THE HELICOPTER, 2 BOLT HEADS WERE POPPED OFF THE STABILIZER BAR MOUNTING AREA AND ALL OTHER BOL	TS WERE LOOSE.  RECORDS INDICATED 110 HRS AGO, ONE BOLT WAS FOUND LOOSE ON A PREVIOUS INSPECTION.  SUBMITTER RECOMMENDS 	THE AN 6H BOLTS AND MS2000266 WASHERS OF THE MILITARY CONFIGURATION BE CHANGED TO THE NAS1306 BOLTS AND AN960-616 WASHER	S OF THE BELL HELICOPTER CONFIGURATION.  BOLT HAS MUCH HIGHER TENSILE STRENGTH AND WASHER HAS BETTER CONTACT AREA ON BOL	T HEAD.		1	G	7	1 	4U				EXPA1G71					 
1997012300330	19970123	00330	NE  	1997	1	23	97ZZZX402        	1	19970108	G	6720	7640003191043	CONTROL CABLE   			SKRSKY	S76   	S76A        	8143006	NE  										T/R CONTROL	MISMANUFACTURED 	B	L	A	ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										WHILE ATTEMPTING TO INSTALL A NEW TAIL ROTOR CABLE, THE TECHNICIAN DISCOVERED THAT THE THREADED 'MALE' END OF THE CABLE 	WAS THREADED IMPROPERLY.  THE CABLE WAS THREADED WITH LEFT-HAND THREADS INSTEAD OF THE REQUIRED RIGHT-HAND THREADS.  THE	 OPERATOR FOUND NINE OTHER NEW CABLES IN THEIR STOCK THAT WERE THREADED INCORRECTLY.  THE CABLES WERE ALL PURCHASED DIRE	CTLY FROM AN AUTHORIZED SIKORSKY PARTS DISTRIBUTOR AND CONTAINED SIKORSKY PACKAGING.			1	G	7	2 	3U			 	H1NE    					 
1997091800783	19970918	00783	SW  	1997	9	18	97ZZZX4024       	1	19970822	G	6710	A21810064603	SWITCH          			HUGHES	500N  	500N        	3027374	SW  										STICK TRIM	FAILED          	G		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	527FB	164  				LN007				RUNAWAY TRIM, FORE AND AFT, DUE TO STICK TRIM SWITCH FAILURE.						1	G	7	1 	3U			NC	H3WE    					 
1997091800784	19970918	00784		1997	9	18	97ZZZX4025       	1	19970903	G	7333	912767	SENSOR          								ALLSN 	AE300 	AE3007A     		GL  					FUEL FLOW	LEAKS           	B			AG4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01					8087					INVESTIGATION FOR SENSOR LEAK FOUND SCREW THAT RETAINS SKEW RUDDER BROKE AT HEAD.  ALLOWED SKEW RUDDER TO BACK OUT ALLOW	ING FUEL TO LEAK.  CAUSE OF HEAD BREAKAGE UNDER INVESTIGATION.  BEING REPORTED TO AFFECTED ENGINE MANUFACTURERS.  THIS I	S THE THIRD INCIDENT IN EIGHT MONTHS.  LEAKAGE IS MINIMAL AND SHOULD NOT CONSTITUTE A FIRE HAZARD.									4	F			TE6CH				 
1997092500001	19970925	00001		1997	9	25	97ZZZX4032       	4	19970813	G	2562	ELT10	ELT             	NARCO       		CESSNA	310   	310R        	2074245	CE  										OUTPUT	WEAK            	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	123RA		394  		A23108	310R0221				DURING ROUTINE ELT CHECK, FOUND THE ELT HAD A WEAK SIGNAL.  ELT WAS REPAIRED, RECERTIFIED, AND NEW BATTERY BY NARCO ON 1	2-21-95.  BATTERY DUE OFF DATE IS JANUARY 17, 1998.  A REPLACEMENT BATTERY WAS TRIED, BUT DID NOT FIX THE PROBLEM.					1	L	7	2 	3O				3A10    					 
1997092500002	19970925	00002	CE  	1997	9	25	97ZZZX4033       	1	19970507	G	2701	05131663	WHEEL           			CESSNA	172   	172E        	2072412	CE  										CONTROL WHEEL	BROKE           	D	S			O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	03	35975	4778 				17250797				COPILOT'S CONTROL WHEEL BROKE APPROXIMATELY IN HALF WITH THE OUTBOARD HALF SEPARATING FROM THE INBOARD.  THE INBOARD HAL	F REMAINED ATTACHED TO THE TUBE.  THIS HAPPENED WHEN THE INSTRUCTOR WAS CORRECTING THE PILOT'S CROSS-WIND LANDING TECHNI	QUE.  THE LAST ANNUAL INSPECTION WAS 1-2-91.				1	H	7	1 	3O			NT	3A12    					 
1997092500003	19970925	00003	SO  	1997	9	25	97ZZZX4034       	1	19970902	G	5712	670151	RIB             			PIPER 	PA28  	PA28R180    	7102809	SO  										WS 49.25	RIVET SHEARED   	B			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	3741T	3750 				28R30957				RIB NR 3 AT STA 69.24 WHERE ANGLES RIVET TO FALSE SPAR RIVETS SHEAR ALLOWING STRUT TO PUSH UP THROUGH UPPER SKIN.  ALSO 	DAMAGES RIB NR 2 AT STA 49.25 AND CRACKS BOTH UPPER AND LOWER FALSE SPAR CAPS.  POSSIBLE CAUSE, HARD LANDING OPERATING W	ITH FLAT STRUT OR OVERPRESSURIZED STRUT AND TIRE.				1	L	7	1 	3O				2A13    					 
1997092500006	19970925	00006	CE  	1997	9	25	97ZZZX4037       	1	19970801	G	3231	08411066	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  										RT MLG DOOR	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4264J	2511 				310R0201				RIGHT MAIN INBOARD GEAR DOOR WOULD NOT CLOSE AFTER EXTENSION.  FOUND BROKEN IDLER BELLCRANK.  GEAR WAS FOUND RIGGED PROP	ERLY.  SUBMITTER STATED CAUSE OF  MALFUNCTION UNKNOWN.					1	L	7	2 	3O				3A10    					 
1997092500007	19970925	00007	SO  	1997	9	25	97ZZZX4038       	1	19970902	G	5712		RIB             			PIPER 	PA28  	PA28R180    	7102809	SO  										WS 69.24	RIVET SHEARED   	B			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	4932J	4603 				28R30653				RIB NR 3 AT STA 69.24 WHERE ANGLES RIVET TO FALSE SPAR RIVETS SHEAR ALLOWING STRUT TO PUSH UP THROUGH UPPER SKIN.  ALSO 	DAMAGES RIB NR 2 AT STA 49.25 AND CRACKS BOTH UPPER AND LOWER FALSE SPAR CAPS.  SUSPECT CAUSE, HARD LANDING OPERATING WI	TH FLAT STRUT OR OVER PRESSURIZED STRUT AND TIRE.				1	L	7	1 	3O				2A13    					 
1997092500008	19970925	00008	CE  	1997	9	25	97ZZZX4039       	1	19970818	G	2410	626543	DRIVE BUSHING   			CESSNA	172   	R172E       	2072413	CE  										ALTERNATOR	DISTORTED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	49885	480  				R1720156				IN RESPONSE TO TCM SB 95-31 (ALT DRIVE), A CHECK OF WEAR HAS BEEN KEPT SINCE NEW.  AT ZERO TIME, RADIAL TRAVEL OF ALTERN	ATOR FAN WAS ZERO TO .1250 INCH.  AT 200 HOURS, FAN TRAVEL WAS .25 INCH TO .3750 INCH.  AT 480 HOURS SINCE NEW, THE FAN 	TRAVEL WAS .75 INCH TO 1 INCH.  BUSHINGS WERE DISTORTED, BUT NOT APPARENTLY READY TO FAIL.				1	H	7	1 	3O				3A17    					 
1997092500010	19970925	00010	CE  	1997	9	25	97ZZZX4041       	1	19970819	G	3340	4313	TAXI LIGHT      			CESSNA	185   	A185F       	2072821	CE  										LIGHT	WRONG PART      	H				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	04	70487					18502190				PILOT REPORTED LANDING LIGHT CIRCUIT BREAKER KEPT TRIPPING.  UPON INVESTIGATION, FOUND LANDING LIGHT CIRCUIT WAS DRAWING	 22 AMPS.  (LANDING LIGHT CIRCUIT BREAKER IS A 20-AMP CIRCUIT BREAKER). FURTHER INVESTIGATION REVEALED THE TAXI LIGHT HA	D BEEN REPLACED WITH A 4313. 250W LAMP.  THE PARTS BOOK CALLS FOR A 4509. 100W LAMP.  INSTALLED CORRECT LAMP.  CIRCUIT D	RAWS 10 AMPS.			1	H	7	1 	3O				3A24    					 
1997092500011	19970925	00011	CE  	1997	9	25	97ZZZX4042       	1	19970904	G	8120		INTERCOOLER     			BEECH 	35    	V35A        	1151544	CE  										TURBOCHARGER	LEAKS           	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	7786R	270  				D8884				LEAKAGE AT OUTLET CONNECTION OF INTERCOOLER FOR TURBOCHARGER ON ENGINE.  OUTLET OF INTERCOOLER IS SQUARE AND A ROUND RUB	BER HOSE IS CLAMPED TO THE SQUARE OUTLET.  OVER TIGHTNING OF CLAMP COULD CAUSE COLLAPSE OF OUTLET.  HOSE PINCHES DURING 	CONNECTION AND LEAKS, VERY HARD TO STOP LEAK.  STC NR SA5223NM AND SE 5222NM.				1	L	7	1 	3O				3A15    					 
1997092500012	19970925	00012	CE  	1997	9	25	97ZZZX4043       	1	19970828	G	5532		STABILIZER      			CESSNA	172   	172RG       	2072438	CE  										VERTICAL STAB	RIVETS LOOSE    	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	360ES	355  				17280010				DURING INSPECTION, FOUND WORKING RIVETS ON TOP OF STABILIZER SKIN JUST UNDERNEATH FAIRING FOR HORIZONTAL STABILIZER TO F	USELAGE.					1	H	7	1 	3O				3A17    					 
1997092500013	19970925	00013	EA  	1997	9	25	97ZZZX4044       	2	19970821	G	8530	LWQ15014	ROCKER ARM      			PIPER 	PA44  	PA44180T    	7104404	SO  	LYC   	O360  	LTO360E1A6  	41515	EA  					LT ENG VALVES	EXCESS WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	49AT	605  				448407041	RL30374T			605 HOURS TT ON ENGINES.  EXCESSIVE WEAR BEWEEN ROCKER ARM AND FULCRUM.  ONE FAILURE IN-FLIGHT.  INSPECTION OF OTHER ENG	INE REVEALED SAME RESULTS.  REPLACED MOST OF THE ROCKER ARMS AND FULCRUMS ON AIRCRAFT.  SUBMITTER RECOMMENDS INSPECTION 	EVERY ANNUAL OR 100 HOURS.  SUSPECT CAUSE - LACK OF LUBRICATION (DESIGN FLAW).				1	L	7	2 	3O	3	O		A19SO   	E26EA				 
1997092500014	19970925	00014	EA  	1997	9	25	97ZZZX4045       	2	19970821	G	8530	LWQ15014	ROCKER ARM      			PIPER 	PA44  	PA44180T    	7104404	SO  	LYC   	O360  	LTO360E1A6  	41515	EA  					RT ENG VALVES	EXCESS WORN     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	49AT	605  				448407041	RL20673T			605 HOURS TT ON ENGINES.  EXCESSIVE WEAR BEWEEN ROCKER ARM AND FULCRUM.  ONE FAILURE IN-FLIGHT.  INSPECTION OF OTHER ENG	INE REVEALED SAME RESULTS.  REPLACED MOST OF THE ROCKER ARMS AND FULCRUMS ON AIRCRAFT.  SUBMITTER RECOMMENDS INSPECTION 	EVERY ANNUAL OR 100 HOURS.  SUSPECT CAUSE - LACK OF LUBRICATION (DESIGN FLAW).				1	L	7	2 	3O	3	O		A19SO   	E26EA				 
1997092500015	19970925	00015	CE  	1997	9	25	97ZZZX4046       	1	19970903	G	3411	589100211	FILTER COVER    		353244903   	BEECH 	33    	F33A        	1151425	CE  										STANDBY AIR	MELTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5581T	601  				CE1350				DURING A PROGRESSIVE INSPECTION, THE MECHANIC FOUND THE FILTER COVER HAD BEEN HEATED TO A POINT AT WHICH THE COVER MELTE	D AND TURNED THE FILTER TO A BROWN BURNT DISTORTED COLOR WHERE THE COVER HAD MELTED.  UPON FURTHER INSPECTION, THERE WAS	 NO EVIDENCE OF EXHAUST LEAK OR LEAKS OF ANY OTHER KIND.  NO DISCREPANCIES WERE FOUND.  SUSPECT CAUSE COULD BE THE MATER	IAL OF WHICH THE PART IS MADE.  ALL ENGINE INDICATING GAUGES SHOWED THE ENGINE OPERATING IN NORMAL CONDITIONS.  THE PART	 WAS REPLACED WITH A NEW PART AND SINCE THEN, HAVE NOT SHOWN ANY SIGNS OF MELTING.		1	L	7	1 	3O				3A15    					 
1997092500016	19970925	00016	CE  	1997	9	25	97ZZZX4047       	1	19970801	G	5520	1705200	BRACKET         			PIPER 	PA23  	PA23150     	7102303	CE  										LT ELEV HINGE	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1258P					23284				WHILE PERFORMING TAIL AREA INSPECTION PER AD 63-26-03, FOUND LEFT ELEVATOR OUTBOARD HINGE BRACKET CRACKED IN AREA OF HIN	GE.  THIS AREA OF THE HINGE IS NOT NORMALLY VISIBLE. THE ELEVATOR HAD BEEN LEFT HANGING IN A VERTICLE POSITION WHEN THE 	ELEVATOR TORQUE TUBE WAS REMOVED TO INSPECT THE CASTINGS AT THE END BRACKETS.  IF THIS AIRCRAFT HAD FORGED PARTS INSTALL	ED, THIS INSPECTION WOULD NOT HAVE BEEN PERFORMED AND THE CRACKED HINGE WOULD NOT HAVE BEEN VISIBLE.  SUBMITTER SUGGESTS	 THAT THIS INSPECTION BE AN AD NOTE.  FAILURE OF THIS PART WOULD BE CATASTROPHIC.		1	L	7	2 	3O			RT	1A10    					 
1997092500017	19970925	00017	CE  	1997	9	25	97ZZZX4048       	1	19970818	G	5551	AN509416R13	SCREW           			CESSNA	210   	T210M       	2073451	CE  										H STAB MOUNT	BROKEN          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6241B	5081 				21062719				100 HOUR INSPECTION FOUND A BROKEN SCREW P/N AN 509-416R13 IN THE HORIZONTAL STABILIZER MOUNT AND MOUNT BRACKET P/N 1212	128-1 CRACKED IN THREE PLACES.					1	H	7	1 	3O				3A21    					 
1997092500018	19970925	00018	CE  	1997	9	25	97ZZZX4049       	1	19970818	G	5551	12121281	BRACKET         			CESSNA	210   	T210M       	2073451	CE  										H STAB MOUNT	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6241B	5081 				21062719				100 HOUR INSPECTION FOUND A BROKEN SCREW P/N AN 509-416R13 IN THE HORIZONTAL STABILIZER MOUNT AND MOUNT BRACKET P/N 1212	128-1 CRACKED IN THREE PLACES.					1	H	7	1 	3O				3A21    					 
1997092500019	19970925	00019	SO  	1997	9	25	97ZZZX4050       	1	19970829	G	2140	FRIDE214EL	HEATER          			PIPER 	PA31T 	PA31T       	7103124	SO  										HEAD FLANGE	CRACKED         	B		A	GW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	77NL		165  		A95120043	31T7720038				THE COMBUSTION HEATER WAS PRESSURE DECAY CHECKED DURING PRE-PURCHASE EVALUATION. ALTHOUGH NOT REQUIRED BY AD 96-20-07, T	HE MANUFACTURER RECOMMENDS A PRESSURE DECAY CHECK AT 500 HOURS INITIAL AND 100-HOUR REPETITIVE INTERVALS.  THE HEATER FA	ILED THE PRESSURE CHECK AND THE UNIT WAS REMOVED FOR A BENCH CHECK.  FURTHER INVESTIATION REVEALED A CRACK WELD AT THE C	OMBUSTION HEAD RETAINING FLANGE.  THE UNIT WAS REPLACED.			1	L	7	2 	3T				A8EA    					 
1997092500020	19970925	00020		1997	9	25	97ZZZX4051       	4	19970731	G	6122	20749	FLY WEIGHT      	MCAULY      	C290D3FT16  															PROP GOVERNOR	BROKEN          	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					793826					PROP GOV FLY WEIGHT CAME APART DURING OPERATION.  SB 214 NOT C/W.																			 
1997092500021	19970925	00021		1997	9	25	97ZZZX4052       	2	19970812	G	7414	ES103827901	COIL            	BENDIX      	D4RN2021    															MAG	CRACKED         	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			469  		5082070R					BOTH COILS IN THIS DUAL MAG HAVE CRACKS IN POTTING COMPOUND EXPOSING COIL WINDINGS AND LEAKING HIGH TENSION VOLTAGE.  BO	TH COILS ARE ELECTROSYSTEMS MANUFACTURED COILS. HAVE SEEN OTHER ELECTRICAL SYSTEM COILS WITH SIMILAR CRACKS.  DOES NOT S	EEM TO OCCUR WITH BENDIX/TCM COILS.  THESE CRACKS COULD RESULT IN A 'DEAD' MAG.																	 
1997092500022	19970925	00022	GL  	1997	9	25	97ZZZX4053       	3	19970904	G	6114		HUB             			BEECH 	45    	A45         	1152006	CE  						MCAULY	2A36C	2A36C23     	GL  	BOTH SOCKETS	CRACKED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03			1506 					737046		PROPELLER WAS IN FOR OVERHAUL.  DURING INSPECTION WITH EDDY CURRENT, BOTH HUB SOCKETS WERE FOUND CRACKED IN THE THREADS 	ON THE ENGINE SIDE OF THE HUB.  THESE THREADS HOLD THE BLADES IN THE PROP.					1	L	7	1 	3O				5A3     		5	C	P880	 
1997092500023	19970925	00023	GL  	1997	9	25	97ZZZX4054       	3	19970904	G	6114		HUB             			CESSNA	188   	188B        	2073007	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 2 SOCKET	CRACKED         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03		800  						921076		PROPELLER WAS IN FOR A SUSPECTED LEAK INTERNALLY.  AFTER DISASSEMBLY, THE PISTON WAS WORN BEYOND ALLOWABLE LIMITS WHICH 	ALLOWED ENGINE OIL TO PASS THE PISTON SEAL INTO THE HUB CAVITY FILLING IT UP AND CAUSING HYDRAULIC LOCK AND STOPPED THE 	PROP FROM ACTUATING.  FURTHER, INSPECTION OF THE PROPELLER HUB SHOWED A CRACK IN THE BLADE RETENTION THREADS OF NR 2 HUB	 SOCKET ON THE ENGINE SIDE.			1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997092500024	19970925	00024	EA  	1997	9	25	97ZZZX4055       	2	19970828	G	7310	LW127996S180	HOSE            		RSA5AD1     	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					FUEL SERVO	LEAK            	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	97100	42   			70124311	17280100	L2709351A			DEFECTIVE HOSE FOUND DURING ROUTINE INSPECTION.  CLAMPS FOR HEAT SLEEVE WERE TIGHTENED EXCESSIVELY, LEAKING AT THAT AREA	.					1	H	7	1 	3O	3	O		3A17    	E286				 
1997092500025	19970925	00025	NE  	1997	9	25	97ZZZX4056       	2	19970305	G	7230	1B5130	BEARING         			BOEING	757   	757*        		NM  	PWA   	2037  	PW2037      		NE  					NR 1	FAILED          	B			WA2D	O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	03		3085 			41337		P727175			AIRCRAFT EXPERIENCED SMOKE IN COCKIT/CABIN AND LOSS OF N1 INDICATION.  GROUND INSPECTION DISCLOSED N1 ROTOR SHIFT/METAL 	IN TAILPIPE.  DISASSEMBLY INSPECTION DISCLOSED NR 1 MAIN BEARING FAILURE (SEVERE DISTRESS FROM A SINGLE BALL FRACTURE). 	 BEARING DELIVERED TO P & W MERL LAB FOR REVIEW.				2	L	7	2 	4F	4	F	RT	A2NM    	E17NE				 
1997092500026	19970925	00026	NE  	1997	9	25	97ZZZX4057       	3	19970804	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		3907 			NR2673			HJ437		INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS, - 4 SLOTS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997092500027	19970925	00027	NE  	1997	9	25	97ZZZX4058       	3	19970905	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		8056 	3860 					HJ163A		INSPECTION FOUND NR 4 BLADE BEARING CRACKED INTO SEVERAL PIECES BOTH INNER AND OUTER HALVES.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997092500028	19970925	00028	NE  	1997	9	25	97ZZZX4059       	3	19970826	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		4498 			2501NR			HJ383		INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TWO SLOTS CR	ACKED.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997092500029	19970925	00029	NE  	1997	9	25	97ZZZX4060       	3	19970825	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		4601 			2728NR			HJ445		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	 
1997092500030	19970925	00030	NE  	1997	9	25	97ZZZX4061       	3	19970730	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		4539 			2530NR			HJ481		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARFD RADIUS OD PITCH PIN ENGAGEMENT SLOTS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997092500045	19970925	00045		1997	9	25	97ZZZX4062       	1	19970910	G	7100	3038	HOSE            	AEROQUIP    																ENGINE	MISMANUFACTURED 	E				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01										IMPROPER MANUFACTURE OF HOSE INTERIOR FOUND DURING ASSY OF NEW HOSE.  HOSE MFG DATE 3Q96.																			 
1997092500046	19970925	00046	SO  	1997	9	25	97ZZZX4063       	1	19970912	G	2121	AE1711AA0	FAN             	TECHNOFAN   		EMB   	120   	EMB120RT    		SO  										GROUND COOL	FAILED          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		2851 	6    							THIS IS A NEW GENERATION FAN ASSEMBLY, PRODUCT IMPROVEMENT.  UPON DISASSEMBLY, FOUND DRIVER P.C. BOARD OVERHEATED AND LO	OSE SOLDER JOINTS.  THIS FAN IS MADE IN FRANCE.  RESOLDERED DEFECTIVE CONNECTIONS TEST RAN FAN, RETURN TO SERVICE.					2	L	7	2 	4T			RT	A31SO   					 
1997092500048	19970925	00048	EA  	1997	9	25	97ZZZX4065       	1	19970818	G	7931	601509193	TRANSDUCER      			CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT ENG OIL PRESS	FAILED          	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			SO	17	175ST	3428 				5023				SHORTLY AFTER DEPARTING FXE, RIGHT ENGINE OIL PRESSURE DROPPED TO ZERO PSI.  RIGHT ENGINE WAS SHUT DOWN AND AIRCRAFT RET	URNED TO DEPARTING AIRPORT FXE.  REPLACED ENGINE OIL PRESSURE TRANSDUCER, RETURNED AIRCRAFT TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
1997092500050	19970925	00050	CE  	1997	9	25	97ZZZX4066       	1	19970630	G	3244	265F864	TIRE            	GOODYEARAERO		BEECH 	200   	200BEECH    	1152920	CE  										NLG	FAILED          	D				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			EA	05	6051C	815  			31542128	BB499				AT ROTATION ON AIRCRAFT TAKEOFF ROLL, CREW HEARD A BANG.  LANDING GEAR WAS LEFT EXTENDED, AND A NORMAL LANDING WAS MADE.	  INVESTIGATION REVEALED THAT CENTER TREAD SECTION HAD SEPARATED FROM TIRE.  NOSE TIRE REMAINED INFLATED.  SUBMITTER STA	TED GOODYEAR MANUAL SPEAKS TO CAUSES OF TREAD SEPARATION.				1	L	7	2 	4T				A24CE   					 
1997092500051	19970925	00051	CE  	1997	9	25	97ZZZX4067       	1	19970821	G	3246	AHA1814	WHEEL ASSY      			RAYTHN	DH125 	HAWKER800XP 		CE  										MLG	BOLT FAILED     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	800XP					258266				WHEEL ASSY BOLT FAILED.  BOLT WAS TESTED IAW MIL-STD-1949 A/2, 5-29-90.						2	L	7	2 	4F			RT	A3EU    					 
1997092500052	19970925	00052	NE  	1997	9	25	97ZZZX4068       	2	19970510	G	7230	55H705	BLADE           		PW4158      	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      		NE  					5TH STAGE HPC	FAILED          	B		A	WA2D	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NE	03	838AB	152  			B24921	676	P724921			EN ROUTE GOING THROUGH FL 370 IN SMOOTH AIR, CREW HEARD ENGINE SURGE AND NOTED PARAMETER DECREASE.  AIR START ATTEMPTED 	UNSUCCESSFULLY.  FLIGHT DIVERTED TO ORLANDO.  DISASSEMBLY REVIEW BY P & W ENGINEERING HAS LED TO A PRELIMINARY CONCLUSIO	N OF A SINGLE 5TH STAGE COMPRESSOR BLADE FAILURE (FRACTURE). THE FAILED MATERIAL (INCLUDING 5TH DISK) HAS BEEN DELIVERED	 TO PRATT & WHITNEY ENGINEERING.  ENGINE TT, 8,484.5; TC 2,575; TSO, 151.33 HOURS; CSO, 91.			2	L	7	2 	4F			RT	A35EU   	E24NE				 
1997013000001	19970130	00001	SW  	1997	1	30	97ZZZX413        	1	19970108	G	7120	2762002001	MOUNT           			SWRNGN	SA226 	SA226*      		SW  										ENG FIREWALL	NOT WELDED      	B	P	A	H7NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										DEFECTIVE LOWER MOUNT ATTACH POINT WHERE THE MOUNT IS ATTACHED TO THE FIREWALL.  THE WELDING OF THE TUBE TO THE MOUNT FA	CE PLATE IS NOT COMPLETE.  WELD WAS NEVER COMPLETED FROM THE MANUFACTURER.  SUBMITTER STATED NEED TO COMPLETELY WELD ALL	 THE WAY AROUND TO ASSURE NO WEAKNESS IN THE TRUSS ATTACH POINT.				2	L	7	2 	4T			RT	A56W    					 
1997092500253	19970925	00253	CE  	1997	9	25	97ZZZX4137       	1	19970823	G	3244	850X10	TIRE            	MCCREARY    		HELIO 	H295  	H295        	4300802	CE  										MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AL	01	6465V	951  			AIH4260	1417				AIRCRAFT WAS INVOLVED IN NUMEROUS OFF-AIRPORT OPERATIONS.  AS AIRCRAFT WAS ON TAKEOFF RUN, UPPER TIRE SIDEWALL AND TUBE 	WERE PUNCTURED, POSSIBLY CAUSED BY ROCKS.  CONDITIONS WERE ROUGH AND PRESUMABLY THE PUNCTURES WERE NOT THE FAULT OF THE 	TIRE AND TUBE.  SUBMITTER WOULD RECOMMEND, HOWEVER, THAT TIRES INVOLVED IN OFF-AIRPORT OPERATION BE CHANGED AT 600-700 H	OURS TO INSURE INTEGRITY OF THE TIRE.			1	H	7	1 	3O				1A8     					 
1997092500255	19970925	00255	SO  	1997	9	25	97ZZZX4139       	1	19970728	G	3242		BRAKE LINING    			PIPER 	PA24  	PA24250     	7102404	SO  										WHEEL	FAILED          	B			QB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15						242007				INSTALL NEW RIVETS IN WHEELS AND BRAKE LININGS.						1	L	7	1 	3O				1A15    					 
1997013000003	19970130	00003	NM  	1997	1	30	97ZZZX414        	1	19970106	G	2761	65233494	ACTUATOR        			BOEING	707   	707321      	138365B	NM  										SPOILER	BROKEN          	B			TR1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	404PA	630  			DA198	18835				SPOILER ACTUATOR ROD END BROKEN AT PISTON END AND EVIDENCE OF INTERNAL FAILURE.  '2ND OCCURRENCE'.  APPEARED TO BREAK AT	 END OF THREAD.  PROBABLY OVERTORQUED.					2	L	7	4 	4J				4A26    					 
1997092500256	19970925	00256	CE  	1997	9	25	97ZZZX4140       	1	19970801	G	3246	C1630040102	WHEEL           			CESSNA	210   	T210L       	2073449	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	117P					21061407				BOTH MAIN WHEELS CRACKED.  THESE ARE 3-PIECE WHEELS USED ON VARIOUS CESSNA SINGLES IN THE 1970'S.  THIS SUBMITTER FEELS 	A MORE LIKELY CAUSE (OTHER THAN OVERTORQUING) IS STRESS CAUSED BY PULLING SMALL AMOUNTS OF ALUMINUM THROUGH THE THREADS 	EACH TIME THE BOLTS ARE REMOVED WHICH TENDS TO SPREAD THE HOLE.				1	H	7	1 	3O				3A21    					 
1997092500261	19970925	00261	CE  	1997	9	25	97ZZZX4145       	1	19970814	G	5220	002430008287	WINDOW SEAL     			BEECH 	36    	A36         	1151604	CE  										LT EMERG EXIT	MISINSTALLED    	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	3147L	370  				E2882				DURING ANNUAL INSPECTION, LEFT CABIN EXIT WINDOW COULD NOT BE OPENED.  WINDOW HAD BEEN SEALED CLOSED BY A BEAD OF RTV AP	PLIED TO FORWARD SEAL AREA.					1	L	7	1 	3O				3A15    					 
1997092500262	19970925	00262	SO  	1997	9	25	97ZZZX4146       	1	19970903	G	3230	9539400	CHANNEL ASSY    			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	38884	5755 				347770352				WHILE PERFORMING A GEAR SWING, NOSE GEAR WOULD NOT RETRACT FULLY.  UNDER FURTHER INSPECTION, FOUND THE NOSE GEAR HAD JUM	PED OUT OF THE TRACK ASSY.  REPLACED THE UPPER CHANNEL ASSY.  OPS CHECK GOOD.  SUSPECT CAUSE:  IMPROPER TOWING, EXCEEDIN	G TOWING LIMITS.				1	L	7	2 	3O				A7SO    					 
1997092500263	19970925	00263	CE  	1997	9	25	97ZZZX4147       	1	19970909	G	2437	C6695600105	AMMETER         			CESSNA	210   	T210N       	2073456	CE  										INST PANEL	MISMARKED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	6621A					21063559				WHILE REPLACING BAD AMMETER, NOTICED THE MARKINGS FOR PLUS AND MINUS WERE OPPOSITE OF THE ORIGINAL GAUGE.  THE AMMETER W	AS BENCH CHECKED FOR PROPER DEFLECTION AND IT WAS FOUND MIS-MARKED.  WHEN INSTALLED AND HOOKED UP AS THE ORIGINAL GAUGE 	WAS, OPS CHECK NORMAL.				1	H	7	1 	3O				3A21    					 
1997092500264	19970925	00264	EA  	1997	9	25	97ZZZX4148       	2	19970908	G	7414	1051324	IMPULSE SPRING  		105136045   	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					MAGNETO	BROKEN          	B			QKKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	7853N	11   			991382	285310	L1383936A			MAGNETO IMPULSE SPRING FOUND BROKEN INTO 3 PARTS.  PART WAS INSTALLED 10-20-94, AND USED 11 HOURS TOTAL.  SUBMITTER SUSP	ECTS CORROSION ON PART STARTED PROBLEM.  SUSPECT MATERIAL MAY BE ANOTHER PROBLEM.  FACTORY CHANGED APPEARANCE OF PART IN	 EARLY '94.  AS OF THIS TIME, ANOTHER CHANGE IN APPEARANCE OCCURRED THIS YEAR.				1	L	7	1 	3O	3	O		2A13    	E286				 
1997092500265	19970925	00265	SO  	1997	9	25	97ZZZX4149       	2	19970905	G	8540	640925	ADAPTER         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					RT ENG GEAR CASE	BROKEN          	B			DC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8174H	29   				348070155	266219R			TACHOMETER DRIVE ADAPTER IS A 90-DEGREE DRIVE THAT REVERSES OUTPUT ROTATION AND ANGLE OF OUTPUT FROM ENGINE TO DRIVE TAC	HOMETER SHAFT.  FOUND MOUNTING NUT AND FLANGE STILL ON ENGINE ACCESSORY CASE AND ADAPTER HANGING ON TACHOMETER DRIVESHAF	T.  FLANGE BROKEN OFF OF ADAPTER.  SUSPECT CAUSE, DEFECTIVE PART.  ADAPTER IS A TELEDYNE CONTINENTAL MOTORS PART.				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1997092500266	19970925	00266	CE  	1997	9	25	97ZZZX4150       	1	19970904	G	3231	0024100381	SHAFT           			BEECH 	58    	58          	1152740	CE  										NLG	FAILED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	7222V	2599 				TH1430				PILOT REPORTED A GROUND OBSERVER INFORMED NLG DOORS REMAINED OPENED AFTER THE GEAR WAS UP.  PILOT HEARD NOISES COMING FR	OM NOSE AREA DURING RECENT FLIGHTS.  INSP REVEALED LOWER PORTION OF CAM PLATE SLOT ON THE SHAFT THAT CLOSES THE NOSE GEA	R DOORS BROKE OFF AND BREAK HAD BEEN POLISHED SMOOTH BY CAM PIN INDICATING THE COND HAD EXISTED FOR SOME TIME.  THE NOIS	E HEARD WAS THE DOORS POPPING BACK OPEN, UNDER SPRING TENSION, AFTER THE CAM SLOT AND SHAFT WERE TAKEN OVER CENTER.  A N	EW SHAFT ASSY WAS INSTALLED, GEAR DOORS ADJUSTED, AND ACFT RETURNED TO SERVICE.  THE PLANE WAS 35 HRS INTO ANNUAL INSPEC	TION.  RECOMMEND BEECH SB 2601 PERTAINING TO BEECH 33, 35, AND 36 BE APPLIED TO INCLUDE THE BARON SERIES AIRCRAFT.	1	L	7	2 	3O				3A16    					 
1997092500268	19970925	00268	CE  	1997	9	25	97ZZZX4152       	1	19970804	G	5531	1862012	SPAR            		186200603   	BEECH 	18    	H18         	1151012	CE  										V-FIN ASSY	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	954	8654 				BA670				INSPECTION FOUND LOWER SECTION OF LEFT VERTICAL FIN HAD SEVERAL CRACKS EMANATING FROM UPPER LIGHTENING HOLE.  CRACKS GRE	W LARGER WHEN SLIGHT SIDE PRESSURE APPLIED TO VERTICAL FIN.					1	L	7	2 	3R				A765    					 
1997092500275	19970925	00275	CE  	1997	9	25	97ZZZX4156       	1	19970909	G	3230		RELEASE CABLE   			BEECH 	MU300 	400A        	1155402	CE  										LT EMERG MLG EXT	FRAYED          	B	P	A	ERYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	39HF	1392 				RK65				DURING THE REQUIRED 200-HOUR INSPECTION INTERVAL, FOUND THE LEFT MAIN GEAR EMERGENCY RELEASE CABLE STRANDS BROKEN AT UPL	OCK RELEASE CABLE END.  SHOULD THIS CABLE BREAK, THE LEFT STRUT WILL NOT EXTEND WHEN EMERGENCY EXTEND LEVER IS ACTUATED.	  THIS FACILITY HAS FOUND COMPLETELY BROKEN CABLE ENDS ON 2 OTHER 400A AIRCRAFT.				2	H	7	2 	4F			RT	A16SW   					 
1997092500276	19970925	00276	CE  	1997	9	25	97ZZZX4157       	1	19970825	G	4930	15000022	FUEL PUMP       	DUKES       		LEAR  	60    	60LEAR      	5170707	CE  										APU	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	8270	4    			0130	60063				APU FUEL PUMP LEAKING.  FORWARDED TO DUKE INC., FOR REPAIR/OVERHAUL AND FAILURE REPORT.						2	L	7	2 	4F			RT	A10CE   					 
1997092500277	19970925	00277	CE  	1997	9	25	97ZZZX4158       	1	19970825	G	4930	15000022	FUEL PUMP       	DUKES       		LEAR  	60    	60LEAR      	5170707	CE  										APU	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	8271	1    			0120	60066				APU PUMP IS LEAKING.  SENT TO DUKES INC., FOR REPAIR/OVERHAUL. REQUEST FAILURE ANALYSIS AND OVERHAUL.						2	L	7	2 	4F			RT	A10CE   					 
1997092500279	19970925	00279	CE  	1997	9	25	97ZZZX4159       	1	19970814	G	2121	EMG724	VENT BLOWER     			BEECH 	2000  	2000        	1152000	CE  										CABIN	FAILED          	B			AKGR	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	05	8074S	1092 			443	NC33				CREW HAD SMOKE IN THE CABIN IN-FLIGHT.  PROBLEM FOUND TO BE COMING FROM THE VENT BLOWER.						1	L	7	2 	4T			RT	A38ACE  					 
1997092500280	19970925	00280	NM  	1997	9	25	97ZZZX4160       	1	19970913	G	2612		WIRE            			BOEING	727   	727         	UTILSYS	NM  										FIRE LOOP LT W/W	LOOSE           	G				A	J			UNSCHED LANDING         	DUMP FUEL               			N			FALSE WARNING             			CL	CLIMB          	1			WP	07										ON DEPARTURE FROM PHX, GOT FIRE WARNING BELL, BUT NO OTHER INDICATION OF A FIRE.  DUMPED FUEL AND RETURNED TO PHX, UNEVE	NTFUL LANDING.  FOUND GROUND WIRE LOOSE ON THE FIRE LOOP IN THE LT WHEELWELL, TIGHTENED WIRE AND FUNCTION TEST NORMAL.					2	L	7	3 	4J			RT	A3WE    					 
1997092500608	19970925	00608	EU  	1997	9	25	97ZZZX4161       	1	19970711	G	5280	WSBS16ATC32Z	BEARING         		7229150148  	SAAB  	SF340 	SF340A      	7850100	EU  										RT MLG DOOR	MIGRATED        	B			AY55	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	747P					340A029				RIGHT MLG DOOR HYDRO TUBE SUPPORT BRACKET BEARING MIGRATED .3125 INCH OUT OF THE HYDRO TUBE SUPPORT BRACKET ASSEMBLY INB	OARD.  UPON REPLACEMENT OF SWAGE BEARING, FOUND INBOARD SIDE OF BEARING UNSWAGED CAUSING BEARING TO MIGRATE INWARD.					2	L	7	2 	4T			RT	A52EU   					 
1997100200055	19971002	00055	NE  	1997	10	2	97ZZZX4183       	2	19970801	G	7230	1B3506	DISK            								PWA   	2037  	F117PW100   		NE  					HPC MODULE	CRACKED         	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		857  			S69965		PWE170097			ENGINE REMOVED FOR EGT LIMITATION.  DISASSEMBLY INSPECTION DETECTED CRACKED BLADE SLOTS ON DISK (6TH STAGE). DISK REMOVE	D FROM ROTOR AND FORWARDED TO PRATT & WHITNEY ENGINEERING IN THE BLADED CONDITION.  CYCLES:  2,127.										4	T			E17NE				 
1997100200056	19971002	00056	EA  	1997	10	2	97ZZZX4184       	2	19970825	G	8530		SHROUD TUBE     			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					NR 2 CYLINDER	FRACTURED       	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	4365T					327200019	L1482440			AFTER RUN-UP, OIL FILM NOTED ON LEFT SIDE OF ENGINE.  OIL CAME FROM DENT IN PUSH ROD SHROUD TUBE WHICH WAS FOUND COMPLET	ELY FRACTURED AT DENT LOCATION.  PUSH ROD HAD APPARENTLY RUBBED SHROUD AND CAUSED THE FRACTURE.  DENT WAS ABOUT .0937 IN	CH DEEP.  OTHER SHROUD TUBES HAD MINOR DENTS APPARENTLY LONG-STANDING.  1100 HRS SMOH/POTENTIAL FOR EXCITING MOMENTS IF 	NOT CORRECTED.			1	L	7	1 	3O	3	O		A3SO    	E295				 
1997100200057	19971002	00057	EA  	1997	10	2	97ZZZX4185       	2	19970825	G	8550	71737	DRAIN TUBE      			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					NR 2 ROCKER	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4365T					327200019	L1482440			NR 2 CYLINDER 71737 ROCKER DRAIN TUBE CHAFED THROUGH ABOUT 90 PERCENT OF WALL THICKNESS BY BOTTLE RETAINER (PIN EASILY P	ENETRATED 'PAPER-THIN' WALL') 68761 TUBES (3 OF EACH) HAD SUBSTANTIAL WEAR MARKS, AGAIN, TRIM BOTTLE RETAINER.  NOTE: TY	 WRAPS ARE NOT A GOOD SUBSTITUTE FOR ADEL CLAMPS.				1	L	7	1 	3O	3	O		A3SO    	E295				 
1997100200058	19971002	00058	EA  	1997	10	2	97ZZZX4186       	2	19970825	G	8550	68761	DRAIN TUBE      			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					NR 2 CYLINDER	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4365T					327200019	L1482440			NR 2 CYLINDER 71737 ROCKER DRAIN TUBE CHAFED THROUGH ABOUT 90 PERCENT OF WALL THICKNESS BY BOTTLE RETAINER (PIN EASILY P	ENETRATED 'PAPER-THIN' WALL') 68761 TUBES (3 OF EACH) HAD SUBSTANTIAL WEAR MARKS, AGAIN, TRIM BOTTLE RETAINER.  NOTE: TY	 WRAPS ARE NOT A GOOD SUBSTITUTE FOR ADEL CLAMPS.				1	L	7	1 	3O	3	O		A3SO    	E295				 
1997100200059	19971002	00059	SO  	1997	10	2	97ZZZX4187       	1	19970825	G	7160	651427	VALVE           			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					CARB AIR BOX	SEAL MISSING    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4365T					327200019	L1482440			SEALING FELT ON AIR BOX VALVE MISSING FROM OUTER EDGES EXCEPT FOR A 1 INCH SECTION THAT WAS 'HANGING ON'. THE FELT MATER	IAL IS SANDWICHED BETWEEN 2 METAL PLATES WITH SOME FELT PROTRUDING TO PROVIDE SEAL.  THE PROTRUDING PART WAS ALMOST ALL 	MISSING.  THE POTENTIAL DANGER COULD BLOCK OR RESTRICT FUEL FLOW IF LODGED ACROSS VENTURI.  IN THIS INSTANCE, MOST MATER	IAL WAS GONE, SO NO PROBLEM EXCEPT FOR SEALING.			1	L	7	1 	3O	3	O		A3SO    	E295				 
1997100200060	19971002	00060	SO  	1997	10	2	97ZZZX4188       	1	19970312	G	3230	9582900	LINK ASSY       			PIPER 	PA34  	PA34200     	7103405	SO  										NLG DOWNLOCK	ROD END FAILED  	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	01	4484T					347250110				P/N 452334 BEARING.  ROD END WHICH IS PART OF LINK ASSY, NLG DOWNLOCK, FAILED BY BENDING AND PARTING IN THREADED PORTION	.  NLG COLLAPSED ON LANDING ROLL-OUT.  WHEN BENT, NLG DRAG BRACE WILL NOT BE OVERCENTER, BUT A DOWN AND LOCKED GREEN LIG	HT WILL BE ON.  THIS IS DUE TO DESIGN OF SYSTEM.				1	L	7	2 	3O				A7SO    					 
1997100200061	19971002	00061	EU  	1997	10	2	97ZZZX4189       	2	19970905	G	7314	996592	PUMP            	ROTAX       		DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	LINE CRACKED    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	545SS	299  				10118				ENGINE DRIVEN FUEL PUMP LINE CRACKED AT PUMP WALL RESULTING IN FUEL DRIPPING INTO LOWER COWL AREA.  CRACK IS AT BEND IN 	LINE WHERE IT MEETS PUMP.  APPEARS LINE WAS BENT TO FACILITATE ROUTING.  INSTALLED NEW PUMP.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
1997100200062	19971002	00062	CE  	1997	10	2	97ZZZX4190       	1	19970909	G	3213	22411001	AXLE FITTING    			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	5316R	5211 				172RG0053				CASTING CRACKED IN TWO LOCATIONS.  CRACKS WERE LOCATED AT 90 DEGREES TO THE BOLT HOLES, AND PARALLEL TO THE BORE DIAMETE	R.  ONE CRACK APPROXIMATELY 2.500 INCHES LONG WAS LOCATED IN THE WEB SECTION ABOVE THE BOLT HOLES.  SECOND CRACK LOCATED	 IN THE LOWER WEB SECTION BELOW THE BOLT HOLES AND APPROXIMATELY 1.500 INCHES LONG.  CRACKS WERE NOT DEEP ENOUGH IN DEPT	H TO INTERSECT THE BOLT HOLES.			1	H	7	1 	3O				3A17    					 
1997100200063	19971002	00063	SW  	1997	10	2	97ZZZX4191       	1	19970815	G	3260	ISE13	SWITCH          			GULSTM	112   	112         	0144701	SW  										NLG	MISADJUSTED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	1195J					195				FOUND NOSE GEAR MICROSWITCH INSTALLED TO FULL FORWARD LIMIT ON MOUNTING BRACKET.  BRACKET MOUNTED ON ENGINE MOUNT WITH H	OSE CLAMPS.  FOUND BRACKET INSTALLED TOO FAR AFT.  THIS PREVENTED PROPER ADJUSTMENT OF MICROSWITCH WHICH WAS MAKING CONT	ACT WITH PAINTED SURFACE ON TOP OF NOSE GEAR.  ADJUSTED BRACKET AND MICROSWITCH TO PROPER LOCATION.  NO INFORMATION ON B	RACKET ADJUSTMENT IN MM.  BRACKET NOT SHOWN IN PARTS  MANUAL.			1	L	7	1 	3O				A12SO   					 
1997100200064	19971002	00064	EU  	1997	10	2	97ZZZX4192       	1	19970905	G	5610		CANOPY          			GROB  	103TWN	G103ATWINII 	1660206	EU  										COCKPIT	OPENED          	C		A		K				NONE                    				O			OTHER                     			CL	CLIMB          	1			EA	11	47938	1400 				3841K87				BOUNCING ON TAKEOFF ROLL AND TURBULENCE ON TOW CAUSED CANOPY LOCK HANDLE TO UNLOCK AND CANOPY OPENED IN-FLIGHT BREAKING 	THE REAR HINGE AND GLASS.  IT DID NOT BREAK LOOSE FROM THE GLIDER.  RECOMMEND OVERCENTER TYPE LOCK SPRING TO HOLD LATCH 	CLOSED.				1	K	0	0 	3O			0	G39EU   					 
1997100200065	19971002	00065	WP  	1997	10	2	97ZZZX4193       	1	19970728	G	2622	893244	EXTINGUISHER    	KIDDE       		DOUG  	DC8   	DC8*        		WP  										FIRE BOTTLE	INOPERABLE      	B		A	C6RR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23					73155DB					FIRE EXTINGUISHER WAS RECEIVED INTO SHOP AS CONDITION UNKNOWN, NO TAG.  UPON DISASSEMBLY, THE FOLLOWING DISCREPANCIES WE	RE NOTED RENDERING UNIT INOPERABLE.  AGENT REMOVED NOT HALON 1301 AS SPECIFIED.  ADDITIONAL COPPER DISK INSTALLED UNDER 	RUPTURED DISK, NOT O.E.M.  RUPTURED DISK NOT RECOGNIZED AS APPROVED PART.  GAUGE READS 'O' PSI.  FAA NOTE:  PART ORIGINA	TED OUTSIDE U.S.			2	L	7	4 	4J			F	4A25    					 
1997100200066	19971002	00066	WP  	1997	10	2	97ZZZX4194       	1	19970728	G	2622	893244	EXTINGUISHER    	KIDDE       		DOUG  	DC8   	DC8*        		WP  										FIRE BOTTLE	INOPERATIVE     	B		A	C6RR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23					17409DW					FIRE EXTINGUISHER WAS RECEIVED INTO SHOP AS CONDITION UNKNOWN.  NO TAG.  UPON DISASSEMBLY, THE FOLLOWING DISCREPANCIES W	ERE NOTED, RENDERING UNIT INOPERATIVE.  AGENT REMOVED NOT HALCON 1301 AS SPECIFICED.  ADDITIONAL DISK INSTALLED UNDER RU	PTURED DISK, NOT O.E.M.  RUPTURED DISK NOT RECOGNIZED AS APPROVED PART.  FAA NOTE:  PART ORIGINATED OUTSIDE U.S.				2	L	7	4 	4J			F	4A25    					 
1997100200067	19971002	00067	WP  	1997	10	2	97ZZZX4195       	1	19970728	G	2622	893244	EXTINGUISHER    	KIDDE       		DOUG  	DC8   	DC8*        		WP  										FIRE BOTTLE	INOPERATIVE     	B		A	C6RR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23					25701DH					FIRE EXTINGUISHER WAS RECEIVED INTO SHOP AS CONDITION UNKNOWN.  NO TAG.  UPON DISASSEMBLY, THE FOLLOWING DISCREPANCIES W	ERE NOTED, RENDERING UNIT INOPERATIVE.  AGENT REMOVED NOT HALON 1301 AS SPECIFIED.  ONLY TRACE OF AGENT IN CONTAINER.  G	AUGE READING 100 PSI.  FAA NOTE:  PART ORIGINATED OUTSIDE U.S.				2	L	7	4 	4J			F	4A25    					 
1997100200068	19971002	00068	WP  	1997	10	2	97ZZZX4196       	1	19970728	G	2622	893244	EXTINGUISHER    	KIDDE       		DOUG  	DC8   	DC8*        		WP  										FIRE BOTTLE	INOPERATIVE     	B		A	C6RR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23					18112C4					FIRE EXTINGUISHER WAS RECEIVED INTO SHOP AS CONDITION UNKNOWN.  NO TAG.  UPON DISASSEMBLY, THE FOLLOWING DISCREPANCIES W	ERE NOTED, RENDERING UNIT INOPERATIVE.  AGENT REMOVED NOT HALON 1301 AS SPECIFIED.  ADDITIONAL COPPER DISK INSTALLED UND	ER SAFETY PLUG.  (PLUG IN BLOWN CONDITION).  RUPTURED DISK NOT RECOGNIZED AS APPROVED PART.  GAUGE READS 'O' PSI.  FAA N	OTE:  PART ORIGINATED OUTSIDE U.S.			2	L	7	4 	4J			F	4A25    					 
1997100200070	19971002	00070	WP  	1997	10	2	97ZZZX4198       	1	19970905	G	7110	5162658	COWLING         			DOUG  	DC4   	C54BDC      	3021516	WP  										NR 2 ENG LT	TORN            	D	L	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	44911					10461				LOWER PORTION OF COWLING MOVED INTO PROPELLER.  COWLING ALIGNMENT PIN MAY HAVE MOVED OUT OF ITS SLOT WHEN THE LEFT HAND 	COWL WAS REMOVED THEN REINSTALLED.  THIS WOULD LET THE WHOLE COWL ASSEMBLY ROTATE.  IF THE COWL ASSEMBLY ROTATES APROXIM	ATELY 2 TO 3 INCHES, IT WILL LEAVE ITS ALIGNMENT LUGS AND BECOME LOOSE.  THIS IS WHAT IS BELIEVED TO HAVE HAPPENED DUE T	O THE RUB MARKS ON THE COWL AND EXPERIMENTS ON THE AIRCRAFT.  DOUGLAS SB DC-4 NR 46 HAD NOT BEEN C/W IN THIS APPLICATION	.  DOUGLAS SB DC-4 NR 46 IS BEING C/W ON THE ENTIRE FLEET.		2	L	7	4 	4R				A762    					 
1997100200072	19971002	00072	CE  	1997	10	2	97ZZZX4200       	1	19970801	G	3510	101380491	HOSE            			BEECH 	200   	B200        	1152922	CE  										OXYGEN SYSTEM	SPLIT           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8093W	1861 				BB1396				OXYGEN HOSE IN LEFT HEADLINER AFT OF COCKPIT 'D' WINDOW WAS FOUND SPLIT WHEN SYSTEM WAS ACTIVATED.  HOSE IS A SHORT FLEX	IBLE HOSE THAT IS VERY TWISTED WHEN INSTALLED.  RECOMMEND A REPLACEMENT OF SHORTER OXYGEN HOSE FOR THIS AREA.					1	L	7	2 	4T				A24CE   					 
1997100200073	19971002	00073	WP  	1997	10	2	97ZZZX4201       	2	19970913	G	7261	30719499	REGULATOR       			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					OIL PUMP	MALFUNCTION     	D				E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			SW	99	97LT		1298 		614057316	202				DURING CLIMB THROUGH 18,000 FEET, OIL PRESSURE INCREASED TO 58 PSI, JUST BELOW RED LINE.  AFTER 30 MINUTES WITH OIL PRES	SURE FLUCTUATING AND DROPPING TO 25 PSI, CREW SHUT ENGINE DOWN.  SUSPECT CAUSE STICKING OR FAILED OIL PUMP REGULATOR.  E	NGINE TT:  3,641 HOURS.  CSN:  2,204.				2	L	7	3 	4F	4	F		A46EU   	E6WE				 
1997100200074	19971002	00074	SO  	1997	10	2	97ZZZX4202       	1	19970801	G	5711		SPAR CAPSTRIP   			LUSCOM	8     	8A          	8190104	SO  										WING	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										AS REQUIRED, CONDUCTED THE WING INSPECTION ON LUSCOMBE METAL WING IAW APPENDIX TO FAA AD96-24-17.  FOUND NO INTERGRANULA	R CORROSION.  DID FIND SOME LOOSE INSULATION AND URINE STAINS WHICH WAS EASILY REMOVED WITH COAT HANGERS AND BY SPRAYING	 OUT THE WING WITH A HOSE.  WHILE LIFTING THE WING TO INSPECT THROUGH THE STRUT HOLE AND AT THE INBOARD ROOT AREA HEARD 	A 'POP' IN THE WING THAT WAS NOT EXPECTED, THOUGHT IT MIGHT BE OIL CANNING OF THE SKINS IN THE WING TOP.  LATER INSPECTI	ON FOUND THE CABIN ROOF SKIN HAD BEEN DEFORMED AT THE WING ROOT, AND THAT THE REAR SPAR CAPSTRIP HAD SEPARATED FROM THE 	SPAR WEB AT THE WING ATTACHMENT FITTING.  THE CRACK IS .75 INCH LONG.	1	H	7	1 	3O				A694    					 
1997100200075	19971002	00075	SO  	1997	10	2	97ZZZX4203       	1	19970829	G	2510	79536000	FRAME ASSY      			PIPER 	PA28  	PA28140     	7102802	SO  										COCKPIT	BROKEN          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	2269Q	4775 				287725189				WHILE REPLACING SEAT COVERING, FOUND SEAT FRAME TUBING BROKEN AND SEPARATED AT BOTH LEFT AND RIGHT FRONT POINTS WHERE SE	AT FRAME IS WELDED TO VERTICAL SUPPORT THAT CONTAINS SEAT TRACK CLAMP.  THIS SEAT HAS BEEN IN SERVICE FOR 20 YEARS.  SUS	PECT CAUSE:  THE STRESS OF MANY LANDINGS AND TAKEOFFS AND LOTS OF PUSHING ON THE SEAT BACK BY USERS.				1	L	7	1 	3O				2A13    					 
1997100200076	19971002	00076	SO  	1997	10	2	97ZZZX4204       	2	19970909	G	7414	36066	DRIVE GEAR      	SLICK       	4201        	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					RT MAG	TEETH STRIPPED  	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	05	11308	98   			90020099	15075317	251159			RUN-UP AT 1,700 RPM AT PROP OF 300 RPM ON THE RT MAG WAS NOTICED, LT MAG AT 1,800-1,900 RPM.  ENGINE STARTED TO BACKFIRE	 WHILE RUNNING ON THE RT MAG.  DECIDED NOT TO TAKE OFF, BROUGHT THE AIRPLANE OVER TO MAINTENANCE.  RT MAG REMOVED AND MA	G DRIVE GEAR HAD 3 TEETH MISSING.  ENGINE WAS REMOVED.  ENGINE HAD 98 HOURS ON TACHOMETER SINCE MAJOR OVERHAUL.				1	H	7	1 	3O	3	O		3A19    	E252				 
1997100200077	19971002	00077	SO  	1997	10	2	97ZZZX4205       	1	19970801	G	3233	21151	ACTUATOR        	WIEBEL      		PIPER 	PA31  	PA31P350    	7103111	SO  										MLG	FAULTY          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	237MA	2961 				31P8414037				PILOT REPORTED INDICATION OF UNWANTED LANDING GEAR EXTENSION.  AFTER TROUBLESHOOTING HYDRAULIC SYSTEM, FOUND RT MAIN ACT	UATOR O-RING AND SCRAPER SEAL ARE OLD.  TEST FLIGHT OK, NO PROBLEM.					1	L	7	2 	3O			RT	A8EA    					 
1997100200078	19971002	00078	EA  	1997	10	2	97ZZZX4206       	2	19970909	G	8520	81619401	BEARING         			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					ENGINE	FLAKED          	B			EIRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	252MA	32   				31P33	RL37262			ENGINE REMOVED AFTER FINDING BEARING MATERIAL IN OIL SCREEN.  DISASSEMBLED, FOUND ABOUT 1.5 SQUARE INCHES OF MATERIAL FL	AKED OFF OF BEARING.  SUSPECT POOR BOND TO BEARING.					1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1997100200079	19971002	00079	SO  	1997	10	2	97ZZZX4207       	2	19970801	G	7320	630119	FITTING         		6405636A1   	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					LT ENGINE	BROKEN          	B	S	A	VIB3	O				OTHER                   				K	Y		FLUID LOSS                	ENGINE STOPPAGE           		CR	CRUISE         	1			SO	03	34ME					347870045				FITTING BROKE IN THREADS WHERE THEY SCREW INTO THROTTLE CONTROL.  ENGINE QUIT IN FLIGHT.  CONTINUED FLIGHT ON OTHER ENGI	NE TO BNA.  PILOT SAW FUEL COMING FROM COWLING AFTER ENGINE QUIT.  REMOVED AND REPLACED BROKEN FITTINGS.  LEAK AND OPS C	HECK OK.  FITTING APPEARED DAMAGED BY PREVIOUS REMOVAL ATTEMPT.  THIS AREA IS MISTAKEN FOR HAVING A SCREEN TO INSPECT, B	UT NO SCREEN IS INSTALLED.			1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1997100200080	19971002	00080	SO  	1997	10	2	97ZZZX4208       	1	19970909	G	5321		FLOOR PANEL     			PIPER 	PA23  	PA23250     	7102308	SO  										BAG COMPT	DAMAGED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	40599	7586 				277405345				REAR BAGGAGE FLOOR DAMAGED FROM ABUSE LOADING FREIGHT.						1	L	7	2 	3O				1A10    					 
1997100200081	19971002	00081	NE  	1997	10	2	97ZZZX4209       	2	19970911	G	7414	1068256011	MAGNETO         	BENDIX      	D6LN3000    	MAULE 	M6    	M6235       	5460160	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					ENGINE	CASE CRACKED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	56464	3158 	388  		4678	7416C	L2187448A			MAGNETO CASE BROKEN AT TOP HOLD-DOWN LOCATION.  DISCREPANCY DISCOVERED DURING 100-HOUR INSPECTION.						1	H	7	1 	3O	3	O		3A23    	1E4				 
1997100200082	19971002	00082	GL  	1997	10	2	97ZZZX4210       	3	19970731	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	SPINNER	CHAFED          	B	L		DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	67510	44   				15281879		RB003		REPLACED PROPELLER DUE TO FAILED AD 97-06-16.  NEW PROPELLER HAS A LARGER HUB AND THERE IS INTERFERENCE WITH PROPELLER S	PINNER.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997100200084	19971002	00084	EA  	1997	10	2	97ZZZX4212       	2	19970801	G	8530	7510	COVER PLATE     			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					NR 1 INTAKE	DISPLACED       	G				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	07	9595M		75   			670172	L391451A			ENGINE BEGAN TO RUN ROUGH IN FLIGHT, PRECAUTIONARY LANDING.  FOUND INTAKE ROCKER SHAFT ON NR 1 CYLINDER HAD MOVED OUT OF	 POSITION DUE TO LOSS OF COVER PLATE, 7510.  CAUSE OF COVER PLATE LOSS UNDETERMINED.  SUBMITTER RECOMMENDS PERIODICAL RE	-CHECK OF COVER PLATE NUT TORQUE.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1997100200085	19971002	00085	EU  	1997	10	2	97ZZZX4213       	1	19970905	G	6220	704A33633156	STOP BEARING    			SNIAS 	350   	AS350B      	8680801	EU  										BLUE BLADE	FAILED          	H				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	13	4AK	2193 				2544				PILOT REPORTS VERTICAL VIBRATION AND RETURNED TO BASE.  INSPECTION REVEALED 'BLUE' M/R SPHERICAL STOP BEARING, P/N 204A3	3-633 156, FAILED.  REPLACED ALL THREE M/R SPHERICAL STOPS WITH P/N 704A33633-109.  RUN-UP OPS CHECK GOOD.					1	G	7	1 	3U				H9EU    					 
1997100200086	19971002	00086	EU  	1997	10	2	97ZZZX4214       	1	19970915	G	2913	5026780	PUMP            			SNIAS 	350   	AS350BA     	8680817	EU  										HYDRAULIC SYSTEM	WORN SPLINE     	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	13	599BK	5640 			20221913	2735				DURING IN-FLIGHT, HYDRAULIC LIGHT ILLUMINATED AND HYDRAULIC HORN CAME ON.  PILOT MADE A PRECAUTIONARY LANDING AT AIRPORT	 TERMINAL.  INSPECTED HYDRAULIC PUMP AND FOUND WORN SPLICE.  REMOVED HYDRAULIC PUMP ASSY AND INSTALLED SERVICEABLE HYDRA	ULIC PUMP ASSY.				1	G	7	1 	3U			NC	H9EU    					 
1997100200087	19971002	00087	EA  	1997	10	2	97ZZZX4215       	2	19970815	G	8530		PISTON PIN      			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480G1D6   	41527	EA  					CYLINDER NR 5	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	2FOR	499  			17328	1244	L33937			OPERATORS WERE NOTIFIED AIRCRAFT'S ENGINE CONTAINED A PISTON PIN FROM THE BATCH LISTED IN LYC SB 527C.  AIRCRAFT WAS REM	OVED FROM SERVICE AND ALL CYLINDERS REMOVED TO VISUALLY INSPECT FOR BATCH NR 17328.  CYLINDER NR 5 REVEALED BROKEN PIN. 	 NUMERS WERE NOT CLEARLY VISIBLE, SO ALL PINS WERE CHANGED WITH NEW PINS DIRECT FROM LYCOMING.				1	H	7	1 	3O	3	O		1A8     	E275				 
1997100200088	19971002	00088	CE  	1997	10	2	97ZZZX4216       	1	19970131	G	4920		COMPRESSOR      	SUNDSTRANDEM	T62T404     	RKWELL	NA265 	NA26565     	7630107	CE  										APU	BLADE FAILED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	920DY	296  			795508	46550				PILOTS REPORTED THE APU WAS MAKING A HIGH PITCHED UNUSUAL NOISE.  INSPECTION REVEALED A PIECE OF ONE COMPRESSOR BLADE HA	D BROKEN AND STRUCK SEVERAL OTHER BLADES.  NO OTHER DAMAGE NOTED AT THIS TIME.  APU IS BEING SENT TO A REPAIR FACILITY F	OR FURTHER EVALUATION.  CYCLES, 1,146.				2	L	7	2 	4J				A2WE    					 
1997100200089	19971002	00089	NE  	1997	10	2	97ZZZX4217       	2	19970813	G	7530	10138002521	VALVE           	PARKER      		BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60      	52043	NE  					NR 1 ENG BLEED	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4S				12AJ36	FL107				DISCOVERED ON POST-FLIGHT INSPECTION, NR 1 ENGINE BLEED AIR FLOW CONTROL VALVE HAS A BROKEN CONTROL LINKAGE ARM.  APPEAR	S LIKE BALL SOCKET WORN OUT.  REPLACED BLEED AIR CONTROL VALVE ASSEMBLY WITH NEW UNIT OBTAINED FROM BEECH.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997100900099	19971009	00099	GL  	1997	10	9	97ZZZX4247       	1	19970916	G	2810		VENT            			AMTR  	RANS  	RANSS7      	0561265	GL  										FUEL TANK	PLUGGED         	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			SW	99	8251B					1194142				ON APPROACH, THE ENGINE QUIT CAUSING THE PILOT TO LAND SHORT OF RUNWAY. THE AIRCRAFT RECEIVED DAMAGE TO THE LT MLG, PROP	ELLER, AND RT WING.  INVESTIGATION REVEALED THE LT FUEL TANK WAS EMPTY AND THE RT TANK WAS NEARLY FULL. THE CARBURETOR B	OWLS WERE EMPTY.  BY BACK-BLOWING FROM THE FUEL PUMP LINE, THE RT FUEL TANK WAS PRESSURIZED.   UNABLE TO BLOW BACK THROU	GH VENT.  BUILDER STATED WHEN INSTALLING VENT, HE FOUND IT TO BE BLOCKED AND HAD TO BE RE-DRILLED.  PROBLEM COULD BE WIT	H VENT AS RECEIVED OR MAY HAVE BECOME PLUGGED DURING INSTALLATION.  SUGGEST VENT SYSTEM BE TESTED FOR PROPER OPERATION.		1	H	7	1 	3I			NC	EXPA1H71					 
1997100900100	19971009	00100	SO  	1997	10	9	97ZZZX4248       	2	19970917	G	8530	637837	SPRING          			CESSNA	310   	T310R       	2074246	CE  	CONT  	O520  	TSIO520B    	17040	SO  					NR 3 CYL EXH VLV	BROKEN          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			GL	21		180  					176718R			ENGINE RUNNING ROUGH.  EXHAUST VALVE LEAKING ON COMPRESSION TEST.  FOUND OUTER SPRING BROKEN 180 HOURS S.F.R.						1	L	7	2 	3O	3	O		3A10    	E8CE				 
1997100900101	19971009	00101	GL  	1997	10	9	97ZZZX4249       	1	19970923	G	3213		GEAR LEG        			AMTR  	KITFOX	KITFOX      	05613LZ	GL  										LT MLG	FAILED          	D	S	A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	01	102KM	178  				1702				AFTER AIRCRAFT LANDED ON RUNWAY AND PROCEEDED TO THE TAXIWAY.  THE LEFT LANDING GEAR FAILED AT WELD AREA.						1	H	7	1 	3I			NC	EXPA1H71					 
1997100900102	19971009	00102	CE  	1997	10	9	97ZZZX4250       	1	19970908	G	5711	NAS464P5	BOLTS           			BEECH 	76    	76          	1153005	CE  										WING CENTER	LOOSE           	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	2009X	1486 				ME66				DURING 100-HOUR INSPECTION, THE CENTER SECTION WING BOLTS THAT ATTACH THE LOWER WING SPAR PLATE TO THE WING SPAR (I.E., 	20 WING BOLTS) WERE ALL FOUND UNDERTORQUED BY ONE-HALF TO ONE FULL TURN.  THE NAS464P5 BOLTS SHOULD BE TORQUED 100-140 I	NCH/POUND.				1	L	7	2 	3O				A29CE   					 
1997100900104	19971009	00104	CE  	1997	10	9	97ZZZX4252       	1	19970729	G	2460	M0012	J BOX           	LAMAR       		CESSNA	172   	172RG       	2072438	CE  										FIRE WALL	FAILED          	D				O				OTHER                   				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			WP	07	360ES	266  			80075612	17280010				IN-FLIGHT ELECTRIAL FAILURE OF ALL ELECTRICAL EQUIPMENT BEING SERVICED BY BUS NR 1.  PILOT COMMENTED SPARKS COMING FROM 	UNDERNEATH INSTRUMENT PANEL.  NO BREAKERS TRIPPED.  FOUND WIRE BUNDLE RESTING ON CIRCUIT BREAKER.  WIRE BURNED OUT LAYIN	G ACROSS WARNING BREAKER (WIRE NR BP1307)  MECHANICALLY INSTALLED LUG CONNECTORS TO BUS NR 1, BUS NR 2, BUT SPLICE ABOVE	 WIRE.			1	H	7	1 	3O				3A17    					 
1997100900105	19971009	00105		1997	10	9	97ZZZX4253       	4	19970821	G	6122	34828014	GOVERNOR        	SIGMATEK    		MOONEY	M20   	M20C        	5870208	SW  										PROPELLER	FAULTY          	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	19	3984N	1633 	300  			680012				INSTALLED 3-BLADE PROPELLER IAW STC SA 4529NM.  STC MAKES NO MENTION OF PROPELLER GOVERNOR.  AFTER 3 HOURS OF OPERATION,	 PROPELLER BEGAN SURGING 100-200 RPM FROM 2,400 RPM.  AFTER NUMEROUS TESTS, DETERMINED THE EDO AIRE (GARWIN) PROPELLER G	OVERNOR CANNOT SUPPLY THE VOLUME OF OIL REQUIRED BY THIS PROPELLER.  REMOVED THIS PROPELLER AND RETURNED TO THE ORIGINAL	 2-BLADE HC-C2YK-1BF/F7666A PROPELLER.  OPERATES NORMALLY AFTER 8 HOURS.			1	L	7	1 	3O				2A3     					 
1997100900107	19971009	00107	CE  	1997	10	9	97ZZZX4255       	1	19970918	G	2750	500000863CR	CONTROL CABLE   			CESSNA	414   	414A        	2075907	CE  										RT FLAP	BROKEN          	B			DBCR	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	13	444BC					414A0340				PILOT REPORTED LOUD BANG WHEN FLAPS SELECTED DOWN.  LEFT FLAP JAMMED AND RIGHT FLAP WAS UNCONTROLLABLE.  PILOT MANAGED A	 SAFE LANDING.  INSPECTION REVEALED THE RIGHT FLAP EXTEND CABLE HAD BROKEN WHERE THE CABLE WRAPS AROUND THE FIRST SET OF	 PULLEYS OUTBOARD OF THE ACTUATOR.  ALSO, THE TURNBUCKLE AND CABLE TERMINAL ENDS JAMMED THE ACTUATOR RENDERING IT INOPER	ABLE.  THE AREA WHERE THE CABLE SEPARATED IS VERY DIFFICULT TO ACCESS.			1	L	7	2 	3O			 	A7CE    					 
1997101500003	19971015	00003	NE  	1997	10	15	97ZZZX4256       	2	19970824	G	7320	3057T20P02	HARNESS         			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   		CFE73811B   		NE  					LT ENG FADEC	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	790Z	584  				31	105125			FADEC WIRING HARNESS CHAFED WHERE IT PASSES THROUGH CLAMP.  SUBMITTER STATED CLAMP NEEDS CUSHION TO PREVENT WIRE FROM BE	ING DAMAGED.					2	K	7	3 	4F	4	F	RT	A50NM   	E44NE				 
1997100900108	19971009	00108	NM  	1997	10	9	97ZZZX4257       	1	19970919	G	5711	41513102	SPAR CAP        			UNIVAR	415   	415E        	0420308	NM  										RT WING	CORRODED        	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	94827	2361 				4941				SEVERE CORROSION ON LOWER CENTER SECTION SPAR CAP.  CORROSION WAS FOUND AFTER RT WING WAS REMOVED FOR REPAIR DURING ANNU	AL INSPECTION.  CORROSION CANNOT BE DETECTED WITH WING INSTALLED.  SUBMITTER RECOMMENDED PANEL BE INSTALLED ON BOTTOM SK	IN PANEL TO CHECK FOR CORROSION.				1	L	7	1 	3O				A787    					 
1997100900109	19971009	00109	NE  	1997	10	9	97ZZZX4258       	1	19970918	G	2120		HOSE            			CONAER	LA4   	LA4200      	5110310	NE  										ALTERNATOR	OMITTED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	9WA					520				THE 2-6050-27 HOSE CONNECTS THE ALTERNATOR COOLING PORT TO THE FLEXIBLE DUCT (SCAT HOSE) THAT BRINGS AIR FROM ABOVE ENGI	NE TO THE ALTERNATOR.  THIS NON-CONDUCTIVE HOSE HAD BEEN OMITTED (AFTER ENGINE CHANGE) WHICH ALLOWED THE WIRE IN THE FLE	X DUCT TO CHAFE ON AND MAKE CONTACT WITH THE ALTERNATOR FIELD TERMINAL CAUSING ALTERNATOR/REGULATOR FAILURE.				1	H	7	1 	3O				1A13    					 
1997100900110	19971009	00110		1997	10	9	97ZZZX4259       	4	19970921	G	2561	KSD35	LIFE VEST       	EAAEROMARINE																CELL	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					F99068					LIFE VEST FAILED 2-POUND PSI TEST.																			 
1997100900111	19971009	00111		1997	10	9	97ZZZX4260       	1	19970901	G	2432	BTCA520	BATTERY         	MARATHON    																CELL ASSY	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										FOUND EXCESSIVE FOAMING OF CELLS.  EXCESSIVE SALTS ON TOP/BOTTOM OF BATTERY CAN ASSY.  ONE CELL HAD HOLE THROUGH PLASTIC	 CASING.																		 
1997100900112	19971009	00112	GL  	1997	10	9	97ZZZX4261       	1	19970911	G	5312		BONDING         			DIAMON	DA20A1	DA20A1      	05626UX	GL  										TAILCONE BLKHD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	332CH	904  				10032				DURING A PRE-PURCHASE INSPECTION, A CRACK WAS NOTICED IN THE BONDING PASTE (THICKENED RESIN) ATTACHING THE AFT BULKHEAD 	TO THE TAIL CONE AT THE LOWER LEFT CORNER.  THE CRACK IS 2.25 INCHES LONG.  THE MANUFACTURER STATED THIS TYPE OF CRACK O	CCURS FROM STRIKING THE TAIL ON THE GROUND (OVER ROTATING) ON TAKEOFF.  SUBMITTER RECOMMENDED INSTALLING A SHOCK ABSORBI	NG MATERIAL ONTO THE TAIL SKID IN PLACE OF THE NYLON ABRASION STRIP.			1	L	7	1 	3O			NT	TA4CH   					 
1997100900113	19971009	00113	EA  	1997	10	9	97ZZZX4262       	2	19970919	G	7322	HA6	CARBURETOR      	FACET       		CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					MIXTURE	STOP WORN       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4975V				DL41158	172RG0440				FULL THROTTLE STOP WORN CAUSING A LEAN MIXTURE.  WHEN THE PART IS FULL RICH WITH THE SCREW TYPE MIX CONTROL, PRESSURE IS	 PUT ON THE FULL RICH STOP.  STOP IS BEHIND A COVER PLATE WHICH HAMPERS VISABILITY.  WEAR CAUSES THE METER HOLE ON MIXTU	RE TO OVER-CENTER CAUSING A MORE LEAN MIXTURE.				1	H	7	1 	3O	3	O		3A17    	E286				 
1997100900114	19971009	00114	CE  	1997	10	9	97ZZZX4263       	1	19970801	G	3260		MOUNT           			PIPER 	PA24  	PA24180     	7102402	CE  										GEAR WARN SWITCH	DISPLACED       	D				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			SW	17	7667P	3121 				242880				AIRCRAFT WAS LANDED GEAR-UP ON GRASS RUNWAY.  PILOT STATED HE HEARD NO WARNING HORN.  WHEN LIFTED AIRCRAFT TO LOWER GEAR	, HORN CHECKED INOPERABLE.  CLOSER LOOK SHOWED THE SWITCH MOUNT ON THROTTLE HAD BEEN PUSHED AWAY FROM A SHAFT NOT ALLOWI	NG SWITCH TO OPERATE.  ALSO, SWITCH WAS ADJUSTED TO MAXIMUM POSITION AWAY FROM THROTTLE ROD.  THE SWITCH MOUNT LOOKED LI	KE IT WAS MOVED FROM CONTACT WITH WIRE BUNDLE ROUTED ABOVE SWITCH.  RECOMMEND CHECK CLEARANCE BETWEEN SWITCH MOUNT AND A	NYTHING ROUTED NEARBY.		1	L	7	1 	3O			NT	1A15    					 
1997100900116	19971009	00116	EA  	1997	10	9	97ZZZX4265       	2	19970919	G	8530	60828	PIN PLUG        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					PISTON	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9083D					288690050	L3125536A			PISTON PIN PLUG FAILURE DUE TO PISTON PIN MIGRATION FORCING THE PLUG TO THE BARREL WALL.  UPON ZERO COMPRESSION CHECK, R	EMOVED CYLINDER AND PLUG WAS FOUND IN A SMALL BALL RIDING WITHIN THE PISTON PIN.  BOTH COMPRESSION RINGS AND OIL CONTROL	 RING DAMAGED ALONG WITH CAM AND CAM FOLLOWER.				1	L	7	1 	3O	3	O		2A13    	E286				 
1997100900117	19971009	00117	SO  	1997	10	9	97ZZZX4266       	2	19970902	G	7322	MA45	CARBURETOR      			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					SERIAL NUMBER	NOT MARKED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	952CC				CL02472	18263638				CARBURETORS BEING PRODUCED BY PRECISION AIRMOTIVE ARE NOT IN C/W MARVEL-SCHEBELER AD 63-22-03. THE LETTER 'V' IS NOT STA	MPED UNDER THE SERIAL NUMBER.  SUBMITTER STATED REQUIRE PRECISION AIRMOTIVE TO RECERTIFY ALL CARBURETORS THEY HAVE PRODU	CED THIS WAY OR REVISE AD 63-22-03 TO REFLECT THE CURRENT MANUFACTURING PROCESS.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1997100900162	19971009	00162	SO  	1997	10	9	97ZZZX4267       	2	19970902	G	7322	MA45	CARBURETOR      			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					SERIAL NUMBER	NOT MARKED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	953CC				CL02784	18264109				CARBURETORS BEING PRODUCED BY PRECISION AIRMOTIVE ARE NOT IN COMPLIANCE WITH MARVEL-SCHEBELER AD 63-22-03.  THE LETTER '	V' IS NOT STAMPED UNDER THE SERIAL NUMBER.  SUBMITTER STATED REQUIRE PRECISION AIRMOTIVE TO RECTIFY ALL CARBURETORS THEY	 HAVE PRODUCED THIS WAY OR REVISE AD 63-22-03 TO REFLECT THE CURRENT MANUFACTURING PROCESS.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1997101500005	19971015	00005	SO  	1997	10	15	97ZZZX4268       	2	19970902	G	7322	MA45	CARBURETOR      			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470R       	17026	SO  					SERIAL NUMBER	NOT MARKED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	954CC				BD0115	18265290				CARBURETORS BEING PRODUCED BY PRECISION AIRMOTIVE ARE NOT IN COMPLIANCE WITH MARVEL-SCHEBELER AD 63-22-03.  THE LETTER '	V' IS NOT STAMPED UNDER THE SERIAL NUMBER.  SUBMITTER STATED REQUIRE PRECISION AIRMOTIVE TO RECTIFY ALL THE CARBURETORS 	THEY HAVE PRODUCED THIS WAY OR REVISE AD 63-22-03 TO REFLECT THE CURRENT MANUFACTURING PROCESS.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997100900163	19971009	00163		1997	10	9	97ZZZX4269       	1	19970918	G	3710	D9181	FILTER          	AIRBORNE    																VAC SYS	FAILED          	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07										WHEN INSTALLING VAC SYS FILTER, ONE OF THE FILTER ENDS STARTED TO BREAK APART.																			 
1997100900164	19971009	00164	CE  	1997	10	9	97ZZZX4270       	1	19970901	G	2710	0510105224	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  										LT AILERON	FRAYED          	B		A	ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	13378	4101 				17262714				LEFT PRIMARY AILERON CABLE WAS FOUND FRAYED DURING ROUTINE INSPECTION.  SEVERAL HARD TO SEE AREAS OF CABLE WERE FRAYED (	TOTAL TIME ON CABLE 4,101.1 HOURS.  SUBMITTER RECOMMENDED CABLES BE REPLACED ON A TIME CHANGE BASIS, CABLE PN 0510105-22	4.				1	H	7	1 	3O			NT	3A12    					 
1997100900165	19971009	00165	SO  	1997	10	9	97ZZZX4271       	1	19970925	G	3244	65010	TIRE            	GOODYEARAERO		PIPER 	PA31T 	PA31T       	7103124	SO  										LT/RT MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SW	99	160NA	187  				31T7720060				AFTER LANDING AND TAXI IN, NOTICED THE LT TIRE S/N 414622043304 HAD A BULGE ON THE INBOARD SIDE OF THE TREAD AND SIDE WA	LL AREA.  THIS TIRE WAS REMOVED AND REPLACED WITH NEW.  NEXT FLIGHT, RT TIRE S/N 41462322 LOST ITS TREAD ON INBOARD SIDE	 FULL CIRCUMFERENCE DURING TAKEOFF, BREAKING OFF THE RT INBOARD GEAR DOOR ACTUATOR BOTTOM FITTING.  AS THE GEAR RETRACTE	D, HYDRAULIC FLUID FOR THE ENGINE DRIVEN PUMPS WAS DEPLETED, AND GEAR HAD TO BE HAND PUMPED DOWN USING EMERGENCY PROCEDU	RES.  THE TIRE REMAINED PROPERLY INFLATED AND AN UNEVENTFUL LANDING WAS MADE.  SUBMITTER STATED TIRES WITH S/N'S 41468XX	X MAY BE A BAD BATCH.  CAREFULLY INSPECT TIRES WITHIN THIS S/N RANGE.	1	L	7	2 	3T				A8EA    					 
1997100900166	19971009	00166	CE  	1997	10	9	97ZZZX4272       	1	19970917	G	3340	GE4522	LANDING LIGHT   			CESSNA	172   	172M        	2072418	CE  										BULB	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	20402	59   				17261261				LANDING LIGHT REPLACED FOR BROKEN ELEMENT.  THIS LAMP, AS WELL AS THE 4509 AND THE 4596, HAVE DETERIORATED TO THE POINT 	THE AVERAGE LIFE IS 50 HOURS TACH TIME.					1	H	7	1 	3O			NT	3A12    					 
1997100900167	19971009	00167	SO  	1997	10	9	97ZZZX4273       	1	19970922	G	5720	6206102	DOUBLER         			PIPER 	PA28  	PA28161     	7102803	SO  										WING WALK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	8079Y	6547 				288016049				THE WING WALK SKIN WAS FOUND TO SAG WHEN STEPPED ON.  INVESTIGATION REVEALED THE REINFORCEMENT DOUBLER RIVETED TO THE UN	DERSIDE OF THE WING WALK SKIN WAS CRACKED ALL ALONG THE BUTT RIB AREA.					1	L	7	1 	3O				2A13    					 
1997100900168	19971009	00168	CE  	1997	10	9	97ZZZX4274       	1	19970922	G	2810	303013	FUEL CELL       			CESSNA	206   	U206F       	2073333	CE  										FITTINGS	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	8433Q				534	U20603292				FUEL CELL IS AN FAA/PMA REPLACEMENT FOR CESSNA PN 1200065-13.  THE CONDITION AT REMOVAL WAS -- PERISHED.  THE FITTINGS D	ISINTEGRATED.  THE TANK ITSELF WAS IN OK CONDITION, BUT ALL THE PARTS THAT WERE SUPPOSED TO BE BONDED TO THE TANK JUST P	ULLED OFF LIKE THE BONDING WAS NOT CORRECTLY DONE.  THIS TANK WAS MAINTAINED FULL AT ALL TIMES AND REFILLED AFTER FLIGHT	.  FUEL CELL MANUFACTED BY:  A.I.R., MEMPHIS, TN.  DATE OF MANUFACTURE:  3/90.  CONSTRUCTION NR:  P2315.			1	H	7	1 	3O				A4CE    					 
1997100900169	19971009	00169	CE  	1997	10	9	97ZZZX4275       	1	19970922	G	2810	303012	FUEL CELL       			CESSNA	206   	U206F       	2073333	CE  										FITTINGS	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	8433Q				586	U20603292				FUEL CELL IS AN FAA/PMA REPLACEMENT FOR CESSNA PN 1200065-12.  THE CONDITION AT REMOVAL WAS -- PERISHED.  THE FITTINGS D	ISINTEGRATED.  THE TANK ITSELF WAS IN OK CONDITION, BUT ALL THE PARTS THAT WERE SUPPOSED TO BE BONDED TO THE TANK JUST P	ULLED OFF LIKE THE BONDING WAS NOT CORRECTLY DONE.  THIS TANK WAS MAINTAINED FULL AT ALL TIMES AND REFILLED AFTER FLIGHT	.  FUEL CELL MANUFACTURED BY A.I.R. OF MEMPHIS, TN.  DATE OF MANUFACTURE:  9/90.  CONSTRUCTION NR:  P2315.			1	H	7	1 	3O				A4CE    					 
1997100900170	19971009	00170	SO  	1997	10	9	97ZZZX4276       	1	19970909	G	5610		WINDOW          			MAULE 	M5    	M5210TC     	5460140	SO  										RT FRONT	RIVETS FAILED   	H		A		O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	11	56294					9001C				FRONT WINDOW RIVETS FAILED IN-FLIGHT LEADING TO TOTAL LOSS OF RT FRONT WINDOW FROM THE AIRCRAFT.  TT:  902 HOURS.						1	H	7	1 	3O			NC	3A23    					 
1997100900171	19971009	00171	NE  	1997	10	9	97ZZZX4277       	3	19970917	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		4652 			2623NR			HJ423		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	 
1997100900172	19971009	00172	NE  	1997	10	9	97ZZZX4278       	3	19970917	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		4529 			2772NR			HJ454		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	 
1997100900174	19971009	00174	EA  	1997	10	9	97ZZZX4279       	1	19970729	G	3260	601577889	HARNESS         			CNDAIR	CL600 	CL6002B16   	1900305	EA  										NLG WIRING	DEFECTIVE       	C				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			EA	11	1622	2385 				5077				AFTER TAKEOFF UPON GEAR RETRACTION, GREEN LIGHTS OUT, RED LIGHT IN HANDLE FLASHING.  RED DOOR OPEN LIGHT ON.  AIRCRAFT R	ETURNED TO AIRPORT.  REPLACED THE NOSE LANDING GEAR WIRING HARNESS PN 601-57788-9.  C/W LANDING GEAR RETRACTION AND EXTE	NSION CHECK.  OPS CHECK OK.  WORK PERFORMED BY GARRETT AVIATION SERVICES IAH CRS XB1R606K W/O 36279.				2	L	7	2 	4F			RT	A21EA   					 
1997100900175	19971009	00175	CE  	1997	10	9	97ZZZX4280       	1	19970731	G	5751	258WS21419A	BEARING         		259GWG1111A 	RAYTHN	DH125 	HAWKER800XP 		CE  										LT AILERON HINGE	FAILED          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	2169X				DHB589	258315				INSTALLED NEW AILERON HINGE BEARING ASSY.  DURING INSTALLATION OF AILERON HINGE BOLT, BEARING CAME APART.  HAD BEARING A	SSY BEEN ASSEMBLED AND INSPECTED PER S26-4558 SPEC, ITEM WOULD NOT HAVE BEEN SOLD TO OUTSIDE COMPANY AS SERVICEABLE PART	.				2	L	7	2 	4F			RT	A3EU    					 
1997100900176	19971009	00176	NE  	1997	10	9	97ZZZX4281       	2	19970918	G	7322	7191991	DRIVE GEAR      	HAMSTD      	7436025     						PWA   	JT8   	JT8D1       	52044	NE  					FUEL CONT	WORN            	B			BN4R	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			WP	05		71968	3536 		92097					ENGINE AUTO ACCEL AT TAKEOFF.  WORN SPLINES ON FUEL CONTROL DRIVE GEAR LED TO ZERO SPEED FAIL SAFE FUEL FLOW.  DRIVE GEA	R AND DRIVESHAFT WERE REPLACED.										4	F			E2EA				 
1997100900177	19971009	00177	CE  	1997	10	9	97ZZZX4282       	1	19970805	G	3241	AC039803	MAXERET COVER   		AHA1814     	RAYTHN	DH125 	HAWKER800XP 		CE  										NR 2 MAIN WHEEL	DAMAGED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	2169X	11   			UK036	258315				LEFT MAIN GEAR MAXERET COVERS CUT ALMOST IN TWO.  CAUSE:  MAIN WHEEL AXLE NUT RETAINING BOLT PN DHS1426-5DD NOT INSTALLE	D CORRECTLY.  BOLT IS SUPPOSED TO BE CUT AT INSTALLATION TO CLEAR INSIDE OF MAXERET COVER.  HOWEVER, THE MM IS NOT CLEAR	.  IT DOES NOT SAY TO CUT BOLT AT INSTALLATION AND WHEN NEW BOLTS ORDERED FROM I.P.C., IT COMES TOO LONG.				2	L	7	2 	4F			RT	A3EU    					 
1997100900178	19971009	00178	CE  	1997	10	9	97ZZZX4283       	1	19970805	G	3241	AC039803	MAXERET COVER   		AHA1814     	RAYTHN	DH125 	HAWKER800XP 		CE  										NR 1 MAIN WHEEL	DAMAGED         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	2169X	11   			UK022	258315				LEFT MAIN GEAR MAXERET COVERS CUT ALMOST IN TWO.  CAUSE:  MAIN WHEEL AXLE NUT RETAINING BOLT PN DHS1426-5DD NOT INSTALLE	D CORRECTLY.  BOLT IS SUPPOSED TO BE CUT AT INSTALLATION TO CLEAR INSIDE OF MAXERET COVER.  HOWEVER, THE MM IS NOT CLEAR	.  IT DOES NOT SAY TO CUT BOLT AT INSTALLATION AND WHEN NEW BOLTS ORDERED FROM I.P.C., IT COMES TOO LONG.				2	L	7	2 	4F			RT	A3EU    					 
1997100900179	19971009	00179	CE  	1997	10	9	97ZZZX4284       	1	19970428	G	2133	1036481	OUTFLOW VALVE   	AIRESRCH    		BEECH 	90    	C90         	1152913	CE  										CABIN	FAILED          	D		A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SO	05	22BM	6290 			203034	LJ360				AFTER TAKEOFF, CABIN PRESSURIZATION STARTED TO PRESSURIZE TO 6,000 FEET CLIMB UNTIL THE SAFETY VALVE OPENED, THE CABIN W	ENT TO A 6,000 FOOT DESCENT. THE CABIN CONTINUED TO OSCILLATE IN THIS MANNER UNTIL PILOT DUMPED THE CABIN AND CONTINUED 	UNPRESSURIZED.  ON TEST FLIGHT, MECHANIC FOUND VALVE RETAINER PLUG BLOCKING OUTLET CAUSING PRESSURIZATION FLUCTUATION. D	EFECT IS COVERED IN BEECH SL (SL 1162 AND SL 1109) AND AIRESEARCH 5-2243, BUT DOES NOT COVER PART NUMBER OR SERIAL NUMBE	R OF DEFECTIVE VALVE.  THIS COULD CAUSE A SERIOUS PROBLEM IF THERE IS AN UNKNOWN SAFETY VALVE DEFECT.		1	L	7	2 	3T				3A20    					 
1997100900180	19971009	00180	CE  	1997	10	9	97ZZZX4285       	1	19970908	G	2742	EM440	ACTUATOR        			CESSNA	650   	650         	2076802	CE  										SECONDARY TRIM	MALFUNCTION     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	2606		5    			650194				DURING PREFLIGHT, DISCOVERED THE SECONDARY TRIM OPERATED BACKWARDS.  THE OVERHAULED ACTUATOR WAS INSTALLED 5 HOURS PREVI	OUSLY.  SUBMITTER STATED REVIEW OVERHAUL, FUNCTIONAL TEST AND QUALITY CONTROL PROCEDURES AT ELECTROMECH TECHNOLOGIES.  F	OLLOW MM PROCEDURES AFTER INSTALLATION.				2	L	7	2 	4F				A9NM    					 
1997100900181	19971009	00181	SO  	1997	10	9	97ZZZX4286       	1	19970909	G	8120	LW15592832	CLAMP           			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					TURBOCHARGER	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	07	722ET	295  				463047	L971461A			AT ALTITUDE, TURBOCHARGER FAILED DUE TO INTER COOLER CLAMP SEPARATION.  THIS IS SECOND SET OF CLAMPS THAT HAVE SEPARATED	.  THE CRIMPED END HAS COME APART.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
1997100900182	19971009	00182	NE  	1997	10	9	97ZZZX4287       	2	19970722	G	7260	3020692	BEVEL GEAR      		3020694     	CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					GEARBOX	FRACTURED       	B			APJR	E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			EA	11	787BA	5014 	3254 		1092	5000143	PCE76357			THE ACCESSORY GEARBOX MAIN DRIVESHAFT HAD FRACTURED. THE REPORTED IN-FLIGHT SHUTDOWN WAS A RESULT FROM FRACTURE OF THE A	CCESSORY GEARBOX MAIN SHAFT DRIVE BEVEL GEAR DUE TO FATIGUE INITIATING AT A GEAR TOOTH RADIUS.  THE FRACTURED GEAR CAUSE	D MECHANICAL DAMAGE TO ITS MATING INPUT GEAR TEETH AND GOUGED BOTH THE GEARBOX HOUSING AND ITS COVER.  TO ALLEVIATE THIS	 CONDITION, A GEAR FEATURING AN INCREASED MATERIAL THICKNESS AT THE GEAR WEB WAS INTRODUCED INITIALLY BY SB 7152 (2-80),	 SUPERSEDED BY SB 7258 (6-87), THEN BY SB 7269 (3-88) FEATURING GEARS MANUFACTURED FROM SUPERIOR MATERIAL AND ACCOMMODAT	ING LARGER BACK LASH.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997100900183	19971009	00183		1997	10	9	97ZZZX4288       	4	19970910	G	3415	99120769	SWITCH          			CESSNA	500   	550         	2076604	CE  										MACH AIRSPD WARN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	846HS		629  			5500669				DURING POST-FLIGHT CHECK, THE MACH AIRSPEED WARNING SYSTEM WOULD NOT TEST PROPERLY.  TROUBLESHOOTING REVEALED A BAD MACH	 AIRSPEED WARNING SWITCH.  REPLACED SWITCH AND SYSTEM TESTED AND OPERATED CORRECTLY.  SUBMITTER STATED THIS SWITCH HAS P	OOR RELIABILITY.  THIS IS THE 3RD SWITCH REPLACED IN 12 MONTHS.  FAILURE OF THE SWITCH CAUSES THE CREW TO LOSE MACH OVER	SPEED WARNING.			1	L	7	2 	4F				A22CE   					 
1997100900184	19971009	00184	SO  	1997	10	9	97ZZZX4289       	1	19970905	G	2613	1173T119	SWITCH          			GULSTM	G1159 	GIV         	3980115	SO  										RT ALT OVERHEAT	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	25	399CC	4234 			2496	1051				AIRCRAFT DEPARTED. EN ROUTE EXPERIENCED RT ENGINE ALTERNATOR OVERHEAT MESSAGE ON EICAS.  PIC TOOK CORRECTIVE ACTION AND 	RETURNED.  TROUBLESHOOTING REVEALED RT ALT OVERHEAT SWITCH FAILED IN TRIPPED CONDITION.  REMOVED AND REPLACED WITH NEW S	WITCH.  OPS CHECK AOK.				2	L	7	2 	4F			RT	A12EA   					 
1997100900185	19971009	00185	CE  	1997	10	9	97ZZZX4290       	1	19970904	G	2710	1455077645	CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  										AILERON	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	13	4614N					5500659				DURING SCHEDULED CABLE INSPECTION, THE AILERON CABALE WHICH RUNS THROUGH THE FUSELAGE WAS FOUND TO HAVE BROKEN STRANDS. 	 UPON RECEIPT OF THE NEW CABLE, FOUND THE TERMINAL END WAS INCORRECT (CLEVIS TYPE INSTEAD OF 'EYE' TYPE).  THE MANUFACTU	RER WAS CONTACTED AND STATED 4 OTHER CABLES WERE FOUND IMPROPERLY MANUFACTURED.				1	L	7	2 	4F			 	A22CE   					 
1997100900186	19971009	00186	CE  	1997	10	9	97ZZZX4291       	1	19970902	G	6120	D60711	PITCH CHANGE ROD			BEECH 	1900  	1900D       	1154162	CE  										PROPELLER	CRACKED         	B			RC2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	03	839CA	1640 			B739	UE36				PITCH CHANGE ROD CRACKED IN LAST THREAD ON ENGINE SIDE.  CRACK PROPAGATED THROUGH THREAD TO INSIDE CAUSING OIL LEAK.  CR	ACK FOUND DURING MAGNETIC PARTICLE INSPECTION AND VERIFIED DURING PRESSURE CHECK OF ROD OUTSIDE OF PROPELLER.  ROD WAS N	EW AT OVERHAUL.				2	L	7	2 	4T			RT	A24CE   					 
1997100900187	19971009	00187	NM  	1997	10	9	97ZZZX4292       	1	19970705	G	2823	D2316P	CONNECTOR       			BOEING	747   	747122      	1384872	NM  										FUEL SOV	MISWIRED        	B			NE1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	33	854FT					19754				APPARENT MALFUNCTION DETECTED DURING OPERATIONAL CHECKS OF THE ENGINE FUEL SHUT OFF VALVES.  IT WAS NOTICED THE INDICATO	R LIGHTS DID NOT RESPOND TO MOVEMENT OF THE ENGINE START LEVERS ON THE PEDESTAL; WHEREAS, NORMAL RESPONSE WAS OBSERVED D	URING OPERATION OF THE FIRE SWITCHES ON THE OVERHEAD PANEL.  INVESTIGATION SHOWED THAT WIRES W629-1Q1221-20 AND 1Q1223-2	0 WERE SPLICED TOGETHER NEAR CONNECTOR D2316P.  THE WIRING DIAGRAM SHOWED THESE WIRES AS TERMINATING IN PINS 12 AND 11 O	F CONNECTOR D2316P.  SIMILAR DISCREPANCIES WERE FOUND FOR EACH OF THE OTHER ENGINE SHUT OFF VALVES.  THE EFFECT OF THIS 	MODIFICATION WAS TO BYPASS THE FUNCTION OF THE ENGINE FUEL SHUT OFF SWITCHES ASSOCIATED WITH THE ENGINE START LEVERS.	2	L	7	4 	4F				A20WE   					 
1997100900188	19971009	00188	NM  	1997	10	9	97ZZZX4293       	1	19970705	G	2823	D2454P	CONNECTOR       			BOEING	747   	747122      	1384872	NM  										FUEL SOV	MISWIRED        	B			NE1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	33	854FT					19754				APPARENT MALFUNCTION DETECTED DURING OPERATIONAL CHECKS OF THE ENGINE FUEL SHUT OFF VALVES.  IT WAS NOTICED THE INDICATO	R LIGHTS DID NOT RESPOND TO MOVEMENT OF THE ENGINE START LEVERS ON THE PEDESTAL; WHEREAS, NORMAL RESPONSE WAS OBSERVED D	URING OPERATION OF THE FIRE SWITCHES ON THE OVERHEAD PANEL.  INVESTIGATION SHOWED THAT WIRES W629-1Q1221-20 AND 1Q1223-2	0 WERE SPLICED TOGETHER NEAR CONNECTOR D2316P.  THE WIRING DIAGRAM SHOWED THESE WIRES AS TERMINATING IN PINS 12 AND 11 O	F CONNECTOR D2316P.  SIMILAR DISCREPANCIES WERE FOUND FOR EACH OF THE OTHER ENGINE SHUT OFF VALVES.  THE EFFECT OF THIS 	MODIFICATION WAS TO BYPASS THE FUNCTION OF THE ENGINE FUEL SHUT OFF SWITCHES ASSOCIATED WITH THE ENGINE START LEVERS.	2	L	7	4 	4F				A20WE   					 
1997100900189	19971009	00189	NM  	1997	10	9	97ZZZX4294       	1	19970822	G	2823	D2454P	CONNECTOR       			BOEING	747   	747122      	1384872	NM  										FUEL SOV	MISWIRED        	B			NE1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	33	853FT					29753				APPARENT MALFUNCTION DETECTED DURING OPERATIONAL CHECKS OF THE ENGINE FUEL SHUT OFF VALVES.  IT WAS NOTICED THE INDICATO	R LIGHTS DID NOT RESPOND TO MOVEMENT OF THE ENGINE START LEVERS ON THE PEDESTAL; WHEREAS, NORMAL RESPONSE WAS OBSERVED D	URING OPERATION OF THE FIRE SWITCHES ON THE OVERHEAD PANEL.  INVESTIGATION CONFIRMED THAT WIRES W629-1Q1221-20 AND 1Q122	3-20 WERE SPLICED TOGETHER NEAR CONNECTOR D2316P.  THE WIRING DIAGRAM SHOWED THESE WIRES AS TERMINATING IN PINS 12 AND 1	1 OF CONNECTOR D2316P.  SIMILAR DISCREPANCIES WERE FOUND FOR EACH OF THE OTHER ENGINE SHUT OFF VALVES. THE EFFECT OF THI	S MODIFICATION WAS TO BYPASS THE FUNCTION OF THE ENGINE FUEL SHUT OFF SWITCHES ASSOCIATED WITH THE ENGINE START LEVERS.	2	L	7	4 	4F				A20WE   					 
1997100900190	19971009	00190	NM  	1997	10	9	97ZZZX4295       	1	19970822	G	2823	D2316P	CONNECTOR       			BOEING	747   	747122      	1384872	NM  										FUEL SOV	MISWIRED        	B			NE1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	33	853FT					29753				APPARENT MALFUNCTION DETECTED DURING OPERATIONAL CHECKS OF THE ENGINE FUEL SHUT OFF VALVES.  IT WAS NOTICED THE INDICATO	R LIGHTS DID NOT RESPOND TO MOVEMENT OF THE ENGINE START LEVERS ON THE PEDESTAL; WHEREAS, NORMAL RESPONSE WAS OBSERVED D	URING OPERATION OF THE FIRE SWITCHES ON THE OVERHEAD PANEL.  INVESTIGATION CONFIRMED THAT WIRES W629-1Q1221-20 AND 1Q122	3-20 WERE SPLICED TOGETHER NEAR CONNECTOR D2316P.  THE WIRING DIAGRAM SHOWED THESE WIRES AS TERMINATING IN PINS 12 AND 1	1 OF CONNECTOR D2316P.  SIMILAR DISCREPANCIES WERE FOUND FOR EACH OF THE OTHER ENGINE SHUT OFF VALVES. THE EFFECT OF THI	S MODIFICATION WAS TO BYPASS THE FUNCTION OF THE ENGINE FUEL SHUT OFF SWITCHES ASSOCIATED WITH THE ENGINE START LEVERS.	2	L	7	4 	4F				A20WE   					 
1997100900191	19971009	00191	SO  	1997	10	9	97ZZZX4296       	1	19970904	G	5610	1159SCB31014	WINDSHIELD      			GULSTM	G1159 	G1159A      	3970109	SO  										RT COCKPIT	SHATTERED       	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	19	98RP	2153 			84426473	328				PILOT REPORTED FLYING AT 41,000 FEET.  NOTICED THE WINDSHIELD HEAT LIGHT WAS OUT.  RECYCLED CIRCUIT BREAKER AND SWITCHED	 BACK ON.  AFTER A SHORT PERIOD OF TIME, NOTICED A SMALL CRACK MOVING ACROSS WINDSHIELD, THEN A LOUD POP WAS HEARD AND T	HE OUTER LAYER SHATTERED INTO A SPIDER WEB PATTERN LEAVING A BURN TRAIL ACROSS THE CENTER.  THE CREW SELECTED A LOWER AL	TITUDE AND PRESSURE DIFFERENTIAL.			2	L	7	2 	4F				A12EA   					 
1997100900193	19971009	00193	CE  	1997	10	9	97ZZZX4297       	1	19970901	G	2752	556517538	GEARBOX         			CESSNA	500   	550         	2076604	CE  										FLAP	SHAFT SHEARED   	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	800LA	107  			1116	5500295				DRIVE GEAR SHEARED AT NARROW PORTION OF GEAR. THIS IS UPDATED MODEL THAT IS SUPPOSED TO PREVENT SHEARING SHAFT IN THIS L	OCATION.					1	L	7	2 	4F				A22CE   					 
1997100900194	19971009	00194	CE  	1997	10	9	97ZZZX4298       	1	19970918	G	2730	5052443931	CONTROL CABLE   			BEECH 	90    	E90         	1152914	CE  										ELEVATOR CONTROL	BROKEN          	B	L	A	DBCR	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	13	7TD	2754 				LW276				FOLLOWING TAKEOFF, AIRCRAFT RETURNED DUE TO ELEVATOR MALFUNCTION.  INSPECTION FOUND ELEVATOR CABLE BROKEN DUE TO CHAFE O	N A CLAMP ON THE BLEED AIR LINE.  EMERGENCY GEAR HANDLE FORCES BLEED LINE DOWNWARD ON TO ELEVATOR CABLE.  SUGGEST RE-ROU	TE BLEED LINE.				1	L	7	2 	3T			 	3A20    					 
1997100900195	19971009	00195		1997	10	9	97ZZZX4299       	4	19970527	G	2562	12630423	SWITCH          	DORNEMARGLN 		SLNSBY	T67   	T67M260     	8323006	EU  										ELT	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3045H	917  				2141				WHILE PERFORMING AN ANNUAL ELT INSPECTION, FOUND THE ELT SENSOR DID NOT COME ON.						1	L	7	1 	3O			NT	A73EU   					 
1997100900196	19971009	00196	EA  	1997	10	9	97ZZZX4300       	2	19970811	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LT MAG DRIVE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	40200	1618 				277304997	L398748			FOUND LEFT MAGNETO DRIVE BEARING ASSEMBLY COMING APART. BEARING ASSEMBLY WAS WEARING INTO GEAR RETAINER ASSEMBLY PN LW-1	9096.  SUBMITTER STATES INSPECTION OF THESE PARTS SHOULD BE ACCOMPLISHED EACH TIME MAGNETO IS REMOVED.					1	L	7	2 	3O	3	O		1A10    	1E4				 
1997100900197	19971009	00197	CE  	1997	10	9	97ZZZX4301       	1	19970826	G	2810	929200203	FUEL CELL       			BEECH 	90    	E90         	1152914	CE  										LT NACELLE	LEAKING         	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	03	3700M					LW340				UPON RETURN FROM A CHECK FLIGHT, THE LEFT NACELLE FUEL CELL STARTED LEAKING (MASSIVELY) JUST PRIOR TO ENGINE SHUT DOWN. 	WHEN THE FUEL SHUT OFF VALVES WERE SET TO THE OFF POSITION, FUEL CONTINUED TO LEAK.  AN INVESTIGATION DISCLOSED THE LEFT	 NACELLE MAIN FUEL LINE NIPPLE HAD BECOME BRITTLE AND CRACKED AT THE BLADDER.  DISCUSSIONS WITH BEECH CRAFT AND SEVERAL 	FUEL CELL REPAIR CENTERS INDICATED THAT NIPPLE MATERIAL COMPOSITION HAD BEEN CHANGED AFTER 1979 TO IMRPOVE ITS DURABILIT	Y.  SUBMITTER RECOMMENDED THAT ANY FUEL CELL OVER 15 YEARS OLD BE A CANDIDATE FOR REPLACEMENT OF THE OPERATOR'S CONVENIE	NCE.	1	L	7	2 	3T				3A20    					 
1997100900198	19971009	00198	NM  	1997	10	9	97ZZZX4302       	1	19970801	G	5720	14050R	REINFORCEMENT   			UNIVAR	415   	415C        	0420302	NM  										RT WING	CORRODED        	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	87114	3938 				287				SEVERE CORROSION FOUND DURING ANNUAL.  THIS OCCURED SINCE LAST ANNUAL JULY, 1996.  CORROSION COULD NOT BE OBSERVED THROU	GH INSPECTION HOLES IN WING.  CAN ONLY BE SEEN WITH AILERON FULLY IN UP POSITION AND LOOKING UPWARD FROM THE GROUND.  IT	 IS NOT READILY SEEN LOOKING DOWN THROUGH THE GAP BETWEEN WING AND AILERON.  SUBMITTER RECOMMENDED OTHER OWNERS INSPECT 	BEFORE NEXT FLIGHT AND 3 TO 4 TIMES A YEAR THEREAFTER.			1	L	7	1 	3O				A718    					 
1997100900199	19971009	00199	SO  	1997	10	9	97ZZZX4303       	2	19970901	G	8530		VALVE           			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					ENGINE EXHAUST	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		3780 								ENGINE FOUND WITH EXHAUST VALVE STICKING OPEN.  AIRCRAFT HAD BEEN RUN ON AUTO GAS.  SMOH:  925 HOURS.						1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997100900200	19971009	00200	SO  	1997	10	9	97ZZZX4304       	2	19970901	G	8530		VALVE           			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  					ENGINE EXHAUST	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	415C	2875 								FOUND ENGINE EXHAUST VALVE STUCK.  AIRCRAFT HAD BEEN RUN ON AUTO GAS.  SMOH:  625 HOURS.						1	L	7	1 	3O	3	O		A718    	E233				 
1997100900201	19971009	00201	EA  	1997	10	9	97ZZZX4305       	2	19970901	G	8530		VALVE           			PIPER 	PA20  	PA20135     	7102010	SO  	LYC   	O290  	O290D2      	41506	EA  					ENGINE EXHAUST	STICKING        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17		2200 								FOUND ENGINE EXHAUST VALVE STICKING.  AIRCRAFT HAD BEEN OPERATED ON AVIA GAS.  VALVE REQUIRED DISSASSEMBLY, CLEANING, AN	D LAPPING IN.  SMOH:  525 HOURS.					1	H	7	1 	3O	3	O		1A4     	E229				 
1997100900202	19971009	00202	NM  	1997	10	9	97ZZZX4306       	1	19970901	G	5720		CORD            			CHILD 	S2    	S2BPITTS    	0110304	NM  										RIB LACE	FAILED          	B			SPDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	6034U	350  				5133				DURING INSP, LOOSE FABRIC WAS FOUND ON TOP RT INBD SECT OF TOP WING (NO FABRIC TORN).  SUCTION CUP WAS ABLE TO LIFT FABR	IC FROM WING RIBS, BOTH TOP AND BOTTOM.  A FABRIC PUNCH TEST WAS COMPLETED AND FOUND FABRIC OK.  UNDER SUPERVISION OF TH	E FAA, TOP WING FABRIC WAS DISSECTED IN LOOSE AREA AND FOUND RIB LACING CORD HAD BROKEN ALLOWING FABRIC TO LIFT FROM THE	 RIBS.  A PULL TEST OF THE RIB LACING CORD REVEALED THE CORD ONLY PULLED 25 TO 30 POUNDS BEFORE BREAKING.  RIB LACING CO	RD WAS WAXED COTTON CORD.  THE COMPLETE ACFT WAS COVERED USING GRADE 'A' COTTON, BUT STILL TESTED IN THE ORANGE USING A 	SEYBOTH NR 3 FABRIC TESTER AND A MAULE TESTER.  LOG ENTRIES IN ACFT LOGS SHOWED SB NR 18 HAD BEEN C/W ANNUALLY.	1	Q	7	1 	3O				A8SO    					 
1997100900203	19971009	00203	NE  	1997	10	9	97ZZZX4307       	3	19970916	G	6112	B40330	LEADS           			BEECH 	200   	B200        	1152922	CE  						MCAULY	4HFR34	4HFR34C754  	NE  	PROPELLER HEAT	DEFECTIVE       	B			MZ4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17	2FOR					BB558				NEW PROPELLER DE-ICE HEAT LEADS WERE PURCHASED FROM AVIATION PROPELLERS, INC., MIAMI.  THESE LEADS WERE IN THE ORIGINAL 	CESSNA AIRCRAFT PACKAGING.  WHEN THE PACKAGE WAS OPENED AND LEADS INSPECTED, FOUND OF THE 5 PACKAGED LEADS, 2 LEADS HAD 	LOOSE TERMINAL ENDS THAT WERE EASILY PULLED LOOSE FROM THE WIRE.  AVIATION PROPELLERS WAS INFORMED AND ADVISED TO CHECK 	THEIR STOCK. THEY INDICATED THEY WOULD ADVISE CESSNA.			1	L	7	2 	4T				A24CE   		6	C	3PNE	 
1997100900204	19971009	00204	WP  	1997	10	9	97ZZZX4308       	2	19970901	G	7260	31017261	SHAFT           			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  					TORQUE SENSOR	SHEARED         	D				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			SW	99	333CA	4719 				11136	P06230			WITH AIRCRAFT AT 4,000 FEET WHILE BEING VECTORED FOR LANDING, LEFT ENGINE FAILED.  PILOT COMPLETED ENGINE SHUT DOWN.  UN	EVENTFUL LANDING MADE.  MAINTENANCE FOUND TORQUE SENSOR SHAFT HAD SHEARED.  THIS GEAR ALSO DRIVES THE OIL SCAVENGE PUMP 	AND THE FUEL PUMP; THUS, WHEN THE ENGINE LOST FUEL PRESSURE, THE ENGINE FLAMED OUT.  TORQUE SENSOR REPLACED WITH NEW STY	LE 3101726-3.			1	H	7	2 	3T	4	T		2A4     	E4WE				 
1997100900205	19971009	00205	NE  	1997	10	9	97ZZZX4309       	2	19970801	G	7250	1A9843	BEARING         			BOEING	757   	757231      	1384950	NM  	PWA   	2037  	PW2037      		NE  					NR 4	FAILED          	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	705TW					28479	P727216			ENGINE REMOVED, POSITION NR 2, AT LAX ON 7-14-97 DUE METAL IN SCREEN/CARBON IN FILTER.  DISASSEMBLY INSPECTION REVEALED 	ROLLER TANG LIBERATION IN BEARING.  BEARING WAS HAND CARRIED TO PRATT & WHITNEY ENGINEERING FOR INVESTIGATION.					2	L	7	2 	4F	4	F	RT	A2NM    	E17NE				 
1997100900206	19971009	00206	EU  	1997	10	9	97ZZZX4310       	1	19970926	G	5753	A57966100002	RIB FITTING     		A57966000164	AIRBUS	300   	A300B4103   	3930104	EU  										LT INBD TE FLAP	CRACKED         	B			C20R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	13983					0092				AFTER REMOVING THE INNER FLAP L/E SKIN FROM AROUND THE INBOARD FLAP ATTACHMENT POINT, THE RIB FITTING (5TH FROM INBOARD)	 WAS FOUND TO HAVE SIDE FLANGE WITH A SMALL CRACK OF APPROXIMATELY .25 INCH WHICH WAS CONFIRMED BY DYE PENETRANT.  THE L	/E SKIN IN THIS AREA HAD SEVERAL DENTS, BUT THE CRACK DOES NOT APPEAR RELATED.				2	L	7	2 	4F				A35EU   					 
1997100900207	19971009	00207	EU  	1997	10	9	97ZZZX4311       	1	19970926	G	5753	A57966101902	RIB FITTING     		A5796602016 	AIRBUS	300   	A300B4203   	3930306	EU  										RT INBD TE FLAP	CRACKED         	B			C20R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	862PA				5D1212	211				AFTER REMOVING THE INNER FLAP L/E SKIN DUE TO FOD, THE L/E RIB FITTING (5TH FROM INBD) WHICH CONTAINS AN ATTACHMENT POIN	T FOR THE FLAP WAS FOUND TO HAVE ALL 4 SIDE FLANGES CRACKED AND BENT APPROXIMATELY 1 INCH FROM THE BOTTOM SIDE OF THE FI	TTING.  THIS FITTING IS APPROXIMATELY 6 FEET FROM THE FOD AREA BEING REPAIRED AND DOES NOT APPEAR RELATED.  THERE IS NO 	OTHER OBVIOUS DAMAGE IN THE AREA.			2	L	7	2 	4F				A35EU   					 
1997100900208	19971009	00208	GL  	1997	10	9	97ZZZX4312       	3	19970905	G	6110		BOLT            			PIPER 	PA31  	PA31325     	7103105	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROP CTWEIGHT	MISINSTALLED    	B			Q2AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	41879	2218 	11   			317712069		DJ4714		DURING ANNUAL INSPECTION, PROPELLER COUNTERWEIGHT ATTACH BOLTS FOUND UNSAFTIED POST OVERHAUL.  HARTZELL MANUAL NR 117D R	EQUIRES THESE BOLTS TO BE REPLACED AT OVERHAUL AND RE-DRILLED FOR ROLL-PIN SAFETY. THESE BOLTS WERE RE-USED AFTER OVERHA	UL SINCE THEY WERE DRILLED IN A LOCATION WHICH COULD NOT BE SAFTIED WITH A ROLL-PIN.				1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997100900209	19971009	00209	SO  	1997	10	9	97ZZZX4313       	1	19970905	G	2820	6010008	HOSE            	AEROQUIP    		PIPER 	PA31  	PA31325     	7103105	SO  										FUEL SYSTEM	LEAK            	B			Q2AR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	41879	2218 				317712069				DURING ANNUAL INSPECTION, FUEL HOSES AT FUEL SELECTOR AND STRAINERS WERE MOVED FOR INSPECTION FOR HARDNESS.  ALL FUEL HO	SES BEGAN TO LEAK FUEL THROUGH EXTERIOR BRAID AFTER BEING DISTURBED.  NEW HOSES CONFORMING TO MIL-H-879U INSTALLED.  ORI	GINAL HOSES MANUFACTURED 2 QTR 1974.				1	L	7	2 	3O				A20SO   					 
1997100900210	19971009	00210	CE  	1997	10	9	97ZZZX4314       	1	19970909	G	2701	07606331	BEARING         			CESSNA	182   	182P        	2075816	CE  										CONTROL COLUMN	FAILED          	B		A	Q2AR	O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SW	17	344K	11956				18263709				PILOT'S CONTROL COLUMN FORWARD SUPPORT ROLLER BEARING FAILED AND CAUSED AILERON CONTROL BINDING IN-FLIGHT.						1	H	7	1 	3O			NT	TA13    					 
1997100900211	19971009	00211	SO  	1997	10	9	97ZZZX4315       	1	19970901	G	3246	4090A	WHEEL           			PIPER 	PA32  	PA32R300    	7103213	SO  										INBOARD HALF	CRACKED         	B			Q2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	62295	2921 				32R7680336				INSPECTION FOUND INBOARD PORTION OF WHEEL HALF BEAD CRACKED ONE-THIRD WAY AROUND WHEEL CAUSING WHEEL TO CONTACT BRAKE CY	LINDER.					1	L	7	1 	3O				A3SO    					 
1997100900488	19971009	00488	SW  	1997	10	9	97ZZZX4316       	1	19970905	G	2823	10648BH11	SWITCH          			BELL  	222   	222         	1182122	SW  										FUEL SOV	FAILED          	H		A		O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	23	40EA	1586 				47061				FUEL VALVE SWITCH VIBRATED LOOSE DURING FLIGHT CAUSING FUEL VALVE TO CLOSE AND ENGINE TO SHUT DOWN DUE TO FUEL STARVATIO	N.  SUSPECTED CAUSE OF FAILURE MECHANICAL LOCKING (INTERNAL).  SUBMITTER RECOMMENDS REPLACEMENT OF SWITCH FOLLOWING 7,50	0 CYCLES OF SWITCH OPERATION.  CYCLES BASED ON 2 ENGINE STARTS PER HOUR, 4 SWITCH OPERATIONS PLUS 1,500 OPERATIONS FOR M	AINTENANCE WORK AND GROUND RUNS, ETC.			1	G	7	2 	3U				H9SW    					 
1997101600001	19971016	00001	EA  	1997	10	16	97ZZZX4327       	2	19970901	G	7414	10682014	DISTRIBUTOR GEAR	BENDIX      	D2000       	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	TEETH FAILED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	733WT		1046 		4085256NCBD	17268613	RL1293			ENGINE FAILED PRE-TAKEOFF MAGNETO CHECK.  PILOT RAN ENGINE AT HIGH RPM AND LEANED ENGINE TO SEE IF PLUGS WERE FOULED.  A	FTER REDUCING POWER ON SECOND MAGNETO CHECK, MAG WAS DEAD.  FOUND 3 TEETH MISSING ON DISTRIBUTOR GEAR.  MAG HAS 1,045 HO	URS TSMO.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997101600002	19971016	00002	SO  	1997	10	16	97ZZZX4328       	1	19970901	G	5510		STABILIZER      			LUSCOM	8     	8A          	8190104	SO  										HORIZONTAL STAB	CORRODED        	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		3400 								AIRCRAFT GROUND LOOPED AND DAMAGED HORIZONTAL TIP.  1991 STORED INSIDE.  REMOVED TIP AND SKINS FOR REPAIR NOTING EXCESSI	VE INTERNAL CORROSION (AIRCRAFT PARKED OVER GRASS). NO INSPECTION HOLES TO ALLOW FOR INSPECTION.  APPARENTLY, NO INSPECT	IONS CONDUCTED AT ANNUAL INSPECTION.  NOTED SIMILAR LACK OF ACCESS TO WINGS FOR INSPECTIONS.				1	H	7	1 	3O				A694    					 
1997101600004	19971016	00004	SO  	1997	10	16	97ZZZX4330       	2	19970828	G	8520	642185A1	STUD ASSY       			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					CRANKSHAFT	MISTORQUED      	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	07	4811K		621  			P21000330	278610R			LOW OIL PRESSURE; ALL EXTERIOR INSPECTION AND TESTS EXHAUSTED.  REMOVED ENGINE AND DIS-ASSEMBLED.  FOUND VISUAL SIGNS OF	 ENGINE MAIN BEARING BORE MISALIGNMENT, I.E., MAIN BEARING PATTERN COVERING ONLY 50 PERCENT OF AREA, ALL FIVE JOURNALS. 	 LOG BOOK ENTRY SHOWS PROPELLER STRIKE, DISASSEMBLY, INSPECTION, REPAIRS AND RE-ASSEMBLY, 99.6 HRS, PREVIOUSLY ON 8-29-9	6, BY CUSTOM AIRMOTIVE, TULSA, OK.  W.O. NR 14148; FAA REPAIR STATION NR DC2R763K.  SUSPECT IMPROPER TORQUE, AND/OR IMPR	OPER TORQUE SEQUENCE AS SET FORTH IN THE MFG M & O MANUAL.		1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997101600005	19971016	00005	CE  	1997	10	16	97ZZZX4331       	1	19970915	G	3231	ARB4EDUS	ROD END         			CESSNA	402   	402C        	207590R	CE  										RT GEAR DOOR	BROKE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	67886					402C0435				RIGHT LANDING GEAR DOOR CONTROL ROD BROKE AT ROD END, DOOR WOULD HANG DOWN WITH GEAR UP.  INSTALLED NEW CONTROL ROD AND 	RIGGED.  NO FURTHER TROUBLE.					1	L	7	2 	3O				A7CE    					 
1997101600006	19971016	00006	SO  	1997	10	16	97ZZZX4332       	1	19970926	G	3230	AN17727	BOLT            		1624004     	PIPER 	PA23  	PA23250     	7102308	SO  										DRAG LEG LINK	FAILED          	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	54757	8979 				277554068				WHEN APPLYING GREASE TO CENTER DRAG LEG ATTACH BOLT, THE MECHANIC NOTICED THE HEAD OF BOLT SLID OUT .25 INCH, AND BECAME	 WEDGED IN FITTING PN 19155-03 LANDING GEAR LOCK SPRING UPPER WHICH PREVENTED BROKEN PORTION OF BOLT FROM FALLING OUT.					1	L	7	2 	3O				1A10    					 
1997101600007	19971016	00007	SO  	1997	10	16	97ZZZX4333       	1	19970921	G	2150		IDLER PULLEY    			PIPER 	PA32  	PA32300     	7103212	SO  										AIR COND	BEARING FAILED  	H	P			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	28893					327940123				AFTER LANDING, THE IDLER PULLEY ASSY DETACHED FROM BEARING ASSY.  PULLEY COULD HAVE HUNG UP IN FLY-WHEEL RING GEAR.  NEW	 ENGINE INSTALLED JUST PRIOR TO FAILURE.  RECOMMEND NEW BEARING BE INSTALLED AT ENGINE OVERHAUL.					1	L	7	1 	3O				A3SO    					 
1997101600008	19971016	00008	SO  	1997	10	16	97ZZZX4334       	1	19970924	G	3240	451209	MASTER CYLINDER 	SCOTT       		PIPER 	PA18  	PA18150     	7101828	SO  										BRAKE	MISSERVICED     	B		A	CF4R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	03	2355H					187909175				BRAKE MASTER CYLINDERS SERVICED BY AN OUTSIDE SHOP DUE TO 'LOW FLUID LEVEL'.  MECH TOLD PILOT THE BRAKES WERE 'PUMPED UP	 HARD'.  PILOT USED CABIN HEAT DURING NEXT FLIGHT.  UPON LANDING, BRAKES WERE 'LOCKED UP'.  ACFT GROUND LOOPED DURING LA	NDING DAMAGING LT WING.  AFTER ACFT SET FOR ABOUT AN HOUR, THE BRAKES WERE 'FREE', AND ABLE TO ROLL THE ACFT.  SUBMITTER	 SUSPECTS THE MECHANIC DID NOT USE THE PROPER SERVICING PROCEDURE OVERSERVICING MASTER CYLINDER.  UPON APPLICATION OF CA	BIN HEAT, FLUID EXPANDED, LOCKING BRAKES.		1	H	7	1 	3O				1A2     					 
1997101600009	19971016	00009	CE  	1997	10	16	97ZZZX4335       	1	19970926	G	3222	12436231	YOKE            			CESSNA	206   	U206E       	2073350	CE  										NLG	FAILED          	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	9129M	3000 				U20601529				CESSNA HEAVY DUTY NOSE FORK SHEARED NEXT TO 4 BOLTS THAT SECURE IT TO THE NOSE STRUT.  PN 1243620-1 NOSE GEAR HUB WAS NO	T BROKEN AND DID NOT FAIL NOR DID THE 4 BOLTS.  THE YOKE SHOWED NO SIGNS OF CORROSION OR CRACKS PREVIOUS TO ACCIDENT.					1	H	7	1 	3O				A4CE    					 
1997101600010	19971016	00010	NE  	1997	10	16	97ZZZX4336       	2	19970925	G	7310	430137601	FUEL MANIFOLD   			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 1 ENGINE	LEAK            	E		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	230H		960  		1TJ03956	7134	45261			PIN HOLE LEAK IN TUBING BETWEEN NOZZLES.  HIGH PRESSURE FUEL SPRAYING INTO ENGINE COMPARTMENT.  SUBMITTER STATED THE TUB	ING BETWEEN NOZZLES SHOULD BE REPLACED AT OVERHAUL.  ALLIED SIGNAL SHOULD FIELD FLEX HOSE MANIFOLD ASAP.					1	G	7	2 	3U	3	U		H13EU   	E5NE				 
1997101600011	19971016	00011	NE  	1997	10	16	97ZZZX4337       	2	19970925	G	7310		FUEL MANIFOLD   			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2 ENGINE	LEAK            	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	230H		32   			7136	45186			HIGH PRESSURE LEAK AT BRAZE JOINT.  FUEL SPRAYING IN ENGINE COMPARTMENT.  SUBMITTER STATED BRAZE JOINT TUBING SHOULD BE 	REPLACED AT OVERHAUL.					1	G	7	2 	3U	3	U		H13EU   	E5NE				 
1997101600012	19971016	00012	SW  	1997	10	16	97ZZZX4338       	1	19970925	G	6300	369A5361	BEARING         		369A535041  	HUGHES	500N  	500N        	3027374	SW  										ORIDE CLUTCH	SEAL CLIP FAILED	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	522FB	256  				LN002				LOWER SEAL RETAINING CLIP FELL OUT DURING FLIGHT.  FOUND DURING 100-HOUR INSPECTION.						1	G	7	1 	3U			NC	H3WE    					 
1997101600013	19971016	00013	SW  	1997	10	16	97ZZZX4339       	1	19970925	G	6300	369A5361	BEARING         			HUGHES	500N  	500N        	3027374	SW  										ORIDE CLUTCH	SEAL CLIP FAILED	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	527FB	297  			369A535041	LN007				LOWER BEARING SEAL CLIP FELL OUT DURING FLIGHT.  FOUND DURING 300-HOUR INSPECTION.						1	G	7	1 	3U			NC	H3WE    					 
1997101600014	19971016	00014	SW  	1997	10	16	97ZZZX4340       	1	19970925	G	2550	HL16600170	HOIST           	BREEZE      		BELL  	206   	206L4       	1182110	SW  										RESCUE	MALFUNCTION     	D				O				OTHER                   				O			OTHER                     			HO	HOVERING       	1			WP	23	6197N				230	52014				DURING A TRAINING PERIOD, THE CABLE CUTTER ENGAGED THE CABLE CAUSING A PARTIAL FAILURE OF THE CABLE WHILE A CREW MEMBER 	WAS BEING LOWERED.  THE HOIST HAS BEEN RETURNED TO THE MANUFACTURER FOR ANALYSIS.  A FOLLOW-UP REPORT STATES MFG ANALYSI	S FOUND THE CABLE CUTTER WAS INCORRECTLY INSTALLED, CAUSING CABLE TO FRAY.				1	G	7	1 	3U			NC	H2SW    					 
1997101600015	19971016	00015	WP  	1997	10	16	97ZZZX4341       	1	19970919	G	6220	269A1329	RING            			HUGHES	269   	TH55A       	4471004	WP  										DROOP STOP	MISINSTALLED    	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	8047L					470699				DURING AN ANNUAL INSPECTION, DISCOVERED THE DROOP STOP RING WAS PREVIOUSLY INSTALLED INVERTED.  THE  MAIN ROTOR HEAD WAS	 ASSEMBLED THREE YEARS AND 60 HOURS PRIOR TO THIS INSPECTION.					1	G	7	1 	3R									 
1997101600017	19971016	00017	EA  	1997	10	16	97ZZZX4342       	1	19970905	G	2621	898526	FIRE BOTTLE     	KIDDE       		BOEING	234   	234         	1385049	EA  										APU	DISCHARGED      	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2FOR				54981EJ	MJ005				AIRCRAFT WAS ON HELIPAD WHEN THE FIRE BOTTLE DISCHARGED.  INVESTIGATION REVEALED THE THERMAL RELIEF VALVE HAD ACTIVATED 	AND BOTTLE PRESSURE WAS ZERO.  THE SKIN OF THE ACFT IS VERY CLOSE TO THE BOTTLE AND IS PAINTED BLACK ON THE OUTSIDE AND 	IN A POSITION OF DIRECT SUNLIGHT IN THE A.M.  THE OAT ON THE HELIPAD WAS 74 DEGREES FAHRENHEIT.  THE FIRE BOTTLE COMPART	MENT INSIDE SKIN TEMP WAS 132 DEGREES FAHRENHEIT.  THE INSIDE SKIN TEMP OF SKIN THAT HAS AN OUTSIDE PAINT OF WHITE NEAR 	SAME AREA WAS 107 DEGREES FAHRENHEIT.  (A COMPANY CALIBRATED INSTRUMENT WAS USED.)  MM, CHAPTER 26-20-00, PAGE 8, PARAGR	APH E, STIPULATES HIGH PRESSURE BLOW-OFF BETWEEN 208 DEGREES TO 220 DEREES FAHRENHEIT.  (X)	2	G	7	2 	4U				H9EA    					 
1997101600018	19971016	00018	NE  	1997	10	16	97ZZZX4343       	2	19970918	G	7314	RG37060A	PUMP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	FAILED          	B		A	PAIR	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	05	995WS	1756 			B1269	UE175	PCE114388			FUEL PUMP ON RT ENG FAILED CAUSING FUEL TO DRAIN FROM VENTED PLUG DURING OPERATION.  THIS VENTED PLUG INSTALLED ON THE P	UMP IS NOT PLUMBED TO DRAIN FUEL OUT OF ENG COMPT DURING PUMP FAILURE.  THIS FAILURE WAS NOT DISCOVERED TILL AFTER FLIGH	T WHEN FUEL WAS NOTED DRIPPING FROM RT NACELLE.  FURTHER INSP FOUND LOWER REAR ENG COMPT SOAKED WITH FUEL.  BEECH 1900D 	IPC ATA 71-70-00 DOES NOT SHOW A DRAIN PLUMBED TO THIS VENT PLUG.  NOTED THE DRAIN MANIFOLD PN 101-910099-19 AND DASH 20	 ATA 71-70-00 ITEM 18 DOES SHOWS AN EXTRA NIPPLE AS VERIFIED ON ACTUAL ACFT.  RECOMMEND VENTED DRAIN ON FUEL PUMP IS PLU	MBED TO THIS EXTRA NIPPLE ON DRAIN MANIFOLD TO PREVENT FUEL FROM DRAINING INTO ENG COMPT DURING PUMP FAILURE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1997101600019	19971016	00019	NE  	1997	10	16	97ZZZX4344       	3	19970919	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		4618 			2049NR			HJ378A		INSPECTION 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	 
1997101600023	19971016	00023	NE  	1997	10	16	97ZZZX4347       	1	19970917	G	6220	6510311065102	BRACKET BOLT    		651001130080	SKRSKY	S64   	S64F        		NE  										M/R DAMPER	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	159AC		997  			64084				DURING OVERHAUL OF THE MAIN ROTOR HEAD, A FLUORESCENT MAGNETIC PARTICLE INSPECTION REVEALED A TOTAL OF 4 CRACK INDICATIO	NS IN BOLT HEAD TO SHANK RADIUS.  LARGEST CRACK IS 0.200 INCH IN LENGTH RADIALLY AROUND SHANK.  THREE SMALL CRACKS ARE 0	.040 INCH LONG EACH.  NO REASON FOR THE CRACKING IS APPARENT.				2	G	7	2 	4U				H6EA    					 
1997101600024	19971016	00024	NE  	1997	10	16	97ZZZX4348       	2	19970917	G	7250	4560119360	CIRCLIP         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					MO 3 BEARING	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	6099P					2818	9365			DURING CLEANING OF REAR BEARING SUPPORT ASSEMBLY, INSPECTION FOUND THE CIRCLIP THAT HOLDS REAR BEARING POWER TURBINE GUI	DE VANE MISSING.  SUSPECT CAUSE:  DURING LAST MAINTENANCE PROCEDURES BY TURBOMECA CO., CIRCLIP WAS NOT INSTALLED.  A/C T	T:  1,699.5 HOURS. ENG TT:  1,563.2 HOURS.				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997101600025	19971016	00025	SW  	1997	10	16	97ZZZX4349       	1	19970823	G	3213	214052052101	CROSSTUBE       			BELL  	214   	214ST       	1182106	SW  										SKID GEAR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	745H					28197				REAR CROSSTUBE FRACTURED DURING GROUND HANDLING OF AIRCRAFT (RAISED ON WHEELS).  TOTAL WT. A/C, 13,535 POUNDS.  ACCEPTAB	LE MOVEMENT LIMITATION, 14,500 POUNDS.					2	G	7	2 	4U				H10SW   					 
1997101600029	19971016	00029	NE  	1997	10	16	97ZZZX4351       	1	19970915	G	3234	0911077004	CONTROL VALVE   			SKRSKY	S76   	S76B        	8143007	NE  										LANDING GEAR	MISWIRED        	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	54C				0557A	760348				THE LANDING GEAR CONTROL VALVE REMOVED FOR OCCASIONAL POPPING OF THE 'MANUAL RESET' BUTTON WHICH KEPT THE GEAR FROM BEIN	G RETRACTED.  AN O/H VALVE, ARKWIN IND, INC., PN 0911077-004, SIKORSKY PN 76650-02802-0911077-004, SIKORSKY PN 76650-028	02-104, SN 0557A WAS INSTALLED IN HELICOPTER.  WHEN ATTEMPTING TO OPERATE THE GEAR, DISCOVERED WITH THE GEAR HANDLE IN T	HE DOWN POSITION, THE GEAR WOULD RETRACT, AND EXTEND WHEN IN THE UP POSITION.  AFTER FURTHER INVESIGATION, FOUND THE UP 	AND DOWN SOLENOIDS ON THE VALVE WERE WIRED BACKWARDS.  ANOTHER VALVE WAS INSTALLED AND THE GEAR OPERATED NORMALLY.		1	G	7	2 	4U				H1NE    					 
1997101600031	19971016	00031	NM  	1997	10	16	97ZZZX4352       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 360 - BS 908	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				NUMEROUS FASTENER HOLES CRACKED BEYOND LIMITS, STR 4L, STA 360 TO STA 908, AND STR 4R, STA 360 TO STA 908.  NUMEROUS FAS	TENER HOLES CRACKED BEYOND LIMITS, STR 10R, STA 727 TO STA 908, AND STR 10L, STA 360 TO STA 540, AND STA 727 TO STA 908.	 ABOVE MENTIONED LIMITS BASED ON AD 94-25-05.  REPAIRED PER DALFORT AVIATION XEA NR X2-53-171, REV 5, DATED 8-5-97.  APP	ROVAL DATA:  FAA FORM 8110-3, DATED 7-9-97.			2	L	7	2 	4F				A16WE   					 
1997101600032	19971016	00032	NM  	1997	10	16	97ZZZX4353       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 498 - BS 887	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				ONE EACH ATTACHMENT HOLE CRACKED BEYOND LIMITS, STR 14R, STA 734 AND STR 10L, STA'S 498 AND 500.  ONE EACH ATTACHMENT HO	LE CRACKED BEYOND LIMITS, STR 14L, STA 416 AND STA 443, AND, STR 20L, STA 827 AND STA 887.  ABOVE MENTIONED LIMITS BASED	 ON AD 94-25-05.  REPAIRED PER DALFORT AVIATION XEA NR X2-53-173, REV 3, DATED 7-1-97.  APPROVAL DATA:  FAA FORM 8110-3,	 DATED 6-26-97.			2	L	7	2 	4F				A16WE   					 
1997101600033	19971016	00033	NM  	1997	10	16	97ZZZX4354       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 485 - BS 957	CRACKS          	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				THREE EACH ATTACHMENT HOLES OUT OF ALLOWABLE LIMITS.  LOCATED AT STR 10L AT STATIONS 445, 485, AND 507.  LIMITS BASED ON	 DALFORT AVIATION XEA NR X2-53-168, REV 2, DATED 6-30-97.  TWO ATTACHMENT HOLES CRACKED BEYOND ALLOWABLE LIMITS.  LOCATE	D ON LOWER ROW SKIN LAP ON STR 10R AT STA 957.25.  LIMITS BASED ON AD 94-25-05.  REPAIRED PER DALFORT AVIATION XEA NR X2	-53-167, REV 1 DATED 6-4-97.  BOEING SB 53A117 REV 1 AND FAA AD 94-25-05.			2	L	7	2 	4F				A16WE   					 
1997101600034	19971016	00034	NM  	1997	10	16	97ZZZX4355       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 344	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				ONE EACH ATTACHMENT HOLE CRACKED BEYOND ALLOWABLE LIMITS, LOWER ROW SKIN LAP.  LOCATED AT STA 344, STR 14R.  LIMITS BASE	D ON AD 95-25-05.  REPAIRED PER DALFORT AVIATION XEA NR X2-53-177 REV 1 DATED 7-17-97 AND XEA NR X2-53-17 REV 3 DATED 7-	1-97.  APPROVAL DATA:  FAA FORM 8110-3 DATED 7-17-97.				2	L	7	2 	4F				A16WE   					 
1997101600035	19971016	00035	NM  	1997	10	16	97ZZZX4356       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										STA 540	HOLES WORN      	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				TWO EACH ATTTACHMENT HOLES CRACKED BEYOND ALLOWABLE LIMITS.  LOCATED IN LOWER ROW SKIN LAP ON STR 14L, STA 540.  LIMITS 	BASED ON AD 94-25-05. REPAIRED PER DALFORT AVIATION XEA NR X2-53-184 REV 1 DATED 8-20-97.  APPROVAL DATA:  FAA FORM 8110	-3 DATED 8-19-97.				2	L	7	2 	4F				A16WE   					 
1997101600036	19971016	00036	NM  	1997	10	16	97ZZZX4357       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 380	DOUBLER CRACKED 	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				PREVIOUS REPAIR IS NOT IN C/W SB 737-53-A 1177 AND THE INNER DOUBLER IS CRACKED AT STA 380, STR 19R.  REPAIRED PER DALFO	RD AVIATION XEA NR X2-53-182 REV 1 DATED 7-31-97.  APPROVAL DATA:  FAA 8110-3 DATED 8-18-97.					2	L	7	2 	4F				A16WE   					 
1997101600037	19971016	00037	NM  	1997	10	16	97ZZZX4358       	1	19970908	G	5315		FLOOR BEAM      			BOEING	737   	7372H4      	138448C	NM  										BS 685	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				FLOOR BEAM CRACKED, STA 685, STR 62R.  REPAIRED PER DALFORT AVIATION XEA NR X2-53-180 REV 1 DATED 7-18-97.  APPROVAL DAT	A:  FAA FORM 8110-3 DATED 7-29-97.					2	L	7	2 	4F				A16WE   					 
1997101600038	19971016	00038	NM  	1997	10	16	97ZZZX4359       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 393	OUT OF LIMITS   	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				ONE EACH 0.233 INCH DIAMETER HOLE OUT OF ALLOWABLE LIMITS PER DALFORT AVIATION XEA NR X2-53-168. LOCATED AT STR 10L, STA	 393.  REPAIRED PER DALFORT AVIATION XEA NR X2-53-168, REV 3 DATED 6-30-97.  APPROVAL DATA:  FAA FORM 8110-3 DATED 6-27-	97.				2	L	7	2 	4F				A16WE   					 
1997013000141	19970130	00141	EA  	1997	1	30	97ZZZX436        	2	19970103	G	7322	95351610	O-RING          	BENDIX      	RSA5AD1     	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					FUEL SERVO	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	1980J	724  	724  			241000				DURING ANNUAL INSPECTION, A PRESSURE TEST OF THE ENGINE FUEL SYSTEM REVEALED A LEAK AT THE MIXTURE CONTROL SHAFT WHICH D	RIPPED ON THE MUFFLER BELOW .  REPLACEMENT OF O - RINGS 953516-10 AND 951401 CURED THE LEAK.  SUBMITTER SUGGESTED CLOSE 	INSPECTION AND PRESSURE TESTING SHOULD EASILY FIND THIS PROBLEM.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1997101600039	19971016	00039	NM  	1997	10	16	97ZZZX4360       	1	19970908	G	5313		STRINGER        			BOEING	737   	7372H4      	138448C	NM  										BS 269 - BS 285	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	26SW	68390				21117				THREE ATTACHMENT HOLES CRACKED BEYOND LIMITS, LOWER SKIN LAP ROW AT STA 269 THROUGH STA 285, STR 19L.  LIMITS BASED ON A	D 64-25-05.  REPAIRED PER DALFORT AVIATION XEA NR X2-53-176 DATED 7-1-97 AND XEA NR X2-53-173 REV 3 DATED 7-1-97.  APPRO	VAL DATA:  FAA FORM 8110-3 DATED 7-17-97.				2	L	7	2 	4F				A16WE   					 
1997101600040	19971016	00040	NM  	1997	10	16	97ZZZX4361       	1	19970901	G	5330		SKIN            			BOEING	727   	72730       	1384008	NM  										BS 360 - BS 441	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	113					18935				FOUND AND REPAIRED CRACKS IN THE FUSELAGE SKIN AT THE FOLLOWING LOCATIONS.  STA 418, STR 21L, 2 EACH.  STA 370 - STA 385	, STR 22L, 5 EACH.  STA 400 BELOW STR 23L, 1 EACH.  STA 420, STR 20L, 2 EACH.  STA 385, STR 23L, 1 EACH.  REPAIRED CORRO	SION AT FS 415, STR 23L.  ALL 6 EACH REPAIRS MADE PER BOEING AIRCRAFT SRM 53-30-3, FIGURE 14.				2	L	7	3 	4F				A3WE    					 
1997101600041	19971016	00041	NM  	1997	10	16	97ZZZX4362       	1	19970826	G	5755		CASTING         			BOEING	727   	72730       	1384008	NM  										RT INBD SPOILER	CRACK           	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	113					18935				RIGHT HAND INBOARD SPOILER CASTING CRACKED TOP INBOARD AFT ATTACH HOLE.  REPAIRED PER APPROVED DATA BOEING AIRCRAFT COOP	ERATION ENGINEERING INSTRUCTIONS, REFERENCE TELEX NR 32-9430 AND BOEING AIRCRAFT DRAWING SKETCH NR 65-19222.					2	L	7	3 	4F				A3WE    					 
1997101600042	19971016	00042	NM  	1997	10	16	97ZZZX4363       	1	19970825	G	5330		SKIN            			BOEING	727   	72730       	1384008	NM  										BS 360 - BS 441	DEFECTIVE       	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	113					18935				AN EXISTING REPAIR HAS BEEN INSTALLED THE FULL LENGTH OF TH FUSELAGE FROM BS 360 TO BS 441 AT LONGERON 19R TO LONGERON 2	6R.  THE EXISTING REPAIR WILL BE CHANGED BY DALFORT AVIATION UNDER XEA, NR X1-53-691.  REVISION ONE.  APPROVED DATA BOEI	NG 727 SRM 53-30-3, FIGURE 14,  BOEING AIRCRAFT DRAWING NR 65-18215 AND NR 65-18219.				2	L	7	3 	4F				A3WE    					 
1997101600408	19971016	00408		1997	10	16	97ZZZX4369       	1	19970924	G	6123	A3496	FEATHER SPRING  													HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	BROKEN          	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15								FW1410		DURING INSPECTION OF PROPELLER, FEATHER SPRING WAS FOUND BROKEN IN TWO.  DEFECTIVE SPRING RETURNED TO HARTZEL PROPELLER,	 INC.															6	C	P56GL	 
1997013000142	19970130	00142	EA  	1997	1	30	97ZZZX437        	2	19970103	G	7322	951401	O-RING          	BENDIX      	RSA5AD1     	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					FUEL SERVO	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	1980J	724  	724  			241000				DURING ANNUAL INSPECTION, A PRESSURE TEST OF THE ENGINE FUEL SYSTEM REVEALED A LEAK AT THE MIXTURE CONTROL SHAFT WHICH D	RIPPED ON THE MUFFLER BELOW .  REPLACEMENT OF O - RINGS 953516-10 AND 951401 CURED THE LEAK.  SUBMITTER SUGGESTED CLOSE 	INSPECTION AND PRESSURE TESTING SHOULD EASILY FIND THIS PROBLEM.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1997101600409	19971016	00409	CE  	1997	10	16	97ZZZX4370       	1	19970918	G	5280	NAS1204	BOLT            			RKWELL	NA265 	NA26565     	7630107	CE  										MLG DOOR	FAILED          	B			QL1R	O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			EA	13	265A	12231				46547				LANDING GEAR DOOR DEPARTED AIRCRAFT IN-FLIGHT (GEAR UP).  LAB REPORT DEFINED PROBLEM IN ONE HINGE ATTACH BOLT ON DOOR TH	AT FATIGUED DUE TO 'HIGH CYCLE' VIBRATION CAUSING CRACKING AND WHEN DOOR DROPPED DOWN, WIND CAUGHT IT BREAKING HINGE AND	 ROD END AND DOOR BROKE AWAY FROM AIRCRAFT CAUSING SUBSTANTIAL COWLING, ENGINE, AND PYLON DAMAGE.  CAUSE OF VIBRATION NO	T KNOWN.  ONLY SUBMITTER RECOMMENDATION, REMOVE AND MAGNAFLUX BOLTS AT A PARTICULAR INTERVAL.  THERE WAS NO MANUFACTURE 	RECOMMENDATION ON INSPECTION INTERVAL FOR THESE BOLTS.		2	L	7	2 	4J				A2WE    					 
1997101600410	19971016	00410	SO  	1997	10	16	97ZZZX4371       	1	19970601	G	2730	1159C20157	BEARING         			GULSTM	G1159 	GIV         	3980115	SO  										ELEVATOR TRIM	FROZE           	D	L	A		O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	13	575SF					1233				FLIGHT FROM PERTH TO MELBOURNE, AUSTRALIA,  PILOT DISCOVERED ELEVATOR/TRIM SYSTEM INOPERATIVE WHEN AN ATTEMPT TO SEEK A 	LOWER ALTITUDE.  APPEARED AS THOUGH THE ELEVATOR SYSTEM WAS FROZEN.  THE SYSTEM BECAME FREE AT A LOWER ALTITUDE AND A SA	FE LANDING WAS MADE.  DURING A POST-FLIGHT INSPECTION, EXAMINATION OF THE COMPLETE TAIL COMPARTMENT ELEVATOR SYSTEM REVE	ALED NO DEFECTS OR ABNORMALITIES THAT WOULD CAUSE THE PROBLEM.  THE TWO PREVIOUS DAYS IN PERTH, THE AIRCRAFT WAS PARKED 	OUTSIDE IN TWO FULL DAYS OF HEAVY RAINS.  IT IS SUBMITTER'S CONTENTION THAT WATER MADE ITS WAY INTO THE BUNGEE (BEARING 	PN 1159C20157 AT FLIGHT STATION 765) MECHANISM; THUS, FREEZING AT ALTITUDE WHICH WOULD IMPEDE ELEVATOR/TRIM OPERATIONS.	2	L	7	2 	4F			RT	A12EA   					 
1997101600411	19971016	00411	NE  	1997	10	16	97ZZZX4372       	2	19970918	G	7230	500588701	STATOR          		716728      						PWA   	JT8   	JT8D219     	52053	NE  					7TH STAGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		27978	4747 		VB0240		716728			ENGINE REMOVED FROM SERVICE DUE TO METAL IN THE TAILPIPE.  DISASSEMBLY OF THE ENGINE REVEALED HEAVY INTERNAL FAILURE OF 	THE HIGH PRESSURE COMPRESSOR STATOR AND ROTOR BEGINNING WITH 7TH STAGE.  FAILURE INVESTIGATION IS IN PROGRESS AT GREENWI	CH.									4	F			E9NE				 
1997101600412	19971016	00412	NE  	1997	10	16	97ZZZX4373       	2	19970917	G	7230	500588701	STATOR          		716728      						PWA   	JT8   	JT8D217A    	52053	NE  					7TH STAGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					VZ0194		709895			ENGINE REMOVED FROM SERVICE DUE TO TURBINE FAILURE.  DISASSEMBLY OF THE ENGINE REVEALED HEAVY INTERNAL FAILURE OF THE HI	GH COMPRESSOR STATOR AND ROTOR BEGINNING WITH 7TH STAGE.  FAILURE INVESTIGATION IS IN PROGRESS AT GREENWICH.										4	F			E9NE				 
1997101600413	19971016	00413	SW  	1997	10	16	97ZZZX4374       	1	19970923	G	2913	PV304426	PUMP            			SWRNGN	SA226 	SA226TB     	8780406	SW  										HYDRAULIC SYSTEM	FAILED          	B			TRKR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	15	59EZ	3554 	1423 			394				AIRCRAFT LOST PARTIAL HYDRAULIC PRESSURE.  GEAR PUT DOWN AND AIRCRAFT LANDED UNEVENTFULLY.  RT ENGINE STIFF TO TURN BY H	AND.  PULLED HYDRAULIC PUMP AND FOUND 90 PERCENT SEIZED.  INSTALLED NEW PUMP, OPERATION CHECKED GOOD.					2	L	7	2 	4T			RT	A5SW    					 
1997101600414	19971016	00414	CE  	1997	10	16	97ZZZX4375       	1	19970915	G	3610	265510162	TUBE            			LEAR  	35    	31A         	5170531	CE  										BLEED AIR	DENTED          	B			NVIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	107FX					102				RECEIVED NEW BLEED AIR TUBE ASSY FROM LEARJET WITH SEVERAL LARGE DENTS.  RETURNED UNUSED TO LEARJJET FOR REPLACEMENT.  R	ECEIVED 2ND TUBE ASSY WITH NO DAMAGE.  INSTALLED ON AIRCRAFT AND RETURNED TO SERVICE.  (PN 2655101-62).					2	L	7	2 	4F			RT	A10CE   					 
1997101600415	19971016	00415	CE  	1997	10	16	97ZZZX4376       	1	19970915	G	7714	1313483	INDICATOR       			LEAR  	35    	31A         	5170531	CE  										ENGINE N2	INOPERATIVE     	B			NVIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	107FX				105B0062	102				RECEIVED NEW N2 INDICATOR UNIT FROM LEARJET.  REMOVED FROM BOX, UNIT INOPERABLE.  RETURNED UNUSED TO LEARJET FOR REPLACE	MENT.  RECEIVED SECOND UNIT.  INSTALLED ON AIRCRAFT AND RETURNED TO SERVICE.  (PN 131348-3).					2	L	7	2 	4F			RT	A10CE   					 
1997101600416	19971016	00416		1997	10	16	97ZZZX4377       	4	19970915	G	3418	54800032	COMPUTER        			LEAR  	55    	55LEAR      	5170702	CE  										STALL WARNING	INOPERATIVE     	B			NVIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	150MS	3400 			062006	55049				RECEIVED NEW STALL COMPUTER UNIT FROM LEARJET, REMOVED FROM BOX, UNIT NOT OPERATING CORRECTLY.  LT TONE TOO LONG, RT WOU	LD NOT TEST.  RETURNED UNUSED TO LEARJET FOR REPLACEMENT.  RECEIVED SECOND UNIT, INSTALLED ON AIRCRAFT AND RETURNED TO S	ERVICE.  (PN 5480003-2).				2	L	7	2 	4F				A10CE   					 
1997101600417	19971016	00417		1997	10	16	97ZZZX4378       	4	19970915	G	3421	501111501	SERVO AMP       			LEAR  	25    	25B         	5170511	CE  										NR 2 HORIZ GYRO	FAILED          	B			NVIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	752CA					137				RECEIVED REPAIRED SERVO AMP UNIT FROM LEARJET, REMOVED FROM BOX, UNIT OPERATED NORMALLY FOR 5 MINUTES AFTER WHICH TIME A	N ELECTRICAL BURNING SMELL WAS EMITTED AND UNIT QUIT OPERATING.  RETURNED SAME TO LEARJET FOR REPLACMENT.  RECEIVED SECO	ND UNIT.  INSTALLED ON AIRCRAFT AND RETURNED TO SERVICE.  (PN 501-0005-01).				2	L	7	2 	4J				A10CE   					 
1997101600418	19971016	00418	SO  	1997	10	16	97ZZZX4379       	2	19971001	G	8520		CRANKCASE       			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 2 CYL ATTACH	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	145ES	1719 	800  			421B0143	218081R			CRANKCASE CRACKED BOTTOM NR 2 CYLINDER ATTACH, AFT .4375 INCH CYLINDER STUD.						1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997013000143	19970130	00143	SO  	1997	1	30	97ZZZX438        	1	19970110	G	8011	MHB4014	STARTER         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	27755		1    		A114356	317852148	L96168A			AIRCRAFT LANDED IN FT YUKON AND SHUT DOWN.  UPON TRYING TO START THE RIGHT ENGINE, THE BENDIX ENGAGED, BUT STARTER WOULD	 NOT SPIN THE PROP.  STARTER WAS RECENTLY OVERHAULED.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997101600419	19971016	00419	SO  	1997	10	16	97ZZZX4380       	1	19971002	G	2430	587829	SWITCH          			PIPER 	PA28  	PA28181     	7102807	SO  										ALTERNATOR	FAULTY          	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	2104U	4000 				287990327				OWNER COMPLAINED OF FLUCTUATING AMMETER AND LIGHTS.  ALTERNATOR, REGULATOR, AND OVERVOLTAGE REGULATOR HAD BEEN PREVIOUSL	Y REPLACED.  AFTER BYPASSING ALTERNATOR SWITCH, FLUCTUATIONS WENT AWAY.  PROBLEM CAUSED BY AGE OF SWITCH.  SUBMITTER STA	TED HAVE SEEN THIS ON OTHER AIRCRAFT.  ONE WAY TO PREVENT PROBLEM COULD BE TO REPLACE UNIT AFTER 2,000 HOURS.				1	L	7	1 	3O				2A13    					 
1997101600420	19971016	00420		1997	10	16	97ZZZX4381       	4	19970925	G	6122	B41832	FLYWEIGHT       		E3          	PIPER 	PA34  	PA34200T    	7103406	SO  										PROPELLER GOV	ARM CRACK       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2121X	1728 			1701S	347970180				GOVERNOR FLYWEIGHT ARM HAS A DIAGONAL CRACK INDICATION APPROXIMATELY .75 INCH LONG.  COULD NOT REMOVE IT WITH LIGHT BUFF	ING.					1	L	7	2 	3O				A7SO    					 
1997101600421	19971016	00421	SO  	1997	10	16	97ZZZX4382       	1	19970924	G	5521	40075	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										ELEV/SPAR & RIB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	282JN	6557 				317552005				UPON COMPLYING WITH PIPER SB 998A INSPECTION OF ELEVATOR SPAR, FOUND THE SPAR CRACKED INBOARD OF THE OUTBOARD HINGE.  ON	LY ABOUT .25 INCH OF THE CRACK WAS VISIBLE.  THE END RIB HAD A CRACK WHERE THE SKIN STIFFENER CHANNEL IS RIVETED TO IT A	ND ONE SKIN STIFFENER CHANNEL END WAS BROKEN OFF WHERE IT ATTACHED TO THE END RIB.  ALSO, THE RIB THAT THE BALANCE WEIGH	TS ATTACHES.  ALL THREE ANCHOR ATTACHES HAD CRACKS RUNNING ACROSS THE NUTPLATES RIGHT OUTBOARD OF RIVET ATTACH HOLES.			1	L	7	2 	3O				A20SO   					 
1997101600422	19971016	00422		1997	10	16	97ZZZX4383       	4	19970924	G	6113	4393303	BULKHEAD        			PIPER 	PA31  	PA31350     	7103110	SO  										SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	282JN	6557 				317552005				BULKHEAD CRACKED WHERE STARTER RING GEAR ATTACHES (FOUND TWO HOLES CRACKED).						1	L	7	2 	3O				A20SO   					 
1997101600423	19971016	00423	SO  	1997	10	16	97ZZZX4384       	1	19970912	G	8011	MHB4104	STARTER         			PIPER 	PA31  	PA31350     	7103110	SO  										RT ENGINE	FAILED          	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	05	4108D	1788 			11B0006	318352018				PILOT REPORTED SPARKS FROM FORWARD RT COWLING DURING STARTING OF ENGINE.  INSPECTED RT ENGINE STARTER AND FOUND FIELD CO	IL HOUSING LOOSE AND BINDING ON ARMATURE.  REMOVED AND REPLACED STARTER WITH OVERHAULED UNIT.					1	L	7	2 	3O				A20SO   					 
1997101600424	19971016	00424	CE  	1997	10	16	97ZZZX4385       	1	19971002	G	2140	45C40	COMBUSTION TUBE 		D83A28      	BEECH 	58    	58          	1152740	CE  										HEATER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	3197W	3114 				TH427				PRESSURE CHECKED HEATER FOR COMBUSTION TUBE LEAK CHECK.  FAILED CHECK AND HEATER WAS DISASSEMBLED.  LOCATED SEVERAL CRAC	KS AT HEATER WELDS.  INSTALLED NEW COMBUSTION TUBE PN 45C40, SN 970902.  RE-CHECK FOR LEAKS OK.					1	L	7	2 	3O				3A16    					 
1997101600425	19971016	00425	CE  	1997	10	16	97ZZZX4386       	1	19970905	G	3710	442CW	PUMP            			BEECH 	80    	65B80       	1152812	CE  										LT ENG VAC	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	46MA	1145 				LD413				VACUUM PUMP FAILED UNDER NORMAL OPERATING CONDITIONS.  SUBMITTER STATED THIS PUMP HAD AN EXCEPTIONALLY LONG SERVICE LIFE	.					1	L	7	2 	3O				3A20    					 
1997101600426	19971016	00426	NE  	1997	10	16	97ZZZX4387       	2	19970925	G	8530	2433952	VALVE           			BEECH 	18    	E18S        	1151006	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ENG CYL EXH	BROKE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	5611D		1460 			BA316	22664			EXHAUST VALVE BROKE DURING A FULL POWER APPLICATION.  SUSPECT CAUSE MAY BE REDUCED LEAD CONTENT IN FUEL.						1	L	7	2 	3R	3	R		A765    	5E1				 
1997101600427	19971016	00427	GL  	1997	10	16	97ZZZX4388       	3	19970715	G	6111		BUSHING         			CESSNA	182   	182         	2072702	CE  						HARTZL	HC82V	HC82V*      	GL  	BLADE PITCH	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6285A					33085		13044		PILOT REPORTED VIBRATION AND POWER LOSS.  INVESTIGATION FOUND PITCH CHANGE PHENOLIC BUSHING ON ONE BLADE BROKEN ALLOWING	 BLADE TO MOVE TO LOWER PITCH THAN OTHER BLADE.					1	H	7	1 	3O			NT	3A13    		5	C	P23EA	 
1997101600428	19971016	00428	SO  	1997	10	16	97ZZZX4389       	1	19971002	G	3234	592610	VALVE           			PIPER 	PA46  	PA46310P    	7104605	SO  										MLG SELECTOR	O-RING FAILED   	B			ESMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	825WS				0502	468408059				RECEIVED NEW VALVE FROM PIPER, BUT VALVE WAS DATED '4Q86'.  INSTALLED VALVE AND CYCLED GEAR.  THE OUTDATED O-RINGS IN VA	LVE 'BLEW OUT' ON THE FIRST RUN.					1	L	7	1 	3O				A25SO   					 
1997101600429	19971016	00429	SO  	1997	10	16	97ZZZX4390       	1	19971002	G	3234	592610	VALVE           			PIPER 	PA46  	PA46310P    	7104605	SO  										MLG SELECTOR	O-RING BROKEN   	B			ESMR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	825WS				0525	468408059				LANDING GEAR SELECTOR VALVE INTERNAL O-RINGS FAILED CAUSING HYDRAULIC PUMP TO RUN CONTINUOUSLY.						1	L	7	1 	3O				A25SO   					 
1997101600430	19971016	00430	SO  	1997	10	16	97ZZZX4391       	2	19970920	G	8520	VAR	CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 2 MAIN	BROKE           	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AL	03	9412Z	1382 			A830M1	U20606473	574416			WHILE IN CRUISE FLIGHT, CRANKSHAFT BROKE WHERE NR 1 ROD THROW COMES OFF REAR OF NR 2 MAIN.  AIRCRAFT ON FLOATS, MADE EME	RGENCY LANDING ON DRY LAKE BED.  FLOATS SHEARED OFF, PLANE WENT UPSIDE DOWN, AND PLANE IS DESTROYED.					1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1997101600431	19971016	00431		1997	10	16	97ZZZX4392       	4	19970923	G	6113	4393304	BULKHEAD        			PIPER 	PA31  	PA31325     	7103105	SO  										LT SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	979SP	4103 				7812015				SPINNER BULKHEAD CRACKED (LEFT BULKHEAD) FROM SPINNER DOME ATTACH SCREW HOLE AROUND AND DOWN BACK OF BULKHEAD, BUT NOT T	HROUGH DOUBLER.					1	L	7	2 	3O				A20SO   					 
1997102300112	19971023	00112	SW  	1997	10	23	97ZZZX4407       	1	19970617	G	6420	406312100101	BEARINGS        		407012101105	BELL  	407   	407         		SW  										T/R YOKE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	903  			A99	53054				PRE-FLIGHT CHECK FOUND 2 EACH BEARINGS 406-312-100-101 INNER RACES WORN BEYOND LIMITS.  ONE EACH OUTER RACE CRACKED.  BE	ARINGS LOCATION INBOARD ON YOKE.					1	G	7	1 	3U			O	H2SW    					 
1997102300113	19971023	00113	SW  	1997	10	23	97ZZZX4408       	1	19970728	G	7722	206375006101	INDICATOR       		SEL019D51   	BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1067D				299BA	45435				AT START-UP, TOT INDICATOR POINTER STOP ARM STUCK TO THE LATEX RUBBER BUMPER.  THIS TYPE OF RUBBER BECOMES STICKY IN THE	 HIGH SUMMER TEMPERATURES.  REPLACE BUMPER WITH RUBBER OR TEFLON THAT DOES NOT BECOME STICKY.					1	G	7	1 	3U				H2SW    					 
1997102300114	19971023	00114	SW  	1997	10	23	97ZZZX4409       	1	19970813	G	7722	206375007103	INDICATOR       			BELL  	206   	206L4       	1182110	SW  										TOT	STUCK           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	177AL				B383BA	52157				AT INITIAL START, TOT INDICATOR STOP ARM STICKING TO LATEX BUMPER.  REPLACE BUMPER WITH A DIFFERENT MATERIAL.						1	G	7	1 	3U			NC	H2SW    					 
1997102300116	19971023	00116	SW  	1997	10	23	97ZZZX4411       	1	19970723	G	7722	206375006101	INDICATOR       		SEL019DS1   	BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2025G				282BA	45690				WHEN STARTING OR OPERATING HELICOPTER, THERE WAS NO TOT TEMPERATURE INDICATION.  FOUND POINTER STOP ARM STUCK TO THE STO	P BUMPER.  VERIFIED VISUALLY AFTER REMOVING THE INSTRUMENT FROM THE CASE.  REPLACE STOP ARM BUMPER WITH A MATERIAL THAT 	DOES NOT GET STICKY WHEN EXPOSED TO THE HEAT.				1	G	7	1 	3U				H2SW    					 
1997102300118	19971023	00118	GL  	1997	10	23	97ZZZX4413       	2	19970722	G	7250	23053299	WHEEL BLADES    		23035128    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FIRST STAGE	ERODED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	768AL	1980 	1641 		X138841	760031				TURBINE ASSEMBLY RECEIVED DUE TO 2,000 HOUR OVERHAUL.  FOUND FIRST STAGE WHEEL HAD BURNED AND ERODED BLADES CAUSED BY SU	LFIDATION.					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997102300128	19971023	00128	NE  	1997	10	23	97ZZZX4423       	1	19970521	G	6720	7640003191043	CONTROL CABLE   			SKRSKY	S76   	S76A        	8143006	NE  										T/R CONTROL	MISMANUFACTURED 	B		A	ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1547K					760085				DURING FLIGHT CONTROL RIGGING, TECHNICIAN COULD NOT RIG THE TAIL ROTOR IAW CHAPTER 67-20-00, PARAGRAPH 1, PAGE 501 OF TH	E SA4077-76-2 MM.  UPON REMOVING CONTROL CABLE 76400-03191-043, FOUND THE CABLE WAS .375 INCH SHORTER THAN THAT OF A KNO	WN SERVICEABLE CABLE.  UPON FURTHER INVESTIGATION FOUND NO OTHER CABLES BAD (SHORT) AT THIS TIME.  MANUFACTURER NEEDS TO	 TIGHTEN QUALITY CONTROL PROCEDURES CONCERNING THE PRODUCTION OF THIS COMPONENT.			1	G	7	2 	3U			 	H1NE    					 
1997102300129	19971023	00129	NE  	1997	10	23	97ZZZX4424       	1	19970521	G	6720	7640003191051	CONTROL CABLE   			SKRSKY	S76   	S76A        	8143006	NE  										FLIGHT CONTROL	MISMANUFACTURED 	B		A	ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1547K					760085				DURING FLIGHT CONTROL RIGGING, TECHNICIAN COULD NOT RIG THE TAIL ROTOR IAW CHAPTER 67-20-00, PARAGRAPH 1, PAGE 501 OF TH	E SA4077-76-2 MM.  UPON REMOVAL OF CONTROL CABLE 76400-03191-051, FOUND THE CABLE WAS .25 INCH SHORTER THAN A KNOWN SERV	ICEABLE CABLE.  UPON FURTHER INVESTIGATION 2 MORE CABLES OF THE SAME PART NUMBER WERE FOUND IN STOCK TO BE .25 INCH SHOR	T.  THE MANUFACTURER NEEDS TO TIGHTEN QUALITY CONTROL PROCEDURES CONCERNING THE PRODUCTION OF THIS COMPONENT.			1	G	7	2 	3U			 	H1NE    					 
1997102300130	19971023	00130	SW  	1997	10	23	97ZZZX4425       	1	19970812	G	6320	206040530101	CASE ASSEMBLY   		206040004115	BELL  	206   	206L4       	1182110	SW  										M/R GEARBOX	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	174AL	4410 	1484 		A294	52067				TRANSMISSION REMOVED AND SENT TO COMPONENT SHOP FOR 4,500 HOUR OVERHAUL.  EXCESSIVE CORROSION WAS FOUND ON MAIN CASE UND	ER INPUT QUILL FLANGE.  ALSO, UNDER OIL JET.  THIS IS THE FIRST TIME THESE AREAS HAVE BEEN DISASSEMBLED SINCE NEW AIRCRA	FT WAS DELIVERED FROM B.H.T.  CAUSE:  MOISTURE PRESENT IN THE UNPROTECTED MAGNESIUM.  RECOMMEND THESE AND OTHER AREAS BE	 PROTECTED BY PRIMER WHEN THE TRANSMISSION CASE IS NEW.			1	G	7	1 	3U			NC	H2SW    					 
1997102300131	19971023	00131	GL  	1997	10	23	97ZZZX4426       	2	19970813	G	7261	23058110	SCAVENGE TUBE   		23004545    	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 1 BEARING	CHAFED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	177AL					52157	CAE895014			UPON DISASSEMBLY OF ENGINE FOR T/C, FOUND SCAVENGE TUBE HAD EXCESSIVE CHAFING FROM CONTACT WITH COMPRESSOR SCROLL.  EXCE	SSIVE CHAFING ON TUBE DUE TO MISALIGNMENT CAUSING CONTACT WITH SCROLL.  SUBMITTER STATED ENSURE PROPER CLEARANCE BETWEEN	 NR 1 SCAVENGE TUBE AND SCROLL AFTER INSTALLATION.				1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
1997102300132	19971023	00132	SW  	1997	10	23	97ZZZX4427       	1	19970728	G	7722	206375006101	INDICATOR       		SEL019D51   	BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3195P				B309BA	45789				AT START-UP, FOUND TOT INDICATOR POINTER STOP ARM STICKING TO THE LATEX RUBBER BUMPER.  THIS TYPE OF RUBBER BECOMES STIC	KY IN THE HIGH SUMMER TEMPERATURE IN SOUTH LOUISIANA.  REPLACE BUMPER WITH RUBBER OUT TEFLON THAT DOES NOT BECOME STICKY	.				1	G	7	1 	3U				H2SW    					 
1997102300133	19971023	00133	SW  	1997	10	23	97ZZZX4428       	1	19970509	G	6220	206011100159	HUB             		206011100159	BELL  	206   	206L3       	1182108	SW  										M/R HUB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	365AL	2388 	1193 		A2867	51376				DEFECT DISCOVERED AT 1,200 HOUR INSPECTION.  FOUND PITTING CORROSION I  SPLINES OF TRUNNION.  SUBMITTER STATES MANUFACTU	RER'S RECOMMENDED LUBRICANT NOT SUFFICIENT.  RECOMMEND A SUFFICIENT LUBRICANT FOR THIS APPLICATION.  MANUFACTURER SPECIF	IES MIL-C-16173 GRADE 2 ON MAST TO TRUNNION SPLINES.  BELIEVE A HEAVY GREASE WOULD HOLD UP BETTER IN THIS LOCATION.				1	G	7	1 	3U				H2SW    					 
1997102300136	19971023	00136	GL  	1997	10	23	97ZZZX4431       	2	19970605	G	7250	23053299	WHEEL BLADES    		23035128    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GP SECT 1ST STG	BROKEN          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	768AL	1648 			X138702	760031				TURBINE ASSEMBLY WAS RECEIVED WITH ENGINE ASSEMBLY DUE TO MAKING METAL.  UPON INSPECTION OF G.P. SECTION, FOUND SULFIDAT	ION ON 1ST STAGE WHEEL.  1ST STAGE WHEEL:  PN 23053299, SN X-138702, TT 1,348.1 HOURS, TC 1,697.  SCRAPPED DUE TO MISSIN	G BROKEN AND CRACKED BLADES CAUSED BY SULFURDATION.				1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997102300137	19971023	00137	SW  	1997	10	23	97ZZZX4432       	1	19970519	G	6310	2060401173	COUPLING        		206040015015	BELL  	206   	206L1       	1182107	SW  										INPUT DRIVE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206SL		81   		A2030437	45245				IN-FLIGHT AND GROUND RUN, FOUND INTERMITTENT HIGH PITCHED WHINE IN CABIN.  INNER COUPLING FOUND TO HAVE UNACCEPTABLE WEA	R PATTERN.  OUTER COUPLING WAS SERVICEABLE; NEITHER COUPLING WAS WORN BEYOND DIMENSIONAL LIMITS.					1	G	7	1 	3U				H2SW    					 
1997102300138	19971023	00138	SW  	1997	10	23	97ZZZX4433       	1	19970813	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3890B				B319BA	45480				AT START, TOT INDICATOR POINTER STOP ARM STICKING TO LATEX BUMPER.  REPLACE BUMPER WITH A DIFFERENT MATERIAL.						1	G	7	1 	3U				H2SW    					 
1997102300202	19971023	00202		1997	10	23	97ZZZX4436       	4	19970918	G	6113	D6199	BULKHEAD        			MOONEY	M20   	M20M        	5870222	SW  										SPINNER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1087M	93   				270047				REAR SPINNER BULKHEAD CRACKED ALL THE WAY AROUND AT RADIUS OF BACKPLATE AND ATTACHING HUB.  SUSPECT CAUSE IS INSUFFICIEN	T SHIMMING AT FRONT BULKHEAD ALLOWING NOSE OF SPINNER TO WOBBLE AND STRESS BACKPLATE.  SEARCH OF AIRCRAFT RECORDS LISTS 	TWO PREVIOUS FAILURES AT 681.5 HOURS AND 1,125.6 HOURS.  AIRCRAFT TOTAL TIME 1,218.7 HOURS.				1	L	7	1 	30			RT	2A3     					 
1997102300203	19971023	00203	CE  	1997	10	23	97ZZZX4437       	1	19970901	G	2820		FUEL LINE       			BEECH 	45    	T34B        	1152014	CE  										RT SUMP VALVE	BLOCKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	349MF					144030				GENERAL - APPLIES TO ALL AIRCRAFT.  DURING TROUBLESHOOTING FUEL SYSTEM FOR LEFT AND RIGHT TANK, UNEVEN FUEL FLOW, FOUND 	PIECE OF AFTER-MARKET 6 INCH ROUND GAS TANK OCTANE RATING PLACARD/STICKER LODGED IN FUEL LINE AT SUMP CHECK VALVE PARTIA	LLY RESTRICTING FUEL FLOW FROM RIGHT TANK.  SMALL PIECE OF VINYL PLACARD APPARENTLY CHIPPED OFF BY FUELING NOZZLE DURING	 RE-FUEL.  SUBMITTER SUGGESTS PLACARDS/STICKERS BE APPLIED FAR ENOUGH AWAY FROM TANK INLETS TO PRECLUDE BEING CHIPPED BY	 FUELING NOZZLE AND ENTERING SYSTEM.		1	L	7	1 	3O				5A3     					 
1997102300204	19971023	00204	CE  	1997	10	23	97ZZZX4438       	1	19970901	G	5343	50420021	TRUSS           			CESSNA	402   	402CESSNA   	207590K	CE  										NLG DRAG BRACE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3278Q	9160 				4020078				NOSE LANDING GEAR DRAG BRACE TRUSS CRACK FOUND DURING SCHEDULED INSPECTION OF LANDING GEAR.  STARTED AT WELD, PROGRESSED	 APPROXIMATELY .8750 INCH OF TUBING DIAMETER.  SUBMITTER STATED CAUSE UNKNOWN, POSSIBLY AGE.					1	L	7	2 	3O				A7CE    					 
1997102300205	19971023	00205	CE  	1997	10	23	97ZZZX4439       	1	19970930	G	3231	08411066	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  										GEAR DOOR	BROKE           	B				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			NM	10	36885	3250 				340A0681				GEAR DOOR UPPER ARM BROKE MID-WAY BETWEEN BEARING AND PIVOT.  OCCURRED AT GEAR EXTEND LEAVING DOOR HANGING OPEN UPON LAN	DING.					1	L	7	2 	3O				3A25    					 
1997013000149	19970130	00149	EA  	1997	1	30	97ZZZX444        	2	19970110	G	7314	RG9080J4A	FUEL PUMP       	ROMEC       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	GASKET FAILED   	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	4082T	424  			D8588	318152089	L214368A			GASKET PUSHED OUT OF VALVE BODY AND DUMPED ALL THE FUEL OVERBOARD.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997102300206	19971023	00206	EA  	1997	10	23	97ZZZX4440       	2	19970701	G	7322	30764	FLOAT           		MA45        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CARBURETOR	LEAKS           	B		A	WTXR	K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			NM	07	965BK		562  		1284	287690271	L3300036A			DURING A RUN-UP PRIOR TO FLIGHT, SMOKE WAS SEEN COMING OUT OF THE COWLING.  THE FIRE THAT FOLLOWED CAUSED SUBSTANTIAL DA	MAGE TO THE AIRCRAFT FIREWALL FORWARD.  THE ENGINE WAS SENT TO THIS FACILITY FOR INSPECTION AND REPAIR RELATED TO DAMAGE	 FROM THE FIRE.  DURING OVERHAUL OF THE CARBURETOR, THE TECHNICIAN NOTED THE FLOAT WAS FULL OF FUEL ON ONE SIDE.  FURTHE	R EXAMINATION SHOWED THE FLOAT HAD A SMALL LEAK ON THE FRONT NEAR THE SOLDER JOINT.  THE CAUSE MAY BE A DEFECTIVE SOLDER	 JOINT.  SUBMITTER STATED TO PREVENT RECURRENCE, IT IS NECESSARY TO LEAK CHECK THE FLOAT AT OVERHAUL.		1	L	7	1 	3O	3	O		2A13    	E286				 
1997102300207	19971023	00207	GL  	1997	10	23	97ZZZX4441       	3	19971003	G	6111	V84334	BLADE           													HARTZL	HCA2V	HCA2VK2     	GL  	NR 2 BUTT	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								H1339		PROPELLER RECEIVED FOR AD NOTE INSPECTION (97-18-02).  AFTER DISASSEMBLY, NR 2 BLADE FOUND CRACKED IN 'V' OF BLADE BUTT.																5	C	P24EA	 
1997102300208	19971023	00208	EA  	1997	10	23	97ZZZX4442       	2	19971001	G	8530	LW13623	PISTON          			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2452L	2689 			P1075	3879A0707	L1882315			A CYLINDER WAS REMOVED DUE TO OIL FOWLING OF THE SPARK PLUGS.  A CHUNK OF METAL WAS MISSING FROM THE PISTON.  REMOVED TH	E OTHER 3 CYLINDERS AND FOUND 3 OF THE 4 PISTONS WERE DAMAGED IN THIS WAY.  ALL CYLINDER COMPRESSIONS TESTED GOOD, MID 7	0/80.				1	L	7	1 	3O	3	O		A18SO   	E223				 
1997102300209	19971023	00209	CE  	1997	10	23	97ZZZX4443       	1	19971002	G	5320	12104022	DOOR SILL       			CESSNA	210   	210E        	2073416	CE  										REAR CORNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	2393F	2500 				21058593				DURING INSPECTION, REMOVED CHROME TRIM OVER DOOR SILL, FOUND REAR CORNER BROKEN ACROSS TOP.  TRIM NOT USUALLY REMOVED FO	R INSPECTION.  SUBMITTER STATED POSSIBLE CAUSE, HARD LANDING.  CLOSER INSPECTION REVEALS SOME PREVIOUS RIVETS REPLACED I	N AREA, NO LOG ENTRY.  RECOMMEND REMOVAL OF TRIM AND CLOSE INSPECTION DUE TO HIGH STRESS AREA AND HIDDEN DAMAGE.				1	H	7	1 	3O				3A21    					 
1997102300210	19971023	00210	SO  	1997	10	23	97ZZZX4444       	1	19970929	G	5521	4007516	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										RT OTBD ELEV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	27368	4788 				317852010				COMPLIED WITH PIPER SB 998A, DATED 8-4-97.  CUT OPEN AND INSPECTED ELEVATOR SPAR FOR CRACKS.  FOUND .75 INCH CRACK IN TI	P OF RIGHT ELEVATOR AND RIVET SHEARED ON SUPPORT TAB.  SPAR REPLACED.					1	L	7	2 	3O				A20SO   					 
1997102300211	19971023	00211	SO  	1997	10	23	97ZZZX4445       	1	19971001	G	2434	4111810	ALTERNATOR      	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					DC SYSTEM	FAILED          	B			R7LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	6807F		43   		7071719	287790170	L22439			INSTALLED ELECTROSYSTEMS ALTERNATOR.  PART FAILED 42 HOURS LATER.  SUBMITTER STATED SERVICE LIFE OF OVERHAULED UNIT SHOU	LD BE SLIGHTLY BETTER THAN 42 HOURS.					1	L	7	1 	3O	3	O		2A13    	E286				 
1997102300212	19971023	00212	GL  	1997	10	23	97ZZZX4446       	3	19971007	G	6111		BLADE           			CESSNA	207   	T207A       	2073614	CE  						MCAULY	D3A34	D3A34C401   	GL  	PROPELLER	CRACKED         	E				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	07	75870					20700648		795454		PILOT REPORTED SLIGHT ENGINE VIBRATION AND PROPELLER SLOW TO RESPOND IN RETURN TO LOW PITCH.  DISASSEMBLY REVEALED ONE B	LADE WAS CRACKED 180 DEGREES NEAR BEARING SURFACE AT ROOT END.  CAUSE UNKNOWN.  CATASTROPHIC FAILURE IMMINENT.  BLADE UN	DER ANALYSIS AT MCCAULEY.				1	H	7	1 	3O				A16CE   		5	C	P47GL	 
1997102300213	19971023	00213	CE  	1997	10	23	97ZZZX4447       	1	19970930	G	5730	08220009	SKIN            			CESSNA	402   	402B        	207590P	CE  										WING NACELLE	CRACKED         	B			OWFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	901BC	8205 				402B0379				MID-WAY BETWEEN FORWARD AND AFT SPAR UNDER NACELLE SKIN INBOARD OF NACELLE AUXILIARY FUEL TANK FOUND CRACKS IN WING SKIN	.  WOULD NOT HAVE BEEN FOUND UNLESS SKIN OVER WING LOCKER AND AUXILIARY FUEL TANK WAS REMOVED FOR REPAIR.  NO ACCESS.					1	L	7	2 	3O				A7CE    					 
1997102300214	19971023	00214		1997	10	23	97ZZZX4448       	4	19971002	G	2562	E01	ELT             	ACK         		CESSNA	182   	182P        	2075816	CE  										G SWITCH	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	60741	533  			009197	18264089				ELT 6 - SWITCH INOPERATIVE.  ELT OPS CHECK OK IN 'ON' POSITION, ELT INSTALLED 7-94. THIS IS SECOND ACK ELT WITH INOPERAT	IVE G - SWITCH IN LAST 2 MONTHS.					1	H	7	1 	3O			NT	TA13    					 
1997102300215	19971023	00215	SO  	1997	10	23	97ZZZX4449       	2	19970905	G	8520	530213	CONNECT ROD     			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8695U	1330 				17252599	25454D77DR			ENGINE CONNECTING ROD BROKE AT ROD CAP .25 INCH BEFORE THREAD.						1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997102300217	19971023	00217	CE  	1997	10	23	97ZZZX4451       	1	19970829	G	3710		HOSE            			CESSNA	172   	172P        	2072436	CE  										VACUUM SYSTEM	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9677A	2411 				17276201				VACUUM SYSTEM SHOWED LOW VACUUM.  PER MM, PUMP REMOVED AND CHECKED SATISFACTORILY.  VACUUM REGULATOR REPLACED.  SYSTEM S	TILL LOW.  INSTRUMENT PANEL REMOVED AND SPECIAL REINFORCED HOSE TO AND FROM REGULATOR FOUND TERRIBLY DECOMPOSED AND SIMP	LY TOUCHING IT WOULD CRUMBLE.  THE INSIDE RED LINER AND OUTSIDE BLACK LAYER WERE OF CRAYON CONSISTANCY.  VACUUM GAUGE CL	EANED OUT AND LINES REPLACED.  SYSTEM OPERATING SATISFACTORILY.			1	H	7	1 	3O			NT	3A12    					 
1997102300218	19971023	00218	CE  	1997	10	23	97ZZZX4452       	1	19970916	G	3230	358251854	RETRACT ROD     			BEECH 	35    	C35BEECH    	1151508	CE  										NLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	656D	4693 				D2924				DURING ANNUAL INSPECTION, AIRCRAFT RECORDS AND CONDITION INDICATED LANDING GEAR RETRACT SYSTEM BE REMOVED.  INSPECT AND 	RECONDITION AS NEEDED.  ROD ENDS WERE REMOVED FROM THE AFT NLG RETRACT ROD AND A LEVEL 3 CORROSION CONDITION WAS FOUND F	ULL OF HEAVY RUST SCALE.  STEEL SHOT WAS ADDED IN ROD ASSY TO CLEAN OUT RUST.  INSPECTION SHOWED PIN HOLE PENETRATION TH	ROUGH TUBE WALL OF AFT END.  UNIT APPEARS TO BE 'SEALED', NO CORROSION PREVENTATIVE COMPOUND FOUND INSIDE.			1	L	7	1 	3O				A777    					 
1997102300219	19971023	00219	CE  	1997	10	23	97ZZZX4453       	1	19970916	G	2720	AN386212A	TAPER PIN       			BEECH 	35    	C35BEECH    	1151508	CE  										LT PEDAL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	656D	4693 				D2924				WHILE TAXIING AIRCRAFT, NOTED STEERING RESPONSE USING COPILOT'S PEDALS WAS POOR TRYING TO STEER LEFT.  OKAY STEERING TO 	RIGHT.  DURING INSPECTION, TAPER PIN THAT COUPLES PILOT SIDE LT RUDDER PEDAL TO TORQUE TUBE WAS FOUND LOOSE.   PIN WAS R	EMOVED AND FOUND 'NECKED-DOWN'.  BY SYSTEM DESIGN, THIS PEDAL IS THE 'MASTER' PEDAL AND THE OTHER 3 PEDALS ARE SLAVED TO	 IT THROUGH BELLCRANKS AND PUSHRODS.  THE CUMULATIVE 'SLOP' IN THE SYSTEM ROD ENDS WAS FOUND TO BE ABOUT EQUAL AND THE L	OOSE TAPER IN WOULD NOT ALLOW ADEQUATE LEFT STEERING COMMANDS.  PIN WAS REPLACED.		1	L	7	1 	3O				A777    					 
1997102300221	19971023	00221	EU  	1997	10	23	97ZZZX4455       	1	19970926	G	3250	860122	STEERING SECTOR 			JETAIR	JETSTM	JETSTM4101  	1500501	EU  										NLG	LOCK UP         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01		1291 			APB961595					UNIT RETURNED TO REPAIR STATION FOR REPAIR.  DURING TESTING WITH HYDRAULIC BENCH, UNIT WOULD LOCK IN THE CLOCKWISE DIREC	TION AND NOT RELEASE PRESSURE.  MALFUNCTION COULD POSSIBLY LOCK NOSE LANDING GEAR STEERING OFF-CENTER.  SUBMITTER STATED	 PROBLEM WAS FOUND ON 2 UNITS WITH SEQUENTIAL SERIAL NUMBER RECEIVED FROM 2 DIFFERENT AIRLINES.				2	L	7	2 	4T			RT	A41NM   					 
1997102800002	19971028	00002	CE  	1997	10	28	97ZZZX4456       	1	19971009	G	2750	1455077639	CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  										FLAP PRESELECT	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	12549					5500501				DURING FLAP RIGGING, FOUND FLAP PRE-SELECT CABLE FRAYED.  ORDERED P/N 14550-776-39 CABLE ASSY.  FOUND BALL SWEDGE LOCATE	D AT 106.69 INCH.  CONFIRM LOCATION OF SWEDGE BALL WITH CESSNA.  CABLE REMOVED FROM AIRCRAFT WAS 103.0 INCHES.  CESSNA I	N PROCESS OF BUILDING A SPECIAL CABLE.  CESSNA PART MANUAL, CHAPTER 27-90-00, PAGE 2, ITEM 81.				1	L	7	2 	4F			 	A22CE   					 
1997102300222	19971023	00222	WP  	1997	10	23	97ZZZX4457       	2	19970902	G	7322	8972001A	SUPPORT         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					FUEL CONTROL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3330S					4410205	P77291			FUEL CONTROL SUPPORT SPLIT BETWEEN TWO BOLT HOLES.  PART NEEDS TO BE LONGER.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
1997102300223	19971023	00223	WP  	1997	10	23	97ZZZX4458       	2	19970930	G	7322	89778017	FUEL CONTROL    	WOODWARD    		SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					LT ENGINE	FAILED          	B			OWFR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	48HH	2826 	28   		1477622	T304	P35030			FUEL CONTROL, INTERNAL FAILURE.  FAILED TO RESPOND TO POWER LEVER MOVEMENT.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
1997102300224	19971023	00224	CE  	1997	10	23	97ZZZX4459       	1	19971003	G	2730	115610010325	TORQUE TUBE     			BEECH 	99    	C99         	1154006	CE  										ELEVATOR	CRACKED         	B		A	EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6656N	482  	54   			U213				ELEVATOR TORQUE TUBE CRACKED AT TAPER PIN HOLE .3750 INCH LONG.  PLAY BETWEEN TUBE AND CASTING FOUND DURING ROUTINE INSP	ECTION.  FURTHER INVESTIGATION REVEALED CRACK.  INSTALLED NEW 115-610010-325 ASSEMBLY.					1	L	7	2 	3T				A14CE   					 
1997102300225	19971023	00225	CE  	1997	10	23	97ZZZX4460       	1	19970922	G	3231	12838002115	CONTROL CABLE   			BEECH 	MU300 	400A        	1155402	CE  										EMERG RELEASE	BROKEN          	B			KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	85CR	2039 				RK22				WHILE ACCOMPLISHING PRE-FLIGHT INSPECTION, TECHNICIAN NOTICED THERE WERE BROKEN STRANDS WHERE CABLE SWAGES INTO MS20668 	CABLE EYE OF LEFT HAND EMERGENCY GEAR DOOR UPLOCK RELEASE CABLE.  SUBMITTER STATED CAUSE OF FAILURE IS IMPROPER CABLE EY	E POSITIONING WHICH RESULTS IN SHORT RADIUS 90 DEGREE BEND OF CABLE.  ON PRE-FLIGHT INSPECTIONS NEED TO VERIFY CABLE AND	 EYE POINT DOWN AS OPPOSED TO BEING VERTICAL.			2	H	7	2 	4F			RT	A16SW   					 
1997102300226	19971023	00226	WP  	1997	10	23	97ZZZX4461       	2	19971003	G	7323	8210260	GOVERNOR        	WOODWARD    		SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					RT ENGINE	FAILED          	B			QWFR	D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			NM	05	727DP		1163 			AT039	54207			INTERNAL FAILURE.  BEARING FAILED ON FOLLOWER GEAR IN THE PRESSURE PUMP ENGINE SHUT DOWN ON TAXIING OUT FOR TAKEOFF.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
1997102300227	19971023	00227		1997	10	23	97ZZZX4462       	4	19970929	G	3441	10090910104	INVERTER        			GULSTM	G1159 	G1159A      	3970109	SO  										IRU NR 2 FAN	FAILED          	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	09	843HS	2345 				496				DURING PRE-DEPARTURE CHECK OF AIRCRAFT, A BURNING ODOR WAS DETECTED IN AFT BAGGAGE AREA.  UPON CLOSER INSPECTION, SMOKE 	NOTED COMING FROM BENEATH THE HAT SHELF.  POWER WAS REMOVED AND THE NR 2 HG-1075 INERTIAL REFERENCE UNIT WAS REMOVED.  T	HE IRU FAN INVERTER WAS FOUND TO BE THE SOURCE OF THE SMOKE.  INSTALLED HONEYWELL DC BLOWER KIT, PN 26012423-105, IN ALL	 3 IRU'S AND RETURNED AIRCRAFT TO SERVICE.			2	L	7	2 	4F				A12EA   					 
1997102300230	19971023	00230	NE  	1997	10	23	97ZZZX4464       	2	19970930	G	7230	PWA419403	BEARING         	SKF         							PWA   	JFTD12	JFTD12A5A   	52047	NE  					ENGINE COMP	FAILED          	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		1692 			178		677820			BEARING REMOVED FROM ENG DURING OVERHAUL WITH TT OF 1691.6 HRS.  DURING OVERHAUL, BEARING WAS INSPECTED AND 2 UNUSUAL CO	NDITIONS FOUND:   BALLS EXHIBITED SEVERE SCRATCHES AND RETAINER SHOWED SMEARED SILVER PLATING IN THE BALL RETENTION AREA	.  AFTER ANALYSIS, REPORT SHOWED RESIDUAL SILICA CARBIDE EMBEDDED IN THE BRONZE RETAINER CAUSING THE BALL SCRATCHES.  SI	LICA CARBIDE WAS LIKELY FROM A MEDIA BLAST DURING MFG PROCESS.  THE SILVER PLATING DISCREPANCY WAS ATTRIBUTED TO A LACK 	OF CLEARANCE BETWEEN THE RETAINER AND BALL DURING THE STAKING PROCESS.  A TYPICAL CLEARANCE OF 0.002 INCH IS NORMAL.  FO	UND CLEARANCE TO BE NEAR 0.0000 INCH.  AS THE SILVER PLATING WAS WORN, THE EMBEDDED SILICA CARBIDE SCRATCHED THE BALLS.						4	U			E15EA				 
1997102300231	19971023	00231	SO  	1997	10	23	97ZZZX4465       	1	19970521	G	8120	MILH5593	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TURBO CONTROLLER	BROKEN          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03		100  				318252019	L294168A			DURING THE 100-HOUR INSPECTION AT 908 HOURS ON 3-17-97 WHILE CHECKING HOSES FOR CONDITION NOTICED THE NR 4 HOSE, MIL-H-5	93, THAT ATTACHED TO THE TURBO DIFFERENTIAL PRESSURE CONTROLLER WAS BROKEN AT THE MS27404 FITTING.  THIS HOSE GOES TO TH	E OIL SUMP AND INDUCTION HOUSING.  NOTICED THE HOSE WAS VERY HARD AT THE FITTING END DUE TO HEAT.  DUE TO THE EXTRA LENG	TH OF HOSE, THE HOSE WAS CUT OFF AND A NEW FITTING INSTALLED PLUS A FIRE SLEEVE TO TAKE CARE OF THE HEAT ON BOTH ENGINES	.  DURING THE NEXT 100-HOUR INSPECTION ON 5-21-97, THE HOSE ON BOTH ENGINES WAS BROKEN OFF AGAIN DUE TO HEAT.  UNABLE TO	 IDENTIFY THE HOSE PART NUMBER IN THE LYCOMING MICROFICHE.	1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997102300232	19971023	00232	EA  	1997	10	23	97ZZZX4466       	2	19970923	G	8550		ENGINE          			GULSTM	AA1   	AA1C        	0631214	SO  	LYC   	O320  	O320D3G     	41508	EA  					OIL PUMP	MISOVERHAULED   	B			TRKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	399X	2110 	310  			AA1C0192	L838839			DURING ANNUAL INSPECTION, COULD NOT FIND VALID SIGN-OFF FOR AD 81-18-04 OR AD 96-09-10 (OIL PUMP AD).  PARTS NOTIFICATIO	N NR 96-083 DATED 5-5-97.  NO PAPER WORK FOR RETURNING PARTS TO SERVICE (YELLOW TAGS) OR AD COMPLIANCE WAS FOUND.  ENGIN	E WAS TORN DOWN AND INSPECTED AND NORMAL PARTS CERTIFIED AND YELLOW TAGGED.  OIL PUMP AD WAS FOUND NOT TO BE DONE.  C/W 	AD NOTE AND ASSEMBLY) ENGINE AND TEST FLEW AIRCRAFT.  NO OTHER PROBLEMS FOUND WITH THE ENGINE.			1	L	7	1 	3O	3	O		A11EA   	E274				 
1997102300233	19971023	00233	NE  	1997	10	23	97ZZZX4467       	2	19971006	G	8500		ENGINE          			DOUG  	DC4   	C54BDC      	3021516	WP  	PWA   	R2000 	R2000*      	52023	NE  					NR 4	FAILED          	D				E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AL	01	44911		1156 			10461	108107			NR 4 ENGINE STARTED RUNNING ROUGH IN CRUISE.  MANIFOLD PRESSURE BEGAN TO INDICATE HIGH AND FLUCTUATING.  ENGINE SHUT DOW	N AND LANDED WITH NO FURTHER PROBLEMS.  INTERNAL FAILURE, METAL IN SCREEN.  ENGINE SENT TO REPAIR STATION FOR TEAR-DOWN 	AND EVALUATION.				2	L	7	4 	4R	4	R		A762    	5E5				 
1997102300234	19971023	00234	EU  	1997	10	23	97ZZZX4468       	1	19970925	G	7160		SCREEN          			RHNFLU	EXT300	EA300L      	70218DG	EU  										AIR INTAKE	BROKEN          	B		A	FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	609JW	179  				033				THE AIRCRAFT'S COWLING MOUNTED ALUMINUM AIR INTAKE SCREEN FOUND BROKEN ALONG THE UPPER AND LOWER EDGES.  THE SCREEN WAS 	ONLY SECURED ON THE EDGES.  FAILURE WOULD RESULT IN PIECES ENTERING THE FUEL INJECTION BODY, WHICH IS UNFILTERED, ON THI	S AIRCRAFT.  A NEW SCREEN, OBTAINED FROM THE MANUFACTURER, IS OF A HEAVIER GAUGE AND IS OF STAINLESS STEEL.  SUBMITTER S	TATED EARLIER AIRCRAFT SHOULD BE REQUIRED TO INCORPORATE THE MODIFIED SCREEN.			1	M	7	1 	3O			NC	EA67U   					 
1997102300235	19971023	00235	CE  	1997	10	23	97ZZZX4469       	1	19971001	G	3230	2441003F	PIVOT SPLINES   			CESSNA	172   	172RG       	2072438	CE  										RT MLG	SHEARED         	G				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	15	5510R	6252 				172RG0066				RIGHT MAIN LANDING GEAR PIVOT SPLINE SHEARED OFF DURING GEAR RETRACTION.  AIRCRAFT LANDED WITH GEAR-UP CONFIGURATION.  M	INOR DAMAGE TO FUSELAGE UNDERCARRIAGE AND PROPELLER.  SUSPECT CAUSE - EXCEEDED LIFE CYCLES.  SUBMITTER RECOMMENDATION: A	N AD ISSUED MAKING CESSNA SEB 90-1 MANDATORY AND RE-INSPECTION INTERVAL AT 500 HOURS.  REFER TO FAA SAFETY RECOMMENDATIO	N 95.294.			1	H	7	1 	3O				3A17    					 
1997102300237	19971023	00237	SW  	1997	10	23	97ZZZX4470       	1	19970826	G	6220	407010150103	FRAHM ASSY      			BELL  	407   	407         		SW  										M/R HEAD	DETERIORATED    	B			ALGR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	437AL				A173	53141				LATERAL VIBRATION IN AIRCRAFT.  FOUND ALL RUBBER PARTS DETERIORATED (ERASER TYPE WEAR) INSIDE FRAHM ASSEMBLY.						1	G	7	1 	3U			O	H2SW    					 
1997102300241	19971023	00241	NE  	1997	10	23	97ZZZX4473       	2	19970929	G	7250		ENGINE          								PWA   	JT8   	JT8D15      	52051	NE  					LPT ROTOR	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	05							708390			ENGINE WAS REMOVED FROM SERVICE DUE TO LPT FAILURE AT TAKEOFF.  PRELIMINARY DISASSEMBLY FINDINGS REVEALED SEVERAL T4 BLA	DES BROKEN AT AIRFOIL WITH EXCESSIVE DAMAGE TO LPT MODULE, T1 DISK AND EXHAUST CASE.  THE OUTER EXHAUST DUCT HAD RUPTURE	D DURING FAILURE.  FAILURE INVESTIGATION IS IN PROCESS AT GREENWICH.									4	F			E2EA				 
1997102300242	19971023	00242	SO  	1997	10	23	97ZZZX4474       	1	19970901	G	3340	A7755028V	LIGHT           	WHELEN      		PIPER 	PA46  	PA46310P    	7104605	SO  										RT TAXI	DISTORTED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	711XL					4608062				NOTICED REFLECTIVE MATERIAL WAS DISTORTED.  SUSPECT CONDITION WAS CAUSED BY EXCESSIVE HEAT.  REPLACED WITH NEW UNIT.						1	L	7	1 	3O				A25SO   					 
1997102300243	19971023	00243	CE  	1997	10	23	97ZZZX4475       	1	19971001	G	5523	9661000667	TRIM TAB ASSY   			BEECH 	55    	E55         	1152732	CE  										ATTACH HORN	BROKEN          	D				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CL	CLIMB          	1			EA	25	9800L	1215 				TE813				LEFT ELEVATOR TRIM TAB HORN ATTACH BROKE IN-FLIGHT JUST AFTER TAKEOFF.  AIRCRAFT ENCOUNTERED VIBRATION AND RETURNED TO L	AND.  INSPECTION FOUND ATTACH HORN OF TRIM TAB BROKEN AND SHOWED SIGNS OF PREVIOUS CRACK.  SUSPECT CAUSE TIGHTENING BOLT	 AND PINCHING HORN CAUSING STRESS AND THEN CRACK.  (BOLT SHOULD BE FREE TO ROTATE).  REPLACED WITH NEW STYLE TAB.  REF: 	 BEECH SI 0610-152, REV II.  PART NUMBER FOR NEW STYLE OFFERRED NOT ORIGINAL PART THAT FAILED.			1	L	7	2 	3O				3A16    					 
1997102300244	19971023	00244	CE  	1997	10	23	97ZZZX4476       	1	19971008	G	5330		SKIN            			CESSNA	210   	210D        	2073414	CE  										TOP CABIN	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	07	3785Y					21058285				TOP CABIN SKIN TORN (OIL CANNED) FROM AERODYNAMIC FORCES ACTING ON THE COMM 1 ANTENNA.  THE ANTENNA WAS IMPROPERLY MOUNT	ED.  IT WAS MOUNTED DIRECTLY TO THE CABIN SKIN WITHOUT THE USE OF A DOUBLER.  SUBMITTER STATED TO PREVENT THIS OCCURRENC	E FROM HAPPENING AGAIN, DOUBLER MUST BE USED WHEN MOUNTING ANTENNAS TO THE AIRCRAFT STRUCTURE.				1	H	7	1 	3O				3A21    					 
1997102300246	19971023	00246	CE  	1997	10	23	97ZZZX4478       	1	19970930	G	2810		CELL            			BEECH 	90    	E90         	1152914	CE  										FUEL SYSTEM	SEAM LEAK       	B			ADKR	K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	05	551MS					LW113				INSTALLED NEW PMA FUEL TANK IN AIRCRAFT.  TANK STARTED LEAKING FROM A SEAM IN THE TANK.  SUBMITTER STATED THIS IS THE SE	COND OCCURRENCE.  REPLACED CELL WITH ANOTHER CELL.					1	L	7	2 	3T				3A20    					 
1997102300416	19971023	00416	CE  	1997	10	23	97ZZZX4480       	1	19971013	G	5720	2324011XXX	EXTRUSION       			LEAR  	55    	55LEAR      	5170702	CE  										WING TE	CORRODED        	B	S		QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1983Y	4293 				079				THE TRAILING EDGE EXTRUSIONS ON WINGS, FLAPS, AND FLIGHT CONTROLS WERE FOUND CORRODED AT EXPOSED EDGE WITH A FEW SMALL A	REAS OF BULBED EDGE COMPLETELY GONE.  DISASSEMBLY OF TRAILING EDGES WAS REQUIRED TO DETERMINE THE EXTENT OF DAMAGE.  NO 	CORROSION WAS FOUND BEYOND THE 'BULBED' EXPOSED EDGE.  ALL EXTRUSIONS WERE REPLACED.				2	L	7	2 	4F				A10CE   					 
1997102300417	19971023	00417	CE  	1997	10	23	97ZZZX4481       	1	19971013	G	5753	543301534	EXTRUSION       			LEAR  	55    	55LEAR      	5170702	CE  										FLAP TE	CORRODED        	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1983Y	4293 				079				THE TRAILING EDGE EXTRUSIONS ON WINGS, FLAPS, AND FLIGHT CONTROLS WERE FOUND CORRODED AT EXPOSED EDGE WITH A FEW SMALL A	REAS OF BULBED EDGE COMPLETELY GONE.  DISASSEMBLY OF TRAILING EDGES WAS REQUIRED TO DETERMINE THE EXTENT OF DAMAGE.  NO 	CORROSION WAS FOUND BEYOND THE 'BULBED' EXPOSED EDGE.  ALL EXTRUSIONS WERE REPLACED.				2	L	7	2 	4F				A10CE   					 
1997102300418	19971023	00418	EU  	1997	10	23	97ZZZX4482       	1	19970919	G	6220	350A31190101	STARFLEX        			SNIAS 	350   	AS350B      	8680801	EU  										BLUE BLADE	FAILED          	D		A	WV0M	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			HO	HOVERING       	1			EA	09	8WV	1957 			M1609	1413				PILOT EXPERIENCED A VIBRATION WHILE IN APPROX 5 FOOT HOVER.  GROUND OBSERVESENCES NOTED A SIGNIFICANT BLADE DEVIATION AT	 THE ONSET OF VIBRATION IN HOVER.  PILOT LOWERED AIRCRAFT TO GROUND AND AT TOUCH DOWN, SEVERITY OF VIBRATION INCREASED. 	 COLLECTIVE WAS BOTTOMED AND ENGINE SHUT DOWN INITIATED WITH CONDITION LEVER.  LARGE OSCILLATIONS CONTINUED AS ROTOR SLO	WED.  AFTER AIRCRAFT WAS SECURED, NOTED THE STARFLEX BLUE BLADE FINGER HAD FAILED COMPLETELY AT APPROX 50 PERCENT SPAN. 	 TAIL BOOM AND JUNCTION WERE DAMAGED AS WELL AS TRANSMISSION SUPPORTS DUE TO LARGE AMPLITUDE OF VIBRATION.  NOTE:  STARF	LEX LIFE LIMIT IS 2,200 HOURS.	1	G	7	1 	3U				H9EU    					 
1997102300419	19971023	00419		1997	10	23	97ZZZX4483       	1	19971010	G	3411	D9181	FILTER          																	VACUUM SYSTEM	DEFECTIVE       	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		200  								DEFECTIVE PARKER AEROSPACE VACUUM FILTER RUBBER MATERIAL.  SECOND PART WITH THE SAME DEFECT IN THE LAST TWO MONTHS.																			 
1997102300420	19971023	00420	SO  	1997	10	23	97ZZZX4484       	2	19971001	G	8520	64200	CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 6 CYL FLANGE	CRACKED         	D				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			SO	03	112BS				243824R	TH628	243824R			RIGHT ENGINE CRANKCASE CRACKED AT THE UPPER STUD AREA OF THE NR 6 CYLINDER ALLOWING THE CYLINDER TO COMPLETELY SEPARATE 	FROM THE CASE CAUSING ENGINE FAILURE UNDER NORMAL FLIGHT CONDITIONS.  SUBMITTER RECOMMENDATION:  DYE PENETRANT, INSPECTI	ON CRANKCASE REF:  AD 77-13-22, FOR EARLIER MODEL ENGINES.				1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997102300421	19971023	00421	CE  	1997	10	23	97ZZZX4485       	1	19971002	G	3411	RA1J47	AIR FILTER      	RAPCO       		BEECH 	58    	58          	1152740	CE  										IN LINE AIR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4626A	309  				TH39				THE IN-LINE AIR FILTER WAS FOUND CRACKED ALTHOUGH NOT SEVERE AT THIS TIME.  PART MAY HAVE ONLY LASTED ANOTHER 25-50 HOUR	S.  AD 97-16-10 WAS ISSUED AGAINST THESE TYPE FILTERS, BUT THE FILTER IS NOT IN THE LOT NUMBER SPECIFIED BY AD.					1	L	7	2 	3O				3A16    					 
1997102300422	19971023	00422	CE  	1997	10	23	97ZZZX4486       	1	19971002	G	3411	RA1J47	AIR FILTER      	RAPCO       		BEECH 	58    	58          	1152740	CE  										INST AIR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4626A	309  				TH39				THE IN-LINE AIR FILTER FOR THE INSTRUMENT AIR WAS FOUND SEVERELY CRACKED ALMOST TO THE POINT OF COMPLETE SEPARATION.  AN	 AD 97-16-10 WAS ISSUED ON THESE TYPE FILTERS, BUT THESE FILTERS WERE NOT INCLUDED BECAUSE OF LOT NUMBER.  BATCH NR 0279	7.				1	L	7	2 	3O				3A16    					 
1997102300423	19971023	00423	SO  	1997	10	23	97ZZZX4487       	1	19970905	G	3230	1497615	ALIGNMENT ROLLER			PIPER 	PA24  	PA24250     	7102404	SO  										NLG	MALFUNCTION     	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	05	5240P					24271				ON TAKE OFF CLIMB, RETRACTION, NOSE GEAR ROLLER TRAVELED OUTSIDE OF 'Y' CHANNEL CAUSING THE NOSE WHEEL TO RETRACT SIDE W	AYS.  CIRCUIT BREAKER TRIPPED WHEN GEAR WAS APPROXIMATELY 7/8 OF THE WAY UP.  ALL ATTEMPTS TO DEPLOY THE GEAR TO A LOCKE	D DOWN POSITION WERE UNSUCCESSFUL.  ON LANDING, AFTER ATTEMPTING UNUSUAL ATTITUDES ETC., GEAR COLLAPSED.				1	L	7	1 	3O				1A15    					 
1997102300424	19971023	00424	SO  	1997	10	23	97ZZZX4488       	1	19971007	G	2430	455151	CONTACTOR       			PIPER 	PA44  	PA44180     	7104402	SO  										BATTERY	BURNED          	D				O				OTHER                   				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			SO	16	926ER	29   				4496016				THE PILOT REPORTED AN ELECTRICAL POWER LOSS FOLLOWED BY THE SMELL OF ELECTRICAL SMOKE.  THE BATTERY CONTACTOR WAS FOUND 	BURNED AT THE 'X2' TERMINAL.  THE TERMINAL WAS FOUND LOOSE.					1	L	7	2 	3O				A19S0   					 
1997102300425	19971023	00425	GL  	1997	10	23	97ZZZX4489       	3	19971010	G	6114	84032L	HUB SPIDER      			PIPER 	PA24  	PA24        	7102402	SO  						HARTZL	HC92Z	HC92ZK8     	GL  	PROPELLER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	5358P				1377L	24306		1377L		CUSTOMER PURCHASED PROPELLER NEW IN 1977.  IN 1991 WITH 639 HOURS, PROPELLER STRUCK A TOW BAR RESULTING IN MINOR BLADE D	AMAGE.  PROP WAS TAKEN IN FOR REPAIR AND AD 73-02-01 WAS C/W.  IN SEPTEMBER OF 1977 WITH 876 TT HOURS, PROP WAS BROUGHT 	IN FOR ROUTINE OVERHAUL.  DURING MAGNAFLUX INSPECTION, A 1 INCH CRACK WAS DETECTED IN ONE ARM OF THE HUB SPIDER.				1	L	7	1 	3O				1A15    		5	C	P892	 
1997102300434	19971023	00434	GL  	1997	10	23	97ZZZX4492       	1	19971002	G	6320	28131709R	TRANSMISSION    			ENSTRM	F28   	F28F        	3300412	GL  										M/R	MAKING METAL    	C		A	PP0M	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	01	8626S	174  			4517S79C	786				TRANSMISSION GENERATING CHIP LIGHTS SINCE NEW ON AVERAGE OF 7-10 HOURS OF OPERATION.  MFG SUGGESTED LESS SENSITIVE CHIP 	PLUG.  XMSN CONTINUED TO GENERATE METAL.  ACFT REMOVED FROM SERVICE WHEN PIECES REACHED .25 INCH IN LENGTH.  MFG HAS NO 	PUBLISHED CRITERIA FOR CHIPS.  REMOVED XMSN WITH 174 HOUR TTSN.  SPARE 'REMANUFACTURED', XMSN INSTALLED.  MFG FEELS META	L GENERATION IS 'NORMAL' BREAK-IN FOR THIS TRANSMISSION.  AVERAGE LIFE ON THIS XMSN IS 200-700 HOURS.  PUBLISHED TBO IS 	1,200 HOURS.		1	G	7	1 	3O				H1CE    					 
1997102300435	19971023	00435	CE  	1997	10	23	97ZZZX4493       	1	19971008	G	3240	1015800281	BRAKE LINE      			BEECH 	200   	200BEECH    	1152920	CE  										COPILOT BRAKE	CHAFED          	B			PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	142SR	7230 				BB380				PHASE 3 INSP FOUND COPILOT'S LT RUDDER PEDAL PUSH/PULL TUBE RUBBING BRAKE LINE.  THE AFT ROD END ON THE PUSH/PULL TUBE I	S ATTACHED WITH CASTLE NUT AND COTTER PIN.  THE END OF THE COTTER PIN WAS THE PART RUBBING THE BRAKE TUBE.  IT CHAFED A 	GROOVE AND THERE WAS ABOUT .010 INCH OF MATERIAL REMAINING.  INSTALLED A NEW LINE AND REPOSITIONED TO GIVE PROPER CLEARA	NCE.  IF THIS LINE HAD RUPTURED, A LOSS OF BRAKE PRESSURE WOULD HAVE OCCURRED.			1	L	7	2 	4T				A24CE   					 
1997102300436	19971023	00436	CE  	1997	10	23	97ZZZX4494       	1	19970929	G	2710	676014514	FEEL BUNGEE     			CESSNA	750   	750         	2076810	CE  										LT AIL FEEL	FREEZE UP       	G	S	A		B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			GL	15	944H	422  				750011				PILOT REPORTED RECEIVING 'TRIM LEFT AILERON WARNING' AT FL 41,000, 20,000, AND A FINAL WARNING AFTER LEVELING OFF JUST B	ELOW 11,000.  AFTER EACH OF THE 2 WARNINGS, PILOT DISCONNECTED AUTOPILOT AND FOUND NO DISCREPANCIES.  WHEN PILOT DISCONN	ECTED AUTOPILOT AFTER THIRD WARNING, UNABLE TO TURN ACFT TO THE LEFT.  FLIGHT CREW DISCONNECTED CONTROL COLUMNS, DECLARE	D EMERGENCY, AND PREPARED FOR FINAL APPROACH.  DURING FINAL APPROACH SEQUENCE, FIRST OFFICER FELT AND HEARD A THUMP IN C	ONTROL YOKE.  FLIGHT CREW RE-CONNECTED CONTROL YOKES.  AFTER GAINING FULL CONTROL OF ACFT, LANDED SAFELY.  AFTER INVESTI	GATION, DETERMINED LT AILERON FEEL BUNGEE WAS COLLECTING WATER AND FREEZING DURING HIGH ALTITUDE FLIGHT.	2	L	7	2 	4J			RT	T00007WI					 
1997102300824	19971023	00824	CE  	1997	10	23	97ZZZX4496       	1	19971013	G	2731	040010757	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										ELEV TRIM TAB	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	24264					15280183				DURING 100-HOUR INSPECTION, NOTED THE UPPER ELEVATOR TRIM TAB CABLE HAD SEVERAL BROKEN STRANDS.  UPON REMOVAL, FOUND THE	 .0937 INCH 7 BY 7 CABLE WAS BROKEN IN TWO AREAS.  ONE FORWARD OF AND THE OTHER AFT OF THE PULLEYS WHICH CHANGE CABLE DI	RECTION IN THE HORIZONTAL STABILIZER.  BREAK FORWARD OF PULLEY HAD ONLY ONE STRAND LEFT.  AFT OF PULLEY HAD TWO STRANDS.	  ANNUAL INSPECTION WAS DONE IN APRIL, 1997.  LAST 100-HOUR INSPECTION ACCOMPLISHED IN JULY, 1997.  BOTH ELEVATOR TRIM T	AB CABLES AND CHAIN WERE REPLACED.  SUBMITTER RECOMMENDS CLOSER LOOK AT ALL CABLES WHERE THEY GO AROUND PULLEYS.		1	H	7	1 	3O			NT	3A19    					 
1997102300825	19971023	00825	EA  	1997	10	23	97ZZZX4497       	2	19971008	G	7421	SR87	SPARK PLUG      			CESSNA	177   	177         	2073704	CE  	LYC   	O320  	O320D2A     	41508	EA  					INSULATOR	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			WP	23	3420T	140  				17700720	L2095127AC			ENGINE RPM DROPPED TO APPROXIMATELY 2,000 RPM ON CLIMB-OUT.  GROUND RUN-UP WAS NORMAL BEFORE AND AFTER FLIGHT AND DURING	 FIRST 200 FEET OF CLIMB OUT.  INSPECTION OF INDUCTION, FUEL AND IGNITION SYSTEMS, REVEALED TWO AUBURN SR-87 AC PLUGS WI	TH BROKEN INSULATORS ON THE COMBUSTION END.  EACH INSULATOR WAS IN TWO PIECES BROKEN LENGTHWISE WITH CENTER ELECTRODE. C	AUSE OF BROKEN INSULATORS UNDETERMINED.			1	H	7	1 	3O	3	O	NT	A13CE   	E274				 
1997102300827	19971023	00827	CE  	1997	10	23	97ZZZX4499       	1	19971009	G	5330	51113031	SKIN            			CESSNA	425   	425         	2076018	CE  										LT FUSELAGE	CRACKED         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	6886V	5126 				4250154				DURING REMOVAL OF WINDSHIELD RETAINER FOR REPLACMENT OF WINDSHIELD, FOUND APPROXIMATEY 2 INCH LONG CRACK UNDER LT LOWER 	CORNER OF WINDSHIELD RETAINER.  CRACK APPARENTLY CAUSED BY IMPROPER REMOVAL PROCEDURES OF RETAINER DURING A PREVIOUS WIN	DSHIELD CHANGE.  AN ENGINEERING ORDER FROM CESSNA WAS REQUIRED TO REPAIR DAMAGE CAUSING THE OPERATOR ADDED EXPENSE AND D	OWN-TIME.  SUBMITTER STATED THE MAINTENANCE MANUAL PROCEDURES SHOULD BE FOLLOWED CLOSELY TO PREVENT THESE TYPES OF DAMAG	E FROM OCCURRING.		1	L	7	2 	3T			RT	A7CE    					 
1997102300828	19971023	00828	CE  	1997	10	23	97ZZZX4500       	1	19971016	G	5711		SPAR            			BBAVIA	8     	8KCAB       	2110612	CE  										WING	CRACKED         	B		A	CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	76KF	2615 				15374				DURING ANNUAL INSPECTION, PERFORMED WING SPAR INSPECTION PER AMERICAN CHAMPION SL 406 FOR WOOD SPARS:   AC-43-16 ALERT N	R 226 MAY97:  FOUND EXTENSIVE COMPRESSION CRACKS AT FRONT, REAR AT BOTTOM OF BOTH WING SPARS.  AIRCRAFT USED FOR AEROBAT	IC FLIGHT.  AD 87-18-09 PREVIOUSLY C/W.  NO ACCIDENT DAMAGE IN LOGS.  AIRCRAFT ALWAYS HANGARED.  EXTRA INSPECTION PANELS	 REQUIRED TO DISCOVER EXTENT OF CRACKING AND TO FACILITATE ACCESS.			1	H	7	1 	3O				A21CE   					 
1997102300829	19971023	00829	CE  	1997	10	23	97ZZZX4501       	1	19971009	G	3250	0813000105	BRACKET         			CESSNA	310   	310L        	2074230	CE  										STEER BELLCRANK	CRACKED         	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2239F	3000 				310L0039				ON DEPLOYMENT OF LANDING GEAR NOSE, WHEEL STUCK 60 DEGREES TO LEFT OF CENTER.  PERFORMED GEAR SWING, FOUND ATTACH BRACKE	TS FOR STEERING BELLCRANK CRACKED.  REPLACED BRACKETS.  GEAR RETRACTION NORMAL.					1	L	7	2 	3O				3A10    					 
1997102300830	19971023	00830	CE  	1997	10	23	97ZZZX4502       	1	19971009	G	3250	0813000106	BRACKET         			CESSNA	310   	310L        	2074230	CE  										STEER BELLCRANK	CRACKED         	B	S	A	CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2239F	3000 				310L0039				ON DEPLOYMENT OF LANDING GEAR NOSE, WHEEL STUCK 60 DEGREES TO LEFT OF CENTER.  PERFORMED GEAR SWING, FOUND ATTACH BRACKE	TS FOR STEERING BELLCRANK CRACKED.  REPLACED BRACKETS.  GEAR RETRACTION NORMAL.					1	L	7	2 	3O				3A10    					 
1997102300831	19971023	00831	CE  	1997	10	23	97ZZZX4503       	1	19971011	G	2820		O-RING          			CESSNA	172   	172F        	2072414	CE  										SUMP STRAINER	DETERIORATED    	D				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	23	8688U	3600 				17252592				A FUEL ODOR BECAME NOTICEABLE THEN STRONG IN THE CABIN OVER A SHORT PERIOD OF TIME.  THE WHOLE FUEL SYSTEM WAS CHECKED A	ND NO LEAKS WERE VISIBLE.  ONLY AFTER A FUEL STAIN (RED MOTOR GAS) WAS SEEN ON THE BELLY WAS THE SEEP TRACED TO THE FUEL	 (STRAINER SUMP) WHERE THE O-RING SEAL AT THE TOP HAD DETERIORATED ALLOWING AN ALMOST INVISIBLE SEEP.  O-RING REPLACMENT	 STOPPED THE PROBLEM.  TIME AT 3,600 HOURS.			1	H	7	1 	3O			NT	3A12    					 
1997102300832	19971023	00832	GL  	1997	10	23	97ZZZX4504       	1	19971003	G	5797		WIRE            			AMTR  	PITTS 	PITTSSPECS1C	       	GL  										DRAG ANTI-DRAG	LOOSE           	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	93LR					RN2851				SEVERAL LOOSE WING DRAG AND ANTI-DRAG WIRES DISCOVERED DURING ANNUAL INSPECTION OF A HOMEBUILT PITTS S1C.  IN ORDER TO C	HECK ALL WIRES, ADDITIONAL INSPECTION HOLES HAD TO BE MADE IN THE WINGS.  WITH ALL WIRES ACCESSIBLE FURTHER INSP REVEALE	D ALL 8 DRAG WIRES AND 5 OF THE 8 ANTI-DRAG WIRES LOOSE.  ACCESS HOLES WERE ADDED AT ALL WIRE ATTACHMENT LOCATIONS.  AT 	THIS POINT, DISCOVERED NUTS MEANT TO SECURE THESE WIRES HAD WORKED LOOSE.  THE WIRES WERE TIGHTENED AND SECURED.  IT WAS	 NOT POSSIBLE TO DETERMINE WHAT CAUSED WIRE NUTS TO WORK LOOSE.  TIME AND VIBRATION ARE THOUGHT TO BE THE MAJOR FACTORS 	INVOLVED.	1	Q	7	1 	3O			 	EXPA1Q71					 
1997102300833	19971023	00833	NE  	1997	10	23	97ZZZX4505       	1	19971010	G	3233	9720031	ACTUATOR ROD    			CONAER	LA4   	LA4200      	5110310	NE  										NLG ACTUATOR	FAILED          	D	S			A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NE	05	1105L	702  				696				AFTER TAKEOFF, MLG RETRACTED NORMALLY AND NLG REMAINED EXTENDED.  LANDING GEAR WAS RE-EXTENDED AND A SAFE LANDING WAS MA	DE.  MAINTENANCE INSP FOUND THE THREADED END  OF NLG ACTUATOR ROD HAD BROKEN OFF ALLOWING NLG ACTUATOR TO HANG FREELY IN	 THE WHEELWELL.  THE NLG DOWNLOCK HELD AND THE AIRCRAFT WAS NOT DAMAGED.  THE SUSPECT CAUSE OF FAILURE WAS IMPROPER NOSE	 GEAR RIGGINGS.  SUBMITTER STATED AIRCRAFT MM IS VAGUE ON THIS SUBJECT.			1	H	7	1 	3O				1A13    					 
1997102300834	19971023	00834	SO  	1997	10	23	97ZZZX4506       	1	19970930	G	5720		RIVETS          			PIPER 	PA28  	PA28R180    	7102809	SO  										WING ASSY	DEFECTIVE       	B	L		RMMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	4620J	5128 				28R30503				DURING REPLACEMENT OF PAN UNDER WING WALK IN THE GEAR WELL, RIB WAS FOUND CRACKED. THE WING WAS REMOVED AND FOUND SEVERA	L WING ATTACHMENT BOLTS CORRODED.  BOLTS AND SPECIAL WASHERS NOT IN PROPER LOCATIONS PER PA28 MM.  (WING ATTACH).  NO SH	IMS AT EITHER WING SPAR.  SEVERAL RIVETS NOT INSTALLED.  (HOLES NOT DRILLED), CHERRY MAX RIVETS THAT WERE TOO SHORT INST	ALLED.  OTHER RIVETS BUCKED POORLY.  BOTH AILERON CABLES WORN, NO STRAND BROKEN, BUT REPLACED FOR PREVENTATIVE MAINTENAN	CE.  LEFT WING ATTACHMENT BOLTS REPLACED ONE AT A TIME.  SEVERAL FOUND CORRODED.		1	L	7	1 	3O				2A13    					 
1997102300835	19971023	00835	SO  	1997	10	23	97ZZZX4507       	1	19970930	G	2710		CONTROL CABLE   			PIPER 	PA28  	PA28R180    	7102809	SO  										AILERON	WORN            	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4620J	5128 				28R30503				DURING REPLACEMENT OF PAN UNDER WING WALK IN THE GEAR WELL, RIB WAS FOUND CRACKED. THE WING WAS REMOVED AND FOUND SEVERA	L WING ATTACHMENT BOLTS CORRODED.  BOLTS AND SPECIAL WASHERS NOT IN PROPER LOCATIONS PER PA28 MM.  (WING ATTACH).  NO SH	IMS AT EITHER WING SPAR.  SEVERAL RIVETS NOT INSTALLED.  (HOLES NOT DRILLED), CHERRY MAX RIVETS THAT WERE TOO SHORT INST	ALLED.  OTHER RIVETS BUCKED POORLY.  BOTH AILERON CABLES WORN, NO STRAND BROKEN, BUT REPLACED FOR PREVENTATIVE MAINTENAN	CE.  LEFT WING ATTACHMENT BOLTS REPLACED ONE AT A TIME.  SEVERAL FOUND CORRODED.		1	L	7	1 	3O			 	2A13    					 
1997102300836	19971023	00836	SO  	1997	10	23	97ZZZX4508       	1	19970930	G	5711	6212100	SHIMS           			PIPER 	PA28  	PA28R180    	7102809	SO  										WING SPAR	MISSING         	B			RMMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	4620J	5128 				28R30503				DURING REPLACEMENT OF PAN UNDER WING WALK IN THE GEAR WELL, RIB WAS FOUND CRACKED. THE WING WAS REMOVED AND FOUND SEVERA	L WING ATTACHMENT BOLTS CORRODED.  BOLTS AND SPECIAL WASHERS NOT IN PROPER LOCATIONS PER PA28 MM.  (WING ATTACH).  NO SH	IMS AT EITHER WING SPAR.  SEVERAL RIVETS NOT INSTALLED.  (HOLES NOT DRILLED), CHERRY MAX RIVETS THAT WERE TOO SHORT INST	ALLED.  OTHER RIVETS BUCKED POORLY.  BOTH AILERON CABLES WORN, NO STRAND BROKEN, BUT REPLACED FOR PREVENTATIVE MAINTENAN	CE.  LEFT WING ATTACHMENT BOLTS REPLACED ONE AT A TIME.  SEVERAL FOUND CORRODED.		1	L	7	1 	3O				2A13    					 
1997102300837	19971023	00837	SO  	1997	10	23	97ZZZX4509       	1	19970930	G	5741		BOLTS           			PIPER 	PA28  	PA28R180    	7102809	SO  										WING ATTACH	WRONG PLACEMENT 	B			RMMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	4620J	5128 				28R30503				DURING REPLACEMENT OF PAN UNDER WING WALK IN THE GEAR WELL, RIB WAS FOUND CRACKED. THE WING WAS REMOVED AND FOUND SEVERA	L WING ATTACHMENT BOLTS CORRODED.  BOLTS AND SPECIAL WASHERS NOT IN PROPER LOCATIONS PER PA28 MM.  (WING ATTACH).  NO SH	IMS AT EITHER WING SPAR.  SEVERAL RIVETS NOT INSTALLED.  (HOLES NOT DRILLED), CHERRY MAX RIVETS THAT WERE TOO SHORT INST	ALLED.  OTHER RIVETS BUCKED POORLY.  BOTH AILERON CABLES WORN, NO STRAND BROKEN, BUT REPLACED FOR PREVENTATIVE MAINTENAN	CE.  LEFT WING ATTACHMENT BOLTS REPLACED ONE AT A TIME.  SEVERAL FOUND CORRODED.		1	L	7	1 	3O				2A13    					 
1997102300838	19971023	00838	SO  	1997	10	23	97ZZZX4510       	1	19970930	G	5741		BOLTS           			PIPER 	PA28  	PA28R180    	7102809	SO  										WING ATTACH	CORRODED        	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4620J	5128 				28R30503				DURING REPLACEMENT OF PAN UNDER WING WALK IN THE GEAR WELL, RIB WAS FOUND CRACKED. THE WING WAS REMOVED AND FOUND SEVERA	L WING ATTACHMENT BOLTS CORRODED.  BOLTS AND SPECIAL WASHERS NOT IN PROPER LOCATIONS PER PA28 MM.  (WING ATTACH).  NO SH	IMS AT EITHER WING SPAR.  SEVERAL RIVETS NOT INSTALLED.  (HOLES NOT DRILLED), CHERRY MAX RIVETS THAT WERE TOO SHORT INST	ALLED.  OTHER RIVETS BUCKED POORLY.  BOTH AILERON CABLES WORN, NO STRAND BROKEN, BUT REPLACED FOR PREVENTATIVE MAINTENAN	CE.  LEFT WING ATTACHMENT BOLTS REPLACED ONE AT A TIME.  SEVERAL FOUND CORRODED.		1	L	7	1 	3O				2A13    					 
1997102300839	19971023	00839	SO  	1997	10	23	97ZZZX4511       	1	19970930	G	5720	6767300	PAN             			PIPER 	PA28  	PA28R180    	7102809	SO  										GEAR WELL	CRACKED         	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4620J	5128 				28R30503				DURING REPLACEMENT OF PAN UNDER WING WALK IN THE GEAR WELL, RIB WAS FOUND CRACKED. THE WING WAS REMOVED AND FOUND SEVERA	L WING ATTACHMENT BOLTS CORRODED.  BOLTS AND SPECIAL WASHERS NOT IN PROPER LOCATIONS PER PA28 MM.  (WING ATTACH).  NO SH	IMS AT EITHER WING SPAR.  SEVERAL RIVETS NOT INSTALLED.  (HOLES NOT DRILLED), CHERRY MAX RIVETS THAT WERE TOO SHORT INST	ALLED.  OTHER RIVETS BUCKED POORLY.  BOTH AILERON CABLES WORN, NO STRAND BROKEN, BUT REPLACED FOR PREVENTATIVE MAINTENAN	CE.  LEFT WING ATTACHMENT BOLTS REPLACED 1 AT A TIME.  SEVERAL FOUND CORRODED.		1	L	7	1 	3O				2A13    					 
1997102300840	19971023	00840	CE  	1997	10	23	97ZZZX4512       	1	19970901	G	2140	22540151	HEAT EXCHANGER  			CESSNA	182   	TR182       	2072735	CE  										CABIN HEAT	CRACKED         	B	L		VX3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	4840T	2223 				R18201775				INSPECTION OF HEAT EXCHANGER FOUND BACK SIDE OF UNIT SPIRAL FINS CRACKED AND LEAKING.  ALSO, FORWARD FLANGE COUPLED TO N	R 1 CYLINDER EXHAUST RISER DETERIORATED.  THESE CRACKS AND LEAKS ARE A HAZARD DUE TO CARBON MONOXIDE IN CABIN HEAT.					1	H	7	1 	3O				3A13    					 
1997102300841	19971023	00841	CE  	1997	10	23	97ZZZX4513       	1	19970901	G	5712	082217579	RIB             			CESSNA	414   	414         	2075908	CE  										WHEELWELL	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MAIN LANDING GEAR SUPPORT STRUCTURE, LT AND RT, MLG WHEELWELL - CRACKS ARE OCCURRING IN THE RIBS, PN 0822175-79, -74, CE	NTER RIB WEB, ORIGINATING AT UPPER AFT CORNER OF THE CUT-OUT HOLE (WHERE THE OPERATING PUSH/PULL ROD PASSES THROUGH) PRO	PAGATING TOWARDS TOP OF RIB.  WING SKINS, P/N 0822000-9, UPPER, INBOARD ARE CRACKING ABOVE RIB, INSIDE BAGGAGE LOCKER (N	ACELLE).  MLG SIDE BRACE SUPPORT CASTINGS, P/N 0822180-7, -8, ARE BOLTED TO THE RIBS, (P/N 0822175-79,-74).  BOTH CASTIN	GS FOUND LOOSE AND ONE, -8, CRACKED.		1	L	7	2 	3O			RT	A7CE    					 
1997102300842	19971023	00842	CE  	1997	10	23	97ZZZX4514       	1	19970901	G	5720	08221808	CASTING         			CESSNA	414   	414         	2075908	CE  										MLG SIDE BRACE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MAIN LANDING GEAR SUPPORT STRUCTURE, LT AND RT, MLG WHEELWELL - CRACKS ARE OCCURRING IN THE RIBS, PN 0822175-79, -74, CE	NTER RIB WEB, ORIGINATING AT UPPER AFT CORNER OF THE CUT-OUT HOLE (WHERE THE OPERATING PUSH/PULL ROD PASSES THROUGH) PRO	PAGATING TOWARDS TOP OF RIB.  WING SKINS, P/N 0811000-9, UPPER, INBOARD ARE CRACKING ABOVE RIB, INSIDE BAGGAGE LOCKER (N	ACELLE).  MLG SIDE BRACE SUPPORT CASTINGS, P/N 0822180-7, -8, ARE BOLTS TO THE RIBS, (P/N 822175-79,-74).  BOTH CASTINGS	 FOUND LOOSE AND ONE, -8, CRACKED.		1	L	7	2 	3O			RT	A7CE    					 
1997102300843	19971023	00843	CE  	1997	10	23	97ZZZX4515       	1	19970901	G	5720	08221807	CASTING         			CESSNA	414   	414         	2075908	CE  										MLG SIDE BRACE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MAIN LANDING GEAR SUPPORT STRUCTURE, LT AND RT, MLG WHEELWELL - CRACKS ARE OCCURRING IN THE RIBS, PN 0822175-79, -74, CE	NTER RIB WEB, ORIGINATING AT UPPER AFT CORNER OF THE CUT-OUT HOLE (WHERE THE OPERATING PUSH/PULL ROD PASSES THROUGH) PRO	PAGATING TOWARDS TOP OF RIB.  WING SKINS, P/N 0811000-9, UPPER, INBOARD ARE CRACKING ABOVE RIB, INSIDE BAGGAGE LOCKER (N	ACELLE).  MLG SIDE BRACE SUPPORT CASTINGS, P/N 0822180-7, -8, ARE BOLTS TO THE RIBS, (P/N 822175-79,-74).  BOTH CASTINGS	 FOUND LOOSE AND ONE, -8, CRACKED.		1	L	7	2 	3O			RT	A7CE    					 
1997102300844	19971023	00844	CE  	1997	10	23	97ZZZX4516       	1	19970901	G	5730	08220009	SKIN            			CESSNA	414   	414         	2075908	CE  										LT/RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MAIN LANDING GEAR SUPPORT STRUCTURE, LT AND RT, MLG WHEELWELL - CRACKS ARE OCCURRING IN THE RIBS, PN 0822175-79, -74, CE	NTER RIB WEB, ORIGINATING AT UPPER AFT CORNER OF THE CUT-OUT HOLE (WHERE THE OPERATING PUSH/PULL ROD PASSES THROUGH) PRO	PAGATING TOWARDS TOP OF RIB.  WING SKINS, P/N 0811000-9, UPPER, INBOARD ARE CRACKING ABOVE RIB, INSIDE BAGGAGE LOCKER (N	ACELLE).  MLG SIDE BRACE SUPPORT CASTINGS, P/N 0822180-7, -8, ARE BOLTS TO THE RIBS, (P/N 822175-79,-74).  BOTH CASTINGS	 FOUND LOOSE AND ONE, -8, CRACKED.		1	L	7	2 	3O			RT	A7CE    					 
1997102300845	19971023	00845	CE  	1997	10	23	97ZZZX4517       	1	19970901	G	5712	082217574	RIB             			CESSNA	414   	414         	2075908	CE  										WHEELWELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MAIN LANDING GEAR SUPPORT STRUCTURE, LT AND RT, MLG WHEELWELL - CRACKS ARE OCCURRING IN THE RIBS, PN 0822175-79, -74, CE	NTER RIB WEB, ORIGINATING AT UPPER AFT CORNER OF THE CUT-OUT HOLE (WHERE THE OPERATING PUSH/PULL ROD PASSES THROUGH) PRO	PAGATING TOWARDS TOP OF RIB.  WING SKINS, P/N 0811000-9, UPPER, INBOARD ARE CRACKING ABOVE RIB, INSIDE BAGGAGE LOCKER (N	ACELLE).  MLG SIDE BRACE SUPPORT CASTINGS, P/N 0822180-7, -8, ARE BOLTS TO THE RIBS, (P/N 822175-79,-74).  BOTH CASTINGS	 FOUND LOOSE AND ONE, -8, CRACKED.		1	L	7	2 	3O			RT	A7CE    					 
1997102300846	19971023	00846	CE  	1997	10	23	97ZZZX4518       	1	19970901	G	5312	501302014	BULKHEAD        			CESSNA	414   	414         	2075908	CE  										NLG WELL	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997102300847	19971023	00847	CE  	1997	10	23	97ZZZX4519       	1	19970901	G	5320	52130286	T ANGLE         			CESSNA	414   	414         	2075908	CE  										NLG WELL	RIVET SHEARED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997013000157	19970130	00157	SO  	1997	1	30	97ZZZX452        	1	19970103	G	5711	62070006	SPAR            		66601004    	PIPER 	PA28  	PA28180     	7102808	SO  										LT WING	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	8968J	3437 				282991				FOUND DURING INSPECTION SEVERE INTERGRANULAR CORROSION OF LT WING SPAR JUST OUTBOARD OF GEAR ATTACHMENT.  REQUIRED SPAR 	REPLACEMENT.  AIRCRAFT HAD SPENT 90 PERCENT OF ITS LIFE NEAR THE OCEAN.  REMOVAL OF FUEL TANK OR CLOSE INSPECTION WITH A	 MIRROR AND LIGHT WILL LOCATE THIS PROBLEM.  WING SPAR P/N 66601-004.				1	L	7	1 	3O				2A13    					 
1997102300848	19971023	00848	CE  	1997	10	23	97ZZZX4520       	1	19970901	G	5320	50130225	T ANGLE         			CESSNA	414   	414         	2075908	CE  										NLG WELL	RIVET SHEARED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997102300849	19971023	00849	CE  	1997	10	23	97ZZZX4521       	1	19970901	G	5320	50130443	STIFFENER       			CESSNA	414   	414         	2075908	CE  										NLG WELL	RIVETS LOOSE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997102300850	19971023	00850	CE  	1997	10	23	97ZZZX4522       	1	19970901	G	5320	501304411	STIFFENER       			CESSNA	414   	414         	2075908	CE  										NLG WELL	RIVETS LOOSE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997102300851	19971023	00851	CE  	1997	10	23	97ZZZX4523       	1	19970901	G	5320	52130453	DOUBLER         			CESSNA	414   	414         	2075908	CE  										NLG LT WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997102300852	19971023	00852	CE  	1997	10	23	97ZZZX4524       	1	19970901	G	5320	52130452	DOUBLER         			CESSNA	414   	414         	2075908	CE  										NLG RT WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943					4140645				NOSE WHEELWELL SUBSTRUCTURE - CRACKS, LOOSE AND SHEARED RIVETS WERE FOUND ON BOTH SIDES OF NOSE GEAR WHEELWELL SUBSTRUCT	URE.  BULKHEAD, P/N 5013020-14, HAD CRACKED BUTT END, RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6 AND P/N 5013022-5 ARE	 RIVETED GUSSETS, P/N 521328-4 AND P/N 5013022-801. LOOSE AND WORKING RIVETS WERE FOUND IN LOWER END OF STIFFENERS, P/N 	5013044, -3, AND -11.  DOUBLERS, P/N 521-3045-3 LT, AND -2 RT, WERE FOUND CRACKED AT UPPER AFT CORNER RADIUS RELIEF CUT-	OUTS.		1	L	7	2 	3O			RT	A7CE    					 
1997103000026	19971030	00026	CE  	1997	10	30	97ZZZX4525       	1	19971010	G	2571		DRAIN TUBE      			CESSNA	182   	182Q        	2072732	CE  										BATTERY BOX	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09										WHILE PERFORMING 100-HOUR INSPECTION, NOTICED DRAIN TUBE FROM BATTERY BOX HAD BEEN LEAKING ACID INTO REAR FUSELAGE.  SUB	MITTER STATED THIS BATTERY BOX IS MOUNTED RIGHT OVER CONTROL CABLES AND CABLES COULD BE DAMAGED.					1	H	7	1 	3O			NT	3A13    					 
1997103000027	19971030	00027	EU  	1997	10	30	97ZZZX4526       	1	19970918	G	7810		MUFFLER         			GROB  	G115  	G115C       	1660303	EU  										LT INLET FLANGE	SEPARATED       	B			HIAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	115SR	489  								MUFFLER INLET FLANGE COMPLETELY SEPARATED FROM BODY OF MUFFLER (LEFT SIDE MUFFLER).						1	L	7	1 	3O			NT	A57EU   					 
1997103000028	19971030	00028	SO  	1997	10	30	97ZZZX4527       	1	19971018	G	2750	40092009	BELLCRANK       			PIPER 	PA22  	PA22160     	7102214	SO  										FLAP	BROKE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	3465Z					227387				REFERENCE ALERT NR 231.  REPLACED A FLAP BELLCRANK.  PUSH/PULL TUBE END BROKE OFF AT BOLT HOLE DURING INSPECTION WHILE R	ECOVERING OPERATION WAS BEING ACCOMPLISHED.  TOTAL TIME, 1,914.1 HOURS.  SUBMITTER STATED PART APPEARS TO BE ORIGINAL. T	HIS COULD HAVE CAUSED A SPLIT FLAP CONDITION.  SUBMITTER STATED AD SHOULD BE IN ORDER TO INSPECT THE FLEET AS IT APPEARS	 TO BE A COMMON PROBLEM.  REF:  FIG 8, INDEX 92, PAZZ PARTS CATALOG, FEB 1961.			1	H	7	1 	3O				1A6     					 
1997103000029	19971030	00029	CE  	1997	10	30	97ZZZX4528       	1	19970828	G	3213	50411081	BEARING         			CESSNA	414   	414         	2075908	CE  										MLG BARREL	CRACKED         	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	414DK	4798 				4140532				IN C/W AD 90-02-13, THE MAIN GEAR BARREL INNER BEARING WAS FOUND CRACKED.  NEW P/N 5141109-1 BEARING INSTALLED.						1	L	7	2 	3O			RT	A7CE    					 
1997103000030	19971030	00030	CE  	1997	10	30	97ZZZX4529       	1	19971001	G	2820	1560013S0350	HOSE            	STRATOFLEX  		CESSNA	210   	T210N       	2073456	CE  										ENGINE COMPT	LEAKS           	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	4905C	311  				21063664				STRATOFLEX HOSE ASSY LEAKS.  HOSE HARD AND BRITTLE.  SUBMITTER STATED HOSES IN THE ENGINE COMPARTMENT OF TURBO AIRCRAFT 	DO NOT SEEM TO LAST AS LONG (DUE TO HEAT).  ONLY 2 YEARS, 6 MONTHS OLD.					1	H	7	1 	3O				3A21    					 
1997103000031	19971030	00031	CE  	1997	10	30	97ZZZX4530       	1	19970303	G	2810	41534	FUEL VENT       		714147      	BBAVIA	8     	8KCAB       	2110612	CE  										INVERTED SYSTEM	OBSTRUCTED      	G		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			WP	09	5027F					57179				AIRCRAFT EXPERIENCED ENGINE FAILURE DURING AEROBATIC FLIGHT.  PILOT ATTEMPTED TO RESTART ENGINE WITH NO SUCCESS.  AIRCRA	FT LANDED ON ROAD, LOST DIRECTIONAL CONTROL, AND IMPACTED A FENCE PARALLELING THE ROAD.  SUBSTANTIAL DAMAGE WAS DONE.  I	NVESTIGATION WAS DONE ON FUEL SYSTEM BY NTSB AND RESULTED IN FINDING CONTAMINATION IN THE FUEL IN THE HEADER TANK WHEN I	T WAS DRAINED.  ALSO, INVERTED FUEL VENT WAS FOUND TO HAVE OVER 50 PERCENT OBSTRUCTION AT AN ELBOW FITTING OF A SOLID MA	TERIAL THAT COVERED THE INLET.  THE SHAPE OF THE PARTICLE CONFORMED TO THE SHAPE OF THE UNOBSTRUCTED PORTION OF THE ELBO	W INLET AND EDGE.	1	H	7	1 	3O				A21CE   					 
1997103000032	19971030	00032	CE  	1997	10	30	97ZZZX4531       	1	19970926	G	2810	541611322	VENT TUBE TABS  			LEAR  	55    	55LEAR      	5170702	CE  										REFUEL VENT	CRACKED         	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1983Y	4293 				079				WELDED TABS AT UPPER END OF VENT TUBE (QUANTITY 3) WHICH FORM ATTACH POINTS FOR THE TUBE WERE FOUND CRACKED DURING FUEL 	CELL MAINTENANCE.  CAUSE UNKNOWN.					2	L	7	2 	4F				A10CE   					 
1997103000035	19971030	00035	CE  	1997	10	30	97ZZZX4534       	1	19971003	G	2730	115610010325	TORQUE TUBE     			BEECH 	99    	C99         	1154006	CE  										ELEVATOR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6645N	481  				U213				FOUND TORQUE TUBE CRACKED DURING ROUTINE INSPECTION.  CRACK ORIGINATED AT THE TAPER PIN HOLE AT THE INBOARD CASTING.						1	L	7	2 	3T				A14CE   					 
1997103000036	19971030	00036	CE  	1997	10	30	97ZZZX4535       	1	19971010	G	2720	551426022	CONTROL CABLE   			CESSNA	501   	501         	2076603	CE  										RUDDER SERVO	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	833JL	278  				5010045				RUDDER SERVO CABLE BROKEN.  DISCOVERED CONDITION WHEN C/W SCHEDULED PHASE 5 CESSNA CITATION INSPECTION.  NEW CABLE INSTA	LLED 8-16-94 AT 3,362 HOURS.  FOUND BROKEN AT 3,640.2 HOURS.  SUBMITTER STATED SAFETY OF FLIGHT ITEM!!					1	L	7	2 	4F			 	A27CE   					 
1997103000037	19971030	00037	CE  	1997	10	30	97ZZZX4536       	1	19971010	G	2720	551426024	CONTROL CABLE   			CESSNA	501   	501         	2076603	CE  										RUDDER SERVO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	833JL	278  				5010045				RUDDER SERVO CABLE BROKEN.  DISCOVERED CONDITION WHEN C/W SCHEDULED PHASE 5 CESSNA CITATION INSPECTION.  NEW CABLE INSTA	LLED 8-16-94 AT 3,362 HOURS.  FOUND BROKEN AT 3,640.2 HOURS.  SUBMITTER STATED SAFETY OF FLIGHT ITEM!!					1	L	7	2 	4F			 	A27CE   					 
1997103000038	19971030	00038	NM  	1997	10	30	97ZZZX4537       	1	19970808	G	7110		COWLING         			BOEING	727   	727         	1384001	NM  										ENG NR 1-NR 3	CORRODED        	B			EG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25					RL825					SEVERE CORROSION UNDER FIRESHIELD.  FIRESHIELD MUST BE REMOVED TO DETECT OR REPAIR.  CORROSION DAMAGE CAUSED BY FAILURE 	OF BOND ALLOWING MOISTURE TO ENTER.					2	L	7	3 	4F				A3WE    					 
1997103000039	19971030	00039	NM  	1997	10	30	97ZZZX4538       	1	19970808	G	7110	6519507222	COWLING         			BOEING	727   	727         	1384001	NM  										ENG NR 1- NR 3	CORRODED        	B			EG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25					RC1155					SEVERE CORROSION UNDER FIRESHIELD.  FIRESHIELD MUST BE REMOVED TO DETECT AND REPAIR CORRISON DAMAGE CAUSED BY FAILURE OF	 BOND ALLOWING MOISTURE TO ENTER.					2	L	7	3 	4F				A3WE    					 
1997103000040	19971030	00040	NM  	1997	10	30	97ZZZX4539       	1	19970808	G	7110	B277101704	COWLING         			BOEING	727   	727         	1384001	NM  										ENG NR 1-NR 3	CORRODED        	B			EG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25					RC137					SEVERE CORROSION UNDER FIRESHIELD.  DISCOVERED WHEN CONVERTING COWLING FROM 65-19507-245 TO HUSK KIT MODEL.  FIRESHIELD 	MUST BE REMOVED TO DETECT AND REPAIR CORROSION.					2	L	7	3 	4F				A3WE    					 
1997103000041	19971030	00041	NM  	1997	10	30	97ZZZX4540       	1	19970808	G	7110	6519507249	COWLING         			BOEING	727   	727         	1384001	NM  										ENG NR 1-NR 3	CORRODED        	B			EG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25					K32939					SEVERE CORROSION UNDER FIRESHIELD.  FIRESHIELD MUST BE REMOVED TO DETECT AND REPAIR.  CORROSION DAMAGE CAUSED BY FAILURE	 OF BOND ALLOWING MOISTURE TO ENTER.					2	L	7	3 	4F				A3WE    					 
1997103000042	19971030	00042	NM  	1997	10	30	97ZZZX4541       	1	19971015	G	5347		TRACK SUPPORT   			BOEING	757   	75723APF    	1384966	NM  										RT BS 860-BS 880	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				RIGHT SEAT TRACK SUPPORT, SECOND FROM CENTER BS 860 TO BS 880, HAS INTERGRANULAR CORROSION.  REPAIRED SEAT TRACK PER SRM	 53-00-52.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000043	19971030	00043	NM  	1997	10	30	97ZZZX4542       	1	19971015	G	5230		SEAM TAPE       			BOEING	757   	75723APF    	1384966	NM  										CARGO COMPT	WRONG PART      	B			EB1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	572CA					24868				SEAM TAPE IN MAIN CARGO COMPARTMENT DOES NOT MEET FAR 25.853 REQUIREMENTS.  REMOVED TAPE AND RETAPED WITH APPROVED TAPE.	  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000044	19971030	00044	NM  	1997	10	30	97ZZZX4543       	1	19971015	G	5315		FLOOR BEAM      			BOEING	757   	75723APF    	1384966	NM  										BS 880 LBL 45.5	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				STA 880 FLOOR BEAM BETWEEN LBL 45.5 AND LBL 24.75, FORWARD UPPER CHORD OUTBOARD, FLOOR BOARD FASTENERS HOLE LOWER SIDE, 	HAS INTERGRANULAR CORROSION.  REPAIR SEAT TRACK PER SRM 53-00-51.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000045	19971030	00045	NM  	1997	10	30	97ZZZX4544       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 880-BS 900	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				RIGHT SEAT TRACK SECOND FROM CENTER SUPPORT CORRODED AT FS 880 TO FS 900.  CLEANED AND TREATED CORROSION PER SRM 53-00-5	2.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000046	19971030	00046	NM  	1997	10	30	97ZZZX4545       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 880 RT	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				RIGHT SEAT TRACK FIRST FROM CENTER SUPPORT STIFFENER CORRODED AT FS 880.  REMOVED AND REPLACED ATTACH BRACKET PER SRM 51	-30-51 AND SRM 51-30-40.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000047	19971030	00047	NM  	1997	10	30	97ZZZX4546       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 880 RT	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				RIGHT SEAT TRACK SECOND FROM CENTER SUPPORT STIFFENER CORRODED AT FS 880.  REMOVED AND REPLACED ATTACH BRACKET PER SRM 5	1-30-51 AND SRM 51-30-40.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000048	19971030	00048	NM  	1997	10	30	97ZZZX4547       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 900 RT	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				INTERGRANULAR CORROSION AROUND FASTENER HOLES BETWEEN CENTER AND RT NR 1 SEAT TRACK AT BS 900.  REPAIRED FLOOR BOARD CHA	NNEL BETWEEN CENTER AND NR 1 SEAT TRACK PER SRM 53-01-60.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000049	19971030	00049	NM  	1997	10	30	97ZZZX4548       	1	19971015	G	5315		FLOOR BEAM      			BOEING	757   	75723APF    	1384966	NM  										BS 879	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				FLOOR BEAM CORRODED AT FS 879 OUTBOARD OF SECOND SEAT TRACK FROM CENTER RT.  REPAIR FLOOR BEAM PER SRM 53-00-51.  TAT: 2	,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000050	19971030	00050	NM  	1997	10	30	97ZZZX4549       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 880-900 LT	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				FLOATING SEAT TRACK LT SIDE STA 880 TO STA 900 HAS INTERGRANULAR CORROSION AND IS CRACKED.  FABRICATED AND INSTALLED REP	AIR ON SEAT TRACK PER DER DWG 97039.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000051	19971030	00051	NM  	1997	10	30	97ZZZX4550       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 970 RT	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				INTERGRANULAR CORROSION ON SEAT TRACK SUPPORT RT, SECOND TRACK FROM CENTER PALLET POSITION NR 7 AT FS 970 RT.  CLEANED A	ND TREATED CORROSION AND INSTALLED STRAP REPAIR ON SUPPORT PER DER DWG 97040A.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000052	19971030	00052	NM  	1997	10	30	97ZZZX4551       	1	19971015	G	5347		SEAT TRACK      			BOEING	757   	75723APF    	1384966	NM  										BS 880-900 LT	CORRODED        	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	572CA					24868				LT OUTBOARD FLOATING SEAT TRACK STA 880 TO STA 900 HAS INTERGRANULAR CORROSION.  REMOVED AND REPLACED UPPER SECTION PER 	SRM 53-00-52.  TAT:  2,628.8 HOURS.  TAC:  5,944.					2	L	7	2 	4F			RT	A2NM    					 
1997103000053	19971030	00053		1997	10	30	97ZZZX4552       	4	19970901	G	3418	370110	STALL VANE      			BEECH 	1900  	1900C       	1154161	CE  										ELECT PINS	STUCK           	B		A	FV1R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			EA	11	31134				209	UC42				STALL WARNING HORN STAYED ON CONTINUOUSLY.  UPON INSPECTION, FOUND STALL VANE STUCK IN POSITION.  WHEN REMOVING CANNON P	LUG FROM ASSEMBLY PRIOR TO REMOVING ASSY FROM AIRCRAFT, FOUND VANE WAS FREE.  AFTER REMOVING ASSEMBLY FROM AIRCRAFT, FOU	ND THE BOARD THE ELECTRICAL PINS WERE ON LOOSE.  FURTHER INSPECTION REVEALED IF THE PINS WERE PUSHED IN (LIKE ATTACHING 	CANNON PLUG), IT WOULD BIND THE MOVEMENT OF THE STALL VANE INTERNALLY.  PART WAS REPLACED WITH NEW.  OPERATION WAS SATIS	FACTORY.  DURING FUTURE INSPECTIONS, IT MAY BE ADVISABLE TO MOVE CANNON PLUG ON STALL VANE AND SEE IF VANE BINDS.		2	L	7	2 	4T			RT	A24CE   					 
1997103000054	19971030	00054	SO  	1997	10	30	97ZZZX4553       	1	19971003	G	3320	BR9800003	LIGHT TUBE      	BRUCE       		GULSTM	G1159 	GIV         	3980115	SO  										RT AFT CABIN	INOPERABLE      	D	P			K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			GL	05	3PG					1260				DURING A ROUTINE LIGHT INSPECTION, THE RIGHT AFT CABIN DOWN-WASH FLUORESCENT LIGHT TUBE WAS FOUND INOPERABLE.  ON TUBE R	EMOVAL, FOUND BURN SPOT ABOUT .50 INCH FROM THE METAL END CONNECTOR. THE HEADLINERS WAS ALSO CHARRED.					2	L	7	2 	4F			RT	A12EA   					 
1997103000055	19971030	00055	NM  	1997	10	30	97ZZZX4554       	1	19971008	G	2820	15256	HOSE            	AEROQUIP    	35461002    	CHRIS 	HUSKY 	A1          	221020X	NM  										AFT FUEL	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	11	2UJ					1140				BOTH REAR FUEL LINE HOSES HAVE FAILED WITHIN A WEEK OF EACH OTHER.  FUEL WAS FOUND SEEPING THROUGH THE OUTER COVERING OF	 HOSE.  AEROQUIP NR 1525-6.					1	H	7	1 	3O			NC	A22NM   					 
1997103000056	19971030	00056	CE  	1997	10	30	97ZZZX4555       	1	19971007	G	2434	6560T	ALTERNATOR      			BEECH 	35    	E35         	1151512	CE  										DC SYSTEM	WEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	33246					D3990				INSTALLED JASCO ALTERNATOR KIT PER STC SA999WE.  WOULD NOT CARRY TWO LANDING LIGHTS.  REPLACED REGULATOR AND ALTERNATOR 	WIRE WAS DOUBLE-CHECKED AND WAS WIRED CORRECTLY.  NEW UNIT WOULD NOT CARRY BOTH LANDING LIGHTS.  REMOVED UNIT AND WILL O	VERHAUL GENERATOR.  SUBMITTER STATED RECEIVED BAD ALTERNATORS.				1	L	7	1 	3O				A777    					 
1997103000057	19971030	00057	CE  	1997	10	30	97ZZZX4556       	1	19970911	G	3230	12436351	TORQUE LINK     			CESSNA	206   	TU206G      	2073357	CE  										NLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	7396C	3627 				U20603920				INSPECTION FOUND NLG UPPER TORQUE LINK ASSY CRACKED.						1	H	7	1 	3O				A4CE    					 
1997103000058	19971030	00058	EU  	1997	10	30	97ZZZX4557       	1	19970902	G	5102	EN1848	LINE            			LBL   	210A  	LBL210A     	5180004	EU  										SUPERCHUTE	BROKE           	D	S	A		K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	99	234TZ	371  				121				ONE OF SEVEN SUPERCHUTE RETAINING LINES FABRICATED FROM P/N EN 1848 KEVLAR CORE 3.5MM ROPE BROKE WHERE IT MAKES A 180 DE	GREE LOOP AROUND THE 5MM (.1875 INCH) SIDE OF THE GUIDE RING ATTACHED TO THE INSIDE OF THE ENVELOPE.  THE BREAKING OF TH	E RETAINING LINE ALLOWED THE PARACHUTE TO OPEN SLIGHTLY ALLOWING  MINOR UNCONTROLLED VENTING FROM THE ENVELOPE.				1	B	0	0 	0 			0	B82EU   					 
1997103000059	19971030	00059	EU  	1997	10	30	97ZZZX4558       	1	19970904	G	5102	B1D7	GAUGE           			COLT  	COLT  	COLT180A    	2301219	EU  										BURNER GAS PRESS	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	728TC	305  				2505				FUEL PRESSURE GAUGE USED ON MODEL C3 AND C3T BURNER ASSY HAS AN OPERATING RANGE OF ZERO TO 200 PSI.  WHEN FUEL TANK PRES	SURE IS ABOVE 150 PSI, OPENING THE LIQUID FUEL SHUT-OFF VALVE ON THE TANK CAUSES A PRESSURE SURGE IN THE BURNER FUEL SYS	TEM DRIVING THE PRESSURE GAUGE BEYOND ITS OPERATING LIMIT DAMAGING ITS INTERNAL MECHANISM.  THE GAUGE IS NOT REPAIRABLE 	AND MUST BE REPLACED WHEN DAMAGED.  THIS HAS BEEN A RECURRING PROBLEM IN 10 BURNER SYSTEMS.			1	B	0	0 	0 			0	B3EU    					 
1997013000161	19970130	00161	EA  	1997	1	30	97ZZZX456        	2	19970106	G	7414	10357426	DISTRIBUTOR BLK 		S6RN25      						LYC   	O360  	O360*       	41514	EA  					MAG	BUSHING SPUN    	B			WS9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					569484					MAG RUBBER BLOCK CENTER BUSHING SPUN IN BLOCK.											3	O			E286				 
1997103000177	19971030	00177	NM  	1997	10	30	97ZZZX4566       	1	19970929	G	7830	315T440328	TRACK BEAM      		315T4014112A	BOEING	747   	747*        		NM  										THRUST REVERSER	EXCESS WEAR     	B			R4JY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	B162				000043					SUBMITTER REPORTS AN INCREASE OF BOEING 747 PW4000 SERIES ENGINE THRUST REVERSER, LOWER TRACK BEAM EXCESS WEAR.  THE WEA	R WAS FOUND ALONG THE AUXILIARY TRACK.					2	L	7	4 	4F			RT	A20WE   					 
1997103000178	19971030	00178	NM  	1997	10	30	97ZZZX4567       	1	19971001	G	7830	315T440328	TRACK BEAM      		315T4014117A	BOEING	747   	747*        		NM  										THRUST REVERSER	EXCESS WEAR     	B			R4JY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	9VSMK				000082					INSPECTION FOUND PW4000 SERIES ENGINE THRUST REVERSER HAD LOWER TRACK BEAM EXCESS WEAR.  THE WEAR WAS FOUND ALONG AUXILI	ARY TRACK.					2	L	7	4 	4F			RT	A20WE   					 
1997103000179	19971030	00179	NM  	1997	10	30	97ZZZX4568       	1	19971001	G	7830	315T440328	TRACK BEAM      		315T4014120A	BOEING	747   	747*        		NM  										THRUST REVERSER	EXCESS WEAR     	B			R4JY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	B2464				000107					FOUND BOEING 747, PW4000 SERIES ENGINE THRUST REVERSER HAD LOWER TRACK BEAM EXCESS WEAR.  THE WEAR WAS FOUND ALONG AUXIL	IARY TRACK.					2	L	7	4 	4F			RT	A20WE   					 
1997103000180	19971030	00180	NM  	1997	10	30	97ZZZX4569       	1	19970929	G	7830	315T440327	TRACK BEAM      		315T401489A 	BOEING	747   	747*        		NM  										THRUST REVERSER	EXCESS WEAR     	B			R4JY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	9VSMA		7488 		000008					SUBMITTER REPORTS AN INCREASE OF BOEING 747 PW4000 SERIES ENGINE THRUST REVERSER WITH LOWER TRACK BEAM EXCESS WEAR.  THE	 WEAR WAS FOUND ALONG THE AUXILIARY TRACK.					2	L	7	4 	4F			RT	A20WE   					 
1997013000162	19970130	00162	GL  	1997	1	30	97ZZZX457        	3	19970106	G	6114	07015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	THREADS CRACKED 	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		4190 	557  					785253		INSPECTION FOUND RETENTION THREADS OF HUB CRACKED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997103000181	19971030	00181	NM  	1997	10	30	97ZZZX4570       	1	19971001	G	7830	315T440327	TRACK BEAM      		315T4014113A	BOEING	747   	747*        		NM  										THRUST REVERSER	EXCESS WEAR     	B			R4JY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	B2460				000048					FOUND BOEING 747, PW4000 SERIES ENGINE THRUST REVERSER WITH LOWER TRACK BEAM EXCESS WEAR.  THE WEAR WAS FOUND ALONG AUXI	LIARY TRACK.					2	L	7	4 	4F			RT	A20WE   					 
1997103000182	19971030	00182	EA  	1997	10	30	97ZZZX4571       	1	19971015	G	7830	MS32154018	CLIP            			CNDAIR	CL600 	CL6002B16   	1900305	EA  										T/R BLOCKER DOOR	MISSING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	399SW					5009				THRUST REVERSER BLOCKER DOOR CONTROL ARM PIN RETAINER CLIPS FOUND MISSING WITH ABNORMAL REGULARITY.  SUBMITTER RECOMMEND	ATION:  RE-DESIGN WITH DRILLED PIN AND INSTALL COTTER PIN VERSUS RETAINER CHIP.					2	L	7	2 	4F			RT	A21EA   					 
1997103000183	19971030	00183	NM  	1997	10	30	97ZZZX4572       	1	19970327	G	5347	BAC15201566	SEAT TRACK      			BOEING	747   	7472D7B     	1384803	NM  										BS 1810-1850	BROKEN          	B			CISY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	523MC					21782				DURING A-CHECK, FOUND SEAT TRACK BROKEN AT STA 1810 TO STA 1850 ON MAIN CARGO DECK AND FLOOR FITTING DAMAGED.  FLOOR FIT	TING REPLACED AND SEAT TRACK REPLACED PER SRM 53-10-05, FIG 33, SHEET 4.					2	L	7	4 	4F			RT	A20WE   					 
1997103000184	19971030	00184	EU  	1997	10	30	97ZZZX4573       	1	19971009	G	5345	11722201103	HINGE           		117222061   	BOLKMS	117   	BK117B2     	5626013	EU  										EQUIP DECK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	300CP	248  				7249				DURING LOWERING OF THE OPTIONAL EQUIPMENT DECK PANEL, NOTED THE LEFT HAND HINGE ASSY WAS CRACKED IN HALF.  FURTHER INSPE	CTION REVEALED RIGHT HAND HINGE CRACKED AND FAILURE WAS IMMINENT.  MATERIAL THICKNESS AND TYPE ARE NOT SUFFICIENT TO SUP	PORT PANEL WITH OPTIONAL EQUIPMENT INSTALLED.  NEW HINGES FROM MANUFACTURER WITH SAME PART NUMBER WERE LARGER AND MADE O	F DIFFERENT MATERIAL.			1	G	7	2 	3U			NC	H13EU   					 
1997103000368	19971030	00368	EA  	1997	10	30	97ZZZX4574       	2	19971001	G	8520	71640	PLUG            		75073       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					CRANKSHAFT	LOOSE           	B			EVGR	E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	33	2FOR	2538 	840  			31474	L907861A			FLIGHT OVER THE GULF OF MEXICO.  PROPELLER RPM STARTED TO DROP OFF.  PROP CONTROL WAS ADVANCED, BUT AFTER ONE HOUR, PROP	ELLER WENT TO FEATHERED POSITION.  AFTER SAFE LANDING, A VARIETY OF TESTS REVEALED THE PLUG, PN 71640, WAS LOOSE INSIDE 	THE CRANKSHAFT ALLOWING OIL TO BYPASS PROPELLER GOVERNOR.  AFTER PLUG WAS PROPERLY SEATED, TESTING REVEALED NORMAL OPERA	TION ONCE AGAIN.  NO METAL WAS FOUND IN FILTER OR SCREWS.  OTHER ENGINE WAS CHECKED AND FOUND OK.  NO RECOMMENDATION.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997103000369	19971030	00369	SO  	1997	10	30	97ZZZX4575       	1	19971012	G	3340	GE4609	LIGHT           			PIPER 	PA28  	PA28180     	7102808	SO  										LANDING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	186KG	12   				283158				LANDING LIGHT FAILED 12 FLIGHT HOURS AFTER INSTALLATION.						1	L	7	1 	3O				2A13    					 
1997103000370	19971030	00370	SO  	1997	10	30	97ZZZX4576       	1	19970710	G	7810	40B19975	PIPE            			PIPER 	PA46  	PA46350P    		SO  										EXHAUST SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	193MM	925  				4622134				DURING C/W SB 521, FOUND ENTIRE EXHAUST CROSSOVER PIPE DEFECTIVE EXCEPT PIPE P/N 40B19974.  REPLACED ALL DEFECTIVE PIPES	 WITH NEW.					1	L	7	1 	3O			RT	A25SO   					 
1997103000371	19971030	00371	SO  	1997	10	30	97ZZZX4577       	1	19970917	G	7810	40B19975	PIPE            			PIPER 	PA46  	PA46350P    		SO  										RT CROSSOVER	DETACHED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	193PM	507  				4622143				C/W SB 521, FOUND CROSSOVER PIPE ENGAGEMENT NOT SATISFACTORY PER SB.  RT CROSSOVER PIPE REPLACED WITH NEW.						1	L	7	1 	3O			RT	A25SO   					 
1997103000372	19971030	00372	SO  	1997	10	30	97ZZZX4578       	1	19970807	G	7810	40B19975	PIPE            			PIPER 	PA46  	PA46350P    		SO  										EXHAUST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	255SW	1642 	1613 			4622064				C/W SB 521, FOUND CROSSOVER ASSY PULLED PART.						1	L	7	1 	3O			RT	A25SO   					 
1997013000163	19970130	00163	GL  	1997	1	30	97ZZZX458        	3	19970106	G	6114	D7015C87	HUB             			CESSNA	310   	310R        	2074245	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROP	THREADS CRACKED 	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		4190 	555  					785021		INSP FOUND RETENTION THREADS OF HUB CRACKED.						1	L	7	2 	3O				3A10    		5	C	P22EA	 
1997103000374	19971030	00374	CE  	1997	10	30	97ZZZX4580       	1	19971008	G	2910		MANIFOLD ASSY   			CESSNA	414   	414A        	2075907	CE  										HYDRAULIC SYSTEM	DEFECTIVE       	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	13	6604C	5060 				414A0030				PILOT REPORTED THE 'HYDRAULIC PRESSURE' LIGHT WOULD NOT EXTINGUISH WHEN THE LANDING GEAR WAS RETRACTED.  RED TRANSIT LIG	HT EXTINGUISHED.  GEAR CYCLED 5 TIMES IN THE AIR WITH NO CHANGE.  AIRCRAFT RETURNED TO STATION.  AIRCRAFT PLACED ON JACK	S.  GEAR CYCLED 5 TIMES.  COULD NOT DUPLICATE DISCREPANCY.  HYDRAULIC PRESSURE SWITCH, P/N 9910287-10, REPLACED.  GEAR C	YCLED 12 TIMES, NO DISCREPANCIES.  AIRCRAFT TEST FLOWN.  'HYDRAULIC PRESSURE' LIGHT WOULD NOT EXTINGUISH.  AIRCRAFT RETU	RNED TO STATION.  HYDRAULIC MANIFOLD ASSEMBLY REPLACED.  GEAR CYCLED 6 TIMES.  AIRCRAFT TEST FLOWN AND RELEASED FOR FLIG	HT.  SUSPECT MANIFOLD ASSEMBLY, P/N 9910188-1, LEAKING INTERNALLY.	1	L	7	2 	3O				A7CE    					 
1997103000375	19971030	00375	SW  	1997	10	30	97ZZZX4581       	1	19971007	G	2810		INSPECTION COVER			MOONEY	M20   	M20C        	5870208	SW  										FUEL TANK	WRONG SEALER    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	6021Q					3232				ALL THE FUEL TANK COVERS HAD THE WRONG TYPE FUEL TANK ACCESS COVER SEALANT.  SEALANT WAS RED IN COLOR.  SUBMITTER RECOMM	ENDS INSPECTING THE FUEL SYSTEM.  USE A HIGH-OCTANE FUEL RESISTANT SEALANT AS USED IN AD 89-18-08 GULFSTREAM.					1	L	7	1 	3O				2A3     					 
1997103000376	19971030	00376	CE  	1997	10	30	97ZZZX4582       	1	19971007	G	3240	8302781	TORQUE PLATE    		C1630320207 	CESSNA	206   	U206G       	2073356	CE  										BRAKE ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	756HK	4714 				U20604102				DURING A PRE-FLIGHT INSPECTION, NOTED RUB MARKS ON INSIDE OF BRAKE DISC.  FURTHER INVESTIGATION FOUND THE TORQUE PLATE C	RACKED AT THE BUSHING FOR THE SLIDE PINS OF THE CALIPER.  SUBMITTER STATED THIS IS THE SECOND CRACKED TORQUE PLATE ON LT	 SIDE OF A 206 SUBMITTER HAS FOUND.				1	H	7	1 	3O				A4CE    					 
1997103000377	19971030	00377		1997	10	30	97ZZZX4583       	4	19971005	G	2562	DMELT81	ELT             	DORNEMARGLN 		CESSNA	172   	172P        	2072436	CE  										G SWITCH	FAILED TEST     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	9935L	1300 			9485	17276651				ELT FAILED G-FORCE TEST REQUIRED BY FAR 91.207D.  ONLY VERY HARD BLOWS WITH A HAMMER WOULD ACTIVATE G-SWITCH.  MANUAL OP	ERATION OF THE ELT WAS NORMAL AND NO CORROSION WAS FOUND.					1	H	7	1 	3O			NT	3A12    					 
1997103000378	19971030	00378	SO  	1997	10	30	97ZZZX4584       	2	19970901	G	8530		CYLINDER        			CESSNA	188   	A188A       	2073008	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 2 CYL EX PORT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9958G		500  			18800758	15988071D			DURING 100-HOUR INSPECTION, EXHAUST STACK WAS REMOVED.  CRACK APPROXIMATELY 1 INCH LONG WAS FOUND IN EXHAUST PORT OF NR 	2 CYLINDER IN THE INBOARD WALL.  THE CYLINDERS ARE CONTINENTAL CYLINDERS THAT WERE OVERHAULED 500 HOURS AGO.					1	L	7	1 	3O	3	O		A9CE    	E5CE				 
1997103000380	19971030	00380	EU  	1997	10	30	97ZZZX4586       	1	19971013	G	5320	117223251	BRACKET ASSY    			BOLKMS	117   	BK117B2     	5626013	EU  										BS 4963	CRACKED         	B	S	A	BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	955ME					7243				INSTALLED ELECTRONIC OVERSPEED BRACKET FOR NR 2 ENGINE SLIGHTLY FORWARD OF STA 4963 AT AIRCRAFT TT 2.2 HOURS.  AT AIRCRA	FT TT 1,848.3 HOURS DURING A 600-HOUR INSPECTION, CRACKS FOUND ON STRINGERS AT BL 215R AND BL 34R AS WELL AS BRACKET ASS	Y, P/N 117-223251.				1	G	7	2 	3U			NC	H13EU   					 
1997103000381	19971030	00381	EU  	1997	10	30	97ZZZX4587       	1	19971013	G	5313		STRINGER        			BOLKMS	117   	BK117B2     	5626013	EU  										BL 34R	CRACKED         	B			BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	955ME					7243				INSTALLED ELECTRIC OVERSPEED BRACKET FOR NR 2 ENGINE SLIGHTLY FORWARD OF STA 4963 AT AIRCRAFT TT 2.2 HOURS.  AT AIRCRAFT	 TT 1,848.3 HOURS DURING A 600-HOUR INSPECTION, CRACKS FOUND ON STRINGERS AT BL 215R AND BL 34R AS WELL AS BRACKET ASSY,	 P/N 117-223251.				1	G	7	2 	3U			NC	H13EU   					 
1997103000382	19971030	00382	EU  	1997	10	30	97ZZZX4588       	1	19971013	G	5313		STRINGER        			BOLKMS	117   	BK117B2     	5626013	EU  										BL 215R	CRACKED         	B			BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	955ME					7243				INSTALLED ELECTRIC OVERSPEED BRACKET FOR NR 2 ENGINE SLIGHTLY FORWARD OF STA 4963 AT AIRCRAFT TT 2.2 HOURS.  AT AIRCRAFT	 TT 1,848.3 HOURS DURING A 600-HOUR INSPECTION, CRACKS FOUND ON STRINGERS AT BL 215R AND BL 34R AS WELL AS BRACKET ASSY,	 P/N 117-223251.				1	G	7	2 	3U			NC	H13EU   					 
1997103000386	19971030	00386	SO  	1997	10	30	97ZZZX4589       	1	19971020	G	7810	40J21019	HEAT SHIELD     			PIPER 	PA46  	PA46350P    		SO  										LT EXHAUST PIPE	CHAFES PIPE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	396PM	304  				4636024				HEAT SHIELD COMES LOOSE AND CHAFES ON THE CROSSOVER SECTION OF THE EXHAUST SYSTEM CAUSING A HOLE IN THE LEFT PIPE.						1	L	7	1 	3O			RT	A25SO   					 
1997103000387	19971030	00387	NM  	1997	10	30	97ZZZX4590       	1	19970618	G	5311		FRAME           			BOEING	747   	747245F     	1384897	NM  										LT/RT NLG WELL	CRACKED         	B			CISY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	636FE					21764				INSPECTION OF THE NOSE WHEELWELL STRUCTURE PER AD 96-26-04 REVEALED CRACKING IN THE STA 300 AND STA 320 FRAME (LT AND RT	).  REPAIR ACCOMPLISHED IAW E.O. NR 4753AD36 AND 4753A039 SUPPLIED BY ATLASAIR.					2	L	7	4 	4F				A20WE   					 
1997103000388	19971030	00388	EU  	1997	10	30	97ZZZX4591       	1	19971006	G	5210		DOOR            			AEROSP	SA365 	SA365N1     	8680668	EU  										LT FWD PAX DOOR	DEPARTED        	B			KO1R	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			EA	25	111EP	2734 				6309				THE AIRCRAFT RETURNED WITHIN A FEW MINUTES OF ITS DEPARTURE, THE LEFT FORWARD PASSENGER DOOR HAD DEPARTED THE AIRCRAFT, 	IN-FLIGHT.  INSPECTION REVEALED NO DEFECTS IN THE JETTISON SYSTEM.  THE JETTISON LEVER WAS IN THE JETTISON POSITION WITH	 THE SAFETY WIRE BROKEN UPON THE AIRCRAFT RETURN.  INSPECTION REVEALED A BROKEN UPPER LATCH AND BROKEN CENTER STRIKER FI	TTING SUPPORT WHICH APPEARS TO BE THE RESULTING DAMAGE FROM THE DOOR DEPARTING THE AIRCRAFT.  THE AIRCRAFT SUSTAINED NO 	FURTHER DAMAGE.  THE DOOR WAS RECOVERED.		1	G	7	2 	3U				H10EU   					 
1997103000393	19971030	00393	EU  	1997	10	30	97ZZZX4596       	1	19971001	G	5320	117223251	BRACKET ASSY    			BOLKMS	117   	BK117B1     	5626012	EU  										BS 4963	CRACKED         	B	S	A	BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	5405G					7179				INSTALLED ELECTRONIC OVERSPEED BRACKET FOR NR 2 ENGINE SLIGHTLY FORWARD OF STA 4963 AT AIRCRAFT TT, 4,853.7 HOURS AT AIR	CRAFT TT, 5,399.3 HOURS DURING A 600-HOUR INSPECTION.  CRACKS WERE FOUND ON STRINGERS AT BL 215R AND BL 34R AS WELL AS B	RACKET ASSY.				1	G	7	2 	3U				H13EU   					 
1997103000394	19971030	00394	EU  	1997	10	30	97ZZZX4597       	1	19971001	G	5313		STRINGER        			BOLKMS	117   	BK117B1     	5626012	EU  										BL 34R	CRACKED         	B			BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	5405G					7179				INSTALLED ELECTRONIC OVERSPEED BRACKET FOR NR 2 ENGINE SLIGHTLY FORWARD OF STA 4963 AT AIRCRAFT TT, 4,853.7 HOURS AT AIR	CRAFT TT, 5,399.3 HOURS DURING A 600-HOUR INSPECTION.  CRACKS WERE FOUND ON STRINGERS AT BL 215R AND BL 34R AS WELL AS B	RACKET ASSY.				1	G	7	2 	3U				H13EU   					 
1997103000395	19971030	00395	EU  	1997	10	30	97ZZZX4598       	1	19971001	G	5313		STRINGER        			BOLKMS	117   	BK117B1     	5626012	EU  										BL 215R	CRACKED         	B	S	A	BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	5405G					7179				INSTALLED ELECTRONIC OVERSPEED BRACKET FOR NR 2 ENGINE SLIGHTLY FORWARD OF STA 4963 AT AIRCRAFT TT, 4,853.7 HOURS AT AIR	CRAFT TT, 5,399.3 HOURS DURING A 600-HOUR INSPECTION.  CRACKS WERE FOUND ON STRINGERS AT BL 215R AND BL 34R AS WELL AS B	RACKET ASSY.				1	G	7	2 	3U				H13EU   					 
1997103000490	19971030	00490	CE  	1997	10	30	97ZZZX4599       	1	19971015	G	3222	55423087	BEARING         		55420009    	CESSNA	500   	550         	2076604	CE  										NLG STRUT	NUT LOOSE       	B		A	KJ4R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SO	15	47SW					5500444				NLG WOULD CYCLE IN THE NOSE WHEELWELL.  HYDRAULIC PRESSURE 'ON' LIGHT WOULD ILLUMINATE EVERY TIME THE GEAR CYCLED.  FOUN	D THE NOSE STRUT BEARING HAD LOOSENED AND BACKED OFF.  THIS ALLOWED THE STRUT TO EXTEND BEYOND LIMITS.  WITH THE STRUT E	XTENDED BEYOND LIMITS, THE GEAR UPLOCK HOOK WOULD NOT ENGAGE IN UPLOCK AND THE GEAR WOULD START TO DROP OUT OF THE WHEEL	WELL. THIS WOULD TURN ON THE HYD DRIVE AND THE GEAR BACK UP INTO THE WHEELWELL.			1	L	7	2 	4F				A22CE   					 
1997013000165	19970130	00165	CE  	1997	1	30	97ZZZX460        	1	19970108	G	2612		FIRE WARN       			BEECH 	200   	200BEECH    	1152920	CE  										RT ENG	MALFUNCTION     	B			BUER	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			GL	23	120RJ					BB423				PILOT REPORTED RIGHT ENGINE FIRE LIGHT ANNUNCIATOR CAME ON IN-FLIGHT.  AIRCRAFT LANDED IN NASHVILLE, TN.  A MECHANIC INS	PECTED RIGHT ENGINE AND FOUND NO EVIDENCE OF FIRE OR HEAT DAMAGE.  ALSO FUNCTIONALLY TESTED FIRE DETECTION SENSORS AND F	OUND OPERATION NORMAL.  (NOTE:  FIRE LIGHT WAS NOT ON WHEN MECHANIC ARRIVED AT AIRCRAFT).  UPON RETURN TO HOME BASE (PTK	), PILOT REPORTED NO FURTHER PROBLEMS.  APPARENTLY A FALSE INDICATION.  VIB33668K/A.D.I. W.O.			1	L	7	2 	4T				A24CE   					 
1997103000492	19971030	00492	SW  	1997	10	30	97ZZZX4601       	1	19971015	G	2710		INDICATOR       			SWRNGN	SA227 	SA227AT     	8780610	SW  										AILERON TRIM	GEAR STRIPPED   	B			W6NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	665A	3186 				AT427				UPON CHECKING AILERON TRIM FOR PROPER RIGGING, THE INDICATOR WAS NOT MOVING AS AILERON TRIM WHEEL WAS TURNED.  FURTHER I	NVESTIGATION FOUND THE GEAR ASSY FOR THE INDICATOR HAD MOST OF THE TEETH STRIPPED OFF.  THE AILERON TRIM TABS WERE MOVIN	G OK.  THE GEAR WAS REPLACED AND TRIM SYSTEM WORKED NORMALLY.				2	L	7	2 	4T			RT	A5SW    					 
1997103000493	19971030	00493	EU  	1997	10	30	97ZZZX4602       	1	19971016	G	3610	AC08991	FILTER PLATE    	DUNLOP      	ACM28786    	FOKKER	F27   	F27MK400    	4990626	EU  										PNEU SYS	DEFORMED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2MIL	7185 				10668				DUNLOP MANUAL DM 1184, REV 90, PART 3, CHAP 5, PAGE 5, DURING C-CHECK INSPECTION FOUND UPON DISASSEMBLY OF THE FILTER AS	SY, ACM 28786, THE ELEMENT WAS PROTRUDING THROUGH THE UPPER PERFORATED PLATE (OR SCREEN), AC08991.  THE PLATE WAS ALSO D	EFORMED IN A CONE SHAPE MATCHING THE CONCAVE SHAPE OF THE COVER ACO 43370.  THE PLATE HAS A SERIES OF DRILLED HOLES WHIC	H INSCRIBE A SQUARE PATTERN APPROXIMATELY .25 INCH IN SIZE AT THE VERY CENTER.  THREE OF THE FOUR LEGS FORMED BY THIS HO	LE PATTERN WERE BROKEN.  THE CENTER PORTION OF THE PLATE WAS BENT UPWARDS INTO THE FILTER ASSEMBLY'S OUTLET PORT.		2	H	7	2 	4T				A817    					 
1997103000494	19971030	00494	EU  	1997	10	30	97ZZZX4603       	1	19971007	G	3250	893954	STEERING UNIT   		893442      	FOKKER	F27   	F27MK400    	4990626	EU  										NLG	BINDING         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2MIL				447	10652				INSPECTION FOR MALFUNCTION OF SLUGGISH NLG STEERING FOUND AIR MOTOR BINDING DUE TO SPLINE SHAFT CONTACTING 2ND STAGE RED	UCTION GEAR INPUT GEAR.  ADDED SHIMS TO PREVENT CONTACT AND STOP BINDING.					2	H	7	2 	4T				A817    					 
1997103000495	19971030	00495	EU  	1997	10	30	97ZZZX4604       	1	19971010	G	5751	3701014031	WEIGHT          			FOKKER	F27   	F27MK400    	4990626	EU  										LT AILERON	WRONG PART      	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2MIL	6753 				10652				FOKKER F27 SM, CHAPTER 51-50-00, 'CONTROL SURFACE BALANCING'.  LT AILERON REMOVED FOR BALANCE CHECK AFTER REPLACEMENT OF	 THE LT BALANCE TAB.  BALANCE TAB REPLACED DUE TO COLLISION WITH CESSNA 340 WHILE PARKED AT ALLEGHENY COUNTY AIRPORT, PI	TTSBURGH, PA.  THE BALANCE CHECK REVEALED ADDITIONAL WEIGHT REQUIRED TO BE PLACED BENEATH THE FRONT NOSE COVER.  UPON RE	MOVAL OF THE FRONT NOSE COVER, FOUND 4 UNAPPROVED BALANCE WEIGHTS MADE FROM LEAD SHEETING SANDWICHED BETWEEN THE ADJUSTM	ENT WEIGHTS.  THESE UNAPPROVED WEIGHTS WERE NOT PLACED IN THE SEQUENCE ILLUSTRATED IN FIGURE TWO, 'SEQUENCE OF WEIGHT DI	STRIBUTION'.  THE LEAD WEIGHTS WERE REMOVED AND REPLACED WITH GENUINE FOKKER BALANCE WEIGHTS.	2	H	7	2 	4T				A817    					 
1997013000166	19970130	00166	CE  	1997	1	30	97ZZZX461        	1	19970102	G	2133	EVA66	EVA TUBING      			BEECH 	100   	B100        	1152919	CE  										AFT CABIN VENT	MELTED          	B		A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	531CB	2802 				BE133				INVESTIGATION FOR MELTED AND COLLAPSED EVA OUTFLOW VALVE TUBING FOUND CABIN AFT VENT WAS BLOCKED WITH BAGGAGE AND AIR VE	NT WAS DETACHED.  APPARENTLY CABIN AIR (HEAT) WAS SUFFICIENT ENOUGH TO MELT/COLLAPSE TUBING.  THE ONLY DAMAGED TUBING WA	S AT THE AREA OF THE AFT VENT.				1	L	7	2 	4T				A14CE   					 
1997110600157	19971106	00157	SO  	1997	11	6	97ZZZX4617       	1	19970730	G	3230		BOLT            			PIPER 	PA34  	PA34200     	7103405	SO  										NLG DRAG LINK	FAILED          	H	L	A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EU	01	2FOR	1350 				347570244				INVESTIGATION FOR NLG COLLAPSE ON LANDING FOUND BOLT CONNECTING DRAG LINK TO GEAR STRUT BROKEN.  BOLT HAD A FATIGUE CRAC	K WHICH WORKED THROUGH BOLT DUE TO CYCLIC LOADING UNTIL BOLT FAILED DURING GEAR EXTENSION.					1	L	7	2 	3O				A7SO    					 
1997110600158	19971106	00158	SO  	1997	11	6	97ZZZX4618       	1	19971018	G	2820	AN8406D	HOSE FITTING    			PIPER 	PA20  	PA20        	7102002	SO  										RT FUEL TANK	PLUGGED         	G	S	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			NM	09	150KS					20678				THIS AIRCRAFT WAS INVOLVED IN AN ACCIDENT.  ON CLIMB-OUT, AIRCRAFT LOST POWER.  LANDED ON LAST 100 FEET OF RUNWAY.  AIRC	RAFT NOSE-OVER, AND CAME TO A STOP INVERTED.  AFTER REPAIR, NEW OWNER WAS INSPECTING FUEL SYSTEM AND FOUND RT FUEL TANK 	AFT OUTLET FITTING COMPLETELY PLUGGED WITH WHAT APPEARS TO BE DIRT.				1	H	7	1 	3O				1A4     					 
1997110600159	19971106	00159	CE  	1997	11	6	97ZZZX4619       	1	19971009	G	7120	121343316	MOUNT           			CESSNA	206   	U206F       	2073333	CE  										RT AFT SUPPORT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	1523U	6804 				U20602234				WHILE INSPECTING BEFORE RE-INSTALLING ENGINE, FOUND RT REAR ENGINE MOUNT SUPPORT HAD A 1 INCH CRACK.  A REPLACEMENT PART	 WAS INSTALLED.  AGE WAS PROBABLY THE CAUSE.					1	H	7	1 	3O				A4CE    					 
1997110600160	19971106	00160	CE  	1997	11	6	97ZZZX4620       	1	19971009	G	5753	12201041	RIB             		122010024   	CESSNA	206   	U206F       	2073333	CE  										RT FLAP	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	1533U	6804 				U20602234				DURING A 100-HOUR INSPECTION, NOTED BLACK STAINS AROUND THE BRACKET WHICH ATTACHES THE OUTBOARD PUSH ROD TO THE RIGHT FL	AP.  FURTHER INVESTIGATION REVEALED A CRACK IN THE NOSE RIB AT STA 112.50.  A NEW PART WAS INSTALLED.  SUBMITTER SUGGEST	S AGE AND MUCH USE WERE REASONS FOR FAILURE.				1	H	7	1 	3O				A4CE    					 
1997110600161	19971106	00161	SO  	1997	11	6	97ZZZX4621       	1	19971010	G	2913	1213HGB310	PUMP            			PIPER 	PA31T 	PA31T       	7103124	SO  										LT ENG HYD	LEAKED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NE	05	29CA	3636 			OA81422	31T780076				PILOT REPORTED THE LANDING GEAR HAD A PROBLEM DURING EXTENSION COMPLETING ITS CYCLE.  AFTER SEVERAL TRIES, THE CYCLE COM	PLETED AND A SAFE LANDING MADE.  WHILE TROUBLESHOOTING, NOTED HYDRAULIC FLUID LEAKING FROM THE DRAIN IN THE BASE OF THE 	HYD PUMP ON LT ENG AND SPREAD OVER THE UNDERSIDE OF THE WING.  AN OVERHAULED PUMP WAS INSTALLED.  A NEW FILTER ON THE LT	 WAS INSTALLED AND THE RESERVOIR WAS FILLED.  THE GEAR WAS CYCLED 3 TIMES ON JACKS WITH NO FAULTS.  SUBSEQUENT TEST FLIG	HT NOTED NO FAULTS THROUGH SEVERAL CYCLES.		1	L	7	2 	3T				A8EA    					 
1997110600162	19971106	00162	CE  	1997	11	6	97ZZZX4622       	1	19970901	G	2720		PULLEY          			BEECH 	33    	F33A        	1151425	CE  										RUDDER CABLE	MISSING         	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	6054D					CE856				DURING A GEAR UP LANDING REPAIR, NOTICED A RUDDER CABLE PULLEY MISSING AND HAD NEVER BEEN INSTALLED AT BEECH.  CABLE DEF	ECTION DUE TO THE MISSING PULLEY WORE THE PAINT OFF STRUCTURE.  A NEW PULLEY INSTALLED, RUDDER RE-RIGGED.					1	L	7	1 	3O				3A15    					 
1997110600163	19971106	00163	CE  	1997	11	6	97ZZZX4623       	1	19970903	G	3230	MS28775112	O-RING          			CESSNA	210   	T210N       	2073456	CE  										NLG ACTUATOR	FAILED          	D	S			O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			WP	07	6355C	2000 				21063874				NLG ACTUATOR FWD O-RING BECAME HARD, BRITTLE, WAS CUT IN 2 SPOTS .25 INCH APART, THEN ROLLED.  WHEN GEAR EXTENDED FOR LA	NDING, HYD PUMP FORCED ALL THE HYD FLUID OVERBOARD THROUGH THE CUT O-RING.  ELECTRIC HYD PUMP CONTINUED TO RUN UNTIL THE	 MAIN GEAR CIRCUIT BREAKER OPENED.  AUX HYDRAULIC HAND PUMP WAS USED TO GET THIS GEAR DOWN, ALL THE HYD FLUID WAS PUMPED	 OVERBOARD.  THE NLG WENT TO THE DOWN AND LOCKED POSITION, BUT THE MLG WENT TO THE TRAIL POSITION.  NLG HELD ENG AND PRO	P UP, BUT WEIGHT OF ACFT CAUSED MLG TO COLLAPSE.  SUBSTANTIAL DAMAGE TO BELLY AND TAIL.  NO INJURIES.		1	H	7	1 	3O				3A21    					 
1997110600164	19971106	00164	CE  	1997	11	6	97ZZZX4624       	1	19971022	G	3244	650C861	TIRE            			CESSNA	421   	421C        	2076016	CE  										TREAD AREA	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	68670	390  			22531060	421C1084				THIS TUBE-TYPE MAIN LANDING GEAR TIRE WAS INSTALLED AND OPERATED FOR 390 FLIGHT HOURS.  ESTIMATE 290 LANDINGS.  THE TIRE	 WAS FOUND TO HAVE BULGES ON THE EDGE OF THE TREAD AREA.  THESE BULGES FEEL LIKE AIR POCKETS BETWEEN THE TREAD AND THE C	ORD.  THE TIRE WAS DEFLATED AND REMOVED FOR INSPECTION AND VERIFIED TO HAVE SEPARATION OF THE TREAD APPROXIMATELY 1 INCH	 WIDE BY 10 INCHES LONG.  THE TIRE WAS REPLACED WITH A NEW UNIT.			1	L	7	2 	3O				A7CE    					 
1997110600165	19971106	00165	SO  	1997	11	6	97ZZZX4625       	2	19971002	G	8520		CRANKCASE       			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					NR 2 CYL BASE	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7342K	3392 	1911 			R1722060	355058			LT CRANKCASE BROKE OFF AT THE TOP SIDE AT THE PERIMETER OF NR 2 CYLINDER BASE.  SUSPECT CAUSE, FAILURE OF FWD THROUGH-BO	LT NUT OR THREADS OR POSSIBLE INTERNAL FLAW IN CRANKCASE HALF.					1	H	7	1 	3O	3	O		3A17    	E1CE				 
1997110600166	19971106	00166	CE  	1997	11	6	97ZZZX4626       	1	19971009	G	7810		EXHAUST ELBOW   			CESSNA	414   	414A        	2075907	CE  										EXHAUST WYE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	78NG					414A0617				DURING MAINTENANCE CHECK, EXHAUST STAIN NOTED ALONG A WELD ON THE ELBOW FROM THE EXH WYE TO THE EXH WASTEGATE.  CLOSER E	XAMINATION SHOWED THE ELBOW CRACKED ALONG EDGE OF THE WELD ON BOTH SIDES.  ON THIS PARTICULAR PART, WHICH IS IDENTIFIED 	AS A PMA REPLACEMENT PART, THE ELBOW IS MADE IN TWO PIECES FITTED TOGETHER AT AN APPROXIMATE 45 DEGREE INTERSECTION TO M	AKE THE NECESSARY 90 DEGREE INSTALLATION REQUIREMENT.  ORIGINAL EQUIPMENT ELBOWS AS NOTED ON OTHER ACFT (CESSNA 340A/414	 AND OTHER 414A'S) DO NOT HAVE SUCH A SPLICE WELD AS THIS ONE DOES AND CRACKS IN THIS PARTICULAR AREA HAVE NOT BEEN OBSE	RVED IN THOSE PARTS.	1	L	7	2 	3O				A7CE    					 
1997110600167	19971106	00167	EA  	1997	11	6	97ZZZX4627       	2	19971018	G	7414	M3048	SHAFT           	SLICK       	4370        	CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	O360A1A     	41514	EA  					MAG ROTOR	WORN            	D	S			O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	99	1011L	184  			94110078	254				PILOT REPORTED ENGINE RUNNING ROUGH.  PERFORMED TROUBLESHOOTING, FOUND RT MAGNETO ROTOR SHAFT AND ROTOR GEAR WORN BEYOND	 LIMITS.  GEAR WAS FOUND LOOSE ON SHAFT.  THIS IS THE SECOND SUCH 4300 SERIES TYPE MAGNETO WITH APPROXIMATELY 500 HOURS 	TT WITH THE SAME PROBLEM.				1	H	7	1 	3O	3	O		1A13    	E286				 
1997110600168	19971106	00168	EA  	1997	11	6	97ZZZX4628       	2	19971018	G	7414	M3827	GEAR            	SLICK       	4370        	CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	O360A1A     	41514	EA  					MAG ROTOR	WORN            	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	99	1011L	184  			9410078	254				PILOT REPORTED ENGINE RUNNING ROUGH.  PERFORMED TROUBLESHOOTING, FOUND RT MAGNETO ROTOR SHAFT AND ROTOR GEAR WORN BEYOND	 LIMITS.  GEAR WAS FOUND LOOSE ON SHAFT.  THIS IS THE SECOND SUCH 4300 SERIES TYPE MAGNETO WITH APPROXIMATELY 500 HOURS 	TT WITH THE SAME PROBLEM.				1	H	7	1 	3O	3	O		1A13    	E286				 
1997110600169	19971106	00169	CE  	1997	11	6	97ZZZX4629       	1	19970920	G	3222	16981001215513	COMPRESSION ASSY			BEECH 	23    	C23         	1151242	CE  										NLG STRUT	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	17	180ED	3575 				M1622				COMPRESSION ASSEMBLY CRACKED ALLOWING PIN TO COME OUT.  ON LANDING, NOSE FORKS SEPARATED FROM COMPRESSION ASSY.  THIS AL	LOWED NOSE FORKS TO COLLAPSE ALLOWING PROPELLER TO STRIKE THE RUNWAY CAUSING SUDDEN STOPPAGE OF THE ENGINE.					1	L	7	1 	3O				A1CE    					 
1997110600170	19971106	00170	SO  	1997	11	6	97ZZZX4630       	1	19971004	G	3030		CONNECTOR       			PIPER 	PA42  	PA42        	7104202	SO  										PITOT HEAT SW	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	28DA	3574 				428001078				CONNECTOR E324 WAS FOUND SEVERELY OVERHEATED IN SWITCH PANEL OVERHEAD.  CONTROLS PITOT STALL/HEAT.  SUSPECT UNDERRATED C	ONNECTOR FOR AMPERAGE.					1	L	7	2 	4T				A23SO   					 
1997110600171	19971106	00171	SO  	1997	11	6	97ZZZX4631       	1	19971002	G	5730	6206102	SKIN            			PIPER 	PA28  	PA28R200    	7102811	SO  										RT INBD WING	CRACKED         	B			FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4516X	3485 				28R7635068				DURING 100-HOUR INSPECTION, THE FORWARD WING WALK AREA WAS FOUND CRACKED.  THE AREA IS DIFFICULT TO INSPECT AND MUST BE 	VIEWED THROUGH THE LANDING GEAR WELL.  THE SKIN IS DOUBLED WITH A CORRUGATED PIECE AND THE CRACKS WERE LOCATED AT EACH R	ADIUS OF THE CORRUGATIONS.  SKIN ASSEMBLY REPLACED.				1	L	7	1 	3O				2A13    					 
1997110600172	19971106	00172	SO  	1997	11	6	97ZZZX4632       	1	19971002	G	5743	NAS680A4	NUTPLATE        			PIPER 	PA28  	PA28R200    	7102811	SO  										MLG FWD TRUNNION	CRACKED         	B		A	FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4516X	3485 				28R7635038				RIGHT FUEL TANK REMOVED TO FACILITATE OTHER MAINTENANCE.  INBOARD LOWER NUTPLATE ON THE FORWARD GEAR TRUNNION WAS FOUND 	CRACKED.  PART TT 3,484.7 HOURS.  GEAR WAS REMOVED, NUTPLATE REPLACED.					1	L	7	1 	3O				2A13    					 
1997110600173	19971106	00173	SO  	1997	11	6	97ZZZX4633       	2	19970901	G	8520	20428	BEARING         			BOEING	75    	E75         	1380120	CE  	CONT  	R670  	W6706N      	17016	SO  					REAR MAIN	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	25	5010V					755351	26870			THIS ENGINE HAD 385 HOURS SINCE OVERHAUL.  THE PILOT NOTED A DROP IN OIL PRESSURE HEADED FOR THE NEAREST AIRPORT 8 MILES	 AWAY.  BEFORE REACHING THE AIRPORT, ELECTED TO MAKE AN EMERGENCY LANDING ON A ROAD.  AFTER CHECKING THE SUMP SCREEN, A 	LARGE QUANTITY OF METAL WAS FOUND.  TEAR DOWN REVEALED THE REAR MAIN BEARING HAD FAILED.				1	Q	7	1 	3R	3	R		A743    	E162				 
1997110600175	19971106	00175	GL  	1997	11	6	97ZZZX4635       	3	19971016	G	6114	D4521	SPACER          			CESSNA	172   	172         	2072402	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	53945	3096 				17274832		83454		SPACER ON PROPELLER FOUND CRACKED THROUGH N.D.T. INSPECTION.  FOUND AT 100-HOUR INSPECTION, A PROPELLER RE-PROFILING.						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997110600176	19971106	00176	SO  	1997	11	6	97ZZZX4636       	2	19971020	G	8530	635448CN	CYLINDER        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					NR 6	CRACKED         	B			FSER	E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			NE	05	567JS		427  			402B1090	510032E			DURING FLIGHT FROM EWR TO PWM, THE PILOT EXPERIENCED THE LEFT ENGINE FAILURE.  ENGINE WAS SHUT DOWN.  FOUND NR 6 CYLINDE	R CRACKED AT CYLINDER BASE CAUSING COMPLETE FAILURE.  ENGINE COMPLETELY DISASSEMBLED AND INSPECTED.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997110600177	19971106	00177	SO  	1997	11	6	97ZZZX4637       	2	19971007	G	7414	101630601	MAGNETO         	BENDIX      	S6RN205     	CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470V      	17026	SO  					ENGINE	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	6961L				A33006	310K0061				DURING ANNUAL INSPECTION, NO RECORDS EXIST OF ANY MAGNETO MAINTENANCE.  ALL 4 MAGS REMOVED FOR TCM 500-HOUR CHECK. THIS 	MAG HAD POINTS IN CONFIGURATION OF COUNTERCLOCKWISE ROTATION, SHOULD HAVE BEEN FOR CW BY P/N AND IPB.  TWO MAGS HAD LOOS	E BEARINGS, ALL 4 HAD WORN DISTRIBUTOR BLOCKS.   THREE SETS HAD BURNED POINTS, BAD CONDENSER, 2 COILS WITH CRACKS.  BOTH	 ENGINES WERE 'MAJOR OVERHAULED' 162.1 HRS AND 369.4 HRS, ENGINE ONLY.  NEITHER HAD ACCESSORIES, FUEL SYSTEM, ETC., OVER	HAULED WITH THE 'MAJORS'.		1	L	7	2 	3O	3	O		3A10    	3E1				 
1997110600178	19971106	00178	CE  	1997	11	6	97ZZZX4638       	1	19971016	G	8120	4066109029	TURBOCHARGER    			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					ENGINE	SEAL LEAK       	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	7250Z				NE0111	EA449	527070			FOUND OIL LEAKING FROM TURBOCHARGER ON COMPRESSOR SIDE AND EXHAUST SIDE OF TURBOCHARGER.  SENT IN FOR OVERHAUL AND FOUND	 EXHAUST TURBINE WHEEL OUT OF BALANCE WHICH WORE OUT THE OIL SEALS ON THE HOT AND COLD SIDE OF TURBO.  ESTIMATED TIME ON	 PART, 1,000 HOURS.				1	L	7	1 	3O	3	O		3A15    	E8CE				 
1997110600179	19971106	00179	CE  	1997	11	6	97ZZZX4639       	1	19971017	G	2436	VR600	REGULATOR       			CESSNA	150   	150M        	2071830	CE  										DC SYSTEM	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			NE	03	8193U					15077908				AIRCRAFT ELECTRICAL SYSTEM EXPERIENCED ON ABRUPT MALFUNCTION, NO CHARGING CONDITION.  FOUND VOLTAGE REGULATOR FAILED.						1	H	7	1 	3O				3A19    					 
1997013000169	19970130	00169	CE  	1997	1	30	97ZZZX464        	1	19970106	G	8120	22501191	CONTROL ARM     			CESSNA	182   	182R        	2072731	CE  										WASTEGATE	MISDRILLED      	B	S		WS9R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07										WASTEGATE CONTROL ARM (NEW PART) WAS MIS-DRILLED.  SUBMITTER HAD TO ORDER 4 UNITS BEFORE RECEIVING A USEABLE PART.						1	L	7	1 	3O			NT	3A13    					 
1997110600180	19971106	00180	CE  	1997	11	6	97ZZZX4640       	1	19971008	G	3230	504501019	TORQUE TUBE     			CESSNA	414   	414         	2075908	CE  										LT MLG	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	854RM	2844 				4140959				CRACK FOUND AT THE FORK BOLT ATTACHMENT.  FOUND DURING ANNUAL INSPECTION.  CRACK LENGTH WAS .50 INCH.						1	L	7	2 	3O			RT	A7CE    					 
1997110600181	19971106	00181	SO  	1997	11	6	97ZZZX4641       	2	19971009	G	8530		PISTON PIN      			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  					NR 6 CYLINDER	FAILED          	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8682U	804  				17252585	28901D			OIL SCREEN FULL OF METAL AND COLLAPSED.  FOUND PIN PLUG NR 6 CYLINDER FAILED.  PIN PLUG IN NR 2 CYLINDER EXPANDED AND LO	OSENED.  SUBMITTER STATED ALUMINUM PLUGS ARE SWAGED.  MAYBE A RELIEF HOLE TO RELIEVE INTERNAL PRESSURE MIGHT BE CONSIDER	ED TO PREVENT EXCESSIVE WEAR.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1997110600182	19971106	00182		1997	11	6	97ZZZX4642       	1	19971021	G	2434	02373	ALTERNATOR      	FORD        																DC SYSTEM	FAILED          	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	17					5093285					SCREWS THAT RETAIN BEARING IN PULLEY END OF HOUSING BACKED OUT.  THIS ALLOWED ENTIRE SHAFT PULLEY AND FAN TO SHIFT BACK 	IN HOUSING UNTIL FAN BLADES CONTACTED HOUSING.  ONE BLADE SEPARATED FROM HOUSING AND MADE A HOLE IN COWLING.  AIRCRAFT L	ANDED SAFELY.  SMOH:  40 HOURS.																	 
1997110600183	19971106	00183		1997	11	6	97ZZZX4643       	2	19971013	G	7414	103910881	COIL            	BENDIX      	103493704   															ENGINE MAG	BURNT           	B			EVGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	P2SIG	15   			K189610FR					MAGNETO STOPPED OPERATION 14.5 HOURS AFTER COIL WAS REPLACED.  INSPECTION REVEALED BURNT COIL.  UNKNOWN CAUSE, NO RECOMM	ENDATIONS.																		 
1997110600184	19971106	00184		1997	11	6	97ZZZX4644       	2	19970909	G	7421	REM40E	SPARK PLUG      	CHAMPION    																ENG IGNITION	DEFECTIVE       	B	L	A	CDMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17										SUBMITTER REPORTS NEW CHAMPION SPARK PLUGS ARE BEING RECEIVED THAT ARE DEFECTIVE.  DIFFERENT P/N'S FROM SEVERAL SHIPMENT	S ARE FOUND TO BE WEAK, DISCOLORED OR WEAK WHEN TESTED.  PLUGS WERE TESTED FROM ZERO TO 125 PSI WITH PROPER GAP.  ESTIMA	TED DEFECTIVE QUANTITY AT 20-50 PERCENT.  REM 38E DATE CODE 3D97.  REM 40E DATE CODE 1H97 AND 3K96.																	 
1997110600185	19971106	00185	CE  	1997	11	6	97ZZZX4645       	1	19971015	G	2121	66001122	BLOWER MOTOR    			LEAR  	25    	25B         	5170511	CE  										CABIN	SEIZED          	B		A	TJ4R	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			GL	11	111MP				656	139				ELECTRICAL SMOKE AND FUMES NOTED AFTER TAKEOFF.  AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE NOTED THE CABIN BLOWER M	OTOR HAD SEIZED AND OVERHEATED.  NO OTHER DAMAGE NOTED.  REPLACED BLOWER MOTOR ASSY.  SYSTEMS CHECK GOOD.					2	L	7	2 	4J				A10CE   					 
1997110600186	19971106	00186	NM  	1997	11	6	97ZZZX4646       	1	19970916	G	5511		SPAR            			BOEING	727   	72723       	1384004	NM  										LT H STAB AFT	CRACKED         	B		A	LVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	1972					18428				DURING ROUTINE INSPECTION OF AIRCRAFT, TWO CRACKS WERE FOUND ON THE LT HORIZONTAL STABILIZER'S AFT SPAR LOWER CHORD.  EA	CH CRACK WAS APPROXIMATELY 1.5 INCH LONG.  ONE CRACK WAS AT STABILIZER STA 169 AND THE OTHER WAS AT STABILIZER STA 179.					2	L	7	3 	4F				A3WE    					 
1997110600187	19971106	00187	CE  	1997	11	6	97ZZZX4647       	1	19971017	G	5533	55120966	SKIN            			CESSNA	500   	500CESSNA   	2076602	CE  										VENTRAL FIN	CORRODED        	B			MUCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	12AM	6303 				5000235				PRE-UNIT, S/N 0274, AIRCRAFT UTILIZE - .020 INCH SKIN FILLED WITH FOAM FOR RIGIDITY IN THE CONSTRUCTION OF THE VENTRAL F	IN.  THE FOAM ALLOWS MOISTURE TO COLLECT AND CORROSION TO DEVELOP ON THE INSIDE SURFACES OF THE SKINS.  POST-UNIT, S/N 0	274, DELETES THE FOAM.				1	L	7	2 	4F				A22CE   					 
1997110600188	19971106	00188	CE  	1997	11	6	97ZZZX4648       	1	19971023	G	3250		STEERING MECH   			LEAR  	60    	60LEAR      	5170707	CE  										NLG	DEFECTIVE       	D		A		O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			SW	05	216FX	235  			104	103				PILOT REPORTED NOSE GEAR VIBRATION ON LANDING THAT KICKED NOSE WHEEL STEERING OFF.  REMOVED NOSE GEAR ASSEMBLY AND FOUND	 STEERING MECHANISM ASSEMBLY LOOSE ON MOUNT BOLTS.  OPENED STEERING BOX AND FOUND ALL 3 MOUNT BOLTS BACKED OFF ONE-QUART	ER TURN.  FOUND NO DAMAGE TO BOX OR NOSE GEAR.  INSTALLED 3 NEW BOLTS, P/N NAS144-13, PER LEAR 60 MM CHAPTER 32-50-02. R	EINSTALLED NOSE GEAR ASSEMBLY.  PERFORMED GEAR SWING AND TAXI TESTS.  ALL OPS CHECKS NORMAL.			2	L	7	2 	4F			RT	A10CE   					 
1997110600189	19971106	00189	WP  	1997	11	6	97ZZZX4649       	1	19971024	G	2740	36479971	ACME NUT        		2706386503  	DOUG  	DC8   	DC851       	3021920	WP  										LONGITUDE TRIM	FAILED          	B		A	DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	508DC					45935				ACME NUT THREADS STRIPPED MAKING LONGITUDINAL TRIM MECHANISM DRIVE UNIT TOTALLY INOPERABLE.  THIS NUT DRIVES THE JACKSCE	W UP OR DOWN.  THE INSIDE DIAMETER IS TOTALLY STRIPPED WHICH WILL NOT ALLOW ANY MOVEMENT OF THE JACKSCREW.  THERE ARE TW	O JACKSCREWS PER AIRCRAFT (RT AND LT).  THE OTHER UNIT REMOVED HAD EXCESSIVE BACKLASH WHICH EXCEEDS MANUFACTURER'S LIMIT	S.  BACKLASH OF SECOND UNIT .090 INCH MAXIMUM ALLOWABLE IS .045 INCH.  MAJOR FAILURE!!			2	L	7	4 	4F				4A25    					 
1997013000170	19970130	00170	SW  	1997	1	30	97ZZZX465        	1	19970110	G	7120	2762114083	MOUNT           			SWRNGN	SA227 	SA227*      		SW  										ENG TRUSS	NOT WELDED      	B		A	H7NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										AREA UNDER PLATE OR UPPER AFT MOUNT NOT WELDED.  PLATE P/N'S 27-62114-073/074 ATTACHES TO TUBES 27-62114-019 AND 27-6211	4-023.  WHILE THIS MOUNT HAD NOT CRACKED, WE INSPECT ALL MOUNTS NOW TO MAKE SURE THEY ARE WELDED.  SUBMITTER HAS SEEN CR	ACKS IN THIS AREA IN THE PAST AND HAS FILED PREVIOUS M OR D REPORTS ON THAT.				2	L	7	2 	4T			RT	A5SW    					 
1997110600190	19971106	00190	CE  	1997	11	6	97ZZZX4650       	1	19970901	G	5321	241139574	FLOORBOARD      			LEAR  	35    	35A         	5170602	CE  										BAG COMPT	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	88JA	10162				118				THE BAGGAGE COMPARTMENT FLOOR IS CONSTRUCTED OF BONDED, HONEYCOMB MATERIAL.  IT HAS TWO SECTIONS, FORWARD AND AFT, THAT 	ARE SPLICED TOGETHER.  DURING AN A2 PHASE INSPECTION, A DELAMINATION WAS DISCOVERED INVOLVING THE UPPER SKIN OF THE FORW	ARD FLOORBOARD.  IT IS SIGNIFICANT ENOUGH TO REQUIRE REPLACMENT OF THE FLOORBOARD.				2	L	7	2 	4F				A10CE   					 
1997110600192	19971106	00192	NE  	1997	11	6	97ZZZX4652       	2	19970929	G	7260	208327004	GEARBOX CASE    								LYC   	LF507 	LF5071F     		NE  					STARTER COVER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										ALL THREADED INSERTS HAVE BEEN PULLED WHERE STARTER COVER (P/N 2-083-260-XX) MOUNTS TO GEARBOX.  OUTER RACE OF BEARING R	EMAINS IN BEARING LINER.  SIGNIFICANT DAMAGE TO AREA ADJACENT TO BEARING LINER.  ALL HOLES WHERE INSERTS WERE INSTALLED 	ARE ELONGATED.  GR823, S/N M125B-039.									4	F			E6NE				 
1997110600193	19971106	00193	GL  	1997	11	6	97ZZZX4653       	2	19971013	G	7210		BEARING         			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					SPARE DRIVE	FAILED          	H				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	99	105RH					S55	CAE835553			NR 1 ENGINE CHIP LIGHT CAME ON AFTER START-UP.  MAINTENANCE FOUND PASTE ON UPPER AND LOWER CHIP PLUGS.  CLEANED PLUGS, O	IL SAMPLE WAS TAKEN; 1.2 HOURS LATER, NR 1 ENGINE CHIP LIGHT CAME ON AGAIN.  MAINTENANCE REMOVED PLUGS.  UPPER PLUG HAD 	CHIPS AND SLIVER.  LOWER PLUG HAD PASTE AND CHIPS.  ENGINE WAS REMOVED FROM SERVICE AND SENT TO ENGINE SHOP.  ENGINE SHO	P FOUND ENGINE GEARBOX SPARE DRIVE  BEARING CAGE CAME LOOSE AND WAS RATTLING AROUND IN GEARBOX.  TIME SINCE LAST INSPECT	ION, 90.1 HRS.  OIL SAMPLE FROM LAST 100-HR INSP SHOWED NO ABNORMAL METALS.		1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997110600194	19971106	00194	CE  	1997	11	6	97ZZZX4654       	1	19971008	G	2140	0800400237	FUEL LINE       			CESSNA	310   	310R        	2074245	CE  										HEATER MAIN FUEL	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4251C					310R1382				MAIN HEATER FUEL FEED LINE FOUND TO HAVE CORROSION AND CHAFING SPOTS.  RECOMMEND VISUAL INSPECTION THOROUGHLY, AND REPLA	CED IF DEFECTS ARE FOUND.					1	L	7	2 	3O				3A10    					 
1997110600195	19971106	00195	CE  	1997	11	6	97ZZZX4655       	1	19971008	G	2140	0800400239	LINE ASSY       			CESSNA	310   	310R        	2074245	CE  										PUMP TO HEATER	CORRODED        	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	15	4251C					310R1382				LINE FROM HEATER FUEL PUMP TO HEATER INLET FOUND TO HAVE CORROSION, A PIN HOLE, AND CHAFING SPOTS.						1	L	7	2 	3O				3A10    					 
1997013000217	19970130	00217	SO  	1997	1	30	97ZZZX466        	1	19970106	G	2810	P46132	FUEL CELL       			PIPER 	PA31T 	PA31T2      	7103127	SO  										LT WING	LEAKS           	G				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			EA	07					A343					PURCHASED AS A DIRECT REPLACEMENT FOR PIPER P/N 462-722.  FUEL CELL S/N A343 WAS INSTALLED AND LEAKED IMMEDIATELY AFTER 	INSTALLATION.  THREE ADDITIONAL FUEL CELLS WERE SHIPPED TO INSTALLER, TWO OF THREE WERE INSTALLED, BUT WOULD NOT FIT FOR	 VARIOUS REASONS.  THE THIRD WAS NOT INSTALLED DUE TO THE PREVIOUS INSTALLATION PROBLEMS.				1	L	7	2 	3T			RT	A8EA    					 
1997110600842	19971106	00842	GL  	1997	11	6	97ZZZX4660       	3	19971013	G	6114		HUB             													MCAULY	3AF32C	3AF32C87    	GL  	NR 2 SOCKET	CRACKED         	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23			120  		787900			782900		FOUND HUB CRACKED DURING OVERHAUL, NR 2 BLADE SOCKET.																5	C	P22EA	 
1997110600843	19971106	00843	EA  	1997	11	6	97ZZZX4661       	1	19970826	G	5415	513485	CASTING         		51859410    	LKHEED	P2V   	P2V5F       	5260110	EA  										ENGINE PYLON	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	9855F					131445				WHILE ACCOMPLISHING A FLEET-WIDE INSPECTION OF AIRCRAFT, A CASTING CRACK WAS FOUND ON A SECOND UNIT WITHIN FLEET.						4	M	7	2 	4R			RT	A17EA   					 
1997110600844	19971106	00844	SO  	1997	11	6	97ZZZX4662       	1	19970809	G	5415	513485	CASTING         		51859410    	LKHEED	P2V   	SP2HJOHNSON 	5269601	SO  										ENGINE PYLON	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	14835				X646	148358				WHILE ACCOMPLISHING PRE-FLIGHT, CREW NOTICED MORE MOVEMENT IN THE RIGHT (NR 2) JET THAN THE LEFT.   FURTHER INVESTIGATIO	N BY MAINTENANCE REVEALED A CRACK EXTENDING HORIZONTALLY THROUGH THE P/N 513485 FORWARD JET PYLON MOUNT CASTING.					2	M	7	4 	4R			J	A1RM    					 
1997110600845	19971106	00845		1997	11	6	97ZZZX4663       	2	19970918	G	7414	M3975	COIL            	SLICK       	4370        															MAGNETO	FAILED          	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		500  			053096					DURING 500-HOUR INSPECTION, FOUND COIL SECONDARY TO HAVE OPEN CIRCUIT.  SUBMITTER STATED COULD LEAD TO DEAD MAGNETO.																			 
1997110600850	19971106	00850	SO  	1997	11	6	97ZZZX4668       	1	19970516	G	2701	7927600	CONTROL WHEEL   			PIPER 	PA28  	PA28140     	7102802	SO  										PILOT SIDE	BROKE           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	15831	7452 				287325174				THE CONTROL WHEEL COMPLETELY BROKE BETWEEN THE OUTER GRIP AND THE HUB.  PILOT REPORTED THE BROKEN PART TO THE FLIGHT SCH	OOL AFTER FLYING AT THE AIRFIELD ON A DAY WITH HIGH CROSS-WINDS.  THE BROKEN CONTROL WHEEL WAS REPLACED WITH A SERVICEAB	LE PART.				1	L	7	1 	3O				2A13    					 
1997110600851	19971106	00851	SO  	1997	11	6	97ZZZX4669       	2	19971023	G	8530	646286	VALVE           			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					CYL 1-2-5 EXH	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	97090	1062 				18266974	286534R			INSPECTION FOUND THE NITRALOY GUIDES WORE THE EX VALVE STEMS LEAVING STEPS IN THE STEM AT THE ENDS OF TRAVEL IN THE GUID	E.  ONE VALVE HAD .070 INCH WEAR.  SUBMITTER STATED CONTINENTAL SHOULD ISSUE A BULLETIN OR SERVICE LETTER ALERTING MECHA	NICS OF THIS PROBLEM.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997110600852	19971106	00852	SO  	1997	11	6	97ZZZX4670       	2	19971015	G	8520	537466	THROUGH BOLT    			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360KB   	17025	SO  					CRANKCASE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	3580H	1154 				250426	309434			DURING AN ANNUAL INSPECTION, THE BOTTOM CRANKCASE THROUGH-BOLT LOCATED BETWEEN NR 1 AND NR 3 CYLINDER POSITION WAS FOUND	 BACKED OUT FROM THE CASE ALMOST TO THE POINT OF FALLING OUT OF ITS MOUNTING HOLE BY APPROXIMATELY 1.1250 INCHES.  WHEN 	BOLT WAS REMOVED, FOUND THE OTHER END AT THE THREADED PORTION MISSING FROM BEING BROKEN OFF.  NO OIL LEAK WAS PRESENT. N	O OTHER CASE BOLTS OR CYLINDER STUDS WERE AFFECTED FROM THIS OCCURRENCE.			1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997110600853	19971106	00853	CE  	1997	11	6	97ZZZX4671       	1	19970925	G	3222		NOSE GEAR       			BEECH 	23    	C23         	1151242	CE  										TRUNNION	DEPARTED        	D				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			SO	03	24041					M1930				NOSE GEAR DEPARTED AIRCRAFT ON TAKEOFF.  THE NOSE GEAR TRUNNION INSIDE THE ENGINE MOUNT CRACKED AT BOLT HOLES FOR NOSE W	HEEL STEERING. THE CRACK PROGRESSED FROM THE BOLT HOLES TO CIRCLE THE TRUNNION DOWN WIND UNTIL IT COMPLETED 360 DEGREES.	  AT THAT TIME, THE GEAR DEPARTED THE AIRCRAFT.  SUSPECT HARD LANDING IN CROSS-WIND OR POSSIBLE TOWING AND TURNING TOO F	AR.			1	L	7	1 	3O				A1CE    					 
1997110600854	19971106	00854	SW  	1997	11	6	97ZZZX4672       	1	19970923	G	2710	73006000	PUSH/PULL TUBE  			MOONEY	M20   	M20J        	5870219	SW  										AILERON	BROKEN          	B	L	A	HX1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	3515H	3345 				241034				DURING CONTROL CHECK JUST PRIOR TO TAKEOFF, NOTED THE RIGHT AILERON DID NOT MOVE.  INVESTIGATION REVEALED THE PUSH ROD L	OCATED IN THE BELLY OF THE AIRCRAFT WAS BROKEN AT A WELD WHERE PART HAS A 90 DEGREE BEND.  THE BREAK WAS JUST AT THE EDG	E OF THE WELD.  IT APPEARED THE CRACK STARTED ON THE INSIDE OF THE 90 DEGREE BEND AND TRAVELED UP THROUGH THE METAL TO N	ON-WELDED PORTION.			1	L	7	1 	3O				2A3     					 
1997110600855	19971106	00855	SW  	1997	11	6	97ZZZX4673       	1	19971028	G	6420	206011809005	PITCH HORN      			BELL  	206   	206L1       	1182107	SW  										T/R HUB	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11										PITCH HORN ON T/R HUB ASSY HAS A LOOSE STUD.						1	G	7	1 	3U				H2SW    					 
1997110600856	19971106	00856	SW  	1997	11	6	97ZZZX4674       	1	19971020	G	2915	206076036101	VALVE           			BELL  	407   	407         		SW  										HYD RELIEF	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	98VG	15   			70128384	53171				INSPECTION FOUND HYDRAULIC RELIEF VALVE FAILED.  REPLACED WITH NEW RELIEF VALVE.						1	G	7	1 	3U			O	H2SW    					 
1997110600857	19971106	00857	NE  	1997	11	6	97ZZZX4675       	3	19971013	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		4579 						HJ484		INSPECTION 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	 
1997110600858	19971106	00858	NE  	1997	11	6	97ZZZX4676       	3	19971001	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		4605 						HJ460		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	 
1997110600859	19971106	00859	EU  	1997	11	6	97ZZZX4677       	1	19971013	G	5210	7253501551	DOOR PANEL      			SAAB  	SF340 	340B        	7860101	EU  										DOUBLER	DEFECTIVE       	B		A	YTQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	250AE					340B250				INSPECTION FOUND DOUBLER HAS 2 HOLES BURNED THROUGH BY ELECTRICAL ARCING.  STATIC ELECTRIC BUILD-UP ON OUTER PANEL TRAVE	LING THROUGH RIVETS TO DOUBLER AND DISCHARGING THROUGH DOUBLER.  THIS IS BEING CAUSED BY A POOR DESIGN OF NOT HAVING THE	 RIVETS INSULATED FROM ANTI-STATIC MATERIAL ON OUTER SURFACE ENHANCED BY THE REPAIR USING EXPANDED METAL AS ANTI-STATIC 	PROTECTION.  THIS REPAIR DOES NOT BOND ADEQUATELY AND GROUND IS NOT RELIABLE AT THE EDGES.  SUBMITTER STATED RIVETS SHOU	LD BE SEALED OVER WITH FIBERGLASS PRIOR TO REPAIRING THE ANTI-STATIC AND EXPANDED METAL SHOULD NOT BE USED IF IT CANNOT 	BE RELIED ON TO HAVE A GOOD BOND.  NOTE:  THERE IS AN OIL CHECK DOOR IN PANEL, A FIRE COULD HAPPEN.	2	L	7	2 	4T			RT	A52EU   					 
1997110600860	19971106	00860	EU  	1997	11	6	97ZZZX4678       	1	19971013	G	5210	7253501551	DOOR PANEL      			SAAB  	SF340 	340B        	7860101	EU  										OUTER SURFACE	DEFECTIVE       	B		A	YTQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	250AE					340B250				INSPECTION FOUND THE ANTI-STATIC MATERIAL WAS FALLING OFF.  THE PANEL HAD PREVIOUSLY BEEN REPAIRED LESS THAN ONE YEAR. T	HE REPAIR IS A SAAB APPROVED REPAIR THAT BONDS STATIC ELECTRICITY CONDUCTIVITY MATERIAL (EXPANDED ALUMINUM) TO REPLACE T	HE ALUMINUM FOIL.  THE SAAB PROCEDURE IS INADEQUATE TO ACHIEVE A RELIABLE BOND.  SUBMITTER STATED SAAB AND/OR THE FAA SH	OULD IMMEDIATELY DISAPPROVE THIS PROCEDURE AND ALL PANELS REPAIRED PER THIS PROCEDURE SHOULD BE REPAIRED USING THE SAAB 	APPROVED PROCEDURE OF FLAME SPRAY.  NOTE: ON 7-23-97, PN 7253501-712, HAD SAME PROBLEM AND DEFECT REPORT WAS SUBMITTED.		2	L	7	2 	4T			RT	A52EU   					 
1997110600865	19971106	00865	SW  	1997	11	6	97ZZZX4681       	1	19971020	G	6330	222031622105	ROD END         			BELL  	222   	222         	1182122	SW  										NODAL BEAM	WORN            	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	911EC	303  				47505				NODAL BEAM INSPECTION FOUND ROD END WORN.  REPLACED WITH NEW ROD END.						1	G	7	2 	3U				H9SW    					 
1997110700009	19971107	00009	NE  	1997	11	7	97ZZZX4682       	2	19971024	G	7210	7757543	BEARING         	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC49 GEAR CASE	SPALLED         	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13407			UDAG083		GEE785379			DISASSEMBLY OF GEAR CASE REVEALED THE INPUT ROLLER BEARING RACE CRACKED, PINION GEAR BEARING SURFACE SPALLED, LEFT AND R	IGHT IDLER GEAR RETAINING RINGS BROKE, AND NO TORQUE ON LEFT IDLER GEAR NUT.  PINION, SN IC641356.  INPUT BEARING, SN 9-	259.  REF:  OPERATOR CONTROL NR SI3R97012, 97ZZZX4683, AND 97ZZZX4684.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997110700010	19971107	00010	NE  	1997	11	7	97ZZZX4683       	2	19971024	G	7210	7922261	RETAINER RING   	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GL49 GEAR CASE	BROKEN          	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13407			UDAG0838		GEE785379			DISASSEMBLY OF GEAR CASE REVEALED THE INPUT ROLLER BEARING RACE CRACKED, PINION GEAR BEARING SURFACE SPALLED, LEFT AND R	IGHT IDLER GEAR RETAINING RINGS BROKE, AND NO TORQUE ON LEFT IDLER GEAR NUT.  PINION, SN IC641356.  INPUT BEARING, SN 9-	259.  REF:  OPERATOR CONTROL NR SI3R97012, 97ZZZX4682, AND 97ZZZX4684.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997110700011	19971107	00011	NE  	1997	11	7	97ZZZX4684       	2	19971024	G	7210	7757533	IDLER GEAR NUT  	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC49 GEAR CASE	LOOSE TORQUE    	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13407			UDAG0838		GEE785379			DISASSEMBLY OF GEAR CASE REVEALED THE INPUT ROLLER BEARING RACE CRACKED, PINION GEAR BEARING SURFACE SPALLED, LEFT AND R	IGHT IDLER GEAR RETAINING RINGS BROKE, AND NO TORQUE ON LEFT IDLER GEAR NUT.  PINION, SN IC641356.  INPUT BEARING, SN 9-	259.  REF:  OPERATOR CONTROL NR SI3R97012, 97ZZZX4682, AND 97ZZZX4683.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997110600870	19971106	00870	CE  	1997	11	6	97ZZZX4685       	1	19970417	G	3244	850T061	TIRE            	GOODYEARAERO		MTSBSI	MU2   	MU2B36      	5780412	CE  										RT MLG	SEPARATED       	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	09	869P	300  			51701608	692				RIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE FOR APPROXIMATELY 1 INCH.  SEPARATION WAS NOTIC	ED DURING A POST-FLIGHT WALK AROUND INSPECTION.  THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERE	NT MU-2'S.  TIRE WAS RETURNED TO MFG FOR EVALUATION.				1	H	7	2 	3T			RT	A10SW   					 
1997110600871	19971106	00871	CE  	1997	11	6	97ZZZX4686       	1	19970430	G	3244	850T061	TIRE            	GOODYEARAERO		MTSBSI	MU2   	MU2B36      	5780412	CE  										LT MLG	SEPARATED       	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	09	500PJ	228  			51582304	668				LEFT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE FOR APPROXIMATELY 10 INCHES.  OCCURRED ON LANDIN	G.  TIRE REMAINED INFLATED.  THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT MU-2'S.  TIRE WAS	 RETURNED TO MFG FOR EVALUATION.				1	H	7	2 	3T			RT	A10SW   					 
1997110600872	19971106	00872	CE  	1997	11	6	97ZZZX4687       	1	19970402	G	3244	850T061	TIRE            			MTSBSI	MU2   	MU2B36      	5780412	CE  										RT MLG	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	500PJ	284  			51710805	668				RIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE COMPLETELY AROUND CIRCUMFERENCE.  OCCURRED ON L	ANDING.  TIRE REMAINED INFLATED.  TREAD STAYED ATTACHED AROUND OUTBOARD EDGE CIRCUMFERENCE.  THIS WAS ONE OF THREE SIMIL	AR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT AIRCRAFT (BOTH MU-2'S).  TIRE RETURNED TO MFG FOR EVALUATION.				1	H	7	2 	3T			RT	A10SW   					 
1997111300039	19971113	00039	EA  	1997	11	13	97ZZZX4705       	2	19971016	G	8530	LW12892	THRUST BUTTON   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ROCKER HSAFT	MISSING         	B			N3XR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	167ER	387  				2841183	RL1870239A			DURING C/W LYC SB 301 AND SB 388 ALL ROCKER SHAFT THRUST BUTTONS WERE DISCOVERED MISSING.  THIS IS A FACTORY REMANUFACUR	ED ENGINE.					1	L	7	1 	3O	3	O		2A13    	E274				 
1997111300040	19971113	00040	SW  	1997	11	13	97ZZZX4706       	1	19971009	G	6310	406340102101	SEAL            			BELL  	407   	407         		SW  										FREEWHEEL	LEAK            	C			L1PM	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	1116H	136  				53046				FREEWHEELING UNIT FORWARD SEAL LEAKS EXCESSIVELY.  REPLACED SEAL AND CORRECTED LEAK.  AIRCRAFT TT:  135.5 HOURS.						1	G	7	1 	3U			O	H2SW    					 
1997111300041	19971113	00041	SW  	1997	11	13	97ZZZX4707       	1	19970625	G	6410	206016201131	BEARING         			BELL  	206   	206B        	1181511	SW  										T/R BLADE	BINDING         	C			L1PM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	212LA	104  			CS2814	3957				ACFT TT:  13,497.8 HOURS.  104.2 HR.  TWO NEW T/R BLADES P/N 206-016-201-131, SN CS-2814 AND SN CS-2815 WERE INSTALLED. 	  PILOT'S COMPLAINT ABOUT T/R PEDAL PROBLEM.  HELICOPTER WAS INSPECTED AND THE FOUR BEARINGS (2 EACH ON BLADES) ON T/R B	LADES WERE FOUND BINDING.  BEARING MATERIAL WAS COMING APART.  T/R BLADES WERE CHANGED AND PROBLEM WENT AWAY.				1	G	7	1 	3U				H2SW    					 
1997111300042	19971113	00042	SW  	1997	11	13	97ZZZX4708       	1	19970625	G	6410	206016201131	BLADE           			BELL  	206   	206B        	1181511	SW  										T/R	BEARING BINDING 	C			L1PM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	212LA	104  			CS2815	3957				ACFT TT:  13,497.8 HOURS.  104.2 HR.  TWO NEW T/R BLADES P/N 206-016-201-131, SN CS-2814 AND SN CS-2815 WERE INSTALLED. 	  PILOT'S COMPLAINT ABOUT T/R PEDAL PROBLEM.  HELICOPTER WAS INSPECTED AND THE FOUR BEARINGS (2 EACH ON BLADES) ON T/R B	LADES WERE FOUND BINDING.  BEARING MATERIAL WAS COMING APART.  T/R BLADES WERE CHANGED AND PROBLEM WENT AWAY.				1	G	7	1 	3U				H2SW    					 
1997111300043	19971113	00043	GL  	1997	11	13	97ZZZX4709       	2	19971011	G	7230		VANE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENG COMP	FAILED          	B			LS1R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	13	206BX	10565	398  			2872	CAE833239			PRECAUTIONARY LANDING DUE TO COMPRESSOR STALL.  FOUND CASE EROSION AND LOSS OF VANE.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997111300044	19971113	00044	SW  	1997	11	13	97ZZZX4710       	1	19971028	G	6320	206040040005	GEARSHAFT       			BELL  	206   	206B3       	1181506	SW  										XMSN SPLINES	WORN            	B		A	KBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	55TV	2997 			B1212149	3788				TRANSMISSION GEARSHAFT SPLINES SEVERLY WORN.  SUSPECT CAUSE DUE TO LENGTH OF CALENDAR TIME INSTALLED INDICATING BREAKDOW	N OF THE LUBRICANT.  PERIOD OF INSTALLATION WAS 13 YEARS.  RECOMMEND A CALENDAR LIMITATION OF 4 YEARS AS WELL AS THE EXI	STING HOURLY FREQUENCY (TO SUNGEAR).				1	G	7	1 	3U				H2SW    					 
1997111300045	19971113	00045	SW  	1997	11	13	97ZZZX4711       	1	19971009	G	6220	407010150101A	FRAHM ASSY      			BELL  	407   	407         		SW  										M/R	WORN            	C			L1PM	K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	23	58236	317  				53069				RUBBER BOOT CAME LOOSE AND SPRINGS ROTATED INSIDE FRAHM.  HELICOPTER HAD A 4 PER VIBRATION AND COULD NOT BE ELIMINATED. 	 REPLACED FRAHM ASSY AND BALANCED HELICOPTER ROTOR SYSTEM TO ACCEPTABLE LEVELS.					1	G	7	1 	3U			O	H2SW    					 
1997111300048	19971113	00048	CE  	1997	11	13	97ZZZX4714       	1	19971001	G	2810		FUEL TANK       			CESSNA	172   	172M        	2072418	CE  										RT WING TANK	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	9359H	5640 				17266115				AFTER REMOVING RIGHT FUEL TANK TO CHECK FOR LEAK, FOUND WEAR ON BOTTOM OF TANK INDENTED WITH RIVET HEAD MARKS.  THE TANK	 RESTS ON A REINFORCEMENT PLATE THAT IS RIVETED TO STIFFENERS.  USING A UNIVERSAL TYPE RIVET HEAD, A RUBBER CHAFE STRIP 	IS LAID OVER THE RIVET HEADS, BUT DUE TO WEIGHT AND MOVEMENT OF THE TANK, THE RUBBER HAS MOVED IN SPOTS REVEALING BARE R	IVET HEADS.  ALSO, RUBBER HAS BECOME BRITTLE AND HARD.  IF LEFT UNCHECKED, RIVETS WOULD HAVE WORN THROUGH TANK IN MULTIP	LE SPOTS.  SUGGEST COUNTERSUNK RIVETS.		1	H	7	1 	3O			NT	3A12    					 
1997111300049	19971113	00049	NE  	1997	11	13	97ZZZX4715       	2	19971027	G	7314	MFP200	PUMP            	CHNDLREVANS 		DOUG  	DC10  	DC10*       		WP  	GE    	CF6   	CF650*      	30018	NE  					ENGINE FUEL	DAMAGED         	B			SF3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03		29362	9483 		CGW10285					PUMP RETURNED FOR OVERHAUL AND SB COMPLIANCE.  FOUND BEYOND REPAIR AND FOD BOLT WAS WEDGED BETWEEN VANES OF IMPELLER SEC	TION ALONG WITH WASHER FRAGMENTS.  INTERNAL DAMAGE TO IMPELLER VANES AND GOUGED HOUSING.  UNIT COULD HAVE SEIZED AND SHE	ARED SHAFT.				2	L	7	3 	4F	4	F		A22WE   	E23EA				 
1997111300050	19971113	00050	EA  	1997	11	13	97ZZZX4716       	1	19971107	G	2530	2003681	HEATER ELEMENT  		1440A10T    	CNDAIR	CL600 	CL6001A11   	1900302	EA  										COFFEE POT	EXPLODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	711SX	4500 			84211098	3007				THE HEATER ELEMENT FAILED WITH AN EXPLOSIVE LIKE CHARGE THAT SENT THE FAILED ELEMENT AND WIRES INTO THE HONEYCOMB GALLEY	 TOP.					2	L	7	2 	4F			RT	A21EA   					 
1997111300051	19971113	00051	EA  	1997	11	13	97ZZZX4717       	1	19971027	G	3230	601P57208101	SWITCH          			CNDAIR	CL600 	CL6002B16   	1900305	EA  										NLG UPLOCK	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			EA	25	399CF					5084				NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF.  FOUND PROBLEM TO BE NOSE LANDING GEAR PROXIMITY SWITCH FAILED CAUSIN	G THE GEAR NOT TO RETRACT.					2	L	7	2 	4F			RT	A21EA   					 
1997111300052	19971113	00052	CE  	1997	11	13	97ZZZX4718       	1	19971027	G	2912	99123727	FILTER          			CESSNA	525   	525         	2076601	CE  										HYDRAULIC SYSTEM	FAULTY          	B			NVIR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	05	525J					5250184				PILOT REPORTED A LEFT HYDRAULIC LOW FLOW LIGHT CAME ON INTERMITTENTLY IN-FLIGHT.  INSPECTED AND FOUND HYDRAULIC FILTER W	AS SLOW IN PASSING FLUID.  INSTALLED NEW FILTER AND OPERATIONAL CHECKS WERE GOOD.					1	L	7	2 	4F			RT	A1WI    					 
1997111300053	19971113	00053	WP  	1997	11	13	97ZZZX4719       	2	19970630	G	7250	30727121	BLADE           		30727303    	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HP TURBINE	FAILED          	B		A	AE0R	O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SO	03	42EH	1244 			KAOU	28				IN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED.  ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR.  FOUND 4 EA	CH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES.  THIS WAS A CONTAINED FAILURE.  THE BLADES AND TURBIN	E DISK WERE NEW AT LAST MAJOR PERIODIC INSPECTION AND HAVE 1,244.0 HOURS AND 781 CYCLES TIME SINCE NEW.  FOD FROM BLADE 	RELEASE ALSO RUINED ALL OTHER HP BLADES, PLUS ALL 1ST, 2ND, AND 3RD, LP TURBINE BLADES.  CAUSE OF FAILURE IS UNKNOWN AT 	THIS TIME ALTHOUGH ENGINE DOES NOT HAVE SB TFE731-72-3434, RELOCATED A4 NOZZLE ASSY, INCORPORATED, WHICH SUPPOSEDLY HELP	S PREVENT THIS PROBLEM. THE FAILED BLADES ARE OF THE LATEST DESIGN.  (SB TFE731-72-3099).  CYCLES, 781.	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997111300054	19971113	00054	WP  	1997	11	13	97ZZZX4720       	2	19970630	G	7250	30727121	BLADE           		30727303    	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HP TURBINE	FAILED          	B		A	AE0R	O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SO	03	42EH	1244 			KADJ	28	P73180C			IN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED.  ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR.  FOUND 4 EA	CH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES.  THIS WAS A CONTAINED FAILURE.  THE BLADES AND TURBIN	E DISK WERE NEW AT LAST MAJOR PERIODIC INSPECTION AND HAVE 1,244.0 HOURS AND 781 CYCLES TIME SINCE NEW.  FOD FROM BLADE 	RELEASE ALSO RUINED ALL OTHER HP BLADES, PLUS ALL 1ST, 2ND, AND 3RD, LP TURBINE BLADES.  CAUSE OF FAILURE IS UNKNOWN AT 	THIS TIME ALTHOUGH ENGINE DOES NOT HAVE SB TFE731-72-3434, RELOCATED A4 NOZZLE ASSY, INCORPORATED, WHICH SUPPOSEDLY HELP	S PREVENT THIS PROBLEM. THE FAILED BLADES ARE OF THE LATEST DESIGN.  (SB TFE731-72-3099).  CYCLES, 781	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997111300055	19971113	00055	WP  	1997	11	13	97ZZZX4721       	2	19970630	G	7250	30727121	BLADE           		30727303    	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HP TURBINE	FAILED          	B		A	AE0R	O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SO	03	42EH	1244 			KADN	28	P73180C			IN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED.  ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR.  FOUND 4 EA	CH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES.  THIS WAS A CONTAINED FAILURE.  THE BLADES AND TURBIN	E DISK WERE NEW AT LAST MAJOR PERIODIC INSPECTION AND HAVE 1,244.0 HOURS AND 781 CYCLES TIME SINCE NEW.  FOD FROM BLADE 	RELEASE ALSO RUINED ALL OTHER HP BLADES, PLUS ALL 1ST, 2ND, AND 3RD, LP TURBINE BLADES.  CAUSE OF FAILURE IS UNKNOWN AT 	THIS TIME ALTHOUGH ENGINE DOES NOT HAVE SB TFE731-72-3434, RELOCATED A4 NOZZLE ASSY, INCORPORATED, WHICH SUPPOSEDLY HELP	S PREVENT THIS PROBLEM. THE FAILED BLADES ARE OF THE LATEST DESIGN.  (SB TFE731-72-3099).  CYCLES, 781	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997111300056	19971113	00056	WP  	1997	11	13	97ZZZX4722       	2	19970630	G	7250	30727121	BLADE           		30727303    	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HP TURBINE	FAILED          	B		A	AE0R	O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SO	03	42EH	1244 			KADM	28	P73180C			IN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED.  ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR.  FOUND 4 EA	CH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES.  THIS WAS A CONTAINED FAILURE.  THE BLADES AND TURBIN	E DISK WERE NEW AT LAST MAJOR PERIODIC INSPECTION AND HAVE 1,244.0 HOURS AND 781 CYCLES TIME SINCE NEW.  FOD FROM BLADE 	RELEASE ALSO RUINED ALL OTHER HP BLADES, PLUS ALL 1ST, 2ND, AND 3RD, LP TURBINE BLADES.  CAUSE OF FAILURE IS UNKNOWN AT 	THIS TIME ALTHOUGH ENGINE DOES NOT HAVE SB TFE731-72-3434, RELOCATED A4 NOZZLE ASSY, INCORPORATEDN WHICH SUPPOSEDLY HELP	S PREVENT THIS PROBLEM. THE FAILED BLADES ARE OF THE LATEST DESIGN.  (SB TFE731-72-3099).  CYCLES, 781	2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997111300057	19971113	00057	CE  	1997	11	13	97ZZZX4723       	1	19971025	G	3250		BUNGEE          			CESSNA	500   	560CESSNA   	2076750	CE  										NLG STEERING	WORN            	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	560FB	1829 				5600148				DURING TROUBLESHOOTING FOR NLG NOISE DUE TO OUT OF BALANCE NLG WHEEL, FOUND NLG STEERING BUNGEE WORN.  WEAR WOULD ALLOW 	BUNGEE TO DROP DOWN AND BIND UP PULLEY BRACKET.  BRACKET WOULD THEN FAIL DURING NOSE WHEEL STEERING TO LEFT.					2	L	7	2 	4F			RT	A22CE   					 
1997111300059	19971113	00059		1997	11	13	97ZZZX4724       	1	19971015	G	6123	A3496	SPRING          													HARTZL	HCB5M	HCB5MP3     	GL  	PROP FEATHER	BROKEN          	B			FG6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11			2059 					EV181		PROPELLER WOULD NOT AUTOFEATHER ON SHUT DOWN.  DISASSEMBLY AND INSPECTION REVEALED FEATHER SPRING BROKEN IN 7 PIECES.																6	C	P44GL	 
1997111300060	19971113	00060	GL  	1997	11	13	97ZZZX4725       	3	19970314	G	6110	RA19832	CLAMP ASSY      			PIPER 	PA31T 	PA31T       	7103124	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	09	23407	4008 	628  			31T7920055		BU9757		CLAMP ASSY RAPCO P/N RA1983-2 WAS SUBSTITUTED FOR A BFG 3E1883-2 UNDER THE ASSUMPTION OF JORDAN PROPELLER SERVICE CRS NR	 2273.  THIS IS REPORTED AS AN FAA-PMH APPROVED PART WHICH IS IN FACT A NON FAA-PMA PART.  THIS CLAMP ASSY FAILED CAUSIN	G THE FOLLOWING REPAIRS:  2 CLAMP ASSY'S PN 3E1883-2, 1 - 1E1150-2 TERMINAL STRIP, 1-4E1889-2 LEAD, 1-57-4E1555-1  SLIP 	RING, 1 - MS21919-DG4 CLAMP.			1	L	7	2 	3T				A8EA    		6	C	P15EA	 
1997111300061	19971113	00061	EA  	1997	11	13	97ZZZX4726       	2	19971021	G	8520		CONNECTING ROD  			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					NR 2 CYLINDER	FAILED          	E				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CL	CLIMB          	1			EA	21	2200J	3223 	1250 			32R7985041	L1927248A			ENGINE HAD A CATASTROPHIC FAILURE 10 MINUTES AFTER TAKEOFF.  A SUCCESSFUL EMERGENCY LANDING WAS MADE IN A HAY FIELD.  PI	LOT AND PASSENGER WERE NOT INJURED, AIRCRAFT WAS SUBSTANTIALLY DAMAGED.  THE NR 2 CONNECTING ROD CREATED FOUR HOLES IN T	HE ENGINE CASE AND THE CAMSHAFT AND A CAM FOLLOWER WERE BROKEN IN THE SAME AREA.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997111300062	19971113	00062	CE  	1997	11	13	97ZZZX4727       	1	19970929	G	3233		ACTUATOR        			CESSNA	210   	210L        	2073448	CE  										LT MLG	SPLIT           	G				A	O			UNSCHED LANDING         	OTHER                   			K			FLUID LOSS                			CL	CLIMB          	1			SW	01	321BT					21060127				AIRCRAFT DEPARTED ON A FAR 135 FLIGHT AT APPROXIMATELY 1400 HOURS TO PORTALES, N.M.  UPON DEPARTURE, THE LANDING GEAR WO	ULD NOT RETRACT.  THE PILOT ELECTED TO RETURN TO ALBUQUERQUE INTERNATIONAL AIRPORT.  WHEN HE MOVED THE GEAR HANDLE TO TH	E UP POSITION, NOTHING HAPPENED.  APPARENTLY, THE LEFT GEAR WAS LOCKED OVERCENTER, BUT THE RIGHT MAIN WAS UNLOCKED.  WHE	N THE AIRCRAFT TOUCHED DOWN, THE RIGHT GEAR LEG COLLAPSED.  DURING INSPECTION OF THE LANDING GEAR, DISCOVERED THE LEFT A	CTUATOR HAD SPLIT ALLOWING THE FLUID TO LEAK OUT OF THE SYSTEM.		1	H	7	1 	3O				3A21    					 
1997111300063	19971113	00063	SO  	1997	11	13	97ZZZX4728       	2	19971011	G	8530	649317	CYLINDER        			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 5	CRACKED         	B			LJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	3435L	1428 	176  			U2060735	1680686F			NR 5 CYLINDER ASSY CRACKED ONE-THIRD AROUND STEEL BARREL APPROXIMATELY 1 INCH BELOW CYLINDER HEAD.						1	H	7	1 	3O	3	O		A4CE    	E5CE				 
1997111300064	19971113	00064	CE  	1997	11	13	97ZZZX4729       	1	19971020	G	5553	NAS464P3A7	BOLT            			CESSNA	150   	152         	2071835	CE  										V FIN BRACKET	WRONG PART      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	16	48877					152781022				PURCHASED PART FROM CESSNA.  PART DID NOT MATCH OLD PART, REORDERED AND NOTIFIED CESSNA ACCORDINGLY.  SECOND ORDER ALSO 	DID NOT  MATCH.  BOLTS RECEIVED WERE NAS464P3A8 BOLTS, AND WERE TOO LONG TO USE - BOLTS HOLDING VERTICAL FIN TO FUSELAGE	 BRACKET.				1	H	7	1 	3O			NT	3A19    					 
1997111300065	19971113	00065	CE  	1997	11	13	97ZZZX4730       	1	19971022	G	2910	20801179	LINE            			CESSNA	177   	177RG       	2073709	CE  										HYDRAULIC SYSTEM	LEAK            	G		A		O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	11	52786	1284 				177RG1270				HYDRAULIC LINE BEGAN LEAKING ON GEAR RETRACTION CAUSING HYDRAULIC MOTOR/PUMP TO PUMP ALL USABLE HYDRAULIC FLUID OVERBOAR	D.  RESULT WAS LANDING WITH GEAR DANGLING FROM AIRCRAFT.  THE CAUSE OF THE LEAK WAS A CORROSION PIT.  LINE IS LOCATED IN	 THE COCKPIT PEDESTAL CAUSING INSPECTABILITY PROBLEM.				1	H	7	1 	3O				A20CE   					 
1997111300066	19971113	00066	CE  	1997	11	13	97ZZZX4731       	1	19971010	G	2720	041130613	TORQUE TUBE     			CESSNA	172   	172F        	2072414	CE  										RUDDER BAR	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	7900U	2135 				17251900				ACFT OWNER/PILOT REPORTED TURN COORDINATOR INDICATING 1 FULL BALL OUT OF CENTER AND EXCESSIVE RUDDER PRESS REQUIRED TO H	OLD COORDINATION.  MX DETERMINED RUDDER WOULD ONLY MOVE IN ONE DIRECTION WHEN MOVED FROM OUTSIDE ACFT.  WHEN ATTEMPT MAD	E TO MOVE THE RUDDER FROM INSIDE ACFT, STIFF OPERATION OBSERVED.  ALSO, SEVERE CORROSION FOUND ON RUDDER PEDAL.  CARPETI	NG CLOSE TO THIS AREA WAS DAMP.  NO OTHER CORROSION IN STRUCTURE FOUND.  THIS AREA IS DIRECTLY BELOW LOWER FWD WINDSHIEL	D STRAP, AND CORROSION POSSIBLY CAUSED BY A LEAKING WINDSHIELD.  RECOMMEND AREA BE CHECKED CLOSELY, AND LEAKS IN WINDHSH	IELD BE REPAIRED.  IF CORROSION IS FOUND ON THESE BARS, THEY WOULD REQUIRE REMOVAL TO CLEAN AND INSPECT.	1	H	7	1 	3O			NT	3A12    					 
1997111300067	19971113	00067	CE  	1997	11	13	97ZZZX4732       	1	19971010	G	2720	041130614	TORQUE TUBE     			CESSNA	172   	172F        	2072414	CE  										RUDDER BAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	7900U	2135 				17251900				ACFT OWNER/PILOT REPORTED TURN COORDINATOR INDICATING 1 FULL BALL OUT OF CENTER AND EXCESSIVE RUDDER PRESS REQUIRED TO H	OLD COORDINATION.  MX DETERMINED RUDDER WOULD ONLY MOVE IN ONE DIRECTION WHEN MOVED FROM OUTSIDE ACFT.  WHEN ATTEMPT MAD	E TO MOVE THE RUDDER FROM INSIDE ACFT, STIFF OPERATION OBSERVED.   ALSO, SEVERE CORROSION FOUND ON RUDDER PEDAL.  CARPET	ING CLOSE TO THIS AREA WAS DAMP.  NO OTHER CORROSION IN STRUCTURE FOUND.  THIS AREA IS DIRECTLY BELOW LOWER FWD WINDSHIE	LD STRAP, AND CORROSION POSSIBLY CAUSED BY A LEAKING WINDSHIELD.  RECOMMEND AREA BE CHECKED CLOSELY, AND LEAKS IN WINDHS	HIELD BE REPAIRED.  IF CORROSION IS FOUND ON THESE BARS, THEY WOULD REQUIRE REMOVAL TO CLEAN AND INSPECT.	1	H	7	1 	3O			NT	3A12    					 
1997111300068	19971113	00068	GL  	1997	11	13	97ZZZX4733       	3	19971010	G	6111		BLADE           			CESSNA	150   	150         	2071802	CE  						MCAULY	1A100	1A100MCM    	GL  	PROPELLER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	8474G	3975 				15062574		F1268		DURING ROUTINE ANNUAL INSPECTION, THE PROPELLER WAS STRIPPED OF PAINT.  AFTER VISUAL INSPECTION, A CRACK MEASURING .5625	 INCH IN LENGTH WAS FOUND APPROXIMATELY 14.50 INCHES IN FROM THE TIP OF THE 'FACE' (BACK) OF THE PROPELLER BLADE.  THIS 	CRACK WAS ONLY VISIBLE AFTER THE PAINT WAS REMOVED FROM THE PROPELLER.  IT IS RECOMMENDED THE PAINT BE REMOVED FROM THE 	PROPELLER AT EACH SCHEDULED INSPECTION OF THE AIRCRAFT.  CAUSE OF THE CRACK WAS NOT FULLY DETERMINED.			1	H	7	1 	3O			NT	3A19    		5	N	P918	 
1997111300291	19971113	00291	NE  	1997	11	13	97ZZZX4737       	2	19971010	G	7320	30B1449G	N2 PROBE        		1240KDC03005	LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       		NE  					LT ENG EEC	DEFECTIVE       	D				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CE	03	8271	769  				066	252			DURING 40-HOUR FLT, LT ENG COMPUTER LIGHT ILLUMINATED.  UPON LANDING, AN 'EA' FAULT (N2 INPUT INTERFACE) IN THE ENG (EDU	) CLEARED AFTER CYCLING PWR.  HANDBOOK STATED 'CONT NORMAL ENG OPER".  ON NEXT LEG DURING DESCENT THRU 25K FT, LT ENG SH	UT DOWN.  EDU CONTAINED AN 'EB' FAULT (N2 RATE OR RANGE).  FADEC REMOVED WITH BOTH N2 PROBES FROM LT ENG.  TESTING OF TH	E FADEC REVEALED NO PROB.  ONE N2 PROBE HAD A BENT PIN IN THE CONNECTOR.  SIGNAL RESULTING FROM THE BENT PIN CREATED AN 	UNUSUAL SIGNAL FREQ THAT THE FADEC INTERPRETED AS A FLUCTUATING N2 SPEED.  FADEC SCHEDULED FUEL TO CORRECT FOR FLUCTUATI	NG N2 SPEED.  FADEC SCHEDULED FUEL TO CORRECT FOR FLUCTUATING N2 AND FUEL FLOW ROLLED BACK FAR ENOUGH TO FLAME OUT ENG.	2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
1997111300292	19971113	00292	GL  	1997	11	13	97ZZZX4738       	2	19971020	G	7323	23057869	GOVERNOR        			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20R2    		GL  					ENGINE N2	FAILED          	C		A	PO7M	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	07	522FB	9770 	638  		29255	LN002	CAE832363			DURING FLIGHT, GOVERNOR LOCKED-UP INTERNALLY CAUSING ENGINE TO SPOOL DOWN TO GROUND IDLE.  THIS CAUSED ACFT TO MAKE A PR	ECAUTIONARY LANDING AT NIGHT ON 10-20-97.					1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
1997111300293	19971113	00293	NM  	1997	11	13	97ZZZX4739       	1	19971023	G	2621	DH7	WIRE HARNESS    			DOUG  	MD11  	MD11        	3023602	NM  										NR 1 FIRE WARN	DEFECTIVE       	H				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			EU	01	103EV					48415				NR 1 ENGINE IN-FLIGHT SHUT DOWN.  MAINTENANCE CHECKED 'ENG 1 FIRE' MESSAGE AND AS PRECAUTION, OPENED COWLING, CHECKED A 	AND B FIRE LOOPS.  CONDITION NORMAL.  GROUND TEST FOUND LOOP B MESSAGE.  AIRCRAFT REJECT TAKEOFF ON NEXT FLIGHT DUE TO '	ENG DET '' WARNING MESSAGE AND SOUND.  CHECK FOUND WIRE HARNESS DH7 TERMINAL, CONDITION - NO GOOD.				2	L	7	3 	4F			RT	A22WE   					 
1997111300294	19971113	00294	EU  	1997	11	13	97ZZZX4740       	1	19971002	G	2435	23079005	GENERATOR       			BAG   	JETSTM	JETSTM3101  	1500215	EU  										START/GEN	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	752JX		60   		3466	752				GENERATOR PORTION OF STARTER/GENERATOR FAILED.  UNIT FAILED UNDER NORMAL OPERATION AND LOAD.  SUSPECT DIODE FAILED.						2	L	7	2 	4T			RT	A21EU   					 
1997111300295	19971113	00295	CE  	1997	11	13	97ZZZX4741       	1	19971028	G	2435	62581038	FILTER CAPACITOR			CESSNA	500   	560CESSNA   	2076750	CE  										START/GEN	OVERHEATED      	B			CWQR	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			GL	05	561EJ	3954 				5600035				DURING PHASE 1 THROUGH 4 INSPECTION, OBSERVED THE LEFT ENGINE STARTER/GENERTOR R.F. NOISE SUPPRESSION CAPACITOR UNIT HAD	 EVIDENCE OF EXTREME OVERHEAT.  OUTER CASE DISTORTED AND DISCOLORED.  TERMINAL ISOLATOR DISTORTED AND CHARRED.  CONTINUE	D OPERATION COULD HAVE RESULTED IN AN IN-FLIGHT FIRE.				2	L	7	2 	4F			RT	A22CE   					 
1997111300297	19971113	00297	CE  	1997	11	13	97ZZZX4743       	1	19971027	G	3213	05411989	SPRING ASSY     			CESSNA	172   	R172K       	2072431	CE  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1092V	2283 				R1722115				FOUND DURING A SCHEDULED INSPECTION.  MAIN LANDING GEAR AND SPRING ASSEMBLY CORRODED AND RUSTY.  AIRCRAFT TOTAL TIME 2,2	83.2 HOURS.  THE SUSPECT CAUSE WAS FAILURE OF NOT REMOVING GEAR FAIRINGS DURING INSPECTIONS.  SUBMITTER RECOMMENDATION I	S TO REMOVE FAIRINGS, CLEAN AND PAINT GEAR SPRINGS EACH 100/ANNUAL INSPECTION.				1	H	7	1 	3O				3A17    					 
1997111300298	19971113	00298	CE  	1997	11	13	97ZZZX4744       	1	19971027	G	3213	054119810	SPRING ASSY     			CESSNA	172   	R172K       	2072431	CE  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1092V	2283 				R1722115				FOUND DURING A SCHEDULED INSPECTION.  MAIN LANDING GEAR AND SPRING ASSEMBLY CORRODED AND RUSTY.  AIRCRAFT TOTAL TIME 2,2	83.2 HOURS.  THE SUSPECT CAUSE WAS FAILURE OF NOT REMOVING GEAR FAIRINGS DURING INSPECTIONS.  SUBMITTER RECOMMENDATION I	S TO REMOVE FAIRINGS, CLEAN AND PAINT GEAR SPRINGS EACH 100/ANNUAL INSPECTION.				1	H	7	1 	3O				3A17    					 
1997112000094	19971120	00094	CE  	1997	11	20	97ZZZX4749       	1	19971018	G	2701	0411257	U-JOINT         			CESSNA	172   	172H        	2072424	CE  										LT CONTROL YOKE	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	2642L	5887 				17255842				DURING ANNUAL INSPECTION, PILOT SIDE CONTROL HAD EXCESS LOOSE MOTION.  THE U-JOINT THAT CONNECTS THE CONTROL WHEEL SHAFT	 TO THE YOKE WAS WORN ENOUGH, THAT IT WAS SOON TO BE HAZARDOUS TO FLIGHT SAFETY.  SUMITTER STATED THIS IS THE FOURTH ONE	 SEEN IN THIS SHAPE.  THIS NEEDS TO BE CHECKED AT EACH INSPECTION.				1	H	7	1 	3O			NT	3A12    					 
1997112000095	19971120	00095	CE  	1997	11	20	97ZZZX4750       	1	19971018	G	7820		MUFFLER         			CESSNA	172   	172H        	2072424	CE  										RT EXH RISER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	2642L	2800 				17255842				BOTH MUFFLERS WERE FOUND CRACKED AT RISERS AND BAFFLES WERE COLLAPSED AND HAD BEEN FOR SOME TIME.  THIS WOULD NOT ALLOW 	ENGINE TO DEVELOP FULL POWER.  FOUND DURING ANNUAL INSPECTION.					1	H	7	1 	3O			NT	3A12    					 
1997112000096	19971120	00096	CE  	1997	11	20	97ZZZX4751       	1	19971018	G	7820		MUFFLER         			CESSNA	172   	172H        	2072424	CE  										LT EXH RISER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	2642L	2800 				17255842				BOTH MUFFLERS WERE FOUND CRACKED AT RISERS AND BAFFLES WERE COLLAPSED AND HAD BEEN FOR SOME TIME.  THIS WOULD NOT ALLOW 	ENGINE TO DEVELOP FULL POWER.  FOUND DURING ANNUAL INSPECTION.					1	H	7	1 	3O			NT	3A12    					 
1997112000097	19971120	00097	EU  	1997	11	20	97ZZZX4752       	2	19971021	G	7260	3353001100	GEARBOX         								CFMINT	CFM56 	CFM563B2    	13802	EU  					ASSORY GRBOX	FAILURE         	B	P	A	LY2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	07		213  			58633		856647			SUSPECTED GEAR FAILURE INTERNAL TO THE ACCESSORY GEARBOX.  GEAR FAILED AND WAS UNCONTAINED IN THE GEARBOX HOUSING.  FAIL	ED UNIT RETURNED TO SNECMA.										4	F			E21EU				 
1997112000098	19971120	00098	CE  	1997	11	20	97ZZZX4753       	1	19971029	G	3243	0541139	PLUG            			CESSNA	210   	210N        	2073453	CE  										BRAKE VENT PLUG	BROKEN          	B	S		DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03										PART RECEIVED FROM STOCK.  WHEN SCREWED INTO MASTER CYLINDER BY HAND, SIDE OF PLUG BROKE OFF.  A SECOND PLUG WAS INSTALL	ED BY HAND AND IT BROKE IN THE SAME AREA.  THESE PLUGS ARE MADE FROM BRITTLE PLASTIC AND WERE SUPPLIED BY CESSNA.					1	H	7	1 	3O				3A21    					 
1997112000099	19971120	00099	SO  	1997	11	20	97ZZZX4754       	1	19971017	G	5711	6244802	FITTING         			PIPER 	PA28  	PA28151     	7102805	SO  										REAR SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	33810					287515303				DURING INSPECTION PER SB 977 FOUND REAR SPAR CARRY THRU LOWER FITTING (LEFT) BADLY CORRODED.  REPLACED PART.						1	L	7	1 	3O				2A13    					 
1997112000100	19971120	00100	EA  	1997	11	20	97ZZZX4755       	2	19971008	G	8550	76152	HOUSING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					FILTER MOUNT PAD	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	27	46SD		50   			278054040	RL1661948A			A FLAW IN THE CASTING NEAR THE UPPER LEFT HAND CORNER OF THE OIL FILTER ADAPTER MOUNTING PAD WAS ALLOWING OIL UNDER PRES	SURE TO LEAK THROUGH THE CASTING.  THE ENGINE HAD BEEN OVERHAULED BY LYCOMING 50 HOURS PRIOR TO THE OCCURRENCE.					1	L	7	2 	3O	3	O		1A10    	1E4				 
1997112000101	19971120	00101	CE  	1997	11	20	97ZZZX4756       	1	19971030	G	5312	05132823	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										LT FWD DOORPOST	CRACKED         	B	S		DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	733JS	8509 				17268335				INSPECTION REVEALED A CRACK IN THE LOWER HINGE LOCATION ON THE LEFT HAND DOORPOST.  CRACK WAS APPROXIMATELY 1.25 INCHES 	LONG.  DOORPOST WAS REPLACED.  NOTE: CRACK ORIGINATES AT AFT HINGE ATTACH HOLE AND PROGRESSES IN EITHER DIRECTION.					1	H	7	1 	3O			NT	3A12    					 
1997112000102	19971120	00102	SO  	1997	11	20	97ZZZX4757       	1	19971009	G	3230	8640902	SWITCH          			PIPER 	PA44  	PA44180     	7104402	SO  										RT MLG DOWNLOCK	SEPARATED       	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	723KD	6465 			7731	447995274				DOWN LIMIT SWITCH INTERIOR SEPARATED FROM SWITCH HOUSING, WIRES BECAME JAMMED UNDER DOWNLOCK HOOK CAUSING INCOMPLETE ENG	AGEMENT OF HOOK, WHEN SUBJECTED TO SIDELOAD HOOKS DISENGAGED AND GEAR RETRACTED.					1	L	7	2 	3O				A19S0   					 
1997112000104	19971120	00104	CE  	1997	11	20	97ZZZX4759       	1	19971030	G	5312	05132823	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										LT FWD DOORPOST	CRACKED         	B	P		DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	734FX	8314 				17268829				DURING TROUBLESHOOTING ON THE LEFT HAND DOOR HOLD OPEN STOP, NOTICED WHEN THE DOOR WAS OPENED AGAINST THE STOP, THE BOTT	OM FUSELAGE DOOR HINGE ATTACHMENT MOVED.  FURTHER INSPECTION REVEALED A CRACK IN THE AFT FORWARD DOORPOST APPROXIMATELY 	2.75 INCHES LONG NECESSITATING REPLACEMENT OF THE DOOR POST.  AN INSPECTION OF THE FLEET OF 172'S FOUND THE SAME CONDITI	ON ON 6 OUT OF 9 AIRCRAFT.  M.D. REPORTS WILL BE FILED ON EACH.			1	H	7	1 	3O			NT	3A12    					 
1997112000105	19971120	00105	CE  	1997	11	20	97ZZZX4760       	1	19971030	G	5312	051300634	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										LT FWD DOORPOST	CRACKED         	B	S	A	DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	734EQ	8176 				17268800				INSPECTION REVEALED A CRACK IN THE LOWER DOOR HINGE LOCATION ON THE LEFT HAND DOORPOST.  CRACK WAS APPROXIMATELY 1.6250 	INCHES LONG.  CRACK ORIGINATES AT AFT HINGE ATTACH HOLE AND PROGRESSES IN EITHER DIRECTION.  DOORPOST WAS REPLACED.					1	H	7	1 	3O			NT	3A12    					 
1997112000106	19971120	00106	SO  	1997	11	20	97ZZZX4761       	1	19971015	G	2430	587837	SWITCH          			PIPER 	PA34  	PA34200T    	7103406	SO  										BATTERY MASTER	FAILED          	D				O	A			OTHER                   	UNSCHED LANDING         			H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	21	7693F					347770068				MASTER SWITCH 'OPENED' INTERNALLY CAUSING COMPLETE ELECTRICAL FAILURE DURING FLIGHT.  GEAR WAS EXTENDED BY EMERGENCY MEA	NS AND LANDING WAS NORMAL.  NEW MASTER SWITCH CORRECTED PROBLEM.					1	L	7	2 	3O				A7SO    					 
1997112000108	19971120	00108	CE  	1997	11	20	97ZZZX4763       	1	19971016	G	8120	406C109005	TURBOCHARGER    	GARRTT      		CESSNA	210   	T210M       	2073451	CE  										CENTER SECT	LOOSE           	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	761KC	1438 			UIR0136P	21062308				AT ANNUAL INSPECTION, NOTED THE CENTER SECTION WAS LOOSE AT THE  BOLTS THAT HOLD THE CENTER SECTION TO THE HOT SIDE OF T	HIS UNIT. THIS HAS BEEN LEAKING AS THERE WAS EVIDENCE OF EXHAUST IN THIS AREA.  IT IS ASSUMED THESE BOLTS WERE LEFT LOOS	E DURING INSTALLATION TO ALLOW TURBO BOLTS TO ALIGN DURING INSTALLATION.  SUBMITTER STATED ALL BOLTS AND NUTS SHOULD BE 	CHECKED FOR TORQUE BEFORE SAFTEYING AND/OR BENDING OVER LOCK TABS.			1	H	7	1 	3O				3A21    					 
1997112000109	19971120	00109	SO  	1997	11	20	97ZZZX4764       	2	19971029	G	8530		SPRING          			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 2 CYL EXH VLV	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	9469S	40   				TE67	287152R			ENGINE RAN ROUGH.  INSPECTION FOUND NR 2 EXHAUST OUTER VALVE SPRING BROKEN.						1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997112000110	19971120	00110	SO  	1997	11	20	97ZZZX4765       	1	19971002	G	3230	6703103	FITTING         			PIPER 	PA28  	PA28R200    	7102811	SO  										LT MLG RETRACT	BROKEN          	B			B2ER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	9392N	3774 				28R35102				WHEN INSPECTING LANDING GEAR FOUND FITTING-GEAR RETRACTION, RIGHT AND LEFT, BROKEN WHERE ROD IS MOUNTED.  WHEN THIS PART	 IS BROKEN IT PREVENTS LANDING GEAR TO EXTEND AND LOCK.					1	L	7	1 	3O				2A13    					 
1997112000111	19971120	00111	SO  	1997	11	20	97ZZZX4766       	1	19971002	G	3230	6703102	FITTING         			PIPER 	PA28  	PA28R200    	7102811	SO  										RT MLG RETRACT	BROKEN          	B		A	B2ER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	9392N	3774 				28R35102				WHEN INSPECTING LANDING GEAR FOUND FITTING-GEAR RETRACTION, RIGHT AND LEFT, BROKEN WHERE ROD IS MOUNTED.  WHEN THIS PART	 IS BROKEN IT PREVENTS LANDING GEAR TO EXTEND AND LOCK.					1	L	7	1 	3O				2A13    					 
1997112000112	19971120	00112	GL  	1997	11	20	97ZZZX4767       	3	19971029	G	6114	D5858C402	HUB             			CESSNA	188   	T188C       	2073012	CE  						MCAULY	D3A34	D3A34C402   	GL  	NR 3 SOCKET	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	9675K					T18803966T		891723		INSPECTION FOUND HUB CRACKED (OVER 3 INCHES LONG) ON FRONT OF NR 3 BLADE SOCKET AND AROUND BOTH LIPS OF NR 3 BLADE SOCKE	T.  NR 3 BLADE BEARING BROKEN AND BUTT AREA OF NR 3 BLADE DAMAGED BEYOND REPAIRABLE LIMITS (BLADE MODEL:  G90DFA-10).  S	CRAP HUB SENT TO MCCAULEY FOR EVALUATION.  CAUSE OF CRACK UNKNOWN.				1	L	7	1 	3O				A9CE    		5	C	P47GL	 
1997112000113	19971120	00113	CE  	1997	11	20	97ZZZX4768       	1	19971029	G	3242	06603300	LINING          	PARKERHANFIN	99448       	CESSNA	310   	310R        	2074245	CE  										LT MLG BRAKE	WORN            	B		A	B3OR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	98834					310R0603				BRAKE LINING WORN THIN.  CALIPER PISTON OUT TOO FAR ALLOWING FLUID TO BYPASS O-RINGS OR FLUID LEVEL WAS LOW FROM CALIPER	 LEAK AND NO FLUID IN MASTER CYLINDER.  O-RINGS LOOKED GOOD.					1	L	7	2 	3O				3A10    					 
1997112000115	19971120	00115	SO  	1997	11	20	97ZZZX4770       	1	19971015	G	2150	22045402	ACM             	AIRESRCH    		EMB   	120   	EMB120RT    		SO  											DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		21778	348  		69512					ACM UNSATISFACTORY DUE TO HIGH FRICTION FROM BEARING.  LIGHT WEAR FOUND ON SHAFT AND RADIAL BEARINGS.  SUSPECT CAUSE OF 	FAILURE:  CONTAMINATION AND POSSIBLE ENVIRONMENT.  SUBMITTER RECOMMENDS PERIODIC SERVICE OF WATER/PARTICLE SEPARATOR PER	 MANUFACTURER'S MM.				2	L	7	2 	4T			RT	A31SO   					 
1997112000116	19971120	00116	NM  	1997	11	20	97ZZZX4771       	1	19971031	G	3252	65445787	MANIFOLD        		65447714    	BOEING	737   	7373T0      	1384582	NM  										SHIMMY DAMPER	CHAFED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					TSC2519					INSPECTION FOUND MANIFOLD ASSY OF DAMPER ASSY CHAFED DUE TO HOSE RUBBING ON OUTSIDE DIAMETER OF COMPENSATOR LOCATION.  R	EPEAT DEFECT.					2	L	7	2 	4F			RT	A16WE   					 
1997112000117	19971120	00117	NM  	1997	11	20	97ZZZX4772       	1	19971031	G	2121	X11375	BEARING         	SUNDSTRANDEM	215201      	BOEING	727   	727232      	1384082	NM  										FAN	FAILED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		713  			252					FAN BALL BEARING STARTING TO COME APART.  PARTIAL FAILURE OF BEARING.  712.42 HOURS SINCE NEW PART INSTALLED.						2	L	7	3 	4F				A3WE    					 
1997112000118	19971120	00118	NM  	1997	11	20	97ZZZX4773       	1	19971031	G	2121	X11374	BEARING         	SUNDSTRANDEM	215201      	BOEING	737   	737232      	1384475	NM  										FAN	FAILED          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		713  								FAN BEARING FAILED (BALL BEARING).  BEARING CAME APART.  ALSO, CAUSED DAMAGE TO END BELL 11840-1.  712.42 HOURS SINCE NE	W PART WAS INSTALLED.					2	L	7	2 	4F			RT	A16WE   					 
1997112000119	19971120	00119	WP  	1997	11	20	97ZZZX4774       	2	19970923	G	7323	8954932	PISTON          	AIRESRCH    	8954907     						GARRTT	TPE331	TPE3315     	01514	WP  					TURB GOV	LEAK            	B		A	DJFR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23					P459C					WHEN PARTS ARE MANUFACTURED, THEY ARE PAINTED WITH ZINC CHROMATE.  SUBMITTER HAS FOUND ON NEARLY EVERY GOVERNOR DISASSEM	BLED FRAGMENTS AND LARGE AMOUNTS OF PAINT LODGED UNDER O-RINGS WHERE THEY CONTACT SEALING AREAS.  THEY CAUSE INTERNAL LE	AKS AND EXTERNAL LEAKS AT THE CONTROL SHAFT.  RECOMMEND ELIMINATION OF CHROMATE PRIMER ON PISTON AND COVER ASSY.									4	T			E4WE				 
1997112000120	19971120	00120	CE  	1997	11	20	97ZZZX4775       	1	19971104	G	5753	CC50380	BEARING         			CESSNA	500   	S550        	2076607	CE  										FLAP ATTACH	WORN            	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	211QS					0011				DURING AIRCRAFT INSPECTION, DETERMINED THE FLAP ATTACH BEARINGS WERE WORN.  RETRIEVED TWO NEW BEARINGS FROM STOCK.  INSP	ECTED NEW BEARINGS.  ONE BEARING HAD COTTER KEY HOLE DRILLED TOO FAR DOWN ON THREADED PORTION OF SHANK TO ALLOW PROPER A	TTACHMENT OF NUT.  THE OTHER BEARING HAD TWO COTTER KEY HOLES DRILLED IN IT, PERPENDICULAR FROM EACH OTHER.				1	L	7	2 	4F			RT	A22CE   					 
1997112000121	19971120	00121	CE  	1997	11	20	97ZZZX4776       	1	19971104	G	5753	CC50380	BEARING         			CESSNA	500   	S550        	2076607	CE  										FLAP ATTACH	MISMANUFACTURED 	B			CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	211QS					0011				DURING AIRCRAFT INSPECTION, DETERMINED THE FLAP ATTACH BEARINGS WERE WORN.  RETRIEVED TWO NEW BEARINGS FROM STOCK.  INSP	ECTED NEW BEARINGS.  ONE BEARING HAD COTTER KEY HOLE DRILLED TOO FAR DOWN ON THREADED PORTION OF SHANK TO ALLOW PROPER A	TTACHMENT OF NUT.  THE OTHER BEARING HAD TWO COTTER KEY HOLES DRILLED IN IT, PERPENDICULAR FROM EACH OTHER.				1	L	7	2 	4F			RT	A22CE   					 
1997112000122	19971120	00122	SW  	1997	11	20	97ZZZX4777       	1	19971023	G	6230	206010443001	BEARING         			BELL  	206   	206B3       	1181506	SW  										M/R MAST	FAILED          	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	374M	193  			19213	4161				FOUND M/R MAST BEARING INNER RACE BREAKING DOWN.						1	G	7	1 	3U				H2SW    					 
1997112000123	19971120	00123	CE  	1997	11	20	97ZZZX4778       	1	19971029	G	7810	K1250860M203	EXHAUST         			CESSNA	210   	T210N       	2073456	CE  										TURBO INLET	CRACKED         	B	S	A	B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	9403Y	230  				21064498				WHILE CHANGING A CRACKED TURBO INLET (PN K1250860M-105), THE HEAT EXCHANGER WAS FOUND CRACKED.  OUT OF 4 AIRCRAFT WITH T	HIS STC EXHAUST, ALL 4 HAVE HAD THE TURBO INLETS CRACK.  THE REPLACEMENTS ARE ASSEMBLED DIFFERENTLY, APPARENTLY TO PREVE	NT THIS PROBLEM.  THE HEAT EXCHANGER IS THE SECOND ONE FOUND CRACKED AT THE WELD LINE WHERE THE NR 6 CYLINDER RISER ATTA	CHES.			1	H	7	1 	3O				3A21    					 
1997112000124	19971120	00124	EA  	1997	11	20	97ZZZX4779       	2	19970924	G	8520	72877	LIFTER          			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4J     	41514	EA  					NR 2 CYLINDER	BROKEN          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19	1851Z	1770 				M2343	L1892236A			TEAR DOWN REVEALED ALL LIFTER BODY HEADS BROKEN OFF AT CAM CONTACT POINT.  BROKEN PIECES THEN LODGED BETWEEN CAM LOBES A	ND ENGINE CASE RESULTING IN THE ENGINE CASE BEING CRACKED AND BROKEN IN SEVERAL PLACES AND LOSS OF ENGINE OIL.  SUSPECT 	INITIAL FAILURE OF NR 2 CYLINDER INTAKE LIFTER BODY.  POSSIBLE METAL FATIGUE.  PIECES FROM THIS WERE DEPOSITED BENEATH O	THER BODIES CAUSING FURTHER BREAKAGE.			1	L	7	1 	3O	3	O		A1CE    	E286				 
1997112000514	19971120	00514	WP  	1997	11	20	97ZZZX4786       	2	19971007	G	7250	30714314	EXHAUST NOZZLE  								GARRTT	TFE731	TFE7313     	01518	WP  					BEARING FLANGE	MISREPAIRED     	B	L		IY2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15		1539 			OP017939					EXHAUST NOZZLE WAS SENT TO REPAIR AND OVERHAUL SHOP FOR REPAIR OF INNER BEARING BORE FLANGE.  INSPECTION OF PART FOLLOWI	NG 'REPAIR' REVEALED THE FOLLOWING DISCREPANCIES.  INNER BEARING BORE WAS NOT REPAIRED.  PART WAS MODIFIED TO PN 3077095	-4.  THIS PART IS USED WHEN C/W SB 72-3482.  REWORKS SECTION AIRWORTHINESS TAG STATES 'PART HAS BEEN WORKED AND INSPECTE	D IAW MANUAL NR 72-02-15 REVISION 00'.  THIS MANUAL DOES NOT CONTAIN ANY BEARING FLANGE OR MODIFICATION DATA TO REWORK T	HIS NOZZLE FROM PN 3071431-4 TO PN 3077095-4.							4	F			E6WE				 
1997112000515	19971120	00515		1997	11	20	97ZZZX4787       	4	19971029	G	2561	PO201	LIFE VEST       	EAAEROMARINE																INFLATE TUBE	FAIL TEST       	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					C03137					FAILED THE MANUFACTURER'S 2-POUND PSI INFLATION TEST.																			 
1997112000516	19971120	00516		1997	11	20	97ZZZX4788       	4	19971029	G	2561	P0201105	LIFE VEST       	EAAEROMARINE																CELLS	FAIL TEST       	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					H24916					FAILED THE MANUFACTURER'S 2-POUND PSI INFLATION TEST.																			 
1997112000517	19971120	00517		1997	11	20	97ZZZX4789       	4	19971001	G	2561	P0101C	LIFE VEST       	EAAEROMARINE																INFLATE TUBE	FAIL TEST       	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					C92873					FAILED THE MANUFACTURER'S 2-POUND PSI INFLATION TEST.																			 
1997112000518	19971120	00518		1997	11	20	97ZZZX4790       	4	19971001	G	2561	P0201	LIFE VEST       	EAAEROMARINE																TUBE	FAIL TEST       	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					C03470					FAILED THE MANUFACTURER'S 2-POUND PSI INFLATION TEST.																			 
1997112000519	19971120	00519		1997	11	20	97ZZZX4791       	4	19971001	G	2561	M3L8	LIFE VEST       	PANAVION    																SEAM	FAIL TEST       	B			KO1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25					352					FAILED THE MANUFACTURER'S 2-POUND PSI INFLATION TEST.																			 
1997112000520	19971120	00520		1997	11	20	97ZZZX4792       	1	19971016	G	2810		FLAPPER VALVE   	USRUBBER    	3538013511  															FUEL CELL	STUCK           	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01					W2507					UPON RECEIVING OVERHAULED LEFT WING FUEL CELL, FOUND FLAPPER VALVE IN FUEL TANK STUCK CLOSED AND COULD NOT BE OPENED.																			 
1997112000521	19971120	00521	CE  	1997	11	20	97ZZZX4793       	1	19971001	G	5711		CARRY THRU SPAR 			CESSNA	210   	T210L       	2073449	CE  										CABIN OVERHEAD	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	121RJ					21059735				INSPECTION FOUND CABIN OVERHEAD CARRY-THROUGH SPAR CORRODED WHERE FRESH AIR DUCT PASSES THROUGH.  SUSPECT DISSIMILAR  ME	TAL CONTACT.					1	H	7	1 	3O				3A21    					 
1997112000522	19971120	00522	CE  	1997	11	20	97ZZZX4794       	1	19971108	G	5350	10210002617	FAIRING         			BEECH 	58    	58P         	1152744	CE  										LT WING	DEFORMED        	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	132Z	4990 				TJ284				UPON INSPECTION OF AIRCRAFT, NOTED LT WING INBOARD FAIRING DENTED AND DEFORMED.  WING HAD JUST BEEN REMOVED AND REINSTAL	LED FOR A STRUCTURAL INSPECTION 7.5 HOURS PRIOR.					1	L	7	2 	3O				A23CE   					 
1997112000523	19971120	00523	CE  	1997	11	20	97ZZZX4795       	1	19971108	G	3230		GEARBOX         			BEECH 	58    	58P         	1152744	CE  										LANDING GEAR	OUT OF RIG      	B			RF1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	132Z	4990 	8    			TJ284				UPON INSPECTION OF AIRCRAFT, THE LANDING GEAR HAD NO INTERNAL GEAR CLEARANCE IN ACTUATOR GEARBOX.  AIRCRAFT HAD BEEN RIG	GED 7.5 HOURS PRIOR AFTER THE NOSE GEAR FORWARD ROD END HAD BEEN REPLACED.					1	L	7	2 	3O				A23CE   					 
1997112000524	19971120	00524	EA  	1997	11	20	97ZZZX4796       	2	19971104	G	8530		CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 2 CYL BARREL	CRACKED         	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	16	162ER	3000 	282  			2841152	L1478339A			THE PILOT REPORTED A ROUGH ENGINE AND MADE A PRECAUTIONARY LANDING.  A COMPRESSION GAUGE REVEALED THE NR 2 CYLINDER LEAK	ING BETWEEN THE HEAD AND BARREL (6 INCHES FROM THE MOUNTING FLANGE).  THIS IS BETWEEN THE COOLING FINS AT THE BASE OF TH	E EXHAUST PORT.  THE CRACK IS ABOUT 4 INCHES LONG.  THE CYLINDER WAS WAS REMOVED AND A NEW ONE INSTALLED.				1	L	7	1 	3O	3	O		2A13    	E274				 
1997112000525	19971120	00525	CE  	1997	11	20	97ZZZX4797       	1	19970922	G	3240	581710240	BRAKE LINE      			CESSNA	402   	402C        	207590R	CE  										LT MASTER CYL	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	16	3246M	15038				402C0294				THE LT MASTER CYLINDER BRAKE LINE CRACKED BECAUSE CONTINUAL FLEXING DURING BRAKING CAUSED THE LINE TO CRACK AT THE 180-D	EGREE END.					1	L	7	2 	3O				A7CE    					 
1997112000526	19971120	00526	CE  	1997	11	20	97ZZZX4798       	1	19971105	G	3222	0543034497	TORQUE LINK     			CESSNA	182   	182G        	2072716	CE  										NLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	3281S	4848 				18255781				DURING AN ANNUAL INSPECTION, THE UPPER TORQUE LINK OF THE NOSE LANDING GEAR WAS FOUND CRACKED IN THE RADIUS OF THE UPPER	 FORGED RIB ADJACENT TO THE ATTACH BOLT HOLE.  BOTH SIDES WERE CRACKED.					1	H	7	1 	3O			NT	3A13    					 
1997112000527	19971120	00527	SW  	1997	11	20	97ZZZX4799       	1	19971020	G	3250		STEERING SYSTEM 			MOONEY	M20   	M20L        	5870221	SW  										RUD-NLG	FAILED          	D	S	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	05	3426X					3399				DURING TOUCH AND GO LANDING, LOST CONTROL OF ACFT FOLLOWING TOUCH DOWN.  ACFT RECEIVED SUBSTANTIAL DAMAGE AFTER VEERING 	TO LEFT.  NLG BROKE AND RT MLG COLLAPSED.  IT IS BELIEVED RUDDER NLG STEERING SYSTEM BOLT SHEARED.					1	L	7	1 	3O			RT	2A3     					 
1997112000528	19971120	00528	CE  	1997	11	20	97ZZZX4800       	1	19971031	G	5511		RIB             			CESSNA	150   	152         	2071835	CE  										HORIZONTAL STAB	CRACKED         	B	S	A	AIHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4837P	7200 				15284828				INSPECTION FOUND FAR RIGHT RIB IN HORIZONTAL STABILIZER CRACKED.  LOWER CRACK FOUND TO BE 1 INCH, WHILE TOP, .75 INCH. T	HESE CRACKS ARE OVER AND BELOW THE ELEVATOR HINGE ATTACH POINT.  IF NOT FOUND, COULD, IN TIME, CAUSE SEPARATION OF ELEVA	TOR FROM STABILIZER.				1	H	7	1 	3O			NT	3A19    					 
1997112000529	19971120	00529	CE  	1997	11	20	97ZZZX4801       	1	19971030	G	2720	24670014	TORQUE TUBE     			CESSNA	172   	172RG       	2072438	CE  										RUDDER CONTROL	BROKEN          	D	S	A		O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	13	6529V	7969 				172RG0755				PILOT REPORTED LOSS OF RUDDER CONTROL IN-FLIGHT ALTHOUGH HE WAS ABLE TO MAINTAIN CONTROL OF THE AIRCRAFT AND MADE AN UNE	VENTFUL LANDING.  FOUND THE AFT (RIGHT HAND) RUDDER PEDAL TORQUE TUBE WAS BROKEN APPROXIMATELY 7/8 OF THE WAY AROUND THE	 TUBE JUST TO THE LEFT SIDE OF THE SECTOR GEAR.  THIS ALLOWED THE TWO SECTOR GEARS TO DISENGAGE WHICH UNSYNCHRONIZED THE	 TWO TORQUE TUBES.  BECAUSE OF THIS, THE RUDDER CABLE TENSION WAS UNABLE TO BE MAINTAINED.			1	H	7	1 	3O				3A17    					 
1997112000530	19971120	00530	SO  	1997	11	20	97ZZZX4802       	1	19971105	G	8120	LW31S444	BOLT            		LW18302     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LEFT ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	7164D					318052013	L859461A			TURBOCHARGER MOUNT LOWER RIGHT HAND ATTACH BOLT LOOSENED AND VIBRATED UNTIL THE NUT AND COTTER KEY FAILED.  BOLT THEN DE	PARTED THE ENGINE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997112000531	19971120	00531	GL  	1997	11	20	97ZZZX4803       	3	19971022	G	6111	M10083	BLADE           			CESSNA	208   	208B        	2073701	CE  						HARTZL	H3B3M	HCB3M       	GL  	BLADE FACE	CRACKED         	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	931FE	5378 	2091 		9865	208B0031		6B256		INSPECTION FOUND ALL 3 BLADES HAVE CHORDWISE CRACKS BEYOND THE 3.5 INCH LIMIT.  ALL CRACKS LEAD UP TO AND POSSIBLY UNDER	 THE EROSION SHIELD.  THE CRACKS WERE FOUND DURING INSPECTION PER HARTZELL JB 169A.  PROPELLER REMOVED FROM SERVICE AT T	HIS TIME.				1	H	7	1 	3T				A37CE   		5	C	P9NE	 
1997112000532	19971120	00532	GL  	1997	11	20	97ZZZX4804       	3	19971022	G	6111	M10083	BLADE           			CESSNA	208   	208B        	2073701	CE  						HARTZL	H3B3M	HCB3M       	GL  	BLADE FACE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	931FE	5378 	2091 		9870	208B0031		6B256		INSPECTION FOUND ALL 3 BLADES HAVE CHORDWISE CRACKS BEYOND THE 3.5 INCH LIMIT.  ALL CRACKS LEAD UP TO AND POSSIBLY UNDER	 THE EROSION SHIELD.  THE CRACKS WERE FOUND DURING INSPECTION PER HARTZELL JB 169A.  PROPELLER REMOVED FROM SERVICE AT T	HIS TIME.				1	H	7	1 	3T				A37CE   		5	C	P9NE	 
1997112000533	19971120	00533	GL  	1997	11	20	97ZZZX4805       	3	19971022	G	6111	M10083	BLADE           			CESSNA	208   	208B        	2073701	CE  						HARTZL	H3B3M	HCB3M       	GL  	BLADE FACE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	931FE	5378 	2091 		9872	208B0031		6B256		INSPECTION FOUND ALL 3 BLADES HAVE CHORDWISE CRACKS BEYOND THE 3.5 INCH LIMIT.  ALL CRACKS LEAD UP TO AND POSSIBLY UNDER	 THE EROSION SHIELD.  THE CRACKS WERE FOUND DURING INSPECTION PER HARTZELL JB 169A.  PROPELLER REMOVED FROM SERVICE AT T	HIS TIME.				1	H	7	1 	3T				A37CE   		5	C	P9NE	 
1997112000534	19971120	00534	NM  	1997	11	20	97ZZZX4806       	1	19971001	G	2780		SWIVEL JOINT    			BOEING	727   	727251      	138408H	NM  										LE SLAT ACTUATOR	LEAKED          	D				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			SW	99	252US					19971				ON DHL CHARTER FLIGHT HYD/ARL, TOTAL A-SYSTEM HYDRAULIC FAILURE REPORTED INTO AUCKLAND.  AIRCRAFT REQUIRED TOW FROM RUNW	AY.  HYDRAULIC LEAK TRACED TO LOOSE SWIVEL JOINT ON L/E SLAT ACTUATOR.  SWIVEL JOINT CORRECTLY TIGHTENED AND SYSTEM REPL	ENISHED.  AIRCRAFT OPERATED BY KITTY HAWK AIRLINES.				2	L	7	3 	4F				A3WE    					 
1997112000535	19971120	00535	CE  	1997	11	20	97ZZZX4807       	1	19971023	G	5753	35165050231	BRACKET         			BEECH 	300   	300BEECH    	1152930	CE  										RT OTBD FLAP SUP	WORN            	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	770GX	2228 								RIGHT OUTBOARD FLAP SUPPORT BRACKET WORN AT INBOARD AFT ROLLER BRACKET P/N 35-165050-31.  ROLLER FRETTED INTO BRACKET WE	ARING ABOUT HALF WAY THROUGH METAL.  SAME AS AD 97-14-16 ON 1900 BEECH.					2	L	7	2 	4T				A24CE   					 
1997112000536	19971120	00536	CE  	1997	11	20	97ZZZX4808       	1	19971020	G	2740	45AS61023137	ACTUATOR        			BEECH 	MU300 	400A        	1155402	CE  										PITCH TRIM	MALFUNCTIONED   	B			KI2R	H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CE	01	85CR				970611	RK22				PILOTS NOTED AUTOPILOT WOULD NOT TRIM AIRCRAFT.  PILOT DE-SELECTED AUTOPILOT AND TRIM FUNCTIONED CORRECTLY IN MANUAL MOD	E 'NORMAL' POSITION, HOWEVER, WOULD NOT FUNCTION WHEN 'EMERGENCY' TRIM WAS SELECTED.  ON THE GROUND, BOTH 'NORMAL' AND '	EMERGENCY' POSITIONS WORKED.  AUTOPILOT OUTPUTS TESTED OK.  PITCH ACTUATOR REPLACED.  AIRCRAFT FUNCTIONED NORMALLY.  SPE	CIFIC FAILURE OR CAUSE UNKNOWN AT THIS TIME.			2	H	7	2 	4F			RT	A16SW   					 
1997112000537	19971120	00537	EU  	1997	11	20	97ZZZX4809       	1	19971014	G	7170	0174078010	VALVE           			AEROSP	SA365 	SA365N1     	8680668	EU  										START DRAIN	LEAKS           	B			KY1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	95MD	4174 			A66B	6320				START DRAIN VALVE UNIT LEAKS.  REPAIR AS NECESSARY.						1	G	7	2 	3U				H10EU   					 
1997112000538	19971120	00538	GL  	1997	11	20	97ZZZX4810       	2	19971016	G	7532	23053176	BLEED VALVE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	STICKING        	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	11	37488		447  		FF28030	2188	CAE823399			VALVE APPARENTLY IS STICKING IN THE CLOSED POSITION AND DOES NOT OPEN UP WHEN POWER DEMAND IS DECREASED.  THIS CREATES A	 MOMENTARY COMPRESSOR STALL RESULTING IN GUNSHOT TYPE SOUNDS COMING FROM THE EXHAUST ON THE TURBINE.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997112000539	19971120	00539	WP  	1997	11	20	97ZZZX4811       	1	19971105	G	7170	A7297	DRAIN TUBE      			ROBSIN	R44   	R44         	7640120	WP  										RT FIREWALL	LEAKS           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	159RP	95   				0342				DRAIN TUBE OPENING IS LOCATED INSIDE AIRFRAME IN TRANSMISSION AREA.  WHEN SUMP DRAIN VALVE LEAKS, FUEL DRAINS INTO AND A	CCUMULATES AT JUNCTION OF FIREWALLS CREATING EXTREME FIRE HAZARD.  SUBMITTER RECOMMENDS REVISING THE SUMP DRAIN PLUMBING	 ALA R22 SYSTEM TO PROVIDE POSITIVE OVERBOARD VENTING OF FUEL IN THE EVENT OF DRAIN VALVE SEEPAGE.  REF:  R44 IPC FIG 8-	5, ITEMS 8 AND 10.			1	G	7	1 	3O				H11NM   					 
1997112000540	19971120	00540	EA  	1997	11	20	97ZZZX4812       	2	19970831	G	7420		P LEAD          			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2B     	41508	EA  					LT-RT MAG	SHORTED         	G	L	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	17	1880G					50				FORCED LANDING DUE TO ENGINE STOPPAGE.  INVESTIGATION DETERMINED ENGINE STOPPAGE DUE TO WIRE BETWEEN MASTER SWITCH LOCAT	ED ABOVE AND LEFT OF PILOT'S HEAD AND THE OVERVOLTAGE RELAY LOCATED ON RIGHT UPPER SIDE OF ENGINE FIREWALL BECOMING EXTR	EMELY HOT.  THE EXTREME TEMPERATURE MELTED WIRE'S INSULATION AND P-LEAD WIRES IN SAME WIRE BUNDLE.  THIS SHORTED THE LEF	T AND RIGHT MAGNETOS CAUSING ENGINE TO CEASE OPERATION.  THERE IS NO CIRCUIT PROTECTION FOR THE WIRE IN QUESTION BETWEEN	 MASTER SWITCH AND OVERVOLTAGE RELAY.  SUBMITTER SUGGESTED A SB TO REQUIRE A BREAKER SWITCH BE INSTALLED IN PLACE OF STA	NDARD MASTER SWITCH AND THIS SB BE MANDATED BY AD.	1	H	7	1 	3O	3	O	NC	A759    	E274				 
1997112000541	19971120	00541	CE  	1997	11	20	97ZZZX4813       	1	19971114	G	8011	ESEBB142A	BENDIX DRIVE    		MHB4014     	BEECH 	76    	76          	1153005	CE  										STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		258  								BENDIX DRIVER FAILED AFTER 194 HOURS, REPLACED WITH SAME, FAILED AFTER 62 HOURS, REPLACED WITH SAME, FAILED AFTER 396.6 	HOURS. REPLACED WITH EBB142A.  EBB142A FAILED TO EXTEND AT 258 HOURS, CLEANED AND LUBED PER MFG, FAILED TO EXTEND AFTER 	21 HOURS.				1	L	7	2 	3O				A29CE   					 
1997112000731	19971120	00731	CE  	1997	11	20	97ZZZX4814       	1	19971108	G	5741	105090A0321UJ	CRUSH WASHER    			BEECH 	58    	58P         	1152744	CE  										LT WING BOLT	DEFORMED        	B		A	RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	132Z	8    				TJ284				UPON INSPECTION OF AIRCRAFT, FOUND LEFT WING SETTING AT A HIGHER ANGLE OF INCIDENCE.  FURTHER INSPECTION REVEALED THE UP	PER AFT CRUSH WASHER AND BOLT HAD SLIPPED DOWN APPROXIMATELY .25 INCH CAUSING LEFT WING TO HAVE MORE LIFT.  AIRCRAFT HAD	 JUST FINISHED WITH A STRUCTURAL INSPECTION.  ALL EIGHT WING BOLTS WERE REMOVED AND MAGNAFLUXED.  THE CRUSH WASHER CLEAR	LY HAD 2 SETS OF SERRATIONS WHERE IT HAD SLIPPED AND WAS RETORQUED.			1	L	7	2 	3O				A23CE   					 
1997112000732	19971120	00732	CE  	1997	11	20	97ZZZX4815       	1	19971108	G	5312	00244002455	BULKHEAD        			BEECH 	58    	58P         	1152744	CE  										AFT FUSELAGE	MISINSTALLED    	B			RF1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	132Z	8    				TJ284				UPON INSPECTION OF AIRCRAFT, FOUND AFT FUSELAGE BULKHEAD IMPROPERLY RIVETED.  RIVET HEADS CLEARLY HAVE DENTS ALMOST LOOK	ING LIKE WRONG SET WAS USED TO DRIVE RIVETS.  MOST OF THE UPSET ENDS WERE NOT PROPERLY BURRED.  ALL RIVETS WERE REMOVED 	AND REPLACED AND PROPERLY RIVETED.				1	L	7	2 	3O				A23CE   					 
1997112000733	19971120	00733	CE  	1997	11	20	97ZZZX4816       	1	19971108	G	5260	00243007621	STEP            			BEECH 	58    	58P         	1152744	CE  										RT SIDE	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	132Z	4990 	8    			TJ284				UPON INSPECTION OF AIRCRAFT, FOUND RIGHT SIDE ASSIST STEP CRACKED WHERE IT HAD BEEN WELDED 7.5 HOURS AGO.						1	L	7	2 	3O				A23CE   					 
1997112000734	19971120	00734	CE  	1997	11	20	97ZZZX4817       	1	19970825	G	2701	15131682	WHEEL           			CESSNA	172   	172D        	2072410	CE  										PILOT YOKE	BROKE           	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	09	21089	2770 				17249608				PILOT CONTROL YOKE BROKE, LEFT SIDE BOTTOM, IN LANDING FULL STALL CONDITION.  PLASTIC MAY HAVE AGED.  AIRCRAFT IS A 1962	 MODEL AND HAS BEEN PARKED OUTSIDE MOST OF THE TIME.					1	H	7	1 	3O			NT	3A12    					 
1997112000735	19971120	00735	SO  	1997	11	20	97ZZZX4818       	1	19971101	G	2410		BELT            			PIPER 	PA32  	PA32R301    	7103218	SO  										ALT DRIVE	FAILED          	G		A		A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	13	415WR	160  				3246072				AIRCRAFT ON IFR FLIGHT PLAN LOST ALL ELECTRICAL POWER.  LANDED WITHOUT ACCIDENT.  INSPECTION REVEALED THE ALTERNATOR IDL	E PULLEY WHICH TENSIONS THE BELT WAS CHAFING ON A COWLING STIFFENER CAUSING THE BELT TO TEAR.  THIS IS A NEW AIRCRAFT, T	OTAL TIME, 159.8 HOURS.  PIPER SERVICE CENTER STATED A SL WAS ISSUED TO RELOCATE THE STIFFENER, BUT THIS AIRCRAFT WAS OV	ERLOOKED AT THE DISTRIBUTER.			1	L	7	1 	3O				A3SO    					 
1997112000736	19971120	00736	SO  	1997	11	20	97ZZZX4819       	1	19971101	G	7810	4701402	BRACKET         			PIPER 	PA31  	PA31P       	7103120	SO  										RT EXHAUST	FAILED          	D		A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SO	01	7325L					317400206				DURING TAKEOFF, RT TAILPIPE FELL OFF AIRCRAFT.  EXHAUST BURNED A HOLE IN LOWER COWL.  INVESTIGATION FOUND ISOLATOR BRACK	ETS BROKEN, AND ALL EXHAUST SLIP JOINTS LOOSE.  SUSPECT LOOSE JOINTS CAUSED VIBRATION THAT BROKE ISOLATOR BRACKET.  SUBM	ITTER RECOMMENDS THE EXHAUST SYSTEM BE PRESSURE TESTED TO FIND LOOSE SLIP JOINTS.				1	L	7	2 	3O				A8EA    					 
1997112000737	19971120	00737	SO  	1997	11	20	97ZZZX4820       	2	19971011	G	8530		CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					RT ENG NR 4	FAILED          	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			SW	15	82LB		148  			TH910	1720929CX			PILOT REPORTED RIGHT ENGINE RUNNING ROUGH.  INVESTIGATION FOUND NR 4 CYL HEAD SEPARATED FROM BARREL.  THE CYLINDER HAD B	EEN INSTALLED 148 HOURS BEFORE.  RECENTLY OVERHAULED.  TOTAL TIME ON CYLINDERS ARE NOT RECORDED.  SUBMITTER RECOMMENDS T	HAT CYLINDERS BE SCRAPPED AFTER THEIR SECOND RUN OR TIME LIFE LIMIT BE ESTABLISHED BY THE MFG ON CURRENT PRODUCTION ENGI	NE.			1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997112000738	19971120	00738		1997	11	20	97ZZZX4821       	4	19971113	G	2564	R0297A109	RAFT            	EAAEROMARINE	T12         															TEMP TIES	MISPACKED       	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										WHILE CONDUCTING A PRELIMINARY INSPECTION ON RAFT, TEMPORARY WEB TIES WERE FOUND INSTALLED.  THESE TIES ARE USED AS SHOP	 AIDS FOR PACKING THE RAFT AND MUST BE REMOVED BEFORE THE UNITS ARE RETURNED TO SERVICE.																		 
1997112000739	19971120	00739	SW  	1997	11	20	97ZZZX4822       	1	19971028	G	6320	20604562101	SUNGEAR         		206040002029	BELL  	206   	206B3       	1181506	SW  										TRANSMISSION	WORN            	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	55TV	2998 			B122661	3788				SPLINES SEVERELY WORN AND 3 CRACKED.  SUSPECT CAUSE DUE TO LENGTH OF CALENDAR TIME INSTALLED INDICATING A BREAK DOWN OF 	THE LUBRICANT.  PERIOD OF INSTALLATION WAS 13 YEARS.  SUBMITTER RECOMMENDS A CALENDAR LIMITATION OF 4 YEARS AS WELL AS T	HE EXISTING HOURLY FREQUENCY.				1	G	7	1 	3U				H2SW    					 
1997112000741	19971120	00741	SW  	1997	11	20	97ZZZX4824       	1	19971023	G	6410	212010750105	BLADE           			BELL  	205   	205A1       	1181414	SW  										T/R BLADE TIP	FAILED          	B			GDMR	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			NM	09	58HJ				A9635	30314				WHILE CARRYING OUT OPERATIONS ON THE AFTERNOON OF 10-23-97, PILOT REPORTED INCREASE OF VIBRATION WHILE IN-FLIGHT RETURNI	NG TO LANDING SITE.  AIRCRAFT WAS SHUT DOWN.  ON EXAMINATION OF TAIL ROTOR, INSIDE PART OF TIP WAS FOUND MISSING.  NO OT	HER DAMAGE WAS APPARENT AND SUBSEQUENT TAIL ROTOR REPLACMENT AND BALANCING CURED PROBLEM.  (X)				1	G	7	1 	4U				H1SW    					 
1997112000743	19971120	00743	CE  	1997	11	20	97ZZZX4826       	1	19971028	G	2435		BEARING         			CESSNA	525   	525         	2076601	CE  										START/GEN	FAILED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	09	31SG	100  				5250207				PILOT REPORTED RT GENERATOR FAILURE.  UPON INITIAL INSPECTION, THE RT STARTER/GENERATOR HAD A STRONG BURNT SMELL.  AFTER	 FURTHER INSPECTION, DISCOVERED THE ARMATURE SUPPORT BEARING HAD FAILED AND PIECES OF THE BEARING CAGE HAD SHORTED THE S	TARTER/GENERATOR COMPONENTS.				1	L	7	2 	4F			RT	A1WI    					 
1997112000744	19971120	00744	CE  	1997	11	20	97ZZZX4827       	1	19971030	G	2742	45AS61023137	ACTUATOR        			BEECH 	MU300 	400A        	1155402	CE  										PITCH TRIM	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	197PF	59   			970704	RK33				THE PILOT REPORTED THE PITCH TRIM ACTUATOR FAILED IN THE STANDBY MODE.  AIRCRAFT SYSTEMS WERE CHECKED AND FOUND TO BE OK	.  REPLACED THE PITCH TRIM ACTUATOR WITH A NEW UNIT.  SUBMITTER STATED THIS IS THE 4TH ACTUATOR TO BE INSTALLED SINCE JA	NUARY, 1997.  THE AUTOPILOT SYSTEM OF THE AIRCRAFT OPERATES THROUGH THE STANDBY MOTOR ON THIS ACTUATOR; THUS, AFFECTING 	THE OPERATION OF THE AIRCRAFT.  AIRCRAFT TOTAL TIME:  2,261.1 HOURS.			2	H	7	2 	4F			RT	A16SW   					 
1997112000745	19971120	00745	EU  	1997	11	20	97ZZZX4828       	1	19971017	G	2450	724440250AV2	TERMINAL BLOCK  			BRAERO	DH125 	BAE125800A  	1500285	EU  										ELECT PANEL	OVERHEATED      	D				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			GL	07	526M	5097 				258032				AFTER FINDING OUT ABOUT THE PROBLEM THAT ANOTHER BAE125 HAD WITH TERMINAL STRIP, INSPECTED N526M AND FOUND TERMINAL STRI	P HM TO ALSO BE DISTORTED AND OVERHEATED.  THE TERMINAL STRIP WAS REPLACED WITH A NEW ONE AND 6 WIRES HAD TERMINALS REPL	ACED THAT WERE ALSO OVERHEATED.				2	L	7	2 	4F			RT	A3EU    					 
1997112000747	19971120	00747	NE  	1997	11	20	97ZZZX4830       	2	19971005	G	7412	103832251	EXCITER         			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 1 ENGINE	FAILED          	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	118LF	869  			95284159	7137	LE45135E			IGNITION EXCITER UNIT INOPERATIVE.  FAILED TO IGNITE ENGINE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U		H13EU   	E5NE				 
1997112000748	19971120	00748	EU  	1997	11	20	97ZZZX4831       	1	19971019	G	7170	0174078010	VALVE           			AEROSP	SA365 	SA365N1     	8680668	EU  										START DRAIN	LEAKS           	B			KY1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	38MD	831  			C187B	6335				DRAIN VALVE LEAKS AT SEAMS.						1	G	7	2 	3U				H10EU   					 
1997112000749	19971120	00749	EU  	1997	11	20	97ZZZX4832       	1	19970821	G	6320	4638302024	BEARING         			BOLKMS	105   	BO105CBS    	5626008	EU  										M/R GEARBOX	SPALLED         	B			EOPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	492HL				4105	S803				TRANSMISSION RECEIVED FOR METAL IN OIL.  INSPECTION REVEALED NOTHING ABNORMAL EXCEPT LT INPUT PINION AND 4638-302-024 BE	ARING HAD A FEW SLIGHT DENTS OR MARKS IN ROLLERS AND ROLLER PATH ON PINION.  BEARING WAS CUT APART AND THE OUTER RACE WA	S FOUND VERY SPALLED.  REPAIRED TRANSMISSION.  REPLACED BEARING.				1	G	7	2 	3U			NC	H3EU    					 
1997112600104	19971126	00104	NE  	1997	11	26	97ZZZX4837       	1	19971105	G	7120	698609	STABILIZER RING 			SKRSKY	S64   	S64A        	8142504	NE  										RING TO FLANGE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										STABILIZER RING ATTACHES THE REAR SUPPORT SYSTEM TO THE FREE TURBINE ASSEMBLY.  IT IS NOT AN ENGINE MOUNT BUT A DAMPER M	OUNT.  THIS PART WAS FOUND CRACKED AT ONE OF THE RING TO FLANGE TRANSITION POINTS.  THE CRACK GOES FROM ONE SIDE OF THE 	RING TO THE OTHER, AND EXTENDS APPROXIMATELY 0.500 INCH ON EACH SIDE.  THIS DEFECT WAS FOUND DURING FLUORESCENT PENETRAN	T INSPECTION (FPI).  PART DOES NOT HAVE A FINITE LIFE.  THE CRACK WAS DETECTED VISUALLY.			2	G	7	2 	4U				H1EA    					 
1997112600105	19971126	00105	CE  	1997	11	26	97ZZZX4838       	1	19971023	G	2913		LEE PLUG        			CESSNA	210   	210C        	2073412	CE  										HYD PWR PACK	MISSING         	B	L		NA3R	O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			WP	11	3670Y	3839 	13   			21058170				THE HYDRAULIC POWER PACK FAILED WHEN PILOT ATTEMPTED TO EXTEND LANDING GEAR.  THE HYDRAULIC POWER PACK LOST ALL PRESSURE	 AND DUMPED HYDRAULIC FLUID OUT THE BACK.  THE AIRCRAFT LANDED GEAR UP.  SENT HYDRAULIC POWER PACK TO THE COMPANY THAT O	VERHAULED UNIT IN 1994.  THIS COMPANY'S EVALUATION OF THE POWER PACK'S FAILURE WAS DUE TO A MISSING LEE PLUG AND STATED 	THE LEE PLUG HOLE IS OVERSIZED AND WILL NOT HOLD WHEN PRESSURE IS APPLIED.			1	H	7	1 	3O				3A21    					 
1997112600106	19971126	00106		1997	11	26	97ZZZX4839       	3	19971107	G	6112	RA12884	DEICE BOOT      	RAPCO       		BEECH 	80    	65B80       	1152812	CE  										NR 2 PROP WIRES	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	110BA	1345 				LD279				DEICE BOOT LEAD BREAKS 12 INCHES FROM TERMINALS AFTER FOLLOWING NEW INSTALLATION SUGGESTIONS.						1	L	7	2 	3O				3A20    					 
1997112600107	19971126	00107		1997	11	26	97ZZZX4840       	3	19971003	G	6112	RA12884	DEICE BOOT      	RAPCO       		BEECH 	80    	65B80       	1152812	CE  										NR 1 PROP WIRES	FAILED          	C	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	107BA	540  				LD358				DEICE BOOT LEADS ARE CONTINUING TO BREAK APPROXIMATELY 12 INCHES FROM THE TERMINALS EVEN AFTER RAPCO'S NEW INSTALLATION 	SUGGESTIONS.					1	L	7	2 	3O				3A20    					 
1997112600108	19971126	00108	SO  	1997	11	26	97ZZZX4841       	1	19971016	G	2750	6273800	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP CONTROL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	16JP	5000 				2825956				CRACKS AT CORNER RADIUS OF ATTACH FLANGE ON FLAP HANDLE SUPPORT BRACKET.						1	L	7	1 	3O				2A13    					 
1997112600109	19971126	00109	SO  	1997	11	26	97ZZZX4842       	2	19971028	G	7322	63291611	FUEL METERING   			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE FUEL	OBSTRUCTED      	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NM	04	118BH		183  		C109311AR	340A0003	290962			PILOT NOTED REDUCED FUEL FLOW AND SOME POWER LOSS ON CLIMB-OUT.  RETURNED TO AIRPORT.  INVESTIGATION FOUND .3750 INCH LO	NG BY .1250 INCH WIDE PIECE OF FERROUS MATERIAL LODGED IN FUEL METERING UNIT DOWNSTREAM OF INLET SCREEN RESTRICTING FUEL	 FLOW.  OBJECT SENT TO TCM ANALYZATION LAB.  SOURCE OF OBJECT DETERMINED TO HAVE ORIGINATED FROM CLEANING BATH POROUS ME	DIA.			1	L	7	2 	3O	3	O		3A25    	E8CE				 
1997112600110	19971126	00110	GL  	1997	11	26	97ZZZX4843       	1	19971112	G	2823	FU560	SELECTOR VALVE  			AMTR  	LANCAR	LANCAIR     	05616TS	GL  										FUEL SELECTOR	MISMANUFACTURED 	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	477RM	12   				LIV060				POST-ACCIDENT INVESTIGATION BY THE NTSB DISCOVERED THE FUEL SELECTOR VALVE SUPPLIED BY THE KIT MANUFACTURER WAS FOUND MO	DIFIED FROM ORIGINAL DESIGN CONFIGURATION.  THE VALVE WAS MODIFIED BY A 'NON-MANUFACTURER SOURCE'.  THE CONFIGURATION OF	 THE VALVE WAS CHANGED FROM AN 'OFF/LEFT/RIGHT' OPERATION TO A 'OFF/BOTH/LEFT/RIGHT' MODE OF OPERATION.  THE KIT MANUFAC	TURER DOES NOT RECOMMEND A 'BOTH' POSITION FOR THESE AIRCRAFT.  TESTS SHOWED WHEN ONE FUEL TANK WAS EMPTY AND THE OPPOSI	TE TANK WAS BEING USED, THE SUBJECT VALVE WOULD ALLOW AIR FROM THE EMPTY TANK TO BE DRAWN INTO THE FUEL SYSTEM; THUS, CA	USING OVERLY LEAN MIXTURES AND/OR INTERRUPTION IN FUEL FLOW.	1	L	7	1 	3O			RT	EXPA1L71					 
1997112600111	19971126	00111	CE  	1997	11	26	97ZZZX4844       	1	19971110	G	5312	05132823	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										LT FWD DOOR POST	CRACKED         	B			DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	734UC	8613 				17269116				INSPECTION REVEALED A CRACK APPROXIMATELY 1.1250 INCHES LONG ON THE LT AFT SECTION OF THE FORWARD DOOR POST.  CRACK STAR	TS ON THE REAR HOLE OF THE LOWER DOOR HINGE ATTACHMENT.  CRACK PROGRESSES EITHER SIDE FROM HOLE.					1	H	7	1 	3O			NT	3A12    					 
1997112600112	19971126	00112	CE  	1997	11	26	97ZZZX4845       	1	19971110	G	5312	051300634	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										LT FWD DOOR POST	CRACKED         	B			DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	734UC	8613 				17269116				INSPECTION REVEALED A CRACK APPROXIMATELY 1.1250 INCHES LONG ON THE LT AFT SECTION OF THE FORWARD DOOR POST.  CRACK STAR	TS ON THE REAR HOLE OF THE LOWER DOOR HINGE ATTACHMENT.  CRACK PROGRESSES EITHER SIDE FROM HOLE.					1	H	7	1 	3O			NT	3A12    					 
1997112600113	19971126	00113		1997	11	26	97ZZZX4846       	4	19971025	G	3416	5035P	ENCODER         			PIPER 	PA46  	PA46310P    	7104605	SO  										END SHAKE	HANG UP         	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	701TF					4608104				INCOMING INSPECTION, TWO CRITICAL SHAFTS IN THE MECHANISM HAD ZERO END SHAKE.  THE OVERHAUL MANUAL CALLS OUT A MINIMUM E	ND SHAKE OF .0020 INCH.  THE ZERO END SHAKE CONDITION IN SIMILAR INSTRUMENTS HAS CAUSED THE POINTERS TO HANG UP IN DESCE	NT AFTER A 1-1/2 HOUR COLD SOAK AT 35 DEGREES FAHRENHEIT.  THE FACTORY HAS INDICATED THAT AN END SHAKE OF .0004 INCH OR 	LESS WILL CAUSE POINTER HANG-UPS AFTER A COLD TEST.			1	L	7	1 	3O				A25SO   					 
1997112600114	19971126	00114	SO  	1997	11	26	97ZZZX4847       	1	19971027	G	7160	8547402	AIRBOX          			PIPER 	PA28  	PA28181     	7102807	SO  										INDUCTION AIR	CRACKED         	B			SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9258N	317  				2843014				DURING ANNUAL INSPECTION, FOUND INDUCTION AIRBOX  CRACKED.  CRACKS WERE IN CARBURETOR INLET VALVE PORTION OF BOX ON EITH	ER SIDE OF CARBURETOR ATTACHMENT ADAPTER.  SUSPECT CAUSE OF CRACKS IS EXCESSIVE SIDE LOADING OF DUCT THAT ATTACHES AIRBO	X TO THE AIR INLET ON LEFT SIDE OF COWLING.  IF DUCT ATTACHMENT AT COWL WAS PLACED AT A BETTER ANGLE, THE SIDE LOAD WOUL	D BE REDUCED.  IN ORDER TO DRAIN THE CARBURETOR BOWL, THE AIRBOX MUST BE REMOVED FROM THE CARBURETOR.  ALSO, THE SUPPORT	 CLAMP FOR THE CARBURETOR HEAT CONTROL CABLE CHAFES ONE OF THE ENGINE MOUNT TUBES.  A RE-ROUTED LONGER CONTROL CABLE SHO	ULD ELIMINATE CHAFE PROBLEM.	1	L	7	1 	3O				2A13    					 
1997112600115	19971126	00115	WP  	1997	11	26	97ZZZX4848       	1	19971113	G	2722	AN2616	BOLT            		59140665501 	DOUG  	DC9   	DC932       	3022066	WP  										RUD ACTUATOR	BENT            	B		A	MZ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	620NW				145	47533				DISCOVERED ON PRIMARY INSPECTION, 2 EACH BOLTS (DC9 IPC 27-20-8, FIG 2, IT 320), P/N AN26-16, SEVERELY BENT, PARTIALLY S	HEARED.  LINK (DC9 IPC 27-20-8, FIG 2, IT 345), P/N 3914065-3.  UPPER EAR BENT, LOWER EAR BROKEN WITH SECTION MISSING. U	NABLE TO LOCATE MISSING SECTION.				2	L	7	2 	4F				A6WE    					 
1997112600116	19971126	00116	WP  	1997	11	26	97ZZZX4849       	1	19971113	G	2722	39140653	LINK            			DOUG  	DC9   	DC932       	3022066	WP  										LOWER EAR	BROKEN          	B		A	MZ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	620NW				145	47533				DISCOVERED ON PRIMARY INSPECTION, 2 EACH BOLTS (DC9 IPC 27-20-8, FIG 2, IT 320), P/N AN26-16, SEVERELY BENT, PARTIALLY S	HEARED.  LINK (DC9 IPC 27-20-8, FIG 2, IT 345), P/N 3914065-3.  UPPER EAR BENT, LOWER EAR BROKEN WITH SECTION MISSING. U	NABLE TO LOCATE MISSING SECTION.				2	L	7	2 	4F				A6WE    					 
1997112600117	19971126	00117	NE  	1997	11	26	97ZZZX4850       	2	19971103	G	7314	0253231013	PUMP            			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					LT ENG FUEL	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	701NC	4878 	1577 		8680	LA55	PCE92163			LEFT ENGINE HIGH PRESSURE FUEL PUMP FAILED.  DISASSEMBLY REVEALED DRIVE COUPLER SPLINES WORN OUT ON PUMP.  OIL MISTING H	OLE PLUGGED, SPLINES RUNNING DRY.  THIS CONDITION CAN BE REVEALED BY PUSHING A PIPE CLEANER INTO PUMP DRAIN CAVITY.  RUS	T DEPOSITS INDICATE LACK OF LUBRICATION TO DRIVE COUPLER.  RECOMMEND PERIODIC INSPECTION OF PUMP DRAINS FOR THIS CONDITI	ON.			1	L	7	2 	4T	4	T		A31CE   	E4EA				 
1997112600118	19971126	00118	WP  	1997	11	26	97ZZZX4851       	2	19971104	G	7240		PLENUM          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					RT ENG	FAILED          	D	L	A		C				ABORTED TAKEOFF         				A	J		FLAME/FIRE                	WARNING INDICATION        		TO	TAKEOFF        	1			EA	17	400AC	9187 	850  			BE12	P27009			ENG FAILURE AT T/O.  CREW HEARD A LOUD POP, THE RT ENG ITT TEMP ROSE AND FLAMES FROM THE RT ENG.  UNABLE TO KILL THE ENG	 USING THE EMERG CUTOFF LEVER, LEVER WAS JAMMED.  THE ENG WAS SHUT DOWN USING THE FIREWALL SOV.  FIRE BOTTLE WAS DISCHAR	GED AND FIRE WAS PUT OUT.  THE LEFT ENG SECURED AND ACFT EVAC.  INSP REVEALED THAT THE PLENUM CASE BROKE OPEN RADIALLY T	OWARD THE TOP OF THE ENG.  THE OPENED PART WAS JAMMED BEHIND THE EMERG CUTOFF LEVER RENDERING IT INOP.  INSP OF THE PLEN	UM CASE SUGGESTS THAT A CRACK BEGAN AT THE POINT WHERE THE WELDS OF BLEED AIR, AND THE P3 BOSSES COME TOGETHER.  THE CRA	CK PROGRESSED TO WHERE THE PLENUM FAILED IN SUCH A WAY THAT THE SHEET METAL RIPPED OPEN TOTAL IS 24 INCHES.	1	L	7	2 	4T	4	T		A14CE   	E4WE				 
1997112600119	19971126	00119	SW  	1997	11	26	97ZZZX4852       	1	19971111	G	2913	PV304426	PUMP            	VICKERS     	MX534590C   	FRCHLD	SA227 	SA227DC     	3377521	SW  										RT ENG HYD	LEAKING         	B			VH2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	459DF		9    			DC803M				PILOT REPORTED HYDRAULIC LEAK RT ENGINE.  MECHANIC FOUND RT ENGINE HYDRAULIC PUMP LEAKING AT AFT END OF CASE.  PUMP REMO	VAL REVEALED THREE OF FOUR VALVE PLATE AND CONTROLS SUBASSEMBLY MOUNTING SCREWS SHEARED CAUSING LEAKAGE.					2	L	7	2 	4T			RT	A18SW   					 
1997112600276	19971126	00276	WP  	1997	11	26	97ZZZX4860       	1	19971003	G	5210	90210001	DOOR            			HUGHES	369   	369HS       	4470728	WP  										CABIN RT MAIN	DEPARTED        	D	L	A		O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			WP	09	831FG					830511S				DURING FLIGHT, THE RIGHT MAIN DOOR OPENED, THEN DEPARTED THE AIRCRAFT.  THE DOOR HINGES WERE MODIFIED BY THE INSTALLATIO	N OF QUICK REMOVAL DOOR HINGES STC SH2530 NM.  DISCOVERED DURING INSPECTION THAT THE LATCHING FEATURE USED WAS NOT PROPE	RLY ENGAGED ALLOWING THE DOOR TO DEPART THE HELICOPTER.  SUBMITTER STATED THE STC DOES NOT CONTAIN PRE-FLIGHT INFORMATIO	N FOR THE PILOT TO FOLLOW.  THE STC NEEDS TO BE REVISED TO INCORPORATE PILOT INFO.			1	G	7	1 	3U				H3WE    					 
1997112600277	19971126	00277	NE  	1997	11	26	97ZZZX4861       	2	19971023	G	7210	446746	BEARING         		758300      						PWA   	JT8   	JT8D217     	52053	NE  					N2 GEARBOX	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05		15446					708486			ENGINE REMOVED FROM SERVICE DUE TO IN-FLIGHT SHUT DOWN FOR LOW OIL PRESSURE.  DISASSEMBLY REVEALED FAILURE OF OIL PUMP D	RIVE GEAR FORWARD BEARING IN THE N2 GEARBOX.  CAUSE OF THE BEARING FAILURE IS UNDER INVESTIGATION BY GREENWICH.										4	F			E9NE				 
1997112600280	19971126	00280	NM  	1997	11	26	97ZZZX4864       	1	19971001	G	5730		PANEL           			BOEING	727   	72730       	1384008	NM  										LT WING NR 15	LEAKING         	H	L			A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	99	113					18935				DEFECT - IN-FLIGHT LEAK FROM LEFT WING.  FOUND 9 LOOSE FASTENERS ON INBOARD END OF FUEL ACCESS PANEL NR 15 ON LEFT WING.	  SUSPECT IMPROPER TORQUE OF FASTENERS DURING LAST HEAVY MAINTENANCE VISIT.  RE-TORQUED FASTENERS IAW BOEING MM 28-11-21	.  ADDITIONALLY, MARKED FASTENERS WITH ALIGNMENT MARKS TO AID VISUAL INSPECTION.  RE-FUELED AIRCRAFT.  NO FURTHER LEAKS 	NOTED.			2	L	7	3 	4F				A3WE    					 
1997112600281	19971126	00281	NE  	1997	11	26	97ZZZX4865       	2	19971007	G	7320	ACL102	ACTUATOR        			BOEING	107   	1072        	9420604	EA  	GE    	CT58  	CT581401    	30011	NE  					NR 1 ENGINE	MALFUNCTIONED   	B			CHIR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	P2CHD	1324 			027	2003				ENGINE WOULD BEEP UP, BUT NOT DOWN.  EMERG SYS WORKED AS REQUIRED.  FOUND THE SYS WOULD APPEAR TO WORK NORMALLY ON THE G	ROUND, BUT WOULD FAIL DURING RAPID CLTV INPUTS.  EVEN THE EMERGENCY SYSTEM FAILED TO BREAK IT FREE.  TAPPING THE UNIT WI	TH A SCREW DRIVER 'BROKE' THE SYSTEM FREE ALLOWING 'NORMAL'OPS.  REPLACED THE ACTUATOR.  RESUMED OPERATIONS.  TROUBLESHO	OTING FOUND THE ACTUATOR WAS 'SLOW' AND NOTICEABLY QUIETER THAN THE NORMALLY OPERATING NR 2 ENG ACTUATOR.  INSTALLED ACT	UATOR S/N 038; TT NEW.  THIS UNIT AT FIRST APPEARED TO WORK ALSO.  THEN IT TOO WOULD FAIL UNDER CLTV INPUT, QUIET AND SL	OW.	2	G	7	2 	4U	4	U		1H16    	1E3				 
1997120400222	19971204	00222	CE  	1997	12	4	97ZZZX4866       	1	19971006	G	7602	5038901021	CONTROL CABLE   			BEECH 	55    	95A55       	1152704	CE  										MIXTURE	BROKEN          	B			EBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	12CM	52   				TC300				RIGHT MIXTURE CABLE WORKING FINE AND SMOOTH.  MADE FLIGHT, ENGINE WOULD NOT SHUT DOWN.  FOUND CABLE BROKEN AT WELD JOINT	 ON ENGINE END UNDER SOLID SHEATH.  INSTALLED NEW CABLE.					1	L	7	2 	3O			 	3A16    					 
1997120400223	19971204	00223	CE  	1997	12	4	97ZZZX4867       	1	19971010	G	2434	DOFF10300J	ALTERNATOR      	FORD        		BEECH 	23    	C24R        	1151254	CE  										DC SYSTEM	FAILED          	B			NV2R	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CE	07	23993		227  		5090305	MC476				ALTERNATOR FAILED IN IMC.  AIRCRAFT WAS LANDED GEAR UP.  SUBSTANTIAL DAMAGE.  NO INJURIES.  INSTALLED NEW ALTERNATOR.  O	PS CHECKED OK.  FAILED ALTERNATOR OVERHAUL. ON 11-15-96.  INSTALLED 5-19-97.					1	L	7	1 	3O				A1CE    					 
1997120400224	19971204	00224	GL  	1997	12	4	97ZZZX4868       	3	19971111	G	6114	D4885C61	HUB             			CESSNA	337   	337C        	2075712	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	NR 2 SOCKET	CRACKED         	A		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2543S				683261	3370843		683261		A CRACK WAS FOUND IN THE REAR OF BLADE SOCKET NR 2 DURING A DYE PENETRANT INSPECTION.  THE HUB WAS RED TAGGED AND RETIRE	D FROM SERVICE.  THE PROPELLER HAD BEEN IN SERVICE 3 YEARS SINCE LAST OVERHAUL AND AD 91-15-04 HAD BEEN C/W AT THAT TIME	.				1	H	7	2 	3O				A6CE    		5	C	P5EA	 
1997120400225	19971204	00225	CE  	1997	12	4	97ZZZX4869       	1	19971016	G	3234	MS25126E	SWITCH          			CESSNA	340   	340CESSNA   	2076404	CE  										GEAR SELECT	FAILED          	B			BXSR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	09	340JE	5304 				3400046				LANDING GEAR WOULD NOT EXTEND WHEN GEAR DOWN WAS SELECTED.  GEAR WAS MANUALLY EXTENDED WITH NO PROBLEM.  TROUBLESHOT AND	 FOUND THE GEAR POSITION SELECTOR SWITCH WOULD REMAIN OPEN IN THE DOWN POSITION.  SWITCH REPLACED.					1	L	7	2 	3O				3A25    					 
1997120400226	19971204	00226	EA  	1997	12	4	97ZZZX4870       	2	19971101	G	8520		CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 2 CYL BOSS	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	3525B		1440 			317952121	L397661A			DURING TROUBLESHOOTING OF OIL LEAK, A CRACK IN THE ENGINE CASE WAS DISCOVERED.  CRACK RUNS FROM LIFTER OIL GALLEY 1 INCH	 FORWARD OF AND ABOVE NR 2 CYLINDER BOSS TO 9 O'CLOCK POSITION ON CYLINDER BOSS HOLE.  A SECOND CRACK INSIDE THE CASE PA	RALLELS THE OUTER CASE CRACK EXCEPT IT STARTS AT THE UPPER FORWARD CYLINDER BASE STUD IN THE 11 O'CLOCK POSITION.  THE T	WO THRU-BOLTS AT REAR OF NR 2 CYLINDER WERE ALSO LOOSE IN THE CASE.  CYLINDER NUTS WERE TIGHT.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997120400227	19971204	00227	GL  	1997	12	4	97ZZZX4871       	3	19970930	G	6114		HUB             			CESSNA	210   	210C        	2073412	CE  						MCAULY	2A34C	D2A34C49    	GL  	MT FLANGE	CRACKED         	B			RC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	3674Y		886  			21058174		757098		PROPELLER INSPECTION FOUND 2 CRACKS DURING DYE PENETRANT INSPECTION.  CRACKS APPEAR TO BEGIN FROM STUD HOLE AND PROGRESS	 OVER THE EDGE TO HUB MOUNTING FLANGE SURFACE.					1	H	7	1 	3O				3A21    		5	C	P3EA	 
1997120400228	19971204	00228	SO  	1997	12	4	97ZZZX4872       	2	19971101	G	7414	M3081	POINTS          	SLICK       		CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  					MAG	WEAK            	B			FE6R	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			NM	11	42818	613  			6210	18259203	1919918R			FOUND POINTS WITH VERY LOW SPRING TENSION.  CAUSED ENGINE TO RUN ROUGH AND QUIT IN FLIGHT AT HIGHER RPM'S.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997120400229	19971204	00229	GL  	1997	12	4	97ZZZX4873       	3	19970805	G	6114	C98	HUB             			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 1 SOCKET	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		800  				18802473T		921076		PROPELLER IN FOR RESEAL AND A CRACK WAS FOUND IN THE BLADE RETENTION THREADS OF NR 1 HUB SOCKET.  THE CRACK HAD NOT YET 	GONE THROUGH THE HUB TO THE OUTSIDE.					1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997120400230	19971204	00230	SO  	1997	12	4	97ZZZX4874       	1	19971119	G	2140		COMBUSTION LINER	JANITROL    	65D793      	PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	4108D		486  		8813071F	318352018				HEATER FAILED PRESSURE DECAY TEST.  UPON REMOVAL, CRACK WAS NOTED IN COMBUSTION LINER.						1	L	7	2 	3O				A20SO   					 
1997120400231	19971204	00231		1997	12	4	97ZZZX4875       	4	19971112	G	6122	B20897	TOP COVER       	MCAULY      	C290D3T23   															PROP GOVERNOR	FAILED          	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					8860617					UPON INSPECTION OF GOVERNOR, TOP COVER WAS FOUND COMPLETELY BROKEN OFF.  NEW TOP COVER WAS INSTALLED AND DEFECTIVE COVER	 WAS SCRAPPED.																		 
1997120400232	19971204	00232		1997	12	4	97ZZZX4876       	4	19971106	G	6122		DRIVE GEAR      		D210680     	BEECH 	35    	35BEECH     	1151502	CE  											CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1748420KMY					INSPECTION FOUND GOVERNOR DRIVE GEAR CRACKED.  INDICATION STARTED BETWEEN TEETH AND EXTENDED AROUND CORNER.						1	L	7	1 	3O				A777    					 
1997120400233	19971204	00233	GL  	1997	12	4	97ZZZX4877       	3	19971106	G	6114		HUB ARM         			PIPER 	PA23  	PA23160     	7102304	SO  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17			633  					K2861N		INSPECTION FOUND CRACK ON OUTSIDE RADIUS OF NR 1 HUB ARM APPROXIMATELY 1 INCH LONG.						1	L	7	2 	3O				1A10    		5	C	P23EA	 
1997120400234	19971204	00234	EA  	1997	12	4	97ZZZX4878       	2	19971113	G	7414	10349234	DISTRIBUTOR GEAR		S4LN1227    	PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENG LT MAG	FAILED          	B			UC2R	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	19	40024	2515 	519  		A181618	28R7737128	L17006651A			PILOT REPORTED ENGINE RUNNING VERY ROUGH DURING ROUTINE TRAINING FLIGHT.  THE AIRCRAFT RETURNED TO THE AIRPORT AND MADE 	AN UNEVENTFUL LANDING.  AN INSPECTION OF THE LEFT MAGNETO WAS PERFORMED AND THE DISTRIBUTOR GEAR WAS FOUND TO HAVE SEVER	AL MISSING TEETH AND WAS BROKEN INTO THREE SEPARATE PIECES.				1	L	7	1 	3O	3	O		2A13    	1E10				 
1997120400235	19971204	00235	EA  	1997	12	4	97ZZZX4879       	2	19971108	G	8530	LW13623	PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER NR 1	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	64874	985  				15281457	L1510615			INSPECTION FOUND HALF OF PISTON SKIRT BROKEN AWAY AND MISSING FROM BOTTOM RING GROOVE TO JUST BEFORE EACH PISTON PIN BOS	S.  OWNER HAD REPORTED AN INCREASE IN OIL COMSUMPTION.  VISUAL INSPECTION OF ENGINE WAS OK.  CYLINDER COMP ALL CHECKED 7	0 OVER 80 OR BETTER.  OIL CHANGE WAS NOT DUE FOR ANOTHER 25 HOURS.  BOTTOM SPARK PLUGS SHOWED ONLY VERY LITTLE OIL DAMPN	ESS ON CYLINDER NR 1.  HOWEVER, A 'POP' COULD BE HEARD DURING THE COMP CHECK OF CYLINDER NR 1 JUST AS THE PISTON PAST TD	C (IT SOUNDED SIMILAR TO THE MAG IMPULSE).  FURTHER CHECKS FOUND THE OIL QUICK DRAIN HARD TO OPERATE (PLUGGED WITH DEBRI	S) AND, OF COURSE, THE OIL FILTER CONTAMINATED.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997120400236	19971204	00236	CE  	1997	12	4	97ZZZX4880       	1	19971118	G	7120		MOUNT           			CESSNA	206   	TU206G      	2073357	CE  										ENGINE SHOCK	FAILED          	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	61DW					620604257				FORWARD ENGINE SHOCK MOUNTS FLATTENED CAUSING OIL TEMPERATURES TO INCREASE.  INSTALLED NEW ENGINE SHOCK MOUNTS WHICH RAI	SED OIL COOLER INTO PROPER AIR STREAM FOR BETTER COOLING.					1	H	7	1 	3O				A4CE    					 
1997120400237	19971204	00237	GL  	1997	12	4	97ZZZX4881       	3	19970930	G	6111	S90A	BLADE           			CESSNA	210   	210C        	2073412	CE  						MCAULY	2A34C	D2A34C49    	GL  	RETAIN THREAD	CRACKED         	B	S		RC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	3674Y		886  		C437YS	21058174		757098		CRACK FOUND DURING PROPELLER DYE PENETRANT INSPECTION.  CRACK PRESENT IN RETENTION THREAD.						1	H	7	1 	3O				3A21    		5	C	P3EA	 
1997120400238	19971204	00238	CE  	1997	12	4	97ZZZX4882       	1	19971106	G	2430	A7002C7	RELAY           			CESSNA	206   	U206G       	2073356	CE  										GEN REV CUR	SHORTED         	B			RF1R	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SW	01	9959R				B77901	U20607000				GENERATOR WOULD NOT STAY ON LINE, FOUND REVERSE CURRENT RELAY FULL OF WATER WHICH SHORTED RELAY.  AIRCRAFT SAT OUTSIDE I	N HEAVY RAIN.  SUGGEST SEALING ELECTRICAL BOX WITH NEOPHRENE GASKET AND WIRE BUNDLE WITH SILICON.  THIS AIRCRAFT IS A SO	LOY CONVERSION.				1	H	7	1 	3O				A4CE    					 
1997120400239	19971204	00239	CE  	1997	12	4	97ZZZX4883       	1	19971119	G	2823		VALVE           			CESSNA	210   	T210N       	2073456	CE  										FUEL SELECTOR	DEFECTIVE       	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4891U	4177 				21064834				LEFT/RIGHT FUEL TANK NOT FEEDING ENGINE EQUALLY.  LT FUEL QUANTITY SLOWER TO EMPTY.  ACTING LIKE ONLY FEEDING FROM RT TA	NK.  FUEL RETURN PORTION OF FUEL SELECTOR INTERNALLY LEAKING CAUSING RETURN FUEL FLOW TO LT TANK ONLY.  RESEAL FUEL SELE	CTOR VALVE.				1	H	7	1 	3O				3A21    					 
1997120400240	19971204	00240	EU  	1997	12	4	97ZZZX4884       	1	19971009	G	2161	9599020134	VALVE           			PILATS	PC12  	PC12        	7090550	EU  										CABIN TEMP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	612PC	436  				146				PILOT REPORTED AIRCRAFT HAD NO HEAT.  TROUBLESHOT E.C.S. SYSTEM.  FOUND HEAT VALVE INOPERABLE.  WOULD NOT OPERATE IN AUT	O OR MANUAL MODES.  REPLACED VALVES.  OPS CHECKED GOOD.					1	L	7	1 	3T			RT	A78EU   					 
1997120400241	19971204	00241	EU  	1997	12	4	97ZZZX4885       	1	19970917	G	2161	9599020134	VALVE           			PILATS	PC12  	PC12        	7090550	EU  										CABIN TEMP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	1TC	1114 			1957676	130				PILOTS AND OWNERS REPORT THE COCKPIT AND CABIN ARE GETTING TOO HOT AND CANNOT CONTROL TEMPERATURE WITH THE E.C.S. IN AUT	OMODE AND THE MANUAL MODE.  VISUALLY INSPECTED TEMPERATURE CONTROL VALVE AND CANNOT SEE VALVE OPENING OR CLOSING.					1	L	7	1 	3T			RT	A78EU   					 
1997120400242	19971204	00242	CE  	1997	12	4	97ZZZX4886       	1	19971105	G	3230	08421201	LINKAGE         			CESSNA	310   	310N        	2074234	CE  										NLG RETRACT	FAILED          	G				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	03	500SH					310N0108				AFTER SELECTING GEAR DOWN ON APPROACH, PILOT NOTICED NOSE GEAR NOT DOWN AND LOCKED.  PILOT MADE SEVERAL ATTEMPTS, BUT GE	AR WAS JAMMED.  PILOT LANDED, NOSE GEAR COLLAPSED.  MINOR DAMAGE TO AIRCRAFT.  NO INJURIES TO PILOT.  MAINTENANCE INSPEC	TION REVEALED THE NOSE GEAR MAY HAVE BEEN RIGGED IMPROPERLY OR GEAR LINKAGE FAILED DUE TO PRIOR HARD LANDINGS.				1	L	7	2 	3O				3A10    					 
1997120400243	19971204	00243	CE  	1997	12	4	97ZZZX4887       	1	19971010	G	2750		PULLEY          			CESSNA	401   	401         	207590C	CE  										FLAP	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	31DB					4010202				ON 100-HOUR INPSPECTION, FOUND FLAP PULLEY ON ACTUATOR CABLE (RETURN CABLE) UNDER AND AFT OF BATTERY BOX FAILED.  CENTER	 BEARING HAD FROZEN DUE TO BATTERY ACID LEAKING FROM BROKEN DRAIN LINE.  WHEN BEARING FROZE, IT BROKE LOOSE FROM PULLEY 	AND PULLEY WAS ROTATING ON OUTER BEARING RACK.  SUBMITTER SUGGESTS CLOSE INSPECTION OF THIS AREA DURING INSPECTIONS.				1	L	7	2 	3O				A7CE    					 
1997120400244	19971204	00244	SO  	1997	12	4	97ZZZX4888       	1	19971111	G	3213	40327000	HOUSING         			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	CRACKED         	E	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	38KC					318352033				FOUND RIGHT MAIN LANDING GEAR HOUSING CRACKED.  CRACK ORIGINATED UNDER CLAMP WHICH ATTACHED BRAKE LINE GUARD TO HOUSING.	  CRACK WAS APPROXIMATELY 1 INCH AND BEGAN BELOW CASTING MARK ON AFT SIDE OF STRUT.					1	L	7	2 	3O				A20SO   					 
1997120400245	19971204	00245	CE  	1997	12	4	97ZZZX4889       	1	19971024	G	2710	0510105322	CONTROL CABLE   			CESSNA	185   	185F        	2072820	CE  										AILERON	FRAYED          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4952E	1573 				18503918				CABLES (ALL 3) WERE FRAYED ON FUSELAGE 90 DEGREE PULLEYS.  THE AIRCRAFT HAD BEEN TREATED INTERNALLY WITH 'THERMAL GARD'.	 THE TREATMENT WAS FOR ANTI-CORROSION.  THE TREATMENT FORMED A SMOOTH BARRIER THAT MADE VISUAL INSPECTION LOOK OK.  CLEA	NING CABLES WITH SOLVENT AND CLOTH RAGS REVEALED MANY BROKEN STRANDS.				1	H	7	1 	3O			 	3A24    					 
1997013000336	19970130	00336	CE  	1997	1	30	97ZZZX489        	1	19970109	G	7170	10138901165	CHECK VALVE     			BEECH 	90    	C90A        	1152911	CE  										LT FUEL PURGE	CONTAMINATED    	D		A		O	A			OTHER                   	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			GL	03	40MH	1313 				LJ1258				ON TAKEOFF, ACFT FILLED WITH SMOKE AND FUEL ODOR.  PILOT SHUT FLOW PACKS OFF AND A/C CLEARED.  NORMAL LANDING.  INVESTIG	ATED AND FOUND LT FUEL PURGE TANK CHECK VALVE CONTAMINATED.  CLEANED CHECK VALVE AND TEST FLIGHT WAS NORMAL.  SUBMITTER 	RECOMMENDS THAT CHECK VALVES BE ADDED TO THE 12 MO PURGE TANK FILTER INSPECTION ON ALL KING AIRS.				1	L	7	2 	3T			RT	3A20    					 
1997120400246	19971204	00246	CE  	1997	12	4	97ZZZX4890       	1	19971024	G	2710	0510105113	CONTROL CABLE   			CESSNA	185   	185F        	2072820	CE  										AILERON	FRAYED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4952E	1573 				18503918				CABLES (ALL 3) WERE FRAYED ON FUSELAGE 90 DEGREE PULLEYS.  THE AIRCRAFT HAD BEEN TREATED INTERNALLY WITH 'THERMAL GARD'.	 THE TREATMENT WAS FOR ANTI-CORROSION.  THE TREATMENT FORMED A SMOOTH BARRIER THAT MADE VISUAL INSPECTION LOOK OK.  CLEA	NING CABLES WITH SOLVENT AND CLOTH RAGS REVEALED MANY BROKEN STRANDS.				1	H	7	1 	3O			 	3A24    					 
1997120400247	19971204	00247	SO  	1997	12	4	97ZZZX4891       	2	19971103	G	8520		CONNECTING ROD  			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 6 CYLINDER	FAILED          	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			CE	03	747PB	622  				414A1006	R800589			PILOT REPORTED NR 2 ENGINE BEGAN RUNNING ROUGH, THEN FAILED TOTALLY.  SUCCESSFUL SINGLE ENGINE LANDING AT SUS.  REMOVED 	COWLING, FOUND NR 6 CYLINDER CONNECTING ROD FAILED WHICH PENETRATED CRANKCASE DESTROYING ENGINE.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997120400248	19971204	00248		1997	12	4	97ZZZX4892       	4	19971008	G	2561	ACRL81A	BATTERY         	EAAEROMARINE																LIFE VEST	SWOLLEN         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										THE LAST 15 VESTS INSPECTED HAVE HAD BAD LIGHTS (SWOLLEN BATTERIES).  ALL OF THE LIGHTS ARE FROM THE SAME BATCH MAR 97 A	ND ARE ONLY 6 MONTHS FROM DATE OF MANUFACTURE.  SUBMITTER STATED BATTERIES FROM OCT 96 ARE ALL FINE, IT JUST SEEMS TO BE	 A BATCH PROBLEM.																	 
1997120400249	19971204	00249	GL  	1997	12	4	97ZZZX4893       	3	19971029	G	6111	C1301	CLAMP           			MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP NR 3 BLADE	CRACKED         	G	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	21CJ	4642 	2493 		EJ2394	789SA		CDA3007		INSPECTION REPORT CONDUCTED BY HARTZELL PROPELLER INC., REVEALED CRACK IN PROPELLER BLADE CLAMP.  SUSPECT CAUSE OF CRACK	 DUE TO FATIGUE.					1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
1997120400250	19971204	00250	GL  	1997	12	4	97ZZZX4894       	3	19971029	G	6111	C1301	CLAMP           			MTSBSI	MU2   	MU2B60      	5780460	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROP NR 4 BLADE	CRACKED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	21CJ	4642 	2493 			789SA		CDA3007		INSPECTION REPORT CONDUCTED BY HARTZELL PROPELLER INC., REVEALED CRACK IN PROPELLER BLADE CLAMP.  SUSPECT CAUSE OF CRACK	 DUE TO FATIGUE.					1	H	7	2 	3T			RT	A10SW   		6	C	P40EA	 
1997120400251	19971204	00251	NE  	1997	12	4	97ZZZX4895       	2	19971113	G	7210	103019501	LOCKCUP         		103035012   	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					OUTPUT GEARBOX	CRACKED         	B			ZP3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	58HJ		1745 		2291	30314	LE07520C			FOLLOWING DISASSEMBLY OF ENGINE FOR METAL CONTAMINATION, DISCOVERED 2 EACH OF THE LOCKCUPS HAD FAILED.  CUPS CRACKED AND	 SPLIT AT THE LOCKING TANGS WHICH ENGAGE THE PLANETARY GEARSHAFTS.  THE RETAINING NUTS WHICH THE LOCKCUPS RETAIN, REMAIN	ED IN PLACE AND THE PIECES OF THE LOCKCUPS WERE FOUND IN THE SCAVENGE SCREEN OF THE ACCESSORY DRIVE GEARBOX AND LAYING I	N THE OUTPUT REDUCTION GEARBOX.			1	G	7	1 	4U	4	U		H1SW    	E17EA				 
1997120400496	19971204	00496	EU  	1997	12	4	97ZZZX4896       	1	19971008	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										T/R	ERODED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5352Y	961  			572	S781				PAINT PEELING AT LEADING EDGE ERODED INTO POLY STRIP AND FIBERGLASS WEBBING.  THESE TWO BLADES REPAIRED JUNE 18, 1997. T	OTAL TIME ON BLADES 647.9 HOURS.					1	G	7	2 	3U				H3EU    					 
1997120400497	19971204	00497	EU  	1997	12	4	97ZZZX4897       	1	19971008	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										T/R	ERODED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5352Y	961  			574	S781				PAINT PEELING AT LEADING EDGE ERODED INTO POLY STRIP AND FIBERGLASS WEBBING.  THESE TWO BLADES REPAIRED JUNE 18, 1997. T	OTAL TIME ON BLADES 647.9 HOURS.					1	G	7	2 	3U				H3EU    					 
1997120400500	19971204	00500	SW  	1997	12	4	97ZZZX4900       	1	19970930	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL					53044				DAILY INSPECTION AND C/W NOTAM NR 51A-97, FOUND DISC CRACKED.  ON NR 7 DISC ASSEMBLY, NR 7 DISC OF THE PACK - 1 DISC ONL	Y.					1	G	7	1 	3U			O	H2SW    					 
1997120400501	19971204	00501	SW  	1997	12	4	97ZZZX4901       	1	19971014	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R D/S COUPLING	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL					53044				DAILY INSPECTION FOUND NR 7 TAIL ROTOR DRIVESHAFT COUPLING, NR 10 DISC ON PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997120400502	19971204	00502	SW  	1997	12	4	97ZZZX4902       	1	19970930	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										NR 7 T/R CPLNG	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL					53054				DAILY CHECK NOTAM 51A-97 OCCURRED DURING NORMAL FLIGHT, FOUND NR 7 COUPLING CRACKED 2 LAMINATES NR 1 AND NR 2 PACK HAS T	EN DISCS.					1	G	7	1 	3U			O	H2SW    					 
1997120400503	19971204	00503	SW  	1997	12	4	97ZZZX4903       	1	19970930	G	6322	406040339105	BEARING         		406040320101	BELL  	407   	407         		SW  										T/R DRIVE	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	634  			960711	53054				NR 2 SHAFT REMOVED FROM AIRCRAFT DUE TO ROUGH BEARING.  FOUND BEARING 406-040-339-105 INSTALLED AT AIRCRAFT HOURS 808.0 	HOURS ROUGH.  ALSO, SHAFT 406-040-320-101, TT 1410.8 HOURS.  FORWARD SPLINES WORN AND CORRODED BEYOND LIMITS.					1	G	7	1 	3U			O	H2SW    					 
1997120400504	19971204	00504	SW  	1997	12	4	97ZZZX4904       	1	19971102	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R SHAFT	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				ON 50-HOUR P.M.I., AND AD 97-22-15, FOUND NR 10 OF 10 DISC CRACKED IN 2 PLACES.						1	G	7	1 	3U			O	H2SW    					 
1997120400505	19971204	00505	SW  	1997	12	4	97ZZZX4905       	1	19970909	G	6510	406040340101	DISC            		407040302101	BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				DURING DAILY INSPECTION, FOUND T/R DRIVE DISC HAS CRACK STARTING ON INSIDE DIAMETER GOING TOWARDS OUTSIDE DIAMETER, NR 1	 DISC (FIRST ON PACK).					1	G	7	1 	3U			O	H2SW    					 
1997120400506	19971204	00506	SW  	1997	12	4	97ZZZX4906       	1	19970930	G	6500	406017113101	MAST NUT        		407012100101	BELL  	407   	407         		SW  										T/R	LOOSE           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				DAILY INSPECTION FOUND COMPLETE LOSS OF TORQUE ON T/R MAST NUT.  THE NUT COULD BE REMOVED BY HAND.  THE SAFETY WIRE BETW	EEN THE NUT AND THE SUPPORT, (P/N 407-012-106-103) KEPT THE NUT FROM SPINNING OFF OF THE TAIL ROTOR GEARBOX OUTPUT SHAFT	.				1	G	7	1 	3U			O	H2SW    					 
1997120400507	19971204	00507	SW  	1997	12	4	97ZZZX4907       	1	19970924	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R DISC PACK	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				SCHEDULED INSPECTION FOUND DISC CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997120400509	19971204	00509	SW  	1997	12	4	97ZZZX4909       	1	19971023	G	6220	407010150101A	DAMPER ASSY     			BELL  	407   	407         		SW  										M/R	DETERIORATED    	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL	58   				53141				DAILY INSPECTION FOUND FRAHM DAMPER ASSY RUBBER DETERIORATING AND STICKING OUT OF DAMPER.						1	G	7	1 	3U			O	H2SW    					 
1997120400510	19971204	00510	SW  	1997	12	4	97ZZZX4910       	1	19971029	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R SHAFT	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				DURING 50-HOUR PMI AND MAINTENANCE NOTAM NR 51B-97, FOUND NR 1 DISC IN PACK ASSEMBLY OF 10 DISC TOTAL, CRACKED IN TWO PL	ACES.					1	G	7	1 	3U			O	H2SW    					 
1997120400511	19971204	00511	NE  	1997	12	4	97ZZZX4911       	1	19971013	G	3230	1945E72A02	JURY BRACE      		1945E175A02 	SKRSKY	S76   	S76A        	8143006	NE  										RT GEAR	FAILED          	B			ALGR	O	A			OTHER                   	UNSCHED LANDING         			J			WARNING INDICATION        			AP	APPROACH       	1			SW	03	741SW					760070				DURING LANDING CHECK, THE RIGHT MAIN LANDING GEAR FAILED TO LOCK DOWN.  AFTER RECYCLING THE LANDING GEAR, THE PROBLEM RE	MAINED.  RETURNED TO BASE.  FOUND RIGHT HAND JURY BRACE BROKEN.  REPLACED BRACE AND SWUNG GEAR.  OPS CHECK GOOD.  RETURN	ED TO SERVICE AT 1,745 HOURS.				1	G	7	2 	3U				H1NE    					 
1997120400512	19971204	00512	NM  	1997	12	4	97ZZZX4912       	1	19971101	G	7120	65187225	MOUNT           			BOEING	727   	727225      	1384077	NM  										NR 1 ENG FWD	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON NR 1 ENGINE FORWARD MOUNT.						2	L	7	3 	4F				A3WE    					 
1997120400513	19971204	00513	NM  	1997	12	4	97ZZZX4913       	1	19971101	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON S19R AT STA 1183.						2	L	7	3 	4F				A3WE    					 
1997120400514	19971204	00514	NM  	1997	12	4	97ZZZX4914       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 1070-1090	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT FRAME, STA 1070 TO STA 1090 AT S27L.						2	L	7	3 	4F				A3WE    					 
1997120400515	19971204	00515	NM  	1997	12	4	97ZZZX4915       	1	19971101	G	5315		FLOOR BEAM      			BOEING	727   	727225      	1384077	NM  										BS 344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR BEAM UPPER CHORD FROM LBL 55 TO RBL 42.						2	L	7	3 	4F				A3WE    					 
1997120400516	19971204	00516	NM  	1997	12	4	97ZZZX4916       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 344-480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN SEAT TRACK FROM STA 344 TO STA 480 AT LBL 45.						2	L	7	3 	4F				A3WE    					 
1997120400517	19971204	00517	NM  	1997	12	4	97ZZZX4917       	1	19971101	G	5330		SKIN            			BOEING	727   	727225      	1384077	NM  										BS 1150-1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON EXTERNAL SKIN, STA 1150 TO STA 1183 BETWEEN S14R AND S20R.						2	L	7	3 	4F				A3WE    					 
1997120400518	19971204	00518	NM  	1997	12	4	97ZZZX4918       	1	19971101	G	5315		FLOOR BEAM      			BOEING	727   	727225      	1384077	NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR BEAM STA 1130, OUTBOARD OF RBL 24.						2	L	7	3 	4F				A3WE    					 
1997120400519	19971204	00519	NM  	1997	12	4	97ZZZX4919       	1	19971101	G	5320		CHORD           			BOEING	727   	727225      	1384077	NM  										NLG BOX BS 328	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON RT SIDE NOSE GEAR BOX LOWER CHORD AT FLOOR WEB, STA 328 TO STA 344.						2	L	7	3 	4F				A3WE    					 
1997120400520	19971204	00520	NM  	1997	12	4	97ZZZX4920       	1	19971101	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 950-950A	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON S27R BETWEEN STA 950 AND STA 950A.						2	L	7	3 	4F				A3WE    					 
1997120400521	19971204	00521	NM  	1997	12	4	97ZZZX4921       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 990-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN SEAT TRACK AT LBL 24 FROM STA 990 TO STA 1030.						2	L	7	3 	4F				A3WE    					 
1997120400522	19971204	00522	NM  	1997	12	4	97ZZZX4922       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 344-480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION WAS NOTED ON CABIN SEAT TRACK AT LBL 24 FROM STA 344 TO STA 480.						2	L	7	3 	4F				A3WE    					 
1997120400523	19971204	00523	NM  	1997	12	4	97ZZZX4923       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 1000-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN LEFT HAND INBOARD SEAT TRACK FROM STA 1000 TO STA 1030.						2	L	7	3 	4F				A3WE    					 
1997120400524	19971204	00524	NM  	1997	12	4	97ZZZX4924       	1	19971101	G	5311		FRAME           			BOEING	727   	727225      	1384077	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON FRAME 1166 BETWEEN S27R AND S28R.						2	L	7	3 	4F				A3WE    					 
1997120400525	19971204	00525	NM  	1997	12	4	97ZZZX4925       	1	19971101	G	5315		FLOOR BEAM      			BOEING	727   	727225      	1384077	NM  										BS 380	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR BEAM UPPER CHORD AT STA 380 FROM RBL 20 TO RBL 45.						2	L	7	3 	4F				A3WE    					 
1997120400526	19971204	00526	NM  	1997	12	4	97ZZZX4926       	1	19971101	G	5510		BEAM            			BOEING	727   	727225      	1384077	NM  										HORIZ RT STAB TE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON RT HAND HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM CHORD.						2	L	7	3 	4F				A3WE    					 
1997120400527	19971204	00527	NM  	1997	12	4	97ZZZX4927       	1	19971101	G	5510		BEAM            			BOEING	727   	727225      	1384077	NM  										HORIZ LT STAB TE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON LEFT HAND HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM CHORD.						2	L	7	3 	4F				A3WE    					 
1997120400528	19971204	00528	NM  	1997	12	4	97ZZZX4928       	1	19971101	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 460-480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON S18R BETWEEN STA 460 AND STA 480.						2	L	7	3 	4F				A3WE    					 
1997120400529	19971204	00529	NM  	1997	12	4	97ZZZX4929       	1	19971101	G	5315		FLOOR BEAM      			BOEING	727   	727225      	1384077	NM  										BS 328	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON UPPER T-CHORD FLOOR BEAM STA 328 AT LBL 55.						2	L	7	3 	4F				A3WE    					 
1997120400530	19971204	00530	NM  	1997	12	4	97ZZZX4930       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 440-460	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT BETWEEN STA 440 - STA 460 AT RBL 12.						2	L	7	3 	4F				A3WE    					 
1997120400919	19971204	00919	SW  	1997	12	4	97ZZZX4933       	1	19971116	G	6520	4764521215	CASE            		476400751   	BELL  	47    	47G2A1      	1181014	SW  										T/R GEARBOX	CORRODED        	H	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	73953	2292 	831  		A133292	2866				WHILE TROUBLESHOOTING FOR A LOOSE TAIL ROTOR GUARD IN TAIL ROTOR GEARBOX HOUSING, PULLED THE GUARD OUT OF THE GEARBOX AN	D FOUND FERTILIZER PACKED INTO CAVITY.  WHILE SCRAPING FERTILIZER OUT OF CAVITY, FOUND CORROSION HAD EATEN THROUGH MAGNE	SIUM HOUSING.  THE PACKED FERTILIZER WAS KEEPING THE OIL FROM LEAKING OUT.				1	G	7	1 	3O				2H3     					 
1997120400920	19971204	00920	NE  	1997	12	4	97ZZZX4934       	2	19970924	G	7230	717623	FRONT HUB       								PWA   	JT8   	JT8D17      	52049	NE  					COMPRESSOR	CORRODED        	B			VF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					9V8439					FRONT HUB RECEIVED FOR SCHEDULED OVERHAUL.  PART INSPECTED PER INSP 01, JT8D ENGINE MANUAL 481672 SECTION 72-36-17.  TIE	-ROD, SHIELDING, AND COUNTERWEIGHT HOLES WERE FOUND WITH EXCESSIVE CORROSION AND PITTING.  PART TAGGED SCRAP AND RETURNE	D.									4	F			E2EA				 
1997120400921	19971204	00921	CE  	1997	12	4	97ZZZX4935       	1	19971031	G	2150		HOSE            			BEECH 	200   	A200        	1152921	CE  										AIR COND	MISINSTALLED    	G	L	A		B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	23	200NY	5    				BC25				ACFT MILES FROM DESTINATION WHEN CREW NOTICED CABIN TEMP WAS HIGH.  CABIN CONTROL WAS ON 'AUTO MODE'.  CHANGING TO 'MANU	AL MODE' AND TOGGLING DOWN TEMPERATURE RESULTED IN A LOUD POP OR BANG THOUGHT TO BE RAPID DECOMPRESSURIZATION.  A MIST F	ORMED IN THE CABIN, SMOKE ISSUED FROM OVERHEAD VENTS, AND STRONG OIL SMELL UPSET OCCUPANTS.  EMERGENCY DECLARED.  UNEVEN	TFUL LANDING ACCOMPLISHED.  FWD EVAPORATOR FOUND RUPTURED IN CAPILLARY/COOLING FIN AREA IN CENTER OF EVAPORATOR.  FURTHE	R INVEST FND AIR COND SUCTION AND DISCHARGE LINES INSTALLED REVERSED WHEN REPLACED WITH NEW 4.5 HRS PREVIOUSLY.  REPAIR 	STATION REPLACED HOSE, INSPECTOR DOUBLE INSPECTED.	1	L	7	2 	4T				A24CE   					 
1997120400922	19971204	00922	EU  	1997	12	4	97ZZZX4936       	1	19971120	G	2432	RG390E	BATTERY         			AMD   	FALC50	FALCON900   	2700160	EU  										DC SYSTEM	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	26LB	675  			CBC263178	51				BATTERY'S SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN IN-FLIGHT OR LANDING ABOUT 2 INCHES.  CONCORDE FAX SAID T	O PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE					2	L	7	3 	4F			RT	A46EU   					 
1997120400923	19971204	00923	EU  	1997	12	4	97ZZZX4937       	1	19971120	G	2432	RG390E	BATTERY         			AMD   	FALC50	FALCON900   	2700160	EU  										DC SYSTEM	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	26LB	675  			CBC263179	51				BATTERY'S SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN IN-FLIGHT OR LANDING ABOUT 2 INCHES.  CONCORDE FAX SAID T	O PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE					2	L	7	3 	4F			RT	A46EU   					 
1997120400924	19971204	00924	EU  	1997	12	4	97ZZZX4938       	1	19971120	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	461W				CBC262926	NA0461				BATTERY SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES.  CONCORDE FAX SAID TO PUSH SLEEVE UP AND TAPE BOT	TOM OF SLEEVE.					2	L	7	2 	4F			RT	A3EU    					 
1997120400925	19971204	00925	EU  	1997	12	4	97ZZZX4939       	1	19971120	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	461W				CBC262927	NA0461				BATTERY SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES.  CONCORDE FAX SAID TO PUSH SLEEVE UP AND TAPE BOT	TOM OF SLEEVE.					2	L	7	2 	4F			RT	A3EU    					 
1997013000341	19970130	00341	CE  	1997	1	30	97ZZZX494        	1	19970122	G	2741	509100501	SENSOR          			LEAR  	35    	35A         	5170602	CE  										STAB MACH TRIM	MISWIRED        	B		A	ESMR	O				OTHER                   				J	W		WARNING INDICATION        	INADEQUATE Q C            		CR	CRUISE         	1			SO	11	815L					142				CREW REPORTED MACH TRIM FAULT LIGHT AND WARNING TONE ABOVE .74 MACH.  REPLACED HORIZONTAL STABLIZER POSITION SENSOR PER 	LEARJET A.M.M.  PROBLEM RECURRED WITH ADDITION OF RAPID NOSE UP OR DOWN TRIM CHANGE ABOVE .69 MACH.  AFTER MUCH TROUBLES	HOOTING, FOUND NEW SENSOR WIRED 180 DEGREES OUT OF PHASE.  ANOTHER SENSOR CORRECTED THE PROBLEM.				2	L	7	2 	4F				A10CE   					 
1997120400926	19971204	00926	EU  	1997	12	4	97ZZZX4940       	1	19971120	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	74NP				CBC275940	NA0449				BATTERY'S SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN IN-FLIGHT OR LANDING ABOUT 2 INCHES.  CONCORDE FAX SAID T	O PUSH TO PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	2 	4F			RT	A3EU    					 
1997120400927	19971204	00927	EU  	1997	12	4	97ZZZX4941       	1	19971120	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	74NP				CBC275939	NA0449				BATTERY'S SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN IN-FLIGHT OR LANDING ABOUT 2 INCHES.  CONCORDE FAX SAID T	O PUSH SLEEVE UPA ND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	2 	4F			RT	A3EU    					 
1997120400928	19971204	00928	EU  	1997	12	4	97ZZZX4942       	1	19971121	G	2432	RG390E	BATTERY         			BRAERO	DH125 	HS125700A   	4230170	EU  										DC SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	810CR				CBC273784	NA0251				BATTERY SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES AND LEAKING.  CONCORDE FAX SAID TO PUSH SLEEVE UP 	AND TAPE BOTTOM OF SLEEVE.					2	L	7	2 	4F				A3EU    					 
1997120400929	19971204	00929	EU  	1997	12	4	97ZZZX4943       	1	19971121	G	2432	RG390E	BATTERY         			BRAERO	DH125 	HS125700A   	4230170	EU  										DC SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	571CH				CBC275865	NA0256				BATTERY SUPPORT SLEEVE ONTHE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES AND LEAKING.  CONCORDE FAX SAID TO PUSH SLEEVE UP A	ND TAPE BOTTOM OF SLEEVE.					2	L	7	2 	4F				A3EU    					 
1997120400930	19971204	00930	EU  	1997	12	4	97ZZZX4944       	1	19971121	G	2432	RG390E	BATTERY         			BRAERO	DH125 	HS125700A   	4230170	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	825CT				CBC275936	NA0229				BATTERY SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES.  CONCORDE FAX SAID TO PUSH SLEEVE UP AND TAPE BOT	TOM OF SLEEVE.					2	L	7	2 	4F				A3EU    					 
1997120400931	19971204	00931	EU  	1997	12	4	97ZZZX4945       	1	19971121	G	2432	RG390E	BATTERY         			BRAERO	DH125 	HS125700A   	4230170	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	825CT				CBC275939	NA0229				BATTERY SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES.  CONCORDE FAX SAID TO PUSH SLEEVE UP AND TAPE BOT	TOM OF SLEEVE.					2	L	7	2 	4F				A3EU    					 
1997120400932	19971204	00932	SO  	1997	12	4	97ZZZX4946       	1	19971118	G	3240	244667	CARRIER         	BFGOODRICH  	21585       	EMB   	120   	EMB120      	3260201	SO  										BRAKE NR 2	BROKEN          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	204SW	3578 			0500	120243				UPON DISASSEMBLY OF BRAKE NR 3, CARRIER AND LINING WERE FOUND BROKEN INTO THREE PIECES.  CARRIER LINING WAS A NEW PART I	NSTALLED AT LAST OVERHAUL.  NOTE:  BRAKE POSITION NR 2.					2	L	7	2 	4T			RT	A31SO   					 
1997120400933	19971204	00933	SO  	1997	12	4	97ZZZX4947       	1	19971118	G	3240	244677	CARRIER         	BFGOODRICH  	21585       	EMB   	120   	EMB120      	3260201	SO  										BRAKE NR 4	BROKEN          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		2085 			0070					UPON DISASSEMBLY OF BRAKE ASSEMBLY, NR 3 CARRIER AND LINING WERE FOUND BROKEN IN HALF.  CARRIER LINING WAS A NEW PART IN	STALLED AT LAST OVERHAUL.  BRAKE POSITION NR 4, EMB120.  BRAKE HOUSING STAMPED WITH INCORRECT TORQUE VALUE.  THERE HAVE 	BEEN NUMEROUS FAILURES OF THIS PART NUMBERED BRAKE.				2	L	7	2 	4T			RT	A31SO   					 
1997120400934	19971204	00934	GL  	1997	12	4	97ZZZX4948       	3	19971106	G	6110	13019S	CLAMP           			AIRTRC	AT500 	AT502       	0390303	SW  						HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					DD4974			BU471		INSPECTION FOUND PROPELLER CLAMP CRACKED AT BOLT HOLE.						1	L	7	1 	3T			NC	A9SW    		6	C	P15EA	 
1997120400935	19971204	00935	SO  	1997	12	4	97ZZZX4949       	2	19971101	G	8550		BYPASS SPRING   			CESSNA	210   	210         	2073402	CE  	CONT  	O520  	IO520L      	17032	SO  					OIL FILTER ADAPT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										OIL FILTER BYPASS SPRING FOUND BROKEN AND DISC FOUND UNDER ENGINE OIL PRESSURE VALVE.  ENGINE HAD NO OIL PRESSURE AFTER 	START-UP.  BYPASS DISC FOUND UNDER ENGINE OIL PRESSURE RELIEF VALVE PREVENTING ENGINE FROM DEVELOPING ANY PRESSURE.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE				 
1997013000342	19970130	00342	CE  	1997	1	30	97ZZZX495        	1	19970108	G	3230	030A387611	CASTING         			MTSBSI	MU2   	MU2B35      	5780411	CE  										MLG THRUST GR BX	EAR BROKEN      	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	92ST	6124 				610				AT 100 HR INSP, LANDING GEAR THRUST GEAR BOX CASTING MOUNT EAR WAS FOUND BROKEN AND MOUNT BOLTS LOOSE.  SUSPECT CAUSE TO	 BE SHIM SPACERS USED BETWEEN BOX AND AIRCRAFT STRUCTURE.  INSP OF OPPOSITE SIDE (RIGHT) REVEALED THAT MOUNT BOLTS WERE 	LOOSE ALSO.  SUBMITTER STATES OTHER MU 2 TECHNICIANS HAVE FOUND THIS CONDITION ON OTHER LONG BODY AGING MU 2'S.  SUBMITT	ER SUGGESTS THAT THESE BOX MOUNT BOLTS BE CHECKED AT 100 OR 150 HOUR INSPECTIONS.			1	H	7	2 	3T			RT	A10SW   					 
1997120400936	19971204	00936		1997	12	4	97ZZZX4950       	4	19971101	G	2561	SMV2102	LIFE VEST       	JCRIND      																CELL	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					1937					LIFE VEST FAILED THE MANUFACTURER'S 2-POUND PSI TEST.																			 
1997120400937	19971204	00937		1997	12	4	97ZZZX4951       	4	19971112	G	3416	10172001999	ALTIMETER       																	COCKPIT	STICKS          	B			JY2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	23					156258					UNIT WAS HANGING UP.  UNIT ALSO MADE A 400 FOOT 'JUMP' ON ASCENT.  THE ALTIMETER WAS 'CLOCKING' ABOVE 8,000 FEET.																			 
1997120400938	19971204	00938	EA  	1997	12	4	97ZZZX4952       	2	19971111	G	7322		NUT             			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					CARBURETOR MOUNT	MISSING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99			291  							ALL FOUR NUTS, FLAT AND LOCK WASHERS, WERE DISCOVERED MISSING FROM THE FOUR STUDS ON THE INTAKE MANIFOLD THAT THE CARBUR	ETOR IS MOUNTED ON.  PROBLEM DISCOVERED WHEN ENGINE FAILED ON LANDING AND WOULD NOT RESTART.  CURRENT COMBINATION OF NUT	, LOCK WASHER AND FLAT WASHER IS NOT SUFFICIENT TO WITHSTAND ENGINE VIBRATION.  SUBMITTER RECOMMENDS PERIODIC TORQUE CHE	CKS OR DIFFERENT LOCKING DEVICE.			1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1997120400939	19971204	00939		1997	12	4	97ZZZX4953       	4	19971117	G	3454	5222450114	RECEIVER        	COLLINS     																SUBASSY	MISREPAIRED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01					12477					IAW MANUFACTURER'S MM DATA, THE APPLIANCE DESCRIBED IN BLOCK 6 CONTAINS SUB-ASSEMBLIES INAPPROPRIATE TO THE PARTICULAR P	ART NUMBER DENOTED ON THE DATA PLATE.																		 
1997120400940	19971204	00940		1997	12	4	97ZZZX4954       	4	19971117	G	3454	5222450115	RECEIVER        																	SUBASSY	MISREPAIRED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01					2446					IAW MANUFACTURER'S MM DATA, THE APPLIANCE DESCRIBED IN BLOCK 6 CONTAINS SUB-ASSEMBLIES INAPPROPRIATE TO THE PARTICULAR P	ART NUMBER DENOTED ON THE DATA PLATE.  THIS UNIT, IF PROPERLY REPAIRED, COULD BE RETURNED TO SERVICE.																		 
1997120400941	19971204	00941	CE  	1997	12	4	97ZZZX4955       	1	19971117	G	7921	LW10025	OIL COOLER      			BEECH 	60    	B60         	1153605	CE  										ENGINE OIL	LEAKING         	B		A	TE1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	7288D	6    			429	P81				THE FIRST OIL COOLER WAS INSTALLED WHEN THE ORIGINAL OIL COOLER DEVELOPED A LEAK AT 2426.8 HOURS.  THIS OIL COOLER DEVEL	OPED A LEAK AFTER ABOUT 6 HOURS.  OIL COOLER NR 2 WAS INSTALLED AND DEVELOPED A LEAK AFTER 2 HRS.  THE NR 2 OIL COOLER W	AS CUT IN TWO TO SEE IF THE CAUSE OF THE LEAKS COULD BE DETERMINED.  FOUND LAST LEAK REPAIRED BY FILLING THE LEAKING SEG	MENT WITH INDUSTRIAL TYPE EPOXY.  THIS UNIT WAS REPLACED WITH A NEW UNIT.			1	L	7	2 	3O				A12CE   					 
1997120400942	19971204	00942	CE  	1997	12	4	97ZZZX4956       	1	19971117	G	7921	LW10025	OIL COOLER      			BEECH 	60    	B60         	1153605	CE  										ENGINE OIL	LEAKING         	B			TE1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	7288D	2    			668	P81				THE FIRST OIL COOLER WAS INSTALLED WHEN THE ORIGINAL OIL COOLER DEVELOPED A LEAK AT 2426.8 HOURS.  THIS OIL COOLER DEVEL	OPED A LEAK AFTER ABOUT 6 HOURS.  OIL COOLER NR 2 WAS INSTALLED AND DEVELOPED A LEAK AFTER 2 HRS.  THE NR 2 OIL COOLER W	AS CUT IN TWO TO SEE IF THE CAUSE OF THE LEAKS COULD BE DETERMINED.  FOUND LAST LEAK REPAIRED BY FILLING THE LEAKING SEG	MENT WITH INDUSTRIAL TYPE EPOXY.  THIS UNIT WAS REPLACED WITH A NEW UNIT.			1	L	7	2 	3O				A12CE   					 
1997120400943	19971204	00943		1997	12	4	97ZZZX4957       	3	19971107	G	6112	RA129884	DEICE BOOT      	RAPCO       		BEECH 	80    	65B80       	1152812	CE  										NR 1 PROPELLER	FAILED          	D	S			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	110BA	438  				LD279				PROPELLER DEICE LEAD BREAK 12 INCHES FROM TERMINALS AFTER FOLLOWING NEW INSTALLATION INSTRUCTIONS.						1	L	7	2 	3O				3A20    					 
1997120400944	19971204	00944	SO  	1997	12	4	97ZZZX4958       	1	19971101	G	7160		HOSE            			PIPER 	PA18  	PA18135     	7101820	SO  										ENGINE INDUCT	FAILED          	D		A		K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			AL	05	1458C					182657				LINING OF INDUCTION HOSES SWELLED INWARD THEN CRACKED AROUND THE INSIDE DIAMETER CIRCUMFERENCE.  SOME LINING BROKE OFF A	ND PASSED THROUGH COMBUSTION CHAMBERS.  THE SWELLED LINING THAT REMAINED SWELLED OUT ENOUGH TO OBSTRUCT FLOW CAUSING THE	 ENGINE TO RUN ROUGH AT HIGH THROTTLE SETTINGS AND LOSE 200 TO 250 RPM'S AT FULL THROTTLE.  THE PROBLEM WAS HARD TO ISOL	ATE BECAUSE THE LINING WOULD SHRINK BACK WHEN THE ENGINE WAS NOT RUN FOR SEVERAL DAYS.  THIS ENGINE WAS A FRESH FACTORY 	OVERHAUL.		1	H	7	1 	3O				1A2     					 
1997120400945	19971204	00945	SO  	1997	12	4	97ZZZX4959       	2	19971114	G	8530	626992	PISTON          			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  					PIN BOSS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3235S	1277 				18255735	1305724R4			SIX ENGINE PISTONS FOUND CRACKED IN PISTON PIN BOSS.  CRACKS WERE ALL IN SAME AREA, UPPER PIN BOSS RUNNING PARALLEL TO P	ISTON PIN.  ONE PISTON HAD LOST ONE-FOURTH OF THE CASTING AROUND PIN.  THIS CONDITION DID NOT CAUSE ANY OPERATIONAL PROB	LEMS.  JUDGING FROM CARBON CONDITION, HAD EXISTED SOME TIME.  THIS PISTON IS SAME DESIGN AS SA626992 WHICH IS COVERED BY	 AD96-12-04.			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997013000343	19970130	00343	CE  	1997	1	30	97ZZZX496        	1	19970115	G	5753		HINGE           			CESSNA	140   	140         	2071602	CE  										LT FLAP	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	1917V					14111				DURING ANNUAL INSPECTION, THE LEFT WING FLAP HINGES WERE FOUND CRACKED.  LEFT AND RIGHT ONLY.  THE AREA OF THE CRACKS WA	S FOUND AT THE ATTACHING SCREW HOLES.  THE CRACKS ORIGINATED IN THE HOLES AND RAN TO EACH CORNER OF THESE HINGES.  PARTS	 TOTAL TIME UNKNOWN.				1	H	7	1 	3O			NC	A768    					 
1997120400946	19971204	00946	CE  	1997	12	4	97ZZZX4960       	1	19971010	G	3230	2162	SPROCKET        			BEECH 	18    	C45H        	1151018	CE  										NLG	FAILED          	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SO	17	486JB	4500 				AF858				LANDING GEAR FAILED TO EXTEND UPON LANDING AT ORLANDO INTERNATIONAL DUE TO THE POSITION OF ACFT.  AFTER REMOVAL FROM THE	 RUNWAY, A DETERMINATION OF CAUSE IS NOT POSSIBLE.					1	L	7	2 	3R				A765    					 
1997120400947	19971204	00947	EU  	1997	12	4	97ZZZX4961       	2	19970501	G	8510	834050	RING GEAR       			AMTR  	KITFOX	KITFOX      	05613LZ	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					ENG STARTER	FAILED          	C	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	61DM	185  				606				PRE-FLIGHT INSPECTION FOUND METAL FILINGS AROUND STARTER.  FURTHER INSP REVEALED A LARGE CRACK NEAR A BOLT HOLE ON THE S	TARTER RING GEAR THAT WAS SEPARATED BY .125 INCH.  SMALLER CRACKS WERE NOTED EMANATING FROM OTHER BOLT HOLES.  REASON FO	R THE CRACKING IS UNKNOWN, HOWEVER, IT HAS BEEN LEARNED THIS IS NOT AN ISOLATED CASE IN THE OLDER ROTAX 582 ENGINES WITH	 THIS TYPE STARTER.  APPARENTLY, SERVICE BULLETIN WAS PUBLISHED TO REPLACE THESE RING GEARS WITH A HEAVIER BUILT UNIT, H	OWEVER, THAT SB WAS NOT AVAILABLE TO THE AUTHOR.  THIS RING GEAR WAS ON THE VERGE OF COMPLETE SEPARATION.  SUBMITTER REC	OMMENDS ALL OWNERS OF ROTAX 582/532 ENGINES PRODUCED PRIOR TO 1994 HAVE A VERY CLOSE LOOK AT THE STARTER RING GEAR.	1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1997120400948	19971204	00948	CE  	1997	12	4	97ZZZX4962       	1	19971110	G	3320	CM35351	POTENTIOMETER   			CESSNA	402   	402C        	207590R	CE  										DIMMER BOARD	FAILED          	C				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NE	01	7037E					402C0471				AN ODOR OF ELECTRICAL SMOKE FILLED THE CABIN.  AIRCRAFT LANDED WITHOUT INCIDENCE.  FOUND THE DIMMER BOARD AT FAULT.  DIM	MER ASSY REPLACED AND AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3O				A7CE    					 
1997120400949	19971204	00949	EA  	1997	12	4	97ZZZX4963       	2	19971031	G	7414	6263	MAGNETO         	SLICK       		PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENG LT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	914DC	747  			89100028	4622127	L937661A			PILOT REPORTED HIGH MAG DROP ON LEFT MAG.  RUN-UP INDICATED NEARLY COMPLETE MAG FAILURE.  DURING DISASSEMBLY, A LARGE AM	OUNT OF DUST WAS NOTED IN THE AREA OF THE CONTACT ASSEMBLY AND CONTACTS WERE BARELY OPENING.  THE CAM WAS FOUND SEVERELY	 WORN.  NO REASON FOR THE UNUSUAL WEAR WAS NOTED.				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
1997120400950	19971204	00950	EA  	1997	12	4	97ZZZX4964       	2	19971120	G	8530	CC20B	PISTON RING     			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					NR 1 CYLINDER	FAILED          	B			GYWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	9773B		854  			172RG1027	L2815936A			EXCESSIVE OIL OUT OF ENGINE BREATHER PROMPTED ENGINE COMPRESSION CHECK WHICH REVEALED LOW COMPRESSION ON NR 1 CYLINDER. 	 REMOVAL OF CYLINDER REVEALED TOP COMPRESSION RING SHATTERED INTO APPROX .25 INCH SEGMENTS AND SECOND COMPRESSION RING B	ROKEN IN SEVERAL PLACES.  OIL RING FOUND STUCK IN GROOVE.  PISTON WAS DAMAGED IN RING GROOVES, BUT CYLINDER SHOWED NO SI	GN (VISUAL OR DIMENSIONAL) OF DAMAGE.  ADJACENT CYLINDER WAS REMOVED FOR INSPECTION, BUT NO DEFECTS WERE FOUND.  NO APPA	RENT OR OBVIOUS CAUSE NOTED OR DETECTED.		1	H	7	1 	3O	3	O		3A17    	E286				 
1997120400951	19971204	00951	EU  	1997	12	4	97ZZZX4965       	1	19971101	G	2435	30702093	DRIVESHAFT      			AMD   	FALC10	FALCON10    	2730101	EU  										START/GEN	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	61TJ					041				STARTER/GENERATOR DRIVESHAFT AND STARTER/GENERATOR DRIVESHAFT SPLINES WORN COMPLETLY AWAY CAUSING GENERATOR TO CEASE FUN	CTIONING DURING OTHERWISE NORMAL FLIGHT.  POSSIBLY LARGER SPLINES COULD HAVE PREVENTED THIS PROBLEM.					2	L	7	2 	4F				A33EU   					 
1997120400952	19971204	00952	CE  	1997	12	4	97ZZZX4966       	1	19971117	G	5541	55331160	RIB             			CESSNA	500   	550         	2076604	CE  										RUDDER	CRACKED         	B		A	SI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	387HA	5921 				0465				UPON REMOVAL OF THE LEFT LOWER RUDDER CLOSEOUT SKIN, THE INTERSPAR RIB WAS FOUND CRACKED ACROSS THE ENTIRE WIDTH OF THE 	RIB.  THE DAMAGE TO THE RIB WAS A CLEAR INDICATION OF A CRACK CAUSED BY FATIGUE.  THE DECREASED INTEGRITY ALSO CAUSED TH	E ATTACHING RUDDER SKIN TO CRACK.				1	L	7	2 	4F				A22CE   					 
1997120400953	19971204	00953	NM  	1997	12	4	97ZZZX4967       	1	19971025	G	2781		TORQUE TUBE     			BOEING	757   	75723A      	1384967	NM  										SLAT NR 9	LOOSE           	W			ANCF	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	23	987AN					25494				CTG/EWR - FLT 024 - EICAS MSG L.E. SLAT AYSM. DISPLAYED WITH FLAP LEVER UP.  FLAP POINTERS STOPPED BETWEEN UP AND 1 DEGR	EE.  FLIGHT RETURNED TO CTG.  SLAT NR 9 TRANSMITTER TORQUE TUBE L.E. WAS FOUND LOOSE.  TORQUE TUBE COUPLING ADJUSTED AND	 REGULATED SYSTEM ACCORDING MM 27-58-01, PAGE 507.  TEST ON GROUND OK.				2	L	7	2 	4F			RT	A2NM    					 
1997120400954	19971204	00954	CE  	1997	12	4	97ZZZX4968       	1	19971117	G	3710	1013202661	TUBE ASSY       			BEECH 	90    	C90A        	1152911	CE  										VACUUM SYSTEM	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	491JV	2299 				LJ1349				VACUUM TUBE ASSY WAS WORN THROUGH IN A 3 INCH BY .1250 INCH AREA.  THE RADAR CRT WAS RESTING ON PIPE.  THERE WAS NO LEAK	 WHEN THE PANEL WAS AT REST.  MOVING THE GEAR HANDLE EXPOSED THE LEAK BY MOVING THE RADAR UNIT FOWARD.  THIS WAS FOUND W	HEN PERFORMING A RETRACTION CHECK ON JACKS IN THE HANGAR.				1	L	7	2 	3T			RT	3A20    					 
1997120400955	19971204	00955	SW  	1997	12	4	97ZZZX4969       	1	19971104	G	6220	206010154003	WASHER          			BELL  	206   	206B3       	1181506	SW  										M/R HUB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25			1200 							M/R HUB S/N JILM 5051.  WASHER WAS FOUND CRACKED STRAIGHT OUT INSIDE DIAMETER TO OUTSIDE DIAMETER DURING HUB OVERHAUL. W	ASHERS ARE NOT SPECIFIED TO BE M.P.I.  NORMAL OVERHAUL PROCEDURES ARE TO M.P.I. THESE ITEMS.					1	G	7	1 	3U				H2SW    					 
1997120400956	19971204	00956	WP  	1997	12	4	97ZZZX4970       	1	19971116	G	2810	37510007	TANK            			HUGHES	369   	369D        	4470706	WP  										AUX FUEL	COLLAPSED       	B		A	LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5027P	2    				611002D				AUXILIARY FUEL TANK COLLAPSED DUE TO VACUUM FROM FUEL TRANSFER TO MAIN TANK.  UPON INVESTIGATION, FOUND MASKING TAPE WAS	 PLUGGING THE VENT STANDPIPE APPARENTLY TO PREVENT PAINT FROM ENTERING THE VENT TUBE WHEN THE TANK WAS PAINTED BY THE MA	NUFACTURER.  AIRCRAFT WAS LANDED WITHOUT INCIDENT.				1	G	7	1 	3U				H3WE    					 
1997120400957	19971204	00957	SW  	1997	12	4	97ZZZX4971       	1	19971002	G	6230	206010443001	DUPLEX BEARING  		206010450113	BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	BRINELLED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577E	510  			GDJG90426	45577				THIS IS NR 6 AND NR 7 DUPLEX BEARING CHANGE FOR BRINELLING ON RACES PARTICULARLY THE LOWER INNER RACE.  ALL HAVE BEEN CH	ANGED WITH LESS THAN 100-HOUR TT SINCE NEW.					1	G	7	1 	3U				H2SW    					 
1997120400958	19971204	00958	SW  	1997	12	4	97ZZZX4972       	1	19971002	G	6230	206010443001	DUPLEX BEARING  		206010450113	BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	BRINELLED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2611	411  			GDJG90483	45417				THIS IS NR 6 AND NR 7 DUPLEX BEARING CHANGE FOR BRINELLING ON RACES PARTICULARLY THE LOWER INNER RACE.  ALL HAVE BEEN CH	ANGED WITH LESS THAN 100-HOUR TT SINCE NEW.					1	G	7	1 	3U				H2SW    					 
1997121100003	19971211	00003	SW  	1997	12	11	97ZZZX4975       	1	19970926	G	2430	SM20ACD200A21	RELAY           			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	INTERMITTENT    	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40LP	708  				45233				INTERMITTENT OPERATION.						1	G	7	1 	3U				H2SW    					 
1997121100004	19971211	00004	GL  	1997	12	11	97ZZZX4976       	2	19970911	G	7323	23057869	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5366Y	1586 			86090403	S782				GOVERNOR HAS NO MORE ADJUSTMENT FOR COMPENSATION.  REPLACED GOVERNOR.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997121100005	19971211	00005	GL  	1997	12	11	97ZZZX4977       	2	19970922	G	7323	23057869	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8776	436  			86220668	S776				UNABLE TO ADJUST DROOP COMP.  REPLACED GOVERNOR.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997121100006	19971211	00006	SW  	1997	12	11	97ZZZX4978       	1	19970924	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										T/R DISK PACK	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL					53054				SCHEDULED INSPECTION FOUND DISK PACK DISK CRACKED.  THREE REPORTS RECEIVED DATED 9-24-97 ON T/R DISK PACK DISK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
1997121100007	19971211	00007	SW  	1997	12	11	97ZZZX4979       	1	19970924	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										T/R DISK PACK	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL					53054				SCHEDULED INSPECTION FOUND DISK PACK DISK CRACKED.  REMOVED AND REPLACED.  THREE REPORTS RECEIVED DATED 9-24-97 ON T/R D	ISK PACK DISK CRACKED.					1	G	7	1 	3U			O	H2SW    					 
1997121100008	19971211	00008	NM  	1997	12	11	97ZZZX4980       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 1060-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN SEAT TRACK, STA 1060 TO STA 1070 AT RBL 45.						2	L	7	3 	4F				A3WE    					 
1997121100009	19971211	00009	NM  	1997	12	11	97ZZZX4981       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 1010-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION WAS NOTED ON CABIN SEAT TRACK BETWEEN STA 1010 - STA 1030 AT LBL 45.						2	L	7	3 	4F				A3WE    					 
1997121100010	19971211	00010	NM  	1997	12	11	97ZZZX4982       	1	19971101	G	5311		FRAME           			BOEING	727   	727225      	1384077	NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION WAS NOTED ON FRAME 1030 BETWEEN S17L AND S26L.						2	L	7	3 	4F				A3WE    					 
1997121100011	19971211	00011	NM  	1997	12	11	97ZZZX4983       	1	19971101	G	5315		FLOOR BEAM      			BOEING	727   	727225      	1384077	NM  										BS 480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON UPPER CHORD FLOOR BEAM STA 480 BETWEEN RBL 65 AND LBL 24.						2	L	7	3 	4F				A3WE    					 
1997121100012	19971211	00012	NM  	1997	12	11	97ZZZX4984       	1	19971101	G	5315		FLOOR BEAM      			BOEING	727   	727225      	1384077	NM  										BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION WAS NOTED ON UPPER CHORD FLOOR BEAM STA 420 BETWEEN RBL 12 AND LBL 14.						2	L	7	3 	4F				A3WE    					 
1997121100013	19971211	00013	NM  	1997	12	11	97ZZZX4985       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 380-400	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT BETWEEN STA 380 TO STA 400 AT RBL 12.						2	L	7	3 	4F				A3WE    					 
1997121100014	19971211	00014	NM  	1997	12	11	97ZZZX4986       	1	19971101	G	5311		FRAME           			BOEING	727   	727225      	1384077	NM  										BS 1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON FRAME WEB AT STA 1050 AT S19L.						2	L	7	3 	4F				A3WE    					 
1997122900001	19971229	00001	NM  	1997	12	29	97ZZZX4987       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 420-440	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT BETWEEN STA 420 - STA 440 AT RBL 12.						2	L	7	3 	4F				A3WE    					 
1997121100015	19971211	00015	NM  	1997	12	11	97ZZZX4988       	1	19971101	G	5312		STIFFENER       			BOEING	727   	727225      	1384077	NM  										BULKHEAD LT 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON STIFFENER FORWARD FACE BOTTOM OF BULKHEAD 1183 AT LBL 18.						2	L	7	3 	4F				A3WE    					 
1997121100016	19971211	00016	NM  	1997	12	11	97ZZZX4989       	1	19971101	G	5312		STIFFENER       			BOEING	727   	727225      	1384077	NM  										BULKHEAD RT 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON FORWARD FACE 1183 BULKHEAD STIFFENER, LOWER SECTION, AT RBL 18.						2	L	7	3 	4F				A3WE    					 
1997121100017	19971211	00017	NM  	1997	12	11	97ZZZX4990       	1	19971101	G	5311		FRAME           			BOEING	727   	727225      	1384077	NM  										BS 740	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, EXFOLIATION CORROSION NOTED ON FORWARD FACE OF STA 740 FRAME SPLICE AT S9R.						2	L	7	3 	4F				A3WE    					 
1997121100018	19971211	00018	NM  	1997	12	11	97ZZZX4991       	1	19971101	G	5330		SKIN            			BOEING	727   	727225      	1384077	NM  										BS 1150-1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON FUSELAGE SKIN BETWEEN STA 1150 AND STA 1183 BETWEEN S14R AND S20R.						2	L	7	3 	4F				A3WE    					 
1997121100019	19971211	00019	NM  	1997	12	11	97ZZZX4992       	1	19971101	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 950-1010	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION AND CRACKING NOTED ON S27R BETWEEN STA 950 AND STA 1010.						2	L	7	3 	4F				A3WE    					 
1997121100020	19971211	00020	NM  	1997	12	11	97ZZZX4993       	1	19971101	G	7120	65187226	MOUNT           			BOEING	727   	727225      	1384077	NM  										NR 3 ENGINE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON NR 3 ENGINE FORWARD MOUNT.						2	L	7	3 	4F				A3WE    					 
1997121100021	19971211	00021	NM  	1997	12	11	97ZZZX4994       	1	19971101	G	5311		FRAME           			BOEING	727   	727225      	1384077	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON BULKHEAD FRAME STA 1166.						2	L	7	3 	4F				A3WE    					 
1997121100022	19971211	00022	NM  	1997	12	11	97ZZZX4995       	1	19971101	G	5320		WEB             			BOEING	727   	727225      	1384077	NM  										LT BS 259.3	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, INTERGRANULAR CORROSION NOTED ON WEB LT SIDE FRAME 259.3.						2	L	7	3 	4F				A3WE    					 
1997121100023	19971211	00023	NM  	1997	12	11	97ZZZX4996       	1	19971101	G	5320		WEB             			BOEING	727   	727225      	1384077	NM  										RT BS 259.5	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, INTERGRANULAR CORROSION NOTED ON WEB RT SIDE FRAME 259.5.						2	L	7	3 	4F				A3WE    					 
1997121100024	19971211	00024	NM  	1997	12	11	97ZZZX4997       	1	19971101	G	5320		CHORD           			BOEING	727   	727225      	1384077	NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR BEAM UPPER CHORD AT STA 1030, FROM RBL 45 TO RBL 65.						2	L	7	3 	4F				A3WE    					 
1997121100025	19971211	00025	NM  	1997	12	11	97ZZZX4998       	1	19971101	G	5320		CHORD           			BOEING	727   	727225      	1384077	NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON LOWER CHORD CABIN FLOOR BEAM AT STA 1130, LBL 24.						2	L	7	3 	4F				A3WE    					 
1997121100026	19971211	00026	NM  	1997	12	11	97ZZZX4999       	1	19971101	G	5320		ANGLE           			BOEING	727   	727225      	1384077	NM  										BS 1010-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON RIGHT HAND CUSP FLOOR SUPPORT ANGLE BETWEEN STA 1010 AND STA 1030.						2	L	7	3 	4F				A3WE    					 
1997121100027	19971211	00027	NM  	1997	12	11	97ZZZX5000       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 1035-1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT BETWEEN STA 1035 AND STA 1050 AT LBL 12.						2	L	7	3 	4F				A3WE    					 
1997121100028	19971211	00028	NM  	1997	12	11	97ZZZX5001       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 1035	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT STA 1035 AT LBL 20.						2	L	7	3 	4F				A3WE    					 
1997121100029	19971211	00029	NM  	1997	12	11	97ZZZX5002       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 312-344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR SUPPORT BETWEEN STA 312 AND STA 344 AT LBL 30.						2	L	7	3 	4F				A3WE    					 
1997121100030	19971211	00030	NM  	1997	12	11	97ZZZX5003       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 1030-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON AFT BAGGAGE PIT FLOOR SUPPORT BETWEEN STA 1030 AND STA 1166 AT LBL 17.						2	L	7	3 	4F				A3WE    					 
1997121100031	19971211	00031	NM  	1997	12	11	97ZZZX5004       	1	19971101	G	5320		SUPPORT         			BOEING	727   	727225      	1384077	NM  										BS 1030-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON AFT BAGGAGE PIT FLOOR SUPPORT, STA 1030 TO STA 1166 AT BL ZERO.						2	L	7	3 	4F				A3WE    					 
1997121100032	19971211	00032	NM  	1997	12	11	97ZZZX5005       	1	19971101	G	5320		CHORD           			BOEING	727   	727225      	1384077	NM  										BS 480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR BEAM UPPER CHORD AT STA 480.						2	L	7	3 	4F				A3WE    					 
1997121100033	19971211	00033	NM  	1997	12	11	97ZZZX5006       	1	19971101	G	5320		ANGLE SUPPORT   			BOEING	727   	727225      	1384077	NM  										BS 480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON 2 ANGLE SUPPORTS STA 480 AT S20L.						2	L	7	3 	4F				A3WE    					 
1997121100034	19971211	00034	NM  	1997	12	11	97ZZZX5007       	1	19971101	G	5320		ANGLE           			BOEING	727   	727225      	1384077	NM  										BS 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON THE 1183 BULKHEAD VERTICAL STIFFENER ATTACH ANGLE AT RBL 18.						2	L	7	3 	4F				A3WE    					 
1997121100035	19971211	00035	NM  	1997	12	11	97ZZZX5008       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 1010-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN SEAT TRACK RIGHT HAND OUTBOARD FROM STA 1010 TO STA 1030.						2	L	7	3 	4F				A3WE    					 
1997121100036	19971211	00036	NM  	1997	12	11	97ZZZX5009       	1	19971101	G	5347		SEAT TRACK      			BOEING	727   	727225      	1384077	NM  										BS 1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON CABIN SEAT TRACK AT LBL 24 AT STA 1050.						2	L	7	3 	4F				A3WE    					 
1997121100037	19971211	00037	NM  	1997	12	11	97ZZZX5010       	1	19971101	G	5320		CHORD           			BOEING	727   	727225      	1384077	NM  										BS 400	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON PREVIOUS REPAIR TO UPPER T-CHORD ON FLOOR BEAM STA 400 APPROXIMATELY RBL 12 TO RBL 20	.					2	L	7	3 	4F				A3WE    					 
1997121100038	19971211	00038	NM  	1997	12	11	97ZZZX5011       	1	19971101	G	5313		STRINGER        			BOEING	727   	727225      	1384077	NM  										BS 460-480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	352PA					20616				DURING C-CHECK, CORROSION NOTED ON S19R BETWEEN STA 460 AND STA 480.						2	L	7	3 	4F				A3WE    					 
1997121100112	19971211	00112	CE  	1997	12	11	97ZZZX5029       	1	19971105	G	7160	265201052	INLET           			LEAR  	35    	35A         	5170602	CE  										RT ENGINE	CRACKED         	B			BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	20DK				376	35143				CRACKS FOUND ON THE INSIDE OF THE ENGINE INLET AT THE FORWARD INLET RING FLANGE.  CRACKS FOUND DURING A PHASE A3 - 300-H	OUR INSPECTION.  INSPECTION REFERENCE NUMBERS 30-20-00, 71-10-10.  AIRCRAFT TOTAL TIME:  7,862.3 HOURS.  AIRCRAFT TOTAL 	CYCLES:  7,469 HOURS.				2	L	7	2 	4F				A10CE   					 
1997013000431	19970130	00431	CE  	1997	1	30	97ZZZX503        	1	19970103	G	2820	5200106206	FUEL LINE       			CESSNA	310   	310R        	2074245	CE  										CROSSFEED	LEAKING         	B		A	AHTR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	11	1743E	6716 				310R1559				DURING ANNUAL INSP, THE LEFT CROSS-FEED FUEL LINE WAS FOUND TO HAVE FUEL STAIN IN AN AREA WHERE THE FUEL LINE PASSES THR	OUGH THE CABIN AT THE MAIN SPAR.  THE AREA WAS ONLY VISIBLE WITH UPHOLSTERY REMOVED.  MUCH LABOR WAS REQUIRED TO REMOVE 	AND REPLACE THE FUEL LINE.  ON REMOVAL, SEVERAL PIN HOLES DUE TO CORROSION WERE FOUND WHEN THE LINE WAS PUT UNDER PRESSU	RE.			1	L	7	2 	3O				3A10    					 
1997121100113	19971211	00113	CE  	1997	12	11	97ZZZX5030       	1	19971105	G	7160	265201051	INLET           			LEAR  	35    	35A         	5170602	CE  										LT ENGINE	CRACKED         	B		A	BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	20DK				131	35143				CRACKS WERE FOUND ON THE INSIDE OF THE ENGINE INLET AT THE FORWARD INLET RING FLANGE.  CRACKS WERE FOUND DURING A PHASE 	A3 - 300-HOUR INSPECTION.  INSPECTION REFERENCE NUMBERS 30-20-00, 71-10-10.  AIRCRAFT TOTAL TIME:  7,862.3 HOURS.  AIRCR	AFT TOTAL CYCLES:  7,469 HOURS.				2	L	7	2 	4F				A10CE   					 
1997121100114	19971211	00114		1997	12	11	97ZZZX5031       	4	19971009	G	3416	804710	ALTIMETER       			AMD   	FALC50	FALCON50MYST	2730106	EU  										STANDBY ALT	ERROR           	B		A	AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	254DV				9003B	085				UPON RECEIVING AN OVERHAULED STANDBY ALTIMETER, INSPECTION REVEALED THE DIGIT INDEXING TO BE 1,000 FEET OFF.  FIELD ELEV	ATION SETTING INDICATED THE PROPER BAROMETRIC PRESSURE (780 FEET, 3014 HG), BUT ROTATING THE KNOB UP TO 1,000 FEET SHOWE	D THE DIGITS READING 0,000.  PART RETURNED.  THIS UNIT HAD AN OVERHAULED DATE OF 8-22-97.				2	L	7	3 	4F				A46EU   					 
1997121100115	19971211	00115	CE  	1997	12	11	97ZZZX5032       	1	19971112	G	2750	556517531	GEARBOX         			CESSNA	500   	550         	2076604	CE  										LT FLAP	SHEARED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	45NS		975  			5500479				WHILE TROUBLEHSHOOTING FLAP DRIVE FAILURE, FOUND LEFT FLAP GEARBOX DRIVESHAFT SHEARED.  THIS WAS CAUSED BY RIGHT FLAP GE	ARBOX SEIZING.  REPLACED GEARBOX WITH UPGRADED DASH 38 UNIT iAW CESSNA SB 558-27-16, REV 7.					1	L	7	2 	4F				A22CE   					 
1997121100116	19971211	00116	EU  	1997	12	11	97ZZZX5033       	1	19970904	G	3710	25VF3323309	VACUUM LINE     			BRAERO	DH125 	HS125700A   	4230170	EU  										FRAME 9	CHAFED          	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	701NW					NA0206				A PRESSURIZATION BUMP WAS FELT WHEN MAIN AIR VALVES WERE TURNED ON OR THROTTLES WERE MOVED.  FOUND RT AILERON CABLE HAD 	CHAFED THROUGH VACUUM LINE AT FRAME 9 ON RT SIDE OF AIRCRAFT.  SUSPECT CABLE TENSION HAD BEEN RELAXED, THEN TENSIONED, W	HICH PUT THE CABLE ON THE LOWER SIDE OF THE LINE INSTEAD OF ON TOP.  SUBMITTER SUGGESTS VISUAL INSPECTION OF LINE WHEN A	CCESS IS AVAILABLE AS WELL AS INSTALLING ADDITIONAL CLAMP AT FRAME 9.  CARE SHOULD BE TAKEN WHENEVER CABLE TENSIONS ARE 	RELAXED TO PREVENT REPOSITIONING OF THE CABLE WHEN LOOSE.		2	L	7	2 	4F				A3EU    					 
1997121100117	19971211	00117	EU  	1997	12	11	97ZZZX5034       	1	19971003	G	3246	2600360	WHEEL HALF      	BENDIX      	26003411    	BAC   	111   	111401AK    	1480268	EU  										MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	765B		122  		B0246	BAC067				15 INCH SECTION SEPARATED/BROKE OFF FROM A MAIN LANDING GEAR WHEEL HALF.						2	L	7	2 	4F				A5EU    					 
1997121100124	19971211	00124	NM  	1997	12	11	97ZZZX5038       	1	19971112	G	7160	35453	AIR BOX         			CHRIS 	HUSKY 	A1          	221020X	NM  										VALVE SHAFT	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	29076	490  				1022				AIR INTAKE BOX SHAFT, ARM AND SLEEVE BUSHINGS FOUND BADLY WORN.  APPEARS TO BE CAUSED BY ENGINE VIBRATION EVEN THOUGH PR	OPELLER WAS BALANCED AT 532.5 HRS TO .013 IPS.  BOX BY DESIGN IS NOT REPAIRABLE DUE TO SHAFT WELDED TO PLATE.  SUBMITTER	 RECOMMENDED BOX BE RE-DESIGNED BY MFG TO INCORPORATE SEALED BALL OR NEEDLE BEARINGS AND PLATE BE ATTACHED TO SHAFT USIN	G MACHINE SCREWS AND NUTS ALLOWING FOR FIELD REPAIRS OF BOX ASSY.			1	H	7	1 	3O			NC	A22NM   					 
1997121100125	19971211	00125	CE  	1997	12	11	97ZZZX5039       	1	19971031	G	5751	MS244624	BEARING         			CESSNA	208   	208B        	2073701	CE  										LT AIL OB HINGE	FROZEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	738FX	996  				208B0482				DURING INSPECTION, AILERON CONTROL WAS DISCOVERED TO HAVE UNUSUALLY HIGH RESISTANCE.  RESISTANCE WAS EVENTUALLY ISOLATED	 TO THE LEFT AILERON.  BOTH BEARINGS WERE REPLACED AND THE OUTBOARD BEARING WAS FOUND ALMOST FROZEN WITH CORROSION.  THE	SE ARE SEALED BEARINGS AND HAD NO OUTWARD SIGNS TO INDICATE A PROBLEM.  NO REASON FOR THE CORROSION WAS NOTED.				1	H	7	1 	3T				A37CE   					 
1997121100126	19971211	00126		1997	12	11	97ZZZX5040       	4	19971107	G	2215	089606705	SCREWS          	KING        	KS270A      	PIPER 	PA46  	PA46350P    		SO  										PITCH SERVO	LOOSENED        	D	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	9284X	235  			28553	4636087				SERVO NOT WORKING PROPERLY.  REMOVED FROM AIRCRAFT AND FOUND THREE SCREWS BACKED OUT UNTIL THEY HIT PLATE 073-0515-03. S	CREWS NEED LOCTITE.					1	L	7	1 	3O			RT	A25SO   					 
1997121100127	19971211	00127	SO  	1997	12	11	97ZZZX5041       	1	19971126	G	3230		BRACKET         			PIPER 	PA31T 	PA31T       	7103124	SO  										MLG UPLOCK	CRACKED         	D	S	A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	11	311AC	3700 				31T8120016				MAIN LANDING GEAR UPLOCK SUPPORT BRACKET CRACKED ALLOWING UPLOCK HOOK TO LOCK SIDEWAYS LODGING BETWEEN ROLLER AND GEAR L	EG.  LEFT MAIN GEAR WOULD NOT EXTEND UNTIL AIRCRAFT WAS PUT THROUGH NEGATIVE GRAVITY.  SECOND AIRCRAFT FOUND WITH THIS P	ROBLEM.				1	L	7	2 	3T				A8EA    					 
1997121100128	19971211	00128	SO  	1997	12	11	97ZZZX5042       	1	19971113	G	5743	67041	TRUNNION BOLT   			PIPER 	PA34  	PA34200     	7103405	SO  										MLG MOUNT	LOOSE           	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	19SW	7650 				347250119				INSPECTION FOUND THE MLG TRUNNION MOUNTING BOLTS LOOSE ON THEIR BRACKETS.  THIS LOOSENING CAUSES THE HOLES IN THE WING S	PAR TO ELONGATE.  SUBMITTER STATED THEY HAVE FOUND THE BOLTS LOOSE REGULARLY ON ALL OF FLEET PA28R AND PA34 AIRCRAFT.					1	L	7	2 	3O				A7SO    					 
1997121100129	19971211	00129	EU  	1997	12	11	97ZZZX5043       	1	19971114	G	3830	5583112140	DRAIN CABLE     			AMD   	FALC50	FALCON900   	2700160	EU  										FWD LAVATORY	DISPLACED       	B		A	YL1R	O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			SW	11	72WS	155  				14				CREW ON TAXI CHECKING FLIGHT CONTROL MOVEMENT NOTICED A RESTRICTION IN RUDDER MOVEMENT.  THE RUDDER WAS LIMITED TO APPRO	XIMATELY HALF TRAVEL TO THE LEFT AND A LOUD CLUNKING NOISE WAS HEARD WITH THE APPLICATION OF RIGHT RUDDER PEDAL.  THE NO	ISE SEEMED TO BE COMING FROM UNDER THE FORWARD LAVATORY FLOOR.  THE AIRCRAFT RETURNED TO DFJC MAINTENANCE AREA FOR AN IN	VESTIGATION,  FOUND FORWARD LAVATORY DRAIN CABLE RESTING AGAINST TORQUE TUBE FOR RUDDER RESTRICTING FULL MOVEMENT.			2	L	7	3 	4F			RT	A46EU   					 
1997121100130	19971211	00130	CE  	1997	12	11	97ZZZX5044       	1	19971114	G	3020		ANTI ICE TUBE   			BEECH 	100   	B100        	1152919	CE  										LT ENG INTAKE	BROKEN          	D		A		O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			CE	01	564CA	5496 	233  			BE58				LEFT ENGINE FLAME-OUT AT 7,000 FEET HOLDING AT FLYING COLD IN ICING CONDITION.  INTAKE ANTI-ICE HAD BEEN ON FOR HALF AN 	HOUR.  FOUND ONE ANTI-ICE TUBE FLARE BROKEN OFF.  SUSPECT SOME LOSS OF BLEED AIR IN THIS AREA COULD HAVE ATTRIBUTED TO I	CE FORMING ON INTAKE LIP AND COMING DISLODGED PRIOR TO FLAME-OUT.  AIRCRAFT IS OPERATED BY CARVER AERO, INC.				1	L	7	2 	4T				A14CE   					 
1997121100131	19971211	00131	CE  	1997	12	11	97ZZZX5045       	1	19971013	G	5210	511151515	HINGE           			CESSNA	441   	441         	2076020	CE  										CABIN DOOR	CRACKED         	B	S		WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2FOR	4946 				4410067				WHILE AIRCRAFT WAS UNDERGOING A SCHEDULED INSPECTION, NOTED THE RIVETS IN THE THE AFT LOWER CABIN DOOR HINGE APPEARED TO	 BE LOOSE.  FURTHER VISUAL AND EDDY CURRENT INSPECTION SHOWED THE HINGE WAS CRACKED AT ALL THREE RIVET LOCATIONS.  THE R	IVETS HAD BEEN INSTALLED PREVIOUSLY IAW CESSNA BULLETIN PJN81-21.  HINGE WAS REMOVED AND NEW PART INSTALLED.				1	L	7	2 	3T			RT	A28CE   					 
1997121100187	19971211	00187	EU  	1997	12	11	97ZZZX5046       	1	19971012	G	7712	G555674	TRANSDUCER      			BOLKMS	117   	BK117A4     	5626017	EU  										ENGINE TORQUE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG				688	7083				TORQUE INDICATOR BEGAN TO SPIN THEN FROZE BELOW ZERO.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997121100188	19971211	00188	EU  	1997	12	11	97ZZZX5047       	1	19970926	G	7712	G555674	PRESSURE XDUCER 			BOLKMS	117   	BK117A4     	5626017	EU  										ENGINE TORQUE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117NG				508	7083				TORQUE STARTED FLUCTUATING THEN TOTAL FAILURE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997121100189	19971211	00189	EU  	1997	12	11	97ZZZX5048       	1	19970501	G	6710	10513142	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				ROD END REJECTED DUE TO CORROSION.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997121100190	19971211	00190	EU  	1997	12	11	97ZZZX5049       	1	19971010	G	2121	19A2772	FAN             			BOLKMS	BK117 	BK117C1     	5626025	EU  										AIR DIST	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FAN INTERMITTENT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997013000433	19970130	00433	SO  	1997	1	30	97ZZZX505        	1	19970107	G	2720	63451000	BRACKET         			PIPER 	PA28  	PA28180     	7102808	SO  										RUDDER PEDAL	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2316R	3800 				285487				DURING ANNUAL INSPECTION, CENTER RUDDER PEDAL BRACKET FOUND CRACKED AT 4 LOWER BOLT HOLES.  SUSPECT NOSE WHEEL SHIMMY AN	D PART DESIGN FOR FAILURE.  SUBMITTER RECOMMENDS A THOROUGH INSPECTION ANNUALLY FOR THESE CRACKS.					1	L	7	1 	3O				2A13    					 
1997121100191	19971211	00191	EU  	1997	12	11	97ZZZX5050       	1	19970501	G	6710	10513141	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				ROD END REJECTED DUE TO CORROSION.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1997121100192	19971211	00192		1997	12	11	97ZZZX5051       	4	19971013	G	3421	060002600	GYRO            		KBV350      	BELL  	230   	230         	1182149	SW  										COCKPIT VG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				3137	23019				GYRO WILL NOT SPOOL UP COMPLETELY.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997121100193	19971211	00193	NE  	1997	12	11	97ZZZX5052       	2	19971016	G	7421	9550166670	IGNITER         			BOLKMS	BK117 	BK117C1     	5626025	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				IGNITER PLUG WORN DOWN.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE				 
1997121100194	19971211	00194		1997	12	11	97ZZZX5053       	4	19971017	G	3421	060002600	GYRO            			BELL  	230   	230         	1182149	SW  										COCKPIT VG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				2640	23019				GYRO SLOW TO TURN UP.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1997121100195	19971211	00195	EU  	1997	12	11	97ZZZX5054       	1	19971005	G	2435	23032022	STARTER/GEN     			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	CHAFED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X	32   			18046	S7038				REMOVED NR 2 STARTER/GENERATOR.  FAN CHAFED HOLE IN SCREEN.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997121100196	19971211	00196	EU  	1997	12	11	97ZZZX5055       	1	19971016	G	3244	5090004910	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										TURN/BANK	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	4    			483A	7103				CIRCUIT BREAKER TRIPS.  INDICATOR HAS INTERNAL SHORT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997121100197	19971211	00197		1997	12	11	97ZZZX5056       	4	19971019	G	3421	4021541671	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										HORIZON	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				84041072	7098				BAD INPUTS TO YAW CSAS.  NOTE:  RED IMPACT INDICATOR.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997013000434	19970130	00434	CE  	1997	1	30	97ZZZX506        	1	19970109	G	3233	1693800601	ACTUATOR        			BEECH 	23    	C24R        	1151254	CE  										LT MLG	PISTON BROKEN   	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NE	01	292WC	2796 			0710	MC460				PILOT DECLARED IN-FLIGHT EMERGENCY.  HEARD LOUD POP AND HAD TO MAINTAIN RIGHT AILERON TO KEEP DIRECTIONAL CONTROL.  THEN	 GOT MAIN GEAR GREEN DOWN AND LOCKED LIGHTS.  THEN PUT ALL GEAR DOWN AND LOCKED.  TROUBLESHOOTING REVEALED LT MAIN GEAR 	ACTUATOR PISTON BROKEN FROM PISTON ROD.  SUSPECT CAUSE OUT OF RIG SITUATION AFTER REMOVAL OF ACTUATOR OR DEFECT IN PART,	 OR ASSEMBLY OF PISTON WITH LOCKNUT OVERTORQUE.			1	L	7	1 	3O				A1CE    					 
1997013000435	19970130	00435	SO  	1997	1	30	97ZZZX507        	1	19970103	G	2822	2B644	PUMP            	AIRBORNE    		PIPER 	PA34  	PA34200T    	7103406	SO  										LT ENG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	5979F	5305 			9B607	347770029				LEFT ENGINE FUEL PUMP (WHICH HAS HIGH AND LOW POSITONS) WOULD NOT WORK ON LOW SETTING DUE TO A HIGH RESISTANCE IN THE MO	TOR.  IT EVENTUALLY BURNED OUT THE RESISTOR THAT HIGH AND LOW ARE WIRED TO.  WHILE TROUBLESHOOTING THE RESISTOR (WHICH W	AS ORIGINALLY THOUGHT TO BE THE PROBLEM), THE PUMP WAS FOUND TO BE NOT WORKING ON THE LOW SETTING, AND NOISEY ON HIGH SE	TTING.  REMOVED PUMP FOR FURTHER CHECKING, AND AFTER REMOVING PUMP, A CLUNKING SOUND CAME FROM THE PUMP WHEN YOU SHOOK I	T.  TOOK PUMP APART, FOUND FUEL IN THE MOTOR, AND LOOSE FIELD.  (FIELD IS JUST GLUED IN).  THE NOISE (CLUNKING) WAS THE 	FIELD BANGING UP AGAINST THE ARMATURE.  WHEN IN A/C AND TURNED ON, MAGNETISM CAUSED LOOSE FIELD TO STICK TO THE ARMATURE	1	L	7	2 	3O				A7SO    					 
1997121100495	19971211	00495	WP  	1997	12	11	97ZZZX5076       	1	19971125	G	7400	369A45143	EPO ASSEMBLY    			HUGHES	369   	369D        	4470706	WP  										ENG REIGNITION	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J		439  			9000801D				DEFECT IN EPO ASSEMBLY CAUSED ENGINE OUT AND AUTO RE-LITE TO COME ON SENDING THE EPO ASSEMBLY IN FOR REPAIR AND/OR AN OV	ERHAUL.					1	G	7	1 	3U				H3WE    					 
1997121100496	19971211	00496		1997	12	11	97ZZZX5077       	4	19971118	G	3421	500DCF	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										HORIZON REF	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY	454  			3628	2871				HORIZON REFERENCE INDICATOR WILL NOT CAGE.						1	G	7	1 	3U				H2SW    					 
1997121100497	19971211	00497	GL  	1997	12	11	97ZZZX5078       	2	19971112	G	7210	6894171	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					MOUNT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	105LC	4962 				S789	836121			ENGINE HAD GEARBOX THAT HAD UPPER LEFT COMPRESSOR MOUNT BROKEN OFF.  FOUND NO REASON FOR BREAKAGE.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997121100498	19971211	00498	NE  	1997	12	11	97ZZZX5079       	2	19971208	G	7321	7911004092	EEC             	HAMSTD      	EEC1311     						PWA   	4060  	PW4060      	52119	NE  					ENGINE CONTROL	MALFUNCTIONED   	B	L	A	SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		8758 			C94062044					ELECTRONIC ENGINE CONTROL UNIT PASSED FUNCTIONAL TESTING, BUT EXHIBITED AN HISTORICAL RAM PARITY CODE (BINARY HICCUP) IN	 ITS FAULT MEMORY.  INTERNAL INSPECTION REVEALED A TOTAL OF 20 QUESTIONABLE SOLDER JOINTS ON UNIT'S GATE ARRAYS.  EACH A	SSEMBLY WAS INVOLVED.  THE SUSPECTED SOLDER JOINT EXHIBITED SUCH CONDITIONS AS STRESS FRACTURES AND/OR INSUFFICIENT SOLD	ER.  THESE CONDITIONS CAN LEAD TO INTERMITTENT OPERATION OF THE FULL AUTHORITY ENGINE CONTROL AND MAY CAUSE EITHER CONTR	OL CHANNEL TO BECOME INOPERABLE.  HAMILTON STANDARD ENGINEERING HAS BEEN NOTIFIED AND IS PRESENTLY EVALUATING THIS CONDI	TION.  UNITS ARE UTILIZED ON PW4000 SERIES ENGINES.						4	F			E24NE				 
1997013000436	19970130	00436	GL  	1997	1	30	97ZZZX508        	3	19970106	G	6114		HUB             			BEECH 	23    	A2324       	1151226	CE  						MCAULY	2D34C	2D34C8      	GL  	NR 2 SOCKET	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6955Q					MA303		67170		PROPELLER SUBMITTED FOR OVERHAUL AND TO C/W AD 91-15-04.  DURING NDI, A 25 INCH LONG CRACK WAS DISCOVERED IN NR 2 BLADE 	SOCKET.  LAST OVERHAUL IN 1985.  A RESEAL FOR A LEAK WAS PERFORMED ON 4-25-91.					1	L	7	1 	3O				A1CE    		5	C	P7EA	 
1997121100499	19971211	00499	EU  	1997	12	11	97ZZZX5080       	1	19971008	G	6520	4639311003	BEARING         			BOLKMS	117   	BK117A3     	5626015	EU  										T/R GEARBOX	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					983					TOLERANCES TOO TIGHT, WOULD NOT FIT ON SHAFT CORRECTLY.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1997121100500	19971211	00500		1997	12	11	97ZZZX5081       	4	19971016	G	3453	4530089	LORAN           		AVA1000     	CESSNA	650   	650         	2076802	CE  										COCKPIT	MALFUNCTIONED   	B			TI1R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	05					18527					LORAN GIVES CONSTANT BATTERY WARNING MESSAGE.  REMOVED AND REPLACED.						2	L	7	2 	4F				A9NM    					 
1997121100501	19971211	00501	CE  	1997	12	11	97ZZZX5082       	1	19970804	G	2740	99141973B	CONTROLLER      			CESSNA	650   	650         	2076802	CE  										STAB CONTROL	MALFUNCTIONED   	B	L		K3GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										UNIT REPORTED TO CAUSE AN INTERMITTENT TRIM FAIL ANNUNCIATOR LIGHT.						2	L	7	2 	4F				A9NM    					 
1997121100502	19971211	00502	NM  	1997	12	11	97ZZZX5083       	1	19971112	G	2510	25W122201502	SEAT            			ISRAEL	1125  	1125        		NM  										PILOT LT AFT	BROKEN          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11		2487 			082	1125046				DURING A C-CHECK INSPECTION, THE PILOT'S SEAT BACK ON THE LEFT ATTACH POINT, THE SPACER TUBE WAS FOUND BROKEN.  SUSPECT 	THE BOLTS WORKED LOOSE ALLOWING ADDITIONAL STRESS TO BE PLACED UPON THE SPACER TUBE.  CHECK OF THE BOLTS DURING INSPECTI	ONS BY VISUAL AND WITH WRENCH TO ENSURE THE BOLTS REMAIN TIGHT.				2	L	7	2 	4F			RT	A16NM   					 
1997121100503	19971211	00503	SW  	1997	12	11	97ZZZX5084       	1	19971124	G	2432	RG390E	BATTERY         			SWRNGN	SA226 	SA226T      	8780122	SW  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05					CBC275815					BATTERY SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES IN-FLIGHT OR DURING LANDING ABOUT 2 INCHES.  CONCO	RDE FAX SAID TO PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	2 	4T			RT	A5SW    					 
1997121100504	19971211	00504	EA  	1997	12	11	97ZZZX5085       	2	19971117	G	7314	RG7570K4	PUMP            	ROMEC       		BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1A4  	41536	EA  					FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	09	1551L	20694	219  		B1939	P391				PUMP WAS SPEWING FUEL AT CASE PARTING LINE AT REGULATOR.  GASKET HAD PUSHED ITS WAY OUT FROM BETWEEN HALVES.  RESEALED B	Y REPAIR STATION.  WAS TOLD THIS WAS OFTEN SEEN DUE TO THINNESS OF GASKET IF ONLY OIL OR GREASE WERE PRESENT ON MATING S	URFACES WHEN ASSEMBLED.  RECOMMEND NEW GASKET DESIGN.				1	L	7	2 	3O	3	O		A12CE   	E10EA				 
1997121100505	19971211	00505	NM  	1997	12	11	97ZZZX5086       	1	19971101	G	5311		FRAME           			BOEING	727   	727251      	138408H	NM  										BS 848 LT	SEPARATED       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK INSPECTION, STR 5L AND STR 6L HAD PULLED FASTENERS AND SEPARATING AT FRAME STA 848.						2	L	7	3 	4F				A3WE    					 
1997121100506	19971211	00506	NM  	1997	12	11	97ZZZX5087       	1	19971101	G	5311		FRAME           			BOEING	727   	727251      	138408H	NM  										BS 848 RT	SEPARATED       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK INSPECTION, STR 6R HAD PULLED FASTENERS AND SEPARATED FROM FRAME AT STA 848.						2	L	7	3 	4F				A3WE    					 
1997121100507	19971211	00507	NM  	1997	12	11	97ZZZX5088       	1	19971101	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 848	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK INSPECTION, STR 17L WAS FOUND CRACKED AT STA 848.						2	L	7	3 	4F				A3WE    					 
1997121100508	19971211	00508	NM  	1997	12	11	97ZZZX5089       	1	19971101	G	5311		FRAME           			BOEING	727   	727251      	138408H	NM  										BS 825	SEPARATED       	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK INSPECTION, STR 5L AND STR 6L HAD PULLED FASTENERS AND SEPARATED FRAME AT STA 825.						2	L	7	3 	4F				A3WE    					 
1997121100509	19971211	00509	NM  	1997	12	11	97ZZZX5090       	1	19971101	G	5743		TRUNNION BEAM   			BOEING	727   	727251      	138408H	NM  										LT MLG WELL	BOLTS SHEARED   	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK INSPECTION, TWO SHEARED BOLTS WERE FOUND ON THE LEFT HAND MAIN LANDING GEAR TRUNNION BEAM AT STA 18A.						2	L	7	3 	4F				A3WE    					 
1997121100510	19971211	00510	EU  	1997	12	11	97ZZZX5091       	1	19971104	G	2840	162J	CONNECTOR       			AMD   	FALC50	FALCON900   	2700160	EU  										FUEL QUANTITY	BROKEN          	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	404VL	687  				158				AIRCRAFT READ ZERO ON GROUP THREE FUEL QUANTITY.  TROUBLESHOT TO A BROKEN WIRE ON 162J CONNECTOR.  WHEN CONNECTOR WAS RE	MOVED, THE POTTING COMPOUND WAS DISINTEGRATING.  SUBMITTER STATED TWO OTHER CASES OF SAME PROBLEM ON SAME CONNECTOR.					2	L	7	3 	4F			RT	A46EU   					 
1997121100511	19971211	00511	CE  	1997	12	11	97ZZZX5092       	1	19971112	G	2913	165FE00503	MOTOR ASSY      	VICKERS     	939789      	RKWELL	NA265 	NA26565     	7630107	CE  										HYDRAULIC PUMP	FAILED          	B			RO3R	O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CE	03	652MK	22   			MX58523	46536				STRONG VIBRATION FELT IN AFT SECTION OF AIRCRAFT DURING FLIGHT.  HYDRAULIC SYSTEM PRESSURE COULD NOT BE MAINTAINED USING	 NR 1 HYDRAULIC PUMP.  NR 1 HYDRAULIC PUMP HAD FAILED.  FOUND METAL CONTAMINATION IN BOTH PRESSURE AND RETURN FILTERS, P	UMP HAD BEEN MODIFIED AT TIME OF INSTALLATION BY C/W VICKERS SL -29-940070-1.  HYDRAULIC PUMP SENT TO MANUFACTURER FOR T	EAR-DOWN.  AWAITING RESULTS AT THIS TIME.			2	L	7	2 	4J				A2WE    					 
1997121100512	19971211	00512	EU  	1997	12	11	97ZZZX5093       	1	19971124	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	300LS				CBC275862					BOTH BATTERIES SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES IN-FLIGHT OR DURING LANDING.  CONCORDE FAX 	SAID TO PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	2 	4F			RT	A3EU    					 
1997121100513	19971211	00513	EU  	1997	12	11	97ZZZX5094       	1	19971124	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	300LS				CBC275863					BOTH BATTERIES SUPPORT SLEEVE ON THE OUTSIDE OF BATTERY SLIDES DOWN ABOUT 2 INCHES IN-FLIGHT OR DURING LANDING.  CONCORD	E FAX SAID TO PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	2 	4F			RT	A3EU    					 
1997121100514	19971211	00514	CE  	1997	12	11	97ZZZX5095       	1	19971104	G	2740	99141973B	ACTUATOR CONTROL			CESSNA	650   	650         	2076802	CE  										PITCH TRIM	FAILED          	D				K				NONE                    				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			GL	19	500FR				249	650208				AIRCRAFT PRIMARY PITCH TRIM INOPERABLE.  IF NOSE UP OR DOWN WAS SELECTED, PITCH TRIM WOULD NOT MOVE AND PITCH TRIM FAIL 	ANNUNCIATOR WOULD COME ON.  TROUBLESHOT DOWN TO ACTUATOR CONTROL UNIT.  ORDERED AND INSTALLED REPLACEMENT UNIT.  TURNED 	AIRCRAFT POWER ON, PITCH TRIM FAIL ANNUNCIATOR WOULD COME ON IMMEDIATELY AND PITCH TRIM WOULD BE INOPERABLE.  RE-CHECKED	 SYSTEM DOWN TO ACTUATOR CONTROL UNIT.  ORDERED AND INSTALLED ANOTHER REPLACMENT UNIT.  THIS ONE WORKED.			2	L	7	2 	4F				A9NM    					 
1997121100515	19971211	00515	EU  	1997	12	11	97ZZZX5096       	1	19971124	G	2432	RG390E	BATTERY         			AMD   	FALC50	FALCON900   	2700160	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	900NE				CBC262741	83				BOTH SUPPORT SLEEVES ON THE OUTSIDE OF BATTERY SLIDES DOWN ABOUT 2 INCHES IN-FLIGHT OR DURING LANDING.  CONCORDE FAX SAI	D TO PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	3 	4F			RT	A46EU   					 
1997121100516	19971211	00516	EU  	1997	12	11	97ZZZX5097       	1	19971124	G	2432	RG390E	BATTERY         			AMD   	FALC50	FALCON900   	2700160	EU  										DC SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	900NE				CBC262740	83				BOTH SUPPORT SLEEVES ON THE OUTSIDE OF BATTERY SLIDES DOWN ABOUT 2 INCHES IN-FLIGHT OR DURING LANDING.  CONCORDE FAX SAI	D TO PUSH SLEEVE UP AND PUT TAPE ON BOTTOM OF SLEEVE.					2	L	7	3 	4F			RT	A46EU   					 
1997121100517	19971211	00517	SO  	1997	12	11	97ZZZX5098       	2	19971119	G	8530	630046	PIN PLUG        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					NR 2 CYL PISTON	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	1528K	1149 				E2453	675431			ON REMOVAL OF NR 2 CYLINDER FOR LOW COMPRESSION, THE ONE-PIECE FORGED ALUMINUM PLUG IN THE CENTER OF THE WRIST PIN WAS F	OUND BROKEN IN TWO, TWO INCHES FROM THE END.					1	L	7	1 	3O	3	O		3A15    	E3SO				 
1997121100518	19971211	00518	SO  	1997	12	11	97ZZZX5099       	1	19971125	G	5540	51108004	HINGE           			PIPER 	PA31  	PA31310     	7103103	SO  										RUDDER	SEIZED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ	3572 				317712055				FOUND THE RUDDER TOP HINGE BOLT SEIZED IN THE HINGE BEARING AND COULD NOT BE FREED.  BOTH HINGE ASSEMBLIES (THE RUDDER A	ND VERTICAL STABILIZER) HAD TO BE REPLACED.  THE CORROSION WAS SEVERE AND THERE WAS NO EVIDENCE OF LUBRICATION.					1	L	7	1 	3O			RT	A20SO   					 
1997013000438	19970130	00438	CE  	1997	1	30	97ZZZX510        	1	19970118	G	2810	120006524	NIPPLE          			CESSNA	182   	182Q        	2072732	CE  										RT FUEL BLADDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	735SN	1044 				18265649				WHILE CHANGING FUEL LINE CONNECTION HOSES ON LT AND RT FUEL BLADDER, NIPPLES BROKE OFF.  NO EVIDENCE OF CRACKING OR PREV	IOUS LEAKING NOTED.  SUSPECT CAUSE - OLD AGE?					1	H	7	1 	3O			NT	3A13    					 
1997121100519	19971211	00519	SO  	1997	12	11	97ZZZX5100       	1	19971125	G	5530	4805500	HINGE           			PIPER 	PA31  	PA31310     	7103103	SO  										VERT STABILIZER	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ	3572 				317712055				FOUND THE RUDDER TOP HINGE BOLT SEIZED IN THE HINGE BEARING AND COULD NOT BE FREED.  BOTH HINGE ASSEMBLIES (THE RUDDER A	ND VERTICAL STABILIZER) HAD TO BE REPLACED.  THE CORROSION WAS SEVERE AND THERE WAS NO EVIDENCE OF LUBRICATION.					1	L	7	1 	3O			RT	A20SO   					 
1997121100520	19971211	00520		1997	12	11	97ZZZX5101       	4	19971115	G	2210	065501100	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T	541  				318152089				PILOT REPORTED UPON COMPLETION OF PRE-FLIGHT CHECK, ACCELEROMETER SWITCH WOULD NOT TEST OR DISCONNECT AUTOPILOT AS REQUI	RED BY POH INSTRUCTIONS.  THE SYSTEM WAS FOUND TO DISCONNECT IN THE DOWN POSITION SOMETIMES, AND WOULD NOT DISCONNECT IN	 THE UP POSITION.  THE SWITCH IS OF VERY POOR DESIGN AND CONSTRUCTION.  INNER AND OUTER HOUSINGS ARE OF DISSIMILAR METAL	 AND DO NOT EXPAND AND CONTRACT AT THE SAME RATE NOT ALLOWING THE SWITCH TO MOVE AT DIFFERENT TEMPS.  WHOLE SYSTEM IS OV	ER-ENGINEERED.  ONE SIMPLE TSO TO REMOVE THE SWITCH FROM THE SYSTEM WOULD CURE THE PROBLEM.  IF SWITCH IS USED FOR WHAT 	IT WAS DESIGNED, PILOT HAS ALREADY LOST CONTROL OF THE AIRCRAFT!!	1	L	7	2 	3O				A20SO   					 
1997121100521	19971211	00521		1997	12	11	97ZZZX5102       	4	19971119	G	2210	065501100	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T		306  			318152089				DURING A PRE-FLIGHT CHECK, PILOT TESTED THE ACCELEROMETER SWITCH.  IT WOULD TEST OK IN THE DOWN POSITION, BUT WOULD NOT 	TEST IN THE UP POSITION.  SUBMITTER RECOMMENDS THAT THE PART BE TSO'D OUT OF THE SYSTEM.					1	L	7	2 	3O				A20SO   					 
1997121100522	19971211	00522	SO  	1997	12	11	97ZZZX5103       	1	19971124	G	3710	211CC	PUMP            			PIPER 	PA28  	PA28180     	7102808	SO  										VACUUM SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4240T		1    		70588	287205112				PUMP FAILED ON FIRST TAKEOFF.  VACUUM PUMP NEWLY OVERHAULED.						1	L	7	1 	3O				2A13    					 
1997121100523	19971211	00523	CE  	1997	12	11	97ZZZX5104       	1	19971117	G	5531	17330021	SPAR            			CESSNA	177   	177RG       	2073709	CE  										VERTICAL FIN	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	691DB					177RG1314				VERTICAL FIN SPAR CRACKED ON BOTH SIDES RIGHT BEHIND TOP RUDDER HINGE.  CRACKS MEASURE CLOSE TO .75 INCH ON BOTH SIDES. 	 VERTICAL FIN NOT DISTORTED AND RUDDER HINGE SHOWS NO DAMAGE.  CAUSE OF CRACKS UNKNOWN.					1	H	7	1 	3O				A20CE   					 
1997121100524	19971211	00524	EU  	1997	12	11	97ZZZX5105       	2	19971026	G	8500		ENGINE          			AMTR  	500   	MINI500     	13015HW	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					POWER SECTION	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	05	7234Y					231				DURING PATTERN WORK, ENGINE FAILED AT ABOUT 500 FEET AFTER TAKEOFF.  HELICOPTER WAS DESTROYED.  REASON FOR ENGINE FAILUR	E NOT GIVEN.					1	G	7	1 	3I	3	I	NC	EXPA1G71	EXPE3I				 
1997121100525	19971211	00525	CE  	1997	12	11	97ZZZX5106       	1	19971120	G	5520	50350053	FITTING         			CESSNA	421   	421C        	2076016	CE  										LT ELEVATOR	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2656B	4500 				421C0711				DURING A 100-HOUR INSPECTION, THE END FITTING ON THE LT ELEVATOR WAS FOUND CRACKED AT THE HOLE FOR THE TAPERED PIN.  IT 	APPEARS THE END FITTING HAD BEEN REMOVED FROM THE AIRCRAFT BEFORE.  SUBMITTER STATED THE USE OF PROPER TORQUE WHEN INSTA	LLING THE TAPERED PINS WOULD PREVENT CRACKS AT THE PIN HOLE FROM OCCURRING.				1	L	7	2 	3O				A7CE    					 
1997121100527	19971211	00527	EU  	1997	12	11	97ZZZX5108       	1	19971119	G	7714	TG010005006	TACH GENERATOR  			PARTEN	P68   	P68TCOBS    	6780108	EU  										ENGINE	FAILED          	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	737				313	40004OTC				TACHOMETER GENERATOR FAILED.  HIGH TIME ON PART.  SUSPECT NOT ENOUGH LUBRICATION FOR TIME ON PART.  SUBMITTER STATED CHA	NGE AT PROPER LIFE LIMIT.					1	H	7	2 	30				A31EU   					 
1997121100528	19971211	00528	CE  	1997	12	11	97ZZZX5109       	1	19971029	G	3213	169810000663	HOUSING         			BEECH 	23    	C23         	1151242	CE  										NLG WHEEL	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	6638B	5200 				M2217				NOSE WHEEL ASSEMBLY FAILED, DEPARTED AIRCRAFT SHORTLY AFTER TOUCH-DOWN.  LANDING COMPLETED ON MAINS AND NOSE GEAR TRUSS 	COLLAR.  INVESTIGATION REVEALED STRESS CRACKS IN PISTON SLEEVE AT ATTACH POINTS; SUSPECT CAUSED BY OVERSTEERING DURING G	ROUND TO WING WITH POWER TUG.  SUBMITTER RECOMMENDS INSPECTING NOSE GEAR STEERING LIMIT STOP NUT SLEEVE.  IF NYLON BUSHI	NG IS DENTED, NOSE GEAR SHOULD BE DISASSEMBLED AND INSPECTED.			1	L	7	1 	3O				A1CE    					 
1997013000439	19970130	00439	CE  	1997	1	30	97ZZZX511        	1	19970118	G	2810	120006523	NIPPLE          		BTC67       	CESSNA	182   	182Q        	2072732	CE  										LT FUEL BLADDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	735SN	1044 			7682749	18265649				WHILE CHANGING FUEL LINE CONNECTION HOSES ON LT AND RT FUEL BLADDER, NIPPLES BROKE OFF, NO EVIDENCE OF CRACKING OR PREVI	OUS LEAKAGE NOTED.  SUSPECT CAUSE OLD AGE?					1	H	7	1 	3O			NT	3A13    					 
1997121100529	19971211	00529	SO  	1997	12	11	97ZZZX5110       	1	19970801	G	2913	38998005	PUMP            			PIPER 	PA32  	PA32R301T   	7103220	SO  										HYDRAULICS	FAILED          	D	L			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	84KA	3488 				32R8129052				ELECTRO HYDRAULIC PUMP RUNS, BUT PRODUCED INSUFFICIENT HYDRAULIC PRESSURE TO MOVE GEAR PAST HALF RETRACT POSITION.  FOUN	D FLUID LEVEL FULL.  NO EXTERNAL LEAKS.  PUMP SENT TO PIPER FOR REPAIR, BUT THEY LOST UNIT SOMEPLACE, SO WAS UNABLE TO F	IND OUT WHAT WAS WRONG.  INSTALLED NEW PUMP IN AIRCRAFT.				1	L	7	1 	3O				A3SO    					 
1997121100530	19971211	00530	CE  	1997	12	11	97ZZZX5111       	1	19971111	G	2720	12606311	ROD END         			CESSNA	206   	U206G       	2073356	CE  										RUDDER BAR	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	995RA	3084 				U20604252				DURING PRE-FLIGHT INSPECTION, EXCESSIVE FREE MOVEMENT IN RUDDER WAS NOTED.  FURTHER INVESTIGATION REVEALED THE ROD END B	ETWEEN THE RUDDER BAR AND BUNGEE HAD CRACKED OFF.  THE PART SHOWED EVIDENCE OF HAVING BEEN CRACKED FOR A WHILE.  THIS PA	RT SEEMS TO BE VERY SMALL FOR THE STRESS IT COMES UNDER.  SUBMITTER RECOMMENDS TOUGHER MATERIAL OR INCREASED SIZE.  THIS	 IS THE FOURTH BROKEN ROD END SUBMITTER HAS FOUND ON U206 SERIES AIRCRAFT.			1	H	7	1 	3O				A4CE    					 
1997121100531	19971211	00531	SO  	1997	12	11	97ZZZX5112       	1	19970911	G	7603	5697905	CABLE ASSY      			PIPER 	PA42  	PA42720     	7104212	SO  										NR 1 THROTTLE	PARTED          	B	S	A	S88R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	9091J	3446 				425501035				DURING PRE-FLIGHT OPERATIONAL CHECKS, THE LEFT ENGINE THROTTLE CABLE STAINLESS STEEL RIBBON CORE PARTED WHERE THE CABLE 	PASSES THROUGH A CUT-OUT IN THE AILERON BELLCRANK RT MOUNTING BRACKET.  ENGINE CONTROL WAS LOST AND THE MISSION ABORTED.	  INVESTIGATION REVEALED THE CABLE INSTALLATION VIOLATED THE 7 INCH MINIMUM BEND RADIUS AT THE POINT OF PARTING.  THE CU	T-OUT AREA IN THE BRACKET WAS SUBSEQUENTLY ENLARGED TO RELIEVE THE CABLE BEND.  THE CABLE ASSEMBLY WAS REPLACED AND THE 	AIRCRAFT RETURNED TO SERVICE.		1	L	7	2 	4T				A23SO   					 
1998050600139	19980506	00139	WP  	1998	5	6	97ZZZX5113       	2	19971119	G	7230	30756432	RETAINER SEAL   								GARRTT	TFE731	TFE731*     	01518	WP  					HP COMP NR 5	MISIDENTIFIED   	B			IY2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										DURING INSTALLATION OF SB 72-3596 R5 (REPLACEMENT OF MAIN SHAFT CARBON SEALS AND ASSOCIATED COMPONENTS), MECHANIC FOUND 	THE NR 5 SEAL RUNNER RETAINER PN 3075635-2 WAS IDENTIFIED AS PN 3075643-2.  THIS PART NUMBER IS FOR THE NR 4 SEAL RUNNER	 RETAINER.  INSPECTION STAMP ADJACENT TO PART NUMBER IS 16/868.  THIS SERVICE BULLETIN IS VERY COMPLEX AND IS HARD TO ID	 PARTS WITHOUT CURRENT PART NUMBER.  SUBMITTER STATED ALLIED SIGNAL MUST DO A BETTER JOB WITH SUPERVISION AND TRAINING O	F THEIR INSPECTION PERSONNEL.  PART HAS BEEN RETURNED TO ALLIED SIGNAL, PHX.							4	F			E6WE				 
1998050600140	19980506	00140		1998	5	6	97ZZZX5114       	4	19971121	G	3418	1513	LIFT DETECTOR   			BEECH 	55    	E55         	1152732	CE  										SWITCH	SHORTED         	B		A	RT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	163SP	219  			336576	TE872				AIRCRAFT WAS ON RAMP AFTER LANDING IN WET SNOW.  WITH ADDITIONAL SNOW ACCUMULATING ON THE AIRCRAFT, THE STALL WARNING HO	RN BEGAN TO SOUND.  PILOT SILENCED HORN WITH CIRCUIT BREAKER AND ADVISED MAINTENANCE.  LIFT DETECTOR WAS FOUND SHORTED I	NTERNALLY.  AFTER EXTERNAL HEATING OF THE LIFT DETECTOR TO REMOVE MOISTURE, FUNCTION CHECKS WERE NORMAL.  SUBMITTER RECO	MMENDS MANUFACTURER USE ENVIRONMENTALLY SEALED MICROSWITCH IN THE LIFT DETECTOR ASSEMBLY TO AVOID FALSE STALL INDICATION	S.		1	L	7	2 	3O				3A16    					 
1998050600141	19980506	00141	CE  	1998	5	6	97ZZZX5115       	1	19971103	G	5512	5062000153	SKIN            		50600001623 	BEECH 	90    	E90         	1152914	CE  										LT HORIZ STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	228RA	5794 				LW197				AFTER REMOVAL OF THE SURFACE DE-ICE BOOT, A SMALL CRACK APPROXIMATELY .6250 INCH LONG WAS FOUND RADIATING FROM A RIVET H	OLE ON THE LEFT HORIZONTAL STABILIZER AT STA 63.0.  THE CRACK WAS RADIATING OUTBOARD AND AFT.  CRACKED AREA WAS REMOVED 	AND A FLUSH DOUBLER WAS INSTALLED.				1	L	7	2 	3T				3A20    					 
1998050600142	19980506	00142	CE  	1998	5	6	97ZZZX5116       	1	19971009	G	5522	101610000606	ELEVATOR        			BEECH 	200   	200BEECH    	1152920	CE  										RT OUTBOARD	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	520MC	8540 				BB43				AFTER A HANGAR RASH INCIDENT, THE RIGHT ELEVATOR WAS BEING REPAIRED FOR DAMAGE TO THE FIBERGLASS TIP.  AFTER REMOVAL OF 	THE TIP, THREE HOLES IN THE OUTBOARD TRAILING EDGE AREA OF THE SKIN WERE FOUND FILLED WITH BODY FILLER.  THE FILLER WAS 	REMOVED AND AN ALUMINUM DOUBLER WAS INSTALLED AFTER BEING APPROVED ON FORM 8110-3.				1	L	7	2 	4T				A24CE   					 
1998050600143	19980506	00143	CE  	1998	5	6	97ZZZX5117       	1	19971113	G	5753		BRACKET         			BEECH 	200   	200BEECH    	1152920	CE  										RT OTBD FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	56CC	893  				BB189				DURING INSPECTION, A .50 INCH CRACK WAS NOTED WHERE THE BRACKET FOR THE FLAP INNER CONNECT ATTACHES ON THE RIGHT OUTBOAR	D FLAP.  IT APPEARS THE ROD END FOR THE INNER CONNECT WAS LOOSE WHERE IT ATTACHED TO THE BRACKET AND ALLOWED ENOUGH PLAY	 FOR THE ROD END TO STRIKE THE BASE OF THE BRACKET CAUSING A CRACK.				1	L	7	2 	4T				A24CE   					 
1998050600144	19980506	00144	CE  	1998	5	6	97ZZZX5118       	1	19971113	G	5753		SKIN            			BEECH 	200   	200BEECH    	1152920	CE  										INBD FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	56CC	8093 				BB189				DURING INSPECTION, A .75 INCH CRACK WAS FOUND NEAR A RIVET WHICH ATTACHES THE ENGINE NACELLE TRAILING EDGE FAIRING TO TH	E INBOARD FLAP.  THE CRACK WOULD NOT HAVE RESULTED IN ANY DAMAGE, BUT SINCE IT IS PART OF A CONTROL SURFACE, RESULTED IN	 BEING A MAJOR REPAIR.				1	L	7	2 	4T				A24CE   					 
1998050600145	19980506	00145	CE  	1998	5	6	97ZZZX5119       	1	19971113	G	5730		PANEL           			BEECH 	200   	200BEECH    	1152920	CE  										RT WING OTBD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	56CC	8093 				BB189				THE INBOARD AREA OF THE RIGHT OUTBOARD WING PANEL HAS A .3750 INCH CRACK FROM THE TOP OF THE RADIUS CUT-OUT ON THE LEADI	NG EDGE FAIRING.					1	L	7	2 	4T				A24CE   					 
1998050600146	19980506	00146	CE  	1998	5	6	97ZZZX5120       	1	19971118	G	5620	1014301835	WINDOWS         			BEECH 	200   	200BEECH    	1152920	CE  										NR 5 RT	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	60PD					BB58				DURING ROUTINE CLEANING OF THE AIRCRAFT WINDOWS, DELAMINATION BUBBLES WERE NOTED NEAR THE BOTTOM EDGE AREA OF THE NR 5 P	ASSENGER WINDOW.  BUBBLES WERE ABOUT THE SIZE OF A PENCIL ERASER OR SMALLER.  TOTAL AREA WAS APPROXIMATELY 8 INCHES BY .	50 INCH.  WINDOW WAS REPLACED WITH NEW.				1	L	7	2 	4T				A24CE   					 
1998050600147	19980506	00147	SO  	1998	5	6	97ZZZX5121       	1	19971027	G	5412	3575305	FIREWALL        			PIPER 	PA28  	PA28R201T   	7102813	SO  										TURBO AREA	CORRODED        	B			H8AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	36751					28R7803339				DURING MAINTENANCE FOR ALTERNATOR FAILURE, FOUND FIREWALL HAD A HOLE DUE TO CORROSION.  SUSPECT CORROSION DUE TO HEAT EX	POSURE FROM TURBOCHARGER.					1	L	7	1 	3O				2A13    					 
1998050600148	19980506	00148	SO  	1998	5	6	97ZZZX5122       	1	19970917	G	5412	3575305	FIREWALL        			PIPER 	PA28  	PA28R201T   	7102813	SO  										TURBO AREA	CORRODED        	B			H8AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6166H	2108 				28R7803093				HOLE IN FIREWALL OBSERVED DURING ANNUAL INSPECTION.  UPON REMOVAL, FOUND INTERIOR CORROSION MUCH MORE ADVANCED THAN EXTE	RIOR.  HOLE SEEMED TO BE CAUSED BY CONSTANT EXPOSURE TO TURBOCHARGER OPERATING TEMPERATURES.  PLASTIC ON AFT SIDE OF FIR	EWALL EXHIBITED SIGNS OF THERMAL BREAKDOWN AND CHARRING.				1	L	7	1 	3O				2A13    					 
1998050600149	19980506	00149	CE  	1998	5	6	97ZZZX5123       	1	19971017	G	7120	05131329	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENG MT ATTACH	CRACKED         	B	S	A	BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	7518M					55818				ALL FOUR ENGINE MOUNT BRACKETS ON THE FORWARD END OF THE ENGINE MOUNT STRINGERS WERE CRACKED AND HOLE AREA BENT OUT.  TH	IS AREA BULGED OUT AROUND BOLT HOLE.  AIRCRAFT HAS LYCOMING 180 HP MOD.					1	H	7	1 	3O			NT	3A17    					 
1998050600150	19980506	00150	CE  	1998	5	6	97ZZZX5124       	1	19971017	G	7120	051313210	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENG MT ATTACH	CRACKED         	B			BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	7518M					55818				ALL FOUR ENGINE MOUNT BRACKETS ON THE FORWARD END OF THE ENGINE MOUNT STRINGERS WERE CRACKED AND HOLE AREA BENT OUT.  TH	IS AREA BULGED OUT AROUND BOLT HOLE.  AIRCRAFT HAS LYCOMING 180 HP MOD.					1	H	7	1 	3O			NT	3A17    					 
1998050600151	19980506	00151	CE  	1998	5	6	97ZZZX5125       	1	19971017	G	7120	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENG MT ATTACH	CRACKED         	B			BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	7518M					55818				ALL FOUR ENGINE MOUNT BRACKETS ON THE FORWARD END OF THE ENGINE MOUNT STRINGERS WERE CRACKED AND HOLE AREA BENT OUT.  TH	IS AREA BULGED OUT AROUND BOLT HOLE.  AIRCRAFT HAS LYCOMING 180 HP MOD.					1	H	7	1 	3O			NT	3A17    					 
1998050600152	19980506	00152		1998	5	6	97ZZZX5126       	4	19971107	G	6113	075263717	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  										SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	7353S	2302 				18265144				FOUND SPINNER BULKHEAD CRACKED AT ATTACHMENT BOLTS.  SUBMITTER STATED THIRD BULKHEAD FOUND CRACKED THIS YEAR.  OTHER AIR	CRAFT RECORDS SHOW PART TIMES AT 1,560 - 1,890 HOURS.					1	H	7	1 	3O			NT	TA13    					 
1998050600153	19980506	00153	CE  	1998	5	6	97ZZZX5127       	1	19971021	G	3242	164306151	DISC            			CESSNA	172   	172P        	2072436	CE  										RT MLG	OVERHEATED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	97LP					17274398				UPON INSTALLATION OF NEW CLEVELAND BRAKE DISC AND LININGS ON RT MAIN WHEEL, ACFT WAS TAXIED FOR RUN-UP AND LOUD SQUEELIN	G EMITTED FROM RT BRAKE.  PAINT ON DISC DAMAGED LININGS AND CAUSED OVERHEATING.  REMOVED PAINT FROM DISC WHERE PADS RIDE	, INSTALLED NEW LININGS, CHECKED SATISFACTORILY.  SUBMITTER STATED NEW BRAKE DISC'S SHOULD NOT BE PAINTED WHERE LININGS 	RIDE.  CONTACTED PARKER HANNIFIN CORP.			1	H	7	1 	3O			NT	3A12    					 
1998050600154	19980506	00154	SO  	1998	5	6	97ZZZX5128       	2	19971105	G	7322	1048931	CARBURETOR      	FACET       	MA45        	CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					MIX LEVER	WORN            	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NM	03	1331S				CL02539	18264895	464286			INSPECTION OF ENGINE AFTER EMERGENCY LANDING FOUND WHEN MIXTURE WAS FULL RICH, MIXTURE LEVER ON CARBURETOR COULD BE PUSH	ED TO FULL LEAN WHILE CONTROL CABLE STAYED.  CABLE ATTACH BOLT WAS NOT WORN AT ALL, BUT CONTROL LEVER DID HAVE A GROOVE 	WORN INTO IT ALLOWING LEVER TO MOVE.  THE ORIGINAL LOG BOOKS WERE LOST IN 1984.  NO LOG BOOK ENTRY SINCE THEN TO INDICAT	E REPAIR OR OVERHAUL OF CARBURETOR.  TOTAL TIME OF AIRCRAFT AND ENGINE, 1,809.1 HOURS.  IT IS UNKNOWN IF ENGINE WAS EVER	 OVERHAULED.		1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1998050600155	19980506	00155	CE  	1998	5	6	97ZZZX5129       	1	19971101	G	3252	14421121	BARREL          			CESSNA	172   	172RG       	2072438	CE  										SHIMMY DAMPENER	FAILED          	D		A		K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	99	5331V					172RG0506				AIRCRAFT WAS BROUGHT TO MAINTENANCE AFTER A TRAINING FLIGHT WITH REPORT OF A SEVERE NOSE WHEEL VIBRATION.  AN INSPECTION	 REVEALED THAT THE END OF THE SHIMMY DAMPENER BARREL CLOSEST TO THE SERVICE HOLE WAS BROKEN OFF.  THE OUTER RETAINING LI	NE AND BEARING HEAD WERE MISSING.				1	H	7	1 	3O				3A17    					 
1998050600156	19980506	00156	EA  	1998	5	6	97ZZZX5130       	2	19971125	G	7414		MAGNETO         	ELECTROSYS  		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					DISTRIB GEARS	FAILED          	D	P			A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SW	99	59829	1602 			6070845	317652081	L780661A			AFTER DEPARTURE AND CLIMBING THROUGH 1,200 FEET AGL, PILOT REPORTED THE LEFT ENGINE POPPED TWICE AND SHUT DOWN.  UPON IN	SPECTION, FOUND THE MAGNETO DISTRIBUTOR DRIVE GEARS WERE STRIPPED.  ALSO NOTED WAS THE BUSHING IN THE DISTRIBUTOR WAS WO	RN OUT.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998050600158	19980506	00158	EU  	1998	5	6	97ZZZX5132       	1	19971101	G	3310	1179203103	CONTROL         		830000501   	BOLKMS	117   	BK117A3     	5626015	EU  										LIGHTS	OVERHEAT        	D				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	99	911MZ				0550	7098				INSPECTED RHEOSTAT, WIRING, AND INTENSITY CONTROL UNIT.  FOUND CONTROL UNIT TO HAVE STRONG ELECTRICAL ODOR.  REPLACED WI	TH NEW UNIT.  OPS CHECK GOOD.					1	G	7	2 	3U				H13EU   					 
1998050600164	19980506	00164	SW  	1998	5	6	97ZZZX5133       	1	19970929	G	6410	406016100119	BLADE           		407012101107	BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457AL	1257 			A1518	53151				POST-FLIGHT FOUND TAILROTOR BLADE CRACKED AT INBOARD RADIUS INSIDE TOWARD LEADING EDGE.  POSSIBLY STARTED AT CORROSION S	POT.					1	G	7	1 	3U			O	H2SW    					 
1998050600165	19980506	00165	EU  	1998	5	6	97ZZZX5134       	1	19971105	G	5302	1052180110033	PLATE           			BOLKMS	105   	BO105C      	5626005	EU  										TAILBOOM MOUNT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	502AL					S103				DISCOVERED DURING DAILY INSPECTION, WORKING RIVETS AT TAIL ROTOR DRIVESHAFT FORWARD ATTACH BRACKET.  REMOVED BRACKET AND	 DISCOVERED PLATE CRACKED AT RIVET HOLE.					1	G	7	2 	3U				H3EU    					 
1998010700001	19980107	00001	GL  	1998	1	7	97ZZZX5135       	1	19971116	G	2721		SWITCH          			AMTR  	GAIR  	GLASAIRIII  	05691HK	GL  										RUDDER TRIM	STUCK           	D		A		C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			WP	23	540FT					2107				RUDDER TRIM ROCKER SWITCH STUCK IN LEFT POSITION CAUSING FULL LEFT RUDDER TRIM DURING TAKEOFF ROLL.  TAKEOFF ABORTED.  A	FTER MAXIMUM APPLICATION OF BRAKES, BRAKE LINE FAILED AND SUBSEQUENT BRAKE FIRE.  SWITCH FAILURE WAS ABLE TO BE DUPLICAT	ED APPROXIMATELY 1 OUT OF 10 ACTUATIONS OF SWITCH.				1	L	7	1 	3O			RT	EXPA1L71					 
1997121800045	19971218	00045	EA  	1997	12	18	97ZZZX5136       	1	19971125	G	3244	256K433	TIRE            			CNDAIR	CL600 	CL6001A11   	1900302	EA  										SIDEWALL	DEFECTIVE       	B		A	JO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	90UC				71020931	1023				DURING POST-FLIGHT INSPECTION, A BUBBLE WAS FOUND ON THE SIDEWALL OF TIRE.  AFTER TIRE WAS REPLACED, THE S/N WAS CHECKED	 AGAINST ANOTHER TIRE THAT HAD BEEN REMOVED PREMATURELY FOR AIR LEAKING FROM WEEP HOLES IN SIDEWALL.  THAT TIRE S/N WAS 	7102030.  SINCED THESE 2 TIRES WERE PURCHASED IN A LOT OF 3, THE THIRD TIRE, SN 71020929, WAS RESEARCHED. THIS TIRE HAD 	ALSO BEEN REMOVED FROM SERVICE PREMATURELY BECAUSE IT HAD BEEN FOUND ON A POST-FLIGHT WITH VERY LOW PRESSURE.  A VISIBLE	 PUNCTURE HOLE HAD BEEN PRESUMED TO BE AT FAULT, THOUGH THE TIRE WAS NOT TOTALLY FLAT.  SUBMITTER STATED IT APPEARS SOME	 SORT OF MANUFACTURING DEFECT IN THAT S/N BATCH CAUSED ALL 3 DEFECTS.  69 LANDINGS SINCE NEW.	2	L	7	2 	4F			RT	A21EA   					 
1997121800046	19971218	00046	SO  	1997	12	18	97ZZZX5137       	2	19971202	G	8550	1250922200	ADAPTER         			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					OIL FILTER VALVE	FAILED          	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6175N	1969 				21062946	294661R			AS PART OF THE 600-HOUR INSPECTION OF OIL FILTER ADAPTER REQUIRED BY SEB 93-1R1, THE RELIEF VALVE SEALING 'DISK' WAS FOU	ND ASKEW AND NOT SEALING PROPERLY.  FURTHER INSPECTION REVEALED THE SPRING THAT HOLDS THE 'DISK' IN PLACE HAD BEEN CHAFE	D MORE THAN HALFWAY THROUGH BY ITS SUPPORT CAGE.  UNDETECTED, THIS COULD HAVE SERIOUSLY DAMAGED THE ENGINE.				1	H	7	1 	3O	3	O		3A21    	E5CE				 
1997121800047	19971218	00047	SO  	1997	12	18	97ZZZX5138       	1	19971113	G	3230	406163	BRACKET         			PIPER 	PA31T 	PA31T       	7103124	SO  										LT MLG UPLOCK	CRACKED         	B		A	RT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	103SP	4200 				31T8020024				AFT UPLOCK HOOK SUPPORT BRACKET FOR LMLG FOUND CRACKED WHILE GEAR OPERATIONAL CHECKS WERE BEING PERFORMED.  CRACK HAD PR	OPAGATED ACROSS 95 PERCENT OF THE BRACKET.  COMPLETE FAILURE WAS IMMINENT AND WOULD HAVE CAUSED ADDITIONAL LANDING GEAR 	COMPONENT DAMAGE.  IT HAD BEEN ONLY 12 HOURS SINCE THE LANDING GEAR HAD UNDERGONE A DETAILED INSPECTION DURING SCHEDULED	 MAINTENANCE.			1	L	7	2 	3T				A8EA    					 
1997121800048	19971218	00048	CE  	1997	12	18	97ZZZX5139       	1	19971202	G	2750	0512128	BRACKET         			CESSNA	180   	180K        	2072624	CE  										LT FLAP PULLEY	BROKEN          	D				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SO	13	18WL	6913 				18053178				PILOT REPORTED LEFT FLAP WOULD NOT FULLY EXTEND.  AN INSPECTION WAS CONDUCTED AND THE FLAP PULLEY BRACKET WAS FOUND BROK	EN.  THIS CONDITION CAUSED FLAP CABLE TO HAVE EXCESSIVE SLACK.					1	H	7	1 	3O				5A6     					 
1997013000442	19970130	00442	CE  	1997	1	30	97ZZZX514        	1	19970103	G	5320	081308942	DOUBLER         			CESSNA	310   	310R        	2074245	CE  										NLG WHEELWELL	CRACKED         	B			AHTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	98848	6347 				310R0614				DURING ANNUAL INSP, A CRACK WAS NOTICED IN THE DOUBLER FOR THE NLG TRUNNION ATTACH POINT.  UPON FURTHER INVESTIGATION, B	OTH RT AND LT DOUBLERS WERE FOUND CRACKED.  THE DOUBLERS ARE LOCATED AT THE LT AND RT OUTBOARD LOCATIONS ACCESSIBLE THRO	UGH THE NOSE BAGGAGE COMPARTMENT.  SUBMITTER STATES CRACKS IN THE SAME AREAS HAVE BEEN FOUND ON OTHER 310R MODELS.				1	L	7	2 	3O				3A10    					 
1997121800049	19971218	00049	CE  	1997	12	18	97ZZZX5140       	1	19971016	G	7920	035A470105	LINE            			MTSBSI	MU2   	MU2B60      	5780460	CE  										OIL COOLER	CRACKED         	E				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			SO	13	972ST					745SA				PILOT LOST OIL PRESSURE.  SHUT DOWN ENGINE AND DEVELOPED EMERGENCY AND LANDED AT CAE.  FOUND OIL COOLER STAINLESS OIL LI	NE CRACKED.  REPLACED LINE WITH SERVICEABLE LINE.					1	H	7	2 	3T			RT	A10SW   					 
1997121800050	19971218	00050	CE  	1997	12	18	97ZZZX5141       	1	19971028	G	7920	035A470105	LINE            			MTSBSI	MU2   	MU2B60      	5780460	CE  										ENGINE OIL	FAILED          	E				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			SO	13	942ST					756SA				PILOT NOTICED OIL PRESSURE DROPPING ON SHORT FINAL.  LANDED AT CLT.  SHUT DOWN ENGINE WHILE TAXIING IN.  MAINTENANCE FOU	ND OIL LINE LEAKING.  REPLACED LINE.					1	H	7	2 	3T			RT	A10SW   					 
1997013000443	19970130	00443	CE  	1997	1	30	97ZZZX515        	1	19970103	G	5320	081308947	DOUBLER         			CESSNA	310   	310R        	2074245	CE  										NLG WHEELWELL	CRACKED         	B			AHTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	98848	6347 				310R0614				DURING ANNUAL INSP, A CRACK WAS NOTICED IN THE DOUBLER FOR THE NLG TRUNNION ATTACH POINT.  UPON FURTHER INVESTIGATION, B	OTH RT AND LT DOUBLERS WERE FOUND CRACKED.  THE DOUBLERS ARE LOCATED AT THE LT AND RT OUTBOARD LOCATIONS ACCESSIBLE THRO	UGH THE NOSE BAGGAGE COMPARTMENT.  SUBMITTER STATES CRACKS IN THE SAME AREAS HAVE BEEN FOUND ON OTHER 310R MODELS.				1	L	7	2 	3O				3A10    					 
1997121800729	19971218	00729	EU  	1997	12	18	97ZZZX5152       	2	19971122	G	7310	FSFL24	FUEL LINE       			AMTR  	RANS  	RANSS10     	0561654	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					ENGINE COMPT	BURNED          	G		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	803DR					0297180	4401676			THE VINYL/PLASTIC TUBING USED THROUGHOUT THE ENGINE COMPARTMENT IS MADE OF A HIGHLY FLAMMABLE MATERIAL SUPPLIED BY THE K	IT MANUFACTURER.  THIS TUBING LAYING AGAINST THE HOT EXHAUST LINE MAY HAVE CONTRIBUTED CONTRIBUTED TO THE FIRE OF THIS A	IRCRAFT CAUSING SUBSTANTIAL DAMAGE.  SUBMITTER RECOMMENDED KIT MANUFACTURER'S SUPPLY NON-FLAMMABLE MATERIAL IN THEIR AMA	TEUR BUILT KIT FOR THE ENGINE COMPARTMENTS.  THIS AIRCRAFT HAD AN EXPERIMENTAL AIRWORTHINESS CERTIFICATE AND FAR 43 DOES	 NOT APPLY.		1	M	7	1 	3I	3	I	NC	EXPA1M71	EXPE3I				 
1997121800730	19971218	00730	NE  	1997	12	18	97ZZZX5153       	2	19971212	G	7310	3011155	TRANSFER TUBE   			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67      	52043	NE  					NOZZLE MANIFOLD	CORRODED        	B		A	FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	159PB	357  				159	PCE940012			ENGINE FUEL NOZZLES WERE REMOVED FOR FIRST NOZZLE FLOW TEST SINCE ENGINE MANUFACTURED.  UPON ASSEMBLY OF THE FUEL NOZZLE	S BACK ON THE ENGINE, IT WAS NOTED THAT 3 FUEL MANIFOLD TRANSFER TUBES HAD VERY DEEP CORROSION PITS.  PENETRATION OF THE	 WALL THICKNESS PROBABLY EXCEEDS 50 PERCENT.  SUBMITTER BELIEVES THESE TUBES HAVE NOT BEEN IN SERVICE LONG ENOUGH TO HAV	E CORRODED AND SUSPECT DEFECT IN MATERIAL AT MANUFACTURER.  ALL 3 DEFECTIVE PARTS HAVE THE FOLLOWING PART NUMBER AND COD	E:  3011155 8 1229 CPWA-ASPT.  REPLACED DEFECTIVE PARTS WITH NEW.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
1997121800731	19971218	00731	GL  	1997	12	18	97ZZZX5154       	2	19971210	G	7313	6890917	FUEL NOZZLE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					INLET SCREEN	FAILED          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	5119V		256  		A628963	1000800D	CAE834267			FUEL NOZZLE INLET SCREEN, ALSO KNOWN AS (LAST CHANCE FILTER) SHOWS SIGNS OF INITIAL COLLAPSE.  COLLAPSED SCREEN CANNOT B	E DETECTED WITHOUT DISASSEMBLY OF NOZZLE.  SCREEN IS BEING MANUFACTURED FROM TOO THIN OF MATERIAL AND IS COLLAPSING UNDE	R NORMAL CONDITIONS WITHOUT DETECTION.  THIS COLLAPSE WILL CAUSE PARTIAL ENGINE POWER LOSS OR TOTAL ENGINE FAILURE.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997121800733	19971218	00733	NM  	1997	12	18	97ZZZX5156       	1	19971009	G	6220	A005A	HUB             			ROBSIN	R22   	R22MARINER  		NM  										MAIN ROTOR	WORN            	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8324U	752  				2570M				DURING 100-HOUR INSPECTION, EVIDENCE OF FRETTING NOTED AT MAIN ROTOR HUB ATTACH BOLT THRUST WASHERS.  DISASSSEMBLY REVEA	LED SEVERE WEAR ON MAIN ROTOR HEAD HUB BEARINGS AND THE JOURNALS RIDING INSIDE THESE BEARINGS WHICH ALLOWED RELATIVE MOT	ION BETWEEN M/R HUB AND THE ATTACH BOLT.  THE HUB WAS REMOVED AND RETURNED TO ROBINSON FACTORY.  THE HELICOPTER HAD BEEN	 INSPECTED 100 HOURS (LESS THAN ONE MONTH PREVIOUSLY) AND NO DEFECTS DISCOVERED IN THE MAIN ROTOR SYSTEM.  SUBMITTER DOE	S NOT KNOW WHAT CAUSED THIS RAPID WEAR, BUT THE HELICOPTER IS USED IN A HARSH ENVIRONMENT.		1	G	7	1 	3O				H10WE   					 
1997121800734	19971218	00734		1997	12	18	97ZZZX5157       	4	19971114	G	3421	RCA26BK12	INDICATOR       	RCALLEN     		BELL  	206   	206B        	1181511	SW  										GYRO ATTITUDE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322				820737	1736				ATTITUDE GYRO INDICATOR WILL NOT HOLD ATTITUDE.						1	G	7	1 	3U				H2SW    					 
1997121800735	19971218	00735	CE  	1997	12	18	97ZZZX5158       	1	19971204	G	1100	K04504003	DATA PLATE      			CESSNA	150   	150L        	2071826	CE  										RT MUFFLER	DETACHED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	1283Q	300  			34802	15072583				DURING AN OIL CHANGE AND ENGINE CHECK, FOUND THAT ON THE LEFT MUFFLER, THE DATA PLATE TACK WELDS HAD FAILED AND THE DATA	 PLATE ITSELF WAS LOCATED INSIDE THE CABIN HEAT SCAT HOSE.  IF THIS DATA PLATE HAD COME LOOSE ON THE RIGHT MUFFLER, IT V	ERY LIKELY MIGHT BE INJESTED INTO THE CARBURETOR WHEN CARBURETOR HEAT WAS SELECTED.				1	H	7	1 	3O				3A19    					 
1997121800736	19971218	00736	CE  	1997	12	18	97ZZZX5159       	1	19971112	G	2750	0400107145	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										LT FLAP	FAILED          	G		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	15	48863	9050 				15281011				DURING STALL RECOVERY WORK, THE FLAPS WERE BEING MOVED TO A 20 DEGREE POSITION WHEN THE LEFT FLAP RETRACTED TO FULL UP T	RAIL POSITION AND RIGHT FLAP REMAINED DOWN (THIS OCCURRED AFTER A LOUD BANG).  THE ACFT ROLLED LEFT.  PILOT INITIATED EM	ERGENCY PROCEDURES AND LANDED PLANE.  LEFT FLAP CABLE BROKE AT SWAGED BALL END.				1	H	7	1 	3O			NT	3A19    					 
1997121800737	19971218	00737	SO  	1997	12	18	97ZZZX5160       	1	19971113	G	3211	67040015	ATTACH BRACKET  			PIPER 	PA34  	PA34200     	7103405	SO  										RT TRUNNION	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	55777	538  				347350244				WHILE C/W PIPER SB 906, FOUND TRUNNION ATTACH FITTING LOOSE.  THEY WERE REPLACED IN 1995 BECAUSE OF ELONGATED HOLES.  TO	RQUE CHECK HAS BEEN DONE SINCE BULLETIN CAME OUT.  THE GEAR PROBLEM IN THIS PLANE HAS INCREASED CONTINUALLY.					1	L	7	2 	3O				A7SO    					 
1997121800738	19971218	00738	SO  	1997	12	18	97ZZZX5161       	1	19971113	G	3211	67040014	ATTACH BRACKET  			PIPER 	PA34  	PA34200     	7103405	SO  										LT TRUNNION	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	55777	538  				347350244				WHILE C/W PIPER SB 906, FOUND TRUNNION ATTACH FITTING LOOSE.  THEY WERE REPLACED IN 1995 BECAUSE OF ELONGATED HOLES.  TO	RQUE CHECK HAS BEEN DONE SINCE BULLETIN CAME OUT.  THE GEAR PROBLEM IN THIS PLANE HAS INCREASED CONTINUALLY.					1	L	7	2 	3O				A7SO    					 
1997121800739	19971218	00739	SO  	1997	12	18	97ZZZX5162       	2	19971121	G	8530	636697	VALVE SEAT      			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					NR 2 CYL INTAKE	FAILED          	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	6798V	4    			654654A	421C1254	604727			NEW TCM CYLINDER ASSYS INSTALLED AT ENGINE OVERHAUL.  DATE STAMPED ON ROCKER BOSS:  7-97.  AFTER BREAK-IN FLIGHT AND TES	T FLIGHTS, NR 2 CYL ON LT ENGINE WAS NOTED TO HAVE LOW COMPRESSION:  18/80.  LEAKAGE DETERMINED TO BE PAST INTAKE VALVE.	  REMOVAL AND DISASSY REVEALED VALVE NO LONGER SEATED.  CYLINDER WAS LEAK CHECKED BEFORE ASSY WITH NONE NOTED.  SEAT HAS	 SHIFTED AND NO LONGER ALIGNS WITH GUIDE.  SUSPECT SEAT ASSY NOT FULLY SEATED WHEN ASSEMBLED.  WITH CYLINDER HEAD AT OPE	RATING TEMPERATURE, VALVE PUSHES SEAT FULLY IN AND NO LONGER ALIGNS WITH VALVE FACE.  THIS IS THE FIFTH CYLINDER AT THIS	 REPAIR STATION WITH SAME FAILURE.  ALL ARE INTAKE SEATS AND START TO LEAK AFTER FIRST FEW HRS OF OPERATION FROM NEW.	1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997121800740	19971218	00740	CE  	1997	12	18	97ZZZX5163       	1	19971101	G	5210		PUMP            			CESSNA	210   	P210N       	2073454	CE  										SEAL INFLATE	FAILED          	D		A		H	A	F		DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         	ACTIVATE FIRE EXT.      		B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	11	731NX					P21000515				PILOT STATED DOOR SEAL INFLATION PUMP STARTED OPERATING CONTINUOUSLY IN FLIGHT, AND HE WAS UNABLE TO TURN IT OFF.  THE C	ABIN BEGAN TO FILL WITH SMOKE, SO ALL ELECTRICAL EQUIPMENT WAS TURNED OFF WITH MASTER SWITCH, AND EMERGENCY LANDING WAS 	MADE.  A FIRE AT LEFT LOWER UPHOLSTERY PANEL ADJACENT TO PILOT'S LEFT KNEE WAS EXTINGUISHED WITH HAND FIRE EXTINGUISHER.				1	H	7	1 	3O				3A21    					 
1997121800741	19971218	00741	CE  	1997	12	18	97ZZZX5164       	1	19971022	G	3230	ES12704	SPOOL VALVE     			CESSNA	210   	210B        	2073410	CE  	CONT  	O470  	IO470S      	17026	SO  					MLG PWR PACK	STUCK           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	27	9740X					21058040				THE SPOOL VALVE IN THE LANDING GEAR POWER PACK MANIFOLD VALVE ASSEMBLY WAS FOUND STUCK IN THE GEAR UP MODE.  PULLED SOLE	NOID OUT, DEPRESSED THE SPOOL VALVE COUPLE OF TIMES, AND IT SPRUNG BACK INTO THE GEAR DOWN MODE.  THEN GEAR WAS HAND PUM	PED DOWN AND LOCKED.  REASON FOR VALVE TO STICK IN GEAR UP MODE IS UNKNOWN AT THIS DATE.				1	H	7	1 	3O	3	O		3A21    	3E1				 
1997121800742	19971218	00742	CE  	1997	12	18	97ZZZX5165       	1	19971209	G	8097		WIRE            			BEECH 	58    	58          	1152740	CE  										STARTER	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	1071F					TH1771				ENGINE WOULD NOT STAR, HIGH AMP DRAW WITH RELAY ENGAGED.  FOUND STARTER WIRE SHORTED AGAINST ENGINE MOUNT.  TTAF:  381.8	 HOURS.  STARTER WIRES NEED TO BE INSPECTED AND TIED BACK.					1	L	7	2 	3O			 	3A16    					 
1997121800743	19971218	00743	CE  	1997	12	18	97ZZZX5166       	1	19971120	G	2752	995241221	GEAR            			BEECH 	80    	65B80       	1152812	CE  										FLAP GEARBOX	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	15	131BA		39   		012	LD297				INVESTIGATION FOR CAUSE OF FLAP GEAR BOX FAILURE FOUND POOR TEETH ENGAGEMENT OF GEARBOX TEETH AND MOTOR GEAR TEETH.						1	L	7	2 	3O				3A20    					 
1997121800744	19971218	00744	CE  	1997	12	18	97ZZZX5167       	1	19971120	G	2752	995240253	GEAR            			BEECH 	80    	65B80       	1152812	CE  										FLAP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	15	131BA		39   		1981	LD297				INVESTIGATION FOR CAUSE OF FLAP GEAR BOX FAILURE FOUND POOR TEETH ENGAGEMENT OF GEARBOX TEETH AND MOTOR GEAR TEETH.						1	L	7	2 	3O				3A20    					 
1997121800746	19971218	00746	SO  	1997	12	18	97ZZZX5169       	1	19971128	G	2140	44008	SOLENOID        	JANITROL    		PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	E		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	300ED					31785208				DURING WORK ON REAR HEATER, HAD COVER OFF OF FUEL SHUT OFF SOLENOID.  NOTICED FUEL LEAKING FROM GROMMET ON BODY OF SOLEN	OID.  REMOVED PART FROM SERVICE AS IT PRESENTED A FIRE HAZARD.					1	L	7	2 	3O				A20SO   					 
1997121800748	19971218	00748	CE  	1997	12	18	97ZZZX5171       	1	19971204	G	3710		HOSE            			CESSNA	185   	A185F       	2072821	CE  										VACUUM SYSTEM	LEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	735GE	860  				18504447				VACUUM HOSES ORIGINALLY INSTALLED BECAME BRITTLE AND CRACKED ALONG THE HOSE ALLOWING LEAKAGE INTO SYSTEM.  ALL LINES WER	E REPLACED.					1	H	7	1 	3O				3A24    					 
1997121800749	19971218	00749	GL  	1997	12	18	97ZZZX5172       	1	19971126	G	7602	A740	CONTROL CABLE   			AMTR  	VANS  	RV6         	05608  	GL  										CARB MIXTURE	BROKEN          	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	23	44JR	114  				24545				MIXTURE CONTROL CABLE BROKE IN CRUISE FLIGHT CAUSING FORCED LANDING.  SUBMITTER SUGGESTS CAUSE AS VIBRATION STRESS.  REC	OMMEND USING HEAVIER CABLE WITH THREADED TERMINATION.					1	L	7	1 	3O			NC	EXPA1L71					 
1997121800751	19971218	00751	SO  	1997	12	18	97ZZZX5174       	2	19971205	G	8530	637781	VALVE           			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 1 CYLINDER	FAILED          	D	S			O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AL	01	75703	1478 				20700639	810181R			PILOT REPORTED THAT IN CRUISE FLIGHT, THE ENGINE BEGAN RUNNING ROUGH.  IT WAS FOUND THE NR 1 CYLINDER HAD ZERO COMPRESSI	ON.  WHEN THE EXHAUST VALVE WAS REMOVED FROM THE ENGINE, DISCOVERED THE VALVE HAD A MISSING CHUNK.  SUSPECT CAUSE - CARB	ON BETWEEN VALVE AND SEAT CAUSING RAW FUEL TO PASS BY THE VALVE AND BURN THE VALVE WHEN IGNITED.  .25 INCH BY .25 INCH G	ONE FROM VALVE TOP.			1	H	7	1 	3O	3	O		A16CE   	E5CE				 
1997121800752	19971218	00752	EA  	1997	12	18	97ZZZX5175       	2	19971125	G	8540	LW12539	PUMP ADAPTER    			BEECH 	80    	65A80       	1152808	CE  	LYC   	O540  	IGSO540A1A  	41532	EA  					MOUNT FLANGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	95LL	237  				LD235	L105954			FOUND HYDRAULIC PUMP ADAPTER WITH CRACKED MOUNT FLANGE.  SUBMITTER STATED WILL CRACK AROUND ANY OF THE 4 HOLD-DOWN FLANG	ES.					1	L	7	2 	3O	3	O		3A20    	1E7				 
1997121800753	19971218	00753	GL  	1997	12	18	97ZZZX5176       	3	19971202	G	6114	D7015C87	HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C87    	GL  	RETAIN THREADS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07								780493		EXCESSIVE CORROSION AND A CRACK WAS FOUND IN THE RETENTION THREADS.  SUBMITTER STATED PROPER COMPLIANCE TIMES ADHERED TO	 COULD HAVE LESSENED THE SEVERITY OF THE SITUATION.					1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800754	19971218	00754	GL  	1997	12	18	97ZZZX5177       	3	19971202	G	6114	D7015C87	HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE SOCKET	CORRODED        	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15								780370		EXCESSIVE CORROSION IN THREADS OF BLADE SOCKETS.  SUBMITTER STATED PROPER COMPLIANCE TIMES ADHERED TO MAY HAVE LESSENED 	THE PROBLEMS.					1	L	7	2 	3O				3A25    		5	C	P22EA	 
1997121800755	19971218	00755	EA  	1997	12	18	97ZZZX5178       	2	19971211	G	8550	CH48110	OIL FILTER      	CHAMPION    		SLNSBY	T67   	T67M260     	8323006	EU  	LYC   	O540  	AEIO540D4A5 	41532	EA  					FLANGE	CRACKED         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										CRACKS WERE FOUND ON ENGINE OIL FILTERS (NEW FILTERS).  THIS CRACK IS ON THE BASE FLANGE INSIDE OF BASE SEAL AND OUTBOAR	D OF INLET HOLES.  SUSPECT CAUSE MIGHT BE ASSEMBLY DEFECT.  SUBMITTER RECOMMENDED EMERGENCY AD ISSUE ON THIS OIL FILTER 	AND REPLACE IF FOUND CRACKED.				1	L	7	1 	3O	3	O	NT	A73EU   	1E4				 
1997121800756	19971218	00756	NE  	1997	12	18	97ZZZX5179       	2	19971121	G	8520	5999	ROLLER          								PWA   	R1340 	R1340AN1    	52016	NE  					VALVE TRAIN	SPALLED         	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15			456  				25165			VALVE TRAIN ROLLER AND CAM SPALLED.  DISCOVERED WHILE PERFORMING REPAIR TO THE ENGINE.  BOTH THE CAM AND ROLLER WERE FAI	LING BY SPALLING.										3	R			5E2				 
1997121800757	19971218	00757	NE  	1997	12	18	97ZZZX5180       	2	19971121	G	8520	11768	CAM             								PWA   	R1340 	R1340AN1    	52016	NE  					VALVE TRAIN	SPALLED         	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15			456  				25165			VALVE TRAIN ROLLER AND CAM SPALLED.  DISCOVERED WHILE PERFORMING REPAIR TO THE ENGINE.  BOTH THE CAM AND ROLLER WERE FAI	LING BY SPALLING.										3	R			5E2				 
1997121800758	19971218	00758	NE  	1997	12	18	97ZZZX5181       	2	19971124	G	8520	5999	ROLLER          								PWA   	R1340 	R1340AN2    	52016	NE  					VALVE TRAIN	SPALLED         	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15							ZP101676			VALVE TRAIN ROLLER FOUND SPALLED.  WHILE PERFORMING MAINTENANCE AND REPAIRS ON THE ENGINE.											3	R			5E2				 
1997121800759	19971218	00759	EA  	1997	12	18	97ZZZX5182       	2	19971117	G	8500	LW127984S172	HOSE            								LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	MISMANUFACTURED 	B			HUNR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01										NEW REPLACEMENT HOSE ASSY HAS A SCARF-CUT 'FLAPPER' INSIDE THE TAGGED END.  (DEFECT FROM THE MANUFACTURING PROCESS).											3	O			1E10				 
1997121800760	19971218	00760	NE  	1997	12	18	97ZZZX5183       	2	19971117	G	8520		ROLLER          								PWA   	R1340 	R1340AN1    	52016	NE  					VALVE TRAIN	SPALLED         	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15							23562			VALVE TRAIN ROLLER AND CAM SPALLED.  DISCOVERED WHILE PERFORMING REPAIRS AND MAINTENANCE TO THE ENGINE FOR OTHER REASONS	.  PARTS WERE FOUND SPALLING AND FLAKING.										3	R			5E2				 
1997121800761	19971218	00761	NE  	1997	12	18	97ZZZX5184       	2	19971117	G	8520	11768	CAM             								PWA   	R1340 	R1340AN1    	52016	NE  					VALVE TRAIN	SPALLED         	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15							23562			VALVE TRAIN ROLLER AND CAM SPALLED.  DISCOVERED WHILE PERFORMING REPAIRS AND MAINTENANCE TO THE ENGINE FOR OTHER REASONS	.  PARTS WERE FOUND SPALLING AND FLAKING.										3	R			5E2				 
1997121800762	19971218	00762	EU  	1997	12	18	97ZZZX5185       	1	19971212	G	3244	60068PLY	TIRE            			PARTEN	P68   	P68         		EU  										RT MLG	DELAMINATED     	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	01	605	200  				321150B				RIGHT MAIN TIRE BLEW ON LANDING.  PILOTS STATED LANDING WAS NORMAL.  INSPECTION OF TIRE AND WHEEL ASSY REVEALED TUBE WAS	 RUPTURED BY TIRE INNER SIDEWALL DELAMINATION.  SUSPECT POSSIBLE DEFECTIVE TIRE CASING.					1	H	7	2 	3O				A31EU   					 
1997121800763	19971218	00763	EU  	1997	12	18	97ZZZX5186       	1	19971125	G	7810		MUFFLER         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										ENGINE EXHAUST	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	105U	207  				591				EXHAUST HEAT MUFFLER WAS FOUND TO HAVE HOLES IN EXHAUST INTO CABIN HEAT SHROUD EMITTING EXHAUST GAS INTO CABIN HEAT SYST	EM.  EXHAUST SYSTEM WAS NEW IN 10-10-96 WHEN ENGINE WAS OVERHAULED.  (PART LOOKED RELATIVELY NEW).					1	L	7	1 	30			NT	A51EU   					 
1997121800764	19971218	00764	CE  	1997	12	18	97ZZZX5187       	1	19971106	G	5610	45AS31001013	WINDSHIELD      			BEECH 	MU300 	400A        	1155402	CE  										COCKPIT	DEFECTIVE       	B			MZ4R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	17	135BJ	315  			96218H4117	RK135				PILOT REPORTED SMOKE IN THE COCKPIT.  AFTER TROUBLESHOOTING, FOUND LEFT WINDSHIELD HEAT GROUND STRAP LOOSE.  DAMAGE OCCU	RRED TO FACILITATE WINDSHIELD REPLACEMENT.  TEST FLIGHT CARRIED OUT AFTER WINDSHIELD AND WINDSHIELD HEAT CONTROL BOX WAS	 REPLACED.  ALL SYSTEMS CHECKED OK.				2	H	7	2 	4F			RT	A16SW   					 
1997122400001	19971224	00001	GL  	1997	12	24	97ZZZX5189       	3	19971112	G	6114	D3389C67	HUB             													MCAULY	2A34C	D2A34C67    	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								683527		PROPELLER RECEIVED FOR OVERHAUL.  AFTER DISASSEMBLY DURING HUB INSPECTION, HUB DISCOVERED CRACKED NR 2 BLADE SOCKET INSI	DE 6 THREADS IN AT 5 O'CLOCK POSITION. 1.50 INCHES LONG.  CRACK DISCOVERED USING 10X POWER MICROSCOPE.  HUB RETURNED TO 	CUSTOMER.														5	C	P3EA	 
1997122400002	19971224	00002	SO  	1997	12	24	97ZZZX5190       	1	19971208	G	5521	4595106	SPAR            			PIPER 	PA31T 	PA31T       	7103124	SO  										ELEVATOR	CRACKED         	B			JEMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	200NB	6426 				31T7720035				ELEVATOR SKIN CRACKED FROM THE INSIDE.  INVESTIGATION REVEALED CRACKS IN LOWER SPAR RADIUS OUTBOARD HINGE BRACKET.  THIS	 WAS ON BOTH LEFT AND RIGHT ELEVATORS.					1	L	7	2 	3T				A8EA    					 
1997122400006	19971224	00006	SO  	1997	12	24	97ZZZX5194       	1	19971208	G	5521	4595106	SPAR            			PIPER 	PA31T 	PA31T       	7103124	SO  										ELEVATOR	CRACKED         	B		A	JEMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	35RT	4000 				31T7820018				FOUND ELEVATOR SKIN CRACKED FROM THE INSIDE.  INVESTIGATION REVEALED CRACKS IN SPAR RADIUS OUTBOARD HINGE BRACKET.						1	L	7	2 	3T				A8EA    					 
1997122400007	19971224	00007		1997	12	24	97ZZZX5195       	4	19971202	G	6113	055023613	SPINNER         			CESSNA	172   	172         	2072402	CE  										PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	64763	50   				17275620				FATIGUE CRACK FOUND IN PROPELLER SPINNER.  50 HOURS TT.						1	H	7	1 	3O			NT	3A12    					 
1997122400008	19971224	00008		1997	12	24	97ZZZX5196       	4	19971202	G	6113	055023613	SPINNER         			CESSNA	172   	172P        	2072436	CE  										PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	64763	36   				17275620				FATIGUE CRACK FOUND IN PROPELLER SPINNER.  35 HOURS TT.						1	H	7	1 	3O			NT	3A12    					 
1997122400009	19971224	00009		1997	12	24	97ZZZX5197       	4	19971202	G	6113	055023613	SPINNER         			CESSNA	172   	172P        	2072436	CE  										PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	64763	45   				17275620				FATIGUE CRACK FOUND IN PROPELLER SPINNER.  45 HOURS TT.						1	H	7	1 	3O			NT	3A12    					 
1997122400010	19971224	00010		1997	12	24	97ZZZX5198       	4	19971209	G	2312	484208	RELAY           			PIPER 	PA28  	PA28RT201   	7102818	SO  										AVIONIC POWER	BURNT           	B			FO6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	81897	2388 				28R8018063				WHILE TROUBLESHOOTING, INTERMITTENT RADIO OPERATION FOUND AVIONIC POWER RELAY TERMINAL NR 2 IN VERY DETERIORATED CONDITI	ON DUE TO OVER HEATING.  ADJACENT WIRING WAS ALSO DAMAGED.  SUSPECT CORROSION ON TERMINAL.  SUBMITTER STATED DUE TO LOCA	TION IN AN AREA PRONE TO MOISTURE, RECOMMEND SEALING TERMINALS WITH RTV.				1	L	7	1 	3O				2A13    					 
1997122400011	19971224	00011	EU  	1997	12	24	97ZZZX5199       	1	19971125	G	5210		DOOR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										PILOT SIDE	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	105U	2502 				591				BOTH PILOT'S AND COPILOT'S DOORS WERE FOUND CRACKED ALONG THE DOOR HINGE LINE ON THE INSIDE STRUCTURE OF THE DOOR.  2,50	1 HOURS TOTAL TIME.  A FIELD APPROVED REPAIR WAS NEEDED AS SOCATA HAD NO APPROVED STRUCTURAL REPAIR MANUALS.  CRACK IS 1	2 INCHES LONG ON PILOT'S SIDE, AND 14 INCHES LONG ON COPILOT'S SIDE.  INSIDE, DOOR IS CONSTRUCTED OF SOFT 'O' CONDITION 	MATERIAL WHICH CONTRIBUTED TO WEAKNESS OF DOOR IN THIS AREA.			1	L	7	1 	30			NT	A51EU   					 
1997122400012	19971224	00012	EU  	1997	12	24	97ZZZX5200       	1	19971125	G	5210		DOOR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										COPILOT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	105U	2502 				591				BOTH PILOT'S AND COPILOT'S DOORS WERE FOUND CRACKED ALONG THE DOOR HINGE LINE ON THE INSIDE STRUCTURE OF THE DOOR.  2,50	1 HOURS TOTAL TIME.  A FIELD APPROVED REPAIR WAS NEEDED AS SOCATA HAD NO APPROVED STRUCTURAL REPAIR MANUALS.  CRACK IS 1	2 INCHES LONG ON PILOT'S SIDE, AND 14 INCHES LONG ON COPILOT'S SIDE.  INSIDE, DOOR IS CONSTRUCTED OF SOFT 'O' CONDITION 	MATERIAL WHICH CONTRIBUTED TO WEAKNESS OF DOOR IN THIS AREA.			1	L	7	1 	30			NT	A51EU   					 
1997122400014	19971224	00014	GL  	1997	12	24	97ZZZX5202       	3	19971201	G	6110	C52701	BEARING         			CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROP ASSY	DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	5NPAN	4109 	1217 		NB0127			931720		INSPECTION FOUND PROPELLER ASSEMBLY BEARING HAD SHARP INDICATIONS ON BOTH SIDES DIRECTLY ACROSS FROM EACH OTHER APPROXIM	ATELY .3750 INCH ON ONE SIDE AND .6250 INCH ON THE OTHER SIDE.					1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997122400022	19971224	00022	WP  	1997	12	24	97ZZZX5204       	2	19971202	G	7200		ENGINE          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					RT ENGINE	FAILURE         	D				O				OTHER                   				X			ENGINE FLAMEOUT           			AP	APPROACH       	1			EA	25	150YA					BE124	P27257			ENGINE FAILURE ON FINAL.  PILOT REPORTED 20 KNOT CROSSWINDS WITH GUSTS.  AIRCRAFT HAD BEEN IN ICING CONDITIONS.  SUSPECT	 CAUSE OF FAILURE, INGESTION OF ICE.					1	L	7	2 	4T	4	T		A14CE   	E2WE				 
1997122400023	19971224	00023	EU  	1997	12	24	97ZZZX5205       	1	19971203	G	2840	166FT2	CONNECTOR       			AMD   	FALC50	FALCON50MYST	2730106	EU  										RT FEED TANK	INTERMITTENT    	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	96DS	2534 				209				GROUP THREE FUEL QUANTITY READ ZERO INTERMITTENTLY.  FOUND COLD SOLDERED WIRE ON CONNECTOR 166FT2 AND FOUND SEALANT DISI	NTEGRATING.					2	L	7	3 	4F				A46EU   					 
1997122400024	19971224	00024	CE  	1997	12	24	97ZZZX5206       	1	19971205	G	2915	4614	RELIEF VALVE    			CESSNA	500   	560CESSNA   	2076750	CE  										HYD SYSTEM	MALFUNCTION     	B			IW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	331QS	2417 				5600331				TROUBLESHOOTING FOR INCOMPLETE RETRACT CYCLE FOUND HYDRAULIC RELIEF VALVE OPENING PREMATURELY.						2	L	7	2 	4F			RT	A22CE   					 
1997122400025	19971224	00025	CE  	1997	12	24	97ZZZX5207       	1	19971208	G	2915	4614	RELIEF VALVE    			CESSNA	500   	560CESSNA   	2076750	CE  										HYD SYSTEM	MALFUNCTION     	B			IW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	348QS	1699 			1441A	5600348				CREW REPORTS GEAR FAILS TO COMPLETE RETRACT CYCLE.  FOUND 1500 PSI RELIEF VALVE OPENING PREMATURELY @ 1100 PSI.  THIS CA	USED REPORTED CONDITION.  FOUND THIS SAME CONDITION ON 560-0331 WITH 1417 HOURS.  SUBMITTER RECOMMENDS TO ADD PRESSURE C	HECK AT 300 HOUR INTERVALS WHEN GEAR SWINGS ARE PERFORMED.				2	L	7	2 	4F			RT	A22CE   					 
1997122400026	19971224	00026	EU  	1997	12	24	97ZZZX5208       	1	19971020	G	3411	PIT844271	TUBE            			FOKKER	F27   	F27MK400    	4990626	EU  										PITOT BS 3000	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2MIL	7185 				10668				PITOT TUBE BENEATH COCKPIT FLOOR (STA 3000) BETWEEN 'DRAINS' AND AIR DATA COMPUTER FOUND CHAFED BY AILERON FLIGHT CONTRO	L CABLE.  ALUM TUBING CHAFED THRU .028 INCH WALL THICKNESS, 'FLASHING' BLOCKED HOLE PREVENTING PITOT SYS LEAK.  DEFECT L	OCATED 32 INCHES FROM RT END FITTING.  TUBING'S LT END HAS DASH 6 TUBING (3.50 INCHES LONG) WELDED TO DASH 4 ALUMINUM TU	BING APPROX 47 INCHES LONG.  ONLY 1 CLAMP INSTALLED IN 50-INCH SPAN.  TUBING MAY HAVE BEEN BENT BY WORKERS AND ROUTED IN	CORRECTLY, I.E., BETWEEN  AILERON CABLES INSTEAD OF BENEATH.  SUBMITTER RECOMMENDS RE-ROUTING TUBING BENEATH AILERON CAB	LES AND ADD ADDITIONAL CLAMPS TO SUPPORT TUBING.  REF, FOKKER F27 IPC CHAP 34-10-07 FIG 01L-100.	2	H	7	2 	4T				A817    					 
1997122400028	19971224	00028	SO  	1997	12	24	97ZZZX5209       	1	19971208	G	5610	JF4897LF	WINDOW          	PPG         		LKHEED	1329  	132923E     	5263116	SO  										COCIPIT LT AFT	MISINSTALLED    	B	S	A	MGTY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	155AV				83H51401	5104				LOCKHEED JETSTAR COCKPIT LT REAR SIDE WINDOW (IPC 2-232 FIG 23 ITEM D).  WHEN A DEFECT ON LT COCKPIT DV WINDOW WAS INVES	TIGATED, FOUND LT REAR COCKPIT SIDE WINDOW, REAR UPPER AND LOWER WINDOW RETAINERS HAD NOT BEEN BOLTED TO WINDOW SUPPORT 	STRUCTURE.  RETAINERS WERE ONLY ATTACHED TO FUSELAGE OUTER SKIN.  OVER 30 ATTACHMENT BOLTS ARE MISSING AND LOWER RETAINE	R IS NOW MISALIGNED BY APPROX .1875 INCH OUTBOARD.  VISUAL AND NDT INSPECTIONS ARE BEING CARRIED OUT ON WINDOW AREA OF F	USELAGE.  LOCKHEED HAS BEEN INFORMED AND ARE INVESTIGATING REPAIR REQUIREMENTS.  ON REAR RT COCKPIT WINDOW, 2 ATTACHMENT	 BOLTS WERE FOUND MISSING FROM TOP RETAINER.	2	L	7	4 	4J				2A15    					 
1997013000449	19970130	00449	GL  	1997	1	30	97ZZZX521        	2	19970116	G	7250	23031909A	ENERGY RING     								ALLSN 	250C  	250C30P     	03013	GL  					ENG	WORN TANGS      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		5830 	1797 		DD11270		CAT90681			THE 4 TANGS ON THE ENERGY ABSORBING RING ARE WORN ON WIDTH AND ONE IN HEIGHT AND WORN INTO THE PT SUPPORT.  SUBMITTER ST	ATES THIS HAPPENS ON ALL C30 TURBINES.  NEEDS MORE SUPPORT.										3	U			E1GL				 
1997122400473	19971224	00473	SW  	1997	12	24	97ZZZX5211       	1	19971119	G	2710	730006000	CONTROL LINK    			MOONEY	M20   	M20J        	5870219	SW  										RT AILERON	BROKEN          	B	S	A	HUNR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	01	201ZU	2137 				240544				IN-FLIGHT FAILURE.  OWNER-PILOT NOTICED SLOPPY AILERON RESPONSE, SAW RT AILERON 'VIBRATING', NOT RESPONDING TO CONTROL I	NPUT.  RIGHT CONTROL LINK ROD ASSEMBLY LOCATED AT BELLCRANK BELOW CABIN FLOOR HAD BROKEN ALONG FACTORY WELD THEN THROUGH	 THE TUBING WALL.  THE BREAK ALONG THE WELD SHOWED SIGNS OF AGE, THE BREAK THROUGH THE TUBE WALL APPEARED RECENT.  INSPE	CTORS DETERMINED THE AILERONS UP AND DOWN STOPS SHOWED NO SIGNS OF DAMAGE AND THE REST OF THE AILERON SYSTEM SHOWED NO S	IGNS OF DAMAGE OR ABUSE.  NOTE, THE REPLACMENT PART IS SAME PART NUMBER, BUT REINFORCED AT BOTH 90 DEGREE CORNERS.		1	L	7	1 	3O				2A3     					 
1997122400474	19971224	00474		1997	12	24	97ZZZX5212       	4	19971209	G	6113	04500463	BULKHEAD        			CESSNA	150   	150L        	2071826	CE  										PROP SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	21965	521  				15074573				PROPELLER REMOVED FOR CLEANING AND PAINTING. THE SPINNER BACKPLATE WAS FOUND CRACKED 270 DEGREES JUST OUTSIDE PROPELLER 	BOLT HOLES.  SUBMITTER RECOMMENDS AD FOR INSPECTION EVERY 500 HOURS.  HARD TO SEE CRACK WITH PROPELLER INSTALLED ON AIRC	RAFT.				1	H	7	1 	3O				3A19    					 
1997122400479	19971224	00479	NE  	1997	12	24	97ZZZX5216       	1	19971125	G	6520	7636104008101	COUPLING        			SKRSKY	S76   	S76A        	8143006	NE  										INTERMED GRBOX	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72649	209  				760292				COUPLING WAS FOUND CRACKED IN 7 PLACES.  IT WAS LOCATED AT THE INTERMEDIATE GEARBOX OUTPUT FLANGE.  THE PREVIOUS COUPLIN	G WAS ALSO CRACKED.  THE RUN-OUT WAS CHECKED AND FOUND WITHIN  MANUFACTURER'S LIMITS.  THE NR 5 T/R DRIVESHAFT AND INTER	MEDIATE GEARBOX WERE REMOVED FOR FURTHER EVALUATION.  NEW COUPLING WAS INSTALLED.  RUN-OUT CHECK IS WITHIN MANUFACTURER'	S LIMITS.			1	G	7	2 	3U				H1NE    					 
1997122400480	19971224	00480	NE  	1997	12	24	97ZZZX5217       	2	19971203	G	7323	430128903	GOVERNOR        			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ENGINE PT	MALFUNCTIONED   	D	L	A		O				OTHER                   				J			WARNING INDICATION        			HO	HOVERING       	1			WP	21	816CE		991  			1436	LE43432C			GOVERNOR UNITS HAD A MANDATORY SB REQUIRED BY JUNE, 1997. STARTED COMPLYING BY DECEMBER, 1996.  AFTER INSTALLATION OF FI	RST MODEL UNIT, STARTED EXPERIENCING RPM ADJUSTMENT PROBLEMS.  AFTER 20 HOURS, BUT NO MORE THAN 200 HOURS, UNITS WOULD F	AIL TO HOLD RPM SETTINGS.  SUBMITTER STATED THIS ONE WAS THE WORST WITH A SEVERE RPM OSCILLATION IN A HOVER.  HAVE NOW C	HANGED 7 UNITS SINCE DECEMBER, 1996.			1	G	7	1 	3U	3	U		H9EU    	E5NE				 
1997122400481	19971224	00481	NE  	1997	12	24	97ZZZX5218       	2	19971213	G	7310	430128601	MANIFOLD        			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					ENGINE FUEL	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	781SA		993  		7175C	47537	LE47163			FUEL LEAK NOTED ON POST-FLIGHT INSPECTION.  FUEL MANIFOLD WAS FOUND TO HAVE A CRACK OR HOLE AT 5 O'CLOCK POSITION.  UNAB	LE TO DETECT WITH NAKED EYE.  FUEL POOLED IN ENGINE COMPARTMENT AREA MAKING THIS A VERY DANGEROUS SITUATION.  FUEL LEAKI	NG ONTO THE TURBINE SECTION AND DRIPPING ONTO THE DECK.				1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1997013000450	19970130	00450	GL  	1997	1	30	97ZZZX522        	2	19970116	G	7250	23031478	BEARING         								ALLSN 	250C  	250C30P     	03013	GL  					TURB NR 8	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		1797 					CAT90681			INSP FOUND OD OF BEARING BELOW MIN DIMENSION AND INTERNAL CLEARANCE TOO MUCH.  0.0034 INCH MAX AND BEARING WAS 0.00364 I	NCH.  ALLOWED STATOR SEAL TO BE RUBBED BY 35/37 ROTATING SEAL.										3	U			E1GL				 
1997013000451	19970130	00451	NE  	1997	1	30	97ZZZX523        	3	19970110	G	6111	7756721	BLADE PIN       	HAMSTD      												HAMSTD	14SF	14SF7       	NE  	BLADE BUTT	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23		21221	6176 							REFERENCE:  FR25734.  PROP RETURNED FOR A BURNED HEATER.  INSP FOUND WRONG BLADE PIN HAD BEEN INSTALLED:  PROPER P/N IS 	775672-2.  ACTUAL PIN WAS P/N 775672-1.  DIFFERENCE IS IN OVERHAUL LENGTH.  SHORTER PIN (DASH 1) CANNOT ASSURE ADEQUATE 	ENGAGEMENT.														6	C	P7NE	 
1997013000452	19970130	00452	WP  	1997	1	30	97ZZZX524        	1	19970113	G	5512		SKIN            			DOUG  	DC10  	DC1015      	3022118	WP  										LT HORIZ STAB	DENTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	1003L					48258				TEMPORARY REPAIR INSTALLED ON LT HORIZ STAB UPPER SIDE STA XE 103 YA189.  REMOVED REPAIR FOUND DENTS.  OUT OF LIMITS.  C	UT OUT DENTED AREAS IAW DOUGLAS DWG 312891/96-10-16-18.  FABRICATED DOUBLERS PER SAME DWG.  ALODINED AND PRIMED IAW DC 1	0 SRM 51-21-01.  INSTALLED DOUBLERS IAW DOUGLAS DWG 312891/96-10-16-18.				2	L	7	3 	4F				A22WE   					 
1997020600182	19970206	00182	NE  	1997	2	6	97ZZZX528        	3	19970115	G	6111	6607132886	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  						ROTOL	R354	R3544123F13 	NE  	OUTER SLEEVE	CRACKED         	B	S	A	MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	110XJ	15215	6452 		SF3401321366	340A110		DRG178687		DURING INSPECTION FOR OVERHAUL, FOUND OUTER SLEEVE CRACKED WHERE PTFE TAPE FITS.  PROPELLER HAD BEEN REMOVED FOR ROUTINE	 MAINTENANCE.					2	L	7	2 	4T			RT	A52EU   		6	C	P61GL	 
1997020600187	19970206	00187	SO  	1997	2	6	97ZZZX532        	1	19970106	G	2710	62701122	CONTROL CABLE   			PIPER 	PA28  	PA28161     	7102803	SO  										LT AILERON	FRAYED          	B		A	DYTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	167ER	9404 				2841183				UPON INSPECTION OF AIRCRAFT CONTROL SYSTEMS, FOUND LEFT AILERON CABLE AT WS 57.00, WHERE THE CABLE PASSES THROUGH GUIDIN	G PULLEY, WORN AND WITH BROKEN STRANDS ABOUT .50 INCH OF LENGTH.  THIS CRS MAINTAINS A FLEET OF 17 LIKE TRAINING AIRCRAF	T.				1	L	7	1 	3O			 	2A13    					 
1997020600188	19970206	00188		1997	2	6	97ZZZX533        	4	19970110	G	2562	BP1040	BATTERY         		EAGLE       	SWRNGN	SA227 	SA227TT     		SW  										ELT	LEAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	99JW					TT450				DURING AN INSPECTION, THE ELT BATTERY WAS DUE FOR REPLACEMENT.  FOUND BATTERY LEAKING WHEN REMOVED.  NO DAMAGE WAS FOUND	 TO ELT UNIT.  OPS CHECKS SATISFACTORY WITH NEW BATTERY INSTALLED.  APPEARED TO LEAK AROUND CORNER OF CASE THAT WAS SEAL	ED AT MANUFACTURER.				2	L	7	2 	4T			RT	A5SW    					 
1997020600191	19970206	00191	CE  	1997	2	6	97ZZZX536        	1	19970107	G	7160	BA4106	FILTER HOUSING  			CESSNA	150   	152         	2071835	CE  										CARB INTAKE	MISMOUNTED      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	5289B					15283827				IN ORDER TO C/W AD 95-03-02 AND SUBSEQUENT 96-09-06, BRACKETT AIR FILTER, THE FILTER HOUSING MUST BE REMOVED FROM THE AI	R BOX.  WHEN RE-INSTALLING THE FILTER HOUSING OR DURING INITIAL INSTALLATION, IT IS POSSIBLE TO ALLOW THE HOUSING TO DRO	P DOWN FAR ENOUGH SO THAT THE FILTER HOUSING HITS THE BOTTOM COWLING DUE TO THE UP/DOWN MOVEMENT OF THE CESSNA MOUNTING 	HARDWARE ON THE AIR BOX.  THIS RESULTED IN LOOSENING OF THE CARB BOWL ATTACH BOLTS, DAMAGE TO THE VENTURI AND MAIN JET, 	AND THE ACCELERATOR PUMP SPRAY BAR BROKE OFF AND DROPPED INTO THE AIR BOX.		1	H	7	1 	3O			NT	3A19    					 
1997020600192	19970206	00192		1997	2	6	97ZZZX537        	2	19970106	G	7414	10349237	GEAR            		103493505   	BEECH 	58    	58          	1152740	CE  	298741									MAGNETO	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	31T	440  			C119640F	TH121				INSP FOUND COOKED, CORRODED BRUSH IN DIST GEAR DUE TO ARCING.  CARBON BRUSH IN LARGE GEAR ASSY RT MAGNETO, PN 10-349350-	5, MAY HAVE BEEN BROKEN PRIOR TO OR DURING ASSY OF MAGNETO.					1	L	7	2 	3O				3A16    					 
1997020600193	19970206	00193	SO  	1997	2	6	97ZZZX538        	2	19970106	G	8530	21361	VALVE KEEPER    			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					EXH VLV	STRIPPED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	714BE	2165 				15079044	255436			INSP FOUND THE LOCKING PORTION OF THE INSIDE DIAMETER OF PN 21361 (KEEPER) WAS STRIPPED AWAY ALLOWING EXHAUST VALVE TO E	NTER COMBUSTION CHAMBER OF CYL NR 1 DURING FLIGHT.  KEEPERS ARE OBVIOUSLY OF LESS HARDNESS THAN VALVE STEM.  TIME IN SER	VICE, OSCILLATORY FORCES, AND POSSIBLY DETONATION PEAK PRESSURES MAY HAVE RESULTED IN FAILURE.  PERHAPS PART HARDNESS WA	S INSUFFICIENT.			1	H	7	1 	3O	3	O		3A19    	E252				 
1997020600194	19970206	00194	SW  	1997	2	6	97ZZZX539        	1	19970117	G	5720	2893	FITTING         			BBAVIA	7     	7GCBC       	1220601	SW  										LT WING SPAR	CRACKED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	7596F					23970				DURING INVESTIGATION OF FATAL ACCIDENT (MIA97FA047), THE LEFT FORWARD LIFT STRUT TO WING SPAR FITTING WAS FOUND CRCKED I	N 2 PLACES AT THE OUTBOARD WELD TERMINALS.  ONE CRACK CROSSED THE FITTING FLANGE AND PROGRESSED .3750 INCH VERTICALLY ON	 THE WEB OF THE FITTING.  THE OTHER WAS ONLY ON THE FLANGE.  THESE CRACKS WERE NOT CONTRIBUTORY TO THE ACCIDENT.  AD 96-	18-02 DOES NOT APPLY TO THIS S/N AIRCRAFT.			1	H	7	1 	3O			NC	A759    					 
1997020600243	19970206	00243	SW  	1997	2	6	97ZZZX540        	1	19970107	G	6230	206010443001	DUPLEX BARING   		206010450113	BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	ROUGH           	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2618	239  			GDJG90483	45503				SWASHPLATE REMOVED DUE TO ROUGHNESS OF OUTER RING ROTATION.  AT DISASSEMBLY, FOUND DUPLEX BEARING INNER RACE PITTED.  TH	IS IS THE FOURTH BEARING FOUND DEFECTIVE WITH LESS THAN 1,000 HOURS.  THIS IS THE THIRD BEARING USED IN THIS SWASHPLATE 	IN LAST 12 MONTHS.				1	G	7	1 	3U				H2SW    					 
1997020600244	19970206	00244	GL  	1997	2	6	97ZZZX541        	2	19970103	G	7250	6898735	TURBINE         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					PT SUPPORT	CRACKED         	B	S		EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	6995 	524  		CAT33968	1151D	CAE832750			DURING REPLACMENT OF THE NR 1 NOZZLE, A CRACK WAS FOUND IN THE P/T SUPPORT BODY JUST AFT OF THE 6 AND 7 BEARING.  SUMP B	OSS UNIT WAS SENT IN FOR REWORK.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997020600245	19970206	00245	CE  	1997	2	6	97ZZZX542        	1	19970102	G	7160	BA8110	FILTER          			CESSNA	180   	180G        	2072616	CE  										CARB AIR INTAKE	DEFECTIVE       	D	L	A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NE	05	4666U					18051366				DURING CLIMB NEAR TOTAL POWER LOSS.  INVESTIGATION FOUND BRACKET AIR FILTER FAULTY DUE TO BOTTOM CHANNEL CAUSES WATER/IC	E CONTAMINATION OF ENGINE INTAKE BELLOWS JUST FORWARD OF AIR BOX.					1	H	7	1 	3O				5A6     					 
1997020600388	19970206	00388	CE  	1997	2	6	97ZZZX544        	1	19970121	G	5711		CARRY THRU SPAR 			BEECH 	33    	F33A        	1151425	CE  										FUSELAGE	CRACKED         	B		A	VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8252T	6690 				CE1545				INSP FOUND CRACKS IN CARRY THROUGH STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.  THIS IS THE 14TH AIRCRAFT REPORT	ED.					1	L	7	1 	3O				3A15    					 
1997020600389	19970206	00389	CE  	1997	2	6	97ZZZX545        	1	19970121	G	5711		CARRY THRU SPAR 			BEECH 	33    	F33A        	1151425	CE  										FUSELAGE	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8173C	6740 				CE1541				INSP FOUND CRACKS IN CARRY THRU STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.  THIS IS THE 15TH AIRCRAFT REPORTED.						1	L	7	1 	3O				3A15    					 
1997020600390	19970206	00390	CE  	1997	2	6	97ZZZX546        	1	19970121	G	5711		CARRY THRU SPAR 			BEECH 	33    	F33A        	1151425	CE  										FUSELAGE	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5530A	8493 				CE1342				INSP FOUND CRACKS IN CARRY THRU STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.  THIS IS THE 16TH AIRCRAFT REPORTED.						1	L	7	1 	3O				3A15    					 
1997020600393	19970206	00393	CE  	1997	2	6	97ZZZX549        	1	19970103	G	3230	99101543	CYLINDER        			CESSNA	402   	402CESSNA   	207590K	CE  										EMERG GEAR EXT	CRACKED         	B			T4OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										RECEIVED CYLINDER FOR HYDROSTATIC TEST.  DURING INTERNAL INSPECTION, FOUND CRACK IN SHOULDER AREA.  LENGTH OF CRACK APPR	OX .33 INCH TO .50 INCH IN CIRCUMFERENCE.  CESSNA PART NO. 9910154-3 SERIAL NR 1816.  MANUFACTURED FOR FUTURECRAFT CORP.	  PART NR 900294-4.  THIS CYLINDER IS USED FOR EMERGENCY GEAR BLOWDOWN.  THIS CYLINDER'S LAST HYDROSTATIC TEST WAS 6/84.	  CRACK MAY HAVE OCCURRED WHILE BEING OVER PRESSURIZED.			1	L	7	2 	3O				A7CE    					 
1997020600371	19970206	00371	CE  	1997	2	6	97ZZZX558        	1	19970106	G	7160	189100143	ADAPTER         			BEECH 	18    	H18         	1151012	CE  										LT ENG CARB AIR	DISCONNECTED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				DURING INSPECTION OF LEFT ENGINE EXHAUST AS A RESULT OF RIGHT EXHAUST FAILURE, FOUND INBOARD HEAT DUCT DISCONNECTED.  TH	IS WAS DUE TO COLLAPSE OF THE END OF THE ADAPTER ASSY.  UPON DISASSEMBLY OF SYSTEM, FOUND BOTH LEGS OF ADAPTER COLLAPSED	 FROM OVERTORQUE OF DUCT CLAMPS.  REMOVED AND REPLACED ADAPTER.				1	L	7	2 	3R				A765    					 
1997020600372	19970206	00372	CE  	1997	2	6	97ZZZX559        	1	19970106	G	7160	189100143	ADAPTER         			BEECH 	18    	H18         	1151012	CE  										RT ENG CARB AIR	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				WHILE REPAIRING DAMAGE CAUSED BY EXHAUST STACK FAILURE, FOUND OUTBOARD END OF ADAPTER UPPER SIDE BURNED AND MELTED APPRO	XIMATELY 3 INCHES.  MATERIAL MIGRATED INTO INDUCTION HEAD VALVE AND FUEL INJECTOR SERVO.  REPLACED ADAPTER ASSY.					1	L	7	2 	3R				A765    					 
1997020600373	19970206	00373	CE  	1997	2	6	97ZZZX560        	1	19970106	G	7810	18950016	EXHAUST STACK   			BEECH 	18    	H18         	1151012	CE  										RT ENG NR 7 CYL	HOLED           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				PILOT REPORTED RIGHT ENGINE QUIT WHEN INDUCTION HEAT SELECTED DURING RUN-UP.  CARBURETOR TEMPERATURE GAUGE WENT OFF TOP 	OF SCALE.  INVESTIGATION REVEALED 2 INCH BY 4 INCH HOLES IN OUTBOARD UPPER STACK ASSEMBLY OF OLD POOR QUALITY REPAIR.  A	LSO, STACK MISSING NUMEROUS STUDS.  STACK WAS SENT OUT FOR REPAIR.  ALSO, FOUND HEAT DUCT AND ADAPTER ASSEMBLY DAMAGED A	ND MELTED FIBERGLASS IN INTAKE SCOOP, FUEL INJECTOR SERVO FUEL INJECTOR SCREEN.  42.4 HOURS  SINCE ANNUAL INSPECTION AND	 REMOVAL FROM PART 135 OPERATION.		1	L	7	2 	3R				A765    					 
1997020600374	19970206	00374	CE  	1997	2	6	97ZZZX561        	1	19970107	G	7160	130358	SPRING          			BEECH 	18    	H18         	1151012	CE  										CARB AIR VALVE	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				WHILE CLEANING DEBRIS FROM EXHAUST FAILURE, FOUND SPRING MISSING.  SPRING HAD APPARENTLY BEEN MISSING FOR SOME TIME FROM	 APPEARANCE OF MOUNTING HOLES.					1	L	7	2 	3R				A765    					 
1997020600375	19970206	00375	CE  	1997	2	6	97ZZZX562        	1	19970107	G	3020	111716AX5XX9	DUCT            			BEECH 	18    	H18         	1151012	CE  										RT ENGINE	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				DURING REPAIR OF RIGHT EXHAUST, FOUND DUCT BADLY DETERIORATED AND COLLAPSED.  OLD DUCT APPEARED TO BE SINGLE WALL SCAT H	OSE.  NEW DUCT WAS DOUBLE WALLED, HEAVIER, AND BLACK INSTEAD OF ORANGE.  REPLACED DUCT.  42.4 HRS SINCE ANNUAL.					1	L	7	2 	3R				A765    					 
1997020600376	19970206	00376	CE  	1997	2	6	97ZZZX563        	1	19970107	G	3020	111716AX5XX9	DUCT            			BEECH 	18    	H18         	1151012	CE  										LT ENGINE	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				WHILE REPAIRING EXHAUST SYSTEM, FOUND DUCT COLLAPSED AND BADLY DETERIORATED.  OLD DUCT APPEARED TO BE ORANGE SINGLE WALL	 SCAT HOSE.  NEW DUCT WAS BLACK HEAVY DOUBLE WALLED AND BORE BEECH P/N NR I.D. ON OLD DUCT.  REMOVED AND REPLACED DUCT.					1	L	7	2 	3R				A765    					 
1997020600377	19970206	00377	CE  	1997	2	6	97ZZZX564        	1	19970107	G	3020	183800005	DUCT            			BEECH 	18    	H18         	1151012	CE  										RT ENG HEAT	HOLE CHAFED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				WHILE CONDUCTING OTHER WORK ON RIGHT ENGINE, FOUND HOLE CHAFED IN INBOARD INDUCTION HEAT DUCT.  THIS AREA HAD PREVIOUSLY	 BEEN REPAIRED USING A SILICONE SEALER MATERIAL.  REPLACED DUCT AND POSITIONED CLEAR OF EXHAUST.  42.4 HRS SINCE ANNUAL.					1	L	7	2 	3R				A765    					 
1997020600378	19970206	00378	CE  	1997	2	6	97ZZZX565        	1	19970107	G	3020	183800003	DUCT            			BEECH 	18    	H18         	1151012	CE  										RT ENG OTBD	HOLE BURNED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				FOUND OUTBOARD INDUCTION HEAT DUCT BURNED THROUGH (APPROXIMATELY 6 INCH HOLE).  OLD DUCT APPEARED TO BE SCAT HOSE.  NEW 	PART WAS MUCH HEAVIER AND OVAL SHAPED.  REPLACED DUCT.					1	L	7	2 	3R				A765    					 
1997020600379	19970206	00379	CE  	1997	2	6	97ZZZX566        	1	19970106	G	7810	18950016	EXHAUST STACK   			BEECH 	18    	H18         	1151012	CE  										LT ENG	BULGED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	223JW					BA716				LEFT ENGINE EXHAUST WAS INSPECTED AFTER FAILURE OF RIGHT ENGINE EXHAUST STACK.  EXHAUST STACK WAS FOUND BULGED IN SAME A	REA AS FAILURE OF RIGHT STACK (NR 7 CYL).  THIS AREA HAD A PRIOR QUALITY REPAIR AND WAS MISSING NUMEROUS HEAT STUDS.  ST	ACK WAS SENT OUT FOR REPAIR.  42.4 HRS SINCE ANNUAL.				1	L	7	2 	3R				A765    					 
1997020600380	19970206	00380	EA  	1997	2	6	97ZZZX567        	2	19970106	G	7310		HOSE            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					CYL 1-3	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	6206Y					273433	L917248			THIS LINE LOOKED VERY GOOD.  NOT STIFF OR CHAFED IN ANY WAY.  HOWEVER, THE RUBBER HOSE BELOW THE BRAIDED COVER RUPTURED 	AND ALLOWED FUEL TO SOAK BETWEEN CYLINDERS NR 1 AND NR 3 CREATING AN IN-FLIGHT FIRE HAZARD.  ONLY WAY TO CHECK OR TEST I	S REMOVAL OF LINE AND PRESSURIZE WITH AIR UNDER WATER.				1	L	7	2 	3O	3	O		1A10    	1E4				 
1997020600382	19970206	00382	CE  	1997	2	6	97ZZZX569        	1	19970117	G	3260	5801	INDICATOR       		8000        	CESSNA	208   	208         	2073702	CE  										RT MLG	MALFUNCTION     	E		A		K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			NE	03	208RD	250  				20800054				AIRCRAFT WAS FLYING AT 3,000 FEET, REPORTED TEMP OF 22 DEGREES FAHRENHEIT.  AIRCRAFT DID NOT GET RIGHT MAIN LANDING GEAR	 DOWN AND LOCKED LIGHT.  INVESTIGATION DETERMINED LANDING GEAR MAGNETIC POSITION INDICATOR WAS FROZEN.  AFTER AIRCRAFT W	ARMED UP, INDICATOR FUNCTIONED PROPERLY.  EXTREME COLD COULD HAVE CAUSED THE BI-METALIC COMPONENTS TO SHRINK CAUSING THE	M NOT TO MAKE CONTACT, OR MOISTURE PENETRATED SWITCH AND FROZE BETWEEN METAL TABS.  POTTING SWITCH MAY SOLVE THIS PROBLE	M.		1	H	7	1 	3T			NT	A37CE   					 
1997020600384	19970206	00384	CE  	1997	2	6	97ZZZX571        	1	19970122	G	5741	C512122	FITTING         			CESSNA	150   	150H        	2071818	CE  										REAR SPAR ATTACH	CRACKED         	G	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	7046S	5089 	5089 			15067746				REMOVED THE REAR WING SPAR ATTACH BLOCK FITTINGS, CESSNA P/N C512122, FROM EACH END OF THE REAR SPAR/DOORPOST CARRY-THRO	UGH CHANNEL FOR INSPECTION.  AFTER CLEANING, IT WAS NOTED THE RIGHT FITTING WAS CORRODED AND CONTAINED A CRACK EXTENDING	 DIAGONALLY FROM THE FORWARD OUTSIDE BASE CORNER THROUGH TO THE CORRESPONDING INSIDE CORNER.  FURTHER INSPECTION OF THIS	 COMPONENT INDICATES THE CLEVIS END, WHICH MATES WITH THE REAR WING SPAR ATTACHMENT STRUCTURE, HAD BEEN COMPRESSED TO A 	POINT WHERE THE BASE OF THE LEG YIELDED RESULTING IN THE CRACK.		1	H	7	1 	3O				3A19    					 
1997020600385	19970206	00385	CE  	1997	2	6	97ZZZX572        	1	19970122	G	2751	0510105231	CONTROL CABLE   			CESSNA	182   	182P        	2075816	CE  										FLAP INDICATOR	FRAYED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	58776	3390 				18262288				DURING A 100 HR INSPECTION, THE FLAP INDICATOR CABLE WAS FOUND TO BE FRAYED.  THIS CONDITION WAS NOTED TO BE JUST AFT OF	 THE FORWARD PULLEY UNDER THE FLOOR WITH THE FLAPS IN THE FULL DOWN POSITION.  FURTHER INVESTIGATION FOUND THAT WHEN THE	 FLAPS WERE IN THE FULL UP POSITION, THE CABLE BECAME EXCESSIVELY SLACK AND THE FRAYED PORTION CONTACTED THE FORWARD SID	E OF THE HOLE WHERE IT PASSES THROUGH THE FLOOR BOARD.			1	H	7	1 	3O			NT	TA13    					 
1997020600386	19970206	00386	CE  	1997	2	6	97ZZZX573        	1	19970121	G	8120	99102998	EXHAUST WYE     			CESSNA	414   	414         	2075908	CE  										OUTLET TUBE	CRACKED         	B	L	A	VX3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	74DH	520  	520  			4140948				TURBO EXHAUST WYE RECEIVED FOR INSP AND REPAIR.  FOUND UNIT HAD A CRACK AROUND WELD ON OUTLET TUBE SIDE.  IT WAS EVIDENT	 TUBE AND INTERNAL DIVIDER HAD BEEN REPLACED.  IMPROPER MATERIALS HAD BEEN UTILIZED IN THE FABRICATION OF THE OUTLET TUB	E AND DIIVDER.				1	L	7	2 	3O			RT	A7CE    					 
1997020600387	19970206	00387	SO  	1997	2	6	97ZZZX574        	2	19970114	G	7322	6467582	INJECT PUMP     			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					IDLE CUTOFF	PIN DETACHED    	H	L	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	11	28MC		1500 		J238730B2	28R7931271				UPON REACHING AN ALT OF 4500 FEET, THE PILOT LEANED THE MIXTURE CONT.  AT THE POINT OF ENG ROUGHNESS, HE ATTEMPTED TO EN	RICHEN THE MIXTURE.  THE MIXTURE WOULD NOT ADVANCE.  IN THE PROCESS OF TRYING TO FREE THE MIXTURE, THE ENG QUIT, AND THE	 MIXTURE COULD NOT BE ADVANCED FROM THE IDLE CUT-OFF POSITION.  PILOT MADE EMERG LANDING.  THE AIRCRAFT WAS NOT DAMAGED.	  THE ENG INSTALLED ON THIS ACFT UTILIZES A TCM P/N 646758-2 FUEL INJECT PUMP.  THIS FUEL INJECTION PUMP INCORPORATES TH	E FUEL MIXTURE CONT AS AN INTEGRAL PART.  AN INVEST OF THIS 'UNSCHEDULED LANDING' REVEALED THAT THE MIX CONT ARM MECH ST	OP (STEEL ROLL PIN) HAD LOOSENED AND MIGRATED OUT OF POSITION LOCKING THE MIXTURE CONT ARM IN THE IDLE CUTOFF POSIT.	1	L	7	1 	3O	3	O		2A13    	E9CE				 
1997020600539	19970206	00539	WP  	1997	2	6	97ZZZX575        	1	19970122	G	2621	246875	SWITCH GAUGE    		899827      	DOUG  	DC8   	DC8*        		WP  										FIRE EXTINGUISHE	SHORTED         	B			YN2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01					25481DH					SWITCH GAUGE ON FIRE EXTINGUISHER BOTTLE HAS INTERNAL SHORT.  SHORT IS NOT DETECTABLE BY SWITCH GAUGE CHECK PROCEDURE IN	 FIRE EXTINGUISHER OVERHAUL MANUAL.  TO DETECT A DEFECTIVE SWITCH GAUGE, CHECK PINS 1, 2, AND 3 FOR CONTINUITY WITH THE 	GAUGE CASE.  IF ANY PIN HAS CONTINUITY WITH GAUGE CASE, SWITCH GAUGE IS DEFECTIVE.				2	L	7	4 	4J			F	4A25    					 
1997020600540	19970206	00540	EU  	1997	2	6	97ZZZX576        	1	19970123	G	3244	226K086	TIRE            	GOODYEARAERO		AMD   	FALC10	FALCON10    	2730101	EU  										NR 4 MAIN	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	654PC	46   			53461996	131				DURING ROUTINE AIR CHECK, FOUND TIRE PRESSURE LOW (NORMAL 145 POUNDS).  RE-CHECKED TIRE FOR 3 DAYS, FOUND TO LOSE 11 TO 	15 POUNDS PER DAY.  THIS TIRE WAS OKAY ON THE FIRST 40 HOURS OF SERVICE.  REMOVED, FOUND 5 SIDEWALL BLEED VENTS LEAKING.	  REPLACED WHEEL AND TIRE ASSY, NO FURTHER ACTION.				2	L	7	2 	4F				A33EU   					 
1997020600541	19970206	00541	NE  	1997	2	6	97ZZZX577        	2	19970101	G	7250	1358M12P05	BLADE           								GE    	CFM56 	CFM565A     	13802	NE  					ENG HPT	FAILED          	B	L	A	LY2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	07		15782					731642			INSP FOR ENG FAILURE FOUND ALL HPT BLADES BROKEN AT PLATFORM.  IT APPEARS THAT NR 8 BLADE S/N 4L764 WAS THE FIRST BLADE 	TO FAIL.  CAUSE OF FAILURE UNKNOWN AT THIS TIME.  OEM AND OWNER ARE DOING EXTENSIVE INVESTIGATION.										4	F			E29NE				 
1997020600542	19970206	00542	SO  	1997	2	6	97ZZZX578        	2	19970101	G	8530	646283	VALVE           								CONT  	O520  	IO520*      	17032	SO  					CYL INTAKE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										INTAKE VALVE ON 470/520 SERIES ENGINES BUILT BY CONTINENTAL.  THE VALVE FACE IS TOO SOFT AND SHOWS SEVERE WEAR.  SUBMITT	ER CHECKED OVER 50 DIFFERENT CYLINDERS WITH HOURS RANGING FROM 150 HOURS TOTAL TIME TO 1500 HOURS TOTAL TIME AND ALL VAL	VES WITH THIS PART NUMBER HAVE SIGNS OF SEVERE WEAR.									3	O			E5CE				 
1997020600543	19970206	00543	GL  	1997	2	6	97ZZZX579        	2	19970122	G	7250	23034713	PT SHAFT        								ALLSN 	250C  	250C20B     	03013	GL  					N2 SPLINE	CHIPPED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11		4612 	1163 		63005		CAT37434			ENGINE REJECTED DUE TO N2 SPLINE CHIPPED SHAFT.  THE FRONT END OF THE SPLINE WAS CHIPPED.  SUBMITTER BELIEVES THIS IS CA	USED AT INSTALLATION OF TURBINE GEARBOX.										3	U			E4CE				 
1997020600544	19970206	00544	WP  	1997	2	6	97ZZZX580        	2	19970106	G	7322	3598037	DRIVESHAFT      	WOODWARD    	89778024    						GARRTT	TPE331	TPE33110U   	01514	WP  					FCU INPUT	WORN            	B			DSCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25			1548 		1711117		P63045			FUEL CONTROL DRIVESHAFT WAS FOUND TO BE WORN BEYOND MM LIMITS DURING ENGINE REPAIR.  THE CURRENT FUEL CONTROL PART NUMBE	R (89770-24) INDICATES C/W EITHER ALLIED SIGNAL SB 73-0227 OR SB 73-0228. THE PRE SB CONTROLS WERE THE SUBJECT OF AD 94-	26-07.  C/W THESE BULLETINS HAS, IN THE PAST, SOLVED THE PROBLEM OF EXCESSIVE WEAR TO THESE PARTS; HOWEVER, THIS PART CO	NTINUES TO SHOW PRE-BULLETIN COMPLIANCE WEAR PATTERNS.  THE CONTROL HAS BEEN FORWARDED TO WOODWARD FOR EVALUATION.								4	T			E4WE				 
1997020600546	19970206	00546	NM  	1997	2	6	97ZZZX582        	1	19970115	G	3230	108410	VALVE BODY      		1U10B4      	BOEING	727   	727         	1384001	NM  										MLG DOOR VALVE	CRACKED         	B			DM4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19					1439					SEQUENCE VALVE BODY HAS FATIGUE CRACK NEAR PORT VC AND LEAKS WITH 2,500 PSI APPLIED.  BODY IS ALUMINUM.  CASTING UNIT HA	S A TOTAL TIME OF 84,556.19 BUT UNKNOWN HOURS ON ACTUAL BODY.					2	L	7	3 	4F				A3WE    					 
1997020600557	19970206	00557	EA  	1997	2	6	97ZZZX592        	2	19970116	G	7261	3030350	CHIP DETECTOR   			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					RT ENG	BROKEN          	D				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			EA	05	777YP					425501008	PCE99016			IN-FLIGHT, PILOT NOTICED TORQUE FLUCTUATION AND LOSS OF OIL PRESSURE.  LANDED WITHOUT INCIDENT.  RT ENGINE AND COWLING C	OVERED WITH OIL.  INSPECTED ENGINE AND FOUND CHIP DETECTOR BROKEN CAUSING ALL ENG OIL TO DRAIN FROM POWER SECTION.					1	L	7	2 	4T	4	T		A23SO   	E4EA				 
1997020600558	19970206	00558	NM  	1997	2	6	97ZZZX593        	1	19970106	G	7160	6550642512	DUCT ASSY       			BOEING	727   	727276      	138408R	NM  										NR 2 ENG INLET	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				DURING C-7 INSPECTION, CORROSION WAS NOTED IN SEVERAL AREAS THOUGHOUT NR 2 ENGINE INLET UPPER 'S' DUCT ASSY.						2	L	7	3 	4F			RT	A3WE    					 
1997020600562	19970206	00562	EU  	1997	2	6	97ZZZX597        	1	19970110	G	3830	A1AW0012	LINE            			BRAERO	1000  	BAE1251000  	1500287	EU  										GALLEY DRAIN	CRACKED         	B			DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	525QS					259025				80 INCH LONG GALLEY DRAIN LINE WAS FOUND CRACKED FROM WATER EXPANSION.  THIS LINE RUNS FROM GALLEY ALONG LOWER SIDE PLAT	ES INSIDE CABIN AREA.  ATTACH POINTS FOR LINE ONLY ALLOW A LEVEL INSTALLATION UNTIL JUST BEFORE IT ANGLES BELOW THE CABI	N.  THE CRACK WAS IN THE LEVEL AREA.				2	L	7	2 	4F			RT	A3EU    					 
1997020600563	19970206	00563	NM  	1997	2	6	97ZZZX598        	1	19970106	G	7160	6520770535	DUCT ASSY       			BOEING	727   	727276      	138408R	NM  										NR 2 ENG INLET	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	908PG					20951				DURING C-7 INSPECTION, CORROSION WAS NOTED IN SEVERAL AREAS THROUGHOUT NR 2 ENG INLET LOWER S-DUCT ASSY.						2	L	7	3 	4F			RT	A3WE    					 
1997021300047	19970213	00047	SW  	1997	2	13	97ZZZX600        	1	19970114	G	7120	2762114083	TRUSS MOUNT     			SWRNGN	SA227 	SA227*      		SW  										ENG UPPER AFT	NOT WELDED      	B	P	A	H7NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17					407015					INSP OF FAIRCHILD MDL SA227, TPE331 ENG MOUNT TRUSS REVEALED AREA UNDER PLATE OR UPPER AFT MOUNT NOT WELDED.  PLATE P/N 	27-62114-073/074 ATTACHES TO TUBES 27-62114-019 AND -023.  NO CRACK NOTED BUT SUBMITTER NOW INSPECTS ALL MOUNTS TO MAKE 	SURE THEY ARE WELDED IN THIS AREA.  HAVE NOTED CRACKS ON PRIOR MOUNTS AND HAVE FILED M OR D'S ON THEM.  NOTE STAMP FROM 	MANUFACTURE IS EITHER WSA5 OR WSA6 ON ALL THOSE WE HAVE SEEN THE PROBLEM ON.			2	L	7	2 	4T			RT	A5SW    					 
1997021300048	19970213	00048	SW  	1997	2	13	97ZZZX601        	1	19970114	G	7120	2762114083	MOUNT           			SWRNGN	SA227 	SA227*      		SW  										ENG UPPER AFT	NOT WELDED      	B		A	H7NR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17					311017					FOUND AREA UNDER PLATE ON ENG UPPER AFT MOUNT NOT WELDED.  PLATE P/N 27-62114-073/074 ATTACHES TO TUBES 27-62114-019 AND	 -023.  NO CRACK NOTED, BUT SUBMITTER NOW INSPECTS ALL MOUNTS TO MAKE SURE THIS AREA IS WELDED.  ALSO, NOTE STAMP WSA5 O	R WSA6 ON THE ONES FOUND NOT WELDED.  NOTE 2ND REPORT THIS DATE.				2	L	7	2 	4T			RT	A5SW    					 
1997021300049	19970213	00049	EA  	1997	2	13	97ZZZX602        	2	19970126	G	8520		CONNECTING ROD  			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					LT ENG	FAILED          	E				A				UNSCHED LANDING         				Y	K		ENGINE STOPPAGE           	FLUID LOSS                		CR	CRUISE         	1			AL	01	101LJ	1435 	1435 			31267	L173861			AFTER PREVIOUS FLIGHT SHUTDOWN DUE TO OIL LOSS FROM BROKEN OIL LINE, OIL LINE WAS REPLACED AND ENGINE GROUND RUN.  A/C W	AS ON FERRY FLIGHT FROM ARCTIC VILLAGE TO FAIRBANKS WHEN LEFT ENGINE SUFFERED IMMEDIATE STOPPAGE.  THE AIRCRAFT WAS LAND	ED EN ROUTE AT FORT YUKON.  UPON INSPECTION IT WAS FOUND A CONNECTING ROD HAD FAILED AND GONE THROUGH THE CRANKCASE CAUS	ING IMMEDIATE ENGINE FAILURE.  A/C WAS LANDED SAFELY.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997021300050	19970213	00050	EA  	1997	2	13	97ZZZX603        	2	19970123	G	8550		LINE            			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					TURBO	FAILED          	E		A		E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			AL	01	101LJ					31267	L173861			ON A FLIGHT FROM FBXS TO ARCTIC VILLAGE, THE PILOT LOST MANIFOLD PRESSURE AND OIL PRESSURE.  THE PILOT THEN SHUT DOWN TH	E LEFT ENGINE IN-FLIGHT AND LANDED AT ARCTIC VILLAGE.  AFTER LANDING, IT WAS DETERMINED THE OIL LINE FROM THE TURBO WAST	EGATE WAS BROKEN BEHIND THE FITTING CAUSING LOSS OF OIL.  THIS RESULTED IN A CORRESPONDING LOSS OF OIL AND MANIFOLD PRES	SURE.			1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
1997021300051	19970213	00051	SW  	1997	2	13	97ZZZX604        	1	19970124	G	8011	MZ4222	STARTER         		PRESTOLITE  	MOONEY	M20   	M20J        	5870219	SW  										MOUNT	BOLTS LOOSE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	201SQ		34   		4071886	240298				WHILE ATTEMPTING TO START A/C AFTER LANDING AND GETTING FUEL, PILOT REPORTED STARTER STOPPED WORKING AND MIXTURE CABLE W	OULD NOT MOVE.  FOUND STARTER HOUSING ATTACH BOLTS COMPLETELY SHEARED OFF AND MISSING ALLOWING STARTER TO REST ON MIXTUR	E CONTORL ARM AT FUEL CONTROL UNIT.  SUBMITTER STATES THIS IS THE 2ND OCCURRENCE OF THIS SAME PROBLEM ON THIS SAME A/C.				1	L	7	1 	3O				2A3     					 
1997021300054	19970213	00054	EA  	1997	2	13	97ZZZX607        	2	19970101	G	7414		DISTRIBUTOR GEAR	BENDIX      	S6LN1208    	BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					LT ENG MAG	TEETH MISSING   	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NE	05	711CE	750  			A099004E	P437	L114659			ENG QUIT IN FLT.  RETURNED TO 5B5.  FOUND ON BOTH MAGNETOS ALMOST 100 PERCENT OF THE TEETH ON DISTRIBUTOR GEARS WERE MIS	SING (SHEARED OFF), BOTH DISTRIBUTOR GEAR CONTACT FINGERS BROKEN OFF AND WEDGED BETWEEN GEAR AND DIST. BLOCK CAUSING TOT	AL LOSS OF IGNITION.				1	L	7	2 	3O	3	O		A12CE   	E10EA				 
1997021300055	19970213	00055	EA  	1997	2	13	97ZZZX608        	2	19970101	G	7414		DISTRIBUTOR GEAR	BENDIX      	S6LN1209    	BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					LT ENG MAG	TEETH MISSING   	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NE	05	711CE	750  			A129015F	P437	L114659			ENG QUIT IN FLT.  RETURNED TO 5B5.  FOUND ON BOTH MAGNETOS ALMOST 100 PERCENT OF THE TEETH ON DISTRIBUTOR GEARS WERE MIS	SING (SHEARED OFF), BOTH DISTRIBUTOR GEAR CONTACT FINGERS BROKEN OFF AND WEDGED BETWEEN GEAR AND DIST. BLOCK CAUSING TOT	AL LOSS OF IGNITION.				1	L	7	2 	3O	3	O		A12CE   	E10EA				 
1997021300058	19970213	00058	SO  	1997	2	13	97ZZZX611        	2	19970117	G	8500		ENGINE          			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					MIXTURE	MALFUNCTION     	D				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			NM	08	9438M					U20604546	248770R			OAT - 18 DEGREES, WX CLEAR.  TAKEOFF NORMAL.  WHEN POWER REDUCED, ENGINE WENT VERY RICH.  PULLED MIX TO KEEP ENGINE RUNN	ING.  M.P. AND F.F. READ NORMAL.  LANDED.  LOW RPM OK.  CHECKED BOTH METERED AND UNMETERED FUEL PRESSURES ARE WITH THE B	OOK.  FLEW A/C AFTER, ALL WAS NORMAL.  ORIG FUEL CONT REPLACED AT 302.8 TSO, NEXT AT 472.9 TSO.  ENG NOW HAS 1182.3 TSO.				1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1997021300059	19970213	00059	CE  	1997	2	13	97ZZZX612        	1	19970101	G	8011	643259A	CLUTCH          			CESSNA	185   	185         	2072802	CE  										STARTER	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	9855X	850  				1850055				DURING ROUTINE INSPECTION, COULD NOT 'ROCK' PROPELLER.  ENGINE WOULD NOT TURN BACKWARD EVEN WITH CONSIDERABLE TORQUE APP	LIED.  (600 FEET/POUNDS).  AFTER REMOVING STARTER CLUTCH PN 643259A, ENGINE TURNED FREELY.  IF ENGINE WERE TO KICK BACK 	DURING START, POSSIBLE SIGNIFICANT DAMAGE TO ENGINE COULD OCCUR.				1	H	7	1 	3O			NC	3A24    					 
1997021300061	19970213	00061	GL  	1997	2	13	97ZZZX614        	3	19970123	G	6114		HUB             			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 2 SOCKET	CRACKED         	B			UCXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	731XN	2988 	1143 			18803239T		822946		UPON NDT (EDDY CURRENT INSP) IAW MCCAULEY SB 205B, A MICROSCOPIC CRACK WAS FOUND IN THE LOADED SIDE OF THE 3RD THREAD IN	 THE NR 2 BLADE SOCKET.  THE HUB WAS SENT TO MCCAULEY FOR VERIFICATION.					1	L	7	1 	3O				A9CE    		5	C	P3EA	 
1997021300062	19970213	00062	EU  	1997	2	13	97ZZZX615        	1	19970115	G	7500	1379287L403	LINE            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  					ENG BLEED	FAILED          	E		A		K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	11										BLEED AIR LINE FAILED AT ENGINE ATTACHMENT FLANGE.  WELD CRACKED AND LINE SEPARATED IN-FLIGHT. ACFT WAS 10 HRS OUT OF IN	SP WITH NO LEAKS EVIDENT IN THE INSP.  S/B 21-JM-7797 (OPTIONAL) WAS NOT C/W AT THIS TIME.					2	L	7	2 	4T	4	T	RT	A21EU   	E4WE				 
1997021300063	19970213	00063	EU  	1997	2	13	97ZZZX616        	1	19970122	G	2710	5135123	TORQUE TUBE     		513025501   	ISRAEL	1124  	1124A       	4500103	EU  										AILERON	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	2BG					365				UPON PERFORMING SB 1124-27-129 AND AD 96-24-11, FOUND WEAR INDICATED PER AD AND SB.  FURTHER INSPECTION INDICATED GROOVE	S ON THE BOTTOM OF THE TUBE CAUSED BY THE EDGES OF THE ROLLERS.  PILOT STATED THAT THE OTHER TUBE PREVIOUSLY REPLACED HA	D THE SAME GROOVES IN IT.  TWO GROOVES AT THE BOTTOM OF THE TUBE, BOTH ENDS.  GROOVES ARE .50 INCH LONG, AROUND .010 INC	H TO .015 INCH WIDE, AND .015 INCH TO .020 INCH DEEP, INDICATING POSSIBLE FAILURE OF TUBE THAT THE AD AND SB DO NOT ADDR	ESS OR REQUIRE INSPECTION.		2	M	7	2 	4F				A2SW    					 
1997021300064	19970213	00064	SO  	1997	2	13	97ZZZX617        	1	19970127	G	3241		ANTI SKID       			GULSTM	G1159 	G1159A      	3970109	SO  										R CONT VALVE	WIRE DAMAGED    	H				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	23	5105	5453 				445				THE ANIT-SKID LIGHT ILLUMINATED DURING TAKEOFF ROLL. THE CREW ABORTED AND RETURNED TO THE RAMP.  THE SYSTEM WAS RESET WI	TH NO FURTHER FAILURES.  WHEN THE AIRCRAFT RETURNED TO DTW, AN IN-DEPTH INSPECTION OF THE ANTI-SKID SYSTEM REVEALED INSU	LATION ON A WIRE AT THE RIGHT CONTROL VALVE WAS DAMAGED.  REPAIRED THE WIRE.				2	L	7	2 	4F				A12EA   					 
1997021300067	19970213	00067	EU  	1997	2	13	97ZZZX620        	1	19970118	G	2740	TB1034006104	LEVER           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										HORIZ STAB	BENT            	G				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			EA	13	2803A	956  				1036				INSP FOUND BOTH PITCH CONTROL LEVERS BENT OUTWARD FROM CENTER.  PILOT EXPERIENCED INSUFFICIENT NOSE DOWN PITCH CONTROL J	UST AFTER TAKEOFF.  MOST LIKELY CAUSE DETERMINED TO BE A HIGH TAIL WIND GUST OR JET WASH HITTING BACK OF AIRCRAFT WHILE 	PARKED AND CHOCKED ON FBO RAMP.  CONTROL YOKE GUST LOCKS WERE IN PLACE AT TIME PROBLEM DEVELOPED.				1	L	7	1 	3O			RT	A51EU   					 
1997021300068	19970213	00068	EU  	1997	2	13	97ZZZX621        	1	19970118	G	2740	TB1034006103	LEVER           		TB2034001000	SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										HORIZ STAB	BENT            	G		A		O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			EA	13	2803A	956  				1036				INSP FOUND BOTH PITCH CONTROL LEVERS BENT OUTWARD FROM CENTER.  PILOT EXPERIENCED INSUFFICIENT NOSE DOWN PITCH CONTROL J	UST AFTER TAKEOFF.  MOST LIKELY CAUSE DETERMINED TO BE A HIGH TAIL WIND GUST OR JET WASH HITTING BACK OF AIRCRAFT WHILE 	PARKED AND CHOCKED ON FBO RAMP.  CONTROL YOKE GUST LOCKS WERE IN PLACE AT TIME PROBLEM DEVELOPED.				1	L	7	1 	3O			RT	A51EU   					 
1997021300069	19970213	00069	SO  	1997	2	13	97ZZZX622        	1	19970112	G	5741	AN17612	SPAR BOLTS      			PIPER 	PA28  	PA28R201T   	7102813	SO  										WING ATTACH	CORRODED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11			101  							WHEN INSP WINGS PER SB 88C, FOUND ALL WING SPAR ATTACH BOLTS TO BE CORRODED WITH PITS.  BOLTS INSTALLED 101 HRS PRIOR ON	 4-20-92.  BOLTS WERE APPARENTLY INSTALLED USED AND WITHOUT LUBE.					1	L	7	1 	3O				2A13    					 
1997022500001	19970225	00001	CE  	1997	2	25	97ZZZX624        	1	19970120	G	5540	57330142	BRACKET         		573300071   	CESSNA	404   	404CESSNA   	2075901	CE  										RUD BAL WT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	409EX	12346				4040436				ON PRE-FLIGHT INSPECTION, PILOT NOTICED 'CLUNKING' SOUND IN RUDDER WHEN IT WAS MOVED.  INSPECTION OF RUDDER FOUND BALANC	E WEIGHT SEPARATED FROM MOUNTING BRACKET WHICH WAS CRACKED OUT AT BOTH NUTPLATES WHICH ATTACH WEIGHT.  REPAIRED MOUNTING	 BRACKET.  HIGH AIRCRAFT TIME.  WEAK DESIGN,  MOUNT BRACKET IS ONLY .040 INCH 2024-T3 WITH TWO .25 INCH NUTPLATES RIVETE	D TO IT TO HOLD APPROXIMATELY 8 POUNDS OF LEAD WEIGHT.  NOTE:  THIS BRACKET IS ACCESSIBLE FOR INSPECTION BY REMOVING SCR	EWS FOR FAIRINGS AND BALANCE WEIGHT WITHOUT REMOVING RUDDER FROM AIRCRAFT.		1	L	7	2 	3O				A25CE   					 
1997021300071	19970213	00071	CE  	1997	2	13	97ZZZX625        	1	19970114	G	5711	05230202	SPAR CAP        			CESSNA	175   	175         	2072502	CE  										RT WING	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7464M					55764				AFTER REMOVING FUEL TANK COVER PANELS TO REPLACE SOME GASKETS DURING AN ANNUAL INSP, INTERGRANULAR CORROSION WAS FOUND O	N SPAR CAP FWD OF THE RT TANK.  WING LEADING EDGE WAS REMOVED FOR FURTHER INSP AND THE SAME TYPE OF CORROSION WAS FOUND 	ALONG THE FULL LENGTH OF SPAR CAP.  THE SPAR CAP REQUIRED REPLACEMENT.  THIS CORROSION COULD NOT BE SEEN UNTIL FUEL TANK	 COVER PANELS WERE REMOVED.  LT WING SPAR CAP DID NOT APPEAR TO HAVE ANY CORROSION.  RECOMMEND PULLING FUEL TANK COVER P	ANELS EVERY 5 YRS TO INSP FOR CORROSION.		1	H	7	1 	3O			NT	3A17    					 
1997021300072	19970213	00072	SO  	1997	2	13	97ZZZX626        	1	19970110	G	2820	9515327	FUEL LINE       			PIPER 	PA34  	PA34200     	7103405	SO  										LT WING	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	57368					347450054				MAIN FUEL LINE, PN 95153-27 (LEFT) AND DASH 28 (RIGHT) CHAFED 90 PERCENT THROUGH BY CABIN HEAT DUCT, PN 63633-91, IN AFT	 NACELLE.  INSPECTION OF THIS AREA REQUIRES REMOVING AFT NACELLE TOP PANEL, STANDING ON WING, AND USING MIRROR TO EXAMIN	E AFT OUTBOARD CORNER WHERE MAIN FUEL LINE PASSES UNDER CABIN HEAT DUCT.  SUBMITTER SUGGESTS EVERY SENECA I AFTER 1972 W	ILL HAVE THIS PROBLEM.  SOLUTION:  BEND FUEL LINE AWAY FROM DUCT, INSPECT AND PROTECT.			1	L	7	2 	3O				A7SO    					 
1997021300073	19970213	00073	SO  	1997	2	13	97ZZZX627        	1	19970110	G	2820	9515328	FUEL LINE       			PIPER 	PA34  	PA34200     	7103405	SO  										RT WING	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	57368					347450054				MAIN FUEL LINE, PN 95153-27 (LEFT) AND DASH 28 (RIGHT) CHAFED 90 PERCENT THROUGH BY CABIN HEAT DUCT, PN 63633-91, IN AFT	 NACELLE.  INSPECTION OF THIS AREA REQUIRES REMOVING AFT NACELLE TOP PANEL, STANDING ON WING, AND USING MIRROR TO EXAMIN	E AFT OUTBOARD CORNER WHERE MAIN FUEL LINE PASSES UNDER CABIN HEAT DUCT.  SUBMITTER SUGGESTS EVERY SENECA I AFTER 1972 W	ILL HAVE THIS PROBLEM.  SOLUTION:  BEND FUEL LINE AWAY FROM DUCT, INSPECT AND PROTECT.			1	L	7	2 	3O				A7SO    					 
1997021300074	19970213	00074	CE  	1997	2	13	97ZZZX628        	1	19970128	G	7120	08515543	MOUNT BRACKET   			CESSNA	310   	310Q        	2074242	CE  										LT ENG LT FWD	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	1240G					310Q1091				INSP FOUND LT ENG, FWD LT MOUNT, AFT BRACKET CRACKED.						1	L	7	2 	3O				3A10    					 
1997021300075	19970213	00075	SO  	1997	2	13	97ZZZX629        	2	19970101	G	8550	631056	COVER ASSY      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					OIL PUMP	LEAKING         	B			FBLR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17	3093W	520  	520  			TH403	267601H			PILOT COMPLAINING OF OIL LEAK.  FOUND OIL PUMP LEAKING FROM CASTING SCAR IN UNIT.						1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997021300076	19970213	00076	CE  	1997	2	13	97ZZZX630        	1	19970127	G	2720		TRIM ARM        			CESSNA	310   	T310R       	2074246	CE  										ELEV TRIM IND	MISINDEXED      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	4949A	4171 				310R1505				ELEVATOR TRIM INDICATOR ARM FREQUENTLY BECOMES MISINDEXED GIVING ERRONEOUS TRIM SETTING INDICATIONS.  A PILOT'S KNEE, RE	STING AGAINST THE TRIM WHEEL, CAN DISPLACE THE WHEEL ENOUGH TO CAUSE THE TRIM ARM TO MOVE OUT OF THE SPIRAL GROOVE AND I	NTO ANOTHER GROOVE.  AN IDENTICAL PROBLEM OCCURS IN THE OTHER COMPANY OWNED 310R.  THE TRIM WHEEL AND ATTACHING PARTS AR	E TIGHT AND IN GOOD CONDITION.  APPROVED PREVENTATIVE ACTIONS ARE NOT APPARENT.			1	L	7	2 	3O				3A10    					 
1997021300077	19970213	00077	SO  	1997	2	13	97ZZZX631        	2	19970101	G	8530	PE92EL	ROCKER          			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					NR 2 CYL EXH	BROKE           	B			EVGR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	33	2FOR	150  				U20606295	283128R			THE NR 2 EXHAUST 'ROLLER ROCKER' BROKE MID-WAY BETWEEN THE PUSH ROD SOCKET AND THE ROCKER ARM SHAFT.  STC 8594SW.						1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1997021300078	19970213	00078	CE  	1997	2	13	97ZZZX632        	1	19970101	G	2842	385BN812	SENSOR          			CESSNA	206   	U206F       	2073333	CE  										TIP TANK QTY	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	08	2FOR					U20602415				THE FUEL QTY SENDER IN THE TIP TANK (FLINT) CORRODED SEVERELY DUE TO THE TANK BEING LEFT EMPTY MOST OF THE TIME.  CONDEN	SATION AND RUST TOTALLY DESTROYED THE SENDER.  RECOMMEND KEEPING SOME FUEL IN THE TIP TANKS AT ALL TIMES.  STC SA1335SO.					1	H	7	1 	3O				A4CE    					 
1997021300079	19970213	00079	CE  	1997	2	13	97ZZZX633        	1	19970101	G	3231	0024100381	SHAFT ASSY      			BEECH 	58    	58          	1152740	CE  										NLG DOORS	BROKEN          	B			HBKR	A	O			UNSCHED LANDING         	OTHER                   			P			NO WARNING INDICATION     			CL	CLIMB          	1			SW	11	3711Y					TH828				PILOT REPORTED THAT NOSE GEAR DOORS FAILED TO CLOSE WHEN THE GEAR WAS RETRACTED.  INFORMED THAT THE DOORS WERE OPEN BY C	ONTROL TOWER PERSONNEL; PILOT HAD NO COCKPIT INDICATION THAT THE GEAR WAS FUNCTIONING ABNORMALLY.  THE PILOT MANUALLY EX	TENDED THE GEAR AND LANDED WITHOUT DAMAGE.  UPON INSPECTION, PART OF THE NOSE GEAR DOOR RETRACTION MECHANISM WAS FOUND B	ROKEN.  SPECIFICALLY, THE SLOTTED TAB NEAR THE CENTER OF THE NOSE GEAR RETRACTION PIVOT SHAFT HAD BROKEN, LOSING ITS LOW	ER PORTION.  SINCE THIS PORTION OF THE TAB TAKES ALL THE FORCE OF GEAR DOOR CLOSURE, THE GEAR DOORS DID NOT CLOSE.  THIS	 TAB IS RATHER FLIMSY, AND OFTEN FAILS WITHOUT ANY SIGNS OF IMPENDING FAILURE.	1	L	7	2 	3O				3A16    					 
1997021300081	19970213	00081	SO  	1997	2	13	97ZZZX635        	1	19970109	G	2140		CONNECTOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER BLOWER	BURNED          	D	L	A		K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	99	3581C	6924 				318052091				DURING AN INSPECTION, MAINTENANCE FOUND A MOLEX CONNECTOR LOCATED JUST FORWARD OF THE CIRCUIT BREAKER PANEL, BEHIND THE 	SIDE PANEL ON THE PILOT'S SIDE BURNED AND THE WIRE HEATED APPROX .50 INCH OUT OF THE CONNECTOR. THIS MOLEX CONNECTOR NR 	E303 PER THE NAVAJO CHIEFTAIN SERVICE MANUAL WIRING DIAGRAM.  THE WIRE THAT IS OVERHEATING FOUND TO BE FOR THE HEATER BL	OWER, FROM A 20-AMP CIRCUIT BREAKER.			1	L	7	2 	3O				A20SO   					 
1997021300464	19970213	00464	CE  	1997	2	13	97ZZZX678        	1	19970116	G	3234		SELECTOR VALVE  			CESSNA	441   	441         	2076020	CE  										NLG	MISWIRED        	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	555JJ	5777 				4410004				THE NOSE GEAR RETRACTED DURING ENGINE START WITH THE GEAR SELECTOR DOWN AND THREE GREEN GEAR IND LIGHTS.  INVESTIGATION 	FOUND THE LEFT DOWNLOCK SWITCH FAILED IN THE CONTROL CIRCUIT APPLYING POWER TO THE LOADING VALVE AND HYD SLECTOR VALVE. 	 PIN B AND D IN CONNECTOR P52 WERE FOUND REVERSED.  SL PJ81-15 WAS C/W.				1	L	7	2 	3T			RT	A28CE   					 
1997021300466	19970213	00466	SO  	1997	2	13	97ZZZX680        	1	19970123	G	3250	452334	ROD END         	PARKERHANFIN	456015      	PIPER 	PA28  	PA28181     	7102807	SO  										NLG STEERING	FAILED          	B			T6UR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	3023M					287890285				NOSE STEERING SHIMMY DAMPER ROD END BROKEN AT THREAD SHAFT.						1	L	7	1 	3O				2A13    					 
1997021300467	19970213	00467	EA  	1997	2	13	97ZZZX681        	2	19970114	G	7414	1068256011	MAGNETO         			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					MAG HOLD DOWN	BASE WORN       	B			T6UR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	419CC				C079508G	287911268	SNL21652			HOLD DOWN BASE FOR MAGNETO WAS WORN.  CAUSED HOLD DOWN CLAMP TO BE INEFFECTIVE.						1	L	7	1 	3O	3	O		2A13    	E295				 
1997021300469	19970213	00469	CE  	1997	2	13	97ZZZX683        	1	19970117	G	8097	J12A4	WIRE            			BEECH 	58    	58          	1152740	CE  										RT ENG STARTER	SHORTED         	B		A	MZ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	1064C	228  				TH1764				THE RIGHT ENGINE STARTER CABLE (WIRE) NR J12A4) WAS FOUND TO HAVE SHORTED TO THE ENGINE MOUNT.  THIS CAUSED DAMAGE TO TH	E ENGINE MOUNT P/N 96-910010-85 WHICH IN TURN WAS REPLACED WITH A NEW MOUNT.  A NEW STARTER WIRE WAS INSTALLED AND ROUTE	D TO PREVENT ANY FUTURE CHAFING.  SUBMITTER STATED THIS IS NOW THE THIRD INCIDENT OF THIS TYPE ON THE SAME MODEL AIRCRAF	T WITH LOW TIME.  RAYTHEON AIRCRAFT WAS NOTIFIED.			1	L	7	2 	3O			 	3A16    					 
1997021300470	19970213	00470	EA  	1997	2	13	97ZZZX684        	2	19970128	G	7414	103825881	COIL            		1068291018  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT MAG	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	25	4108P	299  			A1459506	318352014	RL12768A			PILOT REPORTED LEFT HAND MAGNETO FAILED.  REMOVED MAG, FOUND BOTH LEFT HAND S/N A-145-9506 AND RIGHT HAND S/N M-145-9505	 IGNITION COILS P/N 10-382588-1 CRACKED.  CRACKS ORIGINATE ON BOTH COILS AT IRON CORE AND EXTEND OUTWARD.  ON LEFT HAND 	COIL, CRACK ALSO PRESENT AT SURFACE FACING ROTATING MAGNET.  SUBMITTED MAGNETO TO MFG FOR EVALUATION FOR POSSIBLE DEFECT	S IN COILS PRODUCED DURING THIS PERIOD OF TIME.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997021300471	19970213	00471	EA  	1997	2	13	97ZZZX685        	2	19970128	G	7414	103825881	COIL            		1068291018  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT MAG	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	25	4108P	299  			M1459505	318352014	RL12768A			PILOT REPORTED LEFT HAND MAGNETO FAILED.  REMOVED MAG, FOUND BOTH LEFT HAND S/N A-145-9506 AND RIGHT HAND S/N M-145-9505	 IGNITION COILS P/N 10-382588-1 CRACKED.  CRACKS ORIGINATE ON BOTH COILS AT IRON CORE AND EXTEND OUTWARD.  ON LEFT HAND 	COIL, CRACK ALSO PRESENT AT SURFACE FACING ROTATING MAGNET.  SUBMITTED MAGNETO TO MFG FOR EVALUATION FOR POSSIBLE DEFECT	S IN COILS PRODUCED DURING THIS PERIOD OF TIME.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997022000125	19970220	00125	CE  	1997	2	20	97ZZZX752        	1	19970128	G	5320	5043014323	SUPPORT         			BEECH 	100   	A100        	1152915	CE  										AIR STAIR DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	115DT	11300				B212				AFTER READING A REPORT IN THE JAN ISSUE ABOUT AIR STAIR STRUCTURE CRACKS, EXAMINED OUR (ACFT DOOR).  FOUND THAT THE AIR 	STAIR DAMPNER UPPER ATTACH POINT WAS FLEXING DURING TRANSITION.  FURTHER INVESTIGATION REVEALED THAT THE STRINGERS THAT 	THE ATTACH POINT IS SECURED TO HAD BROKEN AWAY FROM THE FUSELAGE.  IT IS SUSPECTED THAT THE STRUCTURE HAD WORK-HARDENED 	AND BECAME BRITTLE.  THE UPPER SUPPORT WHICH WAS SLIGHTLY BENT AND TWISTED IS ATTACHED WITH SIX 10-32 SCREWS, OF THESE, 	FIVE WERE BENT 7 DEGREES-20 DEGREES AND ONE WAS SHEARED.  THE FUSELAGE NEEDS REINFORCED IN THIS AREA.		1	L	7	2 	3T				A14CE   					 
1997022000126	19970220	00126		1997	2	20	97ZZZX753        	4	19970204	G	2397		WIRE            			SLNSBY	T67   	T67M260     	8323006	EU  										INTERPHONE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3045S					2142				WIRE BUNDLE CHAFING ON INSTRUMENT MOUNT BRACKET BEHIND RADIOS.  DISCREPANCY IS THE INTERCOM DOES NOT TRANSMIT CLEARLY. C	UTS IN AND OUT.  INSPECTED, FOUND A WIRE CHAFE THROUGH DUE TO THE WIRE BUNDLE ON THE RADIO MOUNT BRACKET.  RECOMMEND RE-	ROUTING OF THE WIRE BUNDLE AND INSTALL A CHAFE PAD.				1	L	7	1 	3O			NT	A73EU   					 
1997022000128	19970220	00128	SO  	1997	2	20	97ZZZX755        	1	19970125	G	7130	6711961	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  										ENG	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	531PU	4193 			T2124	2837039				ENGINE MOUNT REMOVED DURING ENGINE CHANGE DUE TO WEAR IN LOWER TUBES CAUSED BY LOWER COWLING CLAMPS.  AFTER TUBES REPLAC	ED BY APPROVED MOUNT REPAIR SERVICE, FOUND THAT DOWNLOCK BLOCK WAS INCORRECTLY WELDED ON RESULTING IN NOSE GEAR DRAG BRA	CE NOT BEING OVER CENTER AND 'LOCKED'.  NOTE:  LANDING GEAR WORKED NORMALLY AND INDICATORS WERE CORRECT.  TOOK 3 ADDITIO	NAL REPAIR ATTEMPTS BEFORE CORRECT AND SERVICEABLE.			1	L	7	1 	3O				2A13    					 
1997022000129	19970220	00129	SO  	1997	2	20	97ZZZX756        	1	19970206	G	2432	G35	BATTERY         	GILLBATT    		PIPER 	PA34  	PA34200T    	7103406	SO  										NOSE COMPT	BURNED          	D	L	A		O				OTHER                   				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		CR	CRUISE         	1			SO	13	74FF	214  				347570300				PILOT REPORTED A SMELL OF AND TRACES OF SMOKE IN CABIN THAT WAS BRIEF.  NO CAUSES COULD BE DETERMINED IN-FLIGHT.  ALTS W	ERE CHARGING AND ALL SYSTEMS SEEMED NORMAL.  AFTER LANDING, PILOT NOTICED PAINT BUBBLED ON TOP OF NOSE CONE AND LOOKED I	N BAGGAGE COMP.  SOOT COVERED THE ENTIRE AREA, AND NOSE WHEEL/BATTERY COVER WAS SEVERELY BURNED.  WHEN COVER WAS REMOVED	, BATTERY WAS EXPOSED AND APPEARED TO HAVE MELTED DOWN AND BURNED AWAY.			1	L	7	2 	3O				A7SO    					 
1997022000130	19970220	00130	SO  	1997	2	20	97ZZZX757        	1	19970122	G	5210	46624003	DOUBLER         			PIPER 	PA31T 	PA31T       	7103124	SO  										DOOR SUPPORT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8CF	3603 				31T8020062				DURING EVENT 1 AND 2 INSPECTION OF ACFT, FOUND MULTIPLE CRACKS IN DOUBLER BEHIND END FRAME OF CABIN DOOR.  (HINGE END OF	 DOOR).  SUSPECT STRESS FATIGUE DUE TO HINGE AND HINGE PIN WEAR, ALLOWING DOOR TO FLEX DURING BOARDING OPERATIONS, ETC. 	 DISASSEMBLED  HINGE END OF CABIN DOOR; INSTALLED NEW DOUBLER AND HINGE ASSY IAW PIPER MAINTENANCE INSTRUCTIONS.				1	L	7	2 	3T				A8EA    					 
1997022000132	19970220	00132	NE  	1997	2	20	97ZZZX759        	1	19970117	G	2140	BWT1367611	ELBOW           			SKRSKY	S76   	S76C        	8143008	NE  										BAG COMPT	RUPTURED        	B			KS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	702H	126  				760460				CUSTOMER COMPLAINED OF HOT AIR EXITING BAGGAGE COMPARTMENT WHEN UNLOADING BAGGAGE IN COLD WEATHER.  UPON REMOVING CENTER	 OVERHEAD BAGGAGE SHROUD, FOUND C-4 HEATER DUCT ELBOW P/N BWT13671-1 RUPTURED ALLOWING HOT AIR FROM HEATER TO ENTER BAGG	AGE COMPARTMENT.  REPLACED ELBOW WITH NEW PART.  FORWARDED OLD PART TO MANUFACTURER FOR EVALUATION.				1	G	7	2 	3U			NC	H1NE    					 
1997022000133	19970220	00133	NM  	1997	2	20	97ZZZX760        	1	19970123	G	2710	AN3208	ROD ATTACH      			BOEING	727   	72723       	1384004	NM  										LT OUTB OIL	NUT MISSING     	B		A	I44R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19	727WF					20045				DURING C-CHECK INSPECTION OF THE LEFT OUTBOARD AILERON CONTROL ROD TO AILERON, INSPECTION REVEALED THE ATTACH BOLT'S NUT	, WASHER, AND COTTER PIN WERE NOT INSTALLED (MISSING). THE BOLT MIGRATED APPROX  .125 INCH OUTBOARD.  SUSPECT DURING AIL	ERON INSTALLATION, THE MECHANIC FAILED TO INSTALL THE NUT, WASHER, AND COTTER PIN, AND THE HINGE COVER WAS INSTALLED WHI	CH PREVENTS A VISUAL CHECK OF THE INSTALLATION.			2	L	7	3 	4F				A3WE    					 
1997022000134	19970220	00134	NM  	1997	2	20	97ZZZX761        	1	19970106	G	5330		SKIN            			BOEING	727   	727287      	1384020	NM  										FS 300	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	914PG					22603				DURING C-CHECK INSPECTION, DEEP GOUGES WERE NOTED IN AIRCRAFT SKIN AT FS 300 FROM S17R TO S18R.						2	L	7	3 	4F			RT	A3WE    					 
1997022000135	19970220	00135	NM  	1997	2	20	97ZZZX762        	1	19970106	G	5330		SKIN            			BOEING	727   	727287      	1384020	NM  										FS 355 S21R	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	914PG					22603				DURING C-CHECK INSPECTION, A DEEP GOUGE AND CRACK IN THE AIRCRAFT SKIN AT STA 355 JUST BELOW S21R.						2	L	7	3 	4F			RT	A3WE    					 
1997022000136	19970220	00136	NM  	1997	2	20	97ZZZX763        	1	19970106	G	5330		SKIN            			BOEING	727   	727287      	1384020	NM  										FS 370-375	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	914PG					22603				DURING INSPECTION OF EPCP CARD C53-100-01, PT 4, LEVEL 2, CORROSION WAS NOTED UNDER SKIN, RT FWD FS 370 TO 375, JUST BEL	OW S17R.					2	L	7	3 	4F			RT	A3WE    					 
1997022000138	19970220	00138	EU  	1997	2	20	97ZZZX765        	1	19970124	G	2422	ASH6641PF	INVERTER        	LELAND      		BRAERO	DH125 	BAE125800A  	1500285	EU  										NR 1	FAILED          	D	L	A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	15					EJ838M					DATE OF INCIDENT UNKNOWN. USER REPORTED THAT A/C HAD BEEN FLYING IN HEAVY RAIN FOR APPROX. 45 MINUTES (NOV. 95).  DURING	 FINAL APPROACH, THE NR 1 MAIN INVERTER FAIL ANNUNCIATOR ILLUMINATED.  CREW CONTINUED APPROACH AND HAD NORMAL ENDING.  W	HILE TAXIING, CREW ATTEMPTED TO RESET NR 1 INVERTER.  THIS RESULTED IN SEVERAL CIRCUIT BREAKERS TRIPPING, AND NUMEROUS A	VIONICS FAIL FLAGS.  AFTER RESET, VARIOUS SYSTEMS REMAINED INOPERATIVE.  BOTH INVERTERS AND NUMEROUS OTHER COMPONENTS WE	RE REPLACED.  GROUND AND IN-FLIGHT TEST OF AFFECTED SYSTEMS WERE FOUND SATISFACTORY AFTER REPAIRS.		2	L	7	2 	4F			RT	A3EU    					 
1997022000139	19970220	00139	EU  	1997	2	20	97ZZZX766        	2	19970206	G	7250		DIFFUSER CASE   			HWKSLY	DH125 	DH1253ARA   	423013P	EU  	RROYCE	VIPER 	VIPER522    	54552	EU  					RT ENG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	125HS	5421 				NA701	522008			DIFFUSER CASE (RT ENG) CRACKED AT 11:00 (A.L.F.) POSITION.  LENGTH OF CRACK IS 4.1250 INCHES.						2	L	7	2 	4J	4	J		A3EU    	E3EU				 
1997022000140	19970220	00140		1997	2	20	97ZZZX767        	4	19970129	G	2562	4520130	BATTERY PACK    	ARTEX       	1104002     	BEECH 	MU300 	400A        	1155402	CE  										ELT	LEAKING         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3196N	242  			59679	RK96				DURING SCHEDULED BATTERY INSPECTION, FOUND 2 BATTERY CELLS LEAKING.  ELT WAS REPLACED 242.2 HOURS PREVIOUS FOR SAME PROB	LEM.  THIS IS THE 6TH ELT TO BE REPLACED BY THIS OPERATOR ON A 2 AIRCRAFT FLEET.  TWO PREVIOUS MALFUNCTION/DEFECT REPORT	S LISTED CRACKED ELT CASES DUE TO SEVERE LEAKAGE AND RUPTURE OF CASE.				2	H	7	2 	4F			RT	A16SW   					 
1997022000141	19970220	00141	CE  	1997	2	20	97ZZZX768        	1	19970127	G	2121	45053	BLOWER MOTOR    			CESSNA	650   	650         	2076802	CE  										AIR DIST	SEIZED          	D		A		K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	03	600JD	1093 			0200	6500236				BLOWER MOTOR SEIZED CAUSING EXCESSIVE CURRENT DRAW.  THE 15-AMP CIRCUIT BREAKER PROTECTING THE CIRCUIT FAILED TO OPEN. T	HIS CAUSED THE WIRING FOR THE BLOWER MOTOR TO GET HOT AND EMIT SMOKE AND FOUL ODOR.  THE COCKPIT AUX HEATER THEN CIRCULA	TED THE SMOKE INTO THE COCKPIT.  THE BLOWER MOTOR IS RATED AT ABOUT 8 AMPS.  THE CIRCUIT BREAKER SIZE SHOULD BE CLOSER T	O THE RATE CURRENT DRAW OF THE MOTOR.			2	L	7	2 	4F				A9NM    					 
1997022000146	19970220	00146	WP  	1997	2	20	97ZZZX773        	1	19970130	G	3246	2601483	BOLT            		2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILURE         	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B1087					INSP FOUND WHEEL BOLTS WITH FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  TWO REPORTS THIS S/N.  SUBMI	TTER STATES USE SNUG ANGLE TORQUE METHOD.					2	L	7	2 	4F			RT	A6WE    					 
1997022000147	19970220	00147	WP  	1997	2	20	97ZZZX774        	1	19970130	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILURE         	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B2393					INSP FOUND WHEEL BOLT WITH FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER STATES USE SNUG ANG	LE TORQUE METHOD.					2	L	7	2 	4F			RT	A6WE    					 
1997022000148	19970220	00148	CE  	1997	2	20	97ZZZX775        	1	19970129	G	2435		BEARING         	LEARSIEGLER 	23080002    	RKWELL	NA265 	NA26565     	7630107	CE  										START/GEN	FAILED          	D				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	13	265A	6225 	648  		1599	46547				SABRELINER RT ENGINE EXPERIENCED A VIBRATION.  TURNING GENERATOR OFF SILENCED THE VIBRATION.  WHEN TURNING BACK ON, VIBR	ATION STARTED AGAIN.  GENERATOR LIGHT DID NOT COME ON.  LANDED ACFT. SAFELY, CHANGED STARTER/GEN, PROBLEM WENT AWAY.					2	L	7	2 	4J				A2WE    					 
1997022000153	19970220	00153	CE  	1997	2	20	97ZZZX780        	1	19970101	G	3520	727725	BREAKER         			BEECH 	200   	200BEECH    	1152920	CE  										OXY BARO SYS	FAILED          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	6500 				BB832				WHILE DEMONSTRATING THE FUNCTION OF THE CABIN BAROMETRIC SWITCH TO A TRAINEE, IT WAS FOUND THAT WHEN POWER WAS APPLIED T	O THE SOLENOID ON THE BAROMETRIC SYSTEM, THE OXYGEN VALVE DID NOT OPEN AND DROP THE MASKS.  TROUBLESHOOTING FOUND A VOLT	AGE DROP AT THE CIRCUIT BREAKER.  WHEN THE C/B WAS REPLACED, THE SYSTEM WORKED AS ADVERTISED.  THERE IS NO FUNCTIONAL TE	ST OF THE ELECTRICAL PORTION OF THE OXYGEN AUTO DEPLOY SYSTEM, BUT IT MIGHT BE A GOOD IDEA TO PERFORM IT WHEN THE BARO V	ALVE IS OVERHAULED IN 24 MOS.		1	L	7	2 	4T				A24CE   					 
1997022000156	19970220	00156	EA  	1997	2	20	97ZZZX783        	1	19970129	G	7830	22850785261	SAM PANEL       			CNDAIR	CL600 	CL6002B16   	1900305	EA  										THRUST REV	TORN OFF        	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	900CL	2545 				5122				DURING A POST FLIGHT INSP OF THE LEFT ENGINE, THE 6 O'CLOCK SAM PANEL WAS FOUND MISSING.  THE PANEL WAS TORN OFF AFTER C	RACKS IN THE RETAINING BRACKETS CAUSED THEM TO FAIL.  THE PANEL WAS RECOVERED AT THE END OF THE RUNWAY.  REPAIRED BY CAN	ADAIR SB 601-1084 AND FITTED A NEW SAM PANEL.				2	L	7	2 	4F			RT	A21EA   					 
1997022000157	19970220	00157	NM  	1997	2	20	97ZZZX784        	1	19970131	G	3244	H40X14520	TIRE            			BOEING	737   	7373T0      	1384582	NM  										WHEEL	LINER SEPARATION	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05										INSP FOUND PARTIAL TIRE LINER SEPARATION.  CAUSE UNDER INVESTIGATION BY THE TIRE MANUFACCTUR5ER (GOODYEAR).						2	L	7	2 	4F			RT	A16WE   					 
1997022000472	19970220	00472	SO  	1997	2	20	97ZZZX785        	2	19970203	G	8550	631056A1	COVER ASSY      			BEECH 	58    	58TC        	1152746	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					OIL PUMP	LEAK            	D				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			WP	25	6669X	90   				TK108	518929			THE COVER TO OIL PUMP IS SEALED WITH GASKET CEMENT (FORM-A-GASKET PERMATEX) AND A NR 50 SILK THREAD.  THE COVER WAS NOT 	PROPERLY INSTALLED AND TORQUED CAUSING IT TO LEAK OIL WHEN THE SEAL FAILED AFTER A TWO HOUR FLIGHT HAD LEAKED 3 QTS OIL.					1	L	7	2 	3O	3	O		A23CE   	E8CE				 
1997022000476	19970220	00476	GL  	1997	2	20	97ZZZX789        	3	19970129	G	6114		HUB             			BEECH 	35    	N35         	1151528	CE  						MCAULY	2A36C	2A36C23     	GL  	PROP FLANGE	FAILED          	G	L	A		O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			WP	07	7HB					D6750		756778		DURING TAKEOFF WHILE ROTATING FOR LIFT-OFF, THE PROP HUB FAILED, THE PILOT LOST CONTROL, THE ACFT VEERED OFF THE RUNWAY,	 FLIPPED OVER AND WAS DESTROYED.  THE THREE OCCUPANTS RECEIVED MINOR INJURIES.  THE PROP FAILED AT THE HUB. THE PROP INS	TANTANEOUSLY SEPARATED FROM THE AIRCRAFT.  AN AUDIT OF THE ACFT RECORDS WAS ACCOMPLISHED TO DETERMINE IF PREVIOUS DAMAGE	 HAD OCCURRED, AND TO DETERMINE C/W FAR.  WHILE RESEARCHING AD RECORDS, IT WAS FOUND THAT AD 89-26-08 HAD NOT BEEN C/W. 	 IT WAS ALSO DETERMINED THAT AD 89-26-08 DID NOT APPLY ACCORDING TO THE APPLICABILITY SECTION OF THE AD.  THE APPLICABIL	ITY SECTION STATES THAT THE AD APPLIES TO MCCAULEY MDL 2A36C23/84B-0, THE FAILED PROP IS A MCCAULY MDL 2A36C23 - P - E.	1	L	7	1 	3O				3A15    		5	C	P880	 
1997022000477	19970220	00477	SO  	1997	2	20	97ZZZX790        	2	19970120	G	7414		DISTRIBUTOR BLK 	SLICK       	4301        	CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512F      	17008	SO  					LT MAG	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1859V	54   			96060509	14038	28583712			TROUBLESHOT IGNITION SYSTEM.  FOUND LEFT MAGNETO TO BE PROBLEM.  DISASSEMBLED MAGNETO AND FOUND ROTOR GEAR RUBBING ON DI	STRIBUTOR BLOCK HOUSING.  DISTRIBUTOR BLOCK HOUSING WAS WARPED.  ALSO FOUND BUSHING IN DISTRIBUTOR BLOCK HOUSING WAS WOR	N THROUGH ON SIDE TOWARDS CONDENSER.  WEAR HAD PROGRESSED INTO PLASTIC SURROUNDING BUSHING.  SEVERE ARCING AND CARBON TR	ACKING WAS PRESENT IN HOUSING.  FOUND THAT THE ROTOR GEAR WAS NOT PRESSED INTO PLACE AS IS REQUIRED IN SLICK SM.  SUBMIT	TER STATES THE SEALING MARK IS PUT ON MAGNETO HOUSING SCREW AT FACTORY HAD NOT BEEN BROKEN PRIOR TO MECHANIC DOING SO FO	R INSPECTION.	1	H	7	1 	3O	3	O	NC	A768    	E233				 
1997022000480	19970220	00480	CE  	1997	2	20	97ZZZX793        	1	19970131	G	3211	071349520	BRACKET         			CESSNA	180   	180         	2072602	CE  										MLG	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2937A	3092 				30173				DURING INSPECTION OF THE LANDING GEAR, THE OUTBOARD LT LANDING GEAR BRACKET WAS FOUND WITH HEAVY INTERGRANULAR CORROSION	 (I/G) TO THE LOWER FITTING.  SUSPECT CAUSE IS IMPROPER HEAT TREATING DURING MANUFACTURE.  SUBMITTER STATES THIS IS THE 	FOURTH SUCH FITTING FOUND WITH I/G CORROSION.  RECOMMEND CLOSE INSPECTION OF LANDING GEAR BRACKETS DURING INSPECTION OF 	OLDER AIRCRAFT.			1	H	7	1 	3O			NC	5A6     					 
1997022000483	19970220	00483	CE  	1997	2	20	97ZZZX796        	1	19970130	G	2434	DOFF10300B	ALTERNATOR      	FORD        		CESSNA	210   	210L        	2073448	CE  										DC SYS	FAILED          	G				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	03	50DB	6680 				21060107				FORD ALTERNATOR FAILED IN-FLIGHT.  A/C RAN OFF A/C BATTERY.  MAINTENANCE INSTALLED OVERHAULED ALTERNATOR AND A/C WAS RET	URNED TO SERVICE.					1	H	7	1 	3O				3A21    					 
1997022000484	19970220	00484	CE  	1997	2	20	97ZZZX797        	1	19970127	G	2912	MS288786	PACKING         		AN62342     	CESSNA	414   	414A        	2075907	CE  										HYD FILTER	CUT             	H				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		AP	APPROACH       	1			WP	13	5614C					414A0203				PILOT REPORTED THAT BOTH LEFT AND RIGHT HYDRAULIC PRESSURE CAUTION LIGHTS WERE ILLUMINATED.  LANDING GEAR WOULD NOT EXTE	ND.  LANDING GEAR WAS EXTENDED USING THE EMERGENCY EXTENSION PROCEDURE.  AIRPLANE WAS JACKED AND THE LANDING GEAR OPERAT	IONAL CHECK WAS PERFORMED.  FLUID WAS DISCOVERED LEAKING FROM THE RIGHT HYDRAULIC FILTER P/N AN6234-2.  IT WAS FURTHER D	ISCOVERED THAT THE PACKING P/N MS28778-6 USED TO PACK THE ELBOW P/N 833-6D AND HYDRAULIC FILTER ASSEMBLY P/N AN6234-2 HA	D RUPTURED.  PACKING REPLACED.  EMERGENCY BLOW DOWN BOTTLE SERVICED AND LANDING GEAR OPERATIONAL CHECK COMPLETED IAW CES	SNA SM.  AIRPLANE RETURNED TO SERVICE.	1	L	7	2 	3O				A7CE    					 
1997022000485	19970220	00485	EA  	1997	2	20	97ZZZX798        	2	19970128	G	8530	SL10301A1	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 3 CYL EXH VLV	FAILED          	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			SO	13	6599B	1432 				15283958	L2163215			EXHAUST VALVE IN CYLINDER NR 3 BROKE AT STEM, INGESTING INTO CYLINDER, CREATING A HOLE IN THE PISTON.  PIECES OF VALVE A	ND PISTON ENTERED ENGINE, CONTAMINATING THE OIL.  AN OFF AIRPORT LANDING WAS MADE WITHOUT INCIDENT.  AFTER TEAR DOWN, TH	E CONNECTING ROD WAS FOUND BENT AND CRACKED.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997022000486	19970220	00486	SO  	1997	2	20	97ZZZX799        	1	19970202	G	2710	2094304	CONTROL CABLE   			PIPER 	PA24  	PA24250     	7102404	SO  										AILERON	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6862P					241998				AILERON CONTROL CABLES WHERE THEY PASS THROUGH WHEELWELLS APPEARED RUSTY, BUT NO BROKEN STRANDS.  WHEN REMOVED TO INSPEC	T PER AC 43-13-1A, CHAPTER 4, PARA 198, AND FIGURE 4.14, MANY BROKEN STRANDS APPEARED.					1	L	7	1 	3O			 	1A15    					 
1997022000487	19970220	00487	SO  	1997	2	20	97ZZZX800        	1	19970202	G	2710	2094302	CONTROL CABLE   			PIPER 	PA24  	PA24250     	7102404	SO  										AILERON	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6862P					241998				AILERON CONTROL CABLES WHERE THEY PASS THROUGH WHEELWELLS APPEARED RUSTY, BUT NO BROKEN STRANDS.  WHEN REMOVED TO INSPEC	T PER AC 43-13-1A, CHAPTER 4, PARA 198, AND FIGURE 4.14, MANY BROKEN STRANDS APPEARED.					1	L	7	1 	3O			 	1A15    					 
1997022000488	19970220	00488	SO  	1997	2	20	97ZZZX801        	1	19970202	G	2710	1430006	CONTROL CABLE   			PIPER 	PA24  	PA24250     	7102404	SO  										AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6862P					241998				AILERON CONTROL CABLES WHERE THEY PASS THROUGH WHEELWELLS APPEARED RUSTY, BUT NO BROKEN STRANDS.  WHEN REMOVED TO INSPEC	T PER AC 43-13-1A, CHAPTER 4, PARA 198, AND FIGURE 4.14, MANY BROKEN STRANDS APPEARED.					1	L	7	1 	3O			 	1A15    					 
1997022000490	19970220	00490	CE  	1997	2	20	97ZZZX803        	1	19970202	G	5312	07126161	BULKHEAD        			CESSNA	182   	182M        	2072728	CE  										AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	71766	2172 				59746				AFT BULKHEAD CRACKED BETWEEN RUDDER CABLE CUTOUT AND THE BULKHEAD FLANGE.  INSTALLED NEW BULKHEAD ASSY C/W AD 72-07-09 A	MDT 39-1988, PARA A,B,C,D,E, 123 F,G,I.					1	H	7	1 	3O			NT	3A13    					 
1997022000492	19970220	00492	CE  	1997	2	20	97ZZZX805        	1	19970130	G	3233		ACTUATOR        			CESSNA	210   	T210L       	2073449	CE  										MLG	BOLT LOOSE      	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	93285	298  				21060341				DURING ANNUAL INSPECTION, FOUND ONE ATTACHMENT BOLT ON EACH MLG ACTUATOR BACKED OUT.  SUBMITTER STATES CESSNA SHOULD ADD	RESS BY CHANGING P/N BOLTS HAVING BOLT HEADS DRILLED FOR SAFETY WIRE AS IN CAP INSP NR 32-30-01 WHICH IS NOT APPLICABLE 	TO THIS S/N AIRCRAFT.				1	H	7	1 	3O				3A21    					 
1997022000493	19970220	00493	SW  	1997	2	20	97ZZZX806        	1	19970128	G	8120	635218S6S1800	HOSE            			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					TURBO OIL	BIND            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										DURING C/W SB M81-21, IT WAS NOTED TURBO OIL LINE WAS SHORT AND IN A BIND.  SUBMITTER SUGGESTS ADDING 45 DEGREE FITTING 	ON HOSES TO RELIEVE PROBLEM.					1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997022000495	19970220	00495	EU  	1997	2	20	97ZZZX808        	1	19970123	G	2916	137300D435	RESERVOIR       			BAG   	JETSTM	JETSTM3101  	1500215	EU  										HYD SYS	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11		13487								PART REMOVED FOR CLEANING DUE TO BAD S.O.A.P. SAMPLE OF HYDRAULIC SYSTEM.  AT REMOVAL, FOUND THE INSIDE OF TANK SEVERELY	 CORRODED.  WHEN CORROSION WAS CLEANED, FOUND NUMEROUS PITS - SOME WENT THROUGH THE TANK.					2	L	7	2 	4T			RT	A21EU   					 
1997022700060	19970227	00060	CE  	1997	2	27	97ZZZX813        	1	19970205	G	7430	103572001	SWITCH          			BEECH 	36    	A36TC       	1151603	CE  										ENGINE IGNITION	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	772M	3267 				EA14				ON PRE-INSPECTION RUN UP, IT WAS NOTED THAT THE ENGINE WAS NOT PRODUCING ACCEPTABLE POWER.  DISCOVERED IGNITION SWITCH W	AS STILL IN THE 'START' POSITION.  WHEN PHYSICALLY SWITCHING BACK TO THE 'BOTH' POSITION, THE ENGINE RESUMED NORMAL POWE	R.  TRYING SWITCH SEVERAL MORE TIMES PRODUCED THE SAME RESULTS.  (SWITCH STAYING IN THE START POSITION).  INTERNAL INSPE	CTION REVEALED NO OBVIOUS DEFECTS.  PROBLEM RESOLVED BY REPLACEMENT OF SWITCH.			1	L	7	1 	3O				3A15    					 
1997022700061	19970227	00061	SO  	1997	2	27	97ZZZX814        	1	19970205	G	7430	103572001F	SWITCH          	BENDIX      		PIPER 	PA28  	PA28161     	7102803	SO  										ENG IGN	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9086N	5000 			8520	288616057				THIS SWITCH IS NOT INCLUDED IN AD 76-07-12.  HAS WHITE DOT ADJACENT TO BENDIX LOGO.  MAGS DO GROUND WHEN IN 'OFF' POSITI	ON, BUT WHEN SWITCH TURNED COUNTER CLOCKWISE PAST 'OFF', ENGINE RESTARTS.					1	L	7	1 	3O				2A13    					 
1997022700063	19970227	00063	GL  	1997	2	27	97ZZZX816        	3	19970202	G	6111	V8433N4R	BLADE           			GULSTM	680   	680         	0141602	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	BUTT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23			849  					BJ685		INSPECTION FOUND PROPELLER BLADE BUTT CRACKED.  PROBLEM IS COVERED UNDER AD NR 68-19-04.  AIRCRAFT HAS IO720 ENGINE STC.						1	H	7	2 	3O				2A4     		5	C	P6EA	 
1997022700065	19970227	00065	CE  	1997	2	27	97ZZZX818        	1	19970114	G	3230	9038001011	SWITCH          			BEECH 	23    	C24R        	1151254	CE  										MLG SAFETY	MALFUNCTION     	B		A	RH6R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	24028	3153 				MC486				LANDING GEAR RETRACTED DUE TO SAFETY PRESSURE SWITCH NOT DISENGAGING WHEN AIRSPEED DECREASES.  FOUND DEFECTIVE BELLOWS N	EEDED SUCTION PRESSURE TO FULLY DISCONNECT GEAR SYSTEM.  SUBMITTER RECOMMENDS INSTALLING A SQUAT SWITCH INSTEAD.  NO PRE	VENTIVE MAINTENANCE POSSIBLE.  REMOVE AND REPLACE ONLY.				1	L	7	1 	3O				A1CE    					 
1997022700066	19970227	00066	CE  	1997	2	27	97ZZZX819        	2	19970212	G	7322	63255531	LEVER           		6293097A1   	CESSNA	210   	210L        	2073448	CE  										THROTTLE BODY	WORN            	B			DDNR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	27	29069		500  			21059794				DURING AN ANNUAL INSPECTION, BRASS METAL FLAKES WERE NOTED ON THE THROTTLE CABLE ROD END.  UPON DISASSEMBLY, THE THROTTL	E ARM HOLE, WHERE THE CABLE ATTACHES, WAS FOUND SEVERELY WORN.  WEAR WAS SO EXCESSIVE THE ARM WAS WORN TO WITHIN .0625 I	NCH FROM COMPLETE FAILURE.  THE CAUSE OF THIS DEFECT WAS THAT THE REQUIRED BUSHING, P/N 632554-1, WAS NOT INSTALLED.  TH	IS RESULTED IN THE STEEL BOLT WEARING INTO THE SOFTER BRASS ARM.			1	H	7	1 	3O				3A21    					 
1997022700067	19970227	00067	SO  	1997	2	27	97ZZZX820        	2	19970118	G	8550	632801	PICK UP         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					OIL SUMP	PLUGGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	307FM	700  				421C0323	608291			PILOT REPORTED THE RT ENGINE OIL PRESSURE WAS HIGH ON THE GROUND NEAR RED LINE, BUT WOULD FALL IN PRESSURE AT ALTITUDE, 	THE HIGHER THE ALTITUDE, THE LOWER THE OIL PRESSURE WOULD FALL REACHING BOTTOM RED LINE AT 12,000 FEET.  THE OIL PRESSUR	E SPRING WAS REPLACED AND THE VALVE AND SEAT WERE LAPPED HAVING NO CHANGE IN PROBLEM.  THE OIL PAN WAS THEN REMOVED AND 	ORANGE RTV WAS FOUND IN SUCTION TUBE BLOCKING APPROXIMATELY 90-95 PERCENT OF SCREEN.			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1997022700068	19970227	00068	SO  	1997	2	27	97ZZZX821        	1	19970131	G	7603	2489402	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  										RT ENG THROTTLE	BINDING         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	3590L					318052146				PILOT REPORTED RT ENGINE THROTTLE STICKING AT 30 INCHES MP.  UNABLE TO RETARD THROTTLE TO IDLE.  UPON MAINTENANCE INSPEC	TION, CABLE SLEEVE AT ENGINE HAD COME DISLODGED FROM PRIMARY HOUSING AND WAS KINKING CABLE WHICH PREVENTED RETARDING OF 	THROTTLE.  SLEEVE WAS RE-SWEGED INTO HOUSING AND OPS CHECKED GOOD.  CABLE WAS REPLACED DURING ROUTINE MAINTENANCE THIS D	ATE FOLLOWING RETURN TO MAINTENANCE BASE.			1	L	7	2 	3O			 	A20SO   					 
1997022700071	19970227	00071	EA  	1997	2	27	97ZZZX824        	2	19970121	G	8530	SL17235AD	VALVE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER EXHAUST	WORN            	B			RH6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4635L		600  			15287201				INVESTIGATION FOR A PROGRESSIVE DETERIORATION OF ENGINE FOUND EXCESSIVE WEAR ON VALVE STEMS, VALVE SEATS DEFECTIVE, RING	 AND PISTON WEAR EXCESSIVE.  SUBMITTER STATES ENGINE WOULD NOT MAKE 2,400 TBO.  ENGINE OIL CHANGED AT 50-HOUR INTERVALS.	  PHILLIPS 20W50XC OIL USED.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1997022700072	19970227	00072	SO  	1997	2	27	97ZZZX825        	1	19970206	G	5712	784758	RIB             			PIPER 	PA28  	PA28R180    	7102809	SO  										LT WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4990J	5137 				28R30746				REMOVED THE LT AND RT MLG SIDE BRACE STUDS TO C/W AD 95-20-07.  PRIOR TO INSTALLING THE SIDE-STAY ASSY SUPPORT BRACKET, 	THE MECHANIC CLEANED THE MATING SURFACE AT THE SPAR AND RIB, AND NOTICED A CRACK IN THE RIBS, P/N 78475-4 AND P/N 78475-	5 IN THE BEND RADIUS OF THE FORWARD VERTICAL FLANGE.  THE CRACKS WERE ABOUT .50 INCH TO .75 INCH LONG.				1	L	7	1 	3O				2A13    					 
1997022700073	19970227	00073	SO  	1997	2	27	97ZZZX826        	1	19970206	G	5712	784754	RIB             			PIPER 	PA28  	PA28R180    	7102809	SO  										RT WELL	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4990J	5137 				28R30746				REMOVED THE LT AND RT MLG SIDE BRACE STUDS TO C/W AD 95-20-07.  PRIOR TO INSTALLING THE SIDE-STAY ASSY SUPPORT BRACKET, 	THE MECHANIC CLEANED THE MATING SURFACE AT THE SPAR AND RIB, AND NOTICED A CRACK IN THE RIBS, P/N 78475-4 AND P/N 78475-	5 IN THE BEND RADIUS OF THE FORWARD VERTICAL FLANGE.  THE CRACKS WERE ABOUT .50 INCH TO .75 INCH LONG.				1	L	7	1 	3O				2A13    					 
1997022700074	19970227	00074	SO  	1997	2	27	97ZZZX827        	1	19970211	G	2750		SWITCH          			PIPER 	PA31  	PA31310     	7103103	SO  										FLAP UPLIMIT	STICKING        	B			VDNR	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	09	50779	2333 				31740993				PILOT REPORT THAT FLAPS WOULD NOT EXTEND.  FOUND FLAPS UPLIMIT SWITCH STICKING.  CLEANED AND LUBED SWITCH, OPS CHECK SAT	ISFACTORY.					1	L	7	1 	3O			RT	A20SO   					 
1997022700078	19970227	00078	SO  	1997	2	27	97ZZZX829        	1	19970210	G	2710	67550000	BRACKET         			PIPER 	PA28  	PA28R200    	7102811	SO  										AIL BELLCRANK	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	55275		3441 			287335209				THE LOWER RT AILERON BELLCRANK BRACKET WAS CRACKED JUST ABOVE FORWARD AND REAR ATTACH BOLTS.  SUSPECT CAUSE TAIL INTO WI	ND AND NO CONTROL LOCK.					1	L	7	1 	3O				2A13    					 
1997022700079	19970227	00079	CE  	1997	2	27	97ZZZX830        	1	19970213	G	2913	993880029	POWER PACK      			BEECH 	99    	C99         	1154006	CE  										LT MLG	MALFUNCTION     	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	575W				286	U204				NITROGEN PRE-CHARGE LEAKED PAST ACCUMULATOR PISTON CAUSING PRESSURE BUILD-UP IN RETRACT SIDE OF LANDING GEAR SYSTEM AND 	COLLAPSE OF LEFT MAIN GEAR WHILE AIRCRAFT WAS BEING TOWED.  SUBMITTER STATED LATER DASH NUMBER HYDRAULIC POWER PACK INCO	RPORATES A VENT VALVE TO PRECLUDE THIS PRESSURE BUILD-UP IN THE EVENT OF ACCUMULATOR LEAKAGE.  SUBMITTER RECOMMENDS THIS	 POWER PACK BE RETRO FITTED TO EARLIER AIRCRAFT.  MAIN LANDING GEAR WERE FITTED WITH SAFETY PINS FOR GROUND HANDLING OPE	RATIONS.		1	L	7	2 	3T				A14CE   					 
1997022700080	19970227	00080	SO  	1997	2	27	97ZZZX831        	2	19970205	G	7322	46A70	VENTURI         			CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	WORN            	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	03	60228	3040 				15070157	230864R			OWNER REPORTED ENGINE BEING ROUGH AT LOW RPM AND POOR ACCELERATION AND HESITATION WHILE ADDING POWER, AND NOT RUNNING BE	LOW 1,000 RPM.  INSPECTION REVEALED A TWO-PIECE VENTURI STILL INSTALLED AND WORN TO A POINT OF NEAR SEPARATION.  AD 93-1	8-03 FOR INSTALLING A ONE-PIECE WAS NOT INSTALLED ALTHOUGH A V-STAMP HAD BEEN APPLIED TO THE DATA PLATE INDICATING COMPL	IANCE.  NO LOG BOOK ENTRY OF THAT SPECIFIC AD HAD BEEN MADE, JUST AN ENTRY OF 'AD'S CHECKED OR C/W', AT 12-26-93.  AD EF	FECTIVE DATE = 10-29-93.		1	H	7	1 	3O	3	O		3A19    	E252				 
1997022700081	19970227	00081	SW  	1997	2	27	97ZZZX832        	1	19970101	G	5310	32741	TUBE            			MOONEY	M20   	M20C        	5870208	SW  										FUSELAGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6230U	2857 				2069				FUSELAGE STEEL TUBE CRACKED .50 INCH FROM AFT WELD LOCATION.  CRACK SEPARATION WAS APPROXIMATELY .25 INCH WIDE THROUGH T	HE TUBE.  CRACK WAS DETECTED DURING AN ANNUAL INSPECTION.  TUBE ALSO HAD A NOTICEABLE DOWNWARD BEND MID-POINT OF THE TUB	E. THE BEND IS APPROXIMATELY .50 INCH DEEP, 6 INCHES IN LENGTH.				1	L	7	1 	3O				2A3     					 
1997022700082	19970227	00082	CE  	1997	2	27	97ZZZX833        	1	19970130	G	5312	04121751	BULKHEAD        		04120022    	CESSNA	150   	150A        	2071804	CE  										TAIL CONE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	7207X	7109 				15059307				ON THE MOST AFT BULKHEAD OF FS 200.375, THERE WERE CRACKS IN BOTH CORNERS BETWEEN THE FLANGES AND THE WEBS AT THE RUDDER	 STOP BOLTS.  WHILE THE AIRCRAFT WAS TIED DOWN, THE RUDDER WAS LEFT UNSECURED AND FREE TO BE BLOWN BACK AND FORTH BY THE	 WIND.  THE SUSPECT CAUSE WAS THAT THE RUDDER WAS NOT SECURED IN ANY WAY ALLOWING IT TO BE BLOWN BACK AND FORTH BY THE W	IND BEATING IT AGAINST THE RUDDER STOP BOLTS.  THIS BENT THE BULKHEAD FLANGES UNTIL IT CRACKED IN THE CORNERS.			1	H	7	1 	3O				3A19    					 
1997022700084	19970227	00084	CE  	1997	2	27	97ZZZX835        	1	19970104	G	2510	04111031	SEAT FRAME      			CESSNA	150   	150F        	2071814	CE  										LT/RT CREW SEAT	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	8346G	4056 				15062446				FOUND BOTH PILOT AND COPILOT SEAT BACK FRAMES CRACKED DURING AN ANNUAL INSPECTION.  IF LEFT UNDETECTED, POSSIBLE SEAT BA	CK FAILURE.  THIS SHOULD BE INSPECTED CLOSELY DURING EACH INSPECTION.  INSPECTION MAY REQUIRE PARTIAL REMOVAL OF UPHOLST	ERY IN THIS AREA.  THIS PROBLEM HAS BEEN FOUND ON SEVERAL OTHER A/C AS WELL.				1	H	7	1 	3O				3A19    					 
1997022700085	19970227	00085	CE  	1997	2	27	97ZZZX836        	1	19970210	G	7931	0500106292	LINE            			CESSNA	182   	182K        	2072724	CE  										OIL GAUGE	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	15	899F	4479 				18258163				OIL PRESSURE LINE BEHIND INSPECTION PANEL LEAKING ON TOP BETWEEN GAUGE AND FIREWALL.  PILOT REPORTED OIL ON FLOOR BY PED	AL.  NOT ABLE TO SEE AREA FROM BELOW.					1	H	7	1 	3O			NT	3A13    					 
1997022700086	19970227	00086	CE  	1997	2	27	97ZZZX837        	1	19970212	G	5740	NAS15033M	BOLT            			BEECH 	35    	M35         	1151526	CE  										WING ATTACH	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	9580R					D6178				AIRCRAFT INSPECTION FOUND 1 WING BOLT CORRODED AND OTHERS WITH SOME PITTING.  ACFT HAD NEVER HAD BOLTS INSPECTED.  BEECH	 MM GIVES BOLTS AND HARDWARE REPLACEMENT AT 15 YRS AND ANTI-CORROSION TREATMENT.  MM ALSO STATES BOLTS TO BE MAGNAFLUXED	 AND CORROSION TREATED EVERY 5 YEARS.  NONE OF REQUIREMENTS HAD BEEN DONE.				1	L	7	1 	3O				3A15    					 
1997022700182	19970227	00182	WP  	1997	2	27	97ZZZX840        	1	19970206	G	2752	3774158501	BARREL          			DOUG  	DC8   	DC8*        		WP  										FLAP ACTUATOR	BROKEN          	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										FLAP ACTUATOR CYLINDER BARREL RECEIVED BROKEN AT CRANK MOUNT BORE.  SUSPECT CAUSE IS METAL FATIGUE DUE TO CORROSION.						2	L	7	4 	4J			F	4A25    					 
1997022700183	19970227	00183	NE  	1997	2	27	97ZZZX841        	2	19970207	G	7322	7766841	PILOT VALVE     	HAMSTD      	JFC3123     	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R3    	41580	NE  					SLEEVE	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					749A					REF:  FR25681.  CRACKED SHIELD BRACKET.  RETENTION LIPS OF PILOT VALVE SLEEVE FRACTURED (BOTH LIPS).  PART RETURNED TO H	AMILTON STANDARD FOR EVALUATION.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997022700184	19970227	00184	SW  	1997	2	27	97ZZZX842        	1	19970131	G	3250	MS245474	SWITCH          			SWRNGN	SA226 	SA226T      	8780122	SW  										STEERING ARMING	OUT OF ADJUST   	B	L	A	KD4R	O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SO	17	188SC	4093 				T276				PILOT REPORTED LOSS OF NOSE WHEEL STEERING ON TAKEOFF ROLL.  DIRECTIONAL CONTROL WAS LOST AND AIRCRAFT RAN OFF OF THE RU	NWAY ONTO THE GRASS.  AIRCRAFT WAS NOT DAMAGED AND NO INJURIES RESULTED.  AIRCRAFT WAS FERRIED TO MAINTENANCE BASE AND A	 COMPLETE FUNCTIONAL CHECK OF THE NOSE WHEEL STEERING SYSTEM WAS PERFORMED.  THE ONLY DEFECT NOTED WAS THAT THE SPEED LE	VER NOSE STEERING ARMING SWITCH P/N MS24547-4 WAS OUT OF ADJUSTMENT CAUSING THE NOSE WHEEL STEERING TO NOT ACTIVATE WHEN	 THE SPEED LEVERS WERE RETARDED.		2	L	7	2 	4T			RT	A5SW    					 
1997022700187	19970227	00187	EA  	1997	2	27	97ZZZX845        	1	19970114	G	5700	C6W10057	STRUT           			DHAV  	DHC6  	DHC6300     		EA  										LT WING	CORRODED        	B			E6AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	61UT					549				WING SUPPORT STRUTS (P/N C6W1005-7 LEFT, C6W1005-8 RIGHT).  FOUND EXFOLIATON CORROSION ON BEAM FLANGES 12 TO 18 INCHES F	ROM LOWER ATTACH POINTS WHILE PERFORMING INTERNAL STRUT BEAM INSPECTION IAW FAA AD 87-04-23.  SUBMITTER SUGGESTS CORROSI	ON CAUSED BY ELECTROLYTIC ACTION OF DISSIMILAR METAL CONTACT WITH SKIN ATTACHMENT STEEL SCREWS AND PRESENCE OF MOISTURE 	IN STRUTS.  AIRCRAFT TOTAL TIME:  28,791.3 HOURS.			1	H	7	2 	3T				A9EA    					 
1997022700188	19970227	00188	EA  	1997	2	27	97ZZZX846        	1	19970114	G	5700	C6W10058	STRUT           			DHAV  	DHC6  	DHC6300     		EA  										RT WING	CORRODED        	B			E6AY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31	61UT					549				WING SUPPORT STRUTS (P/N C6W1005-7 LEFT, C6W1005-8 RIGHT).  FOUND EXFOLIATON CORROSION ON BEAM FLANGES 12 TO 18 INCHES F	ROM LOWER ATTACH POINTS WHILE PERFORMING INTERNAL STRUT BEAM INSPECTION IAW FAA AD 87-04-23.  SUBMITTER SUGGESTS CORROSI	ON CAUSED BY ELECTROLYTIC ACTION OF DISSIMILAR METAL CONTACT WITH SKIN ATTACHMENT STEEL SCREWS AND PRESENCE OF MOISTURE 	IN STRUTS.  AIRCRAFT TOTAL TIME:  28,791.3 HOURS.			1	H	7	2 	3T				A9EA    					 
1997022700189	19970227	00189	CE  	1997	2	27	97ZZZX847        	1	19970203	G	3210	1058100197	A FRAME         			BEECH 	76    	76          	1153005	CE  										LT MLG	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6632J	4476 				ME337				WHEN INSTALLING LANDING GEAR 'A' FRAMES PER AD 91-14-14 AND SB 2361 REV 3, THE RIGHT AND LEFT 'A' FRAMES WERE REMOVED FR	OM THE AIRCRAFT FOR FURTHER INSPECTION.  A MAGNAFLUX INSPECTION OF THESE PARTS WAS PERFORMED AND THE 'A' FRAMES WERE FOU	ND CRACKED.  THE MAGNAFLUX INSPECTION IS NOT CALLED OUT FOR IN SB 2361, REV 3, BUT THE CRACKS THAT WERE FOUND DID NOT SH	OW UP WITH THE DYE PENETRANT INSPECTION AS REQUIRED BY SB 2361, REV 3.  RECOMMEND REPLACING THE OLD STYLE 'A' FRAMES WIT	H THE NEW STYLE 'A' FRAMES AS LISTED IN SB 2361, REV 3.		1	L	7	2 	3O				A29CE   					 
1997022700190	19970227	00190	CE  	1997	2	27	97ZZZX848        	1	19970203	G	3210	1058100198	A FRAME         			BEECH 	76    	76          	1153005	CE  										RT MLG	CRACKED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	6632J	4476 				ME337				WHEN INSTALLING LANDING GEAR 'A' FRAMES PER AD 91-14-14 AND SB 2361 REV 3, THE RIGHT AND LEFT 'A' FRAMES WERE REMOVED FR	OM THE AIRCRAFT FOR FURTHER INSPECTION.  A MAGNAFLUX INSPECTION OF THESE PARTS WAS PERFORMED AND THE 'A' FRAMES WERE FOU	ND CRACKED.  THE MAGNAFLUX INSPECTION IS NOT CALLED OUT FOR IN SB 2361, REV 3, BUT THE CRACKS THAT WERE FOUND DID NOT SH	OW UP WITH THE DYE PENETRANT INSPECTION AS REQUIRED BY SB 2361, REV 3.  RECOMMEND REPLACING THE OLD STYLE 'A' FRAMES WIT	H THE NEW STYLE 'A' FRAMES AS LISTED IN SB 2361, REV 3.		1	L	7	2 	3O				A29CE   					 
1997022700191	19970227	00191	CE  	1997	2	27	97ZZZX849        	1	19970207	G	2730	1155240463	TORQUE TUBE     			BEECH 	100   	B100        	1152919	CE  										ELEVATOR	WORN            	B		A	BCBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	717D					BE91				'PLAY' WAS NOTED BETWEEN THE ELEVATORS.  INSPECTION FOUND ELEVATOR PINS TO TORUQE TUBE WORN.  REAMING, PER SM, DID NOT R	EMOVE ALL THE PLAY.  REPLACED TORQUE T UBE ASSY WITH NEW PINS.  THERE WAS NO ABNORMAL FLIGHT CONDITIONS BEFORE OR AFTER.	  TORQUE TUBE INSPECTION IS REQUIRED EACH 1,000 HOURS, 126.6 HOURS SINCE LAST PRIMARY INSPECTION.				1	L	7	2 	4T				A14CE   					 
1997022700192	19970227	00192	CE  	1997	2	27	97ZZZX850        	1	19970129	G	2931	P50018LMBE	GAUGE           			BEECH 	200   	B200        	1152922	CE  										ACCUM PRESS	STUCK           	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	961LL	290  				BB1139				THIS GAUGE IS PART OF STC SA 4378-WP AVIA DESIGN, INC., HYDRAULIC LANDING GEAR RETRACTION SYSTEM.  GAUGE FOUND STUCK AT 	1,150 PSI DURING AIRCRAFT INSPECTION.  SUBMITTER RECOMMENDS A BETTER QUALITY GAUGE BE USED IN SYSTEM.					1	L	7	2 	4T				A24CE   					 
1997022700193	19970227	00193	NE  	1997	2	27	97ZZZX851        	3	19970208	G	6111	A2202	BEARING         			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	INBOARD BLADE	SPLIT           	B	P		GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	94UX	6635 	2882 		34	UE94				PROPELLER WAS DISASSEMBLED DUE TO 'LOOSE' BLADES (IN EXCESS OF .75 INCH FORE/AFT).  ON INSPECTION, FOUND BLADE S/N 982 I	NNER BEARING RACE (1 SIDE OF SPLIT BEARING) SPLIT (CRACKED) 1 INCH THROUGH CENTER OF BALL RUN AREA, BALLS WERE PITTED.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997022700194	19970227	00194	NE  	1997	2	27	97ZZZX852        	3	19970208	G	6111	A2202	BEARING         			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	INBOARD BLADE	BROKEN          	B	P	A	GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	94UX	6635 	2882 		9	UE94		HJ211		PROPELLER WAS DISASSEMBLED DUE TO LOOSE BLADES (IN EXCESS OF .75 INCH FORE/AFT).  ON INSPECTION, FOUND BLADE S/N 930 INN	ER BEARING RACE DAMAGED.  ONE SIDE OF SPLIT RACE CRACKED INTO DOWN CENTER OF BALL RIDE AREA AND OTHER HALF OF SPLIT RACE	 CRACKED UP ABOUT ONE-FOURTH OF RADIUS AND BROKEN, ALONG WITH FLATTENED UPPER SURFACE.				2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1997022700195	19970227	00195	NE  	1997	2	27	97ZZZX853        	2	19970211	G	7250	668736	BEVEL GEARSHAFT 								PWA   	JFTD12	JFTD12A5A   	52047	NE  					NR 2 SENSE CABLE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09					97					FOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT.   INDICATORS APPEAR SHARP.  A WELL DEFINED CRACK-T	YPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT.  OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY	 TO INSIDE INDICATIONS.  SHAFT S/N 97 SHOWS 3 INDICATIONS.									4	U			E15EA				 
1997022700196	19970227	00196	NE  	1997	2	27	97ZZZX854        	2	19970211	G	7250	668736	BEVEL GEARSHAFT 								PWA   	JFTD12	JFTD12A5A   	52047	NE  					NR 2 SENSE CABLE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09					84					FOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT.   INDICATORS APPEAR SHARP.  A WELL DEFINED CRACK-T	YPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT.  OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY	 TO INSIDE INDICATIONS.  SHAFT S/N 84 SHOWS 3 INDICATIONS.									4	U			E15EA				 
1997022700197	19970227	00197	NE  	1997	2	27	97ZZZX855        	2	19970211	G	7250	668736	BEVEL GEARSHAFT 								PWA   	JFTD12	JFTD12A5A   	52047	NE  					NR 2 SENSE CABLE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09					197					FOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT.   INDICATORS APPEAR SHARP.  A WELL DEFINED CRACK-T	YPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT.  OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY	 TO INSIDE INDICATIONS.  SHAFT S/N 197 SHOWS 1 INDICATION.									4	U			E15EA				 
1997022700198	19970227	00198	NE  	1997	2	27	97ZZZX856        	2	19970211	G	7250	668736	BEVEL GEARSHAFT 								PWA   	JFTD12	JFTD12A5A   	52047	NE  					NR 2 SENSE CABLE	CRACKED         	B	S		JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										FOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT.   INDICATORS APPEAR SHARP.  A WELL DEFINED CRACK-T	YPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT.  OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY	 TO INSIDE INDICATIONS.  ONE ADDITIONAL SHAFT HAD 4 INDICATIONS (UNKNOWN S/N).									4	U			E15EA				 
1997022700239	19970227	00239	NE  	1997	2	27	97ZZZX860        	1	19970209	G	6320	643520536101	MAIN SHAFT      		643520500048	SKRSKY	S64   	S64F        		NE  										M/R GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	158AC	2969 	2199 		A6148	64081				DURING OVERHAUL OF THE MGB, THE MAIN SHAFT WAS SUBJECTED TO A FMPI.  ONE SPLINE WAS FOUND CRACKED ACROSS THE SPLINE WIDT	H ON THE UPPER END OF THE LOWER SPLINE. THE CRACK DID NOT APPEAR TO ORIGINATE WHERE THE LOWER PLANETARY SPLINE CONTACTS 	THE SHAFT, BUT WAS LOCATED APPROXIMATELY .100 INCH ABOVE THE PLANETARY PLATE SPLINE CONTACT ZONE.  THE CRACK EXTENDED FR	OM THE ROOT OF ONE SPLINE TOOTH TO THE ROOT OF THE ADJACENT SPLINE.  IN ADDITION TO THE ONE CRACK, THERE WERE APPROXIMAT	ELY 30 ADDITIONAL SPLINES THAT HAD UNUSUAL CRACK-LIKE INDICATIONS IN THE ROOT RADIUS OF THE SPLINES.  THE PRESENCE OF TH	ESE INDICATIONS COULD NOT BE VERIFIED TO BE THE START OF CRACK.	2	G	7	2 	4U				H6EA    					 
1997030600001	19970306	00001	CE  	1997	3	6	97ZZZX865        	1	19970225	G	5520		ELEVATOR        			CESSNA	180   	180         	2072602	CE  										FLIGHT CONTROL	MISMOUNTED      	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	07										SUBMITTER REPORTS AN INCIDENT OCCURRED IN 1992 AT A CESSNA 180/185 FLY-IN WHEN AN AIRCRAFT WAS NOTED TO HAVE THE ELEVATO	RS MOUNTED UPSIDE DOWN.  AGAIN, IN FEBRUARY, 1997, A SECOND OCCURRENCE OF ELEVATOR UPSIDE DOWN.  BOTH AIRCRAFT HAD JUST 	COME FROM A PAINT SHOP.  IN BOTH CASES, UP-TRAVEL RESTRICTED.				1	H	7	1 	3O			NC	5A6     					 
1997030600002	19970306	00002	SO  	1997	3	6	97ZZZX866        	1	19970207	G	3233	401195	BOLT            			PIPER 	PA31T 	PA31T2      	7103127	SO  										LT MLG ACTUATOR	BROKEN          	B		A	BCBR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	03	107MC	4520 				31T8166032				LEFT LANDING GEAR WOULD NOT GO DOWN.  AFTER REPEATED ATTEMPTS, CO2 EMERGENCY DOWN WAS ACTUATED AND GEAR DID GO DOWN AND 	LOCK.  LANDING WAS NORMAL.  INSPECTION REVEALED THE BOLT SECURING THE LANDING GEAR ACTUATOR CYLINDER HAD BROKEN.  REF: P	A31T2 PARTS FIG 41, ITEM 81.  INSPECTION OF THE RT GEAR ACTUATOR ATTACH BOLT FOUND NOTHING ABNORMAL.  BOLT APPEARED TO B	E IN GOOD CONDITION.  ATTACH BOLTS WERE REPLACED.  GEAR SERVICED.  RETRACTION CHECKS OK.  NEW CO2 CARTRIDGE WAS INSTALLE	D.		1	L	7	2 	3T			RT	A8EA    					 
1997030600003	19970306	00003	CE  	1997	3	6	97ZZZX867        	1	19970201	G	5312	07125231	BULKHEAD        			CESSNA	182   	182G        	2072716	CE  										FS 230.187	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	28EM					18255209				BULKHEAD WAS FOUND CRACKED AT LEFT RUDDER STOP BOLT AREA.  THIS INSPECTION IS REQUIRED BY AD 72-07-09.  THE CRACK WAS NO	T IN THE AREA CALLED OUT IN THE AD.  THE BULKHEAD IS CALLED OUT FOR REPLACEMENT IF FOUND CRACKED.					1	H	7	1 	3O			NT	3A13    					 
1997030600004	19970306	00004	CE  	1997	3	6	97ZZZX868        	1	19970211	G	3221	05130481	ANGLE           			CESSNA	172   	172A        	2072404	CE  										NLG LT FITTING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7229T					46829				FOUND BOTH ANGLES CRACKED AFT OF FIREWALL.  UPPER NOSE GEAR FITTING ATTACHES TO ANGLES.  RIVETS LOOSE IN FITTING.						1	H	7	1 	3O				3A12    					 
1997030600005	19970306	00005	CE  	1997	3	6	97ZZZX869        	1	19970211	G	3221	05130482	ANGLE           			CESSNA	172   	172A        	2072404	CE  										NLG RT FITTING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7229T					46829				FOUND BOTH ANGLES CRACKED AFT OF FIREWALL.  UPPER NOSE GEAR FITTING ATTACHES TO ANGLES.  RIVETS LOOSE IN FITTING.						1	H	7	1 	3O				3A12    					 
1997030600006	19970306	00006	SO  	1997	3	6	97ZZZX870        	1	19970210	G	2740	402346	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  										STABILATOR HORN	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	7203Y	2842 				30228				WHILE DISASSEMBLING THE STABILATOR TORQUE TUBE, FOUND BOTH (2 EACH) CLOSE TOLERANCE BOLTS VERY CORRODED.  SUBMITTER BELI	EVES THESE BOLTS SHOULD BE REPLACED BY AGE OF 30 YEARS.					1	L	7	2 	3O				A1EA    					 
1997030600007	19970306	00007	CE  	1997	3	6	97ZZZX871        	1	19970211	G	3211	0541153	U-BOLT          			CESSNA	172   	172A        	2072404	CE  										RT MLG	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7229T					46829				INSPECTION FOUND RT MAIN GEAR U-BOLT BROKEN.  PART OF U-BOLT STILL IN NUT.  NUT FOUND IN AIRCRAFT.						1	H	7	1 	3O				3A12    					 
1997030600008	19970306	00008	SO  	1997	3	6	97ZZZX872        	1	19970210	G	2740	402346	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  										STABILATOR HORN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	808BB	3759 				30288				WHILE DISASSEMBLING THE STABILATOR TORQUE TUBE, SUBMITTER FOUND BOTH (2 EACH) CLOSE TOLERANCE BOLTS VERY CORRODED.  SUBM	ITTER BELIEVES THESE SHOULD BE REPLACED BY AGE OF 30 YEARS.  DISASSEMBLED ANOTHER STABILATOR HORN AND FOUND THE SAME CON	DITION.				1	L	7	2 	3O				A1EA    					 
1997030600009	19970306	00009	EA  	1997	3	6	97ZZZX873        	2	19970131	G	7414		BEARING         	BENDIX      	1068291018  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					MAG	FAILED          	D				E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SO	16	31RD	1400 			G199105GR	317852059	L185768A			CRUISE FLIGHT 7,000 FEET.  ENGINE BEGAN RUNNING ROUGH, PRECAUTIONARY SHUT DOWN.  FOUND MAGNETO BEARING FAILED.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997030600010	19970306	00010	CE  	1997	3	6	97ZZZX874        	1	19970212	G	5711		SPAR            			BEECH 	33    	F33A        	1151425	CE  										CARRY THROUGH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8242T	5940 				CE1610				INSPECTION FOUND CRCKS IN CARRY-THROUGH STRUCTURE.  AD 95-04-03 NOT VALID BY SERIAL NUMBER.  SUBMITTER STATED THIS IS TH	E 17TH AIRCRAFT REPORTED.					1	L	7	1 	3O				3A15    					 
1997030600011	19970306	00011	NM  	1997	3	6	97ZZZX875        	1	19970115	G	2720	69356071	CAM SEGMENT     			BOEING	737   	737201      	1384454	NM  										PCU	WORN            	B	S	A	IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										THE SHAFT JUST ABOVE THE BALL IS RUBBING/WEARING ON THE YAW DAMPER SLEEVE.  WHEN THE UNIT WAS EXTENDED AND THE YAW DAMPE	R WAS ENERGIZED IN THE EXTEND POSITION, THE UNIT BOUND AND WOULD NOT RETRACT PER PARA 12, G, 889.  THE AREA OF WEAR HAS 	A RIDGE THAT WILL CATCH ON THE SIDE OF YAW DAMPER SLEEVE CAUSING A BINDING CONDITION.				2	L	7	2 	4F				A16WE   					 
1997030600012	19970306	00012	NM  	1997	3	6	97ZZZX876        	1	19970114	G	2720	596005003	SOLENOID        			BOEING	737   	7373G7      	1384595	NM  										RUDDER PCU	SHORTED OUT     	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			2531 							FLUID PASSING THROUGH ELECTRICAL CONNECTOR SHORTED OUT WIRING.						2	L	7	2 	4F			RT	A16WE   					 
1997030600013	19970306	00013		1997	3	6	97ZZZX877        	4	19970115	G	2210	69356111	ACTUATOR SLEEVE 			BOEING	737   	737201      	1384454	NM  										YAW DAMPER	WORN            	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										THE ELONGATED HOLE WHERE THE CAM SEGMENT IS INSERTED INTO THE YAW DAMPER PISTON IS BEING RUBBED AND WORN BY THE CAM SEGM	ENT.					2	L	7	2 	4F				A16WE   					 
1997030600014	19970306	00014	EA  	1997	3	6	97ZZZX878        	1	19970128	G	5553	C2FS4045A	CHANNEL         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										FIN ATTACH	CRACKED         	B		A	V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	692F					1407				ON VERTICAL FIN ATTACH REINFORCEMENT CHANNEL, THE BOLT HOLES THAT ARE USED TO SECURE RUDDER HINGE CASTING C2FS3705ND WER	E FOUND TO HAVE CRACKS RADIATING FROM THEM.  LACK OF A CONTROL SURFACE LOCK AND HIGH WINDS OVER WINTER MAY HAVE CONTRIBU	TED TO CRACKING.				1	H	7	1 	3R				A806    					 
1997030600015	19970306	00015	EA  	1997	3	6	97ZZZX879        	1	19970127	G	2823	C2CE527A	DRUM            		TC17300     	DHAV  	DHC2  	DHC2MK1     	2800102	EA  										FUEL SELECTOR	CORRODED        	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	692F					1407				FUEL SELECTOR AFT CABLE DRUM WAS FOUND CORRODED DUE TO INTERGRANULAR CORROSION.  CABLE WAS NO LONGER FIRMLY SECURED IN G	ROOVES.					1	H	7	1 	3R				A806    					 
1997030600016	19970306	00016	EA  	1997	3	6	97ZZZX880        	1	19970128	G	2752		ACTUATOR        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										INLET LINE	LEAK            	B			V2AR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	692F					1407				ON INSPECTION, A HYDRAULIC LEAK WAS FOUND AT FLAP ACTUATOR LINE INLET.  ON DISASSEMBLY, DEBRIS WAS NOTICED IN LINE.  A F	URTHER INSPECTION FOUND ALL COMPONENTS OF FLAP SYSTEM HAD THICK DEBRIS THAT MAY BE MIL5606 CONTAMINATED WITH MOISTURE.					1	H	7	1 	3R				A806    					 
1997030600019	19970306	00019	SO  	1997	3	6	97ZZZX882        	1	19970206	G	6120	8930200	ROD END         			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					PROP CONTROL	RUBBING         	B	S	A	LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9251E	653  				3213084	L2527148A			PROPELLER CONTROL NOT MAKING FULL TRAVEL.  THREADED PORTION OF ROD END ASSY RUBBING A TRACK INTO LT FWD BAFFLE ASSY., P/	N 85565-02.  HAVE NOTED THIS ON NEARLY ALL NEW PA32R301 SARATOGA IIHP AIRCRAFT.  SUBMITTER STATES NEED TO MANUFACTURE A 	SUPPORT TO KEEP BAFFLE AWAY FROM RPOPELLER CONTROL OR REDESIGN ROD END.				1	L	7	1 	3O	3	O		A3SO    	1E4				 
1997030600288	19970306	00288	SO  	1997	3	6	97ZZZX884        	1	19970204	G	2750		CONTROL CABLE   			PIPER 	PA28  	PA28161     	7102803	SO  										FLAP CONTROL	FRAYED          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	120ND	6546 				2841218				DURING PHASE ONE INSPECTION, MECHANIC NOTICED DURING RUN-UP PRIOR TO INSPECTION THAT FLAP CONTROL FELT LIKE IT WAS BINDI	NG.  OPENED A/C FOR INSPECTION AND FOUND CABLE FRAYED AND UNRAVELING WHERE CABLE GOES INTO SWAGED TURNBUCKLE AT FLAP HAN	DLE ATTACH POINT.  INSTALLED NEW CABLE AND RIGGED.				1	L	7	1 	3O			 	2A13    					 
1997030600289	19970306	00289	EA  	1997	3	6	97ZZZX885        	2	19970202	G	8520	75190	CAMSHAFT        			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540D4A5   	41532	EA  					GOV DRV GEAR	BROKEN          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	25	1424N		550  			244383	L291348			ENGINE OVERSPED IN CRUISE FLIGHT AT 6,500 FEET.  MAXIMUM OVERSPEED WITNESSED WAS 3,500 RPM.  AIRCRAFT LANDED AT FIRST SU	ITABLE AIRFIELD.  ON INSPECTION, CAMSHAFT WAS FOUND BROKEN IN TWO BETWEEN FORWARD BEARING AND GOVERNOR DRIVE GEAR CAUSIN	G PROPELLER TO DECREASE PITCH CAUSING OVERSPEED.  IT APPEARED THE BREAK IN THE CAM ORIGINATED FROM A CRACK AT THE WOODRU	F KEY SLOT.  NOTE:  ENGINE WAS OVERHAULED 550 HOURS AGO DUE TO SUDDEN STOPPAGE (GEAR -UP LANDING).			1	L	7	1 	3O	3	O		1A15    	1E4				 
1997030600291	19970306	00291	GL  	1997	3	6	97ZZZX887        	3	19970101	G	6111		BLADE           			SLNSBY	T67   	T67M260     	8323006	EU  						HOFMAN	HOV123	HOV123KV    	GL  	BASE	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3004H	873  				2126		B688		INSPECTION FOUND DELAMINATION AT BASE OF BLADE.  SUBMITTER STATED CAUSE UNKNOWN.  AWAITING INFORMATION FROM MANUFACTURER	.					1	L	7	1 	3O			NT	A73EU   		5	C	P5EU2	 
1997030600295	19970306	00295	CE  	1997	3	6	97ZZZX891        	1	19970108	G	7810	991029919	HEADER ASSY     			CESSNA	340   	340A        	2076405	CE  										EXHAUST WYE	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3975C	3113 				340A0991				DURING INSPECTION AND AD 75-23-08R5 CHECK, FOUND EXHAUST WYE CRACKED ONE-THIRD OF THE WAY AROUND AT THE BOTTOM IN THE WE	LD ZONE.					1	L	7	2 	3O				3A25    					 
1997030600296	19970306	00296	SO  	1997	3	6	97ZZZX892        	1	19970101	G	2410	LW18129	BELT            			PIPER 	PA32  	PA32R301T   	7103220	SO  										ALTERNATOR DRV	FAILED          	B			CPNR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SW	17	4294P					32R8329015				PILOT REPORTED LOSS OF ALTERNATOR AFTER 4 HOURS OF FLIGHT.  INVESTIGATION FOUND ALTERNATOR DRIVE BELT BROKEN.  CHECK ALT	ERNATOR, BEARINGS, AND PULLEY, FOUND OK.  AIR COND BELT LOOSE.  REPLACED BELT, SET TENSION.  ALL CHECK OK AT RUN-UP.					1	L	7	1 	3O				A3SO    					 
1997030600297	19970306	00297	GL  	1997	3	6	97ZZZX893        	3	19970101	G	6111		BLADE           			SLNSBY	T67   	T67M260     	8323006	EU  						HOFMAN	HOV123	HOV123KV    	GL  	BASE	DELAMINATED     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	7020D	581  				2109		B641		INSPECTION FOUND DELAMINATION AT BASE OF BLADE.  SUBMITTER STATED CAUSE UNKNOWN.  AWAITING INFORMATION FROM MANUFACTURER	.					1	L	7	1 	3O			NT	A73EU   		5	C	P5EU2	 
1997030600298	19970306	00298	CE  	1997	3	6	97ZZZX894        	1	19970101	G	3230	3581512521	ROD ASSY        			BEECH 	58    	58TC        	1152746	CE  										MLG RETRACT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	97R	2331 				TK45				DURING ANNUAL INSPECTION WHILE PERFORMING GEAR SWING, AN UNUSUAL NOISE (THUD) WAS HEARD.  FOLLOWING EMERGENCY GEAR EXTEN	SION, FOUND CRACKED ROD ASSY AT 8 INCHES OUTBOARD OF ATTACH BOLT.  ALSO, NOTED DOWN TENSION SPRING WAS STACKED.  SUSPECT	 CAUSE INCORRECT TENSION AND RIGGING.				1	L	7	2 	3O				A23CE   					 
1997030600301	19970306	00301		1997	3	6	97ZZZX897        	4	19970212	G	3451	066010690001	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										DME	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	1208F	17   			15102	36146				UNIT WEAK, WILL NOT ALLOW DME HOLD RELAY TO HOLD.  REPLACED WITH NEW DME INDICATOR.						1	G	7	2 	4U				H4SW    					 
1997030600302	19970306	00302	WP  	1997	3	6	97ZZZX898        	1	19970113	G	7330	369H81443	SWITCH          		38655       	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL BYPASS	FAILED          	B		A	GHHR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	01	1109P	730  			T41618	1100849D	CAE833681			AIRCRAFT EXPERIENCED A POWER LOSS AND MADE A PRECAUTIONARY LANDING.  INVESTIGATION SHOWED THAT FUEL CONTAMINATION HAD CO	LLAPSED THE FUEL NOZZLE SCREEN SEVERELY RESTRICTING FUEL FLOW TO ENGINE.  THE FUEL FILTER WAS COMPLETELY PLUGGED AND IN 	BYPASS.  THE PILOT REPORTED THE FUEL BYPASS LIGHT DID NOT ILLUMINATE.  TEST OF SWITCH SHOWED IT TO BE INOPERATIVE AT 24.	5 TO 35 INCHES OF FUEL.			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997030600303	19970306	00303	SW  	1997	3	6	97ZZZX899        	1	19970131	G	6700	204010925009	CONTROL TUBE    			BELL  	212   	212         	1181420	SW  										FLIGHT CONTROL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	16973					30882				FOUND ROD END LOOSE IN CONTROL TUBE DUE TO LOOSE AND WORKING RIVETS.  REPLACED CONTROL TUBE.						1	G	7	1 	4U				H4SW    					 
1997030600304	19970306	00304	SW  	1997	3	6	97ZZZX900        	1	19970117	G	5302	206031004115B	TAIL BOOM       			BELL  	206   	206B        	1181511	SW  										T/R GEARBOX	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	20395	4472 			BCJN08310	3301				AT 100 HOUR INSPECTION, CRACK WAS FOUND AT LEFT HAND REAR ATTACH POINT FOR TAIL ROTOR GEARBOX.  CRACK WAS .25 INCH LONG 	AND EXTENDED THROUGH THE MOUNT HOLE.  CRACK WAS ONLY VISIBLE FROM INSIDE THE TAIL BOOM.					1	G	7	1 	3U				H2SW    					 
1997030600305	19970306	00305	SW  	1997	3	6	97ZZZX901        	1	19970130	G	2910	70061H000A180A	HOSE            			BELL  	206   	206B        	1181511	SW  										HYDRAULIC SYSTEM	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	2777Q					2805				FOUND HYDRAULIC LEAK CAUSED BY CHAFING AT ADEL CLAMP SECURING HOSE TO DECK.  REPLACED LINE AND INSTALLED SERVICEABLE ADE	L CLAMP, P/N MS21919WDG9.					1	G	7	1 	3U				H2SW    					 
1997030600306	19970306	00306	SW  	1997	3	6	97ZZZX902        	1	19970130	G	6730	206076031013	SERVO           			BELL  	206   	206B        	1181511	SW  										FLIGHT CONTROL	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	2777Q	10420	3106 		4604	2805				NOTED BINDING IN-FLIGHT CONTROLS.  REPLACED RT SERVO.  INTERNAL PROBLEMS DUE TO BEING CLOSE TO TBO.						1	G	7	1 	3U				H2SW    					 
1997030600311	19970306	00311	SW  	1997	3	6	97ZZZX907        	1	19970116	G	2913	2060760303	PUMP            			BELL  	206   	206L1       	1182107	SW  										HYD SYSTEM	DEFECTIVE       	H				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SW	09	5748H				A41803852	45490				NOTED CYCLIC CONTROLS BINDING DURING FLIGHT.  LOW HYDRAULIC PRESSURE.  REPLACED PUMP ASSY AND RETURNED AIRCRAFT TO SERVI	CE.					1	G	7	1 	3U				H2SW    					 
1997030600313	19970306	00313	EU  	1997	3	6	97ZZZX909        	1	19970210	G	7170	350A21010148	HOSE            			SNIAS 	350   	AS350B2     	8680813	EU  										DRAIN FUEL OIL	DISCONNECTED    	B		A	RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6103X					2723				DURING 100 HOUR INSPECTION, FOUND FUEL/OIL DRAIN LINE ITEM 30 PG 71.70.10, PG 2, EUROCOPTER AS350B2 PARTS MANUAL, HAD CO	ME LOOSE CAUSING DRAIN FUEL TO DRAIN INTO ELECTRICAL JUNCTION BOX AREA.  THIS PROBLEM WAS ALSO FOUND IN SAME AREA WITH A	NOTHER AIRCRAFT OF SAME MODEL.				1	G	7	1 	3U				H9EU    					 
1997030600314	19970306	00314	WP  	1997	3	6	97ZZZX910        	1	19970212	G	2430	P505A	WIRE            			HUGHES	369   	369E        	4470707	WP  										BATTERY RELAY	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	52475	4201 				0119E				DURING INSPECTION, FOUND WIRES FROM TERMINAL A1 OF K310 BATTERY RELAY TO BATTERY SHUNT AND WIRES FROM THE BATTERY SIDE O	F REVERSE CURRENT RELAY TO TERMINAL A1 OF K301 START RELAY HAD SEVERELY CRACKED COVERING EXPOSING BARE WIRES.  THESE WIR	ES ARE CLAMPED TOGETHER AND COULD HAVE STARTED TOUCHING EACH OTHER AT ANY TIME.  ALL OF THESE WIRES SHOW 'NO' SIGNS OF H	EAT STRESS OR OVERHEATING.  THE CRACKING APPEARS TO BE FROM OLD AGE.  SUBMITTER STATES DURING INSPECTIONS, THIS AREA SHO	ULD BE INSPECTED CLOSELY.		1	G	7	1 	3U			 	H3WE    					 
1997030600315	19970306	00315	WP  	1997	3	6	97ZZZX911        	1	19970212	G	8097	P505B	WIRE            			HUGHES	369   	369E        	4470707	WP  										START RELAY	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	52475	4201 				0119E				DURING INSPECTION, FOUND WIRES FROM TERMINAL A1 OF K310 BATTERY RELAY TO BATTERY SHUNT AND WIRES FROM THE BATTERY SIDE O	F REVERSE CURRENT RELAY TO TERMINAL A1 OF K301 START RELAY HAD SEVERELY CRACKED COVERING EXPOSING BARE WIRES.  THESE WIR	ES ARE CLAMPED TOGETHER AND COULD HAVE STARTED TOUCHING EACH OTHER AT ANY TIME.  ALL OF THESE WIRES SHOW 'NO' SIGNS OF H	EAT STRESS OR OVERHEATING.  THE CRACKING APPEARS TO BE FROM OLD AGE.  SUBMITTER STATES DURING INSPECTIONS, THIS AREA SHO	ULD BE INSPECTED CLOSELY.		1	G	7	1 	3U			 	H3WE    					 
1997030600316	19970306	00316	WP  	1997	3	6	97ZZZX912        	1	19970204	G	6320	2014ACR	GEAR TOOTH      		269A517523  	HUGHES	269   	269C        	4470504	WP  										M/R XMSN	CHIPPED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	6141N	1983 			S0456	S1641				DURING AIRCRAFT RUN-UP, ROTOR TACHOMETER WENT TO ZERO.  FOUND ONE TOOTH ON RING GEAR CHIPPED.  FOUND CHIP JAMMED IN OIL 	PUMP GEARS WHICH CAUSED OIL PUMP DRIVESHAFT TO SHEAR.  SCHWEIZER SB 244.2 ADDRESSES THIS SUBJECT.  THIS IS ALSO ADDRESSE	D IN THE 50/100 HR CHECK LIST.  TRANSMISSION REMOVED AND REPLACED WITH OVERHAULED UNIT.				1	G	7	1 	3O				4H12    					 
1997030600317	19970306	00317	NE  	1997	3	6	97ZZZX913        	1	19970204	G	6320	7635109002050	HOUSING         			SKRSKY	S76   	S76B        	8143007	NE  										M/R GEARBOX	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	76FL	2117 			C00100014	760347				WHILE DOING THE ZONE 5 INSPECTION, FOUND A CRACK IN THE UPPER MAIN GEARBOX HOUSING JUST AFT OF THE RIGHT REAR SUPPORT LE	G.  THE CRACK WAS FOUND IN THE AREA SHOWN IN CHAPTER 5-20-00, PAGE 23, FIGURE 16.  THE MAIN GEARBOX WILL BE CHANGED TO F	IX THIS PROBLEM.  AIRCRAFT TOTAL TIME 2,128.7 HOURS.  M/R GEARBOX P/N 7635109600042.				1	G	7	2 	4U				H1NE    					 
1997030600318	19970306	00318	SW  	1997	3	6	97ZZZX914        	1	19970129	G	6320	2060401201	PINION          		2060400035  	BELL  	206   	OH58A       	1181579	SW  										TRANSMISSION	TEETH BROKEN    	B	P		QJ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05		2372 	358  		B12577					INSPECTION FOUND PINION WITH A BROKEN TOOTH AND PITTING ON THE REST OF THE TEETH.  SUBMITTER BELIEVES THE CAUSE TO BE IM	PROPER BACKLASH.					1	G	7	1 	3U				H2SW    					 
1997030600693	19970306	00693	NE  	1997	3	6	97ZZZX916        	1	19970214	G	5313	7620204001146	LONGERON        			SKRSKY	S76   	S76B        	8143007	NE  										RT TAIL BOOM	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5NJ					760346				ANGLE CRACKED AT STA 467.  AIRCRAFT TT 2,855.3 HOURS.						1	G	7	2 	4U				H1NE    					 
1997030600694	19970306	00694	NE  	1997	3	6	97ZZZX917        	1	19970214	G	5320	7620204002120	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FS 467	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5NJ					760346				UPPER SHEAR DECK WEB CRACKED RT SIDE, STA 467.  AIRCRAFT TT 2,855.3 HOURS.						1	G	7	2 	4U				H1NE    					 
1997030600695	19970306	00695	NE  	1997	3	6	97ZZZX918        	1	19970214	G	5320	7620204002117	DECK WEB        			SKRSKY	S76   	S76B        	8143007	NE  										FS 467	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5NJ					760346				RIGHT TAIL BOOM LONGERON CRACKED AT STA 467.  AIRCRAFT TT 2,855.3 HOURS.						1	G	7	2 	4U				H1NE    					 
1997030600696	19970306	00696	WP  	1997	3	6	97ZZZX919        	1	19970210	G	7160	369A4163	HARNESS         			HUGHES	369   	369D        	4470706	WP  										SCAV AIR SYSTEM	CHAFED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				FOUND SCAV AIR SOLENOID WIRE HARNESS WAS CHAFING ON THE COOLING DUCT FOR THE TRANS OIL COOLER.  REPLACED HARNESS.						1	G	7	1 	3U				H3WE    					 
1997030600697	19970306	00697	WP  	1997	3	6	97ZZZX920        	1	19970210	G	2550	2TC1415	BREAKER         			HUGHES	369   	369D        	4470706	WP  										CARGO HOOK	FAILED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				CARGO HOOK DID NOT FUNCTION.  FOUND CIRCUIT BREAKER WAS INOPERATIVE.  AFTER REMOVING CIRCUIT BREAKER COULD HEAR A RATTLE	 WHEN SHAKING.					1	G	7	1 	3U				H3WE    					 
1997030600698	19970306	00698	GL  	1997	3	6	97ZZZX921        	2	19970210	G	7323	369A70023	ACTUATOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GOV	DEFECTIVE       	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	8265 				1151D				DURING RUN-UP IT WAS DISCOVERED THE GOV NEEDED CONSTANT ADJUSTMENT UP AND DOWN WITH THE TRIM MOTOR.  IT WAS FOUND THAT T	HE TRIM MOTOR HAS SOME INTERNAL SLOP.  REPLACED TRIM MOTOR.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997030600699	19970306	00699	GL  	1997	3	6	97ZZZX922        	2	19970210	G	7310	6844169	LINE            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE FCU	CHAFED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D	CAE832750			DURING RE-ASSEMBLY OF THE ENGINE, IT WAS FOUND THAT THE FUEL LINE FROM FCU TO THE CHECK VALVE WAS CONTACTING ANOTHER LIN	E.  NORMALLY, THIS INDICATES IT IS INSTALLED BACKWARDS, BUT IN THIS CASE, IT HIT BOTH WAYS.  NO PART NUMBER WAS FOUND ON	 THE TUBE, AND A NEW TUBE RECTIFIED THE PROBLEM.  SUSPECT IT HAD BEEN A 'FIELD FIX' SOME TIME PAST.				1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997030600700	19970306	00700	WP  	1997	3	6	97ZZZX923        	1	19970210	G	5330	369H01123	PANEL           			HUGHES	369   	369D        	4470706	WP  										XMSN SUPPORT	CRACKED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				SUBMITTER STATED THIS IS NOT AN UNCOMMON PROBLEM.  THIS PANEL IS ATTACHED TO THE AFT BOTTOM OF THE TRANSMISSION SUPPORT 	STRUCTURE AND ALSO ATTACHES TO THE REAR DOOR FRAME AS IT COMES UP TO THE TRANS SUPPORT.  IT WAS FOUND CRACKED BETWEEN 3 	RIVET HOLES WHERE IT ATTACHES TO THE SUPPORT.  THE SUPPORT IS STAINLESS STEEL AND THE PANEL IS ALUMINUM AND THE ATTACHIN	G RIVETS ARE DASH 5 MODELS.  I BELIEVE THE ACT OF INSTALLING THESE HARD RIVETS AIDS IN THE FAILURE OF THESE PANELS.			1	G	7	1 	3U				H3WE    					 
1997030600701	19970306	00701	WP  	1997	3	6	97ZZZX924        	1	19970210	G	7160	369H8011	BELL MOUNT      			HUGHES	369   	369D        	4470706	WP  										ENGINE INLET	DETERIORATED    	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				FOUND ON REMOVAL OF THE ENGINE THAT THE INLET BELL MOUNT WAS NO LONGER PLIABLE, BUT RIGID AND BRITTLE.  REPLACED WITH NE	W PART.					1	G	7	1 	3U				H3WE    					 
1997030600724	19970306	00724	EU  	1997	3	6	97ZZZX947        	1	19970201	G	3212	C178131	HOSE            			BOLKMS	105   	BO105S      	5626006	EU  										FLOAT	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5059C					S779				HIGH FAILURE RATE OF NR 1 AND NR 4 HOSES ON BO-105S FLOATS D24873-101 AND 102 DUE TO KINKS.  REPLACED HOSES.						1	G	7	2 	3U				H3EU    					 
1997030600725	19970306	00725	EU  	1997	3	6	97ZZZX948        	1	19970114	G	3212	C178131	HOSE            			BOLKMS	105   	BO105S      	5626006	EU  										FLOAT	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	826MB					S771				HIGH FAILURE RATE OF NR 1 AND NR 4 HOSES ON BO-105S FLOATS, P/N D24873-101 AND 102 DUE TO KINKS.  REPLACED HOSES.						1	G	7	2 	3U				H3EU    					 
1997030600840	19970306	00840	EU  	1997	3	6	97ZZZX952        	1	19970121	G	5511	315A3510000101	SPAR            			AEROSP	SA316 	SA315B      	8680615	EU  										HORIZ STAB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	27443				MR368	2426				SPAR TUBE CRACKED AT RT MOUNTING HOLE, CRACK ORIGINATES AT MOUNTING HOLE AND EXTENDS IN BOTH DIRECTIONS COVERING 50 PERC	ENT OF TUBE CIRCUMFERENCE.  THIS DEFECT WAS FOUND WHEN THE STABILIZER WAS BROUGHT IN FOR REPAIR OF WORN MOUNT BUSHING. T	HIS CRACK COULD NOT BE SEEN AS IT IS COVERED BY HALF SHELL REINFORCEMENTS.  SUBMITTER SUGGESTS CAUSE AS LACK OF PREVENTI	VE MAINTENANCE, NOT FOLLOWING INSPECTION SCHEDULES.  T/R OUT OF BALANCE FOR EXTENDED PERIODS.			1	G	7	1 	4U				H1IN    					 
1997030600841	19970306	00841	EU  	1997	3	6	97ZZZX953        	1	19970204	G	6320	350A32106320	GASKET          		350A32011000	SNIAS 	350   	AS350B2     	8680813	EU  										EPICYCLIC	MISFIT          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	6084W	1103 				2672				THESE PARTS WHEN RECEIVED FROM A.E.C., ARE TOO SMALL IN DIAMETER TO CORRECTLY FIT.  AMER EUROCOPTER SAYS TO SOAK THE GAS	KET OR TO TEAR THE OUTSIDE PART OF THE BOLT HOLES TO MAKE IT FIT.  AFTER TRYING TO GET THE GASKET TO SWELL BY SOAKING, T	HE GASKET STILL TORE.  AMER EURO IS AWARE OF PROBLEM BUT AS OF LAST PHONE CALL, IS NOT GOING TO CORRECT THE PROBLEM OF B	AD FITTING GASKETS.  NOTE:  SUBMITTER ALSO REPORTED THE SAME DEFECT WAS NOTED ON 3-22-96 ON N6095U, SAME MAKE/MODEL OF A	/C.  NO M OR D SUBMITTED AT THAT TIME.		1	G	7	1 	3U				H9EU    					 
1997030600842	19970306	00842	GL  	1997	3	6	97ZZZX954        	2	19970129	G	7321	252464429	FUEL CONTROL    	BENDIX      		BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	STUCK           	B			OG5R	R				AUTOROTATION            				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			GL	21	188ND		16   		319777	3992	CAE270376			DURING AUTOROTATION FLIGHT TRAINING, INSTRUCTER ROLLED THROTTLE TO IDLE.  N1 WENT PAST 60 PERCENT N1 IDLE SPEED TO 52 PE	RCENT.  FOUND PR/PG SHAFT NOT WORKING.  SHAFT WOULD NOT FOLLOW CAM ON SHAFT TO ALLOW PR/PG VALVE TO OPEN OR PREVENT UNDE	RSHOOTING IDLE.  RPM OF 60 PERCENT N1.  SUSPECT RUSHING AROUND SHAFT CAME OUT OF POSITION AND ALLOWED CAM TO BEND SHAFT 	IN FUEL CONTROL.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997030600845	19970306	00845	GL  	1997	3	6	97ZZZX957        	2	19970211	G	7250	6898735	TURBINE         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	NOZZLE DAMAGE   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	40AP	8066 	1098 		37363	825D	833309			GROUND PERSONNEL NOTICED NOISE COMING FROM ENGINE DURING START-UP AND SHUT DOWN BETWEEN 20 PERCENT AND 60 PERCENT N1 RPM	.  THE ENGINE RAN NORMAL AT GROUND IDLE.  UPON DISASSEMBLY OF THE ENGINE, THE CAUSE OF THE NOISE WAS FOUND TO BE EXCESSI	VE HEAT DAMAGE TO THE NR 1 TURBINE NOZZLE AND NR 1 TURBINE WHEEL ALONG WITH SUBSEQUENT DAMAGE TO THE REMAINING TURBINE. 	 SUBMITTER SUGGESTED CAUSE WAS A DEFECTIVE FUEL NOZZLE SINCE NO REPORTS OF A HOT START WERE RECORDED.			1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997030600847	19970306	00847	GL  	1997	3	6	97ZZZX959        	3	19970213	G	6114	B4486	MOUNT STUD      			CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03								713633		ALIGNMENT DOWEL STUDS WERE BROKEN BELOW HUB MOUNTING FACE SURFACE.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997030600848	19970306	00848	SO  	1997	3	6	97ZZZX960        	2	19970211	G	8520		CRANKCASE       								CONT  	O360  	IO360C      	17025	SO  					NR 2 CYL BASE	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01							060656R			FACTORY REMANUFACTURED ENGINE:  OPENED CRATE TO INSTALL ENGINE.  FOUND CRACK IN CRANKCASE REAR NR 2 TOP CYLINDER BASE ST	UD.  CRACK APPROXIMATELY .6250 INCH LONG.  ZERO TIME ON ENGINE.										3	O			E1CE				 
1997030600851	19970306	00851	GL  	1997	3	6	97ZZZX963        	1	19970203	G	5542	2055400000	RUDDER          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										TOP TE SKIN	DAMAGED         	D				K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			NM	11	10UV	1418 				10037				DURING A 100 HOUR INSPECTION, NOTED THE TOP CORNER OF THE TRAILING EDGE OF THE RUDDER WAS DAMAGED (APPARENTLY FROM BEING	 PUSHED BACKWARDS) CAUSING SKINS TO SEPARATE FROM THE CENTER FILL MATERIAL (OR CORE). THE DAMAGE IS 1.25 INCHES DOWN FRO	M THE TOP ALONG THE TRAILING EDGE AND .75 INCH FORWARD OF TRAILING EDGE ALONG TOP OF RUDDER.  NO DAMAGE EVIDENT AT HINGE	 OR MOUNTING AREA.			1	L	7	1 	3O			NT	TA4CH   					 
1997030600852	19970306	00852	EA  	1997	3	6	97ZZZX964        	2	19970129	G	8530	ECLW12988CP	CYLINDER        			ENSTRM	F28   	F28C        	3300407	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					NR 2	FAILED          	H	L		GWHV	A				UNSCHED LANDING         				A			FLAME/FIRE                			NR	NOT REPORTED   	1			SW	09	51774	568  			06	440	L1970051A			ON A NIGHT TRAINING FLIGHT, NR 2 CYLINDER BLEW OUT ABOVE THE EXHAUST PORT.  THE BLOW-OUT STEERED THE NR 4 CYLINDER OIL L	INE AND STARTED A FIRE.  AN EMERGENCY LANDING WAS ACCOMPLISHED WITHOUT INJURY TO THE INSTRUCTOR OR THE STUDENT, HOWEVER,	 THE AIRCRAFT WAS COMPLETELY DESTROYED BY FIRE.  SUBMITTER STATES HAVE HAD TWO OTHER SIMILAR FAILURES OF THESE CERMICROM	E CYLINDERS ON THIS ENGINE IN THE LAST 127 HOURS.  (TOTAL OF 3.)			1	G	7	1 	3O	3	O		H1CE    	1E10				 
1997030600853	19970306	00853	CE  	1997	3	6	97ZZZX965        	1	19970107	G	5320	12121281	BRACKET         			CESSNA	210   	T210L       	2073449	CE  										TAIL ASSY LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2074S	3694 				21061041				DURING A REPLACEMENT OF A TAIL TIE-DOWN RING AND AFT TAIL CONE BULKHEAD ASSY, P/N 1212130-2 AT STA 230.187, CRACKS WERE 	FOUND ON BOTH LT AND RT SUPPORT BRACKETS.  THESE BRACKETS ARE PART OF THE HORIZONTAL STABILIZER SUPPORT ON AFT SIDE UNDE	R P/N 1212128-1 AND DASH 2. THE CRACK LOOKS LIKE IT WAS CAUSED BY TOO MUCH CLEARANCE BETWEEN SUPPORT BRACKET P/N 1212128	-1 AND HORIZONTAL STABILIZER AFT BRACKET P/N 12324000-1.  NEW  PARTS WILL BE INSTALLED WITH PARTICULAR ATTENTION TO CLEA	RANCE BETWEEN PARTS.		1	H	7	1 	3O				3A21    					 
1997030600854	19970306	00854	CE  	1997	3	6	97ZZZX966        	1	19970107	G	5320	12121282	BRACKET         			CESSNA	210   	T210L       	2073449	CE  										TAIL ASSY RT	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2074S	3694 				21061041				DURING A REPLACEMENT OF A TAIL TIE-DOWN RING AND AFT TAIL CONE BULKHEAD ASSY, P/N 1212130-2 AT STA 230.187, CRACKS WERE 	FOUND ON BOTH LT AND RT SUPPORT BRACKETS.  THESE BRACKETS ARE PART OF THE HORIZONTAL STABILIZER SUPPORT ON AFT SIDE UNDE	R P/N 1212128-1 AND DASH 2. THE CRACK LOOKS LIKE IT WAS CAUSED BY TOO MUCH CLEARANCE BETWEEN SUPPORT BRACKET P/N 1212128	-1 AND HORIZONTAL STABILIZER AFT BRACKET P/N 12324000-1.  NEW  PARTS WILL BE INSTALLED WITH PARTICULAR ATTENTION TO CLEA	RANCE BETWEEN PARTS.		1	H	7	1 	3O				3A21    					 
1997030600855	19970306	00855	SO  	1997	3	6	97ZZZX967        	2	19970220	G	8530		CYLINDER        			BEECH 	35    	V35TC       	1151540	CE  	CONT  	O520  	TSIO520DB   	17040	SO  					ENGINE	WEAR            	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	222TB	361  				D8242	505012			DURING 100-HOUR INSPECTION, COMPRESSION CHECK REVEALED ALL SIX CYLINDERS LOW.  TOTAL TIME 360.5 HOURS SINCE RAM CONVERSI	ON TO STC SE3631SW ON ALL CYLINDERS.  SUSPECT OVERLEANING.					1	L	7	1 	3O	3	O		3A15    	E8CE				 
1997030600856	19970306	00856	SO  	1997	3	6	97ZZZX968        	2	19970115	G	7310	330996F80240	LINE            			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					ENGINE FUEL	LEAKING         	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	03	317C	218  				EA574	527213			ENGINE WOULD NOT IDLE ON FINAL.  PRESSURE CHECKED HOSE AND FOUND SEVERAL LEAKS.  (NOT VISIBLE WITH FIRE SLEEVE ON).  HOS	E DATE 4TH QUARTER '94.  A/C AIRWORTHINESS 2-95.					1	L	7	1 	3O	3	O		3A15    	E8CE				 
1997030600857	19970306	00857	GL  	1997	3	6	97ZZZX969        	3	19970213	G	6111		BLADE           			SLNSBY	T67   	T67M260     	8323006	EU  						HOFMAN	HOV123	HOV123KV    	GL  	PROPELLER BASE	DELAMINATION    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	31909	999  				2220		B640		INSPECTION OF PROPELLER FOUND A PROPELLER BLADE WITH DELAMINATION AT BASE OF BLADE.  (ONE INCH WIDE BY FOUR INCHES LONG)	.  CAUSE UNKNOWN.  AWAITING INFORMATION FROM HOFFMAN PROPELLER.					1	L	7	1 	3O			NT	A73EU   		5	C	P5EU2	 
1997030600858	19970306	00858	EU  	1997	3	6	97ZZZX970        	1	19970213	G	2810	T67G57007	TANK            			SLNSBY	T67   	T67M260     	8323006	EU  										LT WING ASSY	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	17	3045H	829  				2141				ON A PRE-FLIGHT INSPECTION, A FUEL STAIN WAS NOTICED ON BOTTOM OF LEFT WING.  FURTHER INSPECTION FOUND A CRACK ON THE FW	D INBOARD SIDE OF THE FUEL TANK.  SUBMITTER SUSPECTS POSSIBLE STRESS CRACK.  AWATING REPAIR FROM MANUFACTURER.					1	L	7	1 	3O			NT	A73EU   					 
1997030600859	19970306	00859	CE  	1997	3	6	97ZZZX971        	1	19970124	G	3230	58130441	CHANNEL         			CESSNA	404   	404CESSNA   	2075901	CE  										NLG ACT ATTACH	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	355HC	3029 				4040110				UPON ACCOMPLISHMENT OF CESSNA SB ME78-31 AND SK404-21 (REPLACEMENT OF NOSE GEAR ACTUATOR ALUMINUM ATTACH LUGS WITH STEEL	 ATTACH LUGS) FOUND BOTH CHANNELS TO WHICH LUGS ATTACH WERE CRACKED AT AFT CORNER RADII.  REPLACED CHANNELS.  SUSPECT CA	USE:  HARD LANDING, LANDING ON NOSE GEAR, POSSIBLE INCORRECT RIGGING OF NOSE GEAR WITH INSUFFICIENT PRELOAD OF ACTUATOR 	AGAINST DRAG BRACE; THUS, CAUSING SHOCK LOADS TO BE TRANSMITTED THROUGH ACTUATOR TO ATTACH STRUCTURE.			1	L	7	2 	3O				A25CE   					 
1997030600862	19970306	00862	CE  	1997	3	6	97ZZZX974        	1	19970205	G	2150		AIR INLET       			CESSNA	210   	P210N       	2073454	CE  										FS 172 AIR COND	EXH CONTAMINATED	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6262K					P21000395				DURING INSPECTION, EXHAUST RESIDUE WAS DISCOVERED IN TAIL CONE.  IT WAS DETERMINED THAT EXHAUST WAS ENTERING THROUGH THE	 CONDENSER AIR INLET INSTALLED FOR JB SYSTEMS, INC., AIR CONDITIONING STC NR SA71RM.  THIS INLET WAS COVERED, AND CESSNA	 LOUVERS AND DOUBLER INSTALLED IN UPPER LEFT SIDE OF FUSELAGE IAW CESSNA DRAWING NR 2101029.				1	H	7	1 	3O				3A21    					 
1997030600863	19970306	00863	SO  	1997	3	6	97ZZZX975        	2	19970220	G	8530		VALVE           			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NR 1 CYL	WORN            	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	6457B	825  				21032768	269711R			DURING 100 HOUR INSPECTION, FOUND NR 1 CYLINDER READING 20/80 DURING COMPRESSION CHECK, ALSO, ALL OTHER CYLINDERS IN LOW	 SIXTIES.  TOTAL TIME 824.8 HOURS SINCE TCM.  ZERO TIME REBUILD.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997030600864	19970306	00864	SO  	1997	3	6	97ZZZX976        	2	19970205	G	8530	649543A1	VALVE           			CESSNA	150   	150K        	2071822	CE  	CONT  	O200  	O200A       	17020	SO  					EXH NR 2	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	21	6474G	1270 				15071974	285158R			DURING FLIGHT, PILOT EXPERIENCED ROUGH RUNNING AND POWER LOSS UPON INSPECTION OF CYLINDERS.  FOUND NO COMPRESSION NR 2 C	YLINDER.  REMOVED CYLINDER, FOUND PISTON HEAD DAMAGED AND EXHAUST VALVE HEAD MISSING.  VALVE STEM SEIZED IN GUIDE.  SUBM	ITTER STATED NEEDS BETTER OILING OF VALVE STEM FOR EXHAUST VALVE.				1	H	7	1 	3O	3	O		3A19    	E252				 
1997030600865	19970306	00865	SO  	1997	3	6	97ZZZX977        	2	19970220	G	8530		CYLINDER        			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					ENGINE	WORN            	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	677PC	794  				P21000677	278685R			DURING 100 HOUR INSPECTION, COMPRESSION CHECK REVEALED ALL SIX CYLINDERS LOW AS FOLLOWS:  35/57/50/51/49/51.  CUSTOMER R	EPORTED USING 1 QUART PER HOUR PRIOR TO INSPECTION.  REGULAR SOAP AT 50-HOUR OIL CHANGE REVEALED NO MAJOR PROBLEMS.  TOT	AL TIME 793.8 HOURS SINCE TCM.  ZERO TIME REBUILD.  SUBMITTER SUSPECTS OVERLEANING.				1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997030600866	19970306	00866	SO  	1997	3	6	97ZZZX978        	1	19970211	G	3211	6705403	TRUNNION        			PIPER 	PA28  	PA28RT201   	7102818	SO  										NLG	CRACKED         	B			AIHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	8109D	3301 				28R8018014				NOSE GEAR TRUNNION ASSY HAS SEVERE CRACK WHERE DOWNLOCK LINK ATTACHES WITH BOLT.  REPLACED TRUNNION WITH NEW ASSY.						1	L	7	1 	3O				2A13    					 
1997030600867	19970306	00867	SO  	1997	3	6	97ZZZX979        	1	19970211	G	2910	1114	LINE            	STRATOFLEX  		PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG ACTUATOR	LEAK            	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	16	824CH	102  				318252055				LT NR 534 2Q96.  ASSY DATE 9/96.  INSTALL DATE 9-26-96.  PILOT REPORTED LANDING GEAR NOT GOING UP AND LOCKED.  FOUND RES	ERVOIR LOW.  FOUND UP AND DOWN LINES AT LT GEAR ACTUATOR LEAKING.  ALSO, FOUND ONE HOSE ON RT MAIN ACTUATOR LEAKING.  PR	ESSURE CHECK CONFIRMED LEAK THROUGH HOSE WALL.  ALL HOSES SAME LOT NUMBER AND CURE DATE.  MANUFACTURED BY PROFESSIONAL A	VIATION ASSOCIATES			1	L	7	2 	3O				A20SO   					 
1997030600868	19970306	00868	EA  	1997	3	6	97ZZZX980        	2	19970124	G	8530	STD148	UNION           		LW13561     	BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					CYLINDER DRAIN	DETACHED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	928PT		600  			P174	L122259			CYLINDER DRAIN FITTING CAME OUT OF HEAD.  DRAIN LINE WAS STILL ATTACHED.  THIS CAUSED ERRONEOUS READINGS ON SENSE SYSTEM	.					1	L	7	2 	3O	3	O		A12CE   	E10EA				 
1997030600869	19970306	00869	CE  	1997	3	6	97ZZZX981        	1	19970124	G	7810	77928	PIPE            		77944       	BEECH 	60    	A60         	1153604	CE  										NR 3 CYLINDER	BLOWN           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	928PT					P174				EXHAUST PIPE AT CYLINDER NR 3 BLEW HOLE IN BOTTOM OF PIPE CAUSING MANIFOLD PRESSURE TO GO TO NON-BOOST.						1	L	7	2 	3O				A12CE   					 
1997030600871	19970306	00871	WP  	1997	3	6	97ZZZX983        	2	19970212	G	7250	30720681	BLADE           			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					NR 2 ENG NR 3 LP	SEPARATED       	D		A		E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			GL	05	73B					79	P73298			THE NR 2 ENGINE WAS SHUT DOWN DURING CLIMB-OUT DUE TO EXCESSIVE VIBRATIONS.  INITIAL FINDS DURING TEAR DOWN INDICATE THA	T SEVERAL BLADES SEPARATED FROM THE NR 3 L.P.T.  THIS CAUSED SEVERE VIBRATIONS THAT, IN TURN, CAUSED THE N2 SECTION TO R	UB.				2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997030600873	19970306	00873	WP  	1997	3	6	97ZZZX985        	2	19970212	G	7210		BELLVILLE WASHER			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					PLANETARY GEAR	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	174B					142	P73279			600 HOUR SOAP SAMPLE INDICATED HIGH METAL CONTENT.  SUSPECT FROM THE PLANET GEARS.  INSPECTION INDICATED BELLVILLE WASHE	R WAS SPINNING.  PLANET GEARSHAFT AND WASHER REPLACED.  ENGINE WAS APPROXIMATELY 600 HOURS OUT OF MPI.					2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997030600874	19970306	00874	CE  	1997	3	6	97ZZZX986        	1	19970214	G	5610	10138402518	WINDSHIELD      		96152H8779  	BEECH 	200   	200BEECH    	1152920	CE  										COPILOT	SMOKED          	B			DEBR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CE	03	300JK	150  				BB532				PILOT REPORTED HEAVY SMOKE IN COCKPIT.  INSPECTED AND FOUND L.P. TERMINAL AT WINDSHIELD HAD HIGH RESISTANCE WHICH CAUSED	 SMOKE AND FIRE IN COCKPIT.  REPLACED WINDSHIELD WITH NEW.  OPERATION CHECKED GOOD.					1	L	7	2 	4T				A24CE   					 
1997030600875	19970306	00875	CE  	1997	3	6	97ZZZX987        	1	19970205	G	5610	10138402516	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  										COPILOT INNER	SHATTERED       	G		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			GL	13	59AH	1689 				FA197				COPILOT'S WINDSHIELD INNER PANE OF GLASS SHATTERED IN-FLIGHT AT 35,000 FEET.  AN UNEVENTFUL LANDING WAS MADE AT THE NEAR	EST AIRPORT TEN MINUTES LATER.  WINDSHIELD WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	4T				A24CE   					 
1997030600876	19970306	00876	CE  	1997	3	6	97ZZZX988        	1	19970201	G	5210	551151515	HINGE           			CESSNA	441   	441         	2076020	CE  										CABIN DOOR	BROKEN          	B		A	PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	592G					4410361				DURING PREFLIGHT, FOUND THE AFT LOWER CABIN DOOR HINGE BROKEN IN TWO PIECES AT THE LOCATION OF THREE RIVETS INSTALLED TH	ROUGH THE HINGE AND DOOR FRAME.  NEW HINGE ASSY INSTALLED.					1	L	7	2 	3T			RT	A28CE   					 
1997031300063	19970313	00063	EU  	1997	3	13	97ZZZX993        	1	19970102	G	6310	4638202007	FREEWHEEL       			BOLKMS	105   	BO105S      	5626006	EU  										M/R DRIVE	SLIPPAGE        	B	L		AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50588	1613 			3204	S780				FREEWHEEL UNIT ERRATIC AND SLIPPAGE NOTED.  COULD ONLY FIND SPRAG WEAR ON OUTBOARD SIDE.						1	G	7	2 	3U				H3EU    					 
1998010800060	19980108	00060	GL  	1998	1	8	98ZZZX1          	2	19971205	G	7313	47086	FILTER          								ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										FUEL NOZZLE FILTER SCREEN WAS FOUND WITH UNKNOWN SUBSTANCE, CONTAMINATED 50 PERCENT OF SCREEN AREA.  SUGGEST INSPECTING 	FUEL PUMP FUEL FILTER FOR POSSIBLE BLOCKAGE CAUSING FUEL PUMP TO GO TO FILTER BYPASS.										3	U			E4CE				 
1998010800069	19980108	00069	GL  	1998	1	8	98ZZZX10         	1	19971101	G	7931	K3PS4020	SWITCH          			AMTR  	2+2   	NORTHMAN22  	05620MC	GL  										OIL PRESSURE	LEAK            	D				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			SW	99	239PT	149  				597				OIL PRESSURE SWITCH USED TO TURN ON FLIGHT TIME RECORDER ('HOBBS" METER) BEGAN TO LEAK OIL FROM ONE ELECTRICAL TERMINAL.	  A FEW DROPS OF OIL WERE NOTICED WHILE PRE-FLIGHTING FOR A 2-1/2 HOUR RETURN FLIGHT.  AFTER RETURNING, THERE WAS A LARG	E OIL LEAK.  ENGINE WAS 3 QUARTS LOW.  TESTING SWITCH INDICATES LARGE OIL LEAK AT ELECTRIC TERMINAL.				1	H	7	1 	3O			NT	EXPA1H71					 
1998010800153	19980108	00153	SO  	1998	1	8	98ZZZX100        	2	19971214	G	7414	6310	MAGNETO         	SLICK       		CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					RT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	06	6831M	1000 				2106994	554901			RIGHT MAGNETO DEAD.  OPENED MAG, FOUND COPPER AND CARBON DUST EVERYWHERE.  FOUND BLOCK AND GEAR BEARINGS WORN SEVERELY A	ND GEAR DAMAGED, TEETH VERY SHARP DUE TO MISALIGNMENT OF LARGE GEAR.  MAGS WERE NOT INSPECTED AT 500-HOUR INSPECTION AS 	RECOMMENDED.				1	H	7	1 	3O	3	O		3A21    	E5CE				 
1998031200102	19980312	00102	EA  	1998	3	12	98ZZZX1001       	2	19971220	G	7322	RSA5AD1	SERVO           	BENDIX      		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					FUEL INJECTOR	CORRODED        	B		A	OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	4561H	1196 			70137	240767				CORROSION FOUND INSIDE FUEL INJECTOR SERVO DIAPHRAGM SECTION WAS IMPEDING MOVEMENT OF DIAPHRAGM RESTRICTING FUEL FLOW. S	UBMITTER SUSPECTED WATER LAYING IN THIS AREA CORRODING SMALL SECTION OF INJECTOR HOUSING CAUSED GROWTH OF CORROSION DEPO	SIT.  LAB REPORT ON CORROSION SENT TO PHILA FSDO.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1998031200103	19980312	00103	CE  	1998	3	12	98ZZZX1002       	1	19971016	G	5511	0432160	SPAR            			CESSNA	140   	140         	2071602	CE  										HORIZONTAL STAB	MISSING         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	13	76512	2526 				10944				REINFORCEMENT CHANNEL/SPAR WAS MISSING/NOT INSTALLED.  IT APPEARED THE SPAR HAD NEVER BEEN INSTALLED FROM THE FACTORY.						1	H	7	1 	3O			NC	A768    					 
1998010800154	19980108	00154	SO  	1998	1	8	98ZZZX101        	1	19971218	G	3246	40106	WHEEL           			PIPER 	PA31T 	PA31T       	7103124	SO  										LT MLG OUTBOARD	BROKEN          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	515BA	3600 				31T8120044				POST-FLIGHT REVEALED BROKEN OUTBOARD WHEEL HALF ON LEFT MAIN.						1	L	7	2 	3T				A8EA    					 
1998031200116	19980312	00116	CE  	1998	3	12	98ZZZX1014       	1	19971229	G	3710	212CW	PUMP            			CESSNA	210   	210L        	2073448	CE  										VACUUM SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	732DZ	1103 			5AC2164	21061446				VACUUM PUMP FAILED.  SUBMITTER STATED ROUTINE WEAR CAUSED BY OPERATION HOURS.						1	H	7	1 	3O				3A21    					 
1998031200706	19980312	00706	SW  	1998	3	12	98ZZZX1016       	1	19970120	G	6320	K94120107	OIL PUMP        		K974002009  	KAMAN 	K1200 	K1200       	05625F6	SW  										M/R GEARBOX	FAILED          	H			OWVL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	134KA				0017	A940006				HAD TO REMOVE TRANSMISSION FOR DAMAGED OIL PUMP DRIVE GEAR CAUSED FROM OIL PUMP SEIZURE (NO SHEAR SHAFT ON OIL PUMP).  D	ATE OF INCIDENT 1-20-97.					1	G	7	1 	4F			NT	TR7BO   					 
1998010800155	19980108	00155	EA  	1998	1	8	98ZZZX102        	2	19971218	G	7414	4381	MAGNETO         	SLICK       		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					LT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	94112	182  				15285600	L2295415			INSTALLED TWO NEW 4381 MAGNETOS ON AN ENGINE REBUILD.  LEFT MAG ROTATING MAGNET APPEARS TO HAVE FAILED DUE TO FACTORS UN	KNOWN.  RESULT IS A BENT SHAFT AT THE IMPULSE COUPLING.  NO DAMAGE TO DRIVE GEARS NOTED.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1998031200711	19980312	00711	SO  	1998	3	12	98ZZZX1021       	1	19970811	G	2913	31800002	POWER PAK       			PIPER 	PA23  	PA23160     	7102304	SO  										HYDRAULIC SYSTEM	RUPTURED        	C	L	A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			NE	05	6918		700  		2799	232038				UPON LANDING ROLL-OUT, RT MAIN AND NOSE GEAR COLLAPSED.  DROP CHECK IN HANGAR WITH HAND PUMP SHOWED NO ABNORMALITIES DUR	ING OPERATION.  POWER PAK REMOVED AND SENT FOR TEAR DOWN INSPECTION.  THEY FOUND BLOW HOLE IN MAIN HOUSING CASTING AT PO	PPET HOLE.  EITHER FATIGUED OR A THIN WALL DEFECT EXISTED TO CAUSE BLOW-OUT RESULTING IN SYSTEM PRESSURE GOING BACK TO R	ESERVOIR OF POWER PAK.			1	L	7	2 	3O				1A10    					 
1998031900261	19980319	00261	CE  	1998	3	19	98ZZZX1057       	1	19971022	G	3213	105384001	SHOCK STRUT     			BEECH 	76    	76          	1153005	CE  										MLG	JAMMED          	D		A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	05	6010W				0637	ME98				BOLTS ATTACHING THE UPPER SHOCK STRUT ASSY TO THE UPPER GEAR HOUSING HAD SEVERE STRESS IN THE THREAD AREA.  THIS WAS CAU	SED BY REPEATED OPERATIONS IN FLIGHT TRAINING.  BOLTS FAILED ALLOWING GEAR LEG TO EXTEND AND UPON RETRACTION, JAMMED ON 	LOWER WING SKIN RESULTING IN A GEAR-UP (2 EXTENDED) LANDING.  SUBMITTER SUGGESTED REMOVING BOLTS PERIODICALLY TO CHECK T	HREAD AREA FOR DISTRESS.  HAVE FOUND 6 OTHERS IN FLEET TO HAVE SAME DAMAGE TO THREADS.			1	L	7	2 	3O				A29CE   					 
1998031900278	19980319	00278	WP  	1998	3	19	98ZZZX1071       	2	19970912	G	7200		ENGINE          			ISRAEL	1124  	1124A       	4500103	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					RT ENGINE	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SO	09	849HS	3992 				344	P77437			DURING A TOUCH AND GO LANDING, CONDUCTED FOR CREW PROFICIENCY TRAINING, THE RIGHT ENGINE FAILED SHORTLY AFTER TAKEOFF PO	WER WAS SET ON BOTH ENGINES.					2	M	7	2 	4F	4	F		A2SW    	E6WE				 
1998031900279	19980319	00279	NE  	1998	3	19	98ZZZX1072       	2	19971020	G	7230	50A126	BEARING         			BOEING	777   	777222      	1385219	NM  	PWA   	PW4077	PW4077      		NE  					NR 3 MAIN	FAILED          	B			WA2D	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			NE	03		123  					P777079			LOW OIL PRESSURE MESSAGE APPEARED AFTER LANDING IN BEIJING.  GROUND INSPECTION FOUND METAL IN FILTER AND CHIP DETECTORS.	  DISASSEMBLY INSPECTION FOUND NR 3 MAIN BEARING FAILURE.  BEARING ROUTED TO PRATT & WHITNEY ENGINEERING FOR INVESTIGATI	ON.  CUSTOMER:  ALL NIPPON AIRWAYS OF JAPAN.  CYCLES, 46.				2	L	7	2 	4F	4	F	RT	T0001SE 	E46NE				 
1998031900595	19980319	00595	CE  	1998	3	19	98ZZZX1086       	1	19971125	G	7810	1099500001	EXHAUST STACK   			BEECH 	90    	C90A        	1152911	CE  										RT ENG INBD	CRACKED         	B			KO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1568X	230  				LJ1368				RT ENGINE INBOARD EXHAUST STACK CRACKED AT DEICE TUBE.  PART TT 229.6 HOURS.						1	L	7	2 	3T			RT	3A20    					 
1998010800411	19980108	00411	SW  	1998	1	8	98ZZZX109        	1	19971218	G	6120	8954752	CAM ASSY        	AIRESRCH    	8954812     	GULSTM	690TP 	690B        	7630516	SW  										PROP PITCH CNTRL	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	690HT		2138 		P680	11467				DURING ENGINE REPAIR RESULTING FROM CATASTROPHIC FAILURE OF PROPELLER GOVERNOR, DISSASSEMBLY OF PROPELLER PITCH CONTROL 	REVEALED SEVERE WEAR OF CAM SLOT AND PIN ON SLEEVE ASSY 869647-5.  THERE IS LITTLE DOUBT THAT THIS ASSY WOULD HAVE FAILE	D LONG BEFORE SCHEDULED INSPECTION AT 3,600 HOURS.  FAILURE OF THIS ASSY WILL RESULT IN LOSS OF PROPELLER CONTROL.				1	H	7	2 	3T				2A4     					 
1998010800070	19980108	00070	NM  	1998	1	8	98ZZZX11         	1	19971211	G	7830		COWL            			DOUG  	MD11  	MD11F       	3023600	NM  										RT T/R COWL	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	105EV	13628				48544				INSPECTION FOUND NR 2 ENGINE T/R COWL RT DAMAGED.  ALSO FOUND TRANSLATING COWL RT LOWER SIDE DAMAGE ABOUT 10 CM BY 8 CM 	WHEN TRANSIT IN ANC.  REPLACED RT HALF OF BOTH FAN COWL AND TRANSLATING COWL.					2	L	7	3 	4F			RT	A22WE   					 
1998010800412	19980108	00412	SO  	1998	1	8	98ZZZX110        	1	19971110	G	3230	6716800	SPRING          			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG STRUT	FAILED          	D		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			WP	01	36458					28R7837279				WHILE IN-FLT, PILOT REPORTED LOUD BANG.  WHEN LANDING GEAR SELECTED, NLG WOULD NOT DOWN AND LOCK.  UPON LANDING, NLG RET	RACTED.  NLG DID NOT LOCK DUE TO INNER SPRING BREAKING.  WHEN THE INNER SPRING BROKE AT UPPER HOOK END, THIS BROKEN END 	CAUGHT OUTER SPRING COIL 2/3 OF THE LENGTH OF THE SPRING JAMMING OUTER SPRING AND CAUSING IT TO REMAIN AT A LENGTH OF 11	 INCHES INSTEAD OF A CLOSED LENGTH OF 8 INCHES.  THIS CAUSED  OUTER SPRING TO BEND INTO A V-SHAPE PREVENTING OUTER SPRIN	G FROM PULLING NLG TO A DOWN AND LOCKED POSITION.  SUBMITTER STATED INNER SPRING BREAKING AND BENDING OUTER SPRING IS A 	UNIQUE SITUATION.  SUBMITTER SUGGESTED A REPLACEMENT TIME IN HRS OR CALENDAR TIME.	1	L	7	1 	3O				2A13    					 
1998010800413	19980108	00413	SO  	1998	1	8	98ZZZX111        	1	19970910	G	3233	357972	ACTUATOR        			PIPER 	PA28  	PA28RT201T  	7102817	SO  										NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	2251M				1282	28P7931001				NOSE GEAR ACTUATOR BROKEN AT AFT ATTACH HOLE (BOLT HOLE).  COULD HAVE BROKEN WHEN NOSE GEAR WAS FORCED DOWN AFTER ACCIDE	NT.					1	L	7	1 	3O				2A13    					 
1998010800414	19980108	00414		1998	1	8	98ZZZX112        	4	19971218	G	6122	8954908	GOVERNOR        	WOODWARD    		GULSTM	690TP 	690B        	7630516	SW  										PROPELLER	FAILED          	D		A		D	E			RETURN TO BLOCK         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			GL	25	690HT		2138 			11467				BETA LIGHT FLICKERED IN-FLIGHT.  NO OTHER DISCREPANCIES ON NEXT DEPARTURE DURING TAXI OPERATION .  PROPELLER WENT TOWARD	 COURSE PITCH UNCOMMANDED.  ITT WENT TO RED LINE, PILOT SHUT ENGINE DOWN.  INTERNAL FAILURE OF PROP GOV RESULTED IN META	L EXITING THE PROP GOV THRU OIL PASSAGES.  CLOGGED NTS CHECK VALVE WHICH ELIMINATED OIL SUPPLY TO NEGATIVE SIDE OF TORQU	E SENSOR.  PLUGGED ADAPTER 3101708 ELIMINATING OIL SUPPLY TO POSITIVE SIDE OF TORQUE SENSOR, PLUGGED TURBINE BEARING OIL	 JET, CONTAMINATED FEATHER VALVE WHICH COMPLETELY DISABLED IT MAKING IT IMPOSSIBLE FOR NTS SYSTEM TO FUNCTION AND PROP C	OULD NOT BE FEATHERED MANUALLY.	1	H	7	2 	3T				2A4     					 
1998032600306	19980326	00306	EA  	1998	3	26	98ZZZX1127       	2	19971213	G	8530		CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 1	FAILED          	H				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SO	21	99295	1620 				17276429	L1383239A			FOLLOWING 45 MINUTES OF FLIGHT, ENGINE BECAME ROUGH.  CARBURETOR HEAT APPLIED, BUT ROUGHNESS THE SAME.  APPLIED FULL POW	ER AND RETURNED AND ON SHORT FINAL, TOWER REPORTED HEAVY SMOKE.  INSPECTION FOUND ENGINE HAD ONLY 3 QUARTS OF OIL LEFT. 	 NR 1 CYLINDER PISTON NICKED AND HEAD CRACKED.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1998032600307	19980326	00307	CE  	1998	3	26	98ZZZX1128       	1	19970315	G	2434	646843	ALTERNATOR      			BEECH 	33    	F33A        	1151425	CE  										WINDING	FAILED          	G				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			GL	03	3058S				G009230	CE1099				PILOT EXPERIENCED ELECTRICAL SYSTEM FAILURE.  MADE EMERGENCY LANDING WITHOUT INCIDENT.  FOUND ALTERNATOR FAILED.						1	L	7	1 	3O				3A15    					 
1998010800415	19980108	00415	SO  	1998	1	8	98ZZZX113        	1	19971219	G	2710		BOLT            			PIPER 	PA28  	PA28181     	7102807	SO  										AILERON	WRONG PART      	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15	4511F					287790037				DURING A CUSTOMER REQUESTED AILERON RIGGING CHECK, DISCOVERED THE AFT BOLTS ON BOTH AILERON BELLCRANKS WERE CHAFING ON T	HE AILERON CONTROL ROD AS AILERONS WERE MOVED.  ALL 4 BOLTS CONNECTING THE AILERON CABLES TO THE BELLCRANKS WERE AN23-12	.  AN EXAMINATION OF THE CURRENT PARTS MANUAL REVEALED THE CORRECT BOLT TO BE INSTALLED SHOULD BE A PIPER PN 402-669 (NA	S1103-7D BOLT).  THERE IS A STRENGTH DIFFERENCE BETWEEN THESE TWO BOLTS AS WELL AS A LENGTH DIFFERENCE.  THE AN23-12 IS 	.0625 INCH LONGER THAN THE NAS1103-7D.		1	L	7	1 	3O				2A13    					 
1998010800416	19980108	00416	SO  	1998	1	8	98ZZZX114        	2	19971014	G	8520	SA649520A3	CAMSHAFT        			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	GALLED          	B			EBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	401GS	168  				401A0063	2063570E			LIFTER/CAMSHAFT GALLED.  LIFTER BODY CHIP FOUND IN OIL FILTER.  PRESSURE RELIEF VALVE CAUSING LOW OIL PRESSURE.  ENGINE 	TORN DOWN, NEW PARTS INSTALLED.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1998010800417	19980108	00417	SO  	1998	1	8	98ZZZX115        	2	19971014	G	8520	SA646277	LIFTER          			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE	GALLED          	B			EBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	401GS	168  				401A0063	2063570E			LIFTER/CAMSHAFT GALLED.  LIFTER BODY CHIP FOUND IN OIL FILTER.  PRESSURE RELIEF VALVE CAUSING LOW OIL PRESSURE.  ENGINE 	TORN DOWN, NEW PARTS INSTALLED.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1998010800418	19980108	00418	CE  	1998	1	8	98ZZZX116        	1	19971004	G	7602	5038901021	CONTROL CABLE   			BEECH 	55    	95A55       	1152704	CE  										ENGINE MIXTURE	FAILED          	B			EBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	12CM	57   				TC300				MIXTURE CABLE FAILED ON SHUT DOWN AFTER FLIGHT.  NO PREVIOUS INDICATION OF PROBLEM. INSPECTION SHOWED UNDER SHEATH WELD 	BROKE THAT SECURES SOLID END TO CABLE PORTION.  CANNOT INSPECT HERE DUE TO SHEATH COVERING.  NEW SAME PART NUMBER INSTAL	LED.				1	L	7	2 	3O			 	3A16    					 
1998010800419	19980108	00419		1998	1	8	98ZZZX117        	4	19970515	G	3457	KLX135	GPS             			HOACAU	HK36R 	HK36R       	4170002	EU  										COCKPIT	MISWIRED        	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	400HK				2320	36400				CUSTOMER PURCHASED GPS UNIT FROM AIRCRAFT SPRUCE AND SPECIALTY CO.  UPON INSTALLATION IN AIRCRAFT, FOUND UNIT IMPROPERLY	 WIRED.  WIRED IAW ALLIED SIGNAL INSTALLATION MANUAL AND FOUND UNIT TO OPERATE TO SPECIFICATION.  MANUAL NR 006-10500-00	01.  SUBMITTER RECOMMENDED THAT AVIONICS SHOPS WIRING SYSTEMS REFER TO INSTALLATION  MANUAL AND TEST WIRING HARNESS BEFO	RE DELIVERING TO CUSTOMER.  ALSO, NO MAINTENANCE RELEASE WAS DELIVERED WITH UNIT.			1	K	7	1 	3O			RC	G51EU   					 
1998032600615	19980326	00615	CE  	1998	3	26	98ZZZX1173       	1	19971201	G	5610	5111604202	WINDSHIELD      			CESSNA	421   	421C        	2076016	CE  										COPILOT	DEPARTED        	D				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	05	88584	7500 				421C0642				AS THE AIRCRAFT LEVELLED OFF AT 23,000 FEET MSL, THE COPILOT'S WINDSHIELD DEPARTED THE AIRCRAFT WITH ONLY APPROXIMATELY 	10 PERCENT REMAINING ATTACHED TO THE AIRFRAME.  SPECULATING THAT THE CRACK ORIGINATED AT THE RIGHT LOWER CORNER AND WENT	 STRAIGHT UP TO THE TOP OF THE WINDSHIELD.  SUBMITTER STATED TO PREVENT, SHOULD HAVE RECURRING INSPECTION.  REF:  MEB 83	-33R.			1	L	7	2 	3O				A7CE    					 
1998032600621	19980326	00621		1998	3	26	98ZZZX1179       	4	19971231	G	2562	EBC102A	ELT             			PIPER 	J3    	PA11        	7101102	SO  										COCKPIT	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	5532H				570146	111035				THE ELT DID NOT ACTIVATE ON IMPACT.  IT DID TEST USING AN AM RADIO AFTER TURNING ON MANUALLY.  THE DATE ON THE BATTERY W	AS DUE DECEMBER, 1993.					1	H	7	1 	3O				A691    					 
1998010800071	19980108	00071	SO  	1998	1	8	98ZZZX12         	2	19971210	G	7421	RHB32E	SPARK PLUG      	CHAMPION    		CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					ELECTRODE	SHORTED         	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			SO	14	4667Q					21059567	294623R			UPON INSTALLING NEW SPARK PLUGS, THE ENGINE RAN ROUGH.  WHEN INSPECTING THE SPARK PLUGS, THREE WERE FOUND MILLED IMPROPE	RLY AND SMALL SLIVERS OF METAL SHORTING THE CENTER ELECTRODE.					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1998010800845	19980108	00845	NE  	1998	1	8	98ZZZX123        	2	19970112	G	7250	3360097040	SHAFT           								GE    	CFM56 	CFM565A     	13802	NE  					LPT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		2365 	1543 				731101			AXIAL CRACK 30CM LONG BEGINNING IN A HOLE AFTER THE THREAD AND GOING FROM THE REAR OF THE SHAFT AND DEFORMATION OF THE S	HAFT.  PARTS CURRENTLY UNDER SNECMA/CFMI INVESTIGATION.										4	F			E29NE				 
1998010800846	19980108	00846	WP  	1998	1	8	98ZZZX124        	2	19971224	G	7250	3072316	DISC HUB        								GARRTT	TFE731	TFE7313     	01518	WP  					HPT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		2540 					P76759			FOUND HPT DISC HUB CRACKED DURING NDT INSPECTION AT MAJOR PERIODIC INSPECTION.											4	F			E6WE				 
1998040200002	19980402	00002	EU  	1998	4	2	98ZZZX1240       	1	19971124	G	6520	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R GEARBOX	DEFECTIVE       	B			FBLR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17										TAIL ROTOR BEARING IS DEFECTIVE PER SL 1337-65-97, DATED 11-24-97.						1	G	7	1 	3U				H9EU    					 
1998010800847	19980108	00847	CE  	1998	1	8	98ZZZX125        	1	19971215	G	3230	KP16BS	BEARING         	FAFNIR      		BEECH 	200   	200BEECH    	1152920	CE  										MLG TORQ TUBE	FROZEN          	B			MZ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	202AJ	10900				BB511				INVESTIGATION OF LANDING GEAR RETRACT MECHANISM REVEALED SQUEELING NOISE IN AREA OF TORQUE TUBE UNIVERSAL JOINT JUST OUT	SIDE FUSELAGE ON RIGHT SIDE.  THE KP16BS BEARING WAS FOUND FROZEN/RUSTED IN ITS SUPPORT PLATE WHILE THE SHAFT ADAPTER PN	 101-810021-9, SPUN ON THE BEARINGS NON-BEARING SURFACE. A NEW BEARING AND ADAPTER WERE INSTALLED AND THE AIRCRAFT RETUR	NED TO SERVICE.			1	L	7	2 	4T				A24CE   					 
1998040200423	19980402	00423	NE  	1998	4	2	98ZZZX1257       	1	19971218	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76         	8143010	NE  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	705AL	3588 	440  		A08601843	760267				DISCOVERED DURING 500-HOUR INSPECTION, FOUND M/R BLADE SKIN CRACKED AT FORWARD EDGE OF TRIM TAB.						1	G	7	2 	3U				H1NE    					 
1998040200424	19980402	00424	NE  	1998	4	2	98ZZZX1258       	1	19971201	G	3213	7333FT160N	SEAL            		1945E100B   	SKRSKY	S76   	S76         	8143010	NE  										MLG LOWER CYL	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	705AL	2747 				760267				IN FIELD 12-97, OIL LEAKING FROM STRUT AND PROBLEM SERVICING STRUT.  STRUT WOULD NOT ACTUATE PROPERLY.  FOUND LOW OIL LE	VER IN CYLINDER PREVENTING PROPER ACTUATING OF PISTON HEAD SNUBBER.  THIS ALLOWED UNCONTROLLED EXTENSION OF STRUT PISTON	 DURING AIRCRAFT LIFT-OFF AND HAMMERING OF PISTON HEAD AGAINST EXTENSION STOP AND SHEARING OF PISTON HEAD RETAINING PINS	.  THIS ALLOWED PISTON TO SEPARATE FROM PISTON HEAD.  PISTON JAMMED PISTON HEAD IN TOP OF STRUT CYLINDER AND PREVENTED P	ROPER MOVEMENT OF PISTON IN STRUT CYLINDER.		1	G	7	2 	3U				H1NE    					 
1998040200425	19980402	00425	GL  	1998	4	2	98ZZZX1259       	2	19971106	G	7210	406340104101	GARLOCK SEAL    		23035155    						ALLSN 	250C  	250C28B     	03013	GL  					PTO AFT AREA	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03					CAG70295					NEW PTO SEALS WERE INSTALLED IN REPAIRED GEARBOX.  ENGINE WAS ASSEMBLED AND TESTED ON 11-06-97.  AFTER TEST CELL RUN, FO	UND AFT PTO SEAL BROKEN AT INNER LIP.  NEW PTO SEALS ARE NOT AT SAME DIMENSIONS AS OLD (RED) PTO SEALS.  NEW PTO SEALS A	RE LARGER IN DIAMETER MAKING INSTALLATION EXTREMELY HARD AND CAUSING SEAL TO BOW AND CAUSE LEAKAGE.  SUBMITTER SUGGESTED	 CHANGE DIAMETER OF SEALS TO MATCH THOSE OF THE OLD (RED) SEALS.								3	U			E1GL				 
1998010800848	19980108	00848	SO  	1998	1	8	98ZZZX126        	1	19971222	G	3520	8336102	OXYGEN UNIT     	SCOTT       		GULSTM	G1159 	G1159A      	3970109	SO  										CABIN	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	721FF	948  			0158	421				WHILE PERFORMING CABIN OXYGEN SYSTEM TEST, FOUND TEN MASKS IN SIX  PRESENTATION UNITS WITH NO OXYGEN FLOW AFTER PULLING 	LANYARD.  UNITS ARE MANUFACUTRED BY SCOTT AVIATION.					2	L	7	2 	4F				A12EA   					 
1998040200428	19980402	00428	EU  	1998	4	2	98ZZZX1262       	1	19970823	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										ENG TACHOMETER	FAILED          	B			YWYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	126TV	513  				2944				TACHOMETER INDICATOR READ INTERMITTENTLY LOW.						1	G	7	1 	3U				H9EU    					 
1998040200429	19980402	00429	EU  	1998	4	2	98ZZZX1263       	1	19970823	G	6520	704A33633171	SPHERICAL STOP  			SNIAS 	350   	AS350B2     	8680813	EU  										T/R	DEFECTIVE       	B			YWYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	126TV	513  				2944				BULGES IN T/R SPHERICAL STOP.						1	G	7	1 	3U				H9EU    					 
1998010800849	19980108	00849	SO  	1998	1	8	98ZZZX127        	1	19971222	G	3520	8336102	OXYGEN UNIT     	SCOTT       		GULSTM	G1159 	G1159A      	3970109	SO  										CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	721FF	948  			0177	421				WHILE PERFORMING CABIN OXYGEN SYSTEM TEST, FOUND TEN MASKS IN SIX  PRESENTATION UNITS WITH NO OXYGEN FLOW AFTER PULLING 	LANYARD. UNITS ARE MANUFACUTRED BY SCOTT AVIATION.					2	L	7	2 	4F				A12EA   					 
1998040200441	19980402	00441	GL  	1998	4	2	98ZZZX1274       	2	19971107	G	7210	406340104101	GARLOCK SEAL    		23053349    	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					PTO FWD SEAL	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03					CAG95832					NEW PTO SEALS INSTALLED IN REPAIRED GEARBOX ON 9-23-97.  ENGINE WAS ASSEMBLED AND TESTED ON 11-07-97.  DURING TEST RUN, 	FOUND FORWARD PTO SEAL LEAKING.  NEW PTO SEALS ARE LARGER IN DIAMETER THAN (RED) PTO SEALS PN 524919.  UPON INSTALLATION	, SEALS ARE EXTREMELY TIGHT CAUSING SEALS TO BOW AND CAUSE LEAKAGE.				1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
1998041000032	19980410	00032	NM  	1998	4	10	98ZZZX1279       	1	19970604	G	3231	267222	VALVE BODY      		2670296     	BOEING	747   	747121      	1384871	NM  										NLG DOOR SEQ	LEAKING         	B	S		IU6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01					PA02					NLG SEQUENCE VALVE LEAKING FROM PIN HOLE AT BASE OF DN PORT.						2	L	7	4 	4F				A20WE   					 
1998010800850	19980108	00850	SO  	1998	1	8	98ZZZX128        	1	19971222	G	3520	8336102	OXYGEN UNIT     	SCOTT       		GULSTM	G1159 	G1159A      	3970109	SO  										CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	721FF	948  			0176	421				WHILE PERFORMING CABIN OXYGEN SYSTEM TEST, FOUND TEN MASKS IN SIX  PRESENTATION UNITS WITH NO OXYGEN FLOW AFTER PULLING 	LANYARD.  UNITS ARE MANUFACUTRED BY SCOTT AVIATION.					2	L	7	2 	4F				A12EA   					 
1998010800851	19980108	00851	SO  	1998	1	8	98ZZZX129        	1	19971222	G	3520	8336102	OXYGEN UNIT     	SCOTT       		GULSTM	G1159 	G1159A      	3970109	SO  										CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	721FF	948  			0175	421				WHILE PERFORMING CABIN OXYGEN SYSTEM TEST, FOUND TEN MASKS IN SIX  PRESENTATION UNITS WITH NO OXYGEN FLOW AFTER PULLING 	LANYARD.  UNITS ARE MANUFACUTRED BY SCOTT AVIATION.					2	L	7	2 	4F				A12EA   					 
1998010800072	19980108	00072	CE  	1998	1	8	98ZZZX13         	1	19971203	G	3510	1015601401	TUBE ASSY       			BEECH 	200   	B200        	1152922	CE  										OXYGEN SYSTEM	LEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	63791	6533 				BB1100				OXYGEN SYSTEM LEAK.  INSPECTION FOUND B-NUT CRACKED AT AFT BULKHEAD ATTACHMENT (3 PLACES).  FURTHER INSPECTION REVEALED 	B-NUT AT T-FITTING ATTACHMENT CRACKED IN 2 PLACES.					1	L	7	2 	4T				A24CE   					 
1998010800852	19980108	00852	SO  	1998	1	8	98ZZZX130        	1	19971222	G	3520	8336102	OXYGEN UNIT     	SCOTT       		GULSTM	G1159 	G1159A      	3970109	SO  										CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	721FF	948  			0173	421				WHILE PERFORMING CABIN OXYGEN SYSTEM TEST, FOUND TEN MASKS IN SIX  PRESENTATION UNITS WITH NO OXYGEN FLOW AFTER PULLING 	LANYARD.  UNITS ARE MANUFACUTRED BY SCOTT AVIATION.					2	L	7	2 	4F				A12EA   					 
1998010800853	19980108	00853	SO  	1998	1	8	98ZZZX131        	1	19971222	G	3520	8336102	OXYGEN UNIT     	SCOTT       		GULSTM	G1159 	G1159A      	3970109	SO  										CABIN	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	721FF	948  			0172	421				WHILE PERFORMING CABIN OXYGEN SYSTEM TEST, FOUND TEN MASKS IN SIX  PRESENTATION UNITS WITH NO OXYGEN FLOW AFTER PULLING 	LANYARD.  UNITS ARE MANUFACUTRED BY SCOTT AVIATION.					2	L	7	2 	4F				A12EA   					 
1998041000068	19980410	00068	CE  	1998	4	10	98ZZZX1315       	1	19971105	G	2820	714144	FUEL LINE       			BBAVIA	8     	8KCAB       	2110612	CE  										HEADER TANK	LEAKING         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	276R	100  				71393				PILOT REPORTED ODOR OF FUEL IN THE COCKPIT.  INSPECTION REVEALED FUEL SEEPAGE WHERE THE TUBE ASSEMBLY CONNECTS TO THE TE	E AT THE HEADER TANK INLET (THIS IS THE TUBE ASSY FROM THE LEFT WING TANK).  THE FLARE WAS FOUND TO HAVE AN OUTSIDE DIAM	ETER LARGER THAN THE ASSOCIATED M520819 SLEEVE AND THE TUBE ASSEMBLY WAS EXCESSIVELY MISALIGNED WITH THE TEE CAUSING EXC	ESSIVE PRELOAD RESULTING IN DAMAGE TO THE TUBE DURING ASSEMBLY.  GOOD STANDARD PRACTICE WOULD PREVENT THIS KIND OF DAMAG	E.		1	H	7	1 	3O			 	A21CE   					 
1998010800856	19980108	00856		1998	1	8	98ZZZX134        	4	19971201	G	6122	C290D3FT1	GOVERNOR        																	PROPELLER	MISREPAIRED     	B			DJFR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23					741856					AT DISASSEMBLY FOR OVERHAUL, FOUND UNAPPROVED REPAIRS TO THE MAIN HOUSING IDLER GEAR PUMP SOCKET.  THE IDLER GEAR STUD F	ELL OUT WHEN TURNED UPSIDE DOWN.  THIS IS TO BE A PRESSURE FIT. THE STUD WAS STAKED IN 4 PLACES BY USE OF PRICK PUNCH. A	LSO FOUND SEVERE SCORING OF THE PUMP WALLS.																	 
1998010800857	19980108	00857	EA  	1998	1	8	98ZZZX135        	2	19971215	G	8530	LW14077	PISTON PIN      								LYC   	O360  	LO360E1A6   	41514	EA  					CYLINDER ASSY	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11		280  			17328		L51072T			INSPECTION FOUND PISTON PIN BROKEN AFFECTED BY AD 97-15-11.											3	O			E286				 
1998041000128	19980410	00128	GL  	1998	4	10	98ZZZX1351       	1	19970708	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	236  				752				THROTTLE CONTROL CABLE INTERNAL BINDING CAUSES PARTIAL TO FULL LOSS OF THROTTLE CONTROL.  UNIT IN SERVICE 12 WEEKS.						1	G	7	1 	3O			 	H1CE    					 
1998010800858	19980108	00858	SO  	1998	1	8	98ZZZX136        	2	19971222	G	8520	6524201048	STUD            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					NR 1 CYL BASE	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	2159S	1268 				347970144	306804			NOTICED BASE NUT AND PART OF STUD MISSING ON TOP REAR STUD LOCATION OF NR 1 CYLINDER.  NUT HAD COME OFF OTHER END OF STU	D.  STUD HAD FAILED AT CYLINDER BASE FLANGE.  ENGINE OVERHAULED BY MATTITUCK 1,267 HOURS PREVIOUSLY.  UNKNOWN IF STUD WA	S NEW THEN.  (PART IS COMMONLY CALLED A THRU-BOLT).				1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1998010800860	19980108	00860	SO  	1998	1	8	98ZZZX138        	2	19971223	G	8520	538811	BOLT            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					CRANKCASE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	869CB					421B0863	235117H			DURING ROUTINE 50-HOUR EXHAUST SYSTEM INSPECTION, NOTED BOLT AT RIGHT SIDE FORWARD LOWER CRANKCASE JUST ABOVE OIL PAN ST	ICKING OUT AND TOUCHING EXHAUST CROSS-OVER TUBE.  REMOVED TUBE, FOUND HEAD OF BOLT POPPED OFF.  BOLT HEAD OR WASHER PN 4	01507 COULD NOT BE LOCATED IN COWLING.  INSTALLED NEW BOLT AND WASHER, TORQUED 165 INCH/POUND PER ENGINE OHM.  THIS ENGI	NE IS AN AVIALL OVERHAULED ENGINE FOR TCM COMPLETED 5/89.  BOLT SIZE:  .3750 INCH - 16 INCHES BY 5.25 INCHES LONG.			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1998010800861	19980108	00861	CE  	1998	1	8	98ZZZX139        	1	19971110	G	2810	4149200223	FLUSH VENT      			BEECH 	36    	A36         	1151604	CE  										RT FUEL TANK	BLOCKED         	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	13	66514	2600 				E1522				PILOT REPORTED A SUDDEN LOSS OF ENGINE POWER RESULTING IN AN OFF-AIRPORT LANDING.  ON SITE EXAMINATION REVEALED NO OBVIO	US DEFECTS.  THE ENGINE WAS RE-STARTED, AND RAN FLAWLESSLY.  THE PILOT TOOK OFF AND RETURNED TO BASE WITHOUT FURTHER INC	IDENT.  UPON DETAILED EXAMINATION OF FUEL SYSTEM, THE RT FUEL TANK FLUSH VENT WAS FOUND BLOCKED BY WHAT APPEARED TO BE A	N INSECT NEST.  A SIMILAR LOSS OF POWER HAD BEEN EXPERIENCED TWICE BEFORE IN PREVIOUS YEARS WITH THE SAME FINDINGS.			1	L	7	1 	3O				3A15    					 
1998041000247	19980410	00247	SW  	1998	4	10	98ZZZX1391       	1	19970602	G	7712	H19437	INDICATOR       			KAMAN 	K1200 	K1200       	05625F6	SW  										TORQUE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	436  			138A	A940019				TORQUE INDICATOR'S FIRST LED SEGMENT WILL NOT ILLUMINATE.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000248	19980410	00248	SW  	1998	4	10	98ZZZX1392       	1	19970429	G	2121	K986127001	FAN ASSY        			KAMAN 	K1200 	K1200       	05625F6	SW  										CABIN HEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA					940019				CABIN HEAT FAN ASSY INOPERABLE.  PART TT:  233.8 HOURS.  SUSPECT CAUSE:  ENGINE BLEED AIR PASSES THROUGH FAN ASSY TRANSF	ERRING HEAT TO BEARINGS.					1	G	7	1 	4F			NT	TR7BO   					 
1998041000249	19980410	00249	SW  	1998	4	10	98ZZZX1393       	1	19970508	G	2121	K986127001	FAN ASSY        			KAMAN 	K1200 	K1200       	05625F6	SW  										CABIN HEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA					940019				CABIN HEAT FAN ASSY HOT AND VIBRATION.  PART TT:  47.3 HOURS.  BEARING FAILURE.  SUSPECT CAUSE:  ENGINE BLEED AIR PASSES	 THROUGH FAN ASSY TRANSFERRING HEAT TO BEARINGS.					1	G	7	1 	4F			NT	TR7BO   					 
1998041000250	19980410	00250	SW  	1998	4	10	98ZZZX1394       	1	19970617	G	2121	K986127001	FAN ASSY        			KAMAN 	K1200 	K1200       	05625F6	SW  										CABIN HEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA					940019				CABIN HEAT FAN ASSY HOT AND VIBRATION.  BEARING FAILURE.  PART TT:  257.8 HOURS.  SUSPECT CAUSE:  ENGINE BLEED AIR PASSE	S THROUGH FAN ASSY TRANSFERRING HEAT TO BEARINGS.					1	G	7	1 	4F			NT	TR7BO   					 
1998041000251	19980410	00251	SW  	1998	4	10	98ZZZX1395       	1	19970604	G	6320	1D1326	CHIP DETECTOR   			KAMAN 	K1200 	K1200       	05625F6	SW  										TRANSMISSION OIL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	457  				940019				REMOVAL FOR NORMAL INSPECTION FOUND PHENOLIC RING MISSING FROM TIP.  TT:  456.9 HOURS.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000253	19980410	00253	SW  	1998	4	10	98ZZZX1397       	1	19970708	G	6320	K978113003	OIL TANK        			KAMAN 	K1200 	K1200       	05625F6	SW  										XMSN OIL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA					940019				TRANSMISSON OIL TANK CRACK ON TOP AT VENT LINE FITTING.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000255	19980410	00255	SW  	1998	4	10	98ZZZX1399       	1	19970821	G	6220	KRP168004F	IDLERCRANK BRG  			KAMAN 	K1200 	K1200       	05625F6	SW  										LT RED BLADE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	917  				940019				IDLERCRANK BEARING FAILURES FOUND DURING NORMAL INSPECTION.						1	G	7	1 	4F			NT	TR7BO   					 
1998010800073	19980108	00073	EU  	1998	1	8	98ZZZX14         	1	19971128	G	5753	T700A5755060000	CARRIER         			SOCATA	TBM   	TBM700      	8682000	EU  										FLAP BEARING	CRACKED         	B			CB5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	79Z	789  				19				WHILE CARRYING OUT A 100-HOUR REPETITIVE INSPECTION IAW DGAC AD 94-110, AND SB 70-048-57, IT WAS NOTED THAT ALL 4 FLAP B	EARING CARRIAGES WERE CRACKED.  THE CRACKS WERE NOT LOCATED IN THE INSPECTION AREAS SHOWN IN THE SB 70-048-57, BUT WERE 	LOCATED IN THE WEBS. ALL 4 FLAP BEARING CARRIAGES WERE REPLACED WITH MODIFIED ITEMS BEFORE FURTHER FLIGHT.				1	L	7	1 	3T			RT	A60EU   					 
1998010800862	19980108	00862	CE  	1998	1	8	98ZZZX140        	1	19971226	G	3242	7515	PLATE           	PARKERHANFIN		CESSNA	337   	337A        	2075704	CE  										LT BRAKE	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	09	9739D	3800 				3370466				UPON LANDING, LEFT BRAKE CALIPER TORQUE PLATE BROKE AT UPPER REAR BOLT ATTACH HOLE CAUSING BRAKE CALIPER TO SHIFT INTO T	HE INSIDE OF THE BRAKE DISC CAUSING THE LEFT WHEEL TO LOCK UP.  THE TORQUE PLATE IS DRILLED OVERSIZED AND THEN BUSHED DO	WN TO ACCEPT AXLE ATTACH BOLT.  THE OVERSIZED HOLE REDUCES THE HOLE EDGE DISTANCE CONSIDERABLY.				1	H	7	2 	3O				A6CE    					 
1998041000256	19980410	00256	SW  	1998	4	10	98ZZZX1400       	1	19970821	G	6220	KRP168004F	IDLERCRANK BRG  			KAMAN 	K1200 	K1200       	05625F6	SW  										LT WHITE BLADE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	963  				940019				IDLERCRANK BEARING FAILURES FOUND DURING NORMAL INSPECTION.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000257	19980410	00257	SW  	1998	4	10	98ZZZX1401       	1	19970827	G	6220	KRP168004F	IDLERCRANK BRG  			KAMAN 	K1200 	K1200       	05625F6	SW  										LT RED BLADE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	315  				940019				IDLERCRANK BEARING FAILURES FOUND DURING NORMAL INSPECTION.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000258	19980410	00258	SW  	1998	4	10	98ZZZX1402       	1	19970827	G	6220	KRP168004F	IDLERCRANK BRG  			KAMAN 	K1200 	K1200       	05625F6	SW  										LT WHITE BLADE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	269  				940019				IDLERCRANK BEARING FAILURES FOUND DURING NORMAL INSPECTION.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000259	19980410	00259		1998	4	10	98ZZZX1403       	4	19970918	G	3457	066040310111	GPS             			KAMAN 	K1200 	K1200       	05625F6	SW  										COCKPIT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	1059 			13462	940019				GPS LT CONTROL ROTOR KNOB STICKING.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000260	19980410	00260	SW  	1998	4	10	98ZZZX1404       	1	19970804	G	6730	107227003	DAMPER          			KAMAN 	K1200 	K1200       	05625F6	SW  										STABILIZER	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	313KA	807  			047	940019				STABILIZER DAMPER LEAKING AT SHAFT SEAL.  RECOMMENDATIONS:  ENGINE EXHAUST DIRECTED DOWN ON TAIL BOOM.  EXCESSIVE HEAT B	UILD UP CAUSING EXCESSIVE PRESSURE IN DAMPER.  DAMPER TOO HOT TO TOUCH.  RECOMMEND COOLING AIR TO DAMPER AND HEAT SHIELD	.				1	G	7	1 	4F			NT	TR7BO   					 
1998041000261	19980410	00261	SW  	1998	4	10	98ZZZX1405       	1	19970930	G	6730	107227003	DAMPER          			KAMAN 	K1200 	K1200       	05625F6	SW  										STABILIZER	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	313KA	309  			074	940019				STABILIZER DAMPER LEAKING AT SHAFT SEAL.  RECOMMENDATIONS:  ENGINE EXHAUST DIRECTED DOWN ON TAIL BOOM.  EXCESSIVE HEAT B	UILD UP CAUSING EXCESSIVE PRESSURE IN DAMPER.  DAMPER TOO HOT TO TOUCH.  RECOMMEND COOLING AIR TO DAMPER AND HEAT SHIELD	.				1	G	7	1 	4F			NT	TR7BO   					 
1998041000262	19980410	00262	SW  	1998	4	10	98ZZZX1406       	1	19971218	G	6730	107227003	DAMPER          			KAMAN 	K1200 	K1200       	05625F6	SW  										STABILIZER	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	313KA	283  			082	940019				STABILIZER DAMPER LEAKING AT SHAFT SEAL.  RECOMMENDATIONS:  ENGINE EXHAUST DIRECTED DOWN ON TAIL BOOM.  EXCESSIVE HEAT B	UILD UP CAUSING EXCESSIVE PRESSURE IN DAMPER.  DAMPER TOO HOT TO TOUCH.  RECOMMEND COOLING AIR TO DAMPER AND HEAT SHIELD	.				1	G	7	1 	4F			NT	TR7BO   					 
1998041000263	19980410	00263	SW  	1998	4	10	98ZZZX1407       	1	19970910	G	6240	K983126001	DUAL TACH       			KAMAN 	K1200 	K1200       	05625F6	SW  										ROTOR NEEDLE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	1030 			129	940019				DUAL TACH FAILED.  ROTOR NEEDLE INOPERATIVE.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000264	19980410	00264	SW  	1998	4	10	98ZZZX1409       	1	19971104	G	2550	K983157007	LOAD LINK       			KAMAN 	K1200 	K1200       	05625F6	SW  										EXTERNAL LOAD	ERRATIC         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	1257 				940019				EXTERNAL LOADS READING LIGHT ERRATIC.						1	G	7	1 	4F			NT	TR7BO   					 
1998010800863	19980108	00863	SO  	1998	1	8	98ZZZX141        	1	19971231	G	2730	12027655021	CONTROL CABLE   			EMB   	120   	EMB120ER    	3260203	SO  										BS 13945	FRAYED          	B			MZ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	PHMGH					1200149				DURING THE PERFORMANCE OF A 5A CHECK INSPECTION, THE AFT ELEVATOR CONTROL CABLE WAS FOUND FRAYED AT STA 13945.0.  THE CA	BLE WAS NOT IN CONTACT WITH ANY OTHER OBJECT IN THE AREA EXCEPT FOR THE PHENOLIC GUIDE.  NO WEAR WAS OBSERVED ON THE GUI	DE.  ACFT TT:  11,229.9 HOURS.  ACFT LANDINGS:  11,797.				2	L	7	2 	4T			RT	A31SO   					 
1998041000267	19980410	00267	SW  	1998	4	10	98ZZZX1412       	1	19970820	G	7712	APTE16775D	TRANSMITTER     			KAMAN 	K1200 	K1200       	05625F6	SW  										TORQUE	FLUCTUATIONS    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	912  			47554260	940019				PILOT REPORTED TORQUE INDICATOR FLUCTUATIONS 1.0 PSI TO 2.0 PSI.  RMEOVED S/N 4755-4-260.  TOTAL TIME 912.0 HOURS.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000268	19980410	00268	SW  	1998	4	10	98ZZZX1413       	1	19971230	G	7712	APTE16775D	TRANSMITTER     			KAMAN 	K1200 	K1200       	05625F6	SW  										TORQUE	FLUCTUATIONS    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	518  			49904109	940019				PILOT REPORTED TORQUE INDICATOR FLUCTUATIONS 1.0 PSI TO 2.0 PSI.  REMOVED S/N 4990-4-109.  TOTAL TIME 517.8 HOURS.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000269	19980410	00269	SW  	1998	4	10	98ZZZX1414       	1	19970621	G	7931	K983133001	INDICATOR       			KAMAN 	K1200 	K1200       	05625F6	SW  										ENG OIL PRESS	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	313KA	567  			706765	940019				PILOT REPORTED ENGINE OIL PRESSURE DROPPED TO ZERO.  NO CAUTION LIGHT.  INSTALLED NEW INDICATOR, OPERATION NORMAL.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000270	19980410	00270	SW  	1998	4	10	98ZZZX1415       	1	19970327	G	2550	H19432	INDICATOR       			KAMAN 	K1200 	K1200       	05625F6	SW  										LOAD ON HOOK	ERRATIC         	D				K				NONE                    				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	01	313KA				141B	940019				LOAD ON HOOK INDICATOR ERRATIC.  TT 71 HOURS.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000271	19980410	00271	SW  	1998	4	10	98ZZZX1416       	1	19970507	G	2550	H19432	INDICATOR       			KAMAN 	K1200 	K1200       	05625F6	SW  										LOAD ON HOOK	ERRATIC         	D				K				NONE                    				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	01	313KA				146B	940019				LOAD ON HOOK INDICATOR ERRATIC.						1	G	7	1 	4F			NT	TR7BO   					 
1998041000272	19980410	00272	SW  	1998	4	10	98ZZZX1417       	1	19971230	G	2550	H19432	INDICATOR       			KAMAN 	K1200 	K1200       	05625F6	SW  										LOAD ON HOOK	ERRATIC         	D				K				NONE                    				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	01	313KA				141B	940019				LOAD ON HOOK INDICATOR ERRATIC.  TT:  1,165 HOURS.						1	G	7	1 	4F			NT	TR7BO   					 
1998010800864	19980108	00864	GL  	1998	1	8	98ZZZX142        	3	19971212	G	6114	D4883C55	HUB             													MCAULY	2AF34C	2AF34C55    	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					723855			723855		UPON INSPECTION, HUB WAS FOUND CRACKED IN BLADE SOCKET NR 2, ROW 1, AND ROW 3.  HUB HAS BEEN SCRAPPED.																5	C	P5EA	 
1998041000783	19980410	00783	CE  	1998	4	10	98ZZZX1423       	1	19971105	G	2820	714144	FUEL LINE       			BBAVIA	8     	8KCAB       	2110612	CE  										HEADER TANK	LEAKING         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	276R	100  	25   			71393				PILOT REPORTED ODOR OF FUEL IN THE COCKPIT.  INSPECTION REVEALED FUEL SEEPAGE WHERE THE TUBE ASSEMBLY CONNECTS TO THE TE	E AT THE HEADER TANK INLET (THIS IS THE TUBE ASSY FROM THE LEFT WING TANK).  THE FLARE WAS FOUND TO HAVE AN OUTSIDE DIAM	ETER LARGER THAN THE ASSOCIATED M520819 SLEEVE AND THE TUBE ASSEMBLY WAS EXCESSIVELY MISALIGNED WITH THE TEE CAUSING EXC	ESSIVE PRELOAD RESULTING IN DAMAGE TO THE TUBE DURING ASSEMBLY.  GOOD STANDARD PRACTICE WOULD PREVENT THIS KIND OF DAMAG	E.		1	H	7	1 	3O			 	A21CE   					 
1998010800865	19980108	00865		1998	1	8	98ZZZX143        	4	19971215	G	2562	DEFT1	ELT             	DEFT        																G-SWITCH	FAILED          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09			650  		6452					ELT WAS REPAIRED 1-30-96 BY THE MFG, W.O. 1995.  UNIT SIGNAL 'SOUNDED' WEAK, AND THE G-SWITCH DID NOT ACTIVATE WITH EITH	ER A THROWING MOTION OR A SMACK AGAINST A SYSTEM OBJECT.																		 
1998010800867	19980108	00867	SO  	1998	1	8	98ZZZX145        	1	19970401	G	3222	6705002	STRUT ASSY      			PIPER 	PA32  	PA32301     	7103207	SO  										NLG	LOOSE           	B			EWCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	239A	202  				3246022				PLUG IN BOTTOM OF TUBE NOT SECURED BY BOLT THROUGH TUBE AND LANDING GEAR FORK.  AIRCRAFT WAS INVOLVED IN A GEAR UP LANDI	NG APPROXIMATELY 8 MONTHS AGO.					1	L	7	1 	3O				A3SO    					 
1998041700599	19980417	00599	SO  	1998	4	17	98ZZZX1457       	2	19971214	G	8500		ENGINE          			LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A658        	17003	SO  					POWER SECTION	MALFUNCTIONED   	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	03	72013	5147 	121  			3440	665171646			PILOT REPORTED ENGINE QUIT IN-FLIGHT, PILOT EXECUTED AN EMERGENCY OFF-AIRPORT LANDING.  MINOR DAMAGE TO AIRCRAFT.  ENGIN	E INSPECTED, BUT NOT DISASSEMBLED, ENGINE OIL WAS CLEAN, NO METAL FOUND IN OIL, 6 GALLONS OF FUEL (APPROX) FOUND IN TANK	S, ENGINE COMPRESSION APEARS NORMAL, ENGINE TURNS SMOOTH AND NORMAL NOT TIGHT FROM POSSIBLE LOCK-UP.  MAGNETO TIMER OK. 	 NO DISCREPANCIES FOUND.			1	H	7	1 	3O	3	O		A694    	E205				 
1998010800868	19980108	00868	SO  	1998	1	8	98ZZZX146        	1	19971222	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										RT HYDRAULIC	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	35816	440  			14933297	318052091				PILOT REPORTED TO MAINTENANCE THAT THE LANDING GEAR SLOW TO CYCLE.  HYDRAULIC PUMP CHECK PERFORMED.  RIGHT PUMP INOPERAB	LE.  UPON REMOVAL, FOUND RIGHT ENGINE DRIVEN HYDRAULIC PUMP SHAFT SHEARED.  OPENED PUMP ASSY FOR VISUAL INSPECTION AND F	OUND ONE OF THE TWO CHECK VALVE/RESTRICTORS MISSING FROM ITS PLACE.  FOUND PART OF MISSING CHECK VALVE/RESTRICTOR IN AIR	CRAFT HYDRAULIC FILTER.  BELIEVE THIS PART TO HAVE DISLODGED AND WENT THROUGH PUMP GEARS AND JAMMED THEM, 'SHEARING SHAF	T'.		1	L	7	2 	3O				A20SO   					 
1998010800869	19980108	00869	CE  	1998	1	8	98ZZZX147        	1	19971217	G	5540	MS244624	BEARING         			CESSNA	441   	441         	2076020	CE  										RUDDER HINGE	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4441T	4461 				4410133				UPON REMOVAL OF RUDDER FOR REPAIR TO RUDDER TOP AND MIDDLE RUDDER NEEDLE, BEARING ASSYS FELL APART, I.E., NEEDLES FELL O	UT.  PRESENTLY, CESSNA HAS NO INSPECTION INTERVALS FOR THESE BEARINGS.  THERE NEEDS TO BE SOME KIND OF INSPECTION INTERV	AL IN WHICH THE BEARINGS ARE INSPECTED AND LUBRICATED AT A SPECIFIC TIME.				1	L	7	2 	3T			RT	A28CE   					 
1998010800870	19980108	00870	SO  	1998	1	8	98ZZZX148        	2	19971212	G	8530	653454	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE NR 6	FAILED          	E				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			SW	05	577W	3    				TH375	287355R			DURING A FLIGHT JUST AFTER TAKEOFF, PILOT REPORTED THE ENGINE PERIODICALLY LOST POWER AND VIBRATED.  UPON LANDING, PILOT	 ALSO NOTICED A CONSIDERABLE AMOUNT OF OIL ON THE NACELLE.  UPON INVESTIGATION, DISCOVERED THE NR 6 CYLINDER PUSH ROD WA	S BENT AND PUSH ROD TUBE HAD BROKEN.  AFTER CYLINDER REMOVAL, IT WAS DETERMINED A SCREW HAD BEEN INJESTED INTO THIS CYLI	NDER.  GOOD HOUSEKEEPING PROCEDURES AND ACCOUNTABILITY OF HARDWARE DURING INSTALLATION WOULD REDUCE THE POSSIBILITY OF T	HIS IN THE FUTURE.		1	L	7	2 	3O	3	O		3A16    	E5CE				 
1998010800871	19980108	00871	CE  	1998	1	8	98ZZZX149        	1	19971213	G	2140	83D512	SOLENOID        			BEECH 	76    	76          	1153005	CE  										HEATER FUEL	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6046U	120  				ME195				COMPLAINT OF OVERHEAT AND SHUT DOWN OF HEATER DURING GROUND OPERATION.  INVESTIGATION OF HEATER OPERATION SHOWED HEATER 	NOT SHUTTING DOWN WITH TEMP CONTROL SWITCH.  FOUND FUEL SOLENOID NOT CLOSING.  OVERTEMP SENSOR WOULD THEN POP.  FOUND BL	ACK SEALANT INSIDE SOLENOID.  FACTORY (JANAERO DEVICES) NOTIFIED IMMEDIATELY.  THIS SOLENOID WAS ON NEW HEATER WITH 120.	3 HOURS SINCE NEW.			1	L	7	2 	3O				A29CE   					 
1998010800074	19980108	00074	EU  	1998	1	8	98ZZZX15         	1	19971128	G	5753	T700A5755060101	CARRIER         			SOCATA	TBM   	TBM700      	8682000	EU  										FLAP BEARING	CRACKED         	B			CB5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	79Z	789  				19				WHILE CARRYING OUT A 100-HOUR REPETITIVE INSPECTION IAW DGAC AD 94-110, AND SB 70-048-57, IT WAS NOTED THAT ALL 4 FLAP B	EARING CARRIAGES WERE CRACKED.  THE CRACKS WERE NOT LOCATED IN THE INSPECTION AREAS SHOWN IN THE SB 70-048-57, BUT WERE 	LOCTED IN THE WEBS. ALL 4 FLAP BEARING CARRIAGES WERE REPLACED WITH MODIFIED ITEMS BEFORE FURTHER FLIGHT.				1	L	7	1 	3T			RT	A60EU   					 
1998010800872	19980108	00872	SW  	1998	1	8	98ZZZX150        	1	19971201	G	7922	53E22144	VALVE           			MOONEY	M20   	M20E        	5870212	SW  										THERMO BYPASS	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11										RECEIVED PN 53E22144 AND INSTALLED, OIL TEMPERATURE PROBLEM.  REMOVED AND HAD TRUED PER SB 1316.  FURTHER INSPECTION SHO	WED NUT IMPROPERLY CRIMPED ON NEW VALVE, SEAT COULD NOT SIT SQUARELY ON NUT, NO THREADS PROTRUDED OUT THE TOP OF THE CRI	MPED NUT.  REPLACED WITH NEW VALVE THAT HAD THREADS OUT THE TOP OF THE NUT.				1	L	7	1 	3O				2A3     					 
1998010800873	19980108	00873	SO  	1998	1	8	98ZZZX151        	1	19971210	G	3230	4194902	ROD ASSY        			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	SEIZED          	D				K				NONE                    				P			NO WARNING INDICATION     			AP	APPROACH       	1			SO	17	36BM	3209 				318252008				CUSTOMER REPORTED THE LT MLG DOWNLOCK LIGHT DID NOT ILLUMINATE WHEN THE LANDING GEAR WAS EXTENDED.  AIRCRAFT LANDED WITH	OUT INCIDENT.  INSPECTION REVEALED THE PN 41949-02 LANDING GEAR LOCK ROD ASSY WAS SEIZED DUE TO LACK OF LUBRICATION PREV	ENTING THE DOWNLOCK HOOK FROM FULLY ENGAGING.  SUBMITTER STATED THE MM CALLS FOR A 100-HOUR LUBE.  A MORE FREQUENT LUBRI	CATION MIGHT BE ADVISABLE IN WET/CORROSIVE ENVIRONMENTS.			1	L	7	2 	3O				A20SO   					 
1998010800874	19980108	00874	SW  	1998	1	8	98ZZZX152        	1	19971201	G	2820		LINE            			MOONEY	M20   	M20C        	5870208	SW  										GASCOLATOR	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	78987	2600 				2021				DURING ANNUAL INSPECTION, FUEL LINE WAS FOUND CHAFED NEARLY THROUGH AT HALF-WAY POINT.  CHAFING CAUSED BY CARBURETOR HEA	T CONTROL CABLE WHICH PASSES CLOSE TO THIS LINE WHERE IT GOES THROUGH THE FIREWALL.  AREA IS VERY DIFFICULT TO INSPECT R	EQUIRING A MIRROR AND FLASHLIGHT.  CHAFING HAD BEEN OCCURRING FOR SOME TIME.  FUEL LINE WAS REMOVED, REPLACED, AND ANTI-	CHAFE MATERIAL APPLIED TO CARBURETOR HEAT CONTROL CABLE.			1	L	7	1 	3O				2A3     					 
1998010800875	19980108	00875	CE  	1998	1	8	98ZZZX153        	1	19971226	G	2720	151350013	SUPPORT ASSY    			CESSNA	337   	337A        	2075704	CE  										RUDDER BAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9739D					3370466				PILOT COMPLAINED OF INCONSISTENT RUDDER TRIM INPUTS TO MAINTAIN COORDINATED FLIGHT AND 'FUNNY' RUDDER CONTROL INPUTS.  I	NSPECTION REVEALED BOTH CENTER RUDDER BAR SUPPORTS CRACKED ALLOWING RUDDER BAR TO WANDER WHEREVER IT WANTED TO GO.  AIRC	RAFT HAS HISTORY OF LANDING ACCIDENTS WHEN REGISTERED IN A FOREIGN COUNTRY, BUT THIS IS A NEW DISCREPANCY WITH NO PREVIO	US CONTROL SYSTEM PROBLEMS.			1	H	7	2 	3O				A6CE    					 
1998010800876	19980108	00876	CE  	1998	1	8	98ZZZX154        	1	19971226	G	2720	151350014	SUPPORT ASSY    			CESSNA	337   	337A        	2075704	CE  										RUDDER BAR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9739D					3370466				PILOT COMPLAINED OF INCONSISTENT RUDDER TRIM INPUTS TO MAINTAIN COORDINATED FLIGHT AND 'FUNNY' RUDDER CONTROL INPUTS.  I	NSPECTION REVEALED BOTH CENTER RUDDER BAR SUPPORTS CRACKED ALLOWING RUDDER BAR TO WANDER WHEREVER IT WANTED TO GO. AIRCR	AFT HAS HISTORY OF LANDING ACCIDENTS WHEN REGISTERED IN A FOREIGN COUNTRY, BUT THIS IS A NEW DISCREPANCY WITH NO PREVIOU	S CONTROL SYSTEM PROBLEMS.			1	H	7	2 	3O				A6CE    					 
1998042400340	19980424	00340	SO  	1998	4	24	98ZZZX1546       	1	19971119	G	7603		CONTROL CABLE   			PIPER 	PA31T 	PA31T       	7103124	SO  										RT ENG THROTTLE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	155CA	7358 				31T7820024				RIGHT THROTTLE CABLE BROKE DURING ENGINE POWER UP.  PART TOTAL TIME:  7,358.0 HOURS.						1	L	7	2 	3T			 	A8EA    					 
1998010800877	19980108	00877	WP  	1998	1	8	98ZZZX155        	2	19971202	G	7261	8961734	OIL JET         		310180711   	MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					GEARBOX	BROKE           	B			DJFR	E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	46AK	3227 			P1767	754SA	P36103C			OIL JET BROKE AND LODGED ITSELF IN PLANETARIES AND RING GEAR.  RING GEAR BROKE AND COUPLER SHAFT SHEARED RESULTING IN EN	GINE SHUT DOWN.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
1998042400346	19980424	00346	SW  	1998	4	24	98ZZZX1552       	1	19971229	G	3260	ISE13	SWITCH          			GULSTM	112   	112TCA      	7630307	SW  										LT MLG DOWNLOCK	FAILED          	B			MCIR	O				OTHER                   				P			NO WARNING INDICATION     			CL	CLIMB          	1			WP	11	4708W	1520 				13302				LEFT MLG DOWNLOCK SWITCH FAILED TO CLOSE GIVING NO GEAR DOWN INDICATION.  FOUND SWITCH INOPERATIVE.  REPLACED SWITCH. AI	RCRAFT LANDED WITHOUT INCIDENT.  RECOMMEND STURDIER SWITCH.					1	L	7	1 	3O				A12SO   					 
1998042400351	19980424	00351	CE  	1998	4	24	98ZZZX1557       	1	19971125	G	5330	07133343	SKIN            			CESSNA	182   	182R        	2072731	CE  										LT FORWARD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	9557X	2758 				18268553				THE (FUEL CHECK) STEPS ARE MOUNTED WITH AN3 BOLTS ATTACHED TO THE ACFT'S SKIN, P/N 0713334-3, AND P/N 0713334-4, LEFT AN	D RIGHT FORWARD SKINS.  THE UPPER BACK BOLT WAS THROUGH THE SKIN AND THE BULKHEAD AT STA 1700.  THE USE OF THE STEP CAUS	ED THE BOLT TO BREAK THE FLANGE ON THE BULKHEAD AND CAUSED A CRACK IN THE OUTER SKIN THROUGH THE BOLT HOLE ABOUT 2 INCHE	S LONG.  THE UPPER FORWARD BOLT IS ATTACHED TO THE SKIN ONLY WITH AN OVERSIZED WASHER AND HAS SEVERELY DEFORMED THE OUTE	R SKIN AT THIS LOCATION.  SUBMITTER STATED THIS AREA NEEDS TO BE REINFORCED IF STEPS ARE TO BE USED.		1	L	7	1 	3O			NT	3A13    					 
1998042400352	19980424	00352	CE  	1998	4	24	98ZZZX1558       	1	19971125	G	5330	07133343	SKIN            			CESSNA	182   	182R        	2072731	CE  										RT FORWARD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	9557X	2758 				18268553				THE (FUEL CHECK) STEPS ARE MOUNTED WITH AN3 BOLTS ATTACHED TO THE ACFT'S SKIN, P/N 0713334-3, AND P/N 0713334-4, LEFT AN	D RIGHT FORWARD SKINS.  THE UPPER BACK BOLT WAS THROUGH THE SKIN AND THE BULKHEAD AT STA 1700.  THE USE OF THE STEP CAUS	ED THE BOLT TO BREAK THE FLANGE ON THE BULKHEAD AND CAUSED A CRACK IN THE OUTER SKIN THROUGH THE BOLT HOLE ABOUT 2 INCHE	S LONG.  THE UPPER FORWARD BOLT IS ATTACHED TO THE SKIN ONLY WITH AN OVERSIZED WASHER AND HAS SEVERELY DEFORMED THE OUTE	R SKIN AT THIS LOCATION.  SUBMITTER STATED THIS AREA NEEDS TO BE REINFORCED IF STEPS ARE TO BE USED.		1	L	7	1 	3O			NT	3A13    					 
1998010800878	19980108	00878	CE  	1998	1	8	98ZZZX156        	1	19971201	G	2820	26001017	LINE            			CESSNA	208   	208B        	2073701	CE  										LT/RT FUEL	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	410GV	397  				208B0632				FORWARD FUEL LINE COMING FROM THE WING AS IT ENTERS RESERVOIR TANK COMPARTMENT.  THERE ARE THREE AN3 BOLTS RETAINING A S	EAL IN THE SIDE WALL OF COMPARTMENT.  FORWARD BOLT CHAFING LINE, BOLT TURNED OUT TO BE AN3-4A, PARTS MANUAL CALLS FOR AN	3-3A.  BOTH SIDES OF AIRCRAFT REVEALED THE SAME DISCREPANCY.  AIRCRAFT TOTAL TIME 396.5. HOURS.				1	H	7	1 	3T				A37CE   					 
1998010800879	19980108	00879		1998	1	8	98ZZZX157        	4	19971222	G	3460	101741021	POWER SUPPLY    			AMD   	FALC50	FALCON2000  	2730170	NM  										FLT MGMT SYSTEM	FAILED          	B			QM1R	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	13	77A	660  				17				ON A TRANS-OCEANIC FLIGHT, THE NR 1 FMS CIRCUIT BREAKER TRIPPED.  UPON RESETTING BY THE AIR CREW, THE NR 1 FMS COMPUTER 	BEGAN TO SMOKE.  AIR CREW SHUT DOWN UNIT.  UNIT RETURNED TO MANUFACTURER FOR REPAIRS.  REPAIR BY MANUFACTURER REVEALED T	HE FAILURE WAS CAUSED BY THE INTERFACE BOARD, PN 00101765.				2	K	7	3 	4F			RT	A50NM   					 
1998042400766	19980424	00766	EU  	1998	4	24	98ZZZX1579       	1	19971017	G	6410	355A09103601	BEARING SET     			SNIAS 	350   	AS350B2     	8680813	EU  										T/R	DELAMINATION    	B			VY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	31AS	493  				2689				BEARING REMOVED DUE TO DELAMINATION IN EXCESS OF LIMITS.  REPLACED WITH NEW PART.						1	G	7	1 	3U				H9EU    					 
1998010800880	19980108	00880	CE  	1998	1	8	98ZZZX158        	1	19971217	G	5540	MS244624	BEARINGS        			CESSNA	441   	441         	2076020	CE  										RUDDER HINGE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	84LJ	4268 				4410084				UPON REMOVAL FOR STRIP AND PAINT, TOP AND MIDDLE RUDDER NEEDLE BEARING ASSYS FELL APART, I.E., NEEDLES FELL OUT.  UNITS 	WERE RUSTY ALSO.  SUBMITTER STATED PRESENTLY THERE IS NO INSPECTION INTERVALS FOR THESE BEARINGS.  AIRCRAFT HAS 4,268 HO	URS TT AT TIME OF OCCURRENCE.				1	L	7	2 	3T			RT	A28CE   					 
1998042400767	19980424	00767	EU  	1998	4	24	98ZZZX1580       	1	19971017	G	6520	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R	DELAMIANTED     	B			VY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	31AS	493  				2689				BEARING REMOVED DUE TO DELAMINATION IN EXCESS OF LIMITS.  REPLACED WITH NEW PART.						1	G	7	1 	3U				H9EU    					 
1998010800075	19980108	00075	EU  	1998	1	8	98ZZZX16         	1	19971128	G	5753	T700A5755063100	CARRIER         			SOCATA	TBM   	TBM700      	8682000	EU  										FLAP BEARING	CRACKED         	B			CB5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	79Z	789  				19				WHILE CARRYING OUT A 100-HOUR REPETITIVE INSPECTION IAW DGAC AD 94-110, AND SB 70-048-57, IT WAS NOTED THAT ALL 4 FLAP B	EARING CARRIAGES WERE CRACKED.  THE CRACKS WERE NOT LOCATED IN THE INSPECTION AREAS SHOWN IN THE SB 70-048-57, BUT WERE 	LOCTED IN THE WEBS. ALL 4 FLAP BEARING CARRIAGES WERE REPLACED WITH MODIFIED ITEMS BEFORE FURTHER FLIGHT.				1	L	7	1 	3T			RT	A60EU   					 
1999013000001	19990130	00001	GL  	1999	1	30	98ZZZX1648       	1	19971231	G	5102		GAS VALVE       			CAMRON	R420  	R420        		GL  										BALLOON ENVELOPE	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			WP	07	GJNEE	3    				4232				VALVE AND/OR VALVE INDICATOR SWITCH WORKED SPORADICALLY.  DURING FLIGHT, PILOT WAS UNABLE TO POSITIVELY VERIFY OPENING O	F VALVE WHEN VALVE LINE WAS PULLED.					1	B	0	0 	3X			NC	EXPA1B00					 
1999013000002	19990130	00002	GL  	1999	1	30	98ZZZX1649       	1	19971231	G	5102		CHIMNEY RIP     			CAMRON	R420  	R420        		GL  										BALLOON ENVELOPE	FAILED          	C		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	GJNEE	3    				4232				CHIMNEY RIP FAILED TO OPEN WHEN PULLED PREVENTING DEFLATION AND RESULTING IN PROPERTY DAMAGE.  UPON LANDING, 3 OF 4 SAFE	TY TIES WERE PULLED OPEN BY THE PILOT, BUT THE FOURTH WOULD NOT BREAK.  THE FULL WEIGHT OF THE PILOT (210 POUNDS) JUMPIN	G 20 INCHES WITH THE RED LINE, WOULD NOT ACTUATE THE RIP.  ONCE THE BALLOON WAS BROUGHT UNDER CONTROL, 9 FIREMEN WERE LI	FTED OFF THE GROUND BY THE RED LINE BEFORE THE CHIMNEY OPENED.			1	B	0	0 	3X			NC	EXPA1B00					 
1998011500082	19980115	00082	CE  	1998	1	15	98ZZZX166        	1	19971217	G	2750	0510105193	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										FLAP	MISINSTALLED    	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	361ES	471  				17280011				DURING 100 HOUR INSPECTION, AILERON CABLE WAS BEING REPLACED.  FOUND FLAP DIRECT CABLE NOT SAFETIED.  THIS CABLE IS LOCA	TED BEHIND HEADLINER.  IT WOULD HAVE NEVER BEEN DETECTED IF HEADLINER WAS INSTALLED.  SUBMITTER RECOMMENDED ACCESS PLATE	 TO INSPECT CABLES DURING ROUTINE INSPECTION.				1	H	7	1 	3O			NT	3A12    					 
1998050800885	19980508	00885	EA  	1998	5	8	98ZZZX1664       	2	19971231	G	7414	10682016	DISTRIBUTOR GEAR	ELECTROSYS  	D6LN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	CRACKED         	B	L		YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	59829	1091 	142  		L189515GR	317652081				MAGNETO WAS INSTALLED ON LEFT ENGINE 11-24-97, AND WAS REMOVED 12-31-97 DUE TO CRACKED, MISSING TOOTH.  PREVIOUS MAGNETO	 HAD SUFFERED FAILURES OF BOTH DIST GEARS.  SUSPECT TORSIONAL VIBRATION IN ENGINE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998050800886	19980508	00886	EA  	1998	5	8	98ZZZX1665       	2	19971124	G	7414	10682016	DISTRIBUTOR GEAR	ELECTROSYS  	D6LN2230    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	CRACKED         	B	P		YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	59829	1601 			6070845R	317652081				11-24-97, MAGNETO WAS REMOVED FROM LEFT ENGINE OF N NR 59829 DUE TO FAILED DISTRIBUTOR GEAR TEETH.  MAGNETO HAD 1,601.16	 HOURS SINCE OVERHAUL BY ELECTROSYSTEMS, INC., HOWEVER, GEARS MAY NOT HAVE BEEN NEW AT MAGNETO OVERHAUL.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998011500083	19980115	00083	CE  	1998	1	15	98ZZZX167        	1	19971212	G	2710	0510105360	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										RT AILERON	FRAYED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	361ES	471  				17280011				WHILE PERFORMING A 100-HOUR INSPECTION, FOUND THE RIGHT HAND AILERON CABLE FRAYED/TANGLED AS IF SOMETHING MIGHT HAVE GOT	 BETWEEN IT AND THE PULLEY IN THE SAME AREA AS THE PULLEY.  ALSO, FOUND A ROUND FILE APPROXIMATELY .1875 INCH DIAMETER. 	 IT IS UNCLEAR IF THE FILE GOT BETWEEN THE CABLE AND PULLEY.  THE AREA IN CONCERN IS THE PULLEY AT THE FLOOR AND JUST BE	HIND THE DOOR ON THE PILOT'S SIDE.			1	H	7	1 	3O			NT	3A12    					 
1998011500084	19980115	00084	CE  	1998	1	15	98ZZZX168        	1	19971217	G	2710	0510105360	CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										LEFT AILERON	MISINSTALLED    	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	361ES	471  				17280011				DURING 100-HOUR INSPECTION, FOUND LEFT AILERON DIRECT CABLE TURNBUCKLE NOT SAFETIED.  THE TURNBUCKLE IS NOT VISIBLE WITH	 THE HEADLINER INSTALLED.  IT WOULD HAVE BEEN UNABLE TO DETECT HAD THE HEADLINER NOT BEEN REMOVED TO REPLACE DAMAGED AIL	ERON CABLE.  RECOMMEND RE-DESIGN OF HEADLINER TO GAIN ACCESS TO CABLES DURING ROUTINE INSPECTIONS.				1	H	7	1 	3O			NT	3A12    					 
1998011500085	19980115	00085	EU  	1998	1	15	98ZZZX169        	1	19971209	G	3610	BYLB504231	VALVE           			AMD   	FALC20	FALCON200   	2730150	EU  										BLEED VENTURI	MISWIRED        	B		A	UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	50MG				431	507				AIRCRAFT HAD A DEFECTIVE VENTURI VALVE (19H).  ORDERED AND INSTALLED AN OVERHAULED VALVE.  THIS VALVE DID NOT WORK.  THE	 OPEN INDICATION MICROSWITCH IS WIRED INCORRECTLY AND THERE IS ALOT OF PLAY ON THE BUTTERFLY DRIVE ASSEMBLY.  ORDERED AN	D INSTALLED ANOTHER VALVE FROM DIFFERENT VENDOR.  WORKED OK.  THE OVERHAUL MANUAL FOR THIS VALVE HAS SEVERAL ERRORS IN I	T ALSO.			2	L	7	2 	4F			RT	A7EU    					 
1998050800918	19980508	00918	WP  	1998	5	8	98ZZZX1696       	1	19970420	G	5400		FORMER          			DOUG  	DC10  	DC1010      	3022110	WP  										NR 2 ENG PYLON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	910SF				AVB709627	46524				MULTIPLE CRACKS WERE FOUND IN FORMER WHICH IS LOCATED IN AREA ABOVE NR 2 ENGINE. FORMER IS A PART OF THE AFT PYLON STANG	 AREA.					2	L	7	3 	4F				A22WE   					 
1998010800076	19980108	00076	EU  	1998	1	8	98ZZZX17         	1	19971128	G	5753	T700A5755063101	CARRIER         			SOCATA	TBM   	TBM700      	8682000	EU  										FLAP BEARING	CRACKED         	B		A	CB5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	79Z	789  				19				WHILE CARRYING OUT A 100-HOUR REPETITIVE INSPECTION IAW DGAC AD 94-110, AND SB 70-048-57, IT WAS NOTED THAT ALL 4 FLAP B	EARING CARRIAGES WERE CRACKED.  THE CRACKS WERE NOT LOCATED IN THE INSPECTION AREAS SHOWN IN THE SB 70-048-57, BUT WERE 	LOCATED IN THE WEBS. ALL 4 FLAP BEARING CARRIAGES WERE REPLACED WITH MODIFIED ITEMS BEFORE FURTHER FLIGHT.				1	L	7	1 	3T			RT	A60EU   					 
1998011500086	19980115	00086	CE  	1998	1	15	98ZZZX170        	1	19971227	G	2730	05130631	BRACKET         			CESSNA	172   	172G        	2072420	CE  										ELEV BELLCRANK	CRACKED         	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4477L	5451 				17254572				INSPECTION OF 4 LOOSE RIVETS ON BELLY SKIN BETWEEN WING STRUT LOWER ATTACH POINTS REVEALED THE 'ELEVATOR BELLCRANK BRACK	ET', PN 051306301, HAD BEEN FLEXING.  ON CLOSER EXAMINATION, MANY CRACKS WERE FOUND IN THE BEND RADII OF THE FORWARD AND	 AFT FLANGES WITH COMPLETE SEPARATION OF THE LEFT FORWARD FLANGE.				1	H	7	1 	3O			NT	3A12    					 
1998011500087	19980115	00087	CE  	1998	1	15	98ZZZX171        	1	19970824	G	2520		SEAT ATTACH     			CESSNA	170   	170         	2072302	CE  										AFT SEAT	WRONG PART      	G	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	13	3964V	3133 				18283				DURING ACCIDENT INVESTIGATION, FOUND RIVNUTS WERE SUBSTITUTED FOR 3 NAS684A3 NUTPLATES FOR REAR SEAT ATTACH HARDWARE.  T	HE RIVNUTS EXTRUDED THROUGH THE HOLES IN THE STRUCTURE AND ALLOWED THE REAR SEAT TO PARTIALLY BREAK LOOSE.  PARTS MANUAL	 FIG 20, ITEM NR 12.				1	H	7	1 	3O			NT	A799    					 
1998011500088	19980115	00088	SO  	1998	1	15	98ZZZX172        	2	19970824	G	7310		TEE FITTING     			CESSNA	170   	170         	2072302	CE  	CONT  	C145  	C145*       	17012	SO  					CARBURETOR INLET	BROKEN          	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	13	3964V	20   				18283	8214D32			INVESTIGATION OBSERVED COMMON HARDWARE FITTINGS HAD BEEN INSTALLED IN LIEU OF AN8266D AS DISPLAYED IN CESSNA PARTS MANUA	L FIG 34-32.					1	H	7	1 	3O	3	O	NT	A799    	E253				 
1998051500275	19980515	00275	SO  	1998	5	15	98ZZZX1723       	1	19970407	G	2710	62102000	SUPPORT         			PIPER 	PA32  	PA32300     	7103212	SO  										AIL BELLCRANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	99WD	2221 				327540031				DURING AN ANNUAL INSPECTION, BOTH UPPER AILERON BELLCRANKS SUPPORT BRACKETS WERE FOUND CRACKED.  AILERONS WERE NOT PROPE	RLY RIGGED AND BELLCRANK WAS NOT CONTACTING AFT STUDS CAUSING A TWISTING ACTION ON SUPPORTS IN WINDY CONDITIONS.					1	L	7	1 	3O				A3SO    					 
1998051500276	19980515	00276	SO  	1998	5	15	98ZZZX1724       	1	19970407	G	2710	62102001	SUPPORT         			PIPER 	PA32  	PA32300     	7103212	SO  										AIL BELLCRANK	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	99WD	2221 				327540031				DURING AN ANNUAL INSPECTION, BOTH UPPER AILERON BELLCRANKS SUPPORT BRACKETS WERE FOUND CRACKED.  AILERONS WERE NOT PROPE	RLY RIGGED AND BELLCRANK WAS NOT CONTACTING AFT STUDS CAUSING A TWISTING ACTION ON SUPPORTS IN WINDY CONDITIONS.					1	L	7	1 	3O				A3SO    					 
1998011500398	19980115	00398	CE  	1998	1	15	98ZZZX173        	1	19971219	G	7120	10591001077	MOUNT           			BEECH 	76    	76          	1153005	CE  										ENGINE	MISMANUFACTURED 	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	2009X				4677	ME66				UPON ARRIVAL OF A NEW ENGINE MOUNT, DISCOVERED TWO OF THE WELD JOINTS WERE DEFECTIVE.  THE GUSSET PLATES ON BOTH UPPER B	RACE ARMS WERE NOT WELDED DOWN, ONLY TACK-WELDED TO THE BRACE ARMS.  THE MANUFACTURER SAID THAT ALTHOUGH IT WAS NOT CORR	ECT, SEVERAL UNITS HAD BEEN SHIPPED WITH THIS CONDITION.  SUBMITTER RECOMMENDED THAT ANY DUTCHESS OWNERS THAT HAVE REPLA	CED THEIR ENGINE MOUNTS WITH KOSOLA UNITS (LEFT AND RIGHT ARE IDENTICAL), HAVE THE UPPER GUSSET PLATES INSPECTED FOR GAP	S UNDER THE PLATES.		1	L	7	2 	3O				A29CE   					 
1998011500399	19980115	00399	CE  	1998	1	15	98ZZZX174        	1	19971203	G	2160	1173542	SWITCH          			CESSNA	650   	650         	2076802	CE  										CABIN OVERHEAT	FAILED          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	39WP	6239 			366	650039				DURING SCHEDULED CALIBRATION (OPERATION 12) INSPECTION, CABIN OVERHEAT SWITCH FAILED TEST DUE TO OUT OF TOLERANCE.  REPL	ACED SWITCH WITH SERVICEABLE ASSEMBLY.  NEW SWITCH WAS VERIFIED IN TOLERANCE PRIOR TO INSTALLATION.					2	L	7	2 	4F				A9NM    					 
1998011500400	19980115	00400	CE  	1998	1	15	98ZZZX175        	1	19971209	G	3240	1013810125	VALVE           			BEECH 	B300  	B300        	1159232	CE  										RT BRAKE DEICE	FAILED          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4S	313  			0531	FL107				PILOT REPORTED RT BRAKE DE-ICE DOES NOT ILLUMINATE ON CYCLE AFTER LANDING OR BEFORE TAKEOFF.  REPLACED VALVE ASSEMBLY. S	UBMITTER STATED THESE PARTICULAR VALVES HAVE A VERY POOR RELIABILITY FACTOR.  THEY ARE NOT RELIABLE AND USUALLY ONLY LAS	T ABOUT 6 MONTHS UNTIL THEY FAIL.  THIS VALVE HAD 312.6 HOURS AND 372 CYCLES.  RECOMMEND MANUFACTURER LOOK FOR THE PROBL	EM AND IMPROVE RELIABILITY.			2	L	7	2 	4T			RT	A24CE   					 
1998051500674	19980515	00674	EU  	1998	5	15	98ZZZX1754       	1	19971213	G	6220	10513143	ROD END         			BOLKMS	117   	BK117A4     	5626017	EU  										M/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG	437  				7083				PREMATURE BEARING WEAR.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U				H13EU   					 
1998011500401	19980115	00401	SW  	1998	1	15	98ZZZX176        	1	19971216	G	6700	369A7301501	BELLCRANK       			HUGHES	500N  	500N        	3027374	SW  										FLIGHT CONTROL	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					167					FOUND ON ACCEPTANCE INSPECTION THAT BELLCRANK HAS BOTH PIVOT BEARINGS PRE-LOADED TO A POINT BEARING WILL NOT ROTATE FOR 	INSTALLATION.					1	G	7	1 	3U			NC	H3WE    					 
1998011500402	19980115	00402	SW  	1998	1	15	98ZZZX177        	1	19971216	G	6700	369A7301501	BELLCRANK       			HUGHES	500N  	500N        	3027374	SW  										FLIGHT CONTROL	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					160					FOUND ON ACCEPTANCE INSPECTION THAT BELLCRANK HAS BOTH PIVOT BEARINGS PRE-LOADED TO A POINT OF NO ROTATION.						1	G	7	1 	3U			NC	H3WE    					 
1998011500404	19980115	00404	SW  	1998	1	15	98ZZZX179        	1	19970728	G	6322	476205381C	SLEEVE          			BELL  	47    	47G2        	1181008	SW  										FAN DRIVE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	7730					K821				INSPECTION FOUND FAN DRIVE SLEEVE WITH LARGE THRU-CRACKING IN FLANGE AREA.						1	G	7	1 	3O				H1      					 
1998010800077	19980108	00077	CE  	1998	1	8	98ZZZX18         	1	19971117	G	2711	NAS35860900	PUSH ROD        			LEAR  	35    	35A         	5170602	CE  										AILERON BALANCE	CORRODED        	B	L	A	TJ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	831CW	6651 				390				CORROSION INSIDE AILERON BALANCE TAB PUSH RODS.  CONDITION FOUND DURING A SCHEDULED INSPECTION.  PIN HOLES WERE NOTED ON	 3 OF THE 4 PUSH RODS.  REPLACED ALL 4 WITH NEW RODS.					2	L	7	2 	4F				A10CE   					 
1998011500405	19980115	00405	NM  	1998	1	15	98ZZZX180        	1	19971201	G	5315		FLOOR BEAM      			BOEING	727   	727251      	138408H	NM  										BS 460	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK, CORROSION NOTED ON UPPER CHORD OF CABIN FLOOR BEAM.  STA 460 FROM RBL 25 TO RBL 45.						2	L	7	3 	4F				A3WE    					 
1998011500406	19980115	00406	NM  	1998	1	15	98ZZZX181        	1	19971201	G	5313		STRINGER        			BOEING	727   	727251      	138408H	NM  										BS 720C	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	258US					19977				DURING C-CHECK INSPECTION, STR 15L WAS NOTED CRACKED AT STA 720C.						2	L	7	3 	4F				A3WE    					 
1998011500408	19980115	00408	CE  	1998	1	15	98ZZZX183        	1	19971217	G	3230	508202012	RETRACT CHAIN   			BEECH 	90    	C90         	1152913	CE  										NLG AFT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	321DM	3849 				LW250				NLG AFT RETRACT CHAIN MASTER LINK FAILED.  ALL PIECES OF MASTER LINK FOUND AND IN SERVICEABLE CONDITION.  RECOMMEND INST	ALLATION OF NEW STYLE PRESS FIT LINK, PN 131378-25-2-CL, TO PREVENT RECURRENCE.					1	L	7	2 	3T				3A20    					 
1998011500409	19980115	00409	NE  	1998	1	15	98ZZZX184        	2	19971216	G	8520	5999	ROLLER          			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R1340*      	52016	NE  					VALVE TAPPET	SPALLED         	D				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	15			175  							AT THE TIME OF ROUTINE MAINTENANCE, METAL WAS DISCOVERED IN THE OIL SCREEN AND FILTER AND ALSO THE CHIP DETECTOR LIGHT C	AME ON.  UPON INSPECTION, FOUND THE VALVE TAPPET ROLLERS SPALLING.					1	Q	7	1 	3R	3	R		1A16    	5E2				 
1998011500410	19980115	00410	SO  	1998	1	15	98ZZZX185        	1	19971222	G	7160		CLAMP           			PIPER 	PA46  	PA46310P    	7104605	SO  										INDUCTION TUBE	FAILED          	B			CW7R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	25	146BU					468408057				DURING FLIGHT AT ALTITUDE, AIRCRAFT LOST MANIFOLD PRESSURE RESULTING IN LOSS OF CABIN PRESSURE.  ON GROUND, FOUND LEFT F	ORWARD INDUCTION TUBE CLAMP OFF.  AIRCRAFT WAS A RAM CONVERSION.  RE-INSTALLED CLAMP.  GROUND CHK OK.  SUSPECT LOOSE CLA	MP.				1	L	7	1 	3O				A25SO   					 
1998011500411	19980115	00411	CE  	1998	1	15	98ZZZX186        	1	19971218	G	2731	12346281	TRIM TAB        			CESSNA	206   	TU206G      	2073357	CE  										ELEVATOR	CORRODED        	B			KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	206PD	3748 				676				IN THE PROCESS OF ANNUAL INSPECTION, TECHNICIAN NOTICED WHAT APPEARED TO BE CORROSION STARTING UNDER THE PAINT AROUND TH	E RIVET HEADS ON THE UPPER SURFACE OF THE BRACKET FOR THE ELEV TAB CONTROL ROD.  WHEN PICKED AT THE RIVET HEADS WITH FIN	GERNAIL, SIX OF THE EIGHT RIVET HEADS POPPED OFF.				1	H	7	1 	3O				A4CE    					 
1998052200038	19980522	00038	SW  	1998	5	22	98ZZZX1860       	1	19971202	G	2822	A8152B	FUEL PUMP       	WELDON      		MOONEY	M20   	M20R        	5870225	SW  										FUEL SYSTEM	FAILED          	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	700RT	488  			71756	290097				WHILE UTILIZING THE ELECTRIC FUEL PUMP TO TRANSFER FUEL, THE PUMP FAILED IN ABOUT 15 MINUTES.  THIS IS THE SECOND TIME I	N A MONTH THIS MODEL WELDON PUMP FAILED IN A MOONEY OVATION.  BOTH PUMPS HAVE APPROXIMATELY THE SAME AMOUNT OF TOTAL TIM	E.				1	L	7	1 	3O			RT	2A3     					 
1998011500412	19980115	00412	CE  	1998	1	15	98ZZZX187        	1	19971216	G	2720	35524106	CONTROL TUBE    			BEECH 	35    	V35A        	1151544	CE  										RUDDERVATOR	SEIZED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	2753A					D9052				PER AD 06-11-97, FOUND LEFT RUDDERVATOR TUBE WAS HOLDING TRAPPED WATER AND INBOARD BEARING WAS COMPLETELY SEIZED WITH RU	ST.					1	L	7	1 	3O				3A15    					 
1998052200592	19980522	00592	EA  	1998	5	22	98ZZZX1886       	2	19970506	G	8540	67610	STARTER GEAR    			BELL  	47    	47          	1180602	SW  	LYC   	O435  	VO435A1A    	41516	EA  					LOCK TABS	FAILED          	B		A	PB2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23			300  							AFTER REVIEWING APRIL, 1998 ALERTS AL 43-16, ATA 8011, SUBMITTER REPORTS AN ADDITIONAL OCCURRENCE OF LOCK TAB FAILURE. E	NGINE/AIRCRAFT WAS ON GROUND AND NO DAMAGE OCCURRED.  DISASSEMBLY OF ENGINE REVEALED THAT LOCK TABS DID NOT COVER UP DOW	ELS AND ALLOWED THEM TO FALL OUT AND BOLTS TO BE SHEARED.				1	G	7	1 	3O	3	O		H1      	E279				 
1998011500414	19980115	00414	CE  	1998	1	15	98ZZZX189        	1	19971201	G	2701	07136671	YOKE SHAFT      			CESSNA	182   	182J        	2072722	CE  										LT CONTROL WHEEL	FOULED          	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			EA	21	3546F					18257546				DURING ANNUAL INSPECTION, FOUND UP ELEVATOR TRAVEL BELOW LIMIT BY 30 PERCENT - 18 DEGREES UP - 26 DEGREES PLUS 1 MINUS Z	ERO DEG.  INSPECTION FOUND 'TINNERMAN' TYPE HOSE CLAMP CAUGHT INBETWEEN LT YOKE SHAFT P/N 0713667-1, AND LT CONTROL WHEE	L SUPPORT ASSY STOPPING THE LAST 2.0 INCHES OF TRAVEL.  COULD NOT DETERMINE SOURCE OF CLAMP.  VARIOUS AVIONICS AND 'BEHI	ND PANEL' WORK PERFORMED IN THE LAST 2 YEARS.			1	H	7	1 	3O			NT	3A13    					 
1998052200605	19980522	00605	EU  	1998	5	22	98ZZZX1899       	2	19971007	G	7250	9514M71P04	SHAFT           			BOEING	737   	7373B7      	1384580	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					HPT AFT	FAILED          	B	L		LY2R	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CE	07	373US	22624	12014			22952	724705			HPT AFT SHAFT FAILED ON TAKEOFF ROLL AT 80 PERCENT N1.  HPT AFT SHAFT FAILED AT SEAL TEETH CAUSING EXTENSIVE DAMAGE DOWN	 STREAM IN THE TURINE 2ND LPT AREAS.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
1998010800078	19980108	00078	SO  	1998	1	8	98ZZZX19         	2	19971208	G	8520	635439	BEARING         			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 2 MAIN	FAILED          	G				E	O			ENGINE SHUTDOWN         	OTHER                   			J			WARNING INDICATION        			CR	CRUISE         	1			WP	09	87SC	800  				TE441	1260447C			ENGINE RPM FLUCTUATING IN-FLIGHT.  PRECAUTIONARY ENGINE SHUT DOWN AND FEATHERING ACCOMPLISHED.  AIRCRAFT LANDED WITHOUT 	INCIDENT.  INVESTIGATION DISCLOSED THE STARTER ADAPTER FAILED DUE TO LACK OF OIL. THIS OCCURRED AFTER .5 HOURS OF OPERAT	ION.  DISASSEMBLY OF THE ENGINE DISCLOSED THAT NR 2 MAIN BEARING FAILED ALLOWING THE OIL PRESSURE TO DROP WELL BELOW THE	 MINIMUM PRESSURE REQUIRED TO LUBRICATE THE STARTER HOUSING, ADAPTER.  PRIMARY FAILURE:  NR 2 MAIN BEARING.  SECONDARY F	AILURE:  STARTER ADAPTER HOUSING.		1	L	7	2 	3O	3	O		3A16    	E5CE				 
1998011500415	19980115	00415	EA  	1998	1	15	98ZZZX190        	2	19971203	G	7414	103493943	HOUSING         	BENDIX      	S49L1209    	PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  					ENGINE MAGNETO	CRACKED         	B			RG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	4957J	3885 			23458	28R30704	L512051A			INSPECTION FOUND BOTH MAGNETO HOUSINGS ARE CRACKED IN SEVERAL PLACES.  SUSPECT THAT WHEN NEW COILS WERE INSTALLED, THE W	EDGES WERE INSTALLED INCORRECTLY OR OVERDRIVEN INTO POSITION.					1	L	7	1 	3O	3	O		2A13    	1E10				 
1998011500416	19980115	00416	EA  	1998	1	15	98ZZZX191        	2	19971203	G	7414	103493943	HOUSING         	BENDIX      	S49L1227    	PIPER 	PA28  	PA28R180    	7102809	SO  	LYC   	O360  	IO360B1E    	41514	EA  					ENGINE MAGNETO	CRACKED         	B			RG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	4957J	3885 			23458	28R30704	L512051A			INSP FOUND BOTH MAGNETO HOUSINGS ARE CRACKED IN SEVERAL PLACES.  SUSPECT THAT WHEN NEW COILS WERE INSTALLED, THE WEDGES 	WERE INSTALLED INCORRECTLY OR OVERDRIVEN INTO POSITION.					1	L	7	1 	3O	3	O		2A13    	1E10				 
1998011500418	19980115	00418		1998	1	15	98ZZZX193        	4	19971231	G	6113	U14426000	SPINNER         			PIPER 	PA18  	PA18150     	7101828	SO  										PROPELLER	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	734					185258				DURING 100-HOUR INSPECTION, REMOVED SPINNER AND FOUND CRACKS IN FORWARD SPINNER BULKHEAD PLATE EXTENSION FROM BEND RADIU	S ON LEFT AND RIGHT SIDE APPROXIMATELY 1.5 INCHES.					1	H	7	1 	3O				1A2     					 
1998011500419	19980115	00419	EU  	1998	1	15	98ZZZX194        	1	19971216	G	7922	53E22144	VALVE           			PARTEN	P68   	P68TCOBS    	6780108	EU  										THERMO BYPASS	FAILED          	B			RF1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	01	737	209  				40004OTC				AIRCRAFT HAD HIGH OIL TEMPERATURE AND LOW OIL PRESSURE.  REMOVED BYPASS VALVE ASSY AND TESTED.  VALVE ONLY MOVED .025 IN	CH.  REPLACED WITH NEW VALVE.  OPS CHECKED GOOD.					1	H	7	2 	30				A31EU   					 
1998011500422	19980115	00422	NE  	1998	1	15	98ZZZX197        	2	19971201	G	7230	556582001	STATOR          								PWA   	JT8   	JT8D7B      	52053	NE  					ENG C2	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					55414		654303			ENGINE C2 STATOR CRACKED ON WELDING.											4	F			E2EA				 
1998011500423	19980115	00423	GL  	1998	1	15	98ZZZX198        	2	19970815	G	7230	301288147D	BOOSTER         								GE    	CFM   	CFM562      		GL  					1ST STAGE	MISWELDED       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17					FR00566					ENGINE 1ST STAGE BOOSTER INCOMPLETE WELDED PENETRATION.											4	F			E2GL				 
1998010800061	19980108	00061	GL  	1998	1	8	98ZZZX2          	2	19971215	G	7313	47086	FILTER          								ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	CRUSHED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										APPEARS A FOREIGN OBJECT WAS INSERTED INTO THE INLET END OF THE FUEL NOZZLE CONTACTING THE CRUSTING FILTER ASSY.  NO FOR	EIGN OBJECTS SHOULD EVER BE INSERTED INTO INLET END.										3	U			E4CE				 
1998010800079	19980108	00079	EU  	1998	1	8	98ZZZX20         	1	19971215	G	2160	104568	VALVE           			HWKSLY	DH125 	BH125400A   	4230138	EU  										BLEED CHECK	FAILED          	D				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	07	900WG		1989 		P9532	NA757				AFTER TAKEOFF, VALVE FAILED IN OPEN POSITION.  THIS CAUSED EXCESSIVE HOT BLEED AIR TO REACH COCKPIT.  PRESSURIZATION WAS	 DIFFICULT TO CONTROL AND PILOTS WERE SUBJECTED TO EXTREME HEAT.  AIRCRAFT HAD TO DESCEND AND LAND AS SOON AS POSSIBLE. 	 ONLY BY SHUTTING DOWN RIGHT ENGINE COULD THIS PROBLEM BE RESOLVED IN-FLIGHT.				2	L	7	2 	4J			 	A3EU    					 
1998010800080	19980108	00080	CE  	1998	1	8	98ZZZX21         	1	19971211	G	2931		GAUGE           			BEECH 	200   	200BEECH    	1152920	CE  										HYD ACCUM IND	FAILED          	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	981LL	392  				BB602				THIS GAUGE IS PART OF STC SA 4378WP AVIADESIGN, INC., HYDRAULIC LANDING GEAR RETRACTION SYSTEM.  WITH ZERO PRESSURE IN A	CCUMULATOR, THIS GAUGE WAS STILL SHOWING 500 P.S.I.G. FOR INDICATION.  SUBMITTER RECOMMENDED A BETTER QUALITY GAUGE BE U	SED IN SYSTEM.				1	L	7	2 	4T				A24CE   					 
1998011500435	19980115	00435	SO  	1998	1	15	98ZZZX210        	2	19970812	G	8520	642001	CRANKCASE       								CONT  	O520  	IO520C      	17032	SO  					ENG LT/RT HALF	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										CRANKCASE INSPECTION FOUND BOTH LEFT AND RIGHT HALVES OF ENGINE CASE HAS CRACKING (LENGTHY AND THROUGH).											3	O			E5CE				 
1998061200363	19980612	00363	EA  	1998	6	12	98ZZZX2118       	2	19971101	G	8530	SL14077	PISTON PIN      			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	FAILED          	B			VG1R	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SW	05	1144P	587  				241187	L1704051AC			PISTON PIN BROKE IN-FLIGHT CAUSING MASSIVE DAMAGE INTERNALLY IN ENGINE.  THE CRACKSHAFT AND ONE CYLINDER WERE THE ONLY I	TEMS SALVAGEABLE.  PILOT NOTICED ENGINE ROUGNESS AND LOSS OF OIL PRESSURE.  AIRPLANE LANDED WITHOUT DAMAGE TO AIRCRAFT O	R PILOT.  ENGINE QUIT COMPLETELY AFTER TOUCH-DOWN.				1	L	7	1 	3O	3	O		2A3     	1E10				 
1998012200129	19980122	00129	SO  	1998	1	22	98ZZZX216        	1	19971227	G	5730		WING PLANK      			GULSTM	G159  	G159        	3952202	SO  										INBD LOWER	CORRODED        	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2FOR									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.				2	L	7	2 	4T				1A17    					 
1998012200131	19980122	00131	WP  	1998	1	22	98ZZZX218        	1	19971210	G	3240		EXPANDER TUBE   			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										LT OTBD BRAKE	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	33	58NA					12970				LEFT OUTBOARD BRAKE EXPANDER TUBE FAILED.  REMOVED AND REPLACED LEFT OUTBOARD BRAKE ASSY IAW DOUGLAS DC-3 SM.						2	L	7	2 	4R				A669    					 
1998012200132	19980122	00132	NE  	1998	1	22	98ZZZX219        	2	19971124	G	8540		ACCESSORY SECT  			DOUG  	DC3   	DC3AS1C3G   	3021440	WP  	PWA   	R1830 	R183092     	52020	NE  					ENGINE	FAILED          	G			VNAA	E				ENGINE SHUTDOWN         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			GL	07	24320		575  			20197	351640			WHILE IN CRUISE FLIGHT, ENGINE RAN ROUGH FOR APPROXIMATELY 5 SECONDS, THEN OIL PSI LIGHT AND FUEL LIGHT CAME ON.  ENGINE	 WAS SHUT DOWN AND PROPELLER FEATHERED.  ONCE ON GROUND, IT WAS DETERMINED THE ACCESSORY SECTION WAS NOT WORKING.  SUSPE	CT EITHER A FAILED GEAR IN THE ACCESSORY SECTION OR POSSIBLY A BROKEN CRANKSHAFT.  ENGINE TO BE REPLACED WITH A SERVICEA	BLE UNIT.			2	L	7	2 	4R	4	R		A669    	5E4				 
1998010800081	19980108	00081	CE  	1998	1	8	98ZZZX22         	1	19971205	G	3230		DRAG BRACE      			BEECH 	200   	200BEECH    	1152920	CE  										MLG RT	CORRODED        	B			LX5R	K				NONE                    				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			GL	19	981LL					BB602				THIS AIRCRAFT IS EQUIPPED WITH AVIADESIGN INC., HYDRAULIC LANDING GEAR SYSTEM.  NO DOWN AND LOCKED INDICATION ON RIGHT M	AIN LANDING GEAR.  SUSPECT CAUSE:  FOUND CORROSION ON DRAG BRACE ASSEMBLY PIVOT BOLTS CREATING BINDING SITUATION AND NOT	 ALLOWING LOCKING MECHANISM TO LOCK COMPLETELY.  SUBMITTER RECOMMENDED IN ADDITION TO BEECHCRAFT'S LANDING GEAR LUBRICAT	ION REQUIREMENTS, RECOMMEND DRAG BRACE BOLTS BE REMOVED, INSPECTED, AND LUBRICATED AT AVIADESIGN, INC.  RECOMMENDED GEAR	 INSPECTION INTERNALLY.		1	L	7	2 	4T				A24CE   					 
1998012200135	19980122	00135	EU  	1998	1	22	98ZZZX221        	1	19971223	G	3520	17450401	FACE CUSHION    		C3512000    	BRAERO	DH125 	BAE125800A  	1500285	EU  										PAX O2 MASK	TORN            	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	961JC	4081 				258062				WHILE C/W RAYTHEON SB 35-3014 (INSPECTION OF PASSENGER OXYGEN FACE MASKS FOR TEARS IN FACE CUSHIONS), FIVE MASKS WERE FO	UND TORN.  THE CORE DATES WERE FROM 1986, NOT 1994 AS LISTED IN THE SB.  SUBMITTER STATED THIS IS THE SECOND HAWKER 800 	FOUND WITH EXACT SAME PROBLEM.  RECOMMEND PB AND RAYTHEON REVISE SB'S TO INCLUDE EARLIER CURE DATES.  NELLCOR PURITAN BE	NNETT SB NR C351-2000-35-1 R1.			2	L	7	2 	4F			RT	A3EU    					 
1998012200137	19980122	00137	EA  	1998	1	22	98ZZZX222        	2	19971231	G	8520		CRANKSHAFT      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 4 ROD JOURNAL	FAILED          	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			NE	01	2838D	6600 	180  			287916463	L1304339A			AIRCRAFT TOOK OFF FROM HANSCOM AND LANDED AT NANTUCKET WITHOUT INCIDENT.  PILOT GOT BACK INTO AIRCRAFT AND TAXIED TO THE	 RUNWAY.  DURING TAKEOFF ROLL, PILOT HEARD A LOUD KNOCKING SOUND AND ABORTED TAKEOFF AND TAXIED BACK TO HANGAR.  AFTER P	ULLING ALL THE CYLINDERS OFF AND REMOVING ALL CONNECTING RODS, THE NR 4 CONNECTING ROD JOURNAL WAS FOUND CRACKED IN HALF	.  THE NR 4 CONN ROD WAS HOLDING THE CRANKSHAFT TOGETHER.			1	L	7	1 	3O	3	O		2A13    	E274				 
1998012200138	19980122	00138	EA  	1998	1	22	98ZZZX223        	2	19970102	G	7414	1068291013	MAGNETO         	BENDIX      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					DRIVE GEAR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	59829	142  			L189515GR	317652081	L780661A			UPON TAKING THE CAP OFF THE MAGNETO, NOTED THAT ONE OF THE DRIVE GEAR TEETH WAS BROKEN OFF FROM THE NYLON DISTRIBUTOR GE	AR.  NOTE:  THE DIRECTOR OF MAINTENANCE REPORTED A TIMING TOOL WAS NOT USED.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998012200139	19980122	00139	SO  	1998	1	22	98ZZZX224        	2	19971003	G	8530		ROCKER BOSS     			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300A      	17022	SO  					NR 4 CYLINDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7115M		248  			55415	53818A			DURING ANNUAL INSPECTION, NR 4 CYLINDER COMP AT 50/80 WITH AIR NOISE IN EXHAUST STACK.  ON REMOVAL OF ROCKER BOX COVER, 	THE TOP HALF OF THE LEFT BOSS CAME OUT WITH THE COVER.  TEN HOURS PREVIOUSLY, THE COVER HAD BEEN REMOVED AND PUSH ROD TU	BES HAD BEEN RESEALED.  SUBMITTER STATED THE BOSS MAY HAVE BEEN CRACKED WHEN THE ROCKER ARM SHAFT WAS REMOVED OR INSTALL	ED.			1	H	7	1 	3O	3	O	NT	3A17    	E298				 
1998012200140	19980122	00140	EA  	1998	1	22	98ZZZX225        	2	19971211	G	7314	RA8987	GASKET          								LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL PUMP	LEAKS           	B	L	A	YECR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09										FUEL PUMP OVERHAULED AND BENCH TESTED 2-97 PER RG9080 COMPONENT MM, BUT WAS NOT PLACED INTO SERVICE UNTIL 12/97.  PUMP L	EAKED AT RA8987 GASKET ON INITIAL START-UP OF ENGINE IN TEST CELL.  ALL SCREWS FOUND BELOW MINIMUM 23 INCH/POUND TORQUE 	REQUIRED BY SB 1015B020.  RA8987 GASKET WAS ASBESTOS, BUT IS NOW RUBBER COMBINED WITH DOUBLE RUBBER RELIEF DIAPHRAGMS RA	5326.  THERE APPEARS TO BE TOO MUCH PLIABLE MATERIAL IN THE JOINT TO MAINTAIN PROPER PRE-LOAD.  THIS IS FIFTH OCCURRENCE	.  SB 101SB020 DOES NOT ADDRESS PROBLEM SOON ENOUGH TO PREVENT FUTURE LEAKS.  RA5326 AND RA8987 MATERIAL SHOULD BE REVIS	ED.						3	O			E14EA				 
1998012200142	19980122	00142	SO  	1998	1	22	98ZZZX227        	2	19971203	G	8530	654064	VALVES          								CONT  	O200  	O200*       	17020	SO  					VALVE STEM	PITTED          	B	P		YECR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	3527U									INSPECTION OF 6 NEW VALVES FOUND TWO OF THE VALVE STEMS WERE GENERALLY IN POOR CONDITION.  FURTHER INSPECTION FOUND DEEP	 PITS AND SCRATCHES THAT APPEARED TO BE INCLUSIONS OR OTHER IMPURITIES.										3	O			E252				 
1998012200143	19980122	00143	EA  	1998	1	22	98ZZZX228        	2	19971118	G	7414	10682056	DIST BLOCK      		D6RN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	WORN            	B	P		YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3527U	443  				317952141				INSPECTION OF MAGNETO DISTRIBUTOR BLOCK FOUND BUSHING WEAR AND WEAR DAMAGE TO LARGE DISTRIBUTOR GEAR.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998010800082	19980108	00082	CE  	1998	1	8	98ZZZX23         	1	19971211	G	3230	92467	RESTRICTOR VALVE	GARKENYON   		BEECH 	200   	200BEECH    	1152920	CE  										HYDRAULIC MLG	FAILED          	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	981LL	6236 			96	BB602				THIS UNIT IS PART OF STC SA4378WP AVIADESIGN, INC., HYDRAULIC LANDING GEAR SYSTEM.  FOUND INTERNAL SCREEN BROKEN OFF.						1	L	7	2 	4T				A24CE   					 
1998012200145	19980122	00145	EA  	1998	1	22	98ZZZX230        	2	19971124	G	8550	CH48110	OIL FILTER      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE OIL	BULGED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	05	67932	1    				15282107				FILTER REPLACED 11-24-97.  ENGINE GROUND CHECKED.  0IL PRESSURE NORMAL.  ON NEXT FLIGHT, OIL WAS LOST OVERBOARD.  ON EXA	MINATION, FILTER WAS FOUND ELONGATED AND BULGED.  FILTER TAKEN TO HAGGLIN MOTOR FOR INVESTIGATION.  CONCLUSION WAS BULGI	NG LIFTED FILTER OFF SEAT, DUMPING OIL.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1998012200146	19980122	00146	SO  	1998	1	22	98ZZZX231        	1	19971217	G	5711	7850002	RIB             			PIPER 	PA34  	PA34200     	7103405	SO  										WS 69.24	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	42752					347450172				THE FALSE SPAR AND WING RIB AT STA 69.24 ON THE LEFT WING WERE FOUND BROKEN AT THE 100-HOUR INSPECTION.  SUBMITTER BELIE	VES IT WAS CAUSED BY A HARD OR FAST LANDING, ALTHOUGH NONE WERE REPORTED.  AD 73-11-02 REFERS TO THIS PROBLEM, HOWEVER, 	DOES NOT APPLY TO THIS S/N ACFT.  PIPER KIT 760-696V IS INSTALLED.  REPAIR WILL BE DONE BY INSTALLATION OF NEW RIB AND F	AKE SPAR.			1	L	7	2 	3O				A7SO    					 
1998012200147	19980122	00147	SO  	1998	1	22	98ZZZX232        	1	19971217	G	5711	6707900	FALSE SPAR      			PIPER 	PA34  	PA34200     	7103405	SO  										WS 69.24	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	42752					347450172				THE FALSE SPAR AND WING RIB AT STA 69.24 ON THE LEFT WING WERE FOUND BROKEN AT THE 100-HOUR INSPECTION.  SUBMITTER BELIE	VES IT WAS CAUSED BY A HARD OR FAST LANDING, ALTHOUGH NONE WERE REPORTED.  AD 73-11-02 REFERS TO THIS PROBLEM, HOWEVER, 	DOES NOT APPLY TO THIS S/N ACFT.  PIPER KIT 760-696V IS INSTALLED.  REPAIR WILL BE DONE BY INSTALLATION OF NEW RIB AND F	AKE SPAR.			1	L	7	2 	3O				A7SO    					 
1998012200148	19980122	00148	CE  	1998	1	22	98ZZZX233        	1	19971209	G	3222	6960311	CYLINDER ASSY   			CESSNA	185   	A185F       	2072821	CE  										NLG STRUT	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	61301	5000 				18504144				NLG STRUT ATTACH FAILED ON NOSE WHEELS.  FLOATS HAVE A HISTORY OF SHIMMY PROBLEMS.  THE STRUT UPPER ATTACHMENT BRACKETS 	MAY HAVE BEEN WEAKENED OVER TIME DUE TO THIS CONDITION.  THEY MAY ALSO HAVE BEEN WEAKENED DUE TO NUMEROUS BOW-TYPE DOCKI	NGS.  PART SHOWED NO RUST OR OTHER PROBLEMS BY VISIBLE INSPECTION.				1	H	7	1 	3O				3A24    					 
1998012200149	19980122	00149	CE  	1998	1	22	98ZZZX234        	1	19971218	G	3240	6919	ANCHOR BOLT     	PARKERHANFIN	30182       	CESSNA	208   	208B        	2073701	CE  										BRAKE CALIPER	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	727FX	795  				208B0468				BRAKE CALIPER PINS (ANCHOR BOLTS) WERE SHORTER THAN PINS INSTALLED ON OTHER BRAKE CALIPERS.  THIS WAS A NEW BRAKE ASSEMB	LY INSTALLED ON A NEW AIRCRAFT RECEIVED FROM FACTORY.  RETURNED TO BRAKE MANUFACTURER FOR REPAIR.					1	H	7	1 	3T				A37CE   					 
1998012200150	19980122	00150	SO  	1998	1	22	98ZZZX235        	1	19971223	G	3230	423072	RETRACT LINK    			PIPER 	PA42  	PA42        	7104202	SO  										LT MLG	CRACKED         	B		A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	811DA	4890 				428001029				DURING ROUTINE INSPECTION, 250-HOUR MAGNAFLUX INSPECTION PERFORMED ON RETRACT ARM LINK.  LEFT LINK WAS FOUND CRACKED.  T	IME SINCE LAST INSPECTION, 107 HOURS.  NOTE:  PA42 MM CONTAINS NO NDT INSTRUCTIONS OR WHAT TYPE OF NDT TO BE USED DURING	 THIS INSPECTION.  LANDINGS, 5,062.				1	L	7	2 	4T				A23SO   					 
1998012200151	19980122	00151	SO  	1998	1	22	98ZZZX236        	1	19971201	G	5751	JW10501	AILERON         			LKHEED	1329  	132923D     	5263108	SO  										RT AIL CASTING	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	27RC	8851 				5086				DOING 12-MONTH PERIODIC INSPECTION, FOUND RT AILERON COUNTERWEIGHT CASTING ATTACHMENT CRACKED THROUGH BETWEEN 2 BOLTS. I	NCLUDED:  PART CATALOGUE, PAGE 2-62, ITEM 68.  NOTE:  LEFT AILERON CASTING AND NDT INSPECTION CARRIED OUT.  NO CRACK FOU	ND.				2	L	7	4 	4J				2A15    					 
1998010800083	19980108	00083	SW  	1998	1	8	98ZZZX24         	1	19971112	G	6700	369A7301501	BEARING         			HUGHES	500N  	500N        	3027374	SW  										FLT CONT IDLER	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					0175					IDLER BELLCRANK HAS BOTH PIVOT BEARINGS PRE-LOADED TO A POINT OF NO ROTATION.  BINDING COULD CAUSE BOLT FAILURE.  FOUND 	ON INCOMING ACCEPTANCE INSPECTION.					1	G	7	1 	3U			NC	H3WE    					 
1998012200155	19980122	00155	SW  	1998	1	22	98ZZZX240        	1	19971121	G	6410	406016100119	BLADE           		407012101105	BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	42   			A1978	53044				DAILY INSPECTION FOUND CRACK AT ROOT END OF T/R BLADE ON THE INSIDE OF THE LEADING EDGE.  SUSPECT CAUSE IS HIGH STRESS A	REA.  PART IS UNSERVICEABLE.  INSTALLED BEEF-UP STRESS BLOCK IN LEADING EDGE AT ROOT END OF BLADE.					1	G	7	1 	3U			O	H2SW    					 
1998012200157	19980122	00157	NE  	1998	1	22	98ZZZX242        	1	19971209	G	6210	7615009100049	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741SW	11725			A08600881	760070				DISCOVERED DURING 11,750 HOUR INSPECTION, M/R BLADE, LOWER ROOT END LAMINATE DEBONDED BEYOND ALLOWABLE LIMITS PER SA4047	-76-5, CHAPTER 2.  SENT TO SIKORSKY AIRCRAFT FOR FURTHER EVALUATION/REPAIR.					1	G	7	2 	3U				H1NE    					 
1998012200158	19980122	00158	EU  	1998	1	22	98ZZZX243        	1	19971208	G	6210	355A11002006	BLADE           			AEROSP	AS355 	AS355F      	8680806	EU  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5773X	2150 			4382	5004				DISCOVERED DURING DAILY INSPECTION, M/R BLADE LOWER SURFACE SKIN CRACKED AT STA 1000 MM LEADING EDGE EROSION STRIPS DEBO	NDED.  REPAIRED BY CTI, RETURNED TO SERVICE.					1	G	7	2 	3U				H11EU   					 
1998012200159	19980122	00159	SW  	1998	1	22	98ZZZX244        	1	19971222	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R SHAFT	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				DISCOVERED DURING 25 HOUR INSPECTION, T/R DRIVE SHAFT NR 5 DISK PACK CRACKED ON AFT SIDE IN 2 PLACES.						1	G	7	1 	3U			O	H2SW    					 
1998012200160	19980122	00160	NE  	1998	1	22	98ZZZX245        	1	19970929	G	6210	7615009100049	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	708AL	11505	559  		A08601050	760277				MALFUNCTION WAS DISCOVERED DURING 11,750 HOUR INSPECTION, M/R BLADE ROOT END LAMIMATES DEBONDED BEYOND ACCCEPTABLE LIMIT	S.					1	G	7	2 	3U				H1NE    					 
1998012200161	19980122	00161	NE  	1998	1	22	98ZZZX246        	1	19970929	G	6210	7715009100049	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	708AL	11505	559  		A08601050	760277				DISCOVERED DURING EVALUATION OF BLADE ASSEMBLY PRIOR TO SHIPMENT TO REPAIR FACILITY, TIP RIB ASSEMBLY DEBONDED.						1	G	7	2 	3U				H1NE    					 
1998012200162	19980122	00162	EU  	1998	1	22	98ZZZX247        	1	19971209	G	6210	355A11002011	BLADE           			AEROSP	AS355 	AS355F      	8680806	EU  										M/R	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5773X	1594 			7403	5004				DISCOVERED DURING DAILY INSPECTION, FOUND M/R BLADE LEADING EDGE DAMAGED AT STA 3955 MM DUE TO IMPACT OF FOREIGN OBJECT.						1	G	7	2 	3U				H11EU   					 
1998012200163	19980122	00163	SW  	1998	1	22	98ZZZX248        	1	19971121	G	6510	406040340101	DISK PACK       		407040302101	BELL  	407   	407         		SW  										NR 5	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				FOUND DURING 25 HOUR AD INSPECTION, T/R DRIVESHAFT DISK PACK NR 5 HAS CRACKED COUPLING.  CRACKED ON AFT SIDE OF COUPLING	.  PACK CONSISTS OF 1 DISK.					1	G	7	1 	3U			O	H2SW    					 
1998012200164	19980122	00164	GL  	1998	1	22	98ZZZX249        	2	19971124	G	7210	6898642	GEAR            								ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	WORN            	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					29416					RECEIVING INSPECTION - RECEIVED GEAR FROM ALLISON, TAG INDICATED THE PART WAS NEW.  THE VISUAL INSPECTION OF GEAR INDICA	TED THE GEAR WAS USED AND UNSERVICEABLE BY AIR LOG ENGINE SHOP STANDARDS.										3	U			E1GL				 
1998010800084	19980108	00084	SW  	1998	1	8	98ZZZX25         	1	19971112	G	6700	369A7301501	BEARING         			HUGHES	500N  	500N        	3027374	SW  										FLT CONT IDLER	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					0186					IDLER BELLCRANK HAS BOTH PIVOT BEARINGS PRELOADED TO A POINT OF NO ROTATION.  FOUND DURING INCOMING ACCEPTANCE INSPECTIO	N.					1	G	7	1 	3U			NC	H3WE    					 
1998012200165	19980122	00165	SW  	1998	1	22	98ZZZX250        	1	19971204	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	DELAMINATED     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1068S	2517 			A1305	45436				DISCOVERED DURING DAILY INSPECTION, M/R BLADE SKIN DELAMINATED OVER SPAR AT TIP AND CORROSION OF TIP.						1	G	7	1 	3U				H2SW    					 
1998012200166	19980122	00166	NE  	1998	1	22	98ZZZX251        	1	19971211	G	7120	7630907007048	TUBE            			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE MOUNT	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	164AG					760290				DEFECT DISCOVERED DURING 1,750 HOURLY INSPECTION OF ENGINE MOUNTS.  WHILE BORESCOPING INSIDE OF TUBE, CORROSION WAS FOUN	D THAT EXCEEDED LIMITS.  INSIDE OF TUBE ASSEMBLY CORRODED AND PITTED.  SUBMITTER SUGGESTED USING BETTER CORROSION PREVEN	TATIVE METHODS.				1	G	7	2 	3U				H1NE    					 
1998012200167	19980122	00167	SW  	1998	1	22	98ZZZX252        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206SL	2975 			A1556	45245				DISCOVERED DURING DAILY INSPECTION, M/R BLADE HAD CORROSION AND SKIN DEBOND AT BLADE TIP.						1	G	7	1 	3U				H2SW    					 
1998012200168	19980122	00168	SW  	1998	1	22	98ZZZX253        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27545	1370 			A1856	45234				DISCOVERED DURING DAILY INSPECTION, M/R BLADE SPAR CRACKED AT TIP.						1	G	7	1 	3U				H2SW    					 
1998012200169	19980122	00169	SW  	1998	1	22	98ZZZX254        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	362AL	1421 			A1670	51471				DISCOVERED DURING DAILY INPSECTION, M/R BLADE SKIN CORRODED AND SEPARATED AT TIP AND RAILING EDGE EXTRUSION CORRODED.						1	G	7	1 	3U				H2SW    					 
1998012200170	19980122	00170	NE  	1998	1	22	98ZZZX255        	1	19971202	G	6210	7615009100051	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										M/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL	7208 	487  		A08601424	760002				DISCOVERED DURING 500-HOUR INSPECTION, M/R BLADE TIP RIB STRAP AND DOUBLERS DEBONDED.						1	G	7	2 	3U				H1NE    					 
1998012200171	19980122	00171	SW  	1998	1	22	98ZZZX256        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										M/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	365AL	2445 			A1639	51376				DISCOVERED DURING DAILY INSPECTION, M/R BLADE SPAR CRACKED AT TIP.						1	G	7	1 	3U				H2SW    					 
1998012200172	19980122	00172	SW  	1998	1	22	98ZZZX257        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3890B	2890 			A1323	45480				DISCOVERED DURING DAILY INSPECTION, SKIN CORROSION AND SEPARATION AT TIP.						1	G	7	1 	3U				H2SW    					 
1998012200173	19980122	00173	SW  	1998	1	22	98ZZZX258        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3890B	2758 			A1398	45480				DISCOVERED DURING DAILY INSPECTION, M/R BLADE SKIN SEPARATED AND CORRODED AT TIP.						1	G	7	1 	3U				H2SW    					 
1998012200174	19980122	00174	SW  	1998	1	22	98ZZZX259        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3890B	2951 			A1254	45480				DISCOVERED DURING DAILY INSPECTION, M/R BLADE SKIN SEPARATED AND CORRODED AT TIP.						1	G	7	1 	3U				H2SW    					 
1998010800085	19980108	00085	SW  	1998	1	8	98ZZZX26         	1	19971112	G	6700	369A7301501	BEARING         			HUGHES	500N  	500N        	3027374	SW  										FLT CONT IDLER	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					0148					IDLER BELLCRANK HAS BOTH PIVOT BEARINGS PRELOADED TO A POINT OF NO ROTATION.  FOUND ON INCOMING ACCEPTANCE INSPECTION.						1	G	7	1 	3U			NC	H3WE    					 
1998012200175	19980122	00175	SW  	1998	1	22	98ZZZX260        	1	19971209	G	6510	NAS6604D50	BOLT            			BELL  	407   	407         		SW  										T/R DRV SUPPORT	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	1569 				53044				SCHEDULED MAINTENANCE FOUND TAIL ROTOR DRIVESHAFT NR 2 BOLT WORN OR STEPPED, FRETTING.						1	G	7	1 	3U			O	H2SW    					 
1998080700176	19980807	00176	EA  	1998	8	7	98ZZZX2609       	2	19971217	G	8520	SL75060	BOLT            			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					CONNECT ROD	FAILED          	D				A				UNSCHED LANDING         				B	K	R	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	CL	CLIMB          	1			WP	07	21018	1063 				32R7887186	L560461A			APPEARS THAT THE CONNECTING ROD BOLT FAILED ALLOWING THE CONNECTING ROD TO SEPARATE FROM THE CRANKSHAFT.  THE CONNECTING	 ROD SEPARATED FROM THE CRANKSHAFT SOON AFTER TAKEOFF.  OIL COVERED THE WINDSHIELD AND SMOKE FILLED THE COCKPIT.  A SUCC	ESSFUL LANDING WAS MADE.  THE ENGINE, FOR ABOUT THE PREVIOUS 200 HOURS, HAD A SLIGHT VIBRATION THAT COULD NOT BE PINPOIN	TED.			1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1998012200176	19980122	00176	SW  	1998	1	22	98ZZZX261        	1	19971209	G	6510	406040322101	BEARING         			BELL  	407   	407         		SW  										T/R DRIVE HANGER	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	1569 				53044				SCHEDULED MAINTENANCE FOUND TAIL ROTOR DRIVESHAFT NR 2 HANGER BEARING ROUGH AND WORN, AXIAL PLAY.						1	G	7	1 	3U			O	H2SW    					 
1998080700180	19980807	00180	CE  	1998	8	7	98ZZZX2613       	1	19971228	G	3230	504100112	BELLCRANK       			CESSNA	310   	T310R       	2074246	CE  										RT MLG	FAILED          	B		A	VIB4	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	05	310RH	1916 				310R1878				AIRCRAFT INSPECTED FOR THE CAUSE OF THE RIGHT MAIN LANDING COLLAPSE ON LANDING.  FOUND THAT PARTS OF THE BELLCRANK ASSEM	BLY (P/N 5041001-12) HAD FAILED.  THE BOLT (P/N NAS464P4-26) AT THE UPPER END OF THE BELLCRANK HAD BROKEN AND THE END-FI	TTING (P/N 0841111-3) AT THE LOWER END OF THE BELLCRANK HAD ALSO BROKEN.  SUSPECT THE RIGHT LANDING GEAR HAD EXPERIENCED	 EXCESSIVE SIDE LOAD AT SOME TIME.			1	L	7	2 	3O				3A10    					 
1998080700181	19980807	00181	CE  	1998	8	7	98ZZZX2614       	1	19971228	G	3230	08411113	FITTING         			CESSNA	310   	T310R       	2074246	CE  										RT MLG BELLCRANK	FAILED          	B			VIB4	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	05	310RH	1916 				310R1878				AIRCRAFT INSPECTED FOR THE CAUSE OF THE RIGHT MAIN LANDING COLLAPSE ON LANDING.  FOUND THAT PARTS OF THE BELLCRANK ASSEM	BLY (P/N 5041001-12) HAD FAILED.  THE BOLT (P/N NAS464P4-26) AT THE UPPER END OF THE BELLCRANK HAD BROKEN AND THE END-FI	TTING (P/N 0841111-3) AT THE LOWER END OF THE BELLCRANK HAD ALSO BROKEN.  SUSPECT THE RIGHT LANDING GEAR HAD EXPERIENCED	 EXCESSIVE SIDE LOAD AT SOME TIME.			1	L	7	2 	3O				3A10    					 
1998080700182	19980807	00182	CE  	1998	8	7	98ZZZX2615       	1	19971228	G	3230	NAS464P426	BOLT            			CESSNA	310   	T310R       	2074246	CE  										RT MLG	FAILED          	B			VIB4	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	05	310RH	1916 				310R1878				AIRCRAFT INSPECTED FOR THE CAUSE OF THE RIGHT MAIN LANDING COLLAPSE ON LANDING.  FOUND THAT PARTS OF THE BELLCRANK ASSEM	BLY (P/N 5041001-12) HAD FAILED.  THE BOLT (P/N NAS464P4-26) AT THE UPPER END OF THE BELLCRANK HAD BROKEN AND THE END-FI	TTING (P/N 0841111-3) AT THE LOWER END OF THE BELLCRANK HAD ALSO BROKEN.  SUSPECT THE RIGHT LANDING GEAR HAD EXPERIENCED	 EXCESSIVE SIDE LOAD AT SOME TIME.			1	L	7	2 	3O				3A10    					 
1998080700183	19980807	00183	SO  	1998	8	7	98ZZZX2616       	2	19971230	G	8520		CRANKSHAFT      			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					RT ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	99	3378Q		77   			402B0334	18235172ER			ENGINE SHUT DOWN DURING FLIGHT FROM HOUSTON TO DALLAS.  UPON TEAR DOWN, DISCOVERED THAT THE CRANKSHAFT HAD BROKEN.  SUBM	ITTER STATED CAUSE IS UNKNOWN PENDING FURTHER INVESTIGATION.					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1998012200177	19980122	00177	SW  	1998	1	22	98ZZZX262        	1	19971209	G	6510	407040321101	BRACKET         			BELL  	407   	407         		SW  										T/R DRIVESHAFT	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	1569 				53044				SCHEDULED MAINTENANCE FOUND NR 2 TAIL ROTOR DRIVESHAFT FORWARD BRACKET UPPER BOLT HOLE WORN ELLIPTICAL.						1	G	7	1 	3U			O	H2SW    					 
1998012200178	19980122	00178	SW  	1998	1	22	98ZZZX263        	1	19971118	G	6322	206061432116	BLOWER HOUSING  			BELL  	407   	407         		SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	1442 				53054				BLOWER REMOVED BECAUSE OF ROUGH BEARINGS.  HOUSING ALSO CRACKED.  SHEET METAL HOUSING CRACKED AT RIVETED EDGE WHERE HOUS	ING ATTACHES TO 407-062-021-101 OIL COOLER DUCT ASSEMBLY.  SUBMITTER SUGGESTED THAT POSSIBLY A POOR FIT PUTTING STRAIN O	N SHEET METAL WHEN ATTACHED TO DUCT.				1	G	7	1 	3U			O	H2SW    					 
1998012200179	19980122	00179	SW  	1998	1	22	98ZZZX264        	1	19971127	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL					53044				IN C/W AD 97-24-17 DURING PHASE 6, FOUND ONE CRACKED LAMINATE OF TAIL  ROTOR DRIVESHAFT DISK PACK AT NR 7 HYDRAULIC FORW	ARD LAMINATE.					1	G	7	1 	3U			O	H2SW    					 
1998012200355	19980122	00355		1998	1	22	98ZZZX265        	1	19971031	G	7714	1179405603	INDICATOR       																	ENGINE NG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					634					NG INDICATOR FAILED.  REMOVED AND REPLACED.																			 
1998012200356	19980122	00356		1998	1	22	98ZZZX266        	1	19971115	G	7722	50061036	INDICATOR       																	EXHAUST TEMP	MISWIRED        	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					175					EXHAUST TEMPERATURE INDICATOR WIRED INCORRECTLY.  REMOVED AND REPLACED.																			 
1998012200357	19980122	00357	EU  	1998	1	22	98ZZZX267        	1	19971106	G	6210	1051585403	BUSHING         			BOLKMS	117   	BK117B1     	5626012	EU  										M/R BLADE	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										BUSHING HAS DEFECTIVE PHONELIC LINING.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012200358	19980122	00358	EU  	1998	1	22	98ZZZX268        	1	19971125	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE NG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				403	7061				NG INDICATOR SLOW TO INDICATE, FALLS OFF-LINE AT 5 PERCENT ON DECELERATION.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998081400151	19980814	00151	EA  	1998	8	14	98ZZZX2683       	2	19970201	G	8530	05K21108CKP	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 2 EXH VALVE	FAILED          	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	611DF	73   				318052188	L721861A			EXHAUST VALVE FAILURE IN NR 3 CYLINDER RESULTED IN THE INGESTING OF THE VALVE INTO THE CYLINDER BORE.  THIS CAUSED EXTEN	SIVE DAMAGE TO THE COMBUSTION CHAMBER AND PISTON.  METAL WAS THEN PASSED THROUGH ENTIRE ENGINE OIL SYSTEM.  DAMAGED PART	S INCLUDE ALL BEARINGS AND OIL PUMP IMPELLERS.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998081400152	19980814	00152	EA  	1998	8	14	98ZZZX2684       	2	19971101	G	8530	05K21108CKP	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 1 EXH VALVE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	611DF	123  				318052188	L721861A			EXHAUST VALVE FAILURE IN NR 1 CYLINDER RESULTED IN THE INGESTING OF THE VALVE INTO THE CYLINDER BORE.  THIS CAUSED EXTEN	SIVE DAMAGE TO THE COMBUSTION CHAMBER AND PISTON.  METAL WAS THEN PASSED THROUGH ENTIRE ENGINE OIL SYSTEM.  DAMAGED PART	S INCLUDE ALL BEARINGS AND OIL PUMP IMPELLERS.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998081400155	19980814	00155	SW  	1998	8	14	98ZZZX2687       	1	19971212	G	2434	1101876	GENERATOR       	DELCO       		BBAVIA	7     	S7DC        	21101NG	SW  	CONT  	C85   	C8512F      	17008	SO  					DC SYSTEM	FAILED          	H	P			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	03	84L				16430	7DC3228	2805G712			PARTS 530412 NUT, 2.531325 GEAR 530407, SLEEVE 4.632050 BUSHING 352030 RETAINER.  THESE COMPONENTS FAILED CAUSING THE GE	NERATOR SHAFT TO FAIL.  THE PARTS WERE CHEWED UP BY THE CAMSHAFT GEAR AND METAL CONTAMINATED THE OIL SYSTEM.  THE ACCESS	ORY CASE WAS ALSO DAMAGED BEYOND REPAIR.  THERE WERE SEVERAL BAD NICKS AND GOUGES BY THE OIL PUMP HOUSING.  REQUIRED ENG	INE TEAR DOWN AND MAJOR OVERHAUL.			1	H	7	1 	3O	3	O		A759    	E233				 
1998012200359	19980122	00359	EU  	1998	1	22	98ZZZX269        	1	19971112	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE NG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				634	7061				NG INDICATOR SLOW TO INDICATE.  FALLS OFF-LINE ON DECELERATION AT 8 PERCENT.  READS ALMOST 2 PERCENT LOW.  REMOVED AND R	EPLACED.					1	G	7	2 	3U				H13EU   					 
1998010800086	19980108	00086	SW  	1998	1	8	98ZZZX27         	1	19971112	G	6700	369A7301501	BEARING         			HUGHES	500N  	500N        	3027374	SW  										FLT CONT IDLER	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					0146					IDLER BELLCRANK FOUND TO HAVE BOTH PIVOT BEARINGS PRELOADED TO A POINT OF NO ROTATION.  FOUND ON ACCEPTANCE INSPECTION.						1	G	7	1 	3U			NC	H3WE    					 
1998012200360	19980122	00360	EU  	1998	1	22	98ZZZX270        	1	19971106	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE NG	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				735	7061				NG INDICATOR SLOW TO INDICATE AND FALLS OFF-LINE ON DECELERATION.  PREVIOUSLY SENT FOR WARRANTY REPAIR ON P.O. 93129.  F	AILED APPROXIMATELY ONE WEEK AFTER INSTALLATION.					1	G	7	2 	3U				H13EU   					 
1998012200361	19980122	00361	EU  	1998	1	22	98ZZZX271        	1	19971009	G	2430	SP461300	SWITCH          			BOLKMS	117   	BK117B1     	5626012	EU  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117LU					7144				SWITCH WILL NOT STAY ENGAGED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012200362	19980122	00362	EU  	1998	1	22	98ZZZX272        	1	19971028	G	6720	11731822	PITCH LINK ASSY 			BOLKMS	BK117 	BK117C1     	5626025	EU  										TAIL ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	333  				7509				PITCH LINK ASSY (2 EACH) BEARINGS WORN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012200363	19980122	00363		1998	1	22	98ZZZX273        	4	19971104	G	2211	11788292	COMPUTER        			BOLKMS	BK117 	BK117C1     	5626025	EU  										SPAS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC				1191243	7509				SPAS COMPUTER HAS IMPROPER OUTPUT VOLTS.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012200364	19980122	00364	EU  	1998	1	22	98ZZZX274        	1	19971110	G	7714	1179405303	TRIPLE TACH     			BOLKMS	117   	BK117B1     	5626012	EU  										ENGINE N2	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	214AE	3    			282	7206				TRIPLE TACHOMETER N2 NEEDLE HANGS UP AT 98 PERCENT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012200365	19980122	00365	EU  	1998	1	22	98ZZZX275        	1	19971028	G	6240	1179405303	TRIPLE TACH     			BOLKMS	117   	BK117B1     	5626012	EU  										ROTOR RPM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	214AE				460	7206				TRIPLE TACHOMETER ROTOR RPM NEEDLE LAGS N2'S IN-FLIGHT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012200366	19980122	00366		1998	1	22	98ZZZX276        	4	19971031	G	3416	10222011886	ALTIMETER       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT ENCODER	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				143025	7505				ALTIMETER DROPS 300 FEET AT 10,000 FEET.  WILL NOT HOLD ALTITUDE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012200367	19980122	00367	SW  	1998	1	22	98ZZZX277        	1	19971104	G	6720	230312001101	PITCH LINK      			BELL  	230   	230         	1182149	SW  										TAIL ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				PITCH LINK WORN OUT OF LIMITS.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H9SW    					 
1998012200368	19980122	00368	SW  	1998	1	22	98ZZZX278        	1	19971107	G	6330	222330620103	BEARING         			BELL  	230   	230         	1182149	SW  										XMSN MOUNT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				MOUNT BEARING WORN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1998081400392	19980814	00392	EU  	1998	8	14	98ZZZX2783       	1	19970121	G	5511	315A3510000101	SPAR            			AEROSP	SA316 	SA315B      	8680615	EU  										HORIZ STABILIZER	CRACKED         	B			LH3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	27443				7R368	2426				SPAR TUBE CRACKED AT RT MOUNTING HOSE, CRACK ORIGINATES AT MOUNTING HOLE AND EXTENDS IN BOTH DIRECTION COVERING 50 PERCE	NT OF NBE CIRCUMFERENCE.  THIS DEFECT WAS FOUND WHEN THE STABILIZER WAS BROUGHT IN FOR REPAIR OR WORN MOUNTING BUSHINGS.	  THIS CRACK COULD NOT BE SEEN AS IT IS COVERED BY HALF SHELL REINFORCEMENTS.  SUBMITTER STATED LACK OF PREVENTATIVE MAI	NTENANCE, NOT FOLLOWING INSPECTION SCHEDULES.  T/R OUT OF BALANCE FOR EXTENDED PERIODS.			1	G	7	1 	4U				H1IN    					 
1998012200369	19980122	00369	SW  	1998	1	22	98ZZZX279        	1	19971112	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	286  				23019				SHUNT WORN AND DISCOLORED.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U			NC	H9SW    					 
1998010800087	19980108	00087	SW  	1998	1	8	98ZZZX28         	1	19971112	G	6700	369A7301501	BEARING         			HUGHES	500N  	500N        	3027374	SW  										FLT CONT IDLER	BINDING         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07					0142					IDLER BELLCRANK FOUND TO HAVE BOTH PIVOT BEARINGS PRELOADED TO THE POINT OF NO ROTATION OF BEARING.  FOUND ON INCOMING P	ARTS INSPECTION.					1	G	7	1 	3U			NC	H3WE    					 
1998012200370	19980122	00370	SW  	1998	1	22	98ZZZX280        	1	19971107	G	6330	222331617101	MOUNT           			BELL  	230   	230         	1182149	SW  										TRANSMISSION	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				LK0192	23019				ISOLATION MOUNT HAS WORN BEARING.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW    					 
1998012200371	19980122	00371		1998	1	22	98ZZZX281        	4	19971105	G	2312	4000102000	TRANSCEIVER     		RT138       	BELL  	222   	222         	1182122	SW  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MK				1408	47515				UPON INITIAL TRANSCEIVER INSTALLATION, CIRCUIT BREAKER TRIPS WHEN TRANSMITTER BUTTON IS KEYED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1998012200372	19980122	00372		1998	1	22	98ZZZX282        	4	19971113	G	3421	4021541671	ARTIFICIAL HORIZ		92082227    	BOLKMS	117   	BK117A3     	5626015	EU  										CSAS PITCH	NOISY           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ					7098				ARTIFICIAL HORIZ CAUSES CSAS PITCH ACTUATOR TO FLUCTUATE.  SIGNAL OUT OF PINS, X AND Y ARE TOO NOISY SIMULATING PITCH UP	 OR DOWN.  REMOVED AND REPLACED.					1	G	7	2 	3U				H13EU   					 
1998012200373	19980122	00373		1998	1	22	98ZZZX283        	4	19971113	G	2211	7004206901	COMPUTER        			BOLKMS	117   	BK117A3     	5626015	EU  										CSAS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				89040228	7098				CSAS COMPUTER CAUSES FLUCTUATIONS IN PITCH ACTUATOR.  NOISY SIGNAL COMING OUT OF PINS 18 AND 19.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012200374	19980122	00374	SW  	1998	1	22	98ZZZX284        	1	19971125	G	7120	222060150001	MOUNT           			BELL  	222   	222U        	1182140	SW  										BEARING	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	222HX	284  				47533				ENGINE MOUNT BEARING NOT PROPERLY STAKED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1998012200378	19980122	00378		1998	1	22	98ZZZX288        	4	19971223	G	6122	210735	GOVERNOR        	WOODWARD    		GULSTM	690TP 	690B        	7630516	SW  										PROPELLER	SEIZED          	B			R2JR	E	C	D		ENGINE SHUTDOWN         	ABORTED TAKEOFF         	RETURN TO BLOCK         		J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			EA	21	690HT		2139 		147543814	11467				ON TAXI, ENGINE HAD TO BE SHUT DOWN DUE TO LOW RPM AND HIGH ITT IN BETA.  MAINTENANCE DISCOVERED PROPELLER GOVERNOR HAD 	FAILED INTERNALLY CAUSING MODERATE AMOUNTS OF GROUND METAL TO BE PUMPED INTO NOSE CASE.  GOVERNOR SHAFT SEIZED.  ENGINE 	REMOVED FOR TEAR-DOWN INSPECTION DUE TO ZERO TORQUE AND HIGH OIL PRESSURE AFTER GOVERNOR WAS CHANGED.  SUSPECT METAL CON	TAMINATION.  OIL COOLER, ENGINE, AND OIL CHANGED.  ALL OIL LINES FLUSHED.  GOV SENT TO GARRETT AND ENGINE SENT TO GARETT	 SERVICE CENTER.  GARRETT P/N IS 894418-6Y.		1	H	7	2 	3T				2A4     					 
1998012200379	19980122	00379	SW  	1998	1	22	98ZZZX289        	1	19971217	G	6720	2060017631	BELLCRANK       			BELL  	206   	206L1       	1182107	SW  										ANTI TORQUE	MISMANUFACTURED 	B		A	ZV1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										DURING REPLACEMENT OF COMPONENTS FOUND COULD NOT RIG TAIL ROTOR FOR FULL PEDAL MOVEMENT.  TROUBLESHOOTING FOUND THAT BEL	LCRANK P/N 206-001-763-1 AND ROD ASSY P/N 206-011-751-101 WERE CONTACTING.  FOUND THAT BELLCRANK DID NOT HAVE THE PROPER	 DEPTH GROOVE MACHINED IN IT.  FOUND 2 OTHER BELLCRANKS IN STOCK WITH SAME PROBLEM.  BELL WAS CONTACTED.				1	G	7	1 	3U				H2SW    					 
1998010800088	19980108	00088	CE  	1998	1	8	98ZZZX29         	1	19971003	G	5711		SPAR            			BEECH 	18    	H18         	1151012	CE  										LT WS 32,46,81	CORRODED        	B			NI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	117ME					BA638				CORROSION REVEALED ON FRONT SPAR LT WS 32, WS 46, AND WS 81 AND RT WS 32.  REF:  AD 75-27-09 R2 AND AMDT 39-3878.						1	L	7	2 	3R				A765    					 
1998012200387	19980122	00387	GL  	1998	1	22	98ZZZX297        	2	19971207	G	7323	23057869	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5366Y	7134 			85520222	S782				FLUCTUATING TORQUE SETTING.  FOUND GOVERNOR DRIVE BROKEN.  REPLACED GOVERNOR.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1998012200388	19980122	00388	SW  	1998	1	22	98ZZZX298        	1	19971112	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2611					45417				EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3 FIG 62-21.  ON TEAR-DOWN, 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    					 
1998012200389	19980122	00389	SW  	1998	1	22	98ZZZX299        	1	19971112	G	6230	206010336005	DRIVE SHAFT     			BELL  	206   	206L3       	1182108	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2616					51418				EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3, FIG 62-21.  ON TEAR-DOWN, FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.	  TOTAL TIMES OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW    					 
1998010800062	19980108	00062	CE  	1998	1	8	98ZZZX3          	1	19971101	G	5347	CM32031	SEAT RAIL       			CESSNA	500   	550         	2076604	CE  										COPILOT RT OTBD	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	84EA	6514 				550484				DURING PHASE 5 INSPECTION, FOUND HOLES WORN TO LIMITS AT CO-PILOT'S RIGHT SEAT RAIL HATCH.  SPLICED IN NEW SECTION OF SE	AT RAIL IAW CESSNA 550 SRM FIGURE 801.					1	L	7	2 	4F				A22CE   					 
1998010800089	19980108	00089	CE  	1998	1	8	98ZZZX30         	1	19971003	G	5711		SPAR            			BEECH 	18    	H18         	1151012	CE  										RT WS 32	CORRODED        	B			NI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	117ME					BA638				CORROSION REVEALED ON FRONT SPAR LT WS 32, WS 46, AND WS 81 AND RT WS 32.						1	L	7	2 	3R				A765    					 
1998012200390	19980122	00390	SW  	1998	1	22	98ZZZX300        	1	19971112	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L3       	1182108	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2619					51375				EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3, FIG 62-21.  ON TEAR-DOWN, FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.	  TOTAL TIMES OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW    					 
1998012200391	19980122	00391	SW  	1998	1	22	98ZZZX301        	1	19971114	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3899C				RH0682	45596				EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3, FIG 62-21.  ON TEAR-DOWN, FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.	  TOTAL TIMES OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW    					 
1998012200392	19980122	00392	SW  	1998	1	22	98ZZZX302        	1	19971114	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										M/R MAST	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2621				4132	45400				EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3, FIG 62-21.  ON TEAR-DOWN, FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS.	  TOTAL TIMES OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW    					 
1998012200393	19980122	00393	SW  	1998	1	22	98ZZZX303        	1	19971109	G	6510	406040340101	DISC PACK       		407040302101	BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL				RNFS7130	53044				WHILE C/W AD 97-22-15, FOUND T/R DRIVE DISC PACK CRACKED BETWEEN NR 6 AND NR 7.  SUBMITTER RECOMMENDS FLOATING DRIVESHAF	TS SIMILAR TO THE BELL 206 SERIES.					1	G	7	1 	3U			O	H2SW    					 
1998012200394	19980122	00394	SW  	1998	1	22	98ZZZX304        	1	19971109	G	6510	406040340101	DISC PACK       		407040302101	BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL				RNFS7132	53054				C/W OF AD 97-22-15, FOUND T/R DRIVE COUPLING DISC PACK AFT LAMINATE 'ONE' CRACKED BETWEEN NR 6 AND NR 7.  SUBMITTER RECO	MMENDS FLOATING DRIVESHAFTS SIMILAR TO THE BELL 206 SERIES.					1	G	7	1 	3U			O	H2SW    					 
1998012200395	19980122	00395	SW  	1998	1	22	98ZZZX305        	1	19971111	G	6322	406040339105	BEARING         		407040303101	BELL  	407   	407         		SW  										NR 2 T/R DRIVE	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	1032 			D960750	53107				TWENTY-FIVE HOUR INSPECTION FOUND OIL COOLER BLOWER BEARINGS ROUGH.  ALSO, SHAFT SPLINES SHOW SIGNS OF LACK OF LUBRICATI	ON.  SUBMITTER RECOMMENDED IMPROVING BEARING AND LUBRICATION ON SHAFT TO COUPLING SPLINES.					1	G	7	1 	3U			O	H2SW    					 
1998012200396	19980122	00396	SW  	1998	1	22	98ZZZX306        	1	19971111	G	6322	406040339105	BEARING         		407040303101	BELL  	407   	407         		SW  										NR 2 T/R DRIVE	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	1032 			D960728	53107				TWENTY-FIVE HOUR INSPECTION FOUND OIL COOLER BLOWER BEARINGS ROUGH.  ALSO, SHAFT SPLINES SHOW SIGNS OF LACK OF LUBRICATI	ON.  SUBMITTER RECOMMENDED IMPROVING BEARING AND LUBRICATION ON SHAFT TO COUPLING SPLINES.					1	G	7	1 	3U			O	H2SW    					 
1998010800090	19980108	00090	SO  	1998	1	8	98ZZZX31         	1	19971203	G	5210	4756400	AUXILIARY LOCK  		5661705     	PIPER 	PA42  	PA42        	7104202	SO  										CABIN DOOR	FAILED          	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			SW	99	4100L	5686 				428001061				JUST PRIOR TO VR, DOOR HANDLE ROTATED AND DISENGAGED PINS.  PILOT ABORTED TAKEOFF, CLOSED DOOR, AND TAXIED BACK TO PARKI	NG.  INITIAL INSPECTION REVEALED THAT AUXILIARY LOCK DID NOT ENGAGE.					1	L	7	2 	4T				A23SO   					 
1998012200400	19980122	00400	SW  	1998	1	22	98ZZZX310        	1	19971110	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				AD 97-22-15, 25-HOUR TAIL BOOM INSPECTION FOUND CRACKED DISCS NR 2 TO NR 3, NR 1 DISC IN PACK CRACKED, NR 5 TO NR 6 LOCA	TION NR 10 DISC IN PACK CRACKED.  SUBMITTER RECOMMENDED FLOATING DRIVESHAFTS SIMILAR TO THE BELL 206 SERIES.					1	G	7	1 	3U			O	H2SW    					 
1998012900081	19980129	00081	SO  	1998	1	29	98ZZZX312        	1	19970109	G	5310		FRAME           			PIPER 	PA25  	PA25        	7102502	SO  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	6410Z	3006 				25546				CORROSION AT TUBING CLUSTER 27 INCHES AFT OF FIREWALL ON LOWER LONGERON.  GUSSETS SUPPORTING THE VERTICAL MEMBER HAD ALL	OWED DEBRIS AND MOISTURE TO COLLECT ON LONGERON.  LONGERON WAS PERFORATED BY RUST FORE AND AFT OF VERTICAL MEMBER ON RT 	SIDE.  A SMALLER PERFORATION EXISTED IN FRONT OF VERTICAL MEMBER ON LT SIDE.  GUSSET AREA APPARENTLY FILLED WITH A SEALA	NT AT TIME OF MFG.  THIS HAD BEEN REMOVED AND RTV SUBSTITUTED IN ITS PLACE.  SUBMITTER BELIEVES CORROSION EXISTED PRIOR 	TO RTV APPLICATION.		1	L	7	1 	3O				2A10    					 
1998012900082	19980129	00082	EA  	1998	1	29	98ZZZX313        	2	19971202	G	8520	18486	CRANKSHAFT      			UNIVAR	108   	1082        	9230406	NM  	FRNKLN	6A4165	6A4165B3    	27025	EA  					PROP FLANGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	9504K	406  				1082504	3153			INSPECTION FOUND CRANKSHAFT PROPELLER FLANGE CRACKED BETWEEN HOLES IN TWO PLACES.						1	H	7	1 	3O	3	O		A767    	E238				 
1998012900085	19980129	00085	SW  	1998	1	29	98ZZZX316        	1	19971222	G	7931	98087	SWITCH          			GULSTM	560   	560         	0141402	SW  										LT ENG OIL PRESS	LEAKING         	B			BXSR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	09	500UB	2685 				5600052				LARGE AMOUNTS OF OIL WERE LEAKING FROM THE RT ENGINE.  FOUND THE OIL PRESSURE SWITCH INTERNAL SEAL HAD FAILED.						1	H	7	2 	3O				6A1     					 
1998012900088	19980129	00088	SO  	1998	1	29	98ZZZX319        	1	19970625	G	2435	30E20111B	GENERATOR       			GULSTM	G1159 	G1159B      	3953535	SO  										BRUSHES	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	338AX		29   		1503	30				BLACK SOOT ON COWLING.  CHECKED GENERATOR BRUSHES AND FOUND UNDER ONE-QUARTER LIFE REMAINING.						2	L	7	2 	4F			RT	A12EA   					 
1999013000004	19990130	00004	GL  	1999	1	30	98ZZZX3195       	1	19971231	G	5102		ENVELOPE        	CAMRON      		CAMRON	R420  	R420        		GL  										APPENDIX	FAILED          	C		A		O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			WP	07	GJNEE	1    				4232				BALLOON APPENDICES FAILED TO VENT HELIUM FROM THE GAS CELL RESULTING IN RUPTURE OF THE BOTTOM HALF OF THE CELL.  APPROXI	MATELY ONE HOUR AFTER LAUNCH AT APPROXIMATELY 21,000 FEET, THE GAS CELL RUPTURED WHILE ASCENDING AT APPROXIMATELY 500 FP	M.  SUSPECT CAUSE, THE APPENDIX TORE LOOSE FROM THEIR ATTACHMENT POINTS.  THE LOWER PORTION OF THE APPENDIX AT THE CELL 	ATTACHMENT RIPPED DUE TO THE WEIGHT OF THE UNRESTRAINED APPENDIX WHICH ALSO CAUSED THE APPENDIX TO SEAL OFF THE HELIUM E	XIT POINT AT THE CELL RESULTING IN OVERPRESSURIZATION.  RECOMMENDED SEWING APPENDIX CONTINUOUSLY TO ENVELOPE.		1	B	0	0 	3X			NC	EXPA1B00					 
1998010800091	19980108	00091	CE  	1998	1	8	98ZZZX32         	1	19971108	G	7602	S12203	CONTROL CABLE   			CESSNA	210   	210B        	2073410	CE  										MIXTURE	DEFECTIVE       	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	14	4345X					21058033				UPON INSTALLATION, TWO NEW MIXTURE CABLES FROM CESSNA WERE FOUND DEFECTIVE IN THE VERNIER LOCK WHICH COULD CAUSE THE MIX	TURE TO FLOAT OR JAM.  ZERO HOURS ON PART.					1	H	7	1 	3O			 	3A21    					 
1998012900089	19980129	00089	CE  	1998	1	29	98ZZZX320        	1	19970411	G	5210		DOOR            			RAYTHN	DH125 	HAWKER800XP 		CE  										DOOR ATTACH	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	404BS					258294				DURING A SCHEDULED INSPECTION OF THE CABIN DOOR ATTACH POINTS, FOUND BOTH ATTACH POINT BOLTS, CASTELLATED NUTS WERE MISS	ING COTTER PINS AND VERY LOOSE.  NOTED THAT NEITHER BOLT WAS DRILLED TO ACCEPT A COTTER PIN.  IN FACT, ONE OF THESE BOLT	S WAS SO LONG IT WAS RUBBING AGAINST THE ADJACENT STRUCTURE AS THE DOOR WAS OPENED AND CLOSED.  THIS WAS THE FIRST TIME 	THIS AREA WAS OPENED FOR INSPECTION SINCE DELIVERY OF THE AIRCRAFT FROM RAYTHEON, LITTLE, ROCK, ARK.			2	L	7	2 	4F			RT	A3EU    					 
1998012900090	19980129	00090	CE  	1998	1	29	98ZZZX321        	1	19971204	G	5210		DOOR            			RAYTHN	DH125 	HAWKER800XP 		CE  										CABIN	NOISY           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	404BS					258294				PILOT REPORTED GRINDING NOISE COMING FROM CABIN DOOR WHEN DOOR WAS OPENED OR CLOSED.  UPON INSPECTION OF DOOR INTERIOR S	TRUCTURE AND COMPONENTS, A NR 11 DRILL BIT WAS FOUND JAMMED BETWEEN TENSATOR MOTOR ASSY AND DOOR STRUCTURE.  NO DAMAGE N	OTED.  GRINDING NOISE STOPPED AFTER DRILL BIT WAS REMOVED.  THIS WAS THE FIRST ACCESS OF DOOR INTERIOR AFTER DELIVERY FR	OM RAYTHEON, LITTLE ROCK, ARK.			2	L	7	2 	4F			RT	A3EU    					 
1998012900091	19980129	00091	EU  	1998	1	29	98ZZZX322        	1	19971218	G	2150	51590000	ACM             			BAG   	JETSTM	JETSTM3201  	1500217	EU  										CABIN AIR	OVERSERVICED    	D		A		O				OTHER                   				B	W		SMOKE/FUMES/ODORS/SPARKS  	INADEQUATE Q C            		DE	DESCENT        	1			SO	03	861AE				A0406321	861				WHILE PERFORMING A FLIGHT IDLE DESCENT RATE CHECK FLIGHT, THE COCKPIT FILLED WITH SMOKE. THE CAPTAIN DECLARED AN EMERGEN	CY AND STARTED EMERGENCY PROCEDURES.  THE SMOKE SMELLED LIKE OIL.  THE CAPTAIN SHUT OFF BOTH BLEEDS.  THE SMOKE STOPPED 	AND THE SMELL DIMINISHED.  GROUND CHECKED AND FOUND THE LT ACM OVERSERVICED.  PROPERLY SERVICED BOTH ACM'S AND RAN AIRCR	AFT ON THE GROUND FOR OVER AN HOUR.  NO FURTHER DISCREPANCY WAS NOTICED.			2	L	7	2 	4T			RT	A56EU   					 
1998012900094	19980129	00094	EU  	1998	1	29	98ZZZX325        	2	19970804	G	7412	NB34	IGNITER         			GULSTM	G1159 	G1159B      	3953535	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	338AX				3352	30				IGNITER UNIT OVERHAULED 11 MONTHS, 138 HOURS, 66 CYCLES AGO.  FAILED OPS INSPECTION WITH DISCHARGE ONLY EVERY 5-6 SECOND	S.  SHOULD BE APPROXIMATELY 1 SECOND.					2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
1998091100050	19980911	00050	EA  	1998	9	11	98ZZZX3266       	2	19970127	G	8550	LW15628	SEAL            			PIPER 	PA31  	PA31P350    	7103111	SO  	LYC   	O540  	TIO540V2AD  	41532	EA  					PROPELLER SHAFT	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CE	03	134DE	1436 				31P8414005	L839861A			WHILE IN CRUISE AT FL 250, PROPELLER RPM WAS TO 1200 AND OIL PRESSURE TO ZERO.  ENGINE WAS FEATHERED AND SHUT DOWN AND A	 SAFE LANDING WAS MADE.  INVESTIGATION REVEALED PROPELLER SHAFT SEAL HAD COME LOOSE AND WAS LOOSE ON SHAFT.  SUSPECT BRE	ATHER SYSTEM HAD FROZEN AND CAUSED CRANKCASE PRESSURE RESULTING IN SEAL BEING DISLODGED.  BREATHER SYSTEM WAS INSPECTED 	AND CLEANED.  NEW SEAL WAS INSTALLED AND OIL FILTER WAS CHECKED AND FOUND OK.			1	L	7	2 	3O	3	O	RT	A8EA    	E14EA				 
1998012900097	19980129	00097	EU  	1998	1	29	98ZZZX328        	1	19971125	G	6710	1174123101	BRACKET         			BOLKMS	BK117 	BK117C1     	5626025	EU  										CYLIC	BROKEN          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	393  				7509				BRACKET WELDS BROKE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012900098	19980129	00098		1998	1	29	98ZZZX329        	4	19971204	G	3453	066011481111	LORAN           		KLN89       	BELL  	206   	206L        	1181522	SW  										FACEPLATE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	206MH				100904	45426				LORAN FACE PLATE DISPLAY CRACKED.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW    					 
1998010800092	19980108	00092	CE  	1998	1	8	98ZZZX33         	1	19971003	G	5711		SPAR            			BEECH 	18    	TC45G       	1151016	CE  										LT WS 32 THRU 81	CORRODED        	B			NI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	445DM					AF152				CORROSION FOUND ON FRONT SPART, LT WING STATIONS 32, 46, 57, 60, 62, 64, AND 81, AND RT WING STATION 32.  REF:  AD75-27-	09 R2 AND AMDT 39-3878.					1	L	7	2 	3R				A765    					 
1998012900099	19980129	00099	GL  	1998	1	29	98ZZZX330        	2	19971201	G	7323	23004836	GOVERNOR        		23004545    	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	206MH	236  			BR36199	45426	CAE890566			GOVERNOR REMOVED FOR TORQUE SPIKES WITH POWER CHANGES.  COMPONENT OF ENGINE 23004545, S/N CAE890566.  REMOVED AND REPLAC	ED.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1998091100185	19980911	00185	EU  	1998	9	11	98ZZZX3302       	1	19970416	G	5610	7256110501	RIVET           			SAAB  	SF340 	SF340A      	7850100	EU  										COCKPIT	MISINSTALLED    	B			AY55	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	46XJ					340A046				UPON INSPECTION OF THE PILOT'S AND COPILOT'S SIDE WINDSCREEN, FOUND HI-LOCKS SECURING THE WINDSCREEN PANES TO THEIR FRAM	ES HAVE IMPROPER PROTRUSION THROUGH THE COLLARS.  THIS HAS CAUSED SEVERAL HI-LOCK COLLARS TO LOOSEN AND VIBRATE OFF.  RE	F:  OPERATOR CONTROL NR 98ZZZX3303.				2	L	7	2 	4T			RT	A52EU   					 
1998091100186	19980911	00186	EU  	1998	9	11	98ZZZX3303       	1	19970416	G	5610	7256110502	RIVET           			SAAB  	SF340 	SF340A      	7850100	EU  										COCKPIT	MISINSTALLED    	B			AY55	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	46XJ					340A046				UPON INSPECTION OF THE PILOT'S AND COPILOT'S SIDE WINDSCREEN, FOUND HI-LOCKS SECURING THE WINDSCREEN PANES TO THEIR FRAM	ES HAVE IMPROPER PROTRUSION THROUGH THE COLLARS.  THIS HAS CAUSED SEVERAL HI-LOCK COLLARS TO LOOSEN AND VIBRATE OFF.  RE	F:  OPERATOR CONTROL NR 98ZZZX3302.				2	L	7	2 	4T			RT	A52EU   					 
1998012900100	19980129	00100	EU  	1998	1	29	98ZZZX331        	1	19971018	G	3213	1175000212	SKID            			BOLKMS	BK117 	BK117C1     	5626025	EU  										GEAR SKID	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				PROTECTIVE SKID WORN BEYOND LIMITS.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012900101	19980129	00101	EU  	1998	1	29	98ZZZX332        	1	19971018	G	3213	1175000211	SKID            			BOLKMS	BK117 	BK117C1     	5626025	EU  										GEAR SKID	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				SKID PROTECTIVE WORN BEYOND LIMITS.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012900102	19980129	00102		1998	1	29	98ZZZX333        	4	19971110	G	3453	4309805000	LORAN           		612B        	BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	460H				64336	7142				LORAN HEADINGS AND MILEAGE INCORRECT.  RE:  RMA 652062.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012900103	19980129	00103		1998	1	29	98ZZZX334        	4	19971204	G	2312	064101900	TRANSCEIVER     		KY196       	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTION     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	495LF				13850	S645				UNABLE TO AJDUST SIDE TONE/MIC GAIN DOWN TO A SUITABLE LEVEL TO MATCH OUTPUT OF OTHER AVIONICS EQUIPMENT.  REMOVED AND R	EPLACED.					1	G	7	2 	3U				H3EU    					 
1998012900104	19980129	00104	EU  	1998	1	29	98ZZZX335        	1	19971208	G	3610	97914211	VALVE           			BOLKMS	117   	BK117A3     	5626015	EU  										BLEED SOV	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	527MB				1417	7103				VALVE INOPERATIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012900105	19980129	00105	GL  	1998	1	29	98ZZZX336        	2	19971117	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	B			TI1R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	05	721SP	618  			FF34189	45486	CAE890696			ENGINE HAD COMPRESSOR STALL AT LOW POWER.  REMOVED AND REPLACED BLEED VALVE.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1998012900108	19980129	00108	CE  	1998	1	29	98ZZZX339        	1	19971201	G	3222	67420607	STRUT           			CESSNA	750   	750         	2076810	CE  										NLG	MALFUNCTION     	D		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	5114	370  			BMC017	7500017				THE AIRCRAFT DEPARTED DTW AND ON CLIMB-OUT, THE LANDING GEAR HANDLE WOULD NOT MOVE TO THE RETRACT POSITION.  THE AIRCRAF	T RETURNED TO DTW AND MAINTENANCE WAS ABLE TO DUPLICATE.  UNDER CESSNA'S RECOMMENDATION, NEW SB 750-32-05 AND SB 750-32-	10 INCORPORATED TO ELIMINATE PROBLEMS IN NOSE STRUT EXTENSION.				2	L	7	2 	4J			RT	T00007WI					 
1998010800093	19980108	00093	CE  	1998	1	8	98ZZZX34         	1	19971003	G	5711		SPAR            			BEECH 	18    	TC45G       	1151016	CE  										RT WS 32	CORRODED        	B			NI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	445DM					AF152				CORROSION FOUND ON FRONT SPAR, LT WING STATIONS 32, 46, 57, 60, 62, 64, AND 81, AND RT WING STATION 32.  REF:  AD75-27-0	9 R2 AND AMDT 39-3878.					1	L	7	2 	3R				A765    					 
1998012900109	19980129	00109	CE  	1998	1	29	98ZZZX340        	1	19971201	G	3222	67420607	STRUT           			CESSNA	750   	750         	2076810	CE  										NLG	MALFUNCTION     	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	5116	316  			BMC020	7500019				THE AIRCRAFT DEPARTED DTW AND ON CLIMB-OUT, THE LANDING GEAR HANDLE WOULD NOT MOVE TO THE RETRACT POSITION.  THE AIRCRAF	T RETURNED TO DTW AND MAINTENANCE WAS UNABLE TO DUPLICATE.  GALLING WAS DETECTED IN THE CHROME SECTION OF THE STRUT ASSY	 AND THE UNIT WAS SENT BACK TO WICHITA FOR EVALUATION.				2	L	7	2 	4J			RT	T00007WI					 
1998012900112	19980129	00112	CE  	1998	1	29	98ZZZX344        	1	19971231	G	5720	0512122	BEARING BLOCK   			CESSNA	180   	180         	2072602	CE  										RT AFT BLOCK	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	1682C	3706 				30382				RIGHT REAR BLOCK IN REAR CARRY-THROUGH BULKHEAD CORRODED IN BOLT HOLE AND INTERGRANULAR CORROSION IN BLOCK.						1	H	7	1 	3O			NC	5A6     					 
1998012900113	19980129	00113	SO  	1998	1	29	98ZZZX345        	1	19971231	G	5751	U18279	HINGE FITTING   		U582731     	LUSCOM	8     	8F          	8190114	SO  										RT AIL CENTER	MISMANUFACTURED 	B			FE6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	1895B					6322				A NEW FAA PMA RIGHT AILERON IS PURCHASED FROM UNIVAIR AIRCRAFT FOR INSTALLATION ON AIRCRAFT.  THE AILERON WOULD NOT FIT 	ON THE AIRCRAFT AS RECEIVED DUE TO MISALIGNMENT OF THE CENTER HINGE FITTING.  NO OTHER AILERON WAS AVAILABLE FROM THIS M	ANUFACTURER.  THE MANUFACTURER SHIPPED AN UNDRILLED CENTER HINGE FITTING P/N U18279 WHICH WAS INSTALLED ON THE NEW AILER	ON.  SUBSEQUENT OPERATION WAS NORMAL.			1	H	7	1 	3O				A694    					 
1998012900117	19980129	00117	CE  	1998	1	29	98ZZZX349        	1	19971215	G	3060	W31X2M1620	BREAKER         			CESSNA	340   	340A        	2076405	CE  										PROPELLER DEICE	FAILED          	G		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SO	13	340MT					340A0741				PROPELLER DE-ICE WAS SELECTED ON AIRCRAFT CLIMBING THROUGH SNOW FLURRIES.  THE PROPELLER DE-ICE PIGTAIL WIRES AT PROPELL	ER HUB WERE SHORTED TO THE SPINNER.  THIS CAUSED SMOKE IN THE COCKPIT.  AIRCRAFT RETURNED AND MADE AN UNEVENTFUL LANDING	.  THE PROPELLER DE-ICE CIRCUIT BREAKER DID NOT TRIP TO THE OFF OR OPEN POSITION ALLOWING THE WIRING FROM THE CIRCUIT BR	EAKER TO THE DE-ICE GAUGE TO BURN IN TWO.			1	L	7	2 	3O				3A25    					 
1998010800094	19980108	00094	GL  	1998	1	8	98ZZZX35         	3	19971101	G	6111		BLADE           			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	PROPELLER	BROKE           	G				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	17	6278R					172RG0139		842548		APPROXIMATELY 4 INCHES OF PROPELLER TIP BROKE OFF IN-FLIGHT.  AIRCRAFT MADE EMERGENCY LANDING.						1	H	7	1 	3O				3A17    		5	C	P7EA	 
1998012900124	19980129	00124	CE  	1998	1	29	98ZZZX356        	1	19971201	G	3260	YZ2RN7T	SWITCH          			CESSNA	210   	T210N       	2073456	CE  										NLG UPLOCK	CRACKED         	D				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			SO	16	5515Y					21064233				NOSE GEAR UPLOCK SWITCH PLUNGER CRACKS AT INSERT (PLASTIC).  SECOND AIRCRAFT IN LAST YEAR WITH THIS PROBLEM DISCOVERED D	URING ANNUAL INSPECTION.  THIS CRACKING PERMITS MOISTURE INSIDE THE HOUSING CAUSING ERRONEOUS UNLOCK INDICATIONS IN COCK	PIT WHEN GEAR IS ACTUALLY UP AND LOCKED.				1	H	7	1 	3O				3A21    					 
1998012900126	19980129	00126	SO  	1998	1	29	98ZZZX358        	1	19971219	G	3244	30855	TIRE            	MCCREARY    	65010       	PIPER 	PA31T 	PA31T1      	7103126	SO  										MLG	CHAFED          	E	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	2427W					311104005				INSTALLED TIRE ON WHEEL, NOTICED MINIMUM CLEARANCE ON SIDEWALL TIRE HAS TWO GROOVES CUT IN IT BY THE BRAKES.  SUBMITTER 	STATED TIRE IS A DIFFERENT SHAPE THAN A GOODYEAR TIRE.					1	L	7	2 	3T				A8EA    					 
1998012900127	19980129	00127	CE  	1998	1	29	98ZZZX359        	1	19971201	G	3310	15703014	DIMMER ASSY     			CESSNA	172   	172R        	2072401	CE  										INST LIGHTS	MISWIRED        	B	S	A	N3XR	A				UNSCHED LANDING         				B	W		SMOKE/FUMES/ODORS/SPARKS  	INADEQUATE Q C            		NR	NOT REPORTED   	1			SO	15	403ER	34   				17280245				DURING A TRAINING FLIGHT, THE CREW SMELLED A BURNING SCENT.  AFTER FOLLOWING THE EMERGENCY CHECKLIST, THEY WERE GOING TO	 LAND OFF-FIELD.  THE SMELL DIMINISHED AND THEY PROCEEDED TO X-47.  DURING THE FOLLOWING INSPECTION, A RESISTOR WAS FOUN	D BURNED IN HALF ON THE DIMMER ASSY.  IT WAS DISCOVERED THE UNIT IS WIRED INCORRECTLY.  IT APPEARS TO BE A FLEET PROBLEM	.  AFTER A CALL TO CESSNA, DISABLED THE DIMMERS IN THE ENTIRE FLEET.  SB 97-33-01 APPLIES.			1	H	7	1 	3O			NT	3A12    					 
1998010800095	19980108	00095	SO  	1998	1	8	98ZZZX36         	1	19971124	G	7603		CONTROL         			LUSCOM	8     	8A          	8190104	SO  										THROTTLE	FAILED          	G	S	A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	09	71329					2756				LOSS OF ENGINE THROTTLE CONTROL CONTRIBUTED TO A FORCED LANDING AND SUBSEQUENT LOSS OF DIRECTIONAL CONTROL.  INVESTIGATI	ON DISCLOSED A CRACK IN THE RIGID THROTTLE CONTROL CONDUIT ALLOWING THE FLEXIBLE CONDUIT TO SEPARATE FROM THE FIXED COND	UIT HOUSING.  RECOMMEND CLOSE INSPECTION OF THIS AREA AT THE 100-HOUR ANNUAL INSPECTION.				1	H	7	1 	3O				A694    					 
1998012900130	19980129	00130	SO  	1998	1	29	98ZZZX362        	2	19971211	G	8520	536580	CRANKSHAFT      								CONT  	O470  	O47011      	17026	SO  					1ST FILLET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					176					CRANKSHAFT'S FIRST FILLET AREA CLOSEST TO FLANGE HAD A 50 PERCENT FSH INDICATION.											3	O			E269				 
1998012900133	19980129	00133		1998	1	29	98ZZZX365        	4	19971221	G	3425	5204210002	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										HSI	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117LU				1736	7144				HSI INDICATOR ROTATES CLOCKWISE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998012900134	19980129	00134		1998	1	29	98ZZZX366        	4	19971204	G	3421	4021541671	HORIZON         			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC				82100980	7509				INOPERABLE FOR P/R CSAS SYSTEM.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998012900135	19980129	00135	SW  	1998	1	29	98ZZZX367        	1	19971204	G	3340	SX5	SEARCH LIGHT    			BELL  	206   	206L        	1181522	SW  										NOSE SECTION	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	206MH				1243	45426				SEARCH LIGHT TURNS OFF IN-FLIGHT AND SOMETIMES WILL NOT RE-START.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW    					 
1998012900136	19980129	00136		1998	1	29	98ZZZX368        	4	19971119	G	3120	JB15307	CLOCK           			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				623638	7505				CLOCK LOSES TIME, RUNS SLOW.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998010800096	19980108	00096	SO  	1998	1	8	98ZZZX37         	1	19971212	G	7922	75944	VALVE           			PIPER 	PA28  	PA28140     	7102802	SO  										THERMO BYPASS	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	8215N					2825419				LYCOMING SB 518C APPLIES.  FOUND NUT LOOSE.  REPLACED VERNATHERM.  SUSPECT CAUSE:  AGE AND WEAR.						1	L	7	1 	3O				2A13    					 
1998010800097	19980108	00097	SO  	1998	1	8	98ZZZX38         	2	19971205	G	8520		BOLTS           			LKHEED	T33   	T33A        	5260402	WP  	CONT  	O520  	IO520BB     	17032	SO  					LOWER CASE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	8262D	925  				CE1645	578815			OIL SUMP QUICK DRAIN WOULD NOT OPEN.  REMOVED QUICK DRAIN TO TROUBLESHOOT AND FOUND LOOSE BOLT LAYING ACROSS DRAIN HOLE 	IN OIL PAN.  REMOVED OIL PAN AND FOUND 3 EACH .25 INCH FLANGE BOLTS AND 1 EACH .3125 INCH THROUGH-BOLT LYING IN PAN ALON	G WITH NUTS AND WASHERS.  ALL OTHER CASE (LOWER) BOLTS WERE LOOSE ENOUGH TO ROTATE.  SUBMITTER STATED MOST LIKELY WAS NE	VER TIGHTENED PROPERLY AT FACTORY.  SHOULD HAVE BEEN TORQUED PROPERLY AND LOCKWASHERS OR TABS INSTALLED.  THIS ENGINE HA	S 925 HOURS SINCE NEW.  MFG DATE 1992.		1	L	7	1 	4J	3	O		EXPA1L71	E5CE				 
1998010800098	19980108	00098	SO  	1998	1	8	98ZZZX39         	1	19971206	G	7820	2448401	MUFFLER         			PIPER 	PA24  	PA24400     	7102408	SO  										RT SIDE	CRACKED         	D		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	05	8452P		624  			2627				RIGHT MUFFLER FAILED CAUSING CARBON MONOXIDE TO ENTER CABIN.  PILOT BECAME INCAPACITATED.  AIRCRAFT FLEW FOR 1.9 HOURS U	NTIL FUEL EXHAUSTION, LANDED IN HAYFIELD.  PILOT RECEIVED MINOR INJURIES.  AIRCRAFT WAS DESTROYED.  ACCIDENT NR CHI 98LA	055.				1	L	7	1 	3O				1A15    					 
1998010800063	19980108	00063	SO  	1998	1	8	98ZZZX4          	2	19971211	G	8520	536580	CRANKSHAFT      								CONT  	O470  	O47011      	17026	SO  					FIRST FILLET	DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					176					CRANKSHAFT'S FIRST FILLET AREA CLOSEST TO FLANGE HAD A 59 PERCENT FSH INDICATION.											3	O			E269				 
1998010800099	19980108	00099	SW  	1998	1	8	98ZZZX40         	1	19971210	G	2430		WIRE            			MOONEY	M20   	M20M        	5870222	SW  										BATTERY	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	9164Z	321  				270213				PILOT REPORTED INTERMITTENT STARTING, VOLTAGE FLUCTUATION, AND LOW BATTERY CHARGE.  INSPECTION FOUND NR 1 AND NR 2 BATTE	RY GROUND STRAPS AT AIRFRAME ATTACHMENTS TO HAVE HIGH RESISTANCE AT GROUNDING POINT.  CLEANED AREAS AND INSTALLED HARDWA	RE REFERENCING MOONEY SI M20-97.  SYSTEMS CHECKED OK.  IT APPEARS THE AIRFRAME PRIMER COATING WAS ACTING AS AN INSULATOR	.  WHEN REMOVED, THE SYSTEMS OPERATED CORRECTLY.			1	L	7	1 	3O			RT	2A3     					 
1998010800100	19980108	00100	EA  	1998	1	8	98ZZZX41         	2	19971118	G	8550	60746	IMPELLER        		78528       	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					OIL PUMP	WRONG PART      	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	2083G					28R7918014	L2009651A			ENGINE DISASSEMBLED FOR MAJOR OVERHAUL AND DISCOVERED OIL PUMP HAD PREVIOUSLY BEEN ASSEMBLED WITH A LW18110 DRIVEN IMPEL	LER WHICH IS CARBURIZED, AND A NR 60746 DRIVE IMPELLER WHICH IS NOT NITRIDE HARDENED.  THIS IS CONTRARY TO THE INSTRUCTI	ONS IN LYC SB 524.  THIS WAS A LYC FACTORY OVERHAULED ENGINE SEVERAL YEARS AGO.  THERE WAS NO RECORD OF OIL PUMP REPAIR 	SINCE OVERHAUL BY LYC.  THE IMPELLER, EVEN THOUGH NOT CORRECT IN COMBINATION WITH THE MATING IMPELLER, WAS NOT EXCESSIVE	LY WORN.		1	L	7	1 	3O	3	O		2A13    	1E10				 
1998010800101	19980108	00101	CE  	1998	1	8	98ZZZX42         	1	19970825	G	5741	1054200113	FITTING         			BEECH 	76    	76          	1153005	CE  										LT WING ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	24KK	6447 				ME149				INSPECTION FOUND LEFT WING ATTACH FITTING CRACKED.						1	L	7	2 	3O				A29CE   					 
1998010800102	19980108	00102	CE  	1998	1	8	98ZZZX43         	1	19970909	G	5741	1054200114	FITTING         			BEECH 	76    	76          	1153005	CE  										RT WING ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	272BA					ME90				INSPECTION FOUND LEFT AND RIGHT WING ATTACH FITTINGS CRACKED.						1	L	7	2 	3O				A29CE   					 
1998010800103	19980108	00103	CE  	1998	1	8	98ZZZX44         	1	19970909	G	5741	1054200113	FITTING         			BEECH 	76    	76          	1153005	CE  										LT WING ATTACH	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	272BA					ME90				INSPECTION FOUND LEFT AND RIGHT WING ATTACH FITTINGS CRACKED.						1	L	7	2 	3O				A29CE   					 
1998120400476	19981204	00476	NE  	1998	12	4	98ZZZX4435       	2	19971017	G	7261	0292105230	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 1 ENGINE	MALFUNCTIONED   	B		A	EGRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	886AH					760153	15086			INSTALLED OVERHAULED OIL PUMP S/N 91S0 ON NR 1 ENGINE.  DURING RUNS, FOUND OIL PUMP NOT DELIVERING PROPER AMOUNT OF PRES	SURE.  REMOVED OIL PUMP FROM ENGINE TO INSTALL ANOTHER OIL PUMP.					1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1998120400477	19981204	00477	NE  	1998	12	4	98ZZZX4436       	2	19971017	G	7261	0292105230	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 1 ENGINE	MALFUNCTIONED   	B		A	EGRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	886AH					760153	15086			INSTALLED OVERHAULED OIL PUMP S/N 59S0 ON NR 1 ENGINE.  DURING RUNS, FOUND OIL PUMP NOT DELIVERING PROPER AMOUNT OF PRES	SURE.  REMOVED OIL PUMP (SECOND ONE) TO INSTALL ANOTHER OIL PUMP.  INSTALLED NEW OIL PUMP FROM TURBOMECA TO FIX PROBLEM.					1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1998020500210	19980205	00210	EA  	1998	2	5	98ZZZX445        	2	19971125	G	7314	LW15472	FUEL PUMP       			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					ENGINE FUEL	WRONG PART      	B	L	A	DSBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	9480D					172RG1180	L3014336A			A FACTORY OVERHAULED ENGINE WAS BEING INSTALLED WHEN MECH REPORTED UNABLE TO CONNECT THE FUEL LINES TO THE NEW FUEL PUMP	 (ENG DRIVEN).  THE 'IN' AND 'OUT' PORTS WERE REVERSED.  MFG WAS CONTACTED, AND A SECOND PUMP SENT, BUT IT WAS THE SAME 	P/N AS THE ORIG, BUT THE BOX HAD ANOTHER P/N ON IT.  A 3RD PUMP REC'D WITH PN 2W16775 WHICH WAS THE CORRECT PART.  THE A	CFT PARTS MANUAL SHOWS TWO DIFFERENT FUEL SYSTEMS FOR ACFT SN 0001-0890 AND SN 0890 AND ON.  THE FRIST TWO PUMPS WOULD H	AVE FIT EARLY SERIAL NUMBERED ACFT.		1	H	7	1 	3O	3	O		3A17    	E286				 
1998121100011	19981211	00011	SO  	1998	12	11	98ZZZX4454       	2	19971215	G	8530	653443	VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC	500  				18263638	269416R			DURING A ROUTINE COMPRESSION CHECK, LEAKAGE WAS FOUND PAST THE EXHAUST VALVE ON THE NR 3 CYLINDER.  THE REMOVED CYLINDER	, EXHAUST VALVE AND GUIDE WERE FOUND WORN OUT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS AND/OR ASSEMBLY PR	OCESS FROM THE FACTORY.				1	H	7	1 	3O	3	O	NT	TA13    	E273				 
1998121100016	19981211	00016	SO  	1998	12	11	98ZZZX4459       	2	19970217	G	8530	653446	VALVE GUIDE     			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	CRACKED         	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	962CC	1351 				210649861	294563R			A ROUTINE COMPRESSION CHECK INDICATES LEAKAGE ON THE NR 2 CYLINDER.  FURTHER INVESTIGATION REVEALS A CRACK ON THE CYLIND	ER HEAD THAT EXTENDS FROM THE FUEL INJECTOR HOLE TO THE SPARK PLUG HOLE.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIV	E CYLINDER HEAD INSTALLED ON THE CYLINDER AT REMANUFACTURE OF THE ENGINE.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE				 
1998121100018	19981211	00018	SO  	1998	12	11	98ZZZX4461       	2	19970321	G	8530	653446	VALVE GUIDE     			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	961CC	850  				21064620	270385R			DURING A ROUTINE COMPRESSION CHECK, EXCESSIVE LEAKAGE PAST THE PISTON RINGS WAS FOUND ON THE THE NR 2 CYLINDER.  THE REM	OVED CLYINDER WAS FOUND WORN OUT AND THE PISTON RINGS STUCK IN THE RING GROOVES.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS 	EXCESSIVE LEAD SLUDGE BUILD-UP FROM THE USE OF TCM APPROVED MOBIL AV1 OIL.				1	H	7	1 	3O	3	O		3A21    	E5CE				 
1998121100019	19981211	00019	SO  	1998	12	11	98ZZZX4462       	2	19971021	G	8530	653446	VALVE GUIDE     			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE EXHAUST	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	961CC	650  				21064620	294754R			DURING A ROUTINE COMPRESSION CHECK, LEAKAGE WAS FOUND PAST THE INTAKE VALVE ON THE NR 6 CYLINDER.  THE REMOVED CYLINDER,	 INTAKE VALVE AND GUIDE WERE FOUND WORN OUT.  THE VALVE LASH WAS ALSO FOUND TO BE EXCESSIVE ON THE NR'S 2, 4, AND 6 CYLI	NDERS.  THE PUSH RODS WERE REPLACED WITH .030 INCH OVERSIZE.  THE VALVE LASH ON THE NR'S 1, 3, AND 5 CYLINDERS WERE FOUN	D TO BE WITHIN SPECIFICATIONS AS THEY ALREADY HAD OVERSIZE PUSH RODS INSTALLED.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS D	EFECTIVE PARTS AND ASSEMBLY PROCESS FROM THE FACTORY.		1	H	7	1 	3O	3	O		3A21    	E5CE				 
1998121100022	19981211	00022	SO  	1998	12	11	98ZZZX4465       	2	19970520	G	8530	648168	VALVE GUIDE     			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE EXHAUST	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC	400  				18265290	809905R			DURING A ROUTINE COMPRESSION CHECK, LEAKAGE WAS FOUND PAST THE EXHAUST VALVE ON THE NR 3 CYLINDER.  THE REMOVED CYLINDER	, EXHAUST VALVE AND GUIDE WERE FOUND WORN OUT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS AND/OR ASSEMBLY PR	OCESS FROM THE FACTORY.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1998020500212	19980205	00212	EU  	1998	2	5	98ZZZX447        	1	19971118	G	6320	4639302052	CLUTCH RACE     			BOLKMS	105   	BO105LSA3   	5626020	EU  										M/R XMSN	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV				133	2033				CLUTCH OUTER RACE FAILED IN TRANSMISSION 4649001006, SN 39.  REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU    					 
1998020500213	19980205	00213	EU  	1998	2	5	98ZZZX448        	1	19971118	G	6320	4639202011	CLUTCH ASSY     		4649001006  	BOLKMS	105   	BO105LSA3   	5626020	EU  										M/R XMSN	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV				940	2033				CLUTCH ASSY FAILED IN TRANSMISSION 4649001006, SN 39.  REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU    					 
1998020500214	19980205	00214	EU  	1998	2	5	98ZZZX449        	1	19971118	G	6320	19E2321A	BENDIX SHAFT    		4649001006  	BOLKMS	105   	BO105LSA3   	5626020	EU  										M/R XMSN	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV				E121U	2033				BENDIX SHAFT FAILED IN TRANSMISSION, 4649001006, SN 39. REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU    					 
1998010800104	19980108	00104	CE  	1998	1	8	98ZZZX45         	1	19971201	G	7120		MOUNT BOLT      			CESSNA	182   	182K        	2072724	CE  										ENGINE	DETACHED        	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	2770Q					18257970				DURING OIL FILTER CHANGE, A REAR LORD MOUNT BOLT WAS FOUND DETACHED.  OTHER 3 BOLTS WERE NOT TO TORQUE.  ENGINE INSTALLE	D IN 1988 AND IT IS SUSPECT BOLTS NOT PROPERLY TORQUED.					1	H	7	1 	3O			NT	3A13    					 
1998020500220	19980205	00220	EA  	1998	2	5	98ZZZX453        	2	19971231	G	7250	3033351	CT VANE RING    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE TURBINE	CRACKED         	B			DJSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	36CP		11   			BB178	PCE81488			ON 12-31-97, REPAIR STA (RUHR840H) PERFORMED AN HSI FOR IFL GROUP INC., ON ENGINE, SN 81488, REPLACING CT VANE WITH AN O	VERHAULED ONE.  10.8 HOURS LATER, HAD A 40 DEGREE INCREASE IN ITT.  IFL SPLIT THE ENGINE AND FOUND SOME TIP RUB AND THAT	 THE CT VANE HAD DEVELOPED CRACKS IN 5 VANES ON TRAILING EDGES.  SUSPECT CAUSE OF FAILURE IS THE VANE WAS NOT COMPLETELY	 STRESS RELIEVED AT THE TIME OF OVERHAUL.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998020500221	19980205	00221	CE  	1998	2	5	98ZZZX454        	1	19971201	G	2770	551425033	CONTROL CABLE   			CESSNA	501   	501         	2076603	CE  										ELEV CONT LOCK	FRAYED          	B		A	TRKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	501LL					5010185				WHILE PERFORMING PHASE INSPECTION 1 THROUGH 5, FOUND THE ELEVATOR CABLE FRAYED GOING THROUGH THE CONTROL LOCK CONDUIT. T	HE MM ALLOWS 3 STRANDS BROKEN IN ANY 10 INCH SECTION.  THIS CABLE HAD 6 STRANDS BROKEN.  SUSPECT CAUSE FOR THIS IS THE F	RONT OF THE CONDUIT THE CABLE RIDES THROUGH HAD NYLON BUSHING.  THE AFT END HAS NO BUSHING; THUS, THE CABLE CHAFED THE C	ONDUIT.  SUBMITTER STATED IF BUSHING WERE INSTALLED IN THE AFT PART OF THE CONDUIT,  THIS PROBLEM WOULD NOT EXIST.			1	L	7	2 	4F			 	A27CE   					 
1998020500222	19980205	00222	CE  	1998	2	5	98ZZZX455        	1	19971201	G	3222	67420607	NOSE GEAR       			CESSNA	750   	750         	2076810	CE  										STRUT	MALFUNCTIONED   	C				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	23	5113	548  			BMC011	7500013				THE AIRCRAFT DEPARTED DTW AND ON CLIMB-OUT, THE LANDING GEAR HANDLE WOULD NOT MOVE TO THE RETRACT POSITION.  THE AIRCRAF	T RETURNED TO DTW AND MAINTENANCE WAS ABLE TO DUPLICATE.  UNDER CESSNA'S RECOMMENDATION, NEW SB 750-32-05 AND SB 750-32-	10 INCORPORATED TO ELIMINATE PROBLEMS IN NOSE STRUT EXTENSION.				2	L	7	2 	4J			RT	T00007WI					 
1998121100243	19981211	00243	SO  	1998	12	11	98ZZZX4554       	1	19970910	G	2710	62701200	BALANCE CABLE   			PIPER 	PA32  	PA32R301    	7103218	SO  										AILERON	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9220B	908  				3213048				DURING AN ANNUAL INSPECTION, DISCOVERED A FLAT SHINEY AREA ON THE BOTTOM SIDE OF THE LT AILERON BALANCE CABLE.  THE LOCA	TION OF THE CABLE IN QUESTION IS IN THE LT WING ROOT AREA JUST INBD OF THE WHEELWELL.  AN IDLER PULLEY IS LOCATED IN THI	S AREA.  UPON FURTHER INSPECTION, CABLE WAS FOUND TO HAVE NUMEROUS BROKEN STRANDS.  SUBMITTER STATED THE POSSIBLE CAUSE 	IS AN IDLER PULLEY THAT IS TOO SMALL OR MISALIGNED AND A POSSIBLE FIX WOULD BE TO INSTALL A LARGER PULLEY OR MAKE CABLE 	LIFE LIMITED TO A MAXIMUM OF 1,000 HOURS.		1	L	7	1 	3O				A3SO    					 
1998020500223	19980205	00223	WP  	1998	2	5	98ZZZX456        	1	19971210	G	7921	U16011	OIL COOLER      			DOUG  	DC3   	DC3C        	3021457	WP  										RT ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	03	67588		16   		441861	20536				OIL COOLER FAILED CAUSING LOSS OF OIL PRESSURE NR 2 ENGINE.  SHUT ENGINE DOWN.  EMERGENCY CIRCUMSTANCES REQUIRED RESTART	 OF ENGINE CAUSING ENGINE TO FAIL.					2	L	7	2 	4R				A669    					 
1998121800009	19981218	00009	SO  	1998	12	18	98ZZZX4599       	1	19971110	G	7430		LUG             		IO3572001   	PIPER 	PA28  	PA28161     	7102803	SO  										COCKPIT	DAMAGED         	B	S		CDMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	9752C	1000 			A1297H	287816524				TERMINAL BLOCK LUG FASTENER SHEARED.  THE SCREWS USED TO ATTACH THE TERMINAL LEADS TO THE LUGS ARE DIFFICULT TO MANIPULA	TE WITHOUT SPECIAL TOOLS.  SUBMITTER SUGGESTED USING ALLEN HEAD SCREWS ON TERMINALS AND INCLUDE TORQUE PROCEDURES FOR PR	OPER INSTALLATION.				1	L	7	1 	3O				2A13    					 
1998010800105	19980108	00105	SO  	1998	1	8	98ZZZX46         	1	19971209	G	2436	VR371	REGULATOR       	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  										ALTERNATOR	SHORTED         	G		A		O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	23	2819A	5    			7071398	287990468				ACFT EXPERIENCED OVERVOLTAGE CONDITION THAT CAUSED SYSTEMS THAT WERE TURNED ON TO FAIL, AND ALL RADIOS TO PRODUCE HEAVY 	SMOKE.  REGULATOR TEAR-DOWN REVEALED LARGE RESISTOR FOUND INSIDE UNIT UNATTACHED.  IT APPEARS RESISTOR WAS NOT PROPERLY 	ATTACHED TO C/B.  IF ACFT WAS OPERATING IN IFR CONDITIONS, IT COULD HAVE BEEN AN EASY FATAL.  FOUND PMA HOLDER OF VOLTAG	E REGULATOR, ELECTROSYSTEMS, CALLS FOR GROUND TO BE ATTACHED DIRECTLY TO ALTERNATOR.  PIPER CALLS OUT GROUND BE ATTACHED	 TO REGULATOR.  ELECTROSYSTEMS REP STATED GROUND MUST BE MADE AT ALTERNATOR.  IT IS UNKNOWN IF GROUNDING INCONSISTENCY C	OULD HAVE PREVENTED FAILURE.  INSPECTOR RECOMMENDS THESE VOLTAGE REGULATORS BE INSPECTED FOR POOR SOLDER CONNECTIONS.	1	L	7	1 	3O				2A13    					 
1998121800010	19981218	00010	SO  	1998	12	18	98ZZZX4600       	1	19971215	G	2842	6810102	SENDING UNIT    			PIPER 	PA28  	PA28161     	7102803	SO  										FUEL CELL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	8345Z	3121 				288116167				DURING THE ACCOMPLISHMENT OF PIPER SB 1006 AND INSPECTION OF THE FUEL QUANTITY SENDERS, THE HOLE, IN THE FLOAT WHERE THE	 ARM IS ATTACHED, WAS FOUND SEVERELY WORN.  WITH A LITTLE MORE WEAR, THE FLOAT WOULD COME OFF THE ARM.					1	L	7	1 	3O				2A13    					 
1998020500233	19980205	00233	SW  	1998	2	5	98ZZZX466        	1	19971125	G	6310	406040542106	ADAPTER         			BELL  	206   	206L4       	1182110	SW  										DRIVE ADAPTER	SCORED          	B			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	404W	2043 			A654	52055				DURING INSPECTION DISCOVERED SAFETY WIRE PIGTAIL HAD BEEN TURNED IN WRONG DIRECTION AND HAD WORN A GROOVE IN THE FACE OF	 THE MAIN DRIVESHAFT ADAPTER.  THIS CONDITION, IF NOT DISCOVERED, WOULD EVENTUALLY LEAD TO MAIN DRIVESHAFT FAILURE.					1	G	7	1 	3U			NC	H2SW    					 
1998010800106	19980108	00106	CE  	1998	1	8	98ZZZX47         	1	19971203	G	3213	51411022	AXLE            			CESSNA	402   	402C        	207590R	CE  										RT MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	01	406GA	14350				402C0329				PILOT HAD DIFFICULTY DURING TAXI, RT WHEEL BINDING.  MAINTENANCE FOUND BRAKE DISC CONTACTING LOWER BARREL OF STRUT.  FOU	ND AXLE CRACKED UPON TIRE AND WHEEL REMOVAL.					1	L	7	2 	3O				A7CE    					 
1998020500243	19980205	00243	SW  	1998	2	5	98ZZZX475        	1	19971203	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										M/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3174Y	2114 			A1836	51038				DISCOVERED DURING DAILY INSPECTION, M/R BLADE TRAILING EDGE EXTRUSION CORRODED CAUSING APPROXIMATELY 10 INCH LONG SEPARA	TION.					1	G	7	1 	3U				H2SW    					 
1998010800107	19980108	00107	CE  	1998	1	8	98ZZZX48         	1	19970831	G	5741	1054200113	FITTING         			BEECH 	76    	76          	1153005	CE  										LT WING ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5424M	2283 				ME31				INSPECTION FOUND LEFT AND RIGHT WING ATTACH FITTINGS CRACKED.						1	L	7	2 	3O				A29CE   					 
1998020500436	19980205	00436	CE  	1998	2	5	98ZZZX489        	1	19971223	G	5741	1512122	BEARING BLOCK   			CESSNA	182   	182D        	2072710	CE  										LT/RT WING	CORRODED        	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	9923T	4697 				18253023				UPON REMOVING BOTH WINGS TO INSTALL MONARCH PLASTIC FUEL TANKS, THE REAR SPAR INBOARD ATTACH BLOCKS, LEFT AND RIGHT, WER	E FOUND TO HAVE INTERGRANULAR CORROSION IN THE INBOARD SLOT AREA ABOVE THE LARGE BOLT HOLES.  CORROSION AREA ABOUT .50 I	NCH WIDE BY .1250 INCH DEEP FROM TOP OF BLOCK TO BIG BOLT HOLE ON INBOARD FACE OF SLOT.  THIS AREA IS IMPOSSIBLE TO INSP	ECT VISUALLY WITHOUT REMOVING THE WINGS.			1	H	7	1 	3O			NT	3A13    					 
1998010800108	19980108	00108	CE  	1998	1	8	98ZZZX49         	1	19970831	G	5741	1054200113	FITTING         			BEECH 	76    	76          	1153005	CE  										RT WING ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5424M	2283 				ME31				INSPECTION FOUND LEFT AND RIGHT WING ATTACH FITTINGS CRACKED.						1	L	7	2 	3O				A29CE   					 
1998010800064	19980108	00064	EA  	1998	1	8	98ZZZX5          	2	19971101	G	7414	M3333	IMPULSE COUPLING	SLICK       	6351        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  						DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	1132Q	400  			96030021	327740046	RL2130848A			IMPULSE COUPLING HAS JUST UNDER 400 HOURS TIME IN SERVICE AND IS DEFECTIVE.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1998010800109	19980108	00109	CE  	1998	1	8	98ZZZX50         	1	19971217	G	2434	318	ALTERNATOR      	FORD        		CESSNA	185   	A185F       	2072821	CE  										DC SYSTEM	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	61423				5111176	18504180				ALTERNATOR FAILED.  FOUND BRUSHES COMPLETELY WORN OUT IN JUST 608 HOURS.  SUBMITTER STATED THIS IS THE SECOND ALTERNATOR	 FAILURE WITHIN 700 HOURS.					1	H	7	1 	3O				3A24    					 
1998010800110	19980108	00110	CE  	1998	1	8	98ZZZX51         	1	19971019	G	5741	1054200113	FITTING         			BEECH 	76    	76          	1153005	CE  										LT WING ATTACH	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6049L	10063				ME202				INSPECTION FOUND LEFT WING ATTACH FITTING CRACKED.						1	L	7	2 	3O				A29CE   					 
1998021100042	19980211	00042	CE  	1998	2	11	98ZZZX519        	1	19971224	G	7160	9591911295	BUSHING         		9591911419  	BEECH 	95    	B95         	1153404	CE  										RT CARB AIR BOX	WORN            	D		A		E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			SW	11	2012C	8269 				TD430				THE RIVETS ATTACHING THE WELD ASSY BUSHING PN 95-91912-95 TO THE RT ENGINE CARBURETOR AIR BOX ASSY PN 95-919114-19 WORKE	D LOOSE CAUSING THE BUTTERFLY IN THE CARBURETOR HEAT BOX TO BECOME LODGED IN THE CARBURETOR HEAT ON POSITION RESULTING I	N A FUEL RICH CONDITION FOR THE ENGINE.  WHEN THE CARBURETOR HEAT CONTROL WOULD NOT PUSH IN TO TURN HEAT OFF (BECAUSE OF	 STUCK BUTTERFLY), THE PILOT OPTED TO SHUT DOWN THE ENGINE.			1	L	7	2 	3O				3A16    					 
1998010800111	19980108	00111	NE  	1998	1	8	98ZZZX52         	2	19971204	G	8530	5999	ROLLER          								PWA   	R1340 	R1340AN1    	52016	NE  					TAPPET	SPALLED         	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		700  					9561			VALVE TAPPET ROLLER WAS FOUND TO BE SPALLING AT THE TIME OF OTHER REPAIR TO THE ENGINE.  METAL IN THE OIL SCREEN OR FILT	ERS, AND A CHIP DETECTOR LIGHT WOULD BE EARLY WARNING SIGNS OF A PROBLEM.										3	R			5E2				 
1998021100043	19980211	00043	SO  	1998	2	11	98ZZZX520        	2	19971114	G	8530	SA630046	PISTON PIN      			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  					NR 3 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	191WE		740  			TE1059	560027			ENGINE DISASSEMBLED FOR OVERHAUL.  UPON NR 3 CYLINDER REMOVAL, PISTON PIN PN SA630046 FOUND BROKEN.  NO OTHER DAMAGE NOT	ED.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1998021100045	19980211	00045	SO  	1998	2	11	98ZZZX522        	1	19971224	G	2731	6270197	CONTROL CABLE   			PIPER 	PA34  	PA34200     	7103405	SO  										AP ELEV TRIM	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	15412	1288 				347350060				AFT ELEVATOR TRIM/AUTOPILOT CABLE FRAYED WHERE IT GOES AROUND ELECTRIC TRIM AND AUTOPILOT SERVO PULLEYS.						1	L	7	2 	3O			 	A7SO    					 
1998021100049	19980211	00049	CE  	1998	2	11	98ZZZX526        	1	19970123	G	2150	6462933400	BELT            			BEECH 	36    	A36         	1151604	CE  										AIR CONDITIONING	DELAMINATED     	B			HUNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1066T	292  				E2996				AIR CONDITIONING BELT IS A TOOTH-TYPE BELT.  FOUND 'TEETH' SECTIONS OF THE INSIDE DIAMETER OF THE BELT LAYING INSIDE THE	 ENGINE NACELLE.  ON INSPECTION, FOUND 2.50 INCH SECTION OF BELT INSIDE EDGE MISSING.  ACTT:  292.1 HOURS.					1	L	7	1 	3O				3A15    					 
1998010800112	19980108	00112	NE  	1998	1	8	98ZZZX53         	2	19971210	G	7230		DISK            								PWA   	JT9   	JT9D7       	52054	NE  					STAGE 8	CRACKED         	B			OI5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25		29864					347057			DURING COMPLEX INSPECTION (INCOMING INSP), ONE DOVETAIL WAS DISCOVERED DEFECTIVE.  CRACK WAS ALONG THE WALL OF THE PRESS	URE FACE CONTINUING ON THROUGH APPROXIMATELY HALF-WAY.  THIS CRACK HAS THE CRITERIA ON THE DOVETAIL TO CAUSE LIBERATION.										4	F			E20EA				 
1998021100055	19980211	00055		1998	2	11	98ZZZX532        	1	19971222	G	2520	SL0231202	CYLINDER        		SL43008     															SEAT RECLINE	CRACKED         	B			GVRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05										CABIN SEAT RECLINE MECHANISM HYDROLOK CYLINDER HAS A CRACK.  THE CRACK EXTENDED FROM THE SPLINED FIBER NUT TO THE END OF	 THE CYLINDER.  THE CIRCUMSTANCES UNDER WHICH THE CRACK OCCURRED ARE UNKNOWN, BUT SUBMITTER SUGGESTED THE CAUSE AS FATIG	UE.																	 
1998021100060	19980211	00060	CE  	1998	2	11	98ZZZX537        	1	19971204	G	2822	111TW6003	SWITCH          			LEAR  	35    	35A         	5170602	CE  										FUEL BOOST	SHORTED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	199CJ	130  				071				FUEL BOOST SWITCH IS PART OF SB 35/36-28-11.  THE SWITCH HAS AN INTEGRAL LIGHT.  THE TWO WIRES FOR THE LIGHT ENTER THE S	WITCH IN SUCH A WAY THEY CHAFE AT THE POINT WHERE THEY ENTER THE SWITCH.  THIS CREATED A DIRECT SHORT TO GROUND OF THE P	OWER WIRE FOR THIS LIGHT.  AS A RESULT, THE BOOST PUMP CIRCUIT BREAKER TRIPPED IF THE PUMP WAS TURNED ON.  ALSO, BOTH WA	RNING LIGHT CIRCUIT BREAKERS TRIPPED IF THE ANNUNCIATOR PRESS-TO-TEST SWITCH WAS PRESSED.  THIS HAPPENED ON THE GROUND D	URING A PRE-FLIGHT.		2	L	7	2 	4F				A10CE   					 
1998021100062	19980211	00062	CE  	1998	2	11	98ZZZX539        	1	19970107	G	5220	1014301835	WINDOW          			BEECH 	200   	200BEECH    	1152920	CE  										1ST CABIN RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	175SA	7526 				BB183				INSPECTION FOUND WINDOW IN ESCAPE HATCH CRACKED.						1	L	7	2 	4T				A24CE   					 
1998010800113	19980108	00113	EU  	1998	1	8	98ZZZX54         	1	19971215	G	2435		ARMATURE        	AUXILEC     	8060140     	AMD   	FALC50	FALCON900   	2700160	EU  										START/GEN	FAILED          	B		A	XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		601  			356					ARMATURE, PN PO55742-7, ANTI-DRIVE END BAND DETACHED.  THE WINDINGS AT ANTI-DRIVE END RUBBED STATOR/FRAME ASSEMBLY WINDI	NGS TEARING BOTH WINDINGS FROM ARMATURE AND STATOR APART.  BRUSH RIGGING HOLDERS BENT/DEFORMED AND END BELL CRACKED.  DR	IVE END BEARING BALLS AND CAGE DISINTEGRATED.				2	L	7	3 	4F			RT	A46EU   					 
1998021100063	19980211	00063	CE  	1998	2	11	98ZZZX540        	1	19971126	G	5620	1014301835	WINDOW          			BEECH 	200   	200BEECH    	1152920	CE  										3RD CABIN LT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	175SA	7489 				BB183				INSPECTION FOUND WINDOW CRACKED TOWARD FRONT SIDE.						1	L	7	2 	4T				A24CE   					 
1998021100064	19980211	00064	CE  	1998	2	11	98ZZZX541        	1	19970107	G	5620	1014301835	WINDOW          			BEECH 	200   	200BEECH    	1152920	CE  										3RD CABIN RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	175SA	7526 				BB183				INSPECTION FOUND WINDOW CRACKED ALMOST ALL THE WAY AROUND AFT SIDE.						1	L	7	2 	4T				A24CE   					 
1998021100067	19980211	00067	CE  	1998	2	11	98ZZZX544        	1	19971228	G	3222	1243009201	PISTON ASSEMBLY 			CESSNA	210   	T210L       	2073449	CE  										NOSE GEAR	BROKEN          	G				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	23	732DK	2838 				21061432				AIRCRAFT EXPERIENCED A NOSE LANDING GEAR FAILURE DURING TAXI OPERATIONS AFTER LANDING.  SUBSEQUENT INSPECTION REVEALED T	HE FORK AND PISTON ASSEMBLY BROKE AT THE CASTING AREA LOCATED AT THE POINT WHERE BOTH FORKS ATTACH TO THE PISTON ASSEMBL	Y.				1	H	7	1 	3O				3A21    					 
1998021100072	19980211	00072	EU  	1998	2	11	98ZZZX549        	1	19970131	G	5511	453005509	FITTING         			ISRAEL	1124  	1124        	4500102	EU  										H STAB AFT SPAR	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	1629	7428 				363				CRACKS FOUND IN HORIZONTAL STABILIZER AFT SPAR SPLICE HINGE FITTING OUTBOARD LUGS.  LANDINGS, 5,442.						2	M	7	2 	4F				A2SW    					 
1998010800114	19980108	00114	NE  	1998	1	8	98ZZZX55         	3	19971203	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		8056 	3860 					HJ163A		INNER AND OUTER RACE OF NR 4 BLADE SHANK BEARING FOUND BROKEN AND SEPARATED INTO NUMEROUS PIECES.  HUB RENDERED SCRAP AS	 A RESULT OF BEARING FAILURE.  SUBMITTER SUGGESTS ENGINEERING REVIEW OF LOADS IMPOSED AT BLADE/HUB INTERFACE.  UNDER LOW	 C.F. LOADING, IF THE BLADE IS A MAXIMUM ALLOWABLE TIP MOVEMENT, POST SB A190 CONDITION (.750), THE BEARINGS MAY BE EXPE	RIENCING CYCLICAL LOADS NOT PRESENT DURING ORIGINAL CERTIFICATION.			2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1998021100073	19980211	00073	CE  	1998	2	11	98ZZZX550        	1	19970107	G	2701	051316714	YOKE            			CESSNA	182   	182F        	2072714	CE  										PILOTS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	3655U	4113 				18255055				WHILE CHECKING ELEVATOR TRAVEL, YOKE BROKE WHEN BROUGHT UP AGAINST ELEVATOR STOP LEAVING BROKEN PART IN HAND.  RECOMMEND	 PULL TEST.					1	H	7	1 	3O			NT	3A13    					 
1998021100080	19980211	00080	CE  	1998	2	11	98ZZZX557        	1	19971219	G	5553	04311481	FITTING         			CESSNA	150   	150J        	2071820	CE  										VERTICAL STAB	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	51400					150699981				INSPECTION FOUND VERTICAL STABILIZER ATTACH FITTING CRACKED.						1	H	7	1 	3O				3A19    					 
1998021100082	19980211	00082	WP  	1998	2	11	98ZZZX559        	2	19971215	G	7240	31021731	DIFFUSER VANE   			SWRNGN	SA226 	SA226TB     	8780406	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					HOT SECTOIN	FAILED          	B		A	WD4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17	271DC	2992 				T414	P35151C			DURING HOT SECTION INSPECTION, FOUND DIFFUSER VANE P/N 3102173-1 BROKEN IN SEVERAL PIECES LYING ON TOP OF THE OUTER TRAN	SITION LINER AND WEDGED BETWEEN THE COMPRESSOR HOUSING AND BOTTOM OF TRANSITION LINER.  FURTHER INVESTIGATION REVEALED T	HAT RECOMMENDED GARRETT SB TPE331-72-0458 HAD NOT BEEN C/W.				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
1998010800115	19980108	00115	NE  	1998	1	8	98ZZZX56         	3	19971203	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		7900 	4161 		2109NR			HJ234A		INSPECTION FOUND 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	 
1998021100083	19980211	00083	NE  	1998	2	11	98ZZZX560        	3	19971216	G	6111	57C0792	BEARING         			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	BLADE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8658 	4101 					HJ235A		BLADE INNER BEARING HALF CRACKED.  CRACK IS APPROXIMATELY 2.750 INCHES LONG IN ONE-HALF ONLY.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1998021100085	19980211	00085	WP  	1998	2	11	98ZZZX562        	1	19971223	G	5330	592487250	SKIN            			DOUG  	DC9   	DC951       	3022051	WP  										BS 908	CORRODED        	B	L		ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	420EA	71164				47689				DURING C-CHECK INSPECTION, DISCOVERED CORROSION ON THE FUSELAGE SKIN LAP SEAM AT BS 908, LONGERON 26R.  REPAIRED BY TRIM	MING OUT THE CORRODED OVERLAPPING SKIN, HFEC INSPECTING, FABRICATING AND INSTALLING REPAIR SKIN FILLER, INTERNAL FINGER 	DOUBLER AND EXTERNAL DOUBLER WET WITH SEALANT.  ACCOMPLISHED IAW EVERGREEN AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHOR	IZATION NR N420EA-53-003-EAC.  (X)			2	L	7	2 	4F			RT	A6WE    					 
1998021100086	19980211	00086	NM  	1998	2	11	98ZZZX563        	1	19971106	G	5730		SKIN            			BOEING	727   	7272J4      	1384006	NM  										LT WING TIP	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	696CA	48025				22574				DURING C-CHECK INSPECTION, DISCOVERED A CRACK ON THE LEFT HAND REMOVABLE WING TIP SKIN.  REPAIRED BY TRIMMING AWAY DAMAG	E, HFEC INSPECTING FOR ABSENCE OF CRACKS, FABRICATING AND INSTALLING REPAIR FILLERS, INTERNAL DOUBLER, SHIMS AND STRAP W	ET WITH SEALANT AND ORIGINAL FASTENER TYPES.  ACCOMPLISHED ON EVERGREEN AIR CENTER - ENGINEERING CHANGE/REPAIR AUTHORIZA	TION NR N696CA-57-001-EAC.			2	L	7	3 	4F			RT	A3WE    					 
1998021100087	19980211	00087	CE  	1998	2	11	98ZZZX564        	1	19971201	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										LOWER LEFT	CRACKED         	B	S		BWRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	376ES	271  				17280059				DURING ANNUAL INSPECTION, FOUND FIREWALL CRACKED UNDER COWL FASTENER DOUBLER.  AIRCRAFT HAS ONLY 271.0 HOURS TOTAL TIME.	  ADVISED MANUFACTURER CRACK WAS 2 INCHES LONG WITH ANOTHER CRACK 1 INCH LONG PROTRUDING FROM THE 2 INCH CRACK MAKING A 	'Y'.				1	H	7	1 	3O			NT	3A12    					 
1998021100088	19980211	00088		1998	2	11	98ZZZX565        	4	19971205	G	3457	066040310111	GPS             		KLN90A      															COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					13197					GPS NEVER POWERED UP - HAS BEEN REPAIRED FOR THIS SAME PROBLEM TWICE.  REMOVED AND REPLACED.																			 
1998021100089	19980211	00089		1998	2	11	98ZZZX566        	1	19971128	G	2436	51530001E1	REGULATOR       																	DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					13526					VOLTAGE REGULATOR UNIT FAILED UPON INITIAL USE.  REMOVED AND REPLACED.																			 
1998021100090	19980211	00090		1998	2	11	98ZZZX567        	4	19971208	G	2350	AA95454	AUDIO PANEL     																	ICS SYSTEM	FAILED          	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					2998					AUDIO PANEL BAD OUT OF STOCK AFTER REPAIR.  AIRCRAFT ICS WILL NOT WORK AT ALL.  REMOVED AND REPLACED.																			 
1998010800116	19980108	00116	NE  	1998	1	8	98ZZZX57         	3	19971203	G	6111	57C792	BEARING         			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	NR 1 BLADE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9295 	4635 					HJ239A		INNER AND OUTER RACE OF NR 1 BLADE SHANK BEARING FOUND BROKEN AND SEPARATED INTO NUMEROUS PIECES.  HUB RENDERED SCRAP AS	 A RESULT OF BEARING FAILURE.  SUBMITTER SUGGESTED ENGINEERING REVIEW OF LOADS IMPOSED AT BLADE/HUB INTERFACE.  UNDER LO	W C.F. LOADING, IF THE BLADE IS AT MAXIMUM ALLOWABLE TIP MOVEMENT POST SB A190 CONDITION (.750), THE BEARINGS MAY BE EXP	ERIENCING CYCLICAL LOADS NOT PRESENT DURING ORIGINAL CERTIFICATION.			2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
1998010800117	19980108	00117	EA  	1998	1	8	98ZZZX58         	2	19971101	G	7322	2524054	SERVO           			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  	LYC   	O360  	IO360A1B6   	41514	EA  					FUEL INJECTION	CORRODED        	D	L	A		A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	999TD					1546	L12564A			DURING FLIGHT, ACFT ENGINE LOST POWER FOLLOWING A ONE 'G' POSITIVE MANEUVER.  INVESTIGATION FOUND FUEL INJECTION SERVO W	AS HANGING UP.  SUSPECT CORROSION AND LACK OF LUBE.					1	M	7	1 	3O	3	O	RT	EXPA1M71	1E10				 
1998010800065	19980108	00065	SO  	1998	1	8	98ZZZX6          	2	19971210	G	8530	646226	VALVE           			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					NR 3 CYL EXHAUST	WORN            	B			NT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3046K	1107 				E2362	675310			CYLINDER NR 3 REMOVED DUE TO EXCESSIVE EXHAUST VALVE LEAKAGE DURING A COMPRESSION TEST.  EXHAUST VALVE STEM WAS FOUND WO	RN .023 INCH AT TIP OF STEM TO ABOUT THE CENTER OF STEM.  GUIDE WAS NOT WORN (NITRALOY).  NR 2 CYLINDER WAS REMOVED FOR 	ANOTHER REASON AND THE EXHAUST VALVE CHECKED OK.  NR 6 CYLINDER EXHAUST VALVE WAS REMOVED DUE TO EXCESSIVE WEAR AT 625.7	 HOURS.			1	L	7	1 	3O	3	O		3A15    	E3SO				 
1998021100123	19980211	00123		1998	2	11	98ZZZX600        	4	19971121	G	2562	4520114	BATTERY         		ELT10       	BOLKMS	BK117 	BK117C1     	5626025	EU  										ELT	DISCHARGED      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				ELT BATTERY MAX ALLOWABLE DISCHARGE LIMITS REACHED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998021100124	19980211	00124	SW  	1998	2	11	98ZZZX601        	1	19970902	G	6310	222044607003	COUPLING        			BELL  	222   	222U        	1182140	SW  										M/R DRIVE	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW				A1275	47520				M/R DRIVE INNER COUPLING PITTING CORROSION ON TEETH.  REJECTED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1998021100125	19980211	00125	SW  	1998	2	11	98ZZZX602        	1	19971006	G	6310	222044672101S	COUPLING        			BELL  	222   	222U        	1182140	SW  										MAIN DRIVE	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM				A954	47573				COUPLING HAS CORROSION, PITTING ON TEETH.  DAMAGED BEYOND LIMITS.  REJECTED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1998021100126	19980211	00126	NE  	1998	2	11	98ZZZX603        	2	19970804	G	7250	311565201	GAS GENERATOR   								PWA   	PT6   	PT6A67D     		NE  					ENGINE	MALFUNCTIONED   	B			MASR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	01		9478 	2167 		9E962		114179			THIS GAS GENERATOR CASE S/N 9E962 IS PRESENTLY AT E.D.M. FOR INVESTIGATION FOR LOW TORQUE COMPRESSOR STALLING.											4	T			E26NE				 
1998021100127	19980211	00127	WP  	1998	2	11	98ZZZX604        	2	19971230	G	7250	30727121	BLADE           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					HP TURBINE	FAILED          	B			JY2R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			GL	23	30HJ	2269 				226	P74659			DURING CRUISE FLIGHT AT 41,000 FEET, THE RT ENGINE APPARENTLY HAD HP BLADE FAILURE RESULTING IN IN-FLIGHT SHUTDOWN.  OPE	RATOR DECLARED EMERGENCY AND HAD UNEVENTFUL LANDING AT TUL.  DISASSEMBLY OF ENGINE CONFIRMED THE FAILURE.  LOT NRS 4161,	 4191, AND 4266.  NOTE:  SB 72-3494 HAD BEEN C/W AND SETS LIFE LIMIT AT 4,500 HOURS ON THIS PART.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1998021100133	19980211	00133	CE  	1998	2	11	98ZZZX610        	1	19971201	G	5720		NUTPLATE        			BEECH 	200   	200BEECH    	1152920	CE  										LT LE WING ROOT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	520MC	8600 				BB43				DURING AN INSPECTION OF THE AIRCRAFT, THE LEFT LEADING EDGE WING ROOT FAIRING WAS REMOVED TO PERFORM MAINTENANCE.  A 2.5	0 INCH CRACK WAS FOUND FROM ONE OF THE RIVETS WHICH HOLD THE NUTPLATE IN PLACE FOR THE WING ROOT FAIRING IN THE PRESSURE	 VESSEL AREA.  CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED.				1	L	7	2 	4T				A24CE   					 
1998021100134	19980211	00134	CE  	1998	2	11	98ZZZX611        	1	19971201	G	5730		SKIN            			BEECH 	200   	200BEECH    	1152920	CE  										LT/RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	520MC	8600 				BB43				DURING AN EVENT 1 INSPECTION, CRACKS IN THE WING SKIN IN THE AREA OF THE LEFT AND RIGHT LOWER WING BOLT FITTING WERE FOU	ND.  THESE CRACKS TEND TO GO THROUGH THE HOLES WHERE SCREWS ARE USED TO SECURE THE SKIN TO THE WING SPAR CAP, AND EXTEND	 TO THE HOLE IN THE SKIN FOR THE FUEL DRAIN.  SUBMITTER STATED SEVERAL OF THE E-90 FLEET  HAVE HAD DOUBLERS INSTALLED TO	 REPAIR THIS PROBLEM IN THE PAST.			1	L	7	2 	4T				A24CE   					 
1998021100135	19980211	00135	CE  	1998	2	11	98ZZZX612        	1	19971201	G	5730		SKIN            			BEECH 	200   	200BEECH    	1152920	CE  										RT WING FUEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	520MC	8600 				BB43				DURING AN EVENT 1 INSPECTION, A .50 INCH CRACK WAS FOUND IN THE SKIN AFT OF THE RIGHT FUEL FILLER CAP.  THE CRACK APPEAR	S TO BE DUE TO IMPROPER USE OF THE FUEL NOZZLE DURING FUELING.  INSTALLATION OF AN INTERNAL DOUBLER WAS REQUIRED.					1	L	7	2 	4T				A24CE   					 
1998021100136	19980211	00136	CE  	1998	2	11	98ZZZX613        	1	19971201	G	5712		RIB             			BEECH 	200   	200BEECH    	1152920	CE  										LT WS 56-65-75	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	520MC	8600 				BB43				DURING AN EVENT 1 INSPECTION, 3 RIBS ON THE LEFT INBOARD WING AT STA 56.00, STA 65.50, AND STA 75.50 AND ONE ON THE RIGH	T AT STA 65.50 WERE FOUND CRACKED ON THE FORWARD RIVET WHERE THE STRINGER IS ATTACHED.  THE CRACK WENT FROM THE RIVET HO	LE FORWARD TO THE EDGE OF THE RIB.  SUBMITTER STATED CAUSE IS UNKNOWN, BUT SUSPECT IT IS DUE TO FLEXING OF THE WING.  RE	PAIRED BY INSTALLING A DOUBLER.			1	L	7	2 	4T				A24CE   					 
1998021100138	19980211	00138	WP  	1998	2	11	98ZZZX615        	1	19971110	G	5330	591140659	SKIN            			DOUG  	DC9   	DC932       	3022066	WP  										BS 221	IMPROPER REPAIR 	B			DU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	913VV					47318				DURING C-CHECK, FOUND REPAIR THAT DOES NOT MEET FUSELAGE PLATING REPAIR CRITERIA CLASS I, CLASS II, OR CLASS III AT FS 2	21 BETWEEN LONGERON 17LT AND CUSP.  FABRICATED REPAIR, DRILLED, TREATED, PRIMED AND INSTALLED IAW ACM SKETCH 97840  REV 	A AND DAC ROD 97-11-17-ON.				2	L	7	2 	4F				A6WE    					 
1998021100139	19980211	00139	NE  	1998	2	11	98ZZZX616        	2	19971222	G	7250	311899101	BLADE           								PWA   	PT6   	PT6A67      	52043	NE  					GAS GENERATOR	DEFECTIVE       	B			MASR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01										D.T.S. RECEIVED THREE SETS OF COMPRESSOR TURBINE BLADES (129 EACH) UNDER SALES ORDER 35879, CUSTOMER ORDER NR 8519.  EXA	MINING THE BLADES REVEALED A SURFACE DEFECT ON THE PARENT METAL ON THREE EACH BLADES THAT EXCEED THE OVERHAUL LIMIT OF 0	.003 INCH.  REF:  CHAPTER 72-50-02, PAGE 305B (2)(A) OF OVERHAUL MANUAL 3038337.  THE THREE BLADES WERE RETURNED TO P & 	W FOR EVALUATION.								4	T			E26NE				 
1998021100141	19980211	00141	NE  	1998	2	11	98ZZZX618        	2	19971223	G	7250	311899101	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 THREE SETS OF COMPRESSOR TURBINE BLADES (129 EACH) UNDER SALES ORDER 36561, CUSTOMER ORDER NR 8612.  EXA	MINING THE BLADES REVEALED A SURFACE DEFECT ON THE PARENT METAL OF 69 EACH BLADES THAT EXCEEDS THE OVERHAUL LIMITS OF 0.	003 INCH.  REF:  CHAPTER 72-50-02 PAGE 305B(2)(A) OF OVERHAUL MANUAL 3038337.  THE 69 BLADES WERE RETURNED TO P & W FOR 	EVALUATION.								4	T			E26NE				 
1998021100142	19980211	00142	NE  	1998	2	11	98ZZZX619        	2	19971222	G	7250	3119899101	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 TWO SETS OF COMPRESSOR TURBINE BLADES (86 EACH) UNDER SALES ORDER NR 36248, CUSTOMER ORDER NR 8661.  EXA	MINING THE 86 EACH BLADES REVEALED A SURFACE DEFECT OF THE PARENT METAL THAT EXCEEDS OVERHAUL LIMITS OF 0.003 INCH.  REF	:  CHAPTER 72-50-02 PAGE 305B(2)(A) OF OH 3038337.  THE BLADE SETS WERE RETURNED TO P & W FOR EVALUATION.									4	T			E26NE				 
1998021100143	19980211	00143	WP  	1998	2	11	98ZZZX620        	2	19971207	G	7250	3072712	BLADE           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					HP TURBINE	FAILED          	B			IY2R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	15	727GL	2869 				127	P74627			DURING FLIGHT AT 41,000 FEET CRUISE, THE RT ENGINE APPARENTLY HAD HP BLADE FAILURE RESULTING IN IN-FLIGHT SHUTDOWN.  OPE	RATOR DECLARED EMERGENCY AND HAD UNEVENTFUL LANDING IN BALTIMORE, MD.  DISASSEMBLY OF ENGINE CONFIRMED THE FAILURE.  NOT	E:  SB 72-3494 HAD BEEN C/W AND SETS LIFE LIMIT AT 4,500 HOURS ON THIS PART.				2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1998021100146	19980211	00146	SW  	1998	2	11	98ZZZX623        	1	19971202	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CORRODED        	B			VE3D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	58236	473  				53069				INSPECTING HELICOPTER PER AD 97-22-15, FOUND TWO T/R DRIVE DISC PACKS BEYOND DAMAGE LIMIT.  DAMAGE WAS DUE TO CORROSION.	  REPLACED DAMAGED PARTS.					1	G	7	1 	3U			O	H2SW    					 
1998021100478	19980211	00478	CE  	1998	2	11	98ZZZX626        	1	19971206	G	5712		RIB             			BEECH 	200   	200BEECH    	1152920	CE  										WS 46,65,85	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5ST	7206 				BB289				RIBS ON THE LEFT WING, ONE STRINGER AFT OF THE LEADING EDGE AT WS 56.50, WS 65.50, AND WS 85.00 ARE CRACKED WHERE THE ST	RINGER AND RIB ATTACH.  THE CRACKS GO FROM THE RIVET HOLE FORWARD TO THE LEADING EDGE OF RIB SECTION.  SUSPECT CRACKS AR	E DUE TO THE FLEXING OF THE WING OVER TIME.   REPAIRED BY INSTALLATION OF A DOUBLER.				1	L	7	2 	4T				A24CE   					 
1998021100480	19980211	00480		1998	2	11	98ZZZX628        	1	19971211	G	7100	3034	HOSE            	AEROQUIP    																ENGINE SYSTEM	DEFECTIVE       	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09										NEW AEROQUIP HOSE DATED 3Q97 WITH A DEFECT ON THE INSIDE DIAMETER.																			 
1998021100481	19980211	00481	SO  	1998	2	11	98ZZZX629        	1	19971101	G	2912	756164	SPRING          			PIPER 	PA31  	PA31310     	7103103	SO  										LT/RT HYD FILTER	MISSING         	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09	272HJ	3572 				317712055				BOTH THE LEFT AND RIGHT HYDRAULIC FILTER HOUSINGS WERE MISSING THEIR SPRINGS.  THE SPRINGS HOLD THE FILTER IN PLACE AND 	WILL COMPRESS SHOULD THE FILTER PLUG UP.  IT IS POSSIBLE THE FILTER COULD FALL OFF ITS INSTALLED POSITION WITHOUT THE SP	RING IN PLACE.				1	L	7	1 	3O			RT	A20SO   					 
1998021100482	19980211	00482	SO  	1998	2	11	98ZZZX630        	1	19971101	G	2731	4248403	CONTROL CABLE   			PIPER 	PA31  	PA31310     	7103103	SO  										ELEVATOR TRIM	DEFECTIVE       	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09	272HJ	3572 				317712055				FOUND THE ELEVATOR TRIM CABLE SPLICED IN TWO PLACES BOTH OF WHICH PASSED AROUND THE SERVO CAPSTAN.  THERE IS NO RECORD O	F THE SPLICES BEING DONE IN THE LOG BOOKS.  THE TRIM SERVO MOTOR HAD BEEN REPLACED 30 HOURS PREVIOUSLY DUE TO IT BEING B	URNED OUT (DID THE SPLICES STRESS THE MOTOR?)				1	L	7	1 	3O			RT	A20SO   					 
1998021100483	19980211	00483	SO  	1998	2	11	98ZZZX631        	1	19971101	G	5520	453226	BOOT            			PIPER 	PA31  	PA31310     	7103103	SO  										ELEVATOR	MISSING         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ	3572 				317712055				FOUND ONE ELEVATOR COUNTER BALANCE LEADING EDGE BOOT MISSING AND THE FIBERGLASS SUB-SURFACE WAS ERODED.  THE OTHER BOOT 	WAS TORN WHICH ALLOWS WATER TO GET INISDE THE BOOT WHICH WILL CHANGE THE BALANCE OF THE CONTROL SURFACE.					1	L	7	1 	3O			RT	A20SO   					 
1998021100484	19980211	00484	SO  	1998	2	11	98ZZZX632        	1	19971101	G	5753		ROLLERS         			PIPER 	PA31  	PA31310     	7103103	SO  										FLAP	SEIZED          	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09	272HJ					317712055				FOUND THE FLAP ROLLERS NOT TURNING DUE TO PAINT BEING ON THE ROLLERS AND TRACKS.  ALSO, FOUND FLIGHT CONTROL SURFACE HAR	DWARE COVERED WITH PAINT (WHERE THE CONTROLS EVEN OFF) AND THE CONTROL SURFACE LEADING EDGES HAD NO PAINT ON THEM.  AIRC	RAFT WAS PAINTED 1/94 BY CIMARRON AIRCRAFT CORP IN EL RENO, OK.				1	L	7	1 	3O			RT	A20SO   					 
1998021100485	19980211	00485	SO  	1998	2	11	98ZZZX633        	1	19971101	G	3213	4205907	TRUNNION        			PIPER 	PA31  	PA31310     	7103103	SO  										MLG	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ	3572 				317712055				INSPECTION FOUND THE CYLINDER SIDEWALL (ON THE OUTSIDE) WITH DEEP INTERGRANULAR GALVANIC CORROSION.  THIS CORROSION IS H	ARD TO SPOT DUE TO ITS BEING IN THE GEARWELL AND BEHIND A LARGE HOSE CLAMP BRACKET.					1	L	7	1 	3O			RT	A20SO   					 
1998021100486	19980211	00486	SO  	1998	2	11	98ZZZX634        	1	19971101	G	2720	40040009	TORQUE TUBE     			PIPER 	PA31  	PA31310     	7103103	SO  										RUDDER	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ					317712055				FOUND THE RUDDER TORQUE TUBE AND WELDED ON ASSEMBLIES VERY CORRODED.  THE WELDED ON PLATE IS ABOVE THE BOTTOM RIB ON THE	 RUDDER AND CAN ONLY BE SEEN THROUGH A SMALL CUT-OUT IN THE RIB WHERE THE TORQUE TUBE PASSES THROUGH.  THE BOTTOM RIB (P	N 40039-00) WAS ALSO UNAIRWORTHY DUE TO CORROSION.				1	L	7	1 	3O			RT	A20SO   					 
1998021100487	19980211	00487	SO  	1998	2	11	98ZZZX635        	1	19971101	G	5541	4003900	RIB             			PIPER 	PA31  	PA31310     	7103103	SO  										RUDDER	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	272HJ					317712055				FOUND THE RUDDER TORQUE TUBE AND WELDED ON ASSEMBLIES VERY CORRODED.  THE WELDED ON PLATE IS ABOVE THE BOTTOM RIB ON THE	 RUDDER AND CAN ONLY BE SEEN THROUGH A SMALL CUT-OUT IN THE RIB WHERE THE TORQUE TUBE PASSES THROUGH.  THE BOTTOM RIB (P	N 40039-00) WAS ALSO UNAIRWORTHY DUE TO CORROSION.				1	L	7	1 	3O			RT	A20SO   					 
1998021100489	19980211	00489	CE  	1998	2	11	98ZZZX637        	1	19971210	G	2460	TB2	TERMINAL BOARD  			CESSNA	402   	402B        	207590P	CE  										WS 27.125	SHORTED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	6387X	4430 				402B1350				DURING ROUTINE MAINTENANCE, CHANGING RIGHT COWL FLAP CABLE, THE HEATER'S FUEL LINE CONTACTED THE NON-INSULATED TERMINAL 	BOARD'S STUD AT RIGHT WING STA 27.125.  PLACING MASTER SWITCH IN ON POSITION PROVIDED A SHORT CIRCUIT AND FIRE.  THE TER	MINAL BOARD'S STUDS NEED TO BE INSULATED FROM FUEL AND OIL LINES IN IMMEDIATE AREA.				1	L	7	2 	3O				A7CE    					 
1998021100494	19980211	00494	SW  	1998	2	11	98ZZZX642        	1	19971211	G	6710	C4264221	RETAINER        	RONSON      	206003      	BELL  	206   	206BELL     	1181502	SW  										M/R SERVO	CRACKED         	B	S		B6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					RH1243					SERVO RETAINER CAME BACK FROM NDT, INDICATED CRACKED.						1	G	7	1 	3U				H2SW    					 
1998021100872	19980211	00872	NE  	1998	2	11	98ZZZX670        	2	19971201	G	7230	817401	HUB             								PWA   	JT8   	JT8D15A     	52051	NE  					C1 BLADE SLOT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		27593	14794				717164			AFTER LANDING AT SURABAYA, THE NR 1 ENGINE WAS FOUND WITH HEAVY COMPRESSOR DAMAGE. DURING INVESTIGATION, DISCOVERED THE 	C-1 HUB HAD A SECTION MISSING AT ONE OF THE BLADE SLOTS.  PART S/N N96749.										4	F			E2EA				 
1998010800001	19980108	00001	NE  	1998	1	8	98ZZZX68         	2	19971209	G	7250	657087	CASE            		658199      	SKRSKY	S64   	S64F        		NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					AFT FLANGE	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	178AC	2205 	705  		225	64097	638213			WHILE INSTALLED, AFT FLANGE OF CASE SN 225 FRACTURED 360 DEGREES WITHIN THE FLANGE WELD JOINT.  FRACTURING OF AFT FLANGE	 ASSY ELIMINATED THE AFT MOUNT FROM ENG SUPPORT.  ENG FREE TO MOVE VERTICALLY, LATERALLY, AND FORE AND AFT, UNRESTRAINED	 BY AFT MOUNT.  THIS MOTION CAUSED DAMAGE TO COMPRESSOR DIFFUSER CASE MOUNT LOCATIONS WHICH WERE DISCOVERED CRACKED SHOR	TLY AFTER REPLACEMENT OF FREE TURBINE ASSY.  SUBMITTER STATED FAILURE OF AFT FLANGE WAS DUE TO AN IMPROPER REPAIR PERFOR	MED BY ANOTHER REPAIR STATION AND CONSISTED OF INCOMPLETE FUSION IN AN EB WELD, MISMATCH BETWEEN WELDED PARTS, AND UNDER	CUT IN HAZ ACTING AS A STRESS RISER.  DEFECTIVE BY MEANS OF IMPROPER ACCOMPLISHMENT OF APPROVED P & W REPAIR PROCESS.	2	G	7	2 	4U	4	U		H6EA    	E15EA				 
1998021900001	19980219	00001	CE  	1998	2	19	98ZZZX688        	1	19970109	G	3244	500X5	TIRE            			BEECH 	36    	36BEECH     	1151602	CE  										NLG	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	05	1194A					E159				NOSE LANDING GEAR TIRE BLOWN ON LANDING.  NO OTHER TROUBLE.						1	L	7	1 	3O				3A15    					 
1998021900002	19980219	00002	CE  	1998	2	19	98ZZZX689        	1	19970107	G	3710	242	PUMP            	AIRBORNE    		BEECH 	36    	36BEECH     	1151602	CE  										VACUUM SYSTEM	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	361BC					E1331				DEPARTED AIRPORT AND WITHIN 30 MINUTES VACUUM PUMP BROKE.  RETURNED TO BASE.  NO OTHER TROUBLE.						1	L	7	1 	3O				3A15    					 
1998021900008	19980219	00008	SO  	1998	2	19	98ZZZX695        	1	19971022	G	2434	3656624	ALTERNATOR      			PIPER 	PA32  	PA32260     	7103206	SO  										FIELD WIRE	SHORTING        	D	S	A		K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	15	7701J	1    			A110854	321068				SUBMITTER HAS FOUND 2 FAULTY ALTERNATORS BACK-TO-BACK WITH THE SAME PROBLEM.  THE FIELD WIRE SOLDERED CONNECTIONS, POINT	S A AND B, STAND UP OFF OF THE ROTOR TOO HIGH AND MOMENTARILY TOUCH CASE.  THIS OCCURRENCE AT HIGH RPM ONLY CAUSES THE F	IELD CIRCUIT BREAKER TO TRIP.  HARD PROBLEM TO FIND, IT ONLY OCCURS IN-FLIGHT AT HIGH 2,750 RPM, AND, ALT TEST BENCH DOE	S NOT SPIN FAST ENOUGH TO FIND THE PROBLEM.			1	L	7	1 	3O				A3SO    					 
1998010800066	19980108	00066	SO  	1998	1	8	98ZZZX7          	1	19971211	G	2150	460102	FAN             		5134900     	PIPER 	PA31T 	PA31T       	7103124	SO  										A/C CONDENSER	FAILED          	D		A		A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	23	57MR				1086	31T7620022				DURING CRUISE FLIGHT, PILOTS NOTICED SPARKS EMITTING FROM RT AFT NACELLE AT AIR CONDITIONING CONDENSER AIR SCOOP.  RT GE	NERATOR WAS SHUT OFF, BUT SPARKS CONTINUED.  DECISION WAS MADE TO SHUT DOWN RT ENGINE AND PROBLEM SUBSIDED.  AIRCRAFT HA	D UNEVENTFUL LANDING.  AN INVESTIGATION REVEALED AIR CONDITIONER CONDENSER IMPELLER FAN SEPARATED FROM CONDENSER FAN MOT	OR SHAFT AND CHAFED A GENERATOR WIRE FROM TERMINAL 'C' TO RT STARTER SOLENOID CAUSING THE FAN BLADES TO ARC ON GENERATOR	 WIRE.		1	L	7	2 	3T				A8EA    					 
1998021900153	19980219	00153	WP  	1998	2	19	98ZZZX734        	1	19971230	G	6320	369D2512711	RING GEAR       			HUGHES	369   	369E        	4470707	WP  										M/R TRANSMISSION	BROKEN          	D		A		O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	01	272MK	499  			0055701304	0256E				PILOTS REPORTED MAIN ROTOR TRANS CHIP LIGHT AND KNOCKING SOUND.  CHECKED CHIP PLUGS AND FOUND DARK GRAY INTERNAL LOOKING	 METAL ON CHIP DETECTOR.  REMOVED MAIN ROTOR TRANSMISSION FROM SERVICE.  SENT MAIN ROTOR TRANSMISSION TO NAC IN LONG BEA	CH.  WHEN DISASSEMBLED FOUND BROKEN TOOTH ON OUTPUT RING GEAR, PN 369D25127-11.				1	G	7	1 	3U				H3WE    					 
1998021900155	19980219	00155	SW  	1998	2	19	98ZZZX736        	1	19971220	G	7712	407375003107	INDICATOR       			BELL  	407   	407         		SW  										ENGINE TORQUE	FAILED          	B			VE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	58236	522  			84	53069				TORQUE INDICATOR WILL LOSE ALL POWER AT TIMES (INTERMITTENT).  REPLACED INDICATOR.						1	G	7	1 	3U			O	H2SW    					 
1998043000245	19980430	00245	CE  	1998	4	30	98ZZZX762        	1	19971118	G	5753		FLAP            			CESSNA	182   	182Q        	2072732	CE  										RT WING	JAMMED          	G				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	23	735YG	3239 				18265786				ON APPROACH, PILOT SELECTED THE FLAP POSITION.  THE RIGHT FLAP JAMMED AND TWISTED INTERFERRING WITH CONTROL OF THE RIGHT	 AILERON.  PILOT LANDED WITHOUT INCIDENT.  SUSPECT CAUSE WAS THE WING ATTACHING POINT SHOWED THE ROLLERS BEING LUBRICATE	D, BUT WERE WORN; THUS, FAILING, CAUSING FLAP TO BIND WHEN EXTENDED.				1	H	7	1 	3O			NT	3A13    					 
1998043000255	19980430	00255	EA  	1998	4	30	98ZZZX772        	2	19971125	G	8520	76948	CRANKSHAFT      								LYC   	O320  	O320*       	41508	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					101280					PART WAS REMOVED FROM INVENTORY AS PRECAUTION.  THE CRANKSHAFT WAS RECENTLY SERVICED BY AIR AGENCY AND FOUND TO HAVE CRA	CKS IN THE JOURNAL RADII.  PART IS SCRAP.										3	O			E274				 
1998010800131	19980108	00131	EU  	1998	1	8	98ZZZX78         	1	19971105	G	3246	C201801202	WHEEL           			AMD   	FALC50	FALCON900   	2700160	EU  										BRAKE LUG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		2465 			U689					DURING EDDY CURRENT INSPECTION REQUIRED BY SL 24, FOUND ONE BRAKE DRIVE LUG CRACKED IN SUSPECT AREA NOTED IN SL.						2	L	7	3 	4F			RT	A46EU   					 
1998010800132	19980108	00132	EU  	1998	1	8	98ZZZX79         	1	19971105	G	3246	C201801202	WHEEL           			AMD   	FALC50	FALCON900   	2700160	EU  										BRAKE LUG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		2465 			U681					DURING EDDY CURRENT INSPECTION REQUIRED BY SL 24, FOUND FIVE BRAKE DRIVE LUGS CRACKED IN SUSPECT AREA NOTED IN SL.						2	L	7	3 	4F			RT	A46EU   					 
1998022600058	19980226	00058	CE  	1998	2	26	98ZZZX792        	1	19970912	G	5512		SKIN            			BEECH 	90    	E90         	1152914	CE  										LT HORIZ STAB	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	00	379VM	4271 				LW27				IT APPEARS THAT VIBRATION AND LEFT HAND PROPELLER HARMONICS CAUSED OIL CANNING BETWEEN TWO STRINGERS THAT INDUCED THE OR	IGINAL SKIN CRACK WHICH ENLARGED ITSSELF.  FOUND DURING THE BEECH COMPLETE INSPECTION.  SUBMITTER STATED IF GONE UNDETEC	TED COULD CAUSE HORIZONTAL STABILIZER FAILURE WITH CATASTROPHIC RESULTS. SUBMITTER STATED TWELVE AMT'S AND REPRESENTATIV	ES OF AVIATION HAVE NEVER SEEN THIS BEFORE.			1	L	7	2 	3T				3A20    					 
1998010800067	19980108	00067	SO  	1998	1	8	98ZZZX8          	1	19971212	G	5711		SPAR            			PIPER 	PA28  	PA28RT201   	7102818	SO  										WING FUEL AREA	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8368H	5560 				28R8118062				COMPLIED WITH MANDATORY SB 1006 DURING ANNUAL INSPECTION.  FOUND AND REPAIRED MINOR FUEL LEAKS AND SURFACE CORROSION IN 	WING SPAR AND WHEELWELL AREAS.  REPAIRED LEAK, CLEANED AND TREATED CORROSION AND PAINTED AREA WITH CHEMICAL RESISTANT EP	OXY ZINC CHROMATE PRIMER.  SUBMITTER SUGGESTS C/W THIS BULLETIN AS SOON AS POSSIBLE ON ALL AFFECTED AIRCRAFT.  SHOULD BE	 MADE AN AD NOTE.			1	L	7	1 	3O				2A13    					 
1998010800133	19980108	00133	NM  	1998	1	8	98ZZZX80         	1	19970725	G	3244		TIRE            			DOUG  	MD11  	MD11        	3023602	NM  										NR 7 WHEEL	FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	103EV					48415				AIRCRAFT HAD SUFFERED A NR 7 TIRE TREAD PEEL-OFF ON 7-25-97 AT AMSTERDAM DURING LANDING.  THE PEELED OFF TIRE CAUSED 6 F	AN BLADES OF NR 3 ENGINE AND RIGHT HAND INBOARD FLAP TO BE DAMAGED.   ALL DAMAGED FAN BLADES WERE REPLACED AND RIGHT INB	OARD FLAP WAS REPAIRED.  THE CAUSE OF NR 7 TIRE PEEL-OFF IS NOT YET DETERMINED.				2	L	7	3 	4F			RT	A22WE   					 
1998010800134	19980108	00134	CE  	1998	1	8	98ZZZX81         	1	19971212	G	5312	9544001337	BULKHEAD        			BEECH 	95    	95B55       	1152729	CE  										BS 271.92	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	111KF	2946 				TC633				DURING ANNUAL INSPECTION, FOUND CRACKING IN TAIL AT FS 271.92 BULKHEAD.  REPAIRED PER BEECHCRAFT SI 990.  AREA VERY HARD	 TO INSPECT.  SI 990 ALSO HAS INSPECTION CRITERIA.  CRACKING FOUND ON 3 AIRCRAFT AT THIS STATION WHILE C/W SI 990.  SUBM	ITTER SUGGESTED BULLETIN AND AD NOTE ON THIS INSPECTION MAKING IT MANDATORY.				1	L	7	2 	3O			RT	3A16    					 
1998022600442	19980226	00442		1998	2	26	98ZZZX813        	4	19971105	G	2210	1015000385	CIRCUIT BOARD   			BEECH 	200   	200BEECH    	1152920	CE  										AUTOTRIM	MISMANUFACTURED 	B		A	ZE4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	33	38473					BB842				FACTORY NEW REPLACEMENT AUTOTRIM RELAY ASSEMBLY (PC BOARD) CAUSES MANUAL AND AUTOTRIM TO RUN BACKWARDS.  ALSO, HAS INCOR	RECT GENDER FASTENERS.  CAME WITH FEMALE FASTENERS, SHOULD HAVE MALE.					1	L	7	2 	4T			 	A24CE   					 
1998010800135	19980108	00135		1998	1	8	98ZZZX82         	4	19971212	G	6122	8210115	GOVERNOR        	WOODWARD    		MTSBSI	MU2   	MU2B40      		CE  										PROPELLER	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	21	157MA				1708431	424SA				IN FLIGHT, RT ENGINE RPM DECAYED AND TORQUE ROSE.  ALL OTHER PARAMETERS NORMAL.  ENGINE WAS SHUT DOWN.  AIRCRAFT RETURNE	D TO RIC AND SAFE LANDING MADE.  TROUBLESHOT BY MAINTENANCE FOUND BETA SYSTEM OK.  PROPELLER GOVERNOR REPLACED WITH OVER	HAULED UNIT. SYSTEM CHECKED OK.  ON GROUND RUN DURING TROUBLESHOOTING, OLD PROPELLER GOVERNOR WOULD TRY TO FEATHER PROPE	LLER WHEN MOVED OUT OF BETA RANGE.  GOVERNOR SENT TO WOODWARD FOR OVERHAUL.  SUSPECT INTERNAL FAILURE.  GARRETT P/N FOR 	GOV IS 897410-7U.		1	H	7	2 	3T				A10SW   					 
1998010800136	19980108	00136	SW  	1998	1	8	98ZZZX83         	1	19971205	G	6220	407010150101A	FRAHM ASY       			BELL  	407   	407         		SW  										M/R HEAD	DEFECTIVE       	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407AP	88   			A37	53020				INSPECTION FOUND M/R FRAHM ASSY HAD LOOSE SPRINGS.  REPLACED WITH NEW FRAHM FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW    					 
1998022600459	19980226	00459	SO  	1998	2	26	98ZZZX831        	1	19971230	G	2820	MIL6000	HOSE            			PIPER 	J3    	PA11        	7101102	SO  										FUEL SYSTEM	DETERIORATED    	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	23	5532H					111035				DURING A FATAL AIRCRAFT ACCIDENT INVESTIGATION, INTERNAL DETERIORATION OF MIL-6000 HOSE WAS FOUND PLUGGING A VENT LINE. 	 THE HOSE WAS DATED DURING 1977 AND 1986.  THE AIRCRAFT WAS OPERATING ON AUTO GAS (STC'D).  THIS CONDITION HAS BEEN SEEN	 AND REPORTED BEFORE.  IT IS IMPSSIBLE FOR A CAR GAS USER TO KNOW WHAT IS IN THE PRODUCT/GAS DUE TO REFINERY SWAPPING OF	 PRODUCT AND CO-MINGLING OF PRODUCTS.  SUBMITTER STATED C/W WITH STC, NOT POSSIBLE AS IT IS WRITTEN.			1	H	7	1 	3O				A691    					 
1998022600464	19980226	00464		1998	2	26	98ZZZX836        	1	19971125	G	2720	WD607	PEDAL           			AMTR  		RV6         												LT RUDDER	FAILED          	G		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	36AH	430  				20814				LEFT RUDDER PEDAL SNAPPED OFF OF CROSS PIECE.  ASSEMBLY WAS FACTORY PURCHASED.  BOTH PARTS SENT TO NTSB FOR ANALYSIS.  N	TSB DETERMINED THERE WAS A FATIGUE CRACK ORIGINATING ON THE REAR OUTSIDE PORTION OF THE TORQUE TUBE.								0 										 
1998010800137	19980108	00137	EA  	1998	1	8	98ZZZX84         	2	19971028	G	7322	293548	BELLOWS         		MA6AA       	BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435A1A   	41516	EA  					CARB MIXTURE	FAILED          	G		A		O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	05	47AH		1086 		AH1383	2645	L10652			HELICOPTER LOST ENGINE POWER IN-FLIGHT.  DURING GROUND RUN TROUBLESHOOTING PROCESS, THE ENGINE WOULD NOT OPERATE ABOVE 1	500 RPM.  THE MARVEL SCHEBELER (MODEL MA-6AA, SN AH-1-383) CARBURETOR WAS BENCH TESTED BY THE NTSB AND WOULD ONLY PERFOR	M APPROXIMATELY 50 PERCENT CAPACITY.  DURING CARBURETOR TEAR DOWN INSPECTION, FOUND PLASTIC RESIN ADHESIVE MISSING.  THI	S ADHESIVE LOCKS THE BELLOWS TO THE SHAFT ON THE AUTOMATIC MIXTURE CONTROL (PN 293-548).  THIS ALLOWED THE BELLOWS TO  M	OVE DOWN THE SHAFT, THEREFORE, LIMITING FUEL OUTPUT.		1	G	7	1 	3O	3	O		2H3     	1E13				 
1998010800138	19980108	00138	SW  	1998	1	8	98ZZZX85         	1	19971112	G	6220	369D21200	HUB             			HUGHES	500N  	500N        	3027374	SW  										M/R	VIBRATION       	G				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	07	524FB	1769 	70   			LN004				ERRATIC TRACK AND BALANCE .89 IPS AT 11:00 TO .15 AT 9:00 CHANGES BY SHAKING COLLECTIVE GRIP LENGTH.  ALSO, APPEARS TO C	HANGE BY PULLING ON BLADES.					1	G	7	1 	3U			NC	H3WE    					 
1998010800139	19980108	00139	SW  	1998	1	8	98ZZZX86         	1	19971212	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										M/R	CRACKED         	B			KUVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	166BH	1579 				45661				DURING 100-HOUR INSPECTION, NOTICED PATCH ON BLADE LIFTING, REMOVED PATCH.  FOUND 10 INCH CRACK RUNNING CHORD-WISE FROM 	REPAIR.  THIS BLADE CAME FROM MANUFACTURER WITH PATCH AS NEW.					1	G	7	1 	3U				H2SW    					 
1998010800140	19980108	00140	NE  	1998	1	8	98ZZZX87         	1	19971124	G	3233	1944L200	ACTUATOR        		S76719441000	SKRSKY	S76   	S76A        	8143006	NE  										NLG DOWNLOCK	FAILED          	B	L	A	B8FR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	25	CGHJL	19088	80   			760214				NOSE LANDING GEAR RETRACT ACTUATOR FAILED TO LOCK IN THE COMPRESSED POSITION (GEAR DOWN) CAUSING THE AIRCRAFT NLG TO COL	LAPSE (MINOR DAMAGE TO AIRFRAME) WITH NO REPORTED INJURIES.  ACTUATOR NEW 1981 AND PERFORMED PER DESIGN UNTIL REMOVAL 19	97 FOR LEAKING.  UNIT RESEALED BY AN OUTSIDE CONCERN (NOT BFG) AND INCIDENT OCCURRED SHORTLY THEREAFTER.				1	G	7	2 	3U				H1NE    					 
1998030500016	19980305	00016	GL  	1998	3	5	98ZZZX870        	3	19971105	G	6111	V84334	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	OUTER SHANK	CRACKED         	B			WD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					A93342			BJ553		WHILE C/W AD 97-18-02, A LARGE CRACK WAS DISCOVERED IN THE 'V' OF THE DOUBLE SHOULDER BLADE SHANK AREA.																5	C	P6EA	 
1998030500017	19980305	00017	GL  	1998	3	5	98ZZZX871        	3	19971105	G	6111	V84334	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	OUTER SHANK	CRACKED         	B			WD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					A93340			BJ553		WHILE C/W AD 97-18-02, A LARGE CRACK WAS DISCOVERED IN THE 'V' OF THE DOUBLE SHOULDER BLADE SHANK AREA.																5	C	P6EA	 
1998030500018	19980305	00018	EA  	1998	3	5	98ZZZX872        	2	19971104	G	8530	LW14995	SHROUD SPRING   								LYC   	O360  	O360A1D     	41514	EA  					PUSHROD TUBE	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23							L666636			THE PUSHROD SHROUD TUBE SPRING RETAINER LOCATED UNDER THE VALVE COVER BROKE, AFTER ABOUT 8 HOURS OF SERVICE, ALLOWING TH	E SHROUD TUBE TO MOVE AND CREATE EXCESSIVE OIL LEAKAGE.										3	O			E286				 
1998030500021	19980305	00021	SO  	1998	3	5	98ZZZX875        	2	19970129	G	8530	65344A6	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					NR 5	CRACKED         	B			ES4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	2043X	1185 				E1387	281961R			NR 5 CYLINDER HAD CRACK AT UPPER SPARK PLUG BOSS.  THIS ENGINE HAS HAD C/W SID 97-2, SID 97-3, AND PROPER MAINTENANCE DU	RING ITS LIFE.  BAFFLING, FUEL SYSTEM SETUP, AND GENERAL MAINTENANCE HAVE BEEN CAREFULLY CONTROLLED ON THIS ENGINE.					1	L	7	1 	3O	3	O		3A15    	E3SO				 
1998010800141	19980108	00141	CE  	1998	1	8	98ZZZX88         	1	19971212	G	5740	60110000	FITTING         			BEECH 	60    	B60         	1153605	CE  										LT/RT WING	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	341D					P397				WHILE C/W WING BOLT REPLACEMENT AND WING INSPECTION, FOUND LOWER AFT WING FITTINGS ON BOTH WINGS WITH COMPRESSION MARKS.	  BEECHCRAFT FIELD SERVICE CONTACTED PER MM INSTRUCTIONS.  SPECIAL TOOLING AVAILABLE TO RESURFACE FITTING FACE.  SUBMITT	ER SUGGESTED OWNERS CONFORM TO WING BOLT INSPECTION/REPLACEMENT PER MM INTERVALS.				1	L	7	2 	3O				A12CE   					 
1998030500033	19980305	00033	CE  	1998	3	5	98ZZZX887        	1	19971115	G	3211	05411211	GEAR SUPPORT    			CESSNA	182   	182         	2072702	CE  										MLG LT OTBD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	6346A	6027 				33146				BOTH LANDING GEAR OUTBOARD SUPPORT CASTINGS FOUND CRACKED DURING ANNUAL INSPECTION.  AIRCRAFT CARRIES 5 PERSONS (PER STC	) DURING SKYDIVING OPERATIONS.  NO RECORD OF PREVIOUS CHANGE OF THESE SUPPORTS.  LANDING GEAR SHOULD BE CHECKED AFTER HA	RD LANDINGS.				1	H	7	1 	3O			NT	3A13    					 
1998030500034	19980305	00034	CE  	1998	3	5	98ZZZX888        	1	19971115	G	3211	05411212	GEAR SUPPORT    			CESSNA	182   	182         	2072702	CE  										MLG RT OTBD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	6346A	6027 				33146				BOTH LANDING GEAR OUTBOARD SUPPORT CASTINGS FOUND CRACKED DURING ANNUAL INSPECTION.  AIRCRAFT CARRIES 5 PERSONS (PER STC	) DURING SKYDIVING OPERATIONS.  NO RECORD OF PREVIOUS CHANGE OF THESE SUPPORTS.  LANDING GEAR SHOULD BE CHECKED AFTER HA	RD LANDINGS.				1	H	7	1 	3O			NT	3A13    					 
1998010800142	19980108	00142	WP  	1998	1	8	98ZZZX89         	2	19971118	G	7210	30724632	DAMPER RING     			HWKSLY	DH125 	DH125400A   	4230140	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					PINION GEAR	FAILED          	G				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	21	545S	5346 				NA0719	P80244			WHILE CRUSING AT 26,000 FEET, PILOT OBSERVED AN INCREASE IN OIL PRESSURE FOLLOWED BY A DROP IN PRESSURE.  AS OIL PRESSUR	E CONTINUED TO DECREASE TO 25 PSI, THE PILOT COMMANDED AN IN-FLIGHT SHUTDOWN.  N1 SPEED WAS REPORTED TO BE AS HIGH AS 10	1.5 PERCENT.  FAILURE OF THE FAN PLANETARY GEAR ASSEMBLY CAUSED BY A SEPARATION OF A SECTION OF THE PINION GEAR DAMPER R	ING.  THE SEPARATED SECTION OF THE DAMPER RING BECAME ENMESHED IN THE PLANETARY GEAR TRAIN AND DAMAGED IT EXTENSIVELY CA	USING THE LP SPOOL AND FAN ASSEMBLY TO BECOME DECOUPLED.		2	L	7	2 	4J	4	F		A3EU    	E6WE				 
1998030500038	19980305	00038	CE  	1998	3	5	98ZZZX892        	1	19971115	G	3211	05411212	GEAR SUPPORT    			CESSNA	182   	182         	2072702	CE  										RT MLG OTBD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5553B	6913 				33553				BOTH LANDING GEAR OUTBOARD SUPPORT CASTINGS FOUND CRACKED AT ANNUAL INSPECTION.  AIRCRAFT CARRY 5 PERSONS (PER STC) DURI	NG SKYDIVING OPERATIONS.  NO RECORD OF PREVIOUS CHANGE OF THESE SUPPORTS.  LANDING GEAR SHOULD BE INSPECTED AFTER HARD L	ANDINGS.				1	H	7	1 	3O			NT	3A13    					 
1998030500039	19980305	00039	CE  	1998	3	5	98ZZZX893        	1	19971115	G	3211	05411211	GEAR SUPPORT    			CESSNA	182   	182         	2072702	CE  										LT MLG OTBD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5553B	6913 				33553				BOTH LANDING GEAR OUTBOARD SUPPORT CASTINGS FOUND CRACKED AT ANNUAL INSPECTION.  AIRCRAFT CARRY 5 PERSONS (PER STC) DURI	NG SKYDIVING OPERATIONS.  NO RECORD OF PREVIOUS CHANGE OF THESE SUPPORTS.  LANDING GEAR SHOULD BE INSPECTED AFTER HARD L	ANDINGS.				1	H	7	1 	3O			NT	3A13    					 
1998030500040	19980305	00040	SO  	1998	3	5	98ZZZX894        	2	19970129	G	8530	653447A	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O550  	IO550*      		SO  					NR 4	CRACKED         	B			ES4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	73463	1076 				20700593	284588R			NR 4 CYLINDER HAD CRACK AT UPPER SPARK PLUG BOSS.  THIS ENGINE HAS HAD C/W SID 97-2, SID 97-3, AND PROPER MAINTENANCE. B	AFFLING, FUEL SYSTEM SET-UP, AND GENERAL MAINTENANCE HAVE BEEN CAREFULLY CONTROLLED ON THIS ENGINE.					1	H	7	1 	3O	3	O		A16CE   	E3SO				 
1998030500041	19980305	00041	SO  	1998	3	5	98ZZZX895        	2	19970129	G	8530	653447A1	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O550  	IO550*      		SO  					NR 1	CRACKED         	B			ES4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	73463					20700593	284588R			NR 1 CYLINDER HAD CRACK AT UPPER SPARK PLUG BOSS.  THIS ENGINE HAS HAD C/W SID 97-2, SID 97-3, AND PROPER MAINTENANCE. B	AFFLING, FUEL SYSTEM SET-UP AND GENERAL MAINTENANCE HAVE BEEN CAREFULLY CONTROLLED ON THIS ENGINE.					1	H	7	1 	3O	3	O		A16CE   	E3SO				 
1998030500044	19980305	00044	EU  	1998	3	5	98ZZZX898        	2	19971127	G	7421		SPARK PLUG      			AMTR  	KITFOX	KITFOX      	05613LZ	GL  	ROTAX 	532   	ROTAX532    	55555	EU  					ENGINE	FAILED          	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99						1				AN EQUIVALENT AUTOMOTIVE SPARK PLUG WAS USED IN PLACE OF THE ENGINE MANUFACTURER-RECOMMENDED SPARK PLUG DUE TO LOCAL AVA	ILABILITY.  AFTER APPROXIMATELY 25 HOURS, A ROUTINE INSPECTION CAUSED BOTH SPARK PLUGS TO BE REMOVED.  THERE IS ONLY ONE	 SPARK PLUG PER CYLINDER AND TWO CYLINDERS PER ENGINE.  THE FRONT SPARK PLUG, CLOSEST TO THE GEAR REDUCTION UNIT, WAS IN	TERNALLY BROKEN - THE METAL ELECTRODE INSIDE THE PORCELAIN HOUSING HAD BROKEN IN HALF AND WAS FREE TO FLOAT INSIDE.			1	H	7	1 	3I	3	I	NC	EXPA1H71	EXPE3I				 
1998010800068	19980108	00068	EA  	1998	1	8	98ZZZX9          	2	19971101	G	7414	M3333	IMPULSE COUPLING	SLICK       	6351        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  						DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8127K	500  			46030011	327940268	L22070048A			MAGNETO REMOVED AT 500 HOURS TIS DUE TO IMPULSE COUPLING DEFECT.						1	L	7	1 	3O	3	O		A3SO    	1E4				 
1998010800143	19980108	00143		1998	1	8	98ZZZX90         	4	19971111	G	3418	A233103	SWITCH          			CESSNA	525   	525         	2076601	CE  										AOA HEAT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	511AC	1837 				5250090				AOA PROBE WOULD NOT HEAT.  TRACED PROBLEM TO DEFECTIVE SWITCH.						1	L	7	2 	4F			RT	A1WI    					 
1998030500613	19980305	00613	NE  	1998	3	5	98ZZZX905        	2	19971020	G	7250	803003	BLADE           								PWA   	JT8   	JT8D217A    	52053	NE  					LPT ROTOR	FAILED          	B			RH2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			6047 				P709747			ENGINE REMOVED FOR METAL IN THE TAILPIPE.											4	F			E9NE				 
1998010800144	19980108	00144	CE  	1998	1	8	98ZZZX91         	1	19971215	G	4930		HOSE            			CESSNA	650   	650         	2076802	CE  										APU FUEL	LEAKING         	C		A		K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			EA	23	67SF					6500045				CREW COMPLAINED OF FUEL ODOR IN AFT BAGGAGE COMPT.  INVEST REVEALED A FUEL HOSE LEAKING THRU OUTER JACKET.   HOSE IS APP	ROX 16 INCHES LONG AND LOCATED ABOVE RT FWD CEILING OF AFT BAGGAGE COMPT BETWEEN APU FUEL SHUT-OFF VALVE AND A UNION.  T	HE OTHER SIDE IS ATTACHED TO ANOTHER HOSE WHICH GOES TO THE APU FUEL FILTER.  TURBOMACH APU PARTS MANUAL SHOWS 1 HOSE TR	AVELING BTWN VALVE AND APU.  HOSES REPLACED WITH NEW TSO'D HOSE ASSY.   OLD HOSES SHOWED SIGNS OF RUBBER BEING EXTRUDED 	THRU SS OUTER JACKET AND NO MARKINGS ON EITHER HOSE.  COULD NOT DETERMINE IF HOSES WERE ORIGINAL.  PATS SB NR SA 289NE-4	 (FUEL VALVE RELOCATION) PREVIOUSLY C/W.  SUBMITTER SUGGESTED A ONE-TIME INSP OF FUEL HOSES FOR APPROVED HOSE ASSYS.	2	L	7	2 	4F				A9NM    					 
1998030500621	19980305	00621	EU  	1998	3	5	98ZZZX913        	1	19971111	G	2430	SP461300	TOGGLE SWITCH   			BOLKMS	117   	BK117B1     	5626012	EU  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										SWITCH SPRING WEAK.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998030500625	19980305	00625	EA  	1998	3	5	98ZZZX917        	2	19970511	G	7314	LW13909	PUMP            			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE FUEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	102PA	152  			D8619	4636068	L976061A			ENGINE WILL NOT SHUT DOWN WITH MIXTURE CONTROL.  FOUND FUEL PUMP LEAKING INTO UPPER DECK LINE.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
1998010800145	19980108	00145	EU  	1998	1	8	98ZZZX92         	1	19971217	G	3520	C3512000	MASK            			BRAERO	DH125 	BAE125800A  	1500285	EU  										FACE CAP	TORN            	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	601RS					258018				TEAR IN MASK FACE CUSHION PER SB 35-3014 AND SB C351-2000-35.  MASK DOES NOT FALL WITHIN SB'S COMPLIANCE EVEN THOUGH THE	 MASK EXHIBITS THE SAME TEARING AS SPECIFIED IN SB.  SUBMITTER SUGGESTED SB C351-2000-35-1 BY PURITAN-BENNETT AND SB 35-	3014 BY RAYTHEON SHOULD INCLUDE ALL MASKS OF THE C351-2000 SERIES.				2	L	7	2 	4F			RT	A3EU    					 
1998030500628	19980305	00628	SO  	1998	3	5	98ZZZX920        	1	19971223	G	3240	492152	VALVE           			PIPER 	PA31  	PA31P       	7103120	SO  										PARKING BRAKE	MALFUNCTIONED   	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21						7300116				SUBMITTER SUGGESTS PARKING BRAKE VALVE P/N 492152 IS DEFECTIVE.  WHEN HANDLE OR LEVER ASSY IS MOVED, IT DISENGAGES AND V	ALVE CANNOT BE SET OR RESET.					1	L	7	2 	3O				A8EA    					 
1998030500637	19980305	00637	EA  	1998	3	5	98ZZZX929        	2	19971125	G	8520	76948	CRANKSHAFT      								LYC   	O320  	O320*       	41508	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					101280					PART REMOVED FROM INVENTORY AS PRECAUTION.  THE CRANKSHAFT WAS RECENTLY SERVICED BY AIR AGENCY AND FOUND TO HAVE CRACKS 	IN THE JOURNAL RADII.  PART IS SCRAP.  NELSON W.O. 1 533.										3	O			E274				 
1998010800146	19980108	00146	CE  	1998	1	8	98ZZZX93         	1	19971212	G	5540		RUDDER          			CESSNA	500   	S550        	2076607	CE  										TIP CAP	LIGHTNING STRIKE	D				K				NONE                    				C			F.O.D.                    			NR	NOT REPORTED   	1			EA	21	674JM	3137 				S5500127				AIRCRAFT ENTERED SHOP FOR ROUTINE MAINTENANCE AND DURING PRELIM INSPECTION NOTICED RUDDER TIP CAP BURNED AND LOOSE.  TEA	R DOWN INSP OF RUDDER SHOWED INTERNAL SIGNS OF OVERHEATING.  OWNER QUESTIONED AND WAS DETERMINED THAT AT SOME PREVIOUS T	IME, ACFT HAD A LIGHTNING STRIKE AND HAD NEVER BEEN INSPECTED PER ATA CHAPTER 5 MM.  RUDDER HAD TO BE REBUILT AND DURING	 INSPECTION, OTHER AREAS OF OF LIGHTNING STRIKES HAD TO BE REPAIRED.  SUBMITTER SUGGESTED PILOTS HAVE ACFT INSPECTED AS 	SOON AS POSSIBLE AFTER LIGHTNING STRIKES.		1	L	7	2 	4F			RT	A22CE   					 
1998010800147	19980108	00147		1998	1	8	98ZZZX94         	4	19971219	G	6122	8210260	GOVERNOR        		WOODWARD    	BEECH 	100   	B100        	1152919	CE  										PROPELLER	FAILED          	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	25	924RM		294  		981946A	BE63				DURING FLIGHT, RIGHT ENGINE FLAMED OUT, NTS AND THE PROP FEATHERED.  AN UNEVENTFUL LANDING WAS PERFORMED.  UPON INSPECTI	ON, FOUND THE ARM HAD FALLEN OFF OF THE PROP GOVERNOR SPLINED SHAFT.  THE MOUNT BOLT WAS STILL SECURE IN THE ARM.  THIS 	IS THE SECOND OCCURRENCE OF A B-100, ONE FAILED ARM HAD A SAFETY AND THIS ONE DID NOT.  IT IS SUGGESTED THAT ON ENGINE I	NSPECTIONS, THE ARM BE PULLED ON FOR SECURITY TEST AND THAT THE MOUNT BOLT BE CHECKED FOR TIGHTNESS.			1	L	7	2 	4T				A14CE   					 
1998030500655	19980305	00655	SW  	1998	3	5	98ZZZX940        	1	19971216	G	6310	222044672101	COUPLING        			BELL  	222   	222U        	1182140	SW  										DRIVE	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM	426  			A1138	47573				OUTER COUPLING HAS CORROSION ON INTERNAL SPLINES, LESS THAN 1 YEAR ON SERVICE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1998030500656	19980305	00656	SW  	1998	3	5	98ZZZX941        	1	19971216	G	6310	222044672101	COUPLING        			BELL  	222   	222U        	1182140	SW  										DRIVE	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	219HM	426  			A1132	47573				OUTER COUPLING HAS CORROSION ON INTERNAL SPLINES.  LESS THAN 1 YEAR IN SERVICE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW    					 
1998030500657	19980305	00657	EU  	1998	3	5	98ZZZX942        	1	19971216	G	6410	117317411	BLADE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				121	7505				T/R BLADE DEBONDED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998030500662	19980305	00662	EU  	1998	3	5	98ZZZX947        	1	19971118	G	2810	1176416901	DRAIN VALVE     			BOLKMS	117   	BK117A3     	5626015	EU  										FUEL TANK	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	1140H					7078				FUEL TANK HAS STATIC LEAK AT DRAIN VALVE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU   					 
1998030500666	19980305	00666	EU  	1998	3	5	98ZZZX951        	1	19971228	G	2140	11798439	CONTROL UNIT    			BOLKMS	BK117 	BK117C1     	5626025	EU  										HEATER	FAILED          	B			TI1R	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	05	117NC				01016	7509				HEATER OVERHEATED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998030500667	19980305	00667	EU  	1998	3	5	98ZZZX952        	1	19971229	G	3610	HTE200016	VALVE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										BLEED SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC				492GB364	7509				BLEED VALVE DOES NOT OPERATE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998030500668	19980305	00668	EU  	1998	3	5	98ZZZX953        	1	19971218	G	3610	HTC200016	VALVE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										BLEED SYSTEM	STICKS          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC				492BG365	7509				VALVE STICKS WHEN SELECTING HEAT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
1998010800149	19980108	00149	CE  	1998	1	8	98ZZZX96         	1	19971217	G	5312	05132833	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  										LT DOOR POST	CRACKED         	B	S		DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	311EH	5246 				17269158				INSPECTION REVEALED A CRACK IN THE LEFT HAND DOOR POST AFT SECTION AT THE LOWER DOOR HINGE LOCATION.  CRACK STARTS AT TH	E AFT SCREW HOLE AND PROGRESSES IN BOTH DIRECTIONS.  CRACK IS APPROXIMATELY 1.3750 INCHES LONG.					1	H	7	1 	3O			NT	3A12    					 
1998043000423	19980430	00423		1998	4	30	98ZZZX960        	4	19971002	G	3424	1394T1007Z	GYRO            			CESSNA	310   	310R        	2074245	CE  										TURN COORDINATOR	FAILED          	D				K				NONE                    				I			FLT. ATTITUDE INST.       			NR	NOT REPORTED   	1			GL	17	3284M				7861084	310R1892				FAILURE OF THE TURN COORDINATOR WAS NOTICED BY THE PILOT BY THE LACK OF MOVEMENT WHILE FLYING, HOWEVER, THE INOP FLAG WA	S NOT PULLED TO THE OFF POSITION.  SUBMITTER STATED AN UNDERSTANDING THAT THE FLAG SHOULD INDICATE FAILURE WHEN THE GYRO	 STOPS SPINNING.				1	L	7	2 	3O				3A10    					 
1998043000424	19980430	00424	CE  	1998	4	30	98ZZZX961        	1	19970819	G	2823	98510675	SELECTOR        			CESSNA	180   	180K        	2072624	CE  										FUEL SYSTEM	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	61858	2386 				18052807				FOUND FUEL SELECTOR VALVE CORRODED AND FLAKING ON ONE SIDE.  THE ONLY WAY TO SEE THIS SIDE OF THE VALVE IS WITH A MIRROR	 THROUGH THE INSPECTION PANEL ON THE BOTTOM OF THE AIRCRAFT.  AIRCRAFT IS ON FLOATS.					1	H	7	1 	3O				5A6     					 
1998043000428	19980430	00428	EA  	1998	4	30	98ZZZX965        	2	19970702	G	7414	M3548	ROTOR           		4370        						LYC   	O360  	O360A3A     	41514	EA  					ENGINE MAG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17					95020074		L769036A			INSPECTION FOR MAGNETO FAILURE FOUND ROTOR CONTACT END BROKEN.											3	O			E286				 
1998010800150	19980108	00150	SO  	1998	1	8	98ZZZX97         	1	19971120	G	3211		ATTACH BOLT     			PIPER 	PA28  	PA28140     	7102802	SO  										LT MLG	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	33138					287525161				WHILE PERFORMING SB 1006, NOTED LOWER ATTACH BOLTS OF THE LT MLG STRUT WERE CORRODED AND ONE BROKEN OFF AT THE HEAD (INS	IDE).  THIS IS THE SECOND SUCH OCCURRENCE FOUND ON TWO AIRCRAFT, AND THE DEFECT WAS IN THE LEFT MLG IN BOTH CASES.  THE 	BOLTS (UPPER AND LOWER) WERE CORRODED.  IN BOTH CASES, THEY WERE BROKEN INSIDE THE WING NEXT TO THE SPAR CAP AREA.  (IN 	THE FIRST CASE, 2 UPPER BOLTS WERE ALSO BROKEN).  THIS WAS HARD TO DETECT FROM THE OUTSIDE.			1	L	7	1 	3O				2A13    					 
1998043000434	19980430	00434	CE  	1998	4	30	98ZZZX971        	1	19971201	G	5610	5111604202	WINDSHIELD      			CESSNA	421   	421C        	2076016	CE  										COPILOT	DEPARTED        	D				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			NM	05	88584	7500 				421C0642				AS THE AIRCRAFT LEVELED OFF AT 23,000 FEET MSL, THE COPILOT'S WINDSHIELD DEPARTED THE AIRCRAFT WITH APPROXIMATELY 10 PER	CENT LEFT ATTACHED TO THE AIRFRAME.  SUSPECT THE FORWARD RIGHT LOWER ATTACH HOLES IS WHERE THE CRACK STARTED, THEN THE C	RACK WENT STRAIGHT UP OR AFT TO THE TOP OF THE WINDSHIELD.  SHOULD HAVE RECURRING INSPECTION OF ATTACH HOLES.  REF:  MEB	 83-33 R-N1.			1	L	7	2 	3O				A7CE    					 
1998043000440	19980430	00440	SO  	1998	4	30	98ZZZX977        	1	19970121	G	3250	2073743	BUSHING         		4713400     	PIPER 	PA31T 	PA31T       	7103124	SO  										NLG STEERING	CORRODED        	B			CTYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	112BL					31T7720037				NOSE GEAR STEERING BELLCRANK BUSHINGS WERE CORRODED IN WHEELWELL AREA.  SYMPTOMS WERE STIFF RUDDER PEDALS.  BUSHINGS AND	 SHAFT, P/N 47080-000, WERE REPLACED.  BUSHINGS HAVE NO GREASE ZERK, BUT SHOWED SIGNS OF PREVIOUS LUBRICATION.					1	L	7	2 	3T				A8EA    					 
1998010800152	19980108	00152	EA  	1998	1	8	98ZZZX99         	2	19971222	G	7414	ES103827901	COIL            	ELECTROSYS  	D4RN2021    	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	73671		452  		60060505	17267605	RL750276T			DURING 500-HOUR INSPECTION, (PULLED AT 452.2 HOURS TSO), BOTH COILS IN TCM 2000 SERIES MAGNETO WERE FOUND CRACKED.  COIL	S HAD THE FOLLOWING MARKINGS:  38/95 AND 8-9, 35/75 AND 10-10.  MAGNETO WAS OVERHAULED BY ELECTROSYSTEMS, INC., FOR LYCO	MING.  ENGINE OVERHAULED ON 8-15-96.  SUSPECT CAUSE IS MANUFACTURING DEFECT OR DESIGN FLOW.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1999010800571	19990108	00571	SW  	1999	1	8	99ZZZM10         	1	19970604	G	3213	AN621A	BOLT            			BBAVIA	8     	8GCBC       	1220803	SW  										STRUT	IMPROPER PART   	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	778AC	32   			38197	38197				FOUND INCORRECT HARDWARD HAD BEEN INSTALLED IN THE UPPER END OF THE LEFT REAR LIFT STRUT.  THE BOLT THROUGH THE UPPER EN	D OF THE LIFT STRUT WAS APPROXIMATELY 1.5 INCHES PLUS TOO LONG.  THE NUT HAD BEEN TIGHTENED UNITL IT BOTTOMED OUT ON THE	 THREADS, LEAVING THE LIFT STRUT FREE TO SLIDE ON THE BOLT.  FLIGHT LOADS HAD BENT THE BOLT AND ELONGATED THE HOLE THROU	GH THE STRUT ATTACH FITTING AND THE REAR SPAR.  THESE PARTS ARE NOT REPAIRABLE PER AMERICAN CHAMPION AIRWORTHINESS LIMIT	ATIONS LIMITATIONS, AND THE LEFT WING WAS REPLACED UNDER FACTOR WARRANTY.  (M)		1	H	7	1 	3O				A21CE   					 
1999010800572	19990108	00572	SW  	1999	1	8	99ZZZM11         	1	19970601	G	2810		FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  										FUSELAGE	CONTAMINATED    	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	778AC				38197	38197				WHILE TROUBLESHOOTING OTHER PROBLEMS (POWER LOSS) FOUND LARGE AMOUNTS OF ALUMINUM PARTICLES IN THE FUEL SYSTEM.  METAL P	ARTICLES WERE LEFT FROM MANUFACTURING PROCESS OF THE FUEL TANKS (GRIND MATERIAL PRIOR TO WELDING).  REQUIRED REPEATED CL	EANING OF THE FUEL SCREENS, AND FLUSH OF THE FUEL SYSTEM.  PARTICALS IN THE GASCOLATOR SCREEN WERE ENOUGH TO RESTICT FUE	L SUPPLY TO THE ENGINE.  (M)			1	H	7	1 	3O				A21CE   					 
1999010800573	19990108	00573	SW  	1999	1	8	99ZZZM12         	1	19970601	G	7160	714755	TUBE            			BBAVIA	8     	8GCBC       	1220803	SW  										COWL	LOOSE           	B			CL4R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AL	03	778AC	18   			38197	38197				NEW AIRCRAFT EN ROUTE FROM AMERICAN CHAMPION FACTORY TO ANCHORAGE, AK, SUFFERED POWER LOSS REQUIRING A PRECAUTIONARY LAN	DING.  INVESTIGATION FOUND THE INDUCTION AIR TUBE BETWEEN THE COWLING AND THE INDUCTION AIRBOX HAD NOT BEEN SECURED TO T	HE COWLING (SECURED ONLY TO THE AIRBOX).  THE HOSE HAD BEEN SUCKED INTO THE FRONT OF THE AIRBOX, PARTIALLY OBSTRUCTING T	HE AIRFLOW INTO THE CARBURETOR.			1	H	7	1 	3O				A21CE   					 
1999010800348	19990108	00348	CE  	1999	1	8	99ZZZX113        	1	19971118	G	2820	1200106263	LINE            			CESSNA	210   	T210M       	2073451	CE  										COCKPIT	CHAFED          	B	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	761VE	2000 				21062546				PILOT REPORTED ERRATIC FUEL FLOW INDICATION.  DURING GROUND ENG RUN-UP FOR T/S, A LOUD POP WAS HEARD, LARGE SPARK SHOT F	ROM BEHIND COPILOT'S INSTRUMENT PANEL, AND THE 3-AMP STEREO CB OPENED.  INVEST REVEALED THE 28-VOLT POWER LEAD FOR THE S	TEREO (INSTALLED SEVERAL YEARS AGO) HAD BEEN CHAFING AGAINST P/N 1200106-263 ALUMINUM LINE (DECK PRESS REF LINE FROM AFT	 SIDE OF FIREWALL TO FUEL FLOW/MAP GAUGE).  CHAFING HAD PROGRESSED TO THE POINT WHERE INSULATION HAD WORN AWAY EXPOSING 	CONDUCTOR WHICH HAD SHORTED AGAINST THE LINE AND ARCING HAD EATEN A .0625 INCH DIA HOLE IN THE LINE.  SINCE THIS IS TURB	OCHARGED INSTALL, LEAK IN THE DECK PRESS LINE RESULTED IN FUEL FLOW READING EXCESSIVELY HIGH AT HIGH POWER SETTINGS.	1	H	7	1 	3O				3A21    					 
1999041700266	19990417	00266	NE  	1999	4	17	99ZZZX1524       	2	19970530	G	7260	795072	BEVEL GEAR      								PWA   	JT8   	JT8*        	52044	NE  					GEARBOX	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					AR1811					PART WAS RECEIVED FROM NORTHWEST A/L - ATLANTA FOR INSPECTION AND REPAIR PER PWA ENGINE MANUAL.  APPROXIMATELY HALF OF T	HE GEAR TEETH WERE SEVERELY CRACKED AND GALLED.										4	F			E2EA				 
1999051400380	19990514	00380	CE  	1999	5	14	99ZZZX1978       	1	19971117	G	3231	0024100381	BRACE           			BEECH 	58    	58P         	1152744	CE  										NLG WW	FAILED          	B	P		SHOR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	XBFTG					TJ264				REF:  ALERT NR 232, 11-97, PG 3, NOSE LANDING GEAR DOOR FAILURE.  DURING ANNUAL INSPECTION, FOUND NOSE GEAR DOORS REMAIN	ED OPEN DURING A RETRACTION TEST.  INSPECTION OF THE SYSTEM FOUND P/N 002-410038-1 BROKEN.  AFTER INSTALLING A NEW PART,	 THE NOSE GEAR DOORS FUNCTIONED PROPERLY.  APPROX TT ON BROKEN PART, 2,000 HOURS.				1	L	7	2 	3O				A23CE   					 
1999051400397	19990514	00397	CE  	1999	5	14	99ZZZX1995       	1	19971024	G	7500		TUBE            			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR	RUPTURED        	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05										AIR CREW REPORTED PROBLEM WITH RT GENERATOR SYSTEM.  DURING T/S, TECH NOTICED HOT AIR COMING FROM AFT FUSELAGE.  A FUSEL	AGE BLEED AIR TUBE WAS FOUND RUPTURED.  A BLEED AIR LEAK WAS FOUND WHEN T/S RT GEN.  THE CAUSE WAS RT FUSELAGE BLEED AIR	 TUBE THAT RUPTURED.  WHEN TUBE RUPTURED, BLEED AIR DUCT FAIL ANNUNCIATOR LIGHT FAILED TO ILLUMINATE.  THE FOUR BLEED AI	R TEMPERATURE SWITCHES TAKEN FROM TT-49 ALL TESTED SATISFACTORY CLOSING BETWEEN 354 DEGREES FAHRENHEIT AND 356 DEGREES F	AHRENHEIT.  THE FAILURE OF THE BLEED AIR TUBE ASSY APPARENTLY DID NOT RAISE TEMPERATURE WITHIN THE AFT FUSELAGE TO A LIM	IT WHICH WOULD ILLUMINATE THE 'BLEED AIR FAIL' WARNING LIGHT.   (BEECHJET 400T-COMMERICAL COUNTERPART BEEECHJET 400A).	2	H	7	2 	4F			RT	A16SW   					 
1999051400479	19990514	00479	CE  	1999	5	14	99ZZZX1999       	1	19970204	G	7500	45A63517071	DUCT            			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		1616 								WHEN PRESSURE CHECK PERFORMED FOR LEFT DUCT REPLACEMENT, FOUND THE RIGHT TO BE LEAKING.  WHEN REMOVED, FOUND WELD BROKEN	 IN SAME PLACE AS THE LEFT ONE.  (BEECHJET 400T - COMMERCIAL COUNTERPART BEECHJET 400A).					2	H	7	2 	4F			RT	A16SW   					 
1999051400480	19990514	00480	CE  	1999	5	14	99ZZZX2000       	1	19970301	G	7500	006244563100	CLAMP           			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										BLEED AIR DUCT FAIL LIGHT - FOUND BROKEN T-BOLT WHICH CAUSED CLAMP TO FALL OFF OF DUCT.  CLAMP WAS OVERTORQUED.  (BEECHJ	ET 400T - COMMERCIAL COUNTERPART BEECHJET 400A).					2	H	7	2 	4F			RT	A16SW   					 
1999051400481	19990514	00481	CE  	1999	5	14	99ZZZX2001       	1	19970204	G	7500	45A63517061	DUCT            			BEECH 	MU300 	400A        	1155402	CE  										BLEED AIR	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	05		1616 								THE NARROWEST PART OF THE DUCT CLOSE TO THE AIRCRAFT SKIN GOING INTO THE ENGINE WAS CRACKED ALL THE WAY AROUND.  AIRCRAF	T HAD A BLEED DUCT FAILURE ANNUNCIATOR LIGHT COME ON IN-FLIGHT.  DUCT WAS IN TWO PIECES WHEN REMOVED.  (SHOULD BE ONE). 	 (BEECHJET 400T - COMMERCIAL COUNTERPART BEECHJET 400A).				2	H	7	2 	4F			RT	A16SW   					 
1999072300540	19990723	00540	EA  	1999	7	23	99ZZZX2725       	2	19970508	G	7414		BEARING         								LYC   	O540  	O540E4C5    	41532	EA  					LT MAGNETO	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23			880  				RL2150940A			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				 
1999091000025	19990910	00025		1999	9	10	99ZZZX3297       	1	19971112	G	6230	206011811101	YOKE            																	MAIN ROTOR	DAMAGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		3127 			AFS5029					TWO INBOARD BUSHING BORES LARGER THAN STANDARD AND SMALLER THAN OVERSIZED.  REMOVED AND REPLACED.																			 
1999012200576	19990122	00576	EA  	1999	1	22	99ZZZX341        	2	19971010	G	8530	ECLN12988CN	STUD            			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					CYLINDER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	51703	100  			01	1118	L1801851A			DURING ANNUAL INSPECTION, 10-10-97, NR 2 CYLINDER COMPRESSION LOW.  AFTER INSPECTION OF CYLINDER, FOUND INTAKE VALVE SEA	T LOOSE AND VALVE BURNT.  SUBMITTER STATED POSSIBLE CAUSE MAY HAVE BEEN OVERBOOSTING ENGINE DURING FLIGHT INSTRUCTION.					1	G	7	1 	3O	3	O		H1CE    	1E10				 
1999012200577	19990122	00577	EA  	1999	1	22	99ZZZX342        	2	19971010	G	8530	LW12988	CYLINDER        			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	51703					1118	L1801851A			DURING ANNUAL INSPECTION, 10-10-97, FOUND NR 2 CYLINDER COMPRESSION WAS LOW.  AFTER INSPECTION OF CYLINDER, INTAKE VALVE	 SEAT WAS FOUND LOOSE, INTAKE VALVE WAS BURNT.  AT THAT TIME, THE OWNER SHOWED 2 MORE CYLINDERS FROM PAST MAINTENANCE WI	TH THE SAME CONDITION, HOWEVER, AFTER RESEARCHING ENGINE LOGS, PART NUMBER IS UNKNOWN.  OWNER ESTIMATES 100 HOURS ON THI	S PART.  OWNER GIVES FLIGHT INSTRUCTION IN AIRCRAFT.  SUBMITTER STATED POSSIBLE CAUSE MAY BE OVERBOOSTING ENGINE.			1	G	7	1 	3O	3	O		H1CE    	1E10				 
1999012900090	19990129	00090	GL  	1999	1	29	99ZZZX409        	2	19971006	G	7250	6886407	BLADE           			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 2 ENGINE	DAMAGED         	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	54197	1493 			X133544	S805	CAE800388F			THE PILOT REPORTED THE NR 2 ENGINE BEGAN TO 'BOG DOWN' DURING A PRECAUTIONARY LANDING TO AN OFFSHORE PLATFORM AFTER THE 	NR 2 ENGINE FIRE WARNING LIGHT ILLUMINATED.  METALURGICAL EXAMINATION BY THE ENGINE MANUFACTURER REVEALED THE FIRST STAG	E TURBINE WHEEL HAD ONE MISSING AIRFOIL (BLADE) AND SEVERAL OTHERS DAMAGED.  THE METALURGICAL REPORTS STATES THE DAMAGE 	WAS MOST LIKELY CAUSED BY SULFIDATION.			1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
1999021900016	19990219	00016	SO  	1999	2	19	99ZZZX576        	2	19971216	G	8520		JOURNAL         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					CRANKCASE	CLOGGED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707DM					421B0145	1881017D			TWO OIL JOURNALS IN CRANKCASE CLOGGED CAUSING TWO PISTONS TO FREEZE AND FAIL.  ON LEFT SIDE OF CRANKCASE THE PISTON BROK	E THROUGH CAUSING A FIST SIZE HOLE ON THE RIGHT SIDE OF THE PISTON BROKE THROUGH CAUSING A SILVER DOLLAR SIZE HOLE.					1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1999030500459	19990305	00459	NE  	1999	3	5	99ZZZX796        	3	19970430	G	6111	8022581	BLADE           		RFC11710C   	SAAB  	SF340 	340B        	7860101	EU  						HAMSTD	14RF	14RF19      	NE  	PROPELLER	DAMAGED         	B			H2SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	330AE	6409 			863679	340B330				UPON EXAMINATION OF BLADE BUTT, AN INDICATION IN THE FILLET RADIUS WAS NOTED.  THE FILLET RADIUS HAS A PORTION OF MATERI	AL MISSING.  THE MISSING PORTION IS APPROXIMATELY 0.170 INCH LONG AND APPROXIMATELY 0.050 INCH WIDE AT ITS WIDEST POINT.	  LOCATION IS APPROXIMATELY 0.500 INCH FROM THE SET SCREW HOLE CENTER APPROXIMTELY 0.250 INCH IN THE COUNTERCLOCKWISE DI	RECTION IF VIEWED FROM THE BUTT END.  THE AREA IS ORIENTED CIRCUMFERENTIALLY IN THE FILLET RADIUS.			2	L	7	2 	4T			RT	A52EU   		6	C	P11NE	 
1999030500485	19990305	00485	NM  	1999	3	5	99ZZZX822        	1	19970115	G	5311		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 WAS NOTED ON FRAME STA 950E AT STR 27R.						2	L	7	3 	4F				A3WE    					 
1999031900750	19990319	00750		1999	3	19	99ZZZX960        	4	19970307	G	2562	E01	ELT             	ACK         		PIPER 	PA12  	PA12        	7101202	SO  										CABIN	FAILED          	H				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	08	3168M	200  			017826	121847				ELT DID NOT FUNCTION DURING 100-HOUR CHECK.  DECELERATION CHECK PER MANUAL; ALSO, HAD LOOSE SCREW INSIDE SEALED ELT ELEC	TRONIC HEAD WHICH WAS REPAIRED BY THE MFG.					1	H	7	1 	3O				A780    					 
1999031900970	19990319	00970	CE  	1999	3	19	99ZZZX969        	1	19971117	G	8011	1971890N	CLUTCH          			CESSNA	150   	150G        	2071816	CE  										STARTER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	3856J	48   			9501393	15065156				TEETH ON PINION GEAR WERE GROUND OFF; METAL WAS FOUND IN THE OIL SUMP AND SCREEN.  THIS PART WAS NEW.  STC SE00262NY CAN	ADIAN AERO MANUFACTURING.					1	H	7	1 	3O				3A19    					 
1997060500299	19970605	00299	NM  	1997	6	5	A3L29707         	1	19970503	G	3246	2607046	WHEEL           		2601571     	BOEING	737   	737*        		NM  										KEY BOSS	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					H5300					WHEEL FLANGE FAILURE AT KEY BOSS.  CRACK PROPAGATED FROM THE TOP CORNER OF THE KEY BOSS.  THERE IS NO NDT INSPECTION REQ	UIRED IN THIS AREA.  SUBMITTER STATED ADD EDDY CURRENT INSPECTION OF THE SIDE AND TOP OF KEY BOSS RELATIVE TO THE CORNER	S.  ADDITIONAL INSPECTION/INSPECTION CYCLE CHANGES MAY BE MADE AFTER COMPLETION OF THE OEM EVALUATION.  (X)				2	L	7	2 	4F			RT	A16WE   					 
1997122400019	19971224	00019	WP  	1997	12	24	A3L297121        	1	19971203	G	3246	9560892	TIE BOLT        		MS21250     	DOUG  	DC9   	DC932       	3022066	WP  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					DEC87107					INSPECTION FOUND WHEEL WITH BROKEN TIE BOLT.  (X)						2	L	7	2 	4F				A6WE    					 
1997122400018	19971224	00018	WP  	1997	12	24	A3L297122        	1	19971204	G	3246	9560892	TIE BOLT        			DOUG  	DC9   	DC932       	3022066	WP  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					MS21250					INSPECTION FOUND WHEEL WITH BROKEN TIE BOLT.  (X)						2	L	7	2 	4F				A6WE    					 
1997122400016	19971224	00016	WP  	1997	12	24	A3L297123        	1	19971205	G	3246	2601483	BOLT            	BENDIX      	20608891    	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B0160					INSPECTION FOUND WHEEL BOLT WITH FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRE-LOAD TORQUE.  SUBMITTER SUGGESTED US	ING SNUG AND ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE    					 
1998040200010	19980402	00010	WP  	1998	4	2	A3L297124        	1	19971216	G	3244	40X1424PR225	TIRE            		3910063511  	DOUG  	DC9   	C9A         		WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					295KH447					TIRE HAD THREAD SEPARATION.  PRELIMINARY ANALYSIS REVEALED DEFECTIVE COAT STOCK MATERIAL USED.  (X)						2	L	7	2 	4F				A6WE    					 
1997092500269	19970925	00269	WP  	1997	9	25	A3L29713         	1	19970905	G	3246	2601483	BOLT            	BENDIX      	26088911A   	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B2119					WHEEL BOLT FATIGUE RELATED FAILURE.  INSUFFICIENT PRE-LOAD TORQUE SUSPECTED CAUSE.  SUBMITTER SUGGESTS USING SNUG ANGLE 	TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE    					 
1997103000190	19971030	00190	WP  	1997	10	30	A3L29714         	1	19971001	G	3246	2601483	BOLT            	BENDIX      	2608891A    	DOUG  	DC9   	DC981       	3022081	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					H0180					INSPECTION FOUND WHEEL BOLT FAILED.  FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRE-LOAD TORQUE.  SUBMITTER SUGGESTE	D USING SNUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F				A6WE    					 
1997103000191	19971030	00191	WP  	1997	10	30	A3L29715         	1	19971001	G	3246	2601483	BOLT            	BENDIX      	2608891A    	DOUG  	DC9   	DC981       	3022081	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B0244					INSPECTION FOUND WHEEL BOLT FAILED.  FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRE-LOAD TORQUE.  SUBMITTER SUGGESTE	D USING SNUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F				A6WE    					 
1997103000189	19971030	00189	WP  	1997	10	30	A3L29716         	1	19971001	G	3246	2601483	BOLT            	BENDIX      	26088911A   	DOUG  	DC9   	DC981       	3022081	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B3230					INSPECTION FOUND WHEEL BOLT FAILED.  FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRE-LOAD TORQUE.  SUBMITTER SUGGESTE	D USING SNUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F				A6WE    					 
1997103000187	19971030	00187	WP  	1997	10	30	A3L29717         	1	19971007	G	3244	401424PR225	TIRE            		3910063511  	DOUG  	DC9   	C9A         		WP  										WHEEL	SEPARATION      	B			A3L2	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					295KH095					TIRE HAS THREAD SEPARATION.  (X)						2	L	7	2 	4F				A6WE    					 
1997103000185	19971030	00185	WP  	1997	10	30	A3L29718         	1	19971009	G	3244	40X1424PR225	TIRE            		3910063511  	DOUG  	DC9   	C9A         		WP  										WHEEL	SEPARATION      	B			A3L2	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					295KH351					TIRE HAS THREAD SEPARATION.  (X)						2	L	7	2 	4F				A6WE    					 
1997103000186	19971030	00186	WP  	1997	10	30	A3L29719         	1	19971009	G	3244	40X1424PR225	TIRE            		3910063511  	DOUG  	DC9   	C9A         		WP  										WHEEL	SEPARATION      	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					42220704					TIRE HAS THREAD SEPARATION.  (X)						2	L	7	2 	4F				A6WE    					 
1997103000188	19971030	00188	NM  	1997	10	30	A3L2974          	1	19971002	G	3246	2601483	BOLT            	BENDIX      	260356112   	BOEING	747   	747*        		NM  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					B9919					INSPECTION FOUND WHEEL BOLT FAILED.  BROKEN BOLT.  (X)						2	L	7	4 	4F			RT	A20WE   					 
1997122400476	19971224	00476	NM  	1997	12	24	A3L397121        	1	19971215	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 WHEEL HAS BROKEN BOLT.  (X)						2	L	7	2 	4F			RT	A16WE   					 
1998040200012	19980402	00012	WP  	1998	4	2	A3L397123        	1	19971216	G	3246	2601483	BOLT            	BENDIX      	26088911    	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B0368					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    					 
1998040200009	19980402	00009	NM  	1998	4	2	A3L397124        	1	19971218	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373T0      	1384582	NM  										WHEEL	FAILED          	B		A	A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B6148					INSPECTION FOUND BROKEN BOLT.  PREVENTIVE ACTION PENDING COMPLETION OF THE INVESTIGATION.  (X)						2	L	7	2 	4F			RT	A16WE   					 
1997092500271	19970925	00271	NM  	1997	9	25	A3L3972          	1	19970907	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					B6372					WHEEL BOLT FATIGUE RELATED FAILURE.						2	L	7	2 	4F			RT	A16WE   					 
1997092500270	19970925	00270	WP  	1997	9	25	A3L3973          	1	19970915	G	3246	2601483	BOLT            	BENDIX      	26088911    	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B1251					WHEEL BOLT FATIGUE RELATED FAILURE.  INSUFFICIENT PRE-LOAD TORQUE SUSPECTED CAUSE.  SUBMITTER SUGGESTS USING SNUG ANGLE 	TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE    					 
1997090400272	19970904	00272	NM  	1997	9	4	A3LD9708         	1	19970820	G	3246	2602540	TIE BOLT        		2609801     	BOEING	737   	737*        		NM  										WHEEL ASSY	FAILED          	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B2850					WHEEL ASSEMBLY TIE BOLT FAILURE.  UNDER EVALUATION BY ALS TEST LAB.  SUBMITTER STATED ADDITIONAL INSPECTION/INSPECTION C	YCLE CHANGES MAY BE MADE AFTER COMPLETION OF THE OEM EVALUATION.  (X)					2	L	7	2 	4F			RT	A16WE   					 
1997090400273	19970904	00273	NM  	1997	9	4	A3LD9709         	1	19970820	G	3246	2602540	TIE BOLT        		2609801     	BOEING	737   	737*        		NM  										WHEEL ASSY	FAILED          	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B3043					WHEEL ASSEMBLY TIE BOLT FAILURE.  SUBMITTER STATED ADDITIONAL INSPECTION/INSPECTION CYCLE CHANGES MAY BE MADE AFTER COMP	LETION OF THE  OEM EVALUATION.  (X)					2	L	7	2 	4F			RT	A16WE   					 
1997090400281	19970904	00281	NM  	1997	9	4	A3LD9710         	1	19970820	G	3246	2602540	TIE BOLT        		2606671     	BOEING	737   	7373A4      	1384585	NM  										WHEEL ASSY	FAILED          	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B4884					DEFECT:  TIE BOLT FAILURE.  CAUSE:  UNDER EVALUATION BY ALS TEST LAB.  PREVENTIVE ACTION:  ADDITIONAL INSPECTION/INSPECT	ION CYCLE CHANGES MAY BE MADE AFTER COMPLETION OF THE OEM EVALUATION.  (X)					2	L	7	2 	4F			RT	A16WE   					 
1997091800413	19970918	00413	WP  	1997	9	18	A3LD9711         	1	19970908	G	3246	L507949	BEARING         	BENDIX      	95502676    	DOUG  	DC9   	DC982       	3022082	WP  										WHEEL ASSY	FAILED          	B			A3LD	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	05					MAR86438					WHEEL ASSY OUTBOARD BEARING FAILURE.  (X)						2	L	7	2 	4F				A6WE    					 
1998040200008	19980402	00008	NM  	1998	4	2	A3LD97112        	1	19971201	G	3246	2602540	BOLT            	BENDIX      	2609801     	BOEING	737   	737524      	1384721	NM  										WHEEL ASSY	FAILED          	B		A	A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B2721					INSPECTION FOUND TIE BOLT FAILURE.  UNDER INVESTIGATION AND PENDING COMPLETION OF THE INVESTIGATION.  (X)						2	L	7	2 	4F			RT	A16WE   					 
1997122400017	19971224	00017	WP  	1997	12	24	A3LD97121        	1	19971205	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	BROKEN          	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B0336					INSPECTION FOUND WHEEL BOLT FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRE-LOAD TORQUE.  SUBMITTER SUGGESTED USING S	NUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE    					 
1997122400015	19971224	00015	WP  	1997	12	24	A3LD97122        	1	19971205	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	BROKEN          	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					B2119					INSPECTION FOUND WHEEL BOLT WITH FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRE-LOAD TORQUE.  SUBMITTER SUGGESTED US	ING SNUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE    					 
1997122400020	19971224	00020	NM  	1997	12	24	A3LD97123        	1	19971211	G	3244	49X17	TIRE            	BENDIX      	26019106    	BOEING	747   	747*        		NM  										MLG	FAILED          	B			A3LD	K				NONE                    				C			F.O.D.                    			NR	NOT REPORTED   	1			EA	05					52020556					TIRE FAILURE DUE TO FOREIGN OBJECT DAMAGE.  (X)						2	L	7	4 	4F			RT	A20WE   					 
1998040200011	19980402	00011	NM  	1998	4	2	AL397122         	1	19971216	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373T0      	1384582	NM  										WHEEL	FAILED          	B		A	A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B4825					INSPECTION FOUND BROKEN BOLT.  PREVENTIVE PENDING COMPLETION OF THE INVESTIGATION.  (X)						2	L	7	2 	4F			RT	A16WE   					 
1997112000275	19971120	00275	EA  	1997	11	20	AU970062         	2	19970127	G	8520		CONNECTING ROD  			GULSTM	GA7   	GA7         	3960401	SO  	LYC   	O320  	O320D1D     	41508	EA  					NR 4 CYL	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							887939A			(AUS) NO4 CYLINDER CONNECTING ROD BROKEN IN AREA JUST BELOW PISTON PIN BOSS						1	L	7	2 	3O	3	O		A17SO   	E274				 
1997112000276	19971120	00276	EU  	1997	11	20	AU970063         	1	19970117	G	4920		COMPRESSOR      	GARRTT      	GTCP36300A  	AIRBUS	320   	A320212     		EU  										APU CORE ENGINE	FAILED          	W				K				NONE                    				E	T		VIBRATION/BUFFET          	ENGINE CASE PENETRATION   		NR	NOT REPORTED   	1			AU	S 			450  							(AUS) APU LOAD COMPRESSOR AND GEARBOX SEIZED - LOAD COMPRESSOR PROTRUDING THROUGH OUTER CASING						2	L	7	2 	4F			RT	A28NM   					 
1997112000277	19971120	00277	CE  	1997	11	20	AU970064         	1	19970123	G	5521	043200121	SPAR            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR SPAR CRACKED FROM UPPER OUTBOARD BENDING RADIUS CUTOUT INBOARD ALONG VERTICAL FACE OF SPAR PASSING ADJ	ACENT TO UPPER RIVET ATTACHING HINGE HALF PNO 0432001-71 - CRACK LENGTH38MM (1.49IN) - DURING REPAIR ANOTHER CRACK WAS F	OUND EXTENDING BELOW LOWER OUTBOARD RIVET ATTACHING TORQUE TUBE ASSEMBLY PNO 0434155-1 - CRACK LENGTH 20MM (0.78IN) - FA	IRY EXTENSIVE CORROSION WAS ALSO FOUND AS NO ANTI CORROSION TREATMENT HAD BEEN APPLIED DURING MANUFACTURE			1	H	7	1 	3O				3A19    		5	N	P50GL	 
1997112000278	19971120	00278	WP  	1997	11	20	AU970065         	2	19970131	G	7313	31029542	NOZZLE          	GARRTT      	TPE3318403S 	CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL INJECTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					NONE					(AUS) FUEL NOZZLE BODY LEAKING - INVESTIGATION FOUND TWO PIN HOLES IN THE BODY BASE - NOZZLES WERE A NEW ITEM						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
1997112000279	19971120	00279	SO  	1997	11	20	AU970066         	2	19970129	G	8520	1108414A	CRANKCASE       	CONT        	IO520A      						CONT  	O520  	IO520A      	17032	SO  					ENGINE NOSE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1108414A		1108414A			(AUS) THE FOLLOWING DEFECTS WERE FOUND DURING ENGINE STRIP FOR OVERHAUL 1. CRANKCASE CRACKED IN NOSE AREA ADJACENT TO TH	ROUGH STUDS 2. CRANKSHAFT CRACKED IN AREA AROUND FORWARD THRUST FACE3. STARTER SHAFT CRACKED4. OIL PUMP BODY AND GEARS W	ORN BEYOND LIMITS									3	O			E5CE				 
1997112000280	19971120	00280	CE  	1997	11	20	AU970067         	1	19970203	G	5720		BRACKET         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	TIP TANK ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING TIP TANK ATTACHMENT BRACKET CRACKED IN AREA OF TOP REAR RADIUS						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997112000281	19971120	00281	EU  	1997	11	20	AU970068         	1	19970203	G	2910	AS1005D080608	UNION           			FOKKER	F27   	F27MK50     		EU  										HYDRAULIC	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR RETRACTION SYSTEM HYDRAULIC LINE UNION LEAKING - LOSS OF HYDRAULIC FLUID						2	H	7	2 	4T			RT	A817    					 
1997112000282	19971120	00282	EA  	1997	11	20	AU970069         	2	19970117	G	7250	3013411	BLADE           			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE	DAMAGED         	W				K				NONE                    				O	C		OTHER                     	F.O.D.                    		IN	INSP/MAINT     	1			AU	S 			5074 		7E247		56820			(AUS) ALL COMPRESSOR TURBINE BLADES DAMAGED BY FOD - DAMAGE INCLUDED BENDING OF BLADE LEADING EDGES AND MISSING SECTIONS	 - INVESTIGATION FOUND FOD TO BE A POWER TURBINE CONTAINMENT RING RETAINING BOLT					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997112000283	19971120	00283	SO  	1997	11	20	AU970070         	2	19970206	G	7414	IO349237	GEAR            	BENDIX      	S6RN1205    	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	MAGNETO/DISTRIBU	MELTED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					932309					(AUS) LH ENGINE RH MAGNETO DISTRIBUTOR GEAR MELTED - HT CONTACT SEPARATED FROM GEAR - BEARING FAILED - LARGE PIECE OF SL	OW SPEED DISTRIBUTOR GEAR MISSING					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997112000284	19971120	00284	GL  	1997	11	20	AU970071         	3	19970206	G	6110		PROPELLER       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER ASSEMB	LOOSE           	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE PROPELLER LOOSE ON CRANKSHAFT - ALL SIX RETAINING NUTS WERE LOOSE - FOLLOWING REMOVAL OF PROPELLER ONE O	F TWO DOWELS WAS FOUND TO BE BROKEN - SUSPECT BOLTS WERE NOT TORQUED WHEN PROPELLER WAS REFITTED TWENTY THREE HOURS PREV	IOUSLY (DEC 1996) - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997112000285	19971120	00285	CE  	1997	11	20	AU970072         	1	19970120	G	2434	260000160	HOUSING         	PRESTOLITE  	ALV9402     	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DC GENERATOR-ALT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			167  		260000160		270623R			(AUS) ALTERNATOR MAIN BEARING COLLAPSED AND OUTER HOUSING CRACKED						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997112000286	19971120	00286	CE  	1997	11	20	AU970073         	1	19970203	G	5210	1144000271	FRAME           	BEECH       	1900C       	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					PASS/CREW DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) CABIN DOOR FRAME EXTENSIVELY CORRODED (RUSTED) AND BROKEN IN AREA ADJACENT TO THE DOOR HINGE - EXTENSIVE DEBONDING	 OF HONEYCOMB STRUCTURE					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997112000287	19971120	00287	SW  	1997	11	20	AU970074         	1	19970115	G	3213	54530011	CYLINDER        	SWRNGN      	MLG         	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NSN					(AUS) MAIN LANDING GEAR UPPER STRUT CYLINDER CRACKED - FOUND DURING INSPECTION IAW AD/SWSA226/78 (SB 226-32-033)						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
1997112000288	19971120	00288	CE  	1997	11	20	AU970075         	1	19970115	G	5741	951100162	FITTING         			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	RT SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					TE751					(AUS) REAR SPAR RH WING FITTING CORRODED - WING BOLT, NUT AND WASHER ALSO CORRODED - FOUND DURING INSPECTION IAW AD/BEEC	H55/79					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P5EA	 
1997112000289	19971120	00289	EA  	1997	11	20	AU970076         	2	19970210	G	7322	13662	BRACKET         		MA45        						LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FUEL CONT/CARB	CRACKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 					75049014		L34747344			(AUS) CARBURETTOR FLOAT BRACKET BROKEN AND SEPARATED - SEE MDR 96/0669AND MDR 96/1045 FOR SIMILAR DEFECTS											3	O			E286	5	C	P27EA	 
1997112000290	19971120	00290	GL  	1997	11	20	AU970077         	3	19970203	G	6111	A1588B	SPRING          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER BLADE	FAULTY          	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			AU	S 			1714 					ED2634		(AUS) PROPELLER LATCH SPRING KIT FOUND TO BE MADE UP OF SUPERCEEDED PARTS - FITTED AT LAST OVERHAUL IN USA - PERSONNEL/M	AINTENANCE ERROR					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1997112000291	19971120	00291	SO  	1997	11	20	AU970078         	2	19970113	G	8550	539523	BUSHING         	CONT        	OILPUMP     						CONT  	O520  	TSIO520M    	17040	SO  					OIL PUMP GEAR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							291531			(AUS) ENGINE OIL PUMP DRIVEN GEAR BRONZE BUSH BROKEN - AIRCRAFT IS REGISTERED IN PNG AS P2-MFV											3	O			E8CE				 
1997112000292	19971120	00292	SO  	1997	11	20	AU970079         	1	19970203	G	3040		WIPER ARM       			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WINDSHIELD	BIRD STRIKE     	W				K				NONE                    				C			F.O.D.                    			DE	DESCENT        	1			AU	S 										(AUS) AIRCRAFT SUFFERED BIRDSTRIKE - IMPACT DAMAGE ON NLG LEG AND IN AREA OF COPILOTS WINDSCREEN WIPER ARM ACTUATOR POST	 RESULTING IN MINOR BENDING OF THE WIPER ARM - NIL OTHER DAMAGE					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997112000293	19971120	00293	CE  	1997	11	20	AU970080         	1	19970204	G	3230	08411065	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	BROKEN          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LH MAIN LANDING GEAR RETRACTION BELLCRANK BROKEN - UNLOCK PUSH/PULL ROD PNO 0840142-1 BENT - LANDING GEAR RETRACTI	ON ROD PNO 0840125-15 INCORRECTLY INSTALLED ALLOWING FASTENER COLLAR TO INTERMITTENTLY CONTACT BOLT HEADS					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997112000294	19971120	00294	CE  	1997	11	20	AU970081         	1	19970130	G	3260	JE6	SWITCH          			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	MLG DOWNLOCK	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH LEAF SPRING BROKEN						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997112000295	19971120	00295	CE  	1997	11	20	AU970082         	1	19970203	G	3222	08410021	TORQUE LINK     			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	NOSE GEAR	STIFF           	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR TORQUE LINKS STIFF IN OPERATION DUE TO THE LOWER ATTACHMENT BOLT BEING OVERTORQUED - NOSE OLEO W	OULD NOT FULLY EXTEND CAUSING NLG TO FOUL ON GEAR DOORS -PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997112000296	19971120	00296	SO  	1997	11	20	AU970083         	1	19970109	G	2430	W110145724	WIRE            		W110470720  	EMB   	120   	EMB120RT    	3260202	SO  	PWA   	118   	PW118A      	 	NE  					DC GENERATING SY	WORN            	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) AUXILIARY GENERATOR WIRES PNO W110-4707-20 AND PNO W110-1457-24 CHAFED IN THE AREA OF THE AIR DATA COMPUTER NO3 CO	NNECTOR - SEE MDR 97/0020 FOR FURTHER INFORMATION					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997112000297	19971120	00297	SO  	1997	11	20	AU970084         	2	19970203	G	8530	646267CA4	CYLINDER        	CONT        	O470U       	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	RECIP ENG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					466249		466249			(AUS) ENGINE CYLINDER BORES EXCESSIVELY WORN IN TOP AND BOTTOM AREAS OF THE CYLINDER. PISTON RING CAUGHT IN WORN GROOVE 	CAUSING IT TO BREAK. ENGINE HAS CHROMED CYLINDERS INSTALLED AND IT IS SUSPECTED THAT THE ENGINE WAS OPERATING WITHOUT AD	EQUATE LUBRICATION.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997112000298	19971120	00298	NM  	1997	11	20	AU970085         	1	19970204	G	2530		OVEN            			BOEING	737   	737376      		NM  										BUFFET/GALLEYS	FAILED          	W				K				NONE                    				O	B		OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 										(AUS) OVEN INSERT JAMMED AGAINST FAN. INVESTIGATION FOUND THAT THE LOCATING PEGS WERE MISALIGNED AND NOT LOCATING IN REC	EPTACLES.THE FOOD OVERHEATED CAUSING SMOKE. PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4F			RT	A16WE   					 
1997112000299	19971120	00299	CE  	1997	11	20	AU970086         	1	19970207	G	5753	052390138	FLAP            			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	TE FLAP STRUCTUR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FLAP DISTORTED - FLAP HAD A BUILT IN CHORDWISE TWIST OFAPPROXIMATELY 2.5 DEGREES - FLAP HAD BEEN DAMAGED AND RE	PAIRED ON 23/7/68 - FLAP HAD WORN FLAP TRACKS AND FLAP CONDITION WAS FOUND WHEN THE TRACKS WERE REPLACED WITH NEW ITEMS 	- INBOARD LOWER FLAP TRACK ATTACHMENT BRACKETS ALSO CRACKED - PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997112000300	19971120	00300	SO  	1997	11	20	AU970087         	1	19970202	G	2410	76026	DRIVE BELT      			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ALTERNATOR	WRONG PART      	W				K				NONE                    				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		TO	TAKEOFF        	1			AU	S 							L598348	CH11551		(AUS) ALTERNATOR DRIVE BELT STRETCHED AND SLIPPING - INVESTIGATION FOUND THAT THE DRIVE BELT FITTED WAS IN FACT AN AUTOM	OTIVE PART (BOSCH 13A0965 FOR FITMENT TO TOYOTA MOTOR VEHICLES) AND NOTAPPROVED FOR FITMENT TO AIRCRAFT - PULLEY PNO 775	79 WAS EXCESSIVELY WORN IN THE GROOVE - PERSONNEL/MAINTENANCE ERROR -UNAPPROVED PART				1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997112000301	19971120	00301	SO  	1997	11	20	AU970088         	1	19970201	G	5753	110262192	SUPPORT         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP STRUCTUR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLAP SUPPORT ASSEMBLY CRACKED - FOUND DURING INSPECTION IAWOSIP 2706 - SUSPECT ORIGINAL FITMENT PNO 4A-2621-4	6					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997112000302	19971120	00302		1997	11	20	AU970089         	4	19970122	G	2562	MN1300	BATTERY         		E01         	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ELT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					013487					(AUS) ELT BATTERY LEAKING - AIRCRAFT OPERATES IN THE TROPICS - SEE MDR96/2008 FOR SIMILAR DEFECT						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997112000303	19971120	00303	EU  	1997	11	20	AU970090         	1	19970209	G	2436	NB813485	REGULATOR       			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	DC VOLTAGE	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) RH ALTERNATOR VOLTAGE REGULATOR BURNT OUT DUE TO FAILURE OF THE DRIVER TRANSISTOR IN THE ALTERNATOR FIELD WINDING						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1997112000304	19971120	00304	CE  	1997	11	20	AU970091         	1	19970214	G	5210	1013840961	HANDLE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PASS/CREW DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR HANDLE BROKEN IN AREA AROUND BEARING HOUSING - HANDLE THEN SEPARATED FROM SQUARE SHAFT.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997112000305	19971120	00305	GL  	1997	11	20	AU970092         	3	19970214	G	6111	83023	LATCH           			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2958 					BV3932		(AUS) PROPELLER STARTING LATCH CRACKED						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997112000306	19971120	00306	GL  	1997	11	20	AU970093         	3	19970207	G	6110		SEAL            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	PROP BLADE NUT	PINCHED         	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			AU	S 								736004		(AUS) PROPELLER BLADE NUT SEALS PINCHED GIVING INEFFECTIVE SEALING -SEALING WAS ACHIEVED BY THE USE OF SILASTIC SEALANT 	BETWEEN THE BLADE NUT THREADS AND HUB AND LOCK RING ASSEMBLY - INCORRECT ASSEMBLY - PERSONNEL/MAINTENANCE ERROR - PROPEL	LER HAD BEEN MODIFIED TO OIL FILLED CONFIGURATION				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997112000307	19971120	00307	GL  	1997	11	20	AU970094         	3	19970214	G	6112	4E1614	SLIP RING       			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER DE-ICE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3011 					BV4305		(AUS) PROPELLER SLIP RING SEPARATING FROM DE-ICE PLATTER - SUSPECT NONAPPROVED REPAIR CARRIED OUT						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997112000308	19971120	00308	SW  	1997	11	20	AU970095         	1	19970211	G	2612	1734361450	DETECTOR        			GULSTM	690TP 	695B        	3970610	SW  						ROTOL	R306	R306382F7   	GL  	RT ENG DET SYS	FAULTY          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) RH ENGINE FIRE DETECTORS SUSPECT FAULTY - DETECTORS WERE CHECKEDSATISFACTORY - SUSPECT RH ENGINE EXHAUST SEAL PNO 	610652-69 MAY HAVE BEEN LEAKING CAUSING HOT AIR TO BE DIRECTED ONTO FIRE DETECTORS - ALTHOUGH THERE WAS NO EVIDENCE OF L	EAKAGE THE SEAL WAS REPLACED				1	H	7	2 	4T			RT	2A4     		6	C	P8EU	 
1997112000309	19971120	00309	EU  	1997	11	20	AU970096         	2	19970130	G	7310	8151GAF	DRAIN VALVE     	RROYCE      	FILTERCOVER 	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					ENGINE FUEL DIST	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 			580  				9286			(AUS) LH ENGINE LP FUEL FILTER DRAIN VALVE LEAKING FROM FLANGE AREA						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997112000310	19971120	00310	EU  	1997	11	20	AU970097         	1	19970126	G	5313	27	STRINGER        			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 40 STRINGER 27 RHS CRACKED - FOUND DURING HIGH FREQUENCY EDDY CURRENT INSPECTION IAW SB A300-53-031	0					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1997112000311	19971120	00311	NM  	1997	11	20	AU970098         	1	19970103	G	5311	A0202	FRAME           			ROBSIN	R22   	R22MARINER  		NM  	LYC   	O320  	O320B2C     	41508	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			888  		2346					(AUS) FUSELAGE UPPER FRAME CRACKED IN AREA UNDER MAIN GEARBOX MOUNT PADS AS REFERRED IN AD/R22/41 AMDT1						1	G	7	1 	3O	3	O		H10WE   	E274				 
1997112000312	19971120	00312	SO  	1997	11	20	AU970099         	1	19970213	G	2912	MS28775217	O-RING          	PUROLATOR   	PR301       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					HYDRAULIC FILTER	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC SYSTEM PUROLATOR FILTER `O' RING SEAL FAULTY - OIL LEAKING - NOSE WHEEL FAILED TO EXTEND - DAMAGE TO FOR	WARD FUSELAGE AND PROPELLERS					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997112000313	19971120	00313	CE  	1997	11	20	AU970100         	1	19970122	G	2730	26340171	TORQUE TUBE     			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					ELEVATOR CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR ASSEMBLY TORQUE TUBE CRACKED LONGITUDINALLY THROUGH RIVET HOLE 60MM (2.36IN) FROM INBOARD END - CORROS	ION FOUND BETWEEN TUBE AND END FITTING WHICH CAUSED THE TUBE TO EXPAND AND CRACK - SUSPECT INADEQUATE TREATMENT DURING A	SSEMBLY - AIRCRAFT OPERATES AS A FLOAT PLANE IN A SALT LADEN ENVIRONMENT				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
1997112000314	19971120	00314	SO  	1997	11	20	AU970101         	2	19970119	G	7314	6328183	PUMP            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE FUEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L238102RB		604094			(AUS) LH ENGINE DRIVEN FUEL PUMP INTERNAL FAILURE - INVESTIGATION BY OVERHAUL SHOP COULD FIND NO FAULTS						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997112000315	19971120	00315	CE  	1997	11	20	AU970102         	1	19970115	G	2510		SEAT BELT       			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A2B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	FLIGHT COMPART	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AUTOMOTIVE WEBBING AND HARDWARE USED FOR SEAT BELTS - UNAPPROVEDPART - PERSONNEL/MAINTENANCE ERROR						1	L	7	1 	3O	3	O		A1CE    	1E10	5	C	P7EA	 
1997112000316	19971120	00316		1997	11	20	AU970103         	4	19970123	G	2397	22GAWIRE	WIRE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	HF COMMUNICATION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HF INSTALLATION SUSPECT FAULTY - INSUFFICIENT PROTECTION OF 22GAWIRE CONNECTING THE LAMP TO THE 15AMP CIRCUIT BREA	KER - IF THE22GA WIRE SHORT CIRCUITS TO THE AIRFRAME IT IS SUSPECTED THAT THE 15AMP CIRCUIT BREAKER WOULD NOT TRIP ALLOW	ING THE WIRE TO THEN BURN/OVERHEAT - AIRCRAFT WAS PREVIOUSLY REGISTERED AS VH-RFX				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
1997112000317	19971120	00317	SO  	1997	11	20	AU970104         	1	19970122	G	2510		SEAT BELT       			PIPER 	PA22  	PA22108     	7102204	SO  	LYC   	O235  	O235C1B     	41505	EA  	SNSNCH	76AM	M76AM       	EA  	FLIGHT COMPART	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NON-APPROVED HARDWARE AND WEBBING USED IN SEAT BELTS - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O		1A6     	E223	5	N	1P210	 
1997112000318	19971120	00318	CE  	1997	11	20	AU970105         	1	19970121	G	3234	99102251	SELECTOR VALVE  			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					GEAR SELECTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					737					(AUS) LANDING GEAR SELECTOR VALVE FAULTY - REPAIRED ITEM HAD BEEN FITTED BEFORE THE PREVIOUS FLIGHT - THE VALVE WAS AGAI	N RETURNEDTO THE OVERHAUL FACILITY - THE VALVE COULD NOT BE FAULTED INITIALLY BUT AFTER REPEATED TESTING THE VALVE FAILE	D - SUSPECT FAULTY SOLENOID OR HIGH HOURS - SEE MDR 96/1940 FOR FURTHER INFORMATION				1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1997112000319	19971120	00319	CE  	1997	11	20	AU970106         	1	19970130	G	2450		CIRCUIT BREAKER 			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ2Y	BHCJ2YF2    	GL  	AC POWER DISTRIB	MISWIRED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TRANSPONDER SYSTEM WIRED TO PRIMARY AH CIRCUIT BREAKER FOLLOWING FAILURE OF CORRECT CB WHICH HAD BEEN DISCONNECTED	 - CIRCUIT BREAKER MARKED `RADAR' WAS REALLY THE COMPASS SYSTEM (COMPASS SYSTEM CB WAS FOUR CIRCUIT BREAKERS AWAY) - HF 	CIRCUIT BREAKER NOT MARKED - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P37EA	 
1997112000320	19971120	00320	EU  	1997	11	20	AU970107         	1	19970218	G	3213	TB1041033000	TORQUE LINK     			SOCATA	TB9   	TB9         	8680694	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR LOWER TORQUE LINK FAILED AT LOWER ATTACHMENT HOLES						1	L	7	1 	3O	3	O	NT	AS1EU   	E274	5	N	P88614	 
1997112000321	19971120	00321	EU  	1997	11	20	AU970108         	1	19970208	G	2720		CONTROL CABLE   			BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RUDDER CONTROLS	MISROUTED       	W				O				OTHER                   				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		NR	NOT REPORTED   	1			AU	S 										(AUS) RUDDER PEDAL ADJUSTMENT CABLE INCORRECTLY ROUTED - CABLE ROUTED BELOW THE CONTROL COLUMN ELECTRICAL CORD INSTEAD O	F ABOVE IT -THIS CAUSED THE CABLE TO SNAG ON THE ELECTRICAL CORD AND JAM THE CONTROL COLUMN IN THE FULL AFT POSITION - P	ERSONNEL/MAINTENANCE ERROR				1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
1997112000322	19971120	00322	EA  	1997	11	20	AU970109         	2	19970129	G	8520	69796	DOWEL           	LYC         	O540B2C5    	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	ENG RT CASE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L1341740		L1341740			(AUS) RH CRANKCASE NO3 DOWEL SHEARED ALLOWING MOVEMENT OF THE MAINBEARINGS - WEAR ALSO TO CRANKCASE TUNNEL AND SCORING O	F THE CRANKCASE JOURNAL - DOWEL WAS SUPERCEDED (STEPPED) TYPE					1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1997112000323	19971120	00323	EA  	1997	11	20	AU970110         	2	19970129	G	8530	SL75089	PISTON          	SUPAIRPART  	SL36000NA20 	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	CYLS 1- 3- 5	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					131132036		L1341740			(AUS) NO1, NO3 AND NO5 PISTONS CRACKED IN AREA OF SKIRT OPPOSITE TO THE PISTON PIN BOSS - NO1, N3 AND NO5 INDUCTION TUBE	S FOUND LOOSE ALLOWING UNMETERED AIR INTO ENGINE CAUSING SUSPECTED LEAN MIXTURE - NO5 CYLINDER SPARK PLUGS IN POOR CONDI	TION - PISTONS ARE HIGH COMPRESSION TYPE - ENGINE RUNS ON MOGAS				1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1997112000324	19971120	00324	NE  	1997	11	20	AU970111         	2	19970216	G	7250	785259	TURBINE         	GE          	CT79B       	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	ENGINE	DAMAGED         	W				K				NONE                    				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			9583 		785259		785259			(AUS) RH ENGINE HOT SECTION AND POWER TURBINE MODULES DAMAGED - HOT SECTION 1. 2ND STAGE TURBINE FORWARD COOLING PLATE D	AMAGED2. 1ST AND 2ND STAGE TURBINE NOZZLES AND ROTOR DAMAGED POWER TURBINE SECTION 1. 3RD AND 4TH STAGE TURBINE NOZZLES 	AND ROTOR DAMAGED2. POSSIBLE HEAT DAMAGE TO INLET GUIDE VANES				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997120400001	19971204	00001	SO  	1997	12	4	AU970112         	1	19970129	G	7922	75944	NUT             		VERNATHERM  	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	OIL TEMP VALVE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1341740			(AUS) THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) NUT LOOSE						1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1997120400002	19971204	00002	EU  	1997	12	4	AU970113         	1	19970215	G	3260	AIR130902	CONNECTOR       			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	GEAR POS SWITCH	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH CONNECTOR INCORRECTLY TIGHTENED DURING MAINTENANCE APPROXIMATELY 160 HOU	RS PREVIOUS - PLUG LOOSENED DUE TO VIBRATION GIVING INTERMITTENT OPERATION -PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997120400003	19971204	00003	EA  	1997	12	4	AU970114         	2	19970129	G	8520	72877	TAPPET          	LYC         	CAMSHAFT    	PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	CAM NR 5 LOBE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1341740			(AUS) CAMSHAFT NO5 LOBE AND ASSOCIATED TAPPET BODIES (2OFF) SEVERELY SPALLED						1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1997120400004	19971204	00004	CE  	1997	12	4	AU970115         	1	19970219	G	3610	67184	GASKET          	LEAR        	31A         	LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE73123B   		WP  					ENGINE BLEED AIR	FAILED          	W		A		K				NONE                    				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			AU	S 							P99223			(AUS) ENGINE TO PYLON BLEED AIR DUCT GASKET BLOWN OUT AND TWO DUCT SECURING NUTS MISSING (BOLTS INTACT) - SUSPECT BOLTS 	NOT TORQUED DURING ENGINE INSTALLATION - PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
1997120400005	19971204	00005	NE  	1997	12	4	AU970116         	2	19970213	G	7510	44E202A	FILTER          			EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	ENGINE ANTI-ICE	CRACKED         	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					RF2084					(AUS) LH ENGINE DE-ICE SYSTEM AIR LINE WATER FILTER HOUSING CRACKED						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1997120400006	19971204	00006	SO  	1997	12	4	AU970117         	2	19970215	G	8520	646778	CONNECTING ROD  	CONT        	O470U       	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 1 CYL	FAILED          	W				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	TO	TAKEOFF        	1			AU	S 			434  		809808R		809808R			(AUS) CONNECTING ROD END CAP SEPARATED - PRELIMINARY INVESTIGATION INDICATES FAILURE IN AREA APPROXIMATELY 10MM (0.393IN	) ABOVE THE BOLT SHOULDER ON THE CAMSHAFT SIDE BEHIND THE HARD FACE FOR THE BEARING SHELL PROGRESSING OUTWARDS UNTIL FAI	LURE FROM OVERLOAD -CRANKCASE HOLED IN AREA OF NO1 CYLINDER PUSHROD TUBE FITMENT				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997120400007	19971204	00007	NM  	1997	12	4	AU970118         	1	19970205	G	2161	6529346	CONTROLLER      			BOEING	757   	757200      	1384950	NM  										CABIN TEMPERATUR	FAULTY          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) AIR CONDITIONING SYSTEM ZONE TEMPERATURE CONTROLLER SUSPECT FAULTY						2	L	7	2 	4F			RT	A2NM    					 
1997120400008	19971204	00008	NM  	1997	12	4	AU970119         	1	19970212	G	2612	D02860	TUBE            		285NOO2821  	BOEING	757   	757200      	1384950	NM  										FIRE DETECTION	SEPARATED       	W				K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 					D02860					(AUS) CARGO AREA FIRE WARNING SYSTEM PRINTED CIRCUIT BOARD SUSPECT FAULTY - INVESTIGATION FOUND FAULT CAUSED BY DISCONNE	CTED DETECTOR TUBE					2	L	7	2 	4F			RT	A2NM    					 
1997120400009	19971204	00009	WP  	1997	12	4	AU970120         	1	19970219	G	6410	369A1613507	BLADE           			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			341  		BLADE0022228					(AUS) TAIL ROTOR BLADE SKIN CRACKED IN AREA INBOARD OF THE LEADING EDGE PROTECTION STRIP RUNNING CHORDWISE FROM THE LEAD	ING EDGE TOWARDS THE TRAILING EDGE - CRACK LENGTH APPROXIMATELY 25.4MM (1IN)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997120400010	19971204	00010	CE  	1997	12	4	AU970121         	1	19970117	G	3242	101800213	BRAKE DISC      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					BRAKE	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LH OUTBOARD BRAKE ROTATING DISC BROKEN - ONE SEGMENT CRACKED AND FELL OUT CAUSING MINOR DAMAGE TO WHEEL						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997120400011	19971204	00011	CE  	1997	12	4	AU970122         	1	19970128	G	3242	101800213	BRAKE DISC      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RT OUTBRD	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RH OUTBOARD BRAKE DISC BROKEN - BROKEN PIECE OF DISC DAMAGED WHEEL ASSEMBLY AND BRAKE BACKPLATE - WHEEL JAMMED						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997120400012	19971204	00012	SO  	1997	12	4	AU970123         	1	19970211	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR POS	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LH MAIN LANDING GEAR SQUAT SWITCH FAULTY						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997120400013	19971204	00013	CE  	1997	12	4	AU970124         	1	19970216	G	3231		NUT             	CESSNA      	210L        	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LANDING GEAR DOO	LOOSE           	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							294762R			(AUS) NOSE LANDING GEAR DOOR ACTUATING ROD JAM NUTS NOT TIGHTENED - PERSONNEL/MAINTENANCE ERROR						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997120400014	19971204	00014	SO  	1997	12	4	AU970125         	2	19970213	G	7314	631683	DRIVE SHAFT     	CONT        	FUELPUMP    	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	ENGINE FUEL PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					D117002B		567450			(AUS) ENGINE DRIVEN FUEL PUMP DRIVE SHAFT WORN - DRIVE SHAFT ROUNDED -FEMALE END IN PUMP ALSO WORN						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997120400015	19971204	00015	EU  	1997	12	4	AU970126         	1	19970127	G	6420	1090130059	PITCH LINK      	AGUSTA      	A109C       	AGUSTA	A109  	A109C       	0260118	EU  										TAIL ROTOR HEAD	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR PITCH LINK BEARINGS NOT STAKED - BEARINGS MOVING IN LINKS AND ONE BEARING DISLODGED - PITCH LINKS HAD B	EEN FITTED NEW A WEEK EARLIER - PERSONNEL/MAINTENANCE ERROR					1	G	7	2 	3U				H7EU    					 
1997120400016	19971204	00016	CE  	1997	12	4	AU970127         	1	19970218	G	2460		CONNECTOR       			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	DC POWER DISTRIB	CORRODED        	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) MAIN ALTERNATOR CABLE TO CURRENT LIMITER AND CURRENT LIMITER TO SHUNT AND MAIN AIRCRAFT DC BUSS CONNECTIONS CORROD	ED					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1997120400017	19971204	00017	CE  	1997	12	4	AU970128         	1	19970205	G	5610	10138402516	WINDSHIELD      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FLIGHT COMPART	CRACKED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) CO-PILOTS WINDSHIELD OUTER LAMINATION CRACKED IN TOP RH CORNER -WINDSHIELD WAS DELAMINATING PRIOR TO CRACKING (THE	 DELAMINATION WAS WITHIN MANUFACTURERS LIMITS)					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997120400018	19971204	00018	EU  	1997	12	4	AU970129         	1	19970214	G	2752	9787320302	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  										TE FLAP ACTUATOR	NOISY           	W				K				NONE                    				O	E		OTHER                     	VIBRATION/BUFFET          		IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP ACTUATOR NOISY - FLAP SHUDDERING ON EXTENSION						1	L	7	1 	3T			RT	A78EU   					 
1997120400019	19971204	00019	GL  	1997	12	4	AU970130         	3	19970218	G	6114	C88	HUB             			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	NR 2 SOCKET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			945  					775046		(AUS) PROPELLER HUB CRACKED IN NO2 BLADE SOCKET AREA - CRACK LENGTH APPROXIMATELY 6.35MM (0.25IN) - FOUND DURING INSPECT	ION IAW AD/PMC/41 FOLLOWING WIRE STRIKE					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997120400020	19971204	00020	CE  	1997	12	4	AU970131         	1	19970204	G	3260	513771	SWITCH          	CESSNA      	210L        	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LANDING GEAR POS	STUCK           	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					61553					(AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH STICKING DUE TO DIRT AND OIL CONTAMINATION						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997120800001	19971208	00001	NM  	1997	12	8	AU970132         	1	19970121	G	2410	729490	CSD             		729490      	BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					NR 1 ENG	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			12469		A0348					(AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) FAULTY - CSD FAILED TO DISCONNECT - EVIDENCE OF OVERHEATING - STRIP REPORT I	NDICATES OUTPUT SPUR GEAR ACCESSORY GEAR FAILURE					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1997120400021	19971204	00021		1997	12	4	AU970133         	4	19970216	G	2210	7690001808103	GYRO            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					AUTOPILOT SYSTEM	INOPERATIVE     	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 					306723306739					(AUS) BOTH YAW RATE GYROS FAULTY						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1997120400022	19971204	00022	NM  	1997	12	4	AU970134         	1	19970101	G	3510		OXYGEN SYSTEM   			BOEING	747   	747312      	1384932	NM  										CREW OXYGEN SYST	DEPLETED        	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) FLIGHT CREW OXYGEN SYSTEM PRESSURE DEPLETED. SUSPECT CREW REGULATOR LEFT IN `100% ON' POSITION						2	L	7	4 	4F			RT	A20WE   					 
1997120400023	19971204	00023	CE  	1997	12	4	AU970135         	1	19970103	G	2910	61510	VALVE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HYDRAULIC, MAIN	SEIZED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC OPEN CENTRE BYPASS VALVE INTERNAL FAULT - VALVE INTERMITTENTLY SEIZED IN THE OPEN POSITION						1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997120400024	19971204	00024	SO  	1997	12	4	AU970136         	1	19970210	G	2910		HYDRAULIC SYSTEM			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYDRAULIC, MAIN	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC SYSTEM CONTAMINATED WITH AIR						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997120800002	19971208	00002	EU  	1997	12	8	AU970137         	1	19970223	G	2611	72111211000	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	SMOKE DETECTION	MALFUNCTION     	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 					A4607					(AUS) CARGO BAY SMOKE DETECTOR ILLUMINATED WARNING LIGHT - CARGO COMPARTMENT EXTINGUISHER FIRED - CHECK OF COMPARTMENT C	OULD FIND NO EVIDENCE OF SMOKE OR FIRE - SUSPECT CAUSED BY HIGH HUMIDITY					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997120800003	19971208	00003	GL  	1997	12	8	AU970138         	3	19970212	G	6111	B24231	CYLINDER        			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	PROPELLER BLADE	SLUDGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2000 					CK1594		(AUS) PROPELLER CYLINDER SLUDGED RESTRICTING OPERATION						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
1997120400025	19971204	00025	CE  	1997	12	4	AU970139         	1	19970221	G	7110		COWLING         			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE COWLINGS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							321072R	715070		(AUS) UNSECURED AND UNATTACHED UPPER AND LOWER ENGINE COWLINGS PICKED UP BY A GUST OF WIND AND BLOWN INTO PROPELLER ARC 	DURING ENGINE GROUND RUN - DAMAGE TO PROPELLER BLADES AND DESTRUCTION OF COWLS- ENGINE BULK STRIP TO BE CARRIED OUT					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997120400026	19971204	00026	SO  	1997	12	4	AU970140         	1	19970127	G	3233	3579705	ACTUATOR        			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LANDING GEAR ACT	FAILED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			3350 							(AUS) NOSE LANDING GEAR HYDRAULIC ACTUATOR FAILED AT FUSELAGE ATTACHMENT POINT						1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920	 
1997120400027	19971204	00027	WP  	1997	12	4	AU970141         	2	19970106	G	7310	C1A	FILTER          			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ENGINE FUEL DIST	WORN            	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					35D2266		23			(AUS) AIRCRAFT FUEL TANK FLOAT DETERIORATED ALLOWING FLOAT PARTICLES TO ENTER AND BLOCK CARBURETTOR MAIN JET - FUEL FILT	ER WORN PREVENTING FILTER FROM BLOCKING CONTAMINATION					1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1997120400028	19971204	00028	SO  	1997	12	4	AU970142         	2	19970116	G	8520	836752R	CRANKCASE       	CONT        	O470        						CONT  	O470  	O470*       	17026	SO  					NR 2 MAIN SUPPRT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					836752R		836752R			(AUS) CRANKCASE NO2 MAIN BEARING SUPPORT CRACKED - EVIDENCE OF MAIN BEARING SADDLE FRETTING - FOUND DURING BULK STRIP FO	LLOWING PROPELLER STRIKE										3	O			E273				 
1997120400029	19971204	00029	NM  	1997	12	4	AU970143         	1	19970218	G	2760	PREPRELCC5141	LINK            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					DRAG CONTROL SYS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH OUTBOARD ROLL SPOILER LINK ASSEMBLY LOOSE BETWEEN ROD AND RODEND AT BOTH ENDS						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997120400030	19971204	00030		1997	12	4	AU970144         	1	19970209	G	7603		CABLE           								ROTAX 	912   	ROTAX912    	55555	EU  					POWER LEVER	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							4076069			(AUS) LH THROTTLE CABLE BROKEN AT CARBURETTOR ATTACHMENT PIVOT - CABLE WAS FLEXING DUE TO STIFF PIVOT											3	I			EXPE3I				 
1997120400031	19971204	00031	EU  	1997	12	4	AU970145         	1	19970206	G	6210	355A11002011	BLADE           			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					MAIN ROTOR BLADE	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE INBOARD TRIM TAB DEBONDED AND LOOSE ON BLADE						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1997120400032	19971204	00032	SO  	1997	12	4	AU970146         	1	19970219	G	7830	1159SCP4253	CONTROL VALVE   	PNEUDRAULICS	CONTROL     	GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     		EU  					THRUST REVERSER	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			986  		205					(AUS) RH ENGINE THRUST REVERSER CONTROL VALVE FAULTY						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
1997120400033	19971204	00033	NM  	1997	12	4	AU970147         	1	19970213	G	3246	2605759A	WHEEL           	BENDIX      	WHEEL       	BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					WHEEL/SKI/FLOAT	FRACTURED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 			387  		ASSYHALFH015					(AUS) NO4 MAIN WHEEL CENTRE HUB FAILED. DAMAGE TO BRAKE AND WHEEL BEARING. FUSE PLUG MELTED AND TYRE DEFLATED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997120400034	19971204	00034	NM  	1997	12	4	AU970148         	1	19970208	G	2752	3947	SCREWJACK       			BOEING	737   	737476      		NM  										TE FLAP ACTUATOR	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 					3947					(AUS) NO2 TRAILING EDGE FLAP SCREWJACK WORN CAUSING THE FLAP BALLNUT ASSEMBLY TO JAM THE SCREWJACK						2	L	7	2 	4F			RT	A16WE   					 
1997120400035	19971204	00035	NM  	1997	12	4	AU970149         	1	19970210	G	2761	4554	ACTUATOR        			BOEING	737   	737376      		NM  										DRAG CONTROL ACT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4554					(AUS) NO5 GROUND SPOILER OUTBOARD ACTUATOR LOWER ATTACHMENT FITTING BROKEN - SUSPECT CAUSED BY CORROSION PITTING OF ALUM	INIUM HOUSING					2	L	7	2 	4F			RT	A16WE   					 
1997120400036	19971204	00036	SW  	1997	12	4	AU970150         	1	19970101	G	2435	150SG117Q	STARTER GEN     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER-GENERATO	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			584  		13956					(AUS) STARTER/GENERATOR HAD EXCESSIVE ARMATURE BALANCE BAND GRINDING TO ACHIEVE BALANCE - PERSONNEL/MAINTENANCE ERROR - 	UNAPPROVED REPAIR					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997120400037	19971204	00037	EA  	1997	12	4	AU970151         	2	19970224	G	8520	L4251627A	CAMSHAFT        	LYC         	O320A2B     						LYC   	O320  	O320A2B     	41508	EA  					RECIP ENG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L4251627A		L4251627A			(AUS) ENGINE CAMSHAFT CAM LOBES WORN BEYOND LIMITS - ALL CYLINDERS AND ASSOCIATED PARTS UNSERVICEABLE											3	O			E274				 
1997120400038	19971204	00038	EA  	1997	12	4	AU970152         	2	19970224	G	8520		CAMSHAFT        	LYC         	IO540K1B5   						LYC   	O540  	IO540K1B5   	41532	EA  					RECIP ENG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							IO540KIB5			(AUS) ENGINE CAMSHAFT LOBES WORN - COUNTERWEIGHT BUSHES OUT OF LIMITS											3	O			1E4				 
1997120400039	19971204	00039	EA  	1997	12	4	AU970153         	2	19970224	G	8520	L3398327A	CRANKCASE       	LYC         	O320E2D     						LYC   	O320  	O320E2D     	41508	EA  					RECIP ENG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L3398327A		L3398327A			(AUS) CRANKCASE SADDLES FRETTING											3	O			E274				 
1997120400040	19971204	00040	EU  	1997	12	4	AU970154         	1	19970226	G	2910	SA767006155	HOSE            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYDRAULIC, MAIN	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) GREEN SYSTEM HYDRAULIC PRESSURE HOSE CHAFING ON COWLING DOOR- LOSS OF HYDRAULIC FLUID						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997120400041	19971204	00041	NM  	1997	12	4	AU970155         	1	19970227	G	5753	113T13698	BRACKET         			BOEING	767   	76733A      		NM  	PWA   	4056  	PW4056      		NE  					TE FLAP STRUCTUR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4964 							(AUS) RH WING OUTBOARD FLAP DEFLECTION CONTROL TRACK FITTING CRACKED ON LH AND RH SIDES - SLIGHT DAMAGE TO RH WING CLOSE	-OUT PANEL					2	L	7	2 	RT	4	F	RT	A1NM    	E24NE				 
1997120400042	19971204	00042	CE  	1997	12	4	AU970156         	1	19970206	G	5521	07341023	ADAPTER         			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	ELEV SPAR/RIB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ELEVATOR TORQUE TUBE ADAPTERS CONTAINED SEVERE CORROSION BETWEEN ADAPTERS AND INBOARD RIBS - FLANGES ON 	ADAPTERS CRACKED DUE TO CORROSION					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997120400043	19971204	00043	CE  	1997	12	4	AU970157         	1	19970124	G	3230		DOWNLOCK        	CESSNA      	210L        	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	GEAR RETRACT	CONTAMINATED    	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 					NSN					(AUS) LH MAIN LANDING GEAR DOWNLOCK HOOK CONTAMINATED WITH DIRT AND GRIT - AIRCRAFT OPERATES FROM DIRT STRIPS						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997120400044	19971204	00044	SO  	1997	12	4	AU970158         	2	19970215	G	8520	574572	CONNECTING ROD  	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RECIP ENG	BROKEN          	W				K				NONE                    				E	K	R	VIBRATION/BUFFET          	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	CL	CLIMB          	1			AU	S 			326  		574572		574572	930788		(AUS) ENGINE NO5 CYLINDER CONNECTING ROD BIG END BEARING FAILED DUE TO LACK OF LUBRICATION/COOLING CAUSED BY LOSS OF OIL	 OVERBOARD - LOSS OF OIL WAS THROUGH A WORN AND HOLED EXHAUST PUSHROD TUBE CAUSED BY A BENT PUSHROD,  DUE TO STICKING VA	LVE - CONNECTING ROD BROKEN - CRANKCASE HOLED				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
1997120400045	19971204	00045	SO  	1997	12	4	AU970160         	1	19970130	G	2460		CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					DC POWER/DISTRIB	CONTAMINATED    	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) RH AUXILIARY GENERATOR ELECTRICAL PLUG CONTAMINATED WITH WATER						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997120400046	19971204	00046	CE  	1997	12	4	AU970161         	1	19970219	G	2432		BATTERY         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BATTERY/CHARGER	MALFUNCTION     	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) BATTERY CHARGE LIGHT ILLUMINATED - BATTERY REMOVED TO BATTERY SHOP - INVESTIGATION COULD FIND NO FAULTS WITH THE B	ATTERY					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997120400047	19971204	00047	SO  	1997	12	4	AU970162         	1	19970218	G	5270		WARNING SYSTEM  			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	DOOR WARNING SYS	MALFUNCTION     	W				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) CARGO DOOR WARNING ILLUMINATED - INVESTIGATION FOUND DOOR CLOSEDAND WARNING SYSTEM SERVICEABLE - DEFECT NOT CONFIR	MED					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1997120400048	19971204	00048	WP  	1997	12	4	AU970163         	1	19970219	G	6410	369A1613507	BLADE           			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			341  		BLADE0022228					(AUS) TAIL ROTOR BLADE SKIN CRACKED IN AREA JUST INBOARD OF THE LEADING EDGE PROTECTIVE STRIP RUNNING CHORDWISE TOWARDS 	THE TRAILING EDGE - CRACK LENGTH APPROXIMATELY 25.4MM (1IN)					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1997120400049	19971204	00049	SO  	1997	12	4	AU970164         	1	19970210	G	2897		WIRE            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ACFT FUEL INDICA	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FUEL TANK CAPACITANCE PROBE WIRES CHAFING ON FUEL PLUMBING IN THREE DIFFERENT AREAS						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1997120400050	19971204	00050	EU  	1997	12	4	AU970165         	1	19970220	G	3213	TB1041033000	TORQUE LINK     			SOCATA	TB9   	TB9         	8680694	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	LT MLG LOWER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR LOWER TORQUE LINK BROKEN AT INBOARD ATTACHMENT LUG - OUTBOARD LUG CONTAINS A HAIR LINE CRACK 	- RH MLG TORQUE LINK CONTAINS SOME PITTING IN THE ATTACHMENT LUG HOLES					1	L	7	1 	3O	3	O	NT	AS1EU   	E274	5	N	P88614	 
1997120400051	19971204	00051		1997	12	4	AU970166         	4	19970204	G	2210	308503	SWITCH          			BOEING	737   	737377      		NM  										AUTOPILOT SYSTEM	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) RUDDER TRIM SWITCH FAULTY - INVESTIGATION FOUND CONTAMINATION BETWEEN THE SWITCH KNOB AND THE LIGHT PLATE CAUSING 	THE SWITCH TO STICK					2	L	7	2 	4F			RT	A16WE   					 
1997120400052	19971204	00052		1997	12	4	AU970167         	4	19970303	G	2562	MN1300	BATTERY         		E01         	CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	EMERG LOCATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					009190					(AUS) ELT BATTERIES DETERIORATED - WHITE POWDER SUBSTANCE ON EXTERIOR OF ELT - DARK STICKY FLUID IN ELT BATTERY BOX - PL	ATING ON SOME BATTERY CONTACTS CORRODED - ELT WOULD NOT FUNCTION - EXPIRE DATE OF BATTERIES JANUARY 1999					1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1997120400053	19971204	00053	CE  	1997	12	4	AU970168         	1	19970206	G	5610	531126110	WINDOW          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	FLIGHT COMPART	FAILED          	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		CR	CRUISE         	1			AU	S 										(AUS) COPILOTS WINDOW FAILED - WINDOW BLEW OUT DURING FLIGHT						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1997120400054	19971204	00054	EA  	1997	12	4	AU970169         	2	19970225	G	8540		PLUNGER         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RECIP ENG	STICKING        	W				K				NONE                    				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AU	S 							L3344736A			(AUS) ENGINE DRIVEN FUEL PUMP PLUNGER STICKING - INVESTIGATION FOUND THAT THE PLUNGER WAS JAMMED BY A SLIVER OF ALUMINIU	M ALLOY APPROXIMATELY 5MM (0.196IN) IN LENGTH - METAL SLIVER APPEARS TO BE A SECTION OF THE REAR COVER RESULTING FROM TH	E MACHINING OFTHE FUEL PUMP PLUNGER HOLE				1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920	 
1997120400055	19971204	00055	CE  	1997	12	4	AU970170         	1	19970228	G	2432		BATTERY         			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	BATTERY/CHARGER	DISCHARGED      	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) BATTERY VOLTAGE LOW - SUSPECT CAUSED BY ALTERNATOR SWITCHES BEING IN THE `OFF' POSITION						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997120400056	19971204	00056		1997	12	4	AU970171         	4	19970210	G	2565	2599	SLIDE           			BOEING	737   	737476      		NM  										ESCAPE SLIDE	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					2599					(AUS) SAFETY SLIDE DID NOT DEPLOY DURING TEST - INVESTIGATION FOUND THE SAFETY PIN STILL INSTALLED - SLIDE OPERATED MANU	ALLY WHEN SAFETYPIN WAS REMOVED - PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4F			RT	A16WE   					 
1997120400057	19971204	00057		1997	12	4	AU970172         	4	19970304	G	6113	TB1058026001	SPINNER         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROP SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3313736A			(AUS) PROPELLER SPINNER CRACKED FROM ATTACHMENT SCREW HOLES - INVESTIGATION FOUND THAT THE SPINNER WAS NOT A FIRM FIT ON	 THE PROPELLER HUB					1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920	 
1997120400058	19971204	00058	CE  	1997	12	4	AU970173         	1	19970218	G	3710	B906	HOSE            		S2501SERIES 	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	VACUUM DISTRIBUT	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VACUUM PUMP AIR HOSES DETERIORATED AND BREAKING UP INTERNALLY - FOUND DURING INSPECTION IAW CESSNA SEB 96-10						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997120400059	19971204	00059	CE  	1997	12	4	AU970175         	1	19970227	G	2910	10558000121	PIPE            			BEECH 	76    	76          	1153005	CE  										HYDRAULIC, MAIN	CORRODED        	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC PIPE CORRODED - LOSS OF HYDRAULIC FLUID FROM PIN HOLE LEAK						1	L	7	2 	3O				A29CE   					 
1997120400060	19971204	00060	WP  	1997	12	4	AU970176         	1	19970211	G	2750		CONTROL ROD     			DOUG  	DC3   	DC3G202A    	3021424	WP  						HAMSTD	23E	23E50       	NE  	TE FLAP CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING FLAP OPERATING ROD CRACKED IN AREA OF OUTBOARD LINKAGE CUTOUT						2	L	7	2 	4R				A618    		6	C	P603	 
1997120400061	19971204	00061	NM  	1997	12	4	AU970177         	1	19970223	G	2435	300SGL127Q	STARTER GEN     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					STARTER-GENERATO	FAULTY          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					1115XL					(AUS) RH ENGINE STARTER-GENERATOR FAULTY						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997120400062	19971204	00062	NM  	1997	12	4	AU970178         	1	19970130	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE MAIN BU	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN THE FOLLOWING AREAS: 1. FORWARD FACE OF BULKHEAD WEB CRACKED AT RBL 5.7 RUNNI	NG BELOW FASTENERS UNDER RADAR SCANNING BRACKET - CRACK LENGTH 7MM (0.275IN) - FOUND USING ULTRASONIC TECHNIQUE 2. FORWA	RD FACE OF BULKHEAD WEB CRACKED AT LBL 5.7 RUNNING UNDER EDGE OF BEAM BELOW FASTENERS - CRACK LENGTH 7MM (0.275MM) - FOU	ND USING ULTRASONIC TECHNIQUE 3. AFT FACE OF BULKHEAD CRACKED IN LEFT VERTICAL CHORD AT BUTTOCK  LINE 5.7 IN THE BOARD R	ADIUS OF THE CHORD - CRACK LENGTH 30MM (1.18IN) - FOUND USING EDDY CURRENT METHOD		2	L	7	2 	4F			RT	A16WE   					 
1997120400063	19971204	00063	SO  	1997	12	4	AU970179         	2	19970116	G	8540	EQ6642	ADAPTER         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIP ENG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			900  		234315		234315			(AUS) ENGINE STARTER ADAPTER HARMONIC BALANCER LOOSE - WHEN REMOVED ITWAS FOUND THAT ALL THE ENGINE NEEDLE BEARINGS WERE	 MISSING (SUSPECT IN SUMP) AND METAL WAS WORN FROM THE BEARING HOSING					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997120800004	19971208	00004	NE  	1997	12	8	AU970180         	2	19970225	G	7250	785265	BLADE           	GE          	CT79B       	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	TURBINE SECTION	SEPARATED       	W		A		K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					785265		785265			(AUS) LH ENGINE NO3 BEARING SPALLED - 2ND STAGE TURBINE BLADE BROKEN CAUSING EXTENSIVE DAMAGE TO HOT END SECTION AND POW	ER TURBINE COMPONENTS					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997121100039	19971211	00039	NE  	1997	12	11	AU970181         	2	19970227	G	7261		OIL SYSTEM      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE ENG OIL	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LF05379			(AUS) NO4 ENGINE OIL FILTER BYPASS BUTTON EXTENDED - FURTHER INVESTIGATION FOUND HEAVY CONTAMINATION OF THE CHIP DETECTO	R AND OIL DISCOLOURATION					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997121100040	19971211	00040	CE  	1997	12	11	AU970183         	1	19970305	G	5311	1144200341	FRAME           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN CABIN DOOR FRAME SUPPORT STRUCTURE CRACKED AT FLOOR LEVEL -CRACK LENGTH 135MM (5.31IN) - FOUND USING ADHOC RA	DIOGRAPHIC INSPECTION					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997122900002	19971229	00002	EU  	1997	12	29	AU970184         	1	19970209	G	2752		ACTUATOR        			AIRBUS	320   	A320212     		EU  										TE FLAP ACTUATOR	MIS RIGGED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING INBOARD AND OUTBOARD TRAILING EDGE FLAPS MISALIGNED - NR 2 FLAP ACTUATOR INCORRECTLY RIGGED						2	L	7	2 	4F			RT	A28NM   					 
1997121100041	19971211	00041		1997	12	11	AU970185         	4	19970306	G	2562	ACKE01	ELT             			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320B2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	EMERGENCY LOCATO	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT BATTERIES DAMAGED AND WORN DUE TO POOR DESIGN OF THE ELT						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
1997121100042	19971211	00042	NM  	1997	12	11	AU970186         	1	19970228	G	4920		TURBINE         	GARRTT      	GTCP85129K  	BOEING	737   	737377      		NM  										APU CORE ENGINE	DAMAGED         	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) APU TURBINE BUCKLED AND WHEEL PROTRUDED THROUGH ENGINE CASING - DAMAGE TO GEARBOX AREA - RH ENGINE MOUNT SHATTERED						2	L	7	2 	4F			RT	A16WE   					 
1997121100043	19971211	00043	NM  	1997	12	11	AU970187         	1	19970227	G	2150	32194211	CONTROL VALVE   			BOEING	737   	737377      		NM  										CABIN COOLING SY	SEIZED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RH AIR CONDITIONING PACK,  SINGLE PACK OPERATION MARGINAL - LH AIR CONDITIONING SYSTEM FAULTY DUE TO 35 DEGREE CON	TROL VALVE PNO321942-1-1 BEING SEIZED IN CLOSED POSITION WITH SHAFT SHEARED AND LH TEMPERATURE CONTROL VALVE PNO 398116-	1-1 HAVING LIMITED MOVEMENT				2	L	7	2 	4F			RT	A16WE   					 
1997121100044	19971211	00044	CE  	1997	12	11	AU970188         	1	19970124	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR PIVOT ASSEMBLY CRACKED AS INDICATED IN SEB 90-1 REV 2.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1997121100045	19971211	00045	GL  	1997	12	11	AU970189         	3	19970304	G	6110		PROPELLER       													MCAULY	3AF32C	3AF32C87    	GL  	AIRCRAFT MANUALS	WRONG TORQUE    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER INSTALLATION TORQUE DISCREPANCY - PROPELLER DECAL AND AIRCRAFT MANUAL INDICATE DIFFERENT TORQUE SETTINGS																5	C	P22EA	 
1997122900003	19971229	00003	EA  	1997	12	29	AU970190         	1	19970221	G	2560		DITCHING DAM    			DHAV  	DHC8  	DHC8311     	1386006	EA  										EMERGENCY EQUIP	FAILURE         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LH DITCHING DAM INFLATED - INVESTIGATION FOUND THAT THE CAUSE WAS THE FAILURE OF THE GASKET INSTALLED IN THE DITCH	ING DAM ADAPTER					2	H	7	2 	4T			RT	A13NM   					 
1997122900004	19971229	00004	EA  	1997	12	29	AU970191         	1	19970224	G	2560		DITCHING DAM    			DHAV  	DHC8  	DHC8311     	1386006	EA  										EMERGENCY EQUIP	DEPLOYED        	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LH UNDERWING DITCHING DAM DEPLOYED IN FLIGHT - SEE MDR 97/0190FURTHER INFORMATION ON SIMILAR DEFECT						2	H	7	2 	4T			RT	A13NM   					 
1997121100046	19971211	00046	CE  	1997	12	11	AU970192         	1	19970305	G	2110	24112	HOSE            		11791005    	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN COMPRESSOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							PCE94638			(AUS) RH AIRCONDITION SYSTEM ENGINE DRIVEN FREON COMPRESSOR SUCTION AND PRESSURE HOSES CONTAMINATED WITH RUBBER PARTICLE	S - SUSPECT DEBRIS FROM INCORRECT MANUFACTURING TECHNIQUE - FORWARD AND REAR EVAPORATOR TRANSFER VALVES ALSO CONTAMINATE	D				1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997121100047	19971211	00047	GL  	1997	12	11	AU970194         	3	19970306	G	6111	T10282H	BLADE           			STBROS	SC7   	SC7SERIES3  	8100512	EU  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER BLADE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			600  					BV2116		(AUS) PROPELLER BLADES CORRODED AT BUTT END - CORROSION WAS BEYOND REPAIRABLE LIMITS - INVESTIGATION FOUND THAT BLADE SH	ANK/RADIUS AREA HAD NOT BEEN PROTECTED AT LAST OVERHAUL WHICH WAS CARRIED OUT IN SOUTH AFRICA					1	H	7	2 	3T			NT	A15EU   		6	C	P15EA	 
1997121100048	19971211	00048	GL  	1997	12	11	AU970195         	3	19970306	G	6111	T10282	BLADE           			STBROS	SC7   	SC7SERIES3  	8100512	EU  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER BLADE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			600  					BV4069		(AUS) PROPELLER BLADE BUTTS CORRODED BEYOND REPAIR - BLADES NOT PROTECTED DURING LAST OVERHAUL - SEE MDR 97/0194 FOR SIM	ILAR DEFECT ON OTHER PROPELLER					1	H	7	2 	3T			NT	A15EU   		6	C	P15EA	 
1997121100049	19971211	00049	EU  	1997	12	11	AU970196         	1	19970227	G	3260	622800200	SWITCH          			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LANDING GEAR POS	FAILED          	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWN AND LOCKED MICROSWITCH INTERNAL SHORT CIRCUIT DUE TO CORROSION						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1997121100050	19971211	00050	GL  	1997	12	11	AU970197         	3	19970306	G	6111	A1851	BEARING         			STBROS	SC7   	SC7SERIES3  	8100512	EU  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			600  					BV2116		(AUS) PROPELLER BLADE BEARING CRACKED - SUSPECT BEARING SPLIT BEARING HALVES MISMATCHED AT LAST OVERHAUL - PROPELLERS LA	ST OVERHAULED IN SOUTH AFRICA - PERSONNEL/MAINTENANCE ERROR - SEE MDR 97/0194 FOR FURTHER INFORMATION					1	H	7	2 	3T			NT	A15EU   		6	C	P15EA	 
1997121100051	19971211	00051	CE  	1997	12	11	AU970198         	1	19970226	G	5753	35165050230	FLAP            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					TE FLAP STRUCTUR	DAMAGED         	W				K				NONE                    				O	C		OTHER                     	F.O.D.                    		LD	LANDING        	1			AU	S 										(AUS) LH OUTBOARD WING FLAP DAMAGED - SPAR BENT AND SKIN CREASED -INVESTIGATION FOUND A DEAD HARE ON THE RUNWAY						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997121100052	19971211	00052	NM  	1997	12	11	AU970199         	1	19970130	G	2120		DUCT            			DHAV  	DHC8  	DHC8201     	2809001	NM  										AIR DISTRIBUTION	SEPARATED       	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) PRESSURISATION SYSTEM RECIRCULATION FAN TO CABIN PRESSURE DOMEBUL BULKHEAD PIPE ASSEMBLY AIR DUCT LINE SEPARATED						2	H	7	2 	4T			RT	A13NM   					 
1997121100053	19971211	00053	NM  	1997	12	11	AU970200         	1	19970116	G	3244		TIRE            			BOEING	747   	747238B     	1384828	NM  										MLG NR 4 FWD	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NO4F BODY LANDING GEAR TYRE TREAD SEPARATED - THE TYRE WAS STILL INFLATED						2	L	7	4 	4F				A20WE   					 
1997121100054	19971211	00054	NM  	1997	12	11	AU970201         	1	19970128	G	3244		TIRE            			BOEING	747   	747438      		NM  										MLG NR 4 RTY	SEPARATED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NO4 RT TYRE TREAD SEPARATED - DAMAGE TO WING TO BODY PANELS (3OFF)						2	L	7	4 	4F			RT	A20WE   					 
1997122900005	19971229	00005	NM  	1997	12	29	AU970202         	1	19970123	G	2597		WIRE            			BOEING	767   	767338      	1385151	NM  										CARGO BAY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS)  FORWARD CARGO HOLD DRIVE SYSTEM WIRE LOCATED IN THE CARGO HOLD FLOOR AT STA 520 POWER DRIVE UNIT SEVERED,  TRIPPE	D CIRCUIT BREAKER RESETTING CAUSED A SMALL FIRE CAUSING DAMAGE TO THE WIRING AND ADJACENT INSULATION.					2	L	7	2 	4F			RT	A1NM    					 
1997121100055	19971211	00055	NM  	1997	12	11	AU970203         	1	19970205	G	3411	HTC7476PP	COVER           			BOEING	747   	747238B     	1384828	NM  										PITOT/STATIC SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LH PITOT PROBE BLOCKED BY A PIECE OF PITOT PROBE COVER MATERIAL						2	L	7	4 	4F				A20WE   					 
1997121100056	19971211	00056		1997	12	11	AU970204         	4	19970111	G	2565	69B520752	CLEVIS          			BOEING	747   	747338      		NM  										ESCAPE SLIDE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO3 MAIN DOOR OFF WING ESCAPE SLIDE DITCHING CLUTCH CLEVIS CRACKED - FOUND DURING INSPECTION IAW BJC C4/52/013						2	L	7	2 	4F			RT	A20WE   					 
1997122900006	19971229	00006	NE  	1997	12	29	AU970205         	2	19970217	G	7240	UL23992	PANEL           	RROYCE      	RB211524G   						RROYCE	RB211 	RB211524G19 		NE  					TURBINE ENGINE C	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ENGSERNO1318					(AUS) ENGINE COMBUSTION LINER METERING PANEL CRACKED - HEAT SHIELDS DISTORTED - MINOR BURNING OF OUTER LINER - FOUND DUR	ING BOROSCOPE INSPECTION - INVESTIGATION FOUND THAT THE PANEL HAD BEEN INCORRECTLY INSTALLED AT THE LAST SHOP VISIT -PER	SONNEL/MAINTENANCE ERROR									4	F			E30NE				 
1997121100057	19971211	00057	NM  	1997	12	11	AU970206         	1	19970203	G	3244		TIRE            			BOEING	747   	747438      		NM  										LT BODY GEAR	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NO6 LH BODY GEAR TYRE TREAD SEPARATED - DAMAGE TO LH BODY GEARDOOR AND STRUT ROD						2	L	7	4 	4F			RT	A20WE   					 
1997122900007	19971229	00007		1997	12	29	AU970207         	1	19970223	G	7330	J221P904	O- RING         								RROYCE	RB211 	RB211524G19 		NE  					ENGINE FUEL IND	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE LOW PRESSURE DIFFERENTIAL PRESSURE SWITCH ELBOW FITTING `O' RING SEAL LEAKING											4	F			E30NE				 
1997121100058	19971211	00058	EU  	1997	12	11	AU970208         	1	19970306	G	2750		FLAP SYSTEM     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAP CONTROL	MALFUNCTIONED   	W				K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) FLAPS WOULD NOT RETRACT - FLAPS WERE RESET AND THEN OPERATED NORMALLY - NO FAULT EVIDENT ON FLAP COMPUTER						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997121100059	19971211	00059	NE  	1997	12	11	AU970209         	2	19970302	G	7250		BLADE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TURBINE SECTION	SEPARATED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							PCE115469			(AUS) RH ENGINE FIRST STAGE POWER TURBINE BLADE SEPARATED - SECOND STAGE POWER TURBINE DAMAGED - METAL CONTAMINATION OF 	OIL SYSTEM - FAILURE WAS DUE TO LOW CYCLE FATIGUE COMBINED WITH CORROSION IN THE LIGHTENING CAVITY					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997121100060	19971211	00060	CE  	1997	12	11	AU970210         	1	19970305	G	2612	302158	DETECTOR        		303267      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RH ENGINE FIRE DETECTORS (3OFF) FAULTY - DETECTOR AMPLIFIER ALSO REPLACED						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997121100061	19971211	00061	SO  	1997	12	11	AU970211         	2	19970305	G	7314	2B729	PUMP            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE FUEL PUMP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5    							(AUS) ENGINE FUEL PUMP FAULTY - SUSPECT INTERNAL STICKING IN SOLENOID - PUMP HAD COMPLETED 4.8 HOURS TIME SINCE OVERHAUL						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
1997121100062	19971211	00062	EU  	1997	12	11	AU970212         	1	19970305	G	2710	5135121	CONTROL ROD     			ISRAEL	1124  	1124        	4500102	EU  										AILERON CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH AILERON CONTROL ROD CONTAINED MEDIUM TO HEAVY CORROSION - FOUND DURING X-RAY INSPECTION						2	M	7	2 	4F				A2SW    					 
1997121100063	19971211	00063	EU  	1997	12	11	AU970213         	1	19970219	G	4920	38001881	AUX POWER UNIT  			AMD   	FALC50	FALCON900   	2700160	EU  										APU CORE ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU LEAKING OIL INTO EXHAUST SYSTEM AND AIRCONDITIONING DUCT -SUSPECT INTERNAL SEAL LEAK - THIS DEFECT WAS RECEIVE	D FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY					2	L	7	3 	4F			RT	A46EU   					 
1997121100064	19971211	00064	EA  	1997	12	11	AU970214         	2	19970208	G	7414	4251R	MAGNETO         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MAGNETO/DISTRIBU	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					5109019		L37639			(AUS) MAGNETO FAILED - INSPECTION FOUND HT COIL SECONDARY WIRING OPEN CIRCUIT						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121100065	19971211	00065	CE  	1997	12	11	AU970215         	1	19970305	G	2510	081278211	SEAT            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	COPILOT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COPILOTS SEAT BASE AUXILIARY SUPPORT STRUCTURE CRACKED IN TWO AREAS						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997121100066	19971211	00066	CE  	1997	12	11	AU970216         	1	19970305	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PILOTS	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) PILOTS WINDSHIELD CRACKED IN SEVERAL PLACES - WINDSHIELD HEAT WAS OPERATING AT THE TIME						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997121100067	19971211	00067		1997	12	11	AU970217         	4	19970131	G	2562	E01	ELT             			AMTR  	JABIRU	JABIRUSK    	05602CU	GL  										EMERGENCY LOCATO	ACTIVATED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ELT ACTIVATED DURING RADIO TRANSMISSION - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY						1	H	7	1 	IO			NC	EXPA1H71					 
1997121100068	19971211	00068	CE  	1997	12	11	AU970218         	1	19970305	G	5511	0532001	SPAR            			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	HORIZONTAL STABI	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER FORWARD SPAR CRACKED AT CENTRE LIGHTENING HOLE AS INDICATED IN SEB 94-8 - CRACK LENGTH APPRO	XIMATELY 10MM (0.393IN) - SUSPECT PROBLEM CONTRIBUTED TO BY INCORRECT GROUND HANDLING					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997121100069	19971211	00069	EA  	1997	12	11	AU970219         	2	19970301	G	8530	LW12397	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	NR 3 & 4 CYLS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1500 		VARIOUS					(AUS) NO1, NO3 AND NO4 CYLINDERS CRACKED FROM LOWER SPARK PLUG HOLES -CRACKS HEADING TOWARDS EXHAUST VALVE SEAT - CYLIND	ERS WERE NITRIDED ITEMS AND HAD COMPLETED TWO ENGINE LIVES					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997121100070	19971211	00070	NE  	1997	12	11	AU970220         	2	19970305	G	7260	J221P035	O-RING          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	RT ENG STARTER	DAMAGED         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 							785598			(AUS) RH ENGINE STARTER DRIVE SEAL FLANGE `O' RING SEAL DAMAGED - FLANGE SEAL HAD BEEN CHANGED 1.2 HOURS PREVIOUS - SUSP	ECT PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997121100071	19971211	00071	SO  	1997	12	11	AU970221         	1	19970313	G	5751	8639604	RIB             		8639804     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					AILERON STRUCTUR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON NOSE RIBS PNO 86396-04 AND PNO 86398-04 CRACKED ATATTACHMENT BRACKETS						1	L	7	2 	3O	3	O		A19S0   	E286				 
1997121100072	19971211	00072	CE  	1997	12	11	AU970222         	1	19970312	G	3233	AFTS1001	COMMUTATOR      	PRESTOLITE  	HYH5001     	BEECH 	76    	76          	1153005	CE  										LANDING GEAR ACT	OPEN CIRCUIT    	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					AFTS1001					(AUS) LANDING GEAR MOTOR COMMUTATOR SEGMENT OPEN CIRCUIT DUE TO LOOSE CRIMP ON THE WINDING						1	L	7	2 	3O				A29CE   					 
1997121100073	19971211	00073	NM  	1997	12	11	AU970223         	1	19970227	G	2750	693923617	PUSHROD         			BOEING	737   	737476      		NM  										TE FLAP CONTROL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD TRAILING EDGE FLAP AFT FLAP INBOARD PUSHROD BENT						2	L	7	2 	4F			RT	A16WE   					 
1997121100074	19971211	00074	NM  	1997	12	11	AU970224         	1	19970227	G	2750	693923617	PUSHROD         		693923618   	BOEING	737   	737476      		NM  										TE FLAP CONTROL	DAMAGED         	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) RH OUTBOARD TRAILING EDGE FLAP AFT FLAP INBOARD AND OUTBOARD DRIVE RODS PNO 69-39236-17 AND PNO 69-39236-18 BENT						2	L	7	2 	4F			RT	A16WE   					 
1997121100075	19971211	00075	SW  	1997	12	11	AU970225         	1	19970312	G	3230	2781025003	PIN             			FRCHLD	SA227 	SA227CC     		SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LANDING GEAR RET	INCORRECT FIT   	W				K				NONE                    				W			INADEQUATE Q C            			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR EMERGENCY GEAR EXTENSION SHUTOFF VALVE HANDLE LOCK PIN INCORRECTLY FITTED - EMERGENCY GEAR EXTENSION 	HANDLE WAS PUSHED FORWARD TOWARDS THE EMERGENCY POSITION PREVENTING CORRECT OPERATION OF THE LANDING GEAR RETRACTION SYS	TEM - PERSONNEL ERROR				2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997121100076	19971211	00076	EU  	1997	12	11	AU970226         	1	19970312	G	3260		SWITCH          	AIRBUS      	A3233265300 	AIRBUS	300   	A300B4622R  		EU  	PWA   	4158  	PW4158      		NE  					LANDING GEAR POS	FAILED          	W				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 					NOTKNOWN					(AUS) LH MAIN LANDING GEAR UPLOCK SWITCH FAULTY						2	L	7	2 	4F	4	F	RT	A35EU   	E24NE				 
1997122900008	19971229	00008	SO  	1997	12	29	AU970227         	2	19970313	G	7414	4052326A	BEARING         	BENDIX      	S6RN1225    	CESSNA	210   	210N        	2073453	CE  	CONT  	O550  	IO550*      		SO  					MAGNETO/DISTRIBU	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					4052326A		289010R			(AUS) MAGNETO CAM END ROTOR BEARING FAILED - MAGNETO CONTAMINATED WITHMETAL DUST						1	H	7	1 	3O	3	O		3A21    	E3SO				 
1997121100077	19971211	00077	SO  	1997	12	11	AU970228         	2	19970314	G	8520	63026143	BUSHING         	CONT        	639199      						CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	COUNTERWEIGHT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NIL		353391			(AUS) ENGINE COUNTERWEIGHT BUSHES AND ROLLERS PNO 639198 AND PNO630261-43 WORN UNEVENLY - INTERNAL CORROSION EVIDENT ON 	STEEL PARTS										3	O			E1CE	5	C	P920	 
1997121100078	19971211	00078	NE  	1997	12	11	AU970229         	1	19970314	G	6720	7640301111041	SUPPORT         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					T/R CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR CONTROL PEDAL CENTRE SUPPORT CRACKED AT THE UPPER SUPPORT TUBE WELDED JOINT						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997121100079	19971211	00079	CE  	1997	12	11	AU970230         	1	19970318	G	5551	17320311	ARM             		17320312    	CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	HORIZ STAB WT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR WEIGHT ARM LH AND RH REAR MOUNTING BRACKETS PNO1732031-1 AND PNO 1732031-2 CRACKED ALONG VERTICAL BENDS						1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1997121100080	19971211	00080	SO  	1997	12	11	AU970231         	2	19970316	G	8530	653446	CYLINDER        			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUEL NOZZLE	STRIPPED        	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			545  				20742978L			(AUS) ENGINE CYLINDER HEAD FUEL NOZZLE RETAINING THREADS STRIPPED - FUEL NOZZLE LOOSE - CYLINDER IS 0.0015IN PLUS OVERSI	ZE WITH UNKNOWN TOTAL TIME IN SERVICE - AD/CON/60 CARRIED OUT 50 HOURSPRIOR TO FAILURE					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997121100532	19971211	00532	CE  	1997	12	11	AU970232         	1	19970318	G	3297		WIRE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR POS	BROKEN          	W				K				NONE                    				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) RH MAIN LANDING GEAR MICROSWITCH EARTH WIRE BROKEN						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
1997121100533	19971211	00533	CE  	1997	12	11	AU970233         	1	19970318	G	2721	96526000	TRIM JACK       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					RUD TAB CONTROL	INCORRECT WIRED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRIM JACK INCORRECTLY LOCKWIRED - THE TRIM JACK ROD END WAS LOCKED TO THE TRIM JACK HOUSING RETAINING NUT A	LLOWING THE TRIM JACK TO ONLY ROTATE ONE TURN - THIS CONDITION HAD EXISTED FOR APPROXIMATELY 800 HOURS - PERSONNEL/MAINT	ENANCE ERROR				1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997121100534	19971211	00534	CE  	1997	12	11	AU970234         	1	19970319	G	5753	3515605084	RIB             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					TE FLAP STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FLAP RIB CRACKED IN AREA OF FLAP ACTUATOR ATTACHMENT - CRACK EMANATES FROM FORWARD ATTACHMENT BOLT HOLE IN A PR	EVIOUSLY REPAIRED AREA - SUSPECT CRACK DUE TO INCORRECT REPAIR					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997121100535	19971211	00535	WP  	1997	12	11	AU970235         	2	19970113	G	8530	77	NUT             			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					CYL HOLD DOWN	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							77			(AUS) CYLINDER HEAD HOLD DOWN NUTS LOOSE - HEAD MOVING ON CYLINDER BARREL						1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1997121100536	19971211	00536	WP  	1997	12	11	AU970236         	2	19970113	G	8520	77	TAPPET          			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ENG VALVES	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							77			(AUS) ALL VALVE TAPPET CLEARANCES OUT OF ADJUSTMENT						1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1997121100537	19971211	00537	WP  	1997	12	11	AU970237         	2	19970113	G	7414	28729	POINTS          	BTH         	AG46        	DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					MAGNETO	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					28729		77			(AUS) MAGNETO POINTS CLOSED - TIMING OUT OF ADJUSTMENT						1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1997121100538	19971211	00538	WP  	1997	12	11	AU970238         	2	19970113	G	8530		NUT             			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ENG EXH MANIFOLD	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							77			(AUS) ENGINE EXHAUST MANIFOLD ATTACHMENT NUTS LOOSE - ONE NUT MISSING - ONE STUD IN CYLINDER HEAD PULLED						1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1997121100539	19971211	00539	SO  	1997	12	11	AU970239         	1	19970205	G	2700		CONTROL CABLE   			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	FLIGHT CONTROLS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UNKNOWN CABLE BROKEN - LIMITED INFORMATION PROVIDED						1	L	7	2 	3O			 	A7SO    		5	C	P920	 
1997121100540	19971211	00540	WP  	1997	12	11	AU970240         	2	19970113	G	7322		CARBURETTOR     			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					FUEL CONTL/CARB	CONTAMINATED    	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			AU	S 							77			(AUS) CARBURETTOR BANJO FITTING CONTAMINATED WITH WATER AND SEDIMENT -AIRCRAFT CRASHED ON TAKEOFF						1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1997121800766	19971218	00766	GL  	1997	12	18	AU970241         	3	19970317	G	6111	660715620	CLAMP           													ROTOL	R352	R3526123F1  	GL  	PROPELLER BLADE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6056 					012COMPSN		(AUS) PROPELLER BLADE LOOSE - INVESTIGATION FOUND P.T.F.E BAND CLAMP FAILED ALLOWING THE PRELOAD RING TO MOVE OUT OF POS	ITION -SUSPECT CAUSED BY OVERTORQUING THE CLAMP BOLT															6	C	P16NG	 
1997121100541	19971211	00541	SO  	1997	12	11	AU970242         	1	19970210	G	7921		O-RING          			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENG OIL COOLER	DETERIORATED    	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) ENGINE OIL COOLER TO PRESSURE LINE `O'- RING SEAL DETERIORATED AND LEAKING						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
1997121100542	19971211	00542	SO  	1997	12	11	AU970243         	1	19970318	G	2822	421136	PUMP            	WELDON      	421136      	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL BOOST PUMP	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 			1507 		09619					(AUS) FUEL BOOST PUMP FAULTY - INVESTIGATION FOUND ONE OF THE MOTOR BRUSHES WORN AWAY - A COUPLING SPLINE BETWEEN THE MO	TOR AND THE PUMP WAS BADLY WORN - PUMP BLADE SUPPORT BLOCK BADLY WORN - COMMUTATOR DAMAGED DUE TO LOSS OF BRUSH					1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997121100543	19971211	00543	NE  	1997	12	11	AU970244         	2	19970314	G	7230		COMPRESSOR      			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TURBINE ENGINE	STALLED         	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 							687608			(AUS) NO2 ENGINE COMPRESSOR STALL.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997121100544	19971211	00544	NM  	1997	12	11	AU970245         	1	19970311	G	3246	300654	WHEEL           	BFGOODRICH  	31448       	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					WHEEL/SKI/FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1462					(AUS) NOSE WHEEL CRACKED IN AREA OF BEAD SEAT - CRACK LENGTH 4MM(0.157IN) - FOUND USING EDDY CURRENT INSPECTION AND CONF	IRMED USING FLUORESCENT DYE PENETRANT					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997121100545	19971211	00545	CE  	1997	12	11	AU970246         	1	19970307	G	5321	04102381	FLOOR           			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	FUSELAGE FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			9182 					JH049		(AUS) FLOOR CRACKED IN AREA OF SEAT RAIL ATTACHMENT AT REAR - SEAT RAIL HAS A RIGHT ANGLE END WHICH CUTS INTO FLOOR						1	H	7	1 	3O				3A19    		5	N	P50GL	 
1997121100546	19971211	00546	SO  	1997	12	11	AU970247         	2	19970228	G	7313	627335D13B	INJECTOR        			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	NR 2 CYL FUEL	BLOCKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			756  				294689	912185		(AUS) NO2 CYLINDER FUEL INJECTOR NOZZLE BLOCKED						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997122900025	19971229	00025	EU  	1997	12	29	AU970248         	1	19970117	G	5210		FITTING         			AIRBUS	320   	A320212     		EU  										PAX/CREW DOOR	MIS RIGGED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 DOOR ARM/DISARM CAM WORN ALLOWING ARMING LEVER TO MOVE FROM DISARMED TO ARMED POSITION WITHOUT REMOVING THE SAF	ETY PIN -INVESTIGATION FOUND THAT THE BORE OF THE BALL PIN FITTING WAS NOT CENTRAL UNDER THE CAM ALLOWING THE ARMING CAM	 TO RIDE PAST THESAFETY PIN				2	L	7	2 	4F			RT	A28NM   					 
1997121100547	19971211	00547	CE  	1997	12	11	AU970249         	1	19970307	G	5711	052340053	SPAR            			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5562 			18253162	191414	725435		(AUS) WING REAR SPAR CRACKED IN RADIUS OF WING ATTACHMENT WEB						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100548	19971211	00548	NM  	1997	12	11	AU970250         	1	19970312	G	2721	441	SWITCH          			BOEING	737   	73733A      	1384673	NM  										RUDDER TAB CONT	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					441					(AUS) RUDDER TRIM SWITCH STICKING DUE TO GROOVES ON CAMSHAFT						2	L	7	2 	4F			RT	A16WE   					 
1997121100549	19971211	00549	CE  	1997	12	11	AU970251         	1	19970307	G	5312	07193005	BULKHEAD        			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE LT AFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5563 			18253162	191414	725435		(AUS) FUSELAGE LH BULKHEAD CRACKED						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100550	19971211	00550	CE  	1997	12	11	AU970252         	1	19970307	G	5711	18253162	SPAR            			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	WING SPAR STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) LH WING FRONT MAIN SPAR CORRODED - SEE MDR 97/0255 TO MDR 97/0265 FOR ADDITIONAL DEFECTS REPORTED UNDER THE SAME M	DR NUMBER					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997122900026	19971229	00026	GL  	1997	12	29	AU970253         	3	19970319	G	6111	SM28775339	SEAL            	HARTZL      		BEECH 	76    	76          	1153005	CE  						HARTZL	HCM2Y	HCM2YR      	GL  	PROPELLER BLADE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			995  					FB275		(AUS) PROPELLER BLADE SEALS LEAKING GREASE - INVESTIGATION FOUND BLADE SEALS TO BE INCORRECT PART - SEALS HAD BEEN SUPER	SEDED BY SEALS PNO Q4339 IN SL 148 DATED 18/3/83 - PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O				A29CE   		5	C	P43GL	 
1997121100551	19971211	00551	SO  	1997	12	11	AU970254         	1	19970317	G	5312	VARIOUS	BULKHEAD        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUSELAGE MAIN BU	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE REAR BULKHEAD CORRODED IN AREA OF STABILATOR ATTACHMENT BRACKETS - RIVETS POPPED AT FRAME OF FORWARD FIN 	ATTACHMENT AREA- FOLLOWING REMOVAL OF TOP AFT FUSELAGE SKIN AND SKIN ON FIN AND STABILISER.   WIDE SPREAD SURFACE CORROS	ION WAS FOUND WHERE FRAMES AND STRINGERS ATTACH - SUSPECT DUE TO LACK OF CORROSION PROTECTION DURING MANUFACTURE				1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
1997121100552	19971211	00552	CE  	1997	12	11	AU970255         	1	19970307	G	5712	18253162	RIB             			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	WING RIB STRUCTU	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) LH AND RH WINGS CORRODED IN AREA BETWEEN RIBS AND SKIN - SEE MDR97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100553	19971211	00553	CE  	1997	12	11	AU970256         	1	19970307	G	5730	18253162	SKIN            			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	WING PLATES	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) LH AND RH WING TOP AND BOTTOM SKINS CORRODED - WING INSPECTION PANELS ALSO CORRODED - SOME RIVETS MISSING - SEE MD	R 97/0252 FORADDITIONAL INFORMATION					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100554	19971211	00554	CE  	1997	12	11	AU970257         	1	19970307	G	5753	18253162	FLAP            	CESSNA      	182D        	CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	TE FLAP STRUCTUR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18253162		191414	725435		(AUS) LH AND RH WING FLAPS CORRODED - SEE MDR 97/0252 FOR ADDITIONALINFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100555	19971211	00555	CE  	1997	12	11	AU970258         	1	19970307	G	5751	18253162	AILERON         			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	AILERON STRUCTUR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) LH AND RH AILERONS CORRODED - SEE MDR 97/0252 FOR ADDITIONALINFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100556	19971211	00556	CE  	1997	12	11	AU970259         	1	19970307	G	5330	18253162	SKIN            			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE MAIN PL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) FUSELAGE SKINS CORRODED IN AREA OF ALL SKIN JOINTS IN BOTTOMS OF BOTH CABIN ENTRY DOORS AND DOOR HINGE ATTACHMENT 	AREAS, CABIN ROOF CORRODED - SEE MDR 97/0252 FOR ADDITIONAL INFORMATION					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100557	19971211	00557	CE  	1997	12	11	AU970260         	1	19970307	G	5312	18253162	BULKHEAD        			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE BULKHD	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) REAR FUSELAGE BULKHEAD CORRODED IN AREA OF DORSAL FIN ATTACHMENT- SEE MDR 97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100558	19971211	00558	CE  	1997	12	11	AU970261         	1	19970307	G	5313	18253162	STRINGER        			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) FUSELAGE STRINGERS CORRODED - SEE MDR 97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100559	19971211	00559	CE  	1997	12	11	AU970262         	1	19970307	G	5520	18253162	ELEVATOR        			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEVATOR STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) LH AND RH ELEVATORS CORRODED - SEE MDR 97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100560	19971211	00560	CE  	1997	12	11	AU970263         	1	19970307	G	5540	18253162	RUDDER          			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	RUDDER STRUCTURE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							191414	725435		(AUS) RUDDER CORRODED - SEE MDR 97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100561	19971211	00561	CE  	1997	12	11	AU970264         	1	19970307	G	5312	05B0069	BULKHEAD        	CESSNA      	182D        	CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18253162		191414	725435		(AUS) FORWARD CENTRE BULKHEAD LOCATED UNDER FLOOR SEVERELY CORRODED - SEE MDR 97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100562	19971211	00562	CE  	1997	12	11	AU970265         	1	19970307	G	5711	121002926	SPAR            			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	WING SPAR STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 						18253162	191414	725435		(AUS) CENTRE SECTION REAR CARRY THROUGH SPAR CORRODED - SEE MDR 97/0252 FOR ADDITIONAL INFORMATION						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997121100563	19971211	00563	GL  	1997	12	11	AU970266         	3	19970319	G	6110		PROPELLER       			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER ASSY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			691  				149313VO	721730		(AUS) LH PROPELLER SUSPECT OUT OF BALANCE - LH ENGINE FORWARD ENGINE MOUNT LOOSE - INVESTIGATION FOUND PROBLEM CAUSED BY	 BLADE ANGLES AND PROFILES					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1997121100564	19971211	00564	SW  	1997	12	11	AU970267         	1	19970317	G	2810	5630061502	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	FUEL STORAGE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING FUEL CELL LEAKING - ON REMOVAL OF THE TANK EXTENSIVE DETERIORATION OF THE INTERNAL AND EXTERNAL COATING OF	 TANK WAS EVIDENT - THE CELL WAS MANUFACTURED IN NOVEMBER 1978 AND CONSTRUCTED FROM BTC-67 MATERIAL					1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA	 
1997121100565	19971211	00565	SO  	1997	12	11	AU970268         	1	19970304	G	2750	110P28311298	SELECTOR SWITCH 			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP CONTROL	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) AFTER TOUCH DOWN THE COPILOTS KNEE ACCIDENTLY BROKE THE FLAP SELECTOR LEVER - INVESTIGATION LATER FOUND THE LEVER 	EXCESSIVELY WORN AND WEAKENED DUE TO THE CONTINUAL SLIDING CONTACT WITH THE DETENT PLATE					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997121100566	19971211	00566	SW  	1997	12	11	AU970269         	1	19970323	G	2913	1084	VALVE           	SWRNGN      	2781009015  	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC PUMP	BINDING         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			842  		1084					(AUS) POWER PACK INTEGRAL BY-PASS VALVE ASSEMBLY STIFF TO OPERATE DUE TO BINDING O-RING SEAL						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997122900027	19971229	00027		1997	12	29	AU970270         	1	19970307	G	2434	634442	ALTERNATOR      								CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	DC GENERATOR-ALT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					E309017		353391			(AUS) ALTERNATOR FRONT HOUSING CONTAINED FIVE CRACKS AROUND THE FLANGES -  ON ENGINE STRIP DOWN (REFER MDR 97/0228) IT W	AS FOUND THAT THE COUNTER WEIGHT ROLLERS ON THE CRANKSHAFT HAD EXCESSIVE WEAR AND THE ASSOCIATED VIBRATION IS SUSPECTED 	TO HAVE BEEN THE CAUSE									3	O			E1CE	5	C	P920	 
1997121100567	19971211	00567	SO  	1997	12	11	AU970271         	2	19970321	G	8520	276347R	CRANKCASE       			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	NR 2 CYL PAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							276347R			(AUS) AT ENGINE OVERHAUL THE FOLLOWING COMPONENTS WERE FOUND UNSERVICEABLE:1. CRANKCASE WAS FPI AND WAS FOUND CRACKED IN	SIDE NO2 CYLINDER PAD2. CAMSHAFT LOBE CRACKED - CRACK LENGTH 19MM (0.75IN) 3. QUILL SHAFT HAD BADLY GALLED SPLINES					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997121100568	19971211	00568	EA  	1997	12	11	AU970272         	2	19970317	G	8520	L1716940A	BUSHING         	LYC         	O540E4CS    						LYC   	O540  	O540E4C5    	41532	EA  					CRANK IDLER GEAR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L1716940A		L1716940A			(AUS) AT ENGINE OVERHAUL THE FOLLOWING WAS FOUND: 1. CRANKCASE GOVERNER IDLER GEAR BUSHING HEAVILY WORN 2. CRANKSHAFT GE	AR LOCK BOLT HAD SNAPPED IN THE CRANKSHAFT AND THE GEAR HAD DAMAGED THE DOWEL HOLE - ALSO DAMAGED WERE THE CRANKSHAFT GE	AR AND IDLER GEARS 3. CAMSHAFT LOBES DAMAGED ENGINE CAME FROM A PNG REGISTERED AIRCRAFT									3	O			E295				 
1997121100569	19971211	00569	EA  	1997	12	11	AU970273         	2	19970213	G	8520	LW18840	CAMSHAFT        			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RECIP ENG LOBES	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1080 				L120351A	CA116		(AUS) ENGINE WAS BULK STRIPPED FOLLOWING METAL CONTAMINATION OF OIL FILTER - CAMSHAFT LOBES FOUND TO BE WORN						1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
1997121100570	19971211	00570	SO  	1997	12	11	AU970274         	2	19970321	G	8530	649168CEA3	CYLINDER        			CESSNA	310   	310N        	2074234	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	RECIP  ENG BORE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							1480787U			(AUS) ENGINE CYLINDER (PNO 649168CEA3) BORES WORN BEYOND LIMITS - CYLINDERS ARE CERMICHROME TYPE						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1997121100571	19971211	00571	SO  	1997	12	11	AU970275         	2	19970318	G	8520	2400925R	SADDLE          	CONT        	IO520F      						CONT  	O520  	IO520F      	17032	SO  					RECIP  ENG MAIN	FRETTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2400925R		240925			(AUS) AT ENGINE OVERHAUL THE FOLLOWING WAS FOUND: 1. CRANKCASE MAIN BEARING SADDLE EVIDENCE OF FRETTING AND NO4  CAMTUNN	EL SCORED 2. CAMSHAFT WAS INSPECTED USING MPI AND CRACKS WERE FOUND ON TWO LOBES.  ENGINE WAS FROM A PNG REGISTERED AIRC	RAFT									3	O			E5CE				 
1997121100572	19971211	00572	WP  	1997	12	11	AU970276         	2	19970318	G	7261	31080801	PIPE            		31035781    	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TURB ENGINE OIL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 							P70220			(AUS) LH ENGINE PIPES PNO 3103578-1 (TURBINE BEARING OIL SUPPLY LINE) AND PNO 3108080-1 (NTS ORIFICE LINE) CHAFING TOGET	HER - OIL LEAKING - SUSPECT INCORRECT FITTING AT ASSEMBLY 296 HOURS PREVIOUSLY					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997121100573	19971211	00573	SO  	1997	12	11	AU970277         	2	19970317	G	8520	280127R	CRANKCASE       			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RECIP  ENG	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							280127R			(AUS) AT ENGINE OVERHAUL THE CRANKCASE WAS BOLTED TOGETHER AND TUNNELS WERE MEASURED OUT OF LIMITS						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997121100574	19971211	00574	EA  	1997	12	11	AU970278         	2	19970311	G	8530	12416	CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	NR 1 CYL PLUG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1343 				RL1534839A			(AUS) NO1 CYLINDER CRACKED FROM BOTH SPARK PLUG HOLES - CRACK LENGTHS 19.05MM (0.75IN) - EXHAUST VALVE SEAT BORE CRACKED	 - CRACK LENGTH 12.7MM (0.5IN)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121100575	19971211	00575	EU  	1997	12	11	AU970279         	1	19970321	G	5310		STRUCTURE       			BNORM 	BN2   	BN2A21      	1520221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AIRCRAFT GENERAL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT STRUCTURE CONTAINED EXTENSIVE CORROSION:-1. MAINPLANES HAD SEALING MATERIAL MISSING FROM LOWER SPAN LAMIN	ATES BETWEEN FUSELAGE AND ENGINE NACELLE ALLOWING  MOISTURE INGRESS AND CORROSION 2. WING SKINS PEELED BACK TO REVEAL EX	FOLIATION CORROSION IN AN  AREA OF THE INTERSPAR STRINGER ONE BACK FROM THE FRONT SPAR IN  AN AREA JUST OUTBOARD OF THE 	FUEL BAY AT APPROXIMATELY STN 200 3. HORIZONTAL STABILISER EXTENSIVE SURFACE CORROSION4. VERTICAL STABILISER EXTENSIVE S	URFACE CORROSION5. ELEVATOR BALANCE WEIGHTS BADLY CORRODED IN STEEL SECTIONS		1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998010500020	19980105	00020	SO  	1998	1	5	AU970280         	2	19970327	G	8540	530406	HUB             	CONT        							CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	DC GEN ALT DRIVE	SHEARED         	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			872  		C269002		353397			(AUS) ALTERNATOR DRIVE HUB SHEARED AT BOTH SHOULDERS - BROKEN PARTS ENTERED ENGINE OIL SYSTEM											3	O			E1CE	5	C	P920	 
1997121100576	19971211	00576	EA  	1997	12	11	AU970281         	2	19970321	G	8530		VALVE           			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NR 3 CYL EXH	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							L2297151A			(AUS) NO3 CYLINDER EXHAUST VALVE HEAD FAILED						1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
1997121100577	19971211	00577	NE  	1997	12	11	AU970282         	2	19970313	G	7261	15515	CHIP DETECTOR   	TMECA       	0292005250  	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					TURBINE ENG OIL	CONTAMINATED    	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					15515		15515			(AUS) NO1 ENGINE OIL SYSTEM CHIP DETECTORS CONTAMINATED - TYPE III PARTICLE (METAL SLIVER) ON MPI 1 CHIP DETECTOR - TYPE	 II PARTICLES (DARK DUST) ON MAGNETIC PLUGS - OIL AND FILTER CHANGEDAND ENGINE GROUND RUN SERVICEABLE					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1997121100578	19971211	00578	GL  	1997	12	11	AU970283         	3	19970306	G	6114	NAS6606D604	BOLT            								LYC   	O320  	O320D1A     	41508	EA  	HARTZL	HCC2Y	HCC2YL1     	GL  	PROPELLER HUB	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								AX685		(AUS) PROPELLER HUB BOLTS (4OFF) INCORRECT PARTS. BOLTS MEASURE .375 -CORRECT MEASUREMENT .371. PERSONNEL/MAINTENANCE ER	ROR. UNAPPROVED PART.										3	O			E274	5	C	P920	 
1997121100579	19971211	00579	GL  	1997	12	11	AU970284         	3	19970324	G	6114	D22017	HUB             	HARTZL      	HCC2YL1BF   						LYC   	O320  	O320D1A     	41508	EA  	HARTZL	HCC2Y	HCC2YL1     	GL  	PROPELLER HUB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AX685			AX685		(AUS) PROPELLER HUB BOLT HOLES (4OFF) TOO LARGE DUE TO INCORRECT DIAMETER BOLTS BEING USED - SEE MDR 97/0283											3	O			E274	5	C	P920	 
1997121100580	19971211	00580	NM  	1997	12	11	AU970285         	1	19970304	G	2700	41552172S	CONTROL CABLE   			UNIVAR	415   	415D        	0420306	NM  						MCAULY	1B90	1B90CM      	GL  	FLIGHT CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL CABLES ATTACHED TO PRIMARY CONTROL QUADRANT IN CONTROL COLUMN YOKE HAD FAULTY SWAGING - DURING TESTING CAB	LES PULLED THROUGH THE NICOPRESS SLEEVES AT A LOAD OF 610 LBS (NORMAL FAILURE LOAD 2200 LBS TO 2300LBS) - AIRCRAFT IS IM	PORTED FROM THE USA AND IS UNDERGOING INITIAL COFA - US REGISTRATION N94022				1	L	7	1 	3O			 	A787    		5	N	P842	 
1997121100581	19971211	00581		1997	12	11	AU970286         	4	19970307	G	2561	42216	MANIFOLD        		KSR35L8W    															LIFE JACKET	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1    		42216					(AUS) LIFE JACKET INFLATION MANIFOLD DELAMINATING AT WELD - LOSS OF AIR																			 
1997121100582	19971211	00582	NE  	1997	12	11	AU970287         	2	19970314	G	7261	15514	OIL SYSTEM      	TMECA       	0292005250  	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					TURBINE ENG OIL	CONTAMINATED    	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 					15514		15514			(AUS) NO2 ENGINE CHIP DETECTORS, MAGNETIC PLUGS AND FILTER CONTAMINATED WITH METAL PARTICLES						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1997121100583	19971211	00583	CE  	1997	12	11	AU970288         	1	19970310	G	3222	SK1759	FORK            			CESSNA	172   	172N        	2072434	CE  										NOSE GEAR	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR FORK SHEARED IN AREA OF PISTON TUBE ATTACHMENT- A HEAVY LANDING INSPECTION HAD BEEN CARRIED OUT 	40 HOURSPREVIOUSLY					1	H	7	1 	3O			NT	3A12    					 
1997121100584	19971211	00584	SW  	1997	12	11	AU970289         	1	19970329	G	3230	27810321013	PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					LANDING GEAR RET	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR `UP' RIGID PIPE HOLED AND LEAKING - PIPE IS MANUFACTURED FROM ALUMINIUM ALLOY						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997121100585	19971211	00585		1997	12	11	AU970290         	4	19970318	G	6122	8971609	GOVERNOR        	WOODWARD    	8971609     	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP GOV	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			24   		P474C					(AUS) RH ENGINE PROPELLER GOVERNOR FAULTY						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997121100586	19971211	00586	CE  	1997	12	11	AU970291         	1	19970219	G	5500		EMPENNAGE       			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	EMPENNAGE STRUCT	LIGHTNING STRIKE	W				K				NONE                    				C			F.O.D.                    			NR	NOT REPORTED   	1			AU	S 										(AUS) AIRCRAFT LIGHTENING STRIKE - ENTRY POINT APPEARS TO BE LH FLAP AND AILERON - BOTH ELEVATORS HAD EXIT HOLES ADJACEN	T TO OUTER STATIC WICKS - RUDDER TOP FAIRING HAD EXIT HOLE AND EVIDENCE OF BURNING - UPPER RUDDER SKIN HAD EVIDENCE OF A	RCING				1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997121100587	19971211	00587	CE  	1997	12	11	AU970292         	1	19970311	G	6120	7715649001	VALVE           	GARRTT      	TPE3318     	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP CONTROL	STICKING        	W				K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 					P31597					(AUS) NTS CHECK VALVE ON GEARCASE STICKING ALLOWING HIGH PRESSURE GOVERNOR OIL TO ACTIVATE BETA SWITCH						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997121100588	19971211	00588	EU  	1997	12	11	AU970293         	1	19970401	G	5751		BALANCE WEIGHT  	SOCATA      	AILERON     	SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AILERON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON BALANCE WEIGHT LOOSE - `POP' RIVETS MOVING						1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920	 
1997121100589	19971211	00589	EU  	1997	12	11	AU970294         	1	19970401	G	3211	115C5031	BRACKET         			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	LT MLG ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR ATTACHMENT BRACKET CRACKED AT FORWARD LOWER SECTION						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
1997121100590	19971211	00590	SO  	1997	12	11	AU970295         	2	19970221	G	8530	652956	VALVE           	CONT        	IO520BB     	BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	NR 3 & 4 EXH	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			3    		573078		573078			(AUS) NO4 CYLINDER EXHAUST VALVE FAULTY - FURTHER INVESTIGATION FOUND NO3 CYLINDER EXHAUST VALVE IN SIMILAR CONDITION - 	METAL CONTAMINATION OF OIL SYSTEM					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1997121100591	19971211	00591	SO  	1997	12	11	AU970296         	2	19970225	G	8520	294762R	CRANKCASE       			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	NR 4 & 5 MAIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							294762R			(AUS) ENGINE BULK STRIPPED FOLLOWING PROPELLER STRIKE - CRANKCASE FOUND TO BE CRACKED BETWEEN NO4 AND NO5 MAIN BEARING S	ADDLES - FOUND  USING FPI					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1997121100592	19971211	00592	CE  	1997	12	11	AU970297         	1	19970320	G	3222	12434262	TORQUE LINK     			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	NOSE GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TORQUE LINK CRACKED ON FORWARD REINFORCING WEBS						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997121100593	19971211	00593	EU  	1997	12	11	AU970298         	1	19970401	G	5712	TB101106100	RIB             			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING ROOT RIB LOWER FLANGE CORRODED IN AREA OF RIB TO LOWER WING SKIN ATTACHMENT RIVETS - AIRCRAFT OPERATES IN 	A SALT LADENENVIRONMENT AND IS NOT HANGARED					1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920	 
1997121100594	19971211	00594	CE  	1997	12	11	AU970299         	1	19970124	G	5210	10542001815	LATCH           			BEECH 	76    	76          	1153005	CE  										PASS/CREW DOOR	STICKING        	W				K				NONE                    				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) LH DOOR LATCH STICKING - SUSPECT CAUSED BY LACK OF LUBRICATION						1	L	7	2 	3O				A29CE   					 
1997121100595	19971211	00595	SW  	1997	12	11	AU970300         	1	19970324	G	5320		STRUCTURE       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STRUCTURE CRACKED  WHERE VERTICAL CONTROL TUNNEL JOINS ROOF STRUCTURE IN AREA BELOW SERVO MOUNTING - FOUN	D DURING INSPECTION IAW AD/BELL206/82					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997121100596	19971211	00596	NM  	1997	12	11	AU970301         	1	19970324	G	3240	DSC252A40230	HOSE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LT MLG BRAKE	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR BRAKE HOSE FAILED AT LOWER FITTING - LOSS OF HYDRAULIC FLUID						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997121100597	19971211	00597	NM  	1997	12	11	AU970302         	1	19970308	G	2424	CR907	DIODE           	WESTINGHOUSE	GCU         	BOEING	737   	737377      		NM  										AC REGULATOR	SHORTED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 			28822		WG436ANSETTS					(AUS) GENERATOR CONTROL UNIT FAULTY - INVESTIGATION FOUND DIODE CR907 SHORT CIRCUITED ALLOWING TRANSFORMER T901 TO OVERH	EAT					2	L	7	2 	4F			RT	A16WE   					 
1997121100598	19971211	00598		1997	12	11	AU970303         	1	19970323	G	7722	CA15000	CABLE           		SW14507     						CFMINT	CFM56 	CFM563C     	13802	EU  					ENG EGT/TIT IND	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					14507					(AUS) ENGINE FORWARD EGT EXTENSION CABLE FAILED											4	F			E21EU				 
1997121100599	19971211	00599	NM  	1997	12	11	AU970304         	1	19970130	G	5610	66193551	PIN             			BOEING	737   	737476      		NM  										NR 2 SLIDER RT	INCORRECT FIT   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 RH SLIDING WINDOW FAILED TO OPEN USING EXTERNAL RELEASE HANDLE - PIN WAS FOUND TO BE TOO SHORT						2	L	7	2 	4F			RT	A16WE   					 
1997121100600	19971211	00600	EU  	1997	12	11	AU970305         	1	19970313	G	2460	M6009336	RELAY           			FOKKER	F27   	F27MK50     		EU  										DC POWER DISTRIB	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) DC EMERGENCY BUS 1 SELECT CONTACTOR SUSPECT FAULTY						2	H	7	2 	4T			RT	A817    					 
1997121100601	19971211	00601	CE  	1997	12	11	AU970306         	1	19970120	G	5712	082217517	RIB             		082217518   	CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	LT WHEEL BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WHEEL BAY CENTRE RIB UPPER CAP CRACKED IN AREA ACROSS ALLTHREE UPPER BRACKET BOLT HOLES						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1997121100602	19971211	00602	SO  	1997	12	11	AU970307         	1	19970319	G	2752	489426	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	TE FLAP ACTUATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP ACTUATOR WORN BEYOND LIMITS						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997121100603	19971211	00603	NE  	1997	12	11	AU970308         	2	19970310	G	7230		BEARING         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENG NR 2	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 							LFO5869			(AUS) NO3 ENGINE NO2 BEARING FAILED - METAL CONTAMINATION OF OIL SYSTEM						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997121100604	19971211	00604	GL  	1997	12	11	AU970309         	3	19970402	G	6110	A1588B	SPRING          	HARTZL      	PHCJ3YF2VF  	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROP ASSEMBLY	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			1505 		ED1529			ED1529		(AUS) PROPELLER CONTAINED THE FOLLOWING DEFECTS:- 1. LATCH PNO B318 BROKEN. 2. LATCH BOLTS PNO A1595 (2OFF) SHEARED AND 	ONE BOLT BENT 3. CYLINDER PNO B2423-1 DAMAGED 4. PISTON PNO B3237 WORN 5. INCORRECT PRESSURE DECAL FITTED. PERSONNEL/MAI	NTENANCE ERROR				1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1997121100605	19971211	00605	EA  	1997	12	11	AU970310         	2	19970325	G	8520	72877	TAPPET BODY     			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					NR 3 CYL INT	BROKEN          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 			797  				L1777448A			(AUS) NO3 CYLINDER INLET VALVE TAPPET BODY BROKEN - PUSHROD TUBES LIGHTLY DISPLACED AND LEAKING OIL						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1997122900028	19971229	00028	NE  	1997	12	29	AU970311         	2	19970304	G	7250		ENGINE          								LYC   	ALF502	ALF502H     	41580	NE  					TURBINE SECTION	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							LF07007			(AUS) NO3 ENGINE VIBRATION WITH SPARKS FROM TAILPIPE - N2 SEIZED WHEN ENGINE SHUT DOWN											4	F			E6NE				 
1997121100606	19971211	00606	CE  	1997	12	11	AU970312         	1	19970211	G	2910	S2178C40150	HOSE            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HYDRAULIC, MAIN	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC HOSE FAILED AT FITTING - SUSPECT INCORRECT HOSE FITTED - UNAPPROVED PART - PERSONNEL/MAINTE	NANCE ERROR					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1997121100607	19971211	00607	EU  	1997	12	11	AU970313         	1	19970329	G	3610		SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					PNEU DISTRIB	LEAKING         	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) ANTI-ICE AIR DUCT SEALS LOCATED AT REAR END OF SPINE LEAKING -NO4 ENGINE AIR VALVE CONNECTOR.  SUSPECT MOISTURE IN	GRESS					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997121100608	19971211	00608	SW  	1997	12	11	AU970314         	1	19970324	G	7120	6250001	MOUNT           	GULSTM      	114         	GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE MOUNT SEC	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					14278		L1645948A			(AUS) ENGINE MOUNT ASSEMBLY TUBE CRACKED AT LH NLG TRUNNION - TRUNNION PIN DEFORMED - AIRCRAFT USED FOR PILOT TRAINING						1	L	7	1 	3O	3	O		A12SO   	1E4	5	C	P920	 
1997121100609	19971211	00609	CE  	1997	12	11	AU970315         	1	19970404	G	3240	0500118126	PIPE            			CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	2A34C203    	GL  	MLG BRAKE	DAMAGED         	W				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LH BRAKE LINE PUNCTURED BY `PK' TYPE SCREW FITTED FOLLOWING REPAINTING - LOSS OF BRAKE FLUID - PERSONNEL/MAINTENAN	CE ERROR					1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121100610	19971211	00610		1997	12	11	AU970316         	4	19970402	G	2562	E01	ELT             			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	EMERG LOCATOR	LOW POWER       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					014709					(AUS) ELT OUTPUT BELOW SPECIFICATION						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
1997121100611	19971211	00611	CE  	1997	12	11	AU970317         	1	19970321	G	5753	501600036	BRACKET         	BEECH       	FLAP        	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	TE FLAP STRUCTUR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					TE423					(AUS) RH FLAP ACTUATOR ATTACHMENT BRACKET CRACKED AND SEPARATED FROM FLAP AT THE CENTRE ATTACHMENT SCREW.  WHEN DOWNWARD	S PRESSURE WAS APPLIED TO THE TRAILING EDGE OF THE FLAP - INVESTIGATION FOUND APREVIOUS REPAIR UNDER THE BRACKET ALSO CR	ACKED AND THE RIB BELOWTHE REPAIR PNO 50-160012-2 CRACKED AND DEFORMED				1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997121100612	19971211	00612	SO  	1997	12	11	AU970318         	1	19970322	G	2915	D559A6D37	VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					HYDRAULIC PRESSU	FAULTY          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LH HYDRAULIC RESERVOIR AIR PRESSURE RELIEF FAULTY - SEAL DETERIORATED						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997121100613	19971211	00613	GL  	1997	12	11	AU970319         	1	19970222	G	3246		WHEEL           			AMTR  	MAXAIR	XP503       	9570746	GL  	AMTR  	582   	582         		GL  					TAIL WHEEL	SEPARATED       	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 										(AUS) TAIL WHEEL SEPARATED FROM AIRCRAFT - AIRCRAFT RAN OFF STRIP - DAMAGE TO RH WING TIP , PITOT AND RH UNDERCARRIAGE L	EG - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY					1	H	7	1 	3I	3	I	NT	EXPA1H71	EXP31				 
1997121100614	19971211	00614	GL  	1997	12	11	AU970320         	1	19970225	G	3244		TYRE            			AMTR  	JABIRU	JABIRUSK    	05602CU	GL  										LT MLG	DEFLATED        	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR TYRE FLAT - AIRCRAFT RAN OFF STRIP AND HIT A MOUND OF DIRT TEARING OFF THE FRONT WHEEL AND MO	UNTING BEFORE DIGGING THE NOSE INTO THE GROUND AND FLIPPING OVER - THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFO	RMATION ONLY				1	H	7	1 	IO			NC	EXPA1H71					 
1997121100615	19971211	00615	NM  	1997	12	11	AU970324         	1	19970216	G	2560	65B096339	FITTING         			BOEING	747   	747SP38     		NM  										EMERG EQUIP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ENTRANCE DOOR L4 GIRT BAR AFT SLIDE FITTING BROKEN						2	L	7	4 	4F			RT	A20WE   					 
1997121100616	19971211	00616	NM  	1997	12	11	AU970325         	1	19970305	G	5754		FAIRING         			BOEING	747   	747SP38     		NM  										LEADING EDGE DEV	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO7 LEADING EDGE FLAP BULLNOSE FAIRING OPERATING RODS AND HINGES BROKEN AWAY - FLAP HANGING BY BONDING STRAPS						2	L	7	4 	4F			RT	A20WE   					 
1997121100617	19971211	00617	NM  	1997	12	11	AU970326         	1	19970306	G	2752	2473T1001	MOTOR           			BOEING	747   	747438      		NM  										TE FLAP ACTUATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATE TRAILING EDGE FLAP DRIVE MOTOR FAULTY						2	L	7	4 	4F			RT	A20WE   					 
1997122900029	19971229	00029	NE  	1997	12	29	AU970327         	2	19970307	G	7240		LINER           	RROYCE      	RB211524D4  						RROYCE	RB211 	RB211524D419	54555	NE  					ENG COMB CHAMBER	BURNT           	W				K				NONE                    				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) NO3 ENGINE COMBUSTION CHAMBER OUTER LINER BURNT THROUGH IN TWO PLACES											4	F			E12EU				 
1997122900030	19971229	00030	NE  	1997	12	29	AU970328         	2	19970308	G	7240		LINER           	RROYCE      	RB211524D4  						RROYCE	RB211 	RB211524D419	54555	NE  					ENG COMB CHAMB	BURNT           	W				K				NONE                    				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) NO3 ENGINE COMBUSTION CHAMBER OUTER LINER BURNT AND HOLED IN TWO PLACES ADJACENT TO THE AFT FLANGE IN THE 3 O'CLOC	K POSITION										4	F			E12EU				 
1997121100618	19971211	00618		1997	12	11	AU970329         	4	19970311	G	2565	PN7A124836	SLIDE           			BOEING	747   	747SP38     		NM  										RT UPPER DECK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PN7A124836					(AUS) RH UPPER DECK ESCAPE SLIDE FAILED TO FULLY DEPLOY DURING TEST DUE TO THE FAILURE OF THE FUSEABLE LINKS/BOLTS TO RE	LEASE THE INFLATED SLIDE					2	L	7	4 	4F			RT	A20WE   					 
1997121100619	19971211	00619	NM  	1997	12	11	AU970330         	1	19970315	G	2560		LATCH           			BOEING	767   	767338      		NM  										ESCAPE SLIDE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OFF-WING ESCAPE SLIDE DOOR LATCHES SEIZED DUE TO LACK OF LUBRICATION AND CORROSION (RUST) ON THE CAM LATCHES						2	L	7	2 	4F			RT	A1NM    					 
1997122900031	19971229	00031		1997	12	29	AU970331         	1	19970207	G	7830	TB377	TERMINAL BLOCK  								RROYCE	RB211 	RB211524G19 		NE  					THRUST REVERSER	INCORRECT FIT   	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							13248			(AUS) NO3 ENGINE THRUST REVERSER TB377 MOD TERMINAL BLOCK INCORRECTLY FITTED RESULTING IN SHORT CIRCUITED CONNECTIONS WH	ICH IN TURN ACTIVATED A RELAY IN THE THRUST REVERSER LOCKING CONTROLS - PERSONNEL/MAINTENANCE ERROR										4	F			E30NE				 
1997121100620	19971211	00620	EA  	1997	12	11	AU970332         	2	19970409	G	8550	MS208234D	ELBOW           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT ENG OIL LINE	LOOSE           	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 							L1413751A			(AUS) LH ENGINE OIL PRESSURE LINE 45 DEGREE ELBOW FITTING LOOSE AND LEAKING - FITTING IS LOCATED ON THE CABIN HEAT EXCHA	NGER EXHAUST MANIFOLD					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1998010500021	19980105	00021	GL  	1998	1	5	AU970333         	1	19970321	G	3222	4000004	GEAR LEG        			AMTR  	EXPRES	EXPRESSFT   	056201G	GL  	LYC   	O540  	IO540N1A5   	41532	EA  	HARTZL	HCF3Y	HCF3YR1     	GL  	NLG	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR LEG FAILED						1	L	7	1 	3O	3	O	NT	EXPA1L71	1E4	5	C	P31EA	 
1997121100621	19971211	00621	CE  	1997	12	11	AU970334         	1	19970402	G	3232		BOLT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LT MLG DOOR	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR OUTBOARD DOOR ACTUATING ARM ATTACHMENT BOLT MISSING - SUSPECT SPLIT PIN WAS NOT FITTED AT LAS	T MAINTENANCE -PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
1997121100622	19971211	00622	CE  	1997	12	11	AU970335         	1	19970304	G	7110		LATCH           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENG COWLING	NOT SECURED     	W		A		K				NONE                    				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 										(AUS) RH ENGINE UPPER FRONT COWL SEPARATED FROM THE LOWER COWL AT THE FRONT LH COWL HOOK - INVESTIGATION FOUND THAT THE 	COWL HAD BEEN INCORRECTLY LATCHED - PERSONNEL/MAINTENANCE ERROR					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1997121800767	19971218	00767	WP  	1997	12	18	AU970336         	2	19970314	G	7200		ENGINE          								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE	LOW POWER       	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE LOW TORQUE DURING TAKEOFF - INVESTIGATION COULD FIND NO FAULT EXCEPT THAT WHEN THE BLEED AIR WAS TURNED 	ON THE POWER DROPPED - AIRCREW MAINTAINED BLEED AIR WAS TURNED OFF DURING TAKEOFF - NO CONCLUSIVE CAUSE COULD BE FOUND A	ND ENGINE TORQUE HAS BEEN OK SINCE									4	T			E4WE	6	C	P61GL	 
1997121800220	19971218	00220	EU  	1997	12	18	AU970337         	1	19970401	G	2710	ND45B351	ACTUATOR        			BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON ACTUATOR ROD OUTER SEGMENT BROKEN DUE TO OUTER BALLJOINT SEIZING - RH AILERON OUTER BALL JOINT ALSO SEI	ZED WITHATTACHMENT BOLT LOOSE IN BRACKET - PERSONNEL/MAINTENANCE ERROR					1	H	7	3 	3O	3	O		A29EU   	E295	5	C	P920	 
1998010500004	19980105	00004		1998	1	5	AU970338         	1	19970309	G	7722		CONNECTOR       								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	ENG. EGT/TIT IND	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RH ENGINE EGT INDICATION ERRATIC - INVESTIGATION FOUND THAT THE ENGINE FIREWALL CONNECTOR WAS CONTAMINATED WITH OI	L										4	T			E4WE	6	C	P61GL	 
1997121800221	19971218	00221	SW  	1997	12	18	AU970339         	1	19970319	G	7120	2762114081	TRUSS           			SWRNGN	SA227 	SA227AT     	8780610	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE MOUNT SEC	CRACKED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P44263			(AUS) ENGINE MOUNT ASSEMBLY CRACKED BETWEEN TWO WELDED SEAMS IN AREA OF UPPER REAR CLUSTER						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	P61GL	 
1997121800222	19971218	00222	EA  	1997	12	18	AU970340         	2	19970322	G	8520	3813	STUD            		5015        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIP ENG CYL	FRACTURED       	W				K				NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 			910  				L823761A			(AUS) LH ENGINE NO1 CYLINDER HOLDDOWN STUDS PNO 38-13 (2OFF) AND PNO50-15 (2OFF) FRACTURED - INDUCTION TUBE SEPARATED FR	OM SUMP					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997121800223	19971218	00223	CE  	1997	12	18	AU970341         	1	19970330	G	2710	NAS261064	CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	AILERON CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON CONTROL CABLE CONTAINED SEVERE CORROSION AND FRAYING IN AREA BENEATH CLAMP BETWEEN AUTOPILOT ROLL SERVO	 TO CONTROL CABLE					1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
1997121800224	19971218	00224	CE  	1997	12	18	AU970342         	1	19970409	G	2720	03101965	SPRING          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER CONTROLS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH RUDDER PEDAL RETURN SPRING BROKEN						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121800225	19971218	00225	CE  	1997	12	18	AU970343         	1	19970410	G	2720	031019612	SPRING          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER CONTROLS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH RUDDER PEDAL RETURN SPRING BROKEN						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121800226	19971218	00226		1997	12	18	AU970344         	4	19970404	G	2562	E01	ELT             																	EMERG LOCATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					017240					(AUS) ELT FAULTY - NO OPERATION																			 
1997121800227	19971218	00227		1997	12	18	AU970345         	4	19970410	G	2562	E01	ELT             																	EMERG LOCATOR	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					012344					(AUS) ELT DOES NOT CONFORM TO MANUFACTURERS SPECIFICATIONS																			 
1997121800228	19971218	00228	GL  	1997	12	18	AU970346         	3	19970407	G	6114	1A103TCM	HUB             	MCAULY      		CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROP HUB SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			400  		771094			771094		(AUS) PROPELLER HUB CRACKED THROUGH TWO BOLT HOLES - SUSPECT PROPELLER HAS NOT BEEN INSPECTED IAW AD/PFP/17 AMDT2 -PERSO	NNEL/MAINTENANCE ERROR					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997121800229	19971218	00229	EU  	1997	12	18	AU970347         	1	19970412	G	6120	6068TS4PO1	HARNESS         			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROP CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							785499	DAP0055		(AUS) LH PROPELLER CONTROL HARNESS FAULTY						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
1997121800230	19971218	00230	WP  	1997	12	18	AU970348         	1	19970329	G	2810	269A8321	VENT            	HUGHES      		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FUEL STORAGE	BLOCKED         	W				K				NONE                    				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			AU	S 					NA		L2336651			(AUS) FUEL TANK VENT BLOCKED BY MUD WASP NEST						1	G	7	1 	3O	3	O		4H12    	1E10				 
1997121800231	19971218	00231	EA  	1997	12	18	AU970349         	2	19970323	G	8520	66734	STUD            	LYC         		HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					RECIP ENG CYL	BROKEN          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			385  		L89543		L89543			(AUS) NO2 CYLINDER HOLD DOWN STUDS BROKEN - INVESTIGATION FOUND SIX CYLINDER BASE NUTS MISSING, THIRTY NUTS LOOSE AND ON	LY TWELVE NUTS TO BE TIGHT - CRANKCASE PARTING SURFACES AND CYLINDER MOUNT PADS FRETTED - NUMEROUS INTERNAL WRENCHING. C	YLINDER BASE NUTLANDS BADLY DAMAGED PREVENTING PROPER TIGHTENING OF THE NUTS -ENGINE WAS LAST OVERHAULED IN THE USA - PE	RSONNEL/MAINTENANCE ERROR			1	G	7	1 	3O	3	O		4H11    	E304				 
1997121800232	19971218	00232	GL  	1997	12	18	AU970350         	3	19970411	G	6114	E18396	HUB             			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	PROP HUB SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								E18396		(AUS) PROPELLER HUB CRACKED IN AREA OF NO1 BLADE BOLT HOLES - REWORK OF HUB REVEALED ONE MAIN CRACK APPROXIMATELY 15.875	MM (0.625IN) LONG TOGETHER WITH THREE SUB-SURFACE CRACKS APPROXIMATELY 6.35MM (0.25IN) LONG					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1997121800233	19971218	00233		1997	12	18	AU970351         	4	19970411	G	2562	E01	ELT             																	EMERG LOCATOR	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					014712					(AUS) ELT DOES NOT MEET MANUFACTURERS SPECIFICATIONS																			 
1997121800234	19971218	00234		1997	12	18	AU970352         	4	19970410	G	2562	E01	ELT             																	EMERG LOCATOR	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					17250					(AUS) ELT DOES NOT MEET MANUFACTURERS SPECIFICATIONS																			 
1997121800235	19971218	00235		1997	12	18	AU970353         	4	19970410	G	2562	E01	ELT             																	EMERG LOCATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					017244					(AUS) ELT DOES NOT MEET MANUFACTURERS SPECIFICATIONS																			 
1997121800236	19971218	00236	EU  	1997	12	18	AU970354         	1	19970403	G	2611	72111211000	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	SMOKE DETECTION	ACTIVATION      	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) CARGO COMPARTMENT SMOKE DETECTORS GIVING FALSE WARNING -INVESTIGATION FOUND NO EVIDENCE OF FIRE OR SMOKE - SUSPECT	 CAUSED BY FAILING FLUORESCENT LAMPS IN THE TOILET AREA					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997121800237	19971218	00237	CE  	1997	12	18	AU970355         	1	19970318	G	5510	17320311	BRACKET         		17320312    	CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR WEIGHT ARM REAR MOUNTING BRACKETS PNO 1732031-1 ANDPNO 1732031-2 CRACKED ON VERTICAL BENDS						1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1997121800238	19971218	00238	CE  	1997	12	18	AU970356         	1	19970316	G	2731	12600741	ACTUATOR        		12600741    	CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	2A34C203    	GL  	ELEV TAB CONTROL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB ACTUATOR SEIZED - INVESTIGATION FOUND THE ACTUATOR JACK SCREW TO BE CORRODED (RUSTY) OVER THE EN	TIRE LENGTH WITH NO EVIDENCE OF LUBRICATION - CAUSED BY A COMBINATION OF HIGH PRESSURE WASHES REMOVING GREASE FROM THE J	ACK AND OPERATIONS IN A COASTAL ENVIRONMENT				1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121800239	19971218	00239	CE  	1997	12	18	AU970357         	1	19970409	G	5210	20394254013	HOOK            		2039        	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PASS/CREW DOOR	BROKEN          	W				K				NONE                    				O	J	D	OTHER                     	WARNING INDICATION        	INFLIGHT SEPARATION       	CL	CLIMB          	1			AU	S 										(AUS) LARGE CABIN DOOR TOP LOCKING HOOK FAILED						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997121800240	19971218	00240	SO  	1997	12	18	AU970358         	2	19970414	G	8520	63026143	ROLLER          	CONT        	COUNTERWEIGH						CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	RECIP ENG SHAFT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							353396			(AUS) CRANKSHAFT COUNTERWEIGHT ROLLERS WORN UNEVENLY											3	O			E1CE	5	C	P920	 
1997121800241	19971218	00241	CE  	1997	12	18	AU970359         	1	19970315	G	3246	LM67010	BEARING         		LM67048     	CESSNA	182   	182Q        	2072732	CE  						MCAULY	2A34C	2A34C203    	GL  	WHEEL/SKI/FLOAT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE AND MAIN WHEEL BEARINGS SEIZED - ALL BEARINGS WERE DRY AND THE LITTLE GREASE REMAINING WAS ALSO HARD AND DRY 	- SUSPECT CAUSED BY USE OF HIGH PRESSURE WATER DURING PAINT STRIPPING					1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
1997121800242	19971218	00242	CE  	1997	12	18	AU970360         	1	19970404	G	2410	632436	NUT             	PRESTOLITE  	ALTERNATOR  	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GEN-ALT DRIVE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			581  		6L000106		292183R			(AUS) ALTERNATOR DRIVE CLUTCH ASSEMBLY SEPARATED FROM ALTERNATOR DUE TO FAILURE OF THE SLOTTED HOLDING NUT - DAMAGE TO E	NGINE GEARS AND CRANKCASE ASSEMBLY - METAL CONTAMINATION OF ENGINE					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
1997121800243	19971218	00243	EU  	1997	12	18	AU970361         	1	19970408	G	3222	6846005	TUBE            			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NOSE/TAIL GEAR	FRACTURED       	W				K				NONE                    				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 			432  							(AUS) NOSE LANDING GEAR STRUT INNER TUBE FRACTURED APPROXIMATELY 203MM(8IN) FROM THE TOP- INNER TUBE APPEARS TO HAVE BEE	N SILVERSOLDERED AROUND THE POINT OF FRACTURE BY UNKNOWN PERSONS -PERSONNEL/MAINTENANCE ERROR - UNAPPROVED REPAIR					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1997121800244	19971218	00244	NM  	1997	12	18	AU970362         	1	19970307	G	3320	65B115210	LIGHT           			BOEING	747   	747338      		NM  										PASS COMPART	SMOKING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) CABIN SIDEWALL LIGHTING SYSTEM LIGHT TUBE TOMBSTONE LOCATED ATSEAT POSITION 30ABC SMOULDERING						2	L	7	2 	4F			RT	A20WE   					 
1997121800245	19971218	00245	NM  	1997	12	18	AU970363         	1	19970324	G	2550		CONTAINER       			BOEING	767   	767338      		NM  										CARGO COMPART	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			DE	DESCENT        	1			AU	S 										(AUS) CARGO CONTAINERS (4OFF) IN AFT CARGO HOLD FORWARD OF THE CARGO HOLD DOOR WERE UNLOCKED ALLOWING MOVEMENT OF THE CO	NTAINERS - INVESTIGATION FOUND LOCKS TO BE SERVICEABLE - FLOOR LOCKS AT POSITIONS 41L AND 41R WERE NOT RAISED - PERSONNE	L/MAINTENANCE ERROR				2	L	7	2 	4F			RT	A1NM    					 
1997121800246	19971218	00246		1997	12	18	AU970364         	4	19970330	G	2310	65B4051227	ANTENNA         			BOEING	747   	747SP38     		NM  										HF COMMUNICATION	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 										(AUS) LH HF ANTENNA BROKE OFF						2	L	7	4 	4F			RT	A20WE   					 
1997121800247	19971218	00247	NM  	1997	12	18	AU970365         	1	19970322	G	3244		TYRE            			BOEING	747   	747438      		NM  										MLG NR 9	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RH BODY LANDING GEAR NO9 TYRE TREAD SEPARATED - INVESTIGATION FOUND THE CARCASS TO BE INTACT AND STILL INFLATED - 	MINOR DAMAGETO DOOR ROD AND FIRE DETECTION WIRE					2	L	7	4 	4F			RT	A20WE   					 
1997121800248	19971218	00248	NE  	1997	12	18	AU970366         	2	19970407	G	7261	781142	PIPE            	PWA         	JT9D7R4     						PWA   	JT9   	JT9D7R4D    	52054	NE  					TURBINE ENG OIL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					716931					(AUS) ENGINE MAIN OIL SUPPLY PIPE WORN THROUGH BY CHAFING ON `J' FLANGE BOLT HEADS											4	F			E3NE				 
1997121800249	19971218	00249	NM  	1997	12	18	AU970367         	1	19970406	G	2560	342	COVER           		7A112718    	BOEING	747   	747238B     	1384828	NM  										ESCAPE SLIDE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					342					(AUS) RH NO3 MAIN ENTRY DOOR SLIDERAFT COVER MATERIAL TORN ALLOWING THE SLIDE PACK TO FALL FROM THE PACKBOARD - COVER MA	TERIAL WAS IN POOR CONDITION WITH EVIDENCE OF MOULD ON THE SURFACES					2	L	7	4 	4F				A20WE   					 
1997121800250	19971218	00250	CE  	1997	12	18	AU970369         	1	19970331	G	2460	9036102334	DEVICE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					DC POWER DISTRIB	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) HALL EFFECT DEVICE FOR BATTERY BUS TIE RELAY FAULTY						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997121800251	19971218	00251	CE  	1997	12	18	AU970370         	1	19970315	G	5320	805030	CLIP            		805031      	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					BULKHEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CLIPS ATTACHING CHANNEL TO STRINGERS AT REAR PRESSURE BULKHEAD CRACKED ON LH SIDE - CLIP PNO 8050-30, PNO 8050-31,	 PNO 8050-32,PNO 8050-33 AND PN0 8050-36					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997121800252	19971218	00252	GL  	1997	12	18	AU970371         	3	19970319	G	6111		BLADE           	MCAULY      		CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER BLADE	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			691  		721730		149313VO	721730		(AUS) INCORRECT PROPELLER BLADES FITTED TO PROPELLER - BLADES FITTED ARE NOT THE BLADES LISTED IN THE LOG BOOK - REDUCED	 DIAMETER PROPELLER FITMENT NOT RECORDED - PROPELLER BLADE ANGLES VARIED BETWEEN BLADES - BLADE PROFILE INCORRECT - NO2 	BLADE ACTUATING PIN DRILLING OUT OF TOLERANCE - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010500005	19980105	00005	NE  	1998	1	5	AU970372         	2	19970411	G	7230		COMPRESSOR      								LYC   	ALF502	ALF502H     	41580	NE  					TURBINE ENG COMP	VIBRATION       	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							7052			(AUS) ENGINE CONTINUED TO WINDMILL FOR APPROXIMATELY 30 MINUTES AFTER BEING SHUT DOWN FOR HIGH VIBRATIONS - SUSPECT VIBR	ATIONS CAUSED BY ICE FORMATION ON THE FAN										4	F			E6NE				 
1998010500006	19980105	00006	NE  	1998	1	5	AU970373         	2	19970413	G	7230		BEARING         								LYC   	ALF502	ALF502H     	41580	NE  					TURBINE ENG COMP	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							7051			(AUS) NO2 ENGINE NO2 BEARING SUSPECT FAILED - METAL CONTAMINATION OF OIL SYSTEM											4	F			E6NE				 
1997121800253	19971218	00253	CE  	1997	12	18	AU970374         	1	19970407	G	2460	727725	CIRCUIT BREAKER 			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	DC POWER DISTRIB	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR RELAY CIRCUIT BREAKER FAILED						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1997121800254	19971218	00254	CE  	1997	12	18	AU970375         	1	19970416	G	5711	351100611	SPAR            			BEECH 	33    	E33         	1151422	CE  	CONT  	O470  	IO470K      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	WING SPAR STRUCT	INCORRECT REPAIR	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING SPAR INCORRECTLY REPAIRED IN AREA BETWEEN STA 136.188 ANDSTA 148.875 - CORROSION HAD BEEN REMOVED FROM THE	 SPAR CAP TO A DEPTH OF 2.6162MM BY 50.8MM WIDE BY 26.9MM LONG (0.103IN DEEP BY2.0IN WIDE BY 1.060IN LONG) - REPAIR HAD 	BEEN CARRIED OUT THROUGH THICKNESS OF LEADING EDGE SKIN WITH RIVETS GROUND OFF - REPAIR WAS ALSO POORLY FINISHED OFF WIT	H FILLER - REPAIR HAS NOT BEEN CARRIED OUT TO DIMENSIONS SPECIFIED IN ENGINEERING ORDER -PERSONNEL/MAINTENANCE ERROR			1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
1997121800255	19971218	00255	CE  	1997	12	18	AU970376         	1	19970414	G	2460	70243	LOOM            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	INST PANEL	MIS ROUTED      	W				K				NONE                    				O	F		OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 					70243					(AUS) WIRING LOOM BEHIND INSTRUMENT PANEL INTERFERING WITH CORRECT OPERATION OF ELEVATOR CONTROL IN THE `FULL UP' POSITI	ON - AILERON CHAIN TO AILERON CABLE ATTACHMENT LOCKING SPLIT PIN HAD ONE LEG BROKEN OFF AND DAMAGED INTERCOM WIRING					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121800256	19971218	00256	EA  	1997	12	18	AU970377         	2	19970415	G	7313		INJECTOR        	LYC         		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					FUEL INJECT NO 2	BLOCKED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							L520261A			(AUS) NO2 FUEL INJECTOR NOZZLE PARTIALLY BLOCKED BY UNKNOWN FOREIGN MATTER						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997121800257	19971218	00257	CE  	1997	12	18	AU970378         	1	19970325	G	2710		TURNBUCKLE      			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	AILERON CONTROL	FOULED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 										(AUS) LH REAR AILERON CABLE TURNBUCKLE BETWEEN LH REAR AILERON CABLE PNO 5815103-26 AND BELLCRANK PNO 5815114-1 INTERMIT	TENTLY CATCHING ON FLOOR SUPPORT BRACKET					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1998010500007	19980105	00007	WP  	1998	1	5	AU970379         	2	19970418	G	7322	89711014	FCU             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL CONT	MALFUNCTIONED   	W				K				NONE                    				E	M		VIBRATION/BUFFET          	OVER TEMP                 		DE	DESCENT        	1			AU	S 			3447 		A727C		P31378			(AUS) ENGINE FUEL CONTROL UNIT SUSPECT FAULTY - ENGINE SURGED AND EGT REACHED APPROXIMATELY 520 DEGREES C (OVERTEMP) - A	N HOT END INSPECTION WAS CARRIED OUT WITH NO MAJOR DAMAGE FOUND					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
1997121800258	19971218	00258	EU  	1997	12	18	AU970380         	1	19970214	G	3244	769	TYRE            			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	TIRE	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					769		L2398840A	A43934		(AUS) RH MAIN LANDING GEAR TYRE AND WHEEL UNSERVICEABLE.						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800259	19971218	00259		1997	12	18	AU970381         	4	19970220	G	3457	CI158C2	ANTENNA         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	GLOBAL POSITION	FAILED          	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		IN	INSP/MAINT     	1			AU	S 										(AUS) GPS ANTENNA SHEARED OFF FLUSH WITH MOUNT BASE						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
1997121800260	19971218	00260	SO  	1997	12	18	AU970382         	2	19970414	G	8520	639292	SPLIT PIN       	CONT        		MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360G    	17025	SO  					RECIP ENG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			101  		309723		309723			(AUS) NO4 AND NO5 CONNECTING RODS BOTH HAD ONE MISSING SPLIT PIN. PIECES OF SPLIT PIN FOUND IN OIL SYSTEM AND UNDER OIL 	PRESSURE RELIEF VALVE. INVESTIGATION AND MEASUREMENTS FOUND THAT UNDER CERTAIN CIRCUMSTANCES THE SPLIT PIN CAN CONTACT T	HE CYLINDER SKIRT.				1	L	7	1 	3O	3	O		2A3     	E9CE				 
1997121800261	19971218	00261	SW  	1997	12	18	AU970383         	1	19970107	G	5741	201751	ANGLE           			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	22D	22D40       	NE  	WING ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH INBOARD AND OUTBOARD WING ATTACHMENT ANGLES CRACKED IN THE AREA OF THE TOP RADIUS - CRACK LENGTHS 20MM TO 25MM 	BY 1MM DEEP (0.787IN TO 0.98IN BY 0.039IN DEEP) - CRACKING WAS FOUND WITH THE NAKED EYE AND CONFIRMED BY DYE PENETRANT					1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P736	 
1997121800262	19971218	00262	NM  	1997	12	18	AU970384         	1	19970407	G	3213	10100105	STRUT           	MESSIER     		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					DCL03584					(AUS) RH MAIN LANDING GEAR SHOCK STRUT OVEREXTENDED CAUSING TORQUE LINKS TO OVERCENTRE - SUSPECT CAUSED BY FAILURE OF OL	EO EXTENSION STOPS OR DAMPER RING					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997121800263	19971218	00263	CE  	1997	12	18	AU970385         	1	19970227	G	2822	2B729	PUMP            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FUEL BOOST PUMP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			22   							(AUS) ELECTRICAL BOOST PUMP FAULTY - INVESTIGATION FOUND CHIPPED VANE WHICH CAUSED IMPELLER UNBALANCE AND WEAR TO THE VA	NES AND PUMP CAVITY					1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
1997121800264	19971218	00264	CE  	1997	12	18	AU970386         	1	19970415	G	7330	580010729	LINE            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENG FUEL IND	FRACTURED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LH ENGINE TURBOCHARGER PRESSURE DISCHARGE SENSE LINE FRACTURED AT END FITTING						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997121800265	19971218	00265	CE  	1997	12	18	AU970387         	1	19970409	G	2913	M710501	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	HYDRAULIC PUMP	SHORTED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					293					(AUS) HYDRAULIC POWER PACK ELECTRIC MOTOR COMMUTATOR SHORT CIRCUITED						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE	 
1997121800266	19971218	00266	SO  	1997	12	18	AU970388         	1	19970224	G	2823	755837	O-RING          	SCOTT       	492189      	PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	FUEL SELECTOR	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH FUEL SELECTOR VALVES HAD DETERIORATED SPOOL VALVE `O' RING SEALS						1	L	7	2 	3O				A7SO    		5	C	P920	 
1997121800267	19971218	00267	CE  	1997	12	18	AU970389         	1	19970307	G	5751	122005212	HINGE           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	AIL STRUCTURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AILERON HINGE ATTACHMENT ANGLE CRACKED FROM BOTTOM RELIEF NOTCH - CRACK LENGTH APPROXIMATELY 6.35MM (0.25IN)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997121800268	19971218	00268		1997	12	18	AU970390         	4	19970305	G	2565	1747	SLIDE           			BOEING	737   	737376      		NM  										ESCAPE SLIDE	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					1747					(AUS) DOOR 2R ESCAPE SLIDE GROUND MAINTENANCE SAFETY PIN FOUND INSTALLED IN ACTUATION MECHANISM - PERSONNEL/MAINTENANCE 	ERROR					2	L	7	2 	4F			RT	A16WE   					 
1998010500008	19980105	00008	EU  	1998	1	5	AU970391         	1	19970418	G	5610	115G260024	GUIDE           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FLIGHT COMPART	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CANOPY RH AFT GUIDE BLOCK SPLIT						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
1997121800269	19971218	00269	SO  	1997	12	18	AU970392         	2	19970224	G	8520	652541	NUT             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	RECIP ENG CYL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							284172R			(AUS) NO6 CYLINDER LOWER FORWARD THROUGH BOLT NUT CRACKED DUE TO CADMIUM EMBRITTLEMENT						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
1997121800270	19971218	00270	EU  	1997	12	18	AU970393         	2	19970330	G	7310	580	VALVE           								CFMINT	CFM56 	CFM563C     	13802	EU  					ENGINE FUEL DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			9287 		580					(AUS) NO1 ENGINE FUEL VALVE REMAINED CLOSED WITH THE START LEVER AT IDLE - INVESTIGATION FOUND FUEL VALVE ACTUATOR BRUSH	ES WORN WITH SOME CARBON AND SWARF IN THE BRUSH AREA										4	F			E21EU				 
1997121800271	19971218	00271	SW  	1997	12	18	AU970394         	1	19970417	G	5311	310032509	FRAME           			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUSELAGE MAIN FR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FUSELAGE FRAME CRACKED - FOUND DURING INSPECTION IAW AD/AC/93						1	H	7	2 	3O	3	O		6A1     	1E4				 
1997121800272	19971218	00272	SW  	1997	12	18	AU970395         	1	19970417	G	5730	17004569	SKIN            		170045321   	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					WING PLATES/SKIN	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			809  							(AUS) LH WING LOWER SKINS PNO170045-69 AND PNO 170045-321 CRACKED IN AREA OF CUTOUTS - INVESTIGATION FOUND THAT WING SKI	NS FITTED ON 25/2/96 HAD BEEN MACHINED BEYOND LIMITS BEFORE FITMENT - FOUND DURING INSPECTION IAW AD/AC/92 - PERSONNEL/M	AINTENANCE ERROR				1	H	7	2 	3O	3	O		6A1     	1E4				 
1998010500009	19980105	00009	EU  	1998	1	5	AU970396         	1	19970103	G	2700	NO11492NO21	COMPUTER        			AIRBUS	320   	A320212     		EU  										FLIGHT CONTROLS	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					NO11492NO21					(AUS) NO1 AND NO2 ELAC (ELEVATOR/AILERON COMPUTER) FAULTY - WORKSHOP TESTING FOUND FAULTS WITH BOTH COMPUTERS BUT COULD 	NOT CONFIRM THAT THE FAULTS CONTRIBUTED TO THE FAILURES					2	L	7	2 	4F			RT	A28NM   					 
1997121800273	19971218	00273	SW  	1997	12	18	AU970397         	1	19970217	G	6310	212040176101	BOOT            	BELL        	DRIVESHAFT  	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE/TRANS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					42002410					(AUS) ENGINE TO TRANSMISSION DRIVESHAFT BOOT ASSEMBLY FAILED FOR APPROXIMATELY 50% OF CIRCUMFERENCE						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1997121800274	19971218	00274	GL  	1997	12	18	AU970398         	3	19970401	G	6111	IA101	BLADE           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER BLADE	FAILED          	W				K				NONE                    				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CR	CRUISE         	1			AU	S 								G10202		(AUS) SECTION OF PROPELLER BLADE SEPARATED - APPROXIMATELY 279.4MM(11IN) OF BLADE TIP SEPARATED - AIRCRAFT IS USED FOR C	ATTLE MUSTERING FROM UNSEALED STRIPS - EVIDENCE OF STONE DAMAGE ON BLADES					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1997121800275	19971218	00275	SO  	1997	12	18	AU970399         	1	19970407	G	5711	6205401	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  										WING SPAR STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING REAR SPAR CORRODED IN ROOT AREA BENEATH STEEL ATTACHMENT BRACKET						1	L	7	1 	3O				2A13    					 
1997121800276	19971218	00276	EU  	1997	12	18	AU970400         	1	19970214	G	5343	769	DOUBLER         			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LANDING GEAR ATT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					769		L2398840A	A43934		(AUS) LH AND RH MAIN LANDING GEAR UPPER LEG SUPPORT REAR DOUBLERS CRACKED. SEE MDR 97/0380 FOR ADDITIONAL INFORMATION						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800277	19971218	00277	EU  	1997	12	18	AU970401         	1	19970214	G	5500	769	BEARING         			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	EMPENNAGE STRUCT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					769		L2398840A	A43934		(AUS) FLIGHT CONTROL BEARINGS AND HINGES UNSERVICEABLE. SEE MDR 97/0380 FOR ADDITIONAL INFORMATION						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800278	19971218	00278	SO  	1997	12	18	AU970402         	1	19970407	G	5342	6264504	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  										STAB ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILISER FITTING BRACKET CORRODED BETWEEN BRACKET AND SKIN						1	L	7	1 	3O				2A13    					 
1997121800279	19971218	00279	EU  	1997	12	18	AU970403         	1	19970214	G	5753	769	FLAP            			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	TE FLAP STRUCTUR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					769		L2398840A	A43934		(AUS) FLAPS IN NEED OF MAJOR REPAIR. SEE MDR 97/0380 FOR ADDITIONAL INFORMATION						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800280	19971218	00280	EU  	1997	12	18	AU970404         	1	19970214	G	5751	769	AILERON         			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON STRUCTUR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					769		L2398840A	A43934		(AUS) AILERON IN NEED OF MAJOR REPAIR. SEE MDR 97/0380 FOR ADDITIONAL INFORMATION						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800281	19971218	00281	EU  	1997	12	18	AU970405         	1	19970214	G	5520	769	ELEVATOR        			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEV STRUCTURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					769		L2398840A	A43934		(AUS) LH ELEVATOR CRACKED. SEE MDR 97/0380 FOR ADDITIONAL INFORMATION						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800282	19971218	00282	EU  	1997	12	18	AU970406         	1	19970214	G	5310	769	STRUCTURE       			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUSELAGE STRUCTU	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					769		L2398840A	A43934		(AUS) AIRCRAFT STRUCTURE CONTAINED LARGE AMOUNTS OF CORROSION. FOUND DURING UNSCHEDULED INSPECTION IAW AD/BN-2/53. SEE M	DR 97/0380 FOR ADDITIONAL INFORMATION					1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997121800283	19971218	00283	SO  	1997	12	18	AU970407         	1	19970407	G	5342	6245100	FITTING         			PIPER 	PA28  	PA28140     	7102802	SO  										STAB ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FIN ATTACHMENT PLATE BRACKETS CORRODED - TWO OF THE FIVE PLATE ATTACHMENT RIVETS WERE ALSO CORRODED AWAY						1	L	7	1 	3O				2A13    					 
1997121800284	19971218	00284	CE  	1997	12	18	AU970408         	1	19970422	G	5743	951100206	ADAPTER         	BEECH       	951100206   	BEECH 	60    	60          	1153602	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NSN					(AUS) LANDING GEAR ATTACHMENT BRACKET CRACKED						1	L	7	2 	3O	3	O		A12CE   	E10EA	5	C	P31EA	 
1997121800285	19971218	00285	EA  	1997	12	18	AU970409         	2	19970407	G	8520	L4926027A	CRANKCASE       	LYC         		PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320B2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	RECIP ENG CASE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L4926027A		L4926027A			(AUS) ENGINE CRANKCASE TUNNEL OUT OF LIMITS - CAMSHAFT LOBES WORN						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
1997121800286	19971218	00286	NE  	1997	12	18	AU970410         	2	19970404	G	7250	2121100R73	NOZZLE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE SECTION	DAMAGED         	W		A		K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			5981 				LF05505A			(AUS) NO3 ENGINE SECOND STAGE TURBINE BLADES (3OFF) HAD APPROXIMATELY ONE THIRD OF THE BLADE MISSING AND THREE MORE BLAD	ES WITH APPROXIMATELY ONE QUARTER OF THE BLADE MISSING - INVESTIGATION FOUND THAT THE SECOND STAGE TURBINE NOZZLE REAR I	NNER SHROUD WAS CRACKED ALLOWING THE SHROUD TO RUB ON THE SECOND STAGE TURBINE DISC				2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997121800287	19971218	00287	NM  	1997	12	18	AU970411         	1	19970408	G	2520		SEAT            			BOEING	737   	737377      		NM  										PASS COMPART	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEATS 8A AND 8G BLOCKING OFF EMERGENCY EXIT WHEN IN UPRIGHT POSITION DUE TO WEAR						2	L	7	2 	4F			RT	A16WE   					 
1997121800288	19971218	00288	NM  	1997	12	18	AU970412         	1	19970119	G	7722		EGT SYSTEM      			BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					ENG. EGT/TIT IND	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) NO2 ENGINE TGT INDICATIONS ABOVE 1000 DEGREES ON TWO OCCASIONS BEFORE FALLING TO ZERO DEGREES - INTERFACE AND LOWE	R ELECTRICAL COUPLING AS WELL AS INDICATOR WERE CHANGED - INVESTIGATION OF INDICATION SYSTEM COULD FIND NO FAULTS					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
1997121800289	19971218	00289	NM  	1997	12	18	AU970413         	1	19970125	G	7722		EGT SYSTEM      			BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					ENG. EGT/TIT IND	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NO2 ENGINE EGT SYSTEM FAULTY						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
1997121800290	19971218	00290	SO  	1997	12	18	AU970414         	1	19970421	G	2822	2C2720H	PUMP            			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL BOOST PUMP	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 					2AB10					(AUS) LH MAIN FUEL BOOST PUMP FAILED						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997121800291	19971218	00291	NE  	1997	12	18	AU970415         	2	19970326	G	7260	408218016	GEAR            	LYC         		BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					TURB ENG ASSORY	FAILED          	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					W83K001		LE47028			(AUS) NO1 ENGINE ACCESSORY GEARBOX MODULE TORQUEMETER GEAR ASSEMBLY DAMAGED - GEAR HAD SHEARED THE HEAD OFF ONE OF THE E	IGHT BOLTS USED TO HOLD THE ASSEMBLY TOGETHER - TORQUEMETER PISTON HAD WORN A GROOVE IN THE HOUSING - METAL CONTAMINATIO	N OF ENGINE OIL SYSTEM				1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1997121800292	19971218	00292	SO  	1997	12	18	AU970417         	2	19970221	G	8530		CYLINDER        	CONT        		BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	RECIP ENG	GLAZED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) ENGINE CYLINDERS GLAZED - VALVE GUIDES WORN - NO2 CYLINDER ALSO CONTAINED A BROKEN OIL CONTROL RING - AIRCRAFT HAD	 NOT BEEN OPERATATED FOR SEVERAL YEARS AND IT IS SUSPECTED THAT THE ENGINES HAD NOT BEEN INHIBITED IN ANY WAY					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997121800293	19971218	00293	SO  	1997	12	18	AU970418         	2	19970410	G	8520	112536R	CRANKSHAFT      	CONT        		CESSNA	206   	P206B       	2073309	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	RECIP ENG SHAFT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					112536R		112536R	725001		(AUS) ENGINE CRANKSHAFT FAILED FROM CRACKING AT THE REAR FILLET RADIUS OF NO2 MAIN BEARING JOURNAL DUE TO FRICTION FROM 	CONTACT WITH THE BEARING SHELLS					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997121800294	19971218	00294	SO  	1997	12	18	AU970419         	1	19970415	G	3230	4085400	PIPE            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	GEAR RETRACT	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC PRESSURE PIPE FRACTURED AROUND FLARE						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997121800295	19971218	00295	CE  	1997	12	18	AU970420         	1	19970409	G	3260	20700291	SWITCH          			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	GEAR POSITION	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWN MICROSWITCH WIRE BROKEN OFF						1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1997121800296	19971218	00296	NM  	1997	12	18	AU970421         	1	19970412	G	4920	38420722	TURBINE         	GARRTT      	GTCP85      	BOEING	737   	737376      		NM  										APU CORE ENGINE	FAILED          	W		A		K	H			NONE                    	DEACTIVATE SYST/CIRCUITS			E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			3257 		P115					(AUS) APU FAILED - DEBRIS EXITING FROM EXHAUST - INVESTIGATION FOUNDTHAT THE TURBINE WHEEL AND SHAFT ASSEMBLY FAILED AND	 HUB SEPARATED DUE TO `HAFNIUM INCLUSION'					2	L	7	2 	4F			RT	A16WE   					 
1997121800297	19971218	00297	NM  	1997	12	18	AU970422         	1	19970416	G	2782	1360	ACTUATOR        			BOEING	737   	737476      		NM  										LE FLAP ACTUATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1360					(AUS) NO5 LEADING EDGE SLAT ACTUATOR EYE END BROKEN - SUSPECT CAUSED BY CORROSION PITTING						2	L	7	2 	4F			RT	A16WE   					 
1997121800298	19971218	00298	NM  	1997	12	18	AU970423         	1	19970120	G	5610		WINDOW          			BOEING	747   	747312      	1384932	NM  										FLIGHT COMPART	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) COCKPIT WINDOW R3 LOCATED BEHIND FIRST OFFICER DELAMINATED AND THEN CRACKED						2	L	7	4 	4F			RT	A20WE   					 
1998010500010	19980105	00010	NE  	1998	1	5	AU970424         	2	19970317	G	7230		DIFFUSER        			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					TURB ENG COMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P715107			(AUS) NO1 ENGINE NO6 MOUNTING BOSS LOCATED ON THE DIFFUSER CASE CRACKED ON RH SIDE. CRACK LENGTH 4.762MM (0.1875IN). FOU	ND DURING EDDY CURRENT INSPECTION.					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1997121800299	19971218	00299	NM  	1997	12	18	AU970425         	1	19970318	G	5330		SKIN            			BOEING	747   	747312      	1384932	NM  										FUSELAGE MAIN PL	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SECTION 41 RHS SKIN PANELS DEBONDING IN TWO AREAS.						2	L	7	4 	4F			RT	A20WE   					 
1998010700002	19980107	00002	NE  	1998	1	7	AU970426         	2	19970319	G	7250		BLADE           			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P715154			(AUS) NO3 ENGINE FIRST STAGE TURBINE BLADE BROKEN AT MID SPAN. INVESTIGATION FOUND 30% OF BLADES HAD BULLSEYE EROSION ON	 THE CONCAVE SIDE. FOUND DURING BOROSCOPE INSPECTION.					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1997121800300	19971218	00300	CE  	1997	12	18	AU970428         	1	19970426	G	3260	S21121	STRIKER         			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	GEAR POSITION	CRACKED         	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR MICROSWITCH STRIKER ARM CRACKED AND SEPARATED FROM SWITCH						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
1997121800301	19971218	00301		1997	12	18	AU970429         	4	19970421	G	2561	51001	VALVE           	EAAEROMARINE	LIFEJACKET  															LIFE JACKET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4228342244					(AUS) LIFEJACKET MANIFOLD VALVE CRACKED. FOUND DURING PRESSURE TESTING. THE LIFEJACKET WAS MANUFACTURED IN 1989.																			 
1997121800302	19971218	00302	NM  	1997	12	18	AU970430         	1	19970316	G	5102		MANIFOLD        			RAVEN 	RX7   	RX7         	7480503	NM  										BALLOON REPORTS	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 			126  							(AUS) BALLOON PROPANE GAS TANK MANIFOLD FAILED AT BRASS NIPPLE - LOSS OF PROPANE GAS INTO ATMOSPHERE (POTENTIAL FIRE/EXP	LOSION HAZARD)- CAUSED BY EXTENSION OF FITTING AND ADDITION OF QUICK DISCONNECT COUPLING OUTSIDE THE COWL OF THE LP GAS 	CYLINDER PLACING A LOAD ON THE FITTING - PERSONNEL/MAINTENANCE ERROR				1	B	0	6 	O 			O	A15CE   					 
1997121800303	19971218	00303	NE  	1997	12	18	AU970433         	2	19970423	G	7260		GEARBOX         			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	TURB ENG ASSORY	MAKING METAL    	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							PCE56012			(AUS) ENGINE ACCESSORY GEARBOX CONTAMINATED WITH WHITE METAL SLIVERS						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997121800304	19971218	00304	CE  	1997	12	18	AU970434         	1	19970428	G	5730		SKIN            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	WING PLATES/SKIN	MIS REPAIR      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT HAS EVIDENCE OF WING SKIN REPLACEMENT AS WELL AS DISASSEMBLY OF AILERONS, FLAPS, TAILPLANE AND HORIZONTAL	 STABILISER - REPAIR WORK IS OF SUB-STANDARD QUALITY - NO EVIDENCE OF REPAIR WORK IN LOG BOOK - PERSONNEL/MAINTENANCE ER	ROR -UNAPPROVED REPAIR				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121800305	19971218	00305	EA  	1997	12	18	AU970436         	2	19970410	G	8530	LW16740	VALVE           	LYC         	O320H2AD    						LYC   	O320  	O320H2AD    	41508	EA  					RECIP ENG EXH	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) WHEN FITTING A NEW CYLINDER KIT TO THE ENGINE IT WAS FOUND THAT THE INCORRECT EXHAUST VALVE WAS FITTED TO THE CYLI	NDER - EXHAUST VALVE PNO LW16740 (ANGLE VALVE CYLINDER) WAS FITTED INSTEAD OFTHE CORRECT PNO LW19001 - PERSONNEL/MAINTEN	ANCE ERROR - UNAPPROVED PART									3	O			E274				 
1997121800306	19971218	00306	SO  	1997	12	18	AU970437         	2	19970422	G	8540	239168R	GEAR            	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIP ENG	DAMAGED         	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 					239168R		239168R			(AUS) ENGINE STARTER ADAPTER GEAR TEETH MISSING - CRANKCASE GEAR AND CAMSHAFT CLUSTER GEAR TEETH ALSO MISSING - DAMAGE A	LSO TO LH AND RH MAGNETO ADAPTER PLATES AND LH AND RH MAGNETO DRIVE GEARS					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1997121800307	19971218	00307	SO  	1997	12	18	AU970438         	1	19970418	G	2913	OAS29303	POWER PACK      	OZONE       	OAS29303    	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					HYDRAULIC PUMP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					634					(AUS) HYDRAULIC POWER PACK FAULTY - SUSPECT INTERNAL LEAK						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997121800308	19971218	00308	EA  	1997	12	18	AU970439         	2	19970424	G	7414	D4RN3000	MAGNETO         	BENDIX      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MAGNETO/DISTRIBU	FAILED          	W				K				NONE                    				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CR	CRUISE         	1			AU	S 					86080151		L823176			(AUS) MAGNETO FAILED						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997121800309	19971218	00309	WP  	1997	12	18	AU970440         	2	19970425	G	7322	8974575	VALVE           	GARRTT      		FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FUEL CONTROL	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			607  		88082651879		P70208	940963		(AUS) LH ENGINE TEMPERATURE LIMITER BYPASS VALVE FAULTY						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997121800310	19971218	00310	SO  	1997	12	18	AU970441         	2	19970407	G	8530	350027	CYLINDER        	CONT        		CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	RECIP ENG CYL	CRACKED         	W				K				NONE                    				O	E	K	OTHER                     	VIBRATION/BUFFET          	FLUID LOSS                	IN	INSP/MAINT     	1			AU	S 					350027		350027			(AUS) NO4 CYLINDER CRACKED IN AREA BEHIND ROCKER COVERS - OIL LEAK						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
1997121800768	19971218	00768	SO  	1997	12	18	AU970442         	2	19970407	G	8520	6419441048	BOLT            	CONT        		CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	RECIP ENG CASE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					350027		350027			(AUS) ENGINE CRANKCASE THROUGH BOLTS (2OFF) SHEARED - TWO OPPOSITE SIDE THROUGH BOLTS LOOSE						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
1997121800769	19971218	00769	EA  	1997	12	18	AU970443         	2	19970428	G	8530		VALVE           	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENG EXH NR 1	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L83868A			(AUS) RH ENGINE NO1 CYLINDER EXHAUST VALVE FAILED - DAMAGE CAUSED TO PISTON AND CYLINDER HEAD - PART OF VALVE ALSO PASSE	D THROUGH THETURBOCHARGER TURBINE - NO3 CYLINDER EXHAUST VALVE ALSO CRACKED					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997121800770	19971218	00770	NE  	1997	12	18	AU970444         	2	19970414	G	7210	CP6B1208	BEARING         	PWA         		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENG RED GR BOX	SPALLED         	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					CP6B1208		162009262180			(AUS) ENGINE REDUCTION GEARBOX HAD EXCESSIVE METAL CONTAMINATION - CHIP DETECTOR LIGHT ILLUMINATED - INVESTIGATION FOUND	 LH AND RH NO10 BEARINGS SPALLED					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1998010500022	19980105	00022	WP  	1998	1	5	AU970445         	2	19970429	G	7320	8974768	COMPENSATOR     			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENG EGT	LOOSE           	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							P31374C			(AUS) LH ENGINE EGT COMPENSATOR CONNECTOR PLUG LOOSE AND CORRODED						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
1997121800771	19971218	00771	SO  	1997	12	18	AU970446         	1	19970219	G	2434		SUPPRESSOR      			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	DC GENERATOR-ALT	SEPARATED       	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) ALTERNATOR SUPPRESSOR SEPARATED FROM ALTERNATOR - SUPPRESSOR CONNECTING WIRE SHORT CIRCUITING ON EXHAUST SYSTEM CA	USING FAILURE OF VOLTAGE REGULATOR					1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA	 
1997121800772	19971218	00772	SO  	1997	12	18	AU970447         	1	19970502	G	5711	20207T901	SPAR CAP        			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING LOWER SPAR CAP CRACKED THROUGH SPLICE HOLE - CRACK LENGTH APPROXIMATELY 31.75MM (1.25IN) - FOUND DURING MAGNE	TIC PARTICLE INSPECTION IAW SB-AG-39					1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997121800773	19971218	00773		1997	12	18	AU970448         	4	19970502	G	3416	BG3E	ALTIMETER       			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	COCKPIT	ERROR           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTIMETER OT OF CALIBRATION - AT 5000FT THERE WAS A 500FT ERROR - AT 6000FT THERE WAS A 700FT ERROR - ALTIMETER IS	 OF CHINESE MANUFACTURE - FOUND DURING INSPECTION IAW AD/INST/8 AMDT3					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997121800774	19971218	00774	CE  	1997	12	18	AU970449         	1	19970429	G	2435	96150	BEARING         	LUCAS       		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					STARTER-GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					96150					(AUS) LH ENGINE STARTER GENERATOR DRIVE BEARING FAILED						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997121800775	19971218	00775	SO  	1997	12	18	AU970450         	1	19970418	G	7602		CABLE           			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	MIXTURE CONTROL	STUCK           	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) MIXTURE CONTROL CABLE STUCK - CABLE RUNS ADJACENT TO TURBOCHARGER - THROTTLE CABLE AND PROPELLER CONTROL CABLES AL	SO RUN ADJACENT TO THE TURBOCHARGER					1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920	 
1997121800776	19971218	00776		1997	12	18	AU970451         	4	19970428	G	6113	65805200	SPINNER         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	PROP SPINNER	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) PROPELLER SPINNER DOME SEPARATED - SPINNER RETAINING SCREWS WERE INTACT - SPINNER DOME IS OF FIBREGLASS CONSTRUCTI	ON					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
1997121800777	19971218	00777	NM  	1997	12	18	AU970452         	1	19970417	G	2150	78279010	AIRCYCLE MACHINE			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					CABIN COOLING SY	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					921268					(AUS) AIR CONDITIONING SYSTEM AIR CYCLE MACHINE FAULTY						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997121800778	19971218	00778	NM  	1997	12	18	AU970453         	1	19970228	G	5310		FUSELAGE        			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE CONTAINED LEVEL 2 CORROSION. FOUND DURING INSPECTION						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997121800779	19971218	00779	NM  	1997	12	18	AU970454         	1	19970228	G	5310		FUSELAGE        			BOEING	737   	73733A      	1384673	NM  										FUSELAGE STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 2 CORROSION FOUND DURING INSPECTION						2	L	7	2 	4F			RT	A16WE   					 
1997121800780	19971218	00780	NM  	1997	12	18	AU970455         	1	19970228	G	5310		FUSELAGE        			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					FUSELAGE STRUCT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE CONTAINED LEVEL 2 CORROSION - FOUND DURING INSPECTION						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1997121800781	19971218	00781	GL  	1997	12	18	AU970456         	1	19970418	G	5720		WINGLET         			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  										WING MISC	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WINGLET INNER CORE COLLAPSED - AIRCRAFT IS AMATEUR BUILT						1	L	7	1 	3O			RT	EXPA1L71					 
1997121800782	19971218	00782	SO  	1997	12	18	AU970457         	1	19970501	G	5512	4015514	SKIN            		4015515     	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH HORIZONTAL STABILISER LEADING EDGE SKINS PNO 40155-14 AND PNO 40155-15 CONTAINED SEVERE INTERGRANNULAR C	ORROSION -FOUND FOLLOWING REMOVAL OF DE-ICE BOOTS					1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997121800783	19971218	00783	SO  	1997	12	18	AU970458         	1	19970411	G	5751		RIB             			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					AILERON STRUCTUR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON NOSE RIBS (5OFF6) CRACKED AT HINGE BRACKET LOCATION						1	L	7	2 	3O	3	O		A19S0   	E286				 
1997121800784	19971218	00784	SO  	1997	12	18	AU970459         	1	19970502	G	5711	20207T902	SPAR CAP        			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING LOWER SPAR CAP CONTAINED TWO CRACKS FROM 6.35MM (0.25IN)BOLT HOLE - ONE CRACK EXTENDS 3.048MM (0.120IN) FO	RWARD FROM THE HOLE AND ONE CRACK EXTENDS 0.508MM (0.020IN) REARWARDS - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW SB	-AG-39				1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997121800785	19971218	00785	GL  	1997	12	18	AU970460         	2	19970324	G	7412	8331149522	EXCITER         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE IGN	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			1    				CAE800109BA			(AUS) ENGINE EXCITER BOX FAULTY - EXCITER BOX WAS A REPLACEMENT FOR A DEFECTIVE EXCITER BOX PREVIOUSLY REMOVED FOR CORRO	DED OUTPUT TERMINAL - BOX WAS OK FOR THE FIRST START BUT THEN FAILED					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997121800786	19971218	00786	SO  	1997	12	18	AU970461         	1	19970322	G	2430		WIRE            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	LT ALTERNATOR	SHORTED         	W				O				OTHER                   				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		CR	CRUISE         	1			AU	S 										(AUS) LH ALTERNATOR MAIN CABLE SHORT CIRCUITING ON EXHAUST PIPE - LOOSE TERMINALS ON BATTERY SUPPLY RELAYS - INVESTIGATI	ON FOUND THAT THE ALTERNATOR SYSTEM WAS NOT AN APPROVED INSTALLATION (SYSTEM HADBEEN CHANGED FROM GENERATOR TO ALTERNATO	R) - UNAPPROVED MODIFICATION - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
1997121800787	19971218	00787	SO  	1997	12	18	AU970462         	2	19970424	G	8530	538304	PUSHROD         	CONT        		CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENG NR 4 CYL	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					286435R		286435R			(AUS) NO4 CYLINDER EXHAUST VALVE PUSHROD BENT - NO4 AND NO5 CYLINDER EXHAUST VALVES STIFF - NO2 CYLINDER INLET VALVE ROU	GH INOPERATION - NO4 CYLINDER PISTON HAD CONTACTED THE NO4 EXHAUST VALVE - CYLINDERS ARE SUPERIOR ITEMS PNO SA52000A1					1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P47GL	 
1997121800788	19971218	00788	SO  	1997	12	18	AU970463         	2	19970430	G	8520	652560	CRANKCASE       			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	BEARING JOURNAL	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							294694R			(AUS) CRANKCASE MAIN BEARING JOURNALS AND OUTER SHELL SURFACES WORN EXCESSIVELY - CRANKSHAFT CENTRE MAIN JOURNAL BADLY S	CORED - SUSPECT INCORRECT LINE BORING DURING OVERHAUL					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997121800789	19971218	00789	NE  	1997	12	18	AU970464         	2	19970405	G	7313	775723	SEAL            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUEL INJ NOZZLE	LEAKING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			2731 				687513			(AUS) NO1 ENGINE NO9 COMBUSTION CAN FUEL INJECTOR NOZZLE SEAL LEAKING. INVESTIGATION FOUND THAT THE PROBLEM WAS CAUSED B	Y IMPROPER MAINTENANCE ACTIVITIES DURING NOZZLE OVERHAUL.PERSONNEL/MAINTENANCE ERROR.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997121800790	19971218	00790	NM  	1997	12	18	AU970465         	1	19970427	G	2520	309312	NUT             			BOEING	737   	737476      		NM  										AFT CABIN SEAT	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					309312					(AUS) REAR CABIN SEATS 15 DEF FORWARD INBOARD LEG MOUNT ANCHOR NUT FAULTY - SEAT ROWS 16 DEF AND 17 DEF ALSO LOOSE IN TR	ACKS					2	L	7	2 	4F			RT	A16WE   					 
1997121800791	19971218	00791	SO  	1997	12	18	AU970466         	1	19970417	G	5711	20207T901	SPAR CAP        		20207T902   	AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING LOWER SPAR CAPS PNO 20207-T901 AND PNO 20207-T902 CRACKED - LH LOWER SPAR CAP HAS ONE CRACK IN TWO 	HOLES - RH LOWER SPAR CAP HAS TWO CRACKS IN OUTBOARD HOLE - FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION IAW AG	-39				1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997121800792	19971218	00792	SO  	1997	12	18	AU970467         	1	19970502	G	5711		SPAR CAP        			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING LOWER SPAR CAP CRACKED FROM 6.35MM (0.25IN) HOLE - ONECRACK 12.395MM (0.488IN) EXTENDS FORWARD AND ONE CRA	CK 7.975MM(0.314IN) EXTENDS REARWARDS - FOUND DURING MAGNETIC PARTICLE INSPECTION - SEE MDR 97/0447 FOR ADDITIONAL INFOR	MATION				1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997121800793	19971218	00793	SO  	1997	12	18	AU970468         	1	19970502	G	5711		SPAR CAP        			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING LOWER FORWARD SPAR CAP CRACKED FROM 6.35MM (0.25IN) HOLE- ONE CRACK 3.098MM (0.122IN) EXTENDED FORWARD AND	 ONE CRACK0.508MM (0.020IN) EXTENDED REARWARD - FOUND DURING MAGNETIC PARTICLE INSPECTION - SEE MDR 97/0459 FOR FURTHER 	INFORMATION				1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997121800794	19971218	00794	WP  	1997	12	18	AU970469         	2	19970502	G	7314		PUMP            								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE FUEL PUMP	LOW PRESSURE    	W				K	E			NONE                    	ENGINE SHUTDOWN         			O			OTHER                     			LD	LANDING        	1			AU	S 							PA2080			(AUS) LH ENGINE DRIVEN FUEL PUMP OUTLET PRESSURE AT LOW END OF LIMITS - FCU METERING VALVE ALSO SET AT LOW END OF LIMITS											4	T			E4WE	6	C	P61GL	 
1997121800795	19971218	00795	EU  	1997	12	18	AU970470         	1	19970222	G	2722	A5547065020490	FITTING         			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					RUDDER ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER ACTUATOR HINGE FITTING CRACKED ON OUTER FLANGE RADIUS AND INNER WEB						2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1997121800796	19971218	00796	EU  	1997	12	18	AU970471         	1	19970505	G	5330		SKIN            			BAC   	146   	146300A     	1500267	EU  										FUSELAGE AFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED ON LH SIDE IN AREA OF AFT FRAME 10 BELOW THE LOWER LAP JOINT - CRACK LENGTH 68.5MM (2.7IN) -	 DAMAGE CAUSED BY IMPACT WITH TARMAC VEHICLE					2	H	7	4 	4F			RT	A49EU   					 
1997121800797	19971218	00797	NE  	1997	12	18	AU970472         	2	19970430	G	7321	8004142003	EEC             			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					FUEL CONT EEC	FAULTY          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) LH ENGINE ELECTRONIC CONTROL (EEC) SUSPECT FAULTY						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997121800798	19971218	00798	SO  	1997	12	18	AU970473         	1	19970417	G	3230	4A7222119	HOSE            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG RETRACT	LEAKING         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) MAIN LANDING GEAR DOWNLOCK HOSE LEAKING FROM FITTING						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1997121800799	19971218	00799	SO  	1997	12	18	AU970474         	1	19970429	G	5410	4066701	ANGLE           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENG MOUNT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								DJ10865A		(AUS) RH ENGINE NACELLE LOWER ANGLE SHEAR PLATE LOCATED AT WS65.69 ANDWS89.31 HAD LOOSE AND WORKING RIVETS ALLOWING FORE	 AND AFT MOVEMENT OF THE LOWER ENGINE MOUNT ATTACHMENT BRACKETS					1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997121800800	19971218	00800	WP  	1997	12	18	AU970475         	2	19970422	G	7260	31030351	BEARING         	GARRTT      	GEAR        	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENG ACESSORY BOX	DISINTEGRATED   	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					3P3767		P70144			(AUS) ENGINE ACCESSORY GEARBOX BEARING CAGE DISINTEGRATED - METAL CONTAMINATION OF CHIP DETECTOR						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997121800801	19971218	00801	WP  	1997	12	18	AU970476         	2	19970430	G	7230	31033336	BEARING         			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TURB ENG COMP	DISINTEGRATED   	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 							P70143			(AUS) ENGINE MAIN COMPRESSOR SHAFT BEARING DISINTEGRATED - METAL CONTAMINATION OF OIL SYSTEM						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1997121800802	19971218	00802	SO  	1997	12	18	AU970477         	1	19970419	G	3246	300820	WHEEL           	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	WHEEL/SKI/FLOAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0095					(AUS) MAIN WHEEL ASSEMBLY INNER WHEEL HALF CONTAINED MULTIPLE CRACKS IN THE LOWER DRIVE LUGS - FOUND DURING FLUORESCENT 	DYE PENETRANT INSPECTION					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1997121800803	19971218	00803	SO  	1997	12	18	AU970478         	2	19970407	G	8530	648029	PISTON          	CONT        		BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	RECIP ENG	BURNT           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					CS914624L		CS914624L			(AUS) ENGINE PISTON BURNT - ENGINE METAL CONTAMINATION - SUSPECT CAUSED BY POORLY OVERHAULED FUEL SYSTEM						1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P911	 
1997121800804	19971218	00804	NE  	1997	12	18	AU970479         	2	19970509	G	7260		DRIVE           			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR3 ENG OIL PUMP	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 							LF05454			(AUS) NO3 ENGINE OIL PUMP DRIVE FAILED - METAL CONTAMINATION OF OIL SYSTEM - DURING GEARBOX REMOVAL A THREADED INSERT WA	S PULLED FROM THE FAN HOUSING					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1997121800805	19971218	00805	NE  	1997	12	18	AU970480         	2	19970425	G	7230	793353	COMPRESSOR CASE 			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					TURB ENG COMP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			20555				687388			(AUS) NO1 ENGINE INTERMEDIATE COMPRESSOR CASE HOLED AT THE 12 O'CLOCK POSITION BY THE ENGINE LIFTING BEAM FORWARD ATTACH	MENT FITTINGPNO F72714-2 - ENGINE WAS LIFTED WITH ONLY THE UPPER FORWARD CONE BOLT ENGAGED ALLOWING THE ENGINE TO ROLL T	O THE RIGHT AND CONTACTING THE LIFTING BEAM - PERSONNEL/MAINTENANCE ERROR				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997121800806	19971218	00806	NM  	1997	12	18	AU970481         	1	19970307	G	3230	2041561ANSETTSN	HYDRAULIC FUSE  			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					RT MLG RETRACT	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					2041561ANSET					(AUS) RH MAIN LANDING GEAR TRUCK POSITIONER `UP' LINE HYDRAULIC FUSE FAULTY						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1997121800807	19971218	00807	CE  	1997	12	18	AU970482         	1	19970506	G	7603		LINKAGE         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	POWER LEVER	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								ED454		(AUS) LH ENGINE CONTROL LINKAGES FAULTY - THE FOLLOWING DEFECTS WERE FOUND:- 1. THROTTLE CONTROL LINKAGE SEVERELY WORN 2	. THROTTLE ROD END SEPARATED FROM CAGE 3. NYLEX NUT USED ON THROTTLE CROSS SHAFT 4. NYLEX NUT ON MIXTURE CONTROL NOT IN 	SAFETY 5. MIXTURE CONTROL ROD END SLIGHTLY WORN. PROPELLER CONTROL ROD END FAILED 7. RH ENGINE THROTTLE AND MIXTURE CONT	ROLS USING NYLEX NUTS FOUND DURING INSPECTION FOR PROPELLER STRIKE - UNAPPROVED PART -			1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1997121800808	19971218	00808	EU  	1997	12	18	AU970483         	1	19970402	G	5230		HANDLE          			AIRBUS	320   	A320212     		EU  										CARGO/BAG DOOR	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN CARGO DOOR LATCH HANDLE WOULD NOT FULLY ENGAGE - SUSPECT CAUSED BY INTERFERENCE BETWEEN THE CARGO DOOR HANDLE	 AND THE HANDLE LOCKING MECHANISM CAUSING A PRELOAD AGAINST THE HANDLE LATCH HOOK					2	L	7	2 	4F			RT	A28NM   					 
1997121800809	19971218	00809	CE  	1997	12	18	AU970484         	1	19970510	G	3230	35815109	UPLOCK CABLE    	BEECH       	B76         	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	MLG RETRACT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR UPLOCK CABLE FAILED AT OUTBOARD SWAGED FITTING DUE TO CORROSION OF THE EXPOSED STRANDS						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
1997121800810	19971218	00810	SO  	1997	12	18	AU970485         	1	19970508	G	3234	1203859400	SELECTOR        	EMB         		EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					LANDING GEAR SEL	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					12040					(AUS) LANDING GEAR SELECTOR FAULTY - SUSPECT CAUSED BY FAULTY MICRO SWITCHES						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997121800811	19971218	00811	SO  	1997	12	18	AU970486         	1	19970216	G	2410	73965009	DRIVE BELT      			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ALTERNATOR-GENER	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR DRIVE BELT FAULTY - PERSONNEL/MAINTENANCE ERROR						1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1997121800812	19971218	00812	GL  	1997	12	18	AU970487         	3	19970510	G	6111	FC84686R	BLADE           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER BLADE	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								DJ9134A		(AUS) PROPELLER BLADES BELOW MANUFACTURERS MINIMUM LIMITS BY AT LEAST 9.398MM (0.370IN) AT TIP STATIONS - LOG BOOK INADE	QUATE FOR CASA RELEASE - PROPELLER HAD BEEN IMPORTED FROM THE USA AND WAS UNDERGOING ASSEMBLY AND CERTIFICATION BEFORE U	SE -PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997122400271	19971224	00271	SO  	1997	12	24	AU970488         	1	19970509	G	7713	6136402	PIPE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MANIFOLD PRESS	CHAFED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 										(AUS) RH ENGINE MANIFOLD PRESSURE RIGID PIPE FROM ENGINE BULKHEAD FITTING CHAFED THROUGH BY LH COWL FLAP ACTUATOR ROD PN	O 42574.00					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997122400272	19971224	00272	EA  	1997	12	24	AU970489         	2	19970512	G	8500		HOSE            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL ENGINE HOSES FAULTY - WHEN FIRE SLEEVING WAS REMOVED THE HOSES WERE FOUND TO BE MANUFACTURED FROM MIL-H-6000 L	OW PRESSURE HOSE AND NON COMPATIBLE MS FITTINGS - HOSES LEAKED DURING PRESSURE TESTING - SOME HOSES WERE ALSO FOUND TO B	E MANUFACTURED FROM 306 TYPE LOW PRESSURE HOSE - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART				1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1997122400273	19971224	00273	NE  	1997	12	24	AU970490         	2	19970405	G	7240		COMBUSTOR       			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 1 ENG	HOLED           	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							687513			(AUS) NO1 ENGINE NO9 COMBUSTION CAN BURNT THROUGH AT FUEL NOZZLE NUTFACE. FOUND DURING BOROSCOPE INSPECTION. INVESTIGATI	ON FOUND THAT THE PROBLEM WAS CAUSED BY DISCREPANCIES IN THE OVERHAUL OF THE FUEL NOZZLE ASSEMBLIES. PERSONNEL/MAINTENAN	CE ERROR.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997122400274	19971224	00274	GL  	1997	12	24	AU970491         	2	19970304	G	7261	23001819	NOZZLE          	ALLSN       							ALLSN 	250C  	250C20B     	03013	GL  					ENG NR 6 BEARING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			135  		CAE834661		CAE834661			(AUS) NO6 AND NO7 BEARING OIL NOZZLE WORN AND CORRODED											3	U			E4CE				 
1997122400275	19971224	00275		1997	12	24	AU970492         	1	19970226	G	7810	4606AC	CLAMP           								ALLSN 	250C  	250C20B     	03013	GL  					ENG EX COLLECTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							CAE834661			(AUS) ENGINE EXHAUST PIPE CLAMP BROKEN AT RIVET LINE											3	U			E4CE				 
1997122400276	19971224	00276	NE  	1997	12	24	AU970493         	2	19970514	G	7250		BEARING         			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE SECTION	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 							5936			(AUS) ENGINE OIL PRESSURE LOSS - SUSPECT NO4/5 BEARING FAILURE						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997122400277	19971224	00277	EU  	1997	12	24	AU970494         	1	19970505	G	2197		WIRE            			PILATS	PC12  	PC12        	7090550	EU  										CABIN PRESS CONT	WORN            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LOSS OF CABIN PRESSURISATION - CAUSED BY CHAFED AND BURNT WIRING ON PARK BRAKE CABLE NUT BEHIND TRIM PANEL IN AREA	 OF PILOT'S FEET - BURNT WIRING ALSO CAUSED LOSS OF FLOOD FANS AND FAILURE OF CABIN TEMPERATURE GAUGE					1	L	7	1 	3T			RT	A78EU   					 
1997122400278	19971224	00278	GL  	1997	12	24	AU970495         	2	19970514	G	7260	6854521	SEAL            	ALLSN       		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					GRBOX COOLER	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CL	CLIMB          	1			AU	S 					CAG90667					(AUS) NO2 ENGINE ACCESSORY GEARBOX OIL COOLER BLOWER DRIVE SEAL FAILED- LOSS OF ENGINE OIL						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997122400279	19971224	00279	NM  	1997	12	24	AU970496         	1	19970424	G	5551	65B035632	FITTING         			BOEING	747   	747312      	1384932	NM  										HORIZONTAL STAB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH HORIZONTAL STABILISER HINGE FITTING GOUGED ON INBOARD SURFACE- INVESTIGATION FOUND THAT THE HINGE BEARING RETAI	NER HAD ROTATED THROUGH APPROXIMATELY 90 DEGREES CAUSING THE DAMAGE - THE GOUGE WAS APPROXIMATELY 2.54MM (0.100IN) DEEP 	BY 12.7MM (0.5IN) WIDE THROUGH A 90 DEGREE ARC - THE BORE OF THE FITTING HOUSING THE BEARING SLEEVE HAD 0.1524MM (0.006I	N) OVALITY			2	L	7	4 	4F			RT	A20WE   					 
1998010600012	19980106	00012	EU  	1998	1	6	AU970497         	1	19970516	G	7160	NH2466808108	DUCT            		NH24668     	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	ENGINE AIR INT	BURNT           	W				K				NONE                    				O	B		OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			AU	S 			5103 		JLSF325C		785235			(AUS) RH ENGINE INLET LOWER DUCT BURNT AROUND THE INNER UPPER LIP ATTHE PARTICLE SEPARATOR MOUNTING FLANGE						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1997122400280	19971224	00280	NM  	1997	12	24	AU970498         	1	19970319	G	2170	1808494	COALESCER BAG   			BOEING	737   	737377      		NM  										HUMIDITY CONTROL	DIRTY           	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LH AIRCONDITIONING PACK WATER SEPARATOR COALESCER BAG DIRTY						2	L	7	2 	4F			RT	A16WE   					 
1997122400281	19971224	00281	NM  	1997	12	24	AU970499         	1	19970409	G	2913	21830	BEARING         			BOEING	737   	737377      		NM  										HYDRAULIC PUMP	FAILED          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			8029 		220484ANSETT					(AUS) HYDRAULIC `B' SYSTEM ELECTRIC PUMP TRUNNION BEARINGS FAILED.DAMAGE CAUSED TO PUMP ROTATING GROUP, PUMP HOUSING AND	 ELECTRIC MOTOR.					2	L	7	2 	4F			RT	A16WE   					 
1997122400282	19971224	00282	EU  	1997	12	24	AU970500         	1	19970131	G	2120	9566300	ARMATURE        			AIRBUS	320   	A320212     		EU  										AIR DISTRIBUTION	OPEN CIRCUIT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					69ANSETTSN00					(AUS) AVIONICS EQUIPMENT VENTILATION SYSTEM SKIN AIR OUTLET VALVE MOTOR ARMATURE HAD OPEN CIRCUIT ON THREE ADJACENT COMM	UTATOR SEGMENTS					2	L	7	2 	4F			RT	A28NM   					 
1997122400283	19971224	00283	EU  	1997	12	24	AU970501         	1	19970211	G	5610	NP1653114	WINDSHIELD      			AIRBUS	320   	A320212     		EU  										FLIGHT COMPART	CRACKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					96205H3073AN					(AUS) FIRST OFFICERS WINDSCREEN OUTER PANE CRACKED						2	L	7	2 	4F			RT	A28NM   					 
1997122400284	19971224	00284	EU  	1997	12	24	AU970502         	1	19970504	G	3411	147013207	TUBE            			BNORM 	BN2   	BN2A6       	1520205	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PITOT/STATIC SYS	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PITOT-STATIC SYSTEM LINES LEAKING - INVESTIGATION FOUND LEAKS WERE FROM HEAT SHRINK TUBING (THERMOFIT) USED AT JOI	NS IN THE PLUMBING AND APPLIED DURING MANUFACTURE - FOUND DURING INSPECTION IAW AD/INST/9 (PITOT/STATIC SYSTEM LEAK CHEC	K)				1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920	 
1997122400285	19971224	00285	CE  	1997	12	24	AU970503         	1	19970519	G	2612	61423473275	FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENG	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE FIRE WARNING SYSTEM FIRE DETECTOR FAULTY - SUSPECT MOISTURE INGRESS AS RAIN FELL DURING THE PREVIOUS NIG	HT					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997122400286	19971224	00286	WP  	1997	12	24	AU970504         	1	19970514	G	6310	C1842	BEARING         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TRANSMISSION	ROUGH           	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 					SNS					(AUS) ENGINE TO TRANSMISSION CLUTCH UPPER SHEAVE BEARING NOISY AND ROUGH IN OPERATION - NO EVIDENCE OF LUBRICATION - TEL	ETEMP INDICATOR HAD NOT ACTIVATED					1	G	7	1 	3O	3	O		H11NM   	E295				 
1997122400287	19971224	00287		1997	12	24	AU970505         	4	19970420	G	2350	AVIX	HEADSET         			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	AUDIO INTEGRATIN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HEADSET LEAD MELTED DUE TO SHORT CIRCUIT BETWEEN CO-PILOTS PHONEJACK AND INSTRUMENT LIGHTING WIRE						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
1997122400288	19971224	00288	GL  	1997	12	24	AU970506         	3	19970502	G	6114	861246	LATCH           	MCAULY      		CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER HUB	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					861246			861246		(AUS) RH PROPELLER LOW PITCH LATCHES FAILED						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997122400289	19971224	00289	CE  	1997	12	24	AU970507         	1	19970506	G	2510	081278211	SEAT            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	COPILOT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CO-PILOTS SEAT CUSHION BASE FRAME SIDE MEMBER CRACKED						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1997122400290	19971224	00290	CE  	1997	12	24	AU970508         	1	19970513	G	5347	58112133	SEAT TRACK      			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3AF34C	3AF34C74    	GL  	BS 300	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD SEAT TRACK CONTAINED EXFOLIATION CORROSION IN AREA OF FLOOR PANEL ATTACHMENT HOLE IN HORIZONTAL FLANGE	 AT FS 300.00 - SUSPECT CAUSED BY LIQUID FLOOR POLISH - POLISH WAS AN UNAPPROVEDPRODUCT					1	L	7	2 	3O				A25CE   		5	C	P22EA	 
1997122400291	19971224	00291		1997	12	24	AU970509         	4	19970512	G	2564	EAMT6	LIFE RAFT       																	LIFE RAFT	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					TF269					(AUS) LIFERAFT INCORRECTLY PACKED - GAS BOTTLE DUE FOR HYDROSTATIC TEST ON 10/96 - LIFERAFT HAD JUST ARRIVED FROM OVERSE	AS -PERSONNEL/MAINTENANCE ERROR																		 
1997122400292	19971224	00292	EU  	1997	12	24	AU970510         	1	19970518	G	5312		BULKHEAD        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FUSELAGE MAIN BU	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN THREE AREAS:-1. FORWARD PRESSURE BULKHEAD REAR SIDE AT HORIZONTAL BEAM 7 LEFT	 OF BL325L - CRACK LENGTH 76.2MM (3IN)2. FORWARD PRESSURE BULKHEAD REAR SIDE AT HORIZONTAL BEAM 7 RIGHT  OF BL325R - CRA	CK LENGTH 127MM (5IN) 3. FORWARD PRESSURE BULKHEAD BETWEEN THE FUSELAGE CENTRE LINE AND  STRINGER 3 WHERE THE BULKHEAD M	EETS THE LOWER FUSELAGE SKIN - CRACK LENGTH 107.6MM (4.24IN)CRACKS 1 AND 2 FOUND DURING INSPECTION IAW ER F28-53-10-20 -	CRACK 3 FOUND DURING INSPECTION IAW ER F28-53-10-19F		2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997122400293	19971224	00293	SO  	1997	12	24	AU970511         	2	19970407	G	7314	6381549	PUMP            	CONT        	6381549     	BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	ENGINE FUEL PUMP	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			20   		3580		CS94624C			(AUS) ENGINE DRIVEN FUEL PUMP FAULTY - ROTOR SHAFT UNSERVICEABLE -INCORRECT IDLE ADJUSTMENT SCREW FITTED (TOO SHORT) - T	HRUST PLATES DAMAGED DUE TO INCORRECT CLEARANCES - WATER DAMAGE TO RELIEF VALVE AREA - UNIT HAD JUST RETURNED FROM OVERH	AUL -PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P911	 
1997122400294	19971224	00294	SO  	1997	12	24	AU970512         	2	19970407	G	7322	6252192	FCU             	CONT        	6252192     	BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	FUEL CONTROL/CAR	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			20   		22168		CS94624C			(AUS) FUEL CONTROL UNIT FAULTY - FCU WOULD NOT SHUT OFF IN `IDLE CUTOFF' POSITION - RETURN SPRING NOT FITTED - PERSONNEL	/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P911	 
1997122400295	19971224	00295	SO  	1997	12	24	AU970513         	2	19970407	G	7313	62733312	NOZZLE          	CONT        	627335D12C  	BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	FUEL INJECT NOZ	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			20   		X6		CS94624L			(AUS) ALL FUEL INJECTOR NOZZLES OUT OF CALIBRATION - FUEL FLOW TOO LOW- FOUR NOZZLES ALSO INTERMITTENT IN OPERATION - PE	RSONNEL/MAINTENANCE					1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P911	 
1997122400296	19971224	00296	SO  	1997	12	24	AU970514         	1	19970516	G	2510	CF1010	SEAT BELT       			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	FLIGHT COMPART	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT FAULTY - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997122400297	19971224	00297	SO  	1997	12	24	AU970515         	2	19970407	G	8530	648029	PISTON          	CONT        		BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	RECIP ENG	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CS94624L		CS94624L			(AUS) PISTON BURNT AND TORCHED - ENGINE METAL CONTAMINATION						1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P911	 
1997122400298	19971224	00298	SO  	1997	12	24	AU970516         	2	19970407	G	7320	6314273	VALVE           	CONT        	6314273     	BEECH 	55    	9555        	1152702	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	FUEL CONTROLLING	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			20   		4117		CS914624L			(AUS) ENGINE MANIFOLD VALVE FAULTY - INCORRECT OVERHAUL - SEAL COLLAPSED ON ONE SIDE - PLUNGER OUT OF ROUND - NEEDLE AND	 NUT OF UNKNOWN ORIGIN - GASKET PNO 627124 FITTED - UNAPPROVED PART - PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A16    	3E1	5	C	P911	 
1997122400299	19971224	00299	EA  	1997	12	24	AU970517         	2	19970502	G	7322	RSA5AD1	FCU             								LYC   	O540  	IO540*      	41532	EA  					FUEL CONT/CARB	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					42178					(AUS) FUEL CONTROL UNIT WAS A SUPERSEDED MODEL											3	O			1E4				 
1997122400300	19971224	00300		1997	12	24	AU970518         	4	19970429	G	3421	6229681001	EADI            	COLLINS     	EFD84       	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3A     	NE  	ATT & DIR GYRO	FAILED          	W				K				NONE                    				I			FLT. ATTITUDE INST.       			CL	CLIMB          	1			AU	S 					203					(AUS) CAPTAINS ELECTRONIC ATTITUDE DIRECTION INDICATOR (EADI) FAILED DUE TO INTERNAL FAULT						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
1997122400301	19971224	00301	CE  	1997	12	24	AU970519         	1	19970508	G	3242		O-RING          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT BRAKE	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LH BRAKE SYSTEM FLUID LOSS - SUSPECT CAUSED BY BRAKE BODY INLET FITTING `O' RING SEAL						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997122400302	19971224	00302	CE  	1997	12	24	AU970522         	1	19970509	G	3234		CIRCUIT BOARD   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					GEAR SELECTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR PRINTED CIRCUIT BOARD FAULTY						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997122400303	19971224	00303	CE  	1997	12	24	AU970523         	1	19970512	G	3242	9535088	ADAPTER         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT INB BRAKE	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LH INBOARD BRAKE UNIT ADAPTER LOOSE - LOSS OF BRAKE FLUID - PERSONNEL/MAINTENANCE ERROR						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1998010600013	19980106	00013	WP  	1998	1	6	AU970524         	2	19970424	G	7200		ENGINE          								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	RT ENGINE	LOW POWER       	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AU	S 										(AUS) RH ENGINE LOW POWER											4	T			E4WE	6	C	P61GL	 
1997122400304	19971224	00304	NM  	1997	12	24	AU970525         	1	19970418	G	2612		WARNING SYSTEM  	RROYCE      		BOEING	747   	747438      		NM  										NR 2 ENG	FAULTY          	W				K	F			NONE                    	ACTIVATE FIRE EXT.      			O	N		OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) NO2 ENGINE FIRE WARNING - NO EVIDENCE OF FIRE - BOTH FIRE BOTTLES DISCHARGED						2	L	7	4 	4F			RT	A20WE   					 
1997122400305	19971224	00305	NM  	1997	12	24	AU970526         	1	19970413	G	2780	65B151721	LINK            			BOEING	747   	747238B     	1384828	NM  										LE FLAP CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VARIABLE CAMBER LEADING EDGE FLAP LINK BROKEN - BROKEN LINK HAD IN TURN BROKEN A LEADING EDGE SUPPORT STRUCTURE BE	AM AND ALSO PENETRATED AND CRACKED THE LOWER FIBREGLASS FIXED PANEL PNO 65B10873-28 - CRACK LENGTH 762MM (30IN)					2	L	7	4 	4F				A20WE   					 
1997122400306	19971224	00306	CE  	1997	12	24	AU970527         	1	19970415	G	3242	16402706	BRAKE DISC      			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	RT MLG	WORN            	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR BRAKE WORN - BRAKE LOCKED UP CAUSING TYRE TO BLOW OUT						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997122400307	19971224	00307	EA  	1997	12	24	AU970528         	2	19970429	G	7322	57429	SPINDLE         	BENDIX      	RGA         	PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL CONT/CARB	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1990 		57429		L1464648A			(AUS) ENGINE FUEL CONTROL UNIT IDLE MIXTURE ADJUSTMENT SPINDLE MISSING- SUSPECT CAUSED BY FAILURE OF POSITIONING SPRING 	WHICH THEN ALLOWED THE ADJUSTMENT SPINDLE TO VIBRATE FREE					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997122400308	19971224	00308	CE  	1997	12	24	AU970529         	1	19970515	G	5347	58112131	SEAT TRACK      			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3AF34C	3AF34C74    	GL  	SEAT/CARGO ATTAC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT TRACK CRACKED IN AREA OF FORWARD HORIZONTAL FLANGE						1	L	7	2 	3O				A25CE   		5	C	P22EA	 
1997122400309	19971224	00309	EA  	1997	12	24	AU970530         	2	19970509	G	8530	3116	STUD            	LYC         		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENG CYL	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			2058 		L755076		L755076			(AUS) NO1 CYLINDER EXHAUST VALVE ROCKER STUD BROKEN - INLET VALVE BROKEN AND PUSHROD BENT						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997122400310	19971224	00310	EA  	1997	12	24	AU970531         	2	19970519	G	8520	L261143	CRANKCASE       	LYC         							LYC   	O540  	VO540C2A    	41532	EA  					RECIP ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L261143		L261143			(AUS) ENGINE CRANKCASE CRACKED AND TUNNEL OUT OF LIMITS - CRANKSHAFT WORN BEYOND LIMITS - CAMSHAFT LOBES DAMAGED											3	O			E304				 
1998010600014	19980106	00014	SO  	1998	1	6	AU970532         	2	19970507	G	8520	676405	CRANKCASE       	CONT        		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      		SO  	MCAULY	3AF32C	3AF32C512   	GL  	RECIP ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					676405		676405			(AUS) ENGINE CRANKCASE LH HALF CRACKED IN AREA OF NO2 BEARING SADDLE -NO6 CONNECTING ROD CAP CONTAINED MULTIPLE CRACKING	 - SUSPECT CRACKING ORIGINATED FROM CORROSION PITTING					1	L	7	2 	3O	3	O		3A16    	E3SO	5	C	P22EA	 
1997122400311	19971224	00311	EU  	1997	12	24	AU970533         	1	19970518	G	5312		BULKHEAD        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN THREE PLACES:- 1. REAR SIDE OF FORWARD PRESSURE BULKHEAD WEB AT HORIZONTAL BE	AM NO7 LEFT OF BL325L - CRACK LENGTH 76.2MM (3IN) 2. REAR SIDE OF FORWARD PRESSURE BULKHEAD WEB AT HORIZONTAL BEAM NO7 R	IGHT OF BL325R - CRACK LENGTH 127MM (5IN) 3. BETWEEN FUSELAGE CENTRELINE AND STRINGER NO3 WHERE THE  CIRCUMFERENCE OF TH	E FORWARD PRESSURE BULKHEAD MEETS THE  BOTTOM FUSELAGE SKIN - CRACK LENGTH 107.69MM (4.24IN)CRACKS NO1 AND NO2 WERE FOUN	D DURING INSPECTION IAW ERF28-53-10-20 - CRACK NO3 FOUND DURING INSPECTION IAW ER		2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997122400312	19971224	00312	EA  	1997	12	24	AU970534         	2	19970519	G	8520	L1474639A	CAMSHAFT        	LYC         		ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L1474639A		L1474639A			(AUS) ENGINE CAMSHAFT LOBE DAMAGED - HARDENING BREAKING DOWN						1	G	7	1 	3O	3	O		H10WE   	E274				 
1997122400313	19971224	00313	CE  	1997	12	24	AU970535         	1	19970516	G	5312		BULKHEAD        			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER AFT DOORPOST BULKHEAD CRACKED - FOUND DURING INSPECTION IAW CESSNA SEB 97-1						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400314	19971224	00314	CE  	1997	12	24	AU970536         	1	19970516	G	5312		BULKHEAD        			CESSNA	172   	172L        	2072432	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER AFT DOOR POST BULKHEAD CRACKED - FOUND DURING INSPECTION IAW CESSNA SEB 97-1						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400315	19971224	00315	CE  	1997	12	24	AU970537         	1	19970429	G	5312		BULKHEAD        			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER AFT DOOR POST BULKHEAD CRACKED - FOUND DURING INSPECTION IAW CESSNA SEB 97-1						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400316	19971224	00316	CE  	1997	12	24	AU970538         	1	19970516	G	5312		BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER AFT DOOR POST BULKHEAD CRACKED - FOUND DURING INSPECTION IAW CESSNA SEB 97-1						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1998010600015	19980106	00015		1998	1	6	AU970539         	1	19970502	G	7110		COWLING         																	ENGINE COWLING	DAMAGED         	W				K				NONE                    				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE COWL DAMAGED - SUSPECT COWL LATCH INCORRECTLY FASTENED OR LATCH FAILED																			 
1997122400317	19971224	00317	SO  	1997	12	24	AU970540         	2	19970501	G	8520	465705	CRANKSHAFT      	CONT        		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					465705		465705			(AUS) CRANKSHAFT CONTAINED TWO CRACKS IN NO6 CONNECTING ROD WEB - CRANKCASE BEARING TUNNEL OUT OF LIMITS - DAMAGE CAUSED	 BY HEAVY LANDING AND PROPELLER STRIKE					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1997122400318	19971224	00318	EA  	1997	12	24	AU970541         	2	19970514	G	7414	M3975	COIL            	SLICK       	4371        						LYC   	O360  	O360A4K     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	MAGNETO/DIST	OPEN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					92020112					(AUS) MAGNETO COIL OPEN CIRCUITED ON HIGH TENSION SIDE											3	O			E286	5	N	P857	 
1997122400319	19971224	00319	EA  	1997	12	24	AU970542         	2	19970519	G	8520	L2538548A	CAMSHAFT        	LYC         		BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L2538548A		L2538548A			(AUS) CAMSHAFT LOBE CASE HARDENING DAMAGED						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1997122400320	19971224	00320	CE  	1997	12	24	AU970543         	1	19970509	G	2730	126047512	CONTROL CABLE   			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ELEVATOR CONTROL	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL CABLE WORN - CABLE HAD BEEN INCORRECTLY ROUTED OVER A PULLEY GUARD PNO NAS 427K11 ON THE PULLEY L	OCATED SECOND FROM THE FRONT - AIRCRAFT HAD BEEN REBUILT 242.3 HOURS PREVIOUSLY FOLLOWING AN ACCIDENT - PERSONNEL/MAINTE	NANCE ERROR				1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
1997122400321	19971224	00321	NM  	1997	12	24	AU970544         	1	19970513	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 AT SIDE CHORD RADIUS LH SIDE AT WL207 - CRACK LENGTH APPROXIMATELY 76.2MM (3IN)						2	L	7	2 	4F			RT	A16WE   					 
1997122400322	19971224	00322	EA  	1997	12	24	AU970545         	2	19970521	G	8520	L2538448A	CAMSHAFT        	LYC         		BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L2538448A		L2538448A			(AUS) CAMSHAFT LOBE CASE HARDENING BREAKING DOWN - CRANKSHAFT GEAR ALSO HAD BREAKING DOWN OF THE CASE HARDENING						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1997122400323	19971224	00323	CE  	1997	12	24	AU970546         	1	19970523	G	2910	572700258	LINE            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	HYDRAULIC MAIN	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC LINE BURST DURING RIG TESTING AT APPROXIMATELY 220PSI						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997122400324	19971224	00324	EU  	1997	12	24	AU970547         	1	19970520	G	2823	D1N808G6	UNIVERSAL JOINT 			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					FUEL SELECTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SELECTOR SHAFT LOWER UNIVERSAL JOINT RETAINER PIN (1OFF4)MISSING						1	L	7	1 	3O	3	O	NT	A57EU   	E286				 
1997122400325	19971224	00325		1997	12	24	AU970548         	1	19970519	G	7602	115C6030	BRACKET         								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	MIXTURE CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MIXTURE CONTROL CABLE SUPPORT BRACKET FAILED IN AREA OF ATTACHMENT CLAMP											3	O			E286	5	C	P27EA	 
1997122400326	19971224	00326	SO  	1997	12	24	AU970549         	2	19970508	G	8530	TM652952A	CYLINDER        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENG NR 4	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							286509R			(AUS) NO4 CYLINDER HEAD SEPARATED FROM THE BARREL - INVESTIGATION FOUND THAT THE FAILURE OCCURRED AT THE TOP OF THE THRE	ADED SECTION OF THE HEAD TO BARREL JUNCTION					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997122400327	19971224	00327	EA  	1997	12	24	AU970550         	2	19970401	G	8550		PUMP            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1504527A			(AUS) ENGINE OIL PUMP FAULTY - AD/LYC/81 AMDT3 HAD NOT BEEN COMPLIED WITH - SINTERED IRON IMPELLER STILL FITTED						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997122400328	19971224	00328	GL  	1997	12	24	AU970551         	1	19970524	G	2701	5102	TORQUE TUBE     			AMTR  	PITTS 	S1E         	7221024	GL  	LYC   	O360  	AEIO360B4A  	41514	EA  	SNSNCH	76E	76EM8       	EA  	CONTROL COLUMN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL COLUMN TORQUE TUBE HOUSING CRACKED - AIRCRAFT IS MODIFIED WITH AN `ULTIMATE WING' INSTALLED - THIS WING HA	S FULL SPAN AILERONS WITH INCREASED CHORD					1	Q	7	1 	EO	3	O	NC	EXPA1Q71	1E10	5	N	P4EA	 
1997122400329	19971224	00329	CE  	1997	12	24	AU970552         	1	19970522	G	2432	40576	BATTERY         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DC SYS	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) MAIN BATTERY LOW VOLTAGE						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1997122400330	19971224	00330	EU  	1997	12	24	AU970553         	1	19970517	G	5312	5215075013	STIFFENER       			FOKKER	F27   	F27MK50     		EU  										FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD STIFFENER CORRODED						2	H	7	2 	4T			RT	A817    					 
1997122400331	19971224	00331	SO  	1997	12	24	AU970554         	1	19970205	G	3222	702057505	STRUT           			GULSTM	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320E2G     	41508	EA  					NOSE GEAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR STRUT CORRODED (RUSTED) AND SEIZED IN TORQUE TUBE FITTING - PROTECTION BOOT OLD AND DETERIORATED						1	L	7	1 	3O	3	O		A16EA   	E274				 
1997122400332	19971224	00332	CE  	1997	12	24	AU970555         	1	19970425	G	3260	JE1	SWITCH          			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	LANDING GEAR	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWN LIMIT MICROSWITCH LEVER BROKEN OFF						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
1997122400333	19971224	00333	SO  	1997	12	24	AU970556         	1	19970520	G	2910	6770016	PIPE            			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HYDRAULIC MAIN	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC PIPE CONTAINED PIN HOLE CORROSION - CORROSION CAUSED BY LEAKING WINDOW SEALS - LOSS OF HYDRAULIC FLUID						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1997122400334	19971224	00334	EA  	1997	12	24	AU970557         	2	19970517	G	8550	68761	PIPE            	LYC         		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	RECIP ENG	HOLED           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					L797548		L797548			(AUS) RH ENGINE NO6 CYLINDER ROCKER OIL DRAIN LINE CHAFED ON BAFFLE STAY - ROCKER DRAIN PIPE ATTACHMENT HOSES PERISHED -	PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997122400335	19971224	00335	WP  	1997	12	24	AU970558         	1	19970521	G	6320	269A517515	CASE            	HUGHES      	269A517515  	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					MAIN ROTOR GRBOX	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					WGC5875					(AUS) MAIN ROTOR TRANSMISSION UPPER CASE FLIGHT CONTROL SYSTEM LH MOUNTING LUG BROKEN - INDICATIONS APPEAR THAT THE LUG 	HAD BEEN CRACKED FOR SOME TIME - SUSPECT MOUNTING BOLT OVERTORQUED DURING INSTALLATION					1	G	7	1 	3O	3	O		4H12    	1E10				 
1997122400336	19971224	00336	SO  	1997	12	24	AU970559         	2	19970522	G	8520	838092R	CRANKCASE       	CONT        		CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	OUT OF LIMITS   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					838092R		838092R			(AUS) ENGINE CRANKCASE OUT OF LIMITS - FOUND DURING BULK STRIP DUE TO METAL CONTAMINATION - OTHER DEFECTS FOUND INCLUDED	:-1. CAMSHAFT LOBE CASE HARDENING WORN AND LOBE CRACKED 2. THREE CYLINDERS UNSERVICEABLE WITH ONE CYLINDER WORN THROUGH 	 THE HARD CHROME3. INCORRECT PISTON RINGS WERE FITTED PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997122400337	19971224	00337	SO  	1997	12	24	AU970560         	2	19970522	G	8530	653443	VALVE GUIDE     			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENG EXH	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ST5424ST5425		223546			(AUS) NO3 AND NO4 CYLINDER EXHAUST VALVE GUIDES WORN - AIRCRAFT IS INVOLVED IN PARACHUTING OPERATIONS						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997122400338	19971224	00338	CE  	1997	12	24	AU970561         	1	19970523	G	5312	05121761LH	BULKHEAD        		05121872RH  	CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH LOWER AFT DOOR POST BULKHEADS PNO 0512176-1 (LH) ANDPNO 0512187-2 (RH) CRACKED - FOUND DURING INSPECTION	 IAW CESSNA SEB 97-1					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400339	19971224	00339	SO  	1997	12	24	AU970562         	1	19970517	G	7820	7766902	MUFFLER         			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	ENGINE EXH	DISTORTED       	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			520  				L1904915	K1549		(AUS) REAR MUFFLER BAFFLE DISTORTED AND PARTIALLY BLOCKING OUTLET						1	L	7	1 	3O	3	O		A18SO   	E223	5	N	P9045	 
1997122400340	19971224	00340	CE  	1997	12	24	AU970563         	1	19970529	G	5312	05121871LH	BULKHEAD        		05121872RH  	CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE MAIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH LOWER DOOR POST BULKHEADS PNO 0512187-1 (LH) AND PNO0512187-2 (RH) CRACKED - FOUND DURING INSPECTION IAW	 SERVICEBULLETIN SEB 97-1					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400341	19971224	00341		1997	12	24	AU970564         	1	19970526	G	7602	115C6030	BRACKET         								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	MIXTURE CONTROL	CRACKED         	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) MIXTURE CONTROL CABLE SUPPORT/ATTACHMENT BRACKET CRACKED IN AREAOF CABLE ATTACHMENT CLAMP											3	O			E286	5	C	P27EA	 
1997122400342	19971224	00342	SO  	1997	12	24	AU970565         	2	19970505	G	8530	530830	PISTON PIN      	RROYCE      		CESSNA	150   	150B        	2071806	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ENGINE	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					20R374		20R374			(AUS) PISTON PIN PLUG LOOSE AND GALLING ON CYLINDER BORE						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1997122400343	19971224	00343	NM  	1997	12	24	AU970566         	1	19970429	G	5753	BACB30MR8	BOLT            			BOEING	767   	767338      		NM  										TE FLAP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH OUTBOARD TRAILING EDGE FLAP BOLT BROKEN - FOUND DURING INSPECTION IAW ENGINEERING DIRECTIVE ED 19/97						2	L	7	2 	4F			RT	A1NM    					 
1998010600016	19980106	00016	NE  	1998	1	6	AU970567         	2	19970510	G	7200		ENGINE          								RROYCE	RB211 	RB211524G19 		NE  					ENGINE NR 2	FIRE WARNING    	W				K				NONE                    				N	F		FALSE WARNING             	FLT CONT AFFECTED         		LD	LANDING        	1			AU	S 										(AUS) NO2 ENGINE FIRE WARNING - BOTH FIRE BOTTLES DISCHARGED - NO INDICATION OF FIRE EVIDENT											4	F			E30NE				 
1997122400344	19971224	00344	NM  	1997	12	24	AU970568         	1	19970506	G	5315		BEAM            			BOEING	747   	747338      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER DECK FLOOR BEAM AT BS 330 CRACKED ON LH AND RH SIDES - LH SIDE CRACK LENGTH 41.2MM (1.625IN) - CRACK LENGTH 	RH SIDE 76.2MM(3IN) - FLOOR BEAM HAD NOT BEEN MODIFIED IAW ENGINEERING ORDER15672 - AREA IS PART OF SECTION 41					2	L	7	2 	4F			RT	A20WE   					 
1997122400345	19971224	00345	NM  	1997	12	24	AU970569         	1	19970510	G	5315		CHORD           			BOEING	747   	747338      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER DECK CHORD AT LBL 60 CRACKED - FOUND DURING REPAIR OF FLOOR BEAM FOUND IN MDR 97/0568						2	L	7	2 	4F			RT	A20WE   					 
1997122400346	19971224	00346	NM  	1997	12	24	AU970570         	1	19970517	G	5315		WEB             			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER DECK FLOOR BEAM UPPER WEB AT RBL63 CRACKED THROUGH FOUR FASTENER HOLES - CRACK LENGTH 127MM (5IN) - FOUND DU	RING INSPECTION IAW ENGINEERING DIRECTIVE 28/97 REVISION1					2	L	7	4 	4F				A20WE   					 
1997122400347	19971224	00347		1997	12	24	AU970571         	4	19970513	G	2565	101651303	SLIDE           			BOEING	767   	767338      		NM  										ESCAPE SLIDE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR L1 ESCAPE SLIDE INADVERTENTLY DEPLOYED - SLIDE WOULD NOT INFLATE						2	L	7	2 	4F			RT	A1NM    					 
1997122400348	19971224	00348	NE  	1997	12	24	AU970572         	3	19970525	G	6110	4HFR34C652G	PROPELLER       	MCAULY      		FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROP ASSEMBLY	FLUCTUATES      	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					940963			940963		(AUS) PROPELLER CAUSING RPM FLUCTUATIONS - PROPELLER WAS STRIPPED AND INSPECTED WITH NO SATISFACTORY CAUSE OF THE PROBLE	M FOUND					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
1997122400349	19971224	00349	NM  	1997	12	24	AU970573         	1	19970525	G	3213		BOLT            			BOEING	747   	747238B     	1384828	NM  										MAIN GEAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO1 AND NO14 MAIN LANDING GEAR WHEEL AXLE NUT SAFETY BOLTS (ONE OF TWO PER WHEEL) LOOSE - WHEEL HUB CAPS HAD BROKE	N ATTACHMENT LUGS					2	L	7	4 	4F				A20WE   					 
1997122400350	19971224	00350	NM  	1997	12	24	AU970574         	1	19970526	G	5315		WEB             			BOEING	747   	747SP38     		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOOR BEAM WEB AND CHORD CRACKED IN AREA AT BS330/RBL60.31 -WEB CRACK LENGTH 50.8MM (2IN) EXTENDING THROUGH TWO FA	STENER HOLES - CHORD CRACKED FROM FASTENER HOLES IN THREE AREAS - CRACK LENGTHS 0.508MM (0.020IN), 1.016MM (0.040IN) AND	 6.350MM (0.25IN) - FOUND DURING INSPECTION IAW ED 28/97				2	L	7	4 	4F			RT	A20WE   					 
1997122400351	19971224	00351		1997	12	24	AU970575         	4	19970526	G	6122	8971605	GOVERNOR        	WOODWARD    	8971605     	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROP GOVERNOR	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 			4899 		P670C					(AUS) LH ENGINE PROPELLER GOVERNOR HOUSING CRACKED AT RH SIDE UPPER LUG						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1997122400352	19971224	00352		1997	12	24	AU970577         	4	19970602	G	2562	ELT104	ELT             			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	EMERG LOCATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					017242					(AUS) ELT FAULTY - `G' SWITCH UNSERVICEABLE - BATTERIES OF EUROPEAN ORIGIN FITTED - BATTERY INSULATORS WORN - EVIDENCE O	F MOISTURE INGRESS					1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920	 
1997122400353	19971224	00353	SO  	1997	12	24	AU970578         	1	19970528	G	5730		SKIN            			GULSTM	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					WING PLATES/SKIN	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING LOWER SKIN DELAMINATING - ELEVATOR TRIM TAB ALSO DELAMINATED - FOUND DURING INSPECTION IAW SB -155						1	L	7	1 	3O	3	O		A16EA   	E274				 
1997122400354	19971224	00354	SO  	1997	12	24	AU970579         	1	19970528	G	5751		AILERON         			GULSTM	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL CABLES LOOSE - AILERON BEARINGS WORN - OUTBOARD TORQUE TUBES WORN - TRIM TABS LOOSE - FOUND DURING	 INSPECTION IAW SB 165A					1	L	7	1 	3O	3	O		A16EA   	E274				 
1998010600017	19980106	00017	NE  	1998	1	6	AU970580         	2	19970524	G	7261		OIL SYSTEM      			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					TURBINE ENG OIL	LOW QUANTITY    	W				K	E			NONE                    	ENGINE SHUTDOWN         			K			FLUID LOSS                			CR	CRUISE         	1			AU	S 							715081			(AUS) NO3 ENGINE LOST ALL OIL - SUSPECT CAUSED BY TEMPORARY FAULT WITH NO3 CARBON SEAL						2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1997122400355	19971224	00355	EA  	1997	12	24	AU970581         	2	19970526	G	8520	L913361A	CAMSHAFT        	LYC         		PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L913361A		L913361A			(AUS) ENGINE CAMSHAFT LOBE CASE HARDENING CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997122400356	19971224	00356	SW  	1997	12	24	AU970582         	1	19970516	G	1100		DATA PLATE      			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FUSELAGE	FAULTY          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LARGE NUMBERS OF DISCREPANCIES WERE FOUND IN RELATION TO SERIAL NUMBERS - DATA PLATE FITTED DOES NOT MATCH CASA RE	CORDS - SUSPECT MAJOR REBUILD CARRIED OUT FOLLOWING ACCIDENT IN 1988 -PERSONNEL/MAINTENANCE ERROR					1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400357	19971224	00357	SO  	1997	12	24	AU970583         	2	19970521	G	8520	643200	CRANKCASE       	CONT        		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1753 		565359		565359			(AUS) LH AND RH CRANKCASE HALVES CRACKED IN AREA OF NO1 AND NO4 CYLINDER BASE FLANGE						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1997122400358	19971224	00358	CE  	1997	12	24	AU970584         	1	19970509	G	3211	12416142	STUD            	CESSNA      		CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					MAIN GEAR	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR DOWNLOCK SUPPORT ASSEMBLY FORWARD RETAINING STUDS LOOSE - AIRCRAFT HAD BEEN RECENTLY R	EBUILT FOLLOWING AND ACCIDENT 242.3 HOURS PREVIOUSLY - PERSONNEL/MAINTENANCE ERROR					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1997122400359	19971224	00359	EA  	1997	12	24	AU970585         	2	19970529	G	8520	L173368A	CAMSHAFT        	LYC         		PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L173368A		L173368A			(AUS) ENGINE CAMSHAFT LOBE CASE HARDENING CRACKED - COUNTERWEIGHT BUSHINGS WORN						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997122400360	19971224	00360		1997	12	24	AU970586         	4	19970516	G	2300		RADIO SYSTEM    			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					E/E COMPARTMENT	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RADIOS FITTED WITHOUT CERTIFICATION - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400361	19971224	00361	SW  	1997	12	24	AU970587         	1	19970516	G	3340		LIGHTS          			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					EXTERIOR	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NO LANDING LIGHTS FITTED - PERSONNEL/MAINTENANCE ERROR						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400362	19971224	00362	SW  	1997	12	24	AU970588         	1	19970516	G	5310		TUBE            			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FUSELAGE	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TWO STRUCTURAL TUBES DAMAGED - PERSONNEL/MAINTENANCE ERROR						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400363	19971224	00363		1997	12	24	AU970589         	4	19970516	G	2562		ELT             			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					COCKPIT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT ELT FITTED - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART.						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400364	19971224	00364	SW  	1997	12	24	AU970590         	1	19970516	G	7160		CONTROLLER      			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					ENGINE AIR INT	SEIZED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETTOR HEAT CONTROL SEIZED - PERSONNEL/MAINTENANCE ERROR						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400365	19971224	00365	SW  	1997	12	24	AU970591         	1	19970516	G	2622		EXTINGUISHER    			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FIRE PROTECTION	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FITMENT OF FIRE EXTINGUISHER NOT ENTERED IN LOG BOOKS						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400366	19971224	00366	SW  	1997	12	24	AU970592         	1	19970516	G	2823		FUEL SHUTOFF    			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FUEL SELECTOR	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CUTOFF DISCONNECTED						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400367	19971224	00367	SW  	1997	12	24	AU970593         	1	19970516	G	5302		TOOLBOX         			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					ROTORCRAFT TAIL	UNAPPROVED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TOOLBOX MOUNTED IN TAIL BOOM - PERSONNEL/MAINTENANCE ERROR -UNAPPROVED PART						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400368	19971224	00368	SW  	1997	12	24	AU970594         	1	19970516	G	7714		TACHOMETER      			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					ENGINE RPM IND	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT TACHOMETER FITTED - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400369	19971224	00369	SW  	1997	12	24	AU970595         	1	19970516	G	2510		CABIN           			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FLIGHT COMPART	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SUSPECT CABIN RENEWED WITH NO LOG BOOK ENTRY -PERSONNEL/MAINTENANCE ERROR						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400370	19971224	00370	SW  	1997	12	24	AU970596         	1	19970516	G	2510		INERTIA REEL    			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FLIGHT COMPART	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT INERTIA REEL FAULTY - PERSONNEL/MAINTENANCE ERROR						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400371	19971224	00371	SW  	1997	12	24	AU970597         	1	19970516	G	2841		INDICATOR       			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					FUEL QTY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL GAUGES FAULTY - PERSONNEL/MAINTENANCE ERROR						1	G	7	1 	3O	3	O		2H3     	1E13				 
1997122400372	19971224	00372	SO  	1997	12	24	AU970598         	1	19970602	G	5711	202731	WEB             	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING SPAR INBOARD WEB CRACKED - FOUND FOLLOWING REMOVAL OF SPAR CAPS FOR INSPECTION IAW SB-AG-39						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997122400373	19971224	00373	CE  	1997	12	24	AU970600         	1	19970530	G	5312		DOOR POST       	CESSNA      		CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD DOOR POST FRAME CRACKED						1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400374	19971224	00374	SO  	1997	12	24	AU970601         	1	19970428	G	3297	MILW227591618	WIRE            			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C    	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	GEAR SWITCH	BROKEN          	W				O				OTHER                   				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE BROKEN AT TERMINAL						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
1997122400375	19971224	00375	SW  	1997	12	24	AU970602         	1	19970603	G	2752	7003131	ACTUATOR        			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					TE FLAP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3383					(AUS) FLAP ACTUATOR OVER TRAVEL STOP SEPARATED CAUSING DAMAGE TO THE THREAD AND LOSS OF BALLS FROM THE BALLNUT ASSEMBLY 	- FOUND DURING DISASSEMBLY FOR INCORPORATION OF AD/AT/19 - SERVICE LETTER 140					1	L	7	1 	3R	3	R		A9SW    	5E2				 
1997122400376	19971224	00376	SO  	1997	12	24	AU970604         	1	19970603	G	5753	6232800	RIB             	PIPER       		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2822857					(AUS) FLAP RIBS PNO 62328-00 AND PNO 62328-01 CORRODED DUE TO DISSIMILAR METAL CORROSION BETWEEN ATTACHMENT BRACKET AND 	RIBS					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997122400377	19971224	00377	SO  	1997	12	24	AU970605         	1	19970603	G	5711	20273T002	WEB             	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING INBOARD SPAR LOWER WEB ANGLE CRACKED THROUGH RIVET HOLE - CRACK LENGTH 91.44MM (3.6IN) - ANOTHER CRACK FOU	ND ON UPPER WEB ANGLE - CRACK LENGTH 22.85MM (0.9IN) - FOUND DURING REMOVAL OF SPAR CAPS FOR INSPECTION IAW SB-AG-39					1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1998010600018	19980106	00018		1998	1	6	AU970606         	1	19970523	G	2410	630406	DRIVE HUB       	CONT        							CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ALTERNATOR-GEN	SHEARED         	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			285  		C269007		265176R			(AUS) ALTERNATOR DRIVE HUB SHEARED											3	O			E1CE	5	C	P920	 
1997122400378	19971224	00378	SO  	1997	12	24	AU970607         	1	19970603	G	5711	20273T001	WEB             	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING LOWER SPAR WEB ANGLE CRACKED IN THREE PLACES - CRACK LENGTHS 53.34MM (2.1IN), 66.04MM (2.6IN) AND 44.45MM 	(1.75IN) - FOUND FOLLOWING SPAR CAP REMOVAL FOR INSPECTION IAW SB-AG-39					1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1997122400379	19971224	00379	SO  	1997	12	24	AU970608         	1	19970601	G	7160		AIR BOX         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE AIR INT	BLOCKED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							L2148036A			(AUS) CARBURETTOR AIR BOX PARTIALLY BLOCKED BY MUD HORNETS NEST - EVIDENCE OF HORNET IN CARBURETTOR						1	L	7	1 	3O	3	O		2A13    	E286				 
1997122400380	19971224	00380	SO  	1997	12	24	AU970609         	1	19970516	G	3230	9572402	MOUNT           			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	GEAR ATTACH	LOOSE           	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ACTUATOR MOUNTING BRACKET SEPARATED FROM CHANNEL PNO 95599-02 DUE TO INCORRECT RIVETS	 - AIRCRAFT HAD BEEN REPAIRED APPROXIMATELY 800 HOURS PREVIOUSLY -PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O				A7SO    		5	C	P920	 
1997122400381	19971224	00381	SW  	1997	12	24	AU970610         	1	19970521	G	2750	5101017	PULLEY          			GULSTM	680   	680FL       	0141608	SW  										AIRCRAFT SUB-STA	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NEW CABLE PULLEY FAULTY - GROOVE TOO NARROW FOR CABLE TO SIT CORRECTLY INTO GROOVE - PULLEY WAS TO BE FITTED TO VH	-DCA AN AEROCOMMANDER 680FL TO COMPLY WITH AD/AC/88					1	H	7	2 	3O				2A4     					 
1998010800256	19980108	00256		1998	1	8	AU970611         	1	19970604	G	2520	AV94103	SEAT            																	PASS COMPART	ILLEGAL REPAIR  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) BENNETTS SEAT CONVERTER STOWAGE COMPARTMENT (SEAT MOUNTED CONTAINER) INCORRECTLY REPAIRED - PERSONNEL/MAINTENANCE 	ERROR - UNAPPROVED REPAIR																		 
1997122400382	19971224	00382	SO  	1997	12	24	AU970612         	1	19970407	G	7920		HOSE            	LYC         		PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE OIL DIST	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) FLEXIBLE OIL HOSE FROM REAR OF ENGINE TO OIL COOLER FAILED - HOSE HAD BEEN ROUTED BETWEEN CRANKCASE AND EXHAUST ST	ACKS AND HADHARDENED AND BURNT					1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
1997122400383	19971224	00383	SO  	1997	12	24	AU970613         	1	19970603	G	7603	455185	THROTTLE        		487819      	PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360A1A     	41514	EA  					POWER LEVER	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SUSPECT INCORRECT THROTTLE CONTROL FITTED - NO MICROSWITCH IS FITTED FOR THE UNDERCARRIAGE WARNING SYSTEM AND THE 	WIRING IS SECURED BEHIND THE INSTRUMENT PANEL - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART					1	L	7	1 	3O	3	O		1A15    	E286				 
1997122400384	19971224	00384	EA  	1997	12	24	AU970614         	2	19970526	G	7414	M3183	CONDENSER       	SLICK       	4Z70        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	MAGNETO/DIST	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					F90090270		L2656936A			(AUS) RH MAGNETO CONDENSER OPEN CIRCUIT						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
1997122400385	19971224	00385	CE  	1997	12	24	AU970615         	1	19970509	G	5711	04224063	STIFFENER       		04224075    	CESSNA	150   	A150K       	2071824	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NA					(AUS) LH WING SPAR FORWARD STIFFENER PLATE AND SPAR TOP PLATE CONTAINED EXFOLIATION CORROSION						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1997122400386	19971224	00386	SW  	1997	12	24	AU970616         	1	19970502	G	3246	13685L	BEARING         	BFGOODRICH  		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	WHEEL/SKI/FLOAT	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					1343					(AUS) LH OUTBOARD WHEEL BEARING CONE DISINTEGRATED - WHEEL SEPARATED FROM AXLE DURING TAKEOFF - WHEEL RETAINING NUT STIL	L IN PLACE					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
1997122400387	19971224	00387	CE  	1997	12	24	AU970617         	1	19970530	G	3320	M2275916	HARNESS         		M2275920    	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					PASSENGER COMPAR	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) CABIN READING LIGHT HARNESS WIRES BURNT - WIRES WERE CHAFING ON CABIN ROOF PANELS DUE TO INADEQUATE SECURITY AND P	ROTECTION OFTHE HARNESS					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997122400388	19971224	00388	NE  	1997	12	24	AU970618         	2	19970606	G	7321	7918094004	EEC             								PWA   	PWA120	PW125B      		NE  					FUEL CONTROL	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					031					(AUS) LH ENGINE ELECTRONIC ENGINE CONTROL (EEC) FAULTY - DURING INVESTIGATION ALL CONNECTOR PLUGS WERE REMOVED AND CLEAN	ED ANDTHE ENGINE GROUND RUN WITH NO FURTHER FAULTS										4	T			E20NE				 
1997122400389	19971224	00389	GL  	1997	12	24	AU970619         	3	19970603	G	6114	C23	HUB             	MCAULY      		BEECH 	35    	V35A        	1151544	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	PROP HUB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1200 		770832			770832		(AUS) PROPELLER HUB THREADS FAILED EDDY CURRENT INSPECTION - NO2 BLADE LOOSE IN HUB DUE TO BLADE NUT NOT BEING TORQUED A	T LAST ASSEMBLY (SUSPECT AT INITIAL ASSEMBLY AT FACTORY APPROXIMATELY 20 YEARSPREVIOUSLY) - PERSONNEL/MAINTENANCE ERROR					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
1997122400390	19971224	00390		1997	12	24	AU970620         	4	19970603	G	6113	587330	BULKHEAD        	PIPER       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	PROP SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNER AFT BULKHEAD CRACKED AND A SMALL SECTION OF THE FLANGE SEPARATED - THE SECTION WHICH SEPARATED C	ONTAINED TWO OF THE DOME MOUNTING SCREWS - DAMAGE ALSO TO SPINNER DOME					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997122400391	19971224	00391	NM  	1997	12	24	AU970621         	1	19970527	G	2510		PIN             		3A020004107 	BOEING	747   	747238B     	1384828	NM  										FLIGHT COMPARTME	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRST OFFICERS SEAT ADJUSTMENT LOCKING PIN ENGAGING IN SEAT TRACK BY ONLY 3MM (0.118IN)						2	L	7	4 	4F				A20WE   					 
1998010600019	19980106	00019	CE  	1998	1	6	AU970622         	1	19970412	G	6123	8907	ACCUMULATOR     			BEECH 	76    	76          	1153005	CE  						HARTZL	HCM2Y	HCM2YR      	GL  	PROP FEATHER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					RH					(AUS) PROPELLER UNFEATHERING ACCUMULATOR LEAKING INTERNALLY CAUSING LOSS OF AIR CHARGE - SUSPECT WORN PISTON `O' RING SE	ALS					1	L	7	2 	3O				A29CE   		5	C	P43GL	 
1997122400392	19971224	00392	CE  	1997	12	24	AU970623         	1	19970609	G	5312	75469	BULKHEAD        	CESSNA      		CESSNA	172   	172P        	2072436	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					75469					(AUS) LH AND RH FUSELAGE DOOR FRAME BULKHEADS CRACKED BEHIND LAP JOINT						1	H	7	1 	3O			NT	3A12    					 
1997122400393	19971224	00393	EU  	1997	12	24	AU970624         	1	19970529	G	3212	325761	SHEAR HEAD      	GARRTT      	D24762104   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					EMERGENCY FLOAT	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					1002					(AUS) EMERGENCY FLOTATION DEVICE INFLATED DURING FILLING OF BOTTLE -DAMAGE CAUSED TO SIDE DOOR AND LOWER STRUCTURE - SAF	ETY LOCK PINON SHEAR HEAD FITTED AT THE TIME - INVESTIGATION FOUND THAT THE PISTON ASSEMBLY THAT PREVENTS BOTTLE DISCHAR	GE WAS NOT FULLYENGAGED IN THE SHEAR HEAD ALTHOUGH WITNESS MARKS INDICATED THAT THE PISTON HAD BEEN FULLY ENGAGED AT SOM	E TIME -PERSONNEL/MAINTENANCE ERROR			1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997122400394	19971224	00394	NM  	1997	12	24	AU970625         	1	19970528	G	7921	A6492	OIL COOLER      		20008A      	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE OIL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					L952129125					(AUS) ENGINE OIL COOLER CRACKED AND LEAKING - COOLER HAD COMPLETED ONLY 0.7 HOURS SINCE NEW						1	G	7	1 	3O	3	O		H10WE   	E274				 
1997122400395	19971224	00395	GL  	1997	12	24	AU970626         	2	19970513	G	7230	6890550	COMPRESSOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FOD             	W				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			AU	S 					CAC80223		0001NTZ			(AUS) COMPRESSOR DAMAGED BY FOD - INSPECTION SUGGESTS THAT THE FOD WAS A SOFT OBJECT SUCH AS A WASPS NEST RATHER THAN A 	HARD METALIC TYPE OBJECT					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997122400396	19971224	00396	GL  	1997	12	24	AU970627         	3	19970516	G	6111	A163353	SEAL            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER BLADE	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 								736273		(AUS) PROPELLER BLADE NUT TO HUB SEAL LEAKING						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1997122400397	19971224	00397	SO  	1997	12	24	AU970628         	2	19970609	G	8520	554828	CRANKSHAFT      	CONT        		CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					554828		554828			(AUS) ENGINE CRANKSHAFT CRACKED ON OIL SLINGER FACE - STARTER SHAFT HAD FOUR CRACKED TEETH - CAMSHAFT CRACKED ON GOVERNO	R GEAR SPIGOT - CRANKSHAFT GEAR UNSERVICEABLE - TWO COUNTERWEIGHTS UNSERVICEABLE IAW M93-4 - CRANKCASE FRETTING ON BEARI	NG SADDLES - SUSPECT ENGINE SUBJECTED TO A PROPELLER STRIKE				1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA	 
1997122400398	19971224	00398	EU  	1997	12	24	AU970629         	1	19970108	G	2913	MX446203	PUMP            			AIRBUS	320   	A320212     		EU  										HYDRAULIC PUMP	FAILED          	W		A		K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 					MX446203					(AUS) NO1 ENGINE DRIVEN HYDRAULIC PUMP FAILED - INVESTIGATION FOUND THAT ALL THE PISTONS HAD SEPARATED FROM THE PISTON S	HOES - THE YOKE CONTROL SPRING BROKEN - PUMP CONTAMINATED WITH METAL - LOSS OF HYDRAULIC FLUID THROUGH DRIVE SHAFT SEAL					2	L	7	2 	4F			RT	A28NM   					 
1997122400399	19971224	00399	EA  	1997	12	24	AU970630         	2	19970610	G	8520	LW15452	CRANKCASE       	LYC         							LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIP ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2037 		L51768A		L51768A			(AUS) RH ENGINE CRANKCASE CRACKED ADJACENT TO NO3 CYLINDER - CRACK 82.55MM (3.25IN) INTERNAL LENGTH AND 114.3MM (4.5IN) 	EXTERNAL LENGTH										3	O			E14EA	5	C	P33EA	 
1997122400400	19971224	00400	EU  	1997	12	24	AU970631         	1	19970527	G	2750		STRUT           			AIRBUS	320   	A320212     		EU  										TE FLAP CONTROL	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH TRAILING EDGE FLAP INTERCONNECT STRUT OUT OF ADJUSTMENT						2	L	7	2 	4F			RT	A28NM   					 
1997122400401	19971224	00401	EU  	1997	12	24	AU970632         	1	19970528	G	2750	676101258	RESOLVER        			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAP CONTROL	OUT OF ADJUST   	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					10632ANSETTS					(AUS) GREEN SYSTEM FLAP CONTROL UNIT RESOLVER OUT OF ADJUSTMENT - LH FLAP ASYMMETRY BRAKE SOLENOID SHORT CIRCUIT						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1997122400402	19971224	00402		1997	12	24	AU970633         	4	19970528	G	2330	7430213003	CONTROL UNIT    			BOEING	737   	737376      		NM  										ENTERTAIN SYS	FAULTY          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) VIDEO SYSTEM CONTROL UNIT FAULTY - UNIT SMOKING WITH ACCOMPANYING SMELL						2	L	7	2 	4F			RT	A16WE   					 
1997122400403	19971224	00403	NM  	1997	12	24	AU970634         	1	19970520	G	2760	2732513	CONTROL CABLE   			BOEING	737   	737376      	       	NM  										DRAG CONTROL SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					678					(AUS) GROUND SPOILER CABLE FAILED						2	L	7	2 	4F			RT	A16WE   					 
1997122400404	19971224	00404	NM  	1997	12	24	AU970635         	1	19970131	G	5755	65671868	FITTING         			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					SPOILER	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO5 GROUND SPOILER PANEL OUTBOARD ACTUATOR HINGE BRACKET BROKEN ACROSS THE HINGE ATTACHMENT BEARING LUG						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
1997122400405	19971224	00405	CE  	1997	12	24	AU970636         	1	19970611	G	5311	74785	FRAME           	CESSNA      		CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE MAIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					74785					(AUS) LH AND RH FUSELAGE FRAMES CRACKED FROM RELIEF NOTCH TOWARDS UPPER OUTBOARD `HI-SHEAR' FASTENER OF OUTBOARD UNDERCA	RRIAGE CASTING					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997122400406	19971224	00406	NM  	1997	12	24	AU970637         	1	19970407	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:-1. FORWARD FACE OF BULKHEAD WEB CONTAINED THREE CRACKS I	N AREA BELOW RADAR SCANNING MOUNTING BRACKETS AT RBL 5.7 - CRACK LENGTHS 15MM (0.59IN) - 14MM (0.55IN) AND 3MM (0.118IN)	 - FOUND USING ULTRASONIC TECHNIQUE 2. AFT FACE OF BULKHEAD LEFT VERTICAL CHORD INBOARD RADIUS CRACKED AT LB 5.7 - CRACK	 LENGTH 22MM (0.866IN) - FOUND USING EDDY CURRENT TECHNIQUE FOUND DURING INSPECTION IAW ER B73-53-10-39			2	L	7	2 	4F			RT	A16WE   					 
1997122400407	19971224	00407	NM  	1997	12	24	AU970638         	1	19970524	G	5320	BOE20030031	SEAL            			BOEING	737   	737377      		NM  										FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) APU PNEUMATIC DUCT SEAL IN AFT PRESSURE BULKHEAD TORN.						2	L	7	2 	4F			RT	A16WE   					 
1997122400408	19971224	00408	NM  	1997	12	24	AU970639         	1	19970518	G	2750	5701831	SEAL            			BOEING	737   	73733A      	1384673	NM  										TE FLAP CONTROL	DAMAGED         	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 					5380					(AUS) TRAILING EDGE FLAPS NO4 JACKSCREW BALLNUT FELT SEALS DAMAGED ALLOWING WATER INGRESS						2	L	7	2 	4F			RT	A16WE   					 
1997122400409	19971224	00409	GL  	1997	12	24	AU970640         	1	19970422	G	2700		FLIGHT CONTROLS 			AMTR  	JABIRU	JABIRUSK    	05602CU	GL  										FLIGHT CONTROL	LOOSE           	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) AIRCRAFT CONTROLS LOOSE - AIRCRAFT MADE AN EMERGENCY LANDING IN A PLOUGHED PADDOCK BREAKING THREE BOLTS AND A SADD	LE ON THE LH MAIN LANDING GEAR, THE LH BRAKE LINE AND DAMAGING ALL THE SPATS - THIS DEFECT WAS RECEIVED FROM THE AUF AND	 IS FOR INFORMATION ONLY				1	H	7	1 	IO			NC	EXPA1H71					 
1997122400410	19971224	00410	NM  	1997	12	24	AU970641         	1	19970505	G	5312		WEB             			BOEING	737   	737377      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB CONTAINED THREE CRACKS IN AREA BELOW THE RADAR SCANNING MOUNTING BRACKETS - TWO CRAC	KS LOCATED AT LBL 5.7 - ONE CRACK LOCATED AT RBL 5.7 - CRACK LENGTHS 10MM(0.393IN) - FOUND DURING EDDY CURRENT INSPECTIO	N IAW ER B73-53-10-39A				2	L	7	2 	4F			RT	A16WE   					 
1998010800257	19980108	00257		1998	1	8	AU970642         	4	19970515	G	2565	65C1990120	CABLE           			BOEING	737   	737377      	       	NM  										ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD ENTRY DOOR ESCAPE SLIDE LATCH CABLE FRAYED IN AREA OF SWAGED BALL END TERMINAL						2	L	7	2 	4F			RT	A16WE   					 
1998010800258	19980108	00258	EU  	1998	1	8	AU970643         	1	19970607	G	2910	9302631	HOSE            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	HYD MAIN	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC HOSE BETWEEN HYDRAULIC PUMP AND FILTER HOUSING FAILED						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1998010800259	19980108	00259	EA  	1998	1	8	AU970644         	2	19970611	G	7414	M3975	COIL            	SLICK       	4381        	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	OPEN CIRCUIT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					94010058					(AUS) MAGNETO COIL OPEN CIRCUITED						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
1998010800260	19980108	00260	CE  	1998	1	8	AU970645         	1	19970612	G	2730	ANS11A	BOLT            		MS21042L5   	CESSNA	172   	172R        	2072401	CE  										ELEVATOR CONTROL	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER ELEVATOR PULLEY LOCATED AT BULKHEAD AFT OF ELEVATOR BELLCRANK HAD NUT PNO MS21042L5 AND BOLT PNO ANS-11A LOO	SE BUT STILL IN SAFETY - PERSONNEL/MAINTENANCE ERROR					1	H	7	1 	3O			NT	3A12    					 
1998010800261	19980108	00261	CE  	1998	1	8	AU970646         	1	19970610	G	5312	05121871	BULKHEAD        		05121872RH  	CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	DOOR POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD LH AND RH LOWER AFT DOOR POSTS PNO 0512187-1 LH AND PNO 0512187-2 RH CRACKED IN AREA INDICATED B	Y SERVICE BULLETIN					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1998010800262	19980108	00262	NE  	1998	1	8	AU970647         	3	19970611	G	6110	6607	SLIDEBLOCK      		09241       											ROTOL	R390	R3904123F27 	NE  	PROPELLER ASSY	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								DRG102086		(AUS) PROPELLER ADJACENT SLIDEBLOCKS (2OFF) DISLODGED AND DAMAGED																6	C	P31NE	 
1998010800263	19980108	00263	SO  	1998	1	8	AU970648         	1	19970526	G	2140	39D18	COMBUSTOR       	JANITROL    	90D281      	PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	HEATING SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					11801238					(AUS) CABIN HEATER COMBUSTION CAN SPLIT AROUND CIRCUMFERENCE FORAPPROXIMATELY 60MM (2.36IN) - HEATER WAS BEING OVERHAULE	D TO COMPLY WITH REQUIREMENTS OF AD/AIRCON/9 AMDT5 PARA3					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1998010800264	19980108	00264	SO  	1998	1	8	AU970649         	1	19970603	G	5270		SWITCH          			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DOOR WARNING SYS	OUT OF ADJUST   	W				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) REAR ENTRY DOOR MICROSWITCH OUT OF ADJUSTMENT						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1998010800265	19980108	00265	CE  	1998	1	8	AU970650         	1	19970610	G	3213	50450181	WASHER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG SCISSOR	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR SCISSOR LINK CENTRE BOLT PULLED THROUGH LOWER LINK ALLOWING WHEEL TO ROTATE LATERALLY - DURING L	ANDING THE TYRE AND TUBE BLEW OUT - SUSPECT CAUSED BY FAULTY WASHER AND/OR BUSHING					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998010800266	19980108	00266	CE  	1998	1	8	AU970651         	1	19970612	G	5730	95110014206	SKIN            	BEECH       		BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	WS 66 TO 80	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					TC1317					(AUS) RH WING LOWER SKIN CORRODED THROUGH AT FORWARD INBOARD END -CORROSION INITIATED BETWEEN SKIN AND DOUBLER INSTALLED	 AT INBOARD END OF SKIN BETWEEN WS 66.0 AND WS 80.0					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
1998010800267	19980108	00267	SO  	1998	1	8	AU970652         	1	19970514	G	5320		DOOR POST       			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE DOOR PILLAR AND DOOR MAIN CABLE ATTACHMENT BRACKET CRACKED.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1998010800268	19980108	00268	SO  	1998	1	8	AU970653         	1	19970605	G	3234	12037544001	VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					EMERG GEAR SEL	DAMAGED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) EMERGENCY LANDING GEAR SELECTOR VALVE `O' RING SEAL DAMAGED						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1998010800269	19980108	00269		1998	1	8	AU970655         	4	19970607	G	6122	A259	SPRING          	HARTZL      	F624        															PROPELLER GOV	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B3804T					(AUS) PROPELLER CSU SPEEDER SPRING FAULTY - THIS WAS THE THIRD SPRING FITTED																			 
1998010800270	19980108	00270	EA  	1998	1	8	AU970656         	2	19970613	G	7414	10682014	GEAR            	BENDIX      	D4RN2021    	BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  					ENG MAG DIST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					R3460K		L28671A			(AUS) MAGNETO DISTRIBUTOR GEAR TEETH MISSING						1	L	7	2 	3O	3	O		A29CE   	1E10				 
1998010800271	19980108	00271	SO  	1998	1	8	AU970657         	1	19970605	G	3260		SWITCH          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR POS	INCORRECT WIRED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK SWITCH FAULTY - FAILED INSULATION TEST IAW SB/110/32-0052 REV3 - INVESTIGATION FOUND	 THAT THE SWITCH HAD BEEN WIRED DIRECTLY INTO THE LOOM INSTEAD OF THROUGH THE PLUG - THE WIRING SPLICES HAD EVENTUALLY C	ORRODED CAUSING CRACKING - PERSONNEL/MAINTENANCE ERROR				1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1998010800272	19980108	00272	SO  	1998	1	8	AU970658         	1	19970520	G	3242	54413	BRAKE ADJUSTER  	BFGOODRICH  	21585       	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					BRAKE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			900  							(AUS) BRAKE UNIT ADJUSTERS CORRODED AND SEIZED PREVENTING THE BRAKE PISTONS FROM MOVING THE BRAKE STATOR PACK						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1998010800273	19980108	00273	SO  	1998	1	8	AU970659         	1	19970613	G	3230	M81934222	BUSHING         		C040120     	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7556 							(AUS) NOSE LANDING GEAR MAIN DRAG AND LOCKING STRUT PIVOT BUSHINGS AND SHIMS WERE CORRODED						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
1998010800274	19980108	00274	CE  	1998	1	8	AU970660         	1	19970526	G	2432	407610	BATTERY         			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BATTERY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					062129					(AUS) BATTERY FAULTY - REPORTED AS FLAT PRIOR TO ENGINE START - ON COMPLETION OF THE FLIGHT THE BATTERY WAS INSPECTED AN	D WAS FOUNDTO HAVE BULGED ALL AROUND BY AT LEAST 6.35MM (0.25IN) - NO WARNING LIGHTS HAD ILLUMINATED DURING THE FLIGHT					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
1998010800275	19980108	00275	EA  	1998	1	8	AU970661         	2	19970527	G	7322	CK34843	SCREW           	FACET       		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CARB MIX ADJ	MISSING         	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			AU	S 					CK34843		L516076T			(AUS) CARBURETTOR MIXTURE ADJUSTMENT SCREW MISSING - SUSPECT BROKEN FRICTION SPRING ALLOWED SCREW TO UNWIND						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1998010800276	19980108	00276	NE  	1998	1	8	AU970662         	2	19970526	G	7210	3BE	COMBINING GRBOX 			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	FAULTY          	W				K				NONE                    				J	K		WARNING INDICATION        	FLUID LOSS                		DE	DESCENT        	1			AU	S 					CPGB13019		PCE89648			(AUS) ENGINE COMBINING GEARBOX FAULTY - SUSPECT FAULTY CARBON SEAL ALLOWED OIL TO TRANSFER INTO GEARBOX CAUSING OVERFILL	ING AND LOSS OF OIL OVERBOARD					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1998010800277	19980108	00277	GL  	1998	1	8	AU970663         	2	19970521	G	7260	MS210433	NUT             	ALLSN       		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					ENG 2.5 BEARING	SEPARATED       	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					CAG90574		CAE890296S			(AUS) NO2 ENGINE GEARBOX 2.5 BEARING SUPPORT RETENTION NUTS (2OFF6) MISSING - NUTS WERE EVENTUALLY FOUND IN THE OIL PUMP	 SCAVENGE LINE - NUTS WERE NOTED TO BE OF AN UNUSUAL TYPE - SUSPECT UNAPPROVRD PART					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1998010800278	19980108	00278	EU  	1998	1	8	AU970664         	1	19970401	G	6330	350A38101832	MOUNT           			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					M/R TRANS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN TRANSMISSION BI-DIRECTIONAL MOUNT CRACKED - FOUND DURING INSPECTION IAW AD/AS355/47						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1998010800279	19980108	00279	EA  	1998	1	8	AU970665         	2	19970610	G	8530	SL134441	PISTON PIN      	SUPAIRPART  		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENG NR 3 CYL	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					A995		L922939A			(AUS) NO3 CYLINDER PISTON PIN FAILED RESULTING IN FAILURE OF NO3 PISTON. PARTS OF NO3 PISTON LODGED BENEATH NO4 CYLINDER	 EXHAUST TAPPET CAUSING IT TO FAIL ALSO. SECONDARY DAMAGE CAUSED TO CRANKCASE, CONNECTING RODS, CAMSHAFT, NO3 CYLINDER S	KIRT AND NO1, NO2 AND NO3 CYLINDER TAPPETS.				1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1998010800280	19980108	00280	CE  	1998	1	8	AU970666         	1	19970531	G	3230		LANDING GEAR    			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					EMERG EXT LEVER	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR EXTENSION SYSTEM FAULTY - UNABLE TO MOVE EMERGENCY EXTENSION LEVER - LANDING GEAR 60AMP CIRCUIT BREAK	ER POPPED - CIRCUIT BREAKER RESET, EMERGENCY SYSTEM DISENGAGED AND LANDING GEAR EXTENDED NORMALLY - INSPECTION COULD FIN	D NO APPARENT DEFECT IN SYSTEM APART FROM A BUILDUP OF GREASE AROUND THE CLUTCH AREA - GREASE CLEANED OFF AND CLUTCH LUB	RICATED, NEW MOTOR FITTED AS A PRECAUTION - RETRACTION CHECKS CARRIED OUT WITH NO FAULTS EVIDENT			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998010800281	19980108	00281	SO  	1998	1	8	AU970667         	1	19970617	G	5711	202732LH	WEB             	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					6038					(AUS) LH WING INBOARD WEB CRACKED						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1998010800282	19980108	00282	CE  	1998	1	8	AU970668         	1	19970603	G	2434	0012084	ALTERNATOR      			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	DC GEN ALT	WORN            	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					0012084					(AUS) ALTERNATOR BRUSHES WORN - SUSPECT CAUSED BY BRUSH BOUNCE						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1998010800283	19980108	00283	EA  	1998	1	8	AU970669         	2	19970616	G	8520	LW13769	CRANKCASE       								LYC   	O720  	IO720A1B    	41546	EA  					THRU BOLTS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			295  				L116754A			(AUS) CRANKCASE FRETTING IN AREA OF CRANKCASE THROUGH BOLTS											3	O			1E15				 
1998010800284	19980108	00284	EA  	1998	1	8	AU970670         	2	19970606	G	8520	L2755736A	CRANKCASE       	LYC         							LYC   	O360  	O360A4K     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	CYL BASE PAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L2755736A		L2755736A			(AUS) ENGINE CRANKCASE CRACKED IN WEB BETWEEN CYLINDER BASE PADS -CRANKSHAFT GEAR SPALLED - CAM GEAR TEETH SPALLED - FUE	L PUMP IDLER GEAR TEETH SPALLED - OIL PUMP HOUSING SCORED - STARTER RING GEAR CHIPPED										3	O			E286	5	N	P857	 
1998010800285	19980108	00285	EU  	1998	1	8	AU970671         	1	19970610	G	5343	7253620722	SUPPORT         			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	RT NLG BRACE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					C157					(AUS) RH NOSE LANDING GEAR SUPPORT ASSEMBLY WORN BY DRAG BRACE DUE TO MIGRATION OF THE NLG DRAG BRACE TRUNNION BEARING A	ND PIN					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1998010800286	19980108	00286	EU  	1998	1	8	AU970672         	1	19970613	G	2612	89905202	FIRE DETECTOR   			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	RT ENG	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		NR	NOT REPORTED   	1			AU	S 					0497		4201			(AUS) RH ENGINE FIRE DETECTOR CONTROL UNIT FAULTY						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1998010800287	19980108	00287	SO  	1998	1	8	AU970673         	2	19970612	G	8520		CRANKCASE       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENG NR 2 CYL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			683  				172716R			(AUS) LH CRANKCASE HALF CRACKED AT TOP REAR BELOW LH MAGNETO AND CENTER BETWEEN SPINE AND NO2 CYLINDER - CRACK LENGTH 76	.2MM(3IN) RUNNING FORE AND AFT					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998010800288	19980108	00288	EA  	1998	1	8	AU970674         	2	19970618	G	8550	CH48110	FILTER          								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENG OIL	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3472336A			(AUS) DURING FILTER REMOVAL, THE THREADED ADAPTER SECTION OF THE FILTER WAS RETAINED IN THE ENGINE HOUSING - THE FILTER/	ADAPTER IS A SINGLE UNIT WITH THE ADAPTER BEING PART OF THE FILTER WHICH DOES NOT BELONG TO THE ENGINE										3	O			E286	5	C	P27EA	 
1998010800289	19980108	00289	EU  	1998	1	8	AU970675         	1	19970619	G	2121	7861601	FAN ASSEMBLY    		EC35        	FOKKER	F27   	F27MK50     		EU  										LT AIR COND	SEIZED          	W				K				NONE                    				O	B		OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 					860835					(AUS) LH AIRCONDITIONING SYSTEM RECIRCULATING FAN SEIZED						2	H	7	2 	4T			RT	A817    					 
1998010800290	19980108	00290	EU  	1998	1	8	AU970677         	1	19970614	G	3230	L38710SA	SWIVEL          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	RT MLG HYD	SHEARED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					665					(AUS) RH HYDRAULIC SWIVEL UNION IN LANDING GEAR DOWNLOCK LINE SHEARED THE INTERNAL SPINDLE ALLOWING LOSS OF HYDRAULIC FL	UID					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
1998010800291	19980108	00291		1998	1	8	AU970678         	4	19970615	G	6122	89741010AC	GOVERNOR        	WOODWARD    	89741010AC  	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PROPELLER	FAULTY          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			305  		2482734A					(AUS) LH ENGINE PROPELLER GOVERNOR LEAKING OIL FROM THE REAR BODY JOINT - INVESTIGATION FOUND THE TWO SCREWS ATTACHING T	HE SPEED SETTING SHAFT EXTERNAL RETURN SPRING BRACKET TO THE GOVERNOR BODY WERE LOOSE BUT STILL LOCKWIRED ALLOWING A GAP	 TO EXIST				2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
1998010800292	19980108	00292	CE  	1998	1	8	AU970679         	1	19970311	G	3221		PLATE           			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	NLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							10470VO9			(AUS) NOSE LANDING GEAR FACE PLATE DAMAGED						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800293	19980108	00293	SW  	1998	1	8	AU970680         	1	19970616	G	2612	1734361600F	DETECTOR        	FENWAL      	1734361600  	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	RT ENGINE	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RH ENGINE FIRE WARNING SYSTEM SENSOR FAULTY						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
1998011300004	19980113	00004	EA  	1998	1	13	AU970681         	2	19970608	G	7414	10682014	DISTRIBUTOR     	BENDIX      	D4LN3000    	BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  					MAGNETO	STRIPPED        	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			15   		23344					(AUS) MAGNETO PLASTIC DISTRIBUTOR GEAR TEETH STRIPPED						1	L	7	2 	3O	3	O		A29CE   	E286				 
1998010800294	19980108	00294	CE  	1998	1	8	AU970682         	1	19970619	G	2400		ELECTRICAL SYS  			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	LT FIREWALL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT EXPERIENCED ELECTRICAL PROBLEMS. FIBREGLASS PROTECTIVE SHIELD OVER LH AND RH FIELD FUSES ON THE LH FIREWA	LL HAD CHAFED THROUGH THE LH ALTERNATOR FIELD CABLE. PERSONNEL/MAINTENANCEERROR					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800295	19980108	00295	GL  	1998	1	8	AU970683         	1	19970623	G	3213	GM0013	PIVOT           			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  										MLG LUG	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR PIVOT LUGS CRACKED - AIRCRAFT HAD BEEN MODIFIED 28 HOURS PREVIOUSLY BY FITMENT OF HEAVY DUTY 	OUTBACK LANDING GEAR KIT - COMPARISON OF THE LH AND RH MAIN LANDING GEAR LUGS FOUND THAT THE MATERIAL THICKNESS ON THE C	RACKED LH LUGS WAS ONLY 3.175MM (0.125IN) COMPARED TO 6.35MM (0.25IN) ON THE RH LANDING GEAR LUGS - INVESTIGATION FOUND 	THAT THE LANDING GEAR KIT SUPPLIED CONTAINED ONE HEAVY DUTY LEG AND ONE LIGHT DUTY LEG			1	L	7	1 	3O			RT	EXPA1L71					 
1998010800296	19980108	00296	WP  	1998	1	8	AU970684         	1	19970612	G	6310	A1902	DRIVE BELT      			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENG  TRANS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE FORWARD `V' BELT SPLIT AND ROLLED OFF PULLEY.						1	G	7	1 	3O	3	O		H10WE   	E274				 
1998010800297	19980108	00297	CE  	1998	1	8	AU970685         	1	19970311	G	7120		MOUNT           			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	ENGINE MOUNT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							10470VO9			(AUS) RH ENGINE REAR ENGINE MOUNT RUBBER BROKEN.						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800298	19980108	00298	CE  	1998	1	8	AU970686         	1	19970311	G	7160		DOOR            			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	ENGINE AIR INT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							10470VO9			(AUS) ENGINE ALTERNATE AIR DOOR BRACKET LOOSE AND INCORRECTLY RIGGED						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800299	19980108	00299	CE  	1998	1	8	AU970687         	1	19970311	G	5220		EXIT DOOR       			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	EMERGENCY EXIT	SEALED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							10470VO9			(AUS) EMERGENCY EXIT DOOR SEALED CLOSED. SEALANT HAD TO BE CUT TO ALLOW THE EXIT TO BE REMOVED. AD/GEN/37 LAST CARRIED O	UT ON THE 15TH OCTOBER 1996. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800300	19980108	00300	SO  	1998	1	8	AU970688         	2	19970619	G	8530		CYLINDER        			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	ENG NR 2 & NR 6	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 AND NO6 CYLINDERS DAMAGED BY INGESTION OF SEPARATED ALTERNATE AIR DOOR BRACKET. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800301	19980108	00301	CE  	1998	1	8	AU970689         	1	19970619	G	7160		BRACKET         			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	ENGINE AIR INT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE ALTERNATE AIR DOOR BRACKET SEPARATED AND INGESTED INTO ENGINE						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800302	19980108	00302	CE  	1998	1	8	AU970690         	1	19970619	G	7602		NUT             			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	MIXTURE CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MIXTURE CONTROL CABLE OUTER SHEATH NUT NOT ATTACHED						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800303	19980108	00303	CE  	1998	1	8	AU970691         	1	19970619	G	2434		ALTERNATOR      			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	DC GEN-ALT FIELD	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR EMERGENCY FIELD SYSTEM INOPERATIVE. SEE MDR 97/0682FOR ADDITIONAL INFORMATION.						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800304	19980108	00304	CE  	1998	1	8	AU970692         	1	19970619	G	2432		DIODE           			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	BATTERY MASTER	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BATTERY MASTER SYSTEM DIODE INOPERATIVE.						1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800305	19980108	00305	CE  	1998	1	8	AU970693         	1	19970619	G	7120		MOUNT           			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	RT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE RH REAR ENGINE MOUNT LANDS WORN EXCESSIVELY. SEE MDR97/0685 FOR DEFECT ON RH ENGINE LH REAR MOUNT FAILUR	E					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P22EA	 
1998010800306	19980108	00306	EA  	1998	1	8	AU970694         	2	19970603	G	7322	2525464	BEARING         	BENDIX      	FCU         	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL CONTROL	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 			3374 		A45667		PCE85046			(AUS) RH ENGINE FUEL CONTROL UNIT (FCU) FAULTY - BEARING FAILED - FCU TO FUEL PUMP DRIVE COUPLING SHEARED						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998010800307	19980108	00307	SO  	1998	1	8	AU970695         	1	19970617	G	5711	202732LH	WEB             	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					6038					(AUS) LH WING INBOARD WEB CRACKED - DUPLICATE OF MDR 97/0667						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1998010800308	19980108	00308	SO  	1998	1	8	AU970696         	1	19970523	G	2510		SEAT BELT       			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	M76EMMS     	EA  	FLIGHT COMPART	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELTS REWEBBED WITH INCORRECT HEMCO BRAND SEAT BELT HARDWARE - THIS HARDWARE WAS REQUIRED TO BE REMOVED FROM 	SERVICE IAW AD/RES/27  - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PART					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA4	 
1998010800309	19980108	00309		1998	1	8	AU970697         	4	19970219	G	3417	HG480B13	ADC             			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					AIR DATA COMP	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) NO1 AIR DATA COMPUTER FAILED. WORKSHOP INSPECTION FOUND THAT THE PITOT AND STATIC TRANSDUCERS FAILED THE CALIBRATI	ON TEST BUT WERE NOT CONSIDERED TO BE THE CAUSE OF THE FAILURE. FURTHER INVESTIGATION FOUND A DRY SOLDER JOINT ON ONE OF	 THE DC POWER SUPPLY CONNECTING PINS AND DETERIORATED HEAT SINK COMPOUND FORTHE DIODES.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1998010800310	19980108	00310	NM  	1998	1	8	AU970698         	1	19970505	G	3213	4540	CYLINDER        			BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					LT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			18809		4540					(AUS) LH MAIN LANDING GEAR OUTER CYLINDER FORWARD TRUNNION CONTAINEDSEVERAL AREAS OF CORROSION						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1998010800311	19980108	00311	CE  	1998	1	8	AU970699         	1	19970622	G	2730	07341023	TORQUE TUBE     	CESSNA      	053200173LH 	CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ELEVATOR CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ELEVATOR TORQUE TUBE COLLARS PNO 0734102-3 (INBOARD) AND PNO 0734102-4 (OUTBOARD) SEVERELY CORRODED - RI	VET HEADS LOST - RIBS, SKIN AND STRINGERS ALSO CORRODED					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1998011300005	19980113	00005	EA  	1998	1	13	AU970700         	2	19970624	G	8520		GUIDE           	WRIGHT      		LKHEED	1049  	C121C       	5262118	WP  	WRIGHT	R3350 	R3350*      	67040	EA  	HAMSTD	43E	43E60       	NE  	NR 2 CYL INT VLV	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			980  				W560299			(AUS) NO2 ENGINE FRONT SUMP PLUG CONTAMINATED WITH A SMALL PIECE OF FERROUS MATERIAL - INVESTIGATION FOUND PIECE OF META	L HAD CHIPPED OFF NO2 CYLINDER INLET VALVE TAPPET GUIDE					2	L	7	4 	4R	4	R		6A5     	E272	6	C	P871	 
1998010800312	19980108	00312	NE  	1998	1	8	AU970701         	1	19970611	G	7712	9550165380	TRANSMITTER     	TMECA       		SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 1 ENG TORQ	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					15528		15528			(AUS) NO1 ENGINE TORQUE TRANSMITTER FAULTY						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
1998010800313	19980108	00313	EU  	1998	1	8	AU970702         	1	19970507	G	5712		RIB             			AIRBUS	320   	A320212     		EU  										LT RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING INNER REAR SPAR GEAR SUPPORT RIBS CRACKED IN THE FOLLOWING HOLES:- 1. LH WING HOLE 822. RH WING HOL	E 823. RH WING HOLE 87FOUND DURING EDDY CURRENT INSPECTION					2	L	7	2 	4F			RT	A28NM   					 
1998010800314	19980108	00314	SO  	1998	1	8	AU970703         	2	19970326	G	8530	639272	CYLINDER        	CONT        	639272      	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	NR 6 CYL INJ	WORN            	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			548  				20742973L			(AUS) NO6 CYLINDER FUEL INJECTOR NOZZLE HOLE WORN OUT						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1998010800315	19980108	00315	SO  	1998	1	8	AU970704         	2	19970510	G	8530	639272	CYLINDER        	CONT        	639272      	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	SPARK PLUG HOLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			53   		R9059		20742973L			(AUS) ENGINE CYLINDER CRACKED BETWEEN TOP SPARK PLUG HOLE AND INJECTOR NOZZLE - SUSPECT CYLINDER HAD BEEN WELD REPAIRED						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1998010800316	19980108	00316	SO  	1998	1	8	AU970705         	2	19970510	G	8530	639272	CYLINDER        	CONT        	639272      	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	SPARK PLUG HOLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			601  				20742973L			(AUS) ENGINE CYLINDER CRACKED BETWEEN TOP SPARK PLUG HOLE AND INJECTOR NOZZLE						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL	 
1998010800317	19980108	00317	NM  	1998	1	8	AU970706         	1	19970617	G	2760		CONTROL VALVE   			BOEING	747   	747238B     	1384828	NM  										NR 4 SPOILER	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NO4 SPOILER CONTROL VALVE FAULTY						2	L	7	4 	4F				A20WE   					 
1998010800318	19980108	00318	SO  	1998	1	8	AU970707         	1	19970620	G	3230	9529900	STUD            		9529902     	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT RT MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR SIDE BRACE STUDS SUSPECT FAULTY - FOUND DURING MAGNETIC PARTICLE INSPECTION						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P920	 
1998010800319	19980108	00319	EU  	1998	1	8	AU970708         	1	19970315	G	2460		WIRE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENG FIRE EXT	COLD SOLDER     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FIRE EXTINGUISHER CARTRIDGE FIRING CIRCUIT WIRE HAD HIGH RESISTANCE DUE TO POORLY SOLDERED JOINT AK-A1. WIR	E IS LOCATED BETWEEN CIRCUIT BREAKER 1WB9 AND AIRCRAFT ELECTRICAL GROUND VIA UPPER PRODUCTION BREAK 221-01-00 (CONTACT A	K-A1).				2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998010800320	19980108	00320	NM  	1998	1	8	AU970709         	1	19970515	G	6720	A0311	PITCH CONTROL   			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					TAIL ROTOR CONT	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L1618239A			(AUS) TAIL ROTOR PITCH CHANGE ASSEMBLY FAULTY - ASSEMBLY WAS REFITTED AT THE 2000 HOURLY SERVICING WITH NO WORK RELEASE 	ORDER OR RELEASE NUMBER SHOWING IT TO BE OVERHAULED BY ROBINSON HELICOPTER - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED PA	RT				1	G	7	1 	3O	3	O		H10WE   	E274				 
1998010800321	19980108	00321	WP  	1998	1	8	AU970710         	2	19970621	G	7321	210132214	COMPUTER        			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENG FUEL CONT	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			1746 				P31075			(AUS) ENGINE FUEL COMPUTER ELECTRONIC FAILURE						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
1998010800322	19980108	00322	NM  	1998	1	8	AU970711         	1	19970610	G	2761	65448517	ACTUATOR        			BOEING	737   	73733A      	1384673	NM  										NR 4 SPOILER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					5019					(AUS) NO4 SPOILER OUTBOARD ACTUATOR FORWARD ATTACHMENT LUG BROKEN OFF - MINOR DAMAGE TO STRUCTURE ADJACENT TO ACTUATOR						2	L	7	2 	4F			RT	A16WE   					 
1998011300006	19980113	00006	CE  	1998	1	13	AU970712         	1	19970602	G	3260	0003610121	ACTUATOR        			BEECH 	58    	58A         		CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	MLG POS SWITCH	BROKEN          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR MICROSWITCH ACTUATOR STRIKER PLATE BROKEN						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1998010800323	19980108	00323	NM  	1998	1	8	AU970713         	1	19970515	G	6322	A1814	BEARING         			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					COOLING FAN	OUT OF HOURS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1618239A			(AUS) FANSHAFT ASSEMBLY LOWER BEARING OUT OF HOURS - BEARING HAD NOTBEEN REPLACED AT THE 2000 HOURLY INSPECTION - FANSHA	FT ASSEMBLY HAD NO RELEASE NUMBER FROM ROBINSON HELICOPTERS					1	G	7	1 	3O	3	O		H10WE   	E274				 
1998010800324	19980108	00324	NM  	1998	1	8	AU970714         	1	19970529	G	5320		POST            			BOEING	737   	737377      		NM  										WINDOW C-D	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WINDOW POSTS C-D CRACKED IN THE FOLLOWING AREAS:- 1. LH SIDE - CRACK LENGTH 20MM (0.787IN)2. RH SIDE - CRACK LENGT	H 40MM (1.574IN)FOUND DURING EDDY CURRENT INSPECTION					2	L	7	2 	4F			RT	A16WE   					 
1998010800325	19980108	00325	NM  	1998	1	8	AU970715         	1	19970610	G	5754	69388023	ARM             			BOEING	737   	737377      		NM  										LT FOREFLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH FOREFLAP SUPPORT ARM CRACKED THROUGH BOLT HOLE						2	L	7	2 	4F			RT	A16WE   					 
1998010800326	19980108	00326	NM  	1998	1	8	AU970716         	1	19970515	G	6230	A0172	SWASHPLATE      			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR MAST	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1618239A			(AUS) SWASHPLATE ASSEMBLY OUT OF HOURS - ASSEMBLY HAD NO RELEASE NUMBER FOR OVERHAUL AT 2000 HOURS						1	G	7	1 	3O	3	O		H10WE   	E274				 
1998010800327	19980108	00327	NM  	1998	1	8	AU970717         	1	19970610	G	5312	651630084	CHORD           			BOEING	737   	737377      		NM  										FWD PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD LH SIDE CHORD CRACKED IN RADIUS AT WL 207 - CRACK LENGTH 40MM (1.574IN) AND WL 195 - CRA	CK LENGTH 51.5MM (2.027IN) - FOUND DURING INSPECTION IAW ER B73-53-10-39					2	L	7	2 	4F			RT	A16WE   					 
1998010800328	19980108	00328	NM  	1998	1	8	AU970718         	1	19970529	G	5320		POST            			BOEING	737   	737377      		NM  										LT & RT WINDOW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH C-D WINDOW POSTS CRACKED IN UPPER CORNERS - FOUND DURING EDDY CURRENT INSPECTION						2	L	7	2 	4F			RT	A16WE   					 
1998010800329	19980108	00329	SO  	1998	1	8	AU970719         	1	19970626	G	7700		INDICATOR SYSTEM			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AND LH TORQUE SYSTEMS, RH AND LH T5 INDICATORS, RH T5 CIRCUIT RESISTANCE, LH AND RH FUEL PRESSURE INDICATION SY	STEMS, RH LOWFUEL WARNING SYSTEM, LH AND RH FUEL QUANTITY SYSTEMS, LH OIL PRESSURE INDICATION, LH GYRO COMPASS, STANDBY 	COMPASS AND RH GYRO COMPASS SYSTEM ALL OUT OF ADJUSTMENT.				1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA	 
1998010800330	19980108	00330		1998	1	8	AU970720         	4	19970219	G	2565	1RDOOR00061LDOO	SLIDE           			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					DOOR 1L & 1R	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					1RDOOR00061L					(AUS) DOOR 1L AND 1R ESCAPE SLIDES HAD MAINTENANCE PINS FITTED -PERSONNEL/MAINTENANCE ERROR						2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998010800331	19980108	00331	EU  	1998	1	8	AU970721         	1	19970513	G	3620	EL12400	DETECTOR        			AMD   	FALC50	FALCON900   	2700160	EU  										BLEED OVHEAT	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) BLEED AIR OVERHEAT DETECTOR UNIT FAULTY - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION 	ONLY					2	L	7	3 	4F			RT	A46EU   					 
1998010800332	19980108	00332	EU  	1998	1	8	AU970722         	1	19970517	G	3620	EL12400	DETECTOR        			AMD   	FALC50	FALCON900   	2700160	EU  										BLEED OVHEAT	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) BLEED AIR OVERHEAT DETECTOR UNIT FAULTY - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION 	ONLY					2	L	7	3 	4F			RT	A46EU   					 
1998010800333	19980108	00333	EU  	1998	1	8	AU970723         	1	19970522	G	3260	D576871	BRACKET         			AMD   	FALC50	FALCON900   	2700160	EU  										MLG  POS SWITCH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR PROXIMITY SWITCH ATTACHMENT BRACKET CRACKED- THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF	 AND IS FOR INFORMATION ONLY					2	L	7	3 	4F			RT	A46EU   					 
1998010800334	19980108	00334	CE  	1998	1	8	AU970724         	1	19970630	G	5341	08113507	FITTING         			CESSNA	411   	411         	2075902	CE  	CONT  	O520  	GTSIO520C   	17032	SO  	MCAULY	3AF34C	3AF34C74    	GL  	RT WING ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER RH FUSELAGE WING ATTACHMENT FITTING CONTAINED EXFOLIATION CORROSION ON LOWER SURFACE						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P22EA	 
1998010800335	19980108	00335	EU  	1998	1	8	AU970725         	1	19970626	G	3240	704841	CONTROL VALVE   			FOKKER	F27   	F27MK50     		EU  										RT MLG  BRAKE	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					101					(AUS) RH ALTERNATE BRAKE CONTROL VALVE FAULTY - BOTH RH MLG TYRES BLEW						2	H	7	2 	4T			RT	A817    					 
1998010800336	19980108	00336	NE  	1998	1	8	AU970726         	2	19970627	G	7250	6082T17G01	TURBINE         	GE          	6082T17G01  	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	LT ENGINE	FAILED          	W		A		K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			2184 		GEL085343		785239	7250		(AUS) LH ENGINE POWER TURBINE MODULE FAILED - INVESTIGATION FOUND THAT THE STAGE 2 FORWARD COOLING PLATE HAD SEPARATED A	T THE OUTER RIM- THE COOLING PLATE WAS A PRE SB 72-392 ITEM					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
1998010800337	19980108	00337	GL  	1998	1	8	AU970727         	3	19970620	G	6111	BV561	BLADE           	HARTZL      		MTSBSI	MU2   	MU2B30      	5780410	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	RT PROPELLER	SEPARATED       	W				K	E			NONE                    	ENGINE SHUTDOWN         			E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CR	CRUISE         	1			AU	S 					BV561			BV561		(AUS) RH PROPELLER NO3 BLADE SEPARATED AT BLADE ROOT. EXTENSIVE DAMAGE CAUSED TO REDUCTION GEARBOX, ENGINE, ENGINE MOUNT	S, COWLING AND NACELLE.					1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1998010800338	19980108	00338	GL  	1998	1	8	AU970729         	1	19970610	G	2701	54130SF198ZA	CONTROL COLUMN  			AMTR  	XL    	EAGLEXL2    		GL  										HAND GRIP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL COLUMN HAND GRIP BROKEN						1	H	7	1 	3I				EXPA1H71					 
1998010800339	19980108	00339	SO  	1998	1	8	AU970730         	2	19970627	G	8540	21502	SEAL            								CONT  	O240  	IO240A      		SO  					VAC PUMP PAD	LOOSE           	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 							806015			(AUS) VACUUM PUMP DRIVE SHAFT SEAL LOOSE - FOUND WHEN PAD BLANKING PLATE REMOVED TO RECTIFY OIL LEAK - NO VACUUM PUMP FI	TTED TO THIS AIRCRAFT										3	O			E7SO				 
1998010800340	19980108	00340	CE  	1998	1	8	AU970731         	1	19970601	G	2434	ALV9407	ALTERNATOR      	CONT        		CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GEN-ALT	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) LH ALTERNATOR FAILED - INSPECTION FOUND THAT THE FAILURE WAS DUE TO THE DIODE PLATE GROUND WIRE BEING LOOSE						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL	 
1998010800341	19980108	00341	SO  	1998	1	8	AU970732         	2	19970622	G	8520	642001	CRANKCASE       	CONT        		CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NR 3 & NR 5 CYL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			610  				200545			(AUS) CRANKCASE CRACKED IN AREA OF NO3 AND NO5 CYLINDER PADS - CRACKS RADIATED FROM CYLINDER BASE STUD HOLES						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1998010800342	19980108	00342	EA  	1998	1	8	AU970733         	2	19970319	G	8520	SL11575	BEARING         	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NR 3 JOURNAL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L86868AC		L86868AC			(AUS) NO3 BEARING FAULTY - BEARING DOWEL ON NO3 JOURNAL HAD MOVED - SUSPECT INCORRECT FITMENT						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998010800343	19980108	00343	EA  	1998	1	8	AU970734         	2	19970603	G	8520	LW16514	CAMSHAFT        	LYC         		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L31872			(AUS) CAMSHAFT LOBES SPALLED AND VALVE LIFTER FACES DAMAGED - METAL CONTAMINATION OF OIL SYSTEM - LW16702ADDITIVE USED A	T EACH OILCHANGE					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1998010800344	19980108	00344	EA  	1998	1	8	AU970735         	2	19970603	G	8520	LW16514	CAMSHAFT        	LYC         		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE LIFTER	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L31872			(AUS) ENGINE CAMSHAFT LOBES SPALLED AND VALVE LIFTER FACES DAMAGED -METAL CONTAMINATION OF OIL SYSTEM - LW16702 ADDITIVE	 USED AT EACH OIL CHANGE					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1998010800345	19980108	00345	CE  	1998	1	8	AU970736         	1	19970517	G	3230	70000150	CIRCUIT BREAKER 			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG MOTOR	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR MOTOR 50AMP CIRCUIT BREAKER INTERMITTENT						1	L	7	2 	3T	3	T		3A20    	E4EA	6	C	P15EA	 
1998010800346	19980108	00346	WP  	1998	1	8	AU970737         	1	19970617	G	3710	CV6770	PUMP            		V3035       	DOUG  	DC3   	DC3CR183090C	3021466	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	LT ENG VAC	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					P96668		629			(AUS) LH ENGINE DRIVEN VACUUM PUMP FAULTY						2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603	 
1998011300007	19980113	00007	SO  	1998	1	13	AU970738         	1	19970627	G	5711	20207T902	SPAR CAP        	AYRES       		AYRES 	S2    	S2RT65      		SO  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					010DC					(AUS) RH WING LOWER SPAR CAP CRACKED FROM BOLT HOLE - CRACK LENGTH 3.048MM (0.120IN) - FOUND DURING MAGNETIC PARTICLE IN	SPECTION					1	L	7	1 	4F	4	T	RT	A4SW    	E4EA	6	C	P44GL	 
1998010800347	19980108	00347	GL  	1998	1	8	AU970739         	3	19970623	G	6114	D22015	HUB             	HARTZL      							CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	SEAL GROOVE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AM3027			AM3027		(AUS) PROPELLER HUB EXTENSIVELY CORRODED IN MOUNTING SEAL GROOVE											3	O			E1CE	5	C	P920	 
1998011300008	19980113	00008		1998	1	13	AU970740         	1	19970301	G	6123	C5328	SPRING          													MCAULY	4HFR34	4HFR34C652  	NE  	PROP FEATHER	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								890966		(AUS) PROPELLER FEATHERING/UNREVERSING SPRING FAILED																6	C	3PNE	 
1998010800348	19980108	00348	GL  	1998	1	8	AU970741         	3	19970616	G	6114	DP215	HUB             	HARTZL      												HARTZL	HCE2Y	HCE2YR2     	GL  	PROP HUB	ILLEGAL MOD     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					DP215			DP215		(AUS) PROPELLER HUB HAD UNAPPROVED MODIFICATIONS - HUB HAD BEEN ILLEGALLY MODIFIED FROM -E2YR TO -E2YL CONFIGURATION BY 	INSERTION OF VARIOUS ILLEGALLY MADE BUSHES BEING INSERTED INTO THE DOWELHOLES - PERSONNEL/MAINTENANCE ERROR - UNAPPROVED	 MODIFICATION														5	C	P9EA	 
1998010800349	19980108	00349	SO  	1998	1	8	AU970742         	1	19970621	G	3232	WTE22461	ACTUATOR        	WIEBEL      	WTE22461    	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					MLG  DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1075					(AUS) LH OUTBOARD MAIN LANDING GEAR DOOR ACTUATOR TOP BEARING LUG BROKEN						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1998010800350	19980108	00350	GL  	1998	1	8	AU970743         	2	19970622	G	7230	6853337	COMPRESSOR      	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE COMP	FOD             	W				K				NONE                    				E	R	C	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	F.O.D.                    	CL	CLIMB          	1			AU	S 			3045 		CAT22383P		CAT22383P			(AUS) COMPRESSOR DAMAGED BY FOD						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998011500128	19980115	00128	NM  	1998	1	15	AU970744         	1	19970430	G	5312		STRAP           			BOEING	747   	747312      	1384932	NM  										BS 1241	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD SPLICE STRAP LOCATED AT BS1241 CRACKED ON LHAND RH SIDES AT FORWARD AND AFT HOLES						2	L	7	4 	4F			RT	A20WE   					 
1998011500129	19980115	00129	NM  	1998	1	15	AU970745         	1	19970516	G	5411		FASTENER        			BOEING	747   	747312      	1384932	NM  										NR 1 & NR4 PYLON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO1 AND NO4 PYLON AFT DIAGONAL BRACE FORWARD MOUNT FITTINGS HAD LOOSE HILOCK FASTENERS.						2	L	7	4 	4F			RT	A20WE   					 
1998011500130	19980115	00130	NM  	1998	1	15	AU970746         	1	19970516	G	2700		CABLE GUARD     			BOEING	747   	747312      	1384932	NM  										FLIGHT CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NUMEROUS CABLE GUARD ASSEMBLIES IN MAIN CABIN CABLE VERTICAL RUNS CRACKED AND EMBRITTLED - CABLE OPERATING SYSTEMS	 INCLUDED AILERON, WING FLAP, NOSEWHEEL STEERING AND LANDING GEAR BRAKES -IN ADDITION VERTICAL CABLE GUARDS IN FORWARD C	ARGO COMPARTMENTFOR NO3 AND NO4 ENGINE CONTROL CABLES WERE FOUND BROKEN				2	L	7	4 	4F			RT	A20WE   					 
1998011500131	19980115	00131	NM  	1998	1	15	AU970747         	1	19970527	G	5315		BEAM            			BOEING	747   	747312      	1384932	NM  										BS 980	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER DECK FLOOR BEAM STRUCTURE AT BS 980 CONTAINED CORROSION IN AREA OF CART LIFT CUTOUT ON THE AFT FACE OF THE U	PPER CHORD BETWEEN RBL 20 AND RBL 30 - CORROSION WAS CLASSIFIED AS LEVEL 2 AND LEVEL 3 - FOUND DURING INSPECTION IAW BOE	ING ALERT SB 747-53A2400 - MINOR CORROSION ALSO FOUND ON UPPER FAILSAFE STRAP				2	L	7	4 	4F			RT	A20WE   					 
1998011500132	19980115	00132	NM  	1998	1	15	AU970748         	1	19970528	G	5313		STRINGER        			BOEING	747   	747312      	1384932	NM  										BS 1820-1840	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRINGERS 51L AND 51R LOCATED IN AFT CARGO COMPARTMENT FUSELAGE BILGE AREA (SECTION 46) CONTAINED EXFOLIATION CORR	OSION IN AREAS FROM BS 1820 TO BS 1840:- STRINGER 51L - EXFOLIATION CORROSION IN VERTICAL FLANGE OF TOP HAT SECTION OF E	XTRUDED STRINGER STRINGER 51R - CORROSION IN BASE OF TOP HAT EXTRUDED STRINGER -  CRACK ALSO FOUND AT BS 1860				2	L	7	4 	4F			RT	A20WE   					 
1998011500133	19980115	00133	NM  	1998	1	15	AU970749         	1	19970527	G	5320		CHORD           			BOEING	747   	747312      	1384932	NM  										BS 400	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL WELL STRUCTURE LOWER CHORD AT BS 400 BADLY CORRODED FROM STRINGER 42L TO STRINGER 42R						2	L	7	4 	4F			RT	A20WE   					 
1998011500134	19980115	00134	NE  	1998	1	15	AU970750         	2	19970425	G	7210	314166A	BEARING         	PWA         		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					RED GRBOX NR 10	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2416 		CP6B1208		62519128			(AUS) RH REDUCTION GEARBOX NR10 BEARING SPALLED ON BALLS AND INNER ANDOUTER RACES - LH REDUCTION GEARBOX NR10 BEARING HA	D SLIGHT SPALLING ON THE INNER RACE AND DENTS ON THE BEARING SPLIT LINEEDGE					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1998011500135	19980115	00135		1998	1	15	AU970752         	4	19970508	G	6113		NUT             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROP SPINNER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH PROPELLER SPINNER FORWARD SECURING NUT LOOSE AND LOCKWIRE BROKEN - THREAD ON STUD STRIPPED						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998011500136	19980115	00136	NM  	1998	1	15	AU970754         	1	19970611	G	5312	BS178	BULKHEAD        			BOEING	737   	737376      		NM  										BS 178	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PRESSURE BULKHEAD WEB AT BS 178 CRACKED IN FIVE PLACES ADJACENT TO WEATHER RADAR SUPPORT BRACKET ATTACHMENTS						2	L	7	2 	4F			RT	A16WE   					 
1998011500137	19980115	00137	SO  	1998	1	15	AU970755         	1	19970622	G	2731	4173428	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	ELEV TAB CONT	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) ELEVATOR FORWARD TRIM CABLE KINKED IN AREA OF TRIM SERVO PULLEY						1	L	7	2 	3O			 	A20SO   		5	C	P33EA	 
1998011500138	19980115	00138	CE  	1998	1	15	AU970756         	1	19970519	G	5220		EXIT DOOR       			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	EMERGENCY EXIT	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) EMERGENCY EXIT DOOR SEPARATED FROM AIRCRAFT - AIRCRAFT HAD JUST COMPLETED A STRIP AND REPAINT AND IT IS SUSPECTED 	THAT THE EXIT DOOR HAD BEEN DISTURBED DURING THIS PROCESS					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998011500139	19980115	00139	NM  	1998	1	15	AU970760         	1	19970424	G	2897	11892221	WIRE            		6098976     	BOEING	747   	747312      	1384932	NM  										FUEL BOOST PUMP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					11892221					(AUS) NO2 FUEL BOOST PUMP ELECTRICAL WIRING INSULATION FAILED DUE TO CONDUCTIVE CORROSION AT THE WIRE TERMINAL ASSEMBLY						2	L	7	4 	4F			RT	A20WE   					 
1998011500140	19980115	00140	CE  	1998	1	15	AU970761         	1	19970612	G	5720	21976	FITTING         			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	AEIO320E2B  	41508	EA  	SNSNCH	74D	74DM        	EA  	WING STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING STRUT ATTACHMENT FITTING CRACKED - FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/CHA22/2 - CRACK ORIGINATE	D FROM AIRCRAFT TIEDOWN ATTACHMENT					1	H	7	1 	3O	3	O		A21CE   	1E12	5	N	P88614	 
1998011500141	19980115	00141	CE  	1998	1	15	AU970762         	1	19970507	G	3242	1773	PIN             	PARKERHANFI 	KIT19961    	CESSNA	195   	195A        	2073110	CE  	JACOBP	R755  	R755A2      	35006	SW  	HAMSTD	2B	2B20        	NE  	BRAKE	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							3151	6317		(AUS) LH BRAKE FAILED. TWO LININGS SEPARATED FROM BACKING PLATE AND WHEEL ASSEMBLY. LH WING TIP, LH ELEVATOR AND STABILI	SER TIP CONTACTED RUNWAY. INVESTIGATION FOUND THAT THE BRAKE DISCS HAD BEEN GROUND AND WERE APPROXIMATELY 1.524MM (0.060	IN) UNDER SIZE.THE AIRCRAFT WAS ON THE FIRST FLIGHT FOLLOWING A PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR				1	H	7	1 	3R	3	R		A790    	TC237	5	C	P255	 
1998011500142	19980115	00142	CE  	1998	1	15	AU970763         	1	19970609	G	2910	5817127	PIPE            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3AF34C	3AF34C74    	GL  	HYDRAULIC	WORN            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PRESSURE PIPE ATTACHED TO `T' UNION WORN AND CRACKED						1	L	7	2 	3O				A25CE   		5	C	P22EA	 
1998011500143	19980115	00143	CE  	1998	1	15	AU970768         	1	19970630	G	2820	R58	PIPE            	CESSNA      		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT &RT FUEL TANK	MIS-INSTALLED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					R0058					(AUS) FUEL TRANSFER SYSTEM INCORRECTLY FITTED - FUEL LINES TO THE TRANSFER PUMP WERE REVERSED - PROBLEM FOUND IN BOTH RH	 AND LH FUEL TANKS - PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998011500144	19980115	00144	EA  	1998	1	15	AU970769         	2	19970630	G	8550	76539	VALVE           			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENG OIL FILTER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			49   				L219474A			(AUS) ENGINE OIL FILTER VALVE STUCK - FILTER COLLAPSED AND FILTER HOUSING BASE GASKET BLEW OUT - SUSPECT CAUSED BY COLD 	MORNING STARTS (VISCOUS OIL) AND POOR STARTING TECHNIQUES					1	L	7	1 	3O	3	O		2A13    	E295	5	C	P27EA	 
1998011500145	19980115	00145	SO  	1998	1	15	AU970770         	2	19970624	G	7314	64621217A1	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE FUEL PUMP	WORN            	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					A109710BR		27763R			(AUS) ENGINE DRIVEN FUEL PUMP VANES DAMAGED. SMALL PORTIONS OF THE PUMP BLADES LODGED IN THE RELIEF VALVE						1	L	7	2 	3O	3	O		3A10    	E5CE				 
1998011500146	19980115	00146	NM  	1998	1	15	AU970771         	1	19970626	G	3242	AHA1693	BRAKE           			BOEING	757   	757260PF    		NM  										NR6 MLG WHEEL	WORN            	W				K				NONE                    				O	A		OTHER                     	FLAME/FIRE                		NR	NOT REPORTED   	1			AU	S 										(AUS) NO6 MAIN WHEEL BRAKE ASSEMBLY CAUGHT FIRE WHEN PARK BRAKE SET - FLASH FIRE WAS EXTINGUISHED BY ITSELF - SUSPECT GR	EASE INCORRECTLY APPLIED BETWEEN AXLE BUSH AND SPACE DURING WHEELCHANGE IGNITED					2	L	7	2 	4F			RT	A2NM    					 
1998011500147	19980115	00147	EU  	1998	1	15	AU970772         	1	19970217	G	2420	HC924H915	LOOM            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 AC GEN	CHAFED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) NO1 GENERATOR PHASE `B' GENERATOR FEEDER CABLE AND NEUTRAL CURRENT TRANSFORMER SHORT CIRCUITING DUE TO CHAFING ON 	`P' CLIP					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998011500148	19980115	00148	EU  	1998	1	15	AU970773         	1	19970322	G	3234	9361	CLUTCH          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					GEAR SELECTOR	SLIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					786GB290HANS					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR CLUTCH SLIPPING.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998011500149	19980115	00149	NE  	1998	1	15	AU970775         	1	19970420	G	3230		LANDING GEAR    			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					GEAR RETRACT	MALFUNCTION     	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR WOULD NOT RETRACT - SUSPECT INTERMITTENT PROBLEM CAUSED BY THERMAL EXPANSION						1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1998012100002	19980121	00002	EU  	1998	1	21	AU970776         	1	19970613	G	5350	365A231424	FAIRING         			AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING FAIRING CRACKED						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1998011500150	19980115	00150	SO  	1998	1	15	AU970778         	1	19970620	G	5280		DOOR            			PIPER 	PA34  	PA34200T    	7103406	SO  						MCAULY	3AF34C	3AF34C503   	GL  	GEAR DOOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR DOOR OUTER SKIN SEPARATED FROM INTERNAL STRUCTURE -DAMAGE HAD BEEN COVERED WITH SILASTIC						1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1998011500151	19980115	00151	SO  	1998	1	15	AU970779         	1	19970620	G	3211	67415W	TRUNNION        			PIPER 	PA34  	PA34200T    	7103406	SO  						MCAULY	3AF34C	3AF34C503   	GL  	MLG	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR LEG TRUNNION FAULTY - THE FOUR MAIN ATTACHMENTHOLES WERE OVERSIZE COMPARED TO THE FASTENERS - HO	LES WERE7.937MM (0.3125IN) DIAMETER INSTEAD OF 6.35MM (0.25IN)					1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1998011500152	19980115	00152	CE  	1998	1	15	AU970780         	1	19970620	G	5341	512122	BLOCK           	CESSNA      		CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	WING ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					17255097					(AUS) FUSELAGE REAR SPAR WING ATTACHMENT BLOCK CRACKED AND CORRODED						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1998011500153	19980115	00153	CE  	1998	1	15	AU970781         	1	19970206	G	5341	512122	BLOCK           	CESSNA      		CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	WING ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					17254962					(AUS) FUSELAGE REAR SPAR WING ATTACHMENT BLOCK CRACKED AND CORRODED BETWEEN BLOCKS AND INNER SURFACE OF SPAR						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1998011500154	19980115	00154	CE  	1998	1	15	AU970783         	1	19970624	G	5520	12346251	HINGE           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ELEV LT OUTB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD ELEVATOR HINGE ASSEMBLY CRACKED ALONG WELD - CRACK LENGTH APPROXIMATELY 8MM (0.314IN)						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1998011500155	19980115	00155	CE  	1998	1	15	AU970784         	1	19970630	G	5511	523198	SPAR            	CESSNA      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER FORWARD SPAR PNO 0523001-98 AND CENTRE SKIN PNO 0532001-23 CRACKED - SPAR HAD PREVIOUSLY BEE	N REPAIRED -FOUND DURING INSPECTION IAW AD/C170/59 AND CESSNA SB 94-8					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1998011500156	19980115	00156	SW  	1998	1	15	AU970787         	1	19970628	G	2913	RD24336	COUPLING        	ROMEC       	206076022   	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYDRAULIC PUMP	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 					B4327					(AUS) HYDRAULIC PUMP DRIVE COUPLING FAILED						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998011500157	19980115	00157	EU  	1998	1	15	AU970788         	1	19970630	G	6410	355A1244	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR BLADE LEADING EDGE EROSION STRIP DELAMINATED (DEBONDED) - DEBONDING EXTENDS SPANWISE FROM AN AREA 105MM	(4.13IN) FROM THE INBOARD END OF THE STRIP TO 98MM (3.85IN) FROM THE OUTBOARD END AND CHORDWISE FROM THE TRAILING EDGE T	O 25MM (1IN) TOWARDS THE LEADING EDGE				1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1998011500158	19980115	00158	NE  	1998	1	15	AU970792         	2	19970427	G	7532	85711ANSETTSN	VALVE           								GE    	CF6   	CF680A      	30025	NE  					RT BLEED	WORN            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					850711ANSETT					(AUS) RH BLEED AIR VALVE FAULTY. WORKSHOP INSPECTION FOUND VALVE SHAFT WORN AT CONVEX SEALING RING.											4	F			E13NE				 
1998011500159	19980115	00159	EU  	1998	1	15	AU970795         	1	19970620	G	5311	TB121112	FRAME           			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME NO9 CRACKED AT TOP RH RADIUS IN AREA ABOVE STABILATOR ATTACHMENT FITTING - FOUND DURING INSPECTION 	IAW AD/TB10/11/01					1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920	 
1998011500160	19980115	00160	EU  	1998	1	15	AU970798         	1	19970415	G	3244	DR2723T	TIRE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT MLG NR 2	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					GV144291ANSS					(AUS) LH MAIN LANDING GEAR NO2 MAIN WHEEL TYRE DEFLATED DUE TO SIDEWALL FAILURE.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998011500161	19980115	00161	SO  	1998	1	15	AU970799         	2	19970620	G	8530	64137	CYLINDER        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	MCAULY	3AF34C	3AF34C503   	GL  	NR 2 - 4 &6	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			780  				3683			(AUS) NO6 CYLINDER EXHAUST FLANGE DISTORTED - 2MM (0.078IN) GAP ON FORWARD SIDE - FURTHER INVESTIGATION FOUND NO2 AND NO	4 CYLINDERS WITH APPROXIMATELY 1MM (0.039IN) GAPS - HEAT DAMAGE TO ENGINE COWLS FROM LEAKING EXHAUST GASSES - NEW GASKET	S HAD BEEN FITTED APPROXIMATELY 50 HOURS PREVIOUSLY				1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1998011500162	19980115	00162	SO  	1998	1	15	AU970800         	1	19970620	G	3246	13889	BEARING         		13836       	PIPER 	PA34  	PA34200T    	7103406	SO  						MCAULY	3AF34C	3AF34C503   	GL  	RT MLG WHEEL	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN WHEEL BEARINGS PNO 13889 AND PNO 13836 IN POOR CONDITION- WATER FOUND IN BEARING HOUSING INDICATING AIRCRA	FT HAD BEEN SUBJECTED TO WET CONDITIONS					1	L	7	2 	3O				A7SO    		5	C	P22EA	 
1998011500163	19980115	00163		1998	1	15	AU970801         	4	19970620	G	2562	ELT114	BATTERY         		ELT1104     	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	EMERG LOCATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					55139					(AUS) ELT BATTERY PACK CRACKED AND LEAKING - ELT BATTERY MOUNTING TRAY AND STRUCTURE BENEATH ELT CONTAMINATED						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1998011500164	19980115	00164	CE  	1998	1	15	AU970805         	1	19970603	G	3260		LIGHT BULB      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG GEAR POS	FAILED          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR INDICATOR LIGHTS BLOWN						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
1998011500165	19980115	00165		1998	1	15	AU970808         	4	19970624	G	2210		AUTOPILOT       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AFCS SYSTEM	MALFUNCTION     	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) AUTOFLIGHT CONTROL SYSTEM (AFCS) SUSPECT FAULTY - UNUSUAL ADVISORY MESSAGES						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998011500166	19980115	00166	NM  	1998	1	15	AU970809         	1	19970626	G	2434		GENERATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					DC GEN-ALT	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) LH AND RH ENGINE DRIVEN DC GENERATORS FAILED - LH AC BUS ALSO FAILED - SUSPECT CAUSED BY STATIC DISCHARGE						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998011500167	19980115	00167		1998	1	15	AU970810         	4	19970528	G	2565	7A12544	SLIDE           			BOEING	747   	747338      		NM  										NR 3 MAIN ENTRY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					G3672					(AUS) NO3 MAIN ENTRY DOOR ESCAPE SLIDE DEFLATE DURING TEST - SUSPECT CAUSED BY TEARING OF THE FABRIC BY THE DOOR DUST SE	AL PLASTIC RETAINER METAL CORNER					2	L	7	2 	4F			RT	A20WE   					 
1998012100003	19980121	00003	GL  	1998	1	21	AU970811         	2	19970619	G	7310		PIPE            								GE    	CF6   	CF680C      		GL  					LT ENGINE FUEL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LH ENGINE FUEL FILTER BYPASS LINE LEAKING											4	F			E23EA				 
1998011500168	19980115	00168	NM  	1998	1	15	AU970812         	1	19970625	G	2730	251U211	ROD             			BOEING	747   	747438      		NM  										ELEVATOR CONTROL	CHAFING         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ELEVATOR CONTROL SYSTEM LH AND RH ELEVATOR SERVO CONTROL ROD SAFETY NUTS CONTACTING FORK ENDS ON TORQUE TUBE						2	L	7	4 	4F			RT	A20WE   					 
1998011500169	19980115	00169	CE  	1998	1	15	AU970815         	1	19970617	G	3297	42C18	WIRE            	CESSNA      		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	GEAR SELECTOR	SHORTED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 					402C1008					(AUS) LANDING GEAR SELECTOR WIRE SHORT CIRCUITED IN AREA BEHIND INSTRUMENT PANEL						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
1998012100004	19980121	00004	EU  	1998	1	21	AU970816         	1	19970601	G	5102		GIMBLE          			CAMRON	A315  	A315        		EU  										BALLOON BURNER	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) BALLOON BURNER GIMBLE BLOCK DAMAGED - SUSPECT CAUSED BY UNAUTHORIZED DISASSEMBLY AND ASSEMBLY BY UNQUALIFIED PERSO	NNEL -PERSONNEL/MAINTENANCE ERROR - UNAPPROVED MAINTENANCE					1	B	0	0 	0 			0	B1EU    					 
1998011500170	19980115	00170	NM  	1998	1	15	AU970817         	1	19970629	G	6320	2222	GEAR            	ROBSIN      		ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					M/R GEARBOX	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 			627  		2222					(AUS) MAIN ROTOR TRANSMISSION GEAR FAULTY - METAL CONTAMINATION OF CHIP DETECTOR						1	G	7	1 	3O	3	O		H10WE   	E274				 
1998011500171	19980115	00171		1998	1	15	AU970820         	4	19970430	G	3417	FAD1862	TRANSDUCER      	SMITHSIND   	DAGC        	BOEING	737   	73733A      	1384673	NM  										AIR DATA COMP	INTERMITTENT    	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 					1097					(AUS) NO1 DIGITAL AIR DATA COMPUTER (DADC) FAULTY - FAULT TRACED TO INTERMITTENT OUTPUT SIGNAL DATA FROM THE STATIC PRES	SURE TRANSDUCER					2	L	7	2 	4F			RT	A16WE   					 
1998011500172	19980115	00172		1998	1	15	AU970824         	4	19970624	G	2210		AUTOPILOT       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AFCS SYSTEM	FAULTY          	W				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) AUTOFLIGHT CONTROL SYSTEM (AFCS) SUSPECT FAULTY - UNUSUAL ADVISORY MESSAGES - SEE MDR 97/0808 FOR SIMILAR DEFECT						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998011500173	19980115	00173	NM  	1998	1	15	AU970825         	1	19970501	G	5320		POST            			BOEING	737   	737377      		NM  										NR 1 WINDOW LT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH NO1 WINDOW POST CRACKED IN OUTBOARD UPPER CORNER - FOUND DURING EDDY CURRENT INSPECTION IAW ER B73-53-10-36						2	L	7	2 	4F			RT	A16WE   					 
1998011500174	19980115	00174	NM  	1998	1	15	AU970826         	1	19970603	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										BS 178	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FORWARD PRESSURE BULKHEAD AT STATION 178 CRACKED IN SIXPLACES - FOUND USING EDDY CURRENT AND ULTRASONIC I	NSPECTIONS IAWER B73-53-10-39A					2	L	7	2 	4F			RT	A16WE   					 
1998011500549	19980115	00549	NM  	1998	1	15	AU970827         	1	19970121	G	5320		POST            			BOEING	737   	737377      		NM  										LT NR 1 WINDOW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH NO1 WINDOW POST CRACKED IN AREA OF SUB SURFACE GUSSET FROM CORNER RADIUS TO RIVET - FOUND DURING EDDY CURRENT I	NSPECTION IAW ER B73-53-10-36					2	L	7	2 	4F			RT	A16WE   					 
1998011500550	19980115	00550	NM  	1998	1	15	AU970828         	1	19970530	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE LT FWD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN THE FOLLOWING AREAS:-1. LH FORWARD PRESSURE BULKHEAD SIDE CHORD RADIUS AT WL 	195 -  CRACK LENGTH 63.5MM (2.5IN)2. LH INTERCOSTAL ADJACENT TO BULKHEAD AT WL 1953. RH INTERCOSTAL ADJACENT TO BULKHEAD	 AT WL 195				2	L	7	2 	4F			RT	A16WE   					 
1998011500551	19980115	00551	NM  	1998	1	15	AU970829         	1	19970530	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE FWD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FORWARD PRESSURE BULKHEAD WEB CRACKED IN FIVE PLACES - FOUND DURING EDDY CURRENT AND ULTRASONIC INSPECTIO	N IAW ERB73-53-10-39A					2	L	7	2 	4F			RT	A16WE   					 
1998011500552	19980115	00552	CE  	1998	1	15	AU970833         	1	19970612	G	2720		RUDDER SYSTEM   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RUDDER BOOST	MALFUNCTION     	W				K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) RUDDER BOOST SYSTEM FAULTY - MAINTENANCE CHECKS OF SYSTEM COULD FIND NO FAULTS						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998011500553	19980115	00553	CE  	1998	1	15	AU970834         	1	19970626	G	2731		TRIM SYSTEM     			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ELEV TAB CONTROL	MALFUNCTION     	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) ELEVATOR TRIM FAULTY - MAINTENANCE CHECKS COULD FIND NO FAULTSWITH THE TRIM SYSTEM - SUSPECT CAUSED BY ICING						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998011500554	19980115	00554	SO  	1998	1	15	AU970840         	1	19970418	G	5711	227791	SPAR CAP        		202077902   	AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	LT & RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING LOWER SPAR CAPS PNO 202077901 AND PNO 202077902CRACKED IN SPLICE BLOCK HOLES						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1998011500555	19980115	00555	SW  	1998	1	15	AU970841         	1	19970622	G	6410	261621131	BLADE           	BELL        		BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ATO23					(AUS) TAIL ROTOR BLADE DELAMINATED IN DOUBLER AREA						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998011500556	19980115	00556		1998	1	15	AU970844         	4	19970531	G	2350		TRANSCEIVER     			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	MIC JACK	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RADIO FAILED TO TRANSMIT - CORROSION ON MICROPHONE JACK CONTACTS						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998011500557	19980115	00557	NM  	1998	1	15	AU970845         	1	19970507	G	2910	B47664192	HOSE            			BOEING	737   	73733A      	1384673	NM  										RT MLG UOLOCK	BURST           	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 										(AUS) RH MAIN LANDING GEAR UPLOCK ACTUATOR RETRACTION HOSE BURST NEAR UPPER END - LOSS OF SYSTEM `A' HYDRAULIC FLUID						2	L	7	2 	4F			RT	A16WE   					 
1998011500558	19980115	00558	CE  	1998	1	15	AU970849         	1	19970603	G	2434		BEARING         			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4J     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	DC GENERATOR-ALT	COLLAPSED       	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 							L197236A			(AUS) ALTERNATOR DRIVE END BEARING COLLAPSED						1	L	7	1 	3O	3	O		A1CE    	E286	5	N	P4EA	 
1998011500559	19980115	00559	EA  	1998	1	15	AU970850         	2	19970603	G	8530		VALVE           	CONT        		BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4J     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	NR 3 CYL EXH	DAMAGED         	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							L197236A			(AUS) NO3 CYLINDER EXHAUST VALVE HEAD DAMAGED - APPROXIMATELY 50% OFTHE HEAD WAS MISSING						1	L	7	1 	3O	3	O		A1CE    	E286	5	N	P4EA	 
1998011500560	19980115	00560	NE  	1998	1	15	AU970853         	2	19970616	G	8520	23112	BOLT            	PWA         		DHAV  	DHC2  	DHC2EVANS   	2801832	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CTRWT RETAIN	FAILED          	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			AU	S 					23112		23112			(AUS) ENGINE FAILED - CAUSED BY FAILURE OF THE COUNTERWEIGHT RETAINING BOLT ALLOWING COUNTERWEIGHT TO DEPART CRANKSHAFT 	AND SEIZE THE ENGINE					1	H	7	1 	3O	3	R		A806    	5E1				 
1998011500561	19980115	00561	EU  	1998	1	15	AU970855         	1	19970504	G	5610	TA5189ANSETTSN	WINDSHIELD      			AIRBUS	320   	A320212     		EU  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					TA50189ANSET					(AUS) CAPTAINS WINDSHIELD CRACKED - SUSPECT CAUSED BY WATER INGRESS LEADING TO ARCING IN HEATING SYSTEM						2	L	7	2 	4F			RT	A28NM   					 
1998011500562	19980115	00562		1998	1	15	AU970859         	4	19970529	G	2562	ELT114	ELT             			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	EMERG LOCATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					57820					(AUS) ARTEX ELT CRACKED AND BATTERY LEAKING CAUSING CORROSION - ELT HAD ONLY BEEN FITTED ON 27 FEB 1997 FOLLOWING SIMILA	R CRACKING OF THE PREVIOUS ELT					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998011500563	19980115	00563	SO  	1998	1	15	AU970867         	1	19970618	G	5313		LONGERON        			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	FUSELAGE RT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LOWER RH LONGERON BENT AND DIAGONAL TUBE BENT INWARDS						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614	 
1998011500564	19980115	00564	EU  	1998	1	15	AU970872         	1	19970610	G	3230	C2424561	UPLOCK          			AMD   	FALC50	FALCON900   	2700160	EU  										NLG	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					U465					(AUS) NOSE LANDING GEAR UPLOCK BOX FAULTY - THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY						2	L	7	3 	4F			RT	A46EU   					 
1998011500565	19980115	00565		1998	1	15	AU970876         	4	19970303	G	3416	P933	ALTIMETER       																	COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0496					(AUS) ALTIMETER FAULTY - READING 10,000 FEET AT SEA LEVEL - INVESTIGATION FOUND THAT ONE OF THE TWO ANEROID CAPSULES HAD	 LOST ITS VACUUM - ALTIMETER WAS FITTED TO A JABIRU - REPORT ENTERED IAW AD/INST/39																		 
1998011500566	19980115	00566		1998	1	15	AU970880         	4	19970412	G	2562	ELT114	ELT             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	EMERG LOCATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT COMPLETELY DESTROYED DUE TO BUILDUP OF WATER IN MOUNTING TRAY - WATER IN TRAY GETS INTO ELT BATTERY COMPARTMEN	T CAUSING CORROSION AND EVENTUAL FAILURE					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1998011500567	19980115	00567	NE  	1998	1	15	AU970881         	2	19970420	G	7261	51663	PUMP            		RR369004    	BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					LT ENGINE OIL	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			420  				LE47215			(AUS) LH ENGINE DRIVEN OIL PUMP FAULTY. OIL PRESSURE FLUCTUATING.						1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1998011500568	19980115	00568	CE  	1998	1	15	AU970882         	1	19970506	G	2510		SEAT BELT       			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	COCKPIT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT WAS AUTOMOTIVE PRODUCT - PERSONNEL/MAINTENANCE ERROR -UNAPPROVED PART						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1998011500569	19980115	00569	CE  	1998	1	15	AU970883         	1	19970422	G	5711		SPAR            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FORWARD SPAR FORWARD AND REAR RH WEBS CRACKED - FOUND DURING INSPECTION IAW AD/BEECH55/62 AMDT4 AND BEECH SB2	269					1	L	7	2 	3O	3	O		3A16    	E5CE				 
1998011500570	19980115	00570	NM  	1998	1	15	AU970884         	1	19970420	G	6320	A61	TRANSMISSION    	ROBSIN      	A0061       	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					M/R GEARBOX	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1044					(AUS) MAIN ROTOR TRANSMISSION METAL CONTAMINATION. SUSPECT CAUSED BY FATIGUE SPALLING OF PINION AND RING GEARS.						1	G	7	1 	3O	3	O		H10WE   	E274				 
1998011500571	19980115	00571		1998	1	15	AU970885         	4	19970510	G	6122	DCFS29D2AT	GOVERNOR        			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					760832					(AUS) PROPELLER GOVERNOR HIGH RPM OUT OF ADJUSTMENT						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998011500572	19980115	00572	CE  	1998	1	15	AU970886         	1	19970422	G	3230	9911543	VALVE           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					BLOWDOWN SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1    		1454					(AUS) LANDING GEAR BLOWDOWN BOTTLE OUTLET VALVE FAULTY - INVESTIGATION FOUND THAT THE `O' RING ON THE VALVE POPPET ASSEM	BLY WAS MISSING- REMAINS OF THE `O' RING WERE FOUND DOWNSTREAM IN THE EMERGENCY GEAR BLOWDOWN SYSTEM					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1998011500573	19980115	00573	CE  	1998	1	15	AU970887         	1	19970415	G	2910	9911883	VALVE           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					HYD MANIFOLD	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1066					(AUS) HYDRAULIC MANIFOLD VALVE FAULTY - DURING STRIPDOWN OF THE VALVE PIECES OF `O' RING WERE FOUND - SUSPECT `O' RING C	AME FROM THE EMERGENCY GEAR DOWN BOTTLE PNO 9910154-3 (MDR 97/0886)					1	L	7	2 	3O	3	O		A7CE    	E8CE				 
1998011500574	19980115	00574	CE  	1998	1	15	AU970888         	1	19970307	G	5753	T1221115	ROLLER          	CESSNA      		CESSNA	182   	182Q        	2072732	CE  										LT TE FLAP	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) LH FLAP ROLLERS PNO T-1221010-5 AND PNO R-0523921X3 WORN - FLAP JAMMED ON TRACK SUPPORT BRACKETS						1	H	7	1 	3O			NT	3A13    					 
1998011500575	19980115	00575	GL  	1998	1	15	AU970890         	3	19970518	G	6114		SCREW           			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	RT PROP HUB	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								82243		(AUS) RH PROPELLER DOME SCREWS LOOSE - SCREWS WERE CORRECTLY LOCKWIRED- FIVE OF THE SCREWS HAD SHEARED HEADS - SUSPECT S	CREWS INCORRECTLY TORQUED AT LAST OVERHAUL OR SHOP VISIT -PERSONNEL/MAINTENANCE ERROR					1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998011500576	19980115	00576	CE  	1998	1	15	AU970891         	1	19970620	G	3234	363851	SELECTOR        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	GEAR SELECTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR SELECTOR SWITCH SHAFT BROKEN. INSPECTION FOUND LOCATING TANG ON EMERGENCY LANDING GEAR EXTENSION HAND	LE ALSO BROKEN AND FORK END TO DRIVE SHAFT DAMAGED. EXTENSION HANDLE HOUSING ALSO CRACKED.					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA	 
1998011500577	19980115	00577	SO  	1998	1	15	AU970893         	2	19970519	G	7414	M2369	IMPULSE COUPLING	SLICK       	662         	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MAGNETO	INCORRECT ASSY  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					9020553		572674			(AUS) MAGNETO IMPULSE COUPLING INCORRECTLY ASSEMBLED						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1998011500578	19980115	00578	SO  	1998	1	15	AU970894         	1	19970302	G	2841	755452	INDICATOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL QUANTITY	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FUEL GAUGE EMPTY POTENTIOMETER LOOSE IN PC BOARD - INVESTIGATION FOUND POTENTIOMETER HAD BEEN INCORRECTLY SOLDE	RED TO THE PC BOARD					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P920	 
1998011500579	19980115	00579	SW  	1998	1	15	AU970898         	1	19970625	G	6320	264321	BEARING         	BELL        		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					BKW12075					(AUS) MAIN ROTOR TRANSMISSION DUPLEX BEARING SPALLED - METALCONTAMINATION OF GEARBOX						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998011500580	19980115	00580	CE  	1998	1	15	AU970908         	1	19970318	G	5512		SKIN            			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	HORIZ STAB LE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILISER LEADING EDGE SEPARATED FROM THREE RIBS						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1998011500581	19980115	00581	CE  	1998	1	15	AU970909         	1	19970318	G	5541		RIB             			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP RUDDER RIB AND BALANCE WEIGHT STRUCTURE SEVERELY CORRODED						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1998011500582	19980115	00582	CE  	1998	1	15	AU970910         	1	19970318	G	5551	123241	BRACKET         		12324002    	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	HORIZ STAB ATT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER LH AND RH ATTACHMENT BRACKETS PNO 1232400-1 AND PNO 1232400-2 CONTAINED INTERGRANNULAR CORRO	SION					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1998011500583	19980115	00583		1998	1	15	AU970911         	1	19970623	G	7120	VTB131REVG	BEARING         								GE    	CF6   	CF680A      	30025	NE  					LT AFT ENG MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							58136			(AUS) LH ENGINE AFT ENGINE MOUNT LINK BEARING INNER RACE CRACKED IN TWO PLACES. LOWER FITTING ASSEMBLY BEARING INNER RAC	E CRACKED IN ONEPLACE.										4	F			E13NE				 
1998011500584	19980115	00584	CE  	1998	1	15	AU970912         	1	19970318	G	1100		MAINTENANCE LOG 			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	AIRCFT GEAR DOOR	INCOMPLETE      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LOG BOOK ENTRY INDICATED AN STC HAD BEEN INCORPORATED REGARDING A LANDING GEAR DOOR REMOVAL MODIFICATION - NO DATA	 ACCOMPANIED THE AIRCRAFT RECORDS AND THERE WAS NO ENGINEERING ORDER AUTHORISING THE STC - NO WEIGHT CHANGES WERE RECORD	ED IN THE LOG BOOK				1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1998011500585	19980115	00585	CE  	1998	1	15	AU970913         	1	19970318	G	5330		SKIN            			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	LT FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH UPPER FUSELAGE TAILCONE LAP JOINT CORRODED BETWEEN AFT WINDOW AND REAR BULKHEAD - SEVERE INTERNAL CORROSION ADJ	ACENT TO HF ANTENNA CERAMIC INSULATOR					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1998011500586	19980115	00586	SO  	1998	1	15	AU970915         	1	19970520	G	7602		BEARING         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	MCAULY	3AF34C	3AF34C502   	GL  	MIXTURE CONTROL	BINDIING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							3683			(AUS) LH ENGINE MIXTURE CONTROL ROD END BEARING AND CONTROL ARM BINDING ON FCU						1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1998011500587	19980115	00587	EU  	1998	1	15	AU970921         	1	19970617	G	2450	S26531	CIRCUIT BREAKER 			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RT WINDSHLD HEAT	ARCED           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH WINDSHIELD HEATING SYSTEM PHASE `B' SUPPLY CIRCUIT BREAKER DAMAGED FROM INTERNAL ARCING.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998011500588	19980115	00588	SO  	1998	1	15	AU970933         	1	19970101	G	5531	9812	SPAR            			PIPER 	PA36  	PA36375     	7103620	SO  	LYC   	O720  	IO720D1C    	41546	EA  					VERT STAB	CRACKED         	W				K				NONE                    				F	D		FLT CONT AFFECTED         	INFLIGHT SEPARATION       		TO	TAKEOFF        	1			AU	S 										(AUS) FIN REAR SPAR CRACKED ALLOWING TOP AND MIDDLE RUDDER ATTACHMENT BRACKETS TO SEPARATE						1	L	7	1 	3O	3	O		A10SO   	1E15				 
1998011500589	19980115	00589	NM  	1998	1	15	AU970937         	1	19970531	G	2730	162313	COMPUTER        			BOEING	737   	737377      		NM  										ELEV FEEL CONT	MALFUNCTIONED   	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) ELEVATOR FEEL COMPUTER SUSPECT FAULTY - WORKSHOP INVESTIGATIONCOULD FIND NO DEFECTS						2	L	7	2 	4F			RT	A16WE   					 
1998011500590	19980115	00590	NM  	1998	1	15	AU970938         	1	19970410	G	3260	1899	SENSOR          			BOEING	737   	73733A      	1384673	NM  										MLG	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) AIR SAFETY PROXIMITY SENSOR OUT OF ADJUSTMENT						2	L	7	2 	4F			RT	A16WE   					 
1998011500591	19980115	00591	SO  	1998	1	15	AU970939         	1	19970319	G	5541	98126	SPAR            			PIPER 	PA36  	PA36375     	7103620	SO  	LYC   	O720  	IO720D1C    	41546	EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER SPAR CRACKED ON BOTH SIDES OF HINGE - HINGE BRACKET PNO76847-02 ALSO CRACKED						1	L	7	1 	3O	3	O		A10SO   	1E15				 
1998011500592	19980115	00592	NM  	1998	1	15	AU970941         	1	19970618	G	5230		FRAME           			BOEING	737   	737377      		NM  										CARGO/BAG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD CARGO DOOR FRAME CRACKED AT DOOR FRAME RADIUS FROM LOWERAFT CORNER AND RUNNING UP THE AFT SIDE OF THE DOOR	 - CRACK LENGTH APPROXIMATELY 210MM (9IN) - INVESTIGATION FOUND FURTHER CRACKING IN THE FOLLOWING LOCATIONS:-1. HORIZONT	AL CROSS BEAM ATTACHMENT ANGLE - CRACK LENGTH 70MM  (3IN)2. HORIZONTAL CROSS BEAM WEB CRACKED COMPLETELY THROUGH - CRACK	  LENGTH 100MM (4IN)			2	L	7	2 	4F			RT	A16WE   					 
1998011500593	19980115	00593	EA  	1998	1	15	AU970948         	2	19970630	G	7414	M381	CAPACITOR       	SLICK       	4372        	PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					91030039		RL2427351A			(AUS) MAGNETO CAPACITOR AND POINTS BURNT - FOUND DURING INSPECTION IAWAD/ELECT/46 AMDT 6						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1998011500594	19980115	00594	GL  	1998	1	15	AU970952         	1	19970521	G	6100		PROPELLER       			AMTR  	MAXAIR	XP503       	9570746	GL  	AMTR  	582   	582         		GL  					PROP BLADE LE	FOD             	W				K				NONE                    				C			F.O.D.                    			NR	NOT REPORTED   	1			AU	S 										(AUS) PILOTS VISOR FLEW OFF AND STRUCK PROPELLER CAUSING A SMALL SECTION OF THE LEADING EDGE TO SEPARATE - THIS DEFECT W	AS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY					1	H	7	1 	3I	3	I	NT	EXPA1H71	EXP31				 
1998011500595	19980115	00595	NM  	1998	1	15	AU970954         	1	19970625	G	5312		BULKHEAD        			BOEING	737   	73733A      	1384673	NM  										FUSELAGE FWD WEB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB FORWARD FACE CRACKED IN THE FOLLOWING AREAS:- 1. THREE CRACKS LOCATED AT RBL 5.7 UND	ER RADAR SCANNING SUPPORT  BRACKETS - CRACK LENGTHS 15MM (0.59IN), 20MM (0.787IN) AND  24MM (0.944IN) 2. ONE CRACK LOCAT	ED AT LBL 5.7 UNDER RADAR SCANNING SUPPORT BRACKETS - CRACK LENGTH 23MM (0.905IN) 3. ONE CRACK RUNNING VERTICALLY ADJACE	NT TO BLO JUST ABOVE WL  1845 - CRACK LENGTH 18MM (0.708IN) FOUND DURING ULTRASONIC AND EDDY CURRENT INSPECTIONS IAW ER			2	L	7	2 	4F			RT	A16WE   					 
1998011500596	19980115	00596	EU  	1998	1	15	AU970959         	1	19970516	G	5754	MF2687ANSETTS	BRAKE           			AIRBUS	320   	A320212     		EU  										SLAT SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					MF2687ANSETT					(AUS) SLAT SYSTEM WING TIP BRAKE FAULTY						2	L	7	2 	4F			RT	A28NM   					 
1998011500597	19980115	00597	WP  	1998	1	15	AU970991         	1	19970614	G	6320	23529	GEAR            	HILLER      		HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					M/R GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			535  		10089					(AUS) MAIN ROTOR TRANSMISSION UPPER PLANETARY RING GEAR TOOTH CHIPPED - MINOR DAMAGE TO ONE UPPER PLANETARY GEAR						1	G	7	1 	3O	3	O		4H11    	E304				 
1998011500598	19980115	00598	EU  	1998	1	15	AU971020         	1	19970612	G	2621		FIRE BOTTLE     			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENG	MIS WIRED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NO4 ENGINE FIRE EXTINGUISHER BOTTLE SQUIB WIRES WB14 AND WB15 CROSSED BETWEEN CONNECTOR RF (442-00-00)						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998011500599	19980115	00599	EU  	1998	1	15	AU971035         	1	19970621	G	2710	A788171	QUADRANT        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					RT WING AIL OUTB	CONTAMINATED    	W				K				NONE                    				O	F		OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 										(AUS) RH WING OUTBOARD AILERON LOWER QUADRANT BEARING WATER INGRESS						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1998011500600	19980115	00600	EU  	1998	1	15	AU971040         	1	19970607	G	3246	U1886ANSETTSN3	WHEEL           			AIRBUS	320   	A320212     		EU  										INB NR 1 DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U1886ANSETTS					(AUS) INBOARD WHEEL HALF CRACKED AT THE BASE OF NO1 DRIVE TENON ATPOSITIT POSITION NO4						2	L	7	2 	4F			RT	A28NM   					 
1998011500601	19980115	00601	EU  	1998	1	15	AU971041         	1	19970607	G	3246	U261ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG NR 1 DRIVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2061ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF NO1 DRIVE TENON						2	L	7	2 	4F			RT	A28NM   					 
1998011500602	19980115	00602	EU  	1998	1	15	AU971042         	1	19970607	G	3246	U259ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2059ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF NO1 DRIVE TENON						2	L	7	2 	4F			RT	A28NM   					 
1998011500603	19980115	00603	EU  	1998	1	15	AU971043         	1	19970607	G	3246	U28ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2080ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF FOUR DRIVE TENONS AT POSITION NO3						2	L	7	2 	4F			RT	A28NM   					 
1998011500604	19980115	00604	EU  	1998	1	15	AU971044         	1	19970607	G	3246	U2227ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2227ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH CENTRE AREA ON TWO DRIVE TENONS AT POSITION NO4						2	L	7	2 	4F			RT	A28NM   					 
1998011500605	19980115	00605	EU  	1998	1	15	AU971045         	1	19970607	G	3246	U247ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2047ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH THE CENTRE AREA ON NO1 DRIVE TENON						2	L	7	2 	4F			RT	A28NM   					 
1998011500606	19980115	00606	EU  	1998	1	15	AU971046         	1	19970607	G	3246	U1864ANSETTSN3	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U1864ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH CENTRE AREA ON ONE DRIVE TENON IN POSITION NO2						2	L	7	2 	4F			RT	A28NM   					 
1998011500607	19980115	00607	EU  	1998	1	15	AU971047         	1	19970607	G	3246	U23ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2003ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH CENTRE AREA ON TWO DRIVE TENONS AT POSITION NO4						2	L	7	2 	4F			RT	A28NM   					 
1998011500608	19980115	00608	EU  	1998	1	15	AU971048         	1	19970607	G	3246	U212ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2102ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED IN TUBE WELL AREA AT POSITION NO2						2	L	7	2 	4F			RT	A28NM   					 
1998011500609	19980115	00609	EU  	1998	1	15	AU971049         	1	19970607	G	3246	U278ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2078ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH CENTRE ON THREE DRIVE TENONS AT POSITION NO4						2	L	7	2 	4F			RT	A28NM   					 
1998011500610	19980115	00610	EU  	1998	1	15	AU971050         	1	19970607	G	3246	C2252	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U1865ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF TWO DRIVE TENONS AT POSITION NO1 - FOUND DURING EDDY CURRENT INSPEC	TION					2	L	7	2 	4F			RT	A28NM   					 
1998011500611	19980115	00611	EU  	1998	1	15	AU971051         	1	19970607	G	3246	C2252	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2060ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF FIVE DRIVE TENONS AT POSITION NO3 - FOUND DURING EDDY CURRENT INSPE	CTION					2	L	7	2 	4F			RT	A28NM   					 
1998011500612	19980115	00612	EU  	1998	1	15	AU971052         	1	19970607	G	3246	C2252	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U911ANSETTSN					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF ONE DRIVE TENON AT POSITION NO3 - FOUND DURING EDDY CURRENT INSPECT	ION					2	L	7	2 	4F			RT	A28NM   					 
1998011500613	19980115	00613	EU  	1998	1	15	AU971053         	1	19970607	G	3246	C2252	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2005ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF ONE DRIVE TENON AT POSITION NO2 - FOUND DURING EDDY CURRENT INSPECT	ION					2	L	7	2 	4F			RT	A28NM   					 
1998011500614	19980115	00614	EU  	1998	1	15	AU971054         	1	19970607	G	3246	U362ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U3062ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED IN THE CENTRE OF ONE DRIVE TENONAT POSITION NO3 - FOUND DURING EDDY CURRENT INSPEC	TION					2	L	7	2 	4F			RT	A28NM   					 
1998011500615	19980115	00615	EU  	1998	1	15	AU971055         	1	19970607	G	3246	F4894ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					F4894ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH CENTRE AREAS OF THREE DRIVE TENONS AT POSITION NO1 - FOUND DURING EDDY CUR	RENTINSPECTION					2	L	7	2 	4F			RT	A28NM   					 
1998011500616	19980115	00616	EU  	1998	1	15	AU971056         	1	19970607	G	3246	U298ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2908ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH CENTRE OF FOUR DRIVE TENONS AT POSITION NO2 - FOUND DURING EDDY CURRENT IN	SPECTION					2	L	7	2 	4F			RT	A28NM   					 
1998011500617	19980115	00617	EU  	1998	1	15	AU971057         	1	19970607	G	3246	U363ANSETTSN	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U3063ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH THE CENTRE OF SIX DRIVE TENONS AT POSITION NO2 - FOUND DURING EDDY CURRENT	 INSPECTION					2	L	7	2 	4F			RT	A28NM   					 
1998011500618	19980115	00618	EU  	1998	1	15	AU971058         	1	19970607	G	3246	C225151	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2670ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED THROUGH THE GUIDE PIN HOLES OF TWO TENONS AT POSITION NO2 - FOUND DURING EDDY CURR	ENT INSPECTION					2	L	7	2 	4F			RT	A28NM   					 
1998011500619	19980115	00619	EU  	1998	1	15	AU971059         	1	19970607	G	3246	C225151	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG INB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U4709ANSETTS					(AUS) MAIN WHEEL INBOARD HALF CRACKED AT THE BASE OF FOUR DRIVE TENONS AT POSITION NO4 - FOUND DURING EDDY CURRENT INSPE	CTION					2	L	7	2 	4F			RT	A28NM   					 
1998011500620	19980115	00620	EU  	1998	1	15	AU971060         	1	19970607	G	3246	C2262	WHEEL           			AIRBUS	320   	A320212     		EU  										MLG OUTB HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U2052ANSETTS					(AUS) MAIN WHEEL OUTBOARD HALF CRACKED IN BEAD SEAT AREA AT POSITIONNO4						2	L	7	2 	4F			RT	A28NM   					 
1998011500621	19980115	00621	NM  	1998	1	15	AU971069         	1	19970516	G	2923	MF19655ANSETT	SEAL            			BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					HYD PUMP RAT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					MF190655ANSE					(AUS) RAM AIR TURBINE (RAT) HYDRAULIC PUMP HOUSING SEALS LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1998011500622	19980115	00622		1998	1	15	AU971088         	4	19970219	G	2211		COMPUTER        			AIRBUS	320   	A320212     		EU  										AUTO FLIGHT SYST	MALFUNCTIONED   	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) FLIGHT CONTROL ELAC 2 PITCH FAULT INDICATED ON ECAM. BOTH ELAC COMPUTERS AND SPOILER COMPUTER CHANGED AND SENT TO 	WORKSHOP FOR INVESTIGATION WITH NO FAULTS FOUND.					2	L	7	2 	4F			RT	A28NM   					 
1998012100006	19980121	00006	EU  	1998	1	21	AU971092         	1	19970516	G	3010	HTE984	ACTUATOR        			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT RT WING AI	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					AIVL88636					(AUS) LH AND RH WING OUTER ANTI-ICE VALVES BOTH HAD SLIPPING CLUTCHES.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998011500623	19980115	00623	SW  	1998	1	15	AU971105         	1	19970508	G	1100		DATA PLATE      			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					AIRCRAFT MAINT	INCORRECT DATA  	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L294656			(AUS) SUSPECT INCORRECT DATA PLATE FITTED TO HELICOPTER. AIRCRAFT HAD BEEN EXTENSIVELY REBUILT IN 1989. PERSONNEL/MAINTE	NANCE ERROR.					1	G	7	1 	3O	3	O		2H3     	E279				 
1998011500624	19980115	00624	SW  	1998	1	15	AU971106         	1	19970523	G	6710	KSP5	BEARING         			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					M/R CYCLIC	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LATERAL CYCLIC TORQUE TUBE FORWARD SUPPORT BEARING WORN.						1	G	7	1 	3O	3	O		2H3     	E279				 
1998011500625	19980115	00625	SW  	1998	1	15	AU971112         	1	19970508	G	2622		EXTINGUISHER    			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					FIRE BOTTLE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) UNAPPROVED TYPE OF DRY POWDER FIRE EXTINGUISHER FITTED. UNAPPROVED PART.						1	G	7	1 	3O	3	O		2H3     	E279				 
1998012200180	19980122	00180	SW  	1998	1	22	AU971113         	1	19970523	G	6710	KSP4	BEARING         			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					MAIN ROTOR CONTR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COLLECTIVE LEVER FORWARD BEARING WORN. PERSONNEL/MAINTENANCE ERROR.						1	G	7	1 	3O	3	O		2H3     	E279				 
1998012200181	19980122	00181	NM  	1998	1	22	AU971120         	1	19970610	G	7160	31317	DOOR            			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					ENGINE AIR INT	SEPARATED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							L176948A			(AUS) ENGINE ALTERNATE AIR DOOR SEPARATED FROM INDUCTION AIR BOX ASSEMBLY AND JAMMED THE THROTTLE BUTTERFLY						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
1998012200182	19980122	00182		1998	1	22	AU971128         	4	19970527	G	3417	HG48B13	ADC             			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					AIR DATA COMP	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					P122ANSETTSN					(AUS) NO2 AIR DATA COMPUTER (ADC) FAILED. INVESTIGATION FOUND A DRY SOLDER JOINT ON A PIN CONNECTION AND THE HEAT SINK C	OMPOUND BETWEEN THE POWER DIODES AND THEIR INTERFACE WITH THE MODULE CIRCUIT CARD HAD DETERIORATED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1998012200183	19980122	00183	EA  	1998	1	22	AU971134         	2	19970415	G	7421	REM38E	SPARK PLUG      								LYC   	O360  	O360A4K     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	ENGINE IGN	INTERMITTENT    	W				K				NONE                    				O	E		OTHER                     	VIBRATION/BUFFET          		CR	CRUISE         	1			AU	S 										(AUS) SPARK PLUGS INTERMITTENT IN OPERATION.											3	O			E286	5	N	P857	 
1998012200184	19980122	00184		1998	1	22	AU971142         	4	19970526	G	3417	HG48B42	ADC             			BOEING	737   	73733A      	1384673	NM  										AIR DATA COMP	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 AIR DATA COMPUTER (ADC) SUSPECT FAULTY. WORKSHOP INVESTIGATION COULD FIND NO FAULTS.						2	L	7	2 	4F			RT	A16WE   					 
1998012200185	19980122	00185	EU  	1998	1	22	AU971163         	1	19970423	G	3233	21519	BEARING         			AIRBUS	320   	A320212     		EU  										LT RT MLG ACT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2960 		LHDAASG94RH					(AUS) LH AND RH MAIN LANDING GEAR ACTUATOR ROD END SPHERICAL BEARINGS CRACKED IN SEVERAL PLACES ACROSS THE PIVOTING BALL	.					2	L	7	2 	4F			RT	A28NM   					 
1998012200186	19980122	00186	EU  	1998	1	22	AU971199         	1	19970603	G	2752	L74ANSETT58	ACTUATOR        			AIRBUS	320   	A320212     		EU  										TE FLAP ACTUATOR	CORRODED        	W				K				NONE                    				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 					L704ANSETT05					(AUS) LH NO2 FLAP ACTUATOR FAULTY - TORQUE LIMITER TRIPPED - STRIP INVESTIGATION FOUND SOME INTERNAL COMPONENTS CORRODED	 AND PITTED- SUSPECT CAUSED BY MOISTURE IN THE ACTUATOR					2	L	7	2 	4F			RT	A28NM   					 
1998012200187	19980122	00187	CE  	1998	1	22	AU971218         	1	19970210	G	5312	713683	BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	DOOR POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE DOOR POST BULKHEAD CRACKED IN AREA OF STRESS RELIEF NOTCH. CRACK LENGTH 3.175MM (0.125IN). FOUND DURING I	NVESTIGATION IAW AD/180/75 AMDT1.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1998012200188	19980122	00188	NM  	1998	1	22	AU971224         	1	19970528	G	2612		FIRE DETECTOR   			BOEING	737   	737377      		NM  										APU FIRE WARN	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) APU FALSE FIRE WARNING. SUSPECT CAUSED BY MOISTURE IN FIREDETECTOR SYSTEM.						2	L	7	2 	4F			RT	A16WE   					 
1998012200189	19980122	00189	NM  	1998	1	22	AU971237         	1	19970618	G	3244	DR2582T	TIRE            			BOEING	737   	737377      		NM  										LT NLG WHEEL	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					KA251ANSETTS					(AUS) LH NOSEWHEEL TYRE TREAD SEPARATED. DAMAGE TO LH FRONT CORNER OF E & E BAY DOOR.						2	L	7	2 	4F			RT	A16WE   					 
1998012200190	19980122	00190	NM  	1998	1	22	AU971262         	1	19970213	G	3246	265759A	WHEEL           	BENDIX      		BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 4 MLG	FRACTURED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 			387  		ASSYHALFH015					(AUS) NO4 MAIN WHEEL HALF FAILED IN THE CENTRE HUB AREA. DAMAGE CAUSEDTO THE BRAKE AND WHEEL BEARING. FUSE PLUG MELTED A	ND TYRE DEFLATED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1998012200191	19980122	00191	CE  	1998	1	22	AU971272         	1	19970314	G	3260	ISET3	SWITCH          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT MLG DWNLOCK	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH AND WIRING DETERIORATED DUE TO AGE. FURTHER INVESTIGATION FOUND THE RH M	LG DOWNLOCK SYSTEM INCORRECTLY WIRED.					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998012200192	19980122	00192	CE  	1998	1	22	AU971274         	1	19970630	G	2436	DGR3	REGULATOR       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	DC GEN SYS	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) REGULATOR (2OFF) FAILED DUE TO SHORT CIRCUIT. SUSPECT CAUSED BY FAULTY ALTERNATOR.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1998012200193	19980122	00193	EA  	1998	1	22	AU971332         	2	19970620	G	8530	LW13561	CYLINDER        			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					INLET VALVE SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1017 				L32562			(AUS) ENGINE CYLINDER CRACKED FROM INDUCTION TUBE FACE TOWARDS THE INLET VALVE SEAT. CRACK LENGTH 31.75MM (1.25IN)						1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1998012200194	19980122	00194	EA  	1998	1	22	AU971333         	2	19970502	G	8530	LW13561	CYLINDER        			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					INLET VALVE SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1379 				L21962			(AUS) ENGINE CYLINDER CRACKED FROM INDUCTION TUBE MOUNT FACE TOWARDSTHE INLET VALVE SEAT. CRACK LENGTH 25.4MM (1IN).						1	L	7	2 	3O	3	O		A8EA    	E19EA				 
1998012200195	19980122	00195	WP  	1998	1	22	AU971368         	2	19971008	G	7200		ENGINE          								GARRTT	TPE331	TPE33112UA  	01514	WP  	ROTOL	R333	R333482F12  	GL  	POWER SECT	DEFECTIVE       	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) LH ENGINE LOW ON POWER.											4	T			E4WE	6	C	P61GL	 
1998012200196	19980122	00196	NM  	1998	1	22	AU971369         	1	19970305	G	2730	364ANSETTSN	FEEL UNIT       			BOEING	737   	73733A      	1384673	NM  										ELEVATOR CONTROL	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 					364ANSETTSN0					(AUS) ELEVATOR FEEL AND CENTERING UNIT FAULTY. SOME LINKAGE COMPONENTS DAMAGED.						2	L	7	2 	4F			RT	A16WE   					 
1998012600003	19980126	00003	NE  	1998	1	26	AU971370         	3	19970118	G	6110	28449	SPACER          													HAMSTD	23D	23D40       	NE  	PROP ASSEMBLY	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					ADH3465AQM			ADH3465AQM		(AUS) INCORRECT SPACER FITTED TO PROPELLER. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.																6	C	P719	 
1998012200197	19980122	00197	CE  	1998	1	22	AU971371         	1	19971017	G	5312	713683	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C203    	GL  	LT DOOR POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR POST BULKHEAD CRACKED IN RELIEF NOTCH ON LH SIDE.AIRCRAFT IS USED FOR PARACHUTING OPERATIONS.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA	 
1998012200198	19980122	00198	NE  	1998	1	22	AU971372         	2	19971102	G	7250	34451CL	VANE            	PWA         	125B        						PWA   	PWA120	PW125B      		NE  					HP TURBINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7002 		124011		12411			(AUS) HP TURBINE INLET GUIDE VANE ASSEMBLY HAD ONE VANE COMPLETELY BURNED AWAY AT APPROXIMATELY THE 8 O'CLOCK POSITION.											4	T			E20NE				 
1998012200199	19980122	00199	EA  	1998	1	22	AU971374         	2	19970924	G	7230	MS97147	BOLT            			PILATS	PC6T  	PC6BH2      	7090210	EU  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COMP TURBINE	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 							PCE21674			(AUS) COMPRESSOR TURBINE VANE BOLTS (3OFF) HAD THE BOLT HEADS SEPARATE AND BECOME TRAPPED BETWEEN THE VANE AND TURBINE D	ISC CAUSING DAMAGE TO THE DISC IN THE AREA OF THE FIR TREE AND THE VANE.SUSPECT BOLTS WERE NOT REPLACED DURING THE LAST 	REPAIR WHICH WAS FOR AN ENGINE OVERTEMP.				1	H	7	1 	3T	3	T		7A15    	E4EA	6	C	P15EA	 
1998012200200	19980122	00200	EA  	1998	1	22	AU971375         	2	19971024	G	8520	L236224	CRANKCASE       	LYC         							LYC   	O540  	O540E4C5    	41532	EA  					ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L2362240		L236224			(AUS) CRANKCASE TUNNEL MEASUREMENTS OUT OF LIMITS.											3	O			E295				 
1998012600004	19980126	00004	NM  	1998	1	26	AU971376         	1	19970716	G	7603	AS26117	BOLT            			BOEING	747   	747SP38     		NM  	RROYCE	RB211 	RB211524D419	54555	NE  					POWER LEVER	RUBBING         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) NO2 ENGINE THRUST LEVER PLA TRANSDUCER ROD END EYE BOLT BINDING WITH FFR POWER LEVER INPUT ROD.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
1998012200201	19980122	00201	GL  	1998	1	22	AU971377         	2	19971028	G	7240	6894	HEAT SHIELD     			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					NR 1 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							CAE84232			(AUS) NO1 ENGINE HEAT SHIELD CRACKED.						1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1998012200202	19980122	00202	CE  	1998	1	22	AU971378         	1	19970219	G	5541	5331513	SPAR            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER SPAR CRACKED ADJACENT TO TOP HINGE POINT.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA	 
1998012200203	19980122	00203	NM  	1998	1	22	AU971379         	1	19970812	G	5411	65B8912	BRACE           			BOEING	747   	747238B     	1384828	NM  										NR 4 ENG STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO4 ENGINE STRUT DIAGONAL BRACE REAR OUTBOARD LUG CRACKED. FOUND DURING INSPECTION IAW FAA AD89-07-15 (CASA AD/B74	7/70).					2	L	7	4 	4F				A20WE   					 
1998012200204	19980122	00204	NM  	1998	1	22	AU971380         	1	19970622	G	3411		PIPE            			BOEING	747   	747438      		NM  										PITOT/STATIC SYS	DISCONNECTED    	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) CENTRE AIR DATA COMPUTER (ADC) PITOT/STATIC LINES DISCONNECTED.						2	L	7	4 	4F			RT	A20WE   					 
1998012200205	19980122	00205	SW  	1998	1	22	AU971381         	1	19971101	G	2910	2781322682	PIPE            			FRCHLD	SA227 	SA227CC     		SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE SPLIT IN RADIUS LOCATED ON THE FIRST BEND FORWARD OF THE RH ENGINE FIREWALL.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1998012200206	19980122	00206	NM  	1998	1	22	AU971382         	1	19970811	G	2460	SG62	SOCKET          			BOEING	747   	747438      		NM  										DC POWER DISTRIB	MELTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR 4L VACUUM CLEANER ELECTICAL SOCKET BURNT AND MELTED. SUSPECT CAUSED BY EXCESSIVE CURRENT DRAW FROM WHATEVER D	EVICE HAD BEEN PLUGGED IN AT THE TIME. IN ADDITION THE DEVICE HAD NOT BEEN MAKING FULL CONTACT WITH THE SOCKET FINGERS.					2	L	7	4 	4F			RT	A20WE   					 
1998012200207	19980122	00207	NM  	1998	1	22	AU971383         	1	19970827	G	5414		SKIN            			BOEING	747   	747238B     	1384828	NM  										NR 1 NR 4 NAC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO1 AND NO4 ENGINE NACELLE STRUT OUTBOARD SKIN AND DOUBLER CRACKED BEYOND LIMITS.						2	L	7	4 	4F				A20WE   					 
1998012200208	19980122	00208	SO  	1998	1	22	AU971384         	2	19971031	G	8520	578462	CRANKCASE       	CONT        							CONT  	O520  	IO520B      	17032	SO  					ENG LT CASE HALF	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					578462		578462			(AUS) ENGINE LH CRANKCASE HALF CRACKED IN AREA OF NO3 BEARING SADDLE.											3	O			E5CE				 
1998012200209	19980122	00209	GL  	1998	1	22	AU971386         	3	19971007	G	6111		BLADE           			GULSTM	680   	680FLP      	0141610	SW  	LYC   	O720  	IO720B1B    	41546	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			473  				L19654A	BJ1196		(AUS) PROPELLER BLADE CRACKED. CRACK ORIGINATED FROM A NICK IN THE BLADE LOCATED APPROXIMATELY 76.2MM (3IN) FROM THE BLA	DE TIP.CRACK LENGTH 12.7MM (0.5IN). SUSPECT THE CRACK WAS INITIATED BY A PIECE OF METAL WIRE WHICH WAS FOUND IN THE BLAD	E DURING DRESSING OUT OF THE CRACK.				1	H	7	2 	3O	3	O		2A4     	1E15	5	C	P6EA	 
1998012200210	19980122	00210	CE  	1998	1	22	AU971387         	1	19970915	G	3231	84116	BELLCRANK       			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	MLG RT DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOOR IDLER BELLCRANK BROKEN. FURTHER INVESTIGATION FOUND THE LH IDLER BELLCRANK CRACKED IN TH	E SAMEAREA.					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998012200211	19980122	00211	NM  	1998	1	22	AU971388         	1	19971022	G	5311	A22	FRAME           			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1344					(AUS) FUSELAGE FRAME CRACKED. AIRCRAFT IS USED IN MUSTERING OPERATIONS.						1	G	7	1 	3O	3	O		H10WE   	E274				 
1998012200212	19980122	00212	CE  	1998	1	22	AU971389         	1	19971017	G	3230	24136	PAD             			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	LANDING GEAR	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR PADS MISSING. PADS ARE VULCANISED/BONDED TO A STEELSHELL. CORROSION APPEARS TO HAVE SPREAD BETWEEN TH	E PAD AND THE SHELL CAUSING DELAMINATION.					1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1998012200213	19980122	00213	CE  	1998	1	22	AU971390         	1	19971017	G	3230	MS16555354	PIN             			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	MLG DWNLOCK	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR DOWNLOCK PINS BENT DUE TO DEFECTIVE PADS (SEE MDR97/1389). WHEN THE DAMAGED PINS WERE REMOVED AND COM	PARED TO THE REPLACEMENT ITEMS THEY APPEARED TO BE MANUFACTURED FROM A SOFTER MATERIAL (AN5 BOLTS). PERSONNEL/MAINTENANC	E ERROR.				1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1998012200214	19980122	00214	CE  	1998	1	22	AU971391         	1	19971017	G	7922	75944	VALVE           	LYC         		CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	THERMO BYPASS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L1076851A		L176851A			(AUS) ENGINE OIL COOLER BYPASS VALVE (VERNATHERM) FACE BADLY SCORED FROM CONTACT WITH VALVE SEAT WHICH WAS ALSO DAMAGED.	 FOUND DURING INSPECTION IAW AD/LYC/78 AMDT5 WHICH WAS OVERDUE BY SEVERAL HUNDRED HOURS. PERSONNAL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA	 
1998012200215	19980122	00215	SW  	1998	1	22	AU971392         	1	19970921	G	5313	263132914	FITTING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C30P     	03013	GL  					AFT FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT FUSELAGE LONGERON FITTING CRACKED.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1998012200216	19980122	00216	SO  	1998	1	22	AU971393         	1	19971106	G	3232	756265	SPRING          	OZONE       		PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT MLG DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					2115					(AUS) LH MAIN LANDING GEAR DOOR ACTUATOR SPRING BROKEN.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1998012200217	19980122	00217	NE  	1998	1	22	AU971394         	2	19971103	G	8530	71167	VALVE           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  	HAMSTD	23D	23D40       	NE  	NR 2 CYL EXH	LEAKING         	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			979  				1866			(AUS) NO2 CYLINDER EXHAUST VALVE LEAKING.						1	H	7	1 	3R	3	R		A815    	5E2	6	C	P719	 
1998012200218	19980122	00218	NM  	1998	1	22	AU971395         	1	19971019	G	5101		AIRCRAFT        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					STRUCTURE	LIGHTNING STRIKE	W				K				NONE                    				C			F.O.D.                    			CL	CLIMB          	1			AU	S 										(AUS) AIRCRAFT SUFFERED A LIGHTNING STRIKE. DAMAGE TO BOTH PROPELLERS,RH AND LH INBOARD WINGS AND INBOARD FLAPS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998012200219	19980122	00219	NM  	1998	1	22	AU971396         	1	19971028	G	3230	8415	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					NLG RETRACT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					DCL24489					(AUS) NOSE LANDING GEAR DRAG BRACE ACTUATOR SEPARATED FROM AND DAMAGED NOSE GEAR WHEEL WELL STRUCTURE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998012200220	19980122	00220	CE  	1998	1	22	AU971397         	1	19970926	G	3211	5411212	SUPPORT         			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							486689L4			(AUS) LANDING GEAR SUPPORT CRACKED.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
1998012200221	19980122	00221	SW  	1998	1	22	AU971398         	1	19971108	G	6322	47661297	COOLING FAN     	BELL        	47          	BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1B   	41516	EA  					ROTORCRAFT	CORRODED        	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			359  		A345157					(AUS) COOLING FAN CORRODED. TWO ADJACENT BLADES BROKEN OFF. BROKEN BLADES CUT THROUGH THE VOLTAGE REGULATOR COVER AND IM	PACTED THE REGULATOR COOLING FINS. THEY THEN TRAVELLED DOWNWARDS, DAMAGING THE FUEL GAUGE LINE BEFORE COMING TO REST ON 	THE TAIL ROTOR CONTROL CABLES.				1	G	7	1 	3O	3	O		2H3     	1E13				 
1998012200222	19980122	00222	CE  	1998	1	22	AU971399         	1	19970930	G	2933		SIGHT GLASS     			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HYD QUANTITY	DAMAGED         	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) RH HYDRAULIC RESERVOIR SIGHT TUBE SPLIT AND LEAKING FLUID UNDER PRESSURE. HYDRAULIC CONTROL VALVE ALSO FOUND TO BE	 UNSERVICEABLE.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1998012200223	19980122	00223		1998	1	22	AU971400         	4	19971027	G	2565	7152	ACTUATOR        	AIRBUS      	7015000002  	AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					ESCAPE SLIDE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			29769		ACTUATOR9148					(AUS) DOOR 1R ESCAPE SLIDE DOOR ACTUATOR FAULTY. ACTUATOR DID NOT OPEN THE DOOR CORRECTLY WITH THE SLIDE PUSHING THE DOO	R FULLY OPEN. IT WAS ALSO NOTICED THAT THE EMERGENCY EQUIPMENT FELL OUT OF THE SLIDE. THE SLIDE DEPLOYED FULLY.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998012200224	19980122	00224	NM  	1998	1	22	AU971401         	1	19971028	G	2824	45744	ACTUATOR        			BOEING	737   	737476      		NM  										FUEL CROSSFEED	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 			2413 		3842					(AUS) FUEL SYSTEM CROSSFEED VALVE ACTUATOR SEIZED.						2	L	7	2 	4F			RT	A16WE   					 
1998012200225	19980122	00225	EU  	1998	1	22	AU971402         	1	19970721	G	5730		SKIN            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT RT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING UPPER SKIN LOWER SURFACE DAMAGED IN AREA OF STRINGERS AT RIBS 0 AND 2 ON BOTH LH AND RH SIDES. FOUND DURING I	NSPECTION IAW ER BA6-57-10-9A.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200226	19980122	00226	EU  	1998	1	22	AU971403         	1	19971103	G	2710	6852193	CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD AILERON CABLE STRANDS BROKEN. FOUND DURING INSPECTION IAW AD/P68/44 (PARTENAVIA SB 75 REV3).						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1998012200824	19980122	00824	EU  	1998	1	22	AU971404         	1	19971017	G	2621	5733312	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FIRE BOTTLE	LOW QUANTITY    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5418 		CL9116ANSETT					(AUS) APU FIRE EXTINGUISHER BOTTLE UNDERWEIGHT BY 0.4KG. EVIDENCE OFCORROSION ON THE BOTTLE.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200825	19980122	00825	SO  	1998	1	22	AU971405         	1	19970918	G	3213	653194	CYLINDER        			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L36727A	A55147		(AUS) MAIN LANDING GEAR CYLINDER CRACKED IN TORQUE LINK ATTACHMENTPOINTS.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1998012200826	19980122	00826	EU  	1998	1	22	AU971406         	1	19971103	G	2710	6852193	CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AILERON OUTBOARD CONTROL CABLE STRANDS BROKEN. FOUND DURINGINSPECTION IAW AD/P68/44 (PARTENAVIA SB 75 REV3).						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1998012200827	19980122	00827	EU  	1998	1	22	AU971407         	1	19971103	G	2710	6852195	CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON BALANCE CABLE STRANDS BROKEN. FOUND DURING INSPECTIONIAW AD/P68/44 (PARTENAVIA SB 75 REV3).						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1998012200828	19980122	00828	EU  	1998	1	22	AU971408         	1	19971103	G	2710	6852196	CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH AILERON BALANCE CABLE STRANDS BROKEN. FOUND DURING INSPECTIONIAW AD/P68/44 (PARTENAVIA SB 75 REV3).						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1998012200829	19980122	00829	EU  	1998	1	22	AU971409         	1	19971103	G	2730	6853211	CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FORWARD ELEVATOR CABLE STRANDS BROKEN. FOUND DURING INSPECTION IAW AD/P68/44 (PARTENAVIA SB 75 REV3).						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1998012200830	19980122	00830	EU  	1998	1	22	AU971410         	1	19971103	G	2750	6855312	CONTROL CABLE   			PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	TE FLAP CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FLAP CABLE STRANDS BROKEN. FOUND DURING INSPECTION IAW AD/P68/44 (PARTENAVIA SB 75 REV3).						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
1998012200831	19980122	00831	EU  	1998	1	22	AU971411         	1	19971002	G	2621	573332	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FIRE BOTTLE	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5910 		1248ANSETT00					(AUS) NO2 ENGINE INBOARD FIRE EXTINGUISHER BOTTLE ALMOST EMPTY. SUSPECT CAUSED BY CORROSION ON HEAD ASSEMBLY AND FILL FI	TTINGS ALLOWING LEAKAGE.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200832	19980122	00832	EU  	1998	1	22	AU971412         	1	19970913	G	2621	573332	FIRE BOTTLE     			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					APU FIRE BOTTLE	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6993 		CN2147ANSETT					(AUS) APU FIRE BOTTLE EMPTY. SUSPECT CAUSED BY CORROSION ON HEAD ANDFILL FITTINGS ALLOWING BOTTLE TO LEAK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998012200833	19980122	00833	NM  	1998	1	22	AU971413         	1	19970808	G	3244	397812	TIRE            			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					NR 4 MAIN	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					6456ANSETTSN					(AUS) NO4 MAIN LANDING GEAR TYRE TREAD SEPARATED. DAMAGE CAUSED TO FLAPS, MLG DOORS AND STABILISER LEADING EDGE. DAMAGE 	CAUSED BY A FOREIGN OBJECT PENETRATING THE TOP SIX PLYS OF THE TYRE.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
1998012200834	19980122	00834	SO  	1998	1	22	AU971414         	1	19971110	G	7110		COWLING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE COWLING	DEPARTED        	W				K				NONE                    				D	W		INFLIGHT SEPARATION       	INADEQUATE Q C            		DE	DESCENT        	1			AU	S 										(AUS) LH ENGINE COWLING SEPARATED FROM AIRCRAFT IN FLIGHT. THE TOP COWL WAS JAMMED ON THE LEADING EDGE OF THE OUTBOARD W	ING BY THESLIPSTREAM WHILE THE BOTTOM COWL WAS LOST. THIS WAS THE FIRST FLIGHT AFTER THE COWLS WERE REMOVED TO CARRY OUT	 AD/PHZL/60 A4. SUSPECT THAT THE COWLS WERE NOT CORRECTLY SECURED AFTER MAINTENANCE. PERSONNEL/MAINTENANCE ERROR.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998012200835	19980122	00835	NM  	1998	1	22	AU971415         	1	19971031	G	7540		ELECTRICAL SYS  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					BLEED AIR IND	CONTAMINATED    	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) BLEED AIR SYSTEM ELECTRICAL CIRCUIT CONTAMINATED WITH WATER DUE TO HEAVY RAIN.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998012200836	19980122	00836	EU  	1998	1	22	AU971416         	1	19970708	G	2133	82768	TORQUE LIMITER  			AIRBUS	320   	A320212     		EU  										PRESSURE REG	FAULTY          	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					74ANSETTSNO0					(AUS) AVIONICS COOLING SYSTEM INLET VALVE TORQUE LIMITER FAULTY.						2	L	7	2 	4F			RT	A28NM   					 
1998012200837	19980122	00837	SO  	1998	1	22	AU971417         	1	19971011	G	5520	7172	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ELEVATOR OUTBOARD HINGE CRACKED AND RIVET SHEARED.						1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1998012200838	19980122	00838	EA  	1998	1	22	AU971418         	2	19970925	G	8530	74541	VALVE           	LYC         		PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E2D     	41508	EA  					ENG NR 3 CYL EXH	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1664 				L25227A			(AUS) NO3 CYLINDER EXHAUST VALVE HEAD HAD APPROXIMATELY 30% MISSING.DAMAGE CAUSED TO THE TOP OF THE PISTON.						1	L	7	1 	3O	3	O		2A13    	E274				 
1998012200839	19980122	00839	NE  	1998	1	22	AU971419         	2	19970801	G	7200		ENGINE          								RROYCE	RB211 	RB211524G19 		NE  					LT ENGINE	SMOKE           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) LH ENGINE CAUSING SMOKE/MISTING/ODOUR IN THE CABIN AND SMOKE ALARM ACTIVATION IN THE AFT TOILET. INVESTIGATION FOU	ND THAT THE LH ENGINE HAD COMPLETED A COMPRESSOR WASH PRIOR TO THE FLIGHT.										4	F			E30NE				 
1998012200840	19980122	00840	NM  	1998	1	22	AU971420         	1	19971020	G	5210	41T6844	SWITCH          			BOEING	767   	767238      		NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					PASS NR 1 DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					000022					(AUS) LH SIDE NO1 DOOR CLOSE SWITCH FAULTY. THE DOOR WAS UNABLE TO BE OPENED EITHER BY MANUAL OR ELECTRICAL MEANS.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
1998012200841	19980122	00841	NM  	1998	1	22	AU971421         	1	19971015	G	2497		WIRE            			BOEING	767   	767338      	1385151	NM  										DC POWER DISTRIB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GENERATOR FEEDER CABLE CHAFED AND SHOWING EVIDENCE OF BURN MARKS.  LOCATED AT WING STATION S325 (NR 6 LE SLAT). IN	VESTIGATION FOUND THAT THE CABLE HAD CHAFED ON AN ADJACENT PNEUMATIC OVERHEAT DETECTOR CLIP.					2	L	7	2 	4F			RT	A1NM    					 
1998012200842	19980122	00842	WP  	1998	1	22	AU971422         	1	19971107	G	6220	51452	PIN             	HILLER      		HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					10527A					(AUS) MAIN ROTOR HEAD TENSION/TORSION PIN CRACKED.						1	G	7	1 	3O	3	O		4H11    	E304				 
1998012200843	19980122	00843	NE  	1998	1	22	AU971423         	2	19971102	G	7210	CP6B2254	COMBINING GRBOX 			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TURBINE ENGINE	MAKING METAL    	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			2056 		CP6B2254		CPGB2254			(AUS) ENGINE COMBINING GEARBOX METAL CONTAMINATION. SUSPECT CAUSED BY DETERIORATION OF BEARING CAGE.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1998012200844	19980122	00844	EU  	1998	1	22	AU971424         	2	19971111	G	7200		ENGINE          								CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							725274			(AUS) NR 1 ENGINE HAD LOSS OF POWER AND SEVERE VIBRATION.											4	F			E21EU				 
1998012200845	19980122	00845	NM  	1998	1	22	AU971425         	1	19970926	G	3244	H42X16X19	TIRE            			BOEING	737   	737377      		NM  										LT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					531106239327					(AUS) BOTH LH MAIN WHEEL TYRES FAILED. SUSPECT NO1 OUTBOARD TYRE FAILED FIRST DUE TO FOD. NO2 TYRE THEN FAILED DUE TO HI	GH ENERGY BRAKING COMBINED WITH RAPID DECELERATION. DAMAGE TO FLAPS, MLG DOORS AND BRAKE LINES. SMALL AMOUNTS OF TYRE DE	BRIS ALSO ENTERED THE LH ENGINE CAUSING MINOR DAMAGE TO FAN BLADES.				2	L	7	2 	4F			RT	A16WE   					 
1998012200846	19980122	00846	EU  	1998	1	22	AU971426         	1	19970711	G	2150	VFT215	SUPPORT         			AIRBUS	320   	A320212     		EU  										CABIN COOLING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					32ANSETTSN00					(AUS) SKIN AIR INLET VALVE FAULTY. INSPECTION FOUND EXCESSIVE AMOUNTS OF CORROSION IN THE MANUAL CONTROL HANDLE SUPPORT 	ASSEMBLY WHICH CAUSED THE VALVE TO SEIZE AND ALSO PREVENTED DEPLOYMENT OF THE CONTROL HANDLE PREVENTING MANUAL CLOSURE O	F THE VALVE.				2	L	7	2 	4F			RT	A28NM   					 
1998012200847	19980122	00847	NE  	1998	1	22	AU971427         	2	19971112	G	7200		ENGINE          			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					ENGINE NR 1	FAILED          	W				K				NONE                    				O	R	M	OTHER                     	PARTIAL RPM/PWR LOSS      	OVER TEMP                 	CR	CRUISE         	1			AU	S 							71517			(AUS) NO1 ENGINE LOST POWER AND EXCEEDED EGT LIMITS.						2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1998012200848	19980122	00848		1998	1	22	AU971428         	4	19971012	G	2350	61433	SWITCH          			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	PILOT PTT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS PTT SWITCH LOCATED ON LH CONTROL WHEEL FAILED INTERNALLY IN THE TRANSMIT MODE						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998012200849	19980122	00849	SO  	1998	1	22	AU971429         	2	19971027	G	7310	641486	PIPE            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	LT ENG FUEL DIST	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) LH ENGINE FUEL INJECTOR PIPE BETWEEN MANIFOLD AND INJECTOR CRACKED IN AREA WHERE NIPPLE IS BRAZED TO THE INJECTOR 	LINE.					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1998012200850	19980122	00850	NM  	1998	1	22	AU971430         	1	19971114	G	5311	A22	FRAME           			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					FUSELAGE UPPER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2396					(AUS) FUSELAGE UPPER FRAME CRACKED IN WELD IN AREA DESCRIBED IN AD/R22/41 A1.						1	G	7	1 	3O	3	O		H10WE   	E274				 
1998012200851	19980122	00851	CE  	1998	1	22	AU971431         	1	19971119	G	3233	35825944	ACTUATOR        			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	NLG	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ACTUATOR AFT ATTACHMENT LUG BROKEN OFF.						1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998012200852	19980122	00852	NM  	1998	1	22	AU971432         	1	19971117	G	5311	A22	FRAME           			ROBSIN	R22   	R22BETA     		NM  										TAILBOOM UPPER	MIS REPAIR      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) REPLACEMENT FUSELAGE UPPER FRAME CONTAINED UNAUTHORISED WELD REPAIR IN THE AREA OF THE TAIL BOOM ATTACHMENT. UNAPP	ROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.					1	G	7	1 	3O				H10WE   					 
1998012200853	19980122	00853	CE  	1998	1	22	AU971433         	1	19971007	G	3297		WIRE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT MLG  POS	BROKEN          	W				K				NONE                    				P			NO WARNING INDICATION     			LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE BROKEN.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
1998012200854	19980122	00854	CE  	1998	1	22	AU971434         	1	19971026	G	2810		FUEL SYSTEM     			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUEL STORAGE	CONTAMINATED    	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 							288427R			(AUS) FUEL SYSTEM CONTAMINATED BY WATER. ENGINE FAILURE RESULTED IN FORCED LANDING.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1998012200855	19980122	00855	CE  	1998	1	22	AU971435         	1	19971112	G	3297		WIRE            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	LT MLG POS	BROKEN          	W				K				NONE                    				P			NO WARNING INDICATION     			LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK MICROSWITCH EARTH WIRE (NO4) BROKEN AT TERMINAL.						1	L	7	2 	3O			 	A25CE   		5	C	P45GL	 
1998012200856	19980122	00856	NM  	1998	1	22	AU971436         	1	19971019	G	3242	262125	BRAKE           			BOEING	747   	747338      		NM  										LT BODY GEAR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT BRAKE ASSEMBLY FITTED TO LH BODY GEAR POSITION 7R. THE BRAKE UNIT WAS A &$&SP TYPE UNIT. PERSONNEL/MAINT	ENANCE ERROR.UNAPPROVED PART.					2	L	7	2 	4F			RT	A20WE   					 
1998012200857	19980122	00857	NM  	1998	1	22	AU971437         	1	19971029	G	5753	65B1159844	LUG             			BOEING	747   	747338      		NM  										RT NR 5 TE FLAP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO5 RH TRAILING EDGE FOREFLAP CARRIAGE AND TOGGLE ASSEMBLY DAMAGED. ONE ATTACHMENT LUG BROKEN OFF.						2	L	7	2 	4F			RT	A20WE   					 
1998012600013	19980126	00013	GL  	1998	1	26	AU971439         	3	19971021	G	6111		BLADE           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	LT PROP TIP	FOD             	W				K				NONE                    				O	C		OTHER                     	F.O.D.                    		IN	INSP/MAINT     	1			AU	S 							PCE93583	86287		(AUS) LH PROPELLER BLADE TIP BENT. BLOOD ON THE BLADE LEADS TO THE ASSUMPTION OF AND ANIMAL STRIKE.						1	L	7	2 	4T	4	T		A24CE   	E4EA	5	C	P60GL	 
1998012200858	19980122	00858	EU  	1998	1	22	AU971440         	1	19970923	G	2910	137935A77	HOSE            			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	RT ENG HYD	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC PRESSURE HOSE LOCATED BETWEEN THE RH ENGINE DRIVEN HYDRAULIC PUMP AND THE FIREWALL HAD FAILED. LOSS OF H	YDRAULIC FLUID.					2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1998012200859	19980122	00859		1998	1	22	AU971441         	1	19971020	G	7922		VALVE           								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	RT ENG OIL COOL	SEIZED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RH ENGINE OIL COOLER THERMOSTATIC BYPASS VALVE STUCK.											4	T			E4WE	6	C	P61GL	 
1998012200860	19980122	00860	EU  	1998	1	22	AU971442         	1	19971021	G	2810		CAP             			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	FUEL STORAGE	SERVICEABLE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CAPS FOUND TO BE SERVICEABLE FOLLOWING EAA-QA INVESTIGATION.						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1998012600014	19980126	00014	NM  	1998	1	26	AU971443         	1	19971011	G	2421	727792H	IDG             			BOEING	757   	757200      	1384950	NM  										AC GEN-ALT	FAILED          	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 					A0443					(AUS) LH INTEGRATED DRIVE GENERATOR (IDG) FAULTY.						2	L	7	2 	4F			RT	A2NM    					 
1998012200861	19980122	00861	NM  	1998	1	22	AU971444         	1	19970307	G	3244	222K682	TIRE            		H31X97513   	DHAV  	DHC8  	DHC8102     	2809003	NM  										MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TYRES (2OFF) FAILED. LIMITED INFORMATION PROVIDED.						2	H	7	2 	4T			RT	A13NM   					 
1998012200862	19980122	00862	EU  	1998	1	22	AU971445         	1	19971120	G	5720		FLAP SHROUD     			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WINGS CONTAINED CORROSION IN AREAS OF FLAP SHROUDS AND REAR BAYS.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200863	19980122	00863	EU  	1998	1	22	AU971446         	1	19971120	G	3250	NB4199	RING            			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL STEERING DRIVE RING CRACKED. FOUND DURING INSPECTION IAW SB 214 ISSUE 1.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200864	19980122	00864	EU  	1998	1	22	AU971447         	1	19971120	G	2731		TRIM BOX        			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEV TAB CONT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM BOX CRACKED.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200865	19980122	00865	EU  	1998	1	22	AU971448         	1	19971120	G	5521	NB3151	RIB             			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR RIB CRACKED. LOOSE AND MISSING RIVETS.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200866	19980122	00866	EU  	1998	1	22	AU971449         	1	19971120	G	5410	NB23721	ANGLE           		NB203721    	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH NACELLE BOX ANGLE LOCATED FORWARD OF PNO NB-20-C-5677 CRACKED.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200867	19980122	00867	EU  	1998	1	22	AU971450         	1	19971120	G	5410	NB21843	WEB             			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NAC LT & RT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NACELLE LH AND RH WEBS CRACKED. FOUND DURING INSPECTION IAW SB200.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200868	19980122	00868	NM  	1998	1	22	AU971451         	1	19971114	G	5751		HINGE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LT AIL OUTB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON OUTBOARD ATTACHMENT HINGE DAMAGED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998012200869	19980122	00869	WP  	1998	1	22	AU971452         	2	19971114	G	7200		ENGINE          								GARRTT	TPE331	TPE33112UA  	01514	WP  	ROTOL	R333	R333482F12  	GL  	RT ENGINE	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) RH ENGINE LOW POWER.											4	T			E4WE	6	C	P61GL	 
1998012200870	19980122	00870	EU  	1998	1	22	AU971453         	1	19971120	G	5520		ELEVATOR        			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEV STRUCTURE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CORRODED.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200871	19980122	00871	EU  	1998	1	22	AU971454         	1	19971120	G	5510		STABILIZER      			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	HORIZ STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER CORRODED.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920	 
1998012200872	19980122	00872	EA  	1998	1	22	AU971455         	2	19971117	G	8520	L789661A	CRANKCASE       	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L789661A		L789661A			(AUS) ENGINE CRANKCASE CRACKED. INVESTIGATION FOLLOWING ENGINE STRIP FOUND TWO DAMAGED CAM FOLLOWERS.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998012200873	19980122	00873	SW  	1998	1	22	AU971456         	1	19971117	G	6710	25743H	BOLT            	BELL        		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					M/R CONTROL	INCORRECT PART  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A265					(AUS) COLLECTIVE LEVER ASSEMBLY PIN PNO 412-010-422-103 FALLEN OUT. THE PIN IS LOCATED ON THE TRANSMISSION CASING. BOLT 	PNO 20-057-4-3H AND WASHER PNO AN460-416 WAS ATTACHED TO THE PIN WITH LOCKWIRE. INVESTIGATION FOUND THAT THE BOLT PNO 20	-057-4-3H WAS THE INCORRECT PART, THE CORRECT PART NUMBER WAS PNO NAS6604H5 WHICH IS 3.175MM (0.125IN) LONGER. THE REMAI	NING COLLECTIVE LEVER PIN ALLOWED THE COLLECTIVE LEVER PNO 412-010-401-109 TO BE MISALIGNED RESULTING IN THE LEVER RUBBI	NG ON THE MAIN ROTOR MAST.PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.		1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1998012200874	19980122	00874	CE  	1998	1	22	AU971457         	1	19971124	G	3222	5452112	FORK            			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NLG FORK FITTING	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR FORK END FITTINGS CRACKED. NLG FAILED TO LOCK DOWN.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998012200875	19980122	00875		1998	1	22	AU971458         	4	19970501	G	2310	KHA95	TRANSCEIVER     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HF COMM	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) HF RADIO SCRATCHY AND WEAK ON TRANSMIT.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998012200876	19980122	00876		1998	1	22	AU971459         	4	19971124	G	3457		GPS SYSTEM      	KING        	KC555       	CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	2AF34C	D2AF34C71   	GL  	GLOBAL POSIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GPS INTERFACE TO HSI AND AIRDATA SYSTEM FAULTY ALLOWING AIRCRAFT TO WANDER IN AUTOPILOT NAV MODE.						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P5EA	 
1998012200878	19980122	00878	EU  	1998	1	22	AU971461         	1	19970819	G	5312		WEB             			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FWD PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN TWO PLACES:- 1. WEB AT HORIZONTAL BEAM 7 LOCATED OUTBOARD OF VERTICAL BEAM  B	L325L 2. WEB AT HORIZONTAL BEAM 8 LOCATED OUTBOARD OF VERTICAL BEAM  BL325L FOUND DURING VISUAL INSPECTION IAW ER F28-53	-10-20G.				2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1998012200879	19980122	00879	EU  	1998	1	22	AU971462         	2	19971118	G	7270	3353465	GUIDE VANE      								CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1 ENG FAN	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							721712			(AUS) NO1 ENGINE FAN OUTLET GUIDE VANE FAILED AT MID SPAN AND DEPARTED FROM THE ENGINE.											4	F			E21EU				 
1998012200880	19980122	00880	EU  	1998	1	22	AU971463         	1	19970806	G	5240		DOOR            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					RT SERVICE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH SERVICE/EMERGENCY DOOR CONTAINED TWO CRACKS IN THE LOWER AFT CORNER RUNNING UNDER THE REPAIR DOUBLERS. CRACK LE	NGTHS 5MM AND 6MM (0.19IN AND 0.23IN). FOUND DURING EDDY CURRENT INSPECTION IAW ER F28/53/30/18C.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1998012200881	19980122	00881	NM  	1998	1	22	AU971464         	1	19971103	G	7312	113	HEATER          			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					NR 1 ENG FUEL	STRIPPED        	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 					113					(AUS) NO1 ENGINE P.H.I. FUEL HEATER ASSEMBLY FUEL OUT UNION PN MS9193-07 LOOSE. FURTHER INVESTIGATION FOUND THAT THE THR	EAD INSIDE THE HEATER ASSEMBLY WAS STRIPPED .					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1998012200882	19980122	00882	SO  	1998	1	22	AU971465         	1	19971124	G	5513	63585	TRIM TAB        	PIPER       		PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B2B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR TRIM TABS CRACKED AT INBOARD END ADJACENT TO THE ACTUATING ARM ATTACHMENT. CRACKING EVIDENT IN SKIN PAN	ELS AND INBOARD RIB.					1	L	7	1 	3O	3	O		2A13    	E295	5	C	P920	 
1998012200883	19980122	00883	CE  	1998	1	22	AU971466         	1	19971121	G	7100		HOSE            			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470K      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	POWERPLANT SYS	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							867856K	72339		(AUS) ALL FLUID HOSES IN ENGINE COMPARTMENT NOT PROTECTED BY FIRE SLEEVES. PERSONNEL/MAINTENANCE ERROR.						1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880	 
1998012200884	19980122	00884	EA  	1998	1	22	AU971467         	2	19971118	G	8530		VALVE SEAT      			BELL  	47    	47J2A       	1181106	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					ENG NR 4 CYL EXH	SEPARATED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 			160  				L88252			(AUS) NO4 CYLINDER EXHAUST VALVE SEAT SEPARATED FROM CYLINDER. NO2 CYLINDER EXHAUST VALVE AND VALVE GUIDE UNSERVICEABLE.	 NO2 CYLINDER HEAD EXTENSIVELY CRACKED.					1	G	7	1 	3O	3	O		2H1     	1E13				 
1998012200885	19980122	00885	SW  	1998	1	22	AU971468         	1	19970813	G	8120	466115	TURBOCHARGER    			BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435D1A   	41516	EA  					EXH TURBO	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							L311952			(AUS) ENGINE TURBOCHARGER FAILED. INVESTIGATION FOUND THAT THE EXHAUST TURBINE HAD BEEN SKIDDING ON THE REAR THRUST FACE	.					1	G	7	1 	3O	3	O		2H3     	1E13				 
1998012200886	19980122	00886	CE  	1998	1	22	AU971469         	1	19971114	G	5730	E352	RIVET           	BEECH       	E3052       	BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	LT RT WING SKIN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING UPPER SKIN ATTACHMENT RIVETS SANDED TO A DEGREE WHEREBY UP TO 2/3 OF THE RADIUS MATERIAL HAS BEEN R	EMOVED. THE SANDING HAS ALSO REMOVED ALODINE SURFACE TREATMENT FROM THE UPPER WING SURFACES.					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
1998012600015	19980126	00015	EA  	1998	1	26	AU971471         	2	19971107	G	8500		ENGINE          			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HO360*      	41514	EA  					POWER PLANT	FAILED          	W				A				UNSCHED LANDING         				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CL	CLIMB          	1			AU	S 							L3486836A			(AUS) ENGINE SUFFERED A POWER LOSS FOLLOWED BY A STOPPAGE. AIRCRAFT CRASHED.						1	G	7	1 	3O	3	O		4H12    	E286				 
1998012200887	19980122	00887	EA  	1998	1	22	AU971472         	2	19971118	G	8500	L181964A	ENGINE          	LYC         		PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	LT MAG DRIVE	FAILED          	W				K				NONE                    				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CL	CLIMB          	1			AU	S 			1999 		L1819640A		L181964A	14711		(AUS) ENGINE STOPPED. INITIAL INVESTIGATION FOUND THE LH MAGNETO DRIVE GEAR TO BE DAMAGED AND THE SUPPORT BEARING FAILED	. ROTATING THE PROPELLER DID NOT CAUSE THE REAR CASE GEAR TRAIN TO OPERATE.					1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874	 
1998012200888	19980122	00888	CE  	1998	1	22	AU971473         	1	19971127	G	3260	1SE13	SWITCH          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT MLG DWNLOCK	BROKEN          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 							LH56586	LH768457		(AUS) RH MAIN LANDING GEAR DOWNLOCK MICROSWITCH LEVER BROKEN OFF.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998012200889	19980122	00889	CE  	1998	1	22	AU971474         	1	19971127	G	5341	16941318	FRAME           			BEECH 	23    	A23         	1151204	CE  	CONT  	O346  	IO346A      	17033	SO  					WING ATTACH	MIS REPAIR      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE TO WING ATTACHMENT FRAME FILED OUT ON THE INSIDE RADIUS AND INCORRECT RIVET FITTED TO THE FORWARD WING MA	IN SPAR SUPPORT. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART/REPAIR.					1	L	7	1 	3O	3	O		A1CE    	E3CE				 
1998012200890	19980122	00890	CE  	1998	1	22	AU971475         	1	19971127	G	5512	169621661	STABILIZER      			BEECH 	23    	A23         	1151204	CE  	CONT  	O346  	IO346A      	17033	SO  					HORIZ STAB	INCORRECT MOD   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR INCORRECTLY MODIFIED IAW SI 1167. THE STABILISER HAD ONLY TWO INSPECTION PANELS FITTED TO THE UNDERSIDE	 INSTEAD OF THE FOUR STIPULATED IN SI 1167.					1	L	7	1 	3O	3	O		A1CE    	E3CE				 
1998012200891	19980122	00891	WP  	1998	1	22	AU971476         	1	19971030	G	7160	269A81523	VALVE           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE AIR INT	ILLEGAL MOD     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							RL2215751A			(AUS) INTAKE ALTERNATE AIR VALVE ILLEGALLY MODIFIED. THE VALVE WAS SEALED CLOSED WITH SEALANT AND A PLASTIC OIL BOTTLE W	AS GLUED OVER THE TOP. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION.					1	G	7	1 	3O	3	O		4H12    	1E10				 
1998012200892	19980122	00892	CE  	1998	1	22	AU971477         	1	19971127	G	5730	16911686	PANEL           		110000663   	BEECH 	23    	A23         	1151204	CE  	CONT  	O346  	IO346A      	17033	SO  					WING INSP PANEL	INCORRECT MOD   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING INSPECTION PANELS INCORRECT SIZE. SI 0824-035 REV11 STIPULATES THE PANELS SHOULD BE 127MM (5IN) IN DIAMETER B	UT THOSE FITTED ARE ONLY 100MM (4IN) DIAMETER MAKING ACCESS DIFFICULT.					1	L	7	1 	3O	3	O		A1CE    	E3CE				 
1998012200893	19980122	00893	WP  	1998	1	22	AU971478         	1	19971031	G	6310	269A546	HUB             			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENG-TRANS	MIS INSTALLED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							RL2215751A			(AUS) ENGINE TO TRANSMISSION UPPER CLUTCH HUB INSTALLED THE WRONG WAY AROUND. BEARING SEAT SHOULDER SHEARED OFF. PERSONN	EL/MAINTENANCE ERROR.					1	G	7	1 	3O	3	O		4H12    	1E10				 
1998012200894	19980122	00894	SO  	1998	1	22	AU971479         	2	19971127	G	7414	13571651	COIL            	BENDIX      	201205      	BEECH 	23    	A23         	1151204	CE  	CONT  	O346  	IO346A      	17033	SO  					ENG MAG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAGNETO COILS BREAKING DOWN. MAGNETO LEADS ALSO FAULTY.						1	L	7	1 	3O	3	O		A1CE    	E3CE				 
1998012200895	19980122	00895	WP  	1998	1	22	AU971480         	1	19971031	G	7112	269A853311	SCROLL          			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENG AIR BAFFLE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							RL2215751A			(AUS) ENGINE SCROLL ASSEMBLY LOWER MOUNT SEPARATED. UPPER RH BRACKET PNO 269A8597 WAS ALSO FOUND TO BE UNSERVICEABLE. TH	E SCROLL WAS FOULING ON THE IMPELLER.					1	G	7	1 	3O	3	O		4H12    	1E10				 
1998012200896	19980122	00896	WP  	1998	1	22	AU971481         	1	19971031	G	6310	269A5582	PULLEY          			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENG-TRANS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DRIVE BELT IDLER PULLEY HAD THE ANODIZED COATING WORN THROUGH IN ALL GROOVES.						1	G	7	1 	3O	3	O		4H12    	1E10				 
1998012200897	19980122	00897	EU  	1998	1	22	AU971482         	1	19971120	G	5343		FITTING         			MUDRY 	10    	CAP10B      		EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	LT RT FWD ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH FORWARD UNDERCARRIAGE ATTACHMENT BLOCKS CRACKED. FOUND DURING INSPECTION IAW SB15 2(B).						1	L	7	1 	3O	3	O		A36EU   	1E10	5	N	P3EU	 
1998012200898	19980122	00898	NE  	1998	1	22	AU971483         	2	19971126	G	7261		CHIP DETECTOR   			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENG	SEPARATED       	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) NO1 ENGINE FULL FLOW CHIP DETECTOR DISLODGED ALLOWING A MASSIVE OIL LEAK. ENGINE WAS INSPECTED IAW MAINTENANCE MAN	UAL WITH NO FAULT FOUND AND RETURNED TO SERVICE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998012200899	19980122	00899	NM  	1998	1	22	AU971484         	1	19970624	G	5311	A22	FRAME           	ROBSIN      		ROBSIN	R22   	R22MARINER  		NM  	LYC   	O320  	O320B2C     	41508	EA  					RT MLG GRBOX MT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1088 		2346					(AUS) FUSELAGE UPPER FRAME TUBE FROM RH REAR MAIN GEARBOX MOUNT PAD TO THE RH DECK BOLT CRACKED THROUGH WELD UNDER THE G	EARBOX MOUNT PAD.					1	G	7	1 	3O	3	O		H10WE   	E274				 
1998012200900	19980122	00900	SW  	1998	1	22	AU971485         	1	19971017	G	5744	27344277	BRACKET         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	LT AIL PIVOT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON CENTRE ATTACHMENT BRACKET CRACKED ON UPPER AND LOWER WEBS AT AILERON INPUT BELLCRANK PIVOT BOLT ATTACHM	ENT AREA.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
1998012200901	19980122	00901	CE  	1998	1	22	AU971486         	1	19971127	G	3411	RA1JA7	FILTER          			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	DIRECTIONAL GYRO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INLINE PRESSURE FILTER TO DIR GYRO CRACKED AND LEAKING.						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1998012200902	19980122	00902	EU  	1998	1	22	AU971487         	1	19971018	G	2913	74A33694	DRIVE BELT      	AEROSP      	704A3431006 	SNIAS 	350   	AS350D      	8680803	EU  	ALLSN 	250C  	250C30      	03013	GL  					HYDRAULIC PUMP	LOOSE           	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					10658770					(AUS) HYDRAULIC PUMP DRIVE BELT LOOSE. SEE MDR 97/1319 FOR ADDITIONAL INFORMATION						1	G	7	1 	3U	3	U		H9EU    	E1GL				 
1998012200903	19980122	00903	SO  	1998	1	22	AU971488         	1	19971106	G	7920	338	HOSE            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	ENG OIL DIST	DETERIORATED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							1647936	18469K		(AUS) OIL COOLER HOSES (2OFF) FAULTY. OIL SEEPING THROUGH FIRE SLEEVE.						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
1998012200904	19980122	00904	SO  	1998	1	22	AU971489         	1	19971126	G	3411		LINE            			PIPER 	J3    	J3          	7100502	SO  	CONT  					MCAULY	1A103	1A103TCM    	GL  	PITOT/STATIC SYS	DISCONNECTED    	W				K				NONE                    				I			FLT. ATTITUDE INST.       			CL	CLIMB          	1			AU	S 										(AUS) STATIC LINE DISCONNECTED AT REAR OF ASI. PERSONNEL/MAINTENANCE ERROR.						1	H	7	1 	3O				ATC660  		5	N	P50GL	 
1998012200905	19980122	00905	EU  	1998	1	22	AU971490         	1	19971126	G	2910	A2714201200000	HOSE            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					GREEN HYD	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 					A27142012000					(AUS) HYDRAULIC HOSE TO THE ALL SPEED AILERON LOCATED AT THE LH WING REAR FALSE SPAR ON RIB 6A FAILED. LOSS OF GREEN SYS	TEM HYDRAULIC FLUID.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998012200906	19980122	00906	GL  	1998	1	22	AU971491         	1	19971105	G	3230		TORQUE TUBE     			AMTR  	SEAREY	SEAREY      	05625X5	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					LANDING GEAR RET	DISTORTED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR COLLAPSED. INVESTIGATION FOUND THAT THE LANDING GEAR TORQUE TUBE ASSEMBLY WAS TWISTED WHEN THE AIRCRA	FT FELL OFF A STAND DURING ASSEMBLY. AIRCRAFT IS AMATEUR BUILT.					1	H	7	1 	3I	3	I	RC	1H71EXPA	EXPE3I				 
1998012200907	19980122	00907	NM  	1998	1	22	AU971492         	1	19971128	G	5330		SKIN            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					BS 521 - 545	DAMAG           	W				K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) REAR FUSELAGE DAMAGED JUST FORWARD OF THE CARGO DOOR DUE TO IMPACT BY BAGGAGE HANDLERS TRACTOR. NO TEARING OR CRAC	KING OF THE SKIN WAS EVIDENT ALTHOUGH THE LIMITS OF THE DAMAGE ARE BEYOND THE SIZE ALLOWABLE TO CONTINUE WITHOUT REPAIR.	 DAMAGE WAS LOCATED BETWEEN FS 521 AND FS 545 AND CROSSES FRAMES AT FS 531.5 AND FS 539 BETWEEN STRINGERS 22 AND 23 LEFT	. THE MAXIMUM DEPTH BETWEEN THE FRAMES IS 5.334MM (0.210IN), 5.588MM (0.220IN) AND 4.572MM(0.180IN).			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998012200908	19980122	00908	SW  	1998	1	22	AU971493         	1	19971025	G	2460	PSM	CIRCUIT BREAKER 			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	DC POWER DISTRIB	FAULTY          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL CIRCUIT BREAKERS FAILED TO MEET MANUFACTURERS REQUIREMENTS.						1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P257	 
1998012200909	19980122	00909	SW  	1998	1	22	AU971494         	1	19971128	G	2460		CIRCUIT BREAKER 			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	DC POWER DISTRIB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CIRCUIT BREAKERS FAULTY.						1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P257	 
1998012200910	19980122	00910	SW  	1998	1	22	AU971495         	1	19971201	G	2460		CIRCUIT BREAKER 			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	22D	22D40       	NE  	DC POWER DISTRIB	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CIRCUIT BREAKERS FAULTY.						1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P736	 
1998012200911	19980122	00911		1998	1	22	AU971496         	4	19971202	G	3424	1394T1005Y	INDICATOR       			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	22D	22D40       	NE  	TURN & BANK	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TURN AND SLIP INDICATOR FAULTY. WHITE PAINT BEHIND SLIP BALL IS CRAZED AND FLAKING. ON/OFF FLAG IS PUSHED BACK ONT	O TURN AND SLIP INDICATOR. INSTRUMENT FAILED AD/INST8 AMDT3.					1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P736	 
1998012600016	19980126	00016	NE  	1998	1	26	AU971497         	2	19971119	G	7322		SENSOR          			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					FUEL CONTROL	FOD             	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							657272			(AUS) NO1 ENGINE P2 INLET BLOCKED BY A WASP.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1998012200912	19980122	00912	SO  	1998	1	22	AU971498         	1	19971110	G	7820	66894003	MUFFLER         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	BAFFLE	CRACKED         	W				K				NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 							L817539A			(AUS) MUFFLER BAFFLE COLLAPSED INTERNALLY CAUSING PARTIAL BLOCKING OF THE MUFFLER OUTLET.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1998012200913	19980122	00913	EU  	1998	1	22	AU971499         	1	19970801	G	3234	9036001	GEAR            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LANDING GEAR SEL	SLIPPING        	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					788GB324H890					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR TORQUE LIMITER SLIPPING.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200914	19980122	00914	EU  	1998	1	22	AU971500         	1	19970820	G	3260	HTE9449	SWITCH          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG POS	FAULTY          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		CL	CLIMB          	1			AU	S 			353  		1187GB108HAN					(AUS) LANDING GEAR SELECTOR VALVE AND ACTUATOR ASSEMBLY MICROSWITCH ACTUATING ARM PIVOT PIN DISLODGED.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200915	19980122	00915	CE  	1998	1	22	AU971502         	1	19971111	G	3297		WIRE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NLG	BROKEN          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		CL	CLIMB          	1			AU	S 			10552							(AUS) NOSE LANDING GEAR INDICATOR ARM ACTUATING WIRE BROKEN.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
1998012200916	19980122	00916	EU  	1998	1	22	AU971503         	1	19971113	G	3242		PISTON          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BRAKE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) RH NO3 BRAKE AUXILIARY PISTON LEAKING. LOSS OF HYDRAULIC FLUID FROM GREEN SYSTEM.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200917	19980122	00917	EU  	1998	1	22	AU971504         	1	19971129	G	2910		HOSE            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					GREEN HYD	FAILED          	W				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) RH LANDING GEAR RETRACTION ACTUATOR PRESSURE HOSE FAILED. LOSS OF GREEN SYSTEM HYDRAULIC FLUID.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998012200918	19980122	00918	NM  	1998	1	22	AU971505         	1	19971202	G	5512		SKIN            			DHAV  	DHC8  	DHC8202     	2809007	NM  										HORIZ STAB LE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH HORIZONTAL STABILISER UPPER AND LOWER LEADING EDGES CONTAINED CORROSION AROUND FASTENER HOLES. AIRCRAFT 	OPERATES IN A SALT LADEN ENVIRONMENT AND IS WASHED REGULARLY, HOWEVER THE HEIGHT OF THE TAILPLANE MAKES THE WASHING OF T	HIS AREA DIFFICULT.				2	H	7	2 	4T			RT	A13NM   					 
1998012200919	19980122	00919	EU  	1998	1	22	AU971506         	1	19971125	G	2913		O-RING          			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305       		NE  					NR 1 HYD PUMP.	FAILED          	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 										(AUS) NO1 ENGINE HYDRAULIC PUMP HIGH PRESSURE FITTING `O' RING SEAL FAILED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A3EU    	E35NE				 
1998012200920	19980122	00920	EA  	1998	1	22	AU971507         	2	19971107	G	8530	76190	CYLINDER        			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	INCORRECT ASSY  	W				K				NONE                    				E	R	W	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            	IN	INSP/MAINT     	1			AU	S 										(AUS) RH ENGINE CONTAINED THREE CYLINDERS WITH INCORRECT BARREL/PISTON RING COMBINATION. LH ENGINE HAD ONE CYLINDER WITH	 INCORRECT RINGS. THE AFFECTED CYLINDERS WERE CHROMED CYLINDERS (CERMICROME) BUT DURING THE PREVIOUS ASSEMBLY WERE MISTA	KEN FOR NITRIDED CYLINDERS AND FITTED WITH THE APPROPRIATE PISTON RINGS (CHROME) FOR THAT TYPE CYLINDER RESULTING IN CHR	OME RINGS IN A CHROME CYLINDER. PERSONNEL/MAINTENANCE ERROR			1	H	7	2 	3O	3	O		6A1     	1E4				 
1998021100003	19980211	00003		1998	2	11	AU971508         	4	19971203	G	6113		BULKHEAD        													MCAULY	1A135	1A135BRM    	GL  	PROP SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								OK12		(AUS) PROPELLER SPINNER BULKHEAD CRACKED IN AREA AROUND THREE MOUNTING BOLT HOLES.																5	N	P842	 
1998012200921	19980122	00921	CE  	1998	1	22	AU971509         	1	19971126	G	5210	20394254013	HOOK            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	CABIN DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR UPPER HOOK BROKEN.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1998012200922	19980122	00922	EU  	1998	1	22	AU971510         	1	19971111	G	7830	CF6RHFRAF1	THRUST REVERSER 			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			24701							(AUS) RH OUTBOARD THRUST REVERSER CORRODED AND DAMAGED. METAL STRUT LEADING EDGE DAMAGED AREA BROKEN OFF AND LODGED IN C	ASCADE FORWARD RECESS CAUSING A BLOCKER DOOR TO BREAK AND SEVERE BLOCKER DOOR CARRIAGE DAMAGE.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998012200923	19980122	00923	EU  	1998	1	22	AU971511         	1	19971120	G	7500		DUCT            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					BLEED AIR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 ENGINE 15TH STAGE DUCT CRACKED CIRCUMFERENTIALLY. NUMEROUS TIE ROD ENDS SNAPPED OFF. HP RECOUP TUBE SEVERELY C	HAFFED.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998012200924	19980122	00924	NE  	1998	1	22	AU971512         	2	19970703	G	7310	1602ANSETTSNO	MANIFOLD        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE FUEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1602ANSETTSN		LF05183			(AUS) NO2 ENGINE INBOARD FUEL MANIFOLD CRACKED. FOUND DURING EDDY CURRENT INSPECTION IAW ER ALF73-10-20 PART 2B.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200925	19980122	00925	CE  	1998	1	22	AU971513         	1	19971126	G	2720		SPRING          		1015241863  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER CONTROL	FAULTY          	W				K				NONE                    				F	W		FLT CONT AFFECTED         	INADEQUATE Q C            		NR	NOT REPORTED   	1			AU	S 										(AUS) RUDDER BOOST CABLE TENSION SPRING STRETCHED. INCORRECT TENSION ON THE CABLE ALLOWED THE RUDDER BOOST ACTUATOR ARM 	TO JAM UNDER THE LIP OF THE BULKHEAD. THE BULKHEAD WAS ALSO DAMAGED.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998012200926	19980122	00926	EA  	1998	1	22	AU971514         	2	19970825	G	8520	UO435	CRANKCASE       	LYC         	TVO435D1B   						LYC   	O435  	TVO435D1B   	41516	EA  					ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L1284		L1284			(AUS) CRANKCASE FAULTY. LIMITED INFORMATION PROVIDED.											3	O			1E13				 
1998012200927	19980122	00927	CE  	1998	1	22	AU971515         	1	19971108	G	5610		WINDSHIELD      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COCKPIT RT	BIRD STRIKE     	W				K				NONE                    				O	C		OTHER                     	F.O.D.                    		TO	TAKEOFF        	1			AU	S 										(AUS) BIRDSTRIKE ON RH WINDSCREEN. NIL DAMAGE.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998012200928	19980122	00928	CE  	1998	1	22	AU971516         	1	19971113	G	3260	1013646281	SWITCH          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MLG	INTERMITTENT    	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT OPERATION.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998012200929	19980122	00929	CE  	1998	1	22	AU971517         	1	19971129	G	3246	AN547	BOLT            			CESSNA	210   	210N        	2073453	CE  										NLG FORK	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE WHEEL ATTACHMENT BOLT FAILED. WHEEL TWISTED IN NLG FORK. SUSPECT BROKEN BOLT.						1	H	7	1 	3O				3A21    					 
1998012200930	19980122	00930	SO  	1998	1	22	AU971518         	2	19971122	G	8530	641917A12	VALVE           			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					ENG EXH NR 4	STICKING        	W				A				UNSCHED LANDING         				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			AU	S 							633146A			(AUS) NO4 CYLINDER EXHAUST VALVE STUCK OPEN. LOSS OF POWER AND ROUGH RUNNING RESULTED IN A FORCED LANDING IN THE BUSH.						1	H	7	1 	3O	3	O		3A19    	E252				 
1998012200931	19980122	00931	CE  	1998	1	22	AU971519         	1	19971116	G	3213	51410059	TORQUE LINK     			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR TORQUE LINK SEPARATED AT THE CENTRE HINGE POINT. THE CENTRE HINGE BOLT COMPLETE WITH NUT, SPL	IT PIN, BUSHES AND WASHERS PULLED THROUGH THE LOWER TORQUE LINK. SUSPECT CAUSED BY WORN BUSHES AND/OR IMPROPER SHIMMING 	OF THE CENTRE HINGE POINT.				1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA	 
1998012200932	19980122	00932	SO  	1998	1	22	AU971520         	1	19971201	G	2810	99321	CAP             			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RT OUTB FUEL	SEPARATED       	W				K				NONE                    				O	D		OTHER                     	INFLIGHT SEPARATION       		IN	INSP/MAINT     	1			AU	S 										(AUS) RH OUTBOARD FUEL CAP SEPARATED FROM TANK. INVESTIGATION FOUND THAT THE CAP WAS STILL LOCKED INTO THE ADAPTER RING 	WHICH HAD SEPARATED FROM THE FILLER HOLE DUE TO THE LOCKING TABS ON THE ADAPTER NOT ENGAGING IN THE FILLER SLOT HOLES AL	LOWING THEADAPTER TO ROTATE AND COME LOOSE. FURTHER INSPECTION OF THE OTHER FUEL CAPS FOUND THE RH INBOARD CAP ADAPTER L	OCKING TABS NOT ENGAGED.			1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1998012200933	19980122	00933	CE  	1998	1	22	AU971521         	1	19971205	G	5210	3540001818	HINGE           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	CABIN DOOR	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN CABIN DOOR UPPER FORWARD HINGE FRACTURED AT THE HINGE BOLT HOLE. SUSPECT INITIATED BY INTERGRANULAR CORROSION	 DUE TO DISSIMILAR METAL CONTACT.					1	L	7	2 	3O				3A16    		5	C	P22EA	 
1998012600017	19980126	00017	EA  	1998	1	26	AU971522         	2	19971203	G	7414	IO51324	SPRING          	BENDIX      	IO382754    	BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  					RT ENG MAG	BROKEN          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			1414 							(AUS) RH ENGINE MAGNETO IMPULSE COUPLING SPRING BROKEN.						1	L	7	2 	3O	3	O		A29CE   	E286				 
1998012200934	19980122	00934	GL  	1998	1	22	AU971523         	1	19971120	G	5712	C1W317A1	RIB             			DHAV  	DHC1  	DHC1TMK10   	2801712	GL  	LYC   	O360  	IO360A1A    	41514	EA  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1768851			(AUS) RH WING ROOT RIB CRACKED IN AREA OF FLAP CABLE PULLEY ATTACHMENT.						1	L	7	1 	3O	3	O		EXPA1L71	1E10				 
1998012200935	19980122	00935		1998	1	22	AU971524         	4	19971207	G	6122	89741016	GOVERNOR        													ROTOL	R333	R333482F12  	GL  	LT ENG PROP GOV	MALFUNCTION     	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 					2454730B					(AUS) LH ENGINE PROPELLER GOVERNOR SLUGGISH IN OPERATION.																6	C	P61GL	 
1998012200936	19980122	00936	CE  	1998	1	22	AU971525         	1	19971209	G	3710	RAIJ47	FILTER          			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	VACUUM SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VACUUM SYSTEM CLEAR INLINE PRESSURE FILTER CRACKED AROUND JOINT.						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
1998012200937	19980122	00937	EU  	1998	1	22	AU971526         	1	19971012	G	5210	350A25126820	FITTING         			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					RT DOOR AFT MT	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RH SLIDING DOOR REAR ROLLER MOUNT CRACKED AND BROKEN. WHEN THE DOOR WAS OPENED THE DOOR ATTEMPTED TO SEPARATE FROM	 THE AIRCRAFT BUT WAS HELD IN PLACE BY A PASSENGER.					1	G	7	2 	3U	3	U		H11EU   	E4CE				 
1998012200938	19980122	00938	SW  	1998	1	22	AU971527         	1	19971115	G	5345	412418001	FITTING         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					HOIST BEAM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HOIST BEAM ATTACHMENT FITTING CRACKED.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1998012200939	19980122	00939	CE  	1998	1	22	AU971528         	1	19971202	G	2612	IN4007	DIODE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION	SHORTED         	W				K				NONE                    				E	N		VIBRATION/BUFFET          	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 										(AUS) FIRE AUDIO BOX DIODE SHORT CIRCUITED.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998012200940	19980122	00940	SO  	1998	1	22	AU971529         	1	19971114	G	7922	53E22144	VALVE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENG OIL TEMP	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							L169461			(AUS) ENGINE OIL COOLER BYPASS VALVE FAULTY.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998012200941	19980122	00941	NE  	1998	1	22	AU971530         	2	19971201	G	7250		SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENG NR 4 BRG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LF05937A			(AUS) ENGINE NO4 BEARING SEAL FAULTY. OIL PRESENT IN TAILPIPE.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200942	19980122	00942	WP  	1998	1	22	AU971531         	2	19971207	G	7322	CH14583	PIN             		A148HIM     	DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					THROTTLE LEVER	MISSING         	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					V1809		940			(AUS) TAPER PIN  SECURING THROTTLE LEVER PN CH46158 TO THE THROTTLE SPINDLE PN CH14470 MISSING. THIS ALLOWED THE THROTTL	E LEVER TO MOVE WITHOUT MOVING THE THROTTLE BUTTERFLY.					1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1998012200943	19980122	00943		1998	1	22	AU971532         	4	19971127	G	2360		STATIC WICK     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT AILERON	LIGHTNING STRIKE	W				K				NONE                    				C			F.O.D.                    			TO	TAKEOFF        	1			AU	S 										(AUS) AIRCRAFT SUFFERED A LIGHTNING STRIKE. INSPECTION FOUND THE ONLY POINT OF THE STRIKE WAS ON THE LH AILERON STATIC W	ICK.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200944	19980122	00944	NE  	1998	1	22	AU971533         	2	19971201	G	7260		SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENG IDG	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							LF05290			(AUS) NO4 ENGINE IDG LIP SEAL LEAKING.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998012200945	19980122	00945	EU  	1998	1	22	AU971534         	1	19971122	G	2432	92583	CELL            		97500640    	BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BATTERY	OVERHEATED      	W				K				NONE                    				B	M		SMOKE/FUMES/ODORS/SPARKS  	OVER TEMP                 		CR	CRUISE         	1			AU	S 					C0824ANSETTS					(AUS) MAIN AIRCRAFT BATTERY INTERNAL MONOBLOCS OVERHEATED AND DISTORTED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998012200946	19980122	00946	SW  	1998	1	22	AU971535         	1	19971204	G	3260	2782186057	INDICATOR       			FRCHLD	SA227 	SA227CC     		SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT MLG	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR POSITION LIGHT FAULTY.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
1998012200947	19980122	00947	SO  	1998	1	22	AU971536         	2	19971103	G	8520	6419311075	BOLT            			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	LT NR 6 CYL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							12684470C			(AUS) LH NO6 CYLINDER UPPER THROUGH BOLT BROKEN IN LINE WITH THECYLINDER BASE FLANGE.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA	 
1998012200948	19980122	00948	SW  	1998	1	22	AU971537         	1	19971207	G	3411		STATIC PORT     			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					LT STATIC PORT	CONTAMINATED    	W				K				NONE                    				I			FLT. ATTITUDE INST.       			TO	TAKEOFF        	1			AU	S 										(AUS) LH STATIC PORT BLOCKED BY WATER FOLLOWING HEAVY RAIN.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1998012200949	19980122	00949	SO  	1998	1	22	AU971538         	1	19971113	G	7922	53E22144	VALVE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ENGINE OIL TEMP	FAULTY          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CL	CLIMB          	1			AU	S 							L83056IA			(AUS) ENGINE OIL TEMPERATURE VALVE FAULTY.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998012200950	19980122	00950	NM  	1998	1	22	AU971539         	1	19970918	G	5312		WEB             			BOEING	737   	737377      		NM  										FWD PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB CRACKED IN SEVEN PLACES:- A. AREA UNDER THE RADAR SCANNING MOUNTING BRACKETS CONTAIN	ED FOUR  CRACKS BETWEEN LBL 5.5 AND RBL 5.7 - CRACK LENGTHS 27MM (1.06IN), 13MM (0.5IN) AND TWO CRACKS OF 16MM (0.630IN)	B. TWO CRACKS EITHER SIDE OF BLO JUST ABOVE WL 184 - CRACK LENGTHS 29MM (1.14IN) AND 20MM (0.787IN) C. ONE CRACK IN THE 	WEB ANGLE RADIUS INBOARD OF LBL 5.9 - CRACK  LENGTH 28MM (1.1IN)FOUND DURING ULTRASONIC AND EDDY CURRENT INSPECTION IAW 	ERB73-53-10-39A		2	L	7	2 	4F			RT	A16WE   					 
1998012200951	19980122	00951	NM  	1998	1	22	AU971540         	1	19971013	G	2163	6171661	SENSOR          			BOEING	737   	737377      		NM  										RT AIR COND	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					1274022ANSET					(AUS) RH AIR CONDITIONING PACK RAM AIR TEMPERATURE SENSOR OPEN CIRCUITED CAUSING THE RAM AIR DOOR AND OUTLET LOUVRES TO 	CLOSE AND LIMIT COOLING AIR OVER PRIMARY AND SECONDARY HEAT EXCHANGERS.					2	L	7	2 	4F			RT	A16WE   					 
1998012200952	19980122	00952	EA  	1998	1	22	AU971541         	2	19970721	G	8530	JT162	VALVE SEAT      			BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENG EXHAUST	SEPARATED       	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			2021 		JT162		L231764A			(AUS) EXHAUST VALVE SEAT SEPARATED FROM CYLINDER HEAD.						1	H	7	2 	3O	3	O	RT	A17EU   	E295	5	C	P920	 
1998012200953	19980122	00953	EU  	1998	1	22	AU971542         	1	19971203	G	5315	A38	BEAM            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					GALLEY FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOOR BEAM CRACKED AT EDGE OF PREVIOUS REPAIR IN AREA BENEATH GALLEY AND FIRST CONSOLE. CRACK LENGTH 20MM (0.787IN	). FOUND DURING CORROSION CONTROL PROGRAMME WHICH CONSTITUTES PART OFAD/F28/66.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1998012200954	19980122	00954	EU  	1998	1	22	AU971543         	1	19971128	G	3251		SELECTOR VALVE  			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	NLG STEERING	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NLG STEERING METERING VALVE (FOUR-WAY SELECTION) FAULTY.						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1998012200955	19980122	00955	CE  	1998	1	22	AU971544         	1	19971210	G	5246	65523121	DOOR            			CESSNA	500   	550         	2076604	CE  										FLUID SERVICE	SEPARATED       	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LH ENGINE OIL ACCESS DOOR MISSING. CREW HAD REPORTED NOISE DURING FLIGHT						1	L	7	2 	4F				A22CE   					 
1998012200956	19980122	00956	CE  	1998	1	22	AU971545         	1	19971128	G	2701	1695241879	TORQUE TUBE     			BEECH 	76    	76          	1153005	CE  										PILOT CONTROL	SEPARATED       	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) PILOTS SIDE CONTROL COLUMN TORQUE TUBE BROKE OFF AT RIVETED JOINT DURING FLIGHT.						1	L	7	2 	3O				A29CE   					 
1998012200957	19980122	00957	NM  	1998	1	22	AU971546         	1	19971006	G	5310		STRUCTURE       			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STRUCTURE CONTAINED NUMEROUS CRACKS IN SECTION 41. FOUND DURING INSPECTION IAW AD/B747/85, SECTION 41.						2	L	7	4 	4F				A20WE   					 
1998012200958	19980122	00958	SO  	1998	1	22	AU971547         	2	19971127	G	8520	649896	CRANKSHAFT      			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ENGINE	BROKEN          	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 			323  		551558		551558	744478		(AUS) ENGINE CRANKSHAFT BROKEN.						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA	 
1998012200959	19980122	00959	CE  	1998	1	22	AU971548         	1	19971107	G	5522	96616911112	SKIN            	BEECH       	96610006    	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					RT ELEV OUTB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6357 							(AUS) ELEVATOR SKIN OUTBOARD OF THE RH TRIM TAB FOUND WITH SMALL CRACK. WITH FIRM FORCE APPLIED TO THE TRAILING EDGE, TH	E CRACK OPENED UP TO 127MM (5IN) IN LENGTH.  CLOSER INSPECTION REVEALED SEVERAL MORE CRACKS. CRACKING WAS INITIATED BY C	ORROSION. SUSPECT SKINS ARE MADE OF MAGNESIUM ALLOY.				1	L	7	2 	3O	3	O		3A16    	E5CE				 
1998012200960	19980122	00960	CE  	1998	1	22	AU971549         	1	19971114	G	3213	5541397	SLEEVE          	CESSNA      	6541000003  	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT MLG OLEO	BROKEN          	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					0126					(AUS) LH OLEO WOULD NOT EXTEND AFTER TAKE-OFF PREVENTING LANDING GEAR RETRACTION. LATER THE OLEO EXTENDED ALLOWING GEAR 	RETRACTION. THE OLEO WAS DISASSEMBLED AND SPACER PNO 5541208-1 WAS FOUND JAMMED INSIDE OF A BROKEN BEARING LOWER SLEEVE 	PNO 5541309-7.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1998012200961	19980122	00961	CE  	1998	1	22	AU971550         	1	19970924	G	2110		BEARING         		1131325     	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN AIR COMP	SEIZED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) AIRCONDITIONER BELT SNAPPED. INVESTIGATION FOUND THAT THE AIRCONDITIONING COMPRESSOR WAS TIGHT TO TURN AND BINDING	. THE ASSEMBLY WAS STRIPPED AND ONE THRUST BEARING WAS FOUND WELDED AND SEIZED.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998012600018	19980126	00018		1998	1	26	AU971551         	1	19971211	G	8010	X6112	CONTACTOR       								LYC   	O360  	IO360LYC*   	41514	EA  					ENGINE CRANKING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WHEN THE MASTER SWITCH WAS SELECTED `ON' THE ENGINE TURNED OVER. SUSPECT THE STARTER CONTACTOR WAS ENGAGED.											3	O			1E10				 
1998012200962	19980122	00962		1998	1	22	AU971553         	4	19971210	G	3442	MI591162	TRANSCEIVER     			FOKKER	F27   	F27MK600    	4990706	EU  	RROYCE	DART  	DART5327R   	54509	NE  	ROTOL	R4304	R1934304    	EU  	WEATHER RADAR	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 					2373					(AUS) RADAR TRANSMITTER/RECEIVER FAILED.						2	H	7	2 	4T	4	T		A817    	E297	6	C	P899	 
1998012200963	19980122	00963	NM  	1998	1	22	AU971554         	1	19971202	G	2820	895	VALVE           			BOEING	737   	737476      		NM  										FUEL DIST	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			9779 		895					(AUS) FUEL CROSSFEED VALVE FAULTY.						2	L	7	2 	4F			RT	A16WE   					 
1998012200964	19980122	00964	NM  	1998	1	22	AU971555         	1	19971203	G	2820	889	VALVE           			BOEING	737   	737476      		NM  										FUEL DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			5814 		889					(AUS) FUEL CROSSFEED VALVE FAULTY.						2	L	7	2 	4F			RT	A16WE   					 
1998012200965	19980122	00965	SW  	1998	1	22	AU971556         	1	19971031	G	2432	G172942	CAP             	GILLBATT    	G88         	AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	BATTERY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					G01729420					(AUS) BATTERY VENT CAP VULCANISED CLOSED. GAS BUILDUP CAUSED ACID TO VENT FROM AN ADJACENT CELL.						1	L	7	1 	3R	3	R		A9SW    	5E2	5	C	P257	 
1998012200966	19980122	00966	EU  	1998	1	22	AU971557         	2	19970927	G	7421		SPARK PLUG      								ROTAX 	912   	ROTAX912    	55555	EU  					ENG IGN	FOULED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) ENGINE SPARK PLUG FOULED. THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY.											3	I			EXPE3I				 
1998012200967	19980122	00967	SW  	1998	1	22	AU971559         	1	19971216	G	2460		CIRCUIT BREAKER 			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					DC POWER DIST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CIRCUIT BREAKERS FAULTY.						1	L	7	1 	3R	3	R		A9SW    	5E2				 
1998012200968	19980122	00968	EU  	1998	1	22	AU971560         	1	19970605	G	5753	F5B16324B3	BRACKET         			AMD   	FALC50	FALCON900   	2700160	EU  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DROP SHAPED FOREFLAP BRACKETS CORRODED. THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ON	LY.					2	L	7	3 	4F			RT	A46EU   					 
1998012200969	19980122	00969	EU  	1998	1	22	AU971561         	1	19971107	G	2751	F5B1142121A1	SPRING          		F50B11400212	AMD   	FALC50	FALCON900   	2700160	EU  										TE FLAP POSITION	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP MICROSWITCH BUTTERFLY ARM SPRINGS LOST TENSION AND SLIPPED OFF THE ARM. THIS DEFECT WAS RECEIVE	D FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY.					2	L	7	3 	4F			RT	A46EU   					 
1998012200970	19980122	00970	CE  	1998	1	22	AU971562         	1	19971217	G	2910		PIPE            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	HYD MAIN SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) HYDRAULIC PIPE LEAKING IN AREA OF HYDRAULIC PACK.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
1998012200971	19980122	00971	CE  	1998	1	22	AU971563         	1	19971203	G	3520	1138495	HOSE            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					PASSENGER OXYGEN	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) OXYGEN SYSTEM ON/OFF CONTROL CABLE FAILED. OXYGEN SYSTEM REMAINED ON FOR AN EXTENDED TIME CAUSING THE SUPPLY HOSE 	TO THE CASUALTY OXYGEN MASK TO RUPTURE AND ALLOWING THE OXYGEN SYSTEM TO DISCHARGE TO 0PSI.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998012600019	19980126	00019	EA  	1998	1	26	AU971564         	2	19971216	G	7497		WIRE            								LYC   	O360  	IO360LYC*   	41514	EA  					IGNITION SWITCH	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRE FROM IGNITION SWITCH TO START SOLENOID CHAFING ON FLAP CIRCUIT BREAKER TERMINAL SCREW. MAGNETO P LEAD SHIELD 	WIRE ALSO CHAFED AND SEVERED. BATTERY WIRE TO IGNITION SWITCH CHAFED WITH BARE WIRE VISIBLE. SEE MDR 97/1551 FOR ADDITIO	NAL INFORMATION.									3	O			1E10				 
1998012200972	19980122	00972	SO  	1998	1	22	AU971565         	1	19971215	G	2710	246317	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  										LT AIL CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) DURING TAXI AFTER LANDING, THE AILERON CONTROLS ROLLED LEFT AND DIDN'T ROLL BACK WITH RUDDER INPUT. AILERONS STILL	 HAD FULL AND FREE MOVEMENT BUT WITH A BIAS OF SLIGHT SPRING PRESSURE TO THE LEFT CONTROL DOWN. INVESTIGATION FOUND THE 	LH AILERON/RUDDER INTER-CONNECT CABLE HAD BROKEN.				1	L	7	2 	3O			 	A20SO   					 
1998012200973	19980122	00973	NM  	1998	1	22	AU971566         	1	19971027	G	3232	21ANSETTSN	PISTON SEAT     			BOEING	767   	767277      		NM  										NLG VALVE	FRACTURED       	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			39237		00021ANSETTS					(AUS) AFTER TAKE-OFF, THE GEAR DOOR DISAGREE MESSAGE WARNING DISPLAYED AND EXCESSIVE NOSE GEAR VIBRATIONS WERE FELT DURI	NG GEAR RETRACTION.  GROUND INVESTIGATION FOUND THAT THE NLG PRIORITY VALVE'S PISTON SEAT ASSEMBLY PNO 01715201B2-1 HAD 	FRACTURED PREVENTING BALL PNO MS134359 FROM SEATING.				2	L	7	2 	4F			RT	A1NM    					 
1998012200974	19980122	00974	NE  	1998	1	22	AU971567         	2	19971129	G	7210	CPGB147	COMBINING GRBOX 	PWA         		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1 ENGINE	MAKING METAL    	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 					CPGB1047		667			(AUS) NO1 ENGINE CHIP ILLUMINATION DURING CLIMB. INVESTIGATION FOUND METAL FROM THE COMBINING GEARBOX TO BE OUTSIDE OF M	ANUFACTURERS LIMITS.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1998012200975	19980122	00975	GL  	1998	1	22	AU971568         	3	19971217	G	6114	A2433	BOLT            	HARTZL      		CHILD 	S2    	S2APITTS    	0110201	NM  	LYC   	O360  	AEIO360B4A  	41514	EA  	HARTZL	HCC2Y	HCC2YK4     	GL  	PROP HUB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					DN1577			DN1577		(AUS) WHEN THE PROPELLER WAS REMOVED DUE TO EXCESSIVE GREASE LEAKAGE AT THE BLADE BUTTS, THE THREADED END OF ONE HUB CLA	MPING BOLT WAS FOUND TO BE MISSING.					1	Q	7	1 	3O	3	O		A8SO    	1E10	5	C	P920	 
1998012200976	19980122	00976	EA  	1998	1	22	AU971569         	2	19971221	G	8530	7386P	PUSHROD         	LYC         	LW16703     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 2 CYL EXH	LOOSE           	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 					A29945		L164215			(AUS) PILOT REPORTED REDUCTION IN RPM AND ROUGH RUNNING IN FLIGHT.INVESTIGATION FOUND THE NO2 CYLINDER EXHAUST PUSHROD E	ND FITTINGS WERE LOOSE, WITH ONE END OF THE PUSHROD SPLAYED AND CRACKED.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
1998012200977	19980122	00977	EU  	1998	1	22	AU971570         	1	19971218	G	7120		BRACKET         			PARTEN	P68   	P68B        		EU  										ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT TO WING ATTACHMENT BRACKETS (3OFF) WERE FOUND CRACKED:1. LH LOWER INBOARD PNO 68-1.2027,2. RH UPPER I	NBOARD PNO 68-1.2025-1 AND 3. RH UPPER OUTBOARD PNO 68-1.2025-3. FOUND IAW AD/P68/28A3, SECTION 3.					1	H	7	2 	3O				A31EU   					 
1998012600020	19980126	00020	GL  	1998	1	26	AU971571         	3	19971210	G	6114	22117	HUB             			PIPER 	PA36  	PA36300     	7103612	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROP HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1788248A	95		(AUS) PROPELLER HUB WAS PREVIOUSLY INSPECTED AT THE 50HR INTERVAL IAW HARTZELL SB164C AND FOUND SATISFACTORY. WHEN INSPE	CTED AT THE 100 HOURLY, A PARTICULARLY LARGE CRACK WAS FOUND IN THE REAR HALF OF THE RADIUS AT THE BLADE ROOT.					1	L	7	1 	3O	3	O		A10SO   	1E4	5	C	P920	 
1998012200978	19980122	00978	CE  	1998	1	22	AU971572         	1	19971216	G	3230		LANDING GEAR    			BEECH 	200   	200BEECH    	1152920	CE  										GEAR RETRACT SYS	MALFUNCTION     	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) AFTER TAKE-OFF THE LG WAS SELECTED UP AND VIBRATION AND NOISE WAS HEARD DURING RETRACTION WITH EXTENDED WINDING TI	ME - RED HANDLE UNSAFE LIGHT REMAINED ON WHEN GEAR APPEARED TO BE UP. GROUND INVESTIGATION COULD NOT REPRODUCE THE PROBL	EM. GEAR MICROSWITCHES WERE CHECKED FOR ADJUSTMENT/WEAR, AND THE NLG DRIVE CHAIN AND SPROCKETS WERE ALSO INSPECTED.				1	L	7	2 	4T				A24CE   					 
1998012200979	19980122	00979	CE  	1998	1	22	AU971573         	1	19971215	G	7333	849E	TRANSMITTER     	GULL        	903800097   	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL FLOW SENSOR	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					8490E					(AUS) DURING FLIGHT THE LT ENGINE FUEL FLOW GAUGE REDUCED INDICATION FROM 550 PPH TO 100 PPH AND DIDN'T ALTER WITH POWER	 CHANGES.  GROUND INVESTIGATION FOUND THE LT FUEL TRANSMITTER WAS FAULTY.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998012200980	19980122	00980	SO  	1998	1	22	AU971574         	1	19971203	G	7120	12A1997	MOUNT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L256661A	DJ834A		(AUS) LH LOWER I/B ENGINE MOUNT CRACKED AT THE TURBOCHARGER MOUNT HOLE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998012200981	19980122	00981	SO  	1998	1	22	AU971575         	1	19971203	G	7120	7679	MOUNT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE MOUNT SEC	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L168668A	DJ9482A		(AUS) RH LOWER O/B ENGINE MOUNT CRACKED AT THE TURBOCHARGER MOUNT HOLE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998012200982	19980122	00982	SW  	1998	1	22	AU971576         	1	19971223	G	2730	MS211518	ROD END         			SWRNGN	SA227 	SA227AC     	8780603	SW  										ELEVATOR CONTROL	CREASED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL ROD END BEARING RETAINER/DUST SEAL CREASED ON BOTH SIDES OF ROD END DUST COVERS. FOUND DURING AD/	SWSA226-82.					2	L	7	2 	4T			RT	A8SW    					 
1998012200983	19980122	00983		1998	1	22	AU971577         	1	19971223	G	7312	WA281	HEATER          	STWARNER    	10718D      						PWA   	PWA120	PW125B      		NE  					LT FUEL HEAT	FAULTY          	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					WA281		12451			(AUS) DURING CRUISE THE LH FUEL HEATER HIGH TEMPERATURE LIGHT ILLUMINATED. FAULT WAS TRACED TO THE FUEL HEATER ELEMENT.											4	T			E20NE				 
1998012200984	19980122	00984	CE  	1998	1	22	AU971578         	1	19971218	G	7714	A8266	TACHOMETER      		503800343   	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE RPM IND	DEFECTIVE       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					A8266					(AUS) DURING AN INSPECTION OF A TURBINE TACHOMETER PRIOR TO TESTING,THE FRONT LENS WAS FOUND TO SHOW EVIDENCE OF MOISTUR	E CONTAMINATION (FOGGING). FURTHER INVESTIGATION FOUND THAT THE CASE HAD BEEN SEALED WITH RTV TYPE SEALANT AND NOT HERME	TICALLY SOLDER SEALED. ON TESTING THE INSTRUMENT WAS FOUND TO HAVE EXCESSIVE FRICTION AND SCALE ERROR. FOUND IAW AD/INST	/9. INCORRECT PROCEDURE/PERSONNEL ERROR.			1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998012200985	19980122	00985	CE  	1998	1	22	AU971579         	1	19971117	G	2810	7161246	VALVE           			CESSNA	150   	150M        	2071830	CE  										FUEL VENT	FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AU	S 										(AUS) ENGINE STOPPED DURING CRUISE.  INVESTIGATION FOUND A RESTRICTION (AN INSECT) IN THE LH FUEL TANK VENT TUBE.  ALSO,	 THE VENT TUBE VALVE WAS 'STICKY'.					1	H	7	1 	3O				3A19    					 
1998012200986	19980122	00986	EU  	1998	1	22	AU971580         	1	19971222	G	5711		SPAR            			BNORM 	BN2   	BN2A26      	1520226	EU  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR HAS CRACKS RANGING FROM 12.7MM (0.5IN) TO OVER 25.4MM (1IN). FOUND IAW PBN SB 237.						1	H	7	2 	3O				A17EU   					 
1998012200987	19980122	00987	SO  	1998	1	22	AU971581         	2	19971222	G	7414	M173	COIL            	SLICK       	667         	CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300A      	17022	SO  					ENG RT MAGNETO	CRACKED         	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			AU	S 			25   		691228					(AUS) AFTER APPROXIMATELY 45 MINUTES FLIGHT TIME AND DURING POSTLANDING CHECKS, THE RH MAGNETO WAS SHOWING A 'DEAD CUT'.	 THEMAGNETO WAS SUBSEQUENTLY REMOVED AND DISMANTLED, AND THE COIL WAS FOUND TO BE SPLIT OPEN AND LEAKING.					1	H	7	1 	3O	3	O		3A17    	E298				 
1998012200988	19980122	00988	NE  	1998	1	22	AU971582         	2	19971230	G	7200	PCE1434	ENGINE          	PWA         		AYRES 	S2    	S2RT15NORMAL	0970105	SO  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER SECT	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					PCE14034		PCE1434	BU3965		(AUS) ENGINE SUFFERED COMPLETE FAILURE DURING CRUISE - CAUSE UNKNOWN AT THIS STAGE.						1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA	 
1998021100498	19980211	00498	CE  	1998	2	11	AU971583         	1	19971215	G	2810		FUEL SYSTEM     			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	LT TANK	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH FUEL TANK AND FUEL SYSTEM CONTAMINATED WITH SUGAR.						1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
1998021800003	19980218	00003	EU  	1998	2	18	AU971584         	1	19970919	G	5610	NF20216246ISS4	WINDSHIELD      			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					1ST OFFICER	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					L227216ANSET					(AUS) FIRST OFFICERS WINDSCREEN CRACKED IN SEVERAL PLACES. SUSPECT CRACK ORIGINATED FROM A LOCALISED HOT SPOT ALONG THE 	LOWER EDGE OF THE WINDSHIELD.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998021800004	19980218	00004	EU  	1998	2	18	AU971585         	1	19971014	G	3213	40429	MLG             			GROB  	G115  	G115C       	1660303	EU  						SNSNCH	72C	72CK        	EA  	MAIN LANDING GEA	DISTORTED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 			250  							(AUS) RH MAIN LANDING GEAR LEG BENT AND LOWER FRONT ATTACHMENT BUSH LOOSE. SPIN FIN FAIRING REAR SECTION DAMAGED. CAUSED	 BY HEAVY LANDING.					1	L	7	1 	3O			NT	A57EU   		5	N	P9045	 
1998021100499	19980211	00499	NE  	1998	2	11	AU971586         	2	19971212	G	7200		ENGINE          								LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 							LF05852A			(AUS) NO3 ENGINE CHIP DETECTORS CONTAMINATED. LOW PRESSURE SPOOL DIFFICULT TO ROTATE BY HAND.											4	F			E6NE				 
1998021100500	19980211	00500	SO  	1998	2	11	AU971587         	1	19970729	G	5311	7746709	FRAME           			PIPER 	PA38  	PA38112     	7103812	SO  						SNSNCH	74D	74DM        	EA  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE REAR SPAR FRAME CRACKED IN BOTH LOWER CORNERS. FOUND DURING INSPECTION IAW AD/PA38/25.						1	L	7	1 	3O				A18SO   		5	N	P88614	 
1998021100501	19980211	00501	SO  	1998	2	11	AU971588         	1	19971218	G	3234	1203859400	CONTROL BOX     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					GEAR SELECTOR	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					120186					(AUS) LANDING GEAR CONTROL BOX FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1998021100502	19980211	00502	EU  	1998	2	11	AU971589         	1	19971120	G	7500	1555M14604	DUCT            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					ENGINE BLEED AIR	CRACKED         	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					DUCTASS9067M		528139			(AUS) NO2 ENGINE 14TH STAGE AIR DUCT CRACKED FOR 66% OF CIRCUMFERENCE.NUMEROUS TIE ROD ENDS SNAPPED OFF. HP RECOUP TUBE 	SEVERELY CHAFED.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998021100503	19980211	00503		1998	2	11	AU971590         	4	19971215	G	2562	MN1300	BATTERY         		E01         	CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	EMERG LOCATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					009618					(AUS) ELT BATTERIES CORRODED AND LEAKING.						1	H	7	1 	3O	3	O		A16CE   	E5CE	5	C	P47GL	 
1998021100504	19980211	00504	SO  	1998	2	11	AU971591         	1	19971230	G	5347	6255704	SEAT TRACK      			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RT OUTB SEAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH OUTBOARD SEAT TRACK CONTAINED EXFOLIATION CORROSION.						1	L	7	1 	3O	3	O		2A13    	E295	5	C	P920	 
1998021100505	19980211	00505	EU  	1998	2	11	AU971592         	1	19971222	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					APU FIRE BOTTLE	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CN3915ANSETT					(AUS) APU FIRE EXTINGUISHER BOTTLE EMPTY. NO EVIDENCE OF DISCHARGE. FOUND DURING REMOVAL FOR REWEIGH.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998021100506	19980211	00506	EU  	1998	2	11	AU971593         	1	19971129	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENG  BOTTLE	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1729ANSETT05					(AUS) NO3 ENGINE INBOARD FIRE EXTINGUISHER EMPTY. FOUND DURING REWEIGH.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998021100507	19980211	00507	NE  	1998	2	11	AU971594         	2	19971218	G	7250		BLADE           								LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENG TURB	FAILED          	W				O				OTHER                   				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		CL	CLIMB          	1			AU	S 							LF05502A			(AUS) NO4 ENGINE FAILED. SUSPECT 1ST STAGE HP TURBINE BLADE FAILURE.											4	F			E6NE				 
1998021100508	19980211	00508	NM  	1998	2	11	AU971595         	1	19970307	G	2910	33582	SPRING          		V243602     	BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					HYD SYS	FRACTURED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					2041561ANSET					(AUS) HYDRAULIC SYSTEM RH FUSE PNO V2-4360-2 SPRING PNO 33582 FAILED. SPLIT RING PNO 33581 DAMAGED AND RESET PISTON PNO 	33589 JAMMED INSIDE ADAPTER PNO 33590.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1998021100509	19980211	00509	EU  	1998	2	11	AU971596         	1	19970918	G	5610	NP1701022	WINDSHIELD      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					1ST OFFICERS B	DELAMINATED     	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					94075H3810AN					(AUS) FIRST OFFICERS `B' WINDSCREEN DELAMINATED AND A SECTION OF THE OUTER PANE SEPARATED. SUSPECT CAUSED BY MOISTURE IN	GRESS INTO CONDUCTIVE LAYER CAUSING ARCING.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998021100510	19980211	00510	EU  	1998	2	11	AU971597         	1	19970918	G	5610	NP1701012	WINDSHIELD      	PPG         	NP1701012   	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					1ST OFFICERS A	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					94187H8936AN					(AUS) FIRST OFFICERS `A' WINDSCREEN ARCING FOLLOWED SHORTLY BY CRACKING OF THE OUTER PANE. SUSPECT CAUSED BY MOISTURE IN	GRESS.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998021100511	19980211	00511	EU  	1998	2	11	AU971598         	1	19971223	G	2612		CONNECTOR       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENG DETECT	LOOSE           	W				K				NONE                    				F	N		FLT CONT AFFECTED         	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) NO3 ENGINE FALSE FIRE WARNING DUE TO LOOSE AND DIRTY ELECTRICAL CONNECTOR PLUG. FIRE BOTTLE ACTIVATED.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998021100512	19980211	00512	EU  	1998	2	11	AU971599         	1	19971224	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENG INB	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6151 		CM9503ANSETT					(AUS) NO2 ENGINE INBOARD FIRE EXTINGUISHER BOTTLE EMPTY. FOUND DURING REMOVAL FOR REWEIGH.						2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998021100513	19980211	00513	EU  	1998	2	11	AU971600         	1	19971227	G	2621	57333012	FIRE BOTTLE     	KIDDE       	57333012    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENG OUTB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5697 		CM76545ANSET					(AUS) NO1 ENGINE OUTBOARD FIRE EXTINGUISHER BOTTLE APPROXIMATELY 0.7KG UNDERWEIGHT DURING INSPECTION IAW BA6-26-20-15. C	ORROSION WAS ALSO FOUND ON APPROXIMATELY 20% OF THE NECK AREA.					2	H	7	4 	4F	4	F		A49EU   	E6NE				 
1998021800005	19980218	00005	NE  	1998	2	18	AU971601         	2	19971122	G	7250		BLADE           			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					NR 1 ENG 1ST STG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P715074			(AUS) NO1 ENGINE FIRST STAGE TURBINE BLADE FAILED. APPROXIMATELY 50%OF THE BLADE WAS MISSING. SUSPECT STAGE ONE BLADES S	UBJECTED TO HIGHER THAN NORMAL TEMPERATURES.					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
1998021100514	19980211	00514	NM  	1998	2	11	AU971602         	1	19971025	G	3244	0397812	TIRE            		314392      	BOEING	737   	73733A      	1384673	NM  										RT OUTB TIRE	SEPARATED       	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					6442ANSETTSN					(AUS) RH OUTBOARD TYRE TREAD SEPARATED DUE TO FATIGUE IN THE SHOULDER SECTION. TYRE REMAINED INFLATED. DAMAGE CAUSED TO 	THE AIRFRAME.					2	L	7	2 	4F			RT	A16WE   					 
1998021100515	19980211	00515	NM  	1998	2	11	AU971603         	1	19971001	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FWD PRESSURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN THE FOLLOWING LOCATIONS:-1. THREE CRACKS IN THE BULKHEAD WEB BETWEEN LBL 5.7 	AND RBL 5.7  LOCATED UNDER THE RADAR SCANNER MOUNTING BRACKETS - CRACK LENGTHS 24MM (0.944IN) - 14MM (0.551IN) - 13MM (0	.511IN) 2. CRACK IN VERTICAL BULKHEAD CHORD AT LBL 5.7 - CRACK LENGTH 8MM  (0.314IN)FOUND DURING ULTRASONIC AND EDDY CUR	RENT INSPECTION IAW ERB73-53-10-39C ANDSB B737-53-1173.			2	L	7	2 	4F			RT	A16WE   					 
1998021100516	19980211	00516	NM  	1998	2	11	AU971604         	1	19971020	G	7830	S315N3702	LOCK            			BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					LT INB TR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					N05236ANSETT					(AUS) LH INBOARD THRUST REVERSER SYNCH LOCK FAULTY. WORKSHOP TESTING COULD FIND NO MALFUNCTION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
1998021100517	19980211	00517	EU  	1998	2	11	AU971605         	2	19971205	G	7210	GESNMABN9440	BEARING         	GE          	INLETGEARBOX						CFMINT	CFM56 	CFM563C     	13802	EU  					GRBOX BRG NR 3	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					61X25767		856367			(AUS) ENGINE INLET GEARBOX NO3 THRUST BEARING FAILED. A FRAGMENT MISSING FROM THE INNER RACE WAS FOUND LODGED IN THE FAN	 FRAME.										4	F			E21EU				 
1998021100518	19980211	00518	NM  	1998	2	11	AU971606         	1	19971216	G	5620	85323497101	CLIP            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					PASS WINDOW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WINDOW TO WINDOW FRAME ATTACHMENT CLIPS CRACKED IN RADIUS OF FOLD LINE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998021100519	19980211	00519	CE  	1998	2	11	AU971607         	1	19971216	G	5320	52130409	WEB             	CESSNA      	C404        	CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	LT NOSE WELL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4040820					(AUS) LH NOSE WHEEL WELL WEB CRACKED IN AREA OF NLG ATTACHMENT FORWARDTWO BOLT HOLES.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998021100520	19980211	00520	CE  	1998	2	11	AU971608         	1	19971216	G	5320	521304010	WEB             	CESSNA      	C404        	CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	RT NOSE WELL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4040820					(AUS) RH NOSE WHEEL WELL WEB CRACKED IN AREA OF NLG ATTACHMENT FORWARDTWO BOLT HOLES.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998021100521	19980211	00521	CE  	1998	2	11	AU971609         	1	19971215	G	7540	903800021	SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	BLEED AIR IND	MIS WIRED       	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) LH BLEED AIR WARNING SWITCH PRESSURE LINE TRANSPOSED WITH RH SWITCH. RH BLEED AIR SENSE LINE CONTAINED A SMALL HOL	E WHICH HAD ACTIVATED THE (INCORRECT) WARNING LIGHT. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998021100522	19980211	00522	EU  	1998	2	11	AU971610         	2	19971111	G	7230		BEARING         								CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1 ENG NR 4	FAILED          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							725274			(AUS) NO1 ENGINE NO4 BEARING FAILED.											4	F			E21EU				 
1998021100523	19980211	00523	NM  	1998	2	11	AU971611         	1	19971222	G	2560	B732560133	CABLE           			BOEING	737   	737377      	       	NM  										AFT ESCAPE SLIDE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT ENTRY DOOR ESCAPE SLIDE COVER RELEASE CABLE BROKEN IN LOOP AT THE GIRT BAT ATTACHMENT END.						2	L	7	2 	4F			RT	A16WE   					 
1998021100524	19980211	00524	NM  	1998	2	11	AU971612         	1	19971215	G	5320		SKIN            			BOEING	737   	737377      		NM  										RT C-D WINDOW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH C-D FLIGHT COMPARTMENT WINDOW POST UPPER GUSSET SKIN CRACKED.CRACK LENGTH 3.175MM (0.125IN). FOUND DURING EDDY 	CURRENT INSPECTION.					2	L	7	2 	4F			RT	A16WE   					 
1998021100525	19980211	00525	NM  	1998	2	11	AU971613         	1	19971229	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 CRACKED IN TEN SEPARATE POSITIONS.						2	L	7	2 	4F			RT	A16WE   					 
1998021100526	19980211	00526	CE  	1998	2	11	AU971614         	1	19971218	G	7714	AN55443	TACH GENERATOR  			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE N1	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					AF5005874					(AUS) RH ENGINE N1 TACH GENERATOR DRIVE SHAFT SHEARED						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998021100527	19980211	00527	NE  	1998	2	11	AU971615         	2	19970801	G	7311	1601422	FUEL HEATER     								GE    	CF6   	CF680A      	30025	NE  					ENGINE FUEL-OIL	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					AEY00350ANSS		580347			(AUS) LH ENGINE FUEL/OIL HEAT EXCHANGER CRACKED AND LEAKING AT FORWARD END HEADER. CRACK LENGTH 25.4MM (1IN).											4	F			E13NE				 
1998021100528	19980211	00528	CE  	1998	2	11	AU971616         	1	19971112	G	5540	513300032	BRACKET         		513300011   	CESSNA	402   	402A        	207590M	CE  						MCAULY	3AF32C	3AF32C87    	GL  	RUDDER HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER RUDDER HINGE ATTACHMENT BRACKET CRACKED. LOWER RUDDER RIB BADLY CORRODED.						1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998021100529	19980211	00529	NE  	1998	2	11	AU971617         	2	19970702	G	7230		ENGINE          								GE    	CF6   	CF680A      	30025	NE  					RT ENGINE	DEFECTIVE       	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							580233			(AUS) RT ENGINE VIBRATING.  SUSPECT HIGH PRESSURE COMPRESSOR ROTOR SLIGHTLY OUT OF BALANCE.  ENGINE HAS A HISTORY OF VIB	RATIONS.										4	F			E13NE				 
1998021100530	19980211	00530	NM  	1998	2	11	AU971619         	1	19971216	G	5312	651630084	BULKHEAD        			BOEING	737   	737476      		NM  										FWD PRESSURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FORWARD PRESSURE BULKHEAD CRACKED IN TWO POSITIONS.						2	L	7	2 	4F			RT	A16WE   					 
1998021100531	19980211	00531	SO  	1998	2	11	AU971620         	1	19971226	G	3230	9555123	MOUNT           			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG RETRACT	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR MOUNT TUBE TO CENTERING CHANNEL WELD FAILED.						1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
1998021100532	19980211	00532	NM  	1998	2	11	AU971621         	1	19971202	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 CRACKED IN EIGHT POSITIONS.						2	L	7	2 	4F			RT	A16WE   					 
1998021100533	19980211	00533	EU  	1998	2	11	AU971622         	1	19971230	G	2810	F1701468401	PANEL           			FOKKER	F27   	F27MK50     		EU  										FUEL STORAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REFUELLING POINT PANEL CRACKED IN NUMEROUS PLACES.						2	H	7	2 	4T			RT	A817    					 
1998021100534	19980211	00534	EU  	1998	2	11	AU971623         	1	19971118	G	5312		BULKHEAD        			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FWD FUSELAGE	CRACKED         	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			AU	S 										(AUS) FRONT BULKHEAD CRACKED THROUGH TWO BOLT HOLES. FOUND FOLLOWING REMOVAL OF THE UPPER NOSE LEG MOUNT PLATE DUE TO TO	WING DAMAGE. DAMAGE CAUSED BY INCORRECT GROUND HANDLING.					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920	 
1998021100535	19980211	00535	SO  	1998	2	11	AU971624         	1	19971223	G	5751	8639802	RIB             	PIPER       	LHAILERON   	PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AILERON NOSE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AILERON HINGE NOSE RIB CRACKED. CRACK LENGTH 40MM (1.57IN).ADDITIONAL CRACKING ALSO EVIDENT.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1998021100536	19980211	00536	NM  	1998	2	11	AU971625         	1	19971216	G	5620	85323497101	CLIP            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					PASS WINDOW	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WINDOW CLIPS CRACKED AT RADIUS ALONG FOLD LINE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998021100537	19980211	00537	NE  	1998	2	11	AU971626         	2	19971103	G	7210	MS949034	BOLT            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LT ENG RED GRB	FAILED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE REDUCTION GEARBOX FIRST STAGE PLANET GEAR CARRIER BOLT FAILED. INVESTIGATION FOUND THAT THE BOLT HEAD HA	D SEPARATED AND ENTERED THE FIRST STAGE GEAR TRAIN. EXAMINATION OF THE CARRIER BOLTS REVEALED FOUR BOLTS FRACTURED IN TH	E THREADED AREA AND ONE BOLT FRACTURED UNDER THE BOLT HEAD. SUSPECT BOLTS OVERTORQUED DURING ASSEMBLY. PERSONNEL/MAINTEN	ANCE ERROR. METAL CONTAMINATION OF ENGINE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
1998021100538	19980211	00538	CE  	1998	2	11	AU971627         	1	19971213	G	3231	S11044	ROD END         	CESSNA      	310Q        	CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	2AF34C	D2AF34C71   	GL  	RT MLG DOOR	SEIZED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					NA					(AUS) RH NOSE LANDING GEAR DOOR RETRACTION RODEND BROKEN. DOOR CAUGHT THE NOSE GEAR DURING RETRACTION AND JAMMED THE NLG	 HALFWAY UP.RODEND BEARING PARTIALLY SEIZED DUE TO LACK OF LUBRICATION.					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA	 
1998021100539	19980211	00539	SO  	1998	2	11	AU971628         	2	19971230	G	8530	570008	CYLINDER        	CONT        	IO520L      	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	ENG NR 1 CYL	CRACKED         	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1382 		570008		570008			(AUS) NO1 CYLINDER HEAD CRACKED.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9	 
1998021800006	19980218	00006	NM  	1998	2	18	AU971629         	1	19970517	G	2432	63412	CELL            	SAFT        	401767      	BOEING	747   	747*        		NM  										BATTERY	FAILED          	W				K				NONE                    				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			AU	S 					93165					(AUS) AIRCRAFT MAIN BATTERY CELL FAILED AND BATTERY OVERHEATED. BATTERY CHARGER PNO 2-792-02 DAMAGED. AIRCRAFT IS FOREIG	N REGISTEREDN124KK.					2	L	7	4 	4F			RT	A20WE   					 
1998021100540	19980211	00540	SW  	1998	2	11	AU971630         	1	19971216	G	5512	528	SKIN            	MTSBSI      	MU2B30      	MTSBSI	MU2   	MU2B30      	5780410	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					528					(AUS) HORIZONTAL STABILISER LEADING EDGE SKINS CRACKED. CRACKS ORIGINATE FROM RIB RIVETS FOR THE OUTBOARD ELEVATOR HINGE	. CRACK LENGTH 50.8MM (2IN). FOUND DURING INSPECTION IAW AD/MU2/35.					1	H	7	2 	3T				A2PC    		6	C	P15EA	 
1998021100541	19980211	00541	NM  	1998	2	11	AU971631         	1	19971230	G	2750		PUSHROD         			BOEING	747   	747312      	1384932	NM  										TE FLAP CONTROL	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT INBOARD TRAILING EDGE NR 5 AFT FLAP PUSHROD INCORRECT PART.  PUSHROD WAS ALSO 20.637MM (0.8125 INCH) TOO SHORT.	  GENEVA CAMS NR 5 AND NR 6 ALSO TRANSPOSED.					2	L	7	4 	4F			RT	A20WE   					 
1998021100542	19980211	00542	WP  	1998	2	11	AU971632         	2	19971229	G	8520	447	CRANKSHAFT      			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					447		UK			(AUS) ENGINE CRANKSHAFT CRACKED. FOUND DURING ULTRASONIC INSPECTION IAW AD/DHE/18A4.						1	Q	7	1 	3I	3	I		A8EU    	A8EU				 
1998021100543	19980211	00543	EU  	1998	2	11	AU971633         	1	19971213	G	3242	AHO809723	RIVET           	DUNLOP      	BRAKEUNIT   	BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	BRAKE	SHEARED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					FD133					(AUS) LH MAIN LANDING GEAR BRAKE PAD RIVET SHEARED. BRAKE PADS WEDGED BETWEEN THE STATOR AND ROTOR ASSEMBLIES.. THRUST P	LATE ASSEMBLY PNO AHO 84638 ALSO DAMAGED AND DISTORTED					2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
1998021100826	19980211	00826	CE  	1998	2	11	AU971634         	1	19971220	G	5220	50111302	WINDOW          			CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	EMERGENCY EXIT	FAILED          	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) EMERGENCY EXIT WINDOW FAILED AT THE TOP. AS THE WINDOW SWUNG DOWN IT TORE THROUGH THE TWO ATTACHMENT POINTS AND CA	USED MINOR DAMAGE TO THE WING SKIN.					1	L	7	2 	3O				A7CE    		5	C	P22EA	 
1998021100827	19980211	00827	NE  	1998	2	11	AU971635         	2	19971022	G	7261	3527	OIL SYSTEM      	TMECA       	ARRIEL1S    	SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE OIL	FLUCTUATES      	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 					3527		3527			(AUS) LH ENGINE VENTED OIL OVERBOARD. OIL PRESSURE FLUCTUATING.						1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1998021100828	19980211	00828	CE  	1998	2	11	AU971636         	1	19971231	G	7810	991030132	EXHAUST PIPE    			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE COLLECTOR	CRACKED         	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							238901	696105		(AUS) RH ENGINE INBOARD EXHAUST HEADER PIPE CRACKED UNDER CLAMP ATFLANGE JOINT.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1998021100829	19980211	00829	SO  	1998	2	11	AU971637         	2	19970922	G	8500		ENGINE          			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT ENGINE	MALFUNCTION     	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							278486R			(AUS) RH ENGINE RUNNING ROUGH IN CRUISE. GROUND RUN COULD FIND NO FAULT.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1998021100830	19980211	00830	SO  	1998	2	11	AU971638         	2	19971212	G	8520	276439R	CRANKCASE       	CONT        	GTSIO520M   	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 					276439R		276439R			(AUS) CRANKCASE CRACKED. FOUND DURING INSPECTION IAW TCM CSB 97-9.						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL	 
1998021800008	19980218	00008	EU  	1998	2	18	AU971639         	1	19971231	G	5730		SKIN            			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER WING SURFACE SKIN CRACKED IN THREE PLACES. CRACKS EMANATING FROM THE CENTRE FUEL TANK OVERWING REFUEL CAP CU	TOUT IN THE WINGPLANK SKIN.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
1998021100831	19980211	00831	NM  	1998	2	11	AU971640         	1	19971226	G	2760	BACC2A3A03051FG	CONTROL CABLE   			BOEING	737   	737377      	       	NM  										SPOILER WS 230	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO6 FLIGHT SPOILER CABLE WSB2-4 FAILED ADJACENT TO THE PULLEYS AT RH WING STN 230 AT WBL157.0. EVIDENCE OF ADVANCE	D INTERNALCORROSION.					2	L	7	2 	4F			RT	A16WE   					 
1998021100832	19980211	00832	NM  	1998	2	11	AU971641         	1	19971201	G	2761	654494713	HOUSING         	BOEING      	ACTUATOR    	BOEING	737   	73733A      	1384673	NM  										LT INB SPOILER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			23588		5765ANSETTSN					(AUS) LH INBOARD GROUND SPOILER OUTBOARD ACTUATOR HOUSING PIVOT BEARING LUG BROKEN. SUSPECT CAUSED BY FATIGUE CRACKING O	RIGINATING FROM MINOR CORROSION PITTING IN THE CENTRE OF THE BEARING BORE.					2	L	7	2 	4F			RT	A16WE   					 
1998021100833	19980211	00833	NM  	1998	2	11	AU971642         	1	19971018	G	2520	737M254570114	SEAT            			BOEING	737   	737476      		NM  										CABIN	SEPARATED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			3082 		317143					(AUS) PASSENGER SEAT OUTBOARD FORWARD SEAT LEG TRACK FITTING SEPARATEDFROM FLOOR TRACK. SEAT WAS LOCATED AT ROW 21 A B C	.					2	L	7	2 	4F			RT	A16WE   					 
1998021100834	19980211	00834	EU  	1998	2	11	AU971643         	1	19970722	G	3231	A52810000500051	ARM             			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					NLG DOOR	BROKEN          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR LH AFT DOOR ACTUATING ROD BROKEN.						2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998021100835	19980211	00835	NM  	1998	2	11	AU971644         	1	19971226	G	3230	273T63016	ACTUATOR        	BOEING      	273T63016   	BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					LT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					00181AANSETT					(AUS) LH MAIN LANDING GEAR LEFT HAND DRAG BRACE ACTUATOR PISTON ROD SHEARED IN THREADED AREA.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
1998021100836	19980211	00836	CE  	1998	2	11	AU971645         	1	19971205	G	2822	476411	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TRANSFER PUMP INTERNAL ELECTRICAL FAULT. FEED THROUGH WIRE BROKEN AT SPOT WELD.						1	L	7	2 	3O	3	O		3A10    	E5CE				 
1998021100837	19980211	00837	CE  	1998	2	11	AU971646         	1	19970608	G	2750	500000861	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	TE FLAP CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAP CABLE SNAPPED.						1	L	7	2 	3O			 	A7CE    		5	C	P45GL	 
1998021100838	19980211	00838	NE  	1998	2	11	AU971647         	1	19971216	G	2910	SS48CT3A132000	HOSE            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					MAIN HYD	HOLED           	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 										(AUS) NO2 HYDRAULIC SYSTEM PRESSURE HOSE TO RETRACTION ACTUATOR CONTAINED A SMALL PIN HOLE LEAK.						1	G	7	2 	3U	3	U		H1NE    	E19EU				 
1998021100839	19980211	00839	SO  	1998	2	11	AU971648         	1	19970925	G	7922	53E22144	VALVE           	LYC         	53E22144    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	THERMO BYPASS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					80961		L2551			(AUS) ENGINE OIL SYSTEM  THERMAL BYPASS VALVE (VERNATHERM) RETAINING CLIP FAILED PREVENTING THE VALVE FROM CORRECT OPERA	TION.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998021800009	19980218	00009	EU  	1998	2	18	AU971649         	1	19971106	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										CABIN DOOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN CABIN DOOR R1, R2 AND L2 CONNECTING LINK LOWER BUSHES MIGRATED. FOUND DURING INSPECTION IAW ER A32-52-10-7B.						2	L	7	2 	4F			RT	A28NM   					 
1998021800010	19980218	00010	EU  	1998	2	18	AU971650         	1	19971230	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										CABIN DOOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 AND R1 MAIN CABIN DOOR LOWER CONNECTION LINK BUSHES MIGRATED.FOUND DURING INSPECTION IAW ER A32-52-10-7C.						2	L	7	2 	4F			RT	A28NM   					 
1998021800011	19980218	00011	EU  	1998	2	18	AU971651         	1	19971125	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										CABIN DOOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1, L2 AND R1 MAIN CABIN DOOR LOWER LINK BUSHES MIGRATED. FOUND DURING INSPECTION IAW ER A32-52-10-7C.						2	L	7	2 	4F			RT	A28NM   					 
1998021100840	19980211	00840	EU  	1998	2	11	AU971652         	1	19971125	G	2913	401852	PUMP            			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A1      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	HYDRAULIC	FAULTY          	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 			2967 		IB32					(AUS) HYDRAULIC PUMP FAULTY. PUMP MOTOR OVERHEATED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P61GL	 
1998021100841	19980211	00841	CE  	1998	2	11	AU971653         	1	19971225	G	7540	903800021	SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	BLEED AIR IND	MIS INSTALLED   	W				K				NONE                    				W			INADEQUATE Q C            			CR	CRUISE         	1			AU	S 										(AUS) LH AND RH BLEED AIR SENSE LINES TRANSPOSED. LH LINE CONNECTED TO RH SWITCH AND VICE VERSA. A HOLE IN THE RH SENSE 	LINE ACTIVATED THE LH BLEED AIR WARNING. SEE MDR 97/1609 FOR MORE INFORMATION.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA	 
1998021100842	19980211	00842	EU  	1998	2	11	AU971654         	2	19971209	G	7322	0164168190	FCU             			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					NR 2 ENG FC	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			534  		6315		1123			(AUS) NO2 ENGINE FUEL CONTROL UNIT FAULTY.						2	G	7	2 	4U	4	U		H4EU    	E12NE				 
1998021100843	19980211	00843	GL  	1998	2	11	AU971655         	2	19971211	G	7210	23004220	COVER           	ALLSN       	250C30      						ALLSN 	250C  	250C30      	03013	GL  					ENG NR 3-4 BRG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAG70066		CAE895019			(AUS) ENGINE NO3 AND NO4 BEARING HOUSING BROKEN AT PREVIOUSLY REPAIRED AREA. ENGINE WAS BEING OVERHAULED FOLLOWING AND E	NGINE FAILURE WHICH RESULTED IN A HARD LANDING AND SUDDEN STOPPAGE. ENGINE IS FROM A PNG REGISTERED AIRCRAFT P2-HBB.										3	U			E1GL				 
1998021100844	19980211	00844	EU  	1998	2	11	AU971656         	1	19970720	G	3230	C288393	SPRING          			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5625 							(AUS) LH MAIN LANDING GEAR AFT DOWNLOCK ASSEMBLY AFT OUTER DOWNLOCK SPRING BROKEN AND SPRING LOWER ATTACHMENT FITTING BE	NT.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998021100845	19980211	00845	EU  	1998	2	11	AU971657         	1	19971111	G	7830	CF6RHFRAF1	THRUST REVERSER 			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					R 2 ENG OUTB	CORRODED        	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			24701		R476938					(AUS) NO2 ENGINE OUTBOARD THRUST REVERSER HALF CORRODED AND DAMAGED.METAL STRUT LEADING EDGE DAMAGED AND BROKEN OFF LODG	ING INCASCADE FORWARD RECESS CAUSING A BLOCKER DOOR TO BREAK AND SEVERE BLOCKER DOOR CARRIAGE DAMAGE.					2	L	7	2 	4F	4	F		A35EU   	E23EA				 
1998021100846	19980211	00846	NM  	1998	2	11	AU971658         	1	19970915	G	5220		TRIM            			BOEING	737   	737376      		NM  										EMERGENCY EXIT	BLOCKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT DOOR EMERGENCY HATCH PULL HANDLE TRIM INTERFERING WITH THE MEL DOCUMENT HOLDER PREVENTING THE HATCH FROM F	ALLING INTOTHE COCKPIT AS DESIGNED.					2	L	7	2 	4F			RT	A16WE   					 
1998021100847	19980211	00847		1998	2	11	AU971659         	1	19971113	G	7830		SLEEVE          								CFMINT	CFM56 	CFM563B2    	13802	EU  					NR 2 ENG TR	WORN            	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) NO2 ENGINE THRUST REVERSER INBOARD `SLEEVE NOT STOWED' PROXIMITY SWITCH SLEEVE WORN AND OUT OF ADJUSTMENT.											4	F			E21EU				 
1998021100848	19980211	00848	NM  	1998	2	11	AU971660         	1	19970922	G	2520	737M254570114	SEAT            			BOEING	737   	7374Q8      		NM  										CABIN	SEPARATED       	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 					344238					(AUS) PASSENGER SEAT AFT OUTBOARD SEAT LEG TRACK FITTING SEPARATED FROM THE FLOOR TRACK DUE TO THE LOCKING SCREW BACKING	 OUT OF THE TRACK FITTING. THE SEAT WAS LOCATED AT POSITION ROW 14 DEF.					2	L	7	2 	4F			RT	A16WE   					 
1997042400868	19970424	00868	CE  	1997	4	24	BCBR3786         	1	19970315	G	2497		WIRE            			CESSNA	206   	U206F       	2073333	CE  										ACFT CLOCK	MISINSTALLED    	B			BCBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	59146	2210 				U20602624				DURING AN AUTOPILOT INSTALLATION, THE PLUS (POS) WIRE TO THE A/C CLOCK CONTACTED GROUND.  THE WIRE OVERHEATED AND BURNED	 THROUGH THE PVC INSULATION.  THIS WIRE WAS CONNECTED TO THE BATTERY SIDE OF THE MASTER SOLENOID WITH NO CIRCUIT PROTECT	ION, WIRE WAS NOT ROUTED PER AC43.13-1A AND IT WAS WRAPPED AROUND THE FUEL AND PRIMER LINES THEN THROUGH THE FIREWALL. T	HE WIRE WAS RUN AROUND THE PILOT'S YOKE SUPPORT BRACKET.  NO CHAFE PROTECTION WAS PROVIDED.  MINOR WIRE BUNDLE DAMAGE OC	CURRED.  (X)		1	H	7	1 	3O			 	A4CE    					 
1997121100118	19971211	00118	SO  	1997	12	11	BTVR110597       	1	19971106	G	2121	39714411	VALVE           			GULSTM	G1159 	G1159A      	3970109	SO  										COOLING FAN	FAILED          	B			BTVR	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	23	803CC	7085 			P467	378				DURING GROUND OPERATION WITH THE APU OPERATING, THE FLIGHT CREW DETECTED A STRONG 'HOT SMELL' IN THE CABIN.  AFTER A PHO	NE CONFERENCE WITH HOME BASE MAINTENANCE, THE COOLING TURBINE WAS SUSPECTED.  PRESSURIZATION SYSTEM WAS DEFERRED USING M	.E.L. PROCEDURES AND ACFT RETURNED TO HOME BASE.  FURTHER T/S REVEALED THE GROUND COOLING FAN DID NOT APPEAR TO OPERATE 	PROPERLY WHICH WOULD CAUSE THE AIR CONDITIONING DISTRIBUTION AND SUPPLY DUCTING'S TEMPERATURE TO INCREASE PRODUCING A 'H	OT SMELL'.  THE FAN'S CONTROL VALVE WAS CHANGED.  THE SYSTEM WAS OPERATED FOR AN EXTENDED PERIOD WITH NO DEFECTS.  AIRCR	AFT RETURNED TO SERVICE.  (X)	2	L	7	2 	4F				A12EA   					 
1997092500049	19970925	00049	CE  	1997	9	25	BTVR82997        	1	19970829	G	5320	620022012	HEAT BARRIER    		62002201    	CESSNA	650   	650         	2076802	CE  										RT AFT FUSELAGE	CORRODED        	B	P		BTVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	367G	7770 				6500053				EXHAUST OUTLET WAS REMOVED FOR WELD REPAIR.  FUSELAGE DOUBLER WAS CORRODED THROUGH (2 PLACES) WITH SUBSEQUENT CORROSION 	ON AIRCRAFT SKIN.  REPAIRED IAW CESSNA REPORT S650-0033/01RD WHICH REPLACED HEAT BARRIER WITH HIGH TEMP (RED) RTV 106. T	HIS WILL PREVENT INGRESS OF WATER WHICH CAUSED RESULTING CORROSION.  (X)				2	L	7	2 	4F				A9NM    					 
1998031900251	19980319	00251	CE  	1998	3	19	CA930526402      	1	19970218	G	2910		HYDRAULIC FLUID 			CESSNA	206   	TU206G      	2073357	CE  										PUMP INLET	CONTAMINATED    	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) WHILE TROUBLESHOOTING FLOAT GEAR MOTOR INOP, FOUND HYDRAULIC FLUID HAD DIRT, FUNGI GROWTH (A BLACK MASS) COVERING 	THE PUMP INLET SCREEN.  WIPAIRE SERVICE LETTER NR 15 REFERS TO THIS SUBJECT.					1	H	7	1 	3O				A4CE    					 
1997042800088	19970428	00088	NM  	1997	4	28	CA970106009      	1	19970122	G	3297		WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  										NLG DOWNLOCK	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON GEAR DOWN SELECTION, YELLOW CAUTION LIGHT ON MOMENTARILY. NOSE WHEEL RED AND AMBER DOOR LIGHT ON. WHEN GEAR HAN	DLE TOUCHED, ALL GREEN LIGHTS ON. AFTER LANDING, RED NOSE GEAR LIGHT ON AGAIN WITH GEAR HANDLE LIGHT AND WARNING HORN. N	OSE WHEEL STEERING LOST. INSPECTION FOUND ONE WIRE TO NOSE DOWNLOCK SWITCH BROKEN AND HARNESS FLATTENED WHERE IT PASSES 	OVER TRUNNION.			2	H	7	2 	4T			RT	A13NM   					 
1997042800097	19970428	00097	NM  	1997	4	28	CA970109001      	1	19970103	G	2100	3033716X2	SEALS           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AIR COND SYS	LEAKING         	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								120854			(CAN) HAZE IN CABIN AND LAV. SMOKE DETECTOR SOUNDED. #1 AND #2 ENGINE COMPRESSOR DRAINS CHECKED FOR OIL. NONE FOUND. P2.	5 AND P3 SWITCHING VALVE PISTON RINGS REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042800098	19970428	00098	NE  	1997	4	28	CA970109002      	3	19970103	G	6112	SFA13M1ROA	BLADE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	DEICE BOOT	BURNED BOOT     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8380 	8380 				120226	881010		(CAN) #2 PROPELLER BLADE DE-ICE BOOT SHORTED BURNED RUBBER OFF THE BLADE. BLADE REPAIRED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
1997042800100	19970428	00100	EU  	1997	4	28	CA970109012      	1	19970106	G	2910	AE2463921G01	HYDRAULIC LINE  			AIRBUS	320   	A320211     	3930320	EU  										LT GEAR DOOR	LEAKING         	W				K				NONE                    				J	K		WARNING INDICATION        	FLUID LOSS                		TX	TAXI/GRND HDL  	1			CA											(CAN)DURING TAXI TO RAMP GREEN HYDRAULIC SYSTEM FAILED. INVESTIGATION REVEALED HYDRAULIC LINE ON LH GEAR DOOR RETRACT FO	UND LEAKING. DEFECTIVE LINE REPLACED.					2	L	7	2 	4F			RT	A28NM   					 
1997050100354	19970501	00354	EU  	1997	5	1	CA970109013      	1	19970106	G	5610		WINDSHIELD      		STA320241   	AIRBUS	320   	A320211     	3930320	EU  										FIRST OFFICER	CRACKED         	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA						760					(CAN) AT CRUISE FIRST OFFICERS WINDSHIELD CRACKED, ALTITUDE REDUCED AS PER FCOM. THERE WAS LOSS OF HEAT TO RIGHT WINDSHI	ELD, OUTER PANE ARCING NOTED, CB PULLED. WINDSHIELD REPLACED.					2	L	7	2 	4F			RT	A28NM   					 
1997050100355	19970501	00355	EU  	1997	5	1	CA970109014      	1	19970106	G	3233	MS2125008020	BOLT            	AIRBUS      	D57252160   	AIRBUS	320   	A320211     	3930320	EU  										RH LANDING GEAR	CHAFE TANK      	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE FUEL FOUND LEAKING AT RH MAIN LANDING GEAR ACTUATOR FITTING DUE TO BOLTS BEING TOO LONG	. BOLTS REPLACED WITH CORRECT TYPE AS SPECIFIED IN DRAWING NO.D57252160 AND TANK RESEALED.					2	L	7	2 	4F			RT	A28NM   					 
1997050100367	19970501	00367	WP  	1997	5	1	CA970110002      	2	19970115	G	7321	30708165	PT SENSOR       			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					#2 ENGINE	FAULTY          	W				A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			9657 					P74369			(CAN) DURING TAKEOFF THE #2 ENGINE RPM BEGAN TO OSCILLATE. THE ENGINE COMPUTER WAS SELECTED TO THE OFF POSITION. THE ENG	INE RPM STABILIZED BUT WOULD NOT MAKE POWER, APPROXIMATELY 80 PERCENT N1. THE AIRCRAFT RETURNED TO BASE AND LANDED WITHO	UT INCIDENT. TROUBLESHOOTING FOUND THE PT2 SENSOR PROBE TO BE THE FAULT, ALTHOUGH NO DAMAGE TO THE PROBE WAS EVIDENT. TH	E PROBE WAS REPLACED AND THE ENGINE GROUND RUN WITH THE COMPUTERS ON AND OFF CARRIED OUT. ALL PARAMETERS NORMAL AND THE 	AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F		A10CE   	E6WE				 
1997050100368	19970501	00368	NM  	1997	5	1	CA970110003      	1	19970101	G	2435	1243106	STARTER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					#1  ENG	FAILED          	W				O	F			OTHER                   	ACTIVATE FIRE EXT.      			B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA						575A		120549			(CAN) CREW ABORTED START DUE TO SMOKE FROM #1 ENGINE NACELLE. ON PREVIOUS FLIGHT GENERAL CAUTION LIGHT HAD FAILED WITH E	XCITER BREAKER POP. STARTER/GENERATOR REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997050100372	19970501	00372	EA  	1997	5	1	CA970114001      	2	19970105	G	8550	CH48103	OIL FILTER      	CHAMPION    		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENG OIL	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L613961A			(CAN) DURING OIL FILTER REPLACEMENT, THE OIL FILTER WAS FOUND COLLAPSED. COLD WEATHER OPERATION IS THE SUSPECTED CAUSE. 	LYCOMING SERVICE BULLETIN #1442 COMPLIED WITH TO PREVENT REOCCURRENCE.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997050100382	19970501	00382	EA  	1997	5	1	CA970114019      	2	19970107	G	8550	CCB3700	VALVE DRAIN     	CURTIS      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					BOTTOM #1 ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA				1925 				L159368A			(CAN) OIL LEAK ON #2 ENGINE FOLLOWING FLIGHT. INSPECTION FOUND THE OIL DRAIN COCK LEAKING. OIL SEAL APPEARED AGED AND HA	RDENED. OIL SEAL REPLACED AND DRAIN COCK CLEANED AND REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997050100387	19970501	00387	WP  	1997	5	1	CA970114026      	1	19970101	G	2150	21700091	AIR CYCLING MACH			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					LH AIR CONDITION	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								P656990D			(CAN) LEFT HAND AIR CONDITIONING PACK CAUSED OIL SMELL IN CABIN. LEFT AIR CONDITIONING AIR CYCLING MACHINE CHANGED. OPER	ATION AND LEAK CHECKED CARRIED OUT. SYSTEM CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050100388	19970501	00388	EU  	1997	5	1	CA970114027      	1	19970106	G	2750		FLAP LIMITER    			AIRBUS	320   	A320211     	3930320	EU  										OUTB FLAP DRIVE	FAILED          	W				O				OTHER                   				O	F		OTHER                     	FLT CONT AFFECTED         		AP	APPROACH       	1			CA											(CAN) FLAPS FAILED TO EXTEND ON APPROACH. FLAPLESS LANDING CARRIED OUT. MAINTENANCE FOUND RIGHT INBOARD FLAP OUTBOARD DR	IVE LIMITER TRIPPED. FLAPS OPERATED NORMALLY AFTER LANDING. FLAP OUTBOARD DRIVE LIMITER RESET, INSPECTION HOLES CHECKED 	FOR CONTAMINATION. OPERATIONAL CHECKED CARRIED OUT SERVICEABLE.				2	L	7	2 	4F			RT	A28NM   					 
1997050100389	19970501	00389	WP  	1997	5	1	CA970114028      	1	19970104	G	2131	21011403	CONTROLLER      			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					NR 1 PRESSURE	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			O			OTHER                     			CR	CRUISE         	1			CA								P657224D			(CAN) LOSS OF PRESSURIZATION AT 12,600 FT. CABIN OVER 10,000 FT. OXYGEN MASKS DEPLOYED. BITE CHECK CARRIED OUT AND SHOWE	D #1 CONTROLLER AT FAULT. BOTH AUTO PRESSURIZATION CONTROLLERS CHANGED AND OPERATIONALLY CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050100390	19970501	00390	EA  	1997	5	1	CA970114029      	1	19970101	G	3260	16215103	BRACKET         			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NLG PROX SWITCH	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			5312 					807157			(CAN) AFTER NOSE GEAR RETRACTION, NOSE GEAR REMAINED DOWN. GEAR DISAGREE AND NOSE DOOR OPEN MESSAGES APPEARED. FOUND NOS	E LANDING GEAR CENTERING PROXIMITY SWITCH BRACKET DAMAGED. BRACKET REPLACED AND SWITCH ADJUSTED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100392	19970501	00392	SW  	1997	5	1	CA970115002      	1	19970107	G	6322	204060448001	BLOWER          			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					OIL COOLER	ROUGH BEARING   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE18135A			(CAN) BEARINGS IN OIL COOLER BLOWER SOUND ROUGH AND DRY WHEN FAN IS TURNED BY HAND. BLOWER REMOVED AND BEARINGS REPLACED	.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
1997050100393	19970501	00393	EA  	1997	5	1	CA970115006      	1	19970108	G	2421	755469C	IDG             	SUNDSTRANDEM		CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					#2 ENGINE	FAILED          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			CA			2253 					H807335			(CAN) AIRCRAFT REJECTED TAKEOFF DUE TO #2 GENERATOR TRIPPING OFF LINE. INTEGRATED DRIVE GENERATOR REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050100395	19970501	00395	SW  	1997	5	1	CA970115008      	1	19970103	G	7603	MS20392211	CLEVIS PIN      	SWRNGN      	2761002009  	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					POWER LEVER	FRETTING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P54024			(CAN) IN REFERENCE TO SERVICE DIFFICULTY ADVISORY AV-96-06, INSPECTION CARRIED OUT ON THE CLEVIS PIN IN THE POWER LEVER 	SYSTEM. THE PINS IN THE LEFT AND RIGHT ENGINES WERE NOTICEABLY WORN, AND THE COTTER PIN HOLES ELONGATED. BOTH CLEVIS AND	 COTTER PINS WERE REPLACED.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997050100396	19970501	00396	CE  	1997	5	1	CA970117001      	1	19970104	G	2730	1156100181	SUPPORT         	BEECH       	115610010325	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					ELEV TORQ TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9005 					PCE50045			(CAN) CRACK FOUND ON THE INBOARD TAPER PIN HOLE ON THE TORQUE TUBE SUPPORT BRACKET WHERE IT ATTACHES TO THE ELEVATOR.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997050100397	19970501	00397	GL  	1997	5	1	CA970117002      	3	19970109	G	6111	900CA2	PROP BLADE      			CESSNA	180   	180F        	2072614	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LEADING EDGE	STONE NICKED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				134  				842373R4	750677		(CAN) DURING CORROSION INSP PROPELLER BLADES WERE FOUND "STONE" NICKED. NICKS WERE TRIMMED OUT.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997050100398	19970501	00398	EU  	1997	5	1	CA970117006      	1	19970109	G	3230		LANDING GEAR    			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	NOSE	ICED UP         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								120905	880501		(CAN) AFTER TAKEOFF THE NOSE LANDING GEAR DID NOT RETRACT. MAINTENANCE FOUND THE NOSE GEAR BAY CONTAMINATED WITH A LOT O	F SNOW AND ICE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
1997050100399	19970501	00399	GL  	1997	5	1	CA970117007      	1	19970104	G	3270		TAILSKID        			AMTR  	REBEL 	REBEL       	05612SG	GL  										END	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			74   								(CAN) PILOT LOST RUDDER CONTROL WHILE TAXIING ON GRASS STRIP COVERED BY ONE INCH OF SNOW. INVESTIGATION REVEALED THE TAI	L SKID TO BE BROKEN. SUBMITTER CONTACTED THE MANUFACTURER AND WAS INFORMED OF A MODIFICATION TO THE DESIGN.					1	L	7	1 	3O			NC	EXPA1L71					 
1997061900496	19970619	00496	EU  	1997	6	19	CA970121002      	1	19970115	G	3241	AC60742	MAXARET         	DUNLOP      		BRAERO	748   	HS7482A     	4231001	EU  										ANTI SKID SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						227					(CAN) VALVE STEM LEAKING AT SOLDER JOINT. SPRING DAMAGED DUE TO OVERHEATING DURING SOLDERING.						2	L	7	2 	3T				A24EU   					 
1997050600006	19970506	00006	EU  	1997	5	6	CA970121005      	2	19970101	G	7320	196	FUELFLOW REG    			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					#1 ENGINE	FAULTY          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			2944 			L820		9635			(CAN) ON TAKEOFF ROLL THE #1 ENGINE WOULD NOT SPOOL UP TO FULL POWER. AIRCRAFT RETURNED TO GATE. MAINTENANCE FOUND THE F	UEL FLOW REGULATOR TO BE FAULTY. THE FUEL FLOW REGULATOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997050100400	19970501	00400	EA  	1997	5	1	CA970121006      	1	19970109	G	3010	15323	DEICE VALVE     	BENDIX      		DHAV  	DHC6  	DHC6100     		EA  	PWA   	PT6   	PT6A20      	52043	EA  					WING DE ICE	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA				120  		42952U		PCE21305			(CAN) ON APPROACH AIRCRAFT ENCOUNTERED HEAVY ICING CONDITIONS. AFTER LANDING THE INBOARD HALF OF WING FOUND COVERED WITH	 ICE. WING DEICE DISTRIBUTOR VALVE WAS CYCLED BUT DID NOT WORK. VALVE REPLACED. A MOD WILL BE INTRODUCED TO INSTALL HEAT	ER AROUND THE VALVES AS THE PREVIOUS VALVE HAD MOISTURE IN IT.				1	H	7	2 	3T	3	T		A9EA    	E4EA				 
1997050800720	19970508	00720	SW  	1997	5	8	CA970121007      	1	19970113	G	6520	2060404077	OUTPUT SHAFT    	BELL        	206040400005	BELL  	206   	206BELL     	1181502	SW  										T/R GR BOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2085 			B13551					(CAN) UPON DISASSEMBLY OF T/R GEARBOX FOR MIDLIFE INSPECTION, THE SEAL JOURNAL AREA OF THE OUTPUT SHAFT WAS FOUND TO BE 	SEVERELY WORN TO A DEPTH OF 0.20 INCHES IN A V-SHAPED UNDERCUT FOR THE ENTIRE CIRCUMFERENCE OF THE SHAFT. THIS WORN AREA	 IS DIRECTLY ADJACENT TO THE OUTPUT SEAL LOCATION ON THE OUTPUT CAP OF THE GEARBOX. BEFORE DISASSEMBLY, THE GEARBOX RUN-	OUT WAS CHECKED AND FOUND WITHIN LIMITS AND NO LEAKAGE WAS EVIDENT FROM THE OUTPUT SEAL AREA. HOWEVER, THE INTERIOR OF T	HE GEARBOX WAS COATED IN A FINE PASTE AS WERE ALL THE RELATED INTERNAL PARTS.		1	G	7	1 	3U				H2SW    					 
1997050800721	19970508	00721	CE  	1997	5	8	CA970121009      	1	19970113	G	3260	10038100601	SWITCH          		10038100601 	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					MLG DOWNLOCK	INTERMITTENT    	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA								PCE56069			(CAN) DURING APPROACH, PILOTS UNABLE TO GET GEAR DOWN INDICATION. RETURNED TO BASE AND FLYBY CONFIRMED GEAR DOWN. MAINTE	NANCE FOUND THE DOWNLOCK SWITCH TO BE INTERMITTENT.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997051300021	19970513	00021	EU  	1997	5	13	CA970121010      	1	19970108	G	7160	350A54112220	INLET DUCT      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					START/GEN AIR	LOST IN FLIGHT  	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA								9322			(CAN) STARTER GENERATOR AIR INLET DUCT WAS LOST IN FLIGHT. SUSPECT CAUSE OF SEPARATION IS LOOSENING OF SECURING CLAMP.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1997050800722	19970508	00722	SW  	1997	5	8	CA970121011      	1	19970113	G	3246	13600L	BEARING         	BFGOODRICH  	313571      	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	NR 2 MLG WHEEL	ROLLERS MISSING 	W		A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						5024		P447414	106175		(CAN) OUTSIDE BEARING ON #2 MAIN WHEEL ASSEMBLY FAILED AND RESULTED IN WHEEL DEPARTING THE AIRCRAFT. THE BEARING ROLLERS	 LEFT THE BEARING CAGE ALLOWING THE WHEEL TO EXIT THE AXLE OVER THE SPACER, WASHER AND NUT. INNER BEARING WAS EXCESSIVEL	Y WORN, THERE WAS STILL GREASE IN BEARING. NO SPACER FOUND BETWEEN WHEEL HALVES. AXLE ON DAMAGE ON OPPOSITE WHEEL. INSPE	CTION PROGRAM BEING IMPLEMENTED FOR INITIAL INSPECTION OF WHEEL BEARINGS, CUPS AND AXLES ON ALL SA226/227 AIRCRAFT.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
1997050800723	19970508	00723	EA  	1997	5	8	CA970122001      	1	19970109	G	2920	MX499336	HYDRAULIC LINE  	SPERRYVICRS 	731840      	DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					STDBY POWER	LEAKING         	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J	K		WARNING INDICATION        	FLUID LOSS                		TX	TAXI/GRND HDL  	1			CA						MX499336		123192			(CAN) DURING TAXI CREW NOTICED HYDRAULIC LEAK AND LOSS OF FLUID FROM THE #1 HYDRAULIC SYSTEM.  HYDRAULIC LINE AT THE STA	NDBY POWER UNIT FOUND LOOSE AND LEAKING					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997061900500	19970619	00500		1997	6	19	CA970122002      	4	19970117	G	2562	0025004	BATTERY         	DAYTON      	EB2BCD      	BOEING	75    	B75N1       	1380144	CE  	LYC   	R680  	R680B4E     	41540	EA  					ELT CASE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						39254		13378			(CAN) AFTER TWO YEARS ARTEX BATTERY LEAKED AND CORRODED CHASSIS AND INSIDE OF CASE.						1	Q	7	1 	3R	3	R		A743    	TC108				 
1997050800724	19970508	00724	NE  	1997	5	8	CA970122004      	2	19970114	G	7250	310900301	PT BLADE        								PWA   	118   	PW118       		NE  					ENGINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19129	10153				115070			(CAN) THE OPERATOR OBSERVED POWER TURBINE DAMAGE AND THE ENGINE WAS SENT FOR INVESTIGATION. DISASSEMBLY REVEALED THE ENG	INE SUFFERED A PRIMARY FAILURE OF ONE POWER TURBINE BLADE. THE FRACTURE WAS THROUGH THE CORED POCKET APPROXIMATELY 1/4" 	ABOVE THE INNER PLATFORM. IT WAS CONCLUDED THE FAILURE OCCURRED DUE TO HIGH TIME ON THE BLADE.									4	T			E20NE				 
1997050800726	19970508	00726	CE  	1997	5	8	CA970128001      	1	19970115	G	5210	05170392	DOOR HANDLE     	CESSNA      	0711023105  	CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	STEEL INSERT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			153  					462647	950479		(CAN) A NEW STYLE OF HANDLE WAS INSTALLED WITH A STEEL BUSHING IN AN ALUMINUM HANDLE. THE TWO PART ASSEMBLY SEPARATED AT	 THE UNION. THE PART WAS SENT BACK FOR WARRANTY.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997050800727	19970508	00727	GL  	1997	5	8	CA970128003      	1	19970118	G	5610	2056501100	CANOPY          	DIAMON      	2056501100  	DIAMON	DA20A1	DA20A1      	05626UX	GL  										L/H LOCK BARREL	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			100  								(CAN) A 30 INCH CRACK DEVELOPED IN THE CANOPY, RADIATING FROM THE CANOPY LOCK CYLINDER ON THE LEFT OF THE CANOPY RAIL AN	D MOVING UPWARDS TO THE 11 O'CLOCK POSITION.					1	L	7	1 	3O			NT	TA4CH   					 
1997050800728	19970508	00728	GL  	1997	5	8	CA970128004      	1	19970117	G	2752		FLAP ACTUATOR   			DIAMON	DA20A1	DA20A1      	05626UX	GL  										BELLY	BROKEN WIRE     	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) ICE IN THE BELLY OF THE AIRCRAFT PREVENTED THE FLAP ACTUATOR FROM FUNCTIONING AND POPPED THE CIRCUIT BREAKER. A BR	OKEN WIRE WAS FOUND UPON THAWING THE ICE. SUBMITTER BELIEVES THE WIRE BROKE WHILE DEPLOYING THE FLAPS.					1	L	7	1 	3O			NT	TA4CH   					 
1997050800729	19970508	00729	EA  	1997	5	8	CA970128005      	2	19970122	G	8550	75288	SHAFT           			GULSTM	112   	112         	0144701	SW  	LYC   	O360  	IO360C1D6   	41514	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	OIL PUMP	WORN KEYWAY     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			985  					L955051A	DK330		(CAN) DURING COMPLIANCE WITH AD 96-09-10 IT WAS DISCOVERED THE DRIVE GEAR AND DRIVE SHAFT CONTAINED A KEYWAY. THE KEYWAY	 AND DRIVE GEAR WERE WORN APPROXIMATELY 0.060". THIS KEYWAY SHOULD HAVE BEEN REMOVED BY AD 75-08-09, BUT THIS ENGINE, BY	 SERIAL NUMBER, IS NOT APPLICABLE TO AD 75-08-09. A REPLACEMENT DRIVE SHAFT WAS INSTALLED.				1	L	7	1 	3O	3	O		A12SO   	1E10	5	C	P9EA	 
1998040200031	19980402	00031	EA  	1998	4	2	CA970128006      	1	19970124	G	7830	12675862	PNEUMATIC DR UNI			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      		NE  					LT ENGINE	MIS ADJUSTED    	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								GEE350177			(CAN) LEFT THRUST REVERSER PDU UNLOCKED, LIGHT REMAINED ON WHEN THRUST REVERSER STOWED.  FLEX LOCK FOUND DISENGAGED.  IN	TERNAL TIMING FOUND OUT OF LIMITS.  REPLACED PNEUMATIC DRIVE UNIT.					1	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
1997050800730	19970508	00730	CE  	1997	5	8	CA970128007      	1	19970120	G	7931	100381173	INDICATOR       	AEROMECH    		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					#2 ENG OIL PRESS	FAULTY          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J	N		WARNING INDICATION        	FALSE WARNING             		CR	CRUISE         	1			CA						27C18		PCE50253			(CAN) AIRCRAFT WAS IN CRUISE WHEN THE RIGHT HAND OIL PRESSURE INDICATOR WAS FLICKERING, ALL OTHER PARAMETERS WERE NORMAL	. SEVERAL MINUTES LATER THE OIL PRESSURE WENT TO "0". THE #2 ENGINE WAS SHUTDOWN. POST FLIGHT INSPECTION FOUND THE OIL P	RESSURE/TEMPERATURE GAUGE TO BE FAULTY. THE GAUGE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997051300023	19970513	00023	EA  	1997	5	13	CA970128010      	1	19970120	G	2435	215T5091010	DUCT INLET      	AIRPTS      	215T5091018 	CNDAIR	CL215 	CL2151A10   		EA  										START/GEN	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			161  								(CAN) WELD ON COOLING DUCT FOR STARTER GENERATOR HAS NO METAL PENETRATION.  SKIN JOINT SPLIT AND PARTS ALMOST CHAFED THR	OUGH AN OIL RETURN LINE.  BOTH DUCT INLETS WERE IN SIMILAR CONDITION.  ONE OF THE SPLITS WAS .25 INCH AND THE OTHER .50 	INCH WIDE.  INSPECTION CARRIED OUT AS PER CANADAIR REQUEST.				2	H	7	2 	4R				A14EA   					 
1997050800731	19970508	00731	CE  	1997	5	8	CA970128011      	1	19970122	G	5210	50430043163	CHANNEL         	BEECH       	50430043622 	BEECH 	80    	65B80       	1152812	CE  	LYC   	O540  	IGSO540A1D  	41532	EA  					CABIN DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7437 					RL370750			(CAN) CABIN DOOR HINGE HAD EXCESSIVE PLAY. WHILE REPLACING THE RIVETS A CRACK WAS FOUND IN THE STRUCTURE.						1	L	7	2 	3O	3	O		3A20    	1E7				 
1997050800732	19970508	00732	WP  	1997	5	8	CA970129001      	1	19970113	G	3222	MS288891	AIR VALVE       			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					NLG OLEO	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P657766D			(CAN) ON TAKEOFF, UNABLE TO RAISE NOSE GEAR AND NOSE GEAR LIGHT CAME ON. QUICK REFERENCE HANDBOOK CHECK LIST CARRIED OUT	. ON ARRIVAL FOUND NOSE GEAR OLEO FLAT. NOSE GEAR SERVICED AND SCHRADER VALVE REPLACED.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800733	19970508	00733	WP  	1997	5	8	CA970129002      	1	19970114	G	2841	DC26F16265	FUEL INDICATOR  			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					RH FUEL QUANTITY	INOPERATIVE     	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								P656873D			(CAN) ELECTRICAL SMELL DETECTED AND RH FUEL QUANTITY INDICATOR FAILED. TROUBLESHOOTING OF SNAG REVEALED RH INDICATOR CIR	CUIT BREAKER HAD POPPED. DEFECTIVE INDICATOR REPLACED AND SYSTEM CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800734	19970508	00734	EA  	1997	5	8	CA970129003      	1	19970112	G	3230		BRACKET         			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NOSE GEAR	OUT OF ADJUST   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			3517 					807267			(CAN) AFTER TAKEOFF UNABLE TO RETRACT NOSE GEAR. TARGET BRACKET REMOVED AND REPAIRED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050800735	19970508	00735	EA  	1997	5	8	CA970129004      	1	19970115	G	2740	70607	HSTU            			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					H STAB TRIM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3204 					807281			(CAN) AFTER TAKEOFF FLIGHT REPORTED STABILIZER TRIM MESSAGE ON ECAM. HORIZONTAL STABILIZER TRIM UNT (HSTU) REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050800736	19970508	00736	WP  	1997	5	8	CA970129005      	1	19970115	G	2530	CA167072	RECEPTACLE      			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					GALLEY	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								P654065D			(CAN) ELECTRICAL SMELL DETECTED IN FLIGHT DECK. MAINTENANCE TROUBLESHOOTING FOUND #4 OVEN RECEPTACLE BURNT. OVEN RECEPTA	CLE REPLACED AND CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997050800745	19970508	00745	NE  	1997	5	8	CA970129017      	2	19970101	G	7220		FAN BLADES      								PWA   	4056  	PW4056      		NE  					#2 ENGINE	SHINGLED/DAMAGED	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA								P724426			(CAN) HIGH VIBRATION ON #2 ENGINE WITH FAN BLADE SHINGLING. INSPECTION FOUND ALL FAN BLADES SHINGLED, MOST OF THE BLADES	 HAD EXTENSIVE DAMAGE IN THE SHROUD AREA. THE ENGINE PICKED UP HEAVY SNOW DURING TAKEOFF. ALL FAN BLADES REMOVED. STAGE 	2 FAN EXIT VANES AND EXHAUST CHECKED SERVICEABLE. FAN BLADE SET REPLACED. GROUND RUN AND VIBRATION SURVEY CARRIED OUT SE	RVICEABLE.								4	F			E24NE				 
1997050800746	19970508	00746	EA  	1997	5	8	CA970129018      	2	19970123	G	7261		O-RING          			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					TRANSFER TUBE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			CA								PCE40147			(CAN) OIL PRESSURE AND TORQUE FLUCTUATION IN FLIGHT NECESSITIATED ENGINE SHUTDOWN OF #1 ENGINE. POST FLIGHT INSPECTION F	OUND AN "O" RING ON THE OIL TRANSFER TUBE AT THE "C" FLANGE WAS WORN FLAT AND LEAKING, CAUSING OIL TO LEAK ON THE EXHAUS	T CAN.				1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997050800749	19970508	00749	NM  	1997	5	8	CA970130008      	1	19970109	G	2150		AIRCYCLE MACHINE			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AIR COND	SEIZED          	W				O	H			OTHER                   	DEACTIVATE SYST/CIRCUITS			B	O		SMOKE/FUMES/ODORS/SPARKS  	OTHER                     		CR	CRUISE         	1			CA								120275			(CAN) PILOT REPORTED AIRCRAFT OPERATING WITH BATTERY ONLY AS AN ELECTRICAL BURNING SMELL WAS NOTED IN THE COCKPIT. MAINT	ENANCE FOUND THE AIR CYCLE MACHINE SEIZED. PILOT PROCEDURE IS TO SHUT DOWN BLEED SYSTEMS AND THEN GENERATORS UNTIL SMOKE	 CLEARS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997050800750	19970508	00750	NM  	1997	5	8	CA970130012      	1	19970123	G	2761	A44700007	ACTUATOR        	DOWTY       		DHAV  	DHC8  	DHC8101     	2809002	NM  										LH INB SPOILER	JAMMED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			9661 			1743					(CAN) AFTER LIFT OFF THE CREW EXPERIENCED A LEFT WING DOWN ROLL, AND INPUT OPPOSITE WHEEL FORCE TO CORRECT. AN EMERGENCY	 DECLARED AND AIRCRAFT LANDED OK. ON GROUND THE CREW NOTED THAT THE LEFT HAND INBOARD ROLL SPOILER INDICATION ON THE PFC	S INDICATOR, SHOWING SOME UP DEFLECTION. GROUND CREW CONFIRMED THAT THE LH INBOARD ROLL SPOILER ACTUATOR WAS JAMMED IN T	HE MID POSITION AND WOULD NOT RETRACT. ACTUATOR SENT TO DOWTY FOR STRIP DOWN.			2	H	7	2 	4T			RT	A13NM   					 
1997050800751	19970508	00751	EA  	1997	5	8	CA970130013      	2	19970119	G	7414	1038255514	MAGNETO         	BENDIX      	O4RN2000    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	DIST GEAR	BROKEN TEETH    	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				700  				L830076T	731179		(CAN) SHORTLY AFTER TAKEOFF THE ENGINE BEGAN TO RUN ROUGH AND LOSE POWER. AIRCRAFT RETURNED TO BASE. RUN UP THE FOLLOWIN	G DAY REVEALED THE LEFT MAGNETO WAS DEAD. DISASSEMBLY OF THE MAGNETO REVEALED BROKEN TEETH ON THE DISTRIBUTOR GEARS.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997050800752	19970508	00752	GL  	1997	5	8	CA970130014      	3	19970122	G	6111	900H1316E	BLADE           													MCAULY	2D34C	B2D34C214   	GL  	BLADE AIRFOIL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				918  							(CAN) HEAVY STONE DAMAGE TO LEADING EDGE ON PROPELLER FACE SIDE.																5	C	P7EA	 
1997050800753	19970508	00753	EA  	1997	5	8	CA970130017      	1	19970124	G	2730	C3CF1957	CONTROL CABLE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					STA.308	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								9594			(CAN) AS A RESULT OF THE ELEV CABLE RUBBING ON THE PULLEY SOME CABLE STRANDS WERE BROKEN.						1	H	7	1 	3R	3	R	 	A815    	5E2				 
1997050800754	19970508	00754	EA  	1997	5	8	CA970130018      	1	19970124	G	2720	C3CF1975	CONTROL CABLE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					STA.60	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								9594			(CAN) RUDDER CABLE FRAYED AT TWO PLACES, ON THE RUDDER QUADRANT AND ON A PULLEY TWO FEET AFT.						1	H	7	1 	3R	3	R	 	A815    	5E2				 
1998040200034	19980402	00034	CE  	1998	4	2	CA970130019      	1	19970117	G	2910	651713670	HYD LINE        			CESSNA	500   	560CESSNA   	2076750	CE  										RESERVIOR RETURN	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1430 								(CAN) DURING A PHASE 3 INSPECTION, A GROUNDING STRAP (P/N 047-5824-01) OF KHF950 AMPLIFIER (NOT INSTALLED) WAS FOUND TO 	BE LOOSE AND CHAFING THE HYDRAULIC RESERVOIR RETURN LINE.  LINE CHAFED APPROX 75 PER CENT THROUGH THE WALL THICKNESS.  G	ROUNDING STRAP SECURED PROPERLY AND LINE REPLACED.  PART TC:  1,149.				2	L	7	2 	4F			RT	A22CE   					 
1997050800755	19970508	00755	NE  	1997	5	8	CA970130020      	2	19970121	G	7250	311260201	TURBINE BLADES  								PWA   	PW121 	PW121       	52124	NE  					AIRFOIL	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17523	13037				120518			(CAN) THE ENGINE HAD SUFFERED FRACTURE OF TWO LP TURBINE BLADES.											4	T			E20NE				 
1997050800756	19970508	00756	CE  	1997	5	8	CA970130022      	1	19970122	G	5610	1143840202	WINDSHIELD      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					COCKPIT RT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								PCE32052			(CAN) PLANE WAS AT 24,000 FEET CRUISING ALTITUDE WHEN R/H WINDSHIELD CRACKED IN PIECES. AIRCRAFT MADE AN UNSCHEDULED, SA	FE, LANDING FOR REPAIR.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1997050800757	19970508	00757	GL  	1997	5	8	CA970131002      	3	19970123	G	6111	F76632R	PROP BLADE      													HARTZL	HCC3Y	PHCC3YF1    	GL  	LE FACE SIDE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				219  					FE1345		(CAN) INSPECTION FOUND LIGHT STONE DAMAGE TO THE LEADING EDGE OF THE PROPELLER FACE SIDE.																5	C	P25EA	 
1997050800758	19970508	00758	EA  	1997	5	8	CA970131004      	1	19970123	G	3230		SWITCH          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NOSE GEAR	BENT            	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA			5480 					807157			(CAN) GEAR DISAGREEMENT ON TAKEOFF. GEAR CYCLED TWICE, SAME INDICATION. NOSE GEAR SHOWED DOWN DOOR OPEN. GEAR EXTENDED, 	3 GREEN LIGHTS. FOUND NOSE GEAR EXTEND PROXIMITY SWITCH BENT AWAY FROM TARGET.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997050800759	19970508	00759	EU  	1997	5	8	CA970131005      	1	19970124	G	3213		GEAR            			AIRBUS	320   	A320211     	3930320	EU  										MLG	LOW INFLATION   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, LANDING GEAR SHOCK ABSORBER FAULT CAME ON. LANDING GEAR WOULD NOT RETRACT. INVESTIGATION REVEALED B	OTH MAIN LANDING GEAR OLEOS INFLATION WERE LOW. BOTH GEARS SERVICED AND CHECKED SERVICEABLE.					2	L	7	2 	4F			RT	A28NM   					 
1997050800760	19970508	00760	NM  	1997	5	8	CA970203001      	1	19970108	G	7500		CABIN           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					BLEED AIR	SMOKE           	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			19190					120854			(CAN) REPEAT OF PREVIOUS SMOKE IN CABIN PROBLEM. AFTER BLEEDS SELECTED ON #1 ENGINE THE CABIN FILLED WITH SMOKE. THIS TI	ME OIL WAS FOUND IN THE ENGINE BLEED AIR SYSTEM.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997050800761	19970508	00761		1997	5	8	CA970203003      	4	19970121	G	2200		FLIGHT RECORDER 			AIRBUS	320   	A320211     	3930320	EU  										AUTOLAND	INOPERATIVE     	W				H				DEACTIVATE SYST/CIRCUITS				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) AUTOLAND WITH 5 KTS TAILWIND CAUSED HEAVY LANDING. AIRBUS ADVISED AND REPLIED WITH CAUSE FROM DOWNLOADED DFDR INFO	 INCLUDING SIDE WIND FACTORS NOT REPORTED AT TIME OF INCIDENT. ALL AUTOLANDS SUSPENDED UNTIL FURTHER NOTICE.					2	L	7	2 	4F			RT	A28NM   					 
1997050800762	19970508	00762	EA  	1997	5	8	CA970203006      	1	19970116	G	2910	AN62074	CHECK VALVE     	PARKER      		DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					FLAPS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			331  					PCE42076			(CAN) DURING PREFLIGHT THE HYDRAULIC SYSTEM FOUND TO CYCLE DUE TO LOW PRESSURE. FLAP CHECK VALVE FOUND LEAKING.						1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997061900510	19970619	00510		1997	6	19	CA970203007      	4	19970123	G	3416	265411	COUNTER         			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					ALTIMETER	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P653620B			(CAN) DURING BI-ANNUAL CALIBRATION IT WAS IDENTIFIED THAT THE COUNTER IN THE ALTIMETER WAS CAUSING THE INSTRUMENT TO STI	CK AT VARIOUS ALTITUDES. REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997050800764	19970508	00764	CE  	1997	5	8	CA970203010      	1	19970124	G	5210	1014301071	CHANNEL         	BEECH       	1014301071  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12865					PCE80204			(CAN) WITH CABIN DOOR OPEN, A CRACK WAS FOUND IN THE UPPER FRAME MEMBER. THE CRACK WAS APPROXIMATELY 6 INCHES LONG, ALON	G THE DOOR HINGE RIVET LINE, RUNNING FROM THE AFT EDGE FORWARD.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997051900001	19970519	00001	NE  	1997	5	19	CA970203011      	2	19970124	G	7240	RK47289	COMB CHAMBER    			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5352    	54509	NE  					NOSE CONE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						19460		1860			(CAN) DURING INSPECTION THE NOSE CONE OF ONE OF THE COMBUSTION CHAMBERS WAS FOUND BROKEN AWAY FROM THE COMBUSTION CHAMBE	R BODY.					2	L	7	2 	3T	4	T		A24EU   	E297				 
1997050800765	19970508	00765	EA  	1997	5	8	CA970203012      	1	19970124	G	3020	7SC0058012	DE-ICER BOOT    	BFGOODRICH  		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	#4 NACELLE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE86302	237483		(CAN) AFTER LANDING AND DURING WALKAROUND BEFORE TURN AROUND, PILOT NOTICED OUTBOARD OF #4 NACELLE BOOT MISSING. BOOT FO	UND ON BUTTON OF RUNWAY.					2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE	 
1997051500277	19970515	00277	EU  	1997	5	15	CA970203013      	1	19970124	G	2913	6506606	HYD PUMP        			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      		NE  					#1 SYSTEM	SHEARED SPLINE  	W				H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			CR	CRUISE         	1			CA								717722			(CAN) GREEN  HYDRAULIC SYSTEM DEPLETED IN FLIGHT. GROUND INSPECTION FOUND THE #1 GREEN SYSTEM ENGINE DRIVEN PUMP (EDP) D	RIVE SHAFT HAD SHEARED INTERNALLY. PUMP CASE LEAKED, CAUSING LOSS OF GREEN SYSTEM HYDRAULIC FLUID.					2	L	7	2 	4F			RT	A35EU   	E24NE				 
1997051500278	19970515	00278	NE  	1997	5	15	CA970203015      	2	19970119	G	7200		ENGINE          			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					#3 ENGINE	FAILED          	W				D				RETURN TO BLOCK         				K	O		FLUID LOSS                	OTHER                     		NR	NOT REPORTED   	1			CA			10955	3794 				P709477			(CAN) ON #3 ENGINE START N2 IMMEDIATELY ROSE TO 35 PERCENT THEN DROPPED TO 30 PERCENT AND FLUCTUATED. NO N1 ROTATION. OI	L QUANTITY DROPPED TO ONE GALLON. ENGINE REPLACED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997051500280	19970515	00280	WP  	1997	5	15	CA970204002      	1	19970122	G	3260	902624917	ANNUNCIATR PANEL			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					LT MLG INDICATIO	LOOSE WIRE      	W				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			CA								501795			(CAN) LEFT HAND MAIN LANDING GEAR DID NOT INDICATE DOWN AND LOCKED. MAINTENANCE TROUBLESHOOTING REVEALED A LOOSE WIRE ON	 THE REAR OF THE LH LANDING GEAR DOWN (GREEN) LIGHT SOCKET. WIRE REPAIRED.					2	L	7	2 	4R	4	T		6A6     	E282				 
1997051500281	19970515	00281	EA  	1997	5	15	CA970204004      	1	19970126	G	3260		SENSOR          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					NOSE LANDNG GEAR	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			CA			2364 					807337			(CAN) NOSE LANDING GEAR FAILED TO RETRACT ON TAKEOFF. NOSE GEAR PROXIMITY SENSOR ADJUSTED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997051500282	19970515	00282	NE  	1997	5	15	CA970204005      	2	19970123	G	7250	MS969611	BOLT            								PWA   	118   	PW118       		NE  					INTERSTAGE CASE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11982					115571			(CAN) THE ENGINE WAS SENT FOR A SCHEDULED OVERHAUL. UPON DISASSEMBLY IT WAS DISCOVERED THE ENGINE HAD POWER TURBINE DAMA	GE RESULTING FROM AN INTERSTAGE CASE BOLT FAILURE. THE ENGINE WAS PRE MOD 21175 AND THE LIBERATED BOLT HEAD INFLICTED IM	PACT DAMAGE TO ALL THE 1ST STAGE PT ROTOR BLADES AND TO THE 2ND STAGE PT STATOR LOCKING LUGS. SECONDARY DAMAGE FROM PIEC	ES OF DAMAGED PT1 BLADES WAS ALSO SUSTAINED BY THE PT STATOR AIRFOILS AND THE PT2 BLADE LEADING EDGES. IT IS THOUGHT THA	T CORROSION OF THE BOLT BELOW THE HEAD COUPLED WITH SOME FLANGE CORROSION LEAD TO THE FRACTURE OF THE BOLT.							4	T			E20NE				 
1997051500283	19970515	00283	CE  	1997	5	15	CA970206001      	1	19970124	G	7810		EXHAUST DUCT    			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					AT #3 BEARING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3950 				PCE50550			(CAN) DURING TROUBLESHOOTING OF HIGH OIL PRESSURE PROBLEM, NOTED OIL STAIN AND SMELL. FURTHER INSPECTION FOUND EXHAUST D	UCT BROKEN AWAY AT #3 BEARING COVER. POWER SECTION SENT FOR REPAIR.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997051500284	19970515	00284	EU  	1997	5	15	CA970206002      	1	19970127	G	7700	M2217BB	THRUST METER    			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 1 ENG	STUCK           	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			CA			7853 			140		9111			(CAN) CREW REJECTED TAKEOFF DUE TO #1 ENGINE THRUST INDEX ON LEFT HAND THRUST METER BEING STUCK AT 85 PERCENT AND UNABLE	 TO ADJUST. AIRCRAFT RETURNED TO BASE AND THE THRUST INDICATOR WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997051500285	19970515	00285	EU  	1997	5	15	CA970206003      	2	19970120	G	7320	CASC211	REGULATOR       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					#2 ENG FUEL FLOW	FAULTY          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA			4227 	2584 				9279			(CAN) ON TAKEOFF ROLL THE #2 ENGINE DID NOT PRODUCE TAKEOFF RATED THRUST. THE TAKEOFF WAS REJECTED. MAINTENANCE FOUND TH	E PROBLEM TO BE AN AIR LEAK. CORR UJOINT AND 3 GASKETS WERE REPLACED ON THE #2 ENGINE FUEL FLOW REGULATOR AT THE P3 CONN	ECTION. ENGINE WAS GROUND RUN SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997051500286	19970515	00286	EA  	1997	5	15	CA970206004      	1	19970122	G	3010	MS33205	CIRCUIT BREAKER 			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					ELEV HORN HEAT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								123192			(CAN) PILOT NOTED THAT THE LEFT ELEVATOR HORN HEAT CAUTION LIGHT CAME ON. HORN CIRCUIT BREAKER WAS FOUND UNSERVICEABLE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997051500287	19970515	00287	GL  	1997	5	15	CA970206005      	3	19970127	G	6110		PROPELLER       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	BALANCE	HIGH VIBRATION  	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				13   				291253R	529A		(CAN) HARTZELL PROPELLER INSTALLED AS PER STC #SA685AL. TROUBLESHOT VIBRATION SINCE INSTALLATION. INSTALLED SECOND PROP 	AND DID DYNAMIC BALANCE, THIS CHANGED THE POSITION OF VIBRATION. REMOVED PROP AND INSTALLED ZERO TIME MCCAULEY PROP. VIB	RATION GONE.				1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
1998041700423	19980417	00423	WP  	1998	4	17	CA970206006      	2	19970129	G	7314	307085046	FUEL PUMP       			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			CA				4573 				P84447			(CAN) ENGINE DRIVEN FUEL PUMP HAD NO OUTPUT PRESSURE, UNABLE TO GET START AFTER ENGINE SPOOLED DOWN FROM IDLE.  TEAR DOW	N REPORT REVEALED DAMAGED BEARING AT VANE STAGE WITH METAL IN UNIT AND ROTOR SMEARED.  PART TC:  3,248.					2	L	7	2 	4F	4	F		A3EU    	E6WE				 
1997051500288	19970515	00288	EU  	1997	5	15	CA970206008      	1	19970108	G	2910	NOR407S	VALVE BODY      		A24518001   	AMD   	FALC50	FALCON50MYST	2730106	EU  										NR 1 HYD SYS	MISSING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			CA			1857 								(CAN) AIRCRAFT LANDED WITH A COMPLETE LOSS OF #1 HYDRAULIC SYSTEM. PRESSURE REDUCING VALVE BODY FOUND CRACKED AND LEAKIN	G HYDRAULIC FLUID. TEAR DOWN INSPECTION OF VALVE FOUND BALL BEARING MISSING.					2	L	7	3 	4F				A46EU   					 
1997051500290	19970515	00290	CE  	1997	5	15	CA970206013      	1	19970109	G	8011	64150020	STARTER         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					DRIVE	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			387  					254684H			(CAN) STARTER WOULD NOT ENGAGE. FAULTY STARTER CLUTCH DAMAGED STARTER DRIVE.						1	H	7	1 	3O	3	O		3A19    	E252				 
1997051500291	19970515	00291	EA  	1997	5	15	CA970206014      	2	19970123	G	7261		O-RING          			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					C  FLANGE	WORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA								PCE40147			(CAN) "O" RING ON THE OIL PRESSURE TRANSFER TUBE AT THE "C" FLANGE WAS FOUND WORN FLAT IN ONE AREA, CAUSING OIL TO LEAK 	OUT ON TO THE EXHAUST CAN. THIS CAUSED A FLUCTUATION IN OIL PRESSURE AND TORQUE PROMOTED THE PILOT TO DO A PRECAUTIONARY	 SHUTDOWN AND RETURN TO BASE.				1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997051500292	19970515	00292	NE  	1997	5	15	CA970206019      	2	19970126	G	7220		FAN             			LKHEED	1011  	1011385114  		WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					#3 ENGINE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			38292	3239 				10321			(CAN) NO N1 ROTATION DURING START OF #3 ENGINE. LP FAN FOUND SEIZED. ENGINE REPLACED.						2	L	7	3 	4F	4	F		A23WE   	E12EU				 
1997051500293	19970515	00293	EA  	1997	5	15	CA970206020      	2	19970131	G	7314	27720007	FUEL PUMP       	SUNDSTRAND  		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					DRAIN PIPE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			CA				4505 		PE1416		CPPS61075			(CAN) AFTER TEST FLIGHT FOLLOWING 600 HOUR INSPECTION FUEL WAS SEEN COMING FROM THE DRAIN AT THE BOTTOM OF THE ENGINE. I	NSPECTION FOUND THE FUEL WAS COMING FROM THE PIPE THAT DRAINS THE AUTOMATIC FUEL CONTROL SEAL. CLOSER INVESTIGATION FOUN	D THE ENGINE DRIVEN FEUL PUMP WAS LEAKING AND THE DRAIN FOR THE FUEL SEAL WAS BLOCKED CAUSING FUE TO EVACUATE FROM THE A	FCU SEAL. BOTH THE FUEL CONTROL AND THE FUEL PUMP WERE REPLACED.			1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997051500294	19970515	00294	EU  	1997	5	15	CA970206021      	2	19970131	G	7250		BLADE           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					#2 ENG LP TURB	MISSING         	W		A		E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			29600	27348				9299			(CAN) DURING CLIMB THROUGH FL270 THE CREW HEARD A "BANG" AND FELT A VIBRATION FROM #2 ENGINE, WHILE THE ENGINE WAS STILL	 MAKING POWER. AIRCRAFT RETURNED TO THE POINT OF DEPARTURE. INITIAL INSPECTION REVEALED A LOW PRESSURE TURBINE BLADE MIS	SING. THIS ENGINE SUFFERED A SIMILAR FAILURE ON 5 JANUARY 1990. THERE IS NO RECORD OF AN SDR AT THAT OCCURRENCE.				2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997051500295	19970515	00295	NE  	1997	5	15	CA970206022      	2	19970129	G	7230	311161801	BEARING         								PWA   	120   	PW120A      		NE  					HP ROTOR	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA			16992					120767			(CAN) ENGINE WAS SENT FOR REPAIR AFTER A LOSS OF OIL PRESSURE AND AN INFLIGHT SHUTDOWN. METAL WAS FOUND IN THE REDUCTION	 GEARBOX, OIL FILTERS, CHIP DETECTORS. DISASSEMBLY OF THE ENGINE REVEALED TWO FAILURES, THE #4 BEARING AND THE AC GENERA	TOR. IT IS THE OPINION OF THE R&O SHOP THAT THE FAILURE OF THE #4 BEARING WAS THE CAUSE OF THE AC GENERATOR FAILURE.									4	T			E20NE				 
1997051500296	19970515	00296	NM  	1997	5	15	CA970210004      	1	19970123	G	2720		CIRCUIT BREAKER 			DHAV  	DHC8  	DHC8202     	2809007	NM  										RUD CONTROL	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF AND ACCELERATING THROUGH APPROXIMATELY 140 KIAS, THE RUDDER PRESSURE AND RUDDER FULL PRESSURE AND #1 RU	DDER HYDRAULIC WARNING LIGHTS CAME ON. ON DECELERATION THROUGH APPROXIMATELY 140 KIAS, THE WARNING EXTINGUISHED. LANDED 	OK. FAULTY CIRCUIT BREAKER FOUND.				2	H	7	2 	4T			RT	A13NM   					 
1997061900522	19970619	00522	CE  	1997	6	19	CA970211001      	1	19970131	G	3240	124K0016CL0150	HOSE            	BFGOODRICH  	215297      	CESSNA	500   	560CESSNA   	2076750	CE  										RT BRAKE	LEAKING         	W				L				ABORTED APPROACH        				L			NO TEST                   			AP	APPROACH       	1			CA			1245 								(CAN) PILOT CONFIRMED NO BRAKE PEDAL PRESSURE. LONG LANDING CARRIED OUT SAFELY. INSPECTION FOUND A LEAK OF HYDRAULIC FLU	ID FROM UNDER THE HOSE COVER APPROXIMATELY 1 INCH FROM THE SWAGE FITTING ON THE RIGHT HAND BRAKE FLEX HOSE. NEW HOSE INS	TALLED.				2	L	7	2 	4F			RT	A22CE   					 
1997051500299	19970515	00299	SO  	1997	5	15	CA970211002      	1	19970202	G	8120	4067870010	TURBINE SHAFT   	AIRESEARCH  	4091709001R 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENG TURBO	SHEARED         	W				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA				3    		ZGO29356		L216068A			(CAN) TURBOCHARGER WAS INSTALLED AS PART OF AN OVERHAULED ENGINE. TURBOCHARGER WAS PREOILED AND GROUND RUNS WERE SATISFA	CTORY. TWO TRAINING FLIGHTS WERE CARRIED OUT PRIOR TO THE FAILURE. PILOT REPORTED FLUCTUATING OIL PRESSURE AND SHUT THE 	ENGINE DOWN. POST FLIGHT INVESTIGATION FOUND THE TURBINE SHAFT HAD SHEARED ALLOWING THE COMPRESSOR TO DESTROY ITSELF.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997051500300	19970515	00300	NE  	1997	5	15	CA970211004      	2	19970204	G	7322	32447593	FUEL CONTROL    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					#1 ENGINE	FAULTY          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA								71718			(CAN) DURING CRUISE FLIGHT THE #1 ENGINE ROLLED BACK FROM CRUISE POWER TO APPROXIMATELY 80 PERCENT N2 AT FL390. AFTER LA	NDING THE "O" RINGS IN THE P3 PLUMBING WAS REPLACED AND THE ENGINE GROUND RUN SERVICEABLE. FOLLOWING DAY THE SAME PROBLE	M RECURRED AND THE FUEL CONTROL UNIT WAS REPLACED. THE ENGINE RUN AND TEST FLIGHT WERE CARRIED OUT SERVICEABLE AND THE A	IRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997051500301	19970515	00301	NM  	1997	5	15	CA970211005      	1	19970202	G	3220		NOSE GEAR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HYD SYS	SLOW TO EXTEND  	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			CA								120542			(CAN) ON DESCENT NOSE GEAR SLOW TO EXTEND, BUT FINALLY INDICATED DOWN AND LOCKED. EXCESSIVE AMOUNT OF AIR FOUND IN HYDRA	ULIC SYSTEM FROM MAINTENANCE ON PREVIOUS DAY (NOSE GEAR HAD BEEN REPLACED THE DAY BEFORE).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997051500302	19970515	00302	EU  	1997	5	15	CA970211006      	2	19970201	G	7260		DRIVE           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    		EU  					ACCESSORY GEARBX	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				5919 				7344			(CAN) AIRCRAFT WAS IN CRUISE FLIGHT WHEN THE PILOT REPORTED LOSS OF ACCESSORY GEARBOX ON #1 ENGINE. POST FLIGHT INSPECTI	ON FOUND THE #1 ENGINE INTERNAL DRIVE FOR THE ACCESSORY GEARBOX FAILED, RESULTING IN METAL CONTAMINATION OF THE LUBRICAT	ION SYSTEM. THE CONTAMINATION WAS WIDESPREAD AFFECTING ALL MAIN LINE BEARINGS, REDUCTION GEAR LAYSHAFTS AND PROPSHAFT, A	S WELL AS OIL PUMPS AND LOWER BEVEL DRIVES.			2	L	7	2 	3T	4	T		A24EU   	A196				 
1997051500303	19970515	00303	SO  	1997	5	15	CA970212003      	1	19970204	G	3220	9582900	LINK ASSY       	PIPER       		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	MCAULY				NLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA			5737 					307973H			(CAN) AIRCRAFT WAS ON A PILOT TRAINING FLIGHT.  PILOT SELECTED GEAR DOWN AND THE SYSTEM INDICATED DOWN AND LOCKED.  3 GR	EEN AND VISUAL IDENT THROUGH THE SIDE MIRROR.  UPON TOUCHDOWN THE NOSE GEAR COLLAPSED.  AWAITING FURTHER INFORMATION.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1997051500304	19970515	00304	CE  	1997	5	15	CA970212004      	1	19970127	G	3411		STATIC TUBE     			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY				TAIL STATIC PORT	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								503283			(CAN) SUSPECT WATER IN THE LINE, BETWEEN THE STATIC PORT AND THE SUMP, FROZE AND SPLIT THE PIPE.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
1997051500305	19970515	00305	EA  	1997	5	15	CA970212008      	2	19970130	G	7322		CARBURETOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	ICING           	W				A	B	E		UNSCHED LANDING         	EMER. DESCENT           	ENGINE SHUTDOWN         		E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L243976			(CAN) THE AIRCRAFT WAS FLYING IN -30 DEGREES CELCIUS TEMPERATURE. AFTER 30 MINUTES OF FLIGHT THE ENGINE QUIT. THE PILOT 	MANUALLY PRIMED THE ENGINE AND IT RAN AFTER EACH SHOT. POST FLIGHT INSPECTION OF THE CARBURETOR AND FILTER FOUND MANY WA	TER DROPLETS. IT IS CONCLUDED WATER IN THE FUEL, PERHAPS THROUGH CONDENSATION, CAUSED CARBURETOR ICING.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997051500306	19970515	00306	EA  	1997	5	15	CA970213008      	2	19970207	G	7532	310082903	BLEED VALVE     			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					COMPRESSOR	ORIFICE DIRTY   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1174 		9E551		PCE42076			(CAN) DURING START THE #2 ENGINE TEMPERATURE WAS HOTTER THAN #1 ENGINE. THE COMPRESSOR BLEED VALVE WAS CHANGED AND DURIN	G SUBSEQUENT STARTS THE TEMPERATURE WAS COOLER. TREND MONITORING CONFIRMED THE COOLER OPERATION.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997051500307	19970515	00307		1997	5	15	CA970213009      	4	19970207	G	3444	2300303000	DRIVE MOTOR     	COLLINS     	6221204002  	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					RADIO ALT	INTERMITTENT    	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CL	CLIMB          	1			CA						691		PCE42076			(CAN) DURING TAKEOFF ROTATION THE RADIO ALTIMETER WOULD FLAG AND NOT REACTIVATE UNTIL 25 TO 30 MINUTES LATER. SYSTEM DEA	CTIVATED. DRIVE MOTOR ASSEMBLY IN THE INDICATOR WAS FAULTY.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997051500308	19970515	00308	EA  	1997	5	15	CA970213012      	2	19970211	G	7261	3020958	RELIEF VALVE    		3026887     	BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A27      	52043	EA  					OIL SYSTEM	SCORED          	W				C	E			ABORTED TAKEOFF         	ENGINE SHUTDOWN         			O			OTHER                     			TO	TAKEOFF        	1			CA								40919			(CAN) ON TAKEOFF THE AIRCRAFT EXPERIENCED A MAJOR YAW TO THE LEFT. THE YAW WAS OF A SURGING NATURE AND THE LEFT HAND ENG	INE WAS SHUTDOWN. THE AIRCRAFT RETURNED TO ITS DEPARTURE POINT. POST FLIGHT INSPECTION FOUND THE PRESSURE REGULATOR HAD 	EXCESSIVE SCORING ON THE SEAT FACE.THE SEAT WAS REPLACED AND THEAIRCRAFT WAS GROUND RUN SERVICEABLE AND THE AIRCRAFT RET	URNED TO SERVICE.			1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997051500309	19970515	00309	NE  	1997	5	15	CA970213013      	2	19970205	G	7250	310750201	BLADE           								PWA   	PW120 	PW123       		NE  					LP TURBINE	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			6094 					123189			(CAN) THE ENGINE WAS SENT FOR REPAIR AFTER THE OPERATOR REPORTED AN LP TURBINE BLADE FAILURE. DISASSEMBLY OF THE ENGINE 	FOUND THE LP TURBINE BLADE FAILURE WAS CAUSED BY CORROSION IN THE CORE POCKETS OF 3 LP TURBINE BLADES. SECONDARY DAMAGE 	FROM THE FAILURE CAUSED DAMAGE TO THE 1ST AND 2ND STAGE PT BLADES; THE 1ST AND 2ND STAGE PT STATORS; THE REMAINING LP TU	RBINE BLADES; THE LP SHROUD SEGMENTS AND THE LP STATOR. THE #3 AND #6 BEARINGS WERE SCRAPPED AS A PRECAUTION.								4	T			E20NE				 
1997051500310	19970515	00310	NE  	1997	5	15	CA970217001      	2	19970207	G	7210	310119101	BEARING         								PWA   	120   	PW120A      		NE  					RED GRBX NR 10	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10334					120225			(CAN) THE REDUCTION GEARBOX WAS SENT FOR INVESTIGATION OF METAL CONTAMINATION AND OVERHAUL. DISASSEMBLY OF THE RED GB RE	VEALED THE SOURCE OF THE METAL CONTAMINATION WAS A SPALLED #10 BEARING. THIS BEARING IS A LIFED ITEM AND IT IS THE OPINI	ON OF THE REPAIR SHOP THAT THIS BEARING FAILED AT REACHING THE END OF ITS LIFE.									4	T			E20NE				 
1997051500313	19970515	00313	WP  	1997	5	15	CA970218001      	1	19970131	G	2750		BOLT            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					FLAP CONTROL	LOOSE           	W		A		O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA								P654059D			(CAN) UNABLE TO RETRACT FLAPS TO LESS THAN 15 DEGREES DUE TO FLAP LEVER JAMMING. TROUBLESHOOTING REVEALED FLAP CONTROL L	EVER INTERFERENCE CAUSED BY LOOSE BOLT. BOLT TIGHTENED AND LEVER MECHANISM OPERATED NORMALLY CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997051500314	19970515	00314	EA  	1997	5	15	CA970218002      	1	19970130	G	3260		BRACKET         			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG PROX SWITCH	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3984 					807194			(CAN) ON DEPARTURE CREW GOT AN AURAL MESSAGE AND AN EICAS MESSAGE. GEAR DISAGREE, NOSE DOOR OPEN. CENTERING TARGET LOOKE	D WORN. PROXIMITY SWITCH S23 BRACKET REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997051500315	19970515	00315	NE  	1997	5	15	CA970218003      	2	19970210	G	7250	50062201	TIEBOLT         								PWA   	JT9   	JT9D7R4D    	52054	NE  					LP TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				15602				107J			(CAN) THE ENGINE WAS SENT FOR REPAIR AFTER OIL WAS FOUND IN THE EXHAUST. DURING DISASSEMBLY IT WAS FOUND THAT THE 3RD ST	AGE TURBINE TIE BOLT HAD FRACTURED. SECONDARY DAMAGE CAUSED BY THE TIE BOLT FAILURE WAS THE HP TURBINE FRONT HUB; LP TUR	NBINE STAGES 3,4,5 WERE SCRAPPED. THE #3 AIRSEAL WAS REPAIRED.									4	F			E3NE				 
1997051500316	19970515	00316	SW  	1997	5	15	CA970219003      	1	19970115	G	2820	206061667001	TUBE ASSEMBLY   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			90   					CAE821536			(CAN) ALUMINUM MAIN FUEL SYSTEM SUPPLY TUBE HAS A STEEL SLEEVE BETWEEN THE "B" NUT AND THE TUBE (FLARE), THIS SLEEVE WAS	 FOUND BADLY CORRODED. THE TUBE FLARE AND ADJOINING FITTING WERE ALSO CORRODED ALMOST TO THE POINT OF FAILING.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997051500317	19970515	00317		1997	5	15	CA970219005      	4	19970209	G	6113	4393308	BULKHEAD        			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP SPINNER	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA				1566 					DJ7957		(CAN) WHILE INITIATING DESCENT THE PILOT NOTICED A CHANGE IN THE PROFILE OF THE PROPELLER SPINNER (NOSE). AFTER LANDING 	HE INSPECTED THE PROPELLER AND SPINNER AND FOUND THE BULKHEAD BROKEN. MAINTENANCE INSTALLED A NEW BULKHEAD ASSEMBLY AND 	THE AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	2 	3O				A20SO   		5	C	P33EA	 
1997051500318	19970515	00318	SW  	1997	5	15	CA970219006      	1	19970205	G	2710	2770018011	CONTROL CABLE   			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	AILERON	FRAYED          	W		A		K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			1447 					44131C	108152		(CAN) WHILE COMPLYING WITH FAIRCHILD 'B' INSPECTION, LEFT AILERON CONTROL CABLE WAS FOUND WITH THREE BROKEN STRANDS WHER	E THE CABLE RUNS THROUGH THE PHENOLIC GUIDE BLOCK ATTACHED TO THE FUSELAGE BULKHEAD AT STATION 227-271. FAA AD 87-02-02 	CALLS FOR CHECKS EVERY 400 HOURS AND REPLACEMENT AT 10,000 HOURS. THIS CABLE HAS BEEN INSPECTED AT EACH 'B' CHECK, THAT 	IS EVERY 200 HOURS AND SHOWED NO PROBLEMS UNTIL NOW.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
1997051900003	19970519	00003	EA  	1997	5	19	CA970219007      	2	19970209	G	8550	LW14728	DIPSTICK        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	ENG OIL SYS	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				84   				L491261A	FH780		(CAN) ON POST FLIGHT INSPECTION AN OIL LEAK WAS FOUND. INVESTIGATION FOUND THE OIL LEAK WAS A RESULT OF A BROKEN OIL DIP	 STICK. THE ROD HAD FALLEN OUT OF THE HANDLE DUE TO A MISSING PIN.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P52GL	 
1997051500319	19970515	00319		1997	5	15	CA970219009      	2	19970213	G	7414	D6LN3200	MAGNETO         	BENDIX      																DISTRIBUTOR GEAR	FAILURE         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						E19127					(CAN) MAJOR FAILURE OF THE DISTRIBUTOR GEAR. MAGNETO HOUSING WAY OUT OF SPECIFICATIONS. THIS IS A 2000 SERIES MAGNETO TH	AT HAS BEEN RE-IDENTIFIED AS A 3000 SERIES BY OBLITERATING AND RESTAMPING THE NAME PLATE. THE ENGINE WAS RECENTLY OVERHA	ULED.																	 
1997051500320	19970515	00320	EU  	1997	5	15	CA970219011      	2	19970129	G	7250		TURBINE BLADE   			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					AFT TURBINEWHEEL	MISSING         	W		A		A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			29603					9299			(CAN) #2 ENGINE EXPERIENCED SUDDEN VIBRATIONS THROUGH FL270. ALL ENGINE PARAMETERS WERE FINE BUT VIBRATIONS COULD BE FEL	T THROUGH THE AIRCRAFT AND POWER LEVERS. ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO ITS POINT OF DEPARTURE. POST F	LIGHT INSPECTION FOUND A BLADE MISSING FROM THE AFT TURBINE WHEEL. THE ENGINE WAS REPLACED, THE AIRCRAFT GROUND RUN SERV	ICEABLE AND THE AIRCRAFT RETURNED TO SERVICE. THE FAILED ENGINE WAS SENT TO ROLLS ROYCE FOR INVESTIGATION, FURTHER REPOR	T TO FOLLOW.		2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
1997051500321	19970515	00321	EA  	1997	5	15	CA970219013      	1	19970213	G	2421	731579	GENERATOR       			CNDAIR	CL600 	CL6002A12   	1900304	EA  	GE    	CF34  	CF341A      		NE  					IDG	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								350143			(CAN) INTEGRATED DRIVE GENERATOR OIL LEVEL FOUND LOW ON DAILY INSPECTION. CHIP DETECTOR PULLED AND FOUND METAL CONTAMINA	TED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997051500322	19970515	00322	SO  	1997	5	15	CA970219014      	1	19970209	G	3710		GASKET          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					VACUUM PUMP	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA								L286061A			(CAN) AFTER TAKEOFF THE PILOT NOTICED A DROP IN MANIFOLD AND OIL PRESSURES ON #2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE	 AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECITON FOUND THE #2 ENGINE COWLING SATURATED WITH ENGINE OIL. FURTHER INVEST	IGATION FOUND THE VACUUM PUMP GASKET WAS LEAKING. THE PUMP WAS NEWLY INSTALLED AND THE FAULTY GASKET CAME WITH THE PUMP.	 A NEW LYCOMING VACUUM PUMP GASKET P/N 8313 WAS INSTALLED AND THE ENGINE GROUND RUN SERVICEABLE.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997051500323	19970515	00323	GL  	1997	5	15	CA970219016      	1	19970203	G	6520	28135255R	GEARBOX         			ENSTRM	F28   	280         	3300502	GL  	LYC   	O360  	HIO360C1A   	41514	EA  					T/R	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			719  					RL672751A			(CAN) CHIPS FOUND ON DETECTOR DURING 100 HOUR INSPECTION.						1	G	7	1 	3O	3	O		H1CE    	1E10				 
1997051500324	19970515	00324	NE  	1997	5	15	CA970219017      	2	19970210	G	7260	M06118	GEARBOX         			LKHEED	1011  	1011385114  		WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					ACCESSORY GRBOX	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1930 					10145			ACESSORY GEAR BOX MAKING METAL						2	L	7	3 	4F	4	F		A23WE   	E12EU				 
1997051500325	19970515	00325	NE  	1997	5	15	CA970219018      	2	19970206	G	7210	310924401	BEARING         								PWA   	PW121 	PW121       	52124	NE  					RED GEARBX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9773 					121239			(CAN) THE REDUCTION GEARBOX WAS SENT FOR REPAIR AND INVESTIGATION AFTER THE OPERATOR REPORTED THE ENGINE WAS MAKING META	L. DISASSEMBLY OF THE REDUCTION GEARBOX FOUND THE CAUSE OF THE ENGINE CONTAMINATION WAS A SPALLED ROLLER OF THE #15 BEAR	ING. THE #15 BEARING ROLLERS AND OUTER RACE HAD EXTENSIVE ELECTRICAL PITTING. IT IS THE OPINION OF THE REPAIR FACILITY T	HAT THE LIKELY CAUSE OF THE FAILURE WAS A LIGHTNING STRIKE.								4	T			E20NE				 
1998120400001	19981204	00001	SW  	1998	12	4	CA970219019      	1	19970205	G	6730	RH0119	BEARING         	RONSON      	206076062003	BELL  	206   	206L        	1181522	SW  										RT HYD SERVO	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11959			RH0119					(CAN) ON DAILY INSPECTION, RT HYDRAULIC SERVO, BEARING CONNECTING TUBE ASSY 206-001-193-001, PART OF TEFLON LINING OF BE	ARING FOUND ON THE DECK AND THE REST OF THE TEFLON SLIPPED PARTLY OUT OF THE BEARING.					1	G	7	1 	3U				H2SW    					 
1997052900233	19970529	00233	NE  	1997	5	29	CA970220003      	2	19970210	G	7210	310703301	BEARING         								PWA   	120   	PW120A      		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12306					121098			(CAN) REDUCTION GEARBOX WAS SENT FOR INVESTIGATION AFTER METAL CONTAMINATION WAS FOUND IN THE ENGINE. DISASSEMBLY OF THE	 GEARBOX FOUND THE #15 BEARING SEVERELY SPALLED ON THE OUTER RACE WITH SUBSTANTIAL MATERIAL LOSS. THE #15 AND #18 BEARIN	GS BOTH HAD ELECTRICAL EROSION TYPE CHAIN PITTING TYPICAL OF LOW ENERGY ELECTRICAL DISCHARGE AND ALSO SOME DEEPER, ARCIN	G TYPE PITTING, TYPICAL OF HIGH ELECTRICAL DISCHARGE. THE MAGNETISM IN THE RGB IS RELATIVELY MINOR AND CERTAINLY NOT TYP	ICAL OF THE MAGNETIC PROFILE THAT TYPICALLY ARISES FOLLOWING A LIGHTNING STRIKE. IT IS THE OPINION OF R&O THAT THE RGB W	AS SUFFERING FROM LOW LEVEL ELECTRICAL EROSION PITTING WHICH EITHER LED TO THIS FAILURE OR WOULD HAVE CAUSED FAILURE IN						4	T			E20NE				 
1997052900234	19970529	00234	EA  	1997	5	29	CA970221003      	1	19970217	G	3241	600870005	SENSOR          			CNDAIR	CL600 	CL6002A12   	1900304	EA  										ANTI SKID	BROKEN          	W				D				RETURN TO BLOCK         				J	L		WARNING INDICATION        	NO TEST                   		TX	TAXI/GRND HDL  	1			CA				1068 							(CAN) DURING TAXI, ANTI-SKID TEST CARRIED OUT. TEST FAILED - INDICATING INBOARD FAIL. WHEEL SPEED SENSOR FOUND DAMAGED, 	AS WELL AS WIRE HARNESS.					2	L	7	2 	4F			RT	A21EA   					 
1997062600008	19970626	00008	CE  	1997	6	26	CA970221004      	1	19970218	G	2913	542088030008	PRESSURE SWITCH 			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					GEAR MOTOR	INTERMITTENT    	W				L				ABORTED APPROACH        				G	P		MULTIPLE FAILURE          	NO WARNING INDICATION     		LD	LANDING        	1			CA								291550R			(CAN) PILOT UNABLE TO GET INDICATION OF GEAR DOWN AND LOCKED. FLEW BY TOWER AND THEN LANDED SAFELY. GEAR MOTOR FOUND UNS	ERVICEABLE BUT WORKED IN THE SHOP AFTER REMOVAL. REPLACED THE PRESSURE SWITCH AND INSTALLED A DIODE AS PER SERVICE LETTE	R, IN ORDER TO EXTEND THE SWITCH LIFE.				1	H	7	1 	3O	3	O		A4CE    	E8CE				 
1997052900235	19970529	00235	EA  	1997	5	29	CA970221005      	2	19970211	G	7322	105135	CARBURETOR SCREW	FACET       	MA4SPA      	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	LOOSE           	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			950  			CK714171		RL125876TA			(CAN) THE ENGINE DID NOT STOP AFTER THE MIXTURE CONTROL WAS CLOSED. THE ENGINE WAS STOPPED BY SHUTTING OFF THE MAGS. INS	EPCTION FOUND THAT FOUR SCREWS THAT HOLD THE CARBURETOR HALVES TOGETHER WERE LOOSE AND ONE OF THE SCREWS WAS BROKEN. THE	 BROKEN SCREW WAS REMOVED AND REPLACED AND THE CARBURETOR WAS REASSEMBLED AND INSTALLED. THE ENGINE GROUND RUN SERVICEAB	LE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1998040200039	19980402	00039	CE  	1998	4	2	CA970225002      	1	19970114	G	3010	99141432	CONTROLLER      		99141432    	CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7313     	01518	WP  					FLAP ANTI ICE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			3011 					P87242			(CAN) DURING CRUISE FLIGHT, THE LEFT HAND STABILIZER ANTI-ICE FAIL LIGHT ILLUMINATED.  FLIGHT LANDED AND CONTROLLER WAS 	CHANGED.					2	L	7	2 	4F	4	F		A9NM    	E6WE				 
1997052900236	19970529	00236	EA  	1997	5	29	CA970225006      	1	19970217	G	2570		SHAFT           	DOWTY       	215750096   	CNDAIR	CL215 	CL2151A10   		EA  										DOOR UPLOCK	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1286 								(CAN) DOOR UPLOCK ACTUATOR SHAFT SHEARED WHILE MAINTENANCE WAS BEING CARRIED OUT ON WATER BOMBER SYSTEM.						2	H	7	2 	4R				A14EA   					 
1997052900237	19970529	00237		1997	5	29	CA970226003      	4	19970212	G	6113	CA4393308	BACKPLATE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25   					RL139461C	DJ11451A		(CAN) THE SPINNER BACKPLATE WAS FOUND CRACKED ON INSPECTION. THE REPORT STATES THAT THIS IS THE THIRD BACKPLATE (IDENTIC	AL PART NUMBERS) THAT HAS CRACKED ON THIS ENGINE SINCE OCTOBER 9, 1996.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997052900239	19970529	00239	EA  	1997	5	29	CA970226005      	2	19970220	G	8530	75362	CYLINDER        			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  					#1 POSITION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1444 				L1281340			(CAN) COMPRESSION CHECK AT INSPECTION REVEALED A CRACKED #1 CYLINDER. THE CRACK WAS AT THE LOWER SPARK PLUG HOLE.						1	H	7	2 	3O	3	O		A17EU   	E295				 
1997052900240	19970529	00240	EA  	1997	5	29	CA970226007      	1	19970204	G	5741	85334180	FITTING         			DHAV  	DHC8  	DHC8311     	1386006	EA  										STA. 424	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6714 								(CAN) FUSELAGE TO WING ATTACH FITTINGS AT FUSELAGE STRINGER 3 WERE CHAFED BY FLAP SECONDARY DRIVE CABLE SHEATHS.						2	H	7	2 	4T			RT	A13NM   					 
1997060500754	19970605	00754	EA  	1997	6	5	CA970226008      	1	19970204	G	5741	85334180	FITTING         			DHAV  	DHC8  	DHC8311     	1386006	EA  										STA.424	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7346 								(CAN) FUSELAGE TO WING ATTACH FITTINGS AT FUSELAGE STRINGER 3 WERE FOUND CHAFED BY FLAP SECONDARY DRIVE CABLE SHEATHS.						2	H	7	2 	4T			RT	A13NM   					 
1997052900241	19970529	00241		1997	5	29	CA970226057      	4	19970214	G	6113	57A24041	LOW PITCH STOP  			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	LH SPINNER	STRIPPED THREADS	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1029 				CS922825L	AN6527		(CAN) DURING A DAILY INSPECTION THE L/H PROPELLER SPINNER WAS FOUND LOOSE. FURTHER INSPECTION REVEALED THE LOCK WIRE SEC	URING THE PROP SPINNER TO THE LOW PITCH STOP ASSEMBLY WAS BROKEN AND THE THREADS ON THE LOW PITCH STOP WERE STRIPPED. TH	E LOW PITCH STOP WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P920	 
1997052900242	19970529	00242	EA  	1997	5	29	CA970226058      	2	19970217	G	7261	3026887	REGULATOR       			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					#1 ENG OIL PRESS	NOT ENGAGED     	W				D	E			RETURN TO BLOCK         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								PCE51808			(CAN) SHORTLY AFTER TAKEOFF THE #1 ENGINE LOST OIL PRESSURE AND HAD TO BE SHUTDOWN. INSPECTION OF THE OIL PRESSURE REGUL	ATOR FOUND THE CLIP ON THE OIL PRESSURE HOUSING WAS NOT FULLY ENGAGED. THE REGULATOR WAS DISASSEMBLED AND INSPECTED, NO 	FAULT WAS FOUND. THE REGULATOR WAS REASSEMBLED AND INSTALLED. THE ENGINE RUN-UP SERVICEABLE AND THE AIRCRAFT RETURNED TO	 SERVICE. IT WAS CONCLUDED THAT THE OIL PRESSURE REGULATOR WAS NOT PROPERLY ENGAGED AND IT CAME LOOSE AND LOST OIL AND T	ORQUE.		1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1998041700500	19980417	00500	SO  	1998	4	17	CA970226063      	1	19970219	G	3710	441CC	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31350     	7103110	SO  										VAC SYS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				1034 		47740					(CAN) VACUUM PUMP FAILED IN-FLIGHT.  SPLINE BROKEN AND DISINTEGRATED. PUMP WAS SEIZED.  SUBMITTER SUGGESTED THAT INSPECT	ION BE CARRIED OUT EVERY 500 HOURS TO DETERMINE PUMP SMOOTH OPERATION.					1	L	7	2 	3O				A20SO   					 
1997052900243	19970529	00243	EA  	1997	5	29	CA970226064      	1	19970129	G	3260	864806	PSEU            			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			CA			2379 					807343			(CAN) ON DESCENT THE PROXIMITY SYSTEM FAULT LIGHT CAME ON ALONG WITH GEAR DOWN RED LIGHTS. WHEN LANDING GEAR LEVER SELEC	TED DOWN NOTHING HAPPENED. LANDING GEAR MANUAL EXTENSION CARRIED OUT. PROXIMITY SENSOR ELECTRONIC UNIT REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997052900244	19970529	00244	WP  	1997	5	29	CA970226065      	1	19970211	G	3230		BRAKE HOSE      			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					LT MLG	MISALIGNED      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P653990D			(CAN) UNABLE TO RAISE L/H MAIN LANDING GEAR. ALSO GEAR DOOR LIGHT REMAINED ON. QRH CARRIED OUT, NIL SUCCESS. MAINTNENANC	E INVESTIGATION REVEALED UPPER FORWARD BRAKE HOSE SUPPORT HAD COME IN CONTACT WITH UPLATCH GUARD BAR. ALSO FOUND LH CEIL	ING STOP DAMAGED. REPAIRS CARRIED OUT, OLEO SERVICED, GEAR SWING CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997052900245	19970529	00245	WP  	1997	5	29	CA970226067      	1	19970213	G	3222		LANDING  GEAR   			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					NLG	OLEO FLAT       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P657363D			(CAN) AFTER TAKEOFF GEAR LEVER SELECTED UP, RED NOSE GEAR UNSAFE LIGHT REMAINED ON. NOSE GEAR APPEARED TO RETRACT PARTIA	LLY. QRH CARRIED OUT, SAME CONDITION REMAINED. GEAR SELECTED DOWN AND AIRCRAFT SAFELY LANDED. MAINTENANCE TROUBLESHOOTIN	G FOUND NOSE OLEO FLAT WITH PISTON CHROME DAMAGE. NOSE LANDING GEAR OLEO PISTON ASSEMBLY CHANGED. GEAR SERVICED AND OPER	ATIONALLY CHECKED SERVICEABLE.			2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997062600048	19970626	00048	SW  	1997	6	26	CA970226068      	1	19970218	G	6710	206001397101	PIVOT SUPPORT   			BELL  	206   	206B        	1181511	SW  										FRICTION SPLIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PIVOT SUPPORT FOUND CRACKED FROM FRICTION SPLIT TO BASE OF SUPPORT. APPROXIMATELY 1" CRACK.						1	G	7	1 	3U				H2SW    					 
1997060300002	19970603	00002		1997	6	3	CA970226069      	1	19970216	G	7120	NAS6606D62	BOLT            	BARRYCTRLS  	9505402     						GARRTT	TPE331	TPE33111U   	01514	WP  					REAR ENG MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4305 					P75077			(CAN) DURING LEFT ENGINE MAINTENANCE THE BOLT FOR REAR ENGINE MOUNT WAS FOUND SHEARED OFF WITH WEAR TO ELASTOMER MOUNT S	HANK. DELAMINATION OF ELASTOMER MOUNT ALSO FOUND.										4	T			E4WE				 
1997052900246	19970529	00246	NM  	1997	5	29	CA970226071      	1	19970218	G	3260	864202	SENSOR          	DOWTY       	8200105     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					DRAG STRUT	FAILED          	W				H	L			DEACTIVATE SYST/CIRCUITS	ABORTED APPROACH        			J			WARNING INDICATION        			AP	APPROACH       	1			CA						DCL190		120699			(CAN) DURING CLIMB, CRUISE AND DESCENT THE MAIN GEAR DOOR LIGHTS AND NOSE GEAR UNSAFE LIGHT PLUS GEAR INTRANSIT LIGHT WE	RE ON PERIODICALLY. ON APPROACH, NOSE GEAR WOULD INDICATE UNSAFE AND THEN SAFE. ALTERNATE EXTENSION CARRIED OUT. NOSE LA	NDING GEAR DOWN LOCK SENSORS AND DRAG STRUT SENSOR WERE UNSERVICEABLE. BOTH SENSORS REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997052900247	19970529	00247	CE  	1997	5	29	CA970227001      	1	19970216	G	7922	3024999	RETAINING PLATE 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					BYPASS VALVE	BROKEN          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K			FLUID LOSS                			CR	CRUISE         	1			CA			6643 					PCE81135			(CAN) OIL LEAK LED TO INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION FOUND THERMOSTATIC OIL BYPASS VALVE RETAINING PLATE BROK	EN. THIS ALLOWED OIL PRESSURE TO FORCE OUT THE PLUG WHICH LED TO AN OIL LEAK CAUSING THE INFLIGHT SHUTDOWN.					1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998041700503	19980417	00503	CE  	1998	4	17	CA970227003      	1	19970218	G	3246	3A0505901	DRAG LINK       	WIPAIR      	3730        	CESSNA	206   	TU206G      	2073357	CE  										MLG	STIFF           	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) GEAR WOULD NOT LOCK DOWN, FOUND MAIN DRAG LINK CENTER JOINT STIFF.  BOLT REMOVED AND HOLE CLEANED.  LUBED AREA AND	 REASSEMBLED.  WIPAIRE RECOMMENDED DISASSEMBLING AND CLEANING EVERY THREE YEARS.					1	H	7	1 	3O				A4CE    					 
1997052900248	19970529	00248	EA  	1997	5	29	CA970228005      	2	19970221	G	8530	LW11775	PLUG PISTON PIN 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					#5 CYLINDER	BROKEN          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	K	M	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                	OVER TEMP                 	CR	CRUISE         	1			CA			1730 					L217368A			(CAN) PILOT NOTICED RISE IN OIL TEMPERATURE AND SMOKE FROM #2 ENGINE. ENGINE WAS SHUTDOWN AND PRECAUTIONARY LANDING WAS 	CARRIED OUT. POST FLIGHT INSPECTION FOUND THE #2 ENGINE, #5 CYLINDER PISTON PIN PLUG BROKEN AND THE DEBRIS HAD SEIZED TH	E RINGS CAUSING THE CRANKCASE TO PRESSURIZE AND DISCHARGE OIL OUT OF THE OIL BREATHER PIPE.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997060500755	19970605	00755	NM  	1997	6	5	CA970228006      	1	19970130	G	2121	DSC704	CLAMP           			DHAV  	DHC8  	DHC8201     	2809001	NM  										AT DUCT	LOOSE           	W				B	I	A		EMER. DESCENT           	CABIN DEPRESSURIZATION  	UNSCHED LANDING         		D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AT APPROXIMATELY 15,000 FEET, A DUCT CONNECTION DECOUPLED AT THE RECIRCULATION FAN. THE CABIN DEPRESS	URIZED. THE CREW FOLLOWED PUBLISHED PROCEDURES AND LANDED SAFELY. THERE WERE NO INJURIES. DUCT CONNECTION HAD RECEIVED M	AINTENANCE 2 DAYS EARLIER AND NOT BEEN PROPERLY SECURED.				2	H	7	2 	4T			RT	A13NM   					 
1997060500756	19970605	00756	NE  	1997	6	5	CA970228007      	2	19970219	G	7532	310092205	HP BLEED VALVE  			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					#1 ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA				303  				PCE93184			(CAN) ON DESCENT THERE WERE TWO LOUD BANGS FROM #1 ENGINE AND A FLASH OF FLAME FROM THE ENGINE EXHAUST DUCT. AFTER FIVE 	SECONDS THIS EVENT REPEATED ITSELF. AN EMERGENCY WAS DECLARED AND AN UNEVENTFUL LANDING WAS CARRIED OUT. POST FLIGHT INV	ESTIGATION FOUND THE #1 ENGINE HIGH PRESSURE BLEED VALVE HAD FAILED. THE VALVE WAS REPLACED.				1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1997060500757	19970605	00757	EU  	1997	6	5	CA970228008      	1	19970222	G	3230	C24589000	UPLOCK BOX      			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	NOSE	FROZEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			16640			N446		120940	900533		(CAN) AIRCRAFT RETURNED TO BLOCKS AFTER LANDING BECAUSE NOSE LANDING GEAR WOULD NOT LOCK IN UP POSITION. UPLOCK BOX FROZ	EN. HEAT APPLIED TO FREE.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
1997060500758	19970605	00758	NE  	1997	6	5	CA970304005      	2	19970301	G	7200		ENGINE          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HP TURB	MAKING METAL    	W				A	E	O		UNSCHED LANDING         	ENGINE SHUTDOWN         	OTHER                   		X	B	O	ENGINE FLAMEOUT           	SMOKE/FUMES/ODORS/SPARKS  	OTHER                     	CL	CLIMB          	1			CA			1960 					71748			(CAN) DURING CLIMB AFTER TAKEOFF A LOUD BANG WAS HEARD FOLLOWED BY A FLAME OUT. THE ENGINE WAS SHUTDOWN AS PER PROCEDURE	S AND THE AIRCRAFT RETURNED TO BASE. POST FLIGHT INSPECTION FOUND FERROUS METAL LAYING IN THE TAILCONE. BOROSCOPE OF THE	 H.P. TURBINE REVEALED TIP CONTACT WITH SHROUD SEGMENTS WITH A LARGE QUANTITY OF ABRADED MATERIAL STILL REMAINING IN THE	 H.P./L.P. TURBINE AREA. THE MAIN OIL FILTER WAS CHECKED AND IT AND THE OIL WERE RETAINED FOR SOAP ANALYSIS.A LARGE QUAN	TITY OF METAL (FERROUS AND NON-FERROUS) CAN BE SEEN IN THE OIL ALONG WITH DISTINCT DISCOLORATION. NO IMPACT DAMAGE APPAR	ENT TO THE ENGINE.	1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997070100003	19970701	00003		1997	7	1	CA970305002      	4	19970219	G	2220	AH144910006	AIRSPEED IND    		AH144910006 	BOEING	727   	727171C     	1384057	NM  										COCKPIT	CALIB ERROR     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1291B					(CAN) MACH-AIRSPEED INDICATOR - RANGE 60-420 KNOTS CALIBRATED IN MPH. COMMAND SPEED, AUTO THROTTLE CALIBRATED 180 KNOTS 	OUT OF PHASE. RECALIBRATED.					2	L	7	3 	4F				A3WE    					 
1997060500760	19970605	00760	EU  	1997	6	5	CA970305003      	1	19970220	G	2720	NB452153	PEDAL BEAMS     	BNORM       		BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  					RUD PEDAL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L1281340			(CAN) DURING INSPECTION PER PBN SB 56 AND 111, FOUND PILOTS LEFT AND RIGHT RUDDER PEDAL BEAM CRACKED. ALSO FOUND JO-BOLT	S LOOSE ON THE STEERING LEVER. NOTE: NB/M/948 AND 428 HAD BOTH BEEN INSTALLED 2500 CYCLES PREVIOUSLY.					1	H	7	2 	3O	3	O		A17EU   	E295				 
1997060500762	19970605	00762	EU  	1997	6	5	CA970305005      	2	19970224	G	7322	CCU5151106A5	FUEL CONTRL UNIT			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    		EU  					#1 ENGINE	FAULTY          	W		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA				459  				7344			(CAN) SHORTLY AFTER REACHING CRUISE ALTITUDE THE RPM ON #1 ENGINE REACHED 14,500 RPM. THE PROP SYNC. WAS TURNED OFF AND 	THE RPM RETURNED TO NORMAL CRUISE RPM. A SHORT WHILE LATER WITH PROP SYNC. ON THE RPM AGAIN INCREASED, A PRECAUTIONARY L	ANDING WAS CARRIED OUT. POST FLIGHT INSPECTION FOUND THE FCU FAULTY AND THE FCU WAS REPLACED AND THE AIRCRAFT RETURNED T	O SERVICE.			2	L	7	2 	3T	4	T		A24EU   	A196				 
1999031200242	19990312	00242	NM  	1999	3	12	CA970305006      	1	19970204	G	3213	10851110000	WELD            	STINSON     	10851110000 	UNIVAR	108   	1082        	9230406	NM  	FRNKLN	6A4165	6A4165B3    	27025	EA  	MCAULY	1A170	1A170DM     	GL  	MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			2925 					31318	P80126		(CAN) THE WELD THAT HOLDS THE AXLE ATTACHMENT BUSHING TO THE LANDING GEAR LEG FAILED.  REPLACED.						1	H	7	1 	3O	3	O		A767    	E238	5	N	P857	 
1997060500763	19970605	00763	NE  	1997	6	5	CA970305007      	2	19970223	G	7200		ENGINE          			BOEING	720   	720B        	1383804	NM  	PWA   	JT3D  	JT3D1       	52039	NE  					#3 ENGINE	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			48558	15384				633053			(CAN) DURING CLIMB THE #3 ENGINE OIL PRESSURE AND TEMPERATURE INCREASED SLIGHTLY ABOVE MAXIMUM. PREVIOUS POWER SETTING W	ERE RESTORED AND THE ENGINE PARAMETERS RETURNED TO NEAR NORMAL. POST FLIGHT INSPECTION FOUND METAL IN THE N2 GEARBOX OIL	 STRAINER AND ENGINE MAIN OIL FILTER. THE ENGINE WAS REPLACED.				2	L	7	4 	4J	4	F		4A28    	1E8				 
1998050100216	19980501	00216	CE  	1998	5	1	CA970306001      	1	19970215	G	3213	07416302	FITTING         		07416302    	CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C*      	GL  	RT MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			1616 					459512	743560		(CAN) ON LANDING, RT GEAR CONTACTED SNOW BANK AND SEPARATED AT AXLE FITTING.  BROKEN GEAR SHOWED SIGNS OF CORROSION ABOU	T 1/3 DIAMETER AT INBOARD AXLE FITTING.  REPLACED.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
1998050100217	19980501	00217	CE  	1998	5	1	CA970306002      	1	19970219	G	2730	115610010325	TORQUE TUBE     			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P50876			(CAN) ELEVATOR TORQUE TUBE ATTACH CASTING CRACKED FROM INBOARD TAPER HOLE TO INBOARD EDGE OF CASTING.  REPLACED.  PART T	T: 18,624 HOURS.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997062600467	19970626	00467		1997	6	26	CA970306003      	1	19970227	G	7120		SHAFT           	LORD        	LM827SDA7   															ENG MOUNT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO DIFFERENT LORD MOUNT ASSEMBLIES USED TO MOUNT THE TPE331 ENGINE FOR THE SA226 AIRCRAFT RECEIVED AFTER OVERHAUL	 WITH FOLLOWING DISCREPANCIES. LM827-2 CENTRE SHAFT, WORN IN TWO PLACES, MAXIMUM WEAR SPOT 0.010 BELOW MINIMUM DIMENSION	 AS PER FAIRCHILD MAINTENANCE MANUAL. NIL CRACKS FOUND. THE SUPPLIED SANDWICH MOUNTS WERE INSPECTED PER MM - #1 PAD AT M	AXIMUM LIMIT. DISBONDING AND METAL RUBBER SEPARATION WAS EVIDENT WITH DEPTH OF DISBONDING REACHING 0.250" IN ONE SANDWIC	H. MAXIMUM ALLOWABLE IS 0.010. SUPPLIED WASHERS WERE STANDARD AN970D WASHERS INSTEAD OF THE 'THICK ALUMINUM' LM827-7 WAS	HER AS REQUIRED. THE OTHER MOUNT ASSEMBLY SHAFT WAS ALSO WORN IN TWO PLACES.														 
1998050100218	19980501	00218		1998	5	1	CA970306004      	4	19970227	G	3424	4644600	EJECTOR         		548092      	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					TURN/BANK	ICED            	W				D				RETURN TO BLOCK         				I			FLT. ATTITUDE INST.       			TX	TAXI/GRND HDL  	1			CA								52694			(CAN) VACUUM TURN AND BANK INDICATOR FAILED TO COME ON LINE AFTER AIRCRAFT WAS SITTING OUTSIDE AT BELOW ZERO DEGREES.  F	OUND EJECTOR TIP PLUGGED WITH ICE. HOSE REPLACED TO EJECTOR SO THAT EJECTOR TIP IS NO LONGER THE LOWEST PART OF SYSTEM.					1	L	7	2 	3T	4	T		A8EA    	E4EA				 
2000020500768	20000205	00768	CE  	2000	2	5	CA970306006      	1	19970227	G	2701	05600144	YOKE            		05600144    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3599 					L528676T	733668		(CAN) CONTROL YOKE CRACKED JUST ABOVE ELEVATOR ATTACH BEARING.  REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997060500764	19970605	00764	NM  	1997	6	5	CA970306008      	1	19970220	G	2760	A44700009	ACTUATOR        	DOWTY       		DHAV  	DHC8  	DHC8101     	2809002	NM  										LT OUTB	DEPLOYED        	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			10446			1713					(CAN) AFTER DEPARTURE THE LEFT OUTBOARD ROLL SPOILER REMAINED DEPLOYED. CREW RETURNED TO AIRPORT. LEFT OUTBOARD SPOILER 	ACTUATOR REPLACED. ACTUATOR SENT FOR STRIP DOWN.					2	H	7	2 	4T			RT	A13NM   					 
1997060500765	19970605	00765	NE  	1997	6	5	CA970306013      	2	19970227	G	7260		PACKING         								PWA   	120   	PW120A      		NE  					#5 BEARING AREA	BROKEN          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA			7234 					121319			(CAN) THE ENGINE WAS REMOVED FROM SERVICE AFTER REPORTS OF SMOKE IN THE CABIN, ONE TIME SO SEVERE IT SET OFF THE SMOKE A	LARM. DISASSEMBLY OF THE ENGINE FOUND THE #5 BEARING AREA PACKING HAD DETERIORATED AND BROKEN. THERE WAS A CONSIDERABLE 	AMOUNT OF OIL IN AREAS WHERE OIL IS NOT SUPPOSED TO EXIST. IT IS CONCLUDED THE PROBLEM HAS ARISEN FROM A COMBINATION OF 	SEAL CLEARANCE DETERIORATIONS UPSETTING THE BALANCE OF THE SECONDARY AIR SYSTEM AND THE BROKEN PACKINGS.								4	T			E20NE				 
1997060500766	19970605	00766	EA  	1997	6	5	CA970310001      	2	19970225	G	7200		ENGINE          								PWA   	PT6   	PT6A50      	52043	EA  					#4 POSITION	FAILED          	W				E				ENGINE SHUTDOWN         				X			ENGINE FLAMEOUT           			AP	APPROACH       	1			CA											(CAN) ON DESCENT THE POWER LEVERS WERE CLOSED TO INCREASE DESCENT AND THE FIRST OFFICER NOTICED THE #4 ENGINE FUEL PRESS	URE CAUTION LIGHT CAME ON. THE AUXILIARY FUEL PUMP WAS SELECTED ON. DURING FINAL TURN AT 1,500 FEET THE #4 ENGINE TORQUE	 WAS VERY LOW AND THE ENGINE FAILED. THE AIRCRAFT COMPLETED A SUCCESSFUL 3 ENGINE LANDING. THERE IS NO FURTHER REPORT.									4	T			E4EA				 
1997060500767	19970605	00767	GL  	1997	6	5	CA970310004      	3	19970307	G	6111	C34112	BEARING         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C201    	GL  	PROP BLADE	WARPED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			3229 	824  				275613R	716093		(CAN) THE C3411-2 BEARING RACE WAS INSTALLED DURING THE ASSEMBLY STAGE OF THE OVERHAUL AND DURING THE BEARING SEATING IN	SPECTION IT WAS FOUND THAT THE BEARING SEATING AREA WAS NOT CONTACTING THE PROPELLER HUB. THE BEARING WAS REMOVED AND CH	ECKED FOR FLATNESS ON A PRECISION GRANITE STONE AND AN AREA 2" LONG DID NOT CONTACT THE STONE. THE BEARING WAS REMOVED F	ROM SERVICE.			1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997061700005	19970617	00005	GL  	1997	6	17	CA970310005      	3	19970306	G	6111		BLADE           			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	TIP STATION	CORRODED        	W				O				OTHER                   				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA			5319 	2846 				657636A	E4829		(CAN) PROPELLER WAS SENT FOR 5 YEAR INSPECTION. CORROSION WAS FOUND PAINTED OVER. PROP HAD NOT BEEN INSPECTED SINCE 1970	.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1998050100220	19980501	00220	GL  	1998	5	1	CA970310006      	2	19970217	G	7230	6871643	BEARING         			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					REAR NR 2	FAILED          	W				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		LD	LANDING        	1			CA								501795			(CAN) NR 1 ENGINE SHUT DOWN AFTER LANDING DUE TO LOW OIL PRESSURE QUANTITY.  MAINTENANCE FOUND THAT THE TURBINE SECTION 	REAR BEARING SCAVENGE PUMP WAS DAMAGED AND LEAKING.  THE ENGINE TURBINE HAD SHIFTED BACK AND DAMAGED THE PUMP.  IT IS SU	SPECTED THE COMPRESSOR SECTION NR 2 BEARING HAD FAILED.  OVERHAUL FACILITY CONFIRMED THAT COMPRESSOR ROTOR BEARING HAD F	AILED ALLOWING THE COMPRESSOR ROTOR TO SHIFT FORWARD CONTACTING THE STATOR VALVE AIRSEALS AND INNER BAND.			2	L	7	2 	4R	4	T		6A6     	E282				 
1997060500768	19970605	00768	NE  	1997	6	5	CA970310008      	2	19970212	G	7260		BEVEL DRIVE GEAR								PWA   	120   	PW120A      		NE  					ACCESSORY GEARBX	FRACTURED       	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			11567					120583			(CAN) #2 ENGINE HAD A UNCOMMANDED SHUTDOWN IN CRUISE. POST FLIGHT INSPECTION FOUND THE CAUSE OF THE FAILURE WAS A FRACTU	RE OF THE ANGLE BEVEL DRIVE GEAR.										4	T			E20NE				 
1997060500769	19970605	00769	NE  	1997	6	5	CA970310009      	2	19970221	G	7260		STARTER DIRVE   								PWA   	PW121 	PW121       	52124	NE  					ACCESSORY GEARBX	BROKEN          	W				E				ENGINE SHUTDOWN         				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA								124688			(CAN) DURING CRUISE THE #2 ENGINE WAS REPORTED TO HAVE A LOSS OF TORQUE. SUBSEQUENT ATTEMPTS TO REGAIN POWER RESULTED IN	 ENGINE GRINDING NOISE WITH SMOKE IN THE CABIN AND A LOSS OF OIL PRESSURE. THE ENGINE WAS SHUTDOWN. POST FLIGHT INSPECTI	ON FOUND A BROKEN STARTER DRIVE GEAR.									4	T			E20NE				 
1997060500770	19970605	00770	NE  	1997	6	5	CA970310010      	2	19970226	G	7313		FUEL NOZZLES    								PWA   	PW120 	PW124B      		NE  					#1 ENGINE	LEAKING         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			9874 	7832 				124367			(CAN) ON AIRCRAFT ROTATION THE #1 ENGINE TORQUE FELL TO ZERO. THE PILOT SATISFACTORILY COMPLETED A SINGLE ENGINE GO AROU	ND. GROUND INSPECTION REVEALED A HEAVY FUEL LEAK FROM THE FUEL MANIFOLD DRAIN. THIS WAS THE FIRST FLIGHT AFTER A FUEL NO	ZZLE CHANGE. IT WAS REPORTED THAT A FUEL LEAK CHECK HAD BEEN CARRIED OUT AFTER THE FUEL NOZZLE CHANGE.									4	T			E2ONE				 
2000020500769	20000205	00769	CE  	2000	2	5	CA970312001      	1	19970219	G	5610	5042006924	WINDSHIELD      		5042006924  	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P50876	BU3196		(CAN) PILOT'S WINDSHIELD CRACKED IN UPPER RIGHT CORNER POSSIBLY STARTING AT SCREW HOLE APPROXIMATELY 3 INCHES LONG AFTER	 REMOVAL. REPLACED.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
1997060500772	19970605	00772	NE  	1997	6	5	CA970312008      	2	19970304	G	8530	ST90P10ER	CYLINDER        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					#5 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1263 				204816			(CAN) DURING INSPECTION THE #5 CYLINDER WAS FOUND CRACKED FROM THE FRONT SPARK PLUG HOLE TO THE REAR SPARK PLUG HOLE, AC	ROSS THE TOP OF THE CYLINDER BETWEEN THE COOLING FINS. THE CYLINDER WAS REPLACED.					1	H	7	1 	3R	3	R		A806    	5E1				 
1997060500773	19970605	00773	NE  	1997	6	5	CA970314003      	2	19970308	G	7322	3028325	AIR LINE        			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					P3 FILTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PS62080			(CAN) #2 ENGINE WOULD NOT START IN AUTO MODE. P3 AIR LINE WAS FOUND BROKEN FROM THE P3 AIR FILTER HOUSING. NEW PART INST	ALLED.					1	G	7	1 	4U	4	U		H4SW    	E22EA				 
1997060500774	19970605	00774	GL  	1997	6	5	CA970314004      	3	19970307	G	6111	S90AT4	PROP BLADE      			CESSNA	185   	A185E       	2072818	CE  						MCAULY	2A34C	D2A34C58    	GL  	LEADING EDGE	CORROSION       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1299 	588  					744911		(CAN) LIGHT EROSION/CORROSION FOUND ON THE LEADING EDGE OF THE PROPELLER BLADE DURING INSPECTION. THE SUBMITTER SUGGESTS	 THAT THIS SHOULD HAVE BEEN TRIMMED OUT.					1	H	7	1 	3O				3A24    		5	C	P3EA	 
1997070300241	19970703	00241	EA  	1997	7	3	CA970314005      	1	19970307	G	2430	720846B	GEN CONTROL UNIT	SUNDSTRAND  		CNDAIR	CL600 	CL6001A11   	1900302	EA  										NR 2 APU GEN	FAILED          	W				L				ABORTED APPROACH        				G	H	I	MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   	FLT. ATTITUDE INST.       	AP	APPROACH       	1			CA											(CAN) DURING FLIGHT APU STARTED AND STABILIZED. THE #2 AC ESSENTIAL BUS WAS KNOCKED OFF LINE. APU GENERATOR CONTROL UNIT	 REPLACED AS WELL AS #2 GENERATOR CONTROL UNIT.					2	L	7	2 	4F			RT	A21EA   					 
1997060500775	19970605	00775	NE  	1997	6	5	CA970318005      	2	19970303	G	7322		FUEL CONTRL UNIT	BENDIX      		PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	O		ENGINE STOPPAGE           	OTHER                     		CL	CLIMB          	1			CA			5871 	2870 				80882			(CAN) ENGINE TORQUE AND TEMPERATURE CONTINUED TO INCREASE AS THROTTLE WAS RETARDED. PILOT SELECTED THROTTLE TO OFF POSIT	ION, TEMPERATURE STILL INCREASED. ENGINE WAS SHUTDOWN. POST FLIGHT INSPECTION FOUND FUEL CONTROL UNIT FAULTY. FCU WAS RE	PLACED.				1	L	7	2 	4T	4	T		A23SO   	E4EA				 
1997060500776	19970605	00776	NE  	1997	6	5	CA970319001      	2	19970310	G	7320	511749	TUBE ASSY       			BOEING	737   	7372A3      	138448A	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					PT 7 MANIFOLD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								665233			(CAN) #2 ENGINE E.P.R. GAUGE WAS READING LOW. MAINTENANCE FOUND THE PT7 MANIFOLD LINE BROKEN. THE LINE WAS REPLACED AND 	THE ENGINE GROUND RUN SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	4F	4	F		A16WE   	E2EA				 
1997060500777	19970605	00777	NE  	1997	6	5	CA970319003      	2	19970303	G	7250	3040911D	CT DISK         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3A     	NE  	DISK PLATFORM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1835 					PCE114295	HJ332		(CAN) DURING HSI THE CT DISK ASSEMBLY WAS FOUND RUBBING ON THE CT AIR SEAL. FURTHER INSPECTION FOUND THAT EIGHT BLADE RO	OTS ON THE OPPOSITE SIDE OF THE DISK ALONG WITH THE DISK PLATFORM WERE GROOVED. THE DEPTHS OF THE GROOVES WERE TO AN UNA	CCEPTABLE LIMIT. THE CT DISK ASSEMBLY AND THE AIR SEAL WERE REPLACED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
1997070300264	19970703	00264		1997	7	3	CA970319004      	1	19970313	G	3246	44	SPREADER BAR    	EDOFLOATS   	442425      															FLOAT REAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEVERE INTERGRANULAR CORROSION AND A 12" LONG CRACK FOUND IN THE REAR SPREADER BAR. SUBMITTER NOTES IT WAS DIFFICU	LT TO FIND BECAUSE ALL BUT 1" TO 2" WAS INSIDE THE FLOAT. DATE OF FLOAT MANUFACTURE WAS 1946.																		 
1997060500778	19970605	00778	SO  	1997	6	5	CA970325001      	2	19970304	G	8530	653446A11	CYLINDER ASSY   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	INTAKE PORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1173 				519163H	820491		(CAN) DURING INSPECTION FUEL STAINS WERE FOUND AT THE COOLING FIN AREA ON ONE OF THE CYLINDERS. THE CYLINDER WAS REMOVED	. FURTHER INVESTIGATION REVEALED A CRACK STARTING ABOVE THE VALVE SEAT UP AND TOWARD THE INTAKE PORT. THE CYLINDER WAS R	EPLACED.				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997060500779	19970605	00779	SO  	1997	6	5	CA970325002      	2	19970313	G	8530	653446A11	CYLINDER ASSY   			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	INTAKE PORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1200 				290342R	950419		(CAN) DURING INSPECTION FUEL STAINS WERE FOUND ON ONE CYLINDER OF THE LH ENGINE AND ONE CYLINDER OF THE RH ENGINE IN THE	 AREA OF THE COOLING FINS. FURTHER INSPECTION FOUND THE CYLINDERS WERE CRACKED. MAINTENANCE HAVE CONCLUDED THE CYLINDERS	 ARE CRACKING AS A ARESULT OF SHOCK COOLING. IT WAS REPORTED THAT THE AIRCRAFT WAS OPERATED AT VERY LOW AMBIENT TEMPERAT	URES. THE CYLINDERS WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997060500780	19970605	00780	EA  	1997	6	5	CA970325005      	2	19970307	G	8520	SL72877	TAPPET BODY     								LYC   	O540  	LTIO540J2BD 	41533	EA  					CAM LOBES	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				49   				RL13968A			(CAN) DURING INSPECTION FERROUS AND NON-FERROUS METAL WAS FOUND IN THE OIL FILTER. CAMSHAFT LOBES #2 EXHAUST AND #5 AND 	#6 INTAKE AND CORRESPONDING TAPPET BODIES STARTING TO FAIL FROM SPALLING. REAR SECTION OF FRONT MAIN BEARING OVERHEATED 	WITH SURFACE MATERIAL MELTED, ROLLING AND FLAKING OFF THE BACKING. THESE FAILURES ARE NORMALLY ASSOCIATED WITH LACK OF L	UBRICATION. AVCO LYCOMING RECOMMENDS AN OIL ADDITIVE BE ADDED.								3	O			E14EA				 
1997060500781	19970605	00781	EA  	1997	6	5	CA970325006      	2	19970217	G	8520	SL13885	FRONT BEARING   	SUPAIRPART  							LYC   	O540  	TIO540A2C   	41532	EA  					CRANKSHAFT	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			49   					L744561A			(CAN) PROP HARD TO CONTROL IN FLIGHT. INSPECTION FOUND NON FERROUS METAL IN THE MAIN OIL FILTER AND THE FINGER SCREENS. 	THE REAR SECTION OF THE FRONT MAIN BEARING INSIDE DIAMETER OVERHEATED WITH SURFACE MATERIAL MELTING, ROLLING AND FLAKING	 OFF THE BEARING BACK. PROP GOVERNOR OIL PRESSURE IS TAKEN FROM THE FRONT MAIN OIL GALLEY, DIRECTING OIL THROUGH THE CEN	TRE SECTION OF THE FRONT MAIN BEARING THROUGH THE CRANKSHAFT AND TO THE PROPELLER. FULL FEATHERING CHECK OF THE PROP IS 	NOT RECOMMENDED ON THE GROUND ON A NEWLY OVERHAULED ENGINE, CONTINUING TO DO SO CAN CAUSE LOSS OF OIL TO THE REAR HALF F	RONT MAIN BEARING. THIS TYPE OF FAILURE IS CONSISTANT WITH LACK OF LUBRICATION DURING COLD WEATHER & EXERCISING THE PROP						3	O			E14EA				 
1997060500782	19970605	00782	EA  	1997	6	5	CA970325007      	2	19970220	G	8520	SL72877	TAPPET BODY     	SUPAIRPART  	SL19340     						LYC   	O540  	TIO540J2BD  	41532	EA  					CAM EXH LOBE	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			930  			HO15		L664861A			(CAN) PILOT REPORTED HIGH EGT ON DESCENT AFTER MAKING A POWER REDUCTION. INSPECTION FOUND THE CAMSHAFT #1 EXHAUST LOBE A	ND #1 TAPPET BODY HAD 1/3 OF THE FACE MATERIAL WORN OFF AND RESTRICTING THE EXHAUST VALVE FROM FULL MOVEMENT. THE MAIN O	IL FILTER HAD METAL CONTAMINATION. THE ENGINE MANUFACTURER CLAIMS THE CAMSHAFT LOBE PITTED AND WORN DUE TO CONTACT BETWE	EN THE LOBE AND A SPALLED OR CHIPPED LIFTER BODY. LOBE DISTRESS IS SECONDARY AND BEGINS AFTER LIFTERS BECOME SPALLED BEC	AUSE OF INSUFFICIENT LUBRICATION FROM EITHER COLD STARTS AND RUN UPS DURING COLD WEATHER OR FROM OVER DILUTION. AVCO LYC	OMING RECOMMENDS THE USE OF AN OIL ADDITIVE P/N 16702 ANTI-SCUFFING AGENT TO REDUCE WEAR. S.I. 1409 REFERS.						3	O			E14EA				 
1997061200848	19970612	00848	GL  	1997	6	12	CA970325011      	3	19970401	G	6111	90DCA2	BLADE           			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LEADING EDGE	EROSION         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			952  					462382	750693		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADE FOUND ERODED ON THE LEADING EDGE.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997061200850	19970612	00850	GL  	1997	6	12	CA970325013      	3	19970318	G	6114	4715	HUB             													MCAULY	2A34C	2A34C*      	GL  	RETAIN THREADS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1079 	333  					763171		(CAN) INSPECTION FOUND THE PROPELLER HUB CRACKED AT THE BLADE RETENTION THREADS. THE BLADE RETENTION NUT WAS ALSO CRACKE	D.															5	C	P3EA	 
1997070300273	19970703	00273		1997	7	3	CA970325017      	4	19970307	G	2562	006062	BATTERY PACK    	DORNEMARGLN 	DMELT61     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ELT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						53639		L758039A			(CAN) ELT BEING CHECKED FOR RECERTIFICATION. BATTERY PACK WAS 2 YEARS OVERDUE AND WAS VERY BADLY LEAKING. BOTTOM OF BATT	ERY CASE WAS COMPLETELY CORRODED, THE SIDEWALL HAD A HOLE ABOUT 1 INCH IN DIAMETER.					1	L	7	1 	3O	3	O		2A13    	E274				 
2000020500775	20000205	00775	CE  	2000	2	5	CA970325020      	1	19970317	G	2820	AN9173D	TEE             			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								570278	851411		(CAN) TEE FITTING UNDER THE LEFT FLOOR CRACKED LOOSING A SMALL AMOUNT OF FUEL.   REPLACED.						1	H	7	1 	3O	3	O		3A24    	E5CE				 
1998050100228	19980501	00228	CE  	1998	5	1	CA970326006      	1	19970303	G	7160	055018016	ARM ASSY        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CARB HEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2242 					L1394339A			(CAN) DURING RUN-UP, CARBURETOR HEAT INOPERATIVE.  CARBURETOR HEAT CONTROL ARM BROKEN.  REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000020500776	20000205	00776	SO  	2000	2	5	CA970326011      	1	19970314	G	3250	1497676	ARM             			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	NLG STEERING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6892 					L104448	BP3110		(CAN) A/C VERY HARD TO STEER ON TAXIING.  ACCUMULATION OF DUST AND DIRT IN STEERING ARM BUSHINGS CAUSED BINDING IN STEER	ING LINKAGE.  CLEANED AND LUBRICATED.					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997070300286	19970703	00286	NM  	1997	7	3	CA970401001      	1	19970320	G	2720	69382933	CENTERING UNIT  	BOEING      	69382933    	BOEING	737   	737*        		NM  										RUDDER FEEL	IMPROPER ASSY   	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			49080	800  		9998					(CAN) DURING A ROUTINE AD INSPECTION A ROUGHNESS WAS DETECTED IN THE RUDDER FEEL AND CENTERING UNIT. THE HOUSING ASSEMBL	Y WAS INSTALLED IN THE REVERSE POSITION ON THE CENTERING UNIT. THE UNIT HAD BEEN RECENTLY OVERHAULED.					2	L	7	2 	4F			RT	A16WE   					 
1998031900903	19980319	00903	CE  	1998	3	19	CA970401008      	1	19970311	G	2810		FILLER TUBE     			CESSNA	172   	172M        	2072418	CE  										RT WING OUTB	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1400 								(CAN) SMALL AMOUNT OF FUEL STAIN NOTED AT INBOARD LOWER TRAILING EDGE OF RIGHT HAND WING.  USUALLY OCCURRED AFTER FILLIN	G TANK.  INSPECTION FOUND A CRACK IN THE WELD AT THE FILLER TUBE.					1	H	7	1 	3O			NT	3A12    					 
1997061200859	19970612	00859	GL  	1997	6	12	CA970401010      	3	19970324	G	6111		BLADE           													MCAULY	1A103	1A103TCM    	GL  	PROP	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									775237		(CAN) PROPELLER BLADE WAS RECEIVED BENT. ATTEMPT TO STRAIGHTEN BLADE WAS MADE PRIOR TO RECEIPT AT PROP SHOP. BLADE WAS B	ENT BEYOND LIMITS.															5	N	P50GL	 
1998050100230	19980501	00230	CE  	1998	5	1	CA970401014      	1	19970324	G	3222	96B200163	STRUT           		96B200163   	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2454 					287103R			(CAN) CRACK FOUND IN OLEO TO STRUT CASTING.  REPLACED.						1	L	7	2 	3O	3	O		3A16    	E5CE				 
1997061200861	19970612	00861	GL  	1997	6	12	CA970402002      	3	19970325	G	6111	D5044	BLADE           			CESSNA	177   	177RG       	2073709	CE  						MCAULY	2D34C	B2D34C207   	GL  	LEADING EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2157 	595  					735063		(CAN) STONE DAMAGE ON THE LEADING EDGE AND THE FACE OF THE PROPELLER BLADE. THE BLADE REQUIRED FILING AND GRINDING. THE 	PROPELLER HUB BREATHER SEALANT WAS MISSING.					1	H	7	1 	3O				A20CE   		5	C	P7EA	 
1997061200862	19970612	00862	GL  	1997	6	12	CA970402003      	3	19970326	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	LEADING EDGE	EROSION         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1062 						730409		(CAN) INSPECTION FOUND LIGHT EROSION ON THE LEADING EDGE OF THE PROPELLER. FILING WAS REQUIRED TO REMOVE THE EROSION.																5	N	P910	 
1997070300290	19970703	00290	NM  	1997	7	3	CA970402004      	1	19970324	G	7603		STOP MECHANISM  	DHAV        	87610018003 	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LT PWR LEVER	MISALIGNED      	W				E				ENGINE SHUTDOWN         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			21897					0			(CAN) DURING ENGINE RUN ON GROUND, THE PILOT BRISKLY BROUGHT BACK THE LEFT POWER LEVER. THE LEVER PASSED THROUGH FLIGHT 	IDLE GATE STOP AND CONTINUED INTO THE BETA RANGE. AIRCRAFT MANUFACTURER INVESTIGATE AND FOUND THE MISALIGNMENT WITH POWE	R LEVER STOP WHICH WAS THERE SINCE MANUFACTURE. A NEW UNIT INSTALLED P/N 87610018-007.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997061200863	19970612	00863	NE  	1997	6	12	CA970407001      	2	19970325	G	7250	414129001	PT ROTOR        			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					ROTOR WHEEL	BLADES DISPLACED	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			676  	203  				43085CE			(CAN) DURING INSPECTION THE POWER TURBINE ROTOR WAS FOUND TO HAVE SOME OF THE TURBINE BLADES DISPLACED AXIALLY BEYOND LI	MITS. ALL BLADES BEYOND LIMITS HAD MOVED AFT. THE ENGINE WAS REMOVED FROM SERVICE AND A ZERO TIME TSO ENGINE INSTALLED.					1	G	7	1 	3U	3	U		H9EU    	E5NE				 
1997061200864	19970612	00864	EA  	1997	6	12	CA970407004      	2	19970326	G	8520	76097	CAMSHAFT        								LYC   	O320  	O320E2D     	41508	EA  					LOBES	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1754 					L1993027A			(CAN) INSPECTION FOUND CAMSHAFT LOBES SPALLED AND TAPPET BODIES WERE PITTED. THE SPALLING ON THE LOBES WAS A RESULT OF C	ORROSION ON THE LOBES AND ON THE TAPPET BODIES. THE CORROSION WAS A RESULT OF LONG PERIODS OF ENGINE INACTIVITY AND NO E	VIDENCE OF INHIBITING BEING CARRIED OUT. THIS ENGINE HAS BEEN IN SERVICE SINCE 1968 AND HAS ACCUMULATED 1745 HOURS.									3	O			E274				 
1998031900905	19980319	00905	SW  	1998	3	19	CA970407005      	1	19970306	G	2821	112B	NIPPLE          		20911       	BBAVIA	7     	7ECA        	21101NN	SW  										FIREWALL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5936 								(CAN) GASCOLATOR FOUND LOOSE IN ITS MOUNTING BRACKET.  NIPPLE REMOVED AND FOUND CHAFED 90 TO 95 PERCENT THROUGH THE WALL	 FROM THE FIREWALL AS THE NIPPLE PASSES THROUGH A HOLE IN FIREWALL. DESIGN OF GASCOLATOR DOES NOT PERMIT USE OF BULKHEAD	 FITTING TO SECURE UNIT AS IT PASSES THROUGH THE FIREWALL.				1	H	7	1 	3O				A759    					 
1997061200865	19970612	00865	GL  	1997	6	12	CA970407006      	3	19970326	G	6111	FL7666A2	BLADE           			CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LEADING EDGE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			495  	281  				L716951A	CH14770		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE LEADING EDGE ERODED/CORRODED. FILING AND DRESSING OUT REQUIRED.						1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P920	 
1997061200866	19970612	00866	GL  	1997	6	12	CA970407007      	3	19970326	G	6114	B24573	FORK            			CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	WORN OUT        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			495  	281  				L716951A	CH14770		(CAN) INSPECTION FOUND PROPELLER FORK WORN.						1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P920	 
1997061200867	19970612	00867	GL  	1997	6	12	CA970407008      	3	19970327	G	6114	3921	HUB             			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	PROP	THREADS FLATENED	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1009 					315475	814635		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION AND HUB THREADS WERE FOUND FLATTENED, DUE TO REMOVING AND INSTALLING T	HE PROPELLER.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1997061200868	19970612	00868	GL  	1997	6	12	CA970407009      	3	19970327	G	6111	82NFA6	BLADE           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	LEADING EDGE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1009 					315475	814635		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION AND THE BLADES WERE FOUND ERODED AND REQUIRED FILING. THE TIP ANGLES W	ERE OUT OF SPECIFICATIONS AND REQUIRED TWISTING.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1997070300291	19970703	00291	NE  	1997	7	3	CA970407012      	3	19970325	G	6114	538867	HUB             													HAMSTD	43D	43D50       	NE  	BARREL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									202016		(CAN) INSPECTION FOUND THE HUB BARREL LOOSE AND SCORED FROM WORKING AGAINST THE BARREL SUPPORTS. THE SHIM SIZES WAS INCR	EASED AND THE INTERFERENCE FIT WAS RESTORED. SERVICE BULLETIN #632B REFERS.															6	C	P8879	 
1997070300292	19970703	00292	GL  	1997	7	3	CA970407013      	3	19970327	G	6111	L82NFA6	BLADE           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C509   	GL  	LEADING EDGE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1009 					315475	814786		(CAN) INSPECTION FOUND PROPELLER LEADING EDGE ERODED/CORRODED, WHICH REQUIRED FILING. THE BLADE TIP ANGLES WERE OUT OF S	PECIFICATIONS AND REQUIRED TWISTING.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P22EA	 
1997070300301	19970703	00301	EA  	1997	7	3	CA970408008      	1	19970331	G	5230	75230413001	FITTING ASSEMBLY	DHAV        		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					FWD PIN MECH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26190					0			(CAN) CRACKED BAGGAGE DOOR FITTING AT LOWER FORWARD PIN. FOUR AIRCRAFT FOUND WITH SAME PROBLEM.						2	H	7	4 	4T	4	T		A20EA   	E4EA				 
1997071700371	19970717	00371	EA  	1997	7	17	CA970408011      	1	19970331	G	5411	C6W151071	FRAME           	DHAV        	C6W100311   	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					RH STA 66.76	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25983	25983							(CAN) DURING INSPECTION AND ENGINE CHANGE, FOUND INTER-GRANULAR CORROSION ON FRAME ASSEMBLY ON RIGHT HAND NACELLE AFT OF	 FIREWALL. SEVERE CORROSION PITTING NOTED ON WING NOSE SPAR LEADING EDGE WHERE THE NACELLE STRUCTURE ATTACHES BETWEEN ST	A. 97.50 AND 122.50.				1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1998041700506	19980417	00506	NM  	1998	4	17	CA970408013      	1	19970316	G	6220	A1541	BEARINGS        			ROBSIN	R22   	R22BETA     		NM  										MAST/HUB	WORN            	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			1708 								(CAN) VIBRATION REPORTED.  ROTOR HEAD DISMANTLED.  AT THE ATTACHMENT POINT OF THE HUB TO THE MAST, THE BEARINGS (A-106-5	 AND A-648-1) AS WELL AS THE RINGS (A-152-1) WERE EXCESSIVELY WORN.  THE TWO BEARINGS (A-648-1) WERE OUT OF ROUND TO THE	 EXTENT OF DAMAGING THE M/R HUB (A-154-1) BEYOND REPAIR.				1	G	7	1 	3O				H10WE   					 
1998050100231	19980501	00231	SO  	1998	5	1	CA970408015      	1	19970327	G	3230	41789000	FORK            			PIPER 	PA31  	PA31        	7103102	SO  										RT MLG	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) RIGHT MAIN LANDING GEAR REMAINED DOWN AND LOCKED ON RETRACTION.  RT MLG LOCK ROD FORK BROKE POSSIBLY ON UP SELECTI	ON.  REPLACED.					1	L	7	2 	3O				A20SO   					 
1997072400917	19970724	00917	EA  	1997	7	24	CA970408017      	1	19970331	G	2520		WOOD VENEER     			CNDAIR	CL600 	CL6002B16   	1900305	EA  										CABIN INTERIOR	UNTREATED       	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) COMPLIANCE TO REQUIREMENTS OF FAR 25.853(A), APPENDIX F, PARAGRAPH (A)(1)(I) FOR 60 SECOND BURN TEST CANNOT BE FUL	LY DEMONSTRATED FOR WOOD VENEER. WOOD VENEER INSTALLED IN CL6002B16 AIRCRAFT AS NOT TREATED WITH FLAME RETARDANT.  34 RE	PORTS IN CANADIAN DATA BASE CONTROL NUMBERS 970408017 THRU 970408051.				2	L	7	2 	4F			RT	A21EA   					 
1997071700375	19970717	00375		1997	7	17	CA970409004      	1	19970402	G	3010	153212A	DEICE VALVE     	BENDIX      																DRAIN HOLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						RF3960					(CAN) DEICE DISTRIBUTION VALVE FAILED BECAUSE OF CORROSION. CORROSION CAUSED BY ACCUMULATION OF MOISTURE-DRAIN HOLE PLUG	GED BY POTTING COMPOUND USED FOR INSTALLATION OF ELECTRICAL HEATERS.																		 
1997071700377	19970717	00377	GL  	1997	7	17	CA970409006      	3	19970403	G	6111		FERRULE         			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A36C	2A36C29     	GL  	PROPELLER	MISDRILLED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			3417 	108  				478557K	62911		(CAN) ON INSPECTION ONE OF THE PROPELLER FERRULE WAS FOUND TO HAVE FIVE HOLES. THE MAXIMUM IS FOUR.						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P880	 
1997072200002	19970722	00002	GL  	1997	7	22	CA970409007      	3	19970403	G	6110		PROPELLER       			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROP ASSY	CORROSION       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			920  	596  				L170455A	BG4669		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.						1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
1997072200003	19970722	00003	GL  	1997	7	22	CA970409008      	3	19970403	G	6114		PROPELLER       			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	HUB	CORROSION       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			920  	596  				L170455A	BG4670		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. HUB CORRODED AND REQUIRED REWORK.						1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
1998031900907	19980319	00907	SO  	1998	3	19	CA970409012      	1	19970402	G	2730	AN34	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										BUNGEE SPRING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10201								(CAN) WHILE DOING SB 626C, ON REMOVAL OF OLD ELEVATOR DOWN SPRING AND LINK, BOLT AN3-4 RETAINING LINK TO EYEBOLT ON TUBE	 ASSEMBLY, (P/N 40847-00) WAS FOUND QUITE WORN DUE TO MISSING WASHER BETWEEN NUT AND EYEBOLT AND IMPROPER TORQUING.					1	L	7	2 	3O				A20SO   					 
1997071700401	19970717	00401	EA  	1997	7	17	CA970421033      	1	19970403	G	3610	C6VW10253	DUCT            			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT ENG FIREWALL	CRACKED         	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCE42076			(CAN) DURING CRUISE THE PNEUMATIC LOW PRESSURE LIGHT CAME ON INDICATING A LEAK IN THE SYSTEM. THE CREW SHUT OFF THE BLEE	D AIR SYSTEM. MAINTENANCE FOUND A CRACKED DUCT AFT OF THE LEFT ENGINE FIREWALL.					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997071700402	19970717	00402	NM  	1997	7	17	CA970421034      	1	19970403	G	2420	902F2425	PANEL           	WESTINGHOUSE		BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					NR 2 GEN	INTERMITTENT    	W				H				DEACTIVATE SYST/CIRCUITS				L			NO TEST                   			CR	CRUISE         	1			CA			2540 	2540 		PL1522		P653620B			(CAN) DURING FLIGHT #2 GENERATOR TRIPPED OFF LINE DUE TO UNDER EXCITATION AND UNDER FREQUENCY. GENERATOR CONTROL PANEL R	EPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997071700403	19970717	00403	EA  	1997	7	17	CA970421035      	1	19970403	G	2430	1N1184	DIODE           			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					AUX BATTERY	OPEN CIRCUIT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE42076			(CAN) DURING FIRST START OF THE DAY, R/H ENGINE STARTED OK, BUT COULD NOT START 2ND ENGINE. AUXILIARY BATTERY BUSS DIODE	 FOUND FAILED PREVENTING START RELAYS FROM OPERATING AFTER THE AUXILIARY BATTERY HAD LOST ITS CHARGE					1	H	7	2 	3T	4	T		A9EA    	E4EA				 
1997070300303	19970703	00303	EA  	1997	7	3	CA970421065      	1	19970331	G	5230	75230413001	FITTING ASSEMBLY	DHAV        		DHAV  	DHC7  	DHC7*       		EA  	PWA   	PT6   	PT6A50      	52043	EA  					FWD PIN MECH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			26115					0			(CAN) CRACKED BAGGAGE DOOR FITTING AT LOWER FORWARD PIN. FOUR AIRCRAFT FOUND WITH SAME PROBLEM.						2	H	7	4 	4T	4	T	RT	A20EA   	E4EA				 
1997070300304	19970703	00304	EA  	1997	7	3	CA970421066      	1	19970331	G	5230	75230413001	FITTING ASSEMBLY	DHAV        		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					FWD PIN MECH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33157					0			(CAN) CRACKED BAGGAGE DOOR FITTING AT LOWER FORWARD PIN. FOUR AIRCRAFT FOUND WITH SAME PROBLEM.						2	H	7	4 	4T	4	T		A20EA   	E4EA				 
1997071700411	19970717	00411	EA  	1997	7	17	CA970421074      	3	19970401	G	6111		BLADE           			PIPER 	PA22  	PA22        	7102202	SO  						SNSNCH	74DM	M74DM       	EA  	BLADE DECALS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									26020		(CAN) AIRWORTHINESS DIRECTIVE 66-23-02, ONE TIME NON REPETITIVE AD ONLY PARTIALLY COMPLIED WITH. CORROSION FROM WATER BA	SED DECALS STILL ON THE BLADES. THIS IS THE FIRST SHOP VISIT FOR THIS PROPELLER SINCE IMPORT INTO CANADA IN 1967.					1	H	7	1 	3O				1A6     		5	N	P88614	 
1997071700414	19970717	00414	EA  	1997	7	17	CA970421077      	3	19970401	G	6111		BLADE           													SNSNCH	74D	74DM        	EA  	WIDTH	BELOW SPEC      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4899 	1600 					K38628		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE FOUND BELOW MINIMUM WIDTH.																5	N	P88614	 
1997071700415	19970717	00415	GL  	1997	7	17	CA970421078      	3	19970410	G	6111		BLADE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FACE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1515 	1515 				RL449376T	82510		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE FACE FOUND WITH STONE DAMAGE AND CORROSION, GRINDING OF STONE D	AMAGE AND THE LEADING EDGE REQUIRED FILLING.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997071700416	19970717	00416	GL  	1997	7	17	CA970421079      	3	19970410	G	6114	B24915	PITCH CHANGE ROD													HARTZL	HCJ3Y	PHCJ3YF2    	GL  	SEAL AREA	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2411 	490  					ED2161		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PITCH CHANGE ROD WORN THROUGH CHROME.																5	C	P36EA	 
1997071700420	19970717	00420	GL  	1997	7	17	CA970421083      	3	19970410	G	6111		BLADE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FACE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1515 	1515 				RL449376T	82510		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE FACE FOUND CORRODED, LEADING EDGE DAMAGE, ANGLES AND FACE ALIGN	MENT OUT OF SPECIFICATIONS.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997071700421	19970717	00421	GL  	1997	7	17	CA970421084      	3	19970414	G	6111	7666A2	BLADE           													HARTZL	HCC2Y	HCC2YK1     	GL  	LEADING EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			516  	516  					AW2519		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. NICKS AND CHIPS NEEDED REPAIRS.																5	C	P920	 
1997071700422	19970717	00422	GL  	1997	7	17	CA970421085      	3	19970411	G	6111		BLADE           			CESSNA	177   	177         	2073704	CE  						MCAULY	1C172	1C172TM     	GL  	LEADING EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1448 	1448 					E8961		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. MANY GOUGES AND DENTS WERE FOUND. PROPELLER WAS LAST IN THE SHOP IN 1	968. THE PROPELLER WAS OVERHAULED.					1	H	7	1 	3O			NT	A13CE   		5	N	P910	 
1997071700425	19970717	00425	GL  	1997	7	17	CA970421088      	3	19970415	G	6111	S82NC2	BLADE           													MCAULY	3A32C	D3A32C90    	GL  	AIRFOIL	OUT OF SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			704  	374  					750621		(CAN) PROPELLER BLADE PITCH FOUND OUT OF SPECIFICATIONS.																5	C	P21EA	 
1997071700426	19970717	00426	GL  	1997	7	17	CA970421089      	3	19970415	G	6111		BLADE           													MCAULY	1B90	1B90CM      	GL  	PROP	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			317  	317  					78359		(CAN) ONE PROPELLER BLADE FOUND BENT. POSSIBLY IT HAD BEEN STRAIGHTENED.																5	N	P842	 
1997071700427	19970717	00427	CE  	1997	7	17	CA970421092      	1	19970410	G	3211	05411211	SUPPORT         	CESSNA      	05112894    	CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	TOP REAR CASTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2000 	2000 				693105LR	731568		(CAN) BOTH MLG  CASTING HAD BEEN REPLACED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997071700432	19970717	00432	NE  	1997	7	17	CA970422015      	2	19970411	G	7260	310625901	BEVEL DRIVE GEAR	PWA         							PWA   	PW121 	PW121       	52124	NE  					ACCESSORY GEARBX	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11568	11568				120583			(CAN) ENGINE WAS SENT FOR INVESTIGATION AFTER OPERATOR REPORTED A SUSPECTED #4 BEARING FAILURE. DISASSEMBLY FOUND THE #4	 BEARING AREA FAILURE WAS THE SPLITTING OF THE HP IMPELLER BEVEL GEAR. ONE OF THE MOST COMMON CAUSES OF THE #4 BEARING A	REA FAILURE IS THE BACKING OFF OF THE IMPELLER BEVEL GEAR RETAINING NUT. THIS RESULTS IN UNUSUAL STRESSES AND EXCESSIVE 	FRETTING AND RUBBING BETWEEN PARTS. UNUSUAL RUBBING AND FRETTING WAS SEEN BETWEEN THE COMPONENTS IN THE #4 BEARING STACK	-UP.							4	T			E20NE				 
1997071700433	19970717	00433	NE  	1997	7	17	CA970422016      	2	19970411	G	7210	310924401	BEARING         								PWA   	119   	PW119B      		NE  					RED GR BOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6714 	6714 				116040			(CAN) REDUCTION GEARBOX WAS SENT FOR INVESTIGATION OF METAL CONTAMINATION. DISASSEMBLY OF THE RGB FOUND THE SOURCE OF TH	E METAL CONTAMINATION WAS A SPALLED #15 BEARING. IT IS NOT CLEAR WHAT CAUSED THE BEARING TO SPALL. THERE WAS NO MAGNETIS	M BEYOND LIMITS AND NO EVIDENCE OF HEAVY ELECTRICAL DISCHARGE PITTING ON THE UNSPALLED PORTION OF THE BEARING, SO LIGHTN	ING STRIKE DOES NOT APPEAR TO BE THE LIKELY CAUSE.								4	T			E20NE				 
1997071700434	19970717	00434	NE  	1997	7	17	CA970422017      	2	19970331	G	7260	311196801	TOWERSHAFT      								PWA   	118   	PW118       		NE  					SPIRAL BEVL GEAR	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16633	535  				115212			(CAN) THE ENGINE WAS SENT FOR REPAIR AFTER THE OPERATOR REPORTED A FAILED TOWERSHAFT. DISASSEMBLY CONFIRMED THE TOWERSHA	FT HAD FRACTURED IN TWO PLACES, BELOW THE UPPER SPIRAL BEVEL GEARSHAFT. EXAMINATION OF THE TWO FRACTURE SURFACES SHOWS T	HAT THE UPPER FAILURE APPEARS TO BE COMPLETELY FATIGUE WHILE THE LOWER FAILURE WAS BATTERED. IT IS CONCLUDED THAT THE UP	PER FAILURE OCCURRED FIRST ALLOWING MISMATCH OF THE GEARS WHICH CAUSED THE EXCESSIVE SIDE LOADS, THE BEARING FAILURE AND	 FINALLY THE SHEARING OF THE SHAFT AT THE LOWER LOCATION.							4	T			E20NE				 
1997071700435	19970717	00435	EU  	1997	7	17	CA970422019      	1	19970411	G	3243	AC67750	BRAKE VALVE     	DOWTY       		STBROS	SD3   	SD360       	8100606	EU  										LEFT MAIN	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA						HL240					(CAN) AFTER LANDING WHEN BRAKES APPLIED, THE LEFT MAIN WHEEL LOCKED AND THE AIRCRAFT STARTED TO PULL TO THE LEFT. RIGHT 	RUDDER AND BRAKES APPLIED TO KEEP AIRCRAFT STRAIGHT. WHEN AIRCRAFT CAME TO REST THE LEFT TIRE BLEW AND RIGHT TIRE HAD RO	TATED ON THE RIM. THE BRAKE CONTROL VALVE WAS FOUND DEFECTIVE.				2	H	7	2 	4T				A41EU   					 
1997071700438	19970717	00438	GL  	1997	7	17	CA970422029      	3	19970411	G	6111		BLADE           													HARTZL	HCE3Y	HCE3YR2     	GL  	LEADING EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2276 	538  					DJ9805A		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE FOUND ON THE LEADING EDGE OF THE PROPELLER.																5	C	P33EA	 
1997071700439	19970717	00439	GL  	1997	7	17	CA970422030      	3	19970416	G	6111	G80VAO	BLADE           			CESSNA	185   	A185F       	2072821	CE  						MCAULY	D3A34	D3A34C403   	GL  	PROP	NOT TO SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1522 	498  					860158		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PITCH DISTRIBUTION FOUND TO BE NOT TO SPECIFICATIONS OF THE MANUFACTU	RES MANUAL.					1	H	7	1 	3O				3A24    		5	C	P47GL	 
1997071700440	19970717	00440	GL  	1997	7	17	CA970422031      	3	19970416	G	6110		PROPELLER       													MCAULY	1C160	1C160DTM    	GL  	HUB ASSY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6656 	5178 					DE032		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER REQUIRED OVERHAUL DUE TO CORROSION.																5	N	P910	 
1997071700443	19970717	00443	GL  	1997	7	17	CA970422036      	3	19970414	G	6111	T10173B8	BLADE           													HARTZL	HCB3T	HCB3TN3     	GL  	LEADING EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10049	1152 					BU2118		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND PROPELLER REVERSING HAS DAMAGED THE PROPELLER, THROU	GH FOD, ON THE LEADING EDGE AND CAMBER. THE TIP ANGLE ON #3 BLADE WAS OUT OF SPECS.															6	C	P15EA	 
1997071700444	19970717	00444	GL  	1997	7	17	CA970422037      	3	19970414	G	6111	78CTA0	BLADE           													MCAULY	2D34C	B2D34C207   	GL  	LEADING EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1200 	384  					755560		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE REPAIR HAD BEEN DONE ON THE LEADING EDGE. FILE MARKS LEF	T IN ON THE ATTEMPTED REPAIR. THE FILE MARKS ARE GOING IN THE CORD WISE DIRECTION.															5	C	P7EA	 
1998041700534	19980417	00534	CE  	1998	4	17	CA970423014      	1	19970415	G	2752	556517538	ACTUATOR        		556517538   	CESSNA	500   	560CESSNA   	2076750	CE  										LT FLAP GRBOX	SHEARED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				136  		1207961					(CAN) FLAPS WILL NOT MOVE WHEN SELECTED.  MOVED INTERMITTENTLY, NOT EVERY SELECTION.  LT FLAP GEARBOX OUTPUT SPROCKET SE	VERED FROM OUTPUT SHAFT.  PUT ALL THE LOAD ON RT MOTOR.   NEW RT MOTOR INSTALLED AND GEARBOX.  PART TC:  223.					2	L	7	2 	4F			RT	A22CE   					 
1997071700458	19970717	00458	GL  	1997	7	17	CA970423017      	3	19970410	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	PROP	OUT OF SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6740 						725640		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BLADES TO BE DIFFERENT LENGTHS; BLADE ANGLES OUT	 OF SPECS AT STATIONS 33 AND 36, TWISTING REQUIRED; LEADING EDGE BLUNT FROM FILING, REQUIRED DRESSING AND HUB NOT STAMPE	D.														5	N	P910	 
1997071700459	19970717	00459	GL  	1997	7	17	CA970423018      	3	19970411	G	6111		BLADE           													MCAULY	2D34C	B2D34C211   	GL  	BLADE FACE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			847  	219  					765267		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE FACE REQUIRED GRINDING DUE TO CORROSION.																5	C	P7EA	 
1997071700465	19970717	00465	SO  	1997	7	17	CA970425002      	2	19970418	G	7414	6310	MAGNETO         	SLICK       		CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	IMPULSE COUPLING	BROKEN SPRING   	W				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			500  			92120139		1338047R	785403		(CAN) ENGINE EXPERIENCED LARGE MAG DROP, ON LEFT MAGNETO, DURING RUN-UP. MAGNETO WAS REMOVED AND INSPECTION FOUND THE IM	PULSE COUPLING SPRING WEAK AND NOT RETURNING TO ITS NORMAL RUN POSITION. THE IMPULSE COUPLING WAS DISASSEMBLED AND A BRO	KEN SPRING WAS FOUND.				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997071700466	19970717	00466	GL  	1997	7	17	CA970425005      	3	19970428	G	6111		BLADE           													MCAULY	2A36C	2A36C29     	GL  	PROP	NICKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			907  	107  					621581		(CAN) PROPELLER BLADE FOUND NICKED DURING INSPECTION.																5	C	P880	 
1998041700543	19980417	00543	EU  	1998	4	17	CA970425006      	2	19970417	G	7520	922253	COOLING HOSE    								ROTAX 	912   	ROTAX912    	55555	EU  					NR 1 EXHAUST	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			263  					4412587			(CAN) CHAFING OF COOLANT LINE GREATER THAN 50 PERCENT OF WALL THICKNESS.  NR 1 EXHAUST SPRING SOURCE OF CHAFING.											3	I			EXPE3I				 
1997071700467	19970717	00467	SO  	1997	7	17	CA970428001      	2	19970414	G	7322	20764	FLOAT ASSEMBLY  	MARVELSCHEB 	NA45        	CESSNA	180   	180E        	2072612	CE  	CONT  	O470  	O470R       	17026	SO  					FLOAT BRACKET	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						3988918		836582R			(CAN) OWNER COMPLAINED OF CONTINUOUS FUEL LEAK FROM THE CARBURETOR. DISASSEMBLY OF THE CARBURETOR FOUND THE FLOAT SECTIO	N SEPARATED FROM THE FLOAT BRACKET AND LAYING IN THE BOTTOM OF THE FLOAT CHAMBER.					1	H	7	1 	3O	3	O		5A6     	E273				 
1997071700468	19970717	00468	EA  	1997	7	17	CA970428003      	3	19970423	G	6111		BLADE           													SNSNCH	76E	76EM8S5     	EA  	LEADING EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1216 						21484K		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER LEADING EDGE AND FACE NICKED AT STATIO	N 23" STATION. AREA REQUIRED FILLING AND GRINDING.															5	N	P4EA	 
1998050100232	19980501	00232	CE  	1998	5	1	CA970428011      	1	19970410	G	3242	06130019	BRAKE           			CESSNA	172   	172M        	2072418	CE  										RT MLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) RIGHT BRAKE HOUSING CRACKED.  REPLACED.						1	H	7	1 	3O			NT	3A12    					 
1997072400722	19970724	00722	EA  	1997	7	24	CA970429006      	3	19970422	G	6111		BLADE           			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2341 	47   				L3154727A	A44820		(CAN) PROPELLER RECEIVED FOR REPITCH. INSPECTION FOUND THE PROPELLER BLADES BENT WITH GOUGES AND CORROSION WHICH REQUIRE	D GRINDING AND FILLING.					1	H	7	1 	3O	3	O		1A6     	E274	5	N	P88614	 
1997072400723	19970724	00723	GL  	1997	7	24	CA970429007      	3	19970422	G	6111	S90AT4	BLADE           			CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROP LE	OUT OF SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			196  						910362		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BLADE PITCH DISTRIBUTION OUT OF SPECIFICATIONS.						1	H	7	1 	3O				3A24    		5	C	P3EA	 
1997072400724	19970724	00724	GL  	1997	7	24	CA970429008      	3	19970422	G	6111	G90DFA10	BLADE           													MCAULY	D3A34	D3A34C402   	GL  	PROP	OUT OF SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			572  	216  					816273		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BLADE PITCH DISTRIBUTION OUT OF SPECIFICATIONS.																5	C	P47GL	 
1997072400725	19970724	00725	GL  	1997	7	24	CA970429009      	3	19970422	G	6111	S90AT4	BLADE           			CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			912  	185  		KH111YS			726057		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADES THREADS CHECKED FOR CRACKS AND FOUND THAT FAILURE WAS IMMINENT	. THE BLADE WAS SCRAPPED.					1	H	7	1 	3O				3A24    		5	C	P3EA	 
1997072400726	19970724	00726	GL  	1997	7	24	CA970429010      	3	19970423	G	6111	G90DCA2	BLADE           			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			425  					986375RR	851761		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. TEN YEARS SINCE LAST OVERHAUL. INSPECTION FOUND BLADES CORRODED. TIP 	ANGLES OUT. FACE ALIGNMENT OUT. ONE ACTUATING PIN; TWO PISTON PINS AND CYLINDER CORRODED. REPAIRS MADE AND CORRODED PART	S REPAIRED OR REPLACED.				1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997072400727	19970724	00727	GL  	1997	7	24	CA970429011      	3	19970422	G	6111		BLADE           													MCAULY	1A90	1A90CF      	GL  	PROP TIPS	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			356  						LB004		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND PROPELLER BLADES PULLED FORWARD 1/32", BLADES REQUIR	ED STRAIGHTENING.															5	N	P842	 
1997072400731	19970724	00731	GL  	1997	7	24	CA970501003      	3	19970416	G	6111	R90DCA10	BLADE           			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	LEADING EDGE	SPRAY CUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3516 	141  				356178	748255		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND SPRAY CUTS ON THE LEADING EDGE AND THE TIP ANGLES OU	T. THE BLADE EDGES WERE FILED AND THE TIP ANGLES WERE REPAIRED.					1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1997121100267	19971211	00267	SW  	1997	12	11	CA970505007      	1	19970415	G	2820	AN737TW74	CLAMP           	CHAMP       		BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  					FUEL HOSE	WRONG TYPE      	W				O				OTHER                   				K	w		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA								L1867836A			(CAN) SHORTLY AFTER REFUELING THE AIRCRAFT, A MAJOR FUEL LEAK OCCURRED. INVESTIGATION REVEALED THAT THE INCORRECT SIZE O	F CLAMPS WERE INSTALLED ON AN INTERCONNECT FUEL TANK HOSE. THE CLAMP FOUND IN USE WAS AN AN737TW-74. THE PARTS MANUAL SH	OWS AN AN737TW-56 CLAMP. THIS PROBLEM IS RELATIVE TO BELLANCA SCOUTS WITH THE 70 GAL LONG RANGE FUEL TANK.				1	H	7	1 	3O	3	O		A21CE   	E286				 
1998041700549	19980417	00549		1998	4	17	CA970505008      	1	19970425	G	7714	2071000501	TACH CABLE      								ROTAX 	912   	ROTAX912    	55555	EU  					FIRE SHIELD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			943  					4380693			(CAN) TACH CABLE PROTECTIVE SLEEVE FOUND MELTED AND SEPARATED FROM THE ATTACH POINT TO THE ENGINE.  REPLACED.											3	I			EXPE3I				 
1997072400736	19970724	00736	GL  	1997	7	24	CA970505009      	3	19970428	G	6114	57B2256	THRUST PLATE    			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROP HUB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1851 	449  				L1253048	CH13991		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THRUST PLATE FOUND WORN CAUSING 32-9731616 BEARING TO BE LOOSE. THIS 	BEARING IS A PRESS FIT WHEN NEW. 57-A2202 BEARING RACE HAD CORROSION PITTING AS WELL AS BALL DAMAGE. 79-0100016 BALLS HA	D CORROSION AND BALL DAMAGE. PITCH DISTRIBUTION ON #1 BLADE WAS OUT OF SPECIFICATIONS.				1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920	 
1998050100233	19980501	00233	SO  	1998	5	1	CA970505015      	1	19970417	G	5330	1974500	RUBBER EXTRUSION			PIPER 	PA23  	PA23250     	7102308	SO  										WING/FUSELAGE	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			6913 								(CAN) FRETTING WHERE WING TO FUSELAGE FAIRING ATTACHES TO WING AND FUSELAGE, NO RUBBER CHAFING STRIPS INSTALLED.  STRIPS	 INSTALLED.  PART TT:  6,957 HOURS.					1	L	7	2 	3O				1A10    					 
1997072400741	19970724	00741	EA  	1997	7	24	CA970505021      	1	19970413	G	2750	855D1007	BPSU            			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					FLAPS	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			2181 					GEE807385			(CAN) FLAPS FAILED MESSAGE ON EICAS. FLAPS UNABLE TO EXTEND. BRAKE AND POSITIONING SENSOR UNIT REPLACED. ALSO FLAP ELECT	RONIC CONTROL UNIT AND POWER DRIVE UNITS REPLACED. FECU P/N 865D100-5 AND PDU P/N 860D100-18.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1998050100234	19980501	00234	CE  	1998	5	1	CA970506001      	1	19970327	G	3150	993642461	AMPLIFIER       			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  						FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			10515					PCE50113			(CAN) INTEGRATED CIRCUITS WITHIN TRIM CONTROL AMPLIFIER FAILED.  NO AURAL WARNING OF TRIM IN MOTION.  REPLACED.						1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1998050100235	19980501	00235	CE  	1998	5	1	CA970506002      	1	19971113	G	2913	204038	FILTER          			BEECH 	1900  	1900D       	1154162	CE  										HYD SYS	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			207  								(CAN) HYDRAULIC FILTER BYPASS INDICATOR POPPED.  FILTER CONTAMINATED.  REPLACED.						2	L	7	2 	4T			RT	A24CE   					 
1997072400751	19970724	00751	GL  	1997	7	24	CA970506004      	3	19970430	G	6111		BLADE           													MCAULY	1A105	1A105SCM    	GL  	PROP	OUT OF SPEC     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			1565 						G14725		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. ONE PROP BLADE WAS 1/4" LONGER THAN THE OTHER AND TRIMMING WAS REQUIR	ED.															5	N	P918	 
1997072400753	19970724	00753	GL  	1997	7	24	CA970506007      	3	19970430	G	6111	FL7666A42	BLADE           			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROP FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1170 	775  				L223535A1	CH25937		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. #1 PROPELLER BLADE HAD DAMAGE TO THE FACE SIDE DUE TO BOLT OR SCREW D	AMAGE WHICH WAS NOT DRESSED OUT, WHEN PROPELLER WAS RECEIVED FOR INSPECTION.					1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P920	 
1997072400754	19970724	00754	GL  	1997	7	24	CA970506008      	3	19970430	G	6111		BLADES          													MCAULY	1A101	1A101HCM    	GL  	PRO LEAD EDGE	NICKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4514 						G10892		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. LEADING EDGES FOUND BLUNT AND REQUIRED FILING. DEEP NICKS WERE FOUND 	IN THE BLADE FACES WHICH REQUIRED GRINDING.															5	N	P918	 
1997072400755	19970724	00755	EA  	1997	7	24	CA970506009      	3	19970429	G	6111		BLADES          													SNSNCH	74DM	M74DM       	EA  	PROP LEAD EDGE	NICKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6948 	590  					K13223		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. TIPS PULLED FORWARD, LIGHT CORROSION ALL OVER, GRINDING WAS REQUIRED.	 LEADING EDGE NICKED, FILING WAS REQUIRED															5	N	P88614	 
1997072400756	19970724	00756	GL  	1997	7	24	CA970506010      	3	19970429	G	6111	S82NC2	BLADE           			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C*     	GL  	PROP LEAD EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			486  	227  				506056	736801		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. LEADING EDGE OF THE PROPELLER BLADE WAS FOUND DAMAGED. REWORK AND GRI	NDING WAS REQUIRED TO FIX THE AIRFOIL ON ALL BLADES.					1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P21EA	 
1997072500026	19970725	00026	SO  	1997	7	25	CA970506013      	2	19970430	G	8530	649317A	PISTON PIN      	CONT        		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C*     	GL  	INSIDE SLEEVE	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA				1050 				514056	775668		(CAN) CYLINDER WAS REMOVED DUE TO LOW COMPRESSION AND INCREASE IN OIL CONSUMPTION. INSPECTION FOUND THE HEADS OF THE PIS	TON PINS MUSHROOMED OVER. FURTHER INSPECTION REVEALED THE ALUMINUM PLUG BROKEN IN HALF. NO DAMAGE WAS FOUND ON THE STEEL	 PIN. INSPECTION OF THE OTHER PISTON PINS FOUND NO FAULT. ENGINE WAS REASSEMBLED.				1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1998050100237	19980501	00237	SO  	1998	5	1	CA970506016      	1	19970428	G	2740	3314902	SPRING          			PIPER 	PA23  	PA23250     	7102308	SO  										STAB BUNGEE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STABILATOR BUNGEE SPRING WORN CORRODED AND WEAK.  WIRE DIAMETER OF LOOP FLATTENED WHERE LOOP CONTACT IS MADE WITH 	HOOKING HOLE.  SPRING WIRE REDUCED BY 50 PERCENT.  LOOP AT OTHER END SHOWS SIGNS OF HARDENING AND SURFACE CORROSION.  RE	PLACED.				1	L	7	2 	3O				1A10    					 
1997072400769	19970724	00769	EA  	1997	7	24	CA970507009      	1	19970423	G	3246	300478	WHEEL HALF      	DHAV        	31354       	DHAV  	DHC7  	DHC7102     	2802708	EA  										INBOARD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2278 		606					(CAN) DURING EDDY CURRENT INSPECTION SEVERAL CRACK INDICATIONS WERE FOUND AT SEVERAL LUG BOSSES ALONG THE BOTTOM SIDE, P	ARALLEL TO THE WHEEL BOLT HOLES. THE CRACKS VARIED IN LENGTH FROM 1/2" TO OVER 1" AND TO A DEPTH OF OVER .060.					2	H	7	4 	4T				A20EA   					 
1998120400002	19981204	00002		1998	12	4	CA970507014      	1	19970424	G	2435	03601018	BEARING         	LUCAS       	23046020    															START/GEN	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						5835					(CAN) BEARINGS REMOVED AT OVERHAUL DID NOT HAVE OEM LOGO AND WERE THE WRONG FAFNIR PART NUMBER.																			 
1997072400775	19970724	00775	NE  	1997	7	24	CA970507020      	2	19970430	G	7210	310703301	BEARING         								PWA   	120   	PW120A      		NE  					RED GR BOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23051	20057				120188			(CAN) ENGINE WAS SENT FOR INVESTIGATION OF OIL LEAK AND METAL CONTAMINATION OF THE RGB. DISASSEMBLY OF THE RGB FOUND THE	 CAUSE OF THE METAL CONTAMINATION TO BE SPALLING OF THE #15 BEARING. THE EXTENSIVE MAGNETISM AND WIDESPREAD ELECTRICAL D	ISCHARGE PITTING DAMAGE ON THIS AND OTHER BEARINGS LEAVES LITTLE DOUBT THAT THIS WAS CAUSED BY ELECTRICAL DISCHARGE AS A	 RESULT OF A LIGHTNING STRIKE. THIS DID NOT APPEAR TO CAUSE ANY SECONDARY DAMAGE. THE OIL LEAK APPEARED TO HAVE OCCURRED	 WHEN PACKING AND AIR/OIL SEALS AROUND THE #5 BEARING DETERIORATED. OVER TIME THE INTEGRITY OF THE PACKING IS LOST. IN T	HIS CASE THE TURBOMACHINE WAS AT 20057.4 HOURS AND IT IS NOT SURPRISING TO FIND THIS DETERIORATION.						4	T			E20NE				 
1997072400782	19970724	00782	NM  	1997	7	24	CA970508008      	1	19970502	G	2822	2580005	PUMP            	ARGOTEC     	2580005     	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					NR 2 TANK RT AFT	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			DE	DESCENT        	1			CA						1003679B		P653620B			(CAN) DURING DESCENT THE LOW PRESSURE LIGHT FOR THE #2 TANK R/H AFT BOOST PUMP CAME ON. THE PUMP WAS SELECTED OFF AND TH	E FLIGHT COMPLETED WITHOUT INCIDENT. PUMP REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997072400783	19970724	00783	NM  	1997	7	24	CA970508009      	1	19970502	G	2730	680005003	BOOST PACK      	BERTEA CORP 	680005003   	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LH ELEVATOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						1973		P653620B			(CAN) DURING PREFLIGHT THE L/H ELEVATOR BOOST PACK WAS FOUND LEAKING WHEN HYDRAULIC SYSTEM NOT POWERED, REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997070300310	19970703	00310	EA  	1997	7	3	CA970508010      	1	19970501	G	5320	85300016113	CLOSING ANGLE   			DHAV  	DHC8  	DHC8311     	1386006	EA  										X387.35,Y265	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13595								(CAN) FUSELAGE TO WING LEFT FORWARD CLOSING ANGLE FOUND WITH 4" CRACK IN RADIUS. INSPECTION OF OTHER CLOSING ANGLES FOUN	D RIGHT FORWARD CLOSING ANGLES ALSO CRACKED 3" IN RADIUS.					2	H	7	2 	4T			RT	A13NM   					 
1997072400784	19970724	00784	GL  	1997	7	24	CA970508014      	3	19970505	G	6114	5262	CYLINDER        			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	PROPELLER	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1332 	205  				2028969R	714226		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER CYLINDER WAS SCORED AND WORN AND HAD TO BE REPLACED.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997072400785	19970724	00785	NE  	1997	7	24	CA970508015      	3	19970502	G	6114	51459	SPIDER          													HAMSTD	2D	2D30        	NE  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1147 					AC4116028		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. ONE CHAFING RING BROKEN, CYLINDER OVERSIZE. PROPELLER OVERHAULED.																5	C	P206	 
1998050100238	19980501	00238	CE  	1998	5	1	CA970513006      	1	19970426	G	5313	07120486	LONGERON        			CESSNA	185   	A185F       	2072821	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5017 								(CAN) .5 INCH CRACK AT TOP END OF RT REINFORCEMENT LONGERON, DUE TO CORROSION.  RT BRACKETS 07123021 AND 2 AND REINFORCE	MENTS 0712304-15 AND 16 REPLACED.  AIRCRAFT TT:  5,017 HOURS.					1	H	7	1 	3O				3A24    					 
1997070300311	19970703	00311	EA  	1997	7	3	CA970513008      	1	19970501	G	2720	85500015001	ROD             			DHAV  	DHC8  	DHC8311     	1386006	EA  										TRAILING RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13595								(CAN) TRAILING RUDDER UPPER RADIUS ROD FORWARD ROD END BEARING P/N DSC4-4 FOUND LOOSE IN RADIUS ROD. JAMB NUT FOUND LOOS	E. ROD END WAS RETAINED IN RADIUS ROD ONLY BY 3/32" RIVET. THREADS ON RADIUS ROD WERE WORN OUT.					2	H	7	2 	4T			RT	A13NM   					 
1998050100240	19980501	00240	CE  	1998	5	1	CA970513011      	1	19970507	G	3297		WIRE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					RT MLG DOWN	BROKEN          	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			CR	CRUISE         	1			CA								PCE40241			(CAN) WHILE ON TRAINING, THE CREW SELECTED THE GEAR DOWN AND THE AIRCRAFT RESPONDED NORMALLY, EXCEPT RT GEAR DOWN LIGHT 	FAILED TO ILLUMINATE.  FLY-BY CONFIRMED THAT GEAR DOWN.   A/C LANDED.  FOUND BROKEN WIRE, REPAIRED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
1997072400792	19970724	00792	GL  	1997	7	24	CA970513013      	3	19970430	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5100 	3984 							(CAN) DURING COMPLIANCE WITH FAA AD 97-06-16 DYE PENETRANT INSPECTION DID NOT FIND THE CRACK, WHICH WAS FOUND THROUGH ED	DBY CURRENT INSPECTION. CRACK AREA HOLLOWED AS PER SB 221B TO DEPTH OF .010, CRACK WAS THEN EVIDENT. CRACK AREA HOLLOWED	 TO .040 AND CRACK WAS NO LONGER VISIBLE WITH LPI. EDDY CURRENT COULD NOT BE USED DUE TO HOLLOW AT CRACK LOCATION. MCCAU	LEY ADVISED, IF CRACK NOT VISIBLE WITH LPI RETURN PROPELLER TO SERVICE.			1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
1997072400793	19970724	00793	GL  	1997	7	24	CA970513014      	3	19970507	G	6114		PROPELLER       													HARTZL	HCC2Y	HCC2YK1     	GL  	PITCH CHANGE	INCORRECT RADIUS	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1335 						CH9773		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND INCORRECT RADIUS ON PITCH CHANGE BLOCK.																5	C	P920	 
1997072400794	19970724	00794	NE  	1997	7	24	CA970513015      	2	19970430	G	7414	SB9RU3	MAGNETO         	BOSCH       							PWA   	R985  	R985*       	52008	NE  					ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				476  				20175			(CAN) MAGNETO APPEARED TO BE TIMED PROPERLY BUT THE POINTS WOULD CLOSE 135 DEGREES AFTER TOP DEAD CENTRE. MAGNETO WAS SE	NT FOR OVERHAUL										3	R			5E1				 
1998041700556	19980417	00556	EU  	1998	4	17	CA970513016      	2	19970425	G	7320		CHOKE CABLE     								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4380693			(CAN) THE CHOKE CABLE WAS FOUND BROKEN WHERE IT THREADS INTO THE 90 DEGREE ROUTING UNIT.											3	I			EXPE3I				 
1997072400798	19970724	00798	NE  	1997	7	24	CA970513025      	2	19970501	G	7210	310924401	BEARING         								PWA   	120   	PW120A      		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19463	13282		RH477		120224			(CAN) THE ENGINE WAS SENT FOR INVEST. OF METAL CONTAMINATION & SUBSEQUENT OVERHAUL. DISASSY FOUND- #15 BEARING SEVERELY 	SPALLED ON ONE ROLLER WITH SUBSTANTIAL MATERIAL LOSS. THIS DAMAGE WAS MORE THAN SUFFICIENT TO EXPLAIN- METAL CONTAMINATI	ON OBSERVED.-RE DOES NOT APPEAR TO BE ANY SIGNIFICIENT SECONDARY DAMAGE.- #15 & #18 BEARINGS BOTH HAD ELECTRICAL EROSION	 TYPE CHAIN PITTING TYPICA L OF LOW ENERGY ELECTRICAL DISCHARGE & ALSO SOME DEEPER ARCING TYPE PITTING TYPICAL OF HIGHER	 ENERGY ELECTRICAL DISCHARGE.- MAGNETISM IN- RGB WAS RELATIVELY MINOR & NOT TYPICAL OF- MAGNETISM PR OFILE THAT TYPICALL	Y ARISES FOLLOWING A LIGHTNING STRIKE. IT IS UNCLEAR IF THIS WAS CAUSED BY A LIGHTNING STRIKE.						4	T			E20NE				 
1997072400799	19970724	00799	NE  	1997	7	24	CA970513026      	2	19970501	G	7210	310703301	BEARING         								PWA   	118   	PW118       		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21801	1445 				115165			(CAN) THE ENGINE WAS SENT FOR INVESTIGATION AFTER THE REDUCTION GEARBOX WAS FOUND WITH METAL CONTAMINATION. DISASSEMBLY 	FOUND THE CAUSE OF THE CONTAMINATION WAS THE SPALLING OF THE #15 BEARING. HIGH MAGNETISM ON SEVERAL COMPONENTS AND ELECT	RICAL PITTING ON THE #15 AND #19 BEARINGS INDICATE THE ENGINE EXPERIENCED A LIGHTNING STRIKE. THE FAILURE OF THE #15 BEA	RING IS THOUGHT TO HAVE BEEN INITIATED BY THE LIGHTNING STRIKE.								4	T			E20NE				 
1998040200081	19980402	00081	CE  	1998	4	2	CA970514002      	1	19970419	G	3222	55422232	SPACER          			CESSNA	500   	560CESSNA   	2076750	CE  										AXLE SHAFT NLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			600  								(CAN) LEFT HAND NOSE WHEEL SPACER FOUND SEIZED TO THE AXLE SHAFT.						2	L	7	2 	4F			RT	A22CE   					 
1997072400800	19970724	00800	NE  	1997	7	24	CA970514004      	2	19970430	G	8530		CYLINDER        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985*       	52008	NE  					#9 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				476  				20175			(CAN) DURING INSPECTION #9 CYLINDER WAS FOUND CRACKED ON THE TOP BETWEEN THE TWO SPARK PLUG HOLES						1	H	7	1 	3R	3	R		A806    	5E1				 
1997072400801	19970724	00801	GL  	1997	7	24	CA970514005      	3	19970506	G	6111	T10173AB6Q	BLADE           													HARTZL	HCB3T	HCB3TN3     	GL  	PROP LE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3924 	967  					BU16054		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADES FOUND DAMAGED FROM GRAVEL - VERY ROUGH - TRIMMED OUT	. BALLS FROM BEARINGS SCUFFED AND WERE REPLACED. DE-ICE BRACKETS WERE FOUND CRACKED AND THEY WERE REPLACED.															6	C	P15EA	 
1997072400804	19970724	00804	NE  	1997	7	24	CA970514008      	2	19970501	G	7322		FUEL CONTRL UNIT								PWA   	119   	PW119B      		NE  					#2 ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA			2420 					116150			(CAN) DURING CLIMB THE ENGINE POWER FLUCTUATED ABOUT 50 PERCENT WITH THE AIRCRAFT YAWING. REPLACEMENT OF THE FUEL CONTRO	L UNIT CLEARED THE PROBLEM.										4	T			E20NE				 
1997072500028	19970725	00028	NE  	1997	7	25	CA970514009      	2	19970312	G	7311		FUEL OIL COOLER 								PWA   	PW120 	PW126A      		NE  					#2 ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			9208 	29   				124041			(CAN) JUST AFTER TAKEOFF THE #2 ENGINE OIL PRESSURE BEGAN TO FLUCTUATE AND LATER IN THE FLIGHT WHEN THE OIL PRESSURE DRO	PPED BELOW 41 PSI THERE WAS A COCKPIT WARNING. THE #2 ENGINE WAS SHUTDOWN. THE FUEL/ OIL COOLER WAS REPLACED.										4	T			E2ONE				 
1998050100242	19980501	00242	CE  	1998	5	1	CA970520001      	1	19970403	G	3213	07410016	GEAR LEG        			CESSNA	185   	A185F       	2072821	CE  										MLG SKI	BROKEN          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			7672 								(CAN) ON TAKEOFF, THE LEG OF THE SKI EQUIPPED AIRCRAFT BROKE.  POSSIBLY PREVIOUSLY CRACKED.   REPLACED.						1	H	7	1 	3O				3A24    					 
1998050100244	19980501	00244	CE  	1998	5	1	CA970520007      	1	19970507	G	5720	1214223	DOUBLERS        			CESSNA	210   	210F        	2073418	CE  	CONT  	O520  	IO520A      	17032	SO  					RT LT WELLS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2826 								(CAN) CRACKS FOUND ON AFT GEAR WELL BULKHEAD DOUBLERS LT AND RT WELLS.  CRACKS EXTEND AROUND BOLT HOLES AND RUN VERTICAL	 ON DOUBLERS.  DOUBLERS REPLACED.					1	H	7	1 	3O	3	O		3A21    	E5CE				 
1997072400920	19970724	00920	GL  	1997	7	24	CA970520009      	3	19970512	G	6114	790100016	BALL BEARING    			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	PROPELLER	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			902  	413  				L17179	EN383		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BALL BEARINGS FOUND GALLED.						1	L	7	1 	3O	3	O		A1CE    	1E10	5	C	P43GL	 
1997072400921	19970724	00921	GL  	1997	7	24	CA970520010      	3	19970512	G	6111	F766A2	BLADE           			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	BALANCE HOLE	CORROSION       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				601  				L141351A	26853		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. ONE BLADE REJECTED DUE TO CORROSION IN THE BALANCE HOLE. HUB PILOT BO	RE OVERSIZE AND HUB HAD CORROSION.					1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
1998050100246	19980501	00246	SO  	1998	5	1	CA970520014      	1	19970508	G	3242	6830	SHIM            	CLEVELAND   	19983       	PIPER 	PA31  	PA31350     	7103110	SO  										BRAKE	MISSING         	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA						S4295GL					(CAN) WHEELS AND BRAKES PREVIOUSLY MODIFIED PER STC AND DWGS.  DUE FOR 100 HR INSP.  RT BRAKE FOUND LEAKING, O-RINGS.  R	T SIDE BOTH BRAKES O-RINGS FOUND FRIED ONTO CASING AND STICKING TO PISTONS.  SHIM PIPER 762421, CLEVLAND 68-30, MISSING 	ON ONE BRAKE AND HOME MADE METAL SHIMS FOUND ON TWO LININGS AND MISSING ON THIRD.  LT, BOTH SHIMS MISSING, O-RINGS HEATE	D.  NO LOCK WASHERS ON BOLTS.  REPLACED.			1	L	7	2 	3O			 	A20SO   					 
1997072400924	19970724	00924	GL  	1997	7	24	CA970521001      	3	19970508	G	6112	SA70111	BRACKET         			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	DE-ICE LEAD	BROKEN          	W				K				NONE                    				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA			884  					290384R	789543		(CAN) AFTER LANDING THE PILOT NOTICED THE LH PROPELLER DE-ICE LEAD HANGING FROM THE PROPELLER SPINNER. INSPECTION FOUND 	THE DE-ICE LEAD BRACKET WHICH RETAINS THE PLUG-IN CONNECTION ON THE BLADE ROOT HAD BROKEN. THE BRACKET, CLIP AND PLUG AS	SEMBLY HAD DEPARTED THE BLADE ROOT AND STRUCK THE AFT FACE OF THE PROPELLER AND THEN CONTACTED THE AIRCRAFT FUSELAGE CAU	SING SOME DENTING. THE PROPELLER DE-ICE PARTS WERE REPLACED, THE BLADE DAMAGE WAS DRESSED OUT AND THE FUSELAGE SKIN WAS 	REPAIRED.		1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
2000021200003	20000212	00003	SO  	2000	2	12	CA970521006      	1	19970514	G	3242	16432A617	BRAKE           	CLEVELAND   	11915       	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								L104448	BP3110		(CAN) DISC 16432A617 FOUND WITH THREE BOLTS LOOSE AND BOLT HOLES ELONGATED IN DISC.  TWO BOLTS FOUND WITH CRACKS.  WHEN 	PRIED, A PIECE 1 INCH BY 2.5 INCHES OF THE LATERAL WALL OF DISC CAME OFF.  WAS NOT EVIDENT LAST 59 HR INSP.  REPLACED.  	MAY BE SOME CONFUSION WITH KITS 119-15 AND 119150.				1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
2000021200004	20000212	00004	EA  	2000	2	12	CA970521007      	2	19970514	G	7414		NUT             	AERO RECIP  	A182AS11    	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	LT MAGNETO	CORRODED        	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			1636 					L104448	BP3110		(CAN) IN CRUISE, LEFT ENGINE STARTED TO RUN ROUGH.  AIRCRAFT LANDED.  MAG CHECK CARRIED OUT, 300 RPM DROP WITH LEFT MAG 	OFF.  NR 4 CYLINDER LEAD DISCONNECTED, RETAINING NUT MISSING ONLY SMALL RING PART FROM NUT FOUND.  INTERGRANULAR CORROSI	ON.  REPLACED.				1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997072400927	19970724	00927		1997	7	24	CA970521010      	1	19970429	G	3244	39X1322PR	TIRE            	GOODYEARAERO																MLG	PATCHED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) TIRE INSPECTION CARRIED OUT PRIOR TO INSTALLATION AND FOUND WITH PATCH ON INSIDE OF TIRE.																			 
1997072400928	19970724	00928	GL  	1997	7	24	CA970521011      	3	19970506	G	6111	T10173AB6Q	BLADE           													HARTZL	HCB3T	HCB3TN3     	GL  	LEADING EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3924 	967  					BU15994		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADES FOUND DAMAGED FROM GRAVEL - VERY ROUGH - TRIMMED OUT	. BALLS FROM BEARINGS SCUFFED AND WERE REPLACED. DE-ICE BRACKETS WERE FOUND CRACKED AND THEY WERE REPLACED.															6	C	P15EA	 
1998050100248	19980501	00248	CE  	1998	5	1	CA970523005      	1	19970505	G	7160	5123015	CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARB HEAT	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			2830 					L3008227A			(CAN) CARBURETOR HEAT CABLE BROKE OFF 3 INCHES FROM KNOB DURING GROUND CHECK. REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
1997072400929	19970724	00929	CE  	1997	7	24	CA970523006      	1	19970514	G	7810	311494001	EXHAUST DUCT    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AFT EDGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			672  					PCE71819			(CAN) DURING INSPECTION A CRACK WAS FOUND IN THE EXHAUST DUCT. THE ONE INCH CRACK WAS RADIATING AXIALLY FORWARD FROM THE	 AFT EDGE OF THE DUCT. THE DEFECTIVE PART WAS REPLACED BY PRATT & WHITNEY SERVICE CENTRE.					1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997070300313	19970703	00313	EA  	1997	7	3	CA970523007      	1	19970508	G	2720		RUDDER          	DHAV        		DHAV  	DHC8  	DHC8311     	1386006	EA  										FLIGHT CONTROL	JAMMED          	W		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) APPARENT RUDDER JAM IMMEDIATELY AFTER ROTATION. FOLLOWING ROTATION INTO A MODERATED CROSSWIND CORRECTIVE RUDDER WA	S APPLIED. RUDDER PEDALS WERE STIFF AND EVEN WITH A CONSIDERABLE FORCE APPLIED THE RUDDER ONLY HAD A LIMITED AMOUNT OF D	IRECTIONAL CONTROL. CONTROL GIVEN TO F.O. FOR VERIFICATION. PRECAUTIONARY LANDING CARRIED OUT OK. EMERGENCY DECLARED. PI	LOT CLAIMED RUDDER COULD BE OPERATED DURING THE FLIGHT USING THE AUTOPILOT AND TRIM SYSTEM. CONTROL CABLES CIRCUITS CHEC	KED OFF. THE TWO RUDDER ACTUATORS AND THE RUDDER DAMPER WERE REPLACED AS A PRECAUTION.		2	H	7	2 	4T			RT	A13NM   					 
1998050100249	19980501	00249	SO  	1998	5	1	CA970523012      	1	19970512	G	5510	1001	VORTEX GEN      			PIPER 	PA31  	PA31350     	7103110	SO  										HORIZ STAB	MISSING         	W				K				NONE                    				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			CA			957  								(CAN) VORTEX GEN MISSING ON TOP OF WING STN 174.5 AND BOTTOM OF RT STAB AT STN BL 9 8.25.  SUBMITTER STATED POSSIBLY LOO	SENED DURING WASHING AND FELL OFF DURING TAXI OR FLIGHT.  VG ON STAB IS PARTLY ON CORNER OF TRIM PANEL.  AIRCRAFT TT:  1	0,273 HOURS.				1	L	7	2 	3O				A20SO   					 
1997072400934	19970724	00934	NE  	1997	7	24	CA970526003      	2	19970430	G	7261		OIL PUMP        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118       		NE  					PROP CONTROL	CRACKED         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA								115447			(CAN) DURING CLIMB THE #2 ENGINE MAIN OIL PRESSURE WENT TO ZERO AND NP WENT TO 102.8. THE CREW TRIED TO FEATHER THE PROP	ELLER WITHOUT SUCCESS. POST FLIGHT INVESTIGATION FOUND THE PROPELLER CONTROL UNIT OIL PUMP WAS CRACKED.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
1997072400944	19970724	00944	EA  	1997	7	24	CA970527008      	2	19970520	G	7322	324475316	FUEL CONTRL UNIT								PWA   	PT6   	PT6A50      	52043	EA  					NR 4 ENG	SHEARED SHAFT   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA				3991 				86288			(CAN) IN CRUISE AT 16,600 FEET THE #4 ENGINE SURGED. THE TORQUE, T5 AND NG ALL CLIMBED BEYOND OPERATING LIMITS. EMERGENC	Y PROCEDURES WERE CONDUCTED AND THE ENGINE SHUTDOWN. POST FLIGHT INSPECTION FOUND THE FUEL CONTROL UNIT TO FUEL PUMP INP	UT SHAFT HAD SHEARED CAUSING THE ENGINE TO OVERSPEED. BOTH THE ENGINE AND PROPELLER WILL BE SHIPPED FOR INVESTIGATION WI	TH A REPORT TO FOLLOW.								4	T			E4EA				 
1998041700570	19980417	00570	CE  	1998	4	17	CA970527010      	1	19970515	G	3222	58420005	FORK TUBE       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4204 					278157R	810799		(CAN) AME NOTICED THE RIGHT HAND LOWER AXLE ATTACH POINT WAS BROKEN.  DAMAGE APPEARS TO HAVE BEEN CAUSED BY A BEARING SE	IZURE.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
1997072400947	19970724	00947	GL  	1997	7	24	CA970527013      	3	19970521	G	6114	792100018	BEARING BALLS   			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HC92Z	HC92ZK8     	GL  	HUB BEARINGS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1920 	198  				L300536	1328L		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADE BEARING BALLS WERE FOUND CORRODED AND REMOVED FRO	M SERVICE.					1	L	7	1 	3O	3	O		1A15    	E286	5	C	P892	 
1997072500030	19970725	00030	GL  	1997	7	25	CA970527014      	3	19970521	G	6110		PROPELLER       			CESSNA	208   	208         	2073702	CE  						MCAULY	3G34C7	3GFR34C701  	GL  	PROP ASSY	MIS OHAULED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									950255		(CAN) PROPELLER RECEIVED FOR BENCH CHECK. NUMEROUS FAILURES FOUND INCLUDING: WRONG TYPE OF DE-ICER BOOT; BULKHEAD INSTAL	LED ON WRONG SIDE OF SLIP RING; LOW STOP COLLAR INSTALLED IN WRONG POSITION; LOW STOP COLLAR RUNOUT WAS GREATER THAN MAX	 ALLOWABLE; SLIP RING RUNOUT WAS .012" MAX .010"; BALANCE OUT BY 21 WEIGHTS ON ONE BLADE; COARSE THREAD SCREW IN FINE TH	READ HOLE; INCORRECT LINK PIN BOLT INSTALLED; DE-ICER LEADS INSTALLED INCORRECTLY; FOUND 1/2" OF LOCKING WIRE IN PROPELL	ER HUB BALL BEARING AND RACE; WRONG SCREWS INSTALLED TO RETAIN SLIP RING; 3 CYLINDER SCREWS NOT LOCKWIRED. PROPELLER REP	AIRED.	1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1997072400957	19970724	00957	NM  	1997	7	24	CA970528010      	1	19970526	G	2420	976J1198	GENERATOR       			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					NR 3 ENGINE	GROUND FAULT    	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			CR	CRUISE         	1			CA				4402 				P653620B			(CAN) DURING CRUISE FLIGHT THE #3 ENGINE DRIVEN GENERATOR TRIPPED OFF LINE DUE TO A DIFFERENTIAL FAULT INDICATION. CSD D	ISCONNECTED AND FLIGHT CONTINUED WITHOUT INCIDENT. UNABLE TO DUPLICATE, GENERATOR REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997072400962	19970724	00962	GL  	1997	7	24	CA970529002      	3	19970514	G	6111	S82NC2	BLADE           			CESSNA	185   	A185F       	2072821	CE  						MCAULY	3A32C	D3A32C*     	GL  	LEADING EDGE	SPRAY CUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				307  					816394		(CAN) 1/4" WAS REMOVED FROM THE LEADING EDGES OF THE PROPELLER BLADES AND HAD TO REDUCE BLADES TO MINIMUM DIAMETER TO RE	TAIN PROPER TIP SHAPE. THE PROPELLER BLADES WERE DAMAGED BY WATER SPRAY CUTS.					1	H	7	1 	3O				3A24    		5	C	P21EA	 
1997072400963	19970724	00963	GL  	1997	7	24	CA970529004      	3	19970512	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	LEAD EDGE & FACE	STONE DAMAGED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1786 						728962		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE TO THE PROPELLER LEADING EDGE REQUIRED FILING,  AND STON	E DAMAGE TO THE PROPELLER FACE REQUIRED GRINDING.															5	N	P910	 
1997072400971	19970724	00971	GL  	1997	7	24	CA970530002      	3	19970523	G	6111	90DCA2	BLADE           			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LEADING EDGE	SPRAY CUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1075 	350  				21212171RR	750680		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. SPRAY CUTS ON THE LEADING EDGE REQUIRED FILING.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA	 
1997072400972	19970724	00972	GL  	1997	7	24	CA970530003      	3	19970522	G	6111	80VA0	BLADES          													MCAULY	D3A34	D3A34C403   	GL  	ALL BLADES	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			896  	626  					812046		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. ALL THREE BLADES WERE FOUND CORRODED AT THE SNAP RING GROOVES																5	C	P47GL	 
1997072400973	19970724	00973	GL  	1997	7	24	CA970530004      	3	19970520	G	6111	90DCA10	BLADE           			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	LEADING EDGE	SPRAY CUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1032 	469  				235885	773631		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADE HAD SPRAY CUT ON LEADING EDGE. THE PROPELLER HUB REAR	 BORE AS OVERSIZE.					1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1997072400974	19970724	00974	GL  	1997	7	24	CA970530005      	3	19970521	G	6111		BLADE           			CESSNA	172   	172M        	2072418	CE  						MCAULY	1A175	1A175*      	GL  	LEADING EDGE	SPRAY CUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1934 	815  					P77660		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. LEADING EDGES OF PROPELLER BLADES FOUND WITH SPRAY CUTS.						1	H	7	1 	3O			NT	3A12    		5	N	P857	 
1997072400975	19970724	00975	GL  	1997	7	24	CA970530006      	3	19970523	G	6111		BLADE           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	LEADING EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11298	1863 				265467H	G15399		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE LEADING EDGES OF THE PROPELLER BLADES W	HICH REQUIRED FILING.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1998050100250	19980501	00250	SO  	1998	5	1	CA970530008      	1	19970522	G	5210	9699506	SKIN            			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O360  	AEIO360A1A  	41514	EA  	HARTZL	HCA2V	BHCA2VF3    	GL  	PAX DOOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			366  					L25667484	HK76A		(CAN) AFT CABIN DOOR SKIN DELAMINATED IN AREA OF FORWARD LOWER LATCH.  REPAIRED.						1	L	7	1 	3O	3	O		A3SO    	1E10	5	C	P24EA	 
1997073100403	19970731	00403	GL  	1997	7	31	CA970602008      	3	19970601	G	6114		HUB             													MCAULY	1A103	1A103TCM    	GL  	FORWARD FACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8260 						R77216		(CAN) PROPELLER REMOVED FOR COMPLIANCE WITH AD 97-06-16. USING EDDY CURRENT NDT CRACKS WERE FOUND IN THE FORWARD FACE OF	 THE PROPELLER HUB.															5	N	P50GL	 
1997073100412	19970731	00412	GL  	1997	7	31	CA970603012      	3	19970529	G	6114	1939	PISTON          			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			823  	1711 				846093R4	745275		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PISTON FOUND WORN, PISTON REPLACED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997073100413	19970731	00413	EA  	1997	7	31	CA970603013      	3	19970527	G	6111		BLADES          			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	PROP LE EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3041 					L3455727A	A52300		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE FOUND ON THE LEADING EDGES OF THE PROPELLER BLADES.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997073100423	19970731	00423	EA  	1997	7	31	CA970603024      	1	19970523	G	5210	44424352	ACTUATOR        			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					MAIN PAX DOOR	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			CA			2440 					GEE807385			(CAN) AFTER FLIGHT ATTENDANT REPORTED LOUD NOISE COMING FROM PASSENGER DOOR, FLIGHT RETURNED TO START POINT. MAIN PASSEN	GER DOOR AFT SNUBBER SHOWED LACK OF CABLE TENSION AND THE LEFT CABLE BRACKET HUNG DOWN AND DAMAGED THE DOOR ON CLOSURE. 	PASSENGER DOOR REPAIRED, AND THE DOOR CUT OUT SEAL DEPRESSOR REPAIRED. NEW CABIN DOOR ASSIST ACTUATOR INSTALLED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1998050100255	19980501	00255	SO  	1998	5	1	CA970603027      	1	19970526	G	3220	9617800	SPRING          			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			CA								L954751A	AU8165A		(CAN) NLG LIGHT WOULD NOT COME ON TO INDICATE DOWN AND LOCKED.  FLY-BY INDICATED NLG IN LANDING POSITION.  AIRCRAFT LAND	ED AND NOSE GEAR COLLAPSED SHORTLY AFTER TOUCHDOWN.  MOST FLUID LOST DUE TO PERFORATED PRESSURE LINE P/N 95153-43 AFTER 	GEAR SELECTED UP.  EMERGENCY GEAR DOWN MECHANISM FAILED TO LOCK THE GEAR DOWN DUE TO SPRING P/N 96178-00 WAS OFF ITS HOO	KS.  SPRING RECONNECTED AND LINE REPLACED.			1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
2000021200005	20000212	00005	SO  	2000	2	12	CA970603028      	1	19970524	G	3246	754759	WHEEL           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA			9165 					L810948	BP9052		(CAN) DURING LANDING, PILOT NOTICED THERE WAS A TIRE BLOW-OUT ON THE RT SIDE.  MAINTENANCE CHECK REVEALED WHEEL RIM WAS 	CRACKED FIVE INCHES.					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997072400977	19970724	00977	NE  	1997	7	24	CA970604004      	2	19970522	G	7200		ENGINE          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					#1 ENGINE	FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			4    					AE0014			(CAN) DURING TEST FLIGHT FOR SNAG CLEARANCE AND IN RESPONSE TO HIGH ITT AND AN INDICATION OF A POSSIBLE UNCONTROLLED UNF	EATHERING OF THE #1 ENGINE ON AN AIR RESTART, THE PILOT-IN-COMMAND SHUT DOWN AND SECURED THE AFFECTED ENGINE IN ACCORDAN	CE WITH STANDARD COMPANY TEST FLIGHT PROCEDURES. THE AIRCRAFT DIVERTED AND AN UNEVENTFUL LANDING WAS CARRIED OUT. THE PR	OP COULD NOT BE TURNED ON THE GROUND. FURTHER REPORT TO FOLLOW.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997073100426	19970731	00426	EA  	1997	7	31	CA970604005      	1	19970515	G	7931		GAUGE           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   									#1 ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE #1 ENGINE OIL PRESSURE WENT TO THE RED LINE. UNSCHEDULED LANDING CARRIED OUT. OIL PRESSURE GAUGE 	REPLACED.					2	H	7	2 	4T			RT	A13NM   					 
1997072400978	19970724	00978	NE  	1997	7	24	CA970604006      	2	19970515	G	7200		ENGINE          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					NR 2 ENGINE	FAILED          	W				A				UNSCHED LANDING         				P	O		NO WARNING INDICATION     	OTHER                     		CL	CLIMB          	1			CA											(CAN) DURING CLIMB #2 ENGINE TORQUE WAS FLUCTUATING +5 PERCENT AND FUEL FLOW WAS ALSO FLUCTUATING. THE CLIMB WAS ABORTED	 AND THE AIRCRAFT RETURNED TO BASE, REPORT TO FOLLOW.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997081500005	19970815	00005	GL  	1997	8	15	CA970604007      	3	19970529	G	6114	2421	LOW STOP        			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER HUB	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				140  				L1355740	CH21303		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND AN INCORRECT STOP INSTALLED. LOW STOP NUT WOULD NOT 	LOCK. A LONGER STOP WAS INSTALLED.					1	L	7	1 	3O	3	O		2A13    	E295	5	C	P920	 
1997081400276	19970814	00276	GL  	1997	8	14	CA970604008      	3	19970522	G	6114		HUB             													MCAULY	1A103	1A103TCM    	GL  	PROP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				5461 					R770128		(CAN) EDDY CURRENT NDT INSPECTION FOUND CRACKS IN THE PROPELLER HUB. THE CRACKS WERE REPAIRED AND THE PROPELLER RETURNED	 TO SERVICE.															5	N	P50GL	 
1997081400277	19970814	00277	EA  	1997	8	14	CA970604009      	1	19970518	G	3244	0316140	TIRES           			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					BOTH NLG WHEEL	BLOWN           	W				C				ABORTED TAKEOFF         				G	O		MULTIPLE FAILURE          	OTHER                     		TO	TAKEOFF        	1			CA								0			(CAN) BOTH LEFT AND RIGHT NOSE GEAR TIRES BLEW ON TAKEOFF ROLL. BOTH TIRES, AS WELL AS BOTH LEFT AND RIGHT NOSE WHEELS S	UFFERED EXTENSIVE DAMAGE. NO REPORT OF DAMAGE TO GEAR OR DOORS. INVESTIGATION UNDERWAY.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997081400278	19970814	00278	NE  	1997	8	14	CA970604011      	2	19970529	G	7210	310703201	BEARING         								PWA   	120   	PW120A      		NE  					RED GRBOX NR 19	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13156					121112			(CAN) REDUCTION GEARBOX WAS SENT FOR INVEST. DUE TO METAL CONTAMINATION. DISASSY FOUND- CAUSE OF- METAL CONTAMINATION WA	S- #19 BEARING WHICH WAS SEVERELY SPALLED ON- INNER RACE WITH SUBSTANTIAL MATERIAL LOSS. THIS DAMAGE WAS MORE THAN SUFFI	CIENT TO EXPLAIN- METAL CONTAMINATION OBSERVED.- #15 BEARING WAS REJECTED FOR ELECTRICAL DISCHARGE PITTING BUT HAD SHED 	NO SERIOUS QUANTITY OF MATERIAL & WAS NOT- SOURCE OF- METAL.-RE IS NO MEASUREABLE RESIDUAL MAGNETISM ON ANY OF- STEEL CO	MPONENTS, SO LIGHTNING IS NOT BELIEVED TO BE INVOLVED. BASED ON- PRESENCE OF ELECTRICAL DISCH ARGE PITTING ON- #15 BEARI	NG,- #19 BEARING ALSO SUFFERED SOME ELECTRICAL DISCHARGE WHICH RESULTED IN SPALLING & MATERIAL LOSS.						4	T			E20NE				 
1998050100157	19980501	00157	SO  	1998	5	1	CA970605007      	1	19970522	G	7112		BAFFLE          			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O360  	AEIO360A1A  	41514	EA  	HARTZL	HCA2V	BHCA2VF3    	GL  	ENGINE AIR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			366  					L25667484	HK76A		(CAN) GOVERNOR ROD END BOLT RUBBING AGAINST FORWARD ENGINE BAFFLE CAUSING GROOVE GREATER THAN 50 PERCENT OF THE THICKNES	S OF THE BAFFLE.  STATICALLY THE BAFFLE IS OK, BUT IN-FLIGHT UNDER AIR LOADS THE BAFFLE MOVES AGAINST THE BOLT CAUSING R	UBBING AGAINST THE BAFFLE.  BAFFLE SECURED.				1	L	7	1 	3O	3	O		A3SO    	1E10	5	C	P24EA	 
1997072400980	19970724	00980	EA  	1997	7	24	CA970605010      	1	19970522	G	3244	0316140	TIRE            			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					LT AND RT NLG	BLOWN           	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			G	O		MULTIPLE FAILURE          	OTHER                     		TO	TAKEOFF        	1			CA											(CAN) BOTH LEFT AND RIGHT NOSE LANDING GEAR TIRES BLEW ON TAKEOFF ROLL AT 100 KNOTS. COMPLETE LOSS OF PRESSURE. TAKEOFF 	ABORTED. SEVERE DAMAGE TO BOTH TIRES. SIGNIFICANT DAMAGE TO NOSE LANDING GEAR WHEEL RIM ASSEMBLIES. ALSO DAMAGE TO AFT N	OSE GEAR DOOR.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997081400282	19970814	00282	NE  	1997	8	14	CA970605011      	2	19970526	G	7210	310703301	BEARING         								PWA   	120   	PW120       		NE  					RED  GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14091					120934			(CAN) REDUCTION GEARBOX (RGB) WAS SENT FOR REPAIR AFTER REPORT THAT THE RGB WAS MAKING METAL. DISASSEMBLY REVEALED THE C	AUSE OF THE RGB MAKING METAL WAS THE SPALLING OF THE #15 BEARING. THE #15 BEARING HAD ELECTRICAL PITTING SUGGESTING DAMA	GE FROM ELECTRICAL DISCHARGE AS THE MOST LIKELY REASON FOR THE SPALLING. NONE OF THE COMPONENTS IN THE RGB HAD HIGH MAGN	ETISM ON DISASSEMBLY SO A LIGHTNING STRIKE IS NOT CONSIDERED LIKELY. IT THEREFORE APPEARS THAT THE ELECTRICAL DISCHARGE 	ORIGINATED FROM STRAY DISCHARGE FROM EXTERNAL SOURCE. THE #15 BEARING BOLTS WERE LOOSE. THESE BOLTS TYPICALLY BACK OFF I	F THERE IS A BEARING FAILURE.						4	T			E20NE				 
1998050100154	19980501	00154	CE  	1998	5	1	CA970609020      	1	19970514	G	7120	11891002537	TRUSS           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20229					PCE32139	FW1017		(CAN) WHILE CARRYING OUT ROUTINE INSPECTION  PER AWD 95-02-18 AND SB 2255, A CRACK WAS FOUND ON THE ENGINE MOUNT.  MOUNT	 ASSEMBLY REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
1997081400289	19970814	00289	GL  	1997	8	14	CA970609023      	3	19970524	G	6111	S90AT8	BLADE           			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	PROP	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			415  	258  				1319545R4	802961		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE ON FACE AND LEADING EDGE OF PROPELLER BLADES. DAMAGE REP	AIRED AND CYLINDER SUPPORT REPLACED.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
1997081400290	19970814	00290	GL  	1997	8	14	CA970609024      	3	19970530	G	6111	A16344	BEARINGS        			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A36C	2A36C18     	GL  	BLADE	WORN RUSTY      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2265 	602  				485949K4	62425		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BALANCE WEIGHTS AND BALLS AND SCREWS RUSTY AND WORN. PARTS REPLACED.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P880	 
1997081400292	19970814	00292	GL  	1997	8	14	CA970609026      	3	19970527	G	6111		BLADE           													MCAULY	1A103	1A103TCM    	GL  	PROP	BELOW SPEC      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13668	5408 					RP772951		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER BLADE BELOW MINIMUM WIDTH AT STATION 3	3" FOR 67" DIAMETER.															5	N	P50GL	 
1997081400293	19970814	00293	GL  	1997	8	14	CA970609027      	3	19970522	G	6111	B3905	ACTUATING PIN   													MCAULY	2A34C	2A34C203    	GL  	BLADE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				351  					767305		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE ACTUATING PIN WAS FOUND WITH THE CHROME WORN.																5	C	P3EA	 
1997081400294	19970814	00294	GL  	1997	8	14	CA970609028      	3	19970530	G	6114	5480	HUB             													MCAULY	2A34C	2A34C66     	GL  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			863  	76   					768777		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. EXTERIOR OF HUB WAS FOUND CORRODED WITH CRACKS IN THE THREADS. HUB WA	S REPLACED WITH HUB S/N 773509. BLADE NUT WAS FOUND CRACKED AND WAS REPLACED. THE CYLINDER SUPPORT WAS ALSO REPLACED.															5	C	P3EA	 
1997081400295	19970814	00295	GL  	1997	8	14	CA970609029      	3	19970530	G	6111	90DHB16E	BLADE           			MOONEY	M20   	M20J        	5870219	SW  						MCAULY	2D34C	B2D34C214   	GL  	SNAP RING GROOVE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				898  					733779		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECITON. BLADE(S) FOUND CORRODED, BLADES WERE MACHINED TO REMOVE CORROSION. BL	ADE AND HUB WERE ANODIZED. ACTUATING PIN FOUND WORN, PIN WAS REPLACED.					1	L	7	1 	3O				2A3     		5	C	P7EA	 
1997081400296	19970814	00296	GL  	1997	8	14	CA970609030      	3	19970603	G	6111	90DCA2	BLADE           	MCAULY      												MCAULY	2A34C	2A34C203    	GL  	LEADING EDGE	SPRAY CUT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			812  						911650		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADES WERE TRIMMED. THE CYLINDER AND SNAP RINGS WERE REPLA	CED.															5	C	P3EA	 
1997081400297	19970814	00297	GL  	1997	8	14	CA970609031      	3	19970602	G	6114		HUB             													MCAULY	1A103	1A103TCM    	GL  	PROP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									RP771358		(CAN) PROPELLER WAS REMOVED FOR COMPLIANCE WITH FAA AD 97-06-16. PROPELLER WAS FOUND CRACKED.																5	N	P50GL	 
1997081400302	19970814	00302	CE  	1997	8	14	CA970610003      	1	19970516	G	5740	MS21042L5	LOCK NUT        			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	WING STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								248666R	807440		(CAN) THE NUT WHICH HOLDS THE LOWER WING STRUT TO THE WING STRUT FITTING WAS FOUND TO BE CRACKED. NUT REPLACED						1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
1998050100152	19980501	00152	CE  	1998	5	1	CA970610006      	1	19970602	G	3246	55422232	SPACER          			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					WHEEL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			611  					PCE500171			(CAN) RIGHT NOSE WHEEL SPACER FOUND SEIZED TO AXLE SHAFT.   EXCESSIVE FRICTION BETWEEN SEAL AND SPACER CAUSING THE SPACE	R TO HEAT UP AND SEIZE TO SHAFT. SECOND CASE WITHIN 11.1 HOURS.  REF:  CESSNA SL 560-32-27.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1997081400308	19970814	00308	NE  	1997	8	14	CA970610011      	2	19970527	G	7250		CT BLADES       								PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	FRACTURED       	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA				1320 				92562			(CAN) DURING DESCENT THERE WAS A LOUD BANG. THE PILOT SECURED THE ENGINE. POST FLIGHT INSPECTION AT THE "C" FLANGE REVEA	LED SEVERAL CT BLADES FRACTURED. THE ENGINE IS BEING RETURNED TO THE MANUFACTURER.										4	T			E4EA				 
1997081400312	19970814	00312	GL  	1997	8	14	CA970612004      	3	19970604	G	6111	A1303A	BLADE BEARING   			CONAER	LA4   	LA4         	5110302	NE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HC92Z	HC92ZK8     	GL  	EXTERIOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				271  				L347636	2236L		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTIOIN. BLADE BEARINGS, BALLS, BLADE CLAMPS AND CYLINDER WERE FOUND CORRODED	. PARTS WERE REPLACED.					1	H	7	1 	3O	3	O		1A13    	E286	5	C	P892	 
1997081400314	19970814	00314	GL  	1997	8	14	CA970612006      	3	19970605	G	6114	3905	PIN BASE ASSEMBL			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	PROP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								356092	799714		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PIN BASE ASSEMBLY REPLACED DUE TO WE						1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1997081400315	19970814	00315	GL  	1997	8	14	CA970612007      	3	19970612	G	6111		BLADE           													MCAULY	1A101	1A101DCM    	GL  	LEADING EDGE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1124 					G4112		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BLADE(S) LEADING EDGES DAMAGED BY STONES.																5	N	P918	 
1997081400317	19970814	00317	NE  	1997	8	14	CA970612010      	2	19970531	G	8530	81888	PISTON          	PWA         	84898       						PWA   	R2800 	R280079     	52026	NE  					#8 CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			746  					086036			(CAN) ENGINE WAS SHUTDOWN IN FLIGHT DUE TO ROUGH RUNNING ENGINE. POST FLIGHT INSPECTION FOUND THE #8 CYLINDER PISTON BRO	KEN. THE SUBMITTER SUGGESTS THAT A HYDRAULIC LOCK PREVIOUSLY MAY HAVE CONTRIBUTED TO THIS FAILURE.										4	R			5E8				 
1998040200082	19980402	00082	CE  	1998	4	2	CA970612011      	1	19970522	G	5530	04310093	BRACKET         		04310093    	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	VERTICAL FIN	SEPERATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10358					L2354915	RJG015		(CAN) WHILE INSPECTING THE VERTICAL FIN, A CRACKLING NOISE WAS NOTED.  INSPECTION REVEALED A FINE CRACK BETWEEN THE BRAC	KETS.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
1998050100150	19980501	00150	SO  	1998	5	1	CA970612013      	1	19970607	G	3260		CONNECTOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	MLG	DISCONNECTED    	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			5997 					L261348	BP3109		(CAN) AIRCRAFT WAS DESCENDING AND SELECTED GEAR BUT DID NOT GET A DOWN AND LOCKED SIGNAL.  VERIFICATION WAS CARRIED OUT 	FOR DOWN AND LOCKED AND AIRCRAFT LANDED.  INSPECTION FOUND THE CONNECTOR WIRE BUNDLE DISCONNECTED.  NO APPARENT REASON.					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1998050100149	19980501	00149		1998	5	1	CA970612014      	1	19970606	G	7910		LID             								AMTRRW	152   	ROTWY152    	99999	GL  					OIL FILTER COVER	SEPERATED       	W				F				ACTIVATE FIRE EXT.      				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA			20   					1266			(CAN) THE FITTING SEPARATED FROM THE COVER ALLOWING AN OIL LEAK INTO THE ENGINE COMPARTMENT.  A FIRE STARTED RESULTING I	N TOTAL LOSS OF AIRCRAFT.  NO INJURY.										3	O			EXPE3O				 
1998050100148	19980501	00148	SO  	1998	5	1	CA970618001      	1	19970607	G	5531	6697200	RIB             			PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320B2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4509 					L476739	A48782		(CAN) VERTICAL STABILIZER REMOVED FOR PAINT STRIPPING.  THE TWO RIBS P/N 66972-00 AND P/N 63506-00 WERE FOUND CORRODED A	ND NEEDED REPLACING.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614	 
1997081400324	19970814	00324	GL  	1997	8	14	CA970618015      	3	19970610	G	6111		BLADE           													MCAULY	1A170	1A170*      	GL  	LEADING EDGE	BLUNTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2587 						MC044		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADE(S) WERE FOUND BLUNTED.																5	N	P857	 
1997081400325	19970814	00325	GL  	1997	8	14	CA970618016      	3	19970610	G	6114	C840	HUB             													HARTZL	HC82V	HC82V*      	GL  	PROP	RUSTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1302 	14   					T1315N		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER HUB AND BLADES CLAMPS WERE FOUND RUSTY. PARTS WERE REPLATED	.															5	C	P23EA	 
1997081400326	19970814	00326	GL  	1997	8	14	CA970618017      	3	19970610	G	6114	2345	ROD PITCH CHANGE													MCAULY	2A34C	2A34C203    	GL  	HUB	PITTED BENT     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5525 	579  					745125		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND AN INTERNAL OIL LEAK AND THE PROPELLER PITCH CHANGE 	ROD PITTED AND BENT. PROPELLER REPAIRED AND THE PITCH CHANGE ROD AND CYLINDER SUPPORT WERE REPLACED.															5	C	P3EA	 
1997081400328	19970814	00328	EU  	1997	8	14	CA970618019      	1	19970525	G	3230	DSB1102	PROX SENSOR     	MESSIER     	D22121300   	AIRBUS	310   	A310304     		EU  										LH LANDING GEAR	FAILED          	W				A				UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA			15977	879  		00B257					(CAN) UNABLE TO RETRACT LANDING GEAR ON SYSTEM #1, SYSTEM #2 SELECTED AND GEAR RETRACTED. AFTER PASSING 'TAKE-OFF INHIB'	 (LIFT OFF PLUS 1 MINUTE) THE FOLLOWING FAILURES OCCURRED. CABIN PRESSURE REG #1 - CAPT. PITOT HEAT AND TAT HEAT - F/O P	ITOT HEAT - FAC #1 - ATS #1. THE LH LANDING GEAR SHOCK ABSORBER (65 GB) WAS REPLACED. CONFIRMED UNSERVICEABLE BY METER C	HECK. RETRACTION TEST CARRIED OUT SERVICEABLE.			2	L	7	2 	4F			RT	A35EU   					 
1998050100144	19980501	00144	SO  	1998	5	1	CA970618022      	1	19970611	G	7810	3342002	EXHAUST STACK   			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	CONNECTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6971 					L104448	BP3110		(CAN) INSPECTION FOUND THE EXHAUST CROSSOVER PIPE BROKEN AT THE SHROUD.  ALSO THE ALTERNATE AIR SPRING DOOR MISSING.  HI	NGE BROKEN.  DOOR FOUND IN BOTTOM OF AIR BOX.					1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA	 
1997081400473	19970814	00473	EU  	1997	8	14	CA970620012      	2	19970603	G	8520		VALVE LIFTERS   								ROTAX 	912   	ROTAX912    	55555	EU  					HEAD ASSY	STICKING        	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				316  				4412587			(CAN) ENGINE FAILED TO DEVELOP FULL POWER ON TAKEOFF. INSPECTION FOUND THE VALVES AND LIFTERS STICKING. THE HEAD ASSEMBL	Y AND ALL THE LIFTERS WERE REPLACED.										3	I			EXPE3I				 
1997081400479	19970814	00479	NE  	1997	8	14	CA970620020      	2	19970609	G	7210	310062301	BEARING         								PWA   	118   	PW118       		NE  					RED GEARBX NR 18	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18127	6260 				115381			(CAN) THE ENGINE WAS REMOVED DUE TO METAL CONTAMINATION IN THE REDUCTION GEARBOX. ON INITIAL DISASSEMBLY THERE WAS NO SI	GN OF OBVIOUS DAMAGE WITH SIGNIFICANT MATERIAL LOSS UNTIL THE #18 BEARING WAS REMOVED. THE BEARING HAD SUBSTANTIAL SPALL	ING ON THE INNER RACE. THE SPALLING WAS LARGELY CONTINUOUS OVER APPROXIMATELY 150 DEGREES OF CIRCUMFERENCE, BEING FORMED	 BY WHAT APPEARED TO BE A SERIES OF CONNECTING PATCHES. THE REGULAR SPACING AND PATCHY APPEARANCE OF THE SPALLING STRONG	LY SUGGESTS THAT IT ORIGINATED WITH BRINNELLING OF THE BEARING FROM SOME AXIAL LOADING AT SOME TIME. THERE IS NO SIGNIFI	CANT MAGNETISM AND LIGHTNING IS NOT THOUGHT TO BE A FACTOR.						4	T			E20NE				 
1998050100142	19980501	00142	WP  	1998	5	1	CA970624001      	1	19970609	G	6300	D1742	FANWHEEL        			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					CENTER HUB	CRACKED         	W				C	A			ABORTED TAKEOFF         	UNSCHED LANDING         			G	S		MULTIPLE FAILURE          	AFFECT SYSTEMS            		HO	HOVERING       	1			CA			44   					L2453840A			(CAN) BEFORE FIRST FLIGHT OF DAY, AIRCRAFT IN HOVER.  CLUTCH LIGHT FLICKERING AND PILOT HEARS GROWLING AND FEELS VIBRATI	ON.  INSPECTION FOUND CENTER HUB IN THE FAN HAD CRACKED COMPLETELY AROUND CAUSING THE CENTER HUB BOLTS TO LOOSEN OFF.  T	HERE WAS ALSO A LOT OF METAL TRANSFER BETWEEN FAN WHEEL AND TAPERED SHAFT OF BEARING ASSY (P/N C007-5).				1	G	7	1 	3O	3	O		H11NM   	E295				 
1997081400480	19970814	00480		1997	8	14	CA970624003      	4	19970616	G	6113	A2405	LOCK NUT        													HARTZL	HCE2Y	HCE2YL2     	GL  	SPINNER	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									BG679		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER SPINNER NUT FOUND TO BE P/N A2405-3 WHICH IS THE WRONG PART	, THE NUT WAS REPLACED WITH THE PROPER NUT P/N A2405-1.															5	C	P9EA	 
1997082200001	19970822	00001	NE  	1997	8	22	CA970624004      	3	19970616	G	6111	70096	BEARING         													HAMSTD	12D	12D40       	NE  	PROP BLADE	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									18786		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER ROLLER BEARINGS WERE FOUND PITTED AND OUT OF SHAPE.																5	C	P257	 
1997081400481	19970814	00481	GL  	1997	8	14	CA970624005      	3	19970612	G	6114	4457	ACTUATING PIN   			MAULE 	M5    	M5210C      	5460134	SO  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	LINK AREA	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				85   				62849R	755340		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. ACTUATING PIN FOUND WORN. THE PIN WAS REPLACED.						1	H	7	1 	3O	3	O		3A23    	E1CE	5	C	P3EA	 
1997081800013	19970818	00013	NE  	1997	8	18	CA970624006      	3	19970613	G	6114	51539	CYLINDER        													HAMSTD	2D	2D30        	NE  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2322 	618  					37245		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CYLINDER AND HUB BARREL WERE FOUND CORRODED. THE HUB BARREL WAS PLATE	D AND THE CYLINDER WAS REPLACED.															5	C	P206	 
1997081400482	19970814	00482	GL  	1997	8	14	CA970624007      	3	19970612	G	6114	2431	HUB BOLTS       			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2708 	625  				L361555A	BG3532		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER HUB NUTS AND BOLTS FOUND CORRODED. HUB NUTS AND BOLTS WERE 	REPLACED.					1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA	 
1997091100349	19970911	00349	NE  	1997	9	11	CA970624020      	2	19970604	G	7230	794909	HP COMP DISC    								PWA   	JT9   	JT9D7AH     	52054	NE  					9TH STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			52272	2576 		H85185		U42			(CAN) DURING DISASSEMBLY AND INSPECTION OF THE HIGH PRESSURE COMPRESSOR A CRACK, BEYOND ACCEPTABLE LIMITS, WAS FOUND IN 	THE BLADE SLOT AREA OF THE 9TH STAGE DISC. THE 9TH STAGE DISC WAS SCRAPPED AND SENT TO THE MATERIAL REVIEW DEPARTMENT FO	R EVALUATION.									4	F			E20EA				 
1997091100350	19970911	00350	NE  	1997	9	11	CA970624021      	2	19970604	G	7240	80455401	GASKET ASSEMBLY 								PWA   	JT9   	JT9D7AH     	52054	NE  					#3 BEARING AREA	PINCHED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			52272	2500 				U54			(CAN) DURING REMOVAL AND INSPECTION OF THE DIFFUSER CASE, IN THE #3 BEARING COMPARTMENT, A GASKET ASSEMBLY OF SPIRAL WOU	ND WAS FOUND PINCHED ALLOWING HOT AIR TO ENTER THE COMPARTMENT. ACCUMULATION OF SOFT COKING ON THE RIGHT HAND SIDE OF TH	E FRONT SUPPORT RESULTED IN SUBSEQUENT CLOGGING OF THE #3 SCAVENGE SCUPPER DRAIN ALLOWING THE OIL TO OVER FLOW IN THE EN	GINE, EXITING IN THE EXHAUST AREA. THE FRONT COOLING AIR DUCT WAS REMOVED TO VERIFY AND INSTALLATION OF THE PARTS. THE C	RUSHED SEAL WILL BE REPLACED AND THE DIFFUSER CASE WILL BE REBUILT.							4	F			E20EA				 
1997091100357	19970911	00357	NE  	1997	9	11	CA970624029      	2	19970527	G	7250	312001101	TURBINE BLADE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					BASE OF BLADE	BROKEN          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			3446 	1420 				PCE92562			(CAN) INFLIGHT ENGINE FAILURE, EMERGENCY LANDING ON SMALL LAKE. POST FLIGHT INSPECTION FOUND COMPRESSOR TURBINE WHEEL BL	ADE FRACTURED, DAMAGING ADJACENT BLADES. THE FAILED BLADE WAS VERIFIED AND IT SHOWED TO HAVE AN OIL CRACK OF ABOUT 3/16"	, PROGRESSING FROM THE LEADING EDGE OF THE BLADE TOWARDS THE CENTRE (OF THE CHORD) AT ABOUT 1/8" FROM THE BASE.				1	H	7	1 	3R	4	T		A815    	E4EA				 
1997091100361	19970911	00361		1997	9	11	CA970624033      	1	19970613	G	7921	311161801	OIL COOLER      								PWA   	118   	PW118       		NE  					ENG OIL	LEAK            	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			16201	1949 				115419			(CAN) THE ENGINE WAS SENT FOR REPAIR AFTER THE OPERATOR REPORTED AN IN-FLIGHT SHUTDOWN AFTER THERE WAS AN OIL WARNING ON	 TAKEOFF ROLL. INSPECTION FOUND THE HP ROTOR LOCKED AND THE ENGINE HAD LOST 10 QUARTS OF OIL. DISASSEMBLY OF THE ENGINE 	FOUND THE #4 AND #5 BEARING HAD LOST METAL WITH HEAVY RUBBING DAMAGE TO THE HP STUB SHAFT, HP IMPELLER, HP IMPELLER HOUS	ING AND MOST OF THE AIR SEALS IN THE AREA OF THE HP ROTATING ASSEMBLY. ALL THIS DAMAGE WAS FOUND TO BE DUE TO LOSS OF OI	L CAUSED BY LEAK IN THE AIRFRAME OIL COOLER.							4	T			E20NE				 
1997091100362	19970911	00362	EU  	1997	9	11	CA970625002      	1	19970612	G	2913	PVB0222	PUMP            			AMD   	FALC50	FALCON50MYST	2730106	EU  										#2 ENG HYD	FAILED          	W				E				ENGINE SHUTDOWN         				J	E		WARNING INDICATION        	VIBRATION/BUFFET          		CR	CRUISE         	1			CA			2938 	2938 							(CAN) AT CRUISE, AN UNUSUAL NOISE AND VIBRATION WAS HEARD AND FELT FOLLOWED BY #2 HYDRAULIC PUMP FAIL LIGHT. #1 SYSTEM P	RESSURE WAS NORMAL. ALTHOUGH NOT REQUIRED, #2 ENGINE WAS SHUT DOWN AS A PRECAUTIONARY MEASURE. POST FLIGHT INSPECTION DE	TERMINED THAT #2 HYDRAULIC PUMP HAD FAILED.				2	L	7	3 	4F				A46EU   					 
1997091100363	19970911	00363	GL  	1997	9	11	CA970625004      	3	19970619	G	6114		HUB             													MCAULY	1A103	1A103TCM    	GL  	PROP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8376 	921  					SRP770650		(CAN) PROPELLER RECEIVED FOR COMPLIANCE WITH FAA AD 97-06-16. PROPELLER HUB FOUND CRACKED.																5	N	P50GL	 
1997091100368	19970911	00368	NE  	1997	9	11	CA970625009      	2	19970612	G	7210	311657801	SPUR GEARSHAFT  								PWA   	120   	PW120       		NE  					REDUCTION GEARBX	SPALLED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			9298 					121229			(CAN) THE REDUCTION GEARBOX WAS SENT FOR REPAIR AFTER IT WAS FOUND MAKING METAL. THE SOURCE OF THE METAL WAS FOUND TO BE	 SPALLING OF ALL 3 OF THE SECOND STAGE GEARS. THERE WAS NO EVIDENCE OF DAMAGE FROM ELECTRICAL DISCHARGE OR LUBRICATION P	ROBLEMS. THERE WAS SOME MISALIGNMENT OF THE SECOND STAGE BEARING BORES THAT DOES NOT APPEAR TO BE SECONDARY DAMAGE FROM 	FRETTING. IT APPEARS LIKELY THAT THE SECOND STAGE GEARS SPALLED DUE TO BEARING BORE MISALGINMENT.								4	T			E20NE				 
1997091100369	19970911	00369	NE  	1997	9	11	CA970625010      	2	19970613	G	7210	210703301	BEARING         								PWA   	120   	PW120A      		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			11922					121186			(CAN) REDUCTION GEARBOX WAS SENT FOR INVESTIGATION AFTER THE OPERATOR REPORTED IT WAS MAKING METAL. DISASSEMBLY OF THE R	EDUCTION GEARBOX FOUND THE CAUSE OF THE MAKING METAL WAS THE SPALLING OF THE #15 BEARING. THE #18 AND #19 BEARINGS AND T	HE OVERSPEED GOVERNOR FRONT BEARING HAD ELECTRICAL ARCING DAMAGE. SEVERAL COMPONENTS HAD VERY HIGH MAGNETISM. IT IS MOST	 LIKELY THE #15 BEARING FAILED (SPALLED) DUE TO LIGHTNING STRIKE.								4	T			E20NE				 
1998050100133	19980501	00133	WP  	1998	5	1	CA970626015      	1	19970514	G	6220	A6481	BEARING         			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					TEETER HINGE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			837  					L1404639A			(CAN) AT 100-HOUR INSPECTION, THE MAIN ROTOR TEETER HINGE BEARING WAS FOUND CHAFED AND ELONGATED.						1	G	7	1 	3O	3	O		H10WE   	E274				 
1997091700003	19970917	00003	EU  	1997	9	17	CA970626017      	1	19970619	G	2611	72111211000	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					AVIONICS RACK	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								0			(CAN) DURING CLIMB, THE AVIONICS RACK SMOKE WARNING LIGHT CAME ON. NO INDICATION OF FIRE OR SMOKE IN AVIONICS RACK. SUBS	EQUENT INVESTIGATION REVEALED NO REASON EXCEPT THAT AVIONICS RACK WAS EXTREMELY DUSTY AND THE DUST COULD HAVE ACTIVATED 	THE WARNING SENSOR. SENSOR REPLACED.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997091100377	19970911	00377	CE  	1997	9	11	CA970626019      	1	19970617	G	5280	4752932	DOOR HINGE      	PIPER       	4752934     	CESSNA	172   	172G        	2072420	CE  	LYC   	O360  	O360A1A     	41514	EA  					L/H GEAR DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8464 					L2821836A			(CAN) ON INSPECTION THE AFT DOOR HINGE WAS FOUND CRACKED ON THE INSIDE OF THE RADIUS OF THE CURVE. SUBMITTER STATES THAT	 THIS PARTICULAR HINGE IS NOT PART OF PIPER SERVICE BULLETIN 682 AND AD 80-26-05.					1	H	7	1 	3O	3	O	NT	3A12    	E286				 
1998050100131	19980501	00131	EU  	1998	5	1	CA970630002      	1	19970623	G	6420	350A33215300	HINGE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BUSHING MOUNT	DELAMINATED     	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			81   					4436			(CAN) DELAMINATIONS CAUSED EXCESSIVE VIBRATION (HIGH FREQ) IN-FLIGHT AND ON GROUND.  SPLITS AND DELAMINATIONS IN EXCESS 	OF ALLOWABLE LIMITS OCCURRED AT VERY LOW T.S.N.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
1998050100130	19980501	00130	SW  	1998	5	1	CA970630003      	1	19970613	G	6220	206010189001	BEARING         		2060101009  	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GRIP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						QSH0038		CAE820326			(CAN) WHEN REPLACING GRIPS FOR TX FOUND BEARING WITH A CRACKED SEPARATOR.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997091100378	19970911	00378	NE  	1997	9	11	CA970630004      	2	19970609	G	7313		FUEL NOZZELS    								PWA   	PWA120	PW125B      		NE  					NR 1 ENGINE	LEAKING         	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			11458					125093			(CAN) DURING THE TAKEOFF ROLL THE #1 ENGINE LOST POWER AND THE "ENGINE OUT" LIGHT ILLUMINATED. THE TAKEOFF WAS ABORTED A	ND THE AIRCRAFT RETURNED TO THE GATE. SUBSEQUENT INSPECTION REVEALED A HEAVY FUEL LEAK THROUGH THE ENGINE DRAIN. THE FUE	L NOZZLES WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.									4	T			E20NE				 
1998050100127	19980501	00127		1998	5	1	CA970702021      	4	19970618	G	6113	0550338K200	SPINNER PROP    		0550338K200 	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	SCREW HEADS	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			63   					355352	776506		(CAN) THE PROP SPINNER WAS CHANGED DUE TO CRACKING AT 21.7 HOURS.   AT 62.5 HOURS THE NEW SPINNER TORE AT THE SCREW ATTA	CH HOLES.  SUBMITTER INSTALLED AN OLDER SPINNER AND SUGGESTS A MANUFACTURING FAULT.					1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1998050100126	19980501	00126	SO  	1998	5	1	CA970702024      	1	19970620	G	3222	9572300	TRUNNION        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	NOSE GEAR	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			5982 					L985751A	AU8166A		(CAN) APPROXIMATELY 1.5 INCH SECTION OF THE TRUNNION LUG ON THE RIGHT HAND SIDE BROKE OFF.  THIS ALLOWED THE NOSE GEAR T	O TRACK OUT OF POSITION BY APPROXIMATELY 15 DEGREES.					1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920	 
1998050100125	19980501	00125	SO  	1998	5	1	CA970703001      	1	19970620	G	5520	5423224	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7604 					RL523561A	DJ9916A		(CAN) WHILE COMPLYING WITH PIPER SB 998, BOTH ELEVATOR SPARS WERE FOUND CRACKED.  REPAIRS COMPLETED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998050100123	19980501	00123	SO  	1998	5	1	CA970707015      	1	19970515	G	5730		SKIN            			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	UPPER WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1722 					528369	AM2891		(CAN) FOUND UPPER AND LOWER WING SURFACE SPAR RIVETS SMOKING.  SUBMITTER STATES THAT A SIMILAR PROBLEM WAS ADDRESSED IN 	PIPER SB 796A.					1	L	7	1 	3O	3	O	RT	A25SO   	E8CE	5	C	P920	 
1999081200323	19990812	00323	SO  	1999	8	12	CA970707023      	1	19970623	G	3240	3068	LINING          	CLEVELAND   	3068        	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					BRAKE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			7162 					L163261			(CAN) INCORRECT BRAKE LININGS AND PADS FOUND ON BRAKE ASSEMBLY.  REPLACED WITH CORRECT PARTS.						1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2000021200006	20000212	00006		2000	2	12	CA970707024      	1	19970623	G	3240	753703	PARTS CATALOGUE 																	PARTS CATALOGUE	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SUBMITTER STATES THAT FIG 41 REV APR 1980 MAIN BRAKE ASSY HAS A FAULT.																			 
1998040200083	19980402	00083	EA  	1998	4	2	CA970709003      	1	19970616	G	5531		VERTICAL STAB   			FLEET 	80    	FLEET80     		EA  	CONT  	C85   	C8512F      	17008	SO  	SNSNCH	76A	76AK        	EA  	LEADING EDGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13069					26862	42595		(CAN) LEADING EDGE 4130 TUBE OF VERTICAL STABILIZER FOUND CRACKED THROUGH JUST ABOVE THE SOCKET ON THE FUSELAGE.						1	H	7	1 	3O	3	O		788     	E233	5	N	1P210	 
1998050100120	19980501	00120	SO  	1998	5	1	CA970709005      	1	19970621	G	5520	5423224	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8934 					L366161A	DJDJ10707A		(CAN) COMPLETED SB 998 AND FOUND BOTH SPARS CRACKED.  REPAIRS AND REPLACEMENTS COMPLETED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1998050100119	19980501	00119	CE  	1998	5	1	CA970709010      	1	19970626	G	7120	05131323	RAIL            			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175ATM    	GL  	BOLT HOLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15020					L4880327A	P73951		(CAN) DURING MAINTENANCE, IT WAS DISCOVERED THAT THE LEFT HAND ENGINE RAIL WAS CRACKED.  P/N 0513132-3 STRINGER ASSY IN 	THE FUSELAGE FRONT SECTION WAS REPLACED.  THE ENGINE RAIL WAS CRACKED AROUND THE ENGINE MOUNT BOLT HOLE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
1998040200085	19980402	00085	CE  	1998	4	2	CA970710003      	1	19970624	G	3320	5104WW	BULB            			BEECH 	1900  	1900C       	1154161	CE  										CABIN	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT, A PASSENGER NOTICED SMOKE COMING FROM AN OVEHEAD PANEL.  INVESTGATION FOUND A BURNT FLOURESC	ENT TUBE WHICH WAS  REPLACED BY MAINTENANCE.					2	L	7	2 	4T			RT	A24CE   					 
1997092500699	19970925	00699	WP  	1997	9	25	CA970710009      	1	19970623	G	5751		LONGERON        			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINEERING ORDER EDDY CURRENT INSPECTION E.O. NO.07-238D AILERON LONGERON 6L AT FUSELAGE STN 688 FOUND CRA	CKED. CONFIRMED BY VISUAL INSPECTION. NEW SECTION OF LONGERON REPLACED AS PER STRUCTURAL REPAIR MANUAL 53-02 PAGE 2A.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997092500714	19970925	00714	CE  	1997	9	25	CA970715017      	1	19970619	G	2730	1200161	SPRING          	CESSNA      	1200161     	CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	ELEV FEEL	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			3225 						751359		(CAN) SPRING FAILED IN FLIGHT. A CHANGE IN ELEVATOR FEEL WAS NOTED IN CRUISE AS WELL AS LANDING.						1	H	7	1 	3O				3A24    		5	C	P3EA	 
1998040200086	19980402	00086		1998	4	2	CA970715018      	1	19970607	G	2710		CONTROL CABLE   																	REAR STRUT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON CABLE VIBRATING ON REAR WING STRUT CAUSES WEAR ON BOTH THE AILERON CABLE AND THE STRUT.  SUBMITTER STATES 	THAT THE OLDER WOODEN SUPPORTS DID NOT EXPERIENCE THIS PROBLEM.  IT ONLY OCCURRED WITH THE NEW PLASTIC SUPPORTS.																		 
1997092900005	19970929	00005	EA  	1997	9	29	CA970715019      	2	19970325	G	8530		VALVE SEAT      			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					#6 CYL EXHAUST	COCKED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA			1010 					L584861A			(CAN) DURING INSPECTION #6 CYLINDER WAS FOUND TO HAVE ZERO COMPRESSION. ON REMOVAL OF THE CYLINDER IT WAS FOUND THAT THE	 EXHAUST VALVE SEAT HAD LIFTED AND WAS COCKED AT AN ANGLE HOLDING THE EXHAUST VALVE OPEN. THIS RESULTED IN LACK OF COMPR	ESSION AND CAUSED ADDITIONAL DAMAGE TO THE ENGINE.				1	L	7	1 	3O	3	O		A3SO    	E14EA				 
1998040200087	19980402	00087	EA  	1998	4	2	CA970715020      	2	19970609	G	7320	10038901832	PRESSURE SWITCH 			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	INTERNAL	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCE32053	FW5B2		(CAN) DURING NORMAL OPERATIONS, THE FLIGHT CREW REPORTED THAT THE LEFT NO FUELTRANSFER INDICATION WAS NOT ACTUATING.  MA	INTENANCE REPLACED THE PRESSURE SWITCH AND THE SYSTEM TESTED OK AND THE AIRCRAFT WAS RELEASED.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
1998040200088	19980402	00088	CE  	1998	4	2	CA970715021      	1	19970609	G	7931	5038912133	PRESSURE SWITCH 			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	INTERNAL	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA								PCE32053	FW5B2		(CAN) DURING GROUND OPERATIONS, THE CREW NOTICED THE RIGHT HAND LOW PRESSURE ANNUNCIATOR WAS ACTIVATED. MAINTENANCE REPL	ACED THE PRESSURE SWITCH AND TESTED THE SYSTEM SERVICEABLE.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
1998040200089	19980402	00089	CE  	1998	4	2	CA970715023      	1	19970709	G	2450	S1232510	CIRCUIT BREAKER 			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	INTERNAL	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			3397 					PCE32053	FW5B2		(CAN) CREW SNAGGED THE NR 1 INVERTER WOULD TRIP BUT WAS RESETTABLE.  THE SNAG WAS NOT DUPLICATED ON THE GROUND. TROUBLES	HOOTING FOUND THE BREAKER WOULD SWITCH ON AND OFF WITHOUT PLUNGER ACTIVATION IF VIBRATION WAS INDUCED.  BREAKER REPLACED	.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
1998040200090	19980402	00090	CE  	1998	4	2	CA970715024      	1	19970707	G	3260	5038004811	RELAY           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	INTERNAL	REPLACED        	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			3397 					PCE32053	FW5B2		(CAN) CREW NOTED THAT DURING GEAR RETRACTION/EXTENSION CYLCES, THE TRANSIT LIGHT WOULD INTERMITTENTLY CYCLE ON AND OFF. 	  MAINTENANCE FOUND THE K1 RELAY WAS FAILING.  RELAY REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
1997092500717	19970925	00717	EA  	1997	9	25	CA970715026      	3	19970708	G	6111		BLADES          													SNSNCH	74D	74DM        	EA  	PROP	BELOW LIMITS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4597 	863  					K27325		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BLADE(S) WIDTH BELOW MINIMUM LIMITS.																5	N	P88614	 
1997092500719	19970925	00719	NE  	1997	9	25	CA970715031      	2	19970708	G	7250	311260201	TURBINE BLADE   								PWA   	120   	PW120       		NE  					LP TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			16057	6803 							(CAN) ENGINE DID NOT MEET POWER ASSURANCE LIMITS SO IT WAS SENT TO R&O. DISASSY FOUND- ENGINE HAD SUSTAINED 2 (2) LP TUR	BINE BLADE FRACTURES WITH- LOSS OF- OUTER 40 PCT OF BOTH AIRFOILS.THIS RESULTED IN SECONDARY DAMAGE TO- NEIGHRING & DOWN	STREAM COMPONENTS.- PRIME CAUSE FOR- LP BLADE AIRFOIL FAILURES WAS PROBABLY DAMAGE TO- BLADE MATERIAL MICROSTRUCTURE: TY	PICALLY THIS COULD OCCUR IN AN OVERTEMP EVENT. HOWEVER,- OPERATOR RPTS THAT HIS EXCEEDANCE MONITORING EQUIP SHOW NO SUCH	 EXCEEDANCE EITHER IN STEADY RUNNING OR IN A STARTING TRANSIENT.- R&O SHOP HAS NO EVIDENCE OF- ENGINE PRIOR TO- LAST HSI	 OR WHETHER-RE WAS EVIDENCE OF HOT STREAKING AT THAT TIME.						4	T			E20NE				 
1997092500720	19970925	00720	NE  	1997	9	25	CA970715032      	2	19970704	G	7250	310641201	BEARING HOUSING 								PWA   	118   	PW118       		NE  					6&7 BEARING AREA	BURNING DAMAGE  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17820	3821 				115351			(CAN) THE ENGINE WAS SENT TO R&O FOR REPLACEMENT OF A TIME EXPIRED HP IMPELLER AND FOR AN HSI. DISASSEMBLY FOUND THERE W	AS UNUSUAL DAMAGE TO THE PT1 STATOR PT1 DISK. THERE HAD BEEN A FIRE IN THE FORWARD CAVITY CAUSED BY OIL LEAKAGE FROM THE	 #6 AND #7 BEARING AREA. RESULTING DAMAGE WAS SUSTAINED BY THE PT1 DISK AND BLADES, FRONT DISK SEAL, PT1 STATOR AND BAFF	LES, #6 AND #7 BEARING HOUSING BAFFLE AND INSULATION BLANKET. THE SPECIFIC CAUSE OF THE OIL LEAKAGE WAS NOT DETERMINED W	ITH ANY DEGREE OF CERTAINTY.							4	T			E20NE				 
1997092500722	19970925	00722	EA  	1997	9	25	CA970716002      	2	19970612	G	8520	679	BOLT            			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					CAMSHAFT GEAR	SHEARED         	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA			144  					L244243			(CAN) ENGINE FAILED IN FLIGHT. ON DISASSEMBLY IT WAS FOUND THAT THE CAMSHAFT GEAR SCREWS HAD SHEARED EXCEPT FOR ONE THAT	 WAS STILL INTACT, BUT LYING IN THE OIL SUMP. THE LOCKTABS WERE STILL BENT OVER. IT APPEARS THAT EITHER A LOCKTAB BROKE 	LETTING A BOLT COME LOOSE OR A BOLT BROKE. AT REASSEMBLY THE NEW BOLTS WERE INSTALLED WITH LOCKTITE AND LOCKTABS.				1	G	7	1 	3O	3	O		4H11    	E304				 
1997092500730	19970925	00730	EA  	1997	9	25	CA970722007      	1	19970715	G	6120	8190026	PRESSURE SWITCH 			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						315113		PCE42076	BU10602		(CAN) DURING PREFLIGHT RUN UP THE CREW COULD NOT ARM THE AUTOFEATHER CIRCUIT. THE SYSTEM WAS TURNED OFF. THE PRESSURE SW	ITCH ON THE RIGHT HAND ENGINE HAD FAILED.					1	H	7	2 	3T	4	T		A9EA    	E4EA	6	C	P15EA	 
1997092500731	19970925	00731	NM  	1997	9	25	CA970722008      	1	19970715	G	2130	32167431	VALVE           	ALLIED SIGNA	32167431    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LT PACK	OPEN            	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				987  		P596		P653620B			(CAN) DURING OPERATION OF APU ON GROUND THE LH PACK SHOWED TEMPERATURE WITH THE PACK SHUT-OFF VALVE CLOSED INDICATING TH	AT THE VALVE BUTTERFLY WAS NOT COMPLETELY CLOSED. VALVE REPLACED					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997092500732	19970925	00732	NM  	1997	9	25	CA970722009      	1	19970715	G	2927		SEAL            		72909       	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					HYD REG SYS	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P653620B			(CAN) DURING ROUTINE SERVICING OF THE HYDRAULIC SYSTEM RESERVOIR HEADER PRESSURE THE REGULATOR HAD A SEAL FAILURE RESULT	ING IN PRESSURE LOSS. THE REGULATOR WAS CHANGED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997101600726	19971016	00726	EA  	1997	10	16	CA970722015      	2	19970710	G	7414	4250	MAGNETO         			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ACROSS COIL CASE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			2793 	823  		9080221		42844127A	724333		(CAN) DURING ANNUAL INSPECTION THE MAGNETO COIL WAS FOUND CRACKED ACROSS ITS CASE. FAA AD 81-16-05 WHICH PERTAINS TO THI	S SUBJECT WAS SIGNED OFF IN THE ENGINE LOG BOOKS, BUT WAS NOT COMPLIED WITH.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000021200007	20000212	00007	CE  	2000	2	12	CA970722016      	1	19970710	G	5312		BULKHEAD        			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	BS 8.12 - 124	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2793 					42844127A	724333		(CAN) DURING THE INSPECTION ON REMOVAL OF THE FLOOR INSPECTION COVERS, IT WAS DISCOVERED THAT THE RUDDER AND ELEVATOR CA	BLES HAD BEEN RIDING ON AND CUTTING THE BULKHEADS BELOW THE FLOOR FROM STA 8.12 TO STA 124.00.  CABLES REMOVED AND INSPE	CTED AND FOUND TO BE SERVICEABLE.  WEAR AREAS OF BULKHEAD REPAIRED.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1997101600730	19971016	00730	GL  	1997	10	16	CA970722022      	3	19970716	G	6111		BLADES          													MCAULY	1B90	1B90CM      	GL  	PROP	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									54940		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES. THIS WAS NOT REPAIRED	 IN THE FIELD AND COULD HAVE LED TO PROPELLER BLADE FAILURE.															5	N	P842	 
1997101600731	19971016	00731	GL  	1997	10	16	CA970722023      	3	19970714	G	6114	B24913	PITCH CHANGE    													HARTZL	HCC3Y	HCC3YR      	GL  	SEAL AREA	ROD WORN        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				680  					CK328		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PITCH CHANGE ROD WAS FOUND WORN THROUGH THE CHROME AT THE SEAL AR	EA															5	C	P25EA	 
1997101600732	19971016	00732	GL  	1997	10	16	CA970722024      	3	19970715	G	6114	B24913	PITCH CHANGE    													HARTZL	HCC3Y	HCC3YR      	GL  	SEAL AREA	ROD WORN        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			680  						CK397		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PITCH CHANGE ROD WORN THROUGH THE CHROME AT THE 	SEAL AREA.															5	C	P25EA	 
1997101600733	19971016	00733	GL  	1997	10	16	CA970722025      	3	19970711	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	PROP	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2200 						725070		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER BLADES DID NOT MEET THE MINIMUM WIDTH 	FOR 75" BLADES. BLADES WERE CUT TO 74" TO MEET MINIMUM DIAMETER FOR INSTALLATION.															5	N	P910	 
1997101600741	19971016	00741	WP  	1997	10	16	CA970722036      	1	19970705	G	2150	21700091	AIRCYCLE MACHINE			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					RT AIR COND	FAILED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								0			(CAN) SMOKE ALARM IN LAVATORY SOUNDED ALONG WITH SMELL OF SMOKE AFTER PUSH BACK. AIRCRAFT RETURNED TO GATE. INSPECTED LA	VATORY, WASTE CONTAINER, LIGHTING, LAVATORY PUMP, BEHIND CEILING AND UNDER SINK, NO FAULT FOUND. LAVATORY DEACTIVATED PE	R MINIMUM EQUIPMENT LIST. CIRCUIT BREAKER PULLED FOR LIGHTING AND LAVATORY. RIGHT HAND AIR CONDITIONING AIR CYCLING MACH	INE AND COALESCER BAG (P/N 18084-1) REPLACED.			2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997101600743	19971016	00743	WP  	1997	10	16	CA970722038      	1	19970706	G	2150	21700091	AIR CYCLE MACH  			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					RT AIR COND	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								0			(CAN) CABIN FILLED WITH SMOKE AFTER AUXILIARY POWER UNIT STARTED AND PACK TURNED ON. MAINTENANCE REPLACED RH AIR CONDITI	ONING AIR CYLING MACHINE AND COALESER BAG (P/N 180849-1).					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997101600746	19971016	00746	EA  	1997	10	16	CA970728004      	2	19970717	G	7414	10357174	BREAKER POINTS  	BENDIX      	S4LN20      	PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O320  	O320A2A     	41508	EA  					MAG	BROKEN          	W				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			100  					L498127			(CAN) ENGINE RUNNING ROUGH ON TAXI. CAM FOLLOWER OF POINTS ASSEMBLY FOUND BROKEN. THIS IS THE SECOND SET OF POINTS TO FA	IL WITH THE SAME CONDITION, IN THE SAME MAGNETO, WITHIN 100 HOURS OF OPERATION. CLOSER INSPECTION FOR PROBABLE CAUSE FOU	ND NOTCHES IN THE CAM, P/N 10-88543-1. THE CAM AND POINTS WERE REPLACED.				1	H	7	1 	3O	3	O		A780    	E274				 
1997102300439	19971023	00439		1997	10	23	CA970728005      	2	19970716	G	7421	REM40E	SPARK PLUGS     	CHAMPION    																ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SPARK PLUGS CHECKS ON INSPECTIONS NUMEROUS PLUGS WERE FOUND WITH LOOSE SCREWS HOLDING THE SPRING AND RESIST	OR IN THE TERMINAL END. IN SOME CASES WHEN THE LEAD WAS REMOVED THE SCREW, SPRING AND RESISTOR FELL OUT. ALSO SOME PLUGS	 HAD LOOSE CERAMIC INSULATORS. FURTHER CHECK OF THE FLEET FOUND THAT 30-40 PERCENT OF THE SPARK PLUGS IN SERVICE WERE IN	 THE SAME CONDITION. THE REMEDIAL ACTION WILL CONSIST OF SWITCHING THE FLEET TO AUBURN SPARK PLUGS.																 
2000021200009	20000212	00009	CE  	2000	2	12	CA970728008      	1	19970716	G	2720	04115261	TUBE WELD       			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	RUDDER PEDAL	CRACKED         	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AB	AEROBATIC      	1			CA								21R302H	G12035		(CAN) RUDDER PEDAL TUBE WELD AT TORQUE TUBE CONNECTION FOUND TO BE CRACKED.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1997100900541	19971009	00541	NE  	1997	10	9	CA970728010      	3	19970718	G	6114	C5503	BETA ROD        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  	MCAULY	4HFR34	4HFR34C652  	NE  	AT THE SEAL	CHROME WORN     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1917 					52694	911229		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BETA ROD CHROME WORN IN THE SEAL AREA.						1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	3PNE	 
1997100900542	19971009	00542	NE  	1997	10	9	CA970728011      	3	19970717	G	6114	C5503	BETA ROD        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  	MCAULY	4HFR34	4HFR34C652  	NE  	AT THE SEAL	CHROME WORN     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1917 					52694	911226		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BETA ROD CHROME WORN AT THE SEAL AREA.						1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	3PNE	 
1997100900543	19971009	00543	EA  	1997	10	9	CA970728012      	3	19970721	G	6111		BLADE           													SNSNCH	74D	74DM        	EA  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1002 					A52008		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER BLADE CORRODED ON THE LEADING EDGES AN	D THE FACE.															5	N	P88614	 
1998050100107	19980501	00107	SW  	1998	5	1	CA970728013      	1	19970627	G	6322	206061505115	OIL TANK        			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					TOP	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			696  					CAE847014			(CAN) OIL FOUND ON DECK UNDER ENGINE OIL RESERVIOR.  FOUND OIL TANK CRACKED ON TOP.   ALSO FOUND BROKEN OIL TANK SUPPORT	S AND OIL COOLER BLOWER SUPPORT BRACKETS.  BROKEN ANGLE BRACKETS AT STA 192.0, WL 73.25.  CAUSE OF CRACKS APPEARS TO BE 	EXCESSIVE VIBRATION OF T/R DRIVE OIL COOLER BLOWER  SHAFT/FLYWHEEL ADAPTER.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1998050100106	19980501	00106	SW  	1998	5	1	CA970728014      	1	19970710	G	6322	206032305129A	BRACKET         			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					OIL COOLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			570  					CAE847021			(CAN) CRACKS FOUND ON OIL COOLER BLOWER SUPPORT BRACKETS AT STA 192.0, WL 73.25.  ALSO FOUND CRACKED ANGLE BRACKETS, FRA	ME AND BONDED OIL COOLER PANEL ASSY OIL COOLER TRANSITION BRACKET HAD SMALL CRACK.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1998040200091	19980402	00091	CE  	1998	4	2	CA970731012      	1	19970725	G	5511		SPAR            			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2314 					34787D6D	E3577		(CAN) HORIZONTAL STABILIZER FRONT SPAR AND CENTER SKIN FOUND CRACKED PER CESSNA SEB 94-8.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
1998040200092	19980402	00092	SW  	1998	4	2	CA970731013      	1	19970728	G	3210	71461	GEAR LEG        		71461       	BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3045 					L188836A	105353		(CAN) LEFT MAIN GEAR FAILED DURING TAXI ONTO RUNWAY FROM GRASS LANDING AREA.  FAILURE OCCURRED IN THE MAIN GEAR LEG JUST	 PAST THE ATTACHMENT SADDLE.  GEAR LEG COMPLETELY SEPARATED FROM THE AIRCRAFT STRUCTURE.  WING AND PROP CONTACTED THE GR	OUND.				1	H	7	1 	3O	3	O		A21CE   	E286	5	N	P874	 
1998040200093	19980402	00093	CE  	1998	4	2	CA970731022      	1	19970723	G	2932	GPP125023	PRESS SWITCH    	WIPLINEINC  	GPP125023   	CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	HYD SYSTEM	DEFECTIVE       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			600  					PCE17490	950917		(CAN) DURING NORMAL OPERATIONS, THE GEAR ON THE AMPHIBIOUS FLOATS WAS EXTENDED AND THE CREW NOTED A LONGER THAN NORMAL E	XTENSION PERIOD.  MAINTENANCE FOUND THAT ONE PUMP ONLY WAS BEING UTILIZED DUE TO A FAULTY PRESSURE SWITCH.					1	H	7	1 	3T			NT	A37CE   		5	C	P60GL	 
1998040200096	19980402	00096	CE  	1998	4	2	CA970731025      	1	19970725	G	2782		ACTUATOR        			BEECH 	1900  	1900C       	1154161	CE  										LE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PRE-FLIGHT CHECKS, THE FLAPS WERE SELECTED AND THEN FROZE DURING ACTUATION.  MAINTENANCE FOUND A CORRODED W	IRE AT THE ASSYMETRY SWITCH.					2	L	7	2 	4T			RT	A24CE   					 
1997102300447	19971023	00447	EU  	1997	10	23	CA970731027      	1	19970704	G	3411		PITOT LINE      			AIRBUS	310   	A310304     		EU  										LT PITOT	FOD             	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			C	J		F.O.D.                    	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) TAKEOFF ABORTED DUE TO AIRSPEED DISCREPANCY BETWEEN L/H & R/H SIDE OF 40 KNOTS. THE L/H PITOT LINE WAS PURGED AND 	A WASP WAS REMOVED. PITOT STATIC TEST WAS CARRIED OUT AND CHECKED SERVICEABLE.					2	L	7	2 	4F			RT	A35EU   					 
1998040200098	19980402	00098	NE  	1998	4	2	CA970806001      	2	19970723	G	7510	19357226	PACKING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3I     	NE  	BLEED AIR SYS	FAILED          	W				D	H			RETURN TO BLOCK         	DEACTIVATE SYST/CIRCUITS			J	M		WARNING INDICATION        	OVER TEMP                 		TX	TAXI/GRND HDL  	1			CA			1451 					PCEPS0007	HJ701		(CAN) BLEED AIR ANNUNCIATOR LIGHT ILLUMINATED ON THE RIGHT HAND SIDE.  CREW  RETURNED TO HANGAR.  INSPECTION FOUND THE P	ACKINGS ON THE BLEED AIR SYSTEM WERE BURNT AND HARD.  SUBMITTER SUSPECTS THE USE OF THE WRONG PACKINGS.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
1997102300454	19971023	00454	GL  	1997	10	23	CA970806007      	3	19970729	G	6114		PROPELLER       													MCAULY	1A100	1A100MCM    	GL  	HUB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2562 						G1457		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER HUB AND BLADE(S) LEADING EDGES WERE FOUND CORRODED.																5	N	P918	 
1997102300455	19971023	00455	GL  	1997	10	23	CA970806008      	3	19970729	G	6111	S90AT4	BLADE           													MCAULY	2A34C	D2A34C58    	GL  	PROP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			114  						851326		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADE WAS FOUND TO HAVE SPRAY CUT																5	C	P3EA	 
1997102300456	19971023	00456	EA  	1997	10	23	CA970806009      	3	19970730	G	6114		HUB             													SNSNCH	74DM	M74DM       	EA  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			695  	3859 					K5121		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER HUB CORRODED AND THE PROPELLER BLADES 	NICKED. FIELD REPAIRED AND THE BLADES WERE BELOW MINIMUM LIMITS.															5	N	P88614	 
1997102300463	19971023	00463	NM  	1997	10	23	CA970807005      	1	19970806	G	3230	65617405	CYLINDER        	BOEING      	65617405    	BOEING	737   	737200      	1384453	NM  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0242					(CAN) TWO OVERHAULED CYLINDERS DISPLAYED MULTIPLE CRACKS ON AFT TRUNNION BEARING AREA. ALSO DISPLAYED A BURN MARK, WITH 	REWORK FLAT SPOT FORMED ON CYLINDER SURFACE. THE CHROME PLATE AND BAKE PROCESS WERE DELAYED 38.5 HOURS AND BOEING MAX BE	TWEEN PROCESSES IS 12 HOURS. TOTAL BAKE TIME SHOWN WAS 11 HOURS AND BOEING PROCESS CALLS FOR 12 HOURS BAKE. REMOVED FROM	 SERVICE.			2	L	7	2 	4F				A16WE   					 
1997102800006	19971028	00006		1997	10	28	CA970807048      	4	19970731	G	6122	B20749	FLY WEIGHT      			MOONEY	M20   	M20K        	5870220	SW  						MCAULY	2A34C	2A34C*      	GL  	PROP GOVERNOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1800 						880448		(CAN) EXCESSIVE WEAR FOUND ON PROPELLER GOVERNOR FLY WEIGHT ASSEMBLY, FLY WEIGHT PINS AND CARRIER CAUSING FLY WEIGHT TO 	COME LOOSE.					1	L	7	1 	3O				2A3     		5	C	P3EA	 
1997102300469	19971023	00469	WP  	1997	10	23	CA970807053      	1	19970722	G	7620	4913805AS03624	CABLE           			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7A      	52053	NE  					LH ENG FUEL SOV	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK AROUND INSPECTION, LEFT HAND FUEL FIRE SHUTOFF CABLE FOUND FRAYED. FUEL FIRE SHUTOFF CABLE REPLACED. T	ENSION ADJUSTED AND OPERATIONALLY CHECKED SERVICEABLE.					2	L	7	2 	4F	4	F		A6WE    	E2EA				 
1997091100385	19970911	00385	NE  	1997	9	11	CA970811003      	2	19970807	G	7200		ENGINE          			BOEING	727   	727200      	138407E	NM  	PWA   	JT8   	JT8D15      	52051	NE  					#3 POSITION	MAKING METAL    	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA								685593			(CAN) ON DESCENT #3 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED, ACCOMPANIED WITH A DROP IN OIL PRESSURE INDICATION. THE F	LIGHT CONTINUED WITH THE OIL PRESSURE LIGHT BEING EXTINGUISHED BY MANIPULATION OF THE #3 ENGINE THRUST LEVER. POST FLIGH	T INSPECTION FOUND THE #3 ENGINE MAIN OIL FILTER WITH METAL CONTAMINATION. THE ENGINE WAS REMOVED FROM THE AIRCRAFT.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
1997102300471	19971023	00471	GL  	1997	10	23	CA970811004      	3	19970801	G	6114		PROPELLER       			CESSNA	172   	172I        	2072426	CE  						MCAULY	1C160	1C160CTM    	GL  	BLADES & HUB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			958  	3391 					720160		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADES AND HUB CORRODED UNDER PAINT. LAST PROP SHOP INSPECTION CARRIE	D OUT ON 13 JULY 1982.					1	H	7	1 	3O			NT	3A12    		5	N	P910	 
1997102300472	19971023	00472	EA  	1997	10	23	CA970811005      	3	19970801	G	6111		BLADES          			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	PROP LE	STONE DAMAGE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			486  	773  				L1794036A	15139K		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADES LEADING EDGES FOUND DAMAGED FROM STONES. BLADES REQU	IRED WIDTH REDUCTION.					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA	 
1997102300474	19971023	00474	SO  	1997	10	23	CA970811007      	2	19970731	G	8530	530830	PLUG PISTON PIN 			LUSCOM	8     	8F          	8190114	SO  	CONT  	C90   	C9012F      	17009	SO  					NR2 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								43775312			(CAN) PISTON PIN PLUG IN NR2 CYLINDER CAME LOOSE AND CAUSED WEAR ON THE CYLINDER WALL. METAL WAS FOUND IN THE OIL FILTER	. ALL CYLINDERS WERE REMOVED FOR INSPECTION.					1	H	7	1 	3O	3	O		A694    	E252				 
1997102300475	19971023	00475	EA  	1997	10	23	CA970811008      	1	19970617	G	3234		SWITCH          		7179015     	CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					GEAR CONTROL	DEFECTIVE       	W				O				OTHER                   				J	O		WARNING INDICATION        	OTHER                     		AP	APPROACH       	1			CA			6560 			59					(CAN) DURING GEAR DOWN SELECTION, MAIN AND NOSE GEAR DID NOT EXTEND. NOSE DOORS OPEN "GEAR DISAGREE" WARNING MESSAGE ON 	EICAS. GEAR INDICATION ON EICAS 3 WHITE BOXES. DURING EVENT CREW ALSO REPORTED "CAS MISCOMP" STATUS MESSAGE ON EICAS. DE	NOTING THE WARNING MESSAGE-DISAGREE BETWEEN GEAR POSITION AND HANDLE POSITION. CREW PROCEDED WITH QRH PROCEDURE-GEAR EXT	ENSION USING MANUAL RELEASE SYSTEM. GEAR EXTENDED AND LOCKED. LANDING GEAR CONTROL HANDLE ASSEMBLY REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
1997091100386	19970911	00386	EU  	1997	9	11	CA970811011      	1	19970728	G	2701	NB45D859	COLUMN          			BNORM 	BN2   	BN2B26      	1520350	EU  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8850 								(CAN) WHILE INSPECTING CONTROL COLUMN ON A REGULAR INSPECTION, AN EXCESSIVE WEAR WAS NOTED, A SLIGHT VERTICAL FORCE APPL	IED ON THE CONTROL WHEEL, BROKE THE COLUMN IN TWO PARTS.					1	H	7	2 	3O			RT	A17EU   					 
1998040200100	19980402	00100	CE  	1998	4	2	CA970812010      	1	19970723	G	7120	145100830	TUBE            	CONT        	IO360C      	CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C59   	GL  	ENGINE MOUNT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4165 			60071CR		60071CR	725721		(CAN) DURING ANNUAL INSPECTION, IT WAS FOUND THAT A REAR ENGINE MOUNT WAS BROKEN.  LOWER RIGHT HAND TUBE 1.5 INCHES BELO	W THE WEB.  CRACKED THROUGH THE ENTIRE DIAMETER.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA	 
1998050100091	19980501	00091		1998	5	1	CA970815011      	4	19970813	G	2562	4520130	BATTERY PACK    	ARTEX       	1104        	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ELT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			540  			55867		L58271A	AU8729A		(CAN) UPON REMOVAL FOR TRANSFER TO ANOTHER AIRCRAFT, THE SPLIT IN THE CASE AND THE LEAKING ELECRTOLYTE WAS FOUND.  THE E	XPIRATION WAS FEB/98 AND THE RECERTIFICATION WAS DEC/97, WELL WITHIN LIMITS.					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920	 
1998040200103	19980402	00103	SO  	1998	4	2	CA970815015      	1	19970802	G	3230		DOWNLOCK        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	DIRTY           	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA								L254161A	DJ9746A		(CAN) RIGHT HAND GEAR DOWNLOCK FOUND DIRTY AND WOULD NOT OPERATE FREELY.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997110600621	19971106	00621		1997	11	6	CA970815016      	4	19970801	G	3460	4020571904	V-NAV CONTROLLER			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					INSTRUMENT PANEL	FAULTY          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			DE	DESCENT        	1			CA			5560 					PCE70986			(CAN) V-NAV SELECTOR SWITCH MOVED INADVERTENTLY BETWEEN POSITIONS DUE TO WORN SWITCH. THIS DISABLED THE ALTITUDE ALERTER	 AND AIRCRAFT DESCENDED BELOW ASSIGNED ALTITUDE. SWITCH HAS BEEN SAFETIED IN ALERTER POSITION UNTIL PARTS ARE AVAILABLE.	 PLACARD INSTALLED IN COCKPIT TO PROVIDE WARNING OF V-NAV INOPERATIVE STATUS.				1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1997091100387	19970911	00387	EU  	1997	9	11	CA970820002      	1	19970730	G	5220	A26500701	DOOR            	FOKKER      	A26500701   	FOKKER	F28   	F28MK1000   	4990808	EU  										EMERGENCY EXIT	CORROSION       	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			37626			454USS					(CAN) DURING TRAINING THE SERVICE EMERGENCY DOOR FAILED IN EMERGENCY MODE. OTHER AIRCRAFT CHECKED AND DOOR FAILED IN EME	RGENCY MODE. FLEET CHECK BEING CARRIED OUT. INVESTIGATION REVEALED CORROSION IN OPERATING SPRINGS AND BOWDEN CABLES. REP	LACED.				2	L	7	2 	4F			RT	A20EU   					 
1997110600628	19971106	00628	EA  	1997	11	6	CA970820009      	1	19970716	G	3320	1640513	CONNECTOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  										X164.91 RH	BURNT           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) WITH GPU CONNECTED TO AIRCRAFT ON RAMP AND BATTERY MASTER/AUXILIARY BATTERY/MAIN BATTERY SWITCHES ON. ELECTRICAL B	URNING SMELL AND SMOKE NOTED COMING FROM BETWEEN TOILET PANEL AND SEAT 1D OVERHEAD STOWAGE. SERVICE BULLETIN A8-33-39, D	ATED 15 AUGUST 1997 RELEASED TO MPROVE CONNECTOR POWER CAPABILITIES.				2	H	7	2 	4T			RT	A13NM   					 
1997110600630	19971106	00630	NE  	1997	11	6	CA970820011      	3	19970730	G	6111	7756722	BLADE PIN       	HAMSTD      	SFA13M10A   											HAMSTD	14SF	14SF7       	NE  	PROPELLER BLADE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				7100 		850431					(CAN) INCORRECT PROPELLER BLADE PIN INSTALLED. NO PART NUMBER ON THE PIN. HAMILTON STANDARD HAVE SIMILAR LOOKING PARTS, 	THE DIFFERENCES ARE DASH NUMBER AND LENGTH. 775672-1 LENGTH 2.48", 775672-2 LENGTH 2.58". HAMILTON STANDARD SB 14SF-61-A	43 WAS ISSUED TO ADDRESS THIS PROBLEM. THE SUBMITTER STATES THIS IS THE THIRD TIME HE HAS CAME ACROSS THIS PROBLEM.														6	C	P7NE	 
1997110600631	19971106	00631	EA  	1997	11	6	CA970820012      	2	19970815	G	7314	RG908014A	FUEL PUMP       			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					DIAPHRAGM	RUPTURED        	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA						D8549		L970461A			(CAN) FUEL PUMP DIAPHRAGM RUPTURED CAUSING FUEL TO LEAK ON THE UPPER DECK. LYCOMING SB #487 REFERS.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
1998050100090	19980501	00090	NM  	1998	5	1	CA970820019      	1	19970807	G	5302	A02323	SKIN            			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					TAIL BOOM	DENTED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			750  			2542		L1445639A			(CAN) DURING SIMULATED ENGINE OUT IN HOVER OVER SOFT GROUND, THE ENGINE FAILURE CAUSED THE HELICOPTER TO ROTATE RIGHT AN	D AT GROUND CONTACT THERE WAS A COUNTERSHOCK.  THIS LED TO THE TAIL CONE DAMAGE.   DAMAGE LOCATED ABOUT 5 O'CLOCK A FEW 	INCHES BEHIND THE ATTACH POINT.				1	G	7	1 	3O	3	O		H10WE   	E274				 
1997112600288	19971126	00288	EA  	1997	11	26	CA970822003      	1	19970812	G	5312	C2FS533	BULKHEAD        			DHAV  	DHC2  	DHC2MK3     	2800107	EA  										FS228	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9385 								(CAN) DURING 100 HOUR INSPECTION CRACKS WERE FOUND AT FUSELAGE STATION 228 ON THE BULKHEAD, ATTACHED TO THE VERTICAL STA	BILIZER SPAR. EMPENNAGE REMOVED AND BULKHEAD WAS REPLACED. TOTAL TIME ACCUMULATED SINCE LAST ANNUAL WAS 65 HOURS. NO REP	ORTS OF ROUGH WATER OR HARD LANDINGS OR FLIGHT TURBULENCE HAD BEEN REPORTED.				1	H	7	1 	3T				A806    					 
1997120300015	19971203	00015	SO  	1997	12	3	CA970822005      	2	19970628	G	7314	6468241	FUEL PUMP       			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENG DRIVEN	SEIZED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			290  					679506	901382		(CAN) ENGINE LOST POWER IN CRUISE DUE TO ENGINE DRIVEN FUEL PUMP FAILURE. THE PILOT COULD NOT MAINTAIN ALTITUDE WITH THE	 AUXILIARY ELECTRIC PUMP AND LANDED IN OPEN WATER ON A LAKE. THE PUMP WAS REPLACED AT A MARINA. INSPECTION OF THE PUMP R	EVEALED A LARGE ACCUMULATION OF RUST AND CORROSION ON THE FUEL PUMP BLADES, WHICH SEIZED THE PUMP AND SHEARED THE DRIVE 	COUPLING. IT WAS DETERMINED THAT THE AIRCRAFT HAD SAT IN A HEATED HANGAR FOR 4 TO 5 MONTHS PREVIOUS TO THE INCIDENT. A T	HOROUGH WINTERIZATION PROGRAM OR MORE FREQUENT USAGE OF THE AIRCRAFT PERHAPS WOULD HAVE PREVENTED THE CORROSION AND SUBS	EQUENT FAILURE.	1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL	 
2000021200010	20000212	00010	CE  	2000	2	12	CA970902004      	1	19970812	G	5210	99420024605	HATCH           			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CREW DOOR	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA								PCE41120	BU7723		(CAN) AFTER TAKEOFF, THE CREW HATCH OPENED AND SEPARATED FROM AIRCRAFT.  THE AIRCRAFT LANDED WITHOUT INCIDENT.  NEW DOOR	 INSTALLED, LATCHING MECHANISM CHECKED SERVICEABLE.   AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA	 
1998050100087	19980501	00087	SW  	1998	5	1	CA970902013      	1	19970821	G	5302		BEAM            			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE07531			(CAN) TAIL BOOM ATTACHMENT POINT T-CAP BEAM FOUND CRACKED.  SOME RIVETS ALSO SHEARED.  CRACK WAS ALONG TWO HI-SHEAR RIVE	T HOLES.					1	G	7	1 	4U	4	U		H1SW    	E17EA				 
1997112600297	19971126	00297	GL  	1997	11	26	CA970902017      	3	19970820	G	6114	B3905	PIN             													MCAULY	2A34C	2A34C203    	GL  	BASE ASSEMBLY	FAILED LOAD TEST	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			532  	1676 					765503		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BASE ASSEMBLY PIN FAILED THE LOAD TEST.																5	C	P3EA	 
1997112600298	19971126	00298	GL  	1997	11	26	CA970902018      	3	19970821	G	6111	S90AT10	BLADE           													MCAULY	2A34C	2A34C66     	GL  	THREADED AREA	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									744344		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. A PROPELLER BLADE THREADS WAS FOUND SCRATCHED																5	C	P3EA	 
1997112600302	19971126	00302	EA  	1997	11	26	CA970902023      	2	19970628	G	7414	10349371	IMPULSE COUPLING	BENDIX      	103493704   	BLANCA	17    	1731A       	1220435	GL  	LYC   	O540  	IO540K1E5   	41532	EA  					LH MAGNETO	WORN            	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA				217  		A25960		L989948			(CAN) AIRCRAFT EXPERIENCED LOSS OF ENGINE POWER IN FLIGHT. EMERGENCY NO POWER LA NDING CARRRIED OUT IN FIELD. AIRCRAFT R	EMOVED FROM FIELD AND DISASSEMBLY OF ENGINE REVEALED THE LEFT HAND MAGNETO IMPULSE COUPLING LOCKED-UP, STRIPPING THE GEA	RS IN THE ACCESSORY CASE, CAUSING COMPLETE ENGINE FAILURE.				1	L	7	1 	3O	3	O		A18CE   	1E4				 
1997112600303	19971126	00303	GL  	1997	11	26	CA970902024      	3	19970822	G	6111	S90AT2	BLADE           			CESSNA	185   	185         	2072802	CE  	CONT  	O470  	IO470F      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	PITCH DISTRIBUT	OUT OF SPECS    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			485  					768043F	912433		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROP BLADES AIRFOIL PITCH DISTRIBUTION WAS NOT TO SPECIFICATIONS.	 THE HUB PILOT TUBE BORE (P/N 4715) WAS OVERSIZE.					1	H	7	1 	3O	3	O	NC	3A24    	3E1	5	C	P3EA	 
1997112600304	19971126	00304	GL  	1997	11	26	CA970902025      	3	19970825	G	6114	57A2433	HUB BOLTS       													HARTZL	HCC2Y	HCC2YK1     	GL  	UNDER BOLT HEADS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1391 					CH12805		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE HUB BOLTS WERE FOUND CORRODED UNDER THE BOLT HEADS. THE PROPELLER	 BLADES BALL BEARING WERE FOUND GALLED.															5	C	P920	 
2000021200013	20000212	00013	SO  	2000	2	12	CA970902032      	1	19970824	G	2432		BATTERY         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	E/E BAY	DISCHARGED      	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			UK	UNKNOWN        	1			CA			10440					L564961A	DJ9380A		(CAN) A SHORT PERIOD OF TIME AFTER THE AIRCRAFT  WAS PARKED, THE ANTI-COLLISION LIGHT APPEARED TO BE OPERATING.   IT WAS	 THOUGHT THE MASTER SWITCH WAS LEFT ON.  THIS WAS NOT THE CASE.  THE NEXT MORNING, THE AIRCRAFT COULD NOT BE STARTED DUE	 TO A WEAK BATTERY.  IT WAS REMOVED AND SERVICED, REINSTALLED.  FURTHER INVESTIGATION REVEALED MASTER SWITCH CAN BE ACTI	VATED BY RAIN IF COVER FOR CIRCUIT BREAKER IS NOT PROPERLY SEALED.			1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA	 
1997112600308	19971126	00308	NE  	1997	11	26	CA970902033      	2	19970725	G	7322		P3 LINE         			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      		NE  					O/S GOVERNOR	FRACTURED       	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			3482 					116125			(CAN) ENGINE POWER ROLLED BACK TO SUB-IDLE DURING CRUISE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT MADE AN UNEVENTFUL SI	NGLE ENGINE LANDING AT ITS DESTINATION. POST FLIGHT INSPECTION REVEALED THE P3 LINE TO BE FRACTURED ADJACENT TO THE OVER	SPEED GOVERNOR. THE TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE				2	H	7	2 	4T	4	T	RT	A45NM   	E20NE				 
1997112600309	19971126	00309	NE  	1997	11	26	CA970902034      	2	19970811	G	7261		REGULATOR       								PWA   	PWA120	PW125B      		NE  					NR2 ENG OIL PRES	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			8645 					124052			(CAN) DURING CLIMB THE OIL PRESSURE ON NR2 ENGINE, BEGAN TO FLUCTUATE BELOW THE MINIMUM OPERATING LEVEL. THE AIRCRAFT RE	TURNED TO  DEPARTURE POINT, AT REDUCED POWER. POST FLIGHT INSPECTION FOUND THE OIL PRESSURE REGULATING VALVE TO BE FAULT	Y. THE VALVE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.									4	T			E20NE				 
1997112600310	19971126	00310	NE  	1997	11	26	CA970902035      	2	19970814	G	7314		FUEL PUMP       								PWA   	PWA120	PW125B      		NE  					NR1 ENG HP	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA			11974	1991 				124253			(CAN) A POPPING SOUND WAS HEARD IMMEDIATELY AFTER TAKEOFF ACCOMPANIED BY DECAYING PARAMETERS AND AN "ENGINE OUT" WARNING	 LIGHT ON NR1 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO ITS POINT OF DEPARTURE. POST FLIGHT INSPECTIO	N FOUND THE HP FUEL PUMP TO BE FAULTY. THE FUEL PUMP WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.									4	T			E20NE				 
1997112600311	19971126	00311	NE  	1997	11	26	CA970902036      	2	19970814	G	7322		FUEL CONTROL    								PWA   	PWA120	PW125B      		NE  					N1 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA			11974	1991 				124253			(CAN) A POPPING SOUND WAS HEARD IMMEDIATELY AFTER TAKEOFF ACCOMPANIED BY DECAYING PARAMETERS AND AN "ENGINE OUT" WARNING	 LIGHT ON NR1 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO ITS DEPARTURE POINT. POST FLIGHT INSPECTION F	OUND THE MAIN FUEL CONTROL UNIT TO BE FAULTY. THE MAIN FUEL WAS REPLACED AND THE AIRCRAFT RETIURNED TO SERVICE.									4	T			E20NE				 
1997112600313	19971126	00313	SO  	1997	11	26	CA970903002      	2	19970410	G	8500		ENGINE          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	#2 POSITION	FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA								228252	785844		(CAN) NR 2 ENGINE FAILED						1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA	 
1997112600315	19971126	00315		1997	11	26	CA970903004      	1	19970603	G	7810	99710000804	EXHAUST MANIFOLD		2075000000  						ROTAX 	912   	ROTAX912    	55555	EU  					UPPER BEND	SEPARATED       	W		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA				669  				4076163			(CAN) EXHAUST MANIFOLD SEPARATED AT THE UPPER WELD. THE MANIFOLD WAS REPLACED. FAILURE OF THE WELD CAUSED: NYLON WRAP TO	 MELT INTO PROP CONTROL CABLE AND CAUSE IT TO FREEZE. PROP CONTROL UNSERVICEABLE. PROP CONTROL REPLACED. FIRE PROTECTION	 SLEEVE ON THE TACHOMETER CABLE ABSORBED MELTED TACH CABLE ON THE PROTECTIVE WRAP. TACH CABLE REPLACED.									3	I			EXPE3I				 
1997120300016	19971203	00016	EA  	1997	12	3	CA970903005      	1	19970828	G	3610	215081505	DUCT BLEED AIR  			CNDAIR	CL600 	CL600*      		EA  	LYC   	ALF502	ALF502*     	41580	EA  					8TH STAGE	CRACKED         	W		A		O				OTHER                   				M			OVER TEMP                 			CL	CLIMB          	1			CA								LF030205			(CAN) ON CLIMB THROUGH 1,500 FEET, THE TEMPERATURE ON NR1 ENGINE SUDDENLY INCREASED BY 100 DEGREES, POWER WAS REDUCED AN	D IN CRUISE THE NR1 ENGINE TEMPERATURE WAS 40 DEGREES HIGHER THAN THE NR2 ENGINE. ON LANDING THERE WAS NO THRUST REVERSE	RS AVAILABLE ON THE NR1 ENGINE. INVESTIGATION FOUND 8TH STAGE BLEED AIR DUCT HAD CRACKED THROUGH 360 DEGREES AT THE WELD	 AND COULD NOT SUPPLY AIR TO DEPLOY THE THRUST REVERSERS.			2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2000021200014	20000212	00014	CE  	2000	2	12	CA970903007      	1	19970717	G	2150	1143800025	PRE COOLER      			BEECH 	1900  	1900C       	1154161	CE  										AIR DISTRIBUTION	LEAKING         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			12818								(CAN) ENGINE ECTM INDICATING RISING ITT.  ALSO NOTICED THROTTLE SPLIT IN CRUISE BUT MARGINAL IMPROVEMENT WITH BLEED AIR 	OFF ON RT ENGINE.  PRECOOLER  FOUND TO BE LEAKING AROUND FINS AND SEAMS.   PRECOOLER REPLACED.					2	L	7	2 	4T			RT	A24CE   					 
1997112600318	19971126	00318	NE  	1997	11	26	CA970903012      	2	19970823	G	7250		PT SHAFT        								PWA   	PW120 	PW124B      		NE  					NR1 ENGINE	FRACTURED       	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			10012	3251 				124420			(CAN) DURING TAXI THERE WAS AN ODOUR OF OIL AND A DROP IN NR1 ENGINE PARAMETERS. GROUND INSPECTION FOUND THE TURBOMACHIN	ERY CHIP DETECTOR AND THE NR4/5 SCAVENGE LINES HEAVILY CONTAMINATED WITH METAL. FURTHER INVESTIGATION FOUND THE PT SHAFT	 HAD FRACTURED IN THE VICINITY OF THE NR4 BEARING.									4	T			E2ONE				 
1997112600331	19971126	00331	CE  	1997	11	26	CA970904016      	1	19970617	G	2435	646275	STARTER         			CESSNA	185   	A185F       	2072821	CE  						MCAULY	D3A34	D3A34C403   	GL  	BRUSHES	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			490  			W249036			770031		(CAN) STARTER FAILED AS BOTH INSULATED BRUSHES WERE SEVERED PROBABLY FROM VIBRATION NEXT TO WHERE BRUSH LEAD IS SANDWICH	ED BETWEEN TWO POLE STRAPS AND SPOT WELDED CLEAR THROUGH. ALL FOUR FIELD COILS WERE LOOSE ON THEIR RESPECTIVE POLE SHOES	 AND HAD CHAFED HALF WAY THROUGH THE INSULATION. THE SUBMITTER STATES THIS IS AN IMPROPER AND UNACCEPTABLE MANUFACTURING	 PROCESS.			1	H	7	1 	3O				3A24    		5	C	P47GL	 
1997121100273	19971211	00273	NM  	1997	12	11	CA970904023      	1	19970718	G	3241	39043A	VALVE           	CRANE       	39043A      	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					MLG ANTI-SKID	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						956B		P653620B			(CAN) LH MAIN LANDING GEAR ANTI-SKID VALVE LEAKING. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121100274	19971211	00274	NM  	1997	12	11	CA970904024      	1	19970815	G	5320		WEB             			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					BS312R WL169	CORROSION       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			43881					P653620B			(CAN) CORROSION ON WEB WL 169 BS 312RLAVATORY CHEMICAL LEAK. REPAIRED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121100275	19971211	00275	NM  	1997	12	11	CA970904025      	1	19970815	G	5330		SKIN            			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LAV SERV PANEL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			43881					P653620B			(CAN) SKIN FORWARD OF FORWARD LAVATORY SERVICE PANEL HAS BULGE AT THE FASTENERS. CORROSION ON THE LOWER SKIN OF THE LAP 	JOINT. SKIN					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
2000021200020	20000212	00020	CE  	2000	2	12	CA970904038      	1	19970821	G	3230	MS243311	SWITCH          	AIRIGHT     	1143800411  	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA								PCE32053	FW562		(CAN) ON APPROACH, LT MAIN LANDING GEAR NOT SHOWING GREEN BUT TRANSIT LIGHTS EXTINGUISHED.  EMERGENCY LANDING SAFELY CAR	RIED OUT.  MAINTENANCE INVESTIGATION FOUND ACTUATOR DOWNLOCK MICROSWITCH INTERMITTENT.  SWITCH REPLACED AND SYSTEM CHECK	ED SERVICEABLE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2000021200021	20000212	00021	CE  	2000	2	12	CA970904039      	1	19970821	G	2420		WIRE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	AC SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCE32053	FW562		(CAN) DURING FLIGHT, THE NR 1 INVERTER CAPTION LIGHT WOULD COME ON, INDICATING INVERTER FAILURE, THEN THE 26 VAC PILOT G	YRO HORIZON CIRCUIT BREAKER  WOULD TRIP AND SELECTION OF NR 2 INVERTER WOULD ALSO INDICATE FAILURE.  FAILURE SEEMED TO O	CCUR DURING RIGHT TURNS.   MAINTENANCE CHECK REVEALED WIRE BUNDLE FROM THE GYRO HAD TO MAKE A TIGHT TURN AT THE CANNON P	LUG.   THIS CONFIGURATION CAUSED A WIRE OF THE BUNDLE TO OCCASIONALLY SHORT OUT.  WIRE BUNDLE AND TUBE ROUTING ADJUSTED 	AND WIRE REPAIRED.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2000021200023	20000212	00023	CE  	2000	2	12	CA970904041      	1	19970822	G	5210		LATCH           	ZENAIR      	20F324      	ZINAIR	CH2000	CH2000      	9950100	CE  										CREW DOOR	FAILED          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			AB	AEROBATIC      	1			CA			40   								(CAN) LATCH OPENED IN-FLIGHT RESULTING IN DOOR SEPARATING FROM AIRCRAFT.  LATCH TOO EASY TO OPEN, ONE PLANE MOTION, TWO 	NOTCHES.   BULKY CLOTHING OR IN THIS CASE A KNEE BOARD WORN BY THE PILOT ON RAISING THE KNEE OPENED LATCH.					1	L	7	1 	3O			NT	TA5CH   					 
1998050100081	19980501	00081	EU  	1998	5	1	CA970905001      	1	19970902	G	2750	677ONL312014	BOLT            		Z4243430000 	ZLIN  	242   	Z242L       	9970204	EU  										FLAP	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1451 								(CAN) DISSASSEMBLY OF THE FLAP CONTROL BELLCRANK AT THE 1500 HR INSPECTION FOUND THE BOLT ATTACHING THE FLAP CONTROL CAB	LE TO THE BELLCRANK WAS BENT AT THE MIDWAY POINT.  THE OTHER WING BELLCRANK BOLT WAS FOUND IN THE SAME CONDITION.					1	L	7	1 	3O			0	A76EU   					 
1997112600337	19971126	00337	GL  	1997	11	26	CA970905002      	3	19970828	G	6112	4E15551	SLIP RING       													HARTZL	HCB3T	HCB3TN3     	GL  	PROP	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1854 	6338 					BU13148		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE DE-ICE SLIP RING SHORTED OUT AT THE TRACKS. THIS	 WAS CAUSING INTERMITTENT DE-ICE OPERATION.															6	C	P15EA	 
1997112600338	19971126	00338	EA  	1997	11	26	CA970905003      	3	19970826	G	6111		BLADE           													SNSNCH	74D	74DM        	EA  	LEADING EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2050 	1191 					A51432		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND STONE DAMAGE TO THE LEADING EDGE AND FACE OF THE PRO	PELLER BLADES															5	N	P88614	 
1997112600339	19971126	00339	GL  	1997	11	26	CA970905004      	3	19970828	G	6111	S90M1D	BLADE           													MCAULY	2A36C	2A36C33     	GL  	BLADE THREADS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			609  	178  					62476		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER BLADE CRACKED. THE SUBMITTER SUGGESTS 	THAT IF THE FIVE YEAR INSPECTION HAD NOT BEEN CARRIED OUT THE BLADE WOULD HAVE FAILED PERHAPS WITH THE LOSS OF AIRCRAFT.															5	C	P880	 
1997112600340	19971126	00340	NE  	1997	11	26	CA970905005      	2	19970827	G	7210	310924401	BEARING         								PWA   	120   	PW120       		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			11970	3315 		121047					(CAN) THE REDUCTION GEARBOX WAS FOUND TO BE GENERATING METAL ANALYSED AS BEING M50.- RGB WAS SENT FOR INVEST. OF- METAL 	CONTAMINATION & RESTROATION. DISASSY OF- RGB FOUND- SOURCE OF THE METAL CONTAMINATION WAS DEFINITELY- SPALLING OF- NR15 	BEARING ON ITS OUTER RACE. THIS BEARING WAS- ORIG BEARING INST AT PRODUCTION.-RE IS AMPLE INDICATION OF ELECTRICAL DISCH	ARGE PIT TING ON- OTHER SURFACES OF- FAILED BEARING & THIS WOULD APPEAR TO BE A CLEAR CASE OF LOW LEVEL ELECTRICAL DISCH	ARGE PITTING LEADING TO FAILURE OF- BEARING. MAGNETISM IS MINIMAL ON ALL GEARS, PROP SHAFT & PCU COUPLING & BEARINGS.-RE	FORE LIGHTNING IS NOT THOUGHT TO BE INVOLVED IN THIS FAILURE:						4	T			E20NE				 
1997101600747	19971016	00747	NM  	1997	10	16	CA970909002      	1	19970826	G	3240	2661943	BRAKE HOUSING   		214665      	DHAV  	DHC8  	DHC8*       		NM  										PISTON HOUSING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12716								(CAN) LIQUID PENETRANT AND EDDY CURRENT INSPECTION WERE COMPLETED ON DHC8-100 BRAKE HOUSINGS. ON ONE UNIT ALL (6) PISTON	 CAVITIES WERE FOUND CRACKED JUST BELOW THE INLET AND BLEEDER PORTS. ON THE SECOND THREE PISTON CAVITIES WERE FOUND CRAC	KED IN THE SAME AREA.				2	H	7	2 	4T			RT	A13NM   					 
2000021200027	20000212	00027	CE  	2000	2	12	CA970909007      	1	19970818	G	3213	12438116	COLLAR          		743627      	CESSNA	206   	P206B       	2073309	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	3A32C	D3A32C*     	GL  	STRUT	BROKEN          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			2106 					1116936A	8601219		(CAN) THE AIRCRAFT IS USED FOR TRANSPORTING SKY DIVERS AND IS SUBJECT TO LONG TAKEOFF RUNS AND CROSSWINDS.  THIS CONDITI	ON SUBJECTS THE LANDING GEAR STRUT TO HIGH STRESS LOADS WHICH CONTRIBUTED TO THE STRUT COLLAR  FAILURE.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA	 
1997101600748	19971016	00748	NE  	1997	10	16	CA970909008      	2	19970821	G	7320	311717502	MFCU            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					P3 AIR LEAK	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA			39   								(CAN) FUEL VENTING FROM STARBOARD OUTBOARD NACA VENT ON CLIMB OUT. MFCU, P3 AIR LEAKING INTERNALLY INTO DRAIN RETURN TO 	FUEL TANK RESULTING IN FUEL TANK PRESSURIZATION AND SUBSEQUENT VENTING. MFCU REPLACED. UNIT RETURNED TO P&W FOR INVESTIG	ATION.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998041700717	19980417	00717	NE  	1998	4	17	CA970909010      	2	19970820	G	7322		FUEL CONTROL    	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343B1     		NE  					LT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN PULLING BACK FROM GATE WITH THRUST REVERSER LEVER ABOUT .500 INCH FORWARD OF FLIGHT IDLE THE LEFT ENGINE RAN 	AWAY.  ALL INDICATIONS WERE HEADING FOR RED.  ENGINE SHUT DOWN.  ONLY INDICATION NOTICED ABOVE RED WAS N1.  THE ITT WENT	 926 DEGREES FOR 1.2 SECOND AND THE N1 WENT 100.9 FOR 1.3.  FCU REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000021200029	20000212	00029	CE  	2000	2	12	CA970909018      	1	19970825	G	3230	991028710	PRESSURE SWITCH 			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MLG	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								290847R	950199		(CAN) ON GEAR RETRACTION AFTER TAKEOFF, THE HYDRAULIC PRESSURE LIGHT REMAINED ILLUMINATED.  LANDING GEAR EXTENDED, LIGHT	 REMAINED ON.  MAINTENANCE INVESTIGATION FOUND AN INOPERATIVE PRESSURE SWITCH.  THE SWITCH WAS REPLACED AND RETRACTION T	ESTS CARRIED OUT, SERVICEABLE.				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2000021200030	20000212	00030	SO  	2000	2	12	CA970909019      	1	19970825	G	5610		WINDOW          			PIPER 	PA31  	PA31        	7103102	SO  										COCKPIT	DAMAGED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) COPILOT'S WINDOW DAMAGED BY HEAT FROM EXHAUST STACK.  SUSPECT THIS CONDITION CAUSED BY PROPELLER IN THE FEATHERED 	POSITION AND AIRCRAFT NOT TURNED INTO THE WIND.  AIRCRAFT RECENTLY HAD ROM AIR KIT INSTALLED STC SA4723NM AND LOW DRAG E	XHAUST ASSY IAW STC SA00046SE.  IT APPEARS UNDER RIGHT CONDITION, PROPS IN FEATHER AND TAIL WIND EXHAUST HEAT CAN DAMAGE	 WINDOW ON RT SIDE.			1	L	7	2 	3O				A20SO   					 
1998041700716	19980417	00716	EU  	1998	4	17	CA970910003      	1	19971003	G	3230	1035052	DRIVER          			GROB  	103CAT	G103TWNASTIR	1660202	EU  										MLG	BENT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			135  								(CAN) GEAR SELECTED DOWN AND WAS BELIEVED TO BE DOWN AND LOCKED.  AT TOUCHDOWN, THE GEAR RETRACTED AND AIRCRAFT SLID ON 	ITS BELLY TO A STOP.   INSPECTION FOUND THE ACTUATING HANDLE IN THE FORWARD COCKPIT BENT.  THIS IS SECOND OCCURRENCE FOR	 THIS AIRCRAFT AND DRIVER TO BE BENT.				1	K	0	0 					G39EU   					 
1997112600345	19971126	00345	SO  	1997	11	26	CA970910004      	2	19970714	G	7322	MA3SPA	CARBURETOR      			CESSNA	150   	150C        	2071808	CE  	CONT  	O200  	O200A       	17020	SO  					CARB HEAT BOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7190 			104115		250488A48			(CAN) DURING CARBURETOR INSPECTION THE FORWARD SUPPORT BRACKET WAS FOUND LOOSE, FURTHER INSPECTION REVEALED THE SCREWS H	OLDING THE BRACKET TO THE CARBURETOR HEAT BOX WERE LOOSE, EVEN THOUGH THE SCREWS WERE INSTALLED WITH LOCKWASHERS AND WER	E PROPERLY LOCKWIRED. INSPECTION OF THE SCREWS FOUND THE THREADS WERE WORN AND DID NOT GRIP. THE LOCATION OF THESE SCREW	S INSIDE THE CARBURETOR HEAT BOX COULD CREATE A INGESTION PROBLEM, THE ONLY WAY TO PROPERLY INSPECT THESE SCREWS IS TO R	EMOVE THE AIR FILTER BOX.		1	H	7	1 	3O	3	O		3A19    	E252				 
1998041700715	19980417	00715	CE  	1998	4	17	CA970910005      	1	19970827	G	2400	2048141	GROUND BLOCK    			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ELECTRICAL POWER	NOT GROUNDED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GROUND BLOCK POORLY GROUNDED TO AIRFRAME.  SURFACES CLEANED AND GOOD BOND SUPPLIED.						2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
1997112600347	19971126	00347	EA  	1997	11	26	CA970910007      	3	19970904	G	6111		BLADE           													SNSNCH	74D	74DM        	EA  	LEADING EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									K37599		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE LEADING EDGE OF THE PROPELLER BLADE																5	N	P88614	 
1997112600348	19971126	00348	EA  	1997	11	26	CA970910008      	3	19970904	G	6111		BLADE           													SNSNCH	74D	74DM        	EA  	LEADING EDGE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									K36246		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. LEADING EDGE OF THE PROPELLER BLADE(S) WAS FOUND ERODED																5	N	P88614	 
1997112600349	19971126	00349	NE  	1997	11	26	CA970910009      	3	19970902	G	6114	B5264	CYLINDER        			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	C3D36C	C3D36C41582 	NE  	PROP SEAL AREA	OVERSIZE        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			123  					L734036A	920431		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE CYLINDER WAS FOUND TO BE OVERSIZE.						1	L	7	1 	3O	3	O		2A3     	E286	5	N	SA645NE	 
1997120300019	19971203	00019	GL  	1997	12	3	CA970910010      	3	19970829	G	6114	3474	ROD             													MCAULY	3AF32C	3AF32C*     	GL  	REAR HUB	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									910662		(CAN) PROPELLER RECEIVED FOR GREASE LEAK. THE RODS WERE FOUND HEAVILY SCORED AND WERE REPLACED.																5	C	P22EA	 
1997112600350	19971126	00350	GL  	1997	11	26	CA970910011      	3	19970829	G	6114		LOW PITCH STOP  			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	PROP	MIS ADJUSTED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				594  				280739R	765471		(CAN) AIRCRAFT NOT GETTING FULL RPM. PROPELLER AND GOVERNOR REMOVED FOR BENCH CHECK. GOVERNOR SET CORRECTLY. PROPELLER W	AS SET TOO HIGH PREVIOUS SETTING, INCORRECT REFERENCE STATIONS WERE USED.					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P880	 
1997112600351	19971126	00351	EA  	1997	11	26	CA970910012      	3	19970905	G	6111		BLADE           													SNSNCH	76AK	M76AK       	EA  	LEADNG EDGE/FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									6690		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADE FOUND WITH STONE DAMAGE.																5	N	1P210	 
1998111300583	19981113	00583	EU  	1998	11	13	CA970910013      	1	19970831	G	2550	878	SPRING          	SIREN       	S16096      	SNIAS 	350   	AS350B2     	8680813	EU  										CARGO HOOK	MISINSTALLED    	W				O				OTHER                   				D	W		INFLIGHT SEPARATION       	INADEQUATE Q C            		CR	CRUISE         	1			CA			58   			878					(CAN) DURING GEOSURVEY WITH A POD HANGING FROM THE CARGO HOOK, APPROXIMATELY 30 MINUTES AFTER TAKEOFF, CARGO RELEASED UN	COMMANDED AND THE POD DROPPED AND WAS DESTROYED.  DISASSEMBLY OF THE CARGO HOOK REVEALED THAT THE RELEASE LEVER RETURN S	PRING WAS NOT ENGAGED IN THE HOLE AT THE BOTTOM OF THE CASING, THEREFORE, NOT DRIVING THE LEVER TO THE FULLY LOCKED POSI	TION.  PART TC:  23			1	G	7	1 	3U				H9EU    					 
1998111300584	19981113	00584	EU  	1998	11	13	CA970910014      	1	19970817	G	2550	864	LEVER           	SIREN       	S16096      	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CARGO HOOK	JAMMED          	W				O				OTHER                   				O			OTHER                     			HO	HOVERING       	1			CA			185  			864		4550			(CAN) CARGO HOOK WOULD NOT RELEASE ELECTRICALLY OR MANUALLY.  THE LOCKING MECHANISM WOULD NOT ROTATE WITHIN THE ASSEMBLY	 ALTHOUGH THE SOLENOID, HEARD CLICKING RELEASING THE TORQUE ON THE RELEASE LEVER BUSHING THRU BOLT, ALLOWED THE HOOK TO 	WORK PROPERLY.  MISMACHINED PARTS, EITHER THE LEVER FULCRUM IS TOO WIDE OR ITS BUSHING NOT WIDE ENOUGH ALLOWING THE SIDE	 PLATE TO CLAMP IT SOLID.  PART TC:  30.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
1997120300020	19971203	00020	NE  	1997	12	3	CA970910017      	2	19970825	G	7250	30A1102	LPT DISK        			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305       		NE  					3RD STAGE	MIS MANUFACTURE 	W		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			50   					CA0043			(CAN) A TURBINE DISK MACHINED, AS A TRIAL, TO AN UNAPPROVED PROCESS WAS ERRONEOUSLY ASSEMBLED INTO A MODULE AND SUBSEQUE	NTLY BUILT INTO ENGINE CA0043 CURRENTLY ON LEARJET 60-103. THE UNAPPROVED PART WAS REPLACED. THIS IS AN ISOLATED CASE AN	D NO OTHER DISKS ARE AFFECTED.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
1997121100277	19971211	00277	EA  	1997	12	11	CA970915003      	3	19970903	G	6111		BLADE           													SNSNCH	74DM	M74DM       	EA  	PROP LE FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2159 	211  					K30298		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADES WERE FOUND TO HAVE STONE DAMAGE TO THE LEADING E	DGES AND THE FACE.															5	N	P88614	 
2000021200033	20000212	00033	CE  	2000	2	12	CA970915004      	1	19970910	G	3246	40177A	WHEEL           			CESSNA	208   	208B        	2073701	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	NLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			415  					PCEPC0489	262459		(CAN) DURING INSPECTION, CORROSION WAS FOUND IN THE BEARING AREA OF NOSE WHEEL. THE BEARING SEALS WERE FOUND IN GOOD CON	DITION.  WATER APPEARS TO HAVE ENTERED THE AREA FROM THE NOSE FORK AND SPACER TRAVELING DOWN AXEL TUBE INTO THE BEARING 	AREA.				1	H	7	1 	3T				A37CE   		5	C	P60GL	 
1998041700713	19980417	00713	CE  	1998	4	17	CA970915005      	1	19970904	G	5712	16214018	RIB             			CESSNA	188   	A188B       	2073005	CE  	CONT  	O550  	IO550D      	17042	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	WS 36.12	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1887 					284027R	EC1042A		(CAN) WHILE CARRYING OUT A 100 HR INSPECTION THE AME, FOUND CRACKS AT THE WING RIBS AT STATION 22.87 AND STATION 36.12. 	 THREE CRACKS WERE FOUND IN THE SECOND AND THIRD LIGHTENING HOLE IN P/N 1621401-8 AND THREE CRACKS WERE FOUND IN THE FIR	ST, SECOND AND THIRD LIGHTENING HOLES.				1	L	7	1 	3O	3	O		A9CE    	E3SO	5	C	P25EA	 
1998041700712	19980417	00712	CE  	1998	4	17	CA970915006      	1	19970903	G	5712	162100917	RIB             		162100917   	CESSNA	188   	A188B       	2073005	CE  	CONT  	O550  	IO550D      	17042	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	WS 20	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1638 					284028	EC1037A		(CAN) WHILE PERFORMING A 100 HR INSPECTION, THE AME FOUND A CRACK AT THE WING RIB AT STATION 20.62. THE CRACK IS APPROXI	MATELY .75 INCH  LONG STARTING FROM THE LIGHTENING HOLE WHICH IS LOCATED 11 INCHES FORWARD OF THE REAR WING ATTACHMENT.					1	L	7	1 	3O	3	O		A9CE    	E3SO	5	C	P25EA	 
1997112600354	19971126	00354	NE  	1997	11	26	CA970915007      	2	19970904	G	7250	311755401	INTERSTAGE CASE 								PWA   	120   	PW120       		NE  					REAR FLANGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10040					121182			(CAN) THE ENGINE WAS REMOVED FROM SERVICE AFTER A ROUTINE BORESCOPE INSPECTION FOUND THE LEADING EDGES OF ALL THE PT1 TU	RBINE BLADES HAD DISTINCT NOTCHED AT THE VERY ROOT OF THE BLADE WITHIN THE AIRFOIL TO PLATFORM RADIUS. DISASSEMBLY FOUND	 THE NOTCHES IN THE PT1 TURBINE BLADE LEADING EDGES WERE CAUSED BY RUBBING CONTACT WITH THE INNER HUB OF THE PT1 STATOR.	 THE PT1 STATOR WAS ABLE TO MOVE REARWARD BECAUSE THE PT RETAINING BOLTS WERE ALL FRACTURED ON THE LH SIDE OF THE ENGINE	, ELIMINATING ANY AXIAL RESTRAINT AT THE OUTER DIAMETER. THE STATOR WAS PUSHED REARWARD ON THE LEFT HAND SIDE OF THE ENG	INE BY MASSIVE LOCALIZED SWELLING OF THE INTERSTAGE CASE REAR FLANGE CAUSED BY CORROSION.						4	T			E20NE				 
2000021200034	20000212	00034	CE  	2000	2	12	CA970916004      	1	19970131	G	2910	1145800501	LINE            		1145800007  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3I     	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			246  					PS0050	HJ666		(CAN) ON INSPECTION, HYDRAULIC LEAK FOUND UNDER LT CENTER SECTION.   INVESTIGATION REVEALED LEAK LOCATION WAS FROM LINE 	BETWEEN POWER PACK AND FILLER.  CRACKED LINE REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2000021200035	20000212	00035	CE  	2000	2	12	CA970916005      	1	19970905	G	5712	07221991	RIB             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	WING	BUCKLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1079 					572171	790584		(CAN) THE BENT RIB CONDITION PROBLEM HAS BEEN PREVIOUSLY FOUND ON OTHER INSPECTIONS.  IT APPEARS THIS CONDITION OCCURS I	N AREA ABOVE THE AILERON HINGE OUTBOARD SECTION AND IS ALSO THE AREA WHERE THE AILERON BALANCE WEIGHTS ARE LOCATED.					1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL	 
1998041700710	19980417	00710	SO  	1998	4	17	CA970916007      	1	19970626	G	2913	66WAY3002	PUMP            	APEX        	66WAY3002   	GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					HYDRAULIC SYSTEM	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA				6    		6218		16062			(CAN) CREW REPORTED NR 1 HYDRAULIC PUMP PRESSURE FAIL LIGHT ON.   PUMP REPLACED.						2	L	7	2 	4T	4	T		1A17    	E297				 
1998041700709	19980417	00709	SO  	1998	4	17	CA970916008      	1	19970626	G	2910	159H10002477LGU4	LINE            			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  	ROTOL	R4304	R1844304    	EU  	HYD SYSTEM	CHAFED          	W				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			CA								16062	DRG2262		(CAN) CREW REPORTED LOSS OF HYDRAULIC FLUID.  CLAMP ON RT EXT HYD LINE CHAFED THROUGH AT CLAMP.   LT AND RT DRIVEN PUMPS	, FILTERS REPLACED AND LINE AND CLAMPS REPLACED.					2	L	7	2 	4T	4	T		1A17    	E297	6	C	P899	 
1997121100284	19971211	00284	NM  	1997	12	11	CA970916015      	1	19970901	G	2410	700842A	CSD             	SUNDSTRAND  		BOEING	720   	720023B     	1383841	NM  	PWA   	JT3D  	JT3D1       	52039	NE  					QUILL SHAFT	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				7815 		11762		645267			(CAN) ON GROUND CHECK PRIOR TO TAKEOFF THE NR1 ENGINE GENERATOR CAME OFF LINE AND COULD NOT BE RESET, SO CONSTANT SPEED 	UNIT/GENERATOR ASSEMBLY WAS DISCONNECTED AND FLIGHT WAS CARRIED OUT AS PLANNED. ON DISASSEMBLY, OF THE CONSTANT SPEED DR	IVE (CSD), THE OIL LEVEL WAS FOUND TO BE BELOW MINIMUM AND FURTHER INVESTIGATION FOUND THE CARBON SEAL WAS BROKEN AT THE	 GENERATOR END OF THE CSD. THE QUILL SHAFT WAS ALSO BROKEN AT THE ENGINE END OF THE CSD.			2	L	7	4 	4F	4	F		4A28    	1E8				 
1999082000210	19990820	00210	EU  	1999	8	20	CA970916017      	1	19970903	G	6320	350A32106038	SCREW           		350A35110121	SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					M/R GEARBOX	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING DISASSEMBLY OF DRIVE SHAFT,  3 OF 12 SCREWS FOUND WERE THE WRONG TYPE.  THERE WAS NO SPLIT PIN HOLE, AND TH	EY HAD BEEN INSTALLED WITH A HEXAGONAL, INTERNAL LOCK NUT.  THE ENDS HAD BEEN CENTER PUNCHED TO PEEN ENDS OVER.  SCREWS 	SHOULD BE CASTELATED WITH SPLIT PIN.				1	G	7	1 	3U	3	U		H9EU    	E5NE				 
1998041700704	19980417	00704	GL  	1998	4	17	CA970916019      	2	19970908	G	7314		SPLINES         	TRW         	6896810     	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2522 			T0278		CAE890603S			(CAN) FUEL PUMP SPLINE SHAFT END WORN.  REPLACED.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
1997121100286	19971211	00286	EA  	1997	12	11	CA970918005      	3	19970911	G	6110		PROPELLER       													SNSNCH	74DM	M74DM       	EA  	HUB ASSY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3004 	723  					K11765		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER HAD EXTENSIVE CORROSION AND AN OVERHAU	L WAS REQUIRED.															5	N	P88614	 
1998041700699	19980417	00699	CE  	1998	4	17	CA970918009      	1	19970909	G	5730	632205313	SKIN            			CESSNA	525   	525         	2076601	CE  										WING	MISSING         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			920  								(CAN) PILOT REPORTED 3 INCH BY 4 INCH SEGMENT OF LOWER WING SKIN MISSING.  REPLACED.  AIRCRAFT TT:  794 HOURS.						1	L	7	2 	4F			RT	A1WI    					 
1997121100288	19971211	00288	NE  	1997	12	11	CA970918010      	2	19970819	G	7250		BLADE           								PWA   	120   	PW120       		NE  					NR2 ENG LPT	FRACTURED       	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA			10265					120162			(CAN) THE PILOT ELECTED TO RETURN TO HIS POINT OF DEPARTURE AFTER THE ENGINE SUFFERED A DROP IN TORQUE FROM 80 PERCENT T	O 30 PERCENT. POST FLIGHT INVESTIGATION FOUND A LOW PRESSURE TURBINE BLADE HAD FRACTURED.										4	T			E20NE				 
1997121100289	19971211	00289	EA  	1997	12	11	CA970918011      	2	19970617	G	7250		BLADE           								PWA   	PT6   	PT6A28      		EA  					NR2 ENG CT	FRACTURED       	W				O				OTHER                   				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			CA				3970 				41175			(CAN) THE NR2 ENGINE HAD AN UNCOMMANDED SHUTDOWN DURING TAKEOFF. INVESTIGAITON REVEALED A COMPRESSOR TURBINE BLADE ROOT 	FRACTURE. IT WAS REPORTED THE CT BLADES WERE NOT MANUFACTURED BY PRATT & WHITNEY CANADA.										4	T			E4EA				 
1997121100290	19971211	00290	NE  	1997	12	11	CA970918012      	2	19970821	G	7260		GARLOCK SEAL    								PWA   	PT6   	PT6A67D     		NE  					ACCESSORY GEARBX	DISLODGED       	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			8039 	155  				114043			(CAN) THE NR1 ENGINE WAS SHUTDOWN FOLLOWING A LOW OIL PRESSURE WARNING. POST FLIGHT INSPECTION FOUND AN ACCESSORY GEARBO	X GARLOCK SEAL OUTSIDE OF ITS CARRIER										4	T			E26NE				 
1997121100291	19971211	00291	NE  	1997	12	11	CA970918013      	2	19970909	G	7250		BLADES          								PWA   	PT6   	PT6A66      	52043	NE  					2ND STAGE	FRACTURED       	W				O				OTHER                   				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			CA			1437 					104027			(CAN) THE NR4 ENGINE SHUTDOWN DURING THE TAKEOFF ROLL AT ABOUT 90 KNOTS. INSPECTION REVEALED 16 SECOND STAGE BLADES HAD 	FRACTURED.										4	T			E26NE				 
1997121100296	19971211	00296	GL  	1997	12	11	CA970922011      	3	19970720	G	6114		SNAP RING       			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER BLADE	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA				25   				248666R	807440		(CAN) A PROPELLER BLADE SNAP RING DEPARTED THE BLADE DURING FLIGHT. POST FLIGHT INSPECTION REVEALED A LOOSE PROPELLER BL	ADE AND A BROKEN PITCH LINK.					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P47GL	 
1997122900013	19971229	00013	GL  	1997	12	29	CA970923004      	3	19970916	G	6111	F7666A2	BLADE           			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1977 	1033 				RL264351A	CH22032		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADE AND THE HUB NUTS (P/N A2043-1) WERE FOUND CORRODED AN	D WERE REPLACED.					1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920	 
1997122900014	19971229	00014	GL  	1997	12	29	CA970923005      	3	19970816	G	6114	B18032	CYLINDER        													HARTZL	HCB3T	HCB3TN3     	GL  	PROP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1814 					BU462		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CYLINDER AND BEARING FOUND WORN AND STAINED AND WERE REPLACED																6	C	P15EA	 
1997122900015	19971229	00015	GL  	1997	12	29	CA970923006      	3	19970816	G	6114	790100018	BEARINGS        													HARTZL	HCB3T	HCB3TN3     	GL  	PROP HUB	STAINED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1976 					BU463		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BEARING  BALLS FOUND STAINED AND WERE REPLACED																6	C	P15EA	 
1997121100308	19971211	00308	NM  	1997	12	11	CA970923007      	1	19970808	G	2731	82700550	CONTROL CABLE   			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					ELEVATOR TRIM	BROKEN          	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		AP	APPROACH       	1			CA			4150 								(CAN) ON APPROACH THE FLIGHT CREW DISCOVERED THAT THE AIRCRAFT WOULD NOT RESPOND TO COCKPIT ELEVATOR TRIM WHEEL INPUTS. 	LANDING OK. INSPECTION FOUND THAT THE CHAIN/CABLE ASSEMBLY LOCATED IN THE HORIZONTAL STABILIZER HAD BROKEN.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997101600752	19971016	00752	NM  	1997	10	16	CA970923008      	1	19970914	G	3200		LANDING GEAR    			DHAV  	DHC8  	DHC8*       		NM  	PWA   	PW120 	PW123       		NE  					MLG & NLG	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) FOLLOWING A NORMAL APPROACH AND DURING LANDING THE AIRCRAFT CAME TO REST ON THE RUNWAY WITH THE MAIN AND NOSE LAND	ING GEAR PARTIALLY RETRACTED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997121100310	19971211	00310	GL  	1997	12	11	CA970923015      	3	19970915	G	6111		BLADE           													HARTZL	HCA3V	PHCA3VF4    	GL  	SHANK AREA	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						E6872			BR269		(CAN) PROPELLER BLADE FOUND CRACKED ON INSPECTION. THE CRACK WAS IN THE SHANK AREA TOWARDS THE TRAILING EDGE																5	C	P6EA	 
1997121100312	19971211	00312	SO  	1997	12	11	CA970930002      	2	19970924	G	7310	630662	FUEL INJECT LINE			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	NR 6 INJECTOR	BROKEN          	W				A	B	E		UNSCHED LANDING         	EMER. DESCENT           	ENGINE SHUTDOWN         		B	R		SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				104  				28656R	785950		(CAN) DURING FLIGHT THE ENGINE WAS RUNNING ROUGH WITH A LOSS OF POWER. THERE WAS ALSO THE SMELL OF FUEL. POST FLIGHT INS	PECTION FOUND THE NR6 FUEL INJECTOR LINE BROKEN AT THE DISTRIBUTOR CENTRE OF THE ENGINE. THE CAUSE OF THE FAILURE WAS TH	E THROTTLE CONTROL COMING IN CONTACT WITH THE FUEL INJECTOR LINE.				1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1997121100314	19971211	00314	GL  	1997	12	11	CA970930011      	3	19970913	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	PROP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									735103		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE BLADES HAD BEEN REPAIRED IN THE FIELD AND WERE N	OW BELOW THE MINIMUM LIMITS.															5	N	P910	 
1997121100315	19971211	00315	GL  	1997	12	11	CA970930012      	3	19970919	G	6111	90DCA14	BLADE           			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	PROP LE	DAMAGE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			949  	614  				356178	772161		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADE FOUND WITH STONE DAMAGE. PROPELLER BLADE WAS TRIMMED.						1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA	 
1997121100316	19971211	00316	GL  	1997	12	11	CA970930013      	3	19970924	G	6111		BLADE           			CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROP LE	DAMAGE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4791 	1068 				254665A48	K20611		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE LEADING EDGE OF THE PROPELLER BLADES, B	LADES WERE TRIMMED. MOUNTING BOLTS (P/N B4622-12) WERE FOUND BENT AND WERE REPLACED.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1997121100317	19971211	00317	GL  	1997	12	11	CA970930014      	3	19970923	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	PROP LE	DAMAGE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1506 						LD008		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE LEADING EDGE AND FACE OF THE BLADE																5	N	P910	 
1999082700100	19990827	00100	GL  	1999	8	27	CA970930019      	2	19970922	G	7321	78109010	PACKING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FCU	FAILED          	W				R	A			AUTOROTATION            	UNSCHED LANDING         			X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		HO	HOVERING       	1			CA								CAE820809			(CAN) IN HOVER, WHILE WAITING TO RELEASE EXTERNAL LOAD, ROTORCRAFT LOST POWER, AUTOROTATED AND LANDED.  THE MAIN ROTOR B	LADES AND SKID GEAR WERE DAMAGED BEYOND REPAIR AND SCRAPPED.  AIRFRAME IS DAMAGED AND MUST BE TRANSPORTED BACK TO BASE F	OR REPAIRS (ALIGNMENT).  IT WAS LATER DETERMINED THAT THE POWER LOSS WAS CAUSED BY AN INTERNAL PACKING WITHIN THE FCU BL	OCKING THE FUEL FLOW AT ONE OF THE FUEL PORTS.			1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998041700691	19980417	00691	EU  	1998	4	17	CA970930021      	1	19970918	G	7160	F10A5B10201111	ENG INLET       	GRUMAN      	F10A5B10201 	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					LT ENG	FAILED          	W				A				UNSCHED LANDING         				C	O		F.O.D.                    	OTHER                     		CL	CLIMB          	1			CA			159  			A144		P73403			(CAN) A PIECE OF THE ENG INLET FROM THE 9 O'CLOCK POSITION BROKE OFF AND WAS INGESTED INTO THE ENGINE.  A/C REQUIRED TO 	MAKE UNSCHEDULED LANDING.  INVESTIGATION REVEALED DAMAGE TO FAN AREA, FOUND PIECE OF METAL WEDGED IN STATOR VANES.  SEVE	N FAN BLADES REPLACED AND BORESCOPE CHECKED CARRIED OUT.  THE LT ENG INLET HAS BEEN REPLACED 4 TIMES IN THE LAST 4 YEARS	.  PART TC:  161.			2	L	7	2 	4F	4	F		A33EU   	E6WE				 
1997121100320	19971211	00320		1997	12	11	CA970930024      	4	19970919	G	6122	8210181A	PUMP            			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					OVSPEED GOV	DEFECTIVE       	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			17943	550  				120526			(CAN) THE ENGINE EXPERIENCED A PT OVERSPEED WHICH LASTED FOR A DURATION OF 43 SECONDS OVER 110 PERCENT NP SPEED REACHING	 A MAXIMUM OF 118.1 PERCENT. THE ENGINE WAS REMOVED AND SHIPPED FOR INSPECTION. DISASSEMBLY FOUND NO DAMAGE TO THE PRINC	IPAL PT COMPONENTS ATTRIBUTED TO THE OVERSPEED CONDITION. IT WAS FOUND THE PROPELLER OVERSPEED GOVERNOR HYDRAULIC PUMP W	AS GENERATING LESS THAN 50 PERCENT OF REQUIRED PRESSURE. THE CAUSE OF THE OVERSPEED WAS THE FAILURE OF THE PROPELLER OVE	RSPEED GOVERNOR HYDRAULIC PUMP TO PRODUCE SUFFICIENT PRESSURE TO CONTROL THE PCU, WHICH CAUSED THE PROPELLER TO GO INTO 	PITCH LOCK AT A FINER PITCH, RESULTING IN NP OVERSPEED. NO REASON FOR THE LOW PRESSURE OUTPUT OF THE PUMP WAS FOUND.	2	H	7	2 	4T	4	T	RT	A53EU   	E20NE				 
1997121100321	19971211	00321	NE  	1997	12	11	CA970930025      	2	19970919	G	7210	31073301	BEARING         								PWA   	118   	PW118A      		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						18C510		115410			(CAN) THE REDUCTION GEARBOX WAS FOUND BY THE OPERATOR TO HAVE METAL CONTAMINATION AND WAS SHIPPED FOR INVESTIGATION AND 	REPAIR. DISASSEMBLY FOUND THE SOURCE OF THE METAL CONTAMINATION TO BE THE NR15 BEARING WHICH HAD SPALLED BADLY ON THE IN	NER RACE. SUBSTANTIAL RESIDUAL MAGNETISM WAS FOUND ON A NUMBER OF STEEL COMPONENTS AND IT IS CONCLUDED THAT A LIGHTNING 	STRIKE WAS PROBABLY THE PRIMARY CAUSE OF THIS FAILURE. SECONDARY DAMAGE FROM THE CONTAMINANTS WAS MINIMAL AND ONLY THE N	R18 AND NR19 BEARINGS, WHICH WERE FOUND TO HAVE ELECTRICAL DISCHARGE TYPE DAMAGE, REQUIRED REPLACEMENT.							4	T			E20NE				 
1997121100323	19971211	00323	GL  	1997	12	11	CA971003006      	3	19971003	G	6111		BLADE           													MCAULY	1A102	1A102OCM    	GL  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2711 					K19961		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND CORROSION ON THE PROPELLER BLADE FACE																5	N	P918	 
1998041700685	19980417	00685	EA  	1998	4	17	CA971007001      	1	19970818	G	6300	A02D31473R	EXTENSION       		A020301110  	BOEING	107   	1072        	9420604	EA  										UPPER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2618 			K1P3154					(CAN) ON 100 HOUR INSPECTION IAW SB 107-393, A POSITIVE IDENTIFICATION WAS DETECTED.  MAG PARTICLE INSPECTION FOUND A CR	ACK IN A PIN HOLE APPROX  0.150 INCH LONG.					2	G	7	2 	4U				1H16    					 
1998041700684	19980417	00684	EA  	1998	4	17	CA971007002      	1	19970915	G	6320	107D22319	CASE            		107D2011515A	BOEING	107   	1072        	9420604	EA  										LOWER	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A9107A					(CAN) TRANSMISSION STARTED LEAKING OIL.  CRACK FOUND IN LOWER CASE.  OIL COMING  FROM MIXBOX.						2	G	7	2 	4U				1H16    					 
1997121800414	19971218	00414	EA  	1997	12	18	CA971007005      	1	19970921	G	2720	82710019001	PIVOT ASSEMBLY  			DHAV  	DHC8  	DHC8311     	1386006	EA  										RUDDER PEDAL	BINDING         	W		A		C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) DURING THE TAKEOFF ROLL, AT APPROXIMATELY 80 KNOTS, THE RUDDER PEDALS BECAME RESTRICTED. TAKEOFF ABORTED. INSPECTI	ON CARRIED OUT. PIVOT ASSEMBLY AND ASSOCIATED BUSHINGS WERE REPLACED.					2	H	7	2 	4T			RT	A13NM   					 
1998041700682	19980417	00682	SW  	1998	4	17	CA971007014      	1	19970929	G	5530	206020113181	SKIN            		206020113223	BELL  	407   	407         	       	SW  										VERT STAB	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) INSPECTION OF FINS FOUND THAT TWO GRINDING MARKS WERE MADE DURING MANUFACTURE AT AFT BOTTOM SECTION OF FORMERS FOR	 INSTALLATION OF FAIRINGS.  AN ASB WILL BE ISSUED TO COVER.					1	G	7	1 	3U			O	H2SW    					 
1997121100331	19971211	00331	EA  	1997	12	11	CA971010001      	1	19970930	G	5413	75421151103	LONGERON        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					STA.XN50-XN79	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28775								(CAN) HEAVY CORROSION FOUND ON UPPER AND LOWER SURFACES OF THE UPPER LONGERONS. SEVERE CORROSION FOUND ON LONGERONS FROM	 STA.XN50 TO XN79.0. THIS CORROSION WAS NOT EVIDENT UNTIL THE COWL SEALS AND LATCH PLATES WERE REMOVED. FURTHER SEVERE C	ORROSION WAS FOUND UNDER TITANIUM DOUBLERS FROM XN79 TO XN96. UPON REMOVAL OF THE NACELLE UPPER LONGERON IT WAS NOTED TH	AT NORMAL PROCEDURES REQUIRED BY EQUALIZED INSPECTION CARD R61 WOULD NOT DETECT THIS CORROSION.			2	H	7	4 	4T	4	T		A20EA   	E4EA				 
1997121100332	19971211	00332	SO  	1997	12	11	CA971010008      	2	19970927	G	7322	104439	CARBURETOR      			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300C       	17022	SO  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	Y		FLUID LOSS                	ENGINE STOPPAGE           		CR	CRUISE         	1			CA				1153 				31632D4C			(CAN) DURING CRUISE THE ENGINE BEGAN TO SUFFER POWER LOSS WITHOUT WARNING. EMERGENCY LANDING WAS CARRIED OUT. POST FLIGH	T INSPECTION FOUND FUEL POURING FROM THE CARBURETOR. THE CARBURETOR WAS REPLACED WITH AN OVERHAULED UNIT AND THE ENGINE 	WAS GROUND RUN SERVICEABLE.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
1998041700675	19980417	00675		1998	4	17	CA971010011      	2	19971001	G	7510	2306696	FIRESHIELD      																	SPOTWELDS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4    								(CAN) SIX SPOTWELD RETAINING ANTI-ICING SOLENOID VALVE ASSEMBLY BRACKETS TO FIRESHIELD ASSY ARE UNDONE CAUSING BRACKET T	O SEPARATE FROM FIRESHIELD.  SUSPECT INCORRECT WELDING PROCESS.   REPLACED.																		 
1998041700674	19980417	00674	SW  	1998	4	17	CA971010012      	1	19970708	G	2750	500012231	CONTROL CABLE   			GULSTM	690TP 	695A        	7630519	SW  										RT INB FLAP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5330 								(CAN) 75 PERCENT OF RT INBOARD FLAP CABLE STRANDS BROKEN.  REPLACED.						1	H	7	2 	4T			 	2A4     					 
1998020500479	19980205	00479	WP  	1998	2	5	CA971014003      	2	19971005	G	7260	31017015	PINION ASSEMBLY 			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					GEARBOX	PRIMARY FAILURE 	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			G	J		MULTIPLE FAILURE          	WARNING INDICATION        		CL	CLIMB          	1			CA								P54215			(CAN) AIRCRAFT WAS IN-FLIGHT WHEN THE L/H CHIP LIGHT ILLUMINATED, OIL PRESSURE DROPPED 50 PSI, TORQUE FLUCTUATED, FEATHE	RED ENGINE. TEARDOWN REVEALED THAT ROTATING GROUP COULD NOT BE TURNED. FORWARD BEARINGIN THE HIGH SPEED PINION BEARING A	SSEMBLY HAD FAILED. SUBMITTER NOTES THAT HIGH SPEED PINION ASSEMBLY REQUIRES DYNAMIC BALANCING AFTER REPAIR OR MODIFICAT	ION. THERE IS NO INDICATION THAT THIS WAS DON E. SUBMITTER SENT FOLLOW-UP REPORT TO VERIFY THAT LAB ANALYSIS FOUND THAT 	THE FRONT ROLLER BEARING HAD A ROLLER END/GUIDE FLANGE PRIMARY FAILURE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
1997121100338	19971211	00338	EU  	1997	12	11	CA971015014      	1	19971003	G	2410	735874C	GENERATOR DRIVE 			AIRBUS	310   	A310304     		EU  										NO ENGINE GEN	OVERHEATED      	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CRUISE NR1 I.D.G. HAD AN OVERHEAT TEMPERATURE READING OF 189 DEGREES. I.D.G. DISCONNECTED AND AIRCRAFT RETU	RNED TO BASE. AS A PRECAUTIONARY MEASURE THE I.D.G. HEAT EXCHANGER AND GENERATOR CONTROL UNIT WERE REPLACED ALONG WITH T	HE I.D.G.				2	L	7	2 	4F			RT	A35EU   					 
1997122900018	19971229	00018	NE  	1997	12	29	CA971015024      	2	19971015	G	8500		ENGINE          			DHAV  	DHC3  	DHC3        	2800202	EA  	WSK   	PZL   	PZLM18      	67203	NE  					POWER SECT	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				923  				KAB734402			(CAN) EXCESSIVE OIL CONSUMPTION AND METAL IN THE OIL SCREEN. TEARDOWN REPORT NOT YET AVAILABLE.						1	H	7	1 	3R	4	R		A815    	E10NE				 
1997121800426	19971218	00426	NM  	1997	12	18	CA971015026      	1	19970925	G	2934	EA1093A2408	TRANSMITTER     			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					A SYS HYD	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			CA								P653620B			(CAN) DURING APPROACH 'A' SYSTEM HYDRAULIC QUANTITY WOULD FLUCTUATE IN TURBULENCE, QUANTITY TRANSMITTER REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121800427	19971218	00427		1997	12	18	CA971015027      	4	19970919	G	2370	5224058002	CVR TAPE        	COLLINS     	CVR         	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					COCKPIT	BROKEN          	W				H				DEACTIVATE SYST/CIRCUITS				L			NO TEST                   			NR	NOT REPORTED   	1			CA						770		P653620B			(CAN) COCKPIT CVR FAILED TEST FUNCTION, CONTINUOUS TAPE REPLACED SERVICEABLE.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121800428	19971218	00428	NM  	1997	12	18	CA971015028      	1	19971001	G	2710	652440014	LOCKOUT         	BOEING      	552440014   	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					RH AILERON	TORN BOOT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P653620B			(CAN) DUST BOOT ON RIGHT HAND AILERON LOCKOUT MECHANISM TORN, REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121800429	19971218	00429	NM  	1997	12	18	CA971015029      	1	19971001	G	5260	65178202	SEAL            	BOEING      	65178202    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					AIR STAIR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						OA535		P653620B			(CAN) AIRSTAIR ACTUATOR LEAKING. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121800430	19971218	00430	NM  	1997	12	18	CA971015030      	1	19971001	G	2133	35584	SEAT            	ALLIED SIGNA	10328051    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LT OUTFLOW	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						35584		P653620B			(CAN) LEFT HAND OUTFLOW VALVE SEAT LEAKING. REPLACED						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400029	19971224	00029	NM  	1997	12	24	CA971015031      	1	19971002	G	8012	97925431	START VALVE     	ALLIED SIGNA	97925431    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					NR 2 ENGINE	HOLE            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						P1921		P653620B			(CAN) NR2 ENGINE START VALVE HAS HOLE IN BODY. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997121100343	19971211	00343	NM  	1997	12	11	CA971015032      	1	19971007	G	7830	65378316	SELECTOR VALVE  			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					THRUST REVERSER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				3725 		1917		P653620B			(CAN) DURING A "C" CHECK INSPECTION THE THRUST REVERSER SELECTOR VALVE OF NR1 ENGINE WAS FOUND TO HAVE A LEAKING SHAFT S	EAL, THE SELECTOR WAS REMOVED AND A SERVICEABLE UNIT INSTALLED AND THE SYSTEM RETURNED TO SERVICE.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400030	19971224	00030	NM  	1997	12	24	CA971015033      	1	19971007	G	5260	65178132	LOCK            	BOEING      	65178132    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					AIR STAIR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						RC625		P653620B			(CAN) AIRSTAIR LOCK ACTUATOR LEAKING. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400031	19971224	00031	NM  	1997	12	24	CA971015034      	1	19971007	G	2780	65319467	SEAL            	BOEING      	65319467    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LE FLAP VALVE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						515		P653620B			(CAN) LEADING EDGE DEVICE SELECTOR VALVE LEAKING BEYOND LIMITS. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400032	19971224	00032	NM  	1997	12	24	CA971015035      	1	19971007	G	7500	69253011	FLANGE          	BOEING      	69253011    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					BLEED DUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P653620B			(CAN) BLEED AIR DUCT CRACKED AT FLANGE. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400033	19971224	00033	NM  	1997	12	24	CA971015036      	1	19971007	G	7500	65322481	DUCT            	BOEING      	65322481    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					BLEED DUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P653620B			(CAN) BLEED AIR DUCT CRACKED AT FLANGE. REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400034	19971224	00034	NM  	1997	12	24	CA971015037      	1	19971009	G	3230	651781011	ROD END BEARING 	BOEING      	651781011   	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					NLG LK ACTUATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						RC1036		P653620B			(CAN) NOSE LANDING GEAR LOCK ACTUATOR ROD END BEARING LOOSE. ACTUATOR REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1997122400035	19971224	00035	NM  	1997	12	24	CA971015038      	1	19971009	G	3010	F61C0058M1	VALVE           			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					LT WING TAI	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								P653620B			(CAN) LEFT HAND WING TAI VALVE LEAKING ALLOWING HOT AIR TO BYPASS WHEN CLOSED.						2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1998040100006	19980401	00006	SW  	1998	4	1	CA971015065      	1	19971007	G	7110	212060805121	COWLING         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					LT SIDE	DEPARTED        	W				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			1    								(CAN) EVERYTHING NORMAL ON TEST FLIGHT.  AFTER SHUTDOWN IT WAS NOTED THAT LEFT COWLING WAS MISSING.  A FASTENER REQUIRED	 PER ASB 412-95-87 HAD NOT BEEN INSTALLED.  THE LEFT STABILIZER WAS DAMAGED AT ITS JUNCTION WITH TAILBOOM BY COWL.					1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1997121100349	19971211	00349	SO  	1997	12	11	CA971016002      	2	19971008	G	8530	648042	PISTON RING     			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					ENG CYL	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			256  					312042			(CAN) DURING CYLINDER REMOVAL TO CORRECT AN OIL CONSUMPTION PROBLEM, IT WAS FOUND THAT PISTON RING (P/N 684042) WAS BROK	EN. IT APPEARS THERE WAS A CASTING PROBLEM DURING MANUFACTURER.					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
1997121100351	19971211	00351	NE  	1997	12	11	CA971016004      	2	19970922	G	7240	767279	COMB OUTER CASE 								PWA   	JT8   	JT8D7B      	52053	NE  					FLANGE HOLES	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			56357					P657387D			(CAN) DURING A SCHEDULED INSPECTION THE COMBUSTION OUTER CASE WAS FOUND CRACKED AT TWO MOUNTING BOLT HOLES ON THE REAR F	LANGE. THE FIRST CRACK EXTENDS HALF THE DEPTH OF THE HOLE AND 1/2" IN LENGTH. THE SECOND CRACK EXTENDS THREE QUARTERS TH	E DEPTH OF THE HOLE AND 3/4" IN LENGTH. THE CASE P/N 767279 WAS MODIFIED FROM P/N 490547 AT 32023 CYCLES. THE CRACKS WER	E FOUND BY FLUORESCENT PENETRANT INSPECTION.								4	F			E2EA				 
1997122400038	19971224	00038	NE  	1997	12	24	CA971016018      	2	19970926	G	7210	312005001	INPUT PINION    			DHAV  	DHC8  	DHC8*       		NM  	PWA   	120   	PW120A      		NE  					REDUCTION GEARBX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7394 					121359			(CAN) RGB SENT FOR INVEST. AFTER A SPALLED INPUT PINION WAS FOUND DURING A BORESCOPE INSP FOLLOWING AN OVERTORQUE OF 170	 PCT.DAMAGE CONFIRMED TO- INPUT PINION TEETH,THIS WAS ACCOMPANIED B Y FROSTING A SPALLING OF- TEETH OF BOTH 1ST STAGE HE	LICAL GEARS.3 NUTS FOUND LOOSE.2 KEYWASHERS FOUND CRACKED & BOTH LAYSHAFT NUTS WERE FINGER TIGHT.HEAVY IMPACT DAMAGE ALS	O DISCOVERED ON #15 BEARING & S PALLING ON 1ST STAGE GEARS IS FAIRLY TYPICAL OF 1ST STAGE GEAR TOOTH DAMAGE EVEN IN RGB'	S NOT EXPOSED TO HIGH TORQUENO IND. THAT DAMAGE WAS RELATED TO OVERTORQUELOOSE NUTS & CRACKED WASHERS ARE INDICATIVE OF 	LONG TERM VIBRATION PROBLEMS CAUSED BY LOOSE GEARS.P&W HAVE RELEASED A MOD TO-IR COMPONENTS WHICH INCORPORATE STIFFER G	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1998032600494	19980326	00494	SW  	1998	3	26	CA971016020      	1	19971008	G	2910	MS21926W6	ELBOW           			BELL  	212   	212         	1181420	SW  										HYD LINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) A SLIGHT LEAK AT A HYDRAULIC LINE P/N 212-076-348-1 BECAME WORSE WHEN THE 'B' NUT WAS TIGHTENED.  ELBOW WAS FOUND 	CRACKED IN 2 LOCATIONS ABOUT 180 DEGREES APART.  THE CRACKS RADIATED FROM END OF FLARE.					1	G	7	1 	4U				H4SW    					 
1998041700433	19980417	00433	CE  	1998	4	17	CA971020006      	1	19970920	G	5510	AN447	BOLT            			BEECH 	23    	A23         	1151204	CE  										STAB ACT TUBE	DAMAGE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2033 								(CAN) UPON REMOVAL OF STABILATOR ACTUATING TUBE BALANCE WEIGHT, IMPACT DAMAGE TO THE ATTACHMENT BOLT WAS FOUND.  DAMAGE 	APPEARED TO BE CAUSED BY REPETITIVE IMPACT RESULTING FROM BALANCE WEIGHT STRIKING THE MICARTA STOP BLOCK.  AIRCRAFT TT: 	 2,033 HOURS.				1	L	7	1 	3O				A1CE    					 
1997122400043	19971224	00043	EA  	1997	12	24	CA971020009      	1	19971007	G	2731	TWF2128U	BEARING         		C6CT10103   	DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ELEV TRIM	NOT LUBED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								0			(CAN) NEW BEARINGS WERE RECEIVED FROM STORES TO REPLACE WORN ELEVATOR TRIM AND FLAP INERCONNECT SCREW JACK BEARINGS. A N	UMBER OF THE NEW BEARINGS WERE NOT LUBRICATED INTERNALLY. THEY APPEARED TO BE DRY. THESE WERE RETURNED TO DE HAVILLAND F	OR INSPECTION. THESE BEARINGS WERE MANUFACTURED BY MINIATURE PRECISION BEARINGS, DIVISION OF MPB CORP., KEENE, NEW HAMPS	HIRE. BEARINGS WERE BOXED AND SEALED IN PLASTIC BAGS WHEN RECEIVED. MANUFACTURE DATE 12/86 AND 8/88.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
1997122400044	19971224	00044	GL  	1997	12	24	CA971020010      	3	19971010	G	6111	90DCA14	BLADE           													MCAULY	2A34C	2A34C203    	GL  	PROP LEAD EDGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2082 	733  					766423		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE LEADING EDGES																5	C	P3EA	 
1998043000046	19980430	00046	NM  	1998	4	30	CA971020015      	1	19970904	G	3234	574205	SELECTOR VALVE  			DHAV  	DHC8  	DHC8102     	2809003	NM  										MLG	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			AP	APPROACH       	1			CA						450					(CAN) WITH NORMAL APPROACH FOR LANDING AND GEAR SELECTION,  GEAR FAILED TO COME DOWN.  ALTERNATE SELECTION MADE, OK.  LA	NDED OK.  SELECTOR VALVE REPLACED.					2	H	7	2 	4T			RT	A13NM   					 
1997122400047	19971224	00047	NE  	1997	12	24	CA971020016      	2	19970926	G	7250		BLADE           								PWA   	118   	PW118       		NE  					LP TURBINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA								115417			(CAN) THE ENGINE WAS SHUTDOWN IN FLT AFTER LOSS OF OIL PRESSURE: POST FLT- PT WAS STIFF TO TURN, SO- ENGINE WAS SENT FOR	 INSP & OVERHAUL. DISASSY REVEALED 2 LP TURBINE BLADES WITH 50 PERCENT OF- AIRFOIL MISSING; OVERTEMP DAMAGE TO ALL 4 STA	GES OF TURBINE BLADES; A FAILED NR6 BEARING; A FRACTURED NR6 & NR 7 BEARING VENT TUBE; NR 6 &NR 7 BEARING HOUSING SEPARA	TED & SPLIT IN-HALF;- PRESSURE RELIEF VALVE STUCK OPEN. IT IS- OPINION OF- SUBMITTER THAT- INIT FAILURE OF 2 (2) LP TURB	INE BLADE AIRFOILS WAS- CAUSE OF- DAMAGE & SHUTDOWN. IT APPEARS THAT THIS FAILURE OCCURRED SOMETIME PRIOR TO- IFSD &- RE	SULTING OUT OF BALANCE & VIBRATION WAS- CAUSE OF SECONDARY DAMAGE & LOSS OF OIL PRESSURE:						4	T			E20NE				 
1998041700435	19980417	00435	EU  	1998	4	17	CA971021001      	1	19971015	G	2435	036010	BEARING         	LUCAS       	23080005    	BRAERO	DH125 	BAE125800A  	1500285	EU  										START/GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2747					(CAN) BEARING FAILURE CAUSED DAMAGE TO ARMATURE.						2	L	7	2 	4F			RT	A3EU    					 
1997122400048	19971224	00048	GL  	1997	12	24	CA971021004      	3	19971015	G	6110		BLADE           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROP ASSY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1740 	262  				61799SA	K18946		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER WAS FOUND WITH EXTENSIVE CORROSION ALL OVER. THE PROPELLER 	WAS OVERHAULED.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918	 
1998010600002	19980106	00002	GL  	1998	1	6	CA971021005      	3	19971015	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	BLADE LE/FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5614 						IA016		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND TO THE PROPELLER BLADE ON THE LEADING EDGE AND	 THE FACE.															5	N	P910	 
1998041700438	19980417	00438	GL  	1998	4	17	CA971021013      	2	19971007	G	7250	705280	BEARING         								ALLSN 	501D  	501D13D     	03004	GL  					NR 3	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			HO	HOVERING       	1			CA				122  				501780			(CAN) THE ENGINE SUFFERED AN IN-FLIGHTT FAILURE DURING DESCENT.  POST-FLIGHT INSP AND INVEST FOUND PRIMARY FAILED ITEM A	S TURBINE COUPLING SHAFT.  ENGINE AND COMPONENTS SHIPPED TO MFG FOR EVALUATION.  MFG DISPUTES ORIG FINDINGS AND STATES T	HE INITIATING EVENT WAS LOSS OR REDUCTION OF OIL SUPPLY TO NR 3 BEARING AREA WHICH REQUIRED MOST OF ITS OIL SUPPLY TO CO	OL BEARING, FOR REASONS UNKNOWN.  IT APPEARS BEARING AND CAGE RETENTION FAILED AND IT MIGRATED FORWARD.  ONCE OFF LOCATI	ON AND WEARING INTO CLAMP NUT, ORBITING SHAFT CAUSED FRACTURE AND FATIGUE FAILURE OF COUPLING SHAFT.							4	T			E282				 
1998042900018	19980429	00018	WP  	1998	4	29	CA971021014      	1	19971008	G	2610		ELEMENT         			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					NR 2 ENG	SHORTED         	W				E	F	D		ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	RETURN TO BLOCK         		N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA								501754			(CAN) SHORTLY AFTER BEGINNING TAXIING AND PRIOR TO TAKEOFF, THE CAPTAIN REACTED TO A  FIRE WARNING FROM ZONE 2 OF THE AI	RCRAFT'S NR 2 ENGINE BY SHUTTING THE ENG DOWN AND RELEASING FIRE AGENT IN THE AFFECTED AREA.  FIRE ELEMENT WAS FOUND FAU	LTY AND REPLACED.				2	L	7	2 	4R	4	T		6A6     	E282				 
1998032600498	19980326	00498	SW  	1998	3	26	CA971021023      	1	19971002	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										NR 7 AFT OUTER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			303  								(CAN) AS PER AD CF-97-19, INSPECTION OF TAIL ROTOR DRIVE SHAFT THOMAS COUPLINGS CARRIED OUT.  THE AFT OUTER DISC OF THE 	NR 7 DISC PACK WAS FOUND BROKEN IN TWO PLACES.  DISC PACKS TAKEN FOR TESTING BY BELL.  BHTC IS REDESIGNING DISCS TO OVER	COME MID-SPAN CRACKING.				1	G	7	1 	3U			O	H2SW    					 
1998010600004	19980106	00004	GL  	1998	1	6	CA971024009      	3	19970930	G	6114	5872	HUB             													MCAULY	3A32C	D3A32C*     	GL  	PROP ASSY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1102 						871205		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER HUB AND PROPELLER BLADES (P/N G82NDB-2) FOUND EXTREMELY COR	RODED. IT WAS 5 YEARS FROM THE LAST CORROSION INSPECTION AND 10 YEARS FROM THE LAST OVERHAUL. THE PROPELLER WAS OVERHAUL	ED														5	C	P21EA	 
1998032600499	19980326	00499	EU  	1998	3	26	CA971024010      	1	19971006	G	6310	4619303081	BEARING         		4638001001  	BOLKMS	105   	BO105S      	5626006	EU  										MAIN XMSN	PEELING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				852  		884					(CAN) MAIN TRANSMISSION LEFT INTERMEDIATE SHAFT BEARING FOUND PEELING.						1	G	7	2 	3U				H3EU    					 
1997122400069	19971224	00069	SO  	1997	12	24	CA971027008      	2	19970918	G	8530	654651A2	CYLINDER ASSY   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	ENGINES	EXCESSIVE WEAR  	W				K				NONE                    				E	R	W	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            	IN	INSP/MAINT     	1			CA			10   	10   				1109615A	703083		(CAN) TEN HOURS AFTER COMPLIANCE OF FAA AD 97-15-01 (SS BY FAA AD 97-21-02), SIDE LOADING OF THE PISTON, THE AIRCRAFT OW	NER COMPLAINED TO THE OVERHAUL SHOP OF ENGINE VIBRATION AND POWER LOSS. INSPECTION OF THE OVERHAULED ENGINE REVEALED EXC	ESSIVE AND PREMATURE CYLINDER BARREL WEAR. THESE CYLINDERS WERE FACTORY "NEW" AND WERE STAMPED "P" IDENTIFYING THEM AS B	EING INSPECTED BY THE FACTORY IN ACCORDANCE WITH CONTINENTAL SB 97-10 (SB 97-10A).			1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P3EA	 
1997121100360	19971211	00360	CE  	1997	12	11	CA971027010      	1	19970717	G	2822	480532	FUEL PUMP       			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  					RIGHT AUXILIARY	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								506848			(CAN) RIGHT AUXILIARY FUEL PUMP FOUND RUSTED. ALSO LEFT AND RIGHT CHECK VALVES PART NO. FACKV-5-100-6 FOUND CLOGGED. THI	S AS A RESULT OF INSTALLATION OF FLINT AUXILIARY SYSTEM STC SA2862WE, SA3266NM OR SA4300WE ACCORDING TO SUBMITTER.					1	H	7	1 	3O	3	O		3A21    	E8CE				 
1997121100361	19971211	00361	CE  	1997	12	11	CA971027011      	1	19970503	G	2822	477003	FUEL PUMP       			CESSNA	206   	U206G       	2073356	CE  										LEFT AUXILIARY	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEFT AUXILIARY FUEL PUMP CORRODED AND BOTH THE LEFT AND RIGHT CHECK VALVES P/N FACKV-4-100-6 FUND CLOGGED. THIS AI	RCRAFT HAS FLINT STC SYSTEM STEEL PARTS WHICH ACCORDING TO SUBMITTER ARE CAUSING THE CORROSION AND CAN CLOG FUEL SYSTEM.	 STC SA4368WE.				1	H	7	1 	3O				A4CE    					 
1997121100362	19971211	00362	CE  	1997	12	11	CA971027012      	1	19970717	G	2842	FA2091	FUEL TRANSDUCER 			CESSNA	206   	U206G       	2073356	CE  										LEFT HAND	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LEFT FUEL TRANSDUCER FOUND RUSTED, REPLACED BY NEW PLASTIC TYPE. THIS AIRCRAFT HAS THE FLINT AUXILIARY SYSTEM 	STC SA4366WE INSTALLED WHICH CONTAINS STEEL PARTS AND ACCORDING TO SUBMITTER IS CAUSING THE CORROSION AND CAN CLOG FUEL 	SYSTEM.				1	H	7	1 	3O				A4CE    					 
1997121100363	19971211	00363	CE  	1997	12	11	CA971027013      	1	19970312	G	2822	477003	FUEL PUMP       			CESSNA	206   	U206G       	2073356	CE  										LEFT AUXILIARY	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEFT AUXILIARY FUEL PUMP FOUND RUSTED. THIS AIRCRAFT CONTAINS FLINT AUXILIARY SYSTEM AS PER STC SA4368WE WHICH CON	TAINS STEEL PARTS AND ACCORDING TO SUBMITTER CAUSES THE RUSTING AND COULD CLOG THE FUEL SYSTEM. THE AIRCRAFT REGISTRATIO	N IS NOW C-FJST				1	H	7	1 	3O				A4CE    					 
1997122400074	19971224	00074	CE  	1997	12	24	CA971028007      	1	19971020	G	2720	505244483	PUSH ROD        	BEECH       	50524402613 	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					PILOT RUD ARM	WORN            	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			3172 					PCE25636			(CAN) DURING A PHASE 3 INSPECTION, IT WAS FOUND THAT THE PILOTS RUDDER ARM ASSEMBLY (P/N 50-524415-10) HAD APPROXIMATELY	 0.020 INCHES DEEP WEAR ON THE INNER SURFACE OF THE FORK LUG WHERE THE PUSH ROD ATTACHES RH ARM. UPON REMOVAL OF THE PUS	H ROD, IT WAS FOUND THAT THE BEARING IN THE ROD END OF THE PUSH ROD WAS DAMAGED. IT WAS DETERMINED THAT THE DAMAGE WAS C	AUSED BY A METAL OBJECT THAT WAS WEDGED BETWEEN THE BEARING AND THE LUG WALL. THIS CREATED THE WEAR. NEW PARTS INSTALLED	.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
1997122400077	19971224	00077	EU  	1997	12	24	CA971028013      	1	19971022	G	3242	5010783	DISC            		50068572    	AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	LT NR 1 BRAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			17207	1155 		SEP87536		0	0		(CAN) DURING TAXI, AIRCRAFT SUDDENLY PULLED TO THE LEFT. AIRCRAFT HAD TO STOP AS TAXIING NO LONGER POSSIBLE. NR1 BRAKE A	ND WHEEL REPLACED. INSPECTION OF BRAKE FOUND THAT THE STATIONARY DISC WAS BROKEN AND THE LOOSE PART WAS JAMMING THE WHEE	L.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
1998041700666	19980417	00666	SO  	1998	4	17	CA971031002      	1	19971024	G	3260	1CH214	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) ON SELECTING GEAR DOWN, RT GEAR SHOWED GREEN AND RED UNSAFE LIGHT ON.  SEVERAL RETRACTIONS CARRIED OUT, NO CHANGE.	  TOWER REPORTED GEAR APPEARED NORMAL AND A/C LANDED SAFELY.  MAINTENANCE INSPECTED GEAR AND CONFIRMED GEAR WAS LOCKED A	ND SWITCH IN NORMAL POSITION.   DEFECTIVE SWITCH REPLACED.				1	L	7	2 	3O				A20SO   					 
1997122400079	19971224	00079	GL  	1997	12	24	CA971031003      	3	19971023	G	6114	C5262	CYLINDER        			BEECH 	23    	A24R        	1151252	CE  	LYC   	O360  	IO360A1B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	PROP HUB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			428  	247  				L685851F	694582		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CYLINDER FOUND WORN AND WAS REPLACED. THE PROPELLER BLADE (P/N S78FBM	-1.5) WAS FOUND NICKED ON THE LEADING EDGE AND THE FACE AND WAS TRIMMED.					1	L	7	1 	3O	3	O		A1CE    	1E10	5	C	P7EA	 
1998010600005	19980106	00005	GL  	1998	1	6	CA971031004      	3	19971024	G	6114	57A2202	BEARING         													HARTZL	HCC2Y	BHCC2YF2    	GL  	PROP ASSY	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1111 	528  					AN6954A		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROP BEARING WAS FOUND DAMAGED ON THE INNER RACE. ONE BOLT (P/N 57A24	33) WAS FOUND CORRODED IN THE SHANK AREA.															5	C	P920	 
1997122400087	19971224	00087	EA  	1997	12	24	CA971031018      	2	19971020	G	7314	GR9080J7A	FUEL PUMP       	ROMEC       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					CASE DRAIN	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						D7138		L586361A			(CAN) PRIOR TO RUN-UP, DURING THE FUEL PUMP PRESSURE AND LEAK TEST, THE FUEL PUMP WAS LEAKING FUEL FROM THE PUMP CASE DR	AIN, WHEN THE BOOSTER PUMPS OR THE AUXILIARY PUMP WERE ACTIVATED. THE ENGINE WAS STARTED WITH USUAL FIRE PRECAUTIONS OBS	ERVED. THE FUEL LEAK DID NOT STOP. THE ENGINE WAS SHUTDOWN AND THE FUEL PUMP REMOVED. THE OVERHAUL SHOP REPORTED THE PUM	P SEAL INSIDE DID NOT SEAT. THE FUEL PUMP FROM THE TX'D ENGINE WAS INSTALLED AND THE PUMP AND ENGINE TESTED SERVICEABLE.			1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1997122400088	19971224	00088	NM  	1997	12	24	CA971031019      	1	19970826	G	3242	2661943	HOUSING         	BFGOODRICH  	214665      	DHAV  	DHC8  	DHC8*       		NM  										BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12716			0220R					(CAN) LIQUID PENETRANT AND EDDY CURRENT INSPECTION WERE COMPLETED ON DHC8 BRAKE HOUSINGS IN ACCORDANCE WITH BF GOODRICH 	COMPONENT MAINTENANCE MANUAL (CMM). ON THIS S/N 3 PISTON CAVITIES WERE FOUND CRACKED JUST BELOW THE INLET AND BLEEDER PO	RTS. DATE OF MANUFACTURE IS JANUARY 1985.				2	H	7	2 	4T			RT	A13NM   					 
1998041700446	19980417	00446	CE  	1998	4	17	CA971104003      	1	19971024	G	3260	IEN1186	SWITCH          			CESSNA	500   	560CESSNA   	2076750	CE  										NLG DOWNLOCK	FAILED          	W				L				ABORTED APPROACH        				P	J		NO WARNING INDICATION     	WARNING INDICATION        		AP	APPROACH       	1			CA			2246 								(CAN) LANDING GEAR SELECTED DOWN AND ONLY THE MAIN GEAR INDICATED DOWN AND LOCKED.  AFTER SEVERAL CYCLES, AN EMERGENCY L	ANDING WAS SUCCESSFULLY CARRIED OUT.  ACTUATOR CHECKED OK. NLG DOWNLOCK SWITCH REPLACED.  OLD NLG SWITCH WAS NOT SEALED,	 POSSIBLE WATER AND FREEZING CAUSED PROBLEM.  PART TC:  3,300.				2	L	7	2 	4F			RT	A22CE   					 
1998041700665	19980417	00665	CE  	1998	4	17	CA971104004      	1	19971029	G	2750	500000863	CABLE ASSY      			CESSNA	402   	402C        	207590R	CE  										FLAP	BROKEN WIRES    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13636								(CAN) DURING THE ROUTINE INSPECTION, BROKEN WIRES/STRANDS OF THE FLAP CONTROL CABLE ASSY WERE FOUND.  DEFECTIVE CABLE AS	SY AND PULLEY P/N S378-4 REPLACED AND SYSTEM CHECKED.					1	L	7	2 	3O				A7CE    					 
1998043000052	19980430	00052	NE  	1998	4	30	CA971104014      	2	19971023	G	7250	MS969611	BOLTS           								PWA   	PW121 	PW121       	52124	NE  					1ST STG STATOR	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16178					121019			(CAN) TURBOMACHINE SENT FOR INVESTIGATION AND REPAIR AFTER OPERATOR REPORTED POWER TURBINE DAMAGE. THE CAUSE OF THE PT D	AMAGE WAS A FAILURE OF SEVEN, 1ST STAGE STATOR RETAINING BOLTS.  FAILURE OF THE 1ST STAGE STATOR RETAINING BOLTS APPEARS	 TO BE THE RESULT OF CORROSION AT THE REAR FLANGE OF THE TURBINE INTERSTAGE CASE WITH ALL OTHER DAMAGE OBSERVED BEING SE	CONDARY.								4	T			E20NE				 
1998043000054	19980430	00054	CE  	1998	4	30	CA971106002      	1	19971030	G	3260	2078101	CONNECTOR       			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      		SO  					NLG DOWNLOCK	LOOSE           	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA								682290			(CAN) DURING LANDING, NOSE WHEEL DOWN LOCK LIGHT CAME ON INTERMITTENTLY.  AIRCRAFT LANDED SAFELY.  TROUBLESHOOTING REVEA	LED A BULKHEAD ELECTRICAL CONNECTOR FROM WHEEL BAY TO THE ENGINE COMPARTMENT WAS DISCONNECTED EVEN THOUGH IT WAS IN PLAC	E.  THE PLASTIC TAB LOCK RING COULD NOT BE SECURED WITH THE PLUG FULLY INSERTED IN THE RECEPTACLE.				1	L	7	1 	3O	3	O		3A15    	E3SO				 
1998043000055	19980430	00055	GL  	1998	4	30	CA971106003      	1	19971030	G	2820	EP160B01BXXC0360	FUEL LINE       			DIAMON	DA20A1	DA20A1      	05626UX	GL  										FUEL PUMP SWAGE	SWOLLEN         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) EIGHT INCH HOSE RECEIVED FROM MANUFACTURER NEW.  FLOW TEST FOUND TO HAVE RESTRICTIONS CAUSING A FAN PATTERN IN THE	 FLOW.					1	L	7	1 	3O			NT	TA4CH   					 
1998043000056	19980430	00056	GL  	1998	4	30	CA971106004      	1	19971031	G	2820	FP160B01BXXC0360	FUEL HOSE       			DIAMON	DA20A1	DA20A1      	05626UX	GL  										FUEL PUMP SWAGE	BENT            	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BRACKET AT ENGINE DRIVEN PUMP OF FUEL SUPPLY LINE FOUND BENT AND WILL NOT FIT THE AIRCRAFT.  SUBMITTER SCRAPPED HO	SES.					1	L	7	1 	3O			NT	TA4CH   					 
1998043000064	19980430	00064	SO  	1998	4	30	CA971110003      	2	19971030	G	8520		CRANKCASE       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 1 CYL BORE	CRACKED         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			CA				1038 				239802R			(CAN) PILOT REPORTED NR 1 ENGINE WAS RUNNING ROUGH.  MAINTENANCE FOUND OIL LEAKS AND EVIDENCE OF COMBUSTION DETONATION A	T NR 1 CYLINDER.  FURTHER INSPECTION FOUND NR 36 STUD WAS PULLED OUT OF THE CRANKCASE THREADS.  THE NR 1 CYLINDER BORE I	N THE CRANKCASE WAS FOUND CRACKED FROM NR 35 STUD THREADS UP INTO THE CYLINER BORE.  THE ENGINE WAS REMOVED FOR REPAIR A	ND A FACTORY REMANUFACTURED ENGINE WAS INSTALLED.			1	L	7	2 	3O	3	O		A7CE    	E7CE				 
1998041700662	19980417	00662	SO  	1998	4	17	CA971110007      	1	19971031	G	7603	554528	CABLE           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					THROTTLE	BROKEN          	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			AP	APPROACH       	1			CA			4385 					RL19077T			(CAN) RT ENGINE CONTROL FAILED ON APPROACH.  INVESTIGATION REVEALED BREAK OCCURRED AT COCKPIT END OF THROTTLE CONTROL AP	PROXIMATELY .25 INCH FROM SWAGED FITTING.  BOTH CONTROL CABLES RT AND LT REPLACED.					1	L	7	2 	3O	3	O		A19S0   	E286				 
1998043000068	19980430	00068	EU  	1998	4	30	CA971110009      	1	19971030	G	2611	CG7PO	SMOKE DETECTOR  			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      		NE  					FORWARD CARGO	INOPERATIVE     	W				A	F			UNSCHED LANDING         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, ECAM MESSAGE INDICATED FORWARD CARGO COMPARTMENT SMOKE INDICATION.  ENGINEER ON BOARD CHECKED THE C	OMPARTMENT.  NO FAULT INDICATION, FIRE BOTTLES DISCHARGED AS PER PROCEDURES.  SUBSEQUENT INVESTIGATION REVEALED SMOKE DE	TECTOR INOPERATIVE.  SERVICEABLE SMOKE DETECTOR INSTALLED.				2	L	7	2 	4F			RT	A35EU   	E24NE				 
1998031900910	19980319	00910	EU  	1998	3	19	CA971110010      	1	19971103	G	2611	CG7PO	SMOKE DETECTOR  			AIRBUS	310   	A310324     	3930206	EU  										AFT CARGO	INOPERATIVE     	W				H				DEACTIVATE SYST/CIRCUITS				J	N		WARNING INDICATION        	FALSE WARNING             		IN	INSP/MAINT     	1			CA						3634					(CAN) AFTER WALK-AROUND AND DURING COCKPIT CHECK AND CARGO DOOR OPEN, ECAM MESSAGE INDICATED SMOKE WARNING.  TROUBLESHOO	TING REVEALED AFT CARGO DETECTOR AT FAULT.  SMOKE DETECTOR DEACTIVATED TO PREVENT FURTHER FALSE WARNINGS. AIRCRAFT DISPA	TCHED UNDER MEL 26-10.				2	L	7	2 	4F			RT	A35EU   					 
1998041700448	19980417	00448	CE  	1998	4	17	CA971110016      	1	19971006	G	2820	5426002013	TUBE            			LEAR  	60    	60LEAR      	5170707	CE  										FUEL SYS	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			292  								(CAN) ELEVATOR AND RUDDER CABLES FOULING ON CROSSOVER TUBE AND TUBE PUNCTURED.  SB A60-28-3 AND AD 95-14-09.  PART TC: 1	85.					2	L	7	2 	4F			RT	A10CE   					 
1998043000072	19980430	00072		1998	4	30	CA971110020      	4	19970919	G	2562	4520130	BATTERY PACK    	ARTEX       	ELT1104     															ELT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						55805					(CAN) DURING ANNUAL TEST ON ELT, IT WAS NOTED THAT WATER HAD INFILTRATED THE BATTERY PACK AND THE BATTERY WAS CORRODED.																			 
1998043000073	19980430	00073		1998	4	30	CA971110021      	4	19970919	G	2562	4520130	BATTERY PACK    	ARTEX       	ELT1104     															ELT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						55871					(CAN) DURING ANNUAL TEST ON ELT, IT WAS NOTED THAT WATER HAD INFILTRATED THE BATTERY PACK AND THE BATTERY WAS CORRODED.																			 
1998043000074	19980430	00074	GL  	1998	4	30	CA971112001      	3	19971030	G	6111		BLADE           													MCAULY	1A101	1A101HCM    	GL  	PROP LE & FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2956 					G7659		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE FOUND ON THE PROPELLER BLADE LEADING EDGE AND FACE.																5	N	P918	 
1998043000075	19980430	00075	GL  	1998	4	30	CA971112002      	3	19971103	G	6111	FJC8459B8R	BLADE           													HARTZL	HCC2Y	BHCC2YF2    	GL  	DEICE BOOT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2367 	330  					AN338		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CORROSION FOUND UNDER DEICER BOOT.																5	C	P920	 
1998031900912	19980319	00912	GL  	1998	3	19	CA971112003      	3	19971030	G	6111	G9DHB16E	BLADE           			MOONEY	M20   	M20J        	5870219	SW  						MCAULY	2D34C	B2D34C214   	GL  	LE & FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1307 	631  					822166		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE FOUND ON THE LEADING EDGES AND THE FACE OF THE BLADES. 	 THE BLADES WERE REPAIRED AND ANODIZED.					1	L	7	1 	3O				2A3     		5	C	P7EA	 
1998031900914	19980319	00914	NE  	1998	3	19	CA971112005      	2	19971024	G	7322		FCU B-NUT       								PWA   	PWA120	PW125B      		NE  					P3 LINE	LOOSE           	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			11733	6745 				124229			(CAN) TAKEOFF WAS ABORTED WHEN NR 2 ENGINE TORQUE FAILED TO MEET TARGET.  TROUBLESHOOTING REVEALED A LOOSE "B" NUT ON TH	E P3 LINE TO THE MAIN FUEL CONTROL UNIT.  PART TC:  13,987.										4	T			E20NE				 
1998031900915	19980319	00915	NE  	1998	3	19	CA971112006      	2	19971010	G	7322		HMU             								PWA   	305   	PW305       		NE  					NR  ENGINE	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	X		WARNING INDICATION        	ENGINE FLAMEOUT           		CR	CRUISE         	1			CA			740  					35224			(CAN) DURING LEVEL FLIGHT AT FL 140, THE NR 1 ENGINE LOW FUEL PRESSURE WARNING LIGHT ILLUMINATED FOLLOWED BY AN AUDIBLE 	ENGINE SHUTDOWN. THE AIRCRAFT DIVERTED AND AN UNEVENTFUL LANDING WAS CARRIED OUT.  POST-FLIGHT INVESTIGATION FOUND A PRO	BLEM WITH THE HYDRO MECHANICAL FUEL CONTROL UNIT.  THE UNIT WAS REPLACED AND CHECKED SERVICEBLE.  THE AIRCRAFT WAS RETUR	NED TO SERVICE.								4	F			E35NE				 
1998031900916	19980319	00916	EA  	1998	3	19	CA971112007      	2	19971014	G	7313		TRANSFER TUBE   								PWA   	PT6   	PT6A65B     	52043	EA  					FUEL NOZZLE	MIS-POSITIONED  	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			22517	626  				3224			(CAN) THE PILOT ABORTED THE TAKEOFF WHEN THE TORQUE ON NR 2 ENGINE FELL BELOW 1,100 FEET/POUNDS.  POST-FLIGHT INSPECTION	 REVEALED A FUEL NOZZLE TRANSFER TUBE TO BE MIS-POSITIONED IN ITS LOCK PLATE AND LEAKING FUEL. THE FUEL NOZZLES HAD BEEN	 REPLACED THE DAY BEFORE.									4	T			E4EA				 
1998041700661	19980417	00661	SO  	1998	4	17	CA971112009      	1	19971104	G	3220	4531603	HOUSING ASSY    		5521402     	PIPER 	PA31  	PA31350     	7103110	SO  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10594								(CAN) IMPROPER TOWING AND TAXIING HAS CONTRIBUTED TO THE FAILURE OF THE NOSE LANDING ASSY HOUSING.  TURNING RIGHT, HOUSI	NG IS WEAKER IN DESIGN AND AFTER CRACKING COLLAR SLIPS UNDER STOPS, FORCES IT OUT, THEN THE STEERING MECHANISM ACTS AS A	 LIMITER.  IN THIS CASE, BOLTS 401268 (AN3H-10A) AND 400743 (AN25-38) HAVEBEEN FOUND BENT.  ONE BOLT AN3H-10A NEARLY SHE	ARED AND TWO AN3-7A BOLTS RETAINING STEER ARM TO CYLINDER SHOWED SIGNS OF STRAIN.			1	L	7	2 	3O				A20SO   					 
1998031900569	19980319	00569		1998	3	19	CA971113022      	1	19971017	G	3710	6198	ADAPTER         																	VACUUM PUMP	FUSED           	W				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA			48   								(CAN) SHORTLY AFTER TAKEOFF, SMELL OF OIL, IND OF NO VACUUM PRESS.  PILOT RETURNED TO DEPART POINT.  INSP FOUND OIL LEAK	ING DOWN SIDE OF A/C AND INVEST FOUND FAULT TO BE VACUUM PUMP ADAPTER.  NON-FERROUS METAL FOUND IN OIL SCREEN.  VACUUM P	UMP DRIVE ADAPTOR WOULD NOT SEPARATE FROM ACCESSORY CASE DESPITE LOOSE ON MOUNTING STUDS.  ADAPTER DRIVE APPEARED NOT CE	NTERED, EVIDENCE OF EXCESSIVE HEAT BUILDUP IN ADAPTER HOUSING.  REAR CASE REMVD, REVEALED PUMP DRIVE SHAFT HAD OVERHEATE	D, MELTED ALUMINUM CASING IN WHICH IT ROTATES CAUSING IT TO MUSHROOM AND PREVENT REMOVAL OF VACUUM PUMP DRIVE SHAFT.  EN	GINEER RETURNED TO MFG, WHO SUGGESTED FAULT CAUSED BY VACUUM PUMP BEING INST TOO LOOSE.  HEAT BUILDUP WAS ALSO A FACTOR.														 
1998031900568	19980319	00568	NM  	1998	3	19	CA971113030      	1	19971023	G	5320		DOOR FRAME      			BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					BS 1110	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			43982					P65362B			(CAN) AFT CARGO DOOR FRAME AT BS 1110 STRINGER 26 RIGHT TO 27 RIGHT WAS FOUND CORRODED.  REPAIRED.  AIRCRAFT TT:  43,882	 HOURS.					2	L	7	3 	4F	4	F		A3WE    	E2EA				 
1998031900559	19980319	00559	EA  	1998	3	19	CA971113075      	2	19971028	G	7250	T12411	BLADE           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  					BLADE ROOT	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11869	3979 				PCE41175			(CAN) TEAR DOWN REPORT INDICATES A SINGULAR CT BLADE FAILURE DUE TO FATIGUE WAS THE SOURCE OF THE DAMAGE TO THE ENGINE. 	THE CT BLADE WAS A PMA PART.  PART TC:  4,759.					1	L	7	2 	3T	4	T		A14CE   	E4EA				 
1997121100365	19971211	00365	EA  	1997	12	11	CA971117001      	1	19970930	G	5413	75421131104	LONGERON        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					STA.XN50-XN79	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28775								(CAN) HEAVY CORROSION FOUND ON UPPER AND LOWER SURFACES OF THE UPPER LONGERONS. SEVERE CORROSION FOUND ON LONGERONS FROM	 STA.XN50 TO XN79.0. THIS CORROSION WAS NOT EVIDENT UNTIL THE COWL SEALS AND LATCH PLATES WERE REMOVED. FURTHER SEVERE C	ORROSION WAS FOUND UNDER TITANIUM DOUBLERS FROM XN79 TO XN96. UPON REMOVAL OF THE NACELLE UPPER LONGERON IT WAS NOTED TH	AT NORMAL PROCEDURES REQUIRED BY EQUALIZED INSPECTION CARD R61 WOULD NOT DETECT THIS CORROSION.			2	H	7	4 	4T	4	T		A20EA   	E4EA				 
1997121100366	19971211	00366	EA  	1997	12	11	CA971117002      	1	19970930	G	5413	75421128101	LONGERON        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					STA.XN50-XN79	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28775								(CAN) HEAVY CORROSION FOUND ON UPPER AND LOWER SURFACES OF THE UPPER LONGERONS. SEVERE CORROSION FOUND ON LONGERONS FROM	 STA. XN50 TO XN79.0. THIS CORROSION WAS NOT EVIDENT UNTIL THE COWL SEALS AND LATCH PLATES WERE REMOVED. FURTHER SEVERE 	COROSION WAS FOUND UNDER TITANIUM DOUBLERS FROM XN79 TO XN96. UPON REMOVAL OF THE NACELLE UPPER LONGERON IT WAS NOTED TH	AT NORMAL PROCEDURES REQUIRED BY EQUALIZED INSPECTION CARD R61 WOULD NOT DETECT THIS CORROSION.			2	H	7	4 	4T	4	T		A20EA   	E4EA				 
1997121100367	19971211	00367	EA  	1997	12	11	CA971117003      	1	19970930	G	5413	75421128102	LONGERON        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					STA.XN50-XN79	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28775								(CAN) HEAVY CORROSION FOUND ON UPPER AND LOWER SURFACES OF THE UPPER LONGERONS. SEVERE CORROSION FOUND ON LONGERONS FROM	 STA. XN50 TO XN79.0. THIS CORROSION WAS NOT EVIDENT UNTIL THE COWL SEALS AND LATCH PLATES WERE REMOVED. FURTHER SEVERE 	CORROSION WAS FOUND UNDER TITANIUM DOUBLERS FROM XN79 TO XN96. UPON REMOVAL OF THE NACELLE UPPER LONGERON IT WAS NOTED T	HAT NORMAL PROCEDURES REQUIRED BY EQUALIZED INSPECTION CARD R61 WOULD NOT DETECT THIS CORROSION.			2	H	7	4 	4T	4	T		A20EA   	E4EA				 
1998041700660	19980417	00660	CE  	1998	4	17	CA971117004      	1	19971106	G	3340	32448	CONNECTORS      			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					LT LANDING LIGHT	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE21451			(CAN) IN COMPLYING WITH AIRCRAFT SERVICES MEMO EWS 97-04, FOUND ONE OVERHEATED KNIFE CONNECTOR.  AFFECTED AREA REPLACED 	WITH RELEASABLE WIRE SPLICE.					1	L	7	2 	3T	3	T		3A20    	E4EA				 
1998041700659	19980417	00659	CE  	1998	4	17	CA971117010      	1	19971110	G	2750	C3010010211	COUPLING        			CESSNA	150   	152         	2071835	CE  										FLAP	DAMAGE          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			CA			11523								(CAN) DURING CHECK, FOUND THAT ALTHOUGH FLAP MOTOR WAS TURNING NORMALLY, FLAPS DID NOT APPEAR TO BE RESPONDING QUICKLY. 	 INVESTIGATION REVEALED DEFECTIVE SPLINE COUPLING ON FLAP MOTOR SHAFT.					1	H	7	1 	3O			NT	3A19    					 
1998050100078	19980501	00078	CE  	1998	5	1	CA971117011      	1	19971106	G	2435	62581038	CAPACITOR ASSY  			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					L/H GENERATOR	BURNED          	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA			2245 					71721			(CAN) THE LT GENERATOR WAS RESET TWICE TO BRING IT BACK ON LINE AND THE AIRCRAFT DEPARTED.  MAINTENANCE PERSONNEL RAN TH	E ENGINE TO CHECK FOR GENERATOR PROBLEMS, BUT EVERYTHING WAS NORMAL.  AFTER REMOVING THE LT LOWER ENGINE COWLING TO DO A	 VISUAL, IT WAS NOTICED THAT THE CAPACITOR ASSY WAS BADLY BURNED INCLUDING SOME WIRING IN THE SAME VICINITY.  ONE LEAD W	AS FOUND BURNED THROUGH AND BROKEN WHICH OPENED THE CIRCUIT.  THIS IS THE SECOND OCCURRENCE ON THIS FLEET.			1	L	7	2 	4F	4	F		A22CE   	E1NE				 
1998031900553	19980319	00553	CE  	1998	3	19	CA971118002      	1	19970920	G	5510	AN447	BOLT            		16962000037 	BEECH 	23    	A23         	1151204	CE  										STAB TUBE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REMOVAL OF STABILATOR ACTUATING TUBE BALANCE WEIGHT, DAMAGE TO THE ATTACHMENT BOLT WAS FOUND.  THE DAMAGE SEC	TIONS OF THE BOLT CORRESPONDED WITH THE DIAMETER OF THE STABILATOR ACTUATING TUBE. THE DAMAGE APPEARS TO HAVE BEEN CAUSE	D BY REPETITIVE IMPACT OF THE BALANCE WEIGHT STRIKING THE MICARTA STOP BLOCK (WHICH LIMITS CONTROL SURFACE MOVEMENT).  A	IRCRAFT TT:  2,033 HOURS.			1	L	7	1 	3O				A1CE    					 
1998031900549	19980319	00549	GL  	1998	3	19	CA971118007      	3	19971113	G	6111		BLADE           													MCAULY	1C160	1C160CTM    	GL  	LE & FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2681 	682  					722304		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE LEADING EDGE AND FACE OF THE BLADE.																5	N	P910	 
1998031900547	19980319	00547	CE  	1998	3	19	CA971118009      	1	19971024	G	2612		FIRE LOOP       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RT FIRE WARN	LOOSE           	W				K				NONE                    				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) DURING LANDING APPROACH, RT FIRE WARNING LIGHT CAME ON INTERMITTENTLY.  ON ROLL-OUT, LIGHT CONTINUED TO FLICKER IN	 RELATION TO TAXIING VIBRATIONS.  MAINTENANCE INVESTIGATION REVEALED A CLAMP RETAINING THE LOOP HAD COME LOOSE, ALLOWING	 THE LOOP TO CONTACT EXHAUST CASE.  FAULT RECORDED AND AIRCRAFT RELEASED.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1998031900546	19980319	00546	EA  	1998	3	19	CA971118010      	2	19971027	G	7200		ENGINE          								PWA   	PT6   	PT6A65B     	52043	EA  					NR 2 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				A	E	J	FLAME/FIRE                	VIBRATION/BUFFET          	WARNING INDICATION        	AP	APPROACH       	1			CA								324			(CAN) ON APPROACH WHEN POWER WAS BEING REDUCED, A LOUD BANG WAS HEARD AND A FLASH OF LIGHT WAS SEEN FROM THE NR 2 ENGINE	.  ALL ENGINE INDICATIONS WERE READING "0".  ENGINE WAS SECURED AND THE AIRCRAFT LANDED. PO-FLIGHT INSPECTION FOUND THE 	ACCESSORY GEARBOX AND THE REDUCTION GEARBOX SEIZED.  DEBRIS OF UNKNOWN ORIGIN WAS FOUND IN THE POWER TURBINE AND THE EXH	AUST AREA.								4	T			E4EA				 
1998031900540	19980319	00540	SO  	1998	3	19	CA971125002      	2	19971007	G	7322	MA45	CARBURETOR      	MARVELSCHEB 		CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  					FLOAT	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			CA			404  			CL0634		46219			(CAN) DURING INSPECTION FUEL WAS FOUND LEAKING FROM THE THROAT OF THE CARBURETOR.  INVESTIGATION FOUND THE FLOAT ASSEMBL	Y BROKEN OFF.  NO INDICATION OF A PROBLEM FROM THE AIRCRAFT OWNER REGARDING ENGINE OPERATION.					1	H	7	1 	3O	3	O		5A6     	E273				 
1998100900149	19981009	00149		1998	10	9	CA971128005      	4	19971104	G	2210		CONTROL CABLE   	ARC         	300A        	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	AFCS	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								235869R	775070		(CAN) AUTOPILOT NOT FUNCTIONING PROPERLY.  AILERON SERVO CABLES INSTALLED IN REVERSE, REPAIRED.						1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
1998031900526	19980319	00526	EU  	1998	3	19	CA971208005      	2	19971125	G	8520		CRANKSHAFT      								ROTAX 	912   	ROTAX912    	55555	EU  					PTO END	BENT            	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			4    					441266			(CAN) VIBRATION NOTICED DURING PRODUCTION TEST FLIGHT.  GEARBOX REMOVED TO INVESTIGATE.  RUN OUT OF CRANKSHAFT AT P.T.O.	 (POWER TAKEOFF END) CHECKED IN ACCORDANCE WITH ROTAX F3 MAINTENANCE MANUAL, MEASURED AT.003.  REQUIREMENTS NEW ARE 0.00	 + 0.03 (MM)/0.00 + 0.0012 (IN), WEAR LIMIT 0.06 (MM)/0.002 (IN).									3	I			EXPE3I				 
1998111300585	19981113	00585	EU  	1998	11	13	CA971208006      	1	19971010	G	2550	877	PIN             	SIREN       	S16096      	SNIAS 	350   	AS350B2     	8680813	EU  										CARGO HOOK	MISSING         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			294  			877					(CAN) AFTER I5 HOURS INTO A GEOSURVEY FLIGHT WITH A POD ON THE CARGO HOOK, THE CARGO HOOK SUDDENLY RELEASED ON ITS OWN, 	LOSING AN EXPENSIVE PIECE OF EQUIPMENT.  DISASSEMBLY OF THE CARGO HOOK REVEALED THAT THE MECHANICAL RELEASE PIN WAS MISS	ING PREVENTING THE RELEASE LEVER FROM RETURNING TO ITS FULLY LOCKED POSITION.				1	G	7	1 	3U				H9EU    					 
1998031900520	19980319	00520	NM  	1998	3	19	CA971208014      	1	19971127	G	3242	2661942	PISTON HOUSING  	BFGOODRICH  	214662      	DHAV  	DHC8  	DHC8102     	2809003	NM  										BRAKE ASSY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21443			0926					(CAN) DURING INSPECTION OF THE BRAKE ASSEMBLY, CRACKS APPROXIMATELY .25 INCH LONG WERE FOUND IN TWO OF THE CYLINDERS OF 	THE PISTON HOUSING.   PART TC:  23,433.					2	H	7	2 	4T			RT	A13NM   					 
1998031900514	19980319	00514	EA  	1998	3	19	CA971210008      	1	19971127	G	3244	256K433	TIRE            		6008512515  	CNDAIR	CL600 	CL6002B16   	1900305	EA  										NR MAIN	SEPARATED       	W				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			310  			JUN81145					(CAN) AFTER TAKEOFF, THE WOW INPUT FAIL LIGHT ILLUMINATED.  GEAR RETRACTED AND TRIP UNEVENTFUL.  FOUND RUBBER ON NR 3 MA	IN TIRE MISSING.  IN SPOTS, IT WAS DOWN 3-PLY, AROUND THE COMPLETE CIRCUMFERENCE OF TIRE.  THE SECTION MISSING WAS FROM 	THE OUTER RIB TO THE EDGE OF THE TIRE. THE TIRE HELD ITS PRESSURE.  SUSPECT FLYING RUBBER DAMAGED THE RIGHT HAND INBOARD	 WOW PROXIMITY SWITCH.  NO OTHER DAMAGE FOUND.  PART TC: 166.			2	L	7	2 	4F			RT	A21EA   					 
1998031900508	19980319	00508	NE  	1998	3	19	CA971212003      	2	19971113	G	7210	3192441	BEARING         								PWA   	120   	PW120       		NE  					RED GRBOX NR 15	SPALLED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			17368	3234 				12661			(CAN) REDUCTION GEARBOX (RGB) WAS SENT FOR INSPECTION AND REPAIR AFTER THE OPERATOR REPORTED THE RGB WAS MAKING M50 META	L.  INVESTIGATION FOUND THE RGB WAS MAKING METAL DUE TO FRACTURING AND SPALLING OF THE INNER RACE OF THE NR 15 BEARING. 	 THE FAILURE APPEARS TO HAVE INITIATED WITH THE FRACTURE THROUGH THE INNER RACE OF THE NR 15 BEARING.  THERE IS NO EVIDE	NCE OF WHY THE INNER RACE FRACTURED, HOWEVER, IT APPEARS LIKELY THAT THIS WAS THE PRIMARY FAILURE OF THE NR 15 BEARING. 	 PART TC:  17,197.							4	T			E20NE				 
1998041700477	19980417	00477	GL  	1998	4	17	CA971216046      	3	19971126	G	6114	H6446	HUB             													MCAULY	2A36C	2A36C23     	GL  	BLADE SOCKET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									768152		(CAN) PROPELLER SENT FOR FIVE-YEAR INSPECTION.  NO REQUIREMENT FOR NDT.  COMPANY POLICY OF CARRYING OUT EDDY CURRENT INS	PECTION LED TO FINDING OF CRACKS IN THE THREADS OF THE HUB BLADE SOCKETS.															5	C	P880	 
1998041700657	19980417	00657	SO  	1998	4	17	CA971216073      	1	19971126	G	5270		PIN             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					BS 111.5	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7393 					L163261			(CAN) PASSENGER DOOR AJAR WARNING LIGHT INOPERATIVE.  MUCH TROUBLE TO FIND THAT A PIN IN A BLOCK CONNECTOR UNDER AND BEH	IND THE CIRCUIT BREAKER AND SWITCH PANEL HAD BROKEN.  THIS PIN CONNECTS WIRES L54EE TO L57ED AND RUNS UNDER SOME UPHOLST	ERY TO REAR OF AIRCRAFT.				1	L	7	2 	3O	3	O		A20SO   	E14EA				 
1998041000445	19980410	00445	NE  	1998	4	10	CA971216075      	2	19971113	G	7210	310703301	BEARING         								PWA   	120   	PW120       		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18257	6880 				120660			(CAN) REDUCTION GEARBOX (RGB) SENT FOR INSPECTION AND REPAIR AFTER THE RGB WAS FOUND MAKING METAL.  DISASSEMBLY OF THE R	GB REVEALED THE SOURCE OF THE METAL WAS THE SPALLING OF THE NR 15 BEARING.  THE SPALLING OF THE NR 15 BEARING APPEARED T	O BE DUE TO ELECTRICAL ARCING DAMAGE. HOWEVER, THE LACK OF HIGH MAGNETISM IN THE RGB WAS NOT CHARACTERISTIC OF A LIGHTNI	NG STRIKE.  SINCE THERE WERE NO BEARING BORE ALIGNMENT OR LUBRICATION PROBLEMS FOUND, IT APPEARED THAT THE NR 15 BEARING	 SPALLED DUE TO ELECTRICAL PITTING CAUSED BY STRAY ELECTRICAL DISCHARGE FROM SOME AIRCRAFT COMPONENT.  PART TC:  17,903.							4	T			E20NE				 
1998041700656	19980417	00656		1998	4	17	CA971219001      	1	19971117	G	7920		LINE            		FP3000E33E38						ROTAX 	912   	ROTAX912    	55555	EU  					OIL SYS	LOOSE ENDS      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			832  					4412584			(CAN) ON 100-HOUR INSPECTION, FOUND BRASS CRIMP RINGS ON THE HOSE END WERE LOOSE.   ONE SLEEVE HAD COME COMPLETELY OFF. 	 WITH SLEEVES LOOSE THERE IS NOTHING TO HOLD THE HOSE ONTO THE FITTING.										3	I			EXPE3I				 
1998041700655	19980417	00655	SO  	1998	4	17	CA971219012      	1	19971127	G	5521	4374301	RIB ASSEMBLY    		5423235     	PIPER 	PA31  	PA31350     	7103110	SO  										RT ELEV	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12634								(CAN) WHEN REPLACING MAIN SPAR IN RIGHT HAND ELEVATOR PER SB 998A, THE END RIB ASSY WAS FOUND CRACKED WHERE THE SPAR ATT	ACHES TO THE RIB.  CRACK ABOUT .50 INCH LONG.  AIRCRAFT TT:  12,445 HOURS.					1	L	7	2 	3O				A20SO   					 
1998041700654	19980417	00654	CE  	1998	4	17	CA971219015      	1	19971124	G	5312	9774400191	BULKHEAD        			BEECH 	100   	100BEECH    	1152916	CE  										AFT PRESS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10608								(CAN)  WHEN GLUED ON INSULATION WAS REMOVED AT REAR SIDE OF AFT PRESSURE BULKHEAD BELOW OUTFLOW VALVES, CORROSION WAS FO	UND.  SUSPECT MOISTURE TRAPPED BENEATH INSULATION.  AIRCRAFT TT:  10,593 HOURS.					1	L	7	2 	3T				A14CE   					 
1998041700653	19980417	00653	EU  	1998	4	17	CA971219020      	2	19971118	G	7314	996592	FUEL PUMP       								ROTAX 	912   	ROTAX912    	55555	EU  					OUTLET FITTING	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			50   					4412619			(CAN) FUEL PUMP LEAKS FUEL FROM HIGH PRESSURE PORT WHICH SPRAYS INTO ENGINE COMPARTMENT.											3	I			EXPE3I				 
1998041700652	19980417	00652	CE  	1998	4	17	CA971219023      	1	19971114	G	3340	3538013243	SWITCH          			BEECH 	33    	F33A        	1151425	CE  										LANDING LIGHT	BROKEN          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA			3482 								(CAN) SLIGHT ELECTRICAL BURNING SMELL NOTED IN COCKPIT BY PILOTS.  LANDING LIGHT CIRCUIT BREAKER SWITCH FOUND FUSED IN T	HE ON POSITION AND VERY WARM TO TOUCH.  TOGGLE COULD BE MOVED WITH NO RESISTANCE.  AIRCRAFT USED IN TRAINING AND HIGH US	AGE MAY BE CAUSE OF DIFFICULTY.				1	L	7	1 	3O				3A15    					 
1998041700651	19980417	00651	SO  	1998	4	17	CA971219026      	1	19971124	G	2910	159H10002428S20	LINE            			GULSTM	G159  	G159        	3952202	SO  										LEFT ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			10   								(CAN) HYDRAULIC FLUID NOTED BELOW LEFT ENGINE AFTER ARRIVAL.  CRACK FOUND IN THE MAIN SUCTION LINE TO THE HYDRAULIC PUMP	.  FURTHER INSP FOUND THAT THE LEFT INBOARD GEARBOX MOUNT LINK ASSY WORN CAUSING A VIBRATION AND MOVEMENT RESULTING IN F	ATIGUE CRACK IN LINE.				2	L	7	2 	4T				1A17    					 
1998041000427	19980410	00427	SO  	1998	4	10	CA971219030      	2	19971117	G	8530	653446D	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					NR 2 CYL	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			10   					22128872D			(CAN) ENGINE PROBLEMS IN-FLIGHT.  THE AIRCRAFT DIVERTED.  POST-FLIGHT INSPECITON FOUND THE NR 2 CYLINDER HAD FAILED AND 	CAUSED DAMAGE TO 1 AND 2 CYLINDERS, CASING AND CRANKSHAFT.  ENGINE REPAIRED AND AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3O	3	O		3A24    	E5CE				 
1998050100066	19980501	00066	CE  	1998	5	1	CA971219037      	1	19971130	G	3246	13600LA90069	BEARING         	LORAL       	50060284    	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RT MLG	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								PCE32185			(CAN) TOWER REPORTED TO PILOT THAT SPARKS WERE SEEN COMING FROM RIGHT HAND MAIN GEAR.  RIGHT OUTBOARD MAIN WHEEL INNER B	EARING WAS DESTROYED ALLOWING WHEEL TO WOBBLE ON AXLE CAUSING DAMAGE TO WHEEL ASSY AND BRAKE ASSY.  IT HAD BEEN 60 HOURS	 SINCE LAST SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
1998041000419	19980410	00419	NE  	1998	4	10	CA971219040      	2	19971205	G	7261	3006084	OIL FILLER CAP  								PWA   	120   	PW120A      		NE  					O-RING GROOVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								120232			(CAN) CRACKED IN "O" RING GROOVE, IMPROPER FITTING OF "O" RING OR IMPROPER "O" RING FITTED TO THE CAP.  POTENTIAL LOSS O	F SEALING OF OIL TANK AND LOSS OF OIL OUT OF FILLER DURING FLIGHT.										4	T			E20NE				 
1998032600533	19980326	00533	NE  	1998	3	26	CA971219044      	2	19971117	G	7250	310920201	LP BLADE        								PWA   	120   	PW120A      		NE  					LP TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20391					120340			(CAN)  ENGINE SENT FOR INVESTIGATION AND REPAIR AFTER FAILURE OF A LP TURBINE BLADE.  DISASSEMBLY OF THE ENGINE CONFIRME	D THE FAILURE OF ONE OR MORE PRE SB 20465, HOLLOW CORE, LP TURBINE BLADES.  THESE WERE HIGH-TIME BLADES WITH VISIBLE PLA	TFORM CORROSION AND IT APPEARS THE FAILURE ORIGINATED FROM A CORROSION SITE WITHIN THE INTERNAL CORED PASSAGE.  SECONDAR	Y DAMAGE WAS SUSTAINED BY THE LP TURBINE STATOR ASSEMBLY, THE LP SHROUD SEGMENTS, PT1 AND PT2 STATORS, PT1 AND PT2 TURBI	NE BLADES.  PART TC:  28,434.							4	T			E20NE				 
1998032600534	19980326	00534	NE  	1998	3	26	CA971219045      	2	19971124	G	7210	310924401	BEARING         								PWA   	120   	PW120       		NE  					RED GRBOX NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17734	4541 				120378			(CAN)  ENGINE SENT FOR REPAIR AFTER REDUCTION GEARBOX WAS FOUND MAKING M50 METAL.  DISASSEMBLY OF ENGINE REVEALED SOURCE	 OF THE M50 METAL CONTAMINATION A SPALLED NR 15 BEARING.  NR 15 BEARING HAD ELECTRO-EROSION ON THE OUTER RACE AND ROLLER	S.  NR 15 BEARING BORE WAS FRETTED AND BEARING HAD SPUN ON THE PROP SHAFT.  SUBMITTER SUGGESTED CAUSE OF BEARING FAILURE	 WAS ELECTRO-EROSION WHICH APPEARED TO BE A STRAY ELECTRICAL DISCHARGE FROM SOME ACFT COMPONENT AND NOT A LIGHTNING STRI	KE.  THERE WAS SECONDARY DAMAGE ON THE BULL GEAR, LT AND RT 2ND STAGE SPUR GEARS,  OVERSPEED GOVERNOR SPUR GEAR AND REDU	CTION GEARBOX SCAVENGE PUMP HOUSING.  PART TC:  19,818.						4	T			E20NE				 
1998032600535	19980326	00535	NE  	1998	3	26	CA971219046      	2	19971128	G	7230	311161801	BEARING         								PWA   	118   	PW118       		NE  					INTER COMP CASE	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			CA			20205	11584		BB9310666		15260			(CAN)  TURBOMACHINE SENT FOR INVEST AFTER ENGINE EXPERIENCED A DROP IN "ALL PARAMETERS" AND SHUT ITSELF DOWN.  A FIREBAL	L WAS SEEN COMING FROM REAR OF  ENGINE AND UPON LDG, OIL WAS NOTICED BLOWN OUT OF INTAKE.  DISASSY OF ENGINE FOUND COMPO	NENTS RETAINED BY NR 4 BEARING RETAINING NUT WERE SEVERELY FRETTED AND NR 4 BEARING RETAINING NUT WAS NO LONGER TIGHT. S	UBMITTER SUGGESTED NR 4 BEARING FAILED DUE TO  BACKING OFF OF NR 4 BEARING RETAINING NUT.  HOWEVER, LOSS OF A NR 3 AND  	NR 4 BEARING AREA MULTIPLE JET OIL NOZZLE PLUG SUGGESTED FAILURE MAY HAVE BEEN DUE TO OIL STARVATION.  LOSS OF NR 3 AND 	NR 4 BEARING AREA MULTIPLE JET OIL NOZZLES FLOODED ENG WITH OIL CAUSING A FIREBALL IN  HOT SECTION.  PART TC:  20,653.						4	T			E20NE				 
1998032600536	19980326	00536	NE  	1998	3	26	CA971219047      	2	19971128	G	7210	310703301	BEARING         								PWA   	120   	PW120A      		NE  					RGB NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24835	2884 		64B454		120167			(CAN REDUCTION GEARBOX SENT FOR INSP AND REPAIR AFTER OPERATOR NOTED A LARGE NUMBER OF SHINY METAL FLAKES IN RGB SCAVENG	E FILTER AND ON RGB CHIP DETECTOR.  DISASSEMBLY OF ENG REVEALED SOURCE OF METAL CONTAM WAS SPALLING OF NR 15 BEARING.  N	R 15 BEARING ROLLERS AND UNDAMAGED PORTION OF OUTER RACE HAD CHAINS OF ELECTRICAL DISCHARGE PITTING WHICH APPEAR TO BE C	AUSE OF THE SPALLED BEARING.  SECONDARY DAMAGE FROM THE SPALLED BEARING LIMITED TO NR 13 LT BEARING.  THERE IS SOME DETE	CTABLE MAGNETISM ON A RANDOM SCATTERING OF STEEL COMPONENTS.  THIS PATTERN IS NOT TYPICAL OF A LIGHTNING STRIKE, SO A LI	GHTNING STRIKE IS NOT THOUGHT TO BE A CAUSE OF NR 15 BEARING FAILURE.  PART TC:  34,042.						4	T			E20NE				 
1998041700650	19980417	00650	WP  	1998	4	17	CA971222002      	2	19970907	G	7314	8973809	FUEL PUMP       			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P77559			(CAN) ENGINE WOULD NOT LIGHT UP DURING START UNTIL 18 PERCENT-20 PERCENT.  A NORMAL START LIGHT OFF IS 12 PERCENT-14 PER	CENT.  FOUND FUEL PUMP OUTPUT PRESSURE AT LOW RPM BELOW SPECS.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
1998041700649	19980417	00649	CE  	1998	4	17	CA971222003      	1	19971007	G	7700	99103261	TRANSDUCER      			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	FAILED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA								P77093			(CAN) TRANSDUCER GAVE INCORRECT SIGNAL TO ENGINE COMPUTER-CAUSING SRL TO BE INCORRECT. THE ERROR WAS GREATER AS THE AIRC	RAFT CLIMBED.  THUS; TORQUE, FUEL FLOW, AND EGT DID NOT MATCH THE OTHER ENGINE AS THE AIRCRAFT CLIMBED.  THIS IS THE  P/	P TRANSDUCER.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
1998032600538	19980326	00538	NE  	1998	3	26	CA971222005      	2	19971212	G	7261	3006084	OIL FILLER CAP  								PWA   	118   	PW118       		NE  					"O"RING GROOVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								115394			(CAN) OIL FILLER CAP SEAL FLANGE FOUND CRACKED.  POTENTIAL FOR IN-FLIGHT LOSS OF ENGINE OIL IF FLANGE FAILS.											4	T			E20NE				 
1998032600540	19980326	00540	NM  	1998	3	26	CA971222007      	1	19971208	G	3320	BV033001248	LAMPHOLDER      			DHAV  	DHC8  	DHC8102     	2809003	NM  										ROW 2AC	BURNT           	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, PASSENGERS SMELLED AND SAW SMOKE AT ROW 2AC OVERHEAD BIN AREA.  AIRCRAFT RETURNED TO FIELD.  MAINTE	NANCE FOUND OVERHEAD LIGHT BULB ARCING AT CONNECTION.					2	H	7	2 	4T			RT	A13NM   					 
1998041700648	19980417	00648	EU  	1998	4	17	CA971222008      	1	19971212	G	3250	223602000000	BRACKET         		273009      	ISRAEL	1124  	1124        	4500102	EU  										STEERING MT EAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPPER STEERING BRACKET FOUND CRACKED.						2	M	7	2 	4F				A2SW    					 
1998032600543	19980326	00543	NE  	1998	3	26	CA971222011      	2	19971203	G	7270	712538	DIFFUSER        								PWA   	JT8   	JT8D17      	52049	NE  					OUTER SURFACE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25551					P707235B			(CAN) PRIOR TO ENGINE INSTALLATION, IT WAS NOTICED THAT STRANDS OF MATERIAL WERE HANGING IN THE BY-PASS DUCT, VISIBLE FR	OM AFT OF THE ENGINE.  REMOVAL OF THE 13TH STAGE BLEED AIR COVER ALLOWED ACCESS TO CONFIRM SEVERE DELAMINATION OF THE DI	FFUSER OUTER SURFACE.  THE ENGINE HAD JUST BEEN RECEIVED FROM THE ENGINE SHOP.  PART TC:  13,954.									4	F			E2EA				 
1998032600544	19980326	00544	NE  	1998	3	26	CA971222012      	2	19971218	G	7322		FUEL CONTROL    								PWA   	PW120 	PW123       		NE  					NR 2 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				O	J		OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			CA			1152 					109029			(CAN) THE NR 2 ENGINE WAS SHUT DOWN AT 5,000 FEET FOLLOWING ZERO TORQUE AND 300 DEGREE CELSIUS ITT INDICATION.  THE AIRC	RAFT CONTINUED TO DESTINATION AND MADE AN UNEVENTFUL SINGLE ENGINE LANDING.  POST-FLIGHT INSPECTION FOUND THE MAIN FUEL 	CONTROL UNIT (MFCU) INPUT DRIVE SHAFT BEARINGS SEVERELY DAMAGED.									4	T			E20NE				 
1998100900151	19981009	00151	SO  	1998	10	9	CA971222014      	1	19971130	G	5210	4166806	GATE            			PIPER 	PA31  	PA31350     	7103110	SO  										PASSENGER DOOR	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) UPPER PORTION OF PASSENGER DOOR DEPARTED IN-FLIGHT DURING DESCENT AT 18O KNOTS MODERATE TURBULANCE.  LOWER PORTION	 REMAINED.  DOOR WAS CLOSED AND LOCKED.  REPAIRED.					1	L	7	2 	3O				A20SO   					 
1998041700647	19980417	00647	CE  	1998	4	17	CA971223002      	1	19970711	G	7410	103784005	IGNITION BOX    			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P77093			(CAN) IGNITION BOX FAILED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
1998032600545	19980326	00545	EA  	1998	3	26	CA971223003      	1	19971210	G	2700	43100012	CIRCUIT BREAKER 			DHAV  	DHC8  	DHC8311     	1386006	EA  										26 VAC.Q1	CHAFED          	W				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			13   								(CAN) THE POWERED FLIGHT CONTROL SYSTEM (PFCS) CIRCUIT BREAKER WAS TRIPPING.  CB LOCATED ON THE LEFT 26VAC BUS, POSITION	 Q1.  APPARENT CAUSE WAS THE CIRCUIT BREAKER LOAD TERMINAL WAS SHORTING TO GROUND VIA THE MOUNTING BRACKET SUPPORTING 24	23-P1.  BRACKET WAS TRIMMED TO ACCOMMODATE. THIS WAS A FACTORY NEW AIRCRAFT.  MANUFACTURER QA WAS NOTIFIED.				2	H	7	2 	4T			RT	A13NM   					 
1998100900152	19981009	00152	CE  	1998	10	9	CA971223004      	1	19971210	G	5710	262207459	WING            			CESSNA	208   	208B        	2073701	CE  										WS 276	BIRD STRIKE     	W				O				OTHER                   				C			F.O.D.                    			AP	APPROACH       	1			CA											(CAN) ON APPROACH BIRD STRIKE, DUCK, ON LT WING LEADING EDGE STA 276L.  LARGE DENT AND RIB DAMAGE, REPAIRED.						1	H	7	1 	3T				A37CE   					 
1998100900153	19981009	00153	CE  	1998	10	9	CA971223009      	1	19971219	G	5320	17120523	STIFFENER       		1712000     	CESSNA	177   	177A        	2073706	CE  	LYC   	O360  	O360A1F     	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4500 					L1315436A			(CAN) LT AND RT LANDING GEAR UPPER ATTACHMENT CRACKED AT ATTACHMENT HOLES.  HOLE EDGE DISTANCE VERY CLOSE.						1	H	7	1 	3O	3	O		A13CE   	E286				 
1998041700645	19980417	00645	GL  	1998	4	17	CA971231008      	2	19971219	G	7320	6875630	TUBE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GOV	CRACKED         	W				E	B			ENGINE SHUTDOWN         	EMER. DESCENT           			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			5443 					CAE821934			(CAN) AIR LINE FROM COMPRESSOR SCROLL TO GOVERNOR CRACKED AT FLARE AT SCROLL END.  THIS CAUSED ENGINE TO GO TO IDLE.						1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998041700644	19980417	00644	GL  	1998	4	17	CA971231009      	2	19971219	G	7320	6875632	LINE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3407 					CAE821934			(CAN) FUEL NOTED DRIPPING FROM THE ENGINE COMPARTMENT OVERBOARD DRAIN.  FUEL LINE BETWEEN FUEL CONTROL AND GOVERNOR LEAK	ING.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998041700643	19980417	00643	SO  	1998	4	17	CA971231010      	1	19971221	G	2434	30E2041A	GENERATOR       			GULSTM	G159  	G159        	3952202	SO  										RIGHT HAND	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						378					(CAN) RIGHT HAND GENERATOR FAILED IN CRUISE.  FIELD COIL FOUND OPEN.						2	L	7	2 	4T				1A17    					 
1998100900154	19981009	00154	CE  	1998	10	9	CA971231015      	1	19971210	G	2720		CONTROL CABLE   			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					RUDDER	MISINSTALLED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA								PCE50438			(CAN) ON LANDING, THE RUDDER CABLES JAMMED.  INVESTIGATION REVEALED THAT THE CABLES WERE ROUTED UNDER THE RUDDER SERVO A	TTACH BRACKET.  THE SWAGED ENDS CAUGHT THE EDGE OF THE BRACKET AND COULD NOT BE MOVED.  CABLES REROUTED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
1998032600556	19980326	00556	GL  	1998	3	26	CA971231017      	3	19971212	G	6111		BLADE           													MCAULY	1C172	1C172EM     	GL  	PROP LE & FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1661 					E1180		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CORROSION FOUND ON ALL SURFACES ACCOMPANIED BY STONE DAMAGE.																5	N	P910	 
1998032600557	19980326	00557	GL  	1998	3	26	CA971231018      	3	19971219	G	6114	790100018	BLADE BEARINGS  			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A5    	41532	EA  	HARTZL	HC82V	HC82V*      	GL  	PROP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3189 	813  				L27440	288G		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  BLADE BALL BEARINGS AND PILOT TUBE FOUND CORRODED.						1	L	7	1 	3O	3	O		1A15    	E295	5	C	P23EA	 
1998032600561	19980326	00561	EA  	1998	3	26	CA971231022      	2	19971229	G	8520		CAMSHAFT        			PIPER 	PA22  	PA22108     	7102204	SO  	LYC   	O235  	O235C1      	41505	EA  					ENGINE	WORN            	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				855  				2792515			(CAN) ENGINE CAMSHAFT FOUND WORN.  ENGINE CAMSHAFT REPLACED.						1	H	7	1 	3O	3	O		1A6     	E223				 
1998032600562	19980326	00562	SO  	1998	3	26	CA971231023      	1	19971211	G	5751	JW3602R	CASTING         		JW10501     	LKHEED	1329  	132923D     	5263108	SO  										RT AIL CTRWT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8850 								(CAN) DURING INSPECTION, FOUND RT AILERON COUNTERWEIGHT CASTING ATTACH CRACKED THROUGH BETWEEN 2 BOLTS.  REPLACED.  PART	 TC:  5,513.					2	L	7	4 	4J				2A15    					 
1998041000407	19980410	00407	SW  	1998	4	10	CA971231024      	1	19971105	G	2810	205061632002	FUEL CELL       			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					FUEL SYS	PEELING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE07525			(CAN) WHEN RIGHT HAND FUEL SUMP DRAINED, BLACK PARTICLES WERE FOUND.  RUBBER COATING OF THE FUEL CELL HAD PEELED OFF.						1	G	7	1 	4U	4	U		H1SW    	E17EA				 
1998100900155	19981009	00155	CE  	1998	10	9	CA971231027      	1	19971218	G	5740	AN823A	BOLT            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5118 					RL560676T	79660		(CAN) DURING REMOVAL OF WINGS FOR TRANSPORT, THE LT WING FORWARD ATTACHMENT BOLT FOUND CORRODED.  REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
1998041000406	19980410	00406	GL  	1998	4	10	CA980113001      	2	19970818	G	7210	406340104101	SEAL            	ALLSN       	6894171     	BELL  	206   	206BELL     	1181502	SW  	ALLSN 	250C  	250C20      	03013	GL  					GR BOX PTO SEAL	BROKEN          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA						CAG30218		CAE821314			(CAN) PILOT REPORTED ERRATIC TORQUE INDICATIONS. GEARBOX REMOVED. PTO SEAL LIP FOUND TORN, AND PIECES OF BROKEN SEAL WER	E BLOCKING TORQUE METER BLEED HOLE.  THIS IS THIRD INCIDENT NOTED BY THIS O/H SHOP.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1998041700642	19980417	00642	SO  	1998	4	17	CA980113003      	2	19971230	G	7322	30764	FLOAT           	MARVELSCHEB 	MA45        	CESSNA	180   	180G        	2072616	CE  	CONT  	O470  	O470R       	17026	SO  					CARB	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								1326706R			(CAN) FUEL DRIPPING HEAVILY FROM CARBURETOR AFTER ENGINE SHUTDOWN.  CARBURETOR REMOVED AND DISASSEMBLED.  CARBURETOR FLO	AT PONTOON SEPARATED FROM STRUCTURE, IT APPEARS BOTH SUPPORT TANGS RADII ARE TOO SMALL WHICH LEADS TO FAILURE FIRST, LOA	DING THE SOLDER JOINT TO FAILURE.				1	H	7	1 	3O	3	O		5A6     	E273				 
1998041700641	19980417	00641		1998	4	17	CA980113004      	4	19971215	G	3452	3420221	RESISTOR        		RT395A      	CESSNA	172   	172N        	2072434	CE  										TRANSPONDER	BURNT           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						14956					(CAN) SMOKE IN COCKPIT. TRANSPONDER FOUND TO HAVE BURNT DIMMING RESISTOR.  REPAIRED AND CERTIFIED.						1	H	7	1 	3O			NT	3A12    					 
1998041700640	19980417	00640	CE  	1998	4	17	CA980113007      	1	19971224	G	5740	8178414	WING BOLT       			BEECH 	100   	B100        	1152919	CE  										SHANK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24   								(CAN) WHILE PERFORMING AD CF-81-25R5, A CRACK WAS DETECTED.  THE RIGHT HAND LOWER FORWARD BOLT WAS FOUND CRACKED AT THE 	SHANK.					1	L	7	2 	4T				A14CE   					 
1998050801410	19980508	01410	EA  	1998	5	8	CA980113014      	2	19971222	G	7261	1781503	OIL LINE        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					RT NACELLE	CUT             	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			6730 					L372748			(CAN) AT SHUTDOWN, OIL LEAK NOTED OUT UNDER RT NACELLE ONTO LANDING GEAR DOORS.  OIL PRESSURE LINE CUT UNDER CLAMP AT FI	REWALL, TWO PLACES, WIDTH OF CLAMP.  IMPROPER SIZE CLAMP.  REPLACED CLAMP.					1	L	7	2 	3O	3	O		1A10    	1E4				 
1998050801411	19980508	01411	SO  	1998	5	8	CA980113015      	1	19971222	G	2710	1430004	CONTROL CABLE   			PIPER 	PA23  	PA23250     	7102308	SO  										AIL BALANCE	CHAFED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			6731 								(CAN) AILERON BALANCE CABLE CHAFING ON FLOOR SKIN AND HYD LINE.  CABLE REPLACED, HYL LINE RECLAMPED AND FLOOR SKIN MOVED	.					1	L	7	2 	3O			 	1A10    					 
1998060500095	19980605	00095	CE  	1998	6	5	CA980113018      	1	19971222	G	3230	131378252CL	CHAIN KEEPER    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NLG	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE81062			(CAN) NOSE GEAR AFT CHAIN MASTER LINK MISSING AND ADJACENT LINK BENT, ONLY HELD ON BY ONE HOLE.  REPAIRED/REPLACED.						1	L	7	2 	4T	4	T		A24CE   	E4EA				 
1998121800368	19981218	00368	GL  	1998	12	18	CA980126001      	2	19970201	G	7323	252466712	GOVERNOR        	BENDIX      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1086 		22928		CAE831201			(CAN) UNABLE TO HOLD STEADY N2 RPM, SURGING OVER/UNDER SPEED.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1998121800369	19981218	00369	GL  	1998	12	18	CA980126002      	2	19970826	G	7323	23007505	GOVERNOR        	BENDIX      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1245 		24933		CAE831201			(CAN) ENGINE UNABLE TO HOLD STEADY N2 RPM, CAUSING ACFT TO YAW DURING FLUCTUATIONS.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1998121800370	19981218	00370	GL  	1998	12	18	CA980126003      	2	19970918	G	7323	252476913	GOVERNOR        	BENDIX      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				256  		23799		CAE831201			(CAN) IN-FLIGHT DROP IN N2 RPM.  TRIM DID NOT BRING RPM UP.  BEEP RANGE SHIFTED DOWN.  UNABLE TO ADJUST WITHIN RANGE.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1998121800371	19981218	00371	GL  	1998	12	18	CA980126004      	2	19971101	G	7323	252466714	GOVERNOR        	BENDIX      		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				165  		24523		CAE831201			(CAN) ENGINE EXPERIENCED A DROP IN ATTAINABLE N2 RPM.  ADJUSTMENT ATTEMPTED, BUT HITTING MAX STOP AFTER ADJUSTMENT.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2001032100071	20010321	00071	SO  	2001	3	21	CA980302002      	2	19971120	G	8530	641370	CYLINDER        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  					ENGINE	SEPARATED       	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			600  								(CAN) THE TOP OF THE CYLINDER CONTAINING THE VALVES AND THE ROCKER ARMS SEPARATED FROM THE CYLINDER.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001032200002	20010322	00002	GL  	2001	3	22	CA980309006      	3	19971220	G	6114	57A22451	BUSHING         		HCE2YL2BSF  	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER HUB	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER WAS DISMANTLED FOR OVERHAUL. LOWER HUB BUSHING WAS MISSING. NO DAMAGE WAS CAUSED BY THE ABSENCE OF THE B	USHING.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2001032200026	20010322	00026	GL  	2001	3	22	CA980313001      	1	19971231	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 ILLUMINATED (WARNING) IN FLIGHT. POST FLIGHT, FUEL PRESSURE SENSOR WAS REPLACED. THE ENGINE WAS GROU	ND RUN SERVICEABLE.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2001032200058	20010322	00058	EU  	2001	3	22	CA980317070      	1	19970919	G	2840	647510032	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL QUANTITY	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			460  								(CAN) FUEL QUANTITY GAUGE STICKING AT 55-80% WHEN REFUELING AIRCRAFT. FUEL QUANTITY TRANSMITTER REPLACED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032200059	20010322	00059	EU  	2001	3	22	CA980317071      	1	19971209	G	2840	647510032	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL QUANTITY	INACCURATE      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN DEFUELING AIRCRAFT, GAUGE READ 20 PERCENT WHEN EMPTY AND LOW LEVEL FUEL LIGHT WAS NOT ILLUMINATED. FUEL TRANS	MITTER REPLACED.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001032200107	20010322	00107	NE  	2001	3	22	CA980318033      	2	19971213	G	7230		STATOR          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2303 								(CAN) DURING HOT SECTION INSPECTION INTERNAL DAMAGE AND FOD WAS FOUND AROUND THE COMBUSTION LINER. INVESTIGATION FOUND T	HAT PART OF THE 3RD STAGE COMPRESSOR FAILED AND DEBRIS FOUND ITS WAY THROUGH THE ENGINE. THE ENGINE WAS REPLACED.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2001032600338	20010326	00338	EA  	2001	3	26	CA980325016      	1	19970526	G	2436	2N5686	TRANSISTOR      	PHOENIX     	VR1010241A  	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					VOLT REGUALTOR	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						3390B					(CAN) POWER TRANSISTOR IN VOLTAGE REGULATOR BASE IS AN UNAPPROVED PART. IT SHOULD BE AN OEM 048504.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2001032600339	20010326	00339	EA  	2001	3	26	CA980325018      	2	19970501	G	7414	10682056	DISTRIBUTOR BLK 	BENDIX      	1038291013  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT MAGNETO	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						32234					(CAN) THE MAGNETO WAS SENT FOR OVERHAUL. ON DISASSEMBLY IT WAS FOUND THAT THE BUSHING, THAT SHOULD HAVE BEEN MOLDED TO T	HE DISTRIBUTOR BLOCK, WAS EXTREMELY LOOSE BUT STILL IN PLACE. THE BUSHING CAN BE TILTED 10 DEGREES EITHER SIDE OF CENTRE	. THE PART WAS REPLACED AND THE UNIT OVERHAULED AND RETURNED TO SERVICE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
1998090400002	19980904	00002	CE  	1998	9	4	CA980325019      	1	19971106	G	2140	G722023	VALVE           	SOUTHWIND   	8259HR2     	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HEATER	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1    		6278		244910R	940455		(CAN) HEATER UNIT OBTAINED AS REPLACEMENT ITEM AND ON FIRST FLIGHT THE PILOTS COMPLAINED THAT THEY WERE NOT ABLE TO CONT	ROL HEATER.  INVESTIGATION REVEALED THAT THE FUEL SOLENOID VALVE SEAL WAS NOT INSTALLED PROPERLY AND THIS ALLOWED FUEL T	O LEAK OUT OF THE COMBUSTION CHAMBER AND WHEN THE VENT PORT WAS PLUGGED, THE FUEL CAME OUT OF THE HEATER EXHAUST.  SEAL 	REPLACED.			1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA	 
2001032600346	20010326	00346	EA  	2001	3	26	CA980325020      	2	19971007	G	7414	10357584	GEAR            	BENDIX      	106006141J12	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					DISTRIBUTOR	DESTROYED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				990  		94023					(CAN)  MAGNETO WAS SENT FOR 500 HOUR INSPECTION. ON DISASSEMBLY A STEEL WASHER WAS FOUND LOOSE IN THE COIL CAVITY. INSPE	CTION REVEALED THE WASHER HAD CAME LOOSE FROM THE GEAR AND AXLE ASSEMBLY ON THE DISTRIBUTOR GEAR. IT WAS ALSO NOTED THAT	 THE AXLE COULD EASILY BE MOVED WITHIN THE NYLON GEAR. THE DEFECTIVE PART WAS REPLACED AND THE UNIT RETURNED TO SERVICE.				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
1998100900157	19981009	00157	SO  	1998	10	9	CA980325048      	1	19971022	G	2923	ESQ125	BRUSHES         	PRESTOLITE  	105476      	PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					HYD PUMP	BROKEN          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			LD	LANDING        	1			CA								L1621051A			(CAN) HYDRAULIC GEAR POWERPACK FAILED ON LANDING.  BRUSHES BROKEN INTO MULTIPLE PIECES.  REPLACED.						1	L	7	1 	3O	3	O		2A13    	1E10				 
1998041700634	19980417	00634	EU  	1998	4	17	CA980330026      	1	19971217	G	3260	9321912044	BOLT            			PILATS	PC12  	PC12        	7090550	EU  										RT WOW SWITCH	SHEARED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			418  								(CAN) UNABLE TO SELECT GEAR UP ON DEPARTURE, RETURNED TO BASE.  SWITCH CLEANED OF SLUSH.  SAME PROBLEM OCCURRED BUT WAS 	CLEARED BY RESETTING CIRCUIT BREAKER.  AFTER RETURN TO BASE, ANNUNCIATOR ILLUMINATED.  INVESTIGATION FOUND THAT RT WEIGH	T- ON-WHEEL TARGET RETAINING BOLT WAS SHEARED ALLOWING TARGET TO MOVE OCCASIONALLY.  BOLT REPLACED AND GEAR SWING CHECKE	D OK.N  PART TC:  273.			1	L	7	1 	3T			RT	A78EU   					 
1998041700622	19980417	00622	NE  	1998	4	17	CA980403008      	2	19971228	G	7310	117050001	TUBE ASSEMBLY   			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					PURGE SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE07641			(CAN) TUBE ASSEMBLY, PURGE SYSTEM, FOUND BROKEN AT THE BRAZING. THIS ASSEMBLY IS IN THE FUEL STARTING SYSTEM.						1	G	7	1 	4U	4	U		H1SW    	E17EA				 
1998041700621	19980417	00621	EA  	1998	4	17	CA980403009      	3	19971230	G	6110		BLADE           			PIPER 	PA28  	PA28180     	7102808	SO  						SNSNCH	76E	76EM8S5     	EA  	PROP LE & FACE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1175 						17434K		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CORROSION FOUND ON FACE SIDE OF THE BLADES ACCOMPANIED BY STONE DAMA	GE.					1	L	7	1 	3O				2A13    		5	N	P4EA	 
1998073100367	19980731	00367		1998	7	31	CA980406001      	4	19970713	G	5301	1B1141A120	RELEASE CABLE   			SCWZER	SG2   	SGS233      	8051604	EA  										RELEASE LEVER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3482 								(CAN) REAR RELEASE CABLE BROKE AT RELEASE LEVER, JUST AFT OF SWAGED THIMBLE.						1	K	0	0 	  			 	G2EA    					 
1998073100380	19980731	00380	EA  	1998	7	31	CA980406019      	1	19970807	G	2917	HP6101002C1	MANIFOLD        			CARSON	S61   	S61LSKRSKY  		EA  										HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				980  							(CAN) ON PRE-FLIGHT CONTINUITY CHECK, PILOT COULD SHUT OFF BOTH HYDRAULIC SYSTEMS AT THE SAME TIME. BOTH PRESSURE GAUGES	 INDICATED ZERO PSI, BUT SMALL AMOUNT OF HYDRAULIC CONTROL REMAINED.   HYDRAULIC MANIFOLD REPLACED.					2	G	7	2 	4U				H8EA    					 
1998073100381	19980731	00381	GL  	1998	7	31	CA980406020      	2	19971223	G	7323	23057870	GOVERNOR        	BENDIX      	23057870    	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			HO	HOVERING       	1			CA				360  		18351		CAE830896			(CAN) WHEN MAKING BEEP ADJUSTMENTS TO GOVERNOR, ESPECIALLY AT HIGHER POWER DEMANDS, GOVENOR WILL HUNT FOR TWO OSCILLATIO	NS AND THEN OVERSPEED.  BLUE GREASE FOUND AT SEAL DRAIN.					1	G	7	1 	3U	3	U		H3WE    	E4CE				 
1998080700105	19980807	00105	EU  	1998	8	7	CA980407015      	1	19970413	G	2913	350A35013003	SPLINE          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	SHEARED         	W				A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			G	K	J	MULTIPLE FAILURE          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			CA								4414			(CAN) HYDRAULIC PRESSURE LOST DURING FLIGHT.  LOSS OF PRESSURE DUE TO SHEARED INTERNAL SPLINES ON THE HYDRAULIC PUMP DRI	VE COUPLING SLEEVE P/N S40.					1	G	7	1 	3U	3	U		H9EU    	E19EU				 
1998090400012	19980904	00012	CE  	1998	9	4	CA980415021      	1	19971209	G	3230		UPLOCK          			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	NLG	FROZEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									804566		(CAN) AT TEMPERATURE BELOW ZERO DEGREES,  CONDENSATION FROZE ON NOSE GEAR UPLOCK.  REPLACED.						1	L	7	2 	3O				A25CE   		5	C	P45GL	 
1998090400027	19980904	00027	CE  	1998	9	4	CA980602001      	1	19970820	G	2510		SCREW           			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	SEAT	LOOSE           	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			50   					464476	765582		(CAN) STC SA00508WI INSTALLED, NEW PILOTS AND COPILOTS SEATS.  DURING A RECENT FLIGHT, ON ROTATION, THE PILOTS SEAT SLIP	PED AND THE PILOT HAD PROBLEMS REGAINING CONTROL OF THE AIRCRAFT.  WHEN CONTROL WAS REGAINED THE AIRCRAFT WAS LANDED.  I	NVESTIGATION REVEALED THAT THE SEAT BACK COULD BE MOVED APPROX 3 - 4 INCHES.  DISASSEMBLY REVEALED THAT THE SET SCREW TH	AT LOCKS ON A FLAT AREA OF THE SHAFT HAD LOOSENED ALLOWING THE CAM FREE TO ROTATE.  ALSO, WHEN IT LOOSENED, IT ALLOWED T	HE CAM TO MISALIGN WITH SUPPORT STRUCTURE AND MISS CONTACT.		1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
1998100900254	19981009	00254	SW  	1998	10	9	CA980615008      	1	19970914	G	2821	8975131	FILTER          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	FUEL SYSTEM	FAILED          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				35   				P44424C	DRG57282		(CAN) DURING TAKEOFF, THE FUEL BYPASS LIGHT CAME ON WITH A LOSS OF TORQUE ON NR 2 ENGINE.  TROUBLESHOOTING WAS CARRIED O	UT ON THE BYPASS AND FUEL SYSTEM.  THE FLOW DIVIDER FILTER WAS CHECKED AND THE FUEL FILTER WAS REPLACED.  GROUND RUNS CO	MPLETED WITH NO FAULT FOUND.  AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
1998091100465	19980911	00465	EA  	1998	9	11	CA980616004      	1	19970912	G	5521		SPAR            		C2TE1A      	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								8730			(CAN) LEFT ELEVATOR SPAR FOUND WITH .50 INCH  CRACK AT OUTBOARD END NEAR THE OUTBOARD BEARING.   SUBMITTER SAYS THAT PRO	BLEM CAUSED BY DOCKHANDS USING ELEVATOR TIP TO MANEUVER AIRCRAFT FOR DEPARTURES AND ARRIVALS.					1	H	7	1 	3R	3	R		A806    	5E1				 
1998111300736	19981113	00736	EU  	1998	11	13	CA980915005      	1	19971015	G	2750	6X77ONL312014	BOLT            			ZLIN  	242   	Z242L       	9970204	EU  										TE FLAP	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1550 								(CAN) AT 1,500 HOUR INSPECTION, THE BOLT ATTACHING THE FLAP CONTROL CABLE TO THE BELLCRANK ARM WAS FOUND BENT APPROXIMAT	ELY 9 DEGREES AT ITS MID-POINT.  INSPECTION OF OPPOSITE BOLT ALSO FOUND BENT.  IT IS SUSPECTED THAT THE BOLTS ARE BEING 	BENT WHEN THE FLAPS ARE SELECTED FULL DOWN WHERE THE AIR LOADS OF THE FLAP ARE TRANSMITTED ON EACH END OF THE SUBJECT BO	LTS.			1	L	7	1 	3O			0	A76EU   					 
1998111300737	19981113	00737	EU  	1998	11	13	CA980915006      	1	19971103	G	2750	6X77ONL312014	BOLT            			ZLIN  	242   	Z242L       	9970204	EU  										TE FLAP	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1550 								(CAN) FLAP CONTROL BELLCRANK BOLT FOUND BENT APPROXIMATELY 7 DEGREES AT ITS MID-POINT.  BOTH SIDES THE SAME.						1	L	7	1 	3O			0	A76EU   					 
1998121800418	19981218	00418	EA  	1998	12	18	CA981013007      	1	19970822	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:  7,282.						2	H	7	2 	4T			RT	A13NM   					 
1997042200006	19970422	00006	NE  	1997	4	22	CHI1752          	1	19970326	G	6520	643566400044	INTERMED GEARBOX			SKRSKY	S64   	CH54A       	8142501	NE  										LT MOUNT LUG	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	548CH	1578 	1301 			18461				UPON INSPECTION IAW COLUMBIA HELICOPTERS SB 54-65-2, THE LEFT LOWER INTERMEDIATE GEARBOX MOUNT LUG WAS FOUND CRACKED.  T	HIS WAS FOUND BY FLUORESCENT PENETRANT AND CONFIRMED BY EDDY CURRENT INSPECTIONS.  THE CRACK APPEARED TO ORIGINATE AT TH	E CORNER OF THE LUG AND PROGRESS TOWARDS THE MOUNT BOLT HOLE APPROXIMATELY .25 INCH LONG.  THIS IS A TROUBLESOME AREA AN	D THE SUBJECT OF THE ABOVE BULLETIN.  SUBMITTER RECOMMENDS A DIFFERENT MATERIAL BE USED IN MANUFACTURE OF THE HOUSING. (	X)		2	G	7	2 	4U				H16NM   					 
1997042400815	19970424	00815	WP  	1997	4	24	CHI1753          	1	19970320	G	6210	107R1202	BLADE           			KAWSKI	KV107 	KV1072      	4820101	WP  										M/R SPAR	VACUUM LEAK     	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	192CH	4735 			A2188	4011				EVACUATED BLADE SPAR INDICATOR SYSTEM (ISIS) SHOWED POSITIVE.  BLADE REMOVED FROM SERVICE TO INVESTIGATE SOURCE OF LEAK.	  THE LEAK WAS DETERMINED COMING FROM A SMALL CORROSION PIT WHICH IS LOCATED IN A TOOLING MARK AT STA 252.  THE TOOLING 	MARK IS APPROXIMATELY 0.38 INCH IN LENGTH ON THE SURFACE OF THE SPAR.  REVIEW OF AUG 96 X-RAYS DID NOT REVEAL THE DEFECT	.  THIS MINUTE DEFECT SHOWED THE EXCELLENT DETECTION CAPABILITIES OF THE ISIS SYSTEM.  (X)			2	G	7	2 	4U				H1PC    					 
1997052200534	19970522	00534	EA  	1997	5	22	CHI1773          	1	19970428	G	6220	234R21973	SLEEVE          		234R21971   	BOEING	234   	234         	1385049	EA  										M/R HEAD	BROKEN          	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	239CH	1058 			A20108	MJ006				THE HORIZONTAL HINGE PIN WAS REMOVED FOR A LEAKING SEAL.  THE HINGE PIN WAS REMOVED AND THE LEADING SLEEVE REMAINED IN T	HE BEARING.  THE SLEEVE WAS SPLIT AND THE BEARING WAS REMOVED WITH THE SLEEVE STILL INSTALLED.  A NEW BEARING AND HORIZO	NTAL HINGE PIN WERE INSTALLED.  THE ROTOR HEAD ASSY A5-1503 HAS ACCUMULATED 212 HOURS SINCE CENTER HUB REPLACEMENT.  (X)				2	G	7	2 	4U				H9EA    					 
1997061200826	19970612	00826	WP  	1997	6	12	CHI1789          	1	19970520	G	6310	5602326	SHAFT SPLINE    			HILLER	UH12  	UH12E       	4360122	WP  										TRANSMISSION	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	62409					1455				UPPER AND LOWER TRANSMISSION COUPLING SPLINE SHAFT HAS ONE SPLINE CRACKED NEAR OUTER END OF SPLINE.  REPLACED CRACKED SH	AFT WITH SERVICEABLE UNIT.  (X)					1	G	7	1 	3O				4H11    					 
1997061200841	19970612	00841	NE  	1997	6	12	CHI1791          	1	19970523	G	6210	S50F11111SN56A	LOCKED IN STUD  	REXNORD     	641520201044	SKRSKY	S64   	CH54A       	8142501	NE  										M/R BLADE	BROKE           	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	548CH	4058 				18461				M/R BLADE STUD BROKE (IN TENSION) DIRECTLY BELOW LOCK RING SPLINES ABOVE FIRST THREAD.  REPLACED AFFECTED MAIN ROTOR BLA	DE WITH SERVICEABLE BLADE.					2	G	7	2 	4U				H16NM   					 
1997070300135	19970703	00135	EA  	1997	7	3	CHI1801          	1	19970603	G	6220	234R21971	PIN             		414R2001    	BOEING	234   	234         	1385049	EA  										FWD YELLOW ARM	SLIPPED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	CFHFH	387  			A20134	MJ001				ROTOR HEAD WAS INSPECTED WHILE IN THE SHOP FOR ROUTINE MAINTENANCE.  IT WAS NOTED THAT THE YELLOW ARM WAS STIFF WHEN MOV	ED DOWN ITS HORIZONTAL AXIS (FLAPPING).  DISASSEMBLY SHOWED THE LAG BEARING RACE ON THE HORIZONTAL PIN HAD MOVED OUTBOAR	D TILL IT TOUCHED THE LAG CAP.  CAUSE MAY BE INADEQUATE INTERFERENCE FIT BETWEEN THE PIN AND THE BEARING RACE.  (X)				2	G	7	2 	4U				H9EA    					 
1997101600016	19971016	00016	EA  	1997	10	16	CHI1906          	1	19970923	G	6300	A02D31473R	SHAFT           		A02D301110  	BOEING	107   	1072        	9420604	EA  										UPPER PIN HOLE	CRACK           	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2FOR	2619 			NI0289UT	5				DURING ROUTINE 100-HOUR EDDY CURRENT INSPECTION OF SHAFT PIN HOLES, A POSITIVE INDICATION WAS DETECTED.  SHAFT WAS REMOV	ED FROM THE AIRCRAFT AND SENT TO THE SHOP FOR EVALUATION.  MAGNETIC PARTICLE INSPECTION REVEALED A CRACK APPROXIMATELY 0	.150 INCH LONG FROM ONE PIN HOLE.  NO OTHER DEFECTS NOTED.  PART IS BEING FORWARDED TO BOEING HELICOPTERS FOR FURTHER EV	ALUATION.  (X)			2	G	7	2 	4U				1H16    					 
1997103000385	19971030	00385	EA  	1997	10	30	CHI1912          	1	19970925	G	6310	107DS2131	CLUTCH          		107D2003516 	BOEING	107   	1072A       	9420606	EA  										MIX BOX NR 1	SLIPPED         	B			CHIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CGHFI	18119	9    		XBW1612	5				AFTER NR 1 IDLER ASSY HAD BEEN REPLACED, AIRCRAFT'S NR 1 CLUTCH, WITH 8.7 HOURS, REPORTED SLIPPING.  TRANSMISSION REPLAC	ED AND NR 1 IDLER ASSY DISASSEMBLED.  AT THAT TIME IT WAS VISUALLY INSPECTED, PARTS WERE ALSO DIMENSIONALLY CHECKED.  AI	RCRAFT HAD SAME PROBLEM 01-30-97.  TSO, 309.9 HOURS.  TT, 17,056.3 HOURS.  (X)				2	G	7	2 	4U				1H16    					 
1997103000384	19971030	00384	EA  	1997	10	30	CHI1913          	1	19970925	G	6310	107DS2131	CLUTCH          		107D2003516 	BOEING	107   	1072A       	9420606	EA  										MIX BOX NR 1	SLIPPED         	B			CHIR	O				OTHER                   				O			OTHER                     			EX	EXTERNAL LOAD  	1			NM	09	CGHFI	18110	1    		XBW1627	5				NR 1 CLUTCH REPORTED SLIPPING DURING LOGGING OPERATION.  NR 1 IDLER ASSY REMOVED AND DISASSEMBLED.  VISUAL AND DIMENSION	AL CHECK DONE ON PINION SPUR GEAR, IDLER HUB, AND CLUTCH SET.  NO PROBLEM FOUND.  AIRCRAFT HAD SAME PROBLEM 01-03-97 TSO	, 309.9 HOURS.  TT, 17,065.3 HOURS.  (X)				2	G	7	2 	4U				1H16    					 
1997102300229	19971023	00229		1997	10	23	CHI1916          	4	19970821	G	2211		COMPUTER        	HONEYWELL   	234VS1007   	BOEING	234   	234         	1385049	EA  										NR 1 AFCS	MALFUNCTION     	B			CHIR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	09	2FOR				M0008	MJ005				A YAW KICK WAS FELT IN-FLIGHT. THE KICK WAS ISOLATED TO THE NR 2 AFCS SYSTEM.  SUBSEQUENT TROUBLESHOOTING REVEALED THE P	ROBLEM TO BE THE NR 2 AFCS COMPUTER CAUSING THE YAW KICK.  A SECOND SPARE COMPUTER WAS INSTALLED IN NR 2 POSITION AND TH	E SAME PROBLEM WAS THERE.  ALSO, A LARGE ENGAGEMENT ERROR WAS NOTICED WHEN TURNING THE SYSTEM ON AND OFF.  FINALLY, REPL	ACED THE NR 1 AFCS COMPUTER FOR TROUBLESHOOTING AND THE PROBLEM WAS GONE.  (X)			2	G	7	2 	4U				H9EA    					 
1997103000396	19971030	00396	EA  	1997	10	30	CHI1921          	1	19970930	G	6710	234HS5603	ACTUATOR        			BOEING	234   	234         	1385049	EA  										STICK BOOST	MALFUNCTION     	B			CHIR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			NM	09	241CH	2431 			0066V	MJ016				ON START-UP, PILOT WAS DOING CONTROL CHECK AND NOTICED HE COULD NOT GET THE FULL TRAVEL AFT THAT IS NORMAL WHILE DOING T	HE CONTROL CHECKS.  TROUBLESHOOTING REVEALED THAT IF ONLY ONE HYDRAULIC SYSTEM WAS SELECTED, THE ACTUATOR WOULD START BI	NDING AND NOT PERMIT FULL TRAVEL OF THE CYCLIC STICK FORWARD OR AFT.  IF BOTH HYDRAULIC SYSTEMS WERE SELECTED, THERE WAS	 NO BINDING IN THE ACTUATOR.  THERE WAS NO INDICATION OF A JAMMED ACTUATOR ACCORDING TO THE JAM INDICATOR BUTTONS.  REPL	ACED ACTUATOR, CONTROL AND TRAVEL CHECKS WERE GOOD.		2	G	7	2 	4U				H9EA    					 
1997103000383	19971030	00383	EA  	1997	10	30	CHI1923          	1	19971002	G	2913		PUMP MOTOR      	SPERRYVICRS 		BOEING	234   	234         	1385049	EA  										AGB HYD	LEAKING         	B			CHIR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	P2CHI				MX358828B	MJ003				AT SHUT DOWN OF AIRCRAFT WHILE STARTING APU, AGB HYDRAULIC MOTOR PUMP STARTED LEAKING AND SPRAYING HYDRAULIC OIL.  AFTER	 SHUTTING DOWN OF APU AND CLOSER INSPECTION OF AGB PUMP, FOUND CASE HALF MOUNTING EARS CRACKED IN HALF WHICH SEPARATED B	ACK HALF OF PUMP FROM FORWARD DRIVE SECTION.  CAUSE UNKNOWN.  (X)				2	G	7	2 	4U				H9EA    					 
1997121100123	19971211	00123	EA  	1997	12	11	CHI1957          	1	19971119	G	6510	107D33421	ADAPTER         			BOEING	107   	1072        	9420604	EA  										DRIVE SHAFT	MISALIGNED      	B			CHIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09					A8671					NEW PART RECEIVED AND ADAPTER HOLES MISALIGNED.  (X)						2	G	7	2 	4U				1H16    					 
1998043000262	19980430	00262	EA  	1998	4	30	CHI2007          	1	19970129	G	6310	107DS2131	CLUTCH          		107D2003515 	BOEING	107   	1072        	9420604	EA  										NR 2	SLIPPING        	B			CHIR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	CGHFI	310  			XBW1574	5				NR 2 CLUTCH SLIPPING.  (X)						2	G	7	2 	4U				1H16    					 
1998043000261	19980430	00261	EA  	1998	4	30	CHI2012          	1	19971220	G	6220	114RS2133	BEARING         		414R200219  	BOEING	234   	234         	1385049	EA  										AFT ROTOR	SPALLED         	B			CHIR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	P2CHI	8902 			WS3187	MJ003				AFTER SHUTDOWN, NOTICED EXCESSIVE OIL LEAKING FROM AFT HEAD.  CLOSER INSPECTION AND SUBSEQUENT REMOVAL OF RED HORIZONTAL	 HINGE PIN BEARING END CAP REVEALED METAL SHAVINGS COMING FROM RED LEADING HORIZONTAL BEARING.  AFTER FURTHER DISASSEMBL	Y, FOUND A CRACKED HORIZONTAL HINGE PIN SLEEVE. CAUSE UNKNOWN.  (X)				2	G	7	2 	4U				H9EA    					 
1999040200487	19990402	00487	SW  	1999	4	2	CZMA061345       	1	19970317	G	2120	212073927003	CONTROLLER      			BELL  	412   	412         	1182202	SW  										AIR DISTRIBUTION	WORN            	E			CZMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	911BE	3358 				36018				SERVO INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1999040900678	19990409	00678	SW  	1999	4	9	CZMA061409       	1	19970317	G	2160	212073927001	MOTOR           			BELL  	412   	412         	1182202	SW  										TEMP CONTROL	WORN            	E			CZMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	911BE	3358 				36018				MOTOR TEMPERATURE CONTROL INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1997102300426	19971023	00426	GL  	1997	10	23	GCHA0000013      	2	19970817	G	7320	23064693	FADEC           			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					NR 1 ENGINE	MALFUNCTION     	B			GCHR	A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			WP	19	175PA				JG7ALK0319	53154	847179			DURING POST-INSPECTION TEST FLIGHT, AIRCRAFT EXPERIENCED A FADEC DEGRADE AND RESTART FAULT LIGHT.  THIS OCCURRED WHILE I	N HOVER PERFORMING A POWER CHECK.  AIRCRAFT WAS LANDED AND PILOT ATTEMPTED TO ROLL THROTTLE TO IDLE.  WHILE FADEC WAS ST	ILL IN AUTOMODE, NR AND NP REMAINED AT 100 PERCENT.  MANUAL MODE WAS SELECTED AND THE NR AND NP RETURNED TO IDLE.  AFTER	 THE ENGINE WAS SHUT DOWN, THE LAP TOP COMPUTER LINK REVEALED FADEC DEGRADE.  NO FAULT AND RESTART FAULT INDICATED.  (X)			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997102300431	19971023	00431	GL  	1997	10	23	GCHR0000012      	2	19970926	G	7320	23068348	FADEC           			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					NR 1 ENGINE	WATER CONTAM    	B			GCHR	H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			WP	19	176PA	26   			JGALK0315	53160	847179			FADEC FAILURE LIGHT ILLUMINATED IN DEPARTURE TRANSITION.  PILOT SWITCHED TO  MANUAL MODE AND LANDED AIRCRAFT.  AIRCRAFT 	BEGAN ENGINE OVERSPEED, SYSTEM BACK-UPS CUT IN AND SHUT DOWN ENGINE.  SYSTEM TROUBLESHOOTING FAILED TO RETRIEVE FLASH CO	DES.  ENTRY TO ECU BY LAP TOP LINK FAILED, NO ECU AVAILABLE.  ALLISON REPORT ENGINE REMOVED FOR OVERSPEED OVERHAUL.  CYC	LES, 18.  (X)			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997102300430	19971023	00430	SW  	1997	10	23	GCHR0000016      	1	19971001	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	WORN            	B			GCHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	176PA					53160				SHAFT IS DIMENSION UNDER MINIMUM.  PRODUCT ENGINEERING RECOMMENDS REPLACE SHAFT WITH 407-040-316-101 ADAPTER.  (X)						1	G	7	1 	3U			O	H2SW    					 
1997102300429	19971023	00429	SW  	1997	10	23	GCHR0000017      	1	19971001	G	6322	406040339105	BEARING         			BELL  	407   	407         		SW  										T/R O/C SHAFT	ROUGH           	B			GCHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	176PA	244  				53160				PART IS ROUGH.  FOUND FORWARD BEARING WORN WHEN REPLACING O/C DRIVESHAFT AND ADAPTER.  REMOVED AND REPLACED BEARING.  (X	)					1	G	7	1 	3U			O	H2SW    					 
1997102300428	19971023	00428	SW  	1997	10	23	GCHR0000019      	1	19971001	G	5302	206032305129A	ANGLE           			BELL  	407   	407         		SW  										TAIL BOOM	CRACKED         	B			GCHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	176PA	244  				53160				ANGLE IS CRACKED.  DURING O/C SHAFTING INSPECTION, THE O/C WAS REMOVED.  WHEN TRYING TO SECURE THE ATTACHING HARDWARE TO	 PREVENT LOSS, THE MECHANIC REMOVED AND REPLACED ANGLE.  (X)					1	G	7	1 	3U			O	H2SW    					 
1997102300427	19971023	00427	SW  	1997	10	23	GCHR0000020      	1	19971001	G	5311	206032305127	FRAME           			BELL  	407   	407         		SW  										TAIL BOOM	CRACKED         	B			GCHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	176PA	244  				53160				FRAME IS CRACKED.  DURING O/C SHAFT-ADAPTER INSPECTION, NUTPLATE WAS FOUND CRACKED.  UPON FURTHER INSPECTION, 127 FRAME 	WAS ALSO FOUND CRACKED.  REMOVED AND REPLACED FRAME.  (X)					1	G	7	1 	3U			O	H2SW    					 
1997041700557	19970417	00557	NM  	1997	4	17	GJOR323E         	1	19970314	G	6320	A0061	GEARBOX         			ROBSIN	R22   	R22BETA     		NM  										M/R GEARBOX	MAKING METAL    	B			GJOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4046A	1707 			1840	1676				AFTER A TRAINING FLIGHT, PILOT NOTIFIED MAINT OF A STRANGE NOISE THAT APPEARED TO BE EMANATING FROM THE DRIVE SYSTEM.  A	FTER A VISUAL OF THE MAIN AND TAIL ROTOR DRIVE SYSTEMS, A MAINT GROUND RUN WAS PERFORMED.  MAINT CONFIRMED A MEDIUM TO L	OW FREQUENCY NOISE RELATED TO THE A006-1 MAIN GEARBOX.  THE MAIN GEARBOX CHIP DETECTOR WAS REMOVED AND FOUND COVERED WIT	H FERROUS.  (X)			1	G	7	1 	3O				H10WE   					 
1997032700267	19970327	00267	SW  	1997	3	27	GJQR97106        	1	19970224	G	2915	212076006105	VALVE           			BELL  	212   	212         	1181420	SW  										HYD SYS	DEFECTIVE       	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	98W	138  				35100				THIS VALVE TRIPS THE REMOTE FILTER CLOGGED INDICATOR WHEN POWER IS APPLIED.  INDICATORS ON FILTER ASSY.  DO NOT TRIP.  F	ILTERS ARE CLEAN.  REPLACED WITH NEW UNIT FROM BELL HELICOPTER.					1	G	7	1 	4U				H4SW    					 
1997020600556	19970206	00556	CE  	1997	2	6	GMCR97001        	1	19970124	G	5610	99143792	WINDOW          			CESSNA	650   	650         	2076802	CE  										RT COCKPIT	SHATTERED       	B			GMCR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	23	5118	2177 			63H6967	6507013				THIRTY MINUTES AFTER DEPARTURE FROM SLC, THE CREW HEARD A LOUD BANG, AND NOTICED THE OUTER PANE OF THE RIGHT COCKPIT WIN	DOW HAD SHATTERED.  THE CREW DECLARED AN EMERGENCY AND HAD AN UNEVENTFUL LANDING BACK AT SLC.  NO FRAGMENTS OF THE OUTER	 PANE HAD SEPARATED CREATING ANY FURTHER DAMAGE.  REPLACED THE COCKPIT WINDOW.				2	L	7	2 	4F				A9NM    					 
1997061200878	19970612	00878	SW  	1997	6	12	HAI00010003      	1	19970602	G	6330	206033516101	FLEXURE         			BELL  	206   	206L1       	1182107	SW  										M/R	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	2251A					45755				FLEXURE BEARINGS WORN AND UNSTAKED.						1	G	7	1 	3U				H2SW    					 
1997061200879	19970612	00879	SW  	1997	6	12	HAI00010066      	1	19970606	G	7722	3030083	TRIM COMPENSATOR			BELL  	412   	412         	1182202	SW  										NR 2 ENGINE	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6559Z					36019				#2 ENGINE ITT INDICATOR IS ERRATIC.  TRIM COMPENSATOR FAULTY.						1	G	7	2 	4U				H4SW    					 
1998042400272	19980424	00272	SW  	1998	4	24	HAIGJQR0106      	1	19970224	G	2915	212076006105	VALVE           			BELL  	212   	212         	1181420	SW  										HYD SYS	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	98W	138  				35100				VALVE TRIPS THE REMOTE FILTER CLOGGED INDICATOR WHEN POWER IS APPLIED.  INDICATORS ON FILTER ASSY. DO NOT TRIP.  FILTERS	 ARE CLEAN. REPLACED WITH NEW UNIT FROM BELL HELICOPTER.					1	G	7	1 	4U				H4SW    					 
1998042400273	19980424	00273	SW  	1998	4	24	HAIGJQR0107      	1	19970224	G	3040	204070907011	WIPER ASSY      			BELL  	212   	212         	1181420	SW  										WINDSHIELD	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	98W	177  				35100				WIPER ASSY. BROKEN AT OUTBOARD PIVOT PIN. REPLACED WITH NEW UNIT FROM BELL HELICOPTER.						1	G	7	1 	4U				H4SW    					 
1998042400274	19980424	00274	SW  	1998	4	24	HAIGJQR0108      	1	19970224	G	7931	1300203	TRANSMITTER     			BELL  	212   	212         	1181420	SW  										OIL PRESS	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	98W	161  				35100				NO PRESSURE INDICATION ON GAUGE WITH 80 PSI SYSTEM PRESSURE. REPLACED WITH NEW UNIT FROM BELL HELICOPTERS						1	G	7	1 	4U				H4SW    					 
1998042400275	19980424	00275	SW  	1998	4	24	HAIGJQR0109      	1	19970224	G	7931	1300205	TRANSMITTER     			BELL  	212   	212         	1181420	SW  										OIL PRESS	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	98W	183  				35100				PRESSURE GAUGE INDICATES 0 PSI WITH ENGINE RUNNING & 75PSI SYSTEM PRESSURE. REPLACED WITH NEW UNIT FROM BELL HELICOPTER.						1	G	7	1 	4U				H4SW    					 
1998042400276	19980424	00276	SW  	1998	4	24	HAIGJQR0110      	1	19970324	G	5610	212030464001	WINDSHIELD      			BELL  	212   	212         	1181420	SW  										COCKPIT	DAMAGED         	H			GJQR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	13	98W	177  				35100				WINDSHIELD WAS DEEPLY SCRATCHED BY WIPER ASSY. THAT BROKE DURING FLIGHT. REPLACED WITH NEW WINDSHIELD						1	G	7	1 	4U				H4SW    					 
1998042400277	19980424	00277	SW  	1998	4	24	HAIGJQR0111      	1	19970324	G	6210	212015501115	BLADE           			BELL  	212   	212         	1181420	SW  										M/R	PEELING         	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	98W	138  				35100				LARGE PATCHES OF PAINT PEELING FROM BLADES.						1	G	7	1 	4U				H4SW    					 
1998042400278	19980424	00278	SW  	1998	4	24	HAIGJQR0133      	1	19970617	G	7920	206040525101	FILTER HOUSING  			BELL  	206   	206L        	1181522	SW  										OIL SYS	LEAKS           	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	13	97PM	59   				52187				FILTER HOUSING OIL LEAKS						1	G	7	1 	3U				H2SW    					 
1998042400279	19980424	00279	SW  	1998	4	24	HAIGJQR0134      	1	19970617	G	7920	206040525101	FILTER HOUSING  			BELL  	206   	206L        	1181522	SW  										OIL SYS	LEAKS           	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	13	97PM	2    				52187				FILTER HOUSING OIL LEAKS						1	G	7	1 	3U				H2SW    					 
1998042400280	19980424	00280	SW  	1998	4	24	HAIGJQR0135      	1	19970617	G	7920	206040129001	FILTER HOUSING  			BELL  	206   	206L        	1181522	SW  										OIL SYS	LEAKS           	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	13	97PM	59   				52187				FILTER HOUSING OIL LEAKS						1	G	7	1 	3U				H2SW    					 
1997101600308	19971016	00308	SW  	1997	10	16	HAIGJQR0144      	1	19971013	G	7931	209070262101	INDICATOR       			BELL  	212   	212         	1181420	SW  										ENG OIL	READS HIGH      	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	365  				35100				ENG OIL TEMP PRESS INDICATOR READS HIGH.  REPLACED WITH NEW PART FROM BELL.						1	G	7	1 	4U				H4SW    					 
1998042400281	19980424	00281	SW  	1998	4	24	HAIGJQR0147      	1	19971024	G	6320	412040111105	SEAL            			BELL  	212   	212         	1181420	SW  										INPUT PINNION	LEAKING         	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	98W	376  				35100				SEAL LEAKING AN UNACCEPTABLE AMOUNT OF OIL. REPLACED WITH NEW SEAL FROM BHT.						1	G	7	1 	4U				H4SW    					 
1998042400282	19980424	00282	SW  	1998	4	24	HAIGJQR0148      	1	19971024	G	6320	214040805001	THERMOSWITCH    			BELL  	206   	206L        	1181522	SW  										M/R GR BOX	SHORTED         	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	97PM	81   				52187				SHORTED - KEEPS LIGHT ON. REPLACED WITH NEW PART FROM CSF.						1	G	7	1 	3U				H2SW    					 
1998042400283	19980424	00283	SW  	1998	4	24	HAIGJQR0158      	1	19971231	G	6320	B3703	CHIP DETECTOR   			BELL  	212   	212         	1181420	SW  										XMSN	DEFECTIVE       	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	472  				35100				NO GROUNDING POINTS THROUGH LOCKING PINS & CASE. REPLACED WITH NEW PART FROM BHT						1	G	7	1 	4U				H4SW    					 
1997041000470	19970410	00470	GL  	1997	4	10	HAIHEEA9214      	2	19970318	G	7250	23055430	NOZZLE          		23031899    						ALLSN 	250C  	250C20B     	03013	GL  					NR 2	DEFECTIVE       	E			HEEA	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03					CAT70200					ENGINE REMOVED DUE TO TURBINE OVERHAUL. TURBINE DISASSEMBLED DUE TO LOW POWER ON TEST CELL.  DISASSEMBLY INSPECTION REVE	ALED:  MATERIAL FLAKING AND MISSING ON #2 NOZZLE #2 TIP PATH. INSTALLED A DALLAS AIRMOTIVE OVERHAULED #2 NOZZLE.										3	U			E4CE				 
1997041000476	19970410	00476	GL  	1997	4	10	HAIHEEA9220      	2	19970319	G	7260	23055466	GEARBOX COVER   		6894171     						ALLSN 	250C  	250C20B     	03013	GL  					ACCY GR BOX	DEFECTIVE       	E			HEEA	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			SW	03					CAG37111		CAE820964F			GEARBOX DISASSEMBLED DUE TO AFT T/M LEAK ON TEST CELL.  DISASSEMBLY INSPECTION REVEALED:  AFT BUSHING HEIGHTH EXCEEDS PR	INT DIMENSION ON GEARBOX COVER. INSTALLED A DALLAS AIRMOTIVE REPAIRED GEARBOX COVER.    TIME SINCE REPAIR 0:00.										3	U			E4CE				 
1997041000480	19970410	00480	GL  	1997	4	10	HAIHEEA9225      	2	19970321	G	7250	23008054	NOZZLE          								ALLSN 	250C  	250C28B     	03013	GL  					NR 1	BELOW SPEC      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MEASURED .044 BELOW MIN. SPECS (6.200) ON #1 NOZZLE AFT ROPE PACKING INNER RIM ID.											3	U			E1GL				 
1997050800028	19970508	00028		1997	5	8	HAIHEEA9446      	4	19970419	G	3442	MI5853011	INDICATOR       	HONEYWELL   	P500        															COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RADAR INDICATOR DISPLAY SHAKES AND IS DISTORTED.																			 
1997051500227	19970515	00227		1997	5	15	HAIHEEA9505      	4	19970423	G	3457	0110005400	GPS 150         	GARMIN      																COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COCKPIT GPS DIRECT TO BUTTON IS UNREADABLE.																			 
1997051500911	19970515	00911	EA  	1997	5	15	HAIHEEA9582      	2	19970424	G	7200		ENGINE          								PWA   	PT6   	PT6A41      	52043	EA  					POWER PLANT	NOISY           	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03							PCE80435			ENGINE MAKING NOISE.    TIME SINCE REPAIR 0:00.											4	T			E4EA				 
1997052200258	19970522	00258		1997	5	22	HAIHEEA9626      	4	19970429	G	3416	LE511	ALTIMETER       																	COCKPIT ENCODER	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MODE C READING VERY HIGH FROM TOWER ALTITUDE.																			 
1997061200374	19970612	00374		1997	6	12	HAIHEEA9750      	4	19970430	G	3452	C2080A	PULSE OSCILLATO 	KING        	KT76A       															TRANSPONDER	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CATHODE PULSE OSCILLATOR CAUSES TRANSPONDER UNIT (KT76A) TO DRAW MORE CURRENT THAN NORMAL.																			 
1997061200920	19970612	00920		1997	6	12	HAIHEEA9843      	4	19970513	G	2350	1022824202	HEADSET         																	COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										HEADSET INTERMITTENT.																			 
1997061200923	19970612	00923		1997	6	12	HAIHEEA9848      	1	19970513	G	3411	10100164	PITOT STATIC    																	AIR SPEED	LEAKS           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STATIC SYS LEAKS DURING PITOT AND STATIC TEST.  AIRSPEED INOPERATIVE.																			 
1997061900398	19970619	00398		1997	6	19	HAIHEEA9865      	4	19970513	G	3416	6302	ALTITUDE INDICAT																	COCKPIT ALT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR DOES NOT READ CORRECTLY.  INDICATOR STAYS STUCK INTERMITTENTLY.																			 
1997062600385	19970626	00385		1997	6	26	HAIHEEA9976      	4	19970530	G	3423	2593379001	COMPENSATOR     	HONEYWELL   																NR 1 COMPASS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										#1 COMPASS SYSTEM OFF BY 10.																			 
1997041000507	19970410	00507	SW  	1997	4	10	HAIW6HR0066      	1	19970108	G	6220	222310115117	BEARING         		222011101105	BELL  	222   	222U        	1182140	SW  										M/R	WORN EXCESSIVELY	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	429MA	1931 				47523				PART IS WORN EXCESSIVELY.  ELASTOMERIC MATERIAL IS SEPERATING.  BEARING WAS PUT IN SERVICE 16 JAN. 1988. PART HELD FOR F	UTURE EVALUATION.					1	G	7	2 	3U				H9SW    					 
1997041000508	19970410	00508	SW  	1997	4	10	HAIW6HR0067      	1	19970108	G	6220	222310115117	BEARING         		222011101105	BELL  	222   	222U        	1182140	SW  										M/R	WORN EXCESSIVELY	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	416MA	1189 				47526				PART IS WORN EXCESSIVELY. ELASTOMERIC MATERIAL IS SEPERATING. BEARING WAS PUT IN SERVICE 14 JUL. 1989. PART HELD FOR FUT	URE EVALUATION.					1	G	7	2 	3U				H9SW    					 
1997041000509	19970410	00509	SW  	1997	4	10	HAIW6HR0068      	1	19970113	G	6220	222310115115	BEARING         		222011101105	BELL  	222   	222U        	1182140	SW  										M/R	WORN EXCESSIVELY	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	416MA	1454 			A29	47526				PART IS WORN EXCESSIVELY.  ELASTORMERIC EXTRUSION, DELAMINATION & SEPERATION.   UNIT FIRST PUT INTO SERVICE 08-03 1983.						1	G	7	2 	3U				H9SW    					 
1997041000510	19970410	00510	SW  	1997	4	10	HAIW6HR0069      	1	19970122	G	6230	204011402125	RING ASSY       		412010402101	BELL  	412   	412         	1182202	SW  										M/R MAST	WORN EXCESSIVELY	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	401MA	137  			RE0055	33060				PART IS WORN EXCESSIVELY.  GIMBAL SUPPORT BUSHING AREA ELONGATED.						1	G	7	2 	4U				H4SW    					 
1997041000511	19970410	00511	NE  	1997	4	10	HAIW6HR0072      	2	19970211	G	7310	430128602	FUEL MANIFOLD   			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					ENGINE	DEFECTIVE       	E			W6HR	E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			IN	INSP/MAINT     	1			WP	21	429MA					47523	LE47194			ENGINE SHOOTS OUT 2 FOOT FLAME PAST EXHAUST EJECTOR DURING START WITHOUT ANY MGT INDICATION UNTIL START PROGRESSES, THEN	 REMAINDER OF START IS NORMAL. SUSPECT EXCESS FUEL GETTING INTO ENGINE AT BEGINNING OF START ENGAGEMENT. SHIPPED CORE RE	TURN MANIFOLD TO RMH 02-11-97, SHIPPING MEMO# 97-0065.   RDM 02/14/97.				1	G	7	2 	3U	3	U		H9SW    	E5NE				 
1997041000512	19970410	00512	SW  	1997	4	10	HAIW6HR0076      	1	19970313	G	3340	4501283	LIGHT           		222175302105	BELL  	222   	222U        	1182140	SW  										EXT SEARCH	BINDING         	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	429MA					47523				PART IS BINDING.  ASSY. WILL NOT MOVE IN ANY DIRECTION. PART HAS BEEN IN SERVICE 3 MONTHS.  REQUEST ASSY. TO BE REPAIRED	 UNDER WARRANTY. REPLACED LIGHT ASSY WITH SERVICEABLE UNIT.					1	G	7	2 	3U				H9SW    					 
1997041000513	19970410	00513	SW  	1997	4	10	HAIW6HR0077      	1	19970323	G	2435	23032048	GENERATOR       		222060060107	BELL  	222   	222B        	1182124	SW  										START/GEN	ARCED           	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	406MA				LE47154AE	47134				PART IS ARCED. COMMUTATOR APPEARS TO HAVE BURNED SPOTS.  STATIC IS HEARD THRU ALL HEAD SETS.  REQUEST WARRANTY REPAIR SI	NCE THIS UNIT HAS ONLY BEEN IN SERVICE 22.0 HRS / 2 MONTHS. REPLACED WITH TSO:0 UNIT. ALL SYS. FUNCTION PROPERLY.					1	G	7	2 	3U				H9SW    					 
1997041000514	19970410	00514	SW  	1997	4	10	HAIW6HR0078      	1	19970328	G	6320	222040061105	CASE ASSY       		222040003111	BELL  	222   	222         	1182122	SW  										M/R	DEFECTIVE       	E			W6HR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21										PART IS DEFECTIVE.  FOUND BOTH SMALLER BORE OIL PASSAGES WHICH SUPPLY OIL TO THE #3 JETS (3EA.) & MAST BEARING TO BE CLO	GGED (BETWEEN THE VERTICAL PASSAGE & THE JET BORE) WITH A HARDENED EPOXY - LIKE SUBSTANCE.  UPON REMOVAL OF THE EPOXY - 	LIKEMATERIAL, FOUND BOTH PASSAGES TO BE IN AN UN-FINISHED STATE (NOT COMPLETELY BORED OUT) WHERE THE ANGLED PASSAGES MEE	T THE VERTICAL PASSAGES. REPLACED WITH ANOTHER NEW TOP CASE ASSY.			1	G	7	2 	3U				H9SW    					 
1997041000515	19970410	00515	SW  	1997	4	10	HAIW6HR0079      	1	19970328	G	6320	222040061105	CASE ASSY       		222040003111	BELL  	222   	222         	1182122	SW  										M/R	DEFECTIVE       	E			W6HR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21										PART IS DEFECTIVE. FOUND BOTH SMALLER BORE OIL PASSAGES WHICH SUPPLY OIL TO THE #3 JETS (3EA.) & MAST BEARING TO BE CLOG	GED (BETWEEN THE VERTICAL PASSAGE & THE JET BORE) WITH A HARDENED EPOXY - LIKE SUBSTANCE. UPON REMOVAL OF THE EPOXY - LI	KEMATERIAL, FOUND BOTH PASSAGES TO BE IN AN UN-FINISHED STATE (NOT COMPLETELY BORED OUT) WHERE THE ANGLED PASSAGES MEET 	THE VERTICAL PASSAGES. THIS IS THE SECOND OCCURRENCE OF THIS SAME TYPE (PREVIOUS OCCURRENCE ON TOP CASE S/N: A217. REPLA	CED WITH ANOTHER NEW TOP CASE ASSY.		1	G	7	2 	3U				H9SW    					 
1997091100567	19970911	00567	SW  	1997	9	11	HAIW6HR0080      	1	19970429	G	2913	2226513201	PUMP            		222180002111	BELL  	222   	222B        	1182124	SW  										HYD SYS	WORN EXCESS     	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	406MA					47134				PART IS WORN EXCESSIVELY. PUMP LEAKS AT SHAFT SEAL.						1	G	7	2 	3U				H9SW    					 
1997091100568	19970911	00568	SW  	1997	9	11	HAIW6HR0084      	1	19970520	G	6340	222375013103	TORQUE SENSOR   		222040003117	BELL  	222   	222U        	1182140	SW  										ROTOR	FLUCTUATES      	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	429MA	179  				47523				ROTOR TORQUE NEEDLE FLUCTUATES ABOVE 85% ROTOR TORQUE.  PART IN SERVICE 4 MONTHS / 178.9 HOURS. REPLACED SENSOR.						1	G	7	2 	3U				H9SW    					 
1997091100569	19970911	00569	SW  	1997	9	11	HAIW6HR0085      	1	19970603	G	5311	222031503101	FRAME ASSY      		222031501125	BELL  	222   	222U        	1182140	SW  										BS 233	CRACKED         	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	415MA	2772 				47568				FRAME ASSY IS CRACKED.   CRACKED @  R/H CORNER THRU FASTNER HOLES. PERFORMED REPAIR I/A/W BHT FIELD REPAIR PROCEDURE  96	R1-036 REV. A  D.O.T. S.O.C. SERIAL # A4753, DATED 3-19-97.					1	G	7	2 	3U				H9SW    					 
1997091100570	19970911	00570	SW  	1997	9	11	HAIW6HR0086      	1	19970603	G	5320		ROOF            		222031501125	BELL  	222   	222U        	1182140	SW  										CABIN	CRACKED         	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	415MA					47568				PART IS CRACKED.  ROOF WAS CRACKED DUE TO FRAME ASSY P/N: 222-031-503-101 (STA 233) CRACKING. INSTALLED STRAP DOUBLER P/	N: 222-031-517-179 I/A/W BHT TB 222U-91-56, DATED 1-15-91.					1	G	7	2 	3U				H9SW    					 
1997091100571	19970911	00571	SW  	1997	9	11	HAIW6HR0087      	1	19970603	G	5330	222031361121	PANEL ASSY      		222131004109	BELL  	222   	222U        	1182140	SW  										BS 233	CRACKED         	E			W6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	415MA	2772 				47568				PANEL ASSY  IS CRACKED.  APPROX. 10 INCH CRACK  STARTING @ R/H AFT CORNER GOING FOWARD AND TOWARDS THE LEFT. THIS CRACK 	HAPPENED DUE TO STA.  233 FRAME ASSY. P/N: 222-031-503-101 CRACKING. PERFORMED BHT FIELD REPAIR PROCEDURE 96R1-037, D.O.	Y. S.O.C. SERIAL # A4266, DATED 11-27-96.				1	G	7	2 	3U				H9SW    					 
1997091100572	19970911	00572	SW  	1997	9	11	HAIW6HR0088      	1	19970626	G	6340	506923	TORQUE SENSOR   		222040003117	BELL  	222   	222U        	1182140	SW  										ROTOR	FAILED          	E			W6HR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			WP	21	429MA					47523				TORQUE SENSOR HAS RESISTANCE-HIGH.  INDICATOR NEEDLE INTERMITTENTLY DROPS OFF TO ZERO.  UNIT WAS INSTALLED FOR APPROX. 1	 MONTH AND HAS 36.5 HRS. SINCE BEING REPAIRED					1	G	7	2 	3U				H9SW    					 
1997062600413	19970626	00413		1997	6	26	HEEA0010008      	1	19970602	G	5520	206023119159	ELEVATOR        																	PIVOT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RT ELEV ASSY CRACKED AT PIVOT HOLE.																			 
1997062600420	19970626	00420		1997	6	26	HEEA0010016      	1	19970602	G	2930	124043	INDICATOR       	MASCO       																HYD PRESS/TEMP	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TEMPERATURE AND PRESSURE INDICATOR HIGH OUT OF TOLERANCE.																			 
1997071000347	19970710	00347		1997	7	10	HEEA0010236      	4	19970625	G	3416	A30	ENCODER         	ACK         																ALTIMETER	WONT CALIB      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ENCODER ALTIMETER WILL NOT CALIBRATE.  TIME SINCE REPAIR 0:00.																			 
1997071000388	19970710	00388		1997	7	10	HEEA0010278      	4	19970625	G	3416	A30	ENCODER         	ACK         																COCKPIT ALT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ENCODER HAS ERRATIC OUTPUT AND DOES NOT HOLD CALIBRATION.  TIME SINCE REPAIR 0:00.																			 
1997071700276	19970717	00276		1997	7	17	HEEA0010319      	4	19970626	G	3457	S67157539	ANTENNA         																	COCKPIT GPS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										GPS ANTENNA NO RECEIVE.																			 
1997071700323	19970717	00323		1997	7	17	HEEA0010366      	4	19970626	G	2561	3500145NL72	LIFE VEST PIN   	AEROMARINE  																INFLATE PIN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EASTERN AERO MARINE ISSUED SERVICE BULLETIN # SBV-25-2 STATING SOME VESTS MAY HAVE DEFECTIVE INFLATION PINS INSTALLED ON	 THE BOTTLE INFLATION.  PHI HAS FOUND SOME OF THESE SUSPECT PINS ON HOOVER INDUSTRIES VESTS.  SERIAL NUMBERS INVOLVED: K	0606803,K0606845, K0606802, K0606852, K0606792, K0606851, K0606769, K0606811, K0606766, K0606840, K0606841, K0606763, K0	606834, K0606791, K0606765, K0606759, K0606810, K0606796, K0606798, K0606805. REPLACED VESTS WITH SERVICEABLE UNITS.																 
1997071700333	19970717	00333	GL  	1997	7	17	HEEA0010378      	2	19970701	G	7250	23008064	NOZZLE          								ALLSN 	250C  	250C30S     	03013	GL  					1ST STAGE	OVER SPEC       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MEASURED .015 OVER SPECS (4.445 - 4.450) ON #1 NOZZLE DIMENSION -AM-.											3	U			E1GL				 
1997072400301	19970724	00301		1997	7	24	HEEA0010448      	1	19970710	G	7722	206075187001	INDICATOR       																	DUAL TEMP	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DUAL TEMP INDICATOR READS LOW OUT OF TOLERANCE THROUGHOUT SCALE.																			 
1997081400152	19970814	00152	GL  	1997	8	14	HEEA0010558      	2	19970805	G	7250	6898731	SUPPORT         								ALLSN 	250C  	250C20B     	03013	GL  					PWR TURB	DEFECTIVE       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  COATING SOFT AND FLAKING OUT OF P.T. SUPPORT 19-24 SEAL BORE.											3	U			E4CE				 
1997081400181	19970814	00181		1997	8	14	HEEA0010587      	4	19970806	G	3422	656520	VALVE           																	FLUX VALVE	DEFECTIVE       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										FLUX VALVE WILL NOT TEST CORRECTLY BETWEEN PINS A & B.																			 
1997081400209	19970814	00209		1997	8	14	HEEA0010616      	1	19970807	G	7712	7645001078106	INDICATOR       																	DUAL TORQUE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										#2 NEEDLE INDICATES HIGH ON LOW END; CANNOT CALIBRATE.																			 
1997091100577	19970911	00577		1997	9	11	HEEA0010746      	4	19970819	G	3442	MI5852221	TRANSCEIVER     	HONEYWELL   	RT3002      															WX RADAR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		50   								INOPERATIVE, WILL NOT COME UP. SENT TO HONEYWELL, TEXAS FOR INSPECTION AND REPAIR.																			 
1997091100609	19970911	00609		1997	9	11	HEEA0010779      	4	19970819	G	3442	RD300	RADAR           																	T SW CABLE	BURNT           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COMPONENTS ON 30 MHZ PULSE DISCUMINATOR BOARD BURNT.																			 
1997091100627	19970911	00627		1997	9	11	HEEA0010800      	4	19970820	G	2312	40001278501	TRANSCEIVER     		RT406F      															COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NO TRANSMISSION.																			 
1997111300232	19971113	00232	GL  	1997	11	13	HEEA0011569      	2	19971020	G	7250	6886407	BLADE           		6898735     	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 WHEEL	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181J	1736 			CAT33490	3771	CAE836333			TURBINE REMOVED DUE TO 1750 HOUR INSPECTION.  UPON INSPECTION OF TURBINE PARTS NOTED:  MINOR SULFIDATION ON NR 1 WHEEL B	LADES.  SCRAPPED WHEEL.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
1997111300233	19971113	00233	SW  	1997	11	13	HEEA0011570      	1	19971020	G	6320	407040006107	TRANSMISSION    			BELL  	407   	407         		SW  										M/R GR BOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH	1054 				53072				METAL IN OIL (LOWER CHIP PLUGS).  NOTE:  TOP CASE P/N 406-040-052-107, S/N A788, REMOVED WITH TRANSMISSION, T.T. 1054:35	 HOURS.					1	G	7	1 	3U			O	H2SW    					 
1997111300235	19971113	00235	SW  	1997	11	13	HEEA0011572      	1	19970927	G	6220	407010104101	CONE            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	841  				53038				REPLACED LOWER CONE AND CONE SET WITH SEAT P/N 407-010-107-103 ON 9-27-97.						1	G	7	1 	3U			O	H2SW    					 
1997111300236	19971113	00236	SW  	1997	11	13	HEEA0011573      	1	19970927	G	6220	407010111101	CONE            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	841  				53038				REPLACED LOWER CONE AND CONE SET WITH SEAT P/N 407-010-107-103 ON 9-27-97.						1	G	7	1 	3U			O	H2SW    					 
1997111300237	19971113	00237		1997	11	13	HEEA0011574      	4	19971020	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										ELEVATOR FBWE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AMPLIFIER WILL NOT ENGAGE.  STARTS TO ENGAGE THEN KICKS OFF.  TIME SINCE REPAIR 0:00.						2	G	7	2 	4U				H10SW   					 
1997111300238	19971113	00238	SW  	1997	11	13	HEEA0011575      	1	19971020	G	6410	214011819101	BEARING         		214011801127	BELL  	214   	214ST       	1182106	SW  										TAIL ROTOR	SPUN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y				A130	28139				INBOARD BEARINGS SPUN.						2	G	7	2 	4U				H10SW   					 
1998062600385	19980626	00385	EU  	1998	6	26	HEEA0011577      	1	19971021	G	6220	1051410142	BOLT            			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										MISMANUFACTURED.  BOLT HOLE TOO SMALL FOR KEY.						1	G	7	2 	3U			 	H3EU    					 
1997111300239	19971113	00239		1997	11	13	HEEA0011578      	4	19971021	G	3452	066106200	TRANSISTOR      			BELL  	206   	206L1       	1182107	SW  										TRANSPONDER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078D					45397				NO REPLY FROM TRANSPONDER.  REPLACED BROKEN Q411 TRANSISTOR AND OPEN Q409 TRANSISTOR.  COOKED UNIT AND BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW    					 
1997111300240	19971113	00240		1997	11	13	HEEA0011579      	4	19971021	G	3452	066106200	CONNECTOR       			BELL  	206   	206L1       	1182107	SW  										TRANSPONDER	DIRTY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745N					45489				NO OUTPUT READ FROM UNIT BY TEST EQUIPMENT.  CLEANED REAR CONNECTOR AND UNIT FIRED UP.   REPLACED WEAK V301 PHOTO DETECT	OR.  ALSO REPLACED INTERMITTENT FRONT SWITCH BOARD ASSEMBLY.  CLEANED SWITCH BOARD AND AJUSTED PULSE.  BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW    					 
1997111300241	19971113	00241	NE  	1997	11	13	HEEA0011580      	1	19971021	G	6210	7615009100051A	SPAR            			SKRSKY	S76   	S76A        	8143006	NE  										M/R BLADE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707AE	8836 				760276				BLADE HAS A CRACK IN THE SPAR AT THE ROOT END.  SCRAPPED BLADE.						1	G	7	2 	3U				H1NE    					 
1997111300242	19971113	00242	SW  	1997	11	13	HEEA0011581      	1	19971021	G	5320	206033110239	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										CABIN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119	2905 				51575				CRACK FROM HI-SHEAR HOLE THROUGH RADIUS AND FLANGE.  REPLACED BROOM CLOSET ANGLE USING P/N 206-033-110-239.						1	G	7	1 	3U				H2SW    					 
1997111300243	19971113	00243	EU  	1997	11	13	HEEA0011582      	1	19971021	G	5330	1173010615	SKIN            			BOLKMS	117   	BK117B1     	5626012	EU  										BS 10,000	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	217UC					7152				CRACK AT APPROXIMATELY STATION 10,000.  MANUFACTURED REPAIR USING .040 INCH 2024T3, STOP DRILLED CRACK AND INSTALLED REP	AIR USING MS20470AD-3 AND 4, CR3243-4, CR3242-4 AND 890 PRO-SEAL.					1	G	7	2 	3U				H13EU   					 
1997111300244	19971113	00244		1997	11	13	HEEA0011583      	4	19971021	G	3453	8015238	LORAN RCU       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81832					S828				LORAN WILL NOT REACH OPERATING MODE.  REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H3EU    					 
1997111300245	19971113	00245		1997	11	13	HEEA0011584      	4	19971021	G	3453	8015238	LORAN RCU       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81832					S828				LORAN TAKES UP TO 30 MINUTES TO REACH OPERATION MODE.  REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U				H3EU    					 
1997111300246	19971113	00246	EU  	1997	11	13	HEEA0011585      	1	19971021	G	6420	1053178103	BUSHING         		11788659    	BOLKMS	117   	BK117B2     	5626013	EU  										TAIL ROTOR	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	134AE					7237				T/R BUSHING RING STAKING CAME LOOSE.  REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			NC	H13EU   					 
1997111300247	19971113	00247	EU  	1997	11	13	HEEA0011586      	1	19971021	G	6420	10531738101	SLEEVE          			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL	1809 				7198				T/R BEARING SEATS WORN.						1	G	7	2 	3U				H13EU   					 
1997111300248	19971113	00248	NE  	1997	11	13	HEEA0011587      	1	19971021	G	6230	SB5162101	BEARING         		761040800004	SKRSKY	S76   	S76A        	8143006	NE  										ROTOR SHAFT	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G				A07200102	760076				BEARINGS ROUGH; EXCESSIVE PITTING IN RACEWAY.  REPLACED WITH NEW BEARING.						1	G	7	2 	3U				H1NE    					 
1997111300249	19971113	00249	SW  	1997	11	13	HEEA0011588      	1	19971021	G	6300	214030603111	SEAT            			BELL  	214   	214ST       	1182106	SW  										ROTOR SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				CORROSION AT CENTER BORE (SEAT) WHERE BEARING P/N 214-030-602-3 IS INSTALLED.  REPLACED WITH NEW SUPPORT.						2	G	7	2 	4U				H10SW   					 
1997111300250	19971113	00250	SW  	1997	11	13	HEEA0011589      	1	19971021	G	2460	MS25036127	TERMINAL        		407076500103	BELL  	407   	407         		SW  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH	606  				53059				CABLES NR P7A8 AND NR P7B8 IN THE CIRCUIT BREAKER PANEL AREA HAVE TERMINALS CRACKED.  (REF: DESIGNATOR 2TB1) DUE TO THE 	STRESSES PUT ON THE CABLES DURING THE OPENING AND CLOSING OF THE OVERHEAD CIRCUIT BREAKER PANEL.  THE TERMINAL ENDS COUL	D POSSIBLY SEVER CAUSING A MAJOR POWER FAILURE.  ANOTHER POSSIBILITY IS THAT ONE CABLE COULD FAIL AND CONTACT THE AIRFRA	ME PRODUCING SEVERE ARCING.  REPLACED AFFECTED TERMINAL ENDS.			1	G	7	1 	3U			O	H2SW    					 
1997111300251	19971113	00251	GL  	1997	11	13	HEEA0011590      	2	19971021	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				BYPASS BUTTON POPPED ON ENGINE OIL FILTER. REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300252	19971113	00252	GL  	1997	11	13	HEEA0011591      	2	19971021	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				ON DAILY INSPECTION, FOUND OIL FILTER BYPASS INDICATOR EXTENDED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300253	19971113	00253	GL  	1997	11	13	HEEA0011592      	2	19971021	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	57416	61   				53070				BYPASS BUTTON POPPED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300254	19971113	00254	GL  	1997	11	13	HEEA0011593      	2	19971021	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	57416	78   				53070				BYPASS BUTTON POPPED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300255	19971113	00255	GL  	1997	11	13	HEEA0011594      	2	19971021	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	57416	31   				53070				BYPASS BUTTON POPPED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300256	19971113	00256	GL  	1997	11	13	HEEA0011595      	2	19971021	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	447PH	23   				53114				RECEIVED ON AIRCRAFT WITH BYPASS BUTTON POPPED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300257	19971113	00257	GL  	1997	11	13	HEEA0011596      	2	19971021	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				FILTER CLOGGED - BYPASSED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300258	19971113	00258	GL  	1997	11	13	HEEA0011597      	2	19971021	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	437PH	55   				53072				ENGINE EXTERIOR OIL FILTER BYPASS BUTTON POPPED.  REPLACED WITH SERVICEABLE FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300259	19971113	00259	SW  	1997	11	13	HEEA0011598      	1	19971021	G	6210	406010121101	STOP PIN        			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				LOWER FLAPPING STOP ON ORANGE BLADE WORN.  REPLACED WITH SERVICEABLE STOP.						1	G	7	1 	3U			O	H2SW    					 
1997111300260	19971113	00260	GL  	1997	11	13	HEEA0011599      	2	19971021	G	7240	6854255	VALVE           			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH	279  				53072				DRAIN VALVE BROKE IN COMBUSTION CASE DRAIN BOSS.  REPLACED WITH SERVICEABLE DRAIN VALVE.  SCRAPPED BROKEN DRAIN VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
1997111300261	19971113	00261		1997	11	13	HEEA0011600      	4	19971021	G	3457	13824020109	TNL2000         			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				GPS WILL NOT PICKUP SIGNAL AND WPT AND APT/VOR BUTTONS, BACK LIGHTING PARTIALLY INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
1997111300262	19971113	00262		1997	11	13	HEEA0011601      	4	19971021	G	2370	9806020023	CVR             			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460	327  				760223				COCKPIT RECORDER REMAINS IN TEST MODE.						1	G	7	2 	3U				H1NE    					 
1997111300263	19971113	00263	SW  	1997	11	13	HEEA0011602      	1	19971021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STAIR MOTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				STEP WILL NOT MOTOR.						1	G	7	2 	4U				H4SW    					 
1997111300264	19971113	00264	SW  	1997	11	13	HEEA0011603      	1	19971021	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA	8168 				33005				TWO UPPER FRETTING PADS UNBONDED.						1	G	7	2 	4U				H4SW    					 
1997111300265	19971113	00265		1997	11	13	HEEA0011604      	4	19971021	G	3416	8503S20LW	ALTIMETER       																	COCKPIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ALTIMETER HAS EXCESSIVE CASE LEAKAGE AROUND BARO KNOB AT VARIOUS SETTINGS.																			 
1997111300266	19971113	00266		1997	11	13	HEEA0011605      	4	19971021	G	2210	7683431	POTENTIOMETER   		769000180210	SKRSKY	S76   	S76A        	8143006	NE  										AUTOFLIGHT SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D	238  			81012170	760077				NR 1 YAW KICKING.  FOUND POTENTIOMETERS CHECKED BAD IN NULL POSITION.						1	G	7	2 	3U				H1NE    					 
1997111300267	19971113	00267	NE  	1997	11	13	HEEA0011606      	1	19971021	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217	10889				760229				TAIL ROTOR BLADE HAS A CRACKED LEADING EDGE ABRASION STRIP ON PADDLE B.						1	G	7	2 	3U				H1NE    					 
1997111300268	19971113	00268		1997	11	13	HEEA0011607      	4	19971021	G	3421	4021541671	GYRO            			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	134AE					7237				UNIT ROLLED TO THE INVERTED POSITION AND STAYED THERE FOR GROUND RUN AND POWER CHECK.  AIRCRAFT WAS HOVERED AND TEST FLO	WN FOR FURTHER OBSERVATION.  GYRO ROLLED UPRIGHT BUT DID NOT REFLECT PROPER ALTITUDE.					1	G	7	2 	3U			NC	H13EU   					 
1997111300269	19971113	00269	EU  	1997	11	13	HEEA0011608      	1	19971021	G	7921	37010200004	OIL COOLER      			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070					S145				OIL COOLER WAS REPAIRED BY VENDOR ON 6-11-97.  FOUND LEAKING AT TWO PLACES.						1	G	7	2 	3U				H3EU    					 
1997111300270	19971113	00270	EU  	1997	11	13	HEEA0011609      	1	19971021	G	7921	37010200004	OIL COOLER      			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070					S145				OIL COOLER LEAK AT LOW CENTER RIGHT SIDE.						1	G	7	2 	3U				H3EU    					 
1997111300271	19971113	00271		1997	11	13	HEEA0011610      	4	19971021	G	3450	40001452502	TRANSCEIVER     		RT138F      	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	137AE					S851				TRANSCEIVER RECEIVES, BUT WILL NOT TRANSMIT.						1	G	7	2 	3U				H3EU    					 
1997111300272	19971113	00272		1997	11	13	HEEA0011611      	4	19971021	G	3457	1624820	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				GPS ANTENNA FAULT DISPLAYED, DOES NOT PICKUP ANY SATELLITES.						1	G	7	1 	3U				H2SW    					 
1997111300273	19971113	00273		1997	11	13	HEEA0011612      	4	19971021	G	3457	1624820	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				GPS ANTENNA NOT PICKING UP SATELLITE SIGNAL.						1	G	7	1 	3U				H2SW    					 
1997111300274	19971113	00274		1997	11	13	HEEA0011613      	4	19971021	G	3457	1624820	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				GPS ANTENNA NOT PICKING UP SIGNAL.						1	G	7	1 	3U				H2SW    					 
1997111300275	19971113	00275		1997	11	13	HEEA0011614      	4	19971021	G	3416	212070238007	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				ALTIMETER NEEDLE FLUCTUATES 100 FEET UP AND DOWN PAST ACTUAL READING.						1	G	7	2 	4U				H4SW    					 
1997111300276	19971113	00276		1997	11	13	HEEA0011615      	4	19971021	G	3422	2891ESR	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019G					45247				GYRO MALFUNCTION, COULD NOT ALIGN HEADINGS.						1	G	7	1 	3U				H2SW    					 
1997111300277	19971113	00277		1997	11	13	HEEA0011616      	4	19971021	G	3457	13824120234	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	49EA					51507				GPS KEEPS LOSING NUMBERS OVERNIGHT WHEN AIRCRAFT POWER IS TURNED OFF.						1	G	7	1 	3U				H2SW    					 
1997111300278	19971113	00278	EU  	1997	11	13	HEEA0011617      	1	19971021	G	5321	350A21135921	PANEL           			SNIAS 	350   	AS350B2     	8680813	EU  										CABIN	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	3060 				2820				COCKPIT PANEL HAS EXTENSIVE CORROSION AT FORWARD BELLY LATCH BRACKETS.  REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H9EU    					 
1997111300279	19971113	00279		1997	11	13	HEEA0011618      	4	19971021	G	3452	066106200	RESISTOR        			BELL  	407   	407         		SW  										TRANSPONDER	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				TRANSPONDER WILL NOT TEST OR IDENT.  PERFORMED PRELIMINARY INSPECTION AND FOUND REPLY LIGHT DIM.  ALSO FOUND RESISTOR R4	77 DETERIORATED.  REPLACED V301 PHOTOCELL AND R477 RESISTOR.  BENCH CHECK GOOD.					1	G	7	1 	3U			O	H2SW    					 
1997111300280	19971113	00280		1997	11	13	HEEA0011619      	4	19971021	G	2370	GA1000000	RECORDER        			BRAERO	DH125 	HS125700A   	4230170	EU  										COCKPIT CVR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	125CS					NA0212				RECORDER NO TEST FUNCTION LIGHT.						2	L	7	2 	4F				A3EU    					 
1997111300281	19971113	00281	GL  	1997	11	13	HEEA0011620      	2	19971021	G	7314	3881005	SPINE           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					FUEL PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078D	910  				45397	CAE860702			FUEL PUMP INTERNAL DRIVE SPLINES WORN.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997111300282	19971113	00282	EU  	1997	11	13	HEEA0011621      	1	19971021	G	2822	1C454	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	618  				2820				BOOST PUMP INTERMITTENT.						1	G	7	1 	3U				H9EU    					 
1997111300283	19971113	00283	SW  	1997	11	13	HEEA0011622      	1	19971021	G	6320	222040003119	TRANSMISSION    			BELL  	230   	230         	1182149	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	1555 				23009				M/R TRANSMISSION MAKING METAL.						1	G	7	2 	3U			NC	H9SW    					 
1997111300284	19971113	00284	NE  	1997	11	13	HEEA0011623      	1	19971022	G	7334	7645001078118	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE FUEL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	792CH					760193				FUEL PRESSURE SENSOR TRANSMITS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE    					 
1997111300285	19971113	00285	NE  	1997	11	13	HEEA0011624      	1	19971022	G	7334	7645001078119	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE FUEL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				FUEL PRESSURE SENSOR MALFUNCTION.  INDICATES HIGH OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE    					 
1997111300286	19971113	00286	EU  	1997	11	13	HEEA0011625      	1	19971022	G	2844	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54197					S805				INDICATOR DROPPED TO ZERO.						1	G	7	2 	3U				H3EU    					 
1997111300287	19971113	00287	EU  	1997	11	13	HEEA0011626      	1	19971022	G	2844	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3533T					S111				TRANSMITS HIGH FROM 50 TO 12.5 PSI.						1	G	7	2 	3U				H3EU    					 
1997111300288	19971113	00288	EU  	1997	11	13	HEEA0011627      	1	19971022	G	2844	BSE206150G3	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3534T					S112				INDICATOR INTERMITTENT, PEGS OUT.						1	G	7	2 	3U				H3EU    					 
1997111300289	19971113	00289	SW  	1997	11	13	HEEA0011628      	1	19971022	G	7714	206075682001	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10814					45415				ENGINE RPM INDICATOR INOPERATIVE.						1	G	7	1 	3U				H2SW    					 
1997111300290	19971113	00290		1997	11	13	HEEA0011629      	4	19971022	G	3414	8000	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21240					45647				AIR SPEED INDICATOR LEAKING.						1	G	7	1 	3U				H2SW    					 
1997112000125	19971120	00125		1997	11	20	HEEA0011630      	4	19971022	G	3414	206070278005	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21240					45647				VSI NEEDLE STICKS AROUND 500 FEET GOING UP.						1	G	7	1 	3U				H2SW    					 
1997112000126	19971120	00126		1997	11	20	HEEA0011631      	4	19971022	G	3416	5934D1	ALTIMETER       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21240					45647				ALTIMETER HAS EXCESSIVE CASE LEAKAGE AND FRICTION ERROR.						1	G	7	1 	3U				H2SW    					 
1997112000127	19971120	00127	SW  	1997	11	20	HEEA0011632      	1	19971022	G	2436	206075447007	REGULATOR       			BELL  	206   	206L1       	1182107	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				REGULATOR HAS NO VOLTAGE OUTPUT.						1	G	7	1 	3U				H2SW    					 
1997112000128	19971120	00128	SW  	1997	11	20	HEEA0011633      	1	19971022	G	7722	35712519129	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				ENGINE TEMPERATURE INDICATOR READS 10 DEGREES HIGH.						1	G	7	1 	3U				H2SW    					 
1997112000129	19971120	00129	SW  	1997	11	20	HEEA0011634      	1	19971022	G	5520	206023119159	ELEVATOR        			BELL  	206   	206L3       	1182108	SW  										TAIL	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6161A					51611				ELEVATOR CORRODED BEYOND LIMITS.						1	G	7	1 	3U				H2SW    					 
1997112000130	19971120	00130	SW  	1997	11	20	HEEA0011635      	1	19971022	G	3213	212030436007	CAP             			BELL  	412   	412         	1182202	SW  										SKID	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				RUBBER DETERIORATED AND WORN.						1	G	7	2 	4U				H4SW    					 
1997112000131	19971120	00131	SW  	1997	11	20	HEEA0011636      	1	19971022	G	6320	206033518007	STOP            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Z					51610				RUBBER STOP DETERIORATED.						1	G	7	1 	3U				H2SW    					 
1997112000132	19971120	00132	SW  	1997	11	20	HEEA0011637      	1	19971022	G	2436	206075447007	REGULATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3207Q					51540				GENERATOR DOES NOT COME ON LINE.						1	G	7	1 	3U				H2SW    					 
1997112000133	19971120	00133		1997	11	20	HEEA0011638      	4	19971022	G	3416	1330061	ALTIMETER       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21240					45647				ALTIMETER HAS EXCESSIVE FRICTION ERROR AND CORRODED ON HOUSING.						1	G	7	1 	3U				H2SW    					 
1997112000134	19971120	00134	NE  	1997	11	20	HEEA0011639      	1	19971022	G	2932	7645001078121	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										NR 1 HYD SYS	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				SLIGHT FLUCTUATION ON NR 1 HYDRAULIC INDICATOR SYSTEM PRESSURE.						1	G	7	2 	3U				H1NE    					 
1997112000135	19971120	00135	NE  	1997	11	20	HEEA0011640      	1	19971022	G	6220	7610608000049	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				DAMPER LEAKING.						1	G	7	2 	3U				H1NE    					 
1997112000136	19971120	00136	SW  	1997	11	20	HEEA0011641      	1	19971022	G	7714	206070266009	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ENGINE RPM NEEDLE STICKS INTERMITTENTLY.						1	G	7	1 	3U				H2SW    					 
1997112000137	19971120	00137		1997	11	20	HEEA0011642      	4	19971022	G	3416	1003511326	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ALTIMETER HAS LOOSE PARTS INSIDE.						1	G	7	2 	4U				H4SW    					 
1997112000138	19971120	00138	EU  	1997	11	20	HEEA0011643      	1	19971022	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911NC					7026				ENGINE RPM INDICATOR HIGH OUT OF TOLERANCE ABOVE 50 PERCENT INTERMITTENT OPERATION.						1	G	7	2 	3U				H13EU   					 
1997112000139	19971120	00139	EU  	1997	11	20	HEEA0011644      	1	19971022	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3526T					S610				ENGINE TOT INDICATOR WILL NOT CALIBRATE EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H3EU    					 
1997112000140	19971120	00140	EU  	1997	11	20	HEEA0011645      	1	19971022	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3526T					S610				ENGINE TOT INDICATOR HAD EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H3EU    					 
1997112000141	19971120	00141	SW  	1997	11	20	HEEA0011646      	1	19971022	G	6240	214074280105	DETECTOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				M/R DECTECTOR INOPERATIVE.						2	G	7	2 	4U				H10SW   					 
1997120400343	19971204	00343		1997	12	4	HEEA0011647      	4	19971022	G	3444	7001840903	TRANSPONDER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				FAILED 4.1 CHECK TEST ON SST BENCH (LED 50 REMAINS ON).						1	G	7	2 	3U				H1NE    					 
1997112000142	19971120	00142		1997	11	20	HEEA0011648      	4	19971022	G	2212	222305005101	SENSOR          			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6957Y					28139				AIRCRAFT DIVES WHEN ALT HOLD ENGAGED.						2	G	7	2 	4U				H10SW   					 
1997112000143	19971120	00143		1997	11	20	HEEA0011649      	4	19971022	G	2210	BHL430515	SENSOR          			BOLKMS	117   	BK117A4     	5626017	EU  										SPAS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				SPAS WOULD NOT TEST.						1	G	7	2 	3U				H13EU   					 
1997112000144	19971120	00144		1997	11	20	HEEA0011650      	4	19971022	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2014K					33020				FAILED 31.2 AND FOLLOWING TEST ON SST.						1	G	7	2 	4U				H4SW    					 
1997112000145	19971120	00145		1997	11	20	HEEA0011651      	4	19971022	G	3416	8800	ENCODER         			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				ENCODER DOES NOT SUPPLY ANY ALTITUDE READINGS TO TEST BOX.						1	G	7	2 	4U				H4SW    					 
1997112000146	19971120	00146	NE  	1997	11	20	HEEA0011652      	1	19971022	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										TIP CAP NEEDS BALANCING.  RECEIVED PART WITH NO FORWARD WEIGHTS, THEREFORE, TIP CAP IS LIGHT.   TIME SINCE REPAIR 0:00.						1	G	7	2 	3U			 	H1NE    					 
1997112000147	19971120	00147	NE  	1997	11	20	HEEA0011653      	1	19971022	G	2841	AT2062	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										FUEL TOTALIZER	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				INDICATOR HAS LOOSE PARTS INSIDE.						1	G	7	2 	3U				H1NE    					 
1997112000148	19971120	00148	SW  	1997	11	20	HEEA0011654      	1	19971022	G	3213	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										CROSS TUBE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				CAP WORN AND DETERIORATED.						1	G	7	2 	4U				H4SW    					 
1997112000149	19971120	00149	SW  	1997	11	20	HEEA0011655      	1	19971022	G	3213	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										CROSS TUBE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				CROSS-TUBE CAP WORN AND DETERIORATED.						1	G	7	2 	4U				H4SW    					 
1997112000150	19971120	00150	SW  	1997	11	20	HEEA0011656      	1	19971022	G	5343	212030437007	CAP             			BELL  	212   	212         	1181420	SW  										SKID	MISSING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				SKID RUBBER CAME OFF CAP.						1	G	7	1 	4U				H4SW    					 
1997112000151	19971120	00151	SW  	1997	11	20	HEEA0011657      	1	19971022	G	6330	206033506101	BEARINGS        			BELL  	206   	206L1       	1182107	SW  										RESTRAINT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V					45217				M/R TRANSMISSION RESTRAINT HAS BOTH BEARINGS WORN.						1	G	7	1 	3U				H2SW    					 
1997112000152	19971120	00152	SW  	1997	11	20	HEEA0011658      	1	19971022	G	7810	212061201012	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EXHAUST MOUNT BRACKET IS CRACKED.						1	G	7	2 	4U				H4SW    					 
1997112000153	19971120	00153	NE  	1997	11	20	HEEA0011659      	1	19971022	G	3350	6013211	BATTERY         			SKRSKY	S76   	S76A        	8143006	NE  										CABIN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				BATTERY HAS DEAD CELL.  EMERGENCY LIGHT WILL NOT COME ON.						1	G	7	2 	3U				H1NE    					 
1997112000154	19971120	00154	CE  	1997	11	20	HEEA0011660      	1	19971022	G	2130	1013800133	PNEUMOSTAT      			BEECH 	200   	200BEECH    	1152920	CE  										CABIN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	789DS					BB478				PNEUMOSTAT FAILED PRESSURE TEST IN-FLIGHT.						1	L	7	2 	4T				A24CE   					 
1997112000155	19971120	00155	SW  	1997	11	20	HEEA0011661      	1	19971022	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					MAIN ROTOR	INOPRATIVE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				M/R ACTUATOR WILL NOT ACTUATE.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997112000156	19971120	00156	SW  	1997	11	20	HEEA0011662      	1	19971022	G	3212	212050207012	VALVE           			BELL  	212   	212         	1181420	SW  										FLOAT BAG	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				FLOAT BAG HAS UNBONDED INLET VALVE.						1	G	7	1 	4U				H4SW    					 
1997112000157	19971120	00157	SW  	1997	11	20	HEEA0011663      	1	19971022	G	3212	212050207103	VALVE           			BELL  	212   	212         	1181420	SW  										FLOATBAG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				FLOAT BAG HAS LEAKING INLET VALVES.						1	G	7	1 	4U				H4SW    					 
1997112000158	19971120	00158		1997	11	20	HEEA0011664      	4	19971022	G	2340	AA20030	AMPLIFIER       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	OVERHEAT        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5007N					45184				INTERPHONE AMPLIFIER GETS EXCESSIVELY HOT; THEN SHUTS DOWN.						1	G	7	1 	3U				H2SW    					 
1997112000159	19971120	00159	SW  	1997	11	20	HEEA0011665      	1	19971022	G	3212	412050013119	FLOAT           			BELL  	412   	412         	1182202	SW  										FUSELAGE	BURST           	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22608					33075				FLOAT BAG BUSTED.						1	G	7	2 	4U				H4SW    					 
1997112000160	19971120	00160	EU  	1997	11	20	HEEA0011666      	1	19971022	G	7722	TM42739	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				TOT INDICATOR HAD EXCESSIVE FRICTION AND READS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H3EU    					 
1997112000161	19971120	00161	SW  	1997	11	20	HEEA0011667      	1	19971022	G	7722	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3108E					51498				TOT NEEDLES WILL NOT INDICATE.						1	G	7	1 	3U				H2SW    					 
1997112000162	19971120	00162	SW  	1997	11	20	HEEA0011668      	1	19971022	G	7722	206075188005	BEZEL           			BELL  	206   	206L1       	1182107	SW  										INDICATOR	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2759U					45267				BEZEL LOOSE FROM TOT GAUGE.						1	G	7	1 	3U				H2SW    					 
1997112000163	19971120	00163	SW  	1997	11	20	HEEA0011669      	1	19971022	G	3310	222375012101	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										INST LIGHTS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8588X					51486				INSTRUMENT LIGHTS POWER SUPPLY INOPERATIVE.						1	G	7	1 	3U				H2SW    					 
1997112000164	19971120	00164	SW  	1997	11	20	HEEA0011670      	1	19971022	G	2913	214076334105	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYDRAULIC SYS	FAILED          	E			HEEA	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	8045T					28101				LOSS OF UTILITY HYD SYSTEM PRESSURE IN-FLIGHT, PUMP FAILED.						2	G	7	2 	4U				H10SW   					 
1997112000165	19971120	00165	SW  	1997	11	20	HEEA0011671      	1	19971022	G	6410	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	992  			53058	53070				INBOARD BEARINGS BEING DAMAGED EXCEEDING LIMITS PER BHT 407MM VOLUME 1 (REV. 4, 12-16-96).  REPLACED TWO EACH BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
1997112000166	19971120	00166		1997	11	20	HEEA0011672      	4	19971022	G	3421	214175241101	GYROSCOPE       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				GYROSCOPE SLOW TO RESPOND.						2	G	7	2 	4U				H10SW   					 
1997112000167	19971120	00167		1997	11	20	HEEA0011673      	4	19971022	G	3421	214175241101	GYROSCOPE       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5748M					28102				AIRCRAFT PORPOISES, ROLLS SIDE TO SIDE.						2	G	7	2 	4U				H10SW   					 
1997112000168	19971120	00168		1997	11	20	HEEA0011674      	4	19971022	G	2562	ELT910	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	5759N					33002				ELT TRANSMITTER GOES OFF INTERMITTENTLY.						1	G	7	2 	4U				H4SW    					 
1997112000169	19971120	00169		1997	11	20	HEEA0011675      	4	19971022	G	2562	ELT910	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	2759U					45267				ELT ACTIVATION LIGHT STAYS ON.						1	G	7	1 	3U				H2SW    					 
1997112000170	19971120	00170	SW  	1997	11	20	HEEA0011676      	1	19971022	G	7332	124044	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				INDICATOR READS LOW OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW    					 
1997112000171	19971120	00171		1997	11	20	HEEA0011677      	4	19971022	G	3416	5035P2P44	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G					760076				INDICATOR READS 100 FEET LOW.						1	G	7	2 	3U				H1NE    					 
1997112000172	19971120	00172	CE  	1997	11	20	HEEA0011678      	1	19971022	G	2822	91380003	FUEL PUMP       			BEECH 	200   	200BEECH    	1152920	CE  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30PH					BB635				FUEL PUMP LEAKING AT DRIVE SHAFT.						1	L	7	2 	4T				A24CE   					 
1997112000173	19971120	00173	SW  	1997	11	20	HEEA0011679      	1	19971022	G	2432	214175379103	CHARGER         			BELL  	214   	214ST       	1182106	SW  										BATT/ CHARGE SYS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				CHARGER NOT TOP CHARGING BATTERY.						2	G	7	2 	4U				H10SW   					 
1997112000174	19971120	00174	SW  	1997	11	20	HEEA0011680      	1	19971022	G	7931	APTE138100G	TRANSMITTER     			BELL  	212   	212         	1181420	SW  										ENGINE OIL SYS	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5736J					31140				ENGINE OIL TRANSMITTER TRANSMITS ERRATIC.						1	G	7	1 	4U				H4SW    					 
1998062600384	19980626	00384		1998	6	26	HEEA0011681      	1	19971022	G	6730	800807	INSERT          																	HYD  PISTON	MISSING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										THREADED INSERTS AT BIG END OF PISTON MISSING.																			 
1997112000175	19971120	00175	SW  	1997	11	20	HEEA0011682      	1	19971022	G	5330	212030378003	PANEL           			BELL  	212   	212         	1181420	SW  										CROSSTUBE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				PANEL BENT AND CRACKED AT CROSSTUBE AREA.						1	G	7	1 	4U				H4SW    					 
1997112000176	19971120	00176	SW  	1997	11	20	HEEA0011683      	1	19971022	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y	1531 				28139				STARTER KICKS GENERATOR OFF ON START UP.						2	G	7	2 	4U				H10SW   					 
1997112000177	19971120	00177	SW  	1997	11	20	HEEA0011684      	1	19971022	G	2840	1103P0553	PRESSURE SWITCH 			BELL  	412   	412         	1182202	SW  										AUX TANK	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				AUXILIARY TANK TRANSFER PUMP SHUTS OFF AT VARIOUS FUEL LEVELS.						1	G	7	2 	4U				H4SW    					 
1997112000178	19971120	00178	EU  	1997	11	20	HEEA0011685      	1	19971022	G	7921	37010200004	OIL COOLER      			BOLKMS	105   	BO105S      	5626006	EU  										NR  2 ENGINE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				NR 2 ENGINE OIL COOLER LEAKING.						1	G	7	2 	3U				H3EU    					 
1997112000179	19971120	00179	SW  	1997	11	20	HEEA0011686      	1	19971022	G	5330	206033201249	PANEL           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				PANEL CORRODED AND SEPARATED.						1	G	7	1 	3U				H2SW    					 
1997112000180	19971120	00180	SW  	1997	11	20	HEEA0011687      	1	19971022	G	5320	206033100291A	SHELL           			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Y					51609				SHELL DENTED AND SEPARATED.						1	G	7	1 	3U				H2SW    					 
1997112000181	19971120	00181		1997	11	20	HEEA0011688      	4	19971022	G	3120	212075514001	CLOCK           			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6957Y					28139				CLOCK INTERMITTENT.						2	G	7	2 	4U				H10SW   					 
1997112000182	19971120	00182	EU  	1997	11	20	HEEA0011689      	1	19971022	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	401PH					7050				RPM INDICATOR WILL NOT INDICATE.						1	G	7	2 	3U				H13EU   					 
1997112000183	19971120	00183		1997	11	20	HEEA0011690      	4	19971022	G	3414	412075009105	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	108X					33115				INDICATOR READS LOW APPROXIMATELY 15 MPH.						1	G	7	2 	4U				H4SW    					 
1997112000184	19971120	00184	SW  	1997	11	20	HEEA0011691      	1	19971022	G	2930	124043	INDICATOR       			BELL  	212   	212         	1181420	SW  										HYDRAULIC SYS	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1082G					31109				TEMPERATURE NEEDLE STICKING.						1	G	7	1 	4U				H4SW    					 
1997112000185	19971120	00185	SW  	1997	11	20	HEEA0011692      	1	19971022	G	2436	206075447007	REGULATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	3108E					51498				REGULATOR MALFUNCTION, WILL NOT REGULATE, TRIPS ON OVER VOLTAGE.						1	G	7	1 	3U				H2SW    					 
1997112000186	19971120	00186	EU  	1997	11	20	HEEA0011693      	1	19971022	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911PF	682  				S718				PAINT PEELING;  RUBBER COATING MISSING AT BLADE TIP.						1	G	7	2 	3U				H3EU    					 
1997112000187	19971120	00187	SW  	1997	11	20	HEEA0011694      	1	19971022	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				TRIPLE TACHOMETER'S NEEDLES HAVE STICKY OPERATION DURING FUNCTION CHECK.						1	G	7	2 	4U				H4SW    					 
1997112000188	19971120	00188		1997	11	20	HEEA0011695      	4	19971022	G	3423	2593379001	COMPENSATOR     			BELL  	212   	212         	1181420	SW  										COCKPIT	SHORTED         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	102PH					30899				COMPASS COMPENSATOR SHORTED OUT INTERNALLY.						1	G	7	1 	4U				H4SW    					 
1997112000189	19971120	00189	NE  	1997	11	20	HEEA0011696      	1	19971022	G	6340	7690001881103	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			SW	03	5435V					760158				TURNING AFFECTS VIBRATION LEVELS IN AMPLIFIER.						1	G	7	2 	3U				H1NE    					 
1997112000190	19971120	00190	SW  	1997	11	20	HEEA0011697      	1	19971022	G	2820	2C271	CARTRIDGE       			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8589X					51487				EJECTOR INOPERATIVE.						1	G	7	1 	3U				H2SW    					 
1997112000191	19971120	00191	EU  	1997	11	20	HEEA0011698      	1	19971022	G	7923	209072433103	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										OIL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3071K					S859				OIL SYSTEM VALVE INOPERATIVE.						1	G	7	2 	3U				H3EU    					 
1997112000192	19971120	00192	SW  	1997	11	20	HEEA0011699      	1	19971022	G	5510	206023119151A	STABILIZER      			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X	8218 				51412				STABILIZER DENTED BEYOND LIMITS.						1	G	7	1 	3U				H2SW    					 
1997112000193	19971120	00193	SW  	1997	11	20	HEEA0011700      	1	19971022	G	7810	212061201012	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				EXHAUST RING CRACKED AT WELDS.						1	G	7	2 	4U				H4SW    					 
1997112000194	19971120	00194	SW  	1997	11	20	HEEA0011701      	1	19971022	G	3213	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										CROSSTUBE	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				CROSS-TUBE RUBBER DETERIORATED.						1	G	7	2 	4U				H4SW    					 
1997112000195	19971120	00195	SW  	1997	11	20	HEEA0011702      	1	19971022	G	3213	212030436007	CAP             			BELL  	412   	412         	1182202	SW  										CROSSTUBE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				CROSS-TUBE RUBBER WORN AND CRACKED.						1	G	7	2 	4U				H4SW    					 
1997112000196	19971120	00196	SW  	1997	11	20	HEEA0011703      	1	19971022	G	6240	206076373001	TACH GEN SHAFT  			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5006F					45181				TACHOMETER GENERATOR HAS WORN SHAFT LOOSE AT LARGE END, CLICKS WHEN TURNED.						1	G	7	1 	3U				H2SW    					 
1997112000197	19971120	00197		1997	11	20	HEEA0011704      	4	19971022	G	3424	206070274005	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	363BH					51345				TURN AND BANK INDICATOR INOPERATIVE.						1	G	7	1 	3U				H2SW    					 
1997112000198	19971120	00198	SW  	1997	11	20	HEEA0011705      	1	19971022	G	6240	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				TACHOMETER READS 2 PERCENT LOW.						1	G	7	2 	4U				H4SW    					 
1997112000199	19971120	00199		1997	11	20	HEEA0011706      	4	19971022	G	3444	7001840913	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				TRANSPONDER FAILED TEST 5.2 ON SST AND HAS LOW OUTPUT.						1	G	7	2 	4U				H4SW    					 
1997112000200	19971120	00200	SW  	1997	11	20	HEEA0011707      	1	19971022	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2251Z					45756				ACTUATOR DOES NOT MOVE IN OR OUT.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
1997112000201	19971120	00201	SW  	1997	11	20	HEEA0011708      	1	19971022	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1997112000202	19971120	00202	EU  	1997	11	20	HEEA0011709      	1	19971022	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	54191					S804				MAST MOMENT LIGHT DOES NOT COME ON.						1	G	7	2 	3U				H3EU    					 
1997112000203	19971120	00203	EU  	1997	11	20	HEEA0011710      	1	19971022	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	54191					S804				LIGHT DOES NOT COME ON.						1	G	7	2 	3U				H3EU    					 
1997112000204	19971120	00204	SW  	1997	11	20	HEEA0011711      	1	19971022	G	2841	206063633001	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	10778					45391				FUEL GAUGE STICKS.						1	G	7	1 	3U				H2SW    					 
1997112000205	19971120	00205	EU  	1997	11	20	HEEA0011712      	1	19971022	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5421E					S806				TOT NEEDLE HAS EXCESSIVE FRICTION.						1	G	7	2 	3U				H3EU    					 
1997112000206	19971120	00206	EU  	1997	11	20	HEEA0011713      	1	19971022	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				RPM WARNING BOX INOPERATIVE.						1	G	7	2 	3U				H3EU    					 
1997112000207	19971120	00207	NE  	1997	11	20	HEEA0011714      	2	19971022	G	7200	3017600	ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					POWER SECT	FAILED          	E			HEEA	K				NONE                    				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			SW	03	5759N	11978				33002				N2 POWER SECTION DROPPED OFF LINE UPON LANDING.   CANNOT ROTATE N2:  N1 TURNS FREELY.						1	G	7	2 	4U	4	U		H4SW    	E22EA				 
1997112000208	19971120	00208	SW  	1997	11	20	HEEA0011715      	1	19971022	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	108X					33115				COMPENSATOR ERRATIC AND INTERMITTENTLY INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1997112000209	19971120	00209	NE  	1997	11	20	HEEA0011716      	1	19971022	G	5320	7635109035102	WEB             			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				WEB IS UNBONDED.						1	G	7	2 	3U				H1NE    					 
1997112000210	19971120	00210	NE  	1997	11	20	HEEA0011717      	1	19971022	G	6210	7615009043050	SKIN            			SKRSKY	S76   	S76A        	8143006	NE  										TIP CAP	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				SKIN TORN ON THE LOWER SIDE, JUST AFT OF THE LEADING EDGE STRIP.						1	G	7	2 	3U				H1NE    					 
1997112600442	19971126	00442	GL  	1997	11	26	HEEA0011718      	2	19971022	G	7310	10561320	PIPE            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3533T					S111				ENGINE FUEL LEAKING FROM SWEDGED RING AT B-NUT.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
1997112000211	19971120	00211	CE  	1997	11	20	HEEA0011719      	1	19971022	G	7712	1013890053	TORQUEMETER     			BEECH 	200   	200BEECH    	1152920	CE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	500PH					BL29				CALIBRATION IS OFF, TORQUEMETER TRANSMITS HIGH.						1	L	7	2 	4T				A24CE   					 
1997112000212	19971120	00212	SW  	1997	11	20	HEEA0011720      	1	19971022	G	7160	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  										AIR INTAKE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				CONPENSATOR INOPERATIVE.						1	G	7	2 	4U				H4SW    					 
1997112000213	19971120	00213	SW  	1997	11	20	HEEA0011721      	1	19971022	G	2822	1C641	BOOST PUMP      			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				PUMP HAS LOW PRESSURE.						1	G	7	2 	4U				H4SW    					 
1997112000214	19971120	00214	SW  	1997	11	20	HEEA0011722      	1	19971022	G	6220	204031920003	BEARING         			BELL  	212   	212         	1181420	SW  										M/R DAMPER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				M/R DAMPER BEARINGS WORN.						1	G	7	1 	4U				H4SW    					 
1997112000215	19971120	00215	SW  	1997	11	20	HEEA0011723      	1	19971022	G	6510	205030236009	SUPPORT         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR SHAFT	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2261D					33076				UNABLE TO MOUNT TAIL ROTOR DRIVE SHAFT SUPPORT ON THE ENGINE DECK BECAUSE OF SMALL RADIUS ON LT FORWARD PART OF SUPPORT.	  TAIL ROTOR DRIVE SHAFT SUPPORT HITS TRIPOD FITTING P/N 212-061-102-001 PREVENTING SUPPORT HOLES TO LINE UP WITH DECK H	OLES.				1	G	7	2 	4U			 	H4SW    					 
1997112000216	19971120	00216	SW  	1997	11	20	HEEA0011724      	1	19971022	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	1295 				28102				STARTER ENGAGE LIGHT COMES ON, BUT STARTER WILL NOT ENERGIZE.						2	G	7	2 	4U				H10SW   					 
1997112000217	19971120	00217	SW  	1997	11	20	HEEA0011725      	1	19971024	G	5330	212030099071S	SKIN            			BELL  	412   	412         	1182202	SW  										TAIL BOOM	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	6559Z					36019				POSITIONED NEW SKIN TO TAILBOOM AND LOCATE AT TOP SECTION NEAR CONTROL TUBE OPENING.  FOUND UPPER AREA OF SKIN ROLLED TO	O TIGHT.  POSITIONED SADDLE SKIN TO WRAP AROUND SKIN P/N 212-030-099-071S AND FOUND .3750 INCH GAP BETWEEN SADDLE SKIN A	ND WRAP-AROUND SKIN AT AFT ROLL AREA.				1	G	7	2 	4U			 	H4SW    					 
1997112000218	19971120	00218	NE  	1997	11	20	HEEA0011726      	2	19971024	G	7310	430137601	MANIFOLD        			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	132AE					7238	LE45609AEF			INSPECTION REVEALED FUEL LEAK IN BEND OF FORWARD LINE BETWEEN FUEL NOZZLES AT 9 O'CLOCK POSITION.  REPLACED  FUEL MANIFO	LD.  INSTALLED S/N 1NL06437.					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
1997112000221	19971120	00221	GL  	1997	11	20	HEEA0011731      	2	19971031	G	7250	23031938	NOZZLE          		6898735     						ALLSN 	250C  	250C20B     	03013	GL  					NR 2 1ST STAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAT38579F					TURBINE DISASSEMBLED DUE TO LOW POWER ON TEST CELL.  UPON INSPECTION OF TURBINE PARTS NOTED:  CRACKED BEYOND SERVICEABLE	 LIMITS ON NR2 NOZZLE 1ST STAGE INNER BAND. INSTALLED A DALLAS AIRMOTIVE OVERHAULED NR2 NOZZLE.										3	U			E4CE				 
1997112600125	19971126	00125		1997	11	26	HEEA0011861      	4	19971110	G	3416	A30	ENCODER         	ACK         																COCKPIT ALT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CANNOT CALIBRATE UNIT.  UNIT DOES NOT HOLD CALIBRATION.  NOTE:  THIS IS THE 4TH TIME THIS UNIT HAS BEEN TO VENDOR FOR TH	E SAME COMPLAINT.  REFERENCE RO#976965 AND RO#977921.																		 
1997112600130	19971126	00130		1997	11	26	HEEA0011866      	4	19971110	G	3457	0110005400	GPS 150         	GARMIN      																COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										GPS NOT PICKING UP SATELLITES AND ENT. BUTTON VERY INTERMITTENT.																			 
1997112600131	19971126	00131		1997	11	26	HEEA0011867      	4	19971110	G	2210	2593996333	TARSYN          																	AUTO FLIGHT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DG PRECESSES EXCESSIVELY.																			 
1997112600145	19971126	00145		1997	11	26	HEEA0011881      	4	19971110	G	3442	7000839904	INDICATOR       																	RADAR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FOUND LOOSE OBJECTS INSIDE RADAR INDICATOR  INSTRUMENT.  TIME SINCE REPAIR 0:00.																			 
1997112600184	19971126	00184		1997	11	26	HEEA0011957      	4	19971112	G	2312	064101902	TRANSCEIVER     	KING        	KY196       															COCKPIT VHF	DISTORTED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSCEIVER MODULATION AT 118 MHZ DISTORTED.																			 
1997120400407	19971204	00407		1997	12	4	HEEA0012087      	2	19971119	G	7314	430112810	FUEL PUMP       																	FUEL SYS	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FUEL PUMP HAS WORN EXTERNAL DRIVE SPLINES.																			 
1997122400161	19971224	00161	NE  	1997	12	24	HEEA0012296      	2	19971208	G	7314	430112810	FUEL PUMP       								LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03										LEAKING FROM DRAIN.  INSTALLED UNIT ON AN ENGINE AND RAN ENGINE ON TEST CELL.  FUEL PUMP LEAKED FROM THE DRAIN EXCESSIVE	LY.										3	U			E5NE				 
1998010800166	19980108	00166		1998	1	8	HEEA0012357      	1	19971217	G	3340	700802	POWER SUPPLY    																	STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										POWER SUPPLY WILL NOT POWER UP.  WILL NOT ACTIVATE STROBE.																			 
1998010800611	19980108	00611		1998	1	8	HEEA0012390      	1	19971229	G	6720	206001763001	BELLCRANK       																	T/R	MIS MFG         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BELLCRANCK MISMANUFACTURED.																			 
1997011600434	19970116	00434	GL  	1997	1	16	HEEA978817       	2	19970107	G	7230	23039791	SPLINE ADAPTER  		6890550     						ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	BELOW SPEC      	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					CAC24241		CAE270204			RECEIVING INSPECTION REVEALED:  EXTERNAL SPLINES BELOW MANUFACTURERS SPECS ON ADAPTER. INSTALLED A NEW ADAPTER.											3	U			E4CE				 
1997012300192	19970123	00192		1997	1	23	HEEA978883       	4	19970114	G	3452	ATC600	TRANSPONDER     	KING        	KT76A       															COCKPIT ATC	FAILS           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AFTER UNIT WARMS UP 45 MINUTES KT76A TRANSPONDER WON'T RECEIVE ATC600 SIGNALS.   TIME SINCE REPAIR 0:00.																			 
1997021300326	19970213	00326	GL  	1997	2	13	HEEA978907       	2	19970120	G	7230	23039791	SPLINE ADAPTER  								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	BELOW SPECS     	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED: SPLINE ADAPTER MEASURED .0039 - .0059 BELOW SPECS (.8994 MIN BP) ON COUPLING EXTERNAL SPL	INES OF THE FOLLOWING SERIAL NUMBERS:  (1) 65186  .0044 BELOW SPECS  (2) 64943  .0059 BELOW SPECS  (3) 65060  .0054 BELO	W SPECS  (4) 65131.0049 BELOW SPECS  (5) 65040  .0059 BELOW SPECS AND (6) 65126  .0039 BELOW SPECS.									3	U			E4CE				 
1997021300339	19970213	00339	GL  	1997	2	13	HEEA978922       	2	19970121	G	7260	6876925	TUBE ASSY.      		23001928    						ALLSN 	250C  	250C20B     	03013	GL  					GR BOX	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		1744 			CAG27204		CAE270204			ENGINE REMOVED DUE TO METAL IN OIL.  UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING:  TUBE ASSEMBLY FAILED DIMENSI	ONAL CHECK PER CEB1307. INSTALLED A NEW TUBE.										3	U			E4CE				 
1997022000496	19970220	00496		1997	2	20	HEEA978953       	4	19970129	G	3416	6302	INDICATOR       																	ALTIMETER	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR DOES NOT READ CORRECTLY.  STAYS STUCK INTERMITTENT. SENT TO EDMO DIST. FOR WARRANTY EXCHANGE.																			 
1997022000511	19970220	00511		1997	2	20	HEEA978968       	1	19970129	G	3340	ACR4F	RESCUE LIGHT    																	SWITCH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										LIGHT ON/OFF SWITCH DOES NOT WORK.																			 
1997022700095	19970227	00095		1997	2	27	HEEA979036       	4	19970211	G	3442	MI5853011	INDICATOR       		P500        															COCKPIT RADAR	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WHEN UNIT IS IN WEATHER MODE AND VARIABLE GAIN IS TURNED OUT OF PRESET,  UNIT INTERMITTENTLY SHOWS CYCLE MODE.  WHEN FRO	NT OF INDICATOR (FACEPLATE) IS WIGGLED CYCLE MODE COMES UP IN WEATHER MODE.  ALSO AFTER UNIT HAD BEEN OPERATING FOR APPR	OXIMATELY 20MINUTES THE DISPLAY SHRINKS SLIGHTLY THEN COMES BACK TO PROPER SIZE.  INTERMITTENT.  TIME SINCE REPAIR 0:00.																	 
1997022700104	19970227	00104		1997	2	27	HEEA979047       	4	19970211	G	2312	40001278500	TRANSCEIVER     		RT40        															COCKPIT	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSCEIVER UNIT HAS LOW POWER OUT.																			 
1997030600392	19970306	00392	GL  	1997	3	6	HEEA979119       	2	19970214	G	7230	23033721	BLADES          								ALLSN 	250C  	250C20B     	03013	GL  					NR 1 COMP WHEEL	DAMAGED         	E			HEEA	K				NONE                    				O	C		OTHER                     	F.O.D.                    		IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MINOR F.O.D. AND CORROSION PITS ON #1 COMPRESSOR WHEEL BLADES. PHI REQUESTING 100% WARRA	NTY REPAIR.  PART OVERHAULED ON DALLAS AIRMOTIVE W/O# LF1015.										3	U			E4CE				 
1997030600393	19970306	00393	GL  	1997	3	6	HEEA979120       	2	19970214	G	7250	6892832	SHIELD          								ALLSN 	250C  	250C30P     	03013	GL  					NR 3 NOZZLE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  CRACKES ON #3 NOZZLE SHIELD AS MARKED.											3	U			E1GL				 
1997030600416	19970306	00416	GL  	1997	3	6	HEEA979151       	2	19970226	G	7260	6877171	HOUSING         								ALLSN 	250C  	250C20B     	03013	GL  					GR BOX	BELOW SPECS     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										GEAR BOX HOUSING RECEIVING INSPECTION REVEALED:  MEASURED .0025 BELOW SPECS (3.8490 MIN) ON GEARBOX HOUSING COMPRESSOR M	OUNT STUD AS MARKED.										3	U			E4CE				 
1997031300428	19970313	00428	GL  	1997	3	13	HEEA979158       	2	19970307	G	7260	6877181	HOUSING         								ALLSN 	250C  	250C20      	03013	GL  					GR BOX	BELOW SPECS     	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MEASURED .005 LEFT/.006 RIGHT BELOW SPECS ON GEARBOX HOUSING.  COMPRESSOR MOUNT PAD STUD	S AS MARKED.										3	U			E4CE				 
1997032000342	19970320	00342		1997	3	20	HEEA979166       	4	19970312	G	3452	066106200	TRANSCEIVER     	KING        	KT76        															COCKPIT ATC	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSCEIVER WEAK SENSITIVITY. PERFORMED PRELIMINARY INSPECTION.  REPLACED MIXER DIODE CR202.  REPAIRED PROBLEM.  ADJUSTE	D FREQUENCY AND PULSE WIDTH.  COOKED UNDER HEAT LAMP, VIBRATED AND PUT IN FREEZER.  BENCH CHECK GOOD.																		 
1997032000381	19970320	00381		1997	3	20	HEEA979210       	4	19970312	G	3457	0110005400	GPS 150         	GARMIN      																COCKPIT GPS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										GPS UNIT INOPERATIVE.																			 
1997052200484	19970522	00484		1997	5	22	IC6R298          	4	19970507	G	2350	899927930	SWITCH          		899926930   	BAG   	ATP   	ATP         		EU  										COCKPIT	FAILED          	B	L		IC6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										STATION BOX HAS 18 EACH OF SWITCH P/N 8-9992-693-0.  SWITCH HAS HIGH FAILURE RATE.  FAILURES RESULT IN NOISY AUDIO, LOW 	VOLUME, OR INOPERATIVE SWITCH FOR AUDIO SELECTION.  NEARLY 75 P ERCENT OF STATION BOX REPAIRS REQUIRE REPLACMENT OF AT L	EAST ONE SWITCH. NO ALTERNATE AVAILABLE.  UFS ONLY CARRIER IN USA OPERATING THIS AIRCRAFT.				2	L	7	2 	4T			RT	A27NM   					 
1997111300410	19971113	00410	WP  	1997	11	13	IXXA9700147      	1	19970925	G	5330		SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  										BS 1723	CORRODED        	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, A CORROSION BULGE WAS FOUND BETWEEN FUSELAGE STATIONS 1723 AND 1745, LONGERON 23 LEFT	.  REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF AN  INTERNAL FILLER AND AN EXTERNAL 	REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL 53-2-1.				2	L	7	4 	4F			RT	4A25    					 
1997111300411	19971113	00411	WP  	1997	11	13	IXXA9700148      	1	19970925	G	5320		SPLICE          			DOUG  	DC8   	DC871F      	302199D	WP  										BS 600	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, FOUND LONGERON 31 RIGHT, SPLICE FITTING CRACKED BETWEEN FUSELAGE STATIONS 600 AND 620	.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED FITTING, FABRICATION AND INSTALLATION OF A NEW FITTING IN ACCORDANCE WITH DER 	APPROVED DRAWING 853-373-97 AND ENGINEERING ORDER 3-DC8-578.				2	L	7	4 	4F			RT	4A25    					 
1997111300412	19971113	00412	WP  	1997	11	13	IXXA9700149      	1	19970923	G	5311		FRAME           			DOUG  	DC8   	DC871F      	302199D	WP  										BS 1394	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON THE BELT FRAME AT FUSELAGE STATION 1394, BETWEEN LONGERONS 33 AN	D 36 RIGHT.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND A REPAI	R DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL  REPAIR MANUAL 53-2-0.				2	L	7	4 	4F			RT	4A25    					 
1997111300413	19971113	00413	WP  	1997	11	13	IXXA9700150      	1	19971021	G	5330		PLATING         			DOUG  	DC8   	DC871F      	302199D	WP  										BS 25.5	CORRODED        	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE EXTERNAL PLATING AT FUSELAGE STATION 25.5, BETWEEN LONGERO	NS 31 LEFT AND 31 RIGHT.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLE	R AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 853-395-97 AND ENGINEERING ORDER 53-DC8-593.				2	L	7	4 	4F			RT	4A25    					 
1997111300414	19971113	00414	WP  	1997	11	13	IXXA9700151      	1	19971021	G	5320		DOUBLER         			DOUG  	DC8   	DC871F      	302199D	WP  										BS 10	CORRODED        	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE EXTERNAL FINGER DOUBLER BETWEEN FUSELAGE STATIONS 10 TO 70	, LONGERON 33 RIGHT.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF NEW FINGER DOUBLER IN	 ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL 53-1-0.				2	L	7	4 	4F			RT	4A25    					 
1997112600488	19971126	00488	WP  	1997	11	26	IXXA9700152      	1	19971021	G	5313		LONGERON        			DOUG  	DC8   	DC871F      	302199D	WP  										BS 10	CORRODED        	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON LONGERON 33 RIGHT, BETWEEN FUSELAGE STATIONS 10 TO 70.  REPAIR	 ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION OF LONGERON SECTION IN ACCORDANCE WITH DER APPROVED DRAWING 853-396-9	7 AND ENGINEERING ORDER 53-DC8-594. INSTALLATION IN ACCORDANCE WITH DOUGLAS STRUCTURAL  REPAIR MANUAL.				2	L	7	4 	4F			RT	4A25    					 
1997111300415	19971113	00415	WP  	1997	11	13	IXXA9700153      	1	19971021	G	5347		SEAT TRACK      			DOUG  	DC8   	DC871F      	302199D	WP  										BS 240	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, FOUND SEAT TRACK TO BE CRACKED IN MAIN CARGO COMPARTMENT  BETWEEN FUSELAGE STATIONS 2	40 AND 247, BUTT LINE X-25.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED TRACK, FABRICATION AND INSTALLATION OF NEW SEAT TRAC	K PLUG IN ACCORDANCE WITH ENGINEERING ORDER 53-DC8-580 AND DOUGLAS STRUCTURAL REPAIR MANUAL 53-2-3.				2	L	7	4 	4F			RT	4A25    					 
1997111300416	19971113	00416	WP  	1997	11	13	IXXA9700154      	1	19970924	G	5330		SKIN            			DOUG  	DC8   	DC871F      	302199D	WP  										BS 1766	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX					45994				DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON THE EXTERNAL PLATING AT FUSELAGE STATION 1766, LONGERON 25 RIGHT	.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAI	R DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 853-372-97 AND ENGINEERING ORDER 53-DC8-576.				2	L	7	4 	4F			RT	4A25    					 
1997111300417	19971113	00417	WP  	1997	11	13	IXXA9700155      	1	19970924	G	5320		FITTING         			DOUG  	DC8   	DC871F      	302199D	WP  										BS 1690	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, FOUND LONGERON 23 RIGHT END FITTING CRACKED AT FUSELAGE STATION 1690.  REPAIR ACCOMPL	ISHED REMOVAL OF FITTING, FABRICATION AND INSTALLATION OF A NEW END FITTING IN ACCORDANCE WITH DER APPROVED DRAWING 853-	377-97 AND ENGINEERING ORDER 53-DC8-582.				2	L	7	4 	4F			RT	4A25    					 
1997111300418	19971113	00418	WP  	1997	11	13	IXXA9700156      	1	19970924	G	5730		PLATING         			DOUG  	DC8   	DC871F      	302199D	WP  										LT WING	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, THE LEFT WING LOWER LEADING EDGE PLATING WAS FOUND WITH TWO CRACKS BETWEEN STATIONS X	FS 294 AND 306.  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREAS, FABRICATION AND INSTALLATION OF TWO INTERNAL FILLERS, AND	 TWO EXTERNAL REPAIR DOUBLERS IN ACCORDANCE WITH DER APPROVED DRAWING 857-384-97 AND ENGINEERING ORDER 57-DC8-588.				2	L	7	4 	4F			RT	4A25    					 
1997111300419	19971113	00419	WP  	1997	11	13	IXXA9700157      	1	19971003	G	5730		PLATING         			DOUG  	DC8   	DC871F      	302199D	WP  										LT WING	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON LEFT WING LEADING EXTERNAL PLATING BETWEEN STATIONS 485 AND 558.	  REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR	 DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 857-385-97 AND ENGINEERING ORDER 57-DC8-589.				2	L	7	4 	4F			RT	4A25    					 
1997111300420	19971113	00420	WP  	1997	11	13	IXXA9700158      	1	19971005	G	5240		PAN             			DOUG  	DC8   	DC871F      	302199D	WP  										RT SERVICE DOOR	CRACKED         	A			IXXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	829BX		2636 			45994				DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON RIGHT AFT SERVICE DOOR PAN, LOWER AFT CORNER.  REPAIR ACCOMPLISH	ED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 852	-386-97 AND ENGINEERING ORDER 52-DC8-590.				2	L	7	4 	4F			RT	4A25    					 
1997111300421	19971113	00421	WP  	1997	11	13	IXXA9700159      	1	19971028	G	3230	4771392501	PIN             			DOUG  	DC8   	DC871F      	302199D	WP  										LT MLG	SHEARED         	A			IXXA	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			GL	23	820BX					46065				EN ROUTE DFW TO TOL UPON GEAR RETRACTION, THE LEFT MAIN GEAR DOWN AND LOCK LIGHT REMAINED ILLUMINATED.  THE CREW RECYCLE	D THE LANDING GEAR AND THE INDICATION REMAINED THE SAME.  THE FLIGHT CONTINUED  TO TOL WITH THE LANDING GEAR IN THE DOWN	 AND LOCKED POSITION AND MADE AN UNEVENTFUL LANDING.  MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE LEFT MAIN GEAR RE	TRACT PIN SHEARED.  MAINTENANCE REPLACED THE RETRACT  PIN IN ACCORDANCE WITH DACO MAINTENANCE MANUAL PROCEDURES.			2	L	7	4 	4F			RT	4A25    					 
1997041700501	19970417	00501	NE  	1997	4	17	JYDR970327       	1	19970313	G	6420	6511107001101	SHOULDER BOLT   			SKRSKY	S64   	S64E        	8142604	NE  										T/R	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	CGJZK	1336 			3U97500205	64003				FOUND CRACK IN FIRST TWO THREADS WITH MPI.  FOUND CRACK-LIKE INDICATION ON INNER RACE ABOUT .750 INCH LONG WITH MPI.  CO	MPONENT P/N 6511007000019.  PART MARKINGS:  VENDOR CODE - 81996 - U. S. ARMY AVIATION AND TROOP COMMAND.  THIS IS A BREA	KOUT PART.  (X)				2	G	7	2 	4U				H4EA    					 
1997041700500	19970417	00500	NE  	1997	4	17	JYDR970328       	1	19970317	G	6320	643520536101	MAIN SHAFT      		643520500048	SKRSKY	S64   	S64F        		NE  										LOWER SPLINES	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	163AC	3473 	338  		65	64093				CRACKS FOUND IN LOWER SPLINES.  CRACKS APPEAR TO START IN SPLINE RADIUS AND TRAVEL AT 45 DEGREES TOWARD THE SPLINE TOOTH	.  INDICATIONS ARE ON THE LOAD SIDE JUST AT OR BELOW ENGAGEMENT AREA.  ELEVEN SPLINES WITH INDICATIONS.  LONGEST INDICAT	ION IS 0.150 INCH LONG AND IS APPROXIMATELY 0.6 INCH BELOW THE TOP OF THE LOWER SPLINE.  (X)				2	G	7	2 	4U				H6EA    					 
1997030300001	19970303	00001	NE  	1997	3	3	JZBR14001        	2	19970110	G	7320	5085T40G03	HMU             			AMD   	FALC50	FALCON2000  	2730170	NM  	CFE   		CFE73811B   		NE  					LT ENG	MALFUNCTION     	B		A	JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2FOR	455  			BECH0521	29	P105157			INSTALLED HMU ON ENG FOR TEST AFTER C/W CFE 7388001.  PERFORMED 2 NORMAL STARTS SATISFACTORILY.  THE 3RD START ATTEMPT A	ND SUBSEQUENT ATTEMPTS FAILED.  RE-INSTALLED ORIG HMU AND STARTS WERE NORMAL.					2	K	7	3 	4F	4	F	RT	A50NM   	E44NE				 
1997041500001	19970415	00001	SO  	1997	4	15	JZBR14058        	1	19970329	G	2437	1159AU213123	AMPLIFIER       			GULSTM	G1159 	G1159       	3953505	SO  										BAT MONITOR	FAILED          	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	711RL				391C	25				CREW REPORTED NR 2 BATT AMPMETER FROZE AT 32 AMPS.  TROUBLESHOOTING REVEALED THE BATTERY MONITOR AMP AT FAULT.  REMOVED 	AND REPLACED THE AMPLIFIER WITH A SERVICEABLE UNIT.  PERFORMED A FUNCTIONAL TEST IAW THE MM AND ALL WAS GOOD.  THE FOLLO	WING DAY MAINTENANCE REMOVED AND REPLACED THE MAIN BATTERIES BECAUSE THERE WERE LOANERS ON BOARD.  A BATTERY INTEGRITY C	K WAS ACCOMPLISHED WITH NO DISCREPANCIES.  A FUNCTIONAL TEST OF THE AMP REVEALED THE UNIT HAD FAILED.  THE UNIT WAS REPL	ACED BY ANOTHER SERVICEABLE UNIT.  FUNCTIONAL TEST WAS GOOD AND AIRCRAFT RETURNED TO SERVICE.  NOTE:  NO TRIPS WERE FLOW	N BETWEEN THESE CHANGES.  THIS IS THE SECOND UNIT THAT FAILED FOLLOWING REPAIR BY THE MANUFACTURER.  (X)	2	L	7	2 	4F			RT	A12EA   					 
1997040300308	19970403	00308	EA  	1997	4	3	JZBR14067        	1	19970122	G	3240		KEYWAY          		6008512361  	CNDAIR	CL600 	CL6002B16   	1900305	EA  											MISSING         	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	449ML				SEPT870004	5022				DURING TIRE CHANGE, FOUND SEVERAL KEYWAYS ON BRAKE ASSEMBLY COMING OFF.  RIVETS THAT HOLD KEYWAY TO DISK LOOSE AND MISSI	NG.  BRAKE WEAK.  INDICATOR SHOWED BRAKE TO HAVE WEAR LEFT.  (X)					2	L	7	2 	4F			RT	A21EA   					 
1997051500032	19970515	00032	CE  	1997	5	15	JZBR14404        	1	19970311	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  										LT COCKPIT	SHATTERED       	B			JZBR	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			EA	25	508MV				94278H5429	BB877				LEFT (PILOT) WINDSHIELD SHATTERED DURING CLIMB-OUT AFTER TAKEOFF.  REMOVED AND REPLACED WINDSHIELD IAW MM 56-10-00 AND K	IT 101-5043-1.  ALL CHECKS WERE GOOD.  AIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	4T				A24CE   					 
1999092400159	19990924	00159		1999	9	24	MVH0064147       	4	19970214	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER'S RECEIVE LIGHT IS ON ALL THE TIME, AND UNIT RECEIVES INTERMITTENTLY.						1	G	7	2 	3U				H10EU   					 
1999092400160	19990924	00160		1999	9	24	MVH0064148       	4	19970314	G	3416	396005241	ENCODER         			AEROSP	SA365 	SA365N      	8680669	EU  										ALTIMETER	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5537 				6068				ALTIMETER ENCODING PN 39600-5214 SN 350 WILL NOT ENCODE.						1	G	7	2 	3U				H10EU   					 
1999092400161	19990924	00161		1999	9	24	MVH0064149       	4	19970321	G	2312	4000103000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER UNIT  WILL TRANSMIT FOR A FEW MINUTES, THEN FAILS.						1	G	7	2 	3U				H10EU   					 
1999092400162	19990924	00162		1999	9	24	MVH0064150       	4	19970326	G	2312	CH45202G	CONTROL UNIT    			AEROSP	SA365 	SA365N      	8680669	EU  										COMMUNICATIONS	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	3779 				6068				UNIT LOCKS UP AND WILL NOT TRANSMIT MOSTLY ON FM2.  WILL TRANSMIT AFTER TURNED OFF AND BACK ON.						1	G	7	2 	3U				H10EU   					 
1999092400163	19990924	00163		1999	9	24	MVH0064151       	4	19970326	G	2312	CH460000	CONTROL UNIT    			AEROSP	SA365 	SA365N      	8680669	EU  										COMMUNICATIONS	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	3779 				6068				UNIT LOCKS UP AND WILL NOT TRANSMIT MOSTLY ON FM2.  WILL TRANSMIT AFTER TURNED OFF AND BACK ON.						1	G	7	2 	3U				H10EU   					 
1999092400164	19990924	00164	NE  	1999	9	24	MVH0064152       	2	19970403	G	7321	0164248670	FCU             		ARRIEL1     	AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					ENGINE	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	1345 			2106	6068				FUEL CONTROL INOPERABLE.  HARD STARTS AND HOT STARTS FIRST START OF THE DAY.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400165	19990924	00165	EU  	1999	9	24	MVH0064153       	1	19970408	G	7714	9580115900	SENSOR          		ARRIEL1     	AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					OVERSPEED	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	1345 			2106	6068	2203			OVERSPEED FAIL LIGHT ILLUMINATES INTERMITTENTLY.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400166	19990924	00166		1999	9	24	MVH0064157       	4	19970425	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 WILL NOT TRANSMIT.						1	G	7	2 	3U				H10EU   					 
1999092400167	19990924	00167	NE  	1999	9	24	MVH0064158       	2	19970512	G	7321	0164248670	FCU             			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					ENGINE	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	422  				6068	2060			FUEL CONTROL INOPERATIVE.  SLOW STARTS AND FLUCTUATING RPM.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400168	19990924	00168	EU  	1999	9	24	MVH0064159       	1	19970512	G	7712	9580113720	TRANSMITTER     			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					TORQUE	NOT CALIBRATED  	H			BAQA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	63CF	564  				6068	2060			TRANSMITTER CALIBRATED IMPROPERLY.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400169	19990924	00169	NE  	1999	9	24	MVH0064160       	2	19970512	G	7200	AR1C	ENGINE          			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					ENGINE BAY	MAKING METAL    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	1936 				6068	2060			ENGINE MAKING METAL AND MODULE 3 DUE TBO.						1	G	7	2 	3U	3	U		H10EU   	E19EU				 
1999092400170	19990924	00170	EU  	1999	9	24	MVH0064168       	1	19970723	G	7931	53408A	TRANSMITTER     			AEROSP	SA365 	SA365N      	8680669	EU  										ENG OIL PRESS	INACCURATE      	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	689  				6068				PRESSURE TRANSMITTER READS 5 BAR WHEN POWER IS ON AND GOES UP FROM THERE.						1	G	7	2 	3U				H10EU   					 
1999092400171	19990924	00171		1999	9	24	MVH0064174       	4	19971028	G	3457	80823000312	GPS             			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	INOPERATIVE     	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				RECEIVED LOANER TNL3000 TRIED TO INSTALL IN A/C.  DISPLAY INDICATED GPS PORTION INOPERABLE.						1	G	7	2 	3U				H10EU   					 
1999092400172	19990924	00172		1999	9	24	MVH0064177       	4	19971112	G	3421	H140CAM1	GYRO            			AEROSP	SA365 	SA365N      	8680669	EU  										ATTITUDE	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				INSTALLED OVERHAULED ATTITUDE INDICATOR.  WITHIN 5 HOURS, UNIT SHOWED SIGNS OF BEING UNSTABLE IN-FLIGHT SUCH AS AUTOPILO	T WOULD NOT STAY ENGAGED; THEN, INDICATOR GOT WORSE AND NOW WILL ROLL OVER IN-FLIGHT.					1	G	7	2 	3U				H10EU   					 
1999092400173	19990924	00173	EU  	1999	9	24	MVH0064178       	1	19971118	G	6730	80321	SERVO           			AEROSP	SA365 	SA365N      	8680669	EU  										MAIN ROTOR	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	4003 				6068				REMOVED FOR SERVO JAM LIGHT INOPERATIVE.						1	G	7	2 	3U				H10EU   					 
1999092400174	19990924	00174		1999	9	24	MVH0064181       	4	19971216	G	2312	4000102000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	MISREPAIRED     	H			BAQA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER INSTALLED IN AIRCRAFT.  ON FIRST FLIGHT, TONES WOULD NOT OPEN AND TRANSMIT WAS BROKEN AND GARBLED.						1	G	7	2 	3U				H10EU   					 
1999092400175	19990924	00175		1999	9	24	MVH0064182       	4	19971231	G	2312	40001452502	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER HAD BROKEN RECEPTION.						1	G	7	2 	3U				H10EU   					 
1999092400176	19990924	00176	EU  	1999	9	24	MVH0064183       	1	19971231	G	3213	1801510001	STRUT           			AEROSP	SA365 	SA365N      	8680669	EU  										MLG	RATCHETS        	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	6127 				6068				STRUT LEAKING AT SHAFT AND RATCHETS.						1	G	7	2 	3U				H10EU   					 
1999092400195	19990924	00195	EU  	1999	9	24	MVH0064268       	1	19970424	G	2420	353Y0314	SENSOR          			AEROSP	SA365 	SA365N      	8680669	EU  										AC SYSTEM	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				INVERTER LIGHT ILLUMINATES OCCASIONALLY.  REMOVED AND REPLACED 115 VOLT SENSOR.						1	G	7	2 	3U				H10EU   					 
1999092400196	19990924	00196	EU  	1999	9	24	MVH0064269       	1	19970512	G	7921	RH2125	OIL COOLER      			AEROSP	SA365 	SA365N      	8680669	EU  										ENGINE	CONTAMINATED    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	5824 				6068				OIL COOLER - METAL, CONTAMINATED, REQUIRED FLUSHING AND RECERTIFICATION.						1	G	7	2 	3U				H10EU   					 
1999092400197	19990924	00197	EU  	1999	9	24	MVH0064278       	1	19971009	G	6300	704A33651118	BEARING         		365A31000204	AEROSP	SA365 	SA365N      	8680669	EU  										M/R DRIVE	CONTAMINATED    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	698  			981	6068				REMOVED DUE SUSPECTED WEAR AND METAL CONTAMINATION.  REMOVED AND REPLACED WITH NEW BEARING.						1	G	7	2 	3U				H10EU   					 
1999092400198	19990924	00198	EU  	1999	9	24	MVH0064279       	1	19971009	G	6210	365A31177120	PIN             		365A31001202	AEROSP	SA365 	SA365N      	8680669	EU  										M/R BLADE	CORRODED        	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	2465 			579	6068				REMOVED BLADE PINS SN'S M10720, M9864, M10730, M10306, M10171, M10137, 8044, M9266  DUE TO CORROSION.  INSTALLED NEW PIN	S SN'S M3081, M3020, M3023, M3024, M3025, M3039, M3187, M3227.					1	G	7	2 	3U				H10EU   					 
1997052200376	19970522	00376	NE  	1997	5	22	PCAA9700363      	2	19970409	G	7261		OIL SYSTEM      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					NR 1 ENGINE	MALFUNCTION     	E			PCAA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	13	818EX					235	120448			OIL SYSTEM MALFUNCTION						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
1997042400024	19970424	00024	EU  	1997	4	24	SADF9700002      	1	19970402	G	5240	HC38370010003	SERVICE DOOR    			BAC   	146   	AVRO146RJ100	1500096	EU  										LAV SERVICE	OUT OF PLACE    	A		A	SADF	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SO	23	511MM	4881 				E3255				ADZ/BOG - FLT 503 - DURING FLIGHT FROM ADZ/BOG, PILOTS EXPERIENCED PRESSURIZATION PROBLEMS WITH FLUCTUATIONS AND CABIN A	LTITUDE CONTROL PROBLEMS.  FLIGHT DIVERTED TO PTY, LANDED WITHOUT FURTHER INCIDENT.  (X)					2	H	7	4 	4F			RT	A49EU   					 
1997121100120	19971211	00120	EU  	1997	12	11	SADF9706         	1	19971103	G	3230	HTE210014	VALVE ACTUATOR  			BAC   	146   	AVRO146RJ100	1500096	EU  										GEAR SELECTOR	FAILED          	A			SADF	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	23	504NM	6582 			391GB450	E3221				AFTER DEPARTURE, LANDING GEAR DID NOT GO UP.  IT REMAINED DOWN.  FLT 396 AIR TURN-BACK TO BOGOTA.  LANDING GEAR ELECTRIC	 ACTUATOR OF SELECTOR VALVE WAS REPLACED IAW MM.					2	H	7	4 	4F			RT	A49EU   					 
1997071000275	19970710	00275	NE  	1997	7	10	SI3R97003        	2	19970605	G	7210	7757571	BEARING         		6044T35P01  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					GC49 GEARBOX	SPALLED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		22234			5200		GEE367288			CHIP DETECTOR WAS SHOWING HEAVY CHIP CONTAMINATION.  DISASSEMBLY OF GEAR CASE REVEALED THE PROPELLER SHAFT FORWARD ROLLE	R BEARING ROLLERS (GROUP 5 FIG 7 ITEM 60 IN CMM 72-11-02) WERE SPALLED.  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
1997071000274	19970710	00274	NE  	1997	7	10	SI3R97005        	2	19970617	G	7322	35853CNX285	INSERT          								PWA   	JT8   	JT8*        	52044	NE  					FUEL CONTROL	WORN            	B	L		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		18154	3477 							"FUEL LEAK NR 2 ENGINE AS OBSERVED BY ANOTHER AIRCRAFT WHILE TAXIING'.  THE LEAK WAS CONFIRMED.  OF THE 3 BOLTS THAT HOL	D TEMPERATURE COMPENSATING BELLOWS ASSY TO MAIN HOUSING, 1 WAS MISSING, AND THE OTHER 2 HAD LOOSENED.  THIS ALLOWED FLAN	GE SEAL TO EXTRUDE OUT OF ITS GROOVE, AND FUEL TO LEAK PAST.  THE ROOT CAUSE IS THE LOCKING FEATURE OF THE INSERTS HAD W	ORN BELOW THE MINIMUM OF 2 INCH/POUND RUNNING TORQUE.  THIS OVERHAUL AND REPAIR STATION PERFORMS MAINTENANCE ON THESE FU	EL CONTROLS, AND HAS INSTITUTED A MANDATORY CHECK OF THE RUNNING TORQUE OF THESE INSERTS.  THIS BOLT AND LOCKING INSERT 	FASTENING SYSTEM IS COMMON TO ALL JFC60 MODELS.  (X)						4	F			E2EA				 
1997091100319	19970911	00319	NE  	1997	9	11	SI3R97006        	2	19970815	G	7210	7757706	RETAIN NUT      	HAMSTD      	5074T51G10  	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 DRIVE GEAR	LOST TORQUE     	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		9770 			1H100173		GEE785524			DURING DISASSEMBLY OF GEARBOX, RETAINING NUT (P/N 775770-6) WAS REMOVED WITH NO OBTAINABLE TORQUE READING USING TORQUE F	IXTURE.  HSS SO NR 62971SE.  CUST:  WINGS WEST  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997120300023	19971203	00023	NE  	1997	12	3	SI3R97007        	2	19970819	G	7210	7757602	BEARING         	HAMSTD      	6044T35P10  	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 IDLER GEAR	SPALLED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		12767			8158		GEE786268			DURING DISASSEMBLY OF GEARBOX, THE RIGHT FORWARD IDLER GEAR BEARING RACE AND ROLLERS WERE FOUND TO BE SPALLED.  (P/N 775	660-2, FIG 8, ITEM 85).  HSS SO NR 63470SE.  CUST:  FLAGSHIP A/L.  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997091100318	19970911	00318	NE  	1997	9	11	SI3R97008        	2	19970909	G	7210	7757612	BEARING         		6044T33TP11 	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79C       	30030	NE  					GC 49 GEARCASE	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		8809 			8292		GEE309111			DISASSEMBLY OF CASE REVEALED EXTENSIVE INTERNAL DAMAGE.  CONDITIONS ARE NOT REPAIRABLE; THUS, THIS GEAR CASE IS CONSIDER	ED SCRAP.  INITIAL EVALUATION OF HARDWARE FINDS POSSIBLE INITIAL BREAKDOWN DUE TO RIGHT IDLER AFT BEARING FAILURE, PN 77	5761-2.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997110600868	19971106	00868	NE  	1997	11	6	SI3R97009        	2	19971009	G	7210	7895781	TAB WASHER      	HAMSTD      	5074T51G11  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC49 GEAR CASE	BROKEN          	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		2448 			1H100038		GEE309179			DISASSEMBLY OF GEAR CASE REVEALED RIGHT IDLER GEAR FORWARD TAB WASHER WAS BROKEN AND CRACKED (PN 789578-1, ITEM 65B, FIG	 1A).  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997110600869	19971106	00869	NE  	1997	11	6	SI3R97010        	2	19971009	G	7210	7757571	ROLLER BEARING  	HAMSTD      	644T35P10   	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC49 GEAR CASE	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13874			UDAG0638		GEE785436			DISASSEMBLY OF GEAR CASE REVEALED FORWARD ROLLER BEARING INNER RACE CRACKED (PN 775757-1, ITEM 60, FIG 7).  (X)						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997110600867	19971106	00867	NE  	1997	11	6	SI3R97011        	2	19971024	G	7210	7757571	ROLLER BEARING  	HAMSTD      	6044T35P02  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					GC49 GEAR CASE	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		23078			0208		GEE367319			DISASSEMBLY OF GEAR CASE REVEALED THE FORWARD ROLLER BEARING INNER RACE CRACKED (PN 775757-1, ITEM 60 FIG 7).  (X)						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6				 
1997110700008	19971107	00008	NE  	1997	11	7	SI3R97012        	2	19971024	G	7210	7757651	ROLLER BEARING  	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC49 GEAR CASE	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13407			UDAG083		GEE785379			DISASSEMBLY OF GEAR CASE REVEALED THE INPUT ROLLER BEARING RACE CRACKED, PINION GEAR BEARING SURFACE SPALLED, LEFT AND R	IGHT IDLER GEAR RETAINING RINGS BROKE, AND NO TORQUE ON LEFT IDLER GEAR NUT.  PINION, SN IC641356.  INPUT BEARING, SN 9-	259.  REF:  OPERATOR CONTROL NR 97ZZZX4682, 97ZZZX4683, AND 97ZZZX4684.  (X)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997122400027	19971224	00027	NE  	1997	12	24	SI3R97014        	2	19971130	G	7210	7757571	BEARING         		5074T51G10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARCASE	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		14625					GEE785213			UPON DISASSEMBLY OF GEARBOX, FOUND CRACKED INNER RACE ON THE FORWARD ROLLER BEARING (PN 775757-1 ITEM 60 FIG 7).  (X)						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
1997092500278	19970925	00278	SO  	1997	9	25	XC4R4848         	1	19970915	G	2121	T600069	PC BOARD        	TECHNOFAN   	AE1711AA0   	EMB   	120   	EMB120RT    		SO  										GROUND COOLING	LOOSE JOINTS    	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		5106 			29					FAN INOPERATIVE AS RECEIVED.  UPON INSPECTION, FOUND ALL COMPONENTS ON DRIVER P.C. BOARD LOOSE.  SOLDER JOINTS OVERHEATE	D.  THIS FAN IS MANUFACTURED IN FRANCE AND IS AN ALLEGED PRODUCT IMPROVEMENT, SAME PROBLEMS AS OLD P/N EVAC2322 FAN ASSE	MBLY.  (X)				2	L	7	2 	4T			RT	A31SO   					 
1997100900173	19971009	00173	SO  	1997	10	9	XC4R4853         	1	19970919	G	2121	T600069	PC BOARD        	TECHNOFAN   	AE1711AA0   	EMB   	120   	EMB120RT    		SO  										GROUND COOL FAN	LOOSE           	B			XC4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19		3701 			100					FAN INOPERATIVE AS RECEIVED.  INSPECTION FOUND ALL DRIVER P.C. BOARD SOLDER JOINTS LOOSE AND DEFECTIVE.  THIS FAN IS MAN	UFACTURED IN FRANCE. THIS REPAIR STATION HAS WITNESSED PREVIOUSLY THE SAME FAULTS ON SAME PART NUMBERED FAN.  (X)					2	L	7	2 	4T			RT	A31SO   					 
1997082800012	19970828	00012	SO  	1997	8	28	XC4R643M         	1	19970806	G	3242	2445902	DISK            	BFGOODRICH  	21585       	EMB   	120   	EMB120RT    		SO  										NR 1 BRAKE	WORN            	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			2788 							NR 1 ROTATING DISK BROKEN AND MISSING.  OTHER ROTATING DISKS AND WEAR PADS OKAY.  WEAR PIN INDICATES 90 PERCENT WORN.  P	ACKINGS AND RETAINERS SHOW NORMAL WEAR.  NO OTHER DAMAGE NOTED.  SUBMITTER STATED HAVE WITNESSED THE OLD P/N BRAKE ASSEM	BLY 2-1479 HAVE THE SAME FAILURE.  THE NEW P/N BRAKE IS NO IMPROVEMENT.				2	L	7	2 	4T			RT	A31SO   					 
1997121100132	19971211	00132	SO  	1997	12	11	XC4R6637         	1	19971124	G	3242	44667	DISC            	BFGOODRICH  	21585       	EMB   	120   	EMB120      	3260201	SO  										NR 3	BROKEN          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		2138 			0076					UPON RECEIPT OF BRAKE ASSEMBLY FOR OVERHAUL, NR 3 CARRIER LINING WAS FOUND BROKEN IN THREE PIECES.  SUBMITTER STATES NUM	EROUS PROBLEMS WITH THIS BRAKE ASSEMBLY.					2	L	7	2 	4T			RT	A31SO   					 
1997032700293	19970327	00293	SO  	1997	3	27	XC4R9720736      	1	19970208	G	2435	230801971	BRUSH           	LUCAS       	23080013    	EMB   	120   	EMB120ER    	3260203	SO  										START/GEN	FAILED          	B		A	XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	296SW	277  			96384	120325				START/GEN BRUSHES FAILED AFTER 277.0 HOURS OF FLIGHT TIME.  THE BRUSH SHUNT LEADS WERE BURNED AND BROKEN OFF.  THIS WAS 	A NEW AIRCRAFT, THIS WAS A NEW STARTER GENERATOR WITH ONLY 277.0 HOURS SINCE NEW.  SUBMITTER RECOMMENDS RE-DESIGNING DEF	ECTIVE BRUSHES.  NOTE:  THIS REPAIR STATION HAS SEEN MANY OF THESE BRUSH FAILURES IN THE PAST.  (X)				2	L	7	2 	4T			RT	A31SO   					 
1997062600276	19970626	00276	EU  	1997	6	26	XC4R9752683      	1	19970519	G	2421	31342350	ROTOR           		31342001    	SAAB  	SF340 	SF340A      	7850100	EU  										AC GENERATOR	FAILED          	B		A	XC4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19			1859 		579					THIS UNIT SUFFERED A MAIN ROTOR BAND FAILURE DURING OPERATION.  ONE EACH OF 2 MAIN ROTOR BANDS DETACHED DURING OPERATION	 CAUSING EXTENSIVE DAMAGE TO THE ROTOR, EXCITER STATOR, AND MAIN STATOR.  THIS FAILURE OCCURRED DURING NORMAL OPERATING 	CONDITIONS.  SUBMITTER STATED THIS FACILITY HAS SEEN NUMEROUS FAILURES SIMILAR TO THIS ONE.  RECOMMEND REPLACMENT OF STA	INLESS BANDS WITH SOLID RINGS OF ALUMINUM.  (X)			2	L	7	2 	4T			RT	A52EU   					 
1997071700625	19970717	00625	SO  	1997	7	17	XC4R9763186      	1	19970612	G	3240	2662011	PISTON HOUSING  	BFGOODRICH  		EMB   	120   	EMB120RT    		SO  										BRAKE ASSY	DEFECTIVE       	B			XC4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19		1527 			0051					BRAKE ASEMBLY RECEIVED FOR FIRST OVERHAUL WITH INCORRECT LUB TORQUE ON HOUSING 450-470 POUND/INCH, BY B.F.G.  SHOULD BE 	215-225 POUND/INCH .  B.F.G. WAS NOTIFIED AND PART IS TO BE SENT TO B.F.G. FOR INSPECTION AND TO RECTIFY THE FACTORY ERR	OR.  PART TT SINCE NEW, 1,526.6 HOURS.  (X)				2	L	7	2 	4T			RT	A31SO   					 
1997071700626	19970717	00626	SO  	1997	7	17	XCR9763120       	1	19970612	G	3242	244608	ROTATING DISK   	BFGOODRICH  	214791      	EMB   	120   	EMB120ER    	3260203	SO  										BRAKE ASSY	BROKEN          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	234SW	926  			1656	120300				RECEIVED  BRAKE ASSEMBLY FOR OVERHAUL.  VISUAL INSPECTION REVEALS ONE EACH ROTATING DISK BROKEN IN HALF.						2	L	7	2 	4T			RT	A31SO