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
2003111300042	20031113	00042	CE  	2003	11	13	001020           	1	20001020	G	3230	1153800025	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	SLOW            	B			R3R2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	7166P									UPON INSTALLATION OF THIS NEWLY OVERHAULED LANDING GEAR RETACT MOTOR THE LANDING GEAR WOULD CYCLE AT ABOUT HALF NORMAL S	PEED.  ALL MECHANICAL AND ELECTRICAL SYSTEMS CHECKED GOOD.   INSTALLED A NEW RETRACT MOTOR AND ALL SYSTEMS OPERATED NORM	ALLY.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000121500182	20001215	00182	CE  	2000	12	15	010304           	1	20001204	G	5730	MS24694C51	SCREW           			CESSNA	500   	550         	2076604	CE  										BOTH WINGS	OVERSIZED       	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6775C					5500677				LEFT WING AND RIGHT WING LEADING EDGE SKIN HAS BEEN CHAFED BY THE UPPER SCREW OF THE OUTBOARD ROW OF SCREWS ATTACHING TH	E HEATED LEADING EDGE TO THE WING.  THE SCREWS INSTALLED WERE TOO LONG, ALTHOUGH THEY WERE THE ONES CALLED FOR IN THE PA	RTS CATALOG.  THEY CHAFED INTO THE WING LEADING EDGE SKIN ABOUT 0.024 INCH DEEP INTO THE LEFT WING AND 0.018 INCH INTO T	HE RIGHT WING.  THE SKIN IS 0.040 INCH ALUMINUM.  CESSNA HAS APPROVED A SHORTER SCREW TO BE INSTALLED AND IS CURRENTLY W	ORKING ON A PERMANENT REPAIR.  (X)		1	L	7	2 	4F			 	A22CE   					 
2000040400458	20000404	00458	EA  	2000	4	4	20000328SH001    	2	20000321	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NOSE	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		DE	DESCENT        	1			SW	99	9559D	724  				17280488	L2757151A			ENGINE RAN ROUGH AND ALMOST SHUT DOWN DURING DESCENT.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000042600035	20000426	00035	EA  	2000	4	26	20000328SH002    	1	20000222	G	5720	219672	SUPPORT BRACKET 	AC          		DHAV  	DHC2  	DHC2*       	2800108	EA  										WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27										BRAND NEW TANK SUPPORTS HAVE BEEN FOUND TO BE CRACKED ALONG THE BEND RADIUS WHERE THE ALUMINUM HAS BEEN COLD-FORMED, CLO	SE TO THE TANK STRAP CLEVIS PEN HOLES.  THIS PROBLEM HAS ALSO BEEN FOUND ON PARTS WITH TIME IN SERVICE, AND THE CRACKS P	ROGRESS WITH USE.  (X)				1	H	7	1 	3R			 	A806    					 
2000040400459	20000404	00459	CE  	2000	4	4	20000328SH003    	1	20000131	G	2750	12957Y	CONTROL CABLE   			BEECH 	60    	B60         	1153605	CE  										TE FLAP	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	341D	794  				P397				CABLE WITH A TWIST TEST OF THE CABLE END SIMILAR TO THE DUKES CABLES ON THE PIPER PA31 FLAP SYSTEMS.  (X)						1	L	7	2 	3O			 	A12CE   					 
2000042500033	20000425	00033	CE  	2000	4	25	20000328SH004    	1	20000302	G	3250	S18233	ROD END         			CESSNA	172   	172R        	2072401	CE  										STEERING COLLAR	SHEARED         	G			DJXS	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	922TA	1013 				17280249				BEARING ROD END THAT ATTACHES STEERING BUNGEE TO STEERING COLLAR SHEARED AT PREVIOUS CRACK AT THE FIRST THREAD.  SUBMITT	ER STATED MAY HAVE HAPPENED AS A RESULT OF ACCIDENT RATHER THAN CAUSE. (X)					1	H	7	1 	3O			NT	3A12    					 
2000032800004	20000328	00004	SO  	2000	3	28	20000328SH005    	1	20000303	G	2750	573801	VALVE           			GULSTM	G1159 	GIV         	3980115	SO  										TE FLAP	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	250VC	3648 				1231				FLAP ACTUATION SLUGGISH WITH ENGINE RUNNING.  WOULD NOT OPERATE USING AUXILIARY SYSTEM.  FOUND FLAP SELECTOR VALVE INTER	NAL SPOOL ACCESS CAP HAD NEVER BEEN SAFETIED (NO SAFETY WIRE MARKS ON UNIT) AND HAD BACKED OUT 3 TURNS.  REPLACED SELECT	OR VALVE (REPLACEMENT UNIT WAS SAFETIED WITH LEAD SEAL).  OPERATION NORMAL.  (X)				2	L	7	2 	4F			RT	A12EA   					 
2000042500034	20000425	00034	CE  	2000	4	25	20000328SH006    	1	20000224	G	2422	2C25001ECM1203	INVERTER        			CESSNA	208   	208B        	2073701	CE  										ELECTRICAL	FAILED          	B			QY5R	D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NE	01	9820F					208B0410				WHILE ON A DATA GATHERING NIGHT FLIGHT.  THE EQUIPMENT POWERED BY THE INVERTER LOST POWER.  WHILE REACHING FOR THE POWER	 DISCONNECT SWITCH, A FLASH WAS NOTICED IN THE AREA IN WHICH THE INVERTER WAS INSTALLED.  POWER TO THE INVERTER WAS CUT 	OFF AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. (X)				1	H	7	1 	3T			 	A37CE   					 
2000040400460	20000404	00460	CE  	2000	4	4	20000328SH007    	1	20000228	G	2510	05142251	SEAT            			CESSNA	172   	172R        	2072401	CE  										COCKPIT	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	405ER	2285 				17280285				REFERENCE DRAWING 0514222 (SEAT BACK ASSY, AFT BENCH 172) VIEWING THE -1 SEAT BACK ASSY.  AT THE LOWER RIGHT HAND CORNER	 OF THE SEAT BACK THRE IS A -11 FRAME END THAT WELDS TO THE -4 FRAME UPPER.  THE WELD IS APPROXIMATELY 7.30 INCHES UP FR	OM THE BOTTOM OF THE -11 FRAME END.  APPROXIMATELY .75 INCH BELOW THIS WELD JOINT THE SEAT BACK HAS BROKE IN HALF.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000032800007	20000328	00007	EU  	2000	3	28	20000328SH011    	1	20000115	G	5610	4AS3430000501	WINDSHIELD      			ISRAEL	GALAXY	GALAXY      	4500307	EU  										COCKPIT	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	505GA	654  				005				THE PILOT''S WINDSHIELD (INNER PANE) SHATTERED AT FL 430.  AT THIS TIME THERE IS NO POSSIBLE CAUSE.  THE WINDSHIELD IS B	EING SHIPPED TO THE MANUFACTURER TO DETERMINE CAUSE.  (X)					2	L	7	2 	4F			RT	A53NM   					 
2000040400463	20000404	00463	WP  	2000	4	4	20000328SH012    	2	20000120	G	7200	30755141	SEAL            								GARRTT	TFE731	TFE7315R    	01518	WP  					ENGINE	LEAKING         	B			U02R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19		1946 					P91165			ENGINE EXPERIENCED IN-FLIGHT SHUT DOWN BY HIGH GEARBOX PRESSURE WHICH EXPANDED OIL TANK AND CREATED HOLE IN OIL TANK AT 	A SPOT WELD DUE TO HIGH GEARBOX PRESSURE.  ENGINE LOST OIL PRESSURE AND WAS SHUT DOWN BY PILOT.  (X)										4	F			E6WE				 
2000040400464	20000404	00464	SW  	2000	4	4	20000328SH013    	1	20000203	G	3230	AN423A	BOLT            			GULSTM	112   	114ARKWELL  	7630315	SW  										MLG	CRACKED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	5923N					14540				UPON LANDING AIRCRAFT, PILOT NOTED RT MAIN LANDING GEAR FELT MUSHY.  VISUAL INSPECTION OF PARKED AIRCRAFT YIELDED THE RT	 MAIN LANDING GEAR FORWARD TRUNNION BOLT WASHER AND NUT WERE MISSING DUE TO THE BOLT SHEARING.  AS A PREVENTATIVE MEASUR	E, THE LT SIDE BOLT WAS REMOVED AND FOUND SIGNS OF EXTREME WEAR, AND WAS REPLACED.  CURRENTLY, THERE ARE NO AIRWORTHINES	S DIRECTIVES OR SERVICE BULLETINS ADDRESSING THIS BOLT.  SUBMITTER STATED THIS BOLT SHOULD BE A TIME REPLACEMENT PART OF	 3-5 YEARS OF 500 LANDINGS.  (X)		1	L	7	1 	3O			 	A12SO   					 
2000040400465	20000404	00465	NE  	2000	4	4	20000328SH014    	2	20000201	G	7200	30756441	SEAL            								GARRTT	TFE731	TFE73121C   	 	NE  					ENGINE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19							P73466			ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND NR NR 5 SEALS AND RUNNE	RS.  (X)										4	F			E6WE				 
2000040400466	20000404	00466	NE  	2000	4	4	20000328SH015    	2	20000201	G	7200	30756392	SEAL            								GARRTT	TFE731	TFE73121C   	 	NE  					ENGINE	LEAKING         	B			UO2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19							P73466			ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND AND NEW NR 5 SEALS AND 	RUNNERS.  (X)										4	F			E6WE				 
2000040400467	20000404	00467	NE  	2000	4	4	20000328SH016    	2	20000201	G	7200	30756332	SEAL            								GARRTT	TFE731	TFE73121C   	 	NE  					ENGINE	LEAKING         	B			UO2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19							P73466			ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND NR 5 SEALS AND RUNNERS.	  (X)										4	F			E6WE				 
2000040400468	20000404	00468	NE  	2000	4	4	20000328SH017    	2	20000201	G	7200	30756451	SEAL            								GARRTT	TFE731	TFE73121C   	 	NE  					ENGINE	LEAKING         	B			UO2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19							P73466			ENGINE EXPERIENCED HIGH GEARBOX PRESSURE AT TEST CELL AFTER ENGINE CORE REPAIR WITH NEW NR 4 AND NEW NR 5 SEALS AND RUNN	ERS.  (X)										4	F			E6WE				 
2000040400470	20000404	00470	EA  	2000	4	4	20000328SH020    	2	20000208	G	8530	65007	RETAINER SEAL   			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR 1 CYLINDER	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	3935H		2006 			240982				DURING ANNUAL INSPECTION, DISCOVERED NR 1 CYLINDER EXHAUST PUSH ROD TUBE SEAL AREA AT CASE HALF RETAINER PROTRUDING AT A	N ANGLE.  REMOVED NR 1 EXHAUST PUSH ROD, FOUND LIFTER BODY CRACKED, AND BROKEN.  LIFTER WILL NOT COME OUT.  SUBMITTER SU	SPECTED CAUSE WAS STUCK EXHAUST VALVE AT SOME TIME.  ENGINE IS AT TBO AND WILL BE REPLACED.  (X)				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2000032900439	20000329	00439	CE  	2000	3	29	20000329SH001    	1	20000211	G	2731		JACKSCREW       			LEAR  	35    	35A         	5170602	CE  										STABILIZER	GALLED          	H				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			NM	09	573LP		501  		171	658				CREW BEGAN TO DESCEND OUT OF CRUISE, AIRCRAFT BECAME NOSE HEAVY.  THE CREW COULD NOT TRIM AIRCRAFT STABILIZER AS BOTH PR	IMARY AND SECONDARY PORTIONS OF THE STAB ACTUATOR FUNCTIONALLY FAILED.  THIS UNIT HAD APPROXIMATELY 500 HOURS ON IT SINC	E ITS 12,000 HOUR INSPECTION.  POSSIBLE CAUSE WOULD BE FAILURE OF A STAB ACTUATOR COMPONENT COMMON TO BOTH PRIMARY AND S	ECONDARY MOTORS, POSSIBLY A GALLED JACK SCREW ASSEMBLY.  TEAR DOWN REPORT CONFIRMED A GALLED JACK SCREW ASSEMBLY.  SUBMI	TTER RECOMMENDED CHANGE IN JACK SCREW DESIGN TO INCREASE SURFACE AREA OF SCREW ASSEMBLY THEREBY REDUCING THE CONTACT SUR	FACE LOADING ON THE SCREW ASSEMBLY.  (X)	2	L	7	2 	4F			 	A10CE   					 
2000040400471	20000404	00471	CE  	2000	4	4	20000329SH002    	1	20000217	G	5347	1210520	SEAT TRACK      			CESSNA	210   	210L        	2073448	CE  										FUSELAGE	MISINSTALLED    	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	5035V					21060823				DURING AIRCRAFT INSPECTION, FOUND SEAT TRACKS NOT FASTENED TO AIRCRAFT STRUCTURE BELOW FLOOR AND IMPROPER FASTENERS SECU	RING SEAT TRACKS.  CONTACTED CESSNA TECH SUPPORT TO OBTAIN PROPER INSTALLATION INSTRUCTIONS AND REINSTALLED SEAT TRACKS 	PROPERLY.  SEAT TRACKS ARE MAJOR STRUCTURE AND NEED TO BE INSTALLED PROPERLY FOR CRUSHWORTHINESS.  (X)				1	H	7	1 	3O			 	3A21    					 
2000040400472	20000404	00472	CE  	2000	4	4	20000329SH003    	1	20000209	G	2750	503801531	JACKSCREW       			BEECH 	99    	99          	1154002	CE  										TE FLAP	WRONG PART      	B			TIMR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	07	199GL				825B98	U15				DURING REPLACEMENT OF FLAP ACTUATORS, LEFT INBOARD FLAP MOVED IN THE OPPOSITE DIRECTION OF FLAP SELECTOR POSITION.  REMO	VED FLAP ACTUATOR AND DETERMINED THAT DRIVE ASSEMBLY WAS INCORRECT FOR INBOARD ACTUATOR.  (X)					1	L	7	2 	3T			 	A14CE   					 
2000040400473	20000404	00473	EA  	2000	4	4	20000329SH004    	2	20000214	G	7322	55018010	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					AIRBOX	CONTAMINATED    	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	27	5259R	3706 				17263473				A ROUGH RUNNING ENGINE, AND A LOSS OF ENGINE POWER (MAXIMUM RPM 2200) CAUSED  PILOT TO MAKE A PRECAUTIONARY LANDING.  TE	CHNICIAN INSPECTED THE INDUCTION SYSTEM AND FOUND THE CARBURETOR HEAT AIR VALVE SEAL MATERIAL HAD SEPARATED AND WAS INGE	STED BECOMING LODGED ACROSS THE CARBURETOR VENTURI.  THIS DISRUPTION OF AIR FLOW THROUGH THE VENTURI CAUSED IMPROPER FUE	L/AIR MIXTURE AND FUEL SCHEDULING RESULTING IN A LOSS OF POWER.  THIS PART HAD NOT BEEN CHANGED SINCE MANUFACTURE OF AIR	CRAFT 25 YEARS AGO.  TOTAL TIME ON AIRCRAFT 3,706.0 HOURS.  RECOMMENDATION:  MORE FREQUENT INSPECTIONS OF CARBURETOR AIR	 BOX ASSEMBLY FOR WEAR AND DETERIORATION AND TOTAL TIME IN SERVICE.  (X)	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000040400474	20000404	00474	EA  	2000	4	4	20000329SH005    	2	20000217	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DIRTY           	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99	477ER	1062 				17280622	L2803951A			DURING FLIGHT, THE PILOT REPORTED ROUGH ENGINE OPERATION FOR SEVERAL SECONDS.  THE SPARK PLUGS WERE SERVICED.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040400475	20000404	00475	EA  	2000	4	4	20000329SH006    	2	20000217	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DIRTY           	H				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	417ER	1903 				17280305	L2727851A			DURING FLIGHT, PILOT REPORTED ROUGH ENGINE OPERATION FOR A FEW SECONDS.  THE INJECTOR NOZZLES WERE CLEANED, THE SPARK PL	UGS WERE SERVICED, AND THE ELECTRIC BOOST PUMP WAS REPLACED.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040400476	20000404	00476	EA  	2000	4	4	20000329SH007    	2	20000217	G	7320		FLOW DIVIDER    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99	460ER					17280668	L2786851A			DURING FLIGHT, THE PILOT REPORTED ROUGH ENGINE OPERATION FOR A FEW SECONDS.  THE FUEL FLOW DIVIDER WAS REPLACED AND THE 	NR 1 NOZZLE WAS REPLACED.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040400477	20000404	00477	NE  	2000	4	4	20000329SH008    	3	20000207	G	6111	C63371	SEAL            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DETERIORATED    	B			LU4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17		5151 	673  					HJ55		NEW STYLE SEAL APPEARS TO HAVE DETERIORATED AFTER 672.4 HOURS OF SERVICE.  RETURNED PARTS TO FACTORY FOR EVALUATION. (X)	 					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
2000040400480	20000404	00480	NE  	2000	4	4	20000329SH034    	3	20000309	G	6111	C60661	PLATE           													HARTZL	HDE6C	HDE6C3B     	NE  	PROPELLER BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05			5018 					HL2747		DURING ROUTINE INSPECTION, FOUR OF THE SIX PRELOAD PLATES WERE FOUND CRACKED.  CRACKS STARTED AT THE PITCH CHANGE BRACKE	T CUT-OUT AREA AND RAN ACROSS THE FACE OF THE PLATE AND DOWN THE OUTSIDE DIAMETER.  (X)															6	C	P34NE	 
2000040400483	20000404	00483	SO  	2000	4	4	20000329SH038    	2	20000214	G	7414	1051324	SPRING          								CONT  	O470  	O470*       	17026	SO  					IMPULSE COUPLING	DAMAGED         	B			QKKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01										NEW PARTS HAVE FINGER PRINTS ON THEM.  PARTS ARE NEW, NOT REMOVED FROM MANUFACTURER''''S BAG SINCE TIME OF BAGGING AT SU	PPLY CENTER.  SUBMITTER STATED PROBLEM IS SPRING STEEL WITH SWEAT FROM THE PERSONS WORKING ON THE PART.										3	O			E273				 
2000040300012	20000403	00012	CE  	2000	4	3	20000329SH039    	1	20000302	G	2612		WARNING LIGHT   			LEAR  	25    	25D         	5170514	CE  										COCKPIT	ILLUMINATED     	H				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			SO	11	969SS					317				EN ROUTE, RIGHT ENGINE FIRE WARNING LIGHT ILLUMINATED BRIEFLY.  DIVERTED FLIGHT.  FALSE ENGINE FIRE WARNING, CHAFED WIRE	.  (X)					2	L	7	2 	4J			 	A10CE   					 
2000040400484	20000404	00484	WP  	2000	4	4	20000329SH040    	1	20000227	G	3244	26088911	TIRE            	GOODYEARAERO		DOUG  	DC9   	DC983       	3022083	WP  										MLG	FAILED          	B			A3L2	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					72930255					DEFECT:  THROWN TREAD FROM CARCASS.  CAUSE:  UNDETERMINED.  TIRE SENT TO MANUFACTURER FOR ANALYSIS.  PREVENTIVE ACTION: 	 PENDING COMPLETE INVESTIGATION (INTERIM) ONLY USING NEW TIRES. (X)					2	L	7	2 	4F			RT	A6WE    					 
2000040400485	20000404	00485	CE  	2000	4	4	20000329SH041    	1	20000220	G	2820	050011874	FUEL LINE       			CESSNA	172   	172M        	2072418	CE  										FUSELAGE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	73366	2428 				17267405				AIRCRAFT ACQUIRED FOR USE IN A FLIGHT SCHOOL.  DURING ITS INITIAL INSP (ANNUAL), A FUEL LINE WAS FOUND CHAFING HARD AGAI	NST THE STEERING ROD.  THIS FUEL LINE IS LOCATED BETWEEN FUEL SELECTOR VALVE AND FUEL STRAINER AND PASSES UNDER COPILOT'	'S RUDDER PEDALS.  EVERY TIME RUDDER PEDALS WERE MOVED, THE STEERING ROD (CONNECTED TO NOSE WHEEL) RUBBED AGAINST THE FU	EL LINE AT A BEND.  FUEL LINE WAS CHAFED TO THE POINT WHERE INTERIOR WALL WAS BENT INWARD AND SO THIN THAT FAILURE WAS I	MMINENT.  IT APPEARED TO HAVE BEEN CHAFING SINCE ACFT WAS BUILT.  NEW FUEL LINE CONTACTED STEERING ROD IN SAME MANNER.  	CORRECTED BY BENDING LINE AWAY FROM STEERING ROD.	1	H	7	1 	3O			NT	3A12    					 
2000040400487	20000404	00487	SO  	2000	4	4	20000329SH043    	1	20000211	G	7110	65202800	LATCH           			PIPER 	PA32  	PA32260     	7103206	SO  										COWL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	3369W					321054				CRACKS FORM AT THE BEND RADIUS OF THE LATCH ASSEMBLY WITHIN A FEW HOURS OF NORMAL OPERATION.  SEVERAL ASSEMBLIES (6) HAV	E FAILED IN THE SAME MANNER.  THIS ASSY IS FORMED WITH A MUCH SMALLER BEND RADIUS AS COMPARED TO AN OLDER STYLE PIPER OE	M LATCH ASSY. 				1	L	7	1 	3O			 	A3SO    					 
2000040400488	20000404	00488	EA  	2000	4	4	20000329SH044    	2	20000302	G	8530	05K21123	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	DAMAGED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	95512	466  				15285911	RL897015			WHILE PERFORMING ANNUAL INSP, ALUMINUM SHAVINGS WERE FOUND IN THE OIL FILTER.  FILTER SENT TO LYC FOR ANALYSIS AND DETER	MINED TO BE PISTON PIN PLUG MATERIAL.  UPON REMOVAL OF ALL 4 CYLINDERS, SEVERE PITTING FOUND AT BOTTOM OF EACH CYL WALL 	AT THE POINT WHERE PISTON TOUCHES ITS LOWEST TRAVEL.  ALL 4 CYL''S REJECTED AND FACTORY NEW INSTALLED.  FACTORY STATES T	HIS IS RESULT OF ENG NOT REACHING PROPER OPERATING TEMP.  ACFT IS OPERATED IN PHOENIZ, AZ, OIL TEMP GAUGE IS ACCURATE.  	 		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000040400489	20000404	00489	EA  	2000	4	4	20000329SH045    	2	20000302	G	8530	05K21123	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	DAMAGED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	757NZ	681  				15279885	L2507515			WHILE PERFORMING ANNUAL INSP, SMALL ALUMINUM PARTICLES WERE FOUND IN THE OIL FILTER.  A BORESCOPE INSP REVEALED WEAR ON 	CYLINDER WALLS AND PITTING AT THE BASE OF EACH CYL (INSIDE) AT THE POINT OF THE PISTON''S FARTHEST TRAVEL DOWNWARDS.  TW	O OF THE CYL''S WERE FACTORY NEW WITH 681 HRS SINCE NEW.  THE OTHER TWO WERE REPAIRED 1,176.7 HRS AGO AT FACTORY''S REQU	EST BY A FACTORY APPROVED REPAIR FACILITY UNDER WARRANTY.  THIS IS 3RD OCCURRENCE IN 1,859.5 HRS SMOH BY LYC.  THE 1ST O	CCURANCE RESULTED IN ALL OF THE ABOVE AND BELOW ACCEPTABLE COMPRESSIONS ON ALL 4 CYL''S.  FACTORY STATES ENGINE IS RUNNI	NG TOO COLD IN PHX, AZ.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000040400490	20000404	00490	GL  	2000	4	4	20000329SH046    	3	20000322	G	6110		CLAMP           													HARTZL	HCA3V	EHCA3VF2    	GL  	PROPELLER BLADE	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05										THE PILOT OF A BEECH BARON DISCOVERED A BROKEN BOLT WITHIN THE PROP ASSEMBLY DURING A CAREFUL PRE-FLIGHT INSPECTION.  BO	TH PROPELLERS HAD RECENTLY UNDERGONE MAINTENANCE AT A PROPELLER REPAIR STATION.  EVIDENCE SUGGESTED THE PROPELLER BLADE 	CLAMP, PN C-3-51 (WHICH HOLDS THE PROP BLADE IN PROP HUB), WAS MAKING CONTACT AND EXERTING FORCE ON THE LATCH BRACKET CA	USING BOLTS SECURING BRACKET TO FAIL.  THE CONTACT BETWEEN THE BLADE CLAMP AND BRACKET WAS A FUNCTION OF THE BLADE ANGLE	 SELECTED BY THE PILOT.  IT IS UNCLEAR WHY CLEARANCE BETWEEN BLADE CLAMP AND LATCH BRACKET HAD DETERIORATED.  HARTZELL C	ONTACTED AND IS INVESTIGATING. 											5	C	P6EA	 
2000040400491	20000404	00491	CE  	2000	4	4	20000329SH047    	1	20000224	G	2910	631700348	TUBE            			CESSNA	525   	525         	2076601	CE  										HYD SYSTEM	CRACKED         	H				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SW	99	49CJ	2467 				5250049				AFTER LANDING GEAR RETRACTION, BOTH HYDRAULIC FLOW AND LOW PRESSURE ANNUNCIATOR LIGHTS ILLUMINATED.  FLIGHT WAS ABORTED 	AND DIVERTED BACK TO PHF (ORIGINATING AIRPORT).  LANDING GEAR WAS EXTENDED BY THE EMERGENCY EXTENSION SYSTEM WITH NO FUR	THER ABNORMALTIES.  MAIN SYSTEM HYDRAULIC FAILURE AS A RESULT OF CRACKED PRESSURE SUPPLY TUBE, PN 6317003-48, TO LOADING	 VALVE (BYPASS VALVE).  FAILED TUBES REPLACED WITH FACTORY-NEW PARTS.   LANDINGS:  3,710.			1	L	7	2 	4F			RT	A1WI    					 
2000040400492	20000404	00492	CE  	2000	4	4	20000329SH048    	1	20000316	G	2822	5100003	PUMP            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL BOOST	INOPERATIVE     	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	416ER	443  				17280281	L2732651A			THE CREW REPORTED THE ELECTRIC BOOST PUMP INOPERABLE.  THE PUMP WAS REPLACED.  THIS PUMP ROUTINELY FAILS IN THIS FLEET O	F 172R AIRCRAFT, AND IN MOST CASES, PRODUCES METAL THAT CONTAMINATED THE FUEL INJECTION COMPONENTS.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040400509	20000404	00509	GL  	2000	4	4	20000330SH001    	1	20000131	G	2720	14D01	PEDAL           			AMTR  	KITFOX	KITFOXIV    	05620EP	GL  										RUDDER CONTROL	BROKEN          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	423GB	194  				JCU106				RIGHT RUDDER PEDAL SEPARATED FROM TORQUE TUBE.  THE AREA WHERE THE TORQUE TUBE AND RUDDER PEDAL ARE ATTACHED CRACKED BEL	OW THE WELD.  THIS WAS CRACKED PRIOR TO THE INCIDENT.  WHEN  HARD RIGHT RUDDER PEDAL WAS APPLIED, IT BROKE AND SPLIT TOR	QUE TUBE LOOSING CONTROL OF AIRCRAFT.  (X)				1	H	7	1 	3I			NC	EXPA    					 
2000040400510	20000404	00510	EA  	2000	4	4	20000330SH002    	2	20000306	G	8500		CASE            			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	3419X	3270 	1250 			1118	L230151A			PILOT NOTED OIL LEAK.  DURING INSPECTION FOR OIL LEAK, ENGINE CASE WAS FOUND CRACKED BELOW NR 1 CYLINDER BASE PAD.  CRAC	K IS APPROXIMATELY 4.5 INCHES PARALLEL TO CYLINDER PAD.  ALSO FOUND NR 1 INTAKE TUBE LOOSE.  					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2000040400511	20000404	00511	SO  	2000	4	4	20000330SH003    	1	20000306	G	3230	762554	ROD END         	WIEBEL      	21151       	PIPER 	PA31  	PA31350     	7103110	SO  										MLG	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	23	628HA	11364			WTC2949	317952085				RIGHT MAIN LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF.  AFTER NUMEROUS ATTEMPTS AND AFTER PERFORMING A MANUAL EXTENSIO	N OF GEAR, A GREEN LIGHT COULD NOT BE OBTAINED ON THE RIGHT GEAR.  AFTER A GROUND VISUAL CHECK, IT APPEARED GEAR WAS DOW	N.  A LANDING WAS PERFORMED, AND AFTER ROLL-OUT, RIGHT LANDING GEAR COLLAPSED.  AIRCRAFT RECEIVED MINOR DAMAGE.  UPON IN	SPECTION, DISCOVERED THE ROD END HAD BROKE OUT ON THE RT MAIN GEAR ACTUATOR.  ROD END FAILED JUST AFTER UNLOCKING THE RT	 GEAR AT A POINT IN WHICH GEAR WOULD NOT FALL BACK INTO A LOCK POSITION.  (X)		1	L	7	2 	3O			 	A20SO   					 
2000040300015	20000403	00015	CE  	2000	4	3	20000330SH004    	1	20000201	G	7810	HS783820041	CLAMP           			RAYTHN	DH125 	HAWKER800XP 	       	CE  										TAIL PIPE	CHAFED          	B			G1FR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	139M					258330				CHAFE DAMAGE OCCURRED TO BOTH ENGINE TAILPIPE V-CLAMPS PN 234-559-9019 (IPC REF 78-10-01, FIG 1, ITEM 15) AND INNER CORE	 COWL CHAFE BRACKET PN HS7838200-41 (IPC REF 78-30-05A, ITEM 245).  EACH ENG CONTAINS 8 BRACKETS AND 1 V-CLAMP.  DAMAGE 	HAS OCCURRED AT SOME OR ALL BRACKET MOUNT LOCATIONS WITH APPROX .020 INCH TO .090 INCH DEPTH WITH TOTAL EDGE SPAN OF 0.3	75 INCH ON THE BRACKETS AND APPROX .010 INCH TO .025 INCH DEPTH AT CONTACT LOCATIONS ON V-CLAMP.   THIS DAMAGE DISCOVERE	D DURING UNSCHEDULED DISASSEMBLY AND REMOVAL OF ENGINES.  REPLACE V-CLAMP AND DRESS FWD EDGE OF CHAFE PAD BRACKETS TO AL	LOW CLEARANCES OF .050 INCH MIN.  	2	L	7	2 	4F			RT	A3EU    					 
2000040400512	20000404	00512	EU  	2000	4	4	20000330SH005    	1	20000308	G	2460	TB2061238001	SWITCH          			SOCATA	TB20  	TB21        	8680697	EU  										ELECTRICAL	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	30582	45   				1618				INTERNAL ELECTRICAL FAILURE OF PRESSURE SWITCH AT 44.8 HOURS.  THIS IS THE 7TH SWITCH INSTALLED IN THIS AIRCRAFT.  SWITC	H FAILURE IS A MIXTURE OF ELECTRICAL AND MECHANICAL (LEAKAGE).  					1	L	7	1 	3O			RT	A51EU   					 
2000040400513	20000404	00513	EA  	2000	4	4	20000330SH006    	2	20000322	G	8550	LW14729	DIPSTICK        			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					OIL CAP	SEPARATED       	H				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			SW	99	9452C		206  			32R7887006	L527061A			PILOT REPORTED TO REPAIR SHOP, THAT AFTER LANDING, HE HAD AN OIL LEAK IN THE ENGINE AREA.  AFTER INSPECTION, FOUND THAT 	DIP ROD IN THE OIL CAP WAS NOT INSTALLED IN THE CAP AND HAD FALLEN DOWN INTO THE OIL FILL TUBE OF THE ENGINE.  UNDER INS	PECTION WITH A MAGNIFYING GLASS, NO SIGNS THE ROLL PIN THAT SHOULD HAVE BEEN INSTALLED TO HOLD THE ROD INTO THE CAP HAD 	EVER BEEN INSTALLED.  THIS ENGINE HAD BEEN OVERHAULED BY THE LYCOMING FACTORY, AND WAS NOT AN AFTER MARKET OVERHAUL.   			1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2000040400514	20000404	00514	NE  	2000	4	4	20000330SH007    	2	20000211	G	7250	2A227401	BEARING         								IAE   	V2528 	V2528D5     	 	NE  					NR 4	DAMAGED         	A			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		1320 					V20006			ENGINE RECEIVED FOR THIRD LPT BLADE DAMAGE. DISASSEMBLY INSPECTION REVEALED FLOODED NR 4 BEARING AREA/POSSIBLE FIRE AND 	CONTACT BETWEEN T2 DISK AND 1-2 AIR SEAL.  (X)										4	F			E40NE				 
2000040400515	20000404	00515	NE  	2000	4	4	20000330SH008    	2	20000211	G	7250	2A227401	BEARING         								IAE   	V2528 	V2528D5     	 	NE  					NR 4	DAMAGED         	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		1320 					V20006			ENGINE RECEIVED FOR 3RD LPT BLADE DAMAGE.  DISASSEMBLY INSPECTION REVEALED FLOODED NR 4 BEARING AREA/POSSIBLE FIRE AND C	ONTACT BETWEEN T2 DISK AND 1-2 AIR SEAL.  (X)										4	F			E40NE				 
2000040400516	20000404	00516	CE  	2000	4	4	20000330SH009    	1	20000330	G	3230	204101738	PLUNGER         			CESSNA	177   	177RG       	2073709	CE  										LT MLG SOLENOID	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1873Q					177RG0273				WHEN THE GEAR WAS RETRACTED, THE SOLENOID PLUNGER EXTENSION WAS NOT PULLING THE DOWNLOCK MECHANISM COMPLETELY OPEN.  WHE	N THE GEAR WAS THEN EXTENDED AND THE GEAR HIT THE DOWNLOCK MECHANISM, IT WOULD DRIVE IT OVERCENTER BACKWARDS.  REPLACING	 WORN PARTS FIXED THE PROBLEM.  (X)				1	H	7	1 	3O			 	A20CE   					 
2000040400517	20000404	00517	SO  	2000	4	4	20000330SH010    	1	20000308	G	2710		CONTROL CABLE   			AMRGEN	AA5   	AA5A        	3960106	SO  										PULLEY CLUSTER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	26086	3500 				AA5A0326				DURING ANNUAL INSPECTION, FOUND CABLES DETERIORATED AND FRAYED AS WOULD BE FOUND IF INSPECTING SERIES AS AN AA1, AS SPEC	IFIED IN AD 72-6-2.  AS THE REST OF THE GRUMMAN SINGLE ENGINE FLEET HAS SIMILAR CABLE RUNS AS THE AA1 SERIES AND THE EAR	LY AA5''''S WITH EARLIER S/N''''S, AD 72-06-02 SHOULD BE AMENDED TO INCLUDE ALL TYPE SERIES THAT EMPLOY THE SIMILAR PULL	EY CLUSTER JUST AHEAD OF THE FRONT SPAR IN THE CABIN.  WEAR APPEARS TO BE FROM NORMAL OPERATIONS/AGE OF CABLES.  NORMAL 	ACCUMULATIONS OF DEBRIS AND DIRT IN AREA OF PULLEYS AND THE PULLEYS WERE NOT FROZEN.  DUE TO THIS INSTALLATIONS DESIGN.		1	L	7	1 	3O			 	A16EA   					 
2000040400518	20000404	00518	SO  	2000	4	4	20000330SH011    	2	20000215	G	8520	630826	BEARING         			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520*      	17032	SO  					CRANKSHAFT	CRAZED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4667Q					21059567				DURING ENGINE TEAR DOWN DUE TO SUDDEN STOPPAGE.  INSPECTION OF THE BEARINGS FOUND 7 OUT OF 12 BEARING HALVES FOUND WITH 	EXCESSIVE CRAZING ON THE SURFACE.  ENGINE WAS ASSEMBLED 12-28-99 AND PUT INTO SERVICE ON 1-29-00 AND WAS DISASSEMBLED 2-	25-00.  SUBMITTER STATED CAUSE AND PREVENTION UNKNOWN.  (X)				1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2000040400519	20000404	00519	SO  	2000	4	4	20000330SH012    	2	20000215	G	8520	653547	BEARING         			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					CRANKSHAFT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4667Q	45   				21059567	295047R			DURING ENGINE TEAR DOWN DUE TO SUDDEN STOPPAGE, INSPECTION OF THE BEARINGS FOUND 4 OUT OF 10 BEARING HALVES WERE FOUND W	ITH EXCESSIVE CRACKING ON THE SURFACE.  ENGINE WAS ASSEMBLED 12-28-99, AND PUT INTO SERVICE ON 1-29-00, AND WAS DISASSEM	BLED 2-25-00.  CAUSE AND PREVENTION UNKNOWN.  (X)				1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2000040400520	20000404	00520	CE  	2000	4	4	20000330SH013    	1	20000313	G	2731	C419175	LINK            			CESSNA	500   	550         	2076604	CE  										PEDESTAL	BENT            	G				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	15	7ZU	6135 				5500433				AIRCRAFT''S PITCH TRIM JAMMED IN-FLIGHT AND A SUCCESSFUL LANDING WAS MADE.  UPON INSPECTION, MECHANICS FOUND THE SAFETY 	CLIP THAT HOLDS TH MASTER LINK TOGETHER CAME OFF AND THEN BENT THE MASTER LINK.  THE MASTER LINK IS PART OF A CHAIN ASSY	 LOCATED IN THE PEDESTAL OF THE COCKPIT TRANSFERRING THE MOTION OF THE ELEVATOR TRIM WHEEL TO TEH CABLE SYSTEM.  THE CHA	IN ASSY WAS REPLACED AND SYSTEM WORKED FINE.  SUBMITTER STATED SPECIAL ATTENTION SHOULD BE ADDRESSED TO THE MASTER LINK 	ON PHASE 5 INSPECTIONS.		1	L	7	2 	4F			 	A22CE   					 
2000040400522	20000404	00522	WP  	2000	4	4	20000330SH015    	2	20000117	G	7230	30756451	CARBON SEAL     			LEAR  	35    	36A         	5170603	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE	FAILED          	B			IY2R	O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	15	32AJ	231  				36A048	P89174			ENGINE EXPERIENCED IN-FLIGHT SHUTDOWN 230.5 HRS FOLLOWING CZI (COMPRESSOR ZONE INSP) AND INSTALL OF NEW STYLE CARBON SEA	LS PER SB 72-3596 REV 7.  ENG TEARDOWN REVEALED FAILURE OF PLANETARY GEAR BEARINGS, PLANETARY GEARS, SUN GEAR, AND RING 	GEAR.  FAILURE CAUSED BY OIL STARVATION TO PLANETARY ASSY DUE TO BLOCKAGES OF PLANETARY OIL MANIFOLDS OIL JET STRAINER, 	PN 894764-3.  THE HAT SHAPED STRAINER WAS PACKED WITH CARBON WHICH REDUCED OIL FLOW TO PLANETARY GEAR AREA.  ENG TOTALLY	 DISASSEMBLED TO ACCOMPLISH LUBRICATION CONTAMINATION INSP AND DETERMINE WHICH COMP GENERATED CARBON PARTICLES.  PARTICL	ES TRACED TO NEW NR 5 CARBON SEAL PN 3075645-1, SN 9919366801122.  (X)	2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2000040400523	20000404	00523	NM  	2000	4	4	20000330SH016    	1	20000204	G	3242		BRAKE           			BOEING	747   	747212B     	1384886	NM  										MLG	OVERHEATED      	B			GK4Y	O				OTHER                   				A	J		FLAME/FIRE                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			WP	03	482EV					20713				ON ARRIVAL, LT WING AND BODY GEAR WHEEL BRAKES OVERHEATED.  NR 4 WHEEL ASSY IGNITED, BUT WAS IMMEDIATELY EXTINGUISHED.  	NR 6 AND NR 7 WHEEL ASSY THERMAL FUSE PLUGS RELIEVED AND WHEELS DEFLATED.  INSP OF GEAR AREAS CARRIED OUT OK AND MAIN WH	EELS REPLACED (4, 6, AND 7).  (X)				2	L	7	4 	4F			 	A20WE   					 
2000040300016	20000403	00016	NE  	2000	4	3	20000330SH017    	2	20000128	G	7230		BLADE           			BOEING	747   	747121      	1384871	NM  	PWA   	JT9   	JT9D7A      	52054	NE  					NR 1 ENGINE	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	480EV					20348				DURING WALKAROUND INSPECTION, SEVEN N1 FAN BLADES WERE FOUND BENT BEYOND LIMITS ON NR 1 ENGINE.  AIRCRAFT WAS GROUNDED N	AN.  FAN BLADES WERE REPLACED AND TEST RUN CARRIED OUT BY EVERGREEN.  (X)					2	L	7	4 	4F	4	F	 	A20WE   	E20EA				 
2000040400524	20000404	00524	WP  	2000	4	4	20000330SH018    	2	20000229	G	7314	31080261	PUMP            								GARRTT	TPE331	TPE331*     	01514	WP  					DRIVE GEAR	FROZEN          	B			UO2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19		13285					P66294			PUMP FROZE DURING FLIGHT STRIPING DRIVE GEAR.  (X)											3	T			E2WE				 
2000040400525	20000404	00525	SO  	2000	4	4	20000331SH001    	1	20000313	G	3242	1331096	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					0207					BRAKE ASSY, PN 2-1585, FAILED PREMATURELY.  NR 1 STATOR BROKEN AND BINDING IN TORQUE TUBE KEY SLOTS.  THIS IS A CONTINUA	L DISCREPANCY.  BRAKE ASSY SHOULD LAST 2,500 CYCLES.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY AND THE  MOST RECENT BRAK	E CONFIGURATION, PN 2-1585.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2000040600061	20000406	00061	WP  	2000	4	6	20000331SH002    	2	20000301	G	7250	30720705	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	NICKED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH TWO SMALL NICKS IN WEB AREA FORWARD SIDE AND DAMAGE IN POST FIR TREE AREA ON BOTH 	SIDES.  (X)										4	F			E6WE				 
2000040600062	20000406	00062		2000	4	6	20000331SH003    	4	20000225	G	2561		LIFE VEST       	EAAEROMARINE																CABIN	FAILED          	B			CHIR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	09					88682					WHILE ATTEMPTING TO INFLATE THIS DUAL CELL ADULT LIFE PRESERVER, BOTH TOGGLES WERE PULLED SIMULTANEOUSLY.  THE BACK CELL	 INFLATED CORRECTLY, THE FRONT CELL FAILED TO INFLATE DUE TO THE ACTUATING LEVER PULLING OUT OF INFLATOR ASSEMBLY HOUSIN	G ALLOWING INFLATOR PIN AND SPRING TO FALL OUT OF ASSEMBLY WITHOUT BREAKING SEAL ON CO2 CARTRIDGE.  DISASSEMBLY OF BOTH 	THE GOOD AND FAILED INFLATOR ASSEMBLIES AND COMPARISON OF THE 2 ACTUATING ARM RETAINER PINS SHOWED THE FAILED ASSEMBLY P	IN WAS APPROX 0.092 INCH SHORTER THAN THE RETAINER PIN OUT OF THE GOOD ASSY.  NOTE THAT BOTH OF THESE PINS ARE STEEL.  T	HIS VEST IS NOT AFFECTED BY EAM SB SBV-25-2 BY DATE OF MFG AND HAVING STEEL PINS.    (X)														 
2000040400526	20000404	00526	EU  	2000	4	4	20000331SH004    	1	20000315	G	3260	SP3982	UPLOCK SWITCH   			AMD   	FALCON	FALCON20    	2730103	EU  										MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	120TF	1    			213	384				TWO NEW SWITCHES WERE INSTALLED IN THE LT MAIN GEAR DOOR UPLATCH.  (BOTH ARE SAME P/N AND DATE OF MFG).  ONE SWITCH CONT	ROLS THE RED DOOR UNLOCK LIGHT, AND THE OTHER CONTROLS DOOR AND GEAR SEQUENCING.  THE GEAR WAS CYCLED SUCCESSFULLY NUMER	OUS TIMES WITH THE ACFT ON JACKS, WHEN THE CREW ATTEMPTED TO EXTEND THE GEAR ON THE SECOND FLIGHT, BOTH NEW SWITCHES FAI	LED.  THIS CAUSED 2 PROBLEMS.  THERE WAS NO INDICATION IN THE COCKPIT THAT THE LT MAIN DOOR OPENED.  (NO RED LIGHT).  TH	E CREW WAS ABLE TO SEE THE LT GEAR DID EXTEND FROM THE COCKPIT PROVING THE DOOR HAD OPENED.  AFTER LANDING, THE CREW THE	N NOTICED THE LT DOOR HAD REMAINED IN THE OPEN POSITION. THIS WAS CAUSED BY THE FAILURE OF THE SECOND SWITCH.  (X)	2	L	7	2 	4F			RT	A7EU    					 
2000040600065	20000406	00065	CE  	2000	4	6	20000331SH007    	1	20000304	G	2140	AHE85D421	SHUTOFF VALVE   			CESSNA	414   	414A        	2075907	CE  										HEATER	FAILED          	B			MI2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	119SK	10   			2008052	414A0660				VALVE WILL NOT SHUT OFF THE FUEL TO THE HEATER AND CAUSED HEATER TO OVERHEAT.  (X)						1	L	7	2 	3O			 	A7CE    					 
2000040600066	20000406	00066	WP  	2000	4	6	20000331SH009    	2	20000307	G	7250	30723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST-FIR TREE AREA.  (X)											4	F			E6WE				 
2000040600068	20000406	00068	CE  	2000	4	6	20000331SH010    	2	20000310	G	7414		PLATE           	SLICK       		MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					MAGNETO MOUNT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	252BA	631  			95030022	251122	317134			WHEN LT AND RT MAGNETOS WERE BEING INSTALLED ON ENGINE AFTER INTERNAL INSPECTION OF MAGNETOS, NOTED MAGNETO HOLD-DOWN PL	ATES FROM ENGINE STUD TO MAGNETO MOUNTING FLANGE ONLY ENGAGED FLANGE BY APPROXIMATELY .0625 INCH IF MOUNTED EVEN, OR ONL	Y ONE CORNER OF PLATE IF COCKED TO ONE SIDE.  SUBMITTER STATED MOUNTING PLATES ARE TYPE NORMALLY SENT WITH NEW MAGNETOS.	  ORDERED 4 EACH TCM, PN 630535, MOUNT PLATES AND INSTALLED, FIT GOOD.  (X)			1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2000040600069	20000406	00069	CE  	2000	4	6	20000331SH011    	2	20000310	G	7414		PLATE           	SLICK       		MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					MAGNETO MOUNT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	252BA				97030194	251122	317134			WHEN LT AND RT MAGNETOS WERE BEING INSTALLED ON ENGINE AFTER INTERNAL INSPECTION OF MAGS, NOTED MAGNETO HOLD-DOWN PLATES	 FROM ENGINE STUD TO MAGNETO MOUNTING FLANGE ONLY ENGAGED FLANGE BY APROXIMATELY .0625 INCH IF MOUNTED EVEN, OR ONLY ONE	 CORNER OF PLATE IS COCKED TO ONE SIDE.  SUBMITTER STATED MOUNTING PLATES ARE TYPE NORMALLY SENT WITH NEW MAGNETOS.  ORD	ERED 4 EACH TCM PN 630535 MOUNT PLATES AND INSTALLED, FIT GOOD.  (X)			1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2000040400540	20000404	00540		2000	4	4	20000331SH012    	4	20000301	G	3416	060030620000	ALTIMETER       			BEECH 	1900  	1900D       	1154162	CE  										COCKPIT	MALFUNCTIONED   	B			GLBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	220GL		148  			UE220				PILOT WRITE UP WAS ''STICKS SEVERAL THOUSAND FEET'', CALIBRATION WAS OUT AT -1,000 AND ZERO FEET AND 500 FEET, ENCODER F	UNCTIONS PROPERLY, COULD NOT VERIFY OR DUPLICATE STICKING.  ALTIMETER WAS 40 FEET LOW AT -1,000 FEET AND PROGRESSIVELY G	OT BETER.  AT +1,000 FEET WAS ZERO ERROR AND WITHIN LIMITS FOR REST OF TEST. (X)				2	L	7	2 	4T			RT	A24CE   					 
2000040400541	20000404	00541		2000	4	4	20000331SH013    	4	20000223	G	3422	6226136002	GYRO            			BEECH 	1900  	1900D       	1154162	CE  										COCKPIT	INOPERATIVE     	B			GLBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	245GL	682  				UE245				CAPTAIN''S DIRECTIONAL GYRO INOPERATIVE.  NR 1 GYRO LOCKED UP. (X)						2	L	7	2 	4T			RT	A24CE   					 
2000040600070	20000406	00070	CE  	2000	4	6	20000331SH014    	1	20000315	G	3233	993880081	ACTUATOR        			BEECH 	99    	C99         	1154006	CE  										MLG	CRACKED         	B				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	11	216CS		72   			U216				HYDRAULIC FLUID FOUND IN WHEELWELL DURING POST-FLIGHT INSPECTION.  LANDING GEAR RETRACTION PERFORMED, FOUND 2 INCH CRACK	 AROUND TOP OF ACTUATOR.  ACTUATOR OVERHAULED.  (X)					1	L	7	2 	3T			 	A14CE   					 
2000040400542	20000404	00542	NM  	2000	4	4	20000331SH015    	1	20000306	G	3244	26066712	TIRE            			BOEING	737   	737*        	       	NM  										MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09										TIRE FAILURE.  OVERLOAD DUE TO ADJACENT FAILURE.  PENDING COMPLETION OF INVESTIGATION.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2000040400543	20000404	00543	NM  	2000	4	4	20000331SH016    	1	20000306	G	3244	H405X145	TIRE            			BOEING	737   	737*        	       	NM  										MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09					B9125					TIRE FAILURE, THROWN TREAD.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2000040400544	20000404	00544	EU  	2000	4	4	20000331SH017    	1	20000308	G	3213	7216FR964T	SEAL            			JETAIR	JETSTM	JETSTM4101  	1500501	EU  										MLG	FAILED          	B			FWIR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03	306UE				APB970039	41020				4046 CSN MFG - 4-97.  UNIT LEAKING FROM GLAND SEAL (PREMATURE FAILURE).  SEAL FOUND ERODED ON OUTBOARD SIDE BETWEEN SEAL	 SURFACE AND BACK-UP.  THIS IS ONE EXAMPLE OF NUMEROUS UNITS RETURNED FOR REPAIR AFTER 3,000 - 5,000 CYLES WHEN THE OVER	HAUL CYLINDER IS 12,000 TO 24,000 DEPENDING ON A/C UNITS WERE MFG IN 1997.  MFG OF SEAL SAID RAMRODS WERE AT FAULT, MFG 	OF UNIT THOUGHT THE SEAL WAS BAD.  NO RESOLUTION TO PROBLEM.  CONDITION AS OCCURRED IN BOTH JS41 AND SAAB340B UNITS (AIR	886410-1 AND AIR86414-1).  (X)		2	L	7	2 	4T			RT	A41NM   					 
2000040600071	20000406	00071	CE  	2000	4	6	20000331SH019    	1	20000303	G	7120	H30024	SHOCK MOUNT     			CESSNA	336   	336         	2075602	CE  	CONT  	O360  	IO360A      	17025	SO  					FIREWALL	FAILED          	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	3856U	1841 				33610156				DIFFICULT TO INSPECT.  PILOT HEARD AND NOTICED COWL RUBBING PROPELER SPINNER DURING SHUT DOWN AT FUEL PIT AT MADERA AIRP	ORT.  (X)					1	H	7	2 	3O	3	O	 	A2CE    	E1CE				 
2000040600072	20000406	00072	CE  	2000	4	6	20000331SH020    	1	20000303	G	3246	4075	WHEEL           			CESSNA	336   	336         	2075602	CE  										MLG	DAMAGED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	3856U	1830 				3360156				BOLTS BENT WHEEL HOLES ELONGATED DUE TO WEIGHT OF AIRCRAFT AND SHORT FIELD LANDINGS.  AIRCRAFT USED FOR SEARCH AND RESCU	E PLUS TRAINING IN FRESNO COUNTY SHERIFF''S AIR SQUADRON.  NOTE:  WHEEL STATIC LOAD 1,800 POUNDS.  (X)					1	H	7	2 	3O			 	A2CE    					 
2000040600073	20000406	00073	EA  	2000	4	6	20000331SH021    	2	20000312	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NOSE	ROUGH           	H				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			SW	99	410ER					17280257	LW2722651A6			THE ENGINE WAS REPORTED ROUGH IN CRUISE.  CORRECTIVE ACTION WAS TAKEN AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040400546	20000404	00546	CE  	2000	4	4	20000331SH022    	1	20000310	G	2133	66001983	VALVE           			LEAR  	35    	35A         	5170602	CE  										FLOW CONTROL	FAILED          	B			O9IR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			NM	09	45AE		2704 			422				AIRCRAFT CABIN DID NOT PRESSURIZE WHEN DEPARTING.  AIRCRAFT RETURNED TO LAS VEGAS FOR REPAIR.  CABIN FLOW CONTROL VALVE 	WAS FOUND DEFECTIVE.  AN OVERHAULED CABIN FLOW CONTROL VALVE WAS INSTALLED.  GROUND RUNS STILL WERE NOT SATISFACTORY.  F	URTHER INVEST REVEALED THE K2 RELAY ON THE PCB1 SQUAT SWITCH RELAY PANEL TO BE INTERMITTENT.  THIS RELAY WAS ALSO CHANGE	D.  FUNCTIONAL CHECK OF THE PRESSURIZATION SYSTEM REVEALED NO FURTHER DISCREPANCIES.  THE DEFECTIVE COMPONENTS ARE ''ON 	CONDITION'' ITEMS WITHOUT SCHEUDLE REPLACEMENT OR OVERHAUL.  A COMPLETE PRESSURIZATION CHECK WAS COMPLETED AS PART OF TH	E LAST C-CHECK (1200 HOUR INSP).  NO DEFECTS WERE NOTED AT THAT TIME (5-13-98, ACTT 4,540.7 HRS).  ACFT TT 5,360.1 HRS.(	2	L	7	2 	4F			 	A10CE   					 
2000040600074	20000406	00074	SO  	2000	4	6	20000331SH023    	2	20000120	G	8530		STUD            	BENDIX      		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE CYLINDER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	42RH	10   				18266776	820036R			NEW REBUILT ENGINE PURCHASED FROM CONTINENTAL.  10.6 HOURS AFTER INSTALLATION, NR 4 CYLINDER, NR 2 AND NR 3 CYLINDER MOU	NTING STUDS BROKE.  NR 5 AND NR 6 MISSING NUTS.  (TORQUE WAS CHECKED ON ALL OTHER CYLINDERS AND FOUND OK).   SAME ENGINE	 UPON INSTALLATION REQUIRED THE REPLACMENT OF THE RIGHT MAGNETO AT ZERO HOURS.  (X)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000040600075	20000406	00075	GL  	2000	4	6	20000331SH024    	3	20000301	G	6111		BLADE           			CESSNA	210   	P210N       	2073454	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER	MISOVERHAULED   	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	4783K	3607 	115  			P21000314		797073		PROPELLER VIBRATING AFTER RECENT OVERHAUL.  DYNAMIC BALANCING HELPED.  FOUND 7 AN 97-3 WASHERS FOR DYNAMIC BALANCE ADDED	 6 MORE TO BRING BALANCE TO A 1 IPS.  ALSO FOUND 6 STATIC WEIGHTS IN SAME LOCATION.  REMOVED PROP FROM AIRCRAFT TO CHECK	 STATIC BALANCE.  COULD NOT.  MEASURED BLADES AT 30.25 INCHES, 33.25 INCHES, AND 36.25 INCHES STA.  FOUND ALL 3 BLADES U	NDER MINIMUM WIDTH AT 30.25 INCHES STA.  BLADE NR 1, 5,803, NR 2 5,775, NR 3, 5,820 (MIN AT 30.25 INCHES IS 5.825.  (X)			1	H	7	1 	3O			 	3A21    		5	C	P47GL	 
2000040600076	20000406	00076	SO  	2000	4	6	20000331SH025    	2	20000306	G	8530		STUD            			CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					NR 5 CYLINDER	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	421CH	628  				4210176	277018R			DURING INSPECTION OF OIL LEAK, FOUND NR 5 CYLINDER BASE FRONT LOWER MOUNT STUD BROKEN.  POSSIBLY, THE STUD WAS HARD AND 	BROKE UNDER STRESS.  (X)					1	L	7	2 	3O	3	O	RT	A7CE    	E7CE				 
2000040600077	20000406	00077	CE  	2000	4	6	20000403SH001    	1	20000114	G	8120	AE366303760274	HOSE            			CESSNA	206   	T206H       	       	CE  										TURBOCHARGER	BURNED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	7264H	24   				T20608103				SCAVENGE OIL HOSE TO TURBOCHARGER BURNED UP BY EXHAUST PIPE.  USED ALTERNATE ROUTE TO BYPASS EXHAUSE PIPE.  (X)						1	H	7	1 	3O			 	A4CE    					 
2000040600078	20000406	00078	SO  	2000	4	6	20000403SH002    	2	20000306	G	8530		STUD            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					ENGINE	FAILED          	B			AZOR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	13	421LH	128  				421C1207	292129R			DURING NORMAL ENGINE OPERATION, NOTICED OIL LEAK ON FRONT OF ENGINE.  AFTER CLEANING AND INSPECTION, FOUND THE FRONT THR	OUGH-STUD BROKEN.  POSSIBLE CAUSE COULD BE IMPROPER HARDENING OF THE BOLT.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2000040600080	20000406	00080	SO  	2000	4	6	20000403SH006    	2	20000225	G	8500		ENGINE          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					RIGHT	MAKING METAL    	B			BSYR	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	07	7383R					TH502				ATL - RIGHT ENGINE PROPELLER WENT INTO FEATHER ON TAKEOFF.  FOUND ALUMINUM PLUGGING PROPELLER SCREEN.  REMOVED AND REPLA	CED ENGINE.  SUBMITTER STATED CAUSE UNKNOWN AT THIS TIME.  (X)					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000040500006	20000405	00006	WP  	2000	4	5	20000403SH007    	2	20000229	G	7200	30756842	RETAINER        			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					ENGINE	BROKEN          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	75V	697  				13	P95151			DISASSEMBLED ENGINE BECAUSE OF BAD S.O.A.P. SAMPLE.  FOUND NR 3 SEAL RUNNER RETAINER BROKEN. (X)						2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2000040500007	20000405	00007	EU  	2000	4	5	20000403SH008    	1	20000306	G	3710	25VF3323309	LINE            			BRAERO	DH125 	BAE125800A  	1500285	EU  										VACUUM SYSTEM	CUT             	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	89NC	4211 				258102				VACUUM LINE FOR THE PRESSURIZATION SYSTEM LINE, PN 25VF3323-309, RUNS UNDER THE AILERON CABLE.  THIS LINE IS .3750 INCH 	OUTSIDE DIAMETER HAD A CUT IN IT FROM CABLE .1875 INCH DEEP.  CUSTOMER REPORTED HAVING PROBLEMS REGULATING PRESSURIZATIO	N SYSTEM IN THE NORMAL OR EMERGENCY SYSTEM.  (X)				2	L	7	2 	4F			RT	A3EU    					 
2000040600083	20000406	00083	SO  	2000	4	6	20000404SH001    	2	20000308	G	8530	652956	EXHAUST VALVE   			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  					NR 1 CYLINDER	WORN            	B			CRJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9606E	145  				7630819	224130R			EXCESSIVE WEAR FOUND DURING COMPRESSION TEST.  EXHAUST VALVE WAS LEAKING.  EX GUIDE MEASURED .4384 INCH AT THE TOP AND .	4624 INCH AT THE BOTTOM.  EX VALVE MEASURED .4337 INCH AT THE TOP OF THE STEM AND .4263 INCH AT APPROX 2 INCHES FROM THE	 BOTTOM OF THE VALVE.  CLEARANCE BETWEEN VALVE AND GUIDE IS .0361 INCH.  SERVICEABLE LIMIT IS .006 INCH.  NO METAL WAS F	OUND IN THE OIL SCREEN.  ENGINE IS NOT EQUIPPED WITH A SPIN ON FILTER.  ALL OTHER CYLINDERS'' COMPRESSIONS TESTED OK.  E	NGINE WAS INSTALLED AFTER FACTORY REMAN IN JAN 98.  M OR D SUBMITTED BY HAP''S AIR SERVICE AMES, IA.  (X)		1	L	7	1 	3O	3	O	 	A18CE   	E5CE				 
2000040600084	20000406	00084	SO  	2000	4	6	20000404SH002    	2	20000308	G	8530	643767	GUIDE           			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  					NR 1 CYLINDER	WORN            	B			CRJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9606E	145  				7630819	224130R			EXCESSIVE WEAR FOUND DURING COMPRESSION TEST.  EXHAUST VALVE WAS LEAKING.  EX GUIDE MEASURED .4384 INCH AT THE TOP AND .	4624 INCH AT THE BOTTOM.  EX VALVE MEASURED .4337 INCH AT THE TOP OF THE STEM AND .4263 INCH AT APPROX 2 INCHES FROM THE	 BOTTOM OF THE VALVE.  CLEARANCE BETWEEN VALVE AND GUIDE IS .0361 INCH.  SERVICEABLE LIMIT IS .006 INCH.  NO METAL WAS F	OUND IN THE OIL SCREEN.  ENGINE IS NOT EQUIPPED WITH A SPIN ON FILTER.  ALL OTHER CYLINDERS'' COMRPESSIONS TESTED OK.  E	NGINE WAS INSTALLED AFTER FACTORY REMAN IN JAN 98.  M OR D SUBMITTED BY HAP''S AIR SERVICE, AMES, IA.  (X)		1	L	7	1 	3O	3	O	 	A18CE   	E5CE				 
2000040600085	20000406	00085	CE  	2000	4	6	20000404SH003    	2	20000227	G	7320	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					FUEL INJECTOR	FAILED          	G				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			WP	07	9299E	16   				3449043	819256R			ON BASE LEG TO GOODYEAR AIRPORT, THE LEFT ENGINE LAGGED POWER TO LANDING.  A SAFE LANDING WAS MADE AND THE AIRCRAFT WAS 	TAKEN TO MAINTENANCE FOR INSP OF THE LEFT ENGINE.  ON GROUND RUN-UP, FOUND THE LEFT ENGINE WAS RUNNING RICH AT LOW POWER	 SETTINGS.  THE LEFT FUEL SERVO WAS REMOVED AND SENT TO TCM FOR WARRANTY.  A NEW FUEL SERVO WAS INSTALLED FROM STOCK AND	 TRIM RUN COMPLETED, THE AIRCRAFT RETURNED TO SERVICE.  (X)			1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000040500023	20000405	00023	EA  	2000	4	5	20000404SH005    	1	20000225	G	3240	7010FS9545708	SEAL            			CNDAIR	CL600 	CL6002B19   	       	EA  										BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1451 								BRAKE ASSY, PN 5010520-1, FAILED PREMATURELY.  ONE EACH PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILLED WI	TH FLUID.  EVIDENCE OF T-SEAL FAILURE. THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSY.  NOTE:  OEM PARTS INSTA	LLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, PN 5010520-1.  (X)				2	L	7	2 	4F			RT	A21EA   					 
2000040600086	20000406	00086	CE  	2000	4	6	20000404SH011    	1	20000225	G	7602	S29991	BALL JOINT      			CESSNA	414   	414A        	2075907	CE  										MIXTURE CONTROL	FAILED          	B			AK6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	692WT	100  				414A0094				THIS BALL JOINT IS THE CONNECTION BETWEEN THE MIXTURE CABLE AND THE THROTTLE ASSY.  WHEN THIS JOINT FAILS THERE IS NO MI	XTURE CONTROL.  SUBMITTER STATED THIS IS SECOND NEW BALL JOINT SEEN FAIL WITH VERY FEW HRS ON THE PART.  SUBMITTER SUSPE	CTED NEW PART USED TO REPLACE THIS DEFECTIVE ONE WILL FAIL PREMATURELY ALSO.  THIS COULD BE A SERIOUS PROBLEM.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000040600087	20000406	00087	CE  	2000	4	6	20000404SH012    	1	20000104	G	2510	08127358	CASTING         	CESSNA      		CESSNA	414   	414A        	2075907	CE  										COCKPIT SEAT	FAILED          	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	254TM	5500 				414A0254				THE CAPTAIN HAD BOTH ENGINES RUNNING AT THE FBO WITH PARKING BRAKE SET.  HE LEANED BACK IN HIS SEAT TO GET READY TO DEPA	RT AND THE CASTING BROKE LANDING HIM FLAT ON HIS BACK, STRAPPED INTO THE SEAT WITH HIS PASSENGER IN THE CABIN.  HE WAS U	NABLE TO REACH THE PEDALS, YOKE, THROTTLES, WHEN PURCHASING A NEW PART AT THE CESSNA DISTRIBUTOR, THEY INDICATED THEY RE	CENTLY WENT THROUGH 5 OF THESE.  THE PART IS CAST AND CONTAINED A FLAW/POROSITY NOTED BY DISCOLORING INSIDE THE CASTING.	  (X)		1	L	7	2 	3O			 	A7CE    					 
2000040500029	20000405	00029	CE  	2000	4	5	20000404SH013    	1	20000208	G	7500	66003353	GASKET          			LEAR  	35    	35LEAR      	5170600	CE  										NR 1 ENGINE	ERODED          	H				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			SW	99	90WR					35022				DURING CRUISE FLIGHT, THE NR 1 ENGINE FIRE WARNING LIGHT ILLUMINATED.  THE PILOT RETARDED POWER, AND LIGHT EXTINGUISHED.	  ADVANCING POWER AGAIN CAUSED THE LIGHT TO ILLUMINATE AGAIN, RETARDING POWER AGAIN CAUSED IT TO EXTINGUISH.  AN UNEVENT	FUL LANDING WAS MADE.  UPON INVEST, MAINTENANCE FOUND THE BLEED AIR GASKET, PN 6600335-3, ERODED.  THIS GASKET IS INSTAL	LED BETWEEN THE BLEED AIR DUCT ASSY, PN 2655100-72, AND BLEED AIR FITTING ASSY, PN 2652083-25, ON THE RIGHT HAND SIDE OF	 THE ENGINE.  THIS ALLOWED BLEED AIR TO ESCAPE WITH THE HOT GASSES HEATING UP THE NEARBY FIRE LOOP.  GASKET REPLACED AND	 ACFT RETURNED TO SERVICE.  (X)	2	L	7	2 	4F			 	A10CE   					 
2000040500031	20000405	00031	NE  	2000	4	5	20000404SH015    	2	20000119	G	7310		MANIFOLD        			BOEING	777   	777*        	UTILUSE	NM  	PWA   	4090  	PW4090      	52119	NE  					FUEL SYSTEM	LEAKING         	H			WA2D	F	C			ACTIVATE FIRE EXT.      	ABORTED TAKEOFF         			J			WARNING INDICATION        			TO	TAKEOFF        	1			NE	03	EICRT	968  					P222110			FIRE WARNING ON TAKEOFF, BOTTLES DISCHARGED, AIR TURN BACK.  DISASSEMBLY INSPECTION REVEALED MANIFOLD NUT BACKED OFF, NO	T SAFETY WIRED.  PRATT & WHITNEY ENG/MFG REVIEWING.  SUSPECT ASSEMBLY ERROR.  (X)					2	L	7	2 	4F	4	F	RT	T00001SE	E46NE				 
2000040500033	20000405	00033	NM  	2000	4	5	20000404SH017    	1	20000118	G	5711		SPAR            			BOEING	737   	737*        	       	NM  										WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										ONE EACH CRACK EXISTS ON THE UPPER AFT T-SPAR MEASURING 1.5 INCHES LONG, LOCATED AT THE INBOARD END OF THE OUTBOARD MID-	FLAP.  (X)					2	L	7	2 	4F			RT	A16WE   					 
2000040500032	20000405	00032	NM  	2000	4	5	20000404SH018    	1	20000118	G	5711		SPAR            			BOEING	737   	737*        	       	NM  										WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										ONE EACH CRACK EXISTED ON THE UPPER AFT T-SPAR MEASURING 5.0 INCHES LONG, LOCATED AT THE INBOARD END OF THE OUTBOARD MID	 FLAP.  (X)					2	L	7	2 	4F			RT	A16WE   					 
2000040600092	20000406	00092	CE  	2000	4	6	20000404SH023    	1	20000121	G	5510	04320016	STRUCTURE       			CESSNA	150   	152         	2071835	CE  										HORIZONTAL STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										OBTAINED ONE RT HORIZ STAB L/E RT ASSY FROM CESSNA FOR REPAIR OF A DAMAGED STAB.  THE NUTPLATE ON THE RIB MUST BE USED T	O PROPERLY ORIENT THE RIB TO THE FUSELAGE STRUCTURE BEFORE RIVET HOLES ARE DRILLED TO ATTACH THE RIB TO THE STAB SPAR AN	D LEADING EDGE SKID.  THE NEW RIB WAS FOUND CURVED EXCESSIVELY ALONG ITS LONGITUDINAL AXIS CAUSING THE TRAILING EDGE OF 	THE RIB TO BE IMPOSSIBLE TO INSTALL WITH PROPER RIVET EDGE DISTANCE.  OBTAINED 2 MORE RIBS FROM CESSNA TO COMPLETE THIS 	REPAIR.  BOTH HAVE THE SAME DEFECT.  THIS DEFECT IS MOST APPARENT WHEN RIBS ARE LAID ON THEIR SIDE ON A FLAT SURFACE AND	 COMPARED TO A PROPERLY FORMED RIB.  (X)	1	H	7	1 	3O			NT	3A19    					 
2000040600093	20000406	00093	GL  	2000	4	6	20000404SH025    	3	20000207	G	6114		HUB             	MCAULY      		CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17			359  					776009		PROPELLER HUB CRACKED IN THE BLADE SOCKET AREA.						1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2000041100099	20000411	00099	CE  	2000	4	11	20000405SH001    	1	20000210	G	7921	3506210	LINE            			CESSNA	172   	172H        	2072424	CE  										OIL COOLER	LEAKING         	B			FM6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	1413F	294  				17254908				LEAKING OIL PRESSURE LINE TO THE OIL COOLER.  PREMATURE HOSE FAILURE STARTED OUT AS AN OILY SPOT INSIDE THE COWL ON THE 	RIGHT SIDE AND PROGRESSED TO A STREAK OF OIL DOWN THE BELLY WITH OIL WEEPING OUT THE SIDE WALL OF THE HOSE THE FULL LENG	TH.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000040600106	20000406	00106	SW  	2000	4	6	20000405SH002    	1	20000211	G	5510	407023001101	SLAT            			BELL  	407   	407         	       	SW  										HORIZONTAL STAB	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	10EW	865  				53262				SLATS REPLACED WITH NEW.  C/W BELL ASB 407-99-32.   (X)						1	G	7	1 	3U			O	H2SW    					 
2000040600107	20000406	00107	SW  	2000	4	6	20000405SH003    	1	20000211	G	5510	407023002117	SLAT            			BELL  	407   	407         	       	SW  										HORIZONTAL STAB	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	175P	276  				53316				SLATS REPLACED WITH NEW.  C/W BELL ASB 407-99-32.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000040600108	20000406	00108	SW  	2000	4	6	20000405SH004    	1	20000211	G	6500	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL ROTOR DRIVE	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	10EW	674  				53262				BEARINGS REPLACED WITH NEW.  C/W BELL AD 2000-02-12.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000040600109	20000406	00109	CE  	2000	4	6	20000405SH005    	1	20000201	G	5720	817841432	BOLT            			BEECH 	90    	E90         	1152914	CE  										WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	16NM	8087 				LW62				DURING INSPECTION OF WING SPARS IAW AD 89-25-10 AND BEECH SIRM MANUAL, THE LEFT LOWER FORWARD WING BOLT WAS FOUND CRACKE	D USING DYE PENETRANT.  (X)					1	L	7	2 	3T			 	3A20    					 
2000040600110	20000406	00110	NM  	2000	4	6	20000405SH006    	1	20000203	G	5751	SR37P28L02	BEARING         	ALIDSG      		BOEING	727   	727*        	       	NM  										AILERON	FAILED          	B			I6UR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01					1102145					BEARINGS (76) SHATTER WHEN SUBMITTED TO HIGH TORQUE LOADS.  THE BEARING FAILURE CAUSES UNIT TO BIND AND BECOME INOPERATI	VE.  SUBMITTER SUGGESTED LOAD RATING OF THE BEARING IS TOO LOW.  (X)					2	L	7	3 	4F			RT	A3WE    					 
2000040600111	20000406	00111		2000	4	6	20000405SH007    	4	20000204	G	2562	DMQ181A	ANTENNA         			CESSNA	500   	550         	2076604	CE  										ELT	MISINSTALLED    	H				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	99	2GG	2941 				5500286				ELT ANTENNA FOUND BROKEN OFF.  DISCOVERED THAT AN ANTENNA DESIGNED FOR UNDER 250 MPH WAS INSTALLED.  WHEN INSTALLLING AN	TENNAS CARE MUST BE TAKEN TO ENSURE THE CORRECT SPEED CAPABILITIES ARE MAINTAINED.  THIS ANTENNA WAS MOUNTED AFT OF THE 	ENGINE INLET SO NO ADDITIONAL DAMAGE WAS SUSTAINED.  (X)				1	L	7	2 	4F			 	A22CE   					 
2000040600112	20000406	00112	SW  	2000	4	6	20000405SH008    	1	20000125	G	6420	206011809109	STUD            			BELL  	206   	206L3       	1182108	SW  										T/R PITCH HORN	LOOSE           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	358AL					51460				TAIL ROTOR PITCH HORNS, PITCH CHANGE LINK STUDS LOOSE.  REPLACED PART.  (X)						1	G	7	1 	3U			 	H2SW    					 
2000040600113	20000406	00113	EA  	2000	4	6	20000405SH009    	2	20000215	G	7324		FLOW DIVIDER    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	403ER	6011 	140  			17280245	L2786651A			ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT.  REPLACED FUEL FLOW DIVIDER, FUEL SERVO, AND ELECTRIC BOOST PUMP.	  (X)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600114	20000406	00114	EA  	2000	4	6	20000405SH010    	2	20000215	G	7313		NOZZLE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	DIRTY           	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	403ER	6014 	144  			17280245	L2786651A			ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT.  CLEANED ALL FUEL NOZZLES.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600115	20000406	00115	EA  	2000	4	6	20000405SH011    	2	20000215	G	7313		NOZZLE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NR 2 CYLINDER	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	445ER	1360 				17280662	L2785651A			ENGINE HAD MOMENTARY ROUGNESS WHILE IN CRUISE FLIGHT.  REPLACED NR 2 CYLINDER INJECTOR NOZZLE.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600116	20000406	00116	EA  	2000	4	6	20000405SH012    	2	20000215	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	445ER	1406 				17280662	L2785651A			ENGINE HAD MOMENTARY ROUGHNESS DURING CRUISE.  CHANGED ONE SPARK PLUG.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600117	20000406	00117	EA  	2000	4	6	20000405SH013    	2	20000215	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	434ER	1275 				17280655	L2784651A			ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT.  REPLACED ALL SPARK PLUGS.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600118	20000406	00118	EA  	2000	4	6	20000405SH014    	2	20000215	G	7310		MANIFOLD        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SYSTEM	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	434ER	1303 				17280655	L2784651A			ENGINE HAD MOMENTARY ROUGHNESS DURING CRUISE.  REPLACED FUEL MANIFOLD.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600119	20000406	00119	EA  	2000	4	6	20000405SH015    	2	20000215	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	443ER	348  				17280661	L2719151A			DURING NORMAL CRUISE, ENGINE RAN ROUGH FOR SEVERAL SECONDS.  THE SPARK PLUGS WERE SERVICED.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600120	20000406	00120	EA  	2000	4	6	20000405SH016    	2	20000215	G	7313		NOZZLE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NR 3 CYLINDER	FAILED          	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	460ER	1290 				17280668	L2786851A			ENGINE HAD MOMENTARY ROUGHNESS WHILE IN CRUISE FLIGHT.  REPLACED NR 3 CYLINDER NOZZLE.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600121	20000406	00121	EA  	2000	4	6	20000405SH017    	2	20000215	G	7421		SPARK PLUG      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	FAILED          	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	478ER	1179 				17280623	L2779151A			ENGINE HAD MOMENTARY ROUGHNESS DURING CRUISE.  CHANGED ONE SPARK PLUG.  INSTALLED NEW SPARK PLUGS.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000040600123	20000406	00123	EU  	2000	4	6	20000405SH019    	1	20000405	G	2450	MS25244255072251	CIRCUIT BREAKER 			AMD   	FALCON	FALCON20    	2730103	EU  										COCKPIT	FAILED          	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	47LP					457				WHILE CHECKING CIRCUIT BREAKERS FOR AD 70-22-04, FOUND THIS BREAKER WITH MFG DATE OF 9-72 NEARLY JAMMED PER BOEING SB 24	-1019 INSPECTION.  BREAKER DID NOT HAVE FALCON JET IDENTIFIER STICKER ''431L2'' ON IT, SO APPARENTLY IT HAS BEEN INSTALL	ED AFTER AIRCRAFT LEFT THE FACTORY (AW DATE 9-25-81).  BREAKER IS FOR RT LANDING LIGHT.  BREAKER FOR LT LANDING LIGHT AP	PEARS ORIGINAL, AND IS  MADE BY MECHANICAL PRODUCTS.  (X)			2	L	7	2 	4F			RT	A7EU    					 
2000040600125	20000406	00125	NE  	2000	4	6	20000405SH022    	1	20000216	G	6510	SB1111004	BEARING         	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  										TAIL ROTOR	MAKING METAL    	B			JYDR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	09	6962R		1    		EAC10444	64058				AFTER A HALF-HOUR GROUND RUN AND 0.5 FLIGHT, FOUND A LARGE VOLUME OF DISCOLORED (PURPLE IN APPEARANCE) AND METAL CONTAMI	NATED GREASE HAD EXTRUDED PAST THE BEARING SEAL AND WAS FOUND ON THE A/C DECK UNDER THE BEARING.  THE BEARING WAS NOT HO	T TO THE TOUCH AT THAT TIME.  ESTIMATED GREASE LOSS WAS 5 CC''S.  THE BEARING IS BEING RETURNED TO THE AIRCRAFT MANUFACT	URER FOR THEIR INVESTIGATION.  (X)			2	G	7	2 	4U			 	H4EA    					 
2000040600126	20000406	00126	SO  	2000	4	6	20000405SH023    	1	20000203	G	3230	2108000	TUBE            			PIPER 	PA24  	PA24250     	7102404	SO  										MLG	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6960P	4595 				242098				UPON INVEST FOLLOWING LANDING GEAR COLLAPSE DURING TOUCH DOWN, FOUND LINKS CONNECTING L/G MOTOR RELEASE ARM TO MOTOR REL	EASE TUBE BENT TO THEIR OTBD SIDES.  INVESTIGATION SUGGESTS AN ATTEMPT WAS MADE TO MANUALLY RAISE GEAR USING EMERGENCY E	XTEND LEVER THAT COULD CAUSE RELEASE TUBE TO DROP.  (X)				1	L	7	1 	3O			 	1A15    					 
2000040600127	20000406	00127	NM  	2000	4	6	20000405SH024    	1	20000201	G	5412		FIREWALL        			DOUG  	600N  	600N        	3027377	NM  										ENGINE BAY	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	611BP					RN041				AFTER REMOVING THE ENGINE FOR FOD, NOTICED THERE WERE TWO RUBBED INDENTATIONS TO THE UPPER LEFT PORTION OF THE FIREWALL.	  UPON FURTHER INVESTIGATION, NOTED THE BLEED VALVE BOLT HEADS WERE WORN CONSIDERABLY.  THIS WAS THE ORIGINAL FACTORY IN	STALLATION.  (X)				1	G	7	1 	3U			NC	H3WE    					 
2000040700024	20000407	00024	CE  	2000	4	7	20000405SH025    	1	20000129	G	2810		FUEL TANK       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					LEFT	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	714VA	7679 	2107 			15279456	L2000615			ENGINE FAILURE AFTER TAKEOFF.  OUTSIDE AIR TEMPERATURE BELOW FREEZING FOR APPROX 2 WEEKS BEFORE FLIGHT.  SNOW/SLEET IN A	REA SEVERAL DAYS PRIOR TO FLIGHT.  POSSIBLE CAUSE WAS WATER CONTAMINATED FUEL OR CARBURETOR ICING.  DRAINED FUEL TANKS, 	WATER FOUND IN LT FUEL TANK.  FLUSHED FUEL SYSTEM.   CHANGED FUEL CAP TO HELP PREVENT RECURRENCE.  (X)				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000040600130	20000406	00130	GL  	2000	4	6	20000405SH028    	2	20000203	G	7240	6870992	COMBUSTION LINER	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE SECTION	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			HO	HOVERING       	1			EA	21	777CP		199  		33573	3429	CAE830498			DURING HOVERING ON A TRAINING FLIGHT, THE PILOT NOTICED THAT TOT TEMPERATURE WAS HIGHER THAN NORMAL.  AFTER TROUBLESHOOT	ING WHICH INCLUDED CHANGING BLEED VALVE AND CHECKING ANTI-ICE FOR PROPER CLOSING, THERE WAS NO CHANGE.  POWER CHECK ON E	NGINE INDICATED SUBSTANTIAL POWER LOSS.  THIS WAS A RENTAL ENGINE SO THE AMOC WHICH OWNED THE ENGINE WAS NOTIFED.  THEY 	CAME AND REMOVED THE ENGINE.  UPON REMOVAL, A CRACK WAS NOTICED ON THE BACK OF THE COMBUSTION CASE NEXT TO THE FUEL NOZZ	LE ABOUT 3 INCHES LONG.  ENGINE RETURNED TO AMOC FOR REPAIR.  (X)		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000040600131	20000406	00131	CE  	2000	4	6	20000405SH029    	1	20000128	G	2720		CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  										RUDDER	MISROUTED       	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	898DM					E3216				DURING AIRCRAFT''S FIRST ANNUAL INSPECTION (SINCE NEW), FOUND RUDDER CABLE PN R-106-524051-5 INCORRECTLY ROUTED (WRONG B	ULKHEAD LIGHTNING HOLE) THROUGH AREA UNDER LANDING GEAR ACTUATOR.  PART WAS NOT DAMAGED, SIMPLE RE-ROUTING THROUGH CORRE	CT HOLE CORRECTED ISSUE.  ACTT:  69.1 HOURS. (X)				1	L	7	1 	3O			 	3A15    					 
2000040600132	20000406	00132	CE  	2000	4	6	20000405SH030    	1	20000128	G	3246	13889	BEARING         			BEECH 	2000  	2000        	1152000	CE  										MLG WHEEL	DISINTEGRATED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	8283S				OCT89116	NC41				PILOT NOTICED RIGHT MAIN LANDING GEAR INBOARD WHEEL ASSEMBLY TILTED AND HUB CAP BULGED.  UPON INSPECTION, FOUND INBOARD 	BEARING (HUBCAP SIDE) HAD FAILED CAUSING DAMAGE TO WHEEL AND BRAKE ASSY.  NO APPARENT FAULT IN WORKMANSHIP FOUND.  (X)					1	L	7	2 	4T			RT	A38ACE  					 
2000040600133	20000406	00133	SO  	2000	4	6	20000405SH031    	1	20000125	G	2840	548671	FLOAT           			PIPER 	PA28  	PA28181     	7102807	SO  										LT WING TANK	BLOCKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	8276V	4122 			1818190056	288190056				PILOT REPORTED FUEL QUANTITY INDICATION ALWAYS ON ''E'' FOR LEFT TANK.  FOUND THE FLOAT BLOCK WAS DETACHED FROM THE FLOA	T SWING ARM.  THE FLOAT BLOCK WAS SO BADLY WORN IT SLIPPED OVER THE RETAINING WASHER ON THE SWING ARM.  POSSIBLE CAUSE, 	TOO SOFT OF A MATERIAL USED IN FLOAT BLOCK, AND NO INSERT TO PREVENT BLOCK FROM WEARING THROUGH.  REF:  IPC SECT VIII FU	EL FIGURE 47. (X)			1	L	7	1 	3O			 	2A13    					 
2000040600140	20000406	00140	SO  	2000	4	6	20000406SH001    	1	20000114	G	5410	12003851002	FRAME           			EMB   	120   	EMB120RT    	       	SO  										RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	273AS					120222				RIGHT NACELLE FRAME 1 CRACKED OUTBOARD OF TORQUE MOUNT.  ENGINE VIBRATION/TORSION.  SB 120-54-0036 IS BEING INCORPORATED	. (X)					2	L	7	2 	4T			RT	A31SO   					 
2000040600141	20000406	00141	SO  	2000	4	6	20000406SH002    	1	20000114	G	5410	12003851001	FRAME           			EMB   	120   	EMB120RT    	       	SO  										LT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	273AS					120222				LEFT NACELLE FRAME 1 CRACKED OUTBOARD OF TORQUE MOUNT.  ENGINE VIBRATION/TORSION.  SB 120-54-0036 IS BEING INCORPORATED.	 (X)					2	L	7	2 	4T			RT	A31SO   					 
2000041100102	20000411	00102	NM  	2000	4	11	20000406SH003    	1	20000131	G	2740	69778551	SPRING          	BOEING      		BOEING	737   	737*        	       	NM  										HORIZONTAL STAB	FAILED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		19059			KEO1657					SPRINGS, PN 69-77855-1, BROKEN IN THE AUXILIARY BRAKE SYSTEM.  IMPROPER HEAT-TREATING, AUSTENITE, FATIGUE AND INCREASED 	SPRING COIL STRESSES.  SPRINGS, PN 69-77855-1, ARE TO BE REPLACED WITH P/N 69-77855-2 SPRINGS ON ACTUATOR ASSEMBLIES MAN	UFACTURED PRIOR TO S/N KE01730 PER BOEING SL 737-SL-27-090-B.  (X)				2	L	7	2 	4F			RT	A16WE   					 
2000040600142	20000406	00142	NM  	2000	4	6	20000406SH004    	1	20000126	G	2761	120611	PISTON          	BOEING      		BOEING	737   	737*        	       	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2760				530					PISTON IS CRACKED IN THE KEYWAY.  FATIGUE/OVERSTRESSED. (X)						2	L	7	2 	4F			RT	A16WE   					 
2000040600143	20000406	00143	NM  	2000	4	6	20000406SH005    	1	20000126	G	2761	116511	PISTON          	BOEING      		BOEING	737   	737*        	       	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2760				8138					PISTON IS CRACKED NI THE KEYWAY.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2000040600144	20000406	00144	EU  	2000	4	6	20000406SH006    	1	20000128	G	7170	0174078010	DRAIN VALVE     			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					START DRAIN	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	94MD	2008 				6317	5069			VALVE LEAKING AROUND SPLIT LINE OF CASING. (X)						1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2000040600145	20000406	00145	NM  	2000	4	6	20000406SH007    	1	20000131	G	2742	69778551	SPRING          	BOEING      		BOEING	737   	737*        	       	NM  										TRIM ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		50559	18889		00602					SPRINGS, PN 69-77855-1, ARE BROKEN IN THE AUXILIARY BRAKE SYSTEM.  IMPROPER HEAT-TREATING, AUSTENITE, FATIGUE AND INCREA	SED SPRING COIL STRESSES.  SPRINGS, PN 69-77855-1, ARE TO BE REPLACED WITH PN 69-77855-2 SPRINGS ON ACTUATOR ASSEMBLIES 	MANUFACTURED PRIOR TO S/N KEO1730 PER BOEING SL 737-SL-27-090-B.  (X)				2	L	7	2 	4F			RT	A16WE   					 
2000040600147	20000406	00147	EU  	2000	4	6	20000406SH009    	1	20000106	G	3340	G62504	LIGHT           			BOLKMS	117   	BK117B1     	5626012	EU  										FUSELAGE	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	460H					7142				SEARCH LIGHT WILL NOT RETRACT.  REMOVED AND REPLACED. (X)						1	G	7	2 	3U			 	H13EU   					 
2000040600157	20000406	00157	SW  	2000	4	6	20000406SH021    	1	20000107	G	7714	222375022105	INDICATOR       			BELL  	222   	222         	1182122	SW  										GAS PRODUCER	FLUCTUATES      	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911LW					47520				INDICATOR SLOW TO COME UP.  FLUCTUATES AT 90 PERCENT.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H9SW    					 
2000040600160	20000406	00160	NE  	2000	4	6	20000406SH025    	2	20000104	G	7321	4302022307	FUEL CONTROL    			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101650C  	41560	NE  					ENGINE	FAILED          	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911MK					47515				FUEL CONTROL FAILED UPON INSTALLATION.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U	3	U	 	H9SW    	E5NE				 
2000041100132	20000411	00132	SW  	2000	4	11	20000406SH052    	1	20000202	G	2742	047414300	BEARING         	BENDIX      		MOONEY	M20   	M20M        	5870222	SW  										PITCH TRIM SERVO	DAMAGED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	9149Y					270112				LUBRICANT IN ROLLER BEARING AT FORWARD END OF PITCH TRIM TUBE BECAME GUMMED UP AND HARDENED TO THE POINT THAT NEITHER EL	ECTRIC OR HAND WHEEL ACTUATION OF PITCH TRIM WAS POSSIBLE.  MALFUNTION WAS CORRECTED BY REPLACING BEARING.  THERE IS NO 	PROVISION FOR PERIODIC LUBRICATION.  AIRCRAFT WAS MANUFACTURED IN 1991.  (X)				1	L	7	1 	3O			RT	2A3     					 
2000041100133	20000411	00133	EU  	2000	4	11	20000406SH053    	1	20000107	G	6220		COUNTERWEIGHT   			SNIAS 	350   	AS350BA     	8680817	EU  										VIBRATION DAMPER	GALLED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	92MH	3022 				2898				LEAD METAL FLAKING DISCOVERED AT SPHERICAL BEARING INSIDE OF FREQUENCY ADAPTERS.  FURTHER INSP REVEALED BROKEN BOLT INSI	DE OF ANTI-VIBRATOR SPRING HOUSING.  UPON REMOVAL AND DISASSEMBLY OF ANTI-VIBRATOR ASSY, THE LEAD WEIGHTS WERE FOUND SEV	ERELY GALLED DUE TO THE LOSS OF TORQUE AND EVENTUAL FAILURE OF THE ATTACHMENT BOLT THAT SECURES THE SMALLER LEADWEIGHT T	O THE INNER SHAFT OF THE ASSY.  THE ALUM LOCATING PIN HAD ALSO FAILED.  RECOMMEND DURING 500-HR ''T'' INSPECTIONS, THE L	IFTING EYE PLUG BE REMOVED FROM THE TIP OF THE ANTI-VIBRATOR ASSY, AND A TORQUE CHECK BE PERFORMED ON THE LEAD WEIGHT BO	LT.  (X)	1	G	7	1 	3U			NC	H9EU    					 
2000041300363	20000413	00363	SW  	2000	4	13	20000406SH055    	1	20000209	G	5302	407023001101	SLAT            			BELL  	407   	407         	       	SW  										TAIL BOOM	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	98VG					53171				SLATS REJECTED.  REPLACED WITH NEW.  C/W BELL ASB 407-99-32.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000041100135	20000411	00135		2000	4	11	20000406SH056    	4	20000131	G	2561	KS9P0101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED MANUFACTURER''S RECOMMENDED 2 PSI TEST IAW 25-60-1.  ITEM DOM:  SEPT 1981.  (X)																			 
2000041100136	20000411	00136	NE  	2000	4	11	20000406SH057    	2	20000209	G	7421	CH34682	IGNITOR         								PWA   	305   	PW305       	 	NE  					ENGINE	FAILED          	B			R14R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										RECEIVED 3 EACH IGNITORS FROM SUPPLY.  THE 4TH IGNITOR OPS CHECKED OK.  BATCH NUMBER UNKNOWN.  THE IGNITOR USED NORMALLY	 IS INSTALLED ON P&W 305 SERIES ENGINES.  P/N 34682.  (X)										4	F			E35NE				 
2000041100137	20000411	00137		2000	4	11	20000406SH058    	4	20000205	G	2561	AV8AS2100	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOTATION DEVICE FAILED MANUFACTURER''S RECOMMENDED 2 PSI TEST IAW 25-60-33.  DOM:  FEB 1986.  (X)																			 
2000041100138	20000411	00138		2000	4	11	20000406SH059    	4	20000204	G	2561	HA5	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED MANUFACTURER''S RECOMMENDED 2 PSI TEST. DOM:  JAN 1983.  (X)																			 
2000041200076	20000412	00076		2000	4	12	20000406SH060    	4	20000106	G	2565	SWD230300201	SLIDE           	BFGOODRICH  		DOUG  	DC10  	DC1030      	3023501	WP  										GIRT ASSY	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										GIRT ASSEMBLY WAS FABRICATED FROM AN UNKNOWN FABRIC AND IDENTIFIED WITH THE MANUFACTURER''S (BFG) P/N AND WITHOUT THE MA	NUFACTURER''S INSPECTION STAMP AND INSPECTION DATE.  THIS PART IS BEING CONSIDERED AS A SUSPECTED UNAPPROVED PART SINCE 	IT DOES NOT MEET THE MFG DRAWINGS.  NOTE:  THIS UNIT WAS LAST OVERHAULED 6-96.  (X)				2	L	7	3 	4F			 	A22WE   					 
2000041100140	20000411	00140	SO  	2000	4	11	20000407SH001    	2	20000221	G	8530	654960A1	CYLINDER        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470U       	17026	SO  					NR 3	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC	765  				18263638	470757			DURING A ROUTINE COMPRESSION CHECK, THE NR 3 CYLINDER WAS FOUND TO HAVE EXCESSIVE LEAKAGE 53/80 PAST THE PISTON RINGS.  	THE REMOVED CYLINDER WAS FOUND WORN OUT AT THE TOP OF THE CYLINDER.  (X)					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2000041100141	20000411	00141	SO  	2000	4	11	20000407SH002    	2	20000221	G	8520	653877	LIFTER          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470U       	17026	SO  					NR 3 CYLINDER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC	1230 				18263638	470757			DURING THE REMOVAL OF THE NR 3 CYLINDER, THE EXHAUST VALVE LIFTER WAS INSPECTED AND FOUND TO HAVE CHIPS OF MATERIAL MISS	ING FROM THE CORNERS NEAR THE LOWER FACE.  THE FACE OF THE LIFTER AND CAM LOBE WERE NOT FOUND TO HAVE ANY DEFECTS.  (X)					1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2000041100142	20000411	00142	CE  	2000	4	11	20000407SH003    	1	20000215	G	5510	115620020	SUPPORT FITTING 			BEECH 	99    	B99         	1154004	CE  										HORIZONTAL STAB	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	950AA					U159				ROUTINE INSPECTION REVEALED HORIZONTAL STABILIZER LOOSE AT PIVOT SUPPORTS.  REPLACED BOTH LEFT AND RIGHT PIVOT SUPPORT B	RACKETS AND BEARINGS AND HARDWARE.  PROBLEM DETERMINED TO BE DUE TO NORMAL WEAR AND POSSIBLE LACK OF LUBRICATION.  (X)					1	L	7	2 	3T			 	A14CE   					 
2000041200078	20000412	00078	CE  	2000	4	12	20000407SH004    	1	20000127	G	3230		BRAKE ASSY      			CESSNA	421   	421B        	2076014	CE  										MLG	DAMAGED         	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	21	13HB					421B0582				ON LANDING, RT SCISSOR ASSY SEPARATED WHEN BRAKE HOSE CLAMP BROKE, BUSHING AND BOLT PULLED THROUGH SCISSOR ASSY.  RE-ASS	EMBLED SCISSOR ASSY WITH NEW BUSHING AND HOSE CLAMP, INSTALLED WASHERS ON BOLT AND NUT SIDE OF SCISSORS TO PREVENT THIS 	PROBLEM.  THE WASHER ON THE NUT, HOSE CLAMP SIDE OF SCISSORS NOT INSTALLED.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000041200079	20000412	00079	NE  	2000	4	12	20000407SH005    	1	20000226	G	6410	S101521203	BLADE           			SKRSKY	S55   	S55         	8141602	NE  										TAIL ROTOR	CRACKED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	19	17754	648  	98   		BC48	V55398T				ITEM CRACKED AT ROOT ATTACH POINT OF TAIL ROTOR BLADE.  REMOVED TAIL ROTOR BLADE FROM ASSY AND DISCOVERED TAIL ROTOR BLA	DE ATTACH BOLTS WERE NOT TORQUED TO MANUFACTURER SPECIFICATIONS.  (X)					1	G	7	1 	3R			 	1H4     					 
2000041700133	20000417	00133	CE  	2000	4	17	20000407SH010    	1	20000220	G	2700	KS271C	SERVO           			CESSNA	182   	182S        	2072701	CE  										RT WING	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	116ZX					18280042				WHILE PERFORMING A SERVICE BULLETIN ON A PRIMARY SERVO (SB KS271C-5 ALERT) NOTED THE SERVO GEAR TEETH TO HAVE EXCESSIVE 	WEAR.  GEAR BEARING APPEARS TO BE MAKING METAL.  MEAL POWDER RESIN VISIBLE UNDER THE GEAR.  GEAR ROTATION IS NOT SMOOTH 	AND MAKES A SLIGHT GRINDING SOUND.  ACFT TOTAL TIME:  390 HOURS.  PITCH AND TRIM SERVOS OK. (X)				1	H	7	1 	3O			NT	3A13    					 
2000041100143	20000411	00143	NM  	2000	4	11	20000407SH011    	1	20000219	G	2430		RCCB            			DOUG  	MD11  	MD11        	3023602	NM  	GE    	CF6   	CF680C2D1F  	30025	NE  					E/E BAY	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	150EV					48544				LAX/TPE - RIGHT EMER AC BUS'' OFF MESSAGE DURING FLIGHT.  DIVERTED TO CTS WITH LIMITED INSTRUMENT.  ''REAC SENS RELAY/IN	TFC'' CURRENT FAULT FOUND ON CFDS, BUT PERFORM EPU R-T-S TEST PASS AND CHECK ALL FUNCTIONAL NORMAL. FOR MAINTENANCE PREV	ENTION, REPLACED RCCB B1-138 IAW MM 24-25-0, AND PERFORM OPERATIONAL TEST, FUNCTION NORMAL.  (X)				2	L	7	3 	4F	4	F	RT	A22WE   	E31N3				 
2000041100144	20000411	00144	CE  	2000	4	11	20000407SH012    	1	20000131	G	3230	081330031	TORQUE TUBE     			CESSNA	310   	310         	2074202	CE  										MLG	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	2640C	3220 				35040				PART FAILED AT GEAR RETRACTION AFTER TAKEOFF, NOSE GEAR COLLAPSED AT LANDING.  COMPONENT WAS REDESIGNED STARTING WITH A/	C SN 35042.  SUBMITTER SUGGESTED ADDED EMPHASIS INSPECTION THIS AREA ON EARLY CE-310 A/C.  (X)					1	L	7	2 	3O			RT	3A10    					 
2000041100147	20000411	00147	CE  	2000	4	11	20000407SH015    	1	20000221	G	8120	640321	SUPPORT BRACKET 			BEECH 	58    	58TC        	1152746	CE  	CONT  	O520  	TSIO520L    	17040	SO  					RT ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	227BR	3304 				TK31	2419489			DURING ANNUAL INSPECTION, FOUND RT ENGINE TURBO MOUNT BRACKET CRACKED UNDER AND NEAR END OF LOWER STIFFENER BEND.  CRACK	 IS APPROXIMATELY ONE INCH LONG AND EXTENDING TOWARD BUT NOT TO LOWER LIGHTING HOLE.  NO EVIDENCE OF CAUSE FOR CRACK.  (	X)				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2000041100148	20000411	00148	SO  	2000	4	11	20000407SH016    	1	20000221	G	3211	40294006	TRUNNION        			PIPER 	PA42  	PA421000    	7104225	SO  										MLG WW	CRACKED         	D			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	325KW	4102 				425527025				PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION.  A SMALL CRACK WAS FOUND IN THE WEB NEXT TO THE INBOARD LOWER BOLT H	OLE ON BOTH RT AND LT MAIN GEAR.  CRACK WAS DETECTED BY PREVIOUS EXPERIENCE.  CRACK WAS VERIFIED BY DYE PENETRANT.  (X)					1	L	7	2 	4T			RT	A23SO   					 
2000041100149	20000411	00149		2000	4	11	20000407SH017    	4	20000228	G	6122	D20594	SHAFT           	MCAULY      		CESSNA	404   	404         	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6764D				801100	4040693C				CRACK INDICATION.  (X)						1	L	7	2 	3O	3	O	RT	A25CE   	E7CE				 
2000041100150	20000411	00150	NE  	2000	4	11	20000407SH018    	3	20000228	G	6110	2202	BEARING         			PIPER 	PA60  	PA60601P    	7106012	NM  						HARTZL	HCC3Y	HCC3YR2     	NE  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	90370	2724 	1134 			61P0234034		CK923		CRACK INDICATION.  (X)						1	M	7	2 	3O			RT	A17WE   		5	C	P25EA	 
2000041100152	20000411	00152	SO  	2000	4	11	20000407SH020    	1	20000221	G	3211	40294006	TRUNNION        			PIPER 	PA42  	PA421000    	7104225	SO  										MLG WW	CRACKED         	D			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	38AF	4881 				425527029				PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION.  A SMALL CRACK WAS FOUND IN THE WEB NEAR TO THE INBOARD LOWER BOLT H	OLE  ON BOTH RT AND LT MAIN GEAR.  CRACK DETECTED FROM PREVIOUS EXPERIENCE.  CRACK WAS VERIFIED BY DYE PENETRANT.  (X)					1	L	7	2 	4T			RT	A23SO   					 
2000041100153	20000411	00153	CE  	2000	4	11	20000407SH021    	1	20000301	G	2780	KS271C	SERVO           			CESSNA	182   	182S        	2072701	CE  										LE FLAP	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	351BR					18280045				WHILE PERFORMING A SERVICE BULLETIN ON PRIMARY SERVO (SB KS271C-5 ALERT NOTED THE SERVO GEAR TEETH TO HAVE EXCESSIVE WEA	R.  GEAR BEARING APPEARS TO BE MAKING METAL.  THERE WAS A BLACKISH METAL POWDER RESIDUE UNDER THE GEAR.  WHEN THE GEAR I	S TURNED BY HAND IT DOES NOT ROTATE SMOOTHLY AND MAKES A SLIGHT GRINDING NOISE.  ACFT TOTAL TIME:  325 HOURS.  (TIM AND 	PITCH SERVOS NORMAL).  (X)			1	H	7	1 	3O			NT	3A13    					 
2000041100165	20000411	00165	SO  	2000	4	11	20000407SH024    	1	20000217	G	2434	7396509	BELT            			PIPER 	PA28  	PA28R200    	7102811	SO  										ALTERNATOR	DISINTEGRATED   	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	32891					28R7535098				ALTERNATAOR BELT CAME APART.  ALTERNATOR QUIT WORKING.  BATTERY DRY OF ACID.  BATTERY DEAD.  AIRCRAFT LANDED.  LANDING G	EAR NOT DOWN AND LOCKED.  RIGHT GEAR WAS NOT LOCKED.  (X)					1	L	7	1 	3O			 	2A13    					 
2000041300364	20000413	00364	SO  	2000	4	13	20000407SH025    	1	20000407	G	3210	20829	STUD            			PIPER 	PA28  	PA28R180    	7102809	SO  										MLG	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4669J					28R30569				ON ANNUAL INSPECTION (AD 97-01-01R1), FOUND BOTH MAIN LANDING GEARS SIDEBRACE STUDS WORN, RT 0.624 INCH AND THE LT, 0.52	4 INCH AND SIDEBRACE BUSHING WORN.  REPLACED BOTH SIDE BRACE STUDS WITH .6250 INCH, P/N 78717-002, AND REAMED EXISTING B	USHING TO 0.624 INCH PER AD 97-01-01R1.  (X)				1	L	7	1 	3O			 	2A13    					 
2000041100166	20000411	00166		2000	4	11	20000407SH026    	4	20000309	G	3416	03753302	ENCODER         			PIPER 	PA28  	PA28181     	7102807	SO  										COCKPIT	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	4145A	1087 				2843150				INTERNAL LEAK IN ALTITUDE ENCODER GREATER THAN THE ALLOWED 100 FEET/MINUTE IN NON-PRESSURIZED AIRCRAFT.  THESE ENCODERS 	ARE NORMALLY VERY RELIABLE, YET THIS UNIT IS ONLY TWO YEARS OLD AND PROBLEM WAS DISCOVERED ON AIRCRAFT''S FIRST RECERTIF	ICATION SINCE PIPER AIRCRAFT INSTALLATION.  POSSIBLE NARCO MFG DEFECT IN ASSEMBLY OF PRESSURE SENSOR.  LEAKS AROUND GLUE	 JOINT IN SENSOR.  (X)			1	L	7	1 	3O			 	2A13    					 
2000041100167	20000411	00167		2000	4	11	20000407SH027    	4	20000309	G	3416	AR850	ENCODER         			PIPER 	PA28  	PA28181     	7102807	SO  										COCKPIT	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	4145X	1177 				2843152				INTERNAL LEAK IN ALTITUDE ENCODER GREATER THAN THE ALLOWED 100 FEET/MINUTE NON- PRESSURIZED AIRCRAFT.  THESE ENCODERS AR	E NORMALLY VERY REALIABLE, YET RECERTIFICATION SINCE PIPER AIRCRAFT INSTALLATION.  POSSIBLE NARCO MANUFACTURE DEFECT IN 	ASSEMBLY OF PRESSURE SENSOR.  LEAKS AROUND GLUE JOINT IN SENSOR.  (X)				1	L	7	1 	3O			 	2A13    					 
2000041100168	20000411	00168		2000	4	11	20000407SH028    	4	20000309	G	3416	AR850	ENCODER         			PIPER 	PA28  	PA28181     	7102807	SO  										COCKPIT	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	4145G	1078 				2843151				INTERNAL LEAK IN ALTITUDE ENCODER GREATER THAN THE ALLOWED 100 FEET/MINUTE IN NON-PRESSURIZED AIRCRAFT.  THESE ENCODERS 	ARE NORMALLY VERY REALIABLE, YET THIS UNIT IS ONLY TWO YEARS OLD AND PROBLEM WAS DISCOVERED ON AIRCRAFT''S FIRST RECERTI	FICATION SINCE PIPER AIRCRAFT INSTALLATION.  POSSIBLE NARCO MANUFACTURE DEFECT IN ASSEMBLY OF PRESSURE SENSOR.  LEAKS AR	OUND GLUE JOINT IN SENSOR.  (X)			1	L	7	1 	3O			 	2A13    					 
2000041100169	20000411	00169	EA  	2000	4	11	20000407SH029    	2	20000306	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NOSE	MALFUNCTIONED   	H				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			SW	99	445ER	1503 				17280662	L2785651A			DURING FINAL APPROACH, THE ENGINE STUMBLED AND RAN ROUGH.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000041100170	20000411	00170	EA  	2000	4	11	20000407SH030    	2	20000307	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					NOSE	MALFUNCTIONED   	H				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99	476ER	1402 				17280638	L2778251A			WHILE IN THE PATTERN ON A DUAL FLIGHT, THE ENGINE BEGAN TO RUN ROUGH ON THE CROSS-WIND LEG.  IT CONTINUED DOING SO ON DO	WN-WIND.  AN EMERGENCY WAS DECLARED AND A SUCCESSFUL LANDING WAS MADE.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000041100172	20000411	00172	SO  	2000	4	11	20000407SH032    	1	20000221	G	3211	40294006	TRUNNION        			PIPER 	PA42  	PA421000    	7104225	SO  										MLG WW	DAMAGED         	D			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	531MC	3439 				425527007				PART IS MAIN LANDING GEAR REAR SIDE BRACE TRUNNION.  A SMALL ERODE WAS FOUND IN THE WEB NEXT TO THE INBOARD LOWER BOLT H	OLE ON BOTH RT AND LT MAIN GEAR.  CRACK WAS DETECTED BY SMALL CRACK IN PAINT.  CRACK WAS VERIFIED BY DYE PENETRANT.  (X)					1	L	7	2 	4T			RT	A23SO   					 
2000041100173	20000411	00173	SO  	2000	4	11	20000407SH033    	2	20000306	G	8520	11577L	CRANKCASE       			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	661CE		881  			4140943	L514353			CRANKCASE CRACKED FROM BASE OF NR 4 CYLINDER ACROSS THE TOP OF THE BACKBONE TO THE BASE OF NR 3 CYLINDER.  CAUSE UNKNOWN	 AT THIS TIME.  (X)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2000041100174	20000411	00174	SO  	2000	4	11	20000407SH034    	1	20000223	G	3211	C4503	FORK            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCC4Y	HCC4YR2     	GL  	MLG	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	585HV	2528 	1479 			317552041		FH452		CRACK INDICATION .75 INCH LONG IN SLOT 3.  (X)						1	L	7	2 	3O			 	A20SO   		5	C	P52GL	 
2000041700064	20000417	00064	SO  	2000	4	17	20000412SH001    	1	20000221	G	3230	40294006	TRUNNION        			PIPER 	PA42  	PA421000    	7104225	SO  										MLG WW	DAMAGED         	D			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	248DJ	3938 				425527021				PART IS  MAIN LANDING GEAR REAR SIDE BRACE TRUNNION.  A SMALL CRACK WAS FOUND IN THE WEB NEXT TO THE INBOARD LOWER BOLT 	HOLE ON BOTH RT AND LT MAIN GEAR.  CRACK WAS DETECTED BY SMALL CRACK IN PAINT AND VERIFIED BY DYE PENETRANT.  (X)					1	L	7	2 	4T			RT	A23SO   					 
2000041300392	20000413	00392	NE  	2000	4	13	20000412SH003    	3	20000223	G	6114	660714255	HUB             	ROTOL       												ROTOL	R390	R3904123F27 	NE  	PROPELLER ASSY	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		7429 						DAP0085		PROPELLER RECEIVED AT DOWTY AEROSPACE PROPELLERS FOR ROUTINE OVERHAUL.  NOTED AT TEAR DOWN OF PROPELLER, 2 CRACKS AT HUB	 SPLIT LINE IN HUB REAR HALF AT NR 1 AND NR 2 BLADE PORT.  HEAVY CHAPPING FOUND ON BOTH FRONT AND REAR HUB MATING FACES.	 (SPLIT LINE).  HUB REJECTED FROM FURTHER SERVICE.  (X)														6	C	P31NE	 
2000041700156	20000417	00156	SO  	2000	4	17	20000412SH005    	1	20000303	G	2752	573801	VALVE           			GULSTM	G1159 	GIV         	3980115	SO  										FLAP ACTUATOR	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	250VC	3648 				1231				FLAP ACTUATION SLUGGISH WITH ENGINE RUNNING.  WOULD NOT OPERATE USING AUXILIARY SYSTEM.  FOUND FLAP SELECTOR VALVE INTER	NAL SPOOL ACCESS CAP HAD NEVER BEEN SAFETIED (NO SAFETY WIRE MARKS ON UNIT) AND HAD BACKED OUT 3 TURNS.  REPLACED SELECT	OR VALVE (REPLACEMENT UNIT WAS SAFETIED WITH LEAD SEAL).  OPERATION NORMAL. (X)				2	L	7	2 	4F			RT	A12EA   					 
2000041700157	20000417	00157	SO  	2000	4	17	20000412SH006    	1	20000222	G	5410		FRAME           			EMB   	120   	EMB120RT    	       	SO  										RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	283UE	22739				120139				RIGHT NACELLE NR 1 FRAME CRACKED AT THE ENGINE TORQUE TUBE MOUNT AREA.  ENGINE VIBRATION IS A POSSIBLE CAUSE.  FRAME IS 	BEING REPLACED WITH 4 EACH NEW FRAMES, P/N 120-540036-004, WHICH HAS A ''BEEFED'' UP WEB AREA AT THE MOUNTING POINT. (X)					2	L	7	2 	4T			RT	A31SO   					 
2000041300406	20000413	00406	CE  	2000	4	13	20000412SH007    	1	20000412	G	2460		BUSS            			CESSNA	340   	340A        	2076405	CE  										COCKPIT	FAILED          	H				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	01	2696P	2700 				340A0779				AIRCRAFT LOST AVIONICS POWER, EMERGENCY AVIONICS ALSO INOPERABLE.  VFR FLIGHT OUTSIDE OF CLASS B OR CLASS C AIRSPACE.  C	AUSED BY THE BUS BAR CHAFING THROUGH AT CHAFE STRP ON A/C STRUCTURE AND SHORTING OUT.  BUS BAR WAS .25 INCH LONGER THAN 	ADJACENT BARS CAUSING IT TO BEAR AGAINST THE STRUCTURE.  BUS BAR WAS TRIMMED FOR ADDITIONAL CLEARANCE AND NEW CHAFE MATE	RIAL INSTALLED. (X)			1	L	7	2 	3O			 	3A25    					 
2000041300407	20000413	00407	GL  	2000	4	13	20000412SH008    	1	20000210	G	2421	ALY8402	WIRE            			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  					ALTERNATOR	ARCED           	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	17	8843V					30367	209105K71			OPERATOR REPORTED DISCHARGE FROM ALTERNATOR IN CRUISE FLIGHT.  MASTER SWITCH WAS TURNED OFF.  AIRCRAFT LANDED WITHOUT IN	CIDENT.  MAINTENANCE DISCOVERED ONE BRUSH WIRE BROKEN AND THE RETAINER SPRING WELDED TO THE HOLDER.  (X)					1	L	7	1 	3O	3	O	 	A18CE   	E5CE				 
2000041700158	20000417	00158	CE  	2000	4	17	20000412SH009    	1	20000312	G	2430	363800611	BATTERY         			BEECH 	36    	A36TC       	1151603	CE  										E/E BAY	SHORTED         	D				O				OTHER                   				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			SW	03	3683D					EA112				WHILE PILOT WAS COMPLETING THE BEFORE TAKEOFF CHECK LIST, A COMPLETE ELECTRICAL SYSTEM FAILURE WAS EXPERIENCED.  INITIAL	 INVESTIGATION REVEALED NO CIRCUIT BREAKERS, FUSES, OR CURRENT LIMITERS HAD FAILED TO OPEN.  THE BATTERY WAS FOUND SMOKI	NG.  UPON REMOVING THE BATTERY CELL CAPS, ALL CELLS WERE FOUND ALMOST COMPLETELY DRY.  SOURCE OF ELEC SHORT FOUND TO BE 	THE THROTTLE CONTROL CABLE, PN 36-380061-1, HAD CHAFED AGAINST THE POSITIVE BATTERY CABLE INSULATION UNTIL THE 2 CABLES 	SHORTED TOGETHER.  THE BATTERY, POSITIVE BATTERY CABLE, AND THROTTLE CONTROL CABLE ALL HAD TO BE REPLACED TO RETURN THE 	AIRCRAFT TO SERVICE. (X)	1	L	7	1 	3O			 	3A15    					 
2000041700159	20000417	00159	NM  	2000	4	17	20000412SH010    	1	20000217	G	3240		BRAKE           			DOUG  	MD11  	MD11        	3023602	NM  										MLG	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	272WA		6984 			48437				BRAKE ASSY WAS RECEIVED FROM AIR CARRIER FOR AN OVERHAUL SERVICE.  UPON DISASSEMBLY, IT WAS IDENTIFIED THE AFFECTED BRAK	E SUFFERED AN EXTREME CARBON OXIDATION BREAK-DOWN ON THE INNER DIAMETER OF THE HEAT SINK.  SUBMITTER SUGGESTED AN ANALYS	IS OR REVIEW OF THE CARBON COMPOSITE MANUFACTURING PROCESSES.  (X)				2	L	7	3 	4F			RT	A22WE   					 
2000041300410	20000413	00410	WP  	2000	4	13	20000412SH011    	2	20000309	G	7250	30723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON FORWARD SIDE IN WEB AREA AND AFT SIDE IN POST FIR TREE AREA.  REF:  LOT 	NUMBER 00P040.  (X)										4	F			E6WE				 
2000041300411	20000413	00411	WP  	2000	4	13	20000412SH012    	2	20000309	G	7230	30723163	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					HP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON FORWARD SIDE IN POST FIR TREE AREA.  REF:  LOT NUMBER 99P243.  (X)											4	F			E6WE				 
2000041300412	20000413	00412	WP  	2000	4	13	20000412SH013    	2	20000316	G	7250	30747522	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA ON BOTH FORWARD AND AFT SIDES.  REF:  LOT NUMBER 99P2	78										4	F			E6WE				 
2000041300413	20000413	00413	WP  	2000	4	13	20000412SH014    	2	20000309	G	7250	30723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON FORWARD SIDE IN POST FIR TREE AREA.  REF: LOT NUMBER 99P341.  (X)											4	F			E6WE				 
2000041300414	20000413	00414	WP  	2000	4	13	20000412SH015    	2	20000310	G	7250	30723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH GRIND MARKS THROUGHOUT FIR TREE AREA.  REF:  LOT NUMBER:  00P040.  (X)											4	F			E6WE				 
2000041700160	20000417	00160	SO  	2000	4	17	20000412SH016    	1	20000307	G	3213	65319004	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  										LT MLG STRUT	CRACKED         	B			C85R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2159H	11250				287916192				MAIN GEAR STRUT HOUSING HAS ATTACH EARS ON IT WHERE UPPER END OF TORQUE LINK ATTACHES.  STUDENT REPORTED SHIMMEY AND VIB	RATION AFTER LANDING.  WHEN ACFT WAS CHECKED, ONE OF TWO EARS ON  THE STRUT HOUSING WAS FOUND BROKEN OFF.  PART THOUGHT 	TO BE ORIGINAL.  ACFT HAS 11,250.0 HRS SINCE NEW IN 1979.  UNKNOWN IF FATIGUE PROBLEM OR STUDENT LANDED IN A GROSS-WIND 	AND SIDE-LOADED GEAR, OR A COMBINATION OF BOTH.  (X)			1	L	7	1 	3O			 	2A13    					 
2000041700161	20000417	00161	EU  	2000	4	17	20000412SH017    	1	20000202	G	6720	AC66375	HOUSING         	DUNLOP      		SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR SERVO	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	911LR	5791 	1852 		GD346	2404				FAILED EDDY CURRENT TESTING.  CRACK DETECTED AT HOLE PLUG (CYLINDER) ON LOWER END OF SERVO BODY.  POSSIBLE CAUSE, DURING	 MANUFACTURING, HOLE PLUG EITHER TOO LARGE OR HOLE PLUG INSTALLED INCORRECTLY.  (X)					1	G	7	1 	3U			 	H9EU    					 
2000041300418	20000413	00418	WP  	2000	4	13	20000412SH018    	1	20000109	G	6420	369021800501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	LACK OF LUBE    	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		1709 			1151D				DURING INSPECTION, THE TAIL ROTOR SWASHPLATE WAS FOUND LOW ON GREASE.  FURTHER INSPECTION REVEALED NO DEFECTS AND UNIT W	AS RE-GREASED AND RETURNED TO SERVICE. (X)					1	G	7	1 	3U			 	H3WE    					 
2000041300419	20000413	00419	GL  	2000	4	13	20000412SH019    	2	20000128	G	7420	6870855	IGNITION LEAD   			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CHAFED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D	CAE832750			DURING POST-FLIGHT, IGNITION LEAD WAS FOUND CHAFING ON THE LOWER B-NUT OF THE PC AIR REFERENCE LINE ON THE GOVERNOR.  FU	RTHER INSPECTION REVEALED THE ADEL CLAMPS FOR THE LEAD AND LINE, AT THAT POINT, WERE MISSING.  REPLACED MISSING CLAMPS. 	 (X)				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000041300428	20000413	00428	WP  	2000	4	13	20000412SH020    	1	20000104	G	6520	369D254225	SEAL            			HUGHES	369   	369D        	4470706	WP  										T/R TRANSMISSION	LEAKING         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R				2136	1151D				DURING INSPECTION, FOUND THE TAIL ROTOR OUTPUT SEAL LEAKING.  REPLACED SEAL. (X)						1	G	7	1 	3U			 	H3WE    					 
2000041300429	20000413	00429	GL  	2000	4	13	20000412SH021    	2	20000104	G	7310	AN8378D	FITTING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C*       	 	GL  					FUEL SYSTEM	LOOSE           	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING INSPECTION, DISCOVERED THE FIREWALL FUEL FITTING (BULKHEAD FITTING) WAS LOOSE IN THE FIREWALL.  RE-TORQUED JAM NU	T.   (X)					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000041300439	20000413	00439	WP  	2000	4	13	20000412SH023    	1	20000110	G	3110		CLAMP           			HUGHES	369   	369D        	4470706	WP  										TOT HARNESS	WRONG PART      	B			EOOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING INSPECTION, THE ADEL CLAMP ON THE TOT LEAD AT THE EXHAUST CLAMP WAS FOUND TO BE THE WRONG PART NUMBER AND SUBSEQU	ENTLY THE CUSHION WAS UNABLE TO SURVIVE THE TEMPERATURES.  REPLACED WITH PROPER PART NUMBER CLAMP.   (X)					1	G	7	1 	3U			 	H3WE    					 
2000041300440	20000413	00440	SW  	2000	4	13	20000412SH024    	1	20000309	G	6310	206040118001	COUPLING        			BELL  	206   	206B        	1181511	SW  										M/R DRIVE	CHIPPED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	304MH					1742				DURING NORMAL 600-HOUR/12-MONTH INSPECTION AND REPACK OF  MAIN ROTOR DRIVESHAFT, DISCOVERED A GEAR TOOTH (ON THE END) OF	 THE OUTER COUPLING WAS CHIPPED.  SUBMITTER SIFTED THROUGH THE GREASE, BUT COULD NOT FIND ANY EVIDENCE OF THIRD CHIP.  P	ART WAS RED-TAGGED AND DESTROYED.  A NEW OUTER COUPLING OF SAME PART NUMBER INSTALLED AND AIRCRAFT RETURNED TO SERVICE. 	(X)			1	G	7	1 	3U			 	H2SW    					 
2000041700162	20000417	00162	GL  	2000	4	17	20000412SH025    	1	20000314	G	3213	2082100701	AXLE            			DIAMON	DA20  	DA20A1      	       	GL  										RT MLG WHEEL	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	125MF	3030 				10016				DURING WALK-AROUND, INSTRUCTOR NOTICED CRACK ON TOP OF AXLE FLANGE BOLT THROUGH-HOLE.  SUSPECT CRACK FORMED BY STRESS CO	RROSION.  SUBMITTER RECOMMENDED AXLE BE REPLACED AT 2,000-HR OR REPLACE ANODIZED ALUMINUM WITH ONE MADE OF STEEL JUST LI	KE THE MATING SURFACE OF GEAR LEG.  (X)				1	L	7	1 	3O			NT	TA4CH   					 
2000041300441	20000413	00441	CE  	2000	4	13	20000412SH026    	1	20000207	G	2731	C419175	CHAIN           			CESSNA	500   	550         	2076604	CE  										ELEVATOR	SEPARATED       	E				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CE	01	7ZU	225  				5500433				UPON DESCENT INTO FCM, PILOT REPORTED ELECTRIC ELEVATOR TRIM WAS UNRESPONSIVE.  PILOT ATTEMPTED TO HAND TRIM THE AIRCRAF	T AND FOUND MANUAL TRIM WHEEL FREE TO TURN WITH NO RESISTANCE.  CREW FOUND ELEVATOR CONTROL HEAVY AND HARD TO MOVE.  THE	 PILOTS ELECTED TO DIVERT INTO MSP.  INVESTIGATION INTO THE CAUSE REVEALED THE TRIM CABLE FORWARD ATTACH CHAIN MASTER LI	NK HAD BECOME DISCONNECTED AND WAS FOUND IN THE BELLY OF THE AIRCRAFT ALONG WITH THE ATTACHING HARDWARE AND THE TRIM CAB	LES.  NO OTHER DISCREPANCIES WERE FOUND WITH THE SYSTEM. (X)		1	L	7	2 	4F			 	A22CE   					 
2000041700163	20000417	00163	EA  	2000	4	17	20000412SH027    	2	20000318	G	7322	LW10540	CARBURETOR      			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					ENGINE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	33	6YB	1800 				321179	L669940			CARBURETOR SEPARATED AT PARTING SURFACE CAUSING BOTTOM HALF OF CARBURETOR TO ALMOST FALL OFF.  LOCKING TABS WERE LOCKED,	 BOLTS WERE LOOSE.  SUBMITTER STATED THIS IS THE 3RD CARBURETOR TO HAVE THIS TYPE FAULT.  (X)					1	L	7	1 	3O	3	O	 	A3SO    	E295				 
2000041300487	20000413	00487	WP  	2000	4	13	20000412SH028    	1	20000307	G	7720		PROBE           			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	DAMAGED         	B			H8OR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	9094F	1000 				1110352S	CEA82310			THE NYLON INSERT IN THE TEMPERATURE PROBE LET GO RESULTING IN FLUCTUATION AND DROPPING OIL PRESSURE AND A LOSS OF OIL.  	THE ENGINE HAD TO BE TORN DOWN FOR INSPECTION.  MAIN DAMAGE SEEMS TO BE THE ENGINE''S NR 8 BEARING WHICH WAS DESTROYED. 	 (X)				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000041300488	20000413	00488	CE  	2000	4	13	20000412SH029    	1	20000316	G	3230	554110313	UPLOCK          			CESSNA	500   	550         	2076604	CE  										LT MLG	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	CCDGA					657				CUSTOMER STATED HE REPLACED LT MLG UPLOCK HOOK DUE TO EXCESS PLAY AT ATTACH BOLT/SPACER AREA.  MAINT FACILITY CONDUCTED 	PHASE-5 INSP AND ADD''L WORK.  DURING L/G EXTEND/RETRACT TEST NOTED DURING EXT CYCLE, NOSE AND RT MLG EXTENDED NORMALLY,	 BUT LT FREE FELL.  AFTER T/S, FOUND PRESS TO UPLOCK CYL, BUT NO PRESS AT OUTSIDE WHICH GOES TO DOWN SIDE OF MLG ACTUATO	R.  FOUND IF CLEVIS PIN WAS REMOVED FROM LINKAGE, THAT CONNECTS UPLOCK ACT TO HOOK, LT GEAR ACT EXTENDED NORMALLY.  NOTI	FIED CESSNA UPLOCK HOOK WAS CONTACTING RADIUS OF SUPPORT BRACKET.  CESSNA BELIEVED CAUSE WAS A RADIUS CUT WAS ELIMINATED	 DURING MFG.  SUPPORT HAD GOUGE WHERE HOOK CONTACTED IT AND CESSNA REQUESTED BOTH HOOK AND SUPPORT BE REPLACED.  (X)	1	L	7	2 	4F			 	A22CE   					 
2000041300489	20000413	00489	NE  	2000	4	13	20000412SH030    	2	20000320	G	7310	30718321	MANIFOLD        			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	29003	NE  					FUEL SYSTEM	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	727AT	6382 				284	P76205			DURING ROUTINE 300-HR ENG INSP, FUEL DISCOVERED PUDDLED INSIDE THE LEFT ENGINE LOWER COWLING.  A LEAK CHECK CONFIRMED FU	EL LEAKING FROM BOTTOM RIB DUCT WHERE THE PRIMARY AND SECONDARY FUEL MANIFOLD LINES ENTER THE 6 O''CLOCK STRUT.  LEAK WA	S PINPOINTED TO A CRACKED INNER FUEL MANIFOLD FITTING INSIDE STRUT.  INNER MANIFOLD HAD CRACKED AT SECONDARY MANIFOLD FI	TTING WHERE IT IS BRAZED ONTO INNER MANIFOLD.  (X)			2	M	7	2 	4F	4	F	 	A2SW    	E6WE				 
2000041300497	20000413	00497	SW  	2000	4	13	20000412SH033    	1	20000114	G	7722		BUMPER BLOCK    	AMETEK      	SEL019DS1   	BELL  	206   	206L1       	1182107	SW  										COCKPIT	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	XATKU				217AB	45697				DURING START, POINTER STOP ARM STUCK TO LATEX BUMPER.  REPLACED LATEX BUMPER WITH NON-STICKING MATERIAL. (X)						1	G	7	1 	3U			 	H2SW    					 
2000041300506	20000413	00506	SW  	2000	4	13	20000412SH034    	1	20000224	G	7722		BUMPER BLOCK    	AMETEK      	SEL019DS1   	BELL  	206   	206L1       	1182107	SW  										COCKPIT	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5740L				300BA	45459				DURING START, POINTER STOP ARM STUCK TO LATEX BUMPER. REPLACED LATEX BUMPER WITH NON-STICKING MATERIAL.  (X)						1	G	7	1 	3U			 	H2SW    					 
2000041300507	20000413	00507	SW  	2000	4	13	20000412SH035    	1	20000305	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR DRIVE	ROUGH           	B			ALGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	437AL	329  			AF8906	53141				BEARINGS NOISEY AND ROUGH.  REMOVED AND REPLACED 2 EACH BEARINGS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000041300508	20000413	00508	SW  	2000	4	13	20000412SH036    	1	20000305	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR DRIVE	ROUGH           	B			ALGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	437AL	5329 			AF8906	53141				BEARINGS NOISEY AND ROUGH.  REMOVED AND REPLACED 2 EACH BEARINGS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000041700165	20000417	00165	SO  	2000	4	17	20000412SH039    	1	20000223	G	7922	53E19600	VERNATHERM      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					OIL TEMP REGULAT	DAMAGED         	B			FGQR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	01	137JH					318252025	L247468A			PILOTS REPORTED ENGINE NOT MAKING FULL POWER AND OIL PRESSURE LOW.  MAINTENANCE FOUND A PIECE OF CLIP UNDER THE OIL PRES	SURE RELIEF VALVE.  THE RETAINING CLIP FOR THE VERNATHERM VALVE FOUND TO BE THE SOURCE.  FOUR NEW VERNOTHERM VALVES INST	ALLED. (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000041700166	20000417	00166	CE  	2000	4	17	20000412SH040    	1	20000222	G	7810	1099500001	EXHAUST PIPE    			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE	CRACKED         	B			BQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	600FL	282  				LJ1540				CRACKED EXHAUST STACK.   2.75 INCH CRACK WAS FOUND AROUND CIRCUMFERENCE AT WELD ATTACH POINT OF NACELLE INLET DE-ICE TUB	E.  SUBMITTER STATED THIS IS THE 5TH OCCURRENCE OF SAME PROBLEM ON SAME AIRCRAFT.  A RAYTHEON REP HAS BEEN CONTACTED AND	 A FUTURE SERVICE BULLETIN IS PENDING RELEASE. (X)				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2000042500114	20000425	00114	EU  	2000	4	25	20000413SH001    	1	20000222	G	5210	1172428112	CATCHER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				CATCHER WORN.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			NC	H13EU   					 
2000042500115	20000425	00115	EU  	2000	4	25	20000413SH002    	1	20000222	G	5210	1172428212	CATCHER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										RT DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				RIGHT CATCHER WORN.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			NC	H13EU   					 
2000041700170	20000417	00170	EU  	2000	4	17	20000413SH004    	1	20000222	G	5210	1172427302	GUIDE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										CREW DOOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				RIGHT GUIDE WORN.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			NC	H13EU   					 
2000041700171	20000417	00171	EU  	2000	4	17	20000413SH005    	1	20000222	G	6330	L633M2001105	MOUNT           			UROCOP	EC135 	EC135P1     	8680990	EU  										TRANSMISSION	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	911SV	391  				0070				LEAKING FLUID.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			O	H88EU   					 
2000041700173	20000417	00173	SW  	2000	4	17	20000413SH007    	1	20000115	G	6322	230365001101	BLOWER          			BELL  	230   	230         	1182149	SW  										OIL COOLER	VIBRATION       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	2135 				23019				OIL COOLER BLOWER HAD HIGH VIBRATION, .4 IPS.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			NC	H9SW    					 
2000041700174	20000417	00174		2000	4	17	20000413SH008    	4	20000302	G	3425	066304605	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT HSI	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4572R					S663				NEEDLE DOES NOT FULLY DEFLECT.   REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H3EU    					 
2000041700175	20000417	00175	SW  	2000	4	17	20000413SH009    	1	20000209	G	6410	222016001131	BLADE           			BELL  	230   	230         	1182149	SW  										TAIL ROTOR	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1257 				23019				PITCH CHANGE BEARINGS CRACKED.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			NC	H9SW    					 
2000041700176	20000417	00176	SW  	2000	4	17	20000413SH010    	1	20000209	G	6410	222016001123	BLADE           			BELL  	230   	230         	1182149	SW  										TAIL ROTOR	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	2465 				23019				PITCH CHANGE BEARINGS CRACKED.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			NC	H9SW    					 
2000041700177	20000417	00177	EU  	2000	4	17	20000413SH011    	1	20000224	G	5320	1176625501	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE BAY	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FIRE WALL ASSEMBLY CRACKED.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2000041700178	20000417	00178	EU  	2000	4	17	20000413SH012    	1	20000215	G	7712	10594575	TRANSMITTER     			BOLKMS	105   	BO105LSA3   	5626020	EU  										ENGINE TORQUE	READS HIGH      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	8118Y	342  				2017				TORQUE TRANSMITTER OUT OF CALIBRATION.  READING HIGH SETTING OF LIGHT.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H3AU    					 
2000041700179	20000417	00179	EU  	2000	4	17	20000413SH013    	1	20000301	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										TRIPLE TACH	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG					7083				NR 2 NEEDLE WENT TO ZERO IN-FLIGHT.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700180	20000417	00180	NE  	2000	4	17	20000413SH014    	2	20000125	G	7313	0283317500	INJECTOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	CLOGGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				INJECTOR CLOGGED.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU				 
2000041700181	20000417	00181	NE  	2000	4	17	20000413SH015    	2	20000125	G	7313	0283317500	INJECTOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	CLOGGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				INJECTOR CLOGGED.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU				 
2000041700183	20000417	00183	EU  	2000	4	17	20000413SH016    	1	20000119	G	6340	1179403605	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRANSMISSION OIL	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC					7509				TRANS OIL INDICATION LIGHT INOPERATIVE.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2000041700184	20000417	00184		2000	4	17	20000413SH017    	4	20000202	G	2397	CIX100XVHGK66P	WIRE            			BOLKMS	105   	BO105S      	5626006	EU  										COMM	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4572R					S663				UPON INITIAL INSTALLATION, CORD SQUEALS AS SOON AS HOOKED UP.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H3EU    					 
2000041700185	20000417	00185	EU  	2000	4	17	20000413SH018    	1	20000203	G	2913	40165	PUMP            			BOLKMS	117   	BK117A1     	5626010	EU  										HYD SYSTEM	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117M					S7023				SPLINES ON HYDRAULIC PUMP WORN.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700188	20000417	00188		2000	4	17	20000413SH020    	4	20000224	G	2311	TFM500G	TRANSCEIVER     			SNIAS 	350   	AS350B2     	8680813	EU  										UHF COMM	INTERMITTENT    	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	40751	221  				3154				TRANSCEIVER TRANSMITS INTERMITTENTLY ON UHF FREQUENCIES.  REMOVED AND REPLACED.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000041700189	20000417	00189	SW  	2000	4	17	20000413SH021    	1	20000118	G	3340	900601	LANDING LIGHT   			BELL  	230   	230         	1182149	SW  										FUSELAGE	INOPERATIVE     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	4UV					23019				LANDING LIGHT HAD NO POWER AT LIGHT.  LIGHT WILL NOT COME ON.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			NC	H9SW    					 
2000041700190	20000417	00190	EU  	2000	4	17	20000413SH022    	1	20000211	G	3310	1179203103	CONTROLLER      			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	INOPERATIVE     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	1140H	3    				7078				COPILOT''S LIGHTING INOPERABLE.  NO OUTPUT FROM UNIT.  WORKED 2.7 HOURS AFTER INSTALLATION.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700191	20000417	00191	EU  	2000	4	17	20000413SH023    	1	20000209	G	3310	1179203103	CONTROLLER      			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	INOPERATIVE     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	1140H					7078				CONTROL LUNIT WILL NOT ILLUMINATE LIGHT.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700195	20000417	00195	EU  	2000	4	17	20000413SH024    	1	20000214	G	6520	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DELAMINATED     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	350AZ	512  				3127				BEARING CRACKED ON OUTER CENTER OF LAMINATION.  REMOVED AND REPLACED.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000041700197	20000417	00197		2000	4	17	20000413SH026    	4	20000115	G	3425	066304605	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT HSI	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG					7083				KI525A INTERNAL LIGHT INOPERATIVE.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700198	20000417	00198	EU  	2000	4	17	20000413SH027    	1	20000124	G	6210	117151321	BLADE           			BOLKMS	117   	BK117B1     	5626012	EU  										MAIN ROTOR	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	170MC	193  				7217				LEADING EDGEOF MAIN ROTOR BLADE  DEBONDING (INBOARD JOINT).  193.4 HOURS SINCE REPAIR/OVERHAUL.  REMOVED AND REPLACED.  	(X)					1	G	7	2 	3U			 	H13EU   					 
2000041700205	20000417	00205		2000	4	17	20000413SH028    	4	20000131	G	3421	5040017926	GYRO            			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	FAILED          	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	170MC					7217				ATTITUDE GYRO WILL NOT CAGE.  TECHNICIAN STATED UNIT ONLY WORKED FOR ONE WEEK AFTER INSTALLATION.  REMOVED AND REPLACED.	   (X)					1	G	7	2 	3U			 	H13EU   					 
2000041700233	20000417	00233	SW  	2000	4	17	20000413SH036    	1	20000106	G	6300	222044006109A	SHAFT           			BELL  	230   	230         	1182149	SW  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	WILL NOT BALANCE	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1246 				23019				ENGINE SIDE OF SHAFT WILL NOT BALANCE.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U	3	U	NC	H9SW    	E1GL				 
2000041700236	20000417	00236		2000	4	17	20000413SH039    	4	20000124	G	3416	1042011968E	ENCODER         			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	MALFUNCTIONED   	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117MK					7196				ALTIMETER OUT OF CALIBRATION.  DOES NOT AGREE WITH COPILOT''S ALTIMETER OR TEST BOX.  OFF AT 3,000 FEET.  REMOVED AND RE	PLACED.   (X)					1	G	7	2 	3U			NC	H13EU   					 
2000041700237	20000417	00237	EU  	2000	4	17	20000413SH040    	1	20000113	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FLUCTUATES      	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	527MB					7103				INDICATOR FLUCTUATES UNDER POWER.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700238	20000417	00238	EU  	2000	4	17	20000413SH041    	1	20000112	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	DAMAGED         	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	527MB					7103				NG INDICATOR TRIPPED CIRCUIT BREAKER WHEN INSTALLED AFTER REPAIR.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000041700242	20000417	00242	EU  	2000	4	17	20000413SH042    	1	20000115	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										TRIPLE TACH	INACCURATE      	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	171MU					7138				TRIPLE TACHOMETER, NR 2 NEEDLE READS IMPROPER.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000042500152	20000425	00152	CE  	2000	4	25	20000413SH044    	1	20000222	G	7810	1099500001	EXHAUST PIPE    			BEECH 	90    	C90A        	1152911	CE  										ENGINE	CRACKED         	B			BQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	600FL	21   				LJ1540				CRACKED EXHAUST STACK.  SUBMITTER STATED THIS IS THE 6TH OCCURRENCE OF SAME PROBLEM ON SAME AIRCRAFT. 1.5 INCH CRACK WAS	 FOUND AROUND CIRCUMFERENCE AT WELD ATTACH POINT OF NACELLE INLET DE-ICE TUBE.  A RAYTHEON REP HAS BEEN CONTACTED AND A 	FUTURE SERVICE BULLETIN IS PENDING RELEASE.   (X)				1	L	7	2 	3T			RT	3A20    					 
2000041900263	20000419	00263	EA  	2000	4	19	20000413SH045    	2	20000102	G	8520		SHAFT           			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  					IDLER GEAR	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	5986Z	1591 				188242	L4842427A			1,590.6 HRS SINCE FACTORY NEW ENGINE INSTALLED.  CRANKSHAFT APPEARED TO BE BINDING WITH SPARK PLUGS REMOVED. METAL (STEE	L & ALUM) IN SCREENS.  UPON REMOVAL OF MAGNETOS, OBSERVED LT IDLER GEAR COCKING BEFORE IT TURNED, WHILE MOVING CRANKSHAF	T FLANGE BACK AND FORTH APPROX 30 DEGREES.  UPON REMOVAL OF ACCESSORY CASE, FOUND LT IDLER SHAFT LOOSE AT CRANKCASE ATTA	CH.   DAMAGE NOTED TO IDLER SHAFT AND CRANKCASE BOSS, RT IDLER SHAFT ATTACH BOLT, LOWER BOLT FND FINGER TIGHT, UPPER, BO	LT FND PROPERLY TORQUED.  BOTH STILL SAFETY WIRED.  ENGINE DISMANTLED FOR COMPLETE O/H.  (X)		1	H	7	1 	3O	3	O	 	1A2     	E274				 
2000041900264	20000419	00264	CE  	2000	4	19	20000413SH046    	1	20000413	G	3241	99123056	CONTROL BOX     		HYTROL7K3427	CESSNA	500   	560CESSNA   	2076750	CE  										ANTI-SKID SYSTEM	FAILED          	H				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	05	560MM	2545 				5600235				DURING TAH, PRIOR TO TAKEOFF, FOOT BRAKES APPLIED, NO BRAKING ACTION TOOK PLACE.  BRAKE SYS PRE-SELECTED TO THE ATTACHED	 MODE.  INVEST REVEALED WITH ANTI-SKID SELECTED THE FAULT LIGHT WAS OUT WITH BRAKES APPLIED.  INITIALLY, BRAKES WENT ON,	 BUT RELEASED AND STAYED RELEASED.  APPEARS ANTI-SKID CONTROL BOX FAILED WITH BRAKE VALVES IN OPEN POSITION.  BRAKE ANTI	-SKID CONTROL BOX, PN 9912305-6, SN 847, WAS REMOVED.  RECORDS SHOWS ORIG INSTALL 12-93, ACFT BUILD DATE.  A TEST OF IND	ICATION SYS FOR ANTI-SKID SHOWED SWITCH ON-LIGHT OUT, BUT ON REPLACEMENT PART, SWITCH ON-LIGHT OUT-LIGHT ON-LIGHT OUT.  	(X)	2	L	7	2 	4F			RT	A22CE   					 
2000041900266	20000419	00266	CE  	2000	4	19	20000413SH048    	1	20000218	G	2820	17160081	SEAL            			CESSNA	206   	206H        	2073301	CE  										FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	7264D	97   				20608062				DURING INITIAL 100-HOUR INSPECTION ON A NEW CESSNA 206H, FUEL WS FOUND LEAKING FROM THE RIGHT SIDE FUEL SENDER SCREWS.  	INSPECTION REVEALED LEAK EMANATING FROM IMPROPERLY SEALED NUT RING.  AFTER REMOVAL, INSPECTION REVEALED TWO VOIDS BETWEE	N NUT RING AND RIB.  EXAMINATION OF AREA REVEALED AN UNKNOWN WHITE POWDERY SUBSTANCE IN THE VOID WHERE SEALANT WAS OMITT	ED.  POSSIBLE CAUSE WAS IMPROPER SEALING TECHNIQUES DURING THE AIRCRAFT''S MANUFACTURING PROCESS.   (X)			1	H	7	1 	3O			RT	A4CE    					 
2000042500156	20000425	00156	EU  	2000	4	25	20000413SH049    	2	20000211	G	7320	CASE504	REGULATOR       			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					RT ENGINE	FAULTY          	B			BTVR	O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			GL	23	7800		3445 			1098	16135			ON DESCENT FROM HIGH ALTITUDE WITH AUTO-THROTTLES DISCONNECTED, THE RT ENGINE WOULD NOT DECREASE TO AN IDLE SETTING WITH	 THE THROTTLES PHYSICALLY IN THE HARD IDLE POSITION.  ENGINE FINALLY RETARDED TO IDLE WHEN DESCENDING BELOW 10,000 FEET,	 SLOWING BELOW 260 KNOTS AND TURNING ON ENGINE AND WING ANTI-ICE.  AIRCRAFT WAS BEING FLOWN ON A MAINTENANCE TEST FLIGHT	 DUE TO A DOUBLE ENGINE CHANGE.  AIRCRAFT LANDED SAFELY.  (X)			2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2000041700004	20000417	00004	EU  	2000	4	17	20000413SH051    	1	20000215	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105LSA3   	5626020	EU  										M/R MAST	READS HIGH      	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	8118Y	342  				2017				MAST INDICATOR OUT OF CALIBRATION.  READING HIGH SETTING OF LIGHT.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			 	H3AU    					 
2000041900270	20000419	00270	CE  	2000	4	19	20000413SH052    	1	20000303	G	2120		SMOKE           			LEAR  	35    	35A         	5170602	CE  										CABIN	DETECTED        	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	99	77NR					503				CARPET EDGE CAME INTO CONTACT WITH WING HEAT DUCT.  WING HEAT WAS USED LONGER THAN NORMAL DUE TO WEATHER CONDITIONS.  TH	E CARPET EDGE WAS HEATED UNTIL IT STARTED SMOKING.  THE AIRCRAFT DIVERTED FOR PRECAUTION.  THE CARPET WAS TRIMMED BACK A	ND ADDITIONAL INSULATION WAS INSTALLED TO PREVENT RECURRENCE.  (X)				2	L	7	2 	4F			 	A10CE   					 
2000041900271	20000419	00271	SO  	2000	4	19	20000413SH053    	1	20000208	G	3222	67037004	STRUT           			PIPER 	PA44  	PA44180     	7104402	SO  										LT MLG	BROKEN          	B				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			GL	21	851ND	5737 				4495005				AFTER THROTTLE ADVANCEMENT ON A TOUCH AND GO LANDING, THE LEFT MAIN GEAR STRUT BROKE INSIDE THE FORK CASTING.  THE MAIN 	WHEEL ASSY AND FORK REMAINED ATTACHED TO THE AIRCRAFT BY THE BRAKE HOSE AND WAS WEDGED UNDER THE LEFT NACELLE AND FLAP. 	 PROPELLER ON LEFT SIDE CONTACTED RUNWAY.  RESEARCH OF MAINTENANCE RECORDS REVEALED STRUT HAD NEVER BEEN REPLACED. (X)				1	L	7	2 	3O			 	A19S0   					 
2000041900272	20000419	00272	EA  	2000	4	19	20000413SH054    	2	20000228	G	8530	LW12416	CYLINDER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NR 4	DAMAGED         	H				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99	9621V	832  				17264401	L3469527A			PILOT REPORTED ROUGH RUNNING ENGINE AND LOW RPM.  MAINTENANCE FOUND NR 4 CYLINDER HAD EXHAUST VALVE STUCK OPEN, NR 4 CYL	INDER PUSH ROD AND HOUSING WERE BENT WITH NO OIL LEAKAGE.  THE PISTON WAS NOT DAMAGED AND NO METAL FOUND IN THE ENGINE O	IL FILTER. (X)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000041900279	20000419	00279	GL  	2000	4	19	20000413SH055    	3	20000328	G	6114	B4426	SNAP RING       			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	HUB	SEPARATED       	D				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	03	735HK					18265435	813259R	767951		INSTALLED OVERHAULED PROPELLER.  FLIGHT TEST PERFORMED, ABOUT 20 MINUTES LATER, FELT SLIGHT VIBRATION.  LANDED FOR CAUSE	 AND FOUND SNAP RING AND SHIMS OUT OF HUB ON BLADE SHANK.  PROPELLER TSO:  .4 HOUR. (X)					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2000042000112	20000420	00112	NE  	2000	4	20	20000413SH056    	3	20000404	G	6111	C60661	BLADE           			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								HL274		DURING SEARCH INSPECTION, 4 EACH C-6066-1 PRELOAD PLATES WERE FOUND CRACKED.  (X)						2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2000042000113	20000420	00113	NE  	2000	4	20	20000413SH057    	3	20000405	G	6114	A4959	BUSHING         			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	HUB	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								HL274		DURING SEARCH INSPECTION, FOUND THE A-4659 VESPEL BUSHING WAS MISSING FROM THE HUB PITCH CHANGE ROD BORE.  FRAGMENTS OF 	THE BUSHING WERE FOUND IN THE HUB ASSEMBLY.   (X)					2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2000042000114	20000420	00114	NE  	2000	4	20	20000413SH058    	3	20000404	G	6111	C60661	PLATE           			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	PROPELLER BLADE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	426JS		2161 			3038		HL221		DURING SEARCH INSPECTION, 4 EACH C-6066-1 PRELOAD PLATES WERE FOUND CRACKED.  ONE EACH PRELOAD PLATE WAS CRACKED IN SUCH	 A MANNER THAT IT BROKE DURING INSPECTION.  TIME SINCE LAST INSPECTION:  2,160:30 HOURS.  (X)					2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2000042000115	20000420	00115	CE  	2000	4	20	20000413SH059    	1	20000404	G	3242	353800657	VALVE           			BEECH 	76    	76          	1153005	CE  										PARKING BRAKE	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	822ER					ME293				DURING ENGINE-OUT TRAINING, IF THE PILOT''S RT RUDDER IS FULLY DEPRESSED AND THE PILOT''S FOOT IS HIGH AND RT ON THE RUD	DER PEDAL, THE PILOT''S RT FOOT CAN INADVERTENTLY PULL BACK ON THE PARKING BRAKE VALVE ACTUATOR ARM AND SET THE BRAKES. 	 IF NOT CAUGHT PRIOR TO LANDING, BLOWN TIRES WILL RESULT WITH POSSIBLE LOSS OF DIRECTIONAL CONTROL.  BEECHCRAFT (RAYTHEO	N) HAS BEEN NOTIFIED.  HAVE REQUESTED THEIR HELP IN POSSIBLE RELOCATION OF THE VALVE.   (X)			1	L	7	2 	3O			 	A29CE   					 
2000042000117	20000420	00117	EA  	2000	4	20	20000413SH060    	2	20000329	G	7322	30766	FLOAT           	FACET       		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	STUCK           	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	15	757NJ				75027003	15279870	L167571			ENGINE LOST POWER.  POSSIBLE CAUSE WAS LACK OF FUEL CAUSED BY STICKING FLOAT. REMOVED CARBURETOR AND DISASSEMBLED.  COUL	D FIND NO CAUSE FOR FLOAT TO STICK.  SUBMITTER SUGGESTED TO PREVENT RECURRENCE, USE NEW STYLE FLOAT AT OVERHAUL. (X)					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000042000118	20000420	00118	SO  	2000	4	20	20000413SH061    	1	20000324	G	3200		LANDING GEAR    			PIPER 	PA24  	PA24250     	7102404	SO  										FUSELAGE	COLLAPSED       	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	6404P					241514				GEAR COLLAPSED ON ROLL-OUT.  PILOT AND PASSENGER OBSERVED GREEN LIGHT ON FINAL.  PIPER SL 782B DESCRIBES SIMILAR SCENERI	O.  (X)					1	L	7	1 	3O			 	1A15    					 
2000042500082	20000425	00082		2000	4	25	20000413SH062    	4	20000327	G	2210	065001790100	ROLL SERVO      			CESSNA	182   	182S        	2072701	CE  										AUTOPILOT	INOPERATIVE     	B			HI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	23383	143  				18280406				FOUND AUTOPILOT ROLL SERVO IDLER GEAR ATTACH NUT BACKED OFF SCREW AND OUTPUT GEAR BEARINGS DEFECTIVE DURING COMPLIANCE W	ITH SB KS271C-5 ALERT DATED FEB 1, 2000.  SUBMITTER STATED FAILURE COULD CAUSE SERVO TO REMAIN ENGAGED EVEN WHEN AUTOPIL	OT IS DISENGAGED.   (X)				1	H	7	1 	3O			NT	3A13    					 
2000042500109	20000425	00109		2000	4	25	20000413SH063    	4	20000324	G	6122	B41832	FLYWEIGHT       	HARTZL      		PIPER 	PA31  	PA31P350    	7103111	SO  										PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	9238Y	1585 			A41J	31P8414023				CRACK INDICATION AT DRIVE END OF BASE.   (X)						1	L	7	2 	3O			RT	A8EA    					 
2000042500084	20000425	00084	EA  	2000	4	25	20000413SH064    	2	20000209	G	8500	NR5	BEARING         			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	MAKING METAL    	B			AJVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	997MA	337  				4636126	L984061A			DURING AN ANNUAL INSPECTION, FOUND METAL IN OIL SCREEN.  REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X)						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000041700128	20000417	00128	EA  	2000	4	17	20000414SH001    	2	20000209	G	8550	NR5	BEARING         			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	MAKING METAL    	B			AJVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9299P	336  				4636123	L984961A			DURING AN ANNUAL INSPECTION, FOUND METAL SHAVINGS IN OIL SCREEN.  REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS.  (X)						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000041700167	20000417	00167	EA  	2000	4	17	20000414SH002    	2	20000209	G	8550	NR5	BEARING         			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540A2A   	41532	EA  					ENGINE	MAKING METAL    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	229MA	215  				4636129	L985961A			DURING AN ANNUAL INSPECTION, FOUND METAL SHAVINGS IN OIL SCREEN.  REMOVED ENGINE AND SENT TO LYCOMING FOR REPAIRS. (X)						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000041700096	20000417	00096	CE  	2000	4	17	20000414SH003    	1	20000320	G	3246	95439914	WHEEL           			LEAR  	35    	35A         	5170602	CE  										MLG	DAMAGED         	E				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	18ST		87   			316				WHEN AIRCRAFT ROLLED UP TO GATE, NOTICED PART OF THE NR 4 OUTER WHEEL HALF WAS  MISSING.  APPROXIMATELY ONE-HALF OF THE 	WHEEL BEND WAS GONE AND TIRE DESTROYED.  NO DAMAGE WAS FOUND AT NR 3 TIRE OR WHEEL.  (X)					2	L	7	2 	4F			 	A10CE   					 
2000042500036	20000425	00036	EA  	2000	4	25	20000414SH004    	2	20000321	G	7322	A44PA	FUEL BOWL       			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					CARBURETOR	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	44542					287415662				WHEN ENGINE WAS UNCOWLED, FOUND CARBURETOR BOWL LOOSE.  THE BOLTS HAD LOCK WASHERS WITH THE TABS BENT UP.  THE BOWL GASK	ET WAS IN PLACE.  THE PRECISION MANUAL CALLS FOR A TORQUE OF 35-45 INCH/POUNDS ON THESE BOLTS.  SUBMITTER STATED UNABLE 	TO VERIFY THIS.  (X)				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000041700153	20000417	00153		2000	4	17	20000414SH006    	4	20000310	G	3416	066306200	ENCODER         			BEECH 	1900  	1900C       	1154161	CE  										COCKPIT	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	123UE		1486 			UC123				PILOT REPORTED THAT ALTIMETER FLAGGED.  COULD NOT DUPLICATE PROBLEM ON TEST BENCH.  RE-CERTIFIED ALTIMETER AND RETURNED 	TO SERVICE. (X)					2	L	7	2 	4T			RT	A24CE   					 
2000041700154	20000417	00154	EA  	2000	4	17	20000414SH007    	2	20000315	G	8520	STD847	BOLT            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O320  	O320*       	41508	EA  					CRANKSHAFT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8804J					282754	L864836A			FOUND CRANKSHAFT DRIVE GEAR ATTACHING BOLT MISSING AFTER REMOVAL OF REAR HOUSING FOR OIL PUMP GEAR REPLACEMENT.  REPLACE	D GEAR, DOWEL PILOT, BOLT AND LOCKPLATE.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000042500055	20000425	00055	CE  	2000	4	25	20000417SH001    	1	20000225	G	2510	08127821	BRACKET         	CESSNA      		CESSNA	414   	414A        	2075907	CE  										UPPER EAR	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	414RM	170  				414A0306				PILOT SEAT - RIGHT HAND BRACKET BROKE.  PILOT BARELY LEANED BACK IN SEAT AND THIS BRACKET BROKE.  THIS IS THE SECOND BRA	CKET THAT BROKE IN THE SAME EXACT PLACE AND UNDER THE SAME CIRCUMSTANCES.  SUBMITTER SUSPECTED IT WAS POSSIBLE THAT IT I	S A CASTING FLAW.  TIME SINCE NEW ON PART: 170.0 HOURS - TSN.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000042500056	20000425	00056	CE  	2000	4	25	20000417SH002    	1	20000317	G	3230	VTB0816	BEARING         			LEAR  	35    	36A         	5170603	CE  										MLG TRUNNION	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	432JW	11866				043				DURING REMOVAL OF BOTH LEFT AND RIGHT LANDING GEAR FORWARD TRUNNION BEARINGS, FOUND THE OUTER HOUSING WAS CRACKED COMPLE	TELY THROUGH.  OLD BEARINGS WERE BEING REMOVED BECAUSE OF LOOSE BALLS.  INSTALLED NEW BEARINGS.  LANDINGS:  6,201. (X)					2	L	7	2 	4F			 	A10CE   					 
2000042500151	20000425	00151	CE  	2000	4	25	20000417SH003    	1	20000229	G	2434	DOFF10300J	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  										ENGINE	FAILED          	B			PE4R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	13	9723V					17264489				SMOKE IN COCKPIT.  TROUBLESHOT SYSTEM, FOUND ALTERNATOR BEARING FROZE.  REPLACED ALTERNATOR WITH OVERHAUL UNIT, PN DOFF1	0300J, SN A-100167.  (X)					1	H	7	1 	3O			NT	3A12    					 
2000042500057	20000425	00057	SO  	2000	4	25	20000417SH004    	1	20000221	G	2420	464656	CIRCUIT BREAKER 			PIPER 	PA24  	PA24250     	7102404	SO  										COCKPIT	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	7404P	2652 				242589				CIRCUIT BREAKER P/N 464-656 5 AMP TO LANDING GEAR SOLENOID FAILED INTERNALLY WHILE GEAR WAS IN TRANSIT STOPPING GEAR PAR	TIALLY EXTENDED.  (X)					1	L	7	1 	3O			 	1A15    					 
2000042500058	20000425	00058	SW  	2000	4	25	20000417SH005    	1	20000204	G	3260	1SE13	SWITCH          	GERDES      		GULSTM	112   	112         	0144701	SW  										NLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	76QR					232				PILOT REPORTED NLG DOWN LIGHT INTERMITTENT.  INVEST SHOWED HYD ACTUATED NLG DOWN SWITCH ROLLER PN 1JE5 HANGING UP AT BOT	TOM OF HOLE AT DNLK ASSY.  RE-RIGGED SWITCH.  WHILE TESTING NLG ACT PN 48805-1 LEAKED.  RESEALED ACT.  WHILE TESTING HYD	 POWER PACK PN 795000-1 FAILED.  AFTER O/H OF POWER PACK NLG DOWN LIGHT STILL WOULD NOT ILLUMINATE. FND NLG HYD DOWN SWI	TCH PN 1SE1-3 WITH HIGH RESISTANCE ON CONTACT THAT OPERATES HYD POWER PACK TO SHUT DOWN WITH ACT APROX .1250 INCH FROM C	OMPLETE EXTENSION OF NLG.  REPLACED SWITCH.  SYS OPERATED NORMALLY EXCEPT AT EMERG EXT, NLG LIGHT FAILED.  SHORTED ACT R	OD END 1/2 TURN.  SYS OPERATES NORMALLY.  (X)	1	L	7	1 	3O			 	A12SO   					 
2000042500059	20000425	00059	SO  	2000	4	25	20000417SH007    	1	20000302	G	3213	6703706	STRUT           			PIPER 	PA32  	PA32R301    	7103218	SO  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	8159B	3351 				32R8013061				DURING AN ANNUAL INSPECTION, CRACKS WERE FOUND IN BOTH MLG STRUT ASSEMBLIES NEAR THE AXLE BOLT HOLES (BOTH TOP) NEAR BOL	T HEADS.  THE CRACKS ARE IN THE OUTSIDE WALLS WHERE THE METAL IS THE THINNEST.  THIS AIRCRAFT HAS NO ACCIDENT HISTORY OR	 ANY HARD LANDINGS.  PAINT REMOVED AND A 10X MAGNIFYING GLASS WERE REQUIRED.  (X)				1	L	7	1 	3O			 	A3SO    					 
2000042500121	20000425	00121	SO  	2000	4	25	20000417SH008    	1	20000417	G	2750		CONTROL CABLE   			PIPER 	PA28  	PA28R200    	7102811	SO  										TE FLAP	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	3021R					28R35652				DURING 100-HR INSPECTION, FLAP CABLE WAS FOUND LODGED IN THE TRIM PULLEYS AND WORN 3/4 THROUGH THE RIGHT PULLEY AND NUME	ROUS STRANDS OF THE CABLE BROKEN.  THIS CONDITION WAS DUPLICATED ON SIMULATING A STICKING FLAP WHEN THE HANDLE IS RELEAS	ED AND THE FLAP RETRACTS RAPIDLY, THE LOOSE CABLE JUMPS AND HOOKS INTO THE TRIM PULLEYS.  INSTALLED A 90 DEGREE ALUM ANG	LE ON THE TOP CLOSE OUT PLATE NEXT TO THE TRIM PULLEYS TO BLOCK THE CABLE FROM HITTING THE PULLEYS AND CHECKING FLAP HIN	GE BEARINGS.  FOR FREEDOM OF MOVEMENT AND LUBRICATION, CABLE AND ONE PULLEY REPLACED.  (X)		1	L	7	1 	3O			 	2A13    					 
2000060500148	20000605	00148	CE  	2000	6	5	20000417SH009    	1	20000228	G	2910	1118	HOSE            			CESSNA	207   	207A        	2073604	CE  										HYD SYSTEM	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01										END OF HOSE WAS CUT OFF WITH A CUT-OFF WHEEL AND HOSE INTERIOR WAS FOUND COLLAPSED.  ANOTHER 1.50 INCH WAS CUT OFF AND T	HE SAME CONDITION WAS FOUND.  NOTE:  SECTION OF HOSE SUBMITTED REPORT FORWARDED TO AEG NE-FSDO-07.  (X)					1	H	7	1 	3O			 	A16CE   					 
2000042500122	20000425	00122	CE  	2000	4	25	20000417SH010    	1	20000321	G	5330		SKIN            			CESSNA	337   	337G        	2075730	CE  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	53522					33701680				DURING A 100-HOUR INSPECTION, A SECTION OF MATERIAL USED FOR DAMPING ''OIL CANNING'' WAS REMOVED FROM THE INTERIOR FUSEL	AGE SKIN BELOW THE AFT SIDE WINDOW.  HEAVY CORROSION WAS FOUND ACROSS THE ENTIRE AREA COVERED BY THE MATERIAL.  THIS MAT	ERIAL IS USED EXTENSIVELY THROUGHOUT THE AIRFRAME AT MANUFACTURE. (X)				1	H	7	2 	3O			 	A6CE    					 
2000042500123	20000425	00123	EA  	2000	4	25	20000417SH011    	2	20000316	G	7314	LW15472	PUMP            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					FUEL SYSTEM	UNSERVICEABLE   	B			DINR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	8269E	93   				288116039	L1334539A			NOTED THE FUEL PRESSURE WOULD DROP OFF AS ALTITUDE INCREASE, FROM 5 PSI AT GROUND LEVEL, TO ABOUT 1-1/2 PSI AT 10,000 FE	ET. TURNING ON BOOST PUMP WOULD RESTORE 5 PSI.  INSTALLED ANOTHER NEW PUMP AND IT CURED THE PROBLEM.  FAILED PUMP, SN 15	4723199.  GOOD PUMP, SN 154720200. (X)				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000042500134	20000425	00134	NE  	2000	4	25	20000417SH012    	2	20000214	G	8530		PUSHROD         			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	MISINSTALLED    	G			LSVG	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	09	23043					3010352	19074			ENGINE VALVE PUSH RODS AND ROCKER ARMS WERE REVERSED DURING INSTALLATION ON THE NR 5 CYLINDER.  SINCE THE INTAKE ROD IS 	LONGER AND ENGINE HAS SOLID TAPPETS, THE PUSH ROD ON THE EXHAUST SIDE BENT, AND THE ROCKER ARM BROKE RESULTING IN ENGINE	 FAILURE.  ENGINE OPERATED NORMALLY FOR AT LEAST SEVERAL HOURS BEFORE FAILURE LEADING TO SPECULATION THAT IT DID NOT FAI	L UNTIL THE ROCKER ARM BROKE PREVENTING THE EXHAUST VALVE FROM OPENING. (X)			1	L	7	1 	3R	3	R	 	A9SW    	5E2				 
2000042500149	20000425	00149	CE  	2000	4	25	20000417SH014    	1	20000310	G	2434	E3FF10300AAPX	ALTERNATOR      			CESSNA	206   	TU206G      	2073357	CE  										ENGINE	FAILED          	B			QY5R	O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	01	232MT		29   			U20606200				ALTERNATOR FAILED DURING FLIGHT.  TROUBLESHOOTING WITH ALTERNATOR TEST BOX SHOWED NO OUTPUT.  CHECKING FIELD WINDING RES	ISTANCE PER CESSNA MM SHOWED EXCESSIVELY HIGH RESISTANCE.  ALTERNATOR REPLACED. (X)					1	H	7	1 	3O			 	A4CE    					 
2000042500145	20000425	00145	CE  	2000	4	25	20000417SH016    	1	20000313	G	3230	12434262	LINK            			CESSNA	210   	T210L       	2073449	CE  										NOSE GEAR	CRACKED         	D			DFQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	6864C	7716 				21061317				DURING ROUTINE INSPECTION, FOUND UPPER TORQUE LINK CRACKED.  SUBMITTER STATED THIS PART NUMBER LINK WAS FOUND CRACKED ON	 ANOTHER T210L IN THE SAME FLEET. (X)					1	H	7	1 	3O			 	3A21    					 
2000042500146	20000425	00146	SO  	2000	4	25	20000417SH017    	2	20000229	G	8550	LW13094	GASKET          	LYC         		PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ENGINE OIL	FAILED          	B			EKIR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	01	6925J	4377 	653  			32R7680388	L2012548A			ENGINE LOST OIL ON START-UP DUE TO EXCESSIVE OIL PRESSURE WHICH BENT PLATE ON OIL FILLER KIT CAUSING GASKET TO BLOW OUT.	 (X)					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000051800008	20000518	00008	SO  	2000	5	18	20000417SH018    	2	20000317	G	8530	639614	ROCKER          			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A658        	17003	SO  					NR 4 CYLINDER	BROKEN          	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	13	84729		500  			7AC3445				PILOT REPORTED A REDUCTION IN POWER.  AFTER INVESTIGATING, THE ROCKER ARM HAD BROKEN AT THE CENTER.  THIS IS THE OLD TYP	E WHICH DOES NOT HAVE AS MUCH MATERIAL AS THE NEW TYPE. (X)					1	H	7	1 	3O	3	O	 	A759    	E205				 
2000042500150	20000425	00150	NE  	2000	4	25	20000417SH020    	3	20000318	G	6114	D61681	HUB             													HARTZL	HDE6C	HDE6C3B     	NE  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05		5942 	1941 					HL155		DURING PENETRANT INSPECTION, CRACKS WERE FOUND IN THE BLADE SEAL GROOVES OF BLADE SOCKETS 3 AND 4.  THE HUB WAS DISPOSIT	IONED TO HARTZEL ENGINEERING FOR FURTHER EVALUATION. (X)															6	C	P34NE	 
2000042500272	20000425	00272	NM  	2000	4	25	20000417SH021    	1	20000221	G	3240		BRAKE           			DOUG  	MD11  	MD11        	3023602	NM  										MLG	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	583FE		2671 			48421				BRAKE ASSY WAS RECEIVED FROM AIR CARRIER ON 2-21-00 FOR REPAIR AND OVERHAUL SERVICE.  UPON DIS-ASSEMBLY, IT WAS IDENTIFI	ED THE AFFECTED BRAKE SUFFERED AN EXTREME CARBON OXIDATION BREAKDOWN ON THE INNER DIAMETER OF THE HEAT SINK.  SUBMITTER 	RECOMMENDATION  WOULD BE AN ANALYSIS OR REVIEW OF CARBON COMPOSITE MANUFACTURING PROCESSES.  (X)				2	L	7	3 	4F			RT	A22WE   					 
2000042500295	20000425	00295	CE  	2000	4	25	20000424SH001    	1	20000304	G	2820		FUEL LINE       			CESSNA	185   	185F        	2072820	CE  	CONT  	O550  	IO550D      	17042	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	CGZTT	2300 				18503490	284122R			RDM/RNO - EN ROUTE 55 MILES NORTH OF LMT, PILOT SENSED A STRONG FUEL ODOR.  BRIEF TROUBLESHOOTING CONFIRMED A FUEL LINE 	FAILURE WITH SYMPTOMS. FUEL FLOW INDICATING ZERO.  HIGHER THAN NORMAL EGT'S AND CHT'S (ACFT EQUIPPED WITH A 12-POINT ENG	 ANALYZER.  STRONG AND DANGEROUS FUEL ODOR. PILOT CORRECTLY ASSESSED THE SITUATION AND LEFT POWER SETTING UNTOUCHED AND 	MIXTURE RICH.  PILOT SET UP ON A HIGH APPROACH TO SOUTH RUNWAY AT LMT.  ENGINE FAILED WHEN THROTTLE RETARDED.  POST-FLIG	HT INSPECTION REVEALED FUEL PRESSURE LINE FROM AFT OF ENGINE BAFFLE TO FIREWALL FAILED.  LINE SEVERED ONE INCH AFT OF EN	GINE BAFFLE.  (X)	1	H	7	1 	3O	3	O	 	3A24    	E3SO				 
2000051800043	20000518	00043	CE  	2000	5	18	20000424SH008    	1	20000229	G	2820	KS271C0650017903	SERVO           			CESSNA	172   	172S        	2072439	CE  										FUEL SYSTEM	LOOSE           	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	642SP	160  				172S08050				FOUND LOOSE FREE SPINNING NUT WHILE C/W HONEYWELL SB SK 271-C5, ALERT KS 271C PRIMARY SERVO.  RETURNED UNIT TO MANUFACTU	RER FOR REPAIR.  (X)					1	H	7	1 	3O			NT	3A12    					 
2000051800044	20000518	00044	SO  	2000	5	18	20000424SH009    	1	20000318	G	2140	A23D0475	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	I			WVBA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	4082T	560  				318152089				DURING ROUTINE INSPECTION, REGULATOR WAS FOUND LEAKING AT PARTING SURFACES.   (X)						1	L	7	2 	3O			 	A20SO   					 
2000051800046	20000518	00046	CE  	2000	5	18	20000424SH012    	1	20000310	G	2434		ROTOR COIL      	FORD        		BEECH 	23    	C24R        	1151254	CE  										ALTERNATOR	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	07	18993		52   		9020493	MC550				ALTERNATOR FAILED WHILE ACFT WAS IMC, VFR CONDITIONS ENCOUNTERED.  AIRCRAFT LANDED WITHOUT INCIDENT.  INVESTIGATION REVE	ALED ROTATING FIELD WAS ELECTRICALLY OPEN DOWN.  STREAM OF SUD RINGS.  PART TSO WAS ONLY 52 HOURS SINCE OVERHAULED.  (X)					1	L	7	1 	3O			 	A1CE    					 
2000051800047	20000518	00047	GL  	2000	5	18	20000424SH013    	1	20000316	G	3213	2032100701	AXLE            			DIAMON	DA20  	DA20A1      	       	GL  										RT MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	126MF	3112 				10017				DURING TIRE CHANGE, FOUND RT WHEEL AXEL FLANGE EXFOLIATING.  SUBMITTER SUSPECTED EXFOLIATION CAUSED BY STRESS CORROSION.	  RECOMMEND REPLACING ANODIZED ALUMINUM ALLOY PART WITH PART MADE OF STEEL.  (X)					1	L	7	1 	3O			NT	TA4CH   					 
2000051800048	20000518	00048	CE  	2000	5	18	20000424SH014    	1	20000403	G	2820	AN816620	FUEL LINE       			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					RT FUEL CELL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	421SE					421B0393				DURING ANNUAL INSP, RT WING AUXILIARY TRANSFER PUMP PRESS SWITCH THAT OPERATES RT AUX PUMP ANNUNCIATOR LIGHT, WAS FOUND 	TO HAVE LIGHT FUEL STAINING AROUND BASE OF MICROSWITCH.  AFTER REMOVING PRESS SWITCH ASSY (DUE TO CONDITION OF LEFT ONE)	,  FOUND PIPE THREAD PORTION OF AN 816-6-20 VISIBLE, EXPOSING SEVERE CORROSION TO THE POINT OF ALMOST HALF DIAMETER BEIN	G ERODED AWAY.  (X)			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2000051800050	20000518	00050	NM  	2000	5	18	20000424SH017    	1	20000213	G	5320	900R1103001113	BEAM            			DOUG  	MD900 	MD900       	3027375	NM  										FUSELAGE	DELAMINATED     	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF					90000012				DELAMINATION ALONG TRAILING EDGE IN Y-AREA.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			NC	H19NM   					 
2000051800051	20000518	00051	NM  	2000	5	18	20000424SH018    	1	20000213	G	5320	900R1103001113	BEAM            			DOUG  	MD900 	MD900       	3027375	NM  										FUSELAGE	DELAMINATED     	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	884  				90000012				DELAMINATION ALONG TRAILING EDGE IN Y-AREA.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			NC	H19NM   					 
2000042500302	20000425	00302	SW  	2000	4	25	20000424SH019    	1	20000308	G	6220	6887772D	BEARING         	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GEARBOX	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	37488				38410	2188	823399			METAL FLAKES DETECTED ON MAGNETIC PICK-UP IN LOWER GEARBOX AND OIL PUMP MAGNETIC PICK-UP.  DISASSEMBLED GEARBOX FOR INSP	ECTION.  BEARING INNER AND OUTER RACES BOTH HAD AREAS THAT HAD FLAKED OFF METAL.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000042500303	20000425	00303	GL  	2000	4	25	20000424SH021    	3	20000316	G	6110		PROPELLER       			CESSNA	210   	210B        	2073410	CE  						HARTZL	HCA2X	HCA2XF1     	GL  	BLADE BORE	MISOVERHAULED   	B			W59R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	9561X	2192 				21057861		2714		PROPELLER WAS ASSEMBLED USING U 8833 N-4 BLADES THAT ARE NOT ELIGIBLE FOR INSTALLATION ON HCA2XF-1 HUB.  STEEL HUB TUBES	 CAUSED EXTREME WEAR ON THE INTERNAL BLADE BORE BECAUSE THE INSTALLING AGENCY REMOVED THE BLADE BOXINGS AND BEARINGS TO 	FACILITATE INSTALLATION OF BLADES ON HUB  (X)				1	H	7	1 	3O			 	3A21    		5	C	P908	 
2000042500304	20000425	00304	CE  	2000	4	25	20000424SH022    	1	20000309	G	5751	99130000605	SKIN            			BEECH 	99    	99          	1154002	CE  										ALIERON	CRACKED         	E			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	199GL					U15				PRE-FLIGHT INSPECTION REVEALED A SMALL PORTION OF THE AILERON SKIN CRACKED AT THE INBOARD SECTION, TOP SKIN, TRAILING ED	GE ADJACENT TO THE MOVABLE TRIM.  FURTHER INSPECTION REVEALED EXTENSIVE CORROSION RELATED CRACKING MOSTLY ALONG THE TRAI	LING EDGE.  REMOVED STATIC WICKS AND FOUND FURTHER UNSERVICEABLE CONDITIONS.  WHEN INSPECTING OLDER CONTROL SURFACES, AN	D/OR CONTROL SURFACES HAVING CRACKS IN THE PAINT, FURTHER INSPECTION WOULD BE MANDATED TO CHECK FOR CRACKS. (X)			1	L	7	2 	3T			 	A14CE   					 
2000042500305	20000425	00305	CE  	2000	4	25	20000424SH023    	1	20000309	G	3230	508103237	SCISSORS        			BEECH 	99    	99A         	1154003	CE  										LANDING GEAR	CRACKED         	A			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	955AA					U128				DURING DETAILED LANDING GEAR INSPECTION, THE SCISSORS ON THE RT MAIN GEAR WERE FOUND CRACKED.  THE CRACKS ARE LOCATED NE	AR THE MACHINED RADIUS WHERE THE TWO SCISSORS CONNECT.  IT WAS DETERMINED THE CRACKS WERE, OR COULD HAVE BEEN CAUSED BY 	THE TORQUE KNEE BOLT/HARDWARE BEING LOOSE.  THE LT GEAR ASSY SCISSORS WERE FOUND TO BE SLOPPY AND THE SUBSEQUENT INSPECT	ION REVEALED WORN BUSHINGS.  (X)			1	L	7	2 	3T			 	A14CE   					 
2000050500076	20000505	00076	NE  	2000	5	5	20000425SH031    	2	20000201	G	7320	3026983	NUT             			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					FCU	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	97DD					5000159	P76506			UPON BORESCOPE OF FUEL CONTROL SHUT OFF MECHANISM, NOTED CLEVIS LANYARD THROUGH-BOLT HAD BACKED OFF FROM CLEVIS ON END O	F BOLT.  (THROUGH-BOLT LOOSE).   NUT HAD BACKED OFF. (X)					1	L	7	2 	4F	4	U	 	A22CE   	E15EA				 
2000050500077	20000505	00077	NE  	2000	5	5	20000425SH032    	2	20000201	G	7320	311707802	BOLT            			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					NR 4 BEARING	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	97DD					5000159	P76506			UPON BORESCOPE OF FUEL CONTROL SHUT OFF MECHANISM, NOTED CLEVIS LANYARD THROUGH-BOLT HAD BACKED OFF FROM CLEVIS ON END O	F BOLT.  (THROUGH-BOLT LOOSE).  NUT HAD BACKED OFF.  (X)					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000050500078	20000505	00078	WP  	2000	5	5	20000425SH033    	2	20000322	G	7250	30723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					NR 1 LPT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  (X)											4	F			E6WE				 
2000050500079	20000505	00079	WP  	2000	5	5	20000425SH034    	2	20000322	G	7250	300723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					NR 1 LPT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  (X)											4	F			E6WE				 
2000051800053	20000518	00053	WP  	2000	5	18	20000425SH035    	2	20000322	G	7250	30725422	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					NR 2 LPT	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA. (X)											4	F			E6WE				 
2000050500080	20000505	00080		2000	5	5	20000425SH036    	4	20000310	G	3422	6226136002	GYRO            			BEECH 	1900  	1900D       	1154162	CE  										COCKPIT DG	FAILED          	B			GLBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	179GL	10225				UE179				PILOT REPORTED THAT ''GYRO FREEZES UP''.  NR 1 DIRECTIONAL GYRO REMOVED AND SENT TO TEST FACILITY.  						2	L	7	2 	4T			RT	A24CE   					 
2000050500081	20000505	00081	CE  	2000	5	5	20000425SH037    	1	20000403	G	2820	S14956	FUEL LINE       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320E2D     	41508	EA  					WING ROOT	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	5444J	5430 				17273798	RL96576T			DURING REPLACEMENT OF CABIN INTERIOR, FOUND ONE EACH HOSE LEAKING.  REPLACED ALL 6 HOSES IN FUEL VENT SYSTEM.  CONDITION	 OF THESE HOSES THE SAME.  AGE OF HOSES, 19 YEARS. (X)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000050500082	20000505	00082	GL  	2000	5	5	20000425SH038    	3	20000403	G	6114	D4883C55	HUB             			BEECH 	95    	95B55       	1152729	CE  						MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6853Q					TC675		715408		CRACK IN HUB  WAS FOUND WITH EDDY CURRENT INSPECTION. (X)						1	L	7	2 	3O			RT	3A16    		5	C	P5EA	 
2000050500083	20000505	00083	SO  	2000	5	5	20000425SH039    	2	20000403	G	8520	629588	DRIVE GEAR      			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					CAMSHAFT	BROKEN          	H				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99	47445	1618 				28R7703379	237331R			PILOT WAS IN-FLIGHT WHEN ENGINE FAILED.  PILOT PERFORMED EMERGENCY PROCEDURES AND RETURNED TO AIRPORT.  INSPECTION REVEA	LED THE GOVERNOR DRIVE GEAR HAD FAILED.  GOVERNOR DRIVE GEAR ALSO DRIVES THE ENGINE DRIVEN FUEL PUMP WHICH, WHEN GEAR FA	ILED, TOOK THE ENGINE DRIVEN FUEL PUMP OFF-LINE.  GOVERNOR DRIVE GEAR APPEARS TO HAVE BEEN CRACKED BEORE FAILURE. (X)				1	L	7	1 	3O	3	O	 	2A13    	E9CE				 
2000050500086	20000505	00086	SO  	2000	5	5	20000425SH042    	1	20000331	G	5510	6356000	SKIN            			PIPER 	PA28  	PA28160     	7102806	SO  										STABILATOR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	00	5542W					28633				SEVERE CORROSION FOUND ON FORWARD INBOARD STABILATOR SPAR AND INBOARD RIB JUNCTION.  FOUND AFTER REMOVING TOP SKIN TO RE	PLACE.  (X)					1	L	7	1 	3O			 	2A13    					 
2000050500091	20000505	00091		2000	5	5	20000426SH003    	4	20000322	G	6122	C20908	FLYWEIGHT       	MCAULY      		CESSNA	402   	402B        	207590P	CE  										PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					641374A					RELEVANT INDICATION ON FLAT BETWEEN TOWERS.  EXTENDS AROUND CORNER.  (X)						1	L	7	2 	3O			 	A7CE    					 
2000050500092	20000505	00092	CE  	2000	5	5	20000426SH004    	1	20000308	G	2820	154729606	PUMP            			CESSNA	177   	177         	2073704	CE  										FUEL SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	2954X					17700354				NEW FUEL PUMP DOES NOT ATTAIN RATED FUEL PRESSURE/FUEL FLOW. THE HIGHEST PRESSURE ATTAINED WAS LESS THAN 2 PSIG AT IDLE 	AND DROPPED TO NEAR ZERO AS RPM INCREASED.  AFTER EXTENSIVE TROUBLESHOOTING OF AIRCRAFT FUEL SYSTEMS, CAME TO THE CONCLU	SION THE PUMP MUST BE FAULTY.  INSTALLED ANOTHER NEW PUMP AND OPERATIONAL CHECK WAS SATISFACTORY.  SUBMITTER SUGGESTED T	HAT ALL LYCOMING/AC PUMPS OF THIS BATCH (DATE CODE 9606) SHOULD BE CHECKED FOR PROPER OPERATION.  (X)			1	H	7	1 	3O			NT	A13CE   					 
2000050500093	20000505	00093	NE  	2000	5	5	20000426SH005    	2	20000330	G	7421	CPW3039828	IGNITOR         								PWA   	JT15  	JT15*       	52060	NE  					ENGINE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										DURING NORMAL MAINTENANCE, FOUND IGNITERS ON TWO SEPARATE AIRCRAFT (BOTH BATCH NR 1H99), CENTER ELECTRODES AND CERAMIC I	NSULATORS RECESSED APPROXIMATELY .75 INCH.  UPON FURTHER INVESTIGATION, FOUND ELECTRODE ASSY WAS LOOSE AND FREE TO FLOAT	 WITHIN IGNITER.  BOTH IGNITERS WERE INOPERABLE UPON REMOVAL.  (X)									4	T			E1NE				 
2000050500094	20000505	00094	NE  	2000	5	5	20000426SH006    	2	20000330	G	7421	CPW3039828	IGNITOR         								PWA   	JT15  	JT15*       	52060	NE  					ENGINE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03										DURING NORMAL MAINTENANCE, FOUND IGNITERS ON TWO SEPARATE AIRCRAFT (BOTH BATCH NR 1H99), CENTER ELECTRODES AND CERAMIC I	NSULATORS RECESSED APPROXIMATELY .75 INCH.  UPON FURTHER INVESTIGATION, FOUND ELECTRODE ASSY WAS LOOSE AND FREE TO FLOAT	 WITHIN IGNITER.  BOTH IGNITERS WERE INOPERABLE UPON REMOVAL.  (X)									4	T			E1NE				 
2000050500095	20000505	00095	NM  	2000	5	5	20000426SH007    	1	20000403	G	3210	9543536	RETAINER        			DOUG  	DC10  	DC10        	N/A-SDR	NM  										RING	DAMAGED         	B			INWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	3240									VISUAL INSPECTION SHOWED RING RETAINER AREA DAMAGED BEYOND LIMITS AND HEAVY CORROSION AT BOLT HOLE AREAS.  (X)						2	L	7	3 	4F			RT	A22WE   					 
2000050500096	20000505	00096	GL  	2000	5	5	20000426SH008    	3	20000327	G	6114	D7015C87	HUB             													MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15								771150		DURING INSPECTION, HUB WAS FOUND CRACKED IN NR 3 THREAD OF NR 3 SOCKET.  HUB HAS BEEN SCRAPPED.  (X)																5	C	P22EA	 
2000050500097	20000505	00097	NE  	2000	5	5	20000426SH009    	3	20000320	G	6111	D5133	EROSION SHIELD  	HARTZL      												HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01					1588			HJ628		CRACKED AND DEBONDED EROSION SHIELDS.  PRELOAD LOOSE.  DISASSEMBLED AND CLEANED PROPELLER.  REPLACED EROSION SHIELDS BLA	DE NR 1 SN 1588.  BLADE NR 2 SN 1590.  SET PRELOADS.  REASSEMBLED PROP, SET BLADE ANGLES.  REV AT 14.5  INCHES, FEATHER 	AT 79.0 INCHES, L.P. AT 18.6 INCHES, STATIC BALANCED PROP IAW HARTZELL CMM.  (X)														5	C	P10NE	 
2000050500098	20000505	00098	NE  	2000	5	5	20000426SH010    	3	20000320	G	6111	D5133	EROSION SHIELD  	HARTZL      												HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01					1590			HJ628		CRACKED AND DEBONDED EROSION SHIELDS.  PRELOAD LOOSE.  DISASSEMBLED AND CLEANED PROPELLER.  REPLACED EROSION SHIELDS BLA	DE NR 1 SN 1588.  BLADE NR 2 SN 1590.  SET PRELOADS.  REASSEMBLED PROP, SET BLADE ANGLES.  REV AT 14.5  INCHES, FEATHER 	AT 79.0 INCHES, L.P. AT 18.6 INCHES, STATIC BALANCED PROP IAW HARTZELL CMM.  (X)														5	C	P10NE	 
2000050500099	20000505	00099	NE  	2000	5	5	20000426SH011    	3	20000216	G	6111	D5133	EROSION SHIELD  	HARTZL      												HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01					1497			HJ395		EROSION SHIELD DEBONDED AND CRACKED BLADE NR 2.  REMOVED AND REPLACED EROSION SHIELD WITH NEW, STATIC BALANCED PROPELLER	 IAW PROCEDURE 001 AND HARTZELL CMM.  NR 2 BLADE SN 1497, BOOT SN 0255.  HYSOL BATCH NR AS9163016 AND 9228-1  (X)															5	C	P10NE	 
2000050500101	20000505	00101	GL  	2000	5	5	20000426SH013    	3	20000407	G	6114	D653012	HUB             	HARTZL      												HARTZL	HCC2Y	HCC2YF2     	GL  	PROPELLER	STRIPPED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								AN7323B		PROPELLER WAS RETURNED FOR LOOSE MOUNTING STUD.  AFTER REMOVAL OF THE STUD, FOUND STUD ATTACHMENT THREADS IN THE HUB WER	E STRIPPED.  (X)															5	C	P920	 
2000050500106	20000505	00106	GL  	2000	5	5	20000426SH018    	3	20000323	G	6114		HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	DAMAGED         	B			SD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	111QT					272849		715		DURING INSPECTION, NOTICED THE PRELOAD SHELF WAS ROLLED.  EVIDENCE SHOWS HUB ENDURED EXCESSIVE FORCES.  HUB WAS RETIRED 	FROM SERVICE.  (X)					1	L	7	2 	3O			 	1A10    		5	C	P920	 
2000050500107	20000505	00107	GL  	2000	5	5	20000426SH019    	3	20000323	G	6114		HUB             			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	DAMAGED         	B			SD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	111QT					272849		BP5674		DURING INSPECTION, NOTICED THE PRELOAD SHELF WAS ROLLED.  EVIDENCE SHOWS HUB ENDURED EXCESSIVE FORCES. HUB WAS RETIRED F	ROM SERVICE.  (X)					1	L	7	2 	3O			 	1A10    		5	C	P9EA	 
2000050500108	20000505	00108	GL  	2000	5	5	20000426SH020    	3	20000323	G	6111	B67536	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PITCH KNOB	CRACKED         	B			SD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	111QT					272849		BP5674		UPON INSPECTION OF THE PROPELLER BLADE DURING OVERHAUL, THE PITCH KNOB ON THE BUTT OF THE BLADE WAS FOUND CRACKED.  BLAD	E WAS RETIRED FROM SERVICE.  (X)					1	L	7	2 	3O			 	1A10    		5	C	P9EA	 
2000050500109	20000505	00109	SW  	2000	5	5	20000426SH021    	1	20000322	G	6710	206001330001	SUPPORT BRACKET 			BELL  	206   	206B        	1181511	SW  										M/R CYCLIC	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	167H					2968				DURING THE ANNUAL INSPECTION, THE PIVOT SUPPORT ASSEMBLY WAS FOUND CORRODED.  REPLACED SUPPORT ASSEMBLY WITH NEW PART.  	SUBMITTER RECOMMENDED SPRAYING A CORROSION PREVENTATIVE COMPOUND IN THE AREA OF THE SUPPORT ASSEMBLY.  (X)					1	G	7	1 	3U			 	H2SW    					 
2000050500110	20000505	00110	SW  	2000	5	5	20000426SH022    	1	20000322	G	2822	1C274	PUMP            			BELL  	206   	206B        	1181511	SW  										FUEL BOOST	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	198H		253  			3647				AFT BOOST PUMP INOPERATIVE.  INSPECTED AIRFRAME FUEL FILTER AND FOUND FILTER WAS COATED WITH A BLACK CARBON LIKE MATERIA	L THAT WAS SUSPECTED TO BE RESIDUE FROM THE MAGNETS SURROUNDING THE BOOST PUMP CORE.  (X)					1	G	7	1 	3U			 	H2SW    					 
2000050800066	20000508	00066	EA  	2000	5	8	20000426SH025    	2	20000328	G	7414	10382681	CAPACITOR       	BENDIX      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	27329					317752150				NUMEROUS MAGNETO PROBLEMS.  UNUSUAL DROP OFF, COMPLETELY DEAD MAG, AND NO HARD STARTING WERE ATTRIBUTED TO CAPACITORS IN	 THE DUAL MAG SYSTEM.  AFTER THE FACT, TCM NOTIFIED AND STATED CAPACITORS CODED PRIOR TO 9946 WERE TO BE PULLED OUT OF S	ERVICE.  REF TCM CSB NR 662A NEWER CODED CAPACITORS WERE INSTALLED AND MAG OPERATION HAS BEEN SATISFACTORY.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000050800067	20000508	00067	SO  	2000	5	8	20000426SH026    	1	20000324	G	3213	6792617	TRUNNION        	PIPER       		PIPER 	PA32  	PA32R301    	7103218	SO  										RT & LT MLG	CRACKED         	B			PRIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	29AM	1845 				32R8113057				ON PRE-FLIGHT, PILOT NOTICED FLUID FROM MIDDLE OF STRUT.  AFTER CLEANING, FLUID RE-APPEARED.  AFTER INSP, FOUND STRUT HO	USING CRACKED BELOW AFT WEB ON STRUT HOUSING (CASTING).  REMOVED AND REPLACED STRUT HOUSING ASSY WITH NEW.  INSPECTED OT	HER GEAR HOUSING AND DISCOVERED CRACKED, BUT NOT LEAKING AT THIS TIME. REPLACED LT SIDE HOUSING. NEW PARTS FROM PIPER HA	VE NEW DESIGN WHERE WEB IS SUPPORTED THE ENTIRE LENGTH OF CASTING AND HAS NEW P/N.  SUBMITTER STATED THESE HOUSINGS ARE 	NOT COVERED IN ANY AD OR SB.  (X)		1	L	7	1 	3O			 	A3SO    					 
2000050800069	20000508	00069	CE  	2000	5	8	20000426SH030    	1	20000331	G	3246	26066712	BOLT            			CESSNA	337   	T337G       	2075726	CE  										MLG WHEEL	BROKEN          	H			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	357					P3370242				TIE BOLT FAILURE, 3 EACH.  UNDETERMINED WHEEL SENT TO MFG FOR ANALYSIS.  BOLT HARD TIME IMPLEMENTED, AND TIE NUT CYCLE P	LAN INPLEMENTED.  (X)					1	H	7	2 	3O			 	A6CE    					 
2000050800071	20000508	00071	SO  	2000	5	8	20000426SH032    	2	20000324	G	7320	0850250189	CONDUIT         			CESSNA	310   	310C        	2074210	CE  	CONT  	O470  	IO470D      	17026	SO  					ENGINE NACELLE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3311H					35835	10512670R			MIXTURE CONTROL CONDUIT IN ENGINE NACELLE BETWEEN MIXTURE CONTROL AND WING ROOT.  CONDUIT THAT HOUSES CABLE FATIGUED AND	 BROKE CAUSING HOUSING TO MOVE AND MIXTURE TO REMAIN IN IDLE CUT-OFF WHICH CAUSED AIRCRAFT TO MAKE AN OFF-AIRPORT LANDIN	G.  THE ENGINE WAS NOT ABLE TO RE-START.  (X)				1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2000050800084	20000508	00084	SW  	2000	5	8	20000427SH002    	1	20000327	G	2841		INDICATOR       			BELL  	206   	206B        	1181511	SW  										FUEL QUANTITY	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	57499					3086				PILOT REPORTED FLUCTUATIONS IN THE FUEL QUANTITY INDICATOR.  FLUCTUATED FROM ZERO TO KNOWN QUANTITY.  SOLDERED WIRE CONN	ECTION AT ZERO ADJUST RESISTOR, WAS CORRODED AND LOOSE.  RE-SOLDERED AND RECALIBRATED FUEL QUANTITY SYSTEM.  SUBMITTER R	ECOMMENDED THAT HEAT SHRINK COVER OVER SOLDER CONNECTION IS INSTALLED.  (X)				1	G	7	1 	3U			 	H2SW    					 
2000042700101	20000427	00101	SW  	2000	4	27	20000427SH003    	1	20000314	G	6510	S3532EC1	PULLEY          			BELL  	407   	407         	       	SW  										T/R DRIVE	LOOSE           	B			ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	58236	2920 			AFS1229	53069				DURING AIRCRAFT RUN-UP FOLLOWING UNRELATED MAINTENANCE, MECHANIC NOTED AIR CONDITIONING COMP STOPPED TURNING WHEN AIR CO	NDITIONER SYSTEM WAS ACTIVATED.  ACFT WAS SHUT DOWN AND MECH FOUND AIR COND DRIVE PULLEY LOOSE ON OIL COOLER BLOWER SHAF	T.  POSSIBLE CAUSE FOR THIS CONDITION WAS LOSS OF TORQUE BETWEEN DRIVE PULLEY FWD OIL COOLER BLOWER BEARING.  DRIVE RING	 LOCK WAS TIGHT AND SAFTIED.  SUBMITTER RECOMMENDED A POSSIBLE INCREASE IN TORQUE VALUE AND/OR AT THE VERY LEAST, A TORQ	UE CHECK REQUIREMENT OF 1 TO 5 HOURS AFTER INSTALLATION. (X)		1	G	7	1 	3U			O	H2SW    					 
2000052500046	20000525	00046	CE  	2000	5	25	20000427SH004    	1	20000427	G	5320	04120101	PLATE           			CESSNA	150   	150L        	2071826	CE  										FUSELAGE	MISMANUFACTURED 	B			YBUR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	03	6556G					15072056				RECEIVED 2 EACH NEW PLATES, P/N 0412010-1.  ONE PLATE HAS CASING LINE ACROSS FLAT SURFACE THROUGH TWO MOUNTING HOLES.  T	HESE TWO PLATES ARE VERY IMPORTANT AND HARD TO INSPECT FOR CRACKS AFTER INSTALLATION.  SUBMITTER STATED PART APPEARED TO	 HAVE BEEN BURNISHED.  (X)				1	H	7	1 	3O			 	3A19    					 
2000050800089	20000508	00089	CE  	2000	5	8	20000427SH014    	1	20000225	G	2400	S337711	SWITCH          			CESSNA	172   	172R        	2072401	CE  										AVIONICS MASTER	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	718EH					17280061				ONE-HALF OF SPLIT AVIONICS MASTER BUS SWITCH FAILED.  DEFECTIVE HALF OF SWITCH WILL NOT TURN OFF LEAVING SOME AVIONICS S	YSTEMS POWER CONTROLLED BY A/C MASTER SWITCH.  SWITCH FAILED UNDER NORMAL OPERATING PARAMETERS.  POSSIBLE CAUSE OF FAILU	RE IS DUE TO POOR SWITCH DESIGN AND SUBMITTER STATED NEEDS TO BE RE-DESIGNED.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000050800090	20000508	00090	SO  	2000	5	8	20000427SH015    	1	20000321	G	3230	6792616	TRUNNION        			PIPER 	PA28  	PA28R201    	7102816	SO  										LEFT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	803ND	9165 				2837003				DURING SCHEDULED INSPECTION, HYDRAULIC FLUID WAS DISCOVERED ON AFT WEB OF THE LT MAIN LANDING GEAR TRUNNION.  UPON FURTH	ER INSPECTION, FOUND IT TO BE CRACKED WHERE THE WEB JOINS THE TRUNNION TUBE ALLOWING FLUID TO LEAK.  SUBMITTER STATED PO	SSIBLE CAUSE COULD BE HIGH TIME IN USE IN A TRAINING ENVIRONMENT.  (X)				1	L	7	1 	3O			 	2A13    					 
2000050800091	20000508	00091	CE  	2000	5	8	20000427SH016    	1	20000404	G	3240	353800657	VALVE           			BEECH 	76    	76          	1153005	CE  										PARKING BRAKE	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	822ER					ME293				DURING ENGINE-OUT TRAINING, IF PILOT''S RT RUDDER IS FULLY DEPRESSED AND THE PILOT''S FOOT IS HIGH AND RIGHT ON THE RUDD	ER PEDAL, THE PILOT''S RT FOOT CAN INADVERTENTLY PULL BACK ON THE PARKING BRAKE VALVE ACTUATOR ARM AND SET THE BRAKES.  	IF NOT CAUGHT PRIOR TO LANDING, BLOWN TIRES WILL RESULT WITH POSSIBLE LOSS OF DIRECTIONAL CONTROL.  RAYTHEON HAS BEEN NO	TIFIED.  (X)			1	L	7	2 	3O			 	A29CE   					 
2000050800094	20000508	00094		2000	5	8	20000427SH019    	4	20000330	G	2562	300011	ELT             			CESSNA	172   	172R        	2072401	CE  										CABIN	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	15	9543P					17280644				DURING 100-HOUR INSPECTION, ELT SYSTEM WAS TESTED FOR OPERATION.  UPON ACTIVATING PANEL MOUNTED REMOTE CABIN SWITCH, PN 	2019-10, ELT WOULD NOT TRANSMIT.  AFTER REPEATED ATTEMPTS, ELT WOULD SOMETIMES TRANSMIT.  ELT WAS REPLACED WITH A SERVIC	EABLE UNIT, PN 3000-11, S/N 326702, AND REMOTE SWITCH WAS REPLACED WITH NEW SWITCH.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000050800097	20000508	00097	CE  	2000	5	8	20000427SH022    	1	20000407	G	7120	0851559	LOCK            			CESSNA	182   	182N        	2072730	CE  										ENGINE MOUNT	MISSING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	9020G					18260560				WHILE PERFORMING THE APRIL, 2000 ANNUAL, FOUND THE MOUNT SAFETY LOCKS, PN 0851559, WERE MISSING ON ALL FOUR ENGINE MOUNT	S, PN J6545-1.  INSTEAD, THERE WAS AN EXTRA WASHER TO TAKE UP THE BOLT LENGTH.  THE MOUNTS WERE INSTALLED 5-19-98.  (X)					1	H	7	1 	3O			NT	3A13    					 
2000050800102	20000508	00102	CE  	2000	5	8	20000427SH027    	1	20000317	G	5711		SPAR            			CESSNA	421   	421C        	2076016	CE  										LT WING	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	60RR	6547 				421C0885				A CRACK  INDICATION WAS NOTED IN THE LT FORWARD UPPER WING SPAR.  THE CRACK INDICATION IS ABOVE THE OUTBOARD HI-LOK AND 	RUNS SPANWISE.  THE INDICATION IS .765 INCH PLUS/MINUS LONG AND IS .3401 PLUS/MINUS ABOVE THE HI-LOK.  INSPECTION WAS PE	RFORMED PER AD 91-25-08R1.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000050800103	20000508	00103	CE  	2000	5	8	20000427SH028    	1	20000315	G	3240	1338932	STATOR          	BFGOODRICH  		CESSNA	500   	500CESSNA   	2076602	CE  										BRAKE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	161CC		393  		0159R	5000161				WHILE PERFORMING CESSNA SB 500-32-47 AND GOODRICH BULLETIN 2-1530-32-2, FOUND 2 EACH STATORS ON LEFT BRAKE ASSEMBLY CRAC	KED IN MULTIPLE PLACES.  CRACKS RANGED IN LENGTH FROM .1850 INCH TO .50 INCH WITH TOTAL FAILURE LENGTH OF .6250 INCH.  A	CCORDING TO GOODRICH, IMPROPER MACHINING CAUSED THIS PROBLEM.  (X)				1	L	7	2 	4F			 	A22CE   					 
2000050800104	20000508	00104	SO  	2000	5	8	20000427SH029    	1	20000304	G	3230	3503002	ROD             			PIPER 	PA23  	PA23250     	7102308	SO  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2471M					277954065				DURING ANNUAL INSPECTION, FUNCTIONAL TEST OF THE MAIN LANDING GEAR REVEALED THE LT MLG WAS NOT GOING ALL THE WAY UP INTO	 THE WELL LEAVING A 1.50 INCH CRACK BETWEEN THE MLG DOORS.  DURING TROUBLESHOOTING, THE SUBJECT PART ACTUATING ROD WAS F	OUND TO HAVE A PIECE CRACKED OUT OF THE THREADED END OF THE ROD.  THE END  CAP WAS ALSO FOUND TO BE BADLY DAMAGED FROM A	 PREVIOUS  MAINTENANCE ACTION.  CYLINDER WAS REPLACED, ADJUSTED IAW MM AND A SUCCESSFUL FUNCTIONAL CHECK OF THE GEAR PER	FORMED.  POSSIBLE CAUSE IS IMPROPER ADJUSTMENT OF THE CYLINDER FOLLOWING REPACK.  (X)		1	L	7	2 	3O			 	1A10    					 
2000050800105	20000508	00105	GL  	2000	5	8	20000427SH030    	3	20000321	G	6114	D32517	HUB             			CESSNA	310   	T310Q       	2074244	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	7542Q	3112 	919  			310Q0042		EB3817A		RAM A/C ENGINE AND PROPELLER MODIFICATIONS PER STC NR SA 4011SW.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P36EA	 
2000050800106	20000508	00106	GL  	2000	5	8	20000427SH031    	3	20000321	G	6114	D32517	HUB             			CESSNA	310   	T310Q       	2074244	CE  						HARTZL	HCC3Y	PHCC3YF2    	GL  	PROPELLER	CRACKED         	H			F3PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	7542Q	3112 	919  			310Q0042		EB3817A		PART CRACKED FROM GREASE FITTING HOLE ACROSS BACK OF HUB TO OPPOSITE SIDE.  SENT TO HARTZEL PROPELLER FOR EVALUATION.  (	X)					1	L	7	2 	3O			 	3A10    		5	C	P25EA	 
2000050800107	20000508	00107	NE  	2000	5	8	20000427SH032    	2	20000313	G	7230	1703A38G02	SHAFT           								GE    	CF6   	CF650*      	30018	NE  					ENGINE SPOOL	DAMAGED         	B			KRDY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31							530197			AFTER SHOP MAINTENANCE AND RETURN TO SERVICE, ENGINE SUSTAINED TRANSPORT DAMAGE TO FAN SECTION.  THE ENGINE WAS RETURNED	 TO THE SHOP FOR REPAIR AND TEST RUN.  DURING TEST RUN, OIL LEAKAGE OCCURRED FORCING A DISASSEMBLY OF THE ENGINE.  AFTER	 DISASSEMBLY, NOTED THE 11/14 SPOOL SHAFT HAD A CRACK IN THE THREADED AREA WHERE THE AIR DUCT CONNECTS.  THIS PART IS UN	DER INVESTIGATION BY GE AND KLM.  PART LIFE LIMIT: 10,000 HOURS.  (X)								4	F			E23EA				 
2000050800108	20000508	00108	SO  	2000	5	8	20000427SH033    	1	20000329	G	8011	MHB4014	LEAD            	PRESTOLITE  		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					STARTER	SEPARATED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	27471	1071 				317852018	L100268A			RIGHT ENGINE FAILED TO START.  INVESTIGATION REVEALED BOTH FIELD BRUSH LEADS WERE SEPARATED FROM THEIR RESPECTIVE BRUSHE	S.  ONE BRUSH SHOWED NO INDICATION OF ARCING IN THE LEAD ATTACH HOLE IN THE BRUSH, WHILE THE OTHER DID.  IT APPEARED ONE	 BRUSH LEAD SEPARATED AND PLACED THE ENTIRE START LOAD ON THE OTHER BRUSH CAUSING IT TO FAIL AT THE LEAD ATTACH POINT.  	THE STARTER''S OVERALL CONDITION WAS EXCELLENT.  THE INSIDE WAS CLEAN AND BRIGHT.  FAILURE APPARENTLY WAS DUE TO A POORL	Y CONSTRUCTED BRUSH/LEAD ASSY THAT LEAD TO PREMATURE FAILURE.  WHEN THE OLD BRUSHES WERE COMPARED TO NEW BRUSHES, THE WE	AR WAS NEGLIGIBLE.  (X)	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000050800022	20000508	00022	EA  	2000	5	8	20000501SH001    	1	20000220	G	2810	2421143	SHUTOFF VALVE   			CNDAIR	CL600 	CL6002B19   	       	EA  										LT FUEL TANK	FAILED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	3899 				7008				TRANSFER SHUTOFF VALVE IS BYPASSING FUEL THROUGH ELECTRICAL CONDUIT.  TOP OF SOV BYPASSES FUEL THROUGH ''POTTING'' AND I	S FOUND DOWNSTREAM OF ELECTRICAL CONDUIT WITNESS HOLES.  SUBMITTER STATED THIS IS THE THIRD LEFT FUEL TRANSFER SOV TO BE	 REPLACED.  FIRST, NOV 1994, SECOND, APR 1995). (X)				2	L	7	2 	4F			RT	A21EA   					 
2000050800023	20000508	00023	EA  	2000	5	8	20000501SH002    	1	20000329	G	3240	7010FS9545708	SEAL            			CNDAIR	CL600 	CL6002B19   	       	EA  										BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1282 			JUN981372					BRAKE ASSY, PN 50105201, FAILED PREMATURELY.  TWO EACH, PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FILLED 	WITH FLUID.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY.  (X)					2	L	7	2 	4F			RT	A21EA   					 
2000050800024	20000508	00024	EA  	2000	5	8	20000501SH003    	1	20000330	G	3240	7010FS9545708	SEAL            			CNDAIR	CL600 	CL6002B19   	       	EA  										BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		805  			MAY991715					BRAKE ASSY, PN 5010520-1, FAILED PREMATURELY.  ONE EACH PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILLED WI	TH FLUID.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSY.  NOTE:  OEM PARTS INSTALLED IN BRA	KE ASSY.  (X)				2	L	7	2 	4F			RT	A21EA   					 
2000050800025	20000508	00025	SO  	2000	5	8	20000501SH004    	1	20000110	G	2823	A23D047524561731	SHUTOFF VALVE   			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	41148	50   				318352038				REPLACED HEATER FUEL SHUTOFF/REGULATOR VALVE DUE TO LEAK AT SEAL.  REPLACEMENT PART (HEAD) FAILED AT 50 HOURS TT.  SAME 	PROBLEM LEAKING FUEL AT SEAL/DIAPHRAGM.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000050800026	20000508	00026	CE  	2000	5	8	20000501SH005    	1	20000326	G	2780	04602171	BELLCRANK       			CESSNA	150   	152         	2071835	CE  										TE FLAP	BENT            	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	922AK	2294 				15281807				FLAPS WERE LOWERED TO 30 DEGREES DURING LANDING.  AS FLAPS WERE RAISED, A POP SOUND WAS HEARD AND FLAPS WOULD NOT EXTEND	.  INVESTIGATED AND FOUND BENT BELLCRANK.  SUSPECT BELLCRANK FAILED DUE TO WEAR ON CAM PORTION AND WORN SPACERS.  NEW PA	RT ON ORDER AND FLAP RIGGING TO BE ACCOMPLISHED.  (X)				1	H	7	1 	3O			NT	3A19    					 
2000050800027	20000508	00027	CE  	2000	5	8	20000501SH006    	1	20000404	G	5400	1225700025	SUPPORT BRACKET 			BEECH 	2000  	2000        	1152000	CE  										ENGINE NACELLE	CRACKED         	B			MZ4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	638LD					NC18				THE SUPPORT ASSY (MOUNTING BRACKET) FOR BOTH THE LEFT AND RIGHT ENGINE FIRE EXTINGUISHER BOTTLES WAS FOUND CRACKED.  THI	S MOUNTING BRACKET HAS BEEN FOUND CRACKED ON SEVERAL OTHER MODEL 2000 AIRCRAFT.  SUBMITTER STATED THEIR EXPERIENCE HAS B	EEN THAT A REPLACEMENT BRACKET OF THE SAME PART NUMBER WILL ALSO CRACK AFTER A VERY SHORT TIME IN SERVICE.  PRESENTLY, S	UBMITTER STATED THEIR CORRECTIVE ACTION HAS BEEN TO MANUFACTURE A REPLACEMENT BRACKET USING A D.E.R. DRAWING.  THIS MANU	FACTURED BRACKET AS OF YET HAS NO SIGNS OF CRACKING.  RAYTHEON AIRCRAFT HAS BEEN ADVISED OF THE PROBLEM AND SUBMITTER''S	 CORRECTIVE ACTION.  (X)	1	L	7	2 	4T			RT	A38ACE  					 
2000050800028	20000508	00028	GL  	2000	5	8	20000501SH007    	3	20000329	G	6110	2202	BEARING         			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	C6PTS	1700 						ED1808		RELEVENT INDICATION OF CRACKS ON BOTH SIDES OF BEARING.    (X)						1	L	7	2 	3O			 	3A16    		5	C	P36EA	 
2000050800029	20000508	00029	GL  	2000	5	8	20000501SH008    	3	20000329	G	6110	3252	FORK            			BEECH 	58    	58          	1152740	CE  						HARTZL	HCJ3Y	PHCJ3YF2    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	C6PTS	1700 						ED1808		CRACK IN BLOCK RETENTION AREA.  (X)						1	L	7	2 	3O			 	3A16    		5	C	P36EA	 
2000050800030	20000508	00030	SW  	2000	5	8	20000501SH009    	1	20000313	G	2910	1114	HOSE            			GULSTM	112   	112         	0144701	SW  										MLG ACTUATOR	DETERIORATED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	31		700  								STRATOFLEX HOSE NR 111-4, CURE DATE 3Q92, FULLY DETERIORATED WHILE INSTALLED ON BELGIAN REGISTERED AIRCRAFT.  NO OTHER C	ASES FOUND WITH INSTALLED HOSES.  THIS PART WAS BOUGHT THROUGH GILL AVIATION, VIA AVIALL.  HOSE INSTALLED ON A ROCKWELL 	112, WITH LYC IO-360-C1D6.  TT EST. 700 HOURS.  RECOMMEND THAT OPERATERS WITH LIKE HOSE INSPECT FOR CURE DATE AND NOTE C	ONDITION OF HOSE ASSY.  (X)			1	L	7	1 	3O			 	A12SO   					 
2000050800031	20000508	00031	CE  	2000	5	8	20000501SH010    	1	20000302	G	3233	S34832326H5	SEAL            	CESSNA      		CESSNA	500   	500CESSNA   	2076602	CE  										MLG ACTUATOR	WRONG PART      	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										CESSNA KITS RECEIVED WITH WRONG PART NUMBER SEAL RING (T-SEAL).  MANUAL 32-32-11 (TEIJIN SEIKI) CALLS FOR S34692-326H1. 	 KITS HAVE S34832-326H5 ENG ASSY MLG ACTUATOR, CESSNA P/N 9912053-17.  TEIJIN SEIKI, P/N 1523100-1.   RE:  CESSNA 500 SE	RIES.  (X)				1	L	7	2 	4F			 	A22CE   					 
2000050800034	20000508	00034	CE  	2000	5	8	20000501SH013    	1	20000329	G	3240	5003541	DISK            			CESSNA	500   	550         	2076604	CE  										RT BRAKE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	10EG		157  		DEC7266	5500055				DURING MAINTENANCE ON RT MLG WHEEL, MECH NOTICED 2 OF 3 BRAKE STATIONARY DISCS DID NOT MOVE WHEN THE WHEEL ASSY WAS REMO	VED.  INVEST REVEALED 2 STATIONARY DISCS FURTHEST FROM THE PISTON AND PRESSURE PLATE ASSY OF THE BRAKE WERE WARPED AND D	ISTORTED.  THE DISTORTION WAS TO THE POINT THE 2 DISCS WERE MAKING CONTACT WITH INNER WHEEL HALF SS HEATSHIELD, PN 50038	43.  THE DISTORTION, WITH DISCS ''GROWING'' IN RADIAL DIRECTION, HAS POTENTIAL TO ''LOCK-UP'' THE WHEEL AND CAUSE LOSS O	F CONTROL OF ACFT DURING GROUND OPERATIONS.  A ''BRAKE WEAR CHECK'' WAS PERFORMED.  CLEARANCE LESS THAN 0.54 INCH ''REMO	VE FOR OVERHAUL'' WEAR DIMENSION.  BRAKES TSO:  157.1 HRS, 148 LANDINGS.  (X)	1	L	7	2 	4F			 	A22CE   					 
2000050800035	20000508	00035	GL  	2000	5	8	20000501SH014    	3	20000302	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	89629	7042 	1359 			15282807		R775560		FOUND CRACK IN HUB AROUND BOLT HOLE EXTENDING TO EDGE OF HUB WHILE INSPECTING FOR AD 97-06-16 PAR(A)(1)(II).  LAST INSPE	CTION 209 HOURS AND TEN MONTHS AGO, SHOWED NO CRACKS.  (X)					1	H	7	1 	3O			NT	3A19    		5	N	P50GL	 
2000051000162	20000510	00162	NE  	2000	5	10	20000502SH008    	1	20000328	G	3222	1944E9A	BEARING         	CLEVELANDPNU	1944        	SKRSKY	S76   	S76A        	8143006	NE  										NLG	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	709AL				AL3988	760278				DURING RETRACTION TEST OF LANDING GEAR, NOSE STRUT PISTON WOULD NOT EXTEND COMPLETELY WITH AIRCRAFT ON JACKS.  WHEEL WOU	LD CENTER 180 DEGREES FROM NORMAL CENTER.  (WHEEL AND FORK ASSY WOULD CENTER BACKWARDS).  LOWER BEARING, PN 1944E9A, MOU	NTING FLANGE BOLT HOLES DRILLED 180 DEGREES OUT OF INDEX WITH BEARING CENTERING CAM LOBE.  (X)				1	G	7	2 	3U			 	H1NE    					 
2000051000163	20000510	00163	SW  	2000	5	10	20000502SH009    	1	20000201	G	6220	406010107105	ADAPTER         	BELL        	407         	BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	567AL	2468 			A266	53246				DURING DISASSEMBLY FOR 2,500 HOUR OVERHAUL, FOUND ADAPTER CORRODED DUE TO PRIMER NOT COMPATIBLE.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000051000164	20000510	00164	SW  	2000	5	10	20000502SH010    	1	20000201	G	6220	407010103101	PITCH HORN      	BELL        	407         	BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	567AL	2468 			A266	53246				DURING DISASSEMBLY FOR 2,500 HOUR OVERHAUL, FOUND PITCH HORN CORRODED DUE TO ADHESIVE NOT COMPATIBLE.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000051000165	20000510	00165	SW  	2000	5	10	20000502SH011    	1	20000201	G	6220	407010103101	PITCH HORN      	BELL        	407         	BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	567AL	2468 			A266	53246				DURING DISASSEMBLY FOR 2,500 HOUR OVERHAUL, FOUND PITCH HORN CORRODED DUE TO ADHESIVE NOT COMPATIBLE.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000051000166	20000510	00166	SW  	2000	5	10	20000502SH012    	1	20000205	G	6320	E6893673	GEAR            	ALLSN       		BELL  	407   	407         	       	SW  										GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	937AL	234  			CAG47125	53383				UPON VISUAL INSPECTION, INSPECTED CHIP DETECTOR PLUGS AND FOUND METAL ON PLUGS.  SPALLING AND GALLING ON TM GEAR TEETH, 	POSSIBLE DUE TO IMPROPER MESHING OF GEAR TEETH.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000051000167	20000510	00167	SW  	2000	5	10	20000502SH013    	1	20000205	G	6320	6893672	PINION GEAR     	ALLSN       		BELL  	407   	407         	1182206	SW  										GEARBOX	GALLED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	937AL	234  			CAG47125	53383				UPON VISUAL INSPECTION, INSPECTED CHIP DETECTOR PLUGS AND FOUND METAL ON PLUGS. SPALLING AND GALLING IN PINION GEAR TEET	H, POSSIBLE DUE TO IMPROPER MESHING OF GEAR TEETH.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000051000168	20000510	00168	NE  	2000	5	10	20000502SH014    	1	20000302	G	6210	7615009000046	BLADE           	SKRSKY      		SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL	18628	440  			760280				DURING 500-HOUR INSPECTION, FOUND TIP PLATE COMPLETELY DEBONDED. (X)						1	G	7	2 	3U			 	H1NE    					 
2000051000174	20000510	00174	EU  	2000	5	10	20000502SH020    	1	20000404	G	6220	1098110163	SCISSORS        			AGUSTA	A109  	A109A2      	0260120	EU  										MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	55NW	4933 				7267				DURING INSPECTION OVERHAUL, THE END OF THE LEVER ASSY (ROTATING SCISSORS ASSY) WAS FOUND TO HAVE A CRACK AT THE BUSHING 	BOSS END APPROXIMATELY 1 INCH LONG.  MATERIAL IS 2 INCHES THICK. (X)					1	G	7	2 	3U			 	H7EU    					 
2000051000175	20000510	00175	WP  	2000	5	10	20000503SH001    	2	20000410	G	7250	30720705	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN CURVIC AREA AND POST FIR TREE AREA.  LOT NR:  00P081.  (X)											4	F			E6WE				 
2000051000176	20000510	00176	WP  	2000	5	10	20000503SH002    	2	20000404	G	7250	30740962	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  LOT NR:  99P350.  (X)											4	F			E6WE				 
2000051000225	20000510	00225	GL  	2000	5	10	20000504SH002    	1	20000402	G	2840		SENSOR          			AMTR  	TITAN 	TITANTORNADO	       	GL  										FUEL CELL	MISINSTALLED    	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			W	Y	J	INADEQUATE Q C            	ENGINE STOPPAGE           	WARNING INDICATION        	NR	NOT REPORTED   	1			GL	15	196KW									SILICONE WAS USED TO INSTALL A FUEL SENSING UNIT INSIDE THE FUEL TANK.  THE SILICONE DISSOLVED AND SUBSEQUENTLY CLOGGED 	THE FUEL FILTER CAUSING THE ENGINE TO FAIL.  AN OFF AIRPORT LANDING WAS MADE CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT.  AC	FT S/N D96618SOKH0204.  (X)				1	H	7	1 	3I			NT	EXPA1H71					 
2000051000227	20000510	00227		2000	5	10	20000504SH004    	4	20000309	G	3416		SENSOR          	NARCO       		PIPER 	PA28  	PA28181     	7102807	SO  										ALTIMETER SYS	LEAKING         	B			UC2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	4145X	1177 			15103	2843152				STATIC SYSTEM LEAK GREATER THAN 100 FEET/MINUTE TRACED TO THIS UNIT.  AR850 ONLY TWO YEARS IN SERVICE SINCE AIRCRAFT WAS	 NEW.  AR850''S ARE NOT KNOWN TO BE FAULTY IN THIS MANNER.  SUBMITTER STATED POSSIBLE NARCO FACTORY DEFECT IN ASSEMBLY O	F SENSOR.   (X)				1	L	7	1 	3O			 	2A13    					 
2000051000228	20000510	00228	SO  	2000	5	10	20000504SH005    	1	20000331	G	8011	MHB2399S	ARMATURE        	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					STARTER	MISMANUFACTURED 	B			UC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	4149G	839  			8050831	2843191	L3632336A			SUBMITTER STATED THEY HAVE FOUND 6 ARMATURES TO HAVE SEEMINGLY SOFT METAL ON THE DRIVE END SPLINES.  THEY HAVE BEEN FOUN	D WITH THE SPLINES COMPLETELY GROUND OR STRIPPED AWAY LEAVING SHARDS OF STEEL IN THE GEAR CASING THAT CONTAMINATE THE RO	LLER BEARINGS.  THE BENDIX DRIVE GEAR IS NOT DAMAGED AND THE SHEAR PIN DOES NOT SHEAR.  THE ARMATURE DRIVE END MAY NOT B	E PROPERLY HEAT TREATED OR MAYBE THE SHEAR PIN IS TOO HARD.  (X)			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000051000231	20000510	00231	NM  	2000	5	10	20000504SH008    	1	20000404	G	5280	6521636185	DOOR            			BOEING	727   	727*        	       	NM  										MLG	WRONG PART      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										DOOR HAS BEEN IDENTIFIED AS A DASH 185.  DOOR IS NOT A DASH 185, BUT A DASH 1. DOOR HAS NOT BEEN MODIFIED PER SB 32-318 	WHICH ALLOWS USE OF LARGER DIAMETER DRAG STRUT FOR MLG.  THIS DOOR WAS  BINDING WITH DRAG STRUT WHICH MAY HAVE CAUSED DI	FFICULTY EXTENDING THE LANDING GEAR.  (X)				2	L	7	3 	4F			RT	A3WE    					 
2000051000232	20000510	00232	CE  	2000	5	10	20000504SH009    	1	20000504	G	3230		TORQUE LINK     			BEECH 	90    	C90         	1152913	CE  										MLG	MISMARKED       	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	04	90LF					LJ852				REF:  RAYTHEON SB 32-3116.  SOME TORQUE KNEES IDENTIFIED AS MLG P/N''S 50-810032-12 AND 50-810295-25 WERE MACHINED TO BE	 NOSE GEAR COMPONENTS.  IF  INSTALLED, THESE TORQUE KNEES WILL ALLOW MAIN GEAR TO OVER EXTEND AND DAMAGE FORWARD PORTION	 OF WHEELWELL UPON RETRACTION.  (X)				1	L	7	2 	3T			 	3A20    					 
2000051000233	20000510	00233	CE  	2000	5	10	20000504SH010    	1	20000415	G	2731		CONTROL CABLE   			CESSNA	182   	182S        	2072701	CE  										ELEVATOR TRIM	OUT OF RIG      	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	789LM	105  				18280043				WHILE CHECKING FOR ELEVATOR TRIM OPERATOR AFTER C/W SB 00-22-01A ON KAP-104 AUTOPILOT SERVO, NOTED THE ELEVATOR TRIM WOU	LD NOT GO FULL TRAVEL.  AFTER INVESTIGATING, NOTED THE SERVO TRIM CABLE SWEDGED BALL WAS OUTSIDE THE SERVO DRUM, THE AUT	OPILOT CABLE WAS NOT PROPERLY CENTERED IN REFERENCE TO ELEV TRIM NEUTRAL.  RIGGED SYSTEM TO CESSNA MM WITH NO RIGGING PR	OBLEMS.  SUBMITTER STATED IT WAS OBVIOUS TRIM WAS NOT RIGGED PROPERLY AT FACTORY.  POSSIBILITY OF OTHERS HAVING SIMILAR 	PROBLEM.  PROBLEM WOULD NOT BE OBVIOUS UNTIL ELEVATOR TRIM IS RUN TO ITS LIMIT ALLOWING THE SWEDGE BALL TO COME OFF THE 	DRUM.  (X)	1	H	7	1 	3O			NT	3A13    					 
2000051000235	20000510	00235	SO  	2000	5	10	20000504SH012    	1	20000405	G	3213	6531904	CLEVIS          	PIPER       		PIPER 	PA28  	PA28151     	7102805	SO  										MLG STRUT	FAILED          	H				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SW	99	41539					287415259				THE UPPER TORQUE LINK ATTACH CASTING CLEVIS BROKE WHILE DOING TOUCH AND GO''S.  THE STRUT PISTON AND WHEEL ASSY SEPARATE	D FROM AIRCRAFT HELD ONLY BY BRAKE LINE.  FAILURE CAUSED BY CRACK IN TORQUE LINK ATTACH CLEVIS ON STRUT.  (X)					1	L	7	1 	3O			 	2A13    					 
2000051000236	20000510	00236	CE  	2000	5	10	20000504SH013    	1	20000406	G	3220	5042000224	TRUNNION        			CESSNA	340   	340CESSNA   	2076404	CE  										NLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	123KK	5957 				3400251				NOSE GEAR TRUNNION FAILED.  (X)						1	L	7	2 	3O			 	3A25    					 
2000051000237	20000510	00237	CE  	2000	5	10	20000504SH014    	1	20000328	G	3230	51232530	CIRCUIT BREAKER 			CESSNA	337   	337H        	2075732	CE  										MLG PUMP	FAILED          	B			LX5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	12445	5306 				33701892				THE CIRCUIT BREAKER FAILED TO THE OPEN POSITION PREVENTING A NORMAL EXTENSION OF THE AIRCRAFT LANDING GEAR.  (X)						1	H	7	2 	3O			 	A6CE    					 
2000051000239	20000510	00239	CE  	2000	5	10	20000504SH016    	1	20000504	G	3060	MS21919WCF6	CLAMP           			CESSNA	340   	340A        	2076405	CE  										PROP DEICE SYS	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	550S					340A0086				PILOT COMPLAINED OF ''POP'' WHEN LANDING GEAR WAS EXTENDED.  LANDING MADE WITHOUT INCIDENT.  UPON INVESTIGATION COULD FI	ND NO PROBLEMS WITH GEAR RETRACTION SYSTEM.  FURTHER INVESTIGATION REVEALED LEFT PROPELLER NR 3 BLADE DEICE WIRE HARNESS	 CLAMP HAD BROKEN OFF AND HIT THE LEFT SIDE OF FUSELAGE CAUSING THE ''POP'' THE PILOT HEARD.  REPLACED BROKEN CLAMP AND 	REPAIRED HARNESS.  (X)			1	L	7	2 	3O			 	3A25    					 
2000051000241	20000510	00241	SO  	2000	5	10	20000504SH018    	1	20000314	G	3230	WTC21351	POWERPACK       			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	FAILED          	A			BSYA	A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			GL	07	4UE					318152061				DTW - AIRCRAFT DID NOT HAVE LEFT GEAR DOWN AND LOCK INDICATION.  FLEW AIRCRAFT BACK TO CMH.  MAINTENANCE REMOVED AND REP	LACED HYDRAULIC POWER PACK.  OPS CHECKED GOOD.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000051000242	20000510	00242	WP  	2000	5	10	20000504SH019    	2	20000309	G	7320	66001983	VALVE           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					FLOW CONTROL	FAILED          	A			BSYA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	56JA					342	P74242C			DEN - LOST PRESSURIZATION AFTER TAKEOFF OUT OF DENVER.  FOUND FLOW CONTROL VALVE STUCK CLOSED.  REMOVED AND REPLACED FLO	W CONTROL VALVE.  OPS CHECKED GOOD.  (X)					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2000051800055	20000518	00055	SO  	2000	5	18	20000504SH020    	1	20000314	G	3260		BULB            			PIPER 	PA31  	PA31350     	7103110	SO  										COCKPIT	FAILED          	A			BSYA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	07	4079Y					318152079				DTW - HAD NO RIGHT GEAR  DOWN AND LOCK LIGHT.  SWAPPED BULBS BETWEEN NOSE AND RIGHT MAIN.  INSTALLED NEW BULB.  OPS CHEC	KED GOOD.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000051800056	20000518	00056	EU  	2000	5	18	20000504SH021    	1	20000331	G	7921	5711012394	COOLER          			PILATS	PC12  	PC1245      	       	EU  										OIL SYSTEM	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	308NA					226				FOUND OIL COOLER VANE CRACKED WITH 3 POPPED RIVETS.  REMOVED AND REPLACED OIL COOLER VANE IAW MANUFACTURER''S SB 71-001.	  NO RECOMMENDATIONS TO PREVENT RECURRENCE SINCE SB 71-001 HAD BEEN PREVIOSULY C/W.  (X)					1	L	7	1 	3T			RT	A78EU   					 
2000051800057	20000518	00057	GL  	2000	5	18	20000504SH022    	3	20000413	G	6110	57C2295	BULKHEAD        													HARTZL	HCC2Y	HCC2YF1     	GL  	BLADE SLOTS	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								AM2897		MULTIPLE CRACKS AT BLADE SLOTS.  (X)																5	C	P920	 
2000051800060	20000518	00060	SO  	2000	5	18	20000504SH025    	2	20000309	G	8520	520	CRANKSHAFT      			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	FAILED          	B			VAIR	O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	19	69520	485  				3400353	514988			ENGINE IN-FLIGHT FAILURE DUE TO BROKEN CRANKSHAFT.  THIS CRANKSHAFT INSTALLED AS NEW ON MAY 4, 1999 TO REPLACE PREVIOUS 	NEW CRANKSHAFT AFFECTED BY AD 99-19-01.  THIS S/N CRANCKSHAFT, SN B129901N, IS NOT IN AD.  CRNAKSHAFT S/N''S  IN AD GO T	HROUGH 12-1998.  (X)				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2000051800061	20000518	00061	NM  	2000	5	18	20000504SH026    	1	20000411	G	2840	600N4004503	CONNECTOR       			DOUG  	600N  	600N        	3027377	NM  										FUEL INDICATOR	CONTAMINATED    	D				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	99	611BP	500  				RN041				PILOT RECEIVED ERRONEOUS FUEL QUANTITY INDICATIONS.  UPON REMOVING ELECTRICAL CONNECTOR AT AFT FUEL BLADDER COVER, NOTED	 THAT FUEL WAS LEAKING INTO PIN AREA.  THIS WAS THE SECOND INSTANCE.  FIRST WAS AT BORDER PATROL AIR OPERATIONS IN LARED	O, TX.  THESE HARNESSES APPARENTLY HAD A SEALING PROBLEM. (X)				1	G	7	1 	3U			NC	H3WE    					 
2000051800062	20000518	00062	NM  	2000	5	18	20000504SH027    	1	20000413	G	5311	65C353502	FRAME           			BOEING	727   	72721       	1384003	NM  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	727LA					19260				RIGHT FRAME AT STA 870 BETWEEN STR 9R - STR 10R HAS CRACK ON FORWARD OUTBOARD FLANGE UNDER SPLICE PLATE.  FOUND WITH ULT	RASOUND INSPECTION. (X)					2	L	7	3 	4F			 	A3WE    					 
2000062100001	20000621	00001	SO  	2000	6	21	20000504SH030    	1	20000322	G	3233	MS3877	O-RING          	GARKENYON   		PIPER 	PA32  	PA32RT300   	7103215	SO  										NLG ACTUATOR	FAILED          	H				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			GL	17	800TM	4343 				32R7985088				AFTER TAKEOFF, THE NOSE GEAR FAILED TO FULLY RETRACT AND WOULD NOT EXTEND TO DOWN AND LOCKED POSITION.  THE PILOT PERFOR	MED VAROIUS MANEUVERS AND GEAR FINALLY EXTENDED DURING A POWER OFF STALL.  AFTER LANDING INSPECTION, FOUND THE SHAFT O-R	ING ON THE NOSE GEAR ACTUATOR BADLY DETERIORATED CAUSING LOSS OF ALL SYSTEM FLUID.  ACTUATORS SHOULD BE INSPECTED CLOSEL	Y AND ANY SIGNS OF LEAKAGE SHOULD BE REPORTED.   (X)			1	L	7	1 	3O			 	A3SO    					 
2000051800065	20000518	00065	WP  	2000	5	18	20000504SH031    	1	20000406	G	6710	369A70099	CONTROL ROD     			HUGHES	369   	369E        	4470707	WP  										COLLECTIVE	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	9204Y	1688 				0532E				DURING INSPECTION, THE ROD END ON TOP OF THE COLLECTIVE MIXER CONTROL ROD WAS FOUND MOVING.  THE JAM NUT ON THE ROD END 	WAS TIGHT.  FURTHER INSPECTION REVEALED THE THREADED INSERT THE ROD END SCREWS INTO WAS LOOSE IN THE CONTROL ROD ITSELF.	  AFTER REMOVAL OF THE CONTROL ROD FROM THE AIRCRAFT FOR REPLACEMENT, IT WAS FOUND TO CONTAIN WATER THAT HAD APPARENTLY 	CENTERED THE TUBE AROUND THE LOOSE INSERT.  THIS IS THE SECOND INCIDENCE OF FINDING A LOOSE INSERT IN A COLLECTIVE MIXER	 CONTROL ROD.  (X)		1	G	7	1 	3U			 	H3WE    					 
2000051000283	20000510	00283	SO  	2000	5	10	20000505SH005    	2	20000405	G	8530	538304P030	PUSHROD         			BEECH 	55    	95A55       	1152704	CE  	CONT  	O520  	IO520CB     	17032	SO  					NR 6 CYLINDER	BENT            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		5115 	190  				244255R			NR 6 EXHAUST PUSHROD BENT, BROKEN AND WORN HALFWAY THRU FROM RUBBING ON INSIDE OF THE PUSHROD HOUSING.  NR 6 INTAKE PUSH	ROD BROKEN IN TWO.  CYL HAS 190 HRS SINCE NEW AND BOTH VALVES MOVED FREELY IN GUIDES.  NR 6 CONNECTING ROD FOUND VISIBLY	 BENT.  INTAKE MANIFOLD DRAINS DID NOT DRAIN WHEN TESTED.  POSSIBLE CAUSE, HYD LOCK, TCM SB96-11.  NR 6 CYL ON THIS INST	ALL (RT ENG OF BEECH BARON) IS FRONT INBD CYL.  CANT OF ENG WOULD MAKE THIS A LOW SPOT IN INTAKE WHERE FUEL WOULD ACCUMU	LATE.  WITH FUEL DRAIN INOP, IT WOULD NOT DRAIN OUT.  RECOMMENDATION IS TO INCLUDE  A TEST OF MANIFOLD  DRAINS AT 100-HR	 ANNUAL INSPECTION.  (X)	1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000051000285	20000510	00285	NE  	2000	5	10	20000505SH007    	2	20000404	G	7250	304418301	BLADE           								PWA   	PT6   	PT6A67D     	 	NE  					POWER TURBINE	DAMAGED         	B			MASR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										PART WAS REMOVED FROM STOCK NEW.  BLADE PLATFORM ON ONE BLADE WAS FOUND TO BE TAPERED AND VERY THIN.  P&WC WAS NOTIFIED 	AND WERE ADVISED TO REMOVE BLADE FROM STOCK AND SHIP BAD BLADE BACK TO P&WC.  PART WAS NEVER PUT INTO SERVICE. (X)										4	T			E26NE				 
2000051000286	20000510	00286	WP  	2000	5	10	20000505SH011    	2	20000414	G	7250	30723163	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					HP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  LOT NR 00P054.  (X)											4	F			E6WE				 
2000051000287	20000510	00287	WP  	2000	5	10	20000505SH012    	2	20000412	G	7250	30723163	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					HP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH 3 DENTS IN POST FIR TREE AREA AFT SIDE.  LOT NR 00P054.  (X)											4	F			E6WE				 
2000051000288	20000510	00288	WP  	2000	5	10	20000505SH013    	2	20000414	G	7250	30723163	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					HP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FRON HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  LOT NR 00P054.  (X)											4	F			E6WE				 
2000052300005	20000523	00005	WP  	2000	5	23	20000505SH014    	2	20000410	G	7230	30720705	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  LOT  NR 99P189.  (X)											4	F			E6WE				 
2000062200050	20000622	00050		2000	6	22	20000505SH016    	4	20000406	G	3418	861CAU2	VANE            																		FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										ANGLE OF ATTACK VANE FAILS ''''ZERO VOLT TEST''''.  AT A VANE ANGLE OF 19 DEGREES, VOLTAGE SHOULD BE 5.988 TO 6.012.  TH	IS VANE READS 6.4 VOLTS. THIS VANE WOULD CAUSE AN EARLY STALL WARNING AND/OR SLAT EXTENSION.  (X)																		 
2000061300352	20000613	00352	CE  	2000	6	13	20000505SH018    	1	20000329	G	7820	075016128	MUFFLER         			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  					EXHAUST	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	2354R					18255454	1301794R			DURING ANNUAL INSPECTION, THE LT INTERNAL BAFFLE WAS FOUND TO HAVE SEPARATED AND WAS PARTIALLY BLOCKING THE EXHAUST PORT	 IN THE MUFFLER.  UPON REMOVAL, THE RT EXHAUST STACK WAS FOUND BADLY DETERIORATED WITH SEVERAL PIECES MISSING.  ONLY  MI	NOR EXHAUST LEAK WAS NOTED FROM UNDER CLAMP.  TIME IN SERVICE OF THESE PARTS IS NOT KNOWN.  (X)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000061400119	20000614	00119	CE  	2000	6	14	20000505SH019    	1	20000329	G	7820	075016131	MUFFLER         			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  					INTERNAL CONNECT	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2354R					18255454	1301794R			DURING ANNUAL INSPECTION, THE LT INTERNAL BAFFLE WAS FOUND TO HAVE SEPARATED AND WAS PARTIALLY BLOCKING THE EXHAUST PORT	 IN THE MUFFLER.  UPON REMOVAL, THE RT EXHAUST STACK WAS FOUND BADLY DETERIORATED WITH SEVERAL PIECES MISSING.  ONLY  MI	NOR EXHAUST LEAK WASNOTED FROM UNDER CLAMP.  TIME IN SERVICE OF THESE PARTS IS NOT KNOWN.  (X)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000061600326	20000616	00326	EU  	2000	6	16	20000505SH024    	1	20000331	G	7921	5711012394	COOLER          			PILATS	PC12  	PC1245      	       	EU  										NOSE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	317NA	1368 				223				FOUND OIL COOLER VANE CRACK WITH 3 POPPED RIVETS.  REMOVED AND REPLACED OIL COOLER VANE IAW MANUFACTURER''''S SB 71-001 	KIT.  NO RECOMMENDATIONS TO PREVENT RECURRENCE SINCE SB 71-001 HAD PREVIOUSLY BEEN C/W. (X)					1	L	7	1 	3T			RT	A78EU   					 
2000061400120	20000614	00120	EA  	2000	6	14	20000505SH025    	2	20000407	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					HEAD	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	4381L	878  				288516016	L1341139A			FOUND ZERO COMPRESSION ON ROUGH RUNNING ENGINE.  FOUND CRACK FROM TOP SPARK PLUG AROUND OUTSIDE OF EXHAUST SEAT TO BOTTO	M SPARK PLUG. (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000061400121	20000614	00121	EA  	2000	6	14	20000505SH026    	2	20000407	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CYLINDER	CRACKED         	B			MW2R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	17	4381L	878  				288516016	L1341139A			FOUND ZERO COMPRESSION ON ROUGH RUNNING ENGINE.  FOUND CRACK FROM TOP SPARK PLUG AROUND OUTSIDE OF EXHAUST SEAT TO BOTTO	M SPARK PLUG. (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000061600327	20000616	00327	EA  	2000	6	16	20000505SH027    	2	20000407	G	8530	AEL6510212	CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					EXHAUST VALVE	BROKEN          	B			MW2R	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			GL	17	4350G	586  				288490058	L2749236A			EXHAUST VALVE BROKE ON FINAL APPROACH. (X)						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000061400126	20000614	00126		2000	6	14	20000505SH028    	4	20000309	G	3415		SENSOR          	NARCO       		PIPER 	PA28  	PA28181     	7102807	SO  											LEAKING         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145A	1086 			15091	2843150				*STATIC SYSTEM LEAK GREATER THAN 100 FEET/MINUTE TRACED TO THIS UNIT.  AR850 ONLY TWO YEARS IN SERVICE SINCE AIRCRAFT WA	S NEW.  AR850''''''''S ARE NOT KNOWN TO BE FAULTY IN THIS MANNER.  SUBMITER STATED  POSSIBLE NARCO FACTORY DEFECT IN ASS	EMBLY OF SENSOR.  THIRD FAILURE KNOWN TO SUBMITTER.  (X)				1	L	7	1 	3O			 	2A13    					 
2000061400127	20000614	00127		2000	6	14	20000505SH029    	4	20000309	G	3416		SENSOR          	NARCO       		PIPER 	PA28  	PA28181     	7102807	SO  											LEAKING         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145G	1078 			15090	2843151				STATIC SYSTEM LEAK GREATER THAN 100 FEET/MINUTE TRACKED TO THIS UNIT.  AR850 ONLY TWO YEARS IN SERVICE SINCE AIRCRAFT WA	S NEW.  AR850''S ARE NOT KNOWN TO BE FAULTY IN THIS MANNER.  SUBMITTER STATED POSSIBLE NARCO FACTORY DEFECT IN ASSEMBLY 	OF SENSOR.  SECOND FAILURE KNOWN TO THIS SOURCE. (X)				1	L	7	1 	3O			 	2A13    					 
2000052500060	20000525	00060	GL  	2000	5	25	20000505SH030    	1	20000418	G	6520	28135000	GEAR            			ENSTRM	F28   	280C        	3300505	GL  										T/R GEARBOX	BROKEN          	B			FSPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	5691W					1176				PILOT REPORTED NOT BEING ABLE TO SEE OIL LEVEL IN SIGHT GLASS.  WHEN SIGHT GLASS REMOVED, A PIECE OF GEAR SET (TOOTH) AB	OUT .4375 INCH LONG WAS  FOUND INSIDE.  ACFT HAD RETURNED FROM FLYING, AND THERE WAS NO VIBS OF NOISE.  WEAR MARKS ON BR	OKEN PART GAVE APPEARANCE OF HAVING BEEN BROKEN FOR QUITE SOME TIME.  INSP OF CHIP PLUG SHOWED NO  METAL FLAKES OR CHIPS	.  SUBMITTER RECOMMENDED PULLING SIGHT GLASS AND LOOKING INSIDE TAIL GEARBOX AT EACH 100-HR OIL CHANGE/AD 90-01-06 INSPE	CTING IT FOR METAL FLAKES.  (X)		1	G	7	1 	3O			 	H1CE    					 
2000061400131	20000614	00131	EA  	2000	6	14	20000505SH031    	2	20000505	G	7414	4150	MAGNETO         			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	AEIO320E1B  	41508	EA  						CONTAMINATED    	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	23	50395					A9379	L567955A			OWNER COMPLAINED OF ROUGH RUNNING/MISSING WHEN ENGINE HOT WHILE AT LOW POWER SETTINGS.  RT MAG (4150) REMOVED.  EXCESS P	LAY IN DIST END BEARING (APPROX PLAY, .030 INCH) SN 9010274.  LT MAG REMOVED (4151) SN 9010270.  FOUND ENTIRE INTERIOR O	F MAG CONTAMINATED BY GREASE FROM DRIVE END BEARING. THESE MAGS (4100 SERIES) ARE NOT REBUILDABLE AND SLICK SB RECOMMEND	S REPLACEMENT AND TIS TO BE NOT IN EXCESS OF 800 HRS.  ENGINE TT:  494 HRS  SINCE NEW.  			1	H	7	1 	3O	3	O	 	A21CE   	1E12				 
2000061400132	20000614	00132	EA  	2000	6	14	20000505SH032    	2	20000505	G	7414	4151	MAGNETO         			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	AEIO320E1B  	41508	EA  						CONTAMINATED    	B				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	23	50395					A9379	L567955A			OWNER COMPLAINED OF ROUGH RUNNING/MISSING WHEN ENGINE HOT WHILE AT LOW POWER SETTINGS.  RT MAG (4150) REMOVED.  EXCESS P	LAY IN DIST END BEARING (APPROX PLAY, .030 INCH) SN 9010274.  LT MAG REMOVED (4151) SN 9010270.  FOUND ENTIRE INTERIOR O	F MAG CONTAMINATED BY GREASE FROM DRIVE END BEARING. THESE MAGS (4100 SERIES) ARE NOT REBUILDABLE AND SLICK SB RECOMMEND	S REPLACEMENT AND TIS TO BE NOT IN EXCESS OF 800 HRS.  ENGINE TT:  494 HRS  SINCE NEW.  (X)			1	H	7	1 	3O	3	O	 	A21CE   	1E12				 
2000061400133	20000614	00133		2000	6	14	20000505SH033    	4	20000413	G	6113	08550301719	SPINNER         			CESSNA	310   	310K        	2074228	CE  										LEFT	CRACKED         	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	6942L	120  				310K0042				BRAND NEW CESSNA SPINNER DOME INSTALLED ON 4-30-99.  LAST INSPECTION ANNUAL ON 7/16/99.  APRIL12, 2000, 100-HOUR INSPECT	ION REVEALS ONE INCH CRACK AT ONE MOST FORWARD SCREW.  TWO SCREW HOLES ARE OVAL, NOT ROUND.  TOTAL PART TIME PLUS/MINUS 	120 HOURS.  (X)				1	L	7	2 	3O			 	3A10    					 
2000052500061	20000525	00061	WP  	2000	5	25	20000505SH034    	1	20000329	G	6720	269A6050S	SWASHPLATE      			HUGHES	269   	269C        	4470504	WP  										TAIL ROTOR	BINDING         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	61447	2428 				0007				INTERMITTENT T/R PEDAL BINDING.  (X)						1	G	7	1 	3O			 	4H12    					 
2000052500062	20000525	00062	SW  	2000	5	25	20000505SH035    	1	20000120	G	6340	209A425013	TACHOMETER      			HUGHES	269   	269C1       	8059504	SW  										MAIN ROTOR	INOPERATIVE     	B			CAXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	6147Q	1393 				0068				ROTOR TACHOMETER INOPERABLE.  (X)						1	G	7	1 	3O			O	4H12    					 
2000061400201	20000614	00201	NE  	2000	6	14	20000508SH003    	1	20000414	G	7120	LA4180	MOUNT           			CONAER	LA4   	LA4         	5110302	NE  										RT LOWER ATTACH	CRACKED         	B			UM9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6653L	757  				416				RIGHT LOWER ENGINE ATTACH POINT CRACKED TO RIGHT STRUT ATTACH POINT.  (RADIALLY THROUGH MOUNT TUBE).  DETECTED DURING AN	NUAL INSPECTION VISUALLY AND VERIFIED BY DIE/PENETRANT.  (X)					1	H	7	1 	3O			 	1A13    					 
2000061400202	20000614	00202	EA  	2000	6	14	20000508SH005    	2	20000324	G	8530	LW15318	ROCKER BOSS     	LYC         		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  						FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	75958		85   			17268069	RL81676			VALVE ROCKER RETAINING STUD, PN 31-16, SHEARED FLUSH WITH THE CYL HEAD SURFACE.  THIS CAUSED PARTS TO MOVE AROUND AT RAN	DOM IN THE HEAD.  IT IS SUSPECTED THESE LOOSE PARTS INTERFERRED WITH OPER OF INTAKE VALVE MECHANISM CAUSING THE INTAKE P	USH ROD TO BEND, CREATING AN OIL LEAK AT THE PUSH ROD HOUSING.  SAME PROBLEM OCCURRED 65.7 HRS EARLIER WITH NR 1  CYL, 1	9.2 HRS SINCE O/H.  INSP OF ENG REVEALED EXH ROTATOR CAP DISLODGED, LAYING IN BOTTOM OF VALVE COVER ON NR 2 CYL.  SUSPEC	TED EXH VALVES MAY BE STICKING IN OPEN POSITION ALLOWING ROTATOR CAP TO FALL OUT OF POSITION.  THE EXCESSIVE CLEARANCE T	HEN CREATED  BETWEEN ROCKER ARM AND EXH VALVE STEM COULD POSSIBLY CAUSE ABNORMAL STRESS TO ROCKER ARM RETAINING STUD. 	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000061300360	20000613	00360		2000	6	13	20000508SH007    	4	20000417	G	2300		LIGHT           			CESSNA	172   	172R        	2072401	CE  										WIRING BUNDLE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	869CP	953  				17280641				PILOT REPORTED THE RADIO LIGHTS WERE FLICKERING WHILE ENGINE WAS RUNNING.  UPON INSPECTION, WIRING BUNDLE THAT RUNS HORI	ZONTALLY ACROSS BOTTOM OF INSTRUMENT PANEL WAS FOUND CHAFING ON ''''RADIO INSTRUMENT LIGHT POTENTIOMETER'''' PN S2091-9 	(REF:  R1002 I CESSNA WIRING DIAGRAM 33-10-01).  THE CHAFING HAD DAMAGED AND CREATED  BARE SPOTS ON THREE WIRES THAT WER	E TRACED TO THE AVIONICS LIGHTING BUS'''' CREATING A SHORT AND CAUSING THE FLICKERING OF LIGHTS.  THE WIRES WERE REPAIRE	D AND WIRING BUNDLE WAS SECURED AND REPOSITIONED IN A WAY TO PREVENT FURTHER CHAFING ON POTENTIOMETER.  (X)		1	H	7	1 	3O			NT	3A12    					 
2000061400203	20000614	00203	CE  	2000	6	14	20000508SH009    	1	20000402	G	3213	J199744G16	BEARING         			CESSNA	172   	172RG       	2072438	CE  										TRUNNION ASSY N/	LACK OF LUBE    	D				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			NE	05	9717B	1770 				172RG0987				AIRCRAFT WOULD NOT STEER ON TAKEOFF ROLL.  BRAKES INEFFECTIVE TO TURN.  DISASSEMBLED NOSE GEAR TRUNNION AND FOUND UPPER 	AND LOWER NACELLE BEARINGS RUSTED AND FROZEN.  NO PROVISIONS FOR LUBRICATION AT THESE POINTS.  AIRCRAFT MANUFACTURED 198	2.  				1	H	7	1 	3O			 	3A17    					 
2000061600332	20000616	00332	CE  	2000	6	16	20000508SH010    	1	20000402	G	3213	J199740G12	BEARING         			CESSNA	172   	172RG       	2072438	CE  										TRUNNION ASSY	FROZEN          	D				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			NE	05	9717B	1770 				172RG0987				AIRCRAFT WOULD NOT STEER ON TAKEOFF ROLL. BRAKES INEFFECTIVE TO TURN.  DISASSEMBLED NOSE GEAR TRUNNION AND FOUND UPPER A	NDFROZEN.  NO PROVISIONS FOR LUBRICATION AT THESE POINTS.  AIRCRAFT MANUFACTURED 1982.  					1	H	7	1 	3O			 	3A17    					 
2000061400205	20000614	00205	CE  	2000	6	14	20000508SH012    	1	20000329	G	7120	909100141	MOUNT           			BEECH 	100   	B100        	1152919	CE  											WORN            	B			WD4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	818PA	5807 				BE18				WHILE DOING A HOT SECTION INSPECTION ON THE RIGHT ENGINE AFTER REMOVAL FROM THE AIRCRAFT, NOTICED DAMAGE TO THE TUBULAR 	ENGINE MOUNT CROSS-MEMBER.  AFTER FURTHER INVESTIGATION, FOUND AN ENGINE MOUNT BRACKET RUBBING AGAINST THE TUBULAR CROSS	-MEMBER.  (X)				1	L	7	2 	4T			 	A14CE   					 
2000061300514	20000613	00514	CE  	2000	6	13	20000508SH016    	1	20000411	G	5753	122101015	FLAP TRACK      			CESSNA	182   	182P        	2075816	CE  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1298M					18264280				SHEARED RIVETS AT FORWARD LOWER END OF FLAP TRACK AND CRACKED FLAP TRACKMOUNTING ANGLE LOWER END FORWARD.  WING FLAP WAS	 DAMAGED WHEN FLAPS WERE RETRACTED AND CONTACT WAS MADE  WITH BRACKET IN FLAP WELL.  POSSIBLE CAUSE, OPERATING FLAPS AT 	HIGHER THAN NORMAL SPEEDS.  (X)				1	H	7	1 	3O			NT	TA13    					 
2000060900521	20000609	00521		2000	6	9	20000508SH017    	4	20000418	G	3416	212070238007	ALTIMETER       			BELL  	412   	412EP       	1182205	SW  										COCKPIT	OUT OF ADJ      	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6400J		20   			36243				ALTIMETER FAILED CALIBRATION.  REPLACED WITH NEW ALTIMETER FROM BELL HELICOPTER. (X)						1	G	7	2 	4U			 	H4SW    					 
2000060900522	20000609	00522		2000	6	9	20000508SH018    	4	20000418	G	3416	212070238	ALTIMETER       			BELL  	412   	412EP       	1182205	SW  										COCKPIT	OUT OF ADJ      	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6400J		20   			36243				ALTIMETER FAILED CALIBRATION.  REPLACED WITH NEW ALTIMETER FROM BELL HELICOPTER. (X)						1	G	7	2 	4U			 	H4SW    					 
2000061400206	20000614	00206	EA  	2000	6	14	20000508SH019    	2	20000414	G	8540		GEAR            			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					CRANKSHAFT	BROKEN          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	21	678TA	6418 	2106 			77	L1395540			ON CRUISE FLIGHT, LEFT ENGINE QUIT.  PILOT LANDED, INVESTIGATION REVEALED BROKEN CRANKSHAFT GEAR.  ENGINE RETIRED FROM S	ERVICE AND AND OVERHAULED ENGINE INSTALLED ON AIRCRAFT. (X)					1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2000061400207	20000614	00207	SO  	2000	6	14	20000508SH020    	2	20000310	G	7421		SPARK PLUG      	CONT        		CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520*      	17032	SO  					NR 2 CYLINDER	FAILED          	A			FMAA	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AL	01	75703					20700639	814764R			PISTON TOP BEGAN TO DISINTEGRATE CAUSING SEVERAL SPARK PLUG FAILURES AND ENOUGH POWER LOSS TO CAUSE A FORCED LANDING.  (	X)					1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2000061400208	20000614	00208	NE  	2000	6	14	20000508SH021    	3	20000404	G	6111	2202	BEARING         	HARTZL      		PIPER 	PA60  	PA60601P    	7106012	NM  						HARTZL	HCC3Y	HCC3YR2     	NE  		CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	LU4R					61P0395135		CK4084A		CRACK INDICATION ON BOTH SIDES OF BEARING.  (X)						1	M	7	2 	3O			RT	A17WE   		5	C	P25EA	 
2000062000009	20000620	00009		2000	6	20	20000508SH022    	4	20000411	G	6122	A3181	COUPLER         	HARTZL      																	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					3487T					RELEVENT CRACK INDICATION OF THE DRIVE SPLINE OF THE DRIVE COUPLER.  (X)																			 
2000062000010	20000620	00010		2000	6	20	20000508SH023    	4	20000404	G	6122	B41832	FLYWEIGHT       	HARTZL      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  						CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	100RN				D2691T	318152080				RELEVENT CRACK INDICATION ON FLYWEIGHT BASE.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000062000011	20000620	00011		2000	6	20	20000508SH024    	4	20000405	G	6122	B20908	FLYWEIGHT       	MCAULY      		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	IO520*      	17032	SO  						CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					860296					RELEVANT CRACK INDICATION ON BASE OF FLYWEIGHT DISC.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E5CE				 
2000062000012	20000620	00012	CE  	2000	6	20	20000508SH025    	1	20000412	G	3230	07106082	ANGLE           			CESSNA	182   	182E        	2072712	CE  										GEARBOX	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9212X	3811 				18253612				DURING ANNUAL INSPECTION, DISCOVERED PN 0710608-2 ANGLE HEAVILY RUSTED.  AIRCRAFT ANNUAL INSPECTION COMPLETED 12 MONTHS 	PRIOR TO THIS INSPECTION, AND THE AIRCRAFT WAS DELIVERED FOR INSIDE STORAGE.  INSPECTION DISCOVERED DRIED MUD AND DEBRIS	 IN THE BELLY.  AIRCRAFT WAS PREVIOUSLY OPERATED ON A GRASS AND DIRT STRIP.  ALL BELLY DRAIN HOLES WERE PLUGGED WITH MUD	 AND DEBRIS, AND ALLOWED WATER TO COLLECT.   SUBMITTER STATED DURING FUTURE ANNUALS, INSPECT BELLY OF AIRCRAFT THOROUGHL	Y.   (X)		1	H	7	1 	3O			NT	3A13    					 
2000062000013	20000620	00013		2000	6	20	20000508SH026    	4	20000329	G	2215		SERVO           	BENDIX      		BEECH 	58    	58          	1152740	CE  											FAILED          	B			XA12	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	05	3033B	149  				TH1869				PILOT REPORTED AUTOPILOT PITCH AXIS FAILED AFTER FLYING THROUGH TURBULENCE.  PITCH SERVO REMAINED ENGAGED, BUT IT WOULD 	NOT FOLLOW FLIGHT DIRECTOR COMMANDS.  COMPLAINT WAS CONFIRMED ON GROUND TEST.  UPON REMOVAL OF PITCH SERVO, AND ROTATING	 IT SIDE TO SIDE, IT WAS DETERMINED THAT NUMEROUS UNKNOWN INTERNAL COMPONENTS HAD BECOME DETACHED.   (X)				1	L	7	2 	3O			 	3A16    					 
2000062100002	20000621	00002	SO  	2000	6	21	20000508SH030    	1	20000508	G	3710	SVS0133	SHUTTLE VALVE   			PIPER 	PA32  	PA32300     	7103212	SO  										VACUUM SYSTEM	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2391U	1013 				327940253				DURING ANNUAL INSP,  VACUUM PUMP DRIVE FOUND SHEARED.  OWNER/PILOT DID NOT KNOW PUMP INOP DURING DELIVERY FLIGHT OR AT A	NY OTHER TIME.  INSP FOUND ACFT TO HAVE PRECISE FLIGHT STANDBY VACUUM SYS INSTALLED, TAE SVS-133  WHICH HAD AN AUTOMATIC	 FLAPPER/SHUTTLE VALVE WHICH DELIVERS VACUUM FROM  ENG INDUCTION SYS, SYS HAS NO INDICATION IN THE COCKPIT TO ALERT PILO	T PRIMARY PUMP HAS FAILED.  VALVE HAD ALUM RIVET WHICH WAS BADLY WORN AND MEASUREMENT OF SIDE CLEARANCE EXCESSIVE.  AD 9	9-24-10 DATED 1-14-00 RECURRING 12/24 MONTHS INSP OF PRECISE FLIGHT STANDBY VACUUM SYS DOES NOT APPLY TO THIS INSTALL.  	 THIS SYS IS STILL LEGAL AND INSTALLED IN ACFT APPROX 1983.  NO PUMP FAILURE INDICATION.  IMPENDING VALVE FAILURE.  (X)	1	L	7	1 	3O			 	A3SO    					 
2000062100003	20000621	00003	SW  	2000	6	21	20000508SH031    	1	20000328	G	7810	40821089	EXHAUST PIPE    	LYC         		MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  					CONNECTS CYL 2	CRACKED         	B			FE6R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	11	139WT	45   				270283	L1036461A			PILOT REPORTED NEW CO2 INDICATOR TURNS BLACK EACH FLIGHT.  FLT WITH DIGITAL CO2 INDICATING INSTRUMENT INDICATES 200 RPM.	  MAINT LOCATED 1.75 INCH CRACK AT BASE OF NR 2 CYL RISER,  FLG MATING TO CYL NR 1 - 5.  (LYC PN''S 40B19822 AND 40B1982	5) FOUND WARPED APPROX .020 INCH.  EXH PIPE COUPLING FLG FOR CYL NR 4 (LYC PN 40B19824) FND DISTORTED WITH GASKET (PN 78	084) JOINING IT TO CYL NR 6 BADLY DAMAGED, OUT OF PLACE.  ALL CRACKED AND DISTORTED COMPONENTS REPLACED WITH FACTORY NEW	.  FLG MATING TO CYL 1- 5 ARE DRESSED ON A SURFACE PLATE.  (X)		1	L	7	1 	3O	3	O	RT	2A3     	E14EA				 
2000062200087	20000622	00087	NE  	2000	6	22	20000509SH001    	2	20000421	G	8550	30506353	ROTOR           								CFE   	      	CFE73811B   	 	NE  					OIL PUMP	MISALIGNED      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										IT WAS FOUND THAT THE SEAL ROTOR, PN 3120524-2, WAS INSTALLED BACKWARDS.  (X)											4	F			E44NE				 
2000073100001	20000731	00001	NE  	2000	7	31	20000509SH002    	2	20000417	G	7261	30506353	PUMP            								CFE   	      	CFE73811B   	 	NE  					SEAL ROTOR	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										IT WAS FOUND THAT THE SEAL ROTOR, PN 3120524-2,WAS INSTALLED BACKWARDS.  (X)											4	F			E44NE				 
2000073100002	20000731	00002	SO  	2000	7	31	20000509SH003    	1	20000422	G	3240	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1 POSITION	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		189  			0291A					BRAKE ASSEMBLY, PN 2-1585R, FAILED PREMATURELY.  NR 1 STATOR CRACKED AT 2 RELIEF HOLES.  SUBMITTER STATED THIS IS A CONT	INUAL DISCREPANCY.   NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY. (X)					2	L	7	2 	4T			RT	A31SO   					 
2000073100003	20000731	00003	SO  	2000	7	31	20000509SH004    	1	20000424	G	3240	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1 & 2	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1351 			1058A					BRAKE ASSEMBLY, PN 2-1585-R, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  SUBMITTER STATED THIS 	IS A CONTINUAL DISCREPANCY.  NOTE: RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2001012900141	20010129	00141	NE  	2001	1	29	20000509SH006    	2	20000411	G	7230	2A2833	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										FLUORESCENT PENETRANT INSPECTION IAW I.A.E. V2500 PSEM, REV 42, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-23-01-230	-501).  PART REJECTED AT F.P.I. DUE TO A CRACK ON THE TOP SURFACE, 0.180 INCH LONG (AS MARKED).  (X)										4	F			E311NE				 
2000062200105	20000622	00105	NE  	2000	6	22	20000509SH007    	2	20000418	G	7230	2A0003	BEARING         	IAE         							IAE   	V2500 	V2500A1     	 	NE  					NR 4 OUTER RACE	SCORED          	B			RA1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		2299 			P421091		V10491			ENGINE WAS REMOVED FOR ''NR 4 BEARING INSPECTION/REPAIR''.  THE NR 4 BEARING EXHIBITED AXIAL SCORING OF THE ROLLERS AND 	OUTER RACE.  .  (X)										4	F			E311NE				 
2001012900005	20010129	00005	WP  	2001	1	29	20000509SH017    	2	20000417	G	7230	30723524	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					POST FIR TREE	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH NUMEROUS SCRATCHES AROUND DISK IN THE POST FIR TREE AREA.  LOT NR:  00P048.  (X)											4	F			E6WE				 
2001012900118	20010129	00118	NE  	2001	1	29	20000509SH042    	2	20000419	G	7230	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					TOP SURFACE	CRACKED         	C			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FROM WESTFIELD GAGE FOR FPI IAW V2500 MANUAL REVISION 42, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-2	3-01-230-501.  PART REJECTED AT FPI DUE TO A CRACK (ONE PLACE ON TOP SURFACE, 0.200 INCH LONG).   NOTE:  SUBMITTER STATE	D SECOND TIME THIS SERIAL NUMBER REJECTED.  									4	F			E311NE				 
2001012900119	20010129	00119	SO  	2001	1	29	20000509SH043    	1	20000426	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1 & NR 2 POSI	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1214 			0097A					BRAKE ASSEMBLY, PN 2-15-85-R, FAILED PREMATURELY.  NR 2 STATOR CRACKED AT MULTIPLE RELIEF HOLES.  SUBMITTER  STATED THIS	 IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2000073100004	20000731	00004	SO  	2000	7	31	20000509SH044    	1	20000426	G	3240	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1 & 2	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		975  			0661A					BRAKE ASSY, P/N 2-1585-R, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT MULTIPLE RELIEF HOLES.  SUBMITTER STATED	 THIS IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2000061300370	20000613	00370	SW  	2000	6	13	20000510SH001    	1	20000302	G	5311	206031308015	FRAME           			BELL  	206   	206B        	1181511	SW  										FUSELAGE	CRACKED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	67882	2378 				5222				FRAME CRACKED AT TOP RIGHT HAND POSITION, (1:00 O''CLOCK).  (X)						1	G	7	1 	3U			 	H2SW    					 
2000062100007	20000621	00007	CE  	2000	6	21	20000510SH002    	1	20000510	G	2820	1200406248	LINE            			CESSNA	206   	206H        	2073301	CE  										LEFT HEADER TANK	DEFECTIVE       	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	7273Q	191  				20608045				DURING A 100-HOUR INSPECTION, THE FUEL LINE BETWEEN THE LEFT HEADER TANK AND THE FUEL SELECTOR WAS FOUND LEAKING AT THE 	FITTING.  UPON REMOVAL, IT WAS DETERMINED THE FLARE WAS DEFECTIVE.  (X)					1	H	7	1 	3O			RT	A4CE    					 
2000062100008	20000621	00008	EA  	2000	6	21	20000510SH003    	2	20000407	G	7310	MS21044N3	NUT             			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	O540*       	41532	EA  					FUEL INJECTION	DEFECTIVE       	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	7273Q	191  				20608045				DURING A 100-HOUR INSPECTION, THE FUEL INJECTION LINE CLAMPS WERE FOUND SECURED WITH FIBER LOCK NUTS, OF WHICH THE FIBER	 LOCK WAS MELTED FROM THE HEAT OF THE ENGINE DURING OPERATION.  ALL NUTS WERE REPLACED WITH ALL-STEEL LOCK NUTS, P/N MS2	1045.  (X)				1	H	7	1 	3O	3	O	RT	A4CE    	E295				 
2001011100560	20010111	00560	GL  	2001	1	11	20000510SH004    	3	20000408	G	6110	B3D36C432B	PROPELLER       			CESSNA	206   	206H        	2073301	CE  						MCAULY	3DF36C	B3DF36C432B 	GL  	ENGINE	LEAKING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	2312V	298  				2608046		991143		DURING A PRE-FLIGHT INSPECTION OF THE AIRCRAFT IN A HANGAR, THE PILOT FOUND A LARGE POOL OF RED OIL ON THE FLOOR BENEATH	 THE PROPELLER.  UPON REMOVAL OF THE SPINNER, DETERMINED THE FLUID WAS LEAKING FROM UNDER A PROPELLER BLADE ROOT.  THE P	ROP WAS REMOVED AND SENT OUT FOR REPAIR.  (X)				1	H	7	1 	3O			RT	A4CE    		5	C	 	 
2000062600001	20000626	00001	NE  	2000	6	26	20000510SH005    	2	20000405	G	7261	MS9388019	O-RING          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE OIL	CUT             	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	1275N	161  				208B0756	PCEPO0686			DURING A POST-FLIGHT INSPECTION, THE PILOT NOTED EXCESSIVE OIL ON THE LOWER COWL AND DOWN THE LEFT SIDE OF THE AIRCRAFT.	  UPON FURTHER INSPECTION, DETERMINED A NR 2 BEARING OIL SCAVENGETUBE COUPLING O-RING LOCATED AT C-FLANGE WAS LEAKING.  	UPON REMOVAL OF THE O-RING, IT WAS FOUND TO BE 75 PERCENT CUT IN HALF.  THE O-RING WAS REPLACED.  (X)				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000062100011	20000621	00011	CE  	2000	6	21	20000510SH006    	1	20000407	G	2810	1200406242	LINE            			CESSNA	206   	206H        	2073301	CE  										HEADER TANK	DEFECTIVE       	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	7273Q	191  				20608045				DURING A 100-HOUR INSPECTION, THE FUEL LINE BETWEEN THE RIGHT HEADER TANK AND THE FUEL SELECTOR WAS FOUND LEAKING AT THE	 FITTING.  UPON REMOVAL, DETERMINED THE FLARE WAS DEFECTIVE.  (X)					1	H	7	1 	3O			RT	A4CE    					 
2000062100012	20000621	00012	CE  	2000	6	21	20000510SH008    	1	20000310	G	7120	9691001061	ENGINE          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					UPPER CROSS-OVER	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	37SF	10525	2344 			TH627	244230			DURING A SCHEDULED INSPECTION, A CRACK WAS DISCOVERED IN THE LEFT ENGINE MOUNT AT THE UPPER CROSSOVER TUBE NEAR THE WELD	 AT THE UPPER INBOARD ENGINE ATTACH POINT (CUSHION MOUNT).  AD 91-15-20 A3 AND C HAD BEEN PREVIOUSLY C/W 2,344.4 HOURS A	GO.  THE MOUNT WAS REMOVED AND REPAIRED BY REPLACING THE DAMAGED TUBE.  A RECORD CHECK SHOWS SUDDEN ENGINE STOPPAGE 1,16	0.8 HOURS PRIOR TO THIS DISCOVERY, AT WHICH TIME THE ENGINE WAS OVERHAULED AND THE MOUNT WAS INSPECTED FOR DAMAGE.  IT I	S BELIEVED THAT IN LIGHT OF THE PAST HISTORY, THE SUDDEN STOPPAGE FATIGUED THE MOUNT AT THIS POINT AND NORMAL ENGINE VIB	RATION ALLOWED THE CRACK TO DEVELOP.  (X)	1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000061600448	20000616	00448	SW  	2000	6	16	20000510SH015    	1	20000415	G	5320	407030801105	BEARING         	BELL        		BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL  ROTOR G/B	FRETTED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	407DD	634  			AFS979	53328	CAE847380			WHILE PERFORMING SCHEDULED LUBRICATION OF TAIL ROTOR HANGER BEARINGS, MECHANIC NOTICED METALLIC FRETTING DUST AROUND TAI	L ROTOR GEARBOX MOUNTING AREA. FURTHER INVESTIGATION REVEALED MOVEMENT BETWEEN TAIL ROTOR GEARBOX AND TAILBOOM.  THIS MA	LFUNCTION IS UNDER INVESTIGATION BY MANUFACTURER AND SUBMITTER IS AWAITING RESULTS  OF THIS INVESTIGATION.  (X)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2000062200133	20000622	00133	SW  	2000	6	22	20000510SH019    	1	20000302	G	5346	212030015101P	FITTING         			BELL  	412   	412         	1182202	SW  										ENGINE MOUNT	CRACKED         	C			ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	302FD	1659 				33200				DURING ENGINEDECK REPLACEMENT, FOUND FUSELAGE FITTING AT LEFT FORWARD ENGINE MOUNT ATTACHMENT CRACKED.  CRACKS EMANATE F	ROM INISDE REAR BOLT HOLE.  POSSIBLE CAUSE IS  HOLES NOT PROPERLY DEBURRED.  SUBMITTER STATED TO PREVENT RECURRENCE, HOL	ES SHOULD BE DEBURRED OR CHAMFERED ENOUGH TO REMOVE SHARP EDGES.  (X)				1	G	7	2 	4U			 	H4SW    					 
2000062100014	20000621	00014	EU  	2000	6	21	20000510SH021    	1	20000428	G	7930	0235237790	CHIP DETECTOR   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	DEFECTIVE       	H				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			WP	13	451H	352  				3231	9643			WHILE PILOT FLYING ON TOUR FLIGHT, NOTICED AN ENGINECHIP LIGHT ILLUMINATED.  PILOT IMMEDIATELY MADE PRECAUTIONARY LANDIN	G.  INSPECTED AIRCRAFT AND FOUND THAT ENGINE CHIP PLUG HAD A DEFECT.  CLEANED CHIP PLUGS AND C/W  OPERATIONAL CHECK AND 	 FUNCTIONALLY CHECKED GOOD.  AIRCRAFT RETURNED TO SERVICE.  (X)				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000062200134	20000622	00134	SW  	2000	6	22	20000510SH024    	1	20000113	G	2913	MS2467813C	SCREW           	ABEX        		BELL  	206   	206L3       	1182108	SW  										SCREW HEAD PORT	BROKEN          	b			XJ2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	41AZ		261  		AU1804433	51087				P/N MS24678-13C - SCREWS FOUND WITH HEAD BROKEN OFF, LOCKWIRE STILL ATTACHED TO SCREW HEAD DURING ACFT INSP ON HYD PUMP.	  HYD PUMP HAS 2 SCREWS OF THIS P/N WHICH RETAIN PORT CAP AND 2 SCREWS WITH DIFFERENT P/N.  THE 2 DIFFERENT P/N SCREWS W	ERE THE ONLY ONES RETAINING PORT CAP ON THE PUMP,  BOTH 2 EACH MS28678-13C HEADS FAILED.  2 FAILED SCREWS TESTED, SEVERE	 HYDROGEN EMBRITTLEMENT.  HYD PUMP O/H 6-23-99, INSTALLED 8-12-99, REMOVED 12-10-99, TSO 260.7 HRS.  2  FAILED SCREWS RE	PLACED  AT O/H WITH NEW, TRACEABLE BY LOT 000062775 MFG 99660-1.  ON SIDE OF SCREW HEAD, MFG IDENTIFIED WITH ''CBS''. HY	D PUMP WITH FAILED SCREWS REPLACED WITH NEW, RETURNED TO SERVICE.  FAILED SCREWS, LOT 000062775, CUSTOMERS TO BE NOTIFIE	1	G	7	1 	3U			 	H2SW    					 
2000062200135	20000622	00135	EU  	2000	6	22	20000510SH025    	1	20000510	G	8010	410CC01Y1	RELAY           			SNIAS 	350   	AS350B2     	8680813	EU  										MASTER ELEC BOX	WRONG PART      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204Y	464  				3101				AIRCRAFT STOPPED AT REMOTE LOCATION FOR FUEL.  UPON ATTEMPTING TO RE-START, WHEN  STARTER BUTTON PRESSED, THE IGNITERS P	OPPED, BUT THE STARTER/GENERATOR WAS DEAD.  DURING T/S, DISCOVERED THE K3 START RELAY WAS THE WRONG PART NUMBER.  IT IS 	SUPPOSED TO BE P/N 411CC01Y1. THE RELAY THAT WAS REMOVED, P/N 410CC1Y1, IS SUPPOSED TO BE USED IN THE K4 THRU K7 POSITIO	NS.  IN THE MASTER ELECTRICAL BOX  THERE IS 1 EACH 411CC01Y1 RELAY AND 4 EACH 410CC01Y1 RELAYS ALL LOCATED TOGETHER ON T	HE SAME BUSS BAR.  AT INITIAL INSTALL, SUSPECT INSTALLER INADVERTENTLY INSTALLED THEM ALL THE SAME. SUBMITTER RECOMMENDS	 CHECKING OTHER LIKE AIRCRAFT FOR THIS DISCREPANCY, IF NO MAINTENANCE HAS BEEN PREVIOUSLY PERFORMED IN THIS AREA.  (X)	1	G	7	1 	3U			 	H9EU    					 
2000080800001	20000808	00001	NM  	2000	8	8	20000510SH028    	1	20000330	G	2910	F2MA751505214A2	LINE            			AMD   	FALC50	FALCON2000  	2730170	NM  										RT PYLON	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	790L					15				RIGHT ENGINE NR 2 SYSTEM HYDRAULIC PRESSURE LINE BECAME UN-SWAGED AT OUTBOARD END CAUSING COMPLETE DRAINAGE OF NR 1 HYDR	AULIC SYSTEM. THIS OCCURRED IN-FLIGHT.  FURTHER INVESTIGATION REVEALED IMPROPER SWAGING.  TUBE WAS INSTALLED APPROXIMATE	LY 1 WEEK PRIOR TO INCIDENT.  (X)				2	K	7	3 	4F			RT	A50NM   					 
2000062300047	20000623	00047	SW  	2000	6	23	20000510SH030    	1	20000420	G	6300	406340102101	SEAL            			BELL  	407   	407         	       	SW  										M/R DRIVE	LEAKING         	B			GS1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	7ZB	159  				53329				SEAL LEAKING ON FREEWHEELING UNIT OUT, BETWEEN ENGINE AND TRANSMISSION.  REPLACED WITH NEW SEAL FROM BELL HELICOPTER.  (	X)					1	G	7	1 	3U			O	H2SW    					 
2000071100001	20000711	00001	EU  	2000	7	11	20000511SH001    	1	20000320	G	6720	350A33214501	PITCH LINK      			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			XSFA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	964SA	4858 				2931				TAIL ROTOR PITCH CHANGE ROD REMOVED DUE TO WEAR ON SPHERICAL BEARING IAW AD 98-4-35.  REMOVED 2 EACH.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000071200107	20000712	00107	EU  	2000	7	12	20000511SH004    	1	20000328	G	7603	704A34130052	CONTROL CABLE   			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL CONTROL	ROUGH           	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	963SA	3755 				2855				FUEL CONTROL CABLE ROUGH AND DIFFICULT TO MOVE. (X)						1	G	7	1 	3U			 	H9EU    					 
2000071100002	20000711	00002	EU  	2000	7	11	20000511SH005    	1	20000328	G	6230	EMRL8RSP3C	ROD END         			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	WORN            	A			XSFA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	963SA	3755 				2855				FORE AND AFT SERVO TOP ROD ENDS AND RIGHT LATERAL SERVO LOWER ROD END HAD WORN  BEARINGS.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000073100005	20000731	00005	CE  	2000	7	31	20000511SH006    	1	20000207	G	3211	671305210	TRUNNION        			CESSNA	750   	750         	2076810	CE  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	9090S	3234 				7500009				NOSE GEAR TRUNNION MOUNT PLATES CRACKED.  THIS IS THE THIRD OCCURRENCE OF THIS TYPE IN A FLEET OF APPROXIMATELY 25 AIRCR	AFT.  (X)					2	L	7	2 	4J			RT	T00007WI					 
2000073100006	20000731	00006	CE  	2000	7	31	20000511SH007    	1	20000207	G	3211	671305210	TRUNNION        			CESSNA	750   	750         	2076810	CE  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	926QS	2629 				7500026				NOSE GEAR TRUNNION MOUNT PLATES CRACKED OR MISSING FASTENERS.  SUBMITTER STATED THIS IS THE THIRD OCCURRENCE OF THIS TYP	E IN A FLEET OF APPROXIMATELY 25 AIRCRAFT.  (X)					2	L	7	2 	4J			RT	T00007WI					 
2000073100007	20000731	00007	CE  	2000	7	31	20000511SH008    	1	20000207	G	3211	671305210	TRUNNION        			CESSNA	750   	750         	2076810	CE  										NLG	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	947QS	1700 				7500047				LEFT NOSE LANDING GEAR TRUNNION LOOSE. THIS IS THE THIRD OCCURRENCE IN A FLEET OF APPROXIMATELY 25 AIRCRAFT.  (X)						2	L	7	2 	4J			RT	T00007WI					 
2000071100005	20000711	00005	SW  	2000	7	11	20000511SH013    	1	20000420	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL BOOM	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	10EW	674  				53262				BEARING ON TAIL ROTOR DRIVESHAFT ON TAILBOOM REJECTED.  REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER.  THESE WERE NOT	 INSTALLED ON THE OIL COOLER HANGARS.  AD 2000-02-12 IS NOT APPLICABLE DUE TO INSTALLED LOCATION.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000071100006	20000711	00006	SW  	2000	7	11	20000511SH014    	1	20000420	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL BOOM	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	10EW	674  				53262				BEARING ON TAIL ROTOR DRIVESHAFT ON TAILBOOM REJECTED.  REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER.  THESE WERE NOT	 INSTALLED ON THE OIL COOLER HANGERS.  AD 2000-02-12 IS NOT APPLICABLE DUE TO INSTALLED LOCATION.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000062600024	20000626	00024	EA  	2000	6	26	20000511SH015    	2	20000501	G	8550	LW13383	BAFFLE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					OIL SUMP	MISALIGNED      	B			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	117NJ	118  				4636138	RL1041561A			TWO EACH AN470AD RIVET HEADS FOUND IN OIL SUCTION SCREEN.  REMOVED SUMP, FOUND BAFFLE HAD 2 RIVETS WITH HEADS MISSING.  	FURTHER EXAMINATION SHOWED RIVET HOLES COUNTERSUNK ON THE HEAD SIDE. THIS BAFFLE WAS THE NEW STYLE WITH 5 EACH AN470-4-4	 AD RIVETS ON EACH BAFFLE PIECE, NOT THE OLDER 3 RIVETS AS PICTURED IN LYC SB 489A. (X)				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000062600025	20000626	00025	EA  	2000	6	26	20000511SH016    	2	20000501	G	8550	61298	GEAR            			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					TEETH	WORN            	B			BJ3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	15	117NJ	119  				4636138	RL10415612A			ON REMOVAL OF OIL PUMP, WEAR WAS NOTED ON ALUMINUM GEAR TEETH FACES.  IT LOOKED LIKE IMPROPER HARDENING.  WEAR ALSO ON T	EETH EDGES.  DATE CODE:  36/99.  (X)					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000071200256	20000712	00256	NE  	2000	7	12	20000511SH040    	1	20000424	G	6320	643520411102	PLANETARY GEAR  	SKRSKY      		SKRSKY	S64   	S64F        	       	NE  										MAIN GEARBOX	FRACTURED       	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	158AC		698  		A6161	64081				1ST STAGE PLANETARY PINION GEAR, PN 6435-20411-102, SN 1477, HAVING AN UNKNOWN TT, FAILED IN MAIN GEARBOX, PN 6435-20500	-048, SN A6-161.  INSP REVEALED TWO-THIRDS OF A 1ST STAGE PLANETARY PINION GEAR TOOTH FRACTURED CAUSING REPLACMENT OF TH	E FOLLOWING ITEMS DUE TO SECONDARY DAMAGE:  18 EACH 2ND STAGE PLANETARY PINION GEARS, PN 6435-20057-012, RING GEAR, PN 6	435-20165-012, 1ST STAGE SUN GEAR, PN 6435-20412-102, 2ND STAGE SUN GEAR, PN 6435-20414-101, AND 6 EACH 1ST STAGE PLANET	ARY PINION GEARS REPLACED.  (X)		2	G	7	2 	4U			 	H6EA    					 
2000062600027	20000626	00027		2000	6	26	20000512SH001    	4	20000303	G	6113	C6178	BULKHEAD        	MCAULY      		CESSNA	414   	414A        	2075907	CE  										LEFT PROPELLER	CRACKED         	B			VA1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	446W	500  			891776	414A0613				BULKHEAD REPLACED IN THE FIELD AND RETURNED FOR WARRANTY CLAIM.  BULKHEAD IS CRACKED FROM CENTER HOLE OUTWARD AT APPROXI	MATELY 45 DEGREES FOR 4  INCHES. CRACK STARTS .5 INCH TO THE SIDE OF  MOUNT HOLE FOR ATTACHMENT TO PROP HUB.  BULKHEAD I	S .075 INCH ALUMINUM, SINGLE LAYER SUPPORTING 18 INCHES DIAMETER SPINNER.  SUBMITTER SUSPECTS BULKHEAD NEEDS DOUBLER.  H	AVE SEEN CRACKS ON OTHER BULKHEADS INSTALLED ON CESSNA 414A MODIFIED PER STC SA7633SW.  (X)			1	L	7	2 	3O			 	A7CE    					 
2000062600028	20000626	00028	NE  	2000	6	26	20000512SH002    	3	20000310	G	6114	660714259	HUB             	ROTOL       												ROTOL	R390	R3904123F27 	NE  	REAR HALF INSERT	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		14655	7448 					DRG400690		PROPELLER RECEIVED FOR ROUTINE OVERHAUL.  DURING NDT INSPECTION, A CRACK WAS FOUND AT NR 1 MOUNTING INSERT IN HUB REAR H	ALF.  APPROXIMATELY 1.5 INCH LONG HUB ASSY REJECTED FROM FURTHER SERVICE.  (X)															6	C	P31NE	 
2000121500001	20001215	00001	CE  	2000	12	15	20000512SH019    	1	20000323	G	5751		NOSE RIB        	CESSNA      		CESSNA	206   	T206H       	       	CE  										BEND RELIEF HOLE	CRACKED         	B			LN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2371H	100  				T20608060				DURING ACFT''S FIRST 100-HR  INSP, A .25 INCH LONG CRACK WAS FOUND IN A NOSE RIB OF THE LT AILERON.  NOSE RIB IS AT THE 	AILERON''S CUT-OUT IN THE LEADING EDGE FOR THE INBD HINGE ATTACH POINT, ON THE OTBD SIDE.  THE CRACK IS AT THE UPPER FWD	 CORNER OF THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES.  THE CRACK IS AT THE UPPER FWD CORNER OF	 THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES.  THE CRACK IS BEST VIEWED THROUGH THE EXISTING .75	 INCH ACCESS HOLE IN AILERON''S BOTTOM SKIN.  INSP, REVEALED ANOTHER CRACK IN THE RT AILERON, SAME LOCATION:  INBD HINGE	 POINT, OTBD NOSE RIB.  BOTH AILERONS RETURNED TO CESSNA.  TWO NEW AILERONS WERE INSTALLED.  CAUSE OF CRACKS UNKNOWN.  (	1	H	7	1 	3O			 	A4CE    					 
2000121500002	20001215	00002	CE  	2000	12	15	20000512SH020    	1	20000323	G	5751		NOSE RIB        	CESSNA      		CESSNA	206   	T206H       	       	CE  										BEND RELIEF HOLE	CRACKED         	B			LN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2371H	100  				T20608060				DURING ACFT''S FIRST 100-HR  INSP, A .25 INCH LONG CRACK WAS FOUND IN A NOSE RIB OF THE LT AILERON.  NOSE RIB IS AT THE 	AILERON''S CUT-OUT IN THE LEADING EDGE FOR THE INBD HINGE ATTACH POINT, ON THE OTBD SIDE.  THE CRACK IS AT THE UPPER FWD	 CORNER OF THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES.  THE CRACK IS AT THE UPPER FWD CORNER OF	 THE NOSE RIB, AT A RELIEF RADIUS FOR THE BEND OF THE ATTACH FLANGES.  THE CRACK IS BEST VIEWED THROUGH THE EXISTING .75	 INCH ACCESS HOLE IN AILERON''S BOTTOM SKIN.  INSP, REVEALED ANOTHER CRACK IN THE RT AILERON, SAME LOCATION: INBD HINGE 	POINT, OTBD NOSE RIB.  BOTH AILERONS RETURNED TO CESSNA.  TWO NEW AILERONS WERE INSTALLED.  CAUSE OF CRACKS UNKNOWN.  (X	1	H	7	1 	3O			 	A4CE    					 
2000121500003	20001215	00003	SO  	2000	12	15	20000512SH021    	1	20000101	G	2721	D1	CONTROL CABLE   			MAULE 	M7    	M7235B      	5460109	SO  										NR 57	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	1002H	518  				23038C				BOTH RUDDER TRIM CABLES FRAYED AT RUDDER AS IT COMES OUT OF FLEX HOUSING.  (X)						1	H	7	1 	3O			NC	3A23    					 
2000121500004	20001215	00004	SO  	2000	12	15	20000512SH022    	1	20000414	G	2720	D7	CONTROL CABLE   			MAULE 	M7    	M7235B      	5460109	SO  										NR 29	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	1002H	518  				23038C				RIGHT RUDDER CABLE FRAYED AT PULLEY AT AFT END OF BAGGAGE COMPARTMENT.  (X)						1	H	7	1 	3O			NC	3A23    					 
2001012900148	20010129	00148	NE  	2001	1	29	20000512SH023    	2	20000413	G	7230	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					ENGINE	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FROM WESTFIELD GAGE CO., FOR FLUORESCENT PENETRANT INSPECTION IAW IAE V2500 PROPULSION SYS ENG MANUAL, REV	 42, SECTION 70-23-01, INSPECTION CHECK-01, TASK 70-23-01-230-501.  PART REJECTED AT F.P.I. DUE TO A CRACK ONE PLACE ON 	TOP SURFACE, 0.200 INCH LONG.  PARK SENT BACK TO WESTFIELD GAGE WITH REJECT TAG ATTACHED TO IT.  (X)									4	F			E311NE				 
2001011100926	20010111	00926	EU  	2001	1	11	20000515SH001    	1	20000301	G	6720	AC66375	HOUSING         	DUNLOP      		SNIAS 	350   	AS350B2     	8680813	EU  										SERVO ACTUATOR	UNDERSIZE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11					BX109					CRACK DETECTED ON LOWER END OF BODY AT PLUGGED PORT HOLE.  UNIT NOT ASSIGNED TO ANY AIRCRAFT, VENDOR SURPLUS/EXCHANGE UN	IT.  POSSIBLE CAUSE:  PLUG BORE UNDERSIZED TOO MUCH.  CRACK OCCURRING IN PLUGGED AREA.  RECURRENCE PREVENTION RECOMMENDA	TION:  WIDEN PLUG BORE.  (X)				1	G	7	1 	3U			 	H9EU    					 
2001012900149	20010129	00149	NE  	2001	1	29	20000515SH004    	3	20000412	G	6114	60714255	HUB             													ROTOL	R390	R3904123F27 	NE  	HUB ASSY	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		6856 						DAP01013		HUB ASSEMBLY RECEIVED FOR ROUTINE OVERHAUL.  DURING INSPECTION, A CRACK WAS FOUND AT NR 1 BLADE PORT IN INNER SEAL LIP A	T HUB SPLIT LINE (BOTH HUB HALVES).  HUB REJECTED FROM SERVICE. (X)															6	C	P31NE	 
2000051800067	20000518	00067	NE  	2000	5	18	20000515SH005    	3	20000417	G	6111	6607132886	BLADE           		PROPELLER   											ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		19014	5017 							BLADE RECEIVED FROM CUSTOMER WITH A CRACK AROUND BLADE ROOT OUTER SLEEVE.  BLADE REJECTED FROM FURTHER SERVICE.  (X)																6	C	P30NE	 
2000051600129	20000516	00129	SW  	2000	5	16	20000515SH006    	1	20000420	G	2435	230650001	BEARING         			GULSTM	690TP 	690         	0141720	SW  										STARTER/GEN	DESTROYED       	B			IC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										UNIT RECEIVED FROM DTA FOR EVALUATION.  INSP DETERMINED UNIT DESTROYED FROM FAILURE OF DRIVE END BEARING.  BEARINGS WERE	 OF LUCAS P/N.  SHAFT SHEARED, ARMATURE DESTROYED FROM DRAGGING ON FIELD POLE SHOES.  FIELD DRUG OUT, DRIVE END BELL DES	TROYED.  UNIT HAD OVERHAUL TAG FROM AMR-COMBS.  NO TT OF TIME SOH DETERMINED.  BEARING MFG THOUGHT TO BE 1997.  IMPOSSIB	LE TO DETERMINE BALANCE CONDITION OF ARMATURE.  RECOMMEND WORK ORDER INFO BE SOUGHT ON BALANCE RECORD OF ARMATURE AT O/H	.  SUBMITTER STATED BEARINGS DO NOT FAIL UNLESS OUT OF BALANCE CAUSES EXCESSIVE RADIAL LOAD TO BE IMPOSED.  		1	H	7	2 	3T			 	2A4     					 
2000051600130	20000516	00130	EA  	2000	5	16	20000515SH007    	2	20000515	G	7322	30800	FLOAT           	PRECISION   	HA6         						LYC   	O360  	O360F1A6    	41514	EA  					CARBURETOR	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09					75062805					100CC FUEL LEAKED INTO THE CHAMBER CLOSEST TO THE FULCRUM OF THE FLOAT ASSEMBLY DUE TO THE COMPROMISED INTEGRITY OF THE 	PLASTIC WELDED SEAM.  (X) 										3	O			E286				 
2000051600131	20000516	00131	EA  	2000	5	16	20000515SH008    	2	20000425	G	8530	LW14995	SPRING          								LYC   	O540  	O540*       	41532	EA  					PUSH ROD	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23		280  								PUSH ROD RETAINER SPRING, PN LW-14995, BROKEN.  PART INSTALLED FROM KIT MFG AFTER DATES LISTED IN LYC SB 519.  (X)											3	O			E295				 
2001012900150	20010129	00150	SO  	2001	1	29	20000515SH009    	2	20000420	G	8540	654720	GEAR            								CONT  	O360  	TSIO360EB   	17025	SO  					OIL PUMP	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										NEW OIL PUMP DRIVEN GEAR DOES NOT HAVE THE CHAMFER ON THE INSIDE OF THE TWO DRIVE SLOTS. THIS IS A MFG''S DEFECT. WHEN T	HE DRIVE IMPELLER NR 653814 IS INSTALLED, AND TACH NUT TORQUED, THE NR 654720 GEAR BOTTOMS ON THE 2 RADIUSES OF THE DRIV	E DOGS THAT ENGAGE THE SHOTS.  A .0015 INCH FEELER GAUGE CAN BE INSERTED UNDER THE GEAR SHAFT WHEN ASSEMBLED.  THIS CAUS	ES STRESS ON THE RADIUSES OF THE NR 653814 IMPELLERS AND CAN CAUSE A FAILURE OF THE OIL PUMP SYSTEM IF IT WEARS OR CRACK	S IN THAT AREA BECAUSE THE TACH NUT WILL LOOSE ITS TORQUE AND THE WHOLE OIL PUMP DRIVE SYSTEM WILL LOOSEN.  REF:  TCM SB	 96-4.  (X)						3	O			E9CE				 
2001012900018	20010129	00018	NE  	2001	1	29	20000515SH010    	2	20000515	G	7230	1B7306	BLADE           	PWA         							PWA   	2037  	PW2037      	 	NE  					COMPRESSOR SECT	FRACTURED       	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					B27203		P727203			DISASSEMBLY INSPECTION REVEALED ONE EACH 6TH STAGE COMPRESSOR BLADE PN IB7306 HAD FRACTURED AT THE BLADE ROOT.  THE FAIL	ED BLADE HAS BEEN FORWARDED TO PRATT & WHITNEY EAST HARTFORD CT (T.C. HOLDER) FOR INVESTIGATION.  (CUSTOMER:  TRANS WORL	D AIRLINES, TWAA).  (X)									4	F			E17NE				 
2001012900019	20010129	00019	CE  	2001	1	29	20000515SH011    	1	20000515	G	7921	SA625303	GASKET          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					OIL COOLER	DAMAGED         	D				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			WP	01	1197M	19   				18264241	269041R			DURING CRUISE, THE PILOT OBSERVED OIL COMING UP THE WINDSHIELD AND BOTH SIDE WINDOWS.  HE DECLARED AN EMERGENCY AND MADE	 A SAFE AIRPORT LANDING.  THE ENGINE HAD APPROXIMATELY 3 QUARTS OF OIL REMAINING.  THE OIL LEAK WAS CAUSED BY A SPLIT IN	 P/N 5A625303 GASKET BETWEEN THE CASE AND P/N 625016 OIL COOLER ADAPTER PLATE.  THE GASKET MATERIAL USED BY SUPERIOR AIR	 PARTS APPEARS TO BE TOO SOFT AS COMPARED TO THE OEM 625303 GASKET AND SHOULD BE REPLACED.  (X)			1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2000051600142	20000516	00142	CE  	2000	5	16	20000515SH013    	1	20000407	G	5320	085112132	BEAM            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CORRODED        	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	269PC	3679 				340A0785				ENGINE BEAM FOUND EXFOLIATED/CRACKED ON THE TOP OUTBOARD ANGLE, JUST FORWARD AND INBOARD OF THE TAILPIPE.  AD 2000-01-16	 PAR(D) HAD BEEN C/W 64 HOURS AND 10 WEEKS PREVIOUSLY.   (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2000051600224	20000516	00224	CE  	2000	5	16	20000515SH014    	1	20000414	G	5751	50210025	BRACKET         			CESSNA	340   	340A        	2076405	CE  										RT AILERON	SHEARED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	269PC					340A0785				FOUND 2 OF 6 RIVETS THAT HOLD THE OUTBOARD AILERON HINGE TO THE WING SPAR SHEARED OFF.  (X)						1	L	7	2 	3O			 	3A25    					 
2000051600146	20000516	00146	CE  	2000	5	16	20000515SH018    	1	20000515	G	3230	HMXL6FG	ROD END         	RAYTHN      		BEECH 	33    	35C33A      	1151410	CE  										AUTO RETRACT	BROKEN          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25		7694 				CE71				FROM THE PILOT IN COMMAND.  UPON RETURNING TO AKR FOR LANDING, WHEN THE LANDING GEAR WAS EXTENDED, HEARD A LOUD BANG AND	 FELT A SENSATION IN THE FLOORBOARDS.  SUBSEQUENTLY, THERE WAS NO NOSE GEAR EXTENDED INDICATION.  AIRCRAFT RECEIVED MINO	R DAMAGE UPON LANDING WHEN THE NOSE GEAR COLLAPSED.  MAINTENANCE FOUND THE ROD END OF THE NOSE GEAR RETRACT ROD AT THE A	CTUATOR ARM BROKEN  IN THE THREADED AREA OF THE TORN RUT.  (X)			1	L	7	1 	3O			 	3A15    					 
2000051600147	20000516	00147	SO  	2000	5	16	20000515SH019    	1	20000405	G	7603	487925	SWITCH          			PIPER 	PA44  	PA44180     	7104402	SO  										THROTTLE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	3048R	6562 				447995242				THE LOW POWER GEAR UP WARNING SWITCH ON THE THROTTLE QUADRANT WAS FOUND BROKEN INTERNALLY.  WHEN THE THROTTLES  WERE ADV	ANCED THE SWITCH WOULD OPEN AND SHORT TO GROUND CAUSING THE LANDING GEAR CONTROL CIRCUIT BREAKER TO OPEN.  WHEN THE THRO	TTLES WERE PULLED BACK TO THE STOP, THE SWITCH WOULD CLOSE AND THE LANDING GEAR SYSTEM WOULD FUNCTION NORMALLY.  SUBMITT	ER STATED THE AGE OF THE SWITCH, NUMBER OF CYCLES, IS POSSIBLY THE CAUSE OF FAILURE.   (X)			1	L	7	2 	3O			 	A19S0   					 
2000051600148	20000516	00148	EA  	2000	5	16	20000515SH020    	2	20000320	G	7322	A105219	FLOAT           		HA6         	AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					CARBURETOR	DAMAGED         	B			HO1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	4553C		225  			AA5B1202	12504236A			ENGINE WOULD NOT RUN UNLESS MIXTURE WAS LEANED ALMOST TO IDLE CUT OFF.  IT WAS  VERY RICH AND WOULD NOT RUN ABOVE 1,500 	RPM.  FOUND PLASTIC FLOAT TO BE FILLED WITH AVGAS TWO OF THREE CHAMBERS.  FLOAT, P/N 30-800, CARBURETOR ASSY DATE, 9-97.	  (X)				1	L	7	1 	3O	3	O	 	A16EA   	E286				 
2000051600035	20000516	00035	SO  	2000	5	16	20000515SH021    	1	20000310	G	3250	63300008	HORN            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					NLG STEERING	BROKEN          	C				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	7615F	5644 				287725090	L4656327A			WHILE LANDING, EXPERIENCED EXTREME SHIMMY IN NOSE GEAR.  NOSE GEAR STEERING HORN, PN 63300-008, FOUND BROKEN AT WELD.  P	ART TT:  5,633.43 HRS.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000051600149	20000516	00149	SO  	2000	5	16	20000515SH022    	1	20000308	G	2731		CONTROL CABLE   			PIPER 	PA34  	PA34200T    	7103406	SO  										ELEVATOR TRIM	BROKEN          	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	7333L	700  				347670099				CABLE BROKE UPON REMOVAL OF ELEVATOR FOR REPAIR.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000051600150	20000516	00150	CE  	2000	5	16	20000515SH023    	1	20000423	G	5753		FLAP TRACK      			CESSNA	182   	R182        	2072734	CE  										RT TE FLAP	SEPARATED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	736WX	5325 				R18200783				FOUND RT INBD FLAP TRACK SEPARATED FROM FWD MOUNT POINT DUE TO SHEARED RIVET.  RIVET MAY HAVE BECOME WORK HARDENED.  LT 	INBD FLAP TRACK ALSO FOUND LOOSE AT SAME LOCATION.  THIS COULD POSSIBLY APPLY TO ALL CESSNA 182''S.  THERE WERE NO OCCUR	RENCES OF FLAP OVERSPEEDING THAT ARE KNOWN.  THIS COULD BE THE RESULT OF NORMAL WEAR AND TEAR UNDER NORMAL OPERATIONS.  	SUBMITTER SUGGESTED ADDING A CHECK FOR FLAP TRACK SECURITY ON PRE-FLIGHT FOR CESSNA 182''S.  (X)			1	H	7	1 	3O			RT	3A13    					 
2000051600151	20000516	00151	SO  	2000	5	16	20000515SH024    	1	20000218	G	5711		SPAR            			PIPER 	PA30  	PA39        	7103902	SO  										RT WING	CRACKED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	13	8898Y	3376 				3933				PILOT REPORTED VIBRATION FELT IN THE ACFT AND RT WING TIP TANK TRAILING END COULD BE SEEN ''FLUTTERING'' APPROX 1 INCH I	N-FLIGHT.  INSP FOUND A CRACK EXTENDING THROUGH THE LOWER SPAR CAP AND UP APPROX 1 INCH INTO FACE OF THE AFT WING SPAR A	T STA 132.  SEVERAL SOLID RIVETS ATTACHING UPPER WING SKIN TO THE AFT SPAR AND SOLID RIVETS ATTACHING THE UPPER WING SKI	N TO AFT SPAR AND RIB AROUND STA 132 HAD BEEN REPLACED BY ''CHERRY TYPE'' RIVETS AT ONE TIME INDICATING THERE MAY HAVE B	EEN PROBLEMS IN THAT AREA BEFORE.  ALSO, RT MAIN GEAR REPLACED AND AFT TAIL BULKHEAD REPAIRED DUE TO A HARD LANDING 10-9	8.  REPAIRS TO DAMAGED WING SPAR WERE MADE USING DER APPROVED DATA.  	1	L	7	2 	3O			 	A1EA    					 
2000051600152	20000516	00152		2000	5	16	20000515SH025    	4	20000426	G	2562	ELT1104	ELT             			PIPER 	PA32  	PA32301T    	7103209	SO  										TAIL	DAMAGED         	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	15	9288X	475  				3257027				REMOVED ELT UNIT FOR FAR 91-207 CHECK.  ACTIVATED.  WOULD NOT TURN OFF.  REMOVED BATTERY, VERY WET.  CHECKED TRANSMITTER	, WET.  SENT TO FACTORY FOR OVERHAUL.  (X)					1	L	7	1 	3O			 	A3SO    					 
2001012900020	20010129	00020	WP  	2001	1	29	20000515SH026    	2	20000426	G	7230	30752272	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					FIRTREE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED WITH DAMAGE IN POST FIRTREE AREA AND NUMEROUS  MANUFACTURING FLAWS IN POST FIRTREE AREA.  RE:  LOT NR 	00P102.  (X)										4	F			E6WE				 
2001012900021	20010129	00021	WP  	2001	1	29	20000515SH027    	2	20000515	G	7230	30752272	WEB             								GARRTT	TFE731	TFE731*     	01518	WP  					HPT DISK	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED WITH A SCRATCH IN THE WEB AREA ON THE AFT SIDE.  RE:  LOT NR 00P098.   (X)											4	F			E6WE				 
2001012900022	20010129	00022	WP  	2001	1	29	20000515SH028    	2	20000503	G	7230	31014051	BEARING         								GARRTT	TPE331	TPE3316     	01514	WP  					GEARBOX	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	19		6118 	15   		P20246		P20246			COMPRESSOR BEARING FAILED 14.7 HOURS AFTER OVERHAUL CAUSING MAJOR FAILURE DAMAGE TO ENGINE.   (X)											4	T			E4WE				 
2001012900023	20010129	00023	WP  	2001	1	29	20000515SH029    	1	20000427	G	3242	1542522	BRAKE ASSY      			DOUG  	DC8   	DC8*        	       	WP  										MLG	OVERHEATED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										TEAR DOWN INSPECTION SHOWS ASSY B.E.R., NO SALVAGEABLE PARTS.  OVERHEATED BRAKES.   (X)						2	L	7	4 	4J			F	4A25    					 
2001012900024	20010129	00024	WP  	2001	1	29	20000515SH030    	1	20000427	G	3242	1542522	BRAKE ASSY      			DOUG  	DC8   	DC8*        	       	WP  										MLG	OVERHEATED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										TEAR DOWN INSPECTION SHOWS ASSY B.E.R.  NO SALVAGEABLE PARTS.  OVERHEATED BRAKES.   (X)						2	L	7	4 	4J			F	4A25    					 
2001012900025	20010129	00025	WP  	2001	1	29	20000515SH031    	1	20000427	G	3242	1542522	BRAKE ASSY      			DOUG  	DC8   	DC8*        	       	WP  										MLG	OVERHEATED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										TEAR DOWN INSPECTION SHOWS ASSY B.E.R.  NO SALVAGEABLE PARTS.  OVERHEATED BRAKE.  (X)						2	L	7	4 	4J			F	4A25    					 
2001012900026	20010129	00026	WP  	2001	1	29	20000515SH032    	1	20000503	G	3246	152059	WHEEL           	BENDIX      		DOUG  	DC8   	DC8*        	       	WP  										MLG	UNSERVICEABLE   	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					B7153					****NO TEXT****  ***I''''M DOING TEXT****INBOARD HALF OF MAIN WHEEL ASSY AT SPOKE AREA UNSERVICEABLE.  OUTBOARD HALF OF 	MAIN WHEEL ASSY, SN B6029.   (X)					2	L	7	4 	4J			F	4A25    					 
2000080300003	20000803	00003	EU  	2000	8	3	20000515SH033    	1	20000424	G	5350	355A5805420414	COWLING         			AEROSP	AS355 	AS355F2     	8680812	EU  										MAIN GEARBOX	DEPARTED        	C			N38A	K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			EA	05	596SJ	3381 				5135				RIGHT HAND MAIN GEARBOX COWLING CAME OFF OF AIRCRAFT DURING FLIGHT.  NO DAMAGE TO AIRCRAFT OTHER THAN MGB COWL ITSELF.  	NO PERSONAL OR PROPERY DAMAGE OCCURRED.     (X)					1	G	7	2 	3U			 	H11EU   					 
2000051600306	20000516	00306	SW  	2000	5	16	20000516SH001    	1	20000421	G	5751	2250000364	CHANNEL         			GULSTM	690TP 	690B        	7630516	SW  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	81703	4616 				11438				AFTER REMOVAL OF BOTH RT AND LT AILERON INBOARD HINGE ASSEMBLIES, FOUND BOTH AILERON ''U'' CHANNELS HAD CRACKS IN THE WE	B AROUND THE LOWER HINGE ATTACH BOLTS.  SUBMITTER RECOMMENDED INSTALLING A REINFORCING PLATE ON AFT SIDE OF WEB IAW AC 4	3.131B PAR 4-58, 4-59.  (X)				1	H	7	2 	3T			 	2A4     					 
2000051600307	20000516	00307	SW  	2000	5	16	20000516SH002    	1	20000421	G	5751	250000373	CHANNEL         			GULSTM	690TP 	690B        	7630516	SW  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	81703	4616 				11438				AFTER REMOVAL OF BOTH RT AND LT AILERON INBOARD HINGE ASSEMBLIES, FOUND BOTH AILERON ''U'' CHANNELS HAD CRACKS IN THE WE	B AROUND THE LOWER HINGE ATTACH BOLTS.  SUBMITTER RECOMMENDED INSTALLING A REINFORCING PLATE ON AFT SIDE OF WEB IAW AC 4	3.131B PAR 4-58, 4-59.  (X)				1	H	7	2 	3T			 	2A4     					 
2000102500001	20001025	00001	EA  	2000	10	25	20000516SH003    	2	20000302	G	8530	05K21123	PLUG            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235H2C     	41505	EA  					CYL INSIDE WALLS	MAKING METAL    	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	95512					15285911	RL897015			WHILE PERFORMING ANNUAL INSP, ALUMINUM SHAVINGS FOUND IN OIL FILTER.  FILTER WAS SENT TO LYC FOR  ANALYSIS AND DETERMINE	D TO BE PISTON PIN PLUG MATERIALS.  UPON REMOVAL OF ALL 4 CYL, SEVERE PITTING FOUND AT BOTTOM OF EACH CYL WHICH AT POINT	 WHERE PISTON REACHES ITS LOWEST TRAVEL.  ALL 4 CYL REJECTED AND FACTORY NEW INSTALLED.  FACTORY STATES THIS IS A RESULT	 OF ENG NOT REACHING PROPER OPERATING TEMP.  ACFT IS OPERTED IN PHOENIX, AZ, OIL TEMP GAUGE IS ACCURATE.  ACFT HAS HISTO	RY AS DO ALL ACFT IN PHX OF RUNNING ABOVE  180 DEGREES WHICH IS THE PROPER (MIN) OIL TEMP FOR OPERATION.   (X)		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000102500002	20001025	00002	EA  	2000	10	25	20000516SH004    	2	20000302	G	8530	05K21123	PISTON          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					CYLINDER WALLS	MAKING METAL    	C			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	757NZ					15279885	L2507515			WHILE PERFORMING ANNUAL INSP, SMALL ALUMINUM PARTICLES FOUND IN OIL FILTER. BORESCOPE INSP REVEALED WEAR ON CYL WALLS AN	D PITTING AT BASE OF EACH CYL (INSIDE) AT THE POINT OF THE PISTONS FARTHEST TRAVEL DOWNWARD.  TWO OF THE CYL WERE FACTOR	Y NEW WITH 618 HRS SINCE NEW.  THE OTHER TWO REPAIRED 1,176.76 HRS AGO AT FACTORY'S REQUEST BY FACTORY APPOINTED REPAIR 	FACILITY UNDER WARRANTY.  THIS IS 3RD OCCURRENCE OF THIS PROBLEM IN 1,859.5 HRS SMOH BY LYC.  1ST OCCURRENCE RESULTED IN	 ALL OF THE ABOVE AND BELOW ACCEPTABLE COMPRESSIONS ON ALL 4 CYL. FACTORY STATED ENGINE IS RUNNING TOO COLD IN PHX, AZ. 	 (X)	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000102500003	20001025	00003	EA  	2000	10	25	20000516SH005    	2	20000322	G	8530	LW11633	CYLINDER        	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER WALLS	MAKING METAL    	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69186	460  				15282536	L2389615			DURING 100-HR INSP, ALUMINIM SHAVING FOUND IN OIL FILTER.  (THIS IS THE 4TH TIME THIS SHOP HAS HAD THIS PROBLEM IN LAST 	18-24 MOS).  ALUM IS FROM PISTON PIN PLUGS RUBBING AGAINST LOWER PART OF  CYL WHICH, AFTER 4-500 HRS, DEVELOPS SEVERE PI	TTING THEN CREATES A WEAR STEP IN CYL WALLS.  ONE ENG LOST COMPRESSION IN ALL 4 CYL BELOW ACCCEPTABLE LIMITS.  SUBMITTER	 STATED MECH SHOULD BORESCOPE ALL O-235-L2C ENGINES AT EACH 50-HR AND ORDER REPLACEMENT CYL AT FIRST SIGNS OF PITTING AT	 LOWEST POINT OF CYL WALL WITH THE PISTON AT B.O.C.  CYL NEED TO BE REPLACED AT FIRST SIGN OF METAL CONTAMINATION, WHICH	 WILL OCCUR VERY RAPIDLY.  ONE 50-HR THERE WILL BE NO  METAL, THE NEXT THERE WILL BE SIGNIFICANT CONTAMINATION.   (X)	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000102500004	20001025	00004	NM  	2000	10	25	20000516SH006    	1	20000427	G	5551		BRACKET         			UNIVAR	108   	108         	9230402	NM  										HORIZ STABILIZER	CRACKED         	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	97142					108142				DURING ANNUAL INSPECTION, FOUND RT FORWARD HORIZONTAL STABILIZER ATTACH BRACKET CRACKED.  CRACK APPROXIMATELY .3750 INCH	 LONG.  CRACK EXTENDED THROUGH UPPER ATTACH POINT BOLT HOLE.  (X)					1	H	7	1 	3O			 	A767    					 
2000102500005	20001025	00005	CE  	2000	10	25	20000516SH009    	1	20000428	G	6120		WIRE            			BEECH 	90    	F90         	1152909	CE  										WS 39.7 WING CTR	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	152WE	5025 				LA152				SEVERAL WIRES IN A WIRE BUNDLE WERE  FOUND CHAFED THROUGH TO GROUND ON A LEADING EDGE RIB.  WIRES GOING TO INTERMITTENT 	GROUND INCLUDE RT AUTOFEATHER WIRE, ELECTRIC HEAT WIRE, BATTERY CHARGE SHUNT-TO-MODULE WIRES.  BUNDLE WAS INSULATED AND 	SECURED AWAY FROM RIB AFTER REPAIR OF WIRING.  FOUND DURING MFG'S PHASE-4 INSPECTION.    (X)				1	L	7	2 	4T			 	A31CE   					 
2001020500042	20010205	00042	SW  	2001	2	5	20000516SH010    	1	20000501	G	3220	041200002L	BUCKLE          			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	O360A1A     	41514	EA  					NLG	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7191V					221189	1333451A			NOSE GEAR BUCKLE OFF AT UPPER TRUSS.  POSSIBLY WEAKENED BY OVERTURNING WITH TOW TRACTOR.  SUBMITTER SUGGESTED HEAVIER ME	TAL, BETTER SUPERVISION AND TRAINING.  (X)					1	L	7	1 	3O	3	O	 	2A3     	E286				 
2000122000001	20001220	00001	EA  	2000	12	20	20000516SH011    	2	20000419	G	8530	74230	GUIDE           			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					NR5, 1,6 & 4 CYL	FAILED          	B			WXHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	7267H	351  				18280591	L2695148A			EXHAUST VALVE STUCK, BENDING PUSH ROD AND HOUSING.  SEE LYC SI  1425H, 1485.  SB388B.  FOUND 3 OTHER CYLINDERS WITH STUC	K VALVES.  SUBMITTER SUGGESTED AD BE ISSUED.  (X)					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2000051600353	20000516	00353	CE  	2000	5	16	20000516SH013    	1	20000428	G	3210	MC815AS1	RELAY           			BEECH 	200   	200BEECH    	1152920	CE  										MLG	INOPERATIVE     	B			CTUA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	21	553R		2082 			BB589				PILOT SELECTED GEAR DOWN, NO RESPONSE.  PERFORMED MANUAL GEAR EXTENSION AND LANDED AIRCRAFT.  TROUBLESHOT GEAR DOWN CIRC	UIT, FOUND ATTACHING SCREENS  FOR GEAR DOWN RELAY IN LANDING.  GEAR CONTROL BOX HAD COME LOOSE.  RE-SECURED RELAY AND PE	RFORMED GEAR RETRACTION, CHECK OK.  GEAR MOTOR CONTROL BOX WAS REPLACED 12-7-93, ACFT TT:  6,446.4 HRS WITH OVERHAULED U	NIT.   (X)			1	L	7	2 	4T			 	A24CE   					 
2001020500043	20010205	00043	SO  	2001	2	5	20000516SH015    	2	20000427	G	8520	6461401	STUD            			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	730P		894  			21062910	512874			BOTH FORWARD AND AFT STUDS BROKEN HALF WAY OUT THROUGH .4375 INCH - 20 INCH THREADS.  (X)						1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000121500007	20001215	00007	EA  	2000	12	15	20000516SH016    	2	20000420	G	7414	10163048	BUSHING         	BENDIX      							LYC   	O360  	O360A1G     	41514	EA  					DRIVE END	OVERSIZED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					9125334					A MAGNETO NEWLY OVERHAULED, WOULD NOT SEAT ON THE ENGINE.  FOUND THE BUSHING WHICH CAME INSTALLED ON THE MAGNETO WAS TOO	 LARGE IN DIAMETER TO CENTER THE BORE OF THE DRIVE GEAR.  COMPARED TO ANOTHER BUSHING .827 INCH, IT WAS .829 INCH.  THE 	LYC TABLE OF LIMITS SPECIFIES .0015 INCH - .0035 INCH LOOSE FIT.  SUBMITTER STATED USE OF THESE BUSHINGS AND THE RESULTI	NG IMPROPER FIT COULD RESULT IN MAGNETO MALFUNCTION.  (X)								3	O			E286				 
2000080300004	20000803	00004	SW  	2000	8	3	20000516SH022    	1	20000131	G	6320	406040021101	BEVEL GEAR      	BELL        		BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CRACKED         	B			GJQR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	01	404W	3185 			A199	52055				TRANSMISSION LOWER CHIP LIGHT  ILLUMINATED IN-FLIGHT.  AFTER LANDING, INSPECTION FOUND FAIRLY LARGE FERROUS CHIP THAT AP	PEARED LIKE PIECE OF GEAR TOOTH.  TEAR-DOWN INSPECTION REVEALED INPUT SPIRAL BEVEL GEAR CRACKED 360 DEGREES THROUGH THE 	RING.  THE CRACK PATH TRAVELED THROUGH A BOLT HOLE.  RING GEAR REPLACEMENT IN PROGRESS AND CRACKED RING GEAR SENT TO BEL	L HELICOPTER PRODUCT SUPPORT ENG FOR EVALUATION AND ANALYSIS.  (X)			1	G	7	1 	3U			NC	H2SW    					 
2001013000001	20010130	00001	SO  	2001	1	30	20000516SH029    	1	20000413	G	5730	6531904	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										LT AND RT WING	CORRODED        	B			AHRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		9258 								CRACKS WERE FOUND USING DYE PENETRANT METHOD, ALL OF THE ABOVE AIRCRAFT WERE DURING ROUTINE MAINTENANCE TO REPAIR FUEL L	EAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED EXTREME CASE OF EXFOLIATION CORROSION THAT 	CAUSED A HOLE THROUGH UPPER WING SKIN.  AFTER FINDING CORROSION ON LEFT SIDE, DECIDED TO PULL OFF RIGHT OVERWING FAIRING	 AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE.  POSSIBLE CAUSES ARE MOISTURE UNDER OVERWING FAI	RINGS.  RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRING AREA.  (X)		1	L	7	1 	3O			 	2A13    					 
2001013000002	20010130	00002	SO  	2001	1	30	20000516SH030    	1	20000413	G	5730	6531904	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										LT AND RT WING	CORRODED        	B			AHRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		9351 								DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED 	EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN.  AFTER FINDING CORROSION ON LEFT SIDE,	 DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE.  POSS	IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS.  RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN	G AREA.  (X)		1	L	7	1 	3O			 	2A13    					 
2001020500152	20010205	00152	SO  	2001	2	5	20000516SH031    	1	20000413	G	5730		SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										LT AND RT  WING	CORRODED        	B			AHRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		6327 								DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED 	EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN.  AFTER FINDING CORROSION ON LEFT SIDE,	 DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE.  POSS	IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS.  RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN	G AREA.  (X)		1	L	7	1 	3O			 	2A13    					 
2001020500153	20010205	00153	SO  	2001	2	5	20000516SH032    	1	20000413	G	5730		SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  										LT AND RT WING	CORRODED        	B			AHRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		6522 								DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED 	EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN.  AFTER FINDING CORROSION ON LEFT SIDE,	 DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE.  POSS	IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS.  RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN	G AREA.  (X)		1	L	7	1 	3O			 	2A13    					 
2001020500046	20010205	00046	SO  	2001	2	5	20000516SH033    	1	20000413	G	5730		SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  										LT AND RT WING	CORRODED        	B			AHRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		6613 								DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED 	EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN.  AFTER FINDING CORROSION ON LEFT SIDE,	 DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE.  POSS	IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS.  RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN	G AREA.  (X)		1	L	7	1 	3O			 	2A13    					 
2001020500047	20010205	00047	SO  	2001	2	5	20000516SH034    	1	20000413	G	5730		SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  										LT AND RT WING	CORRODED        	B			AHRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		8724 								DURING ROUTINE MAINTENANCE TO REPAIR FUEL LEAK FROM OVERWING FAIRING ASSY, REMOVED LEFT OVERWING FAIRING AND DISCOVERED 	EXTREME CASE OF EXFOLIATION CORROSION THAT CAUSED A HOLE THROUGH UPPER WING SKIN.  AFTER FINDING CORROSION ON LEFT SIDE,	 DECIDED TO PULL OFF RIGHT OVERWING FAIRING AND DISCOVERED MORE PITTING CORROSION, BUT NOT AS SEVERE AS LEFT SIDE.  POSS	IBLE CAUSES ARE MOISTURE UNDER OVERWING FAIRINGS.  RECOMMEND CONSCIENTIOUSLY PERFORMED INSPECTION OF THE OVERWING FAIRIN	G AREA.  (X)		1	L	7	1 	3O			 	2A13    					 
2000062900037	20000629	00037	NE  	2000	6	29	20000517SH003    	2	20000428	G	7230	2A0003	BEARING         	IAE         							IAE   	V2500 	V2500A1     	 	NE  					NR 4 OUTER RACE	SPALLED         	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		2703 					V0106			ENGINE REMOVED FOR ''''PERFORMANCE DETERIORATION''''.  THE NR 4 BEARING EXHIBITED AXIAL SCORING OF THE ROLLERS AND OUTER	 RACE.  MINOR FATIGUE SPALLING WAS PRESENT AT THE DAMAGE SITES ON BOTH THE RACE AND ROLLERS.  INVESTIGATION IS IN PROGRE	SS AT GE ENGINE SERVICES - DALLAS.  (X)									4	F			E311NE				 
2000062900038	20000629	00038	NE  	2000	6	29	20000517SH004    	2	20000428	G	7230	2A0003	BEARING         	IAE         							IAE   	V2500 	V2500A1     	 	NE  					NR 4 OUTER RACE	MAKING METAL    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05		4369 					V0340			ENGINE WAS REMOVED FOR ''''''''METAL IN NR 4 MCD''''''''.  THE NR 4 BEARING EXHIBITED A REGION OF FATIGUE BREAK-UP ON TH	E OUTER RACE.  INVESTIGATION IS IN PROGRESS AT GE ENGINE SERVICES - DALLAS.  (X)										4	F			E311NE				 
2000070600128	20000706	00128	CE  	2000	7	6	20000517SH009    	1	20000424	G	2740	505244631	SPRING          			BEECH 	99    	C99         	1154006	CE  										ATTACH POINT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	239AL	15731				U239				SPRINGS TO HORIZONTAL STABILIZER WORN AT BOTH ENDS WHERE THE SPRINGS ATTACH TO THE STRAPS.  (X)						1	L	7	2 	3T			 	A14CE   					 
2000062900039	20000629	00039	CE  	2000	6	29	20000517SH010    	1	20000424	G	2740	99524118	STRAP           			BEECH 	99    	C99         	1154006	CE  										ATTACH POINT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	239AL	15731				U239				STRAPS WORN WHERE THEY ATTACH TO THE HORIZONTAL SPRINGS.  (X)						1	L	7	2 	3T			 	A14CE   					 
2000062900040	20000629	00040	CE  	2000	6	29	20000517SH011    	1	20000424	G	2740	995240501	STRAP           			BEECH 	99    	C99         	1154006	CE  										ATTACH POINT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	239AL	15731				U239				STRAPS WORN WHERE THEY ATTACH TO HORIZONTAL STABILIZER SPRINGS.  (X)						1	L	7	2 	3T			 	A14CE   					 
2000062900041	20000629	00041	CE  	2000	6	29	20000517SH013    	1	20000505	G	5712	57222061	CANOPY          			CESSNA	441   	441         	2076020	CE  											CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	555GD	4170 				4410094				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 LINE 1 INCH LONG. STOP DRILLED PER CESSNA INSTRUCTIONS.  (X)					1	L	7	2 	3T			RT	A28CE   					 
2000062900042	20000629	00042	EA  	2000	6	29	20000517SH017    	2	20000425	G	7414		BUSHING         	SLICK       		BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					DISTRIBUTOR BOX	WORN            	D			FYOA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	999SA	45   			97121325	897	L1966540A			PILOT REPORTED LEFT ENGINE WAS HARD TO START.  REMOVED LEFT MAGNETO INSPECTION AND NOTED ''POINT'' MARKS USED FOR FACTOR	Y SEALING STILL IN PLACE INDICATING MAGNETO INTERNAL INSPECTION REVEALED OILITE BUSHING IN DISTRIBUTOR BLOCK EXCESSIVELY	 WORN PRODUCING A METALLIC DUST COVERING INTERNAL COMPONENTS OF MAGNETO.  BUSHING WAS .023 INCH LARGER THAN SHAFT OF ROT	OR GEAR AND APPEARED TO HAVE NOT BEEN PROPERLY OILED AT FACTORY.  (X)			1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2000062900043	20000629	00043		2000	6	29	20000517SH018    	4	20000424	G	6122	B3124	SHAFT           	HARTZL      		PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	IO540A1A5   	41532	EA  						FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	9051P		1532 		665U	244516				RELEVANT INDICATION ON CONTROL SHAFT AT THE SPEED ADJUSTMENT SHAFT.  (X)						1	L	7	1 	3O	3	O	 	1A15    	1E4				 
2000062900044	20000629	00044		2000	6	29	20000517SH019    	4	20000424	G	6122	A20107	GEAR            	MCAULY      		CESSNA	180   	180         	2072602	CE  											CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					94003					RELEVANT INDICATION IN TEETH AREA OF IDLER GEAR.  (X)						1	H	7	1 	3O			NC	5A6     					 
2000062900045	20000629	00045		2000	6	29	20000517SH020    	4	20000424	G	6122	A20609	LEVER           	MCAULY      		CESSNA	180   	180         	2072602	CE  											FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					94003					RELEVANT INDICATION AT CLAMP RETENTION AREA OF CONTROL LEVER.  (X)						1	H	7	1 	3O			NC	5A6     					 
2000062900046	20000629	00046		2000	6	29	20000517SH021    	4	20000425	G	6122	B3124	SHAFT           	HARTZL      																	FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1696U					RELEVANT INDICATION ON RETENTION AREA OF CONTROL SHAFT.  (X)																			 
2000062900047	20000629	00047	GL  	2000	6	29	20000517SH022    	3	20000501	G	6114	920012	HUB             			CESSNA	206   	U206C       	2073332	CE  						MCAULY	3A32C	D3A32C90    	GL  		CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	29150		88   			U2061120		920012		CRACK STARTING FROM O-RING GROOVE EXTENDING ACROSS FLANGE AREA.  (X)						1	H	7	1 	3O			 	A4CE    		5	C	P21EA	 
2000062900048	20000629	00048		2000	6	29	20000517SH023    	4	20000412	G	6122	210316	FLYWEIGHT       	WOODWARD    																	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1296292K					RELEVANT INDICATION ON FLYWEIGHT BASE.  (X)																			 
2000070600135	20000706	00135	EA  	2000	7	6	20000517SH024    	2	20000320	G	7322	30800	FLOAT           	PRECISION   		AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  						DAMAGED         	B			HO1R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	21	4553C		225  		DL41123	AA5B1202	12504236A			ENGINE WOULD NOT RUN UNLESS MIXTURE WAS LEANED ALMOST TO IDLE CUT-OFF, IT WAS VERY RICH AND WOULD NOT RUN ABOVE 1,500 RP	M.  FOUND PLASTIC FLOAT FILLED 100 II AVGAS TWO OF THREE CHAMBERS, FLOAT PN 30-800 CARBURETOR ASSY, DATE 9-97.  (X)					1	L	7	1 	3O	3	O	 	A16EA   	E286				 
2000062900049	20000629	00049	CE  	2000	6	29	20000517SH025    	1	20000502	G	7920	MILH60003Q98	HOSE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					OIL BREATHER LIN	BLOCKED         	D				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			GL	17	64448					17265235	L4200827A			DURING ANNUAL INSP, ORIG OIL BREATHER LINE FOUND WEATHER CHECKED AND DETERMINED UNAIRWORTHY.  NEW LINE WAS CUT OFF OF BU	LK LENGTH STOCK AND REPLACED ORIG LINE IAW STD PRACTICES, AFTER LINE REPLACED, ACFT TEST RUN, ENG RUN-UP ON GROUND AT TA	KEOFF POWER, CRUISE POWER, AND POST-MAINT CHK IAW CESSNA MM, CESSNA 172M.  PILOTS OPER HANDBOOK WITH NO DISCREPANCIES OR	 OIL LEAKS NOTED,  ACFT RELEASED FROM MAINT.  FIVE MINUTES AFTER TAKEOFF, PILOT NOTED OIL SMOKE ENTERING COCKPIT, DECLAR	ED EMERG, RETURNED TO AIRPORT.  DURING RETURN, FRONT CRANKSHAFT SEAL BLEW OUT CAUSING LOSS OF OIL PRESS, DUMPING OIL OUT	 OF FRONT SEAL.  ACFT  LANDED SAFELY.  INSP FND NEW BREATHER LINE BLOCKED.  PLASTIC CAP SHOVED 4 INCHES UP INSIDE  HOSE.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000081400001	20000814	00001	SW  	2000	8	14	20000518SH002    	1	20000417	G	6510	407340340101	DISC PACK       	BELL        		BELL  	407   	407         	       	SW  										T/R DRIVE	CRACKED         	A			ALGA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	627AL	813  			A1178	53284				DURING 25-HOUR AD INSPECTION, FOUND NR 5 COUPLING CRACKED THROUGH ONE LAMINATE ON AFT FACING SIDE OF COUPLING, POSSIBLE 	CAUSE UNKNOWN.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000081400002	20000814	00002	SW  	2000	8	14	20000518SH003    	1	20000426	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVE SHAFT	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	687AL	1155 			AFS1027	53366				DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-12), ACCUMULATED GREASE EXPELL	ED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000081400003	20000814	00003	SW  	2000	8	14	20000518SH004    	1	20000426	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										SHAFT HANGER	DAMAGED         	B			ALGR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	687AL				A1729	53366				DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-01), DURING LUBRICATION, ACCUM	ULATED GREASE EXPELLED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000081800001	20000818	00001	SW  	2000	8	18	20000518SH005    	1	20000426	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										SHAFT HANGER	LEAKING         	B			ALGR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL					53366				DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-12),  DURING LUBRICATION, ACCU	MULATED GREASE EXPELLED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000062100091	20000621	00091	SW  	2000	6	21	20000518SH006    	1	20000426	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										T/R DRIVE SHAFT	LEAKING         	B			ALGR	O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	687AL	1155 			AFS1027	53366				DURING RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35/AD 2000-02-12), ACCUMULATED GREASE EXPELL	ED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000081800002	20000818	00002	SW  	2000	8	18	20000518SH007    	1	20000503	G	6730	206076062101	SERVO           	KAISER      		BELL  	206   	206L4       	1182110	SW  										FLIGHT CONTROLS	BENT            	B			XJ2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	108W	3595 				52034				SERVO, PN 206-076-062-101, SN''S RH4417A, RH4418A, WERE  REMOVED FROM AIRCRAFT FOR OVERHAUL. BOTH SERVO EXTENSION ASSEMB	LIES WERE BENT TO ONE SIDE, .250 INCH.  PART NUMBER OF EXTENSION ASSY, C42642-69.  THIS SERVO IS THE SAME DESIGN AS THE 	ONE USED ON THE BELL 206L1, L3, EXCEPT THE P/N IS 206-076-062-003.  THE OPERATING PRESSURE IS 600 PSI ON THE 206L1, L3, 	AND THE OPERATING PRESSURE ON THE 206L4 IS 1,000 PSI WHICH THE BENT EXTENSIONS CAME OFF.   (X)			1	G	7	1 	3U			NC	H2SW    					 
2000081800003	20000818	00003	SW  	2000	8	18	20000518SH008    	1	20000503	G	6710	206076062101	SERVO           	KAISER      		BELL  	206   	206L4       	1182110	SW  										FLIGHT CONTROLS	BENT            	B			XJ2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	108W	3595 				52034				SERVO, PN 206-076-062-101, SN''S RH4417A, RH4418A, WERE  REMOVED FROM AIRCRAFT FOR OVERHAUL. BOTH SERVO EXTENSION ASSEMB	LIES WERE BENT TO ONE SIDE, .250 INCH.  PART NUMBER OF EXTENSION ASSY, C42642-69.  THIS SERVO IS THE SAME DESIGN AS THE 	ONE USED ON THE BELL 206L1, L3, EXCEPT THE P/N IS 206-076-062-003.  THE OPERATING PRESSURE IS 600 PSI ON THE 206L1, L3, 	AND THE OPERATING PRESSURE ON THE 206L4 IS 1,000 PSI WHICH THE BENT EXTENSIONS CAME OFF.   (X)			1	G	7	1 	3U			NC	H2SW    					 
2001013000003	20010130	00003	GL  	2001	1	30	20000518SH010    	3	20000310	G	6114		HUB             			AMTR  	FISHER	FISHERCELITY	05626AZ	GL  						MCAULY	1B90	1B90CM      	GL  	HUB ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8205H					AVI001		34090		CRACK IN HUB RADIATING AWAY FROM CENTER PILOT HOLE TOWARD MOUNTING BOLT HOLE.  CRACK FOUND USING DYE PENETRANT.  PROPELL	ER TAKEN OUT OF SERVICE.  (X)					1	Q	7	1 	3O			NC	EXPA1Q71		5	N	P842	 
2001013000004	20010130	00004	NE  	2001	1	30	20000518SH011    	2	20000308	G	7260	4T0170	BEARING         			DOUG  	MD90  	MD9030      	3023690	NM  	IAE   	V2500 	V2500A1     	 	NE  					MAIN GRBX ASSY	FAILED          	H			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					F69703		V20004			GEARBOX REMOVED FOR METAL IN CHIP COLLECTOR AND STRAINER.  DISASSEMBLY, INSPECTION DISCLOSED BEARING (CAGE) FAILURE.  MA	TERIAL FORWARDED TO IAE ENGINEERING FOR REVIEW.  (X)					2	L	7	2 	4F	4	F	RT	A6WE    	E311NE				 
2001013000005	20010130	00005	SO  	2001	1	30	20000518SH012    	1	20000314	G	7820	5327F32	MUFFLER         			MAULE 	MX7   	MX7180B     	5460188	SO  										RT EXHAUST	CRACKED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			SW	07	410TX	223  				22007C				PILOT REPORTED SMELL IN COCKPIT.  NEXT TAKEOFF, HEARD LOUD RATTLE, LANDED.  FOUND RT OUTER MUFFLER SHROUD LOOSE, THEN FO	UND MUFFLER CRACKED AT 100.3 HRS.  LT MUFFLER CHANGED.  FACTORY ADVISED MATERIAL OF MUFFLER HAD BEEN CHANGED; SO, THAT 5	00 HRS SEEMED TO BE THE LIFE OF THESE UNITS AND STATED PROBLEM WAS POSSIBLE DUE TO SHORT HEADER STACKS AND WHEN PILOT PU	LLED THROTTLE BACK FAST, CAUSED BACKFIRING IN MUFFLER AND DAMAGE.  (X)			1	H	7	1 	3O			NC	3A23    					 
2001011601197	20010116	01197		2001	1	16	20000518SH013    	4	20000215	G	2210	1610128050A7	CIRCUIT BREAKER 			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					AUTOPILOT SYS	FAILED          	E			FGHA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	7273Q		120  			20608045	L2694348A			DURING TROUBLESHOOTING OF KING KAP-140 AUTOPILOT SYSTEM, FOUND AUTOPILOT CIRCUIT BREAKER TO BE THE ''NON-PULLABLE'' TYPE	 CONTRARY TO THE PILOT OPERATING HANDBOOK EMERGENCY PROCEDURES FOR AUTOPILOT RUNAWAY **TONY, ISAAC PUT ENG IN SYS**TRIM 	INDICATION.  UPON FLEET INSPECTION OF AIRCRAFT OF SAME MODEL, FOUND SAME SITUATION WITH THE INCORRECT AUTOPILOT CIRCUIT 	BREAKER INSTALLED IN S/N 20608046 AND S/N 20608048.  (X)			1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2001011601264	20010116	01264	EA  	2001	1	16	20000518SH014    	2	20000201	G	8530	LW18944	SHROUD          			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					NR 5 CYLINDER	CRACKED         	E			FGHA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	7281M	48   				20608048	L2697448A			DISCOVERED OIL LEAK IN ENGINE COMPARTMENT COMING FROM RIGHT SIDE PUSH ROD TUBE SHROUD ON NR 5 CYLINDER ASSEMBLY.  ON FUR	THER INSPECTION, TUBE WAS FOUND CRACKED APPROXIMATELY ONE INCH DIAGONALLY THEN EXTENDING AROUND THE CIRCUMFERENCE OF THE	 TUBE (APPROX HALF WAY AROUND).  CRACK WAS LOCATED DIRECTLY ADJACENT TO THE SPARK PLUG AND HAD BEEN PAINTED OVER WITH FA	CTORY PAINT.  NOTE:  ENGINE HAD 47.7 HOURS SINCE NEW.  AIRCRAFT HAD 47.7 HOURS SINCE NEW.  (X)			1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2001011601265	20010116	01265	EA  	2001	1	16	20000518SH015    	2	20000211	G	7497		WIRE            			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					IGNITION SWITCH	SHORTED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	2312V	62   				20608046	L2695848A			PILOT REPORTED SPARKS COMING FROM UNDER THE INSTRUMENT PANEL UPON ENERGIZING THE IGNITION SWITCH.  UPON FURTHER INVESTIG	ATION, FOUND THE WIRE BUNDLE FOR THE CIRCUIT BREAKERS ADJACENT TO THE IGNITION SWITCH WAS TOO LONG AND A WIRE IN THE BUN	DLE HAD CHAFED ON AN IGNTION SWITCH POLE EVENTUALLY ARCING.  WIRE BUNDLE WAS RE-SECURED.  OTHER FLEET AIRCRAFT OF SAME M	ODEL REVEALED ONE OTHER AIRCRAFT WITH THE IDENTICAL PROBLEM, WHICH HAD NOT CHAFED THROUGH.  (X)			1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000091800004	20000918	00004	SO  	2000	9	18	20000522SH001    	2	20000425	G	8540	21208A2	HOUSING         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					HOUSING	CRACKED         	A			FPIA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H					TH219				TACHOMETER DRIVE HOUSING CRACKED AT OIL PRESSURE BOSS.  BOSS ON DRIVE HOUSING NEEDS TO BE BEEFED UP.  CRACKS DUE TO WEAK	 CASTING.  (X)					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000091800005	20000918	00005	NM  	2000	9	18	20000522SH002    	2	20000420	G	7322	8970552L	LINE            			GULSTM	690TP 	690B        	7630516	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					FUEL CONT	BROKEN          	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	690SC					11476	P06926			RIGHT ENGINE WOULD NOT START.  FOUND PY LINE BROKEN JUST AFT OF LINE FITTING.  REPLACED LINE.  (X)						1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2000091800006	20000918	00006	CE  	2000	9	18	20000522SH003    	1	20000406	G	2720	0411526	BAR             			CESSNA	150   	150M        	2071830	CE  											BROKEN          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	9440U	7952 				15078388				UNABLE TO GET NORMAL NOSE WHEEL STEERING DUE TO BREAK IN TUBE ALLOWING PEDAL  MOVEMENT WITHOUT MOVING LINKAGE TO STEERIN	G OR RUDDER.  (X)					1	H	7	1 	3O			 	3A19    					 
2001030100001	20010301	00001		2001	3	1	20000522SH006    	4	20000427	G	2564	FR46	LIFE RAFT       																	SAFETY EQUIPMENT	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	19										DURING SCHEDULED MAINTENANCE, LIFE RAFT FUNCTIONALLY TESTED.  THE INFLATABLE TUBE NR 1 FAILED TO INFLATE PROPERLY.  FURT	HER INVEST, REVEALED THE ASPIRATOR''S AIRFLOW BECAME BLOCKED WITH ITS OWN ANTI-CHAFING COATING FOR THE OUTLET.  THIS COA	TING IS NORMALLY APPLIED DURING MFG OR ACCOMPLISHMENT OF MFG''S SB.  SUSPECT THE COAT SEPARATED DUE TO ITS EXCESSIVE LEN	GTH (2.1250 INCHES) WHICH COVERS AN AREA OF FASTER AIRFLOW AND IS DIFFERENT FROM MFG''S SPEC LENGTH OF .50 TO .75 INCH. 	 THE CONDITION IS NOT NORMALLY INSPECTED DURING SCHEDULED MAINT UNLESS RAFT FAILS FUNCTIONAL TEST.  REF: HOOVER INDUSTRI	ES SB 4600-25-01.  (X)														 
2000062600091	20000626	00091	SO  	2000	6	26	20000522SH007    	1	20000522	G	3222	6705403	TRUNNION        			PIPER 	PA28  	PA28RT201   	7102818	SO  										SHIMMY DAMPER	BROKEN          	H			YBLS	O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	25	2895D					28R7918204				DURING ANNUAL INSPECTION, NOSE GEAR HAD TO BE TURNED.  WHEN IT WAS TURNED TO THE STOP ON THE TRUNNION, A PORTION OF THE 	CASTING BROKE OFF. THIS PORTION OF THE TRUNNION ANCHORS THE SHIMMY DAMPER.  UPON CLOSER INSP, FOUND CASTING HAD THREE AR	EAS THAT HAD OPEN POCKETS IN THE CASTING. THERE WERE ALSO AREAS JUST BELOW THIS AREA THAT SHOWED POROSITY.  THE TRUNNION	  WAS INSTALLED AT TIME OF MFG.  TT AIRCRAFT:  6,984.4 HOURS.  (X)			1	L	7	1 	3O			 	2A13    					 
2000062600092	20000626	00092	SO  	2000	6	26	20000522SH010    	1	20000522	G	3213	7873802	TRUNNION        			PIPER 	PA28  	PA28161     	7102803	SO  										TORQUE LINK LUG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	510PU	8724 				287916061				RIGHT GEAR OLEO PISTON ASSY TORQUE LINK LUGS CRACKED.  EARLY DETECTION CAN ONLY BE DETECTED BY DYE PENETRANT OR OTHER ND	T INSPECTION.  AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME.  (X)					1	L	7	1 	3O			 	2A13    					 
2000062600093	20000626	00093	SO  	2000	6	26	20000522SH011    	1	20000522	G	3213	6531904	TRUNNION        			PIPER 	PA28  	PA28161     	7102803	SO  										RT MAIN GEAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11		9258 				287816587				RIGHT GEAR HOUSING (CYLINDER) CRACKED AT LUG. EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT INS	PECTION.  AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME.  (X)					1	L	7	1 	3O			 	2A13    					 
2000091800007	20000918	00007	SO  	2000	9	18	20000522SH012    	1	20000522	G	3213	6531904	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  										MAIN GEAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	31862	9351 				287816587				LEFT GEAR HOUSING (CYLINDER) CRACKED AT LUG.  EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT INS	PECTION.  AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME.  (X)					1	L	7	1 	3O			 	2A13    					 
2000103100027	20001031	00027	SO  	2000	10	31	20000522SH013    	1	20000522	G	3213	6531904	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  										MAIN GEAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	6148H	6327 				287816230				RIGHT GEAR HOUSING (CYLINDER) CRACKED AT LUG.  EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT, OR OTHER NDT I	NSPECTION.  AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME.  (X)					1	L	7	1 	3O			 	2A13    					 
2000103100028	20001031	00028	SO  	2000	10	31	20000522SH014    	1	20000522	G	3213	6531904	HOUSING         			PIPER 	PA28  	PA28181     	7102807	SO  										MAIN GEAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	8203D	6522 				288290120				LEFT GEAR HOUSING (CYLINDER) CRACKED AT LUG.  EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT INS	PECTION.  AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME.  (X)					1	L	7	1 	3O			 	2A13    					 
2000091800008	20000918	00008	SO  	2000	9	18	20000522SH015    	1	20000522	G	3213	6531904	HOUSING         			PIPER 	PA28  	PA28181     	7102807	SO  										MAIN GEAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	8203D	6613 				288290120				RIGHT GEAR HOUSING (CYLINDER) CRACKED AT LUG.  EARLY DETECTION CAN ONLY BE ACCOMPLISHED BY DYE PENETRANT OR OTHER NDT IN	SPECTION.  AIRCRAFT USED FOR TRAINING 90 PERCENT OF ITS TOTAL TIME.  (X)					1	L	7	1 	3O			 	2A13    					 
2000091800009	20000918	00009	CE  	2000	9	18	20000522SH016    	1	20000515	G	7810	K1250860100	RISER           			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  					NR 4 CYLINDER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	732JF	1300 				21061543	293581R			MAINTENANCE LOOKED AT ACFT BEFORE FLIGHT.  COWLING WAS REMOVED AND EXHAUST SOOT WAS SEEN AROUND LOWER SIDE OF NR 4 CYLIN	DER.  FURTHER INVESTIGATION REVEALED A CRACK AROUND THE EXHAUST RISER THAT WAS ABOUT 270 DEGREES AROUND THE PIPE.  HEAT 	EXCHANGER PORTION OF THE EXHAUST HAD BEEN REPLACED DURING THE PREVIOUS 100-HR INSP ACCOMPLISHED 30 HRS PREVIOUSLY.  THER	E WAS NO PROBLEM IN ALIGNMENT DURING RE-ASSY OF EXHAUST SYS.  SUBMITTER STATED THIS IS THE FIRST CRACKED RISER WITH THIS	 STC'D SYSTEM.  OTHER AREAS THAT CRACKED WERE RE-DESIGNED BY MFG AND HAVE NOT HAD  ANY OTHER PROBLEMS.  (X)		1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000080700004	20000807	00004	EU  	2000	8	7	20000523SH001    	1	20000114	G	3251	2878371	CONTROL BOX     			AMD   	FALC50	FALCON900   	2700160	EU  										NLG STEERING	OUT OF ADJ      	B			AMCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	256DV					20				AFTER RECEIVING A REPLACEMENT STEERING CONTROL UNIT, INCOMING INSPECTION REVEALED THE UNIT MIS-ADJUSTED.  WHEN PRESSING 	DOWN ON THE CONTROL WHEEL, SWITCHES MAKE TO ARM THE NG STEERING.  THE SWITCH WAS ADJUSTED SUCH THAT WHEN THE CONTROL WHE	EL IS TURNED, SLIGHT UP PRESSURE WOULD DISARM THE STEERING.  THREE REPLACEMENT UNITS WERE CONFIRMED TO BE MIS-ADJUSTED. 	 THE VENDOR AND OVERHAUL FACILITY WERE NOTIFIED OF PROBLEM.  (X)			2	L	7	3 	4F			RT	A46EU   					 
2000081800004	20000818	00004	EU  	2000	8	18	20000523SH003    	1	20000222	G	6220	1051410110	BOLT            			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			TI1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				PRIMARY BLADE REMOVED FOR WEAR.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2000081800005	20000818	00005	EU  	2000	8	18	20000523SH004    	1	20000222	G	6230	1051011305	BELLOWS         			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R MAST	WORN            	B			TI1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BELLOWS REMOVED FOR WEAR.  REMOVED AND REPLACED.   (X)						1	G	7	2 	3U			NC	H13EU   					 
2000081800006	20000818	00006	EU  	2000	8	18	20000523SH005    	1	20000222	G	6210	10514101111	BOLT            			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			TI1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				SECONDARY BLADE REMOVED FOR WEAR.  REMOVED AND REPLACED.    (X)						1	G	7	2 	3U			NC	H13EU   					 
2001011601295	20010116	01295	EU  	2001	1	16	20000523SH008    	1	20000203	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					117					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	 ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2001011601297	20010116	01297	EU  	2001	1	16	20000523SH010    	1	20000203	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					584					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	 ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2001011601298	20010116	01298	EU  	2001	1	16	20000523SH011    	1	20000302	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					613					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	 ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2001011601299	20010116	01299	EU  	2001	1	16	20000523SH012    	1	20000203	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					772					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	 ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2001011601494	20010116	01494	EU  	2001	1	16	20000523SH013    	1	20000203	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					758					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	 ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2001011601223	20010116	01223	EU  	2001	1	16	20000523SH014    	1	20000203	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					2498					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	 ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2001011601224	20010116	01224	EU  	2001	1	16	20000523SH016    	1	20000203	G	2822	568127500000	ROTOR           			AIRBUS	320   	A320212     	       	EU  										FUEL PUMP	WILL NOT TEST   	B			IU6R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	01					2983					UPON INCOMING FUNCTIONAL TEST OF THE UNIT, THE UNIT COULD NOT ACHIEVE THE REQUIRED PRESSURES OR FLOW RATES PER THE OHM. 	ON FURTHER INSPECTION, THE ROTOR WAS DETERMINED TO BE THE CAUSE OF TEST FAILURE.  (X)					2	L	7	2 	4F			RT	A28NM   					 
2000091800012	20000918	00012	EA  	2000	9	18	20000523SH019    	2	20000427	G	7420		IGNITION LEAD   	CHAMPION    		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					SHIELDING	FAILED          	B			SL5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	4198F	16   				287790006	L2207836A			IGNITION NOISE IN RADIO REPORTED BY OWNER.  TRACED PROBLEM TO FOUR IGNITION LEADS WITH UNGROUNDED WIRE SHIELDING.  SUBMI	TTER SUSPECTED POOR QUALITY CONTROL/FINAL INSPECTION BY MANUFACTURER.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000091800013	20000918	00013	CE  	2000	9	18	20000523SH020    	1	20000404	G	3397		WIRE            			BEECH 	36    	A36         	1151604	CE  										NAV LIGHT	CHAFED          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	6923R	2980 				E2149				FOUND NAVIGATION LIGHT BREAKER TRIPPED.  FOUND WIRING IN LEFT WING NOT PROPERLY SECURED AND CHAFED WHERE CROSSING THROUG	H RIB; THUS, SHORTING CIRCUIT.  SUBMITTER STATED THAT IT LOOKS LIKE IT WAS INSTALLED THIS WAY BY FACTORY, NO SIGNS OF CL	AMPS.  (X)				1	L	7	1 	3O			 	3A15    					 
2000091800014	20000918	00014	CE  	2000	9	18	20000523SH021    	1	20000413	G	3230	08411121	LINK            			CESSNA	421   	421A        	2076012	CE  										RT MAIN LANDING	SEPARATED       	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	2989Q					421A0089				THE LINK SEPARATED IN THE THREADED AREA WHERE IT ENTERS THE ROD-END IN THE LINK ASSY.  THIS IS PART OF BELLCRANK 5041001	-2.  THE FAILURE CAUSED THE RIGHT MAIN GEAR TO COME OUT OF OVERCENTER IN THE DOWN POSITION AND THEN COLLAPSE.  (X)					1	L	7	2 	3O			 	A7CE    					 
2001013000010	20010130	00010	CE  	2001	1	30	20000523SH022    	1	20000523	G	5410		BEAM            			CESSNA	402   	402B        	207590P	CE  										LT AND RT ENGINE	DAMAGED         	B			X07R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	306					402B0435				LT AND RT ENGINE BEAMS (INBD AND OTBD) BUCKLING AND HEAT DAMAGE.  GENERAL CORROSION BEHIND ENGINES.  LT AND RT ENGINES C	ANTED BULKHEADS.  CORROSION AND HEAT DAMAGE.  LT AND RT WING LOWER SPAR CAPS, OVERSIZED HOLES WITH RIVNUTS INSTALLED.  L	T AND RT  ENGINE NACELLE STIFFENERS BEHIND FWD SPAR HAVE BEEN CUT.  RT ELEVATOR HAS SLOP IN TORQUE TUBE.  SERVICE KIT 40	2-46 WING FRONT SPAR LOWER CAP MODIFICATION AND ACCESS PANEL INSTALLATION IN WORK.  (X)			1	L	7	2 	3O			 	A7CE    					 
2000091800015	20000918	00015	CE  	2000	9	18	20000523SH024    	1	20000508	G	3246	AN535A	BOLT            			BEECH 	95    	95B55       	1152729	CE  										THREADS	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	2189L					TC1993				BOLTS BROKE AT BASE OF THREADS.  MOST LIKELY CAUSED BY OVERTORQUING.  THE BOLTS ARE WHEEL THROUGH BOLTS ON THE MAIN TIRE	S. (X)					1	L	7	2 	3O			RT	3A16    					 
2000091800016	20000918	00016	SW  	2000	9	18	20000523SH025    	1	20000523	G	1100		PLACARD         			MOONEY	M20   	M20R        	5870225	SW  										PILOT SIDE PANEL	INCORRECT       	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	535C					290146				THE OPERATION LIMITATIONS PLACARD DOES NOT MATCH THE TYPE CERTIFICATE DATA SHEET.  THE MANEUVERING SPEED IS DIFFERENT.  	(X)					1	L	7	1 	3O			RT	2A3     					 
2000091800017	20000918	00017	NE  	2000	9	18	20000523SH026    	1	20000414	G	5740	2161110	BEAM            			LAKEAC	LAKE  	250LAKE     	5110321	NE  										REAR WING SPAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	14032	1900 				36				CRACK SEEMS TO ORIGINATE FROM A PUNCHED THROUGH .1250 INCH JIG HOLE, 2.50 INCHES OUT FROM REAR SPAR ATTACH BOLT.  CAN BE	 SEEN FROM GEAR WALL .3750 INCH LONG CRACK.  (X)					1	H	7	1 	3O			NC	1A13    					 
2000091800018	20000918	00018	NE  	2000	9	18	20000523SH027    	1	20000414	G	2730	3225529	BRACKET         	LAKEAC      		LAKEAC	LAKE  	250LAKE     	5110321	NE  										ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	14032	1900 				36				ANNUAL INSPECTION FOUND ELEVATOR HORN ATTTACH BRACKETS, UPPER EAR OF BOTH BRACKETS WERE FOUND CRACKED OFF. (X)						1	H	7	1 	3O			NC	1A13    					 
2000091800019	20000918	00019	CE  	2000	9	18	20000523SH028    	1	20000516	G	2710	355211524	TORQUE TUBE     			BEECH 	36    	A36         	1151604	CE  										ROD END	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	422MM	201  				E3217				UPON ANNUAL INSPECTION, FOUND LT AILERON WITH EXCESSIVE PLAY.  REMOVED TORQUE TUBE AND FOUND THREADED PORTION OF TUBE NO	T THREADED TO THE TOP OF TUBE.  TUBE REMOVED FROM SERVICE AND INSTALLED NEW TUBE.  THE ROD ENDS WERE ALSO REPLACED WITH 	NEW.  (X)				1	L	7	1 	3O			 	3A15    					 
2000061300376	20000613	00376	EU  	2000	6	13	20000523SH030    	1	20000503	G	2400	B3651M0250	RELAY           			AMD   	FALC10	FALCON10    	2730101	EU  										AIRFRAME	FAILED          	B			G1FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	147G					214				DURING AIRFRAME INSPECTION, THE REVERSE CURRENT RELAY WAS REMOVED FOR INSPECTION AND RECERTIFICATION. THE RELAY, WHICH W	AS FUNCTIONING NORMALLY WHEN REMOVED, WAS ROUTED TO A RATED REPAIR STATION FOR CHECK AND RECERTIFICATION.  UPON RETURN F	ROM VENDOR, UNIT WAS RE-INSTALLED AND OPER CHKS PER MM.  AFTER ELEC POWER APPLIED, EXTENSIVE DAMAGE OCCURRED TO WIRING F	ROM MAIN POWER JUNCTION BOX TO OVERHEAD PANEL START SWITCHES.  REVERSE CURRENT RELAY, PN B3651M0-250, SN 2324, WAS DETER	MINED DEFECTIVE AND REPLACED.  RELAY REPLACED WITH NEW UNIT PN B3651M0-250 AND DAMAGED WIRING REPLACED FROM MAIN POWER J	UNCTION BOX TO OVERHEAD  PANEL START SWITCHES.  SUBSEQUENT OPER CHECKS WITH ENG RUNS REVEALED NO FURTHER DEFECTS.  (X)	2	L	7	2 	4F			 	A33EU   					 
2000091800021	20000918	00021	CE  	2000	9	18	20000523SH031    	1	20000517	G	3246	95440253	WHEEL           	GOODYEARAERO		LEAR  	24    	24D         	5170311	CE  										FLANGE	CRACKED         	B			GPER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	281FP				SEP72516	281				PART TSO: 172 LANDINGS.  SINCE EDDY CURRENT INSPECTION, FOUND BY MAINTENANCE AFTER A FLIGHT, NO EVIDENCE THE WHEEL HAD B	EEN STRUCK.  (X)					2	L	7	2 	4J			 	A10CE   					 
2001013000012	20010130	00012	NE  	2001	1	30	20000524SH002    	2	20000501	G	7230	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FROM WESTFIELD GAGE (WNFR711K) FOR PENETRANT INSPECTION PER V2500 ENGINE MANUAL SECTION 70-23-01, TASK 70-	23-01-230-501,  INSPECTION CHECK-01.  PART REJECTED AT PENETRANT INSPECTION DUE TO A CRACK ON OUTSIDE TOP OF PART APPROX	IMATELY .250 INCH LONG.  (X)									4	F			E311NE				 
2001013000015	20010130	00015	NE  	2001	1	30	20000524SH008    	2	20000505	G	7230	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FROM WESTFIELD GAGE (WNFR711K) FOR FPI PER V2500 ENGINE MANUAL REV 42, SECTION 70-23-01, INSPECTION CHECK-	01, TASK 70-23-01-230-501). PART REJECTED AT FPI DUE TO A CRACK, 0.180 INCH ON TOP SURFACE,										4	F			E311NE				 
2001013000016	20010130	00016	NE  	2001	1	30	20000524SH009    	2	20000505	G	7230	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FROM WESTFIELD GAGE (WNFR711K) FOR FPI PER V2500 ENGINE MANUAL REV 42, SECTIO 70-23-01, INSPECTION CHECK-0	1, TASK 70-23-01-230-501). PART REJECTEDAT FPI DUE TO A CRACK 0.325 INCH ON TOP SURFACE.  (X)										4	F			E311NE				 
2001013000017	20010130	00017	EA  	2001	1	30	20000524SH010    	2	20000428	G	7414	10382807	CAPACITOR       		D4LN3200    	ENSTRM	F28   	F28F        	3300412	GL  	LYC   	O360  	HIO360F1AD  	41514	EA  					RIGHT MAGNETO	FAILED          	B			NQ2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	110PD	13   			H269108G	768	L2537651A			SUBJECT CAPACITOR WAS INSTALLED NEW IN AUGUST, 1999.  MAGNETO WAS PART OF SPARE ENGINE NOT INSTALLED UNTIL THIS MONTHV. 	 THE CAPACITOR HAD VERY FEW HOURS (13.3 HRS) WHEN IT CAUSED HEAVY POINT RACING WHICH MELTED THE NYLON FOLLOWER.  WHEN TH	IS HAPPENED, THE POINTS QUIT OPENING AND THE RIGHT HALF OF THE MAG WENT DEAD.  CAPACITOR FAILS THE SEALEY RESISTANCE TES	T ON THE BENCH AND HAS .4 OHM RESISTANCE FROM P-LEAD END TO DIGITAL.  DATE CODE IS 9835 WICH MAKES IT SUBJECT TO TCM BUL	LETIN NR CSB662A, BUT OWNER WAS NOT AWARE OF BULLETIN.  ALSO, BULLETIN ALLOWS 50 HOUR TIME IN SERVICE.  SUBMITTER STATED	 THIS ONE HAD FAR LESS.  (X)	1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2000120700001	20001207	00001	CE  	2000	12	7	20000524SH012    	1	20000515	G	5312	00244002391	BULKHEAD        			BEECH 	55    	E55         	1152732	CE  											CRACKED         	B			NT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3085W	2206 				TE954				DURING ANNUAL INSPECTION, FOUND CRACK .75 INCH LONG (LEFT) AND .3750 INCH LONG (RIGHT) ON BULKHEAD, PN 002-440023-91 AT 	BS 257.6.  CRACKS ARE ADDRESSED IN BEECH SI 0990R2, FIGURE 1.  INSTALLED REPAIR KIT AS DIRECTED BY SI 0990R2.  (X)					1	L	7	2 	3O			 	3A16    					 
2001010300001	20010103	00001	SW  	2001	1	3	20000524SH013    	1	20000511	G	2720	500012263	CONTROL CABLE   			GULSTM	690TP 	690B        	7630516	SW  										BS 99.00	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	690JH	5313 				11529				LEFT AND RIGHT FORWARD RUDDER CABLES HAD BROKEN WIRE STRANDS AT LEFT AND RIGHT PULLEY AT BS 99.00.  FOUND DURING 100-HOU	R INSPECTION.  ROTATED CABLES 10 DEGREES FROM PULLEY TO SEE BROKEN WIRE STRANDS.  CAUSE,  DETERIORATION DUE TO TIME. AIR	CRAFT TT:  5,313 HOURS.  REPLACED CABLE ASSY.  (LEFT FROM RUDDER PEDAL AFT TO TURNBARREL AT STA 335.00) AND (RIGHT FROM 	RUDDER PEDAL AFT TO TURNBARREL AT STA 353.00).			1	H	7	2 	3T			 	2A4     					 
2001013000018	20010130	00018	SW  	2001	1	30	20000524SH014    	1	20000511	G	2720	500012265	CONTROL CABLE   			GULSTM	690TP 	690B        	7630516	SW  										RUDDER CONTROL	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	690JH	5313 				11529				LEFT AND RIGHT FORWARD RUDDER CABLES HAD BROKEN WIRE STRANDS AT LEFT AND RIGHT PULLEY AT BS 99.00.  FOUND DURING 100-HOU	R INSPECTION.  ROTATED CABLES 10 DEGREES FROM PULLEY TO SEE BROKEN WIRE STRANDS.  CAUSE,  DETERIORATION DUE TO TIME. AIR	CRAFT TT:  5,313 HOURS.  REPLACED CABLE ASSY.  (LEFT FROM RUDDER PEDAL AFT TO TURNBARREL AT STA 335.00) AND (RIGHT FROM 	RUDDER PEDAL AFT TO TURNBARREL AT STA 353.00).			1	H	7	2 	3T			 	2A4     					 
2001013000019	20010130	00019	CE  	2001	1	30	20000524SH015    	1	20000227	G	2810	05235221	STRAP           			CESSNA	150   	152         	2071835	CE  										RT FUEL TANK	BROKEN          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	95939					15285988				IT WAS NECESSARY TO PULL THE RT WING FUEL TANK TO CONFIRM FUEL LEAK LOCATION.  THE AFT OUTBOARD STRAP ASSY WAS FOUND BRO	KEN ACROSS THE SCREW HOLE.  FURTHER EXAM OF STRAP REVEALED THE GRAIN OF THE ALUMINUM WAS PARALLEL TO THE BREAK AS WELL A	S THE BEND.  IT IS BELIEVED THAT IF THE GRAIN WERE PERPENDICULAR TO THE BEND RADIUS, THE LIKELIHOOD OF A FAILURE AT THE 	SCREW HOLE OR BEND WOULD BE GREATLY REDUCED.  THE FUEL TANK HAD A PREVIOUS CRACK WHICH WAS WELDED.  THE LOSS OF THIS STR	AP IS BELIEVED TO HAVE CAUSED THE REPEAT FAILURE OF THE TANK AT THIS SAME LOCATION, WHICH WAS AT THE AFT BOTTOM FUEL OUT	PUT  (JUST ABOVE IT).  THE TANK AND STRAP ASSEMBLIES WERE REPLACED WITH NEW ASSEMBLIES.   (X)	1	H	7	1 	3O			NT	3A19    					 
2001013000020	20010130	00020	EA  	2001	1	30	20000524SH016    	2	20000428	G	8520	SL75060	ROD BOLT        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 1 PISTON ROD	FAILED          	H				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CE	05	47977		214  			32R7880031	L1518048A			AIRCRAFT ENGINE OIL TEMPERATURE AT 200 DEGREES.  LOSS OF OIL PRESSURE AT NORMAL CRUISE MADE OFF-AIRPORT LANDING.  FOUND 	NR 1 PISTON ROD HAD FAILED.  POSSIBLE CAUSE FOR FAILURE, SUPERIOR ROD CAP BOLT FAILED CAUSING ROD TO COME LOOSE, KNOCK H	OLE IN ENGINE CASE.   (X)				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000120700002	20001207	00002	CE  	2000	12	7	20000524SH018    	1	20000420	G	5700		RIVET           			BEECH 	58    	58          	1152740	CE  										LEFT	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	2018T					TH954				AIRCRAFT REPAIRED IN 1980 AFTER GEAR UP LANDING.  REPAIRS FOUND TO BE UNACCEPTABLE IN 2000 ANNUAL.  RIVETS WERE INSTALLE	D WITH NO SHOP HEAD, AND RIVET HEADS NOT AGAINST STRUCTURE.  LOCATION OF REPAIR IS UPPER FORWARD WING SPAR JUST OUTBOARD	 OF WING BELT FITTING.  ANNUAL SIGNED OFF UNAIRWORTY, AND OWNER FERRIED AIRCRAFT TO HOME BASE.  OWNER SAYS HE CANNOT BEL	IEVE AIRCRAFT WENT THROUGH 18 ANNUALS AND NO ONE SAW THIS.  SUBMITTER SUGGESTED EXTRA LOOK AT PREVIOUS REPAIRS.  			1	L	7	2 	3O			 	3A16    					 
2001011601235	20010116	01235	NM  	2001	1	16	20000530SH006    	1	20000403	G	3231	600050525	ROD             			PIPER 	PA60  	PA60600     	7106001	NM  										MLG DOOR	BENT            	A			BSYA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	3643D					600835816152				BDL - LANDING GEAR WOULD NOT RETRACT.  FOUND GEAR DOOR ROD ASSY BENT.  REMOVED AND REPLACED ROD ASY.  OPS CHECKED GOOD. 	 (X)					1	M	7	2 	3O			RT	A17WE   					 
2001011601236	20010116	01236	EA  	2001	1	16	20000530SH007    	2	20000426	G	8520	LW10646	CONNECTING ROD  			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					NR 5 CYLINDER	FAILED          	A			BSYA	E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	07	6896B					600919816126	L1841648A			BDL - RT ENGINE ROUGH, THEN PILOT SHUT ENGINE DOWN.  FOUND NR 5 CYLINDER CONNECTING ROD FAILED.  CAUSE UNKNOWN AT THIS T	IME.  REMOVED AND REPLACED ENGINE ASSY.  (X)					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000120700003	20001207	00003	CE  	2000	12	7	20000530SH008    	1	20000509	G	3340		BEACON MOTOR    			BEECH 	58    	58          	1152740	CE  											BURNED          	A			BSYA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	9044V					TH216				BDL - GOT SMOKE IN COCKPIT JUST AFTER TAKEOFF, RETURNED TO BDL.  FOUND POWER WIRE TO ROTATING BEACON BURNT. (X)						1	L	7	2 	3O			 	3A16    					 
2001011601237	20010116	01237	CE  	2001	1	16	20000530SH009    	1	20000505	G	2120		UNKNOWN         			CESSNA	310   	310R        	2074245	CE  										COCKPIT	ODOR            	A			BYSA	C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			GL	07	6122C					310R1290				CMH - PILOT REPORTED BURNING SMELL IN COCKPIT ON TAKEOFF.  ABORTED TAKEOFF AND RETURNED TO BASE.  MAINTENANCE CHECKED HE	ATER, LANDING GEAR, ALL ELECTRICAL COMPARTMENTS, AVIONICS, CHECKED ALL RADIOS.  COULD NOT DUPLICATE SMELL.  RETURNED TO 	SERVICE.  (X)				1	L	7	2 	3O				3A10    					 
2001011601238	20010116	01238	EA  	2001	1	16	20000530SH010    	2	20000505	G	8530		CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT ENGINE NR 2	SEPARATED       	A			BYSA	O				OTHER                   				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			GL	07	525AA					318052111				AGC - LEFT ENGINE NR 2 CYLINDER SEPARATED FROM ENGINE.  CAUSE UNKNOWN AT THIS TIME.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001013000021	20010130	00021		2001	1	30	20000530SH011    	4	20000502	G	6122	4508042	FLYWEIGHT       	WOODWARD    		GULSTM	500   	500RKWELL   	0141102	SW  										PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1450395A					RELEVANT CRACK INDICATION IN CORNER OF FLYWEIGHT DISC.  (X)						1	H	7	2 	3O			 	6A1     					 
2001013000022	20010130	00022	NE  	2001	1	30	20000530SH012    	2	20000510	G	7250	UL10323	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		30494					31009			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2001013000023	20010130	00023	NE  	2001	1	30	20000530SH013    	2	20000510	G	7250	UL10323	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		29018					31118			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2001013000024	20010130	00024	NE  	2001	1	30	20000530SH014    	2	20000510	G	7250	UL27681	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		29778					31030			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2001013000025	20010130	00025	NE  	2001	1	30	20000530SH015    	2	20000510	G	7250	UL27681	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		25399					31091			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2001013000026	20010130	00026	NE  	2001	1	30	20000530SH016    	2	20000510	G	7250	UL27681	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		22970					31014			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2001013000027	20010130	00027	NE  	2001	1	30	20000530SH017    	2	20000510	G	7250	UL27681	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		17201					31031			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2001013000028	20010130	00028	NE  	2001	1	30	20000530SH018    	2	20000510	G	7250	UL27681	DISK            								RROYCE	RB211 	RB211535E4B3	 	NE  					TURBINE SECTION	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		19544					31178			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB.211-72-C817.  (X)											4	F			E12EU				 
2000082200001	20000822	00001		2000	8	22	20000531SH001    	4	20000327	G	2562	AK450	ELT             			PIPER 	PA28  	PA28RT201   	7102818	SO  											FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2241N					28R7918043				ELT FAILED TEST PER FAR 91.207.  NO SWEEPS COULD BE HEARD ON 121.5.  UNIT WAS NEW 12 MONTHS EARLIER.  (X)						1	L	7	1 	3O			 	2A13    					 
2000082200002	20000822	00002	SO  	2000	8	22	20000531SH002    	1	20000518	G	2751	2282002	SENSOR          			PIPER 	PA23  	PA23250     	7102308	SO  										FLAP	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13										FLAP SENDER POTENTIOMETER INSTALLED BACKWARDS.  PART WAS NEW FROM PIPER.  OTHER PART NUMBERS ON UNIT, 2283-002, 2282-3, 	5276.  (X)					1	L	7	2 	3O			 	1A10    					 
2000082200003	20000822	00003		2000	8	22	20000531SH003    	4	20000508	G	2562	AK450	ELT             			CESSNA	177   	177RG       	2073709	CE  											FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	300ZX					177RG0072				ELT UNIT RECEIVED FROM MANUFACTURER AS AN EXCHANGE UNIT.  ELT FAILED TEST AFTER REINSTALLATION.  NO SWEEPS COULD BE HEAR	D ON 121.5.  AN OCCASIONAL SHORT ''CHIRP'' COULD BE HEARD, BUT NO SWEEPS.  (X)					1	H	7	1 	3O			 	A20CE   					 
2000082200004	20000822	00004		2000	8	22	20000531SH004    	4	20000208	G	2562	AK450	ELT             			CESSNA	177   	177RG       	2073709	CE  											FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	300ZX	100  				177RG0072				ELT FAILED TEST PER FAR 91.207.  NO SWEEPS COULD BE HEARD ON 121.5.  UNIT WAS REPAIRED FOR SAME PROBLEM 11 MONTHS EARLIE	R ON 1-19-99.  (X)					1	H	7	1 	3O			 	A20CE   					 
2001013000029	20010130	00029	SO  	2001	1	30	20000531SH005    	2	20000419	G	8520	642133	CASE            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	CRACKED         	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4050Q					421B0274	218398H			CASE CRACKED ON LEFT HALF UPPER AT BACK ABOVE SPLIT, THE 5TH BOLT FROM REAR.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001013000030	20010130	00030	EA  	2001	1	30	20000531SH006    	2	20000502	G	8540	06A19956	SEAL            			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ACCESSORY SECT	FAILED          	B			EKIR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			WP	07	502ER	1512 				172S8002	L2776151A			DURING FINAL APPROACH, PILOT NOTED LOW OIL PRESSURE INDICATION.  DURING INVESTIGATION OF OIL LOSS, IT WAS NOTED THAT THE	 OIL SEAL LIP WAS TURNED OUTWARD AND THE TENSION SPRING WAS MISSING.  APPROXIMATELY 1 QUART OF OIL REMAINED IN THE OIL S	UMP.  SEAL WAS IN LOWER VACUUM PUMP ADAPTER.  (X)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001013000031	20010130	00031	CE  	2001	1	30	20000531SH007    	1	20000502	G	3211	24411001	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	B			EKIR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4802R	5872 				172RG0035				LEFT BRAKE KEPT BECOMING SOFT AND LOOSING HYDRAULIC FLUID WITH NO EXTERNAL LEAKS FOUND.  REMOVAL AND DYE PENETRANT INSPE	CTION OF  LEFT MAIN GEAR PIVOT REVEALED CRACK IN RADIUS OF SPLINES INTO BRAKE FLUID PASSAGE.  (X)					1	H	7	1 	3O			 	3A17    					 
2000122900001	20001229	00001	CE  	2000	12	29	20000531SH008    	1	20000414	G	5260	50430043619	CHANNEL         			BEECH 	100   	B100        	1152919	CE  										CABIN DOOR	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	400AC					BE12				CABIN DOOR WAS OPENED FOR ACCESS TO AIRCRAFT. THE CHANNEL, WHICH FORMS THE BOTTOM OF THE DOOR AND ATTACHES TO THE DOOR H	INGE, FAILED AT ITS AFT END.  UPON INSPECTION, THE CHANNEL WAS FOUND TO HAVE INITIAL CORROSION, (INSIDE THE DOOR STRUCTU	RE) DUE TO THE SEALED NATURE OF THE DOOR, NO DRAIN HOLE IS POSSIBLE AT THIS LOW SPOT.  (X)				1	L	7	2 	4T			 	A14CE   					 
2001013000032	20010130	00032	CE  	2001	1	30	20000531SH009    	1	20000531	G	5220	08112189	CABLE           			CESSNA	310   	310R        	2074245	CE  										EMERGENCY EXIT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	4FA					310R0700				THE CABLE WHICH IS INSTALLED IN THE LEFT FRAMEWORK AROUND THE EMERGENCY EXIT WAS FRAYED IN TWO PIECES, ONE OF WHICH WAS 	BROKEN IN TWO.  THERE ARE FIVE PINS THAT ATTACH TO THE CABLE WHICH HOLD THE EMERGENCY WINDOW IN PLACE.  ONLY TWO PINS WE	RE HOLDING THE WINDOW IN PLACE.  TWO PINS WERE BROKEN OFF AND ONE PIN WAS MISSING.  THIS ITEM IS NOT USUALLY CHECKED DUR	ING ANNUAL INSPECTION.  THE TWO PINS THAT WERE STILL INSTALLED ACCIDENTALLY CAME OUT THE WINDOW, CAME OUT IN-FLIGHT.  (X	)		1	L	7	2 	3O			 	3A10    					 
2001013000033	20010130	00033		2001	1	30	20000531SH010    	4	20000531	G	6122	626737	COLLAR          			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					CRANKSHAFT	SCORED          	B			JZRR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	5343J	70   				340A0416	504283			PROPELLER FEATHERING AT HIGH RPM''S.  OIL TRANSFER COLLAR WAS SCORED CAUSING INSUFFICIENT OIL PRESSURE BETWEEN COLLAR AN	D CRANKSHAFT PILOT SHAFT.  RECOMMEND DESIGN CHANGE ON TRANSFER COLLAR, OR CRANKCASE MODIFICATION TO ALLOW REPLACEMENT OF	 LEFT HALF OF COLLAR INSTEAD OF ENGINE DISASSEMBLY.  (X)				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2001020500058	20010205	00058	CE  	2001	2	5	20000531SH012    	1	20000512	G	3230	95001260102	HOSE            			CESSNA	421   	421C        	2076016	CE  										LANDING GEAR	RUPTURED        	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	21	49TD					421C0025				WHILE AT 13,000 FEET, PILOT NOTICED HYDRAULIC ANNUNCIATOR FLICKERING.  WITHIN 2-3 MINUTES, PILOT HAD COMPLETE HYDRAULIC 	FAILURE.  PILOT DEPLOYED LANDING GEAR IMMEDIATELY AND STARTED DESCENT.  HE GOT 3 GREEN AND CONTINUED DOWN.  LANDED WITH 	NO MISHAP.  UPON INSPECTION, FOUND ACTUATOR UP, HOSE RUPTURED.  PART WAS REPLACED WITH NEW PART. (X)				1	L	7	2 	3O			 	A7CE    					 
2001020100001	20010201	00001	NE  	2001	2	1	20000531SH013    	1	20000509	G	6210	7615009100052	BLADE           			SKRSKY	S76   	S76B        	8143007	NE  										MAIN ROTOR	DELAMINATED     	B			CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	780P	3615 				760359				DURING POST-FLIGHT, TECHNICIAN NOTED A LARGE CRACK OR DELAMINATION OF THE INBOARD ROTOR BLADE STARTING ABOUT 20 INCHES F	ROM THE ROOF ON THE TRAILING EDGE, EXTENDING ABOUT 5 INCHES LENGTHWISE, THEN DIAGONALLY TO JUST BEHIND THESPAR AND THEN 	LENGTHWISE ABOUT 12 INCHES.  CAUSE IS UNDER INVESTIGATION. (X)				1	G	7	2 	4U			 	H1NE    					 
2000082200005	20000822	00005	SW  	2000	8	22	20000531SH014    	1	20000502	G	8100	633358	CLAMP           			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					EXHAUST OUTLET	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	231BT	1    			TSO0100014	250122	309127			TURBO CLAMP THAT ATTACHES EXHAUST PIPE TO TURBO BROKE.  CLAMP WAS SAFTIED AROUND BOLT.  BREAK OCCURRED SOMEWHERE ON CLAM	P.  POSSIBLE SEPARATION WHERE SPOT-WELD HOLDS BOLT IN PLACE.  (X)					1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2000082200006	20000822	00006	GL  	2000	8	22	20000531SH015    	3	20000508	G	6114	D4883C55	HUB             	MCAULY      		BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  		CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	819MC		360  			TE600		740405		RELEVANT ET INDICATION, CRACK OUTER MOST THREAD, BOTH SIDES.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2000082200007	20000822	00007	GL  	2000	8	22	20000531SH016    	3	20000509	G	6110	D3156	COUNTERWEIGHT   	MCAULY      		BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  		CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	819MC					TE600		740405		CRACK INDICATION BETWEEN BOLT ATTACHING HOLES.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2000082200008	20000822	00008	GL  	2000	8	22	20000531SH017    	3	20000511	G	6114		HUB             	MCAULY      		BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  		CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17			1500 					661474		EDDY CURRENT AND PENETRANT TESTING INDICATION IN THREAD AREA.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2000082200009	20000822	00009	GL  	2000	8	22	20000531SH018    	3	20000511	G	6110	C2463	NUT             	MCAULY      		BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	2A36C	2A36C23     	GL  		FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17			1500 					661474		PENETRANT TESTING INDICATION IN O-RING AREA.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2000082200010	20000822	00010		2000	8	22	20000531SH019    	4	20000510	G	6122	A20609	LEVER           	MCAULY      																GOV	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					763256					RELEVANT CRACK INDICATION AT THE RETENTION AREA. (X)																			 
2000082200011	20000822	00011	SO  	2000	8	22	20000531SH020    	2	20000504	G	7310		PRIMER LINE     			BEECH 	35    	E35         	1151512	CE  	CONT  	E225  	E2258       	17015	SO  					CLAMPING AREA	CRACKED         	B			K2YR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	7382B	1549 				D3845	35681D98R			AT CYLINDER REPLACEMENT, FOUND PRIMER LINES NR 1, NR 3 CYLINDERS CRACKED (3/4 AROUND)  UNDER ADEL CLAMP AREA.  EVIDENCE 	OF FATIGUE AND CORROSION. (X)					1	L	7	1 	3O	3	O	 	A777    	E267				 
2000082200012	20000822	00012	SO  	2000	8	22	20000531SH021    	2	20000504	G	8530	23509	CYLINDER        			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					ROCKER ARM BOSSE	BROKEN          	B			K2YR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	21	563G	3246 	245  			15068275	680677A			OWNER STATED ENGINE BEGAN RUNNING ROUGH.  DEVIATED TO NEAREST AIRPORT.  HAD TO KEEP PUMPING THROTTLE TO MAINTAIN ENGINE 	RUNNING.  MADE PRECAUTIONARY LANDING AT AIRPORT.  UPON COLD CYLINDER CHECK, REMOVED CYLINDER ROCKER BOSS COVER.  PIN AND	 BOSSES FELL OUT.  NEW AND OLD CRACKS EVIDENT.  SUBMITTER STATED AD 94-05-05R1 PERTAINS TO THIS.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000062000125	20000620	00125	SO  	2000	6	20	20000531SH022    	2	20000504	G	8530	536727	CYLINDER        			BEECH 	35    	E35         	1151512	CE  	CONT  	E225  	E2258       	17015	SO  					BARREL	SEPARATED       	B			K2YR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	7382B	1548 	752  			D3845	35681D98R			AT ANNUAL INSPECTION, FOUND SIGNS OF SEEPAGE AT BARREL (INDICATIONS OF BARREL SEPARATING FROM HEAD) IN NR  4, NR 5, NR 6	 CYLINDERS.  POSSIBLE CAUSE IS AGE ON CYLINDERS AND TIME IN SERVICE.  (X)					1	L	7	1 	3O	3	O	 	A777    	E267				 
2000062000126	20000620	00126	GL  	2000	6	20	20000531SH023    	3	20000509	G	6110	C5270	BEARING         	MCAULY      		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  		GROOVED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	CTEXT		369  					931446		RELEVANT INDICATION IN BEARING GROOVE.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000062000133	20000620	00133	SW  	2000	6	20	20000601SH002    	1	20000216	G	5302	206030446001F	BULKHEAD        	BELL        		BELL  	206   	206B        	1181511	SW  										TAIL BOOM	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	914HH	8345 				2297				PART IN QUESTION IS LOCATED ON THE AFT MOST SECTION ON THE HELICOPTER TAIL BOOM.  THE TAIL ROTOR GEARBOX AFT MOUNT STUDS	 PASS THROUGH THE TOP OF THIS FITTING ON THE LEFT AND RIGHT SIDES.  CRACKS DEVELOPED FROM THESE STUD HOLES TO ADJACENT M	OUNTING RIVET HOLES.  ALSO, CRACKS WERE NOTED ON THE TOP SIDE OF THIS FITING THAT WERE NOT VISIBLE WITH FITTING INSTALLE	D.  CRACKS WERE FOUND DURING NORMAL 100-HOUR INSPECTION.  POSSIBLE CAUSE CAN BE UNDER OR OVER TORQUING OF INSTALLATION H	ARDWARE, OR EXCESSIVE TAIL ROTOR VIBRATIONS. (X)		1	G	7	1 	3U			 	H2SW    					 
2000062000134	20000620	00134	SO  	2000	6	20	20000601SH004    	1	20000204	G	7800		HEADER          			PIPER 	PA23  	PA23250     	7102308	SO  										EXHAUST	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6913A	2000 				277954108				DURING POST-FLIGHT INSPECTION FOUND EXHAUST HEADER BLOW-OUT OCCURRED AT HEAT EXCHANGER SHROUD INSIDE SHROUD AT CROSSOVER	 PIPE DIRECTING EXHAUST AT FUEL HOSE AND CONTROL.  (X)					1	L	7	2 	3O			 	1A10    					 
2000062100122	20000621	00122	CE  	2000	6	21	20000601SH005    	1	20000601	G	3150		ANNUNCIATOR     			BEECH 	90    	C90A        	1152911	CE  										CABIN	WILL NOT TEST   	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	2354Y	365  				LJ1532				A/P TRIM FAILED, CABIN ALT HIGH, AND CABIN DOOR ANNUNCIATOR LIGHTS INTERMITTENT IN ANNUNCIATOR TEST POSITION.  FOUND GRO	UNDING WIRE WRAPPED AROUND POSTS, BUT NOT SOLDERED.  (X)					1	L	7	2 	3T			RT	3A20    					 
2000062000135	20000620	00135	SO  	2000	6	20	20000601SH006    	1	20000509	G	2410	75536	BUSHING         	LYC         		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  						FAILED          	B			PAIR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	05	61CG					31P30	L47262			PILOT EXPERIENCED ALTERNATOR FAILURE ON LT ENGINE IN-FLIGHT. UPON INSPECTION AFTER LANDING, FOUND LT SIDE OF AIRCRAFT CO	VERED IN OIL AND LT ALTERNATOR LYING INSIDE OF COWLING.  SUBMITTER SUSPECTED FAILURE OF  GENERATOR ADAPTER ASSY BUSHING 	PN 75539 CAUSED MISALIGNMENT OF ALT DRIVESHAFT WHICH CAUSED COUPLING PN LW-14464 TO FAIL IN SUCH A MANNER THAT CAUSED AL	TERNATOR ADAPTER ASSY PN LW-10259 TO FAIL.  (X)			1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2000062000136	20000620	00136	CE  	2000	6	20	20000601SH007    	1	20000505	G	3221	24130023	ATTACH FITTING  			CESSNA	172   	172RG       	2072438	CE  										NOSE LANDING GEA	CRACKED         	G			HO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4914V	11971				172RG0414				REPAIR STATION DISCOVERED, WHILE INSPECTING THE NOSE LANDING GEAR DURING AN ANNUAL INSPECTION, THE NOSE LANDING GEAR RET	RACTION ACTUATOR ATTACH FITTING WAS FOUND CRACKED FROM THE LOWER LEFT INNER BOLT HOLE TO THE OUTER EDGE OF THE FITTING. 	 THE CRACK WAS APPROX ONE INCH IN LENGTH.  ALL OF THE LOWER ATTACHING BOLTS WERE FOUND LOOSE.  SUBMITTER SUSPECTED THE C	RACK RESULTED DUE TO LOOSENING OF THE LOWER ATTACHING BOLTS.  THESE BOLTS SHOULD BE INSPECTED FOR PROPER TORQUE EVERY 10	0 HOURS OR ANNUAL INSPECTION.   AIRCRAFT TT:  11,971.1 HOURS. (X)		1	H	7	1 	3O			 	3A17    					 
2000082200013	20000822	00013	CE  	2000	8	22	20000601SH008    	1	20000601	G	5713		STRINGER        			BEECH 	200   	B200        	1152922	CE  										TAIL	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	86DD	6865 				BB1171				COMPLIED WITH AD 93-25-07 IAW SD 2472.  NR 10 STRINGER ON THE LEFT SIDE WAS FOUND CRACKED.  TOTAL LANDINGS: 7,189.  (X)						1	L	7	2 	4T			 	A24CE   					 
2000062000137	20000620	00137		2000	6	20	20000601SH009    	4	20000522	G	3120	S17111	PRESSURE SWITCH 			CESSNA	150   	152         	2071835	CE  										CABIN	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	65468	2158 				15281569				DURING ROUTINE MAINTENANCE, OIL WAS FOUND ON RIGHT SIDE INBOARD RUDDER PEDAL.  FURTHER INVESTIGATION SHOWED OIL WEEPING 	FROM AROUND CRIMPED HOUSING OF HOURMETER PRESSURE SWITCH.  THIS PROBLEM COULD LEAD TO ERRONEOUS READINGS ON OIL PRESSURE	 GAUGE AND BURNS TO PASSENGERS FEET AND LEGS IF SWITCH WAS TO RUPTURE.  SUBMITTER RECOMMENDED CLOSER INSPECTIONS OF THES	E SWITCHES DURING INSPECTIONS AND ROUTINE MAINTENANCE.  (X)			1	H	7	1 	3O			NT	3A19    					 
2001020100002	20010201	00002	WP  	2001	2	1	20000601SH010    	1	20000517	G	6210	5320003	BLADE           			HILLER	UH12  	UH12E       	4360122	WP  										MAIN ROTOR	DELAMINATED     	B			KQTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	144HA	246  				HA3044				BLADE WAS RETURNED TO BLADE SHOP FOR REPAIR OF SKIN TO TRAILING EDGE DISBOND.  UPON INSPECTION, APPEARS THAT CLEANING AN	D/OR METAL PREP PROCESS FAILED CAUSING SKIN AND TRAILING EDGE TO SEPARATE.  SUBMITTER RECOMMENDED INSPECTING ALL BLADES 	IN METAL PREP BATCH FOR POSSIBLE SKIN SEPARATIONS IN FUTURE.  (X)				1	G	7	1 	3O			 	4H11    					 
2001020200002	20010202	00002	SW  	2001	2	2	20000601SH012    	1	20000322	G	3411	206070895033	STATIC LINE     			BELL  	206   	206B        	1181511	SW  										PITOT SYS	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	57499					3086				PILOT REPORTED AIRSPEED INDICATED LOW AT CRUISE. FOUND THAT LANDING LIGHT CHAFED A HOLE IN THE PITOT STATIC LINE (IPC RE	F:  FIG 95-7, PAGE 28 ITEM 16).  REPLACED TUBE AND REPOSITIONED AS NOT TO CHAFE. (X)					1	G	7	1 	3U			 	H2SW    					 
2000062000138	20000620	00138	SW  	2000	6	20	20000601SH013    	1	20000510	G	2711	2709	HINGE           			BBAVIA	7     	7GCAA       	21101N8	SW  										 BOTTOM TAB	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2665Z	1877 				35178				DURING WINDS OF APPROX 40 KNOTS, AILERON HINGE THAT ATTACHES TO CONTROL ROD TORE LOOSE FROM INBOARD END OF AILERON. FURT	HER INVESTIGATION REVEALED THAT HINGE TABS, TOP AND BOTTOM, THAT ARE RIVETED ONTO SPAR CAPS HAD BROKEN PREVIOUSLY.  THIS	 EVIDENCED BY THE STEEL  HINGE BEING  RUSTED AT THE BREAK.  THIS CONDITION IS NOT READILY NOTICED DURING ROUTINE INSPECT	ION DUE TO  THE FACT THE HINGE TAPS ARE COVERED WITH FABRIC AND FINISH. (X)			1	H	7	1 	3O			 	A759    					 
2000062000139	20000620	00139	GL  	2000	6	20	20000601SH017    	2	20000503	G	7250	FABT8851	TURBINE         								GE    	CF6   	CF6*        	30020	GL  					STACKING BOLTS	MISINSTALLED    	B			SK33	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			3124 				327			CF6-6 ENGINE 451-327 WAS PULLED FOR OVERHAUL AT GE.  FOUND TO BE MISSING THE LOCKWIRES FROM THE STACKING BOLTS TO THE TU	RBINE IN EACH OF 8 POSITIONS.  SUBMITTER STATED FURTHER INVESTIGATION FOUND STACKING CALCULATION ERROR ON THIS AND 26 OT	HER CF6-6 TMF ASSEMBLIES.  (X)									4	F			E23EA				 
2000062000140	20000620	00140	CE  	2000	6	20	20000601SH018    	1	20000425	G	2810	993800007	FUEL CELL       			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A27      	52043	EA  					RT NACELLE	PUNCTURED       	A			TIMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	99GH	33344				U112				RIGHT NACELLE FUEL CELL FOUND LEAKING FUEL.  INSPECTION REVEALED A PUNCTURE IN THE SIDE OF THE CELL CAUSED BY A TANK HAN	GER THAT HAD BECOME DISLODGED FROM ITS ORIGINAL LOCATION.  THE HANGER PROTRUDING CLIP HAD REPOSITIONED TOWARD THE TANK L	INER CAUSING THE TANK TO BE PUNCTURED AS THE FUEL LEVEL INCREASED.  DURING INITIAL INSTALL OF FUEL CELL, SUBMITTER STATE	D CARE SHOULD BE TAKEN TO VERIFY PROPER SEATING OF THE CELL HANGERS TO PREVENT THIS FROM RECURRING.  (CELL DATED 1979 AN	D OTHERWISE APPEARED IN GOOD CONDITION).  (X)		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000062000141	20000620	00141	EA  	2000	6	20	20000601SH019    	2	20000518	G	7414	M3333	IMPULSE COUPLING	SLICK       		PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					PAWL-PLATE RIVET	DESTROYED       	B			JM2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	323CA	309  			96051744	327740026	L1741148A			PAWL-PLATE RIVETS  BROKE.  IMPULSE HOUSING PAWL STEPS BROKEN OFF.  IMPULSE COUPLING FAILED AT START-UP.  CAUSE UNKNOWN. 	 (X)					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000062000142	20000620	00142	CE  	2000	6	20	20000601SH020    	1	20000515	G	5720	0001101122	GUSSET          			BEECH 	90    	C90         	1152913	CE  										BS 160.00 WS 110	CRACKED         	B			UA2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	16					LJ893				RIGHT LOWER OUTBOARD WING HAD CRACK IN DOUBLER AT FORWARD ATTACH POINT AND GUSSET CRACKED AT APPROX BS 160.00 AND WS 110	.11.  TWO CRACKS IN WING SKIN RIGHT WING 4 INCHES BEHIND FORWARD SPAR JUST AFT OF FORWARD WING BOLT ON TOP SIDE OF WING.	  TWO CRACKS IN WING SKIN ON LEFT WING JUST AFT OF FORWARD SPAR BEHIND FORWARD WING BOLT ON TOP SIDE OF WING.  (X)				1	L	7	2 	3T			 	3A20    					 
2000062000155	20000620	00155	CE  	2000	6	20	20000601SH022    	1	20000601	G	5740	50110231	FITTING         			CESSNA	414   	414A        	2075907	CE  										LEFT AFT	CORRODED        	B			GN1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6672C	6667 				414A0053				ON ANNUAL INSPECTION, LT WING AFT SPAR WING ATTACH FITTINGS, PN''S 5011023-1 AND 5-11024-1, INTERGRANULAR CORROSION FOUN	D IN AREAS READILY VISIBLE  EACH AREA OF CORROSION APPROXIMATELY 1.50 SQUARE INCH AND APPROXIMATELY .1250 INCH DEEP.  NO	 IDEA ON SPECIFIC CAUSE.  NOT IN DIRECT AREA OF EXHAUST.  SUBMITTER COMMENDED DETAILED VISUAL INSPECTION TO PREVENT RECU	RRANCE.  FITTINGS CHANGED WITH NEW PARTS.  (X)			1	L	7	2 	3O			 	A7CE    					 
2000071200009	20000712	00009	NM  	2000	7	12	20000601SH027    	1	20000314	G	6710	900C2010214101	LINK ROD        			DOUG  	MD900 	MD900       	3027375	NM  										M/R CONTROL	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	352  				90000012				PITCH LINK ASSEMBLY WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)						1	G	7	2 	3U			NC	H19NM   					 
2000071200010	20000712	00010	NM  	2000	7	12	20000601SH028    	1	20000306	G	6322	900D1400526101	BLOWER          			DOUG  	MD900 	MD900       	3027375	NM  										DRIVE UNIT	LEAKING         	A			R7MA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	901CF	217  				90000012				BLOWER DRIVE ASSEMBLY LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			NC	H19NM   					 
2000071200011	20000712	00011	NM  	2000	7	12	20000601SH029    	1	20000314	G	6230	900C2010183107	SCISSORS        			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	LOOSE           	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	864  				90000012				LINK ASSY, DRIVE, SCISSORS HAD EXCESSIVE PLAY IN JOINT AREA. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001020500061	20010205	00061	SO  	2001	2	5	20000602SH002    	2	20000512	G	8520	649134	CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	UNSERVICEABLE   	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	2216F	66   				U20606504	814988R			PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001020500085	20010205	00085	SO  	2001	2	5	20000602SH003    	2	20000512	G	8520	649141	CRANKSHAFT      			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE	UNSERVICEABLE   	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4UA	89   				32851	833782R			PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	5A6     	E273				 
2001020500086	20010205	00086	SO  	2001	2	5	20000602SH004    	2	20000508	G	8520	649134	CRANKSHAFT      			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	UNSERVICEABLE   	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4447Z	193  				U2061479	574357			PER TELEDYNE CONTINENTAL MOTORS MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000062000156	20000620	00156	SO  	2000	6	20	20000602SH005    	2	20000508	G	8520	649134	CRANKSHAFT      			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  					ENGINE	DAMAGED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9028C	1    				31076	049406R			PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS. (X)						1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2001020500176	20010205	00176	SO  	2001	2	5	20000602SH006    	2	20000502	G	8520	649134	CRANKSHAFT      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					ENGINE	UNSERVICEABLE   	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	6688H	136  				18503335	1580456D			PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2001020500087	20010205	00087	CE  	2001	2	5	20000602SH007    	1	20000419	G	2170		MOTOR           			BEECH 	200   	B200        	1152922	CE  										CONDENSOR	INOPERATIVE     	B			DINR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	260G	738  				BB1525				CONDENSER BLOWER MOTOR NO GOOD.						1	L	7	2 	4T			 	A24CE   					 
2001020200003	20010202	00003	SW  	2001	2	2	20000602SH009    	1	20000523	G	7722	407375001105	INDICATOR       			BELL  	407   	407         	       	SW  										MGT	MALFUNCTIONED   	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407SD	510  				53330				H.A.S. REPLACED WITH NEW MGT INDICATOR FROM BELL HELICOPTER.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200004	20010202	00004	SW  	2001	2	2	20000602SH010    	1	20000523	G	7933	407375004101	INDICATOR       			BELL  	407   	407         	       	SW  										OIL PRESS TEMP	MALFUNCTIONED   	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	407SD	510  				53330				H.A.S. REPLACED WITH NEW OIL PRESSURE  TEMPERATURE INDICATOR FROM BELL HELICOPTER. (X)						1	G	7	1 	3U			O	H2SW    					 
2001030100002	20010301	00002	SW  	2001	3	1	20000602SH011    	1	20000519	G	6220	407010150105A	FRAHM           			BELL  	407   	407         	       	SW  										MAIN ROTOR HEAD	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	98VG	425  				53171				SPRING ROTATED RUBBER BUMPER  MISSING FROM MAIN ROTOR HEAD.  H.A.S. REPLACED WITH NEW FRAHM FROM BELL HELICOPTER.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020500088	20010205	00088	WP  	2001	2	5	20000602SH012    	1	20000525	G	3246	152059	WHEEL           			DOUG  	DC8   	DC8*        	       	WP  										MLG	CRACKED         	B			INWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										NDT INSPECTION SHOWED CRACK INDICATIONS AT SPOKE AREA.  (X)						2	L	7	4 	4J			F	4A25    					 
2001011601506	20010116	01506	EU  	2001	1	16	20000605SH001    	1	20000121	G	6510	593404	BEARING         			SNIAS 	350   	AS350B3     	8680954	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	400  				3128				BEARING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001011601300	20010116	01300	EU  	2001	1	16	20000605SH002    	1	20000420	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B3     	8680954	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	524  				3128				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)						1	G	7	1 	3U			 	H9EU    					 
2001011601301	20010116	01301	EU  	2001	1	16	20000605SH003    	1	20000420	G	6220	117775P	BALL JOINT      			SNIAS 	350   	AS350B3     	8680954	EU  										STARFLEX	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	524  				3128				TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001011601302	20010116	01302	EU  	2001	1	16	20000605SH004    	1	20000420	G	6720	350A33214501	CONTROL ROD     			SNIAS 	350   	AS350B3     	8680954	EU  										T/R PITCH	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	47MA	524  				3129				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001011601303	20010116	01303	EU  	2001	1	16	20000605SH005    	1	20000506	G	7921	1184961	COOLER          			SNIAS 	350   	AS350B3     	8680954	EU  										OIL SYSTEM	LEAKING         	A			R7MA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	104LN	761  				3134				OIL COOLER LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001011601304	20010116	01304	EU  	2001	1	16	20000605SH006    	1	20000205	G	6710	350A33214501	CONTROL ROD     			SNIAS 	350   	AS350B3     	8680954	EU  										T/R PITCH	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	104LN	33   				3134				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900074	20010129	00074	EU  	2001	1	29	20000605SH007    	1	20000122	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B3     	8680954	EU  										PITCH CONTROL	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	104LN	488  				3134				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900076	20010129	00076	EU  	2001	1	29	20000605SH009    	1	20000405	G	6520	350A33215001	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R ROD END	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	101LN	692  				3038				ROD END WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900077	20010129	00077	EU  	2001	1	29	20000605SH010    	1	20000330	G	6220	117775P	BALL JOINT      			SNIAS 	350   	AS350B2     	8680813	EU  										STARFLEX	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	101LN	145  				3038				STARFLEX BALL JOINT - TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900078	20010129	00078	EU  	2001	1	29	20000605SH011    	1	20000226	G	7931	350A67402301AA	CONNECTOR       			SNIAS 	350   	AS350B2     	8680813	EU  										OIL PRESS IND	DAMAGED         	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	102LN	605  				3065				HARNESS INDICATOR, ENGINE OIL PRESSURE HAD INTERNAL SHORT.  ENGINE OIL PRESSURE FLUCTUATED.  REPLACED WITH NEW UNIT, COR	RECTED PROBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001012900079	20010129	00079	EU  	2001	1	29	20000605SH012    	1	20000211	G	6520	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	102LN	586  				3065				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900080	20010129	00080	EU  	2001	1	29	20000605SH013    	1	20000108	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	102LN	543  				3065				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900081	20010129	00081	EU  	2001	1	29	20000605SH014    	1	20000329	G	6520	350A33200406	SPIDER          			SNIAS 	350   	AS350D      	8680803	EU  										TAIL ROTOR	STUCK           	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	350RM	48   				1024				PITCH CHANGE, SPIDER ASSEMBLY - STICKS ON PEDAL MOUNT.  BEARING HAS EXCESS PLAY.  REPLACED WITH NEW UNIT, CORRECTED PROB	LEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001012900082	20010129	00082	EU  	2001	1	29	20000605SH015    	1	20000326	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5771C	621  				1369				LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900083	20010129	00083	EU  	2001	1	29	20000605SH016    	1	20000512	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350D1     	8680804	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	57731	317  				1434				LAMINATED TAIL BEARING, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900084	20010129	00084	EU  	2001	1	29	20000605SH017    	1	20000130	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	6099P	599  				2818				LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900085	20010129	00085	EU  	2001	1	29	20000605SH018    	1	20000301	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	96LG	525  				2817				LAMINATED TAIL BEARING, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900086	20010129	00086	EU  	2001	1	29	20000605SH019    	1	20000207	G	6220	117775P	BALL JOINT      			SNIAS 	350   	AS350B2     	8680813	EU  										STARFLEX	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	96LG	817  				2817				BALL JOINT, STARFLEX - TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900087	20010129	00087	EU  	2001	1	29	20000605SH020    	1	20000207	G	6220	126891P	BALL JOINT      			SNIAS 	350   	AS350B2     	8680813	EU  										STARFLEX	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	96LG	708  				2817				BALL JOINT, RIGHT THREAD, WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900088	20010129	00088	EU  	2001	1	29	20000605SH021    	1	20000301	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	96LG	725  				2817				LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900057	20010129	00057	EU  	2001	1	29	20000605SH022    	1	20000130	G	6420	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	93LG	349  				2654				LAMINATED TAIL BEARING - ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900089	20010129	00089	EU  	2001	1	29	20000605SH023    	1	20000228	G	6420	704A336333116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	94LG	647  				2728				LAMINATED TAIL BEARING - ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900090	20010129	00090	EU  	2001	1	29	20000605SH024    	1	20000127	G	7714	614764021	TACHOMETER      			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INTERMITTENT    	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	94LG	158  				2728				TACHOMETER INDICATOR INOPERATIVE.  NR NEEDLE DROPS OFF TO 250 RPM INTERMITTENTLY.  REPLACED WITH NEW UNIT, CORRECTED PRO	BLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2000062300050	20000623	00050	EU  	2000	6	23	20000605SH025    	1	20000228	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	94LG	647  				2728				LAMINATED HINGE - ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900091	20010129	00091	EU  	2001	1	29	20000605SH026    	1	20000430	G	6410	704A33633171	LAMINATED HINGE 			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	427  				2575				LAMINATED HINGE, ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000061600413	20000616	00413	SO  	2000	6	16	20000605SH030    	1	20000605	G	5102		ENVELOPE        			BALWKS	FIREFY	FIREFLY11   	1050125	SO  										FABRIC PNLS	DETERIORATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3288H					F11B001				EXCESSIVE AND PREMATURE DETERIORATION OF FABRIC PANELS AT GORE TAPE SEAM.  GORE TAPE MATERIAL IS STIFF WITH SHARP EDGES 	AND CUTS INTO FABRIC PANELS WHERE PANELS OVERLAP TAPE APPROXIMATELY 1 INCH FROM PANEL EDGE.  IT APPEARED THE AIRCRAFT MA	NUFACTURER HAD CHANGED THE GORE TAPE MATERIAL FROM A SOFTER MORE PLIABLE TAPE TO A STIFF TAPE WITH SHARP EDGES.  (X)				1	B	0	0 	  			 	A14SO   					 
2000061300423	20000613	00423		2000	6	13	20000607SH001    	4	20000522	G	6122	B20268	FLYWEIGHT       	MCAULY      																GOV	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					74134					RELEVANT CRACK INDICATION ON BASE OF FLYWEIGHT DISC.  (X)																			 
2000061300424	20000613	00424		2000	6	13	20000607SH002    	4	20000517	G	6122	C20908	FLYWEIGHT       	MCAULY      																	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					781399					RELEVANT CRACK INDICATION ON THE BASE OF FLYWEIGHT DISC.  (X)																			 
2000061600372	20000616	00372		2000	6	16	20000607SH003    	4	20000516	G	6122	213908	FLYWEIGHT       	MCAULY      																	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					771223					RELEVANT CRACK INDICATION ON THE BASE OF FLYWEIGHT DISC.  (X)																			 
2000061400300	20000614	00300	GL  	2000	6	14	20000607SH004    	2	20000324	G	7322		FUEL CONTROL    			AMTR  	KR2   	KR2         	       	GL  	AMTRVW	VW    	VW2200      	99999	GL  						FAILED          	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	07	73BP					3634				FAILURE OF MAIN MIXTURE ADJUSTMENT NEEDLE LOCKING DEVICE DURING FLIGHT CAUSING MIXTURE TO GO RICH DRAMATICALLY INCREASIN	G FUEL CONSUMPTION WHICH LED TO FUEL STARVATION AND A FORCED LANDING.   (X)					1	L	7	1 	3O	3	O	 	EXPA1L71	EXP3O				 
2000061300425	20000613	00425	SO  	2000	6	13	20000607SH005    	1	20000525	G	3240	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1 AND 2	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1271 			1477A					BRAKE ASSEMBLY, PN 2-1585-R, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED UNEV	EN WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.     NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSE	MBLY.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2000061300426	20000613	00426	SO  	2000	6	13	20000607SH006    	1	20000525	G	3240	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1395 			0112A					BRAKE ASSEMBLY, PN 2-1585-R, FAILED PREMATURELY.  NR 1 STATOR WARPED BEYOND SERVICEABLE LIMITS.  SUBMITTER STATED THIS I	S A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2000062000220	20000620	00220	EU  	2000	6	20	20000607SH009    	1	20000516	G	5260	14860011	STEP            			AEROSP	SA365 	AS365N2     	8680815	EU  										A/C ENTRANCE	INOPERATIVE     	A				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM					6429				STEP ACTUATOR INOPERATIVE, INTERMITTENT.  REMOVED AND REPLACED.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2000062900094	20000629	00094	NE  	2000	6	29	20000607SH010    	2	20000509	G	7314	9A2045	PUMP            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					A/C FUEL SYSTEM	INTERMITTENT    	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	761  				EC1350054				UNIT OPERATES INTERMITTENTLY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2000062000221	20000620	00221	EU  	2000	6	20	20000607SH011    	1	20000229	G	6420	1053170023	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	378  				7527				BEARING WORN BEYOND SERVICEABLE LIMITS.  CORE SCRAPPED LOCALLY BY MECHANIC.  REPLACED 2 EACH WITH NEW UNITS, CORRECTED P	ROBLEM.  (X)					1	G	7	2 	3U			NC	H13EU   					 
2000062000222	20000620	00222	EU  	2000	6	20	20000607SH012    	1	20000331	G	6420	1053170023	BEARING         			BOLKMS	117   	BK117A4     	5626017	EU  										TAIL ROTOR	WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	446  				7127				BEARING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH2 EACH  NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062700130	20000627	00130	EU  	2000	6	27	20000607SH013    	1	20000214	G	6320	IPT20RT1100080G	TRANSMITTER     			BOLKMS	117   	BK117B1     	5626012	EU  										M/R TRANSMISSION	FLUCTUATES      	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	10UM	312  				7231				PRESSURE TRANSMITTER UNIT CAUSES PRESSURE GAUGE TO FLUCTUATE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000061300428	20000613	00428	EU  	2000	6	13	20000607SH014    	1	20000410	G	6410	134616P	BUSHING         			BOLKMS	117   	BK117B1     	5626012	EU  											WORN            	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117BK	551  				7229				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062300073	20000623	00073	EU  	2000	6	23	20000607SH015    	1	20000410	G	6410	134617P	BUSHING         			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	UNSERVICEABLE   	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117BK	551  				7229				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062300074	20000623	00074	EU  	2000	6	23	20000607SH016    	1	20000410	G	6420	1053170023	BEARING         			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL  ROTOR	UNSERVICEABLE   	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117BK	551  				7229				BEARING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062700131	20000627	00131	EU  	2000	6	27	20000608SH024    	1	20000601	G	6520	350A33200406	SPIDER          			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	UNDERTORQUED    	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	147BH	908  			M577	1273				AFTER THE LAST FLIGHT OF THE DAY, INSP REVEALED TAIL ROTOR SPIDER ASSY LOSS OF TORQUE AT CASTELLATED NUT SECURING SPIDER	 ASSY. THIS FINDING PROMPTED REMOVAL AND REPLACEMENT OF SPIDER ASSY WITH SERVICEABLE COMPONENT.  SPIDER ASSY P/N 350A33.	2004.06.  TT IN SERVICE 186.6 FLYING HRS SINCE -06 MODIFICATION C/W BY AMERICAN EUROCOPTER.  POSSIBLE CAUSE OF LOSS OF T	ORQUE, UNKNOWN.  RECOMMENDATION TO PREVENT RECURRENCE, INCREASE TORQUE VALVE AT CASTELLATION.  (X)			1	G	7	1 	3U			 	H9EU    					 
2000062700132	20000627	00132	EU  	2000	6	27	20000608SH025    	1	20000329	G	7712	G555674	TRANSDUCER      			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	INOPERATIVE     	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	625MB	376  				7108				PRESSURE TRANSDUCER UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062300075	20000623	00075	EU  	2000	6	23	20000608SH027    	1	20000223	G	6410	134617P	BUSHING         			BOLKMS	117   	BK117A3     	5626015	EU  										TAIL ROTOR	WORN            	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV	464  				7089				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062300076	20000623	00076	EU  	2000	6	23	20000608SH028    	1	20000223	G	6410	134616P	BUSHING         			BOLKMS	117   	BK117A3     	5626015	EU  										TAIRL ROTOR	WORN            	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV	464  				7089				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062300077	20000623	00077	EU  	2000	6	23	20000608SH029    	1	20000328	G	6410	134617P	BUSHING         			BOLKMS	117   	BK117A4     	5626017	EU  										TAIL ROTOR	WORN            	B			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	586BH	107  				7129				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062300078	20000623	00078	EU  	2000	6	23	20000608SH030    	1	20000328	G	6410	134616P	BUSHING         			BOLKMS	117   	BK117A4     	5626017	EU  										TAILROTOR	WORN            	B			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	586BH	107  				7129				BUSHING TEFLON LINERS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000062600107	20000626	00107	EU  	2000	6	26	20000609SH001    	1	20000524	G	6410	1053170023	BEARING         			BOLKMS	117   	BK117A4     	5626017	EU  										TAIL ROTOR	WORN            	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	586BH	95   				7129				BEARING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM. (X)						1	G	7	2 	3U			 	H13EU   					 
2000062600108	20000626	00108		2000	6	26	20000609SH002    	4	20000316	G	3423	40205773	COMPASS         			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT DASH	INOPERATIVE     	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	414  				7527				COMPASS UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2000062600109	20000626	00109	EU  	2000	6	26	20000609SH003    	1	20000229	G	5244	1173084103	HINGE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R FAIRING	WORN            	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	509  				7527				HINGE WORN BEYOND SERVICEABLE LIMITS.  CORE SCRAPPED LOCALLY BY MECHANIC.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (	X)					1	G	7	2 	3U			NC	H13EU   					 
2000062600110	20000626	00110	EU  	2000	6	26	20000609SH004    	1	20000307	G	2497	117188001	WIRE            			BOLKMS	BK117 	BK117C1     	5626025	EU  										DC SYSTEM	WORN            	A				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	390  				7527				CABLE WORN BEYOND SERVICEABLE LIMITS.  CORE SCRAPPED LOCALLY BY MECHANIC. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X	)					1	G	7	2 	3U			NC	H13EU   					 
2000062700133	20000627	00133	EU  	2000	6	27	20000609SH006    	1	20000317	G	5210	1172461611	FITTING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										PILOT DOOR	WORN            	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	415  				7527				FITTING ASSY (UPPER) WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2000061300457	20000613	00457	CE  	2000	6	13	20000609SH009    	1	20000427	G	2140	51A45	COMBUSTION CHAMB	JANITROL    		BEECH 	95    	B95         	1153404	CE  											DEACTIVATED     	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	802QD				4600128	TD432				JANITROL COMBUSTION HEAD ASSY, PN 51A45, ON HEATER ASSY, PN D83A28, HAD A ONE INCH DIAMETER  RUST HOLE. THIS HOLE WAS CA	USED BY AGE, DETERIORATION AND USE. THE HEATER HAD BEEN IN OPERATION SINCE 1960.  SUBMITTER RECOMMENDED A RECURRING ADVI	SORY DIRECTIVE FOR AGING BEECH BARON MODELS 55, A55, B55, AND B55A, AND BEECH TRAVELAIR MODELS 95, B95, B95A, D95A, AND 	E95 THAT CORPORATE THE JANITROL 83A28 SERIES COMBUSTION ACFT HEATERS.  THERE IS A REGULARLY SCHEDULED MAINTENANCE PROCED	URE CALLED OUT IN THE 83A28 SERIES JANITROL OVERHAUL MANUAL.  (X)		1	L	7	2 	3O			 	3A16    					 
2000061300458	20000613	00458	CE  	2000	6	13	20000609SH010    	1	20000518	G	2435	2304818	STARTER GEN     			BEECH 	99    	99          	1154002	CE  											INOPERATIVE     	A			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	199GL					U15				OVERHAULED STARTER/GENERATOR.  INSTALLED ON AIRCRAFT, WAS FOUND DEFECTIVE.  ITEM WAS REMOVED FROM AIRCRAFT AND RETURNED.	  (X)					1	L	7	2 	3T			 	A14CE   					 
2000061300459	20000613	00459	SO  	2000	6	13	20000609SH011    	1	20000514	G	2820	37756003	SWITCH          	ALCO        		PIPER 	PA44  	PA44180T    	7104404	SO  	LYC   	O360  	TO360E1A6   	41514	EA  					INTERNAL OF SW	SHORTED         	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			NE	03	2913U	1350 				448107057	617173			LEFT ENGINE IN-FLIGHT ROUGH AND SMOKE.  FOUND ELECTRICAL FUEL PRIMER SOLENOID ACTIVATED AND TIME MASTER SWITCH ON.  PUSH	 TO PRIME SWITCH AT COCKPIT INSTRUMENT PANEL SHORTED TO A CONTINUOUS CLOSED CIRCUIT.  REPLACED DEFECTIVE SWITCH WITH SAM	E PART NUMBER.  PROBLEM REPAIRED.  (X)				1	L	7	2 	3O	3	O	 	A19SO   	E26EA				 
2000061300460	20000613	00460	EU  	2000	6	13	20000609SH012    	1	20000531	G	2913	S40	DRIVE GEAR      			SNIAS 	350   	AS350B2     	8680813	EU  										HYD PUMP DRIVE	FAILED          	A				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	09	350JG	370  			90191088	3232				HYDRAULIC PUMP FAILED IN-FLIGHT.  PRECAUTIONARY LANDING COMPLETED.  INSP REVEALED DRIVE SPLINES AT HYD DRIVE COUPLING (F	EMALE SPLINES), AND THE DRIVE SPLINES AT THE HYD PUMP (MALE SPLINES) WERE PREMATURELY WORN.  SPLINE ENGAGEMENT INSUFFICI	ENT FOR DRIVE DEMAND.  HYD PUMP DRIVE SPLINES INSPECTED AND GREASED AT BASIC INSP.  500 FLYING HRS OR 15 MONTHS BY CALEN	DER.  POSSIBLE CAUSE OF FAILURE UNKNOWN.  RECOMMENDED TO PREVENT RECURRENCE, INSPECT HYD DRIVE SPLINES WHEN ACFT IS DELI	VERED NEW, AND EACH 100-HOUR AIRFRAME INSP INTERVAL UP TO THE 500-HR INSP FOR A TREND ANALYSIS. ENCOUNTER PREMATURE WEAR	 ON DRIVE SPLINES,  (X)	1	G	7	1 	3U			 	H9EU    					 
2000061300461	20000613	00461	NE  	2000	6	13	20000609SH013    	2	20000504	G	8530		CYLINDER HEAD   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					NUMBER 7	CRACKED         	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NM	01	357AS		694  			357	P5844			UPON CLIMB-OUT AFTER TAKEOFF, PILOT REPORTED ROUGH RUNNING ENGINE AND A LOSS OF POWER.  PILOT STARTED TURNING BACK FOR A	IRPORT AND DECIDED NOT ENOUGH POWER AND LANDED SAFELY IN A FARMER''S FIELD.  DISCOVERED, NR 7 CYLINDER HEAD CRACKED FROM	 ONE SPARK PLUG HOLE ALL THE WAY TO THE OTHER.  MAINTENANCE SUGGESTED ALONG WITH A VISUAL INSPECTION OF CYLINDER AND WHI	LE DOING A COMPRESSION CHECK, ALSO DO A SOAP AND WATER CHECK FOR CRACKS WHEN AIR IS PUT TO THE CYLINDER.  (X)			1	H	7	1 	3R	3	R	 	A815    	5E2				 
2000061300462	20000613	00462	SO  	2000	6	13	20000609SH014    	1	20000426	G	5730	6208700	SKIN            			PIPER 	PA32  	PA32300     	7103212	SO  										INBD/OTBD EDGES	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4114W	3372 				3240177				LEFT WING-SKIN ASSY-TOP, INBOARD ROOT HAD NUMEROUS CRACKS AT BOTH ENDS OF BOTH STRINGERS AND FOUND ONE STRINGER INBOARD 	END CRACKED.  THIS SKIN, AFTER REMOVAL, WAS FOUND HAVING NO REINFORCEMENT DOUBLERS AT THE ENDS OF BOTH STRINGERS. THE NE	W SKIN HAS THE REINFORCEMENT DOUBLERS AND THIS SHOULD PREVENT CRACKING.  SUBMITTER RECOMMENEDED THAT ALL PIPERS WITH SAM	E WING DESIGN SHOULD BE CHECKED THAT THE DOUBLERS ARE INSTALLED.  (X)			1	L	7	1 	3O			 	A3SO    					 
2000061300463	20000613	00463	SO  	2000	6	13	20000609SH015    	1	20000519	G	2700		CONTROL CABLE   			PIPER 	PA46  	PA46350P    	7104602	SO  										FLIGHT CONTROL	BINDING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	41676	18   				4636268				PILOT NOTICED FLIGHT CONTROLS GETTING STIFF IN ROLL DIRECTION.  INSPECTED ENTIRE SYSTEM FOR PROPER ROUTING OF CABLES AND	 CORRECT TENSION ON PRIMARILY AND AUTOPILOT CABLES.  NO DISCREPANCY NOTED.  WENT THROUGH ENTIRE SYSTEM AND LUBED ALL ROT	ATIONAL POINTS UNTIL CONTROLS FREED UP.  POSSIBLY CAUSED BY LACK OF LUBRICATION OF FACTORY.  AIRCRAFT ONLY HAD 18 HOURS 	SINCE NEW.   (X)			1	L	7	1 	3O			RT	A25SO   					 
2000061300516	20000613	00516	SW  	2000	6	13	20000609SH017    	1	20000515	G	2721	B2085400053	BEARING SUPPORT 			GULSTM	690TP 	695A        	7630519	SW  										RUDDER PEDAL	LACK OF LUBE    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	508AB	5792 				96034				RUDDER PEDAL BEARINGS FAILED DUE TO LACK OF LUBRICATION.  NO WAY TO LUBE WITHOUT COMPLETE DISASSEMBLY.  BEARINGS CUT HAL	F WAY THROUGH RUDDER PEDAL TUBES, TUBES ARE ONLY .0625 INCH THICK.  FOUND DURING GRAND RENAISSANCE PROGRAM.  SUBMITTER S	TATED NEED WAY TO LUBE RUDDER PEDAL TUBE BEARINGS DURING 100-HOUR INSPECTION OR AT LEAST EVERY 1,000 HOURS.  REPLACED TU	BES AND BEARINGS.  (X)			1	H	7	2 	4T			 	2A4     					 
2000061300517	20000613	00517	CE  	2000	6	13	20000609SH018    	1	20000519	G	7120	503403034	MOUNT           	CESSNA      		CESSNA	421   	421C        	2076016	CE  										LT ENGINE BAY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	5491G	5233 				421C0238				DURING ANNUAL INSPECTION, FOUND ONE INCH CRACK LEFT SIDE, AFT CORNER, LEFT ENGINE BAY,  CANTED BULKHEAD TOP CAP.  EXHAUS	T CORROSION IN THIS AREA WAS NOTED.  PER AD 2000-01-16 EXHAUST SYSTEM, FOUND CRACKS ON EXHAUST COMPONENTS ALSO IN THIS A	REA THAT MAY HAVE CONTRIBUTED TO THIS FAILURE. (X)				1	L	7	2 	3O			 	A7CE    					 
2000061300518	20000613	00518	CE  	2000	6	13	20000609SH019    	1	20000307	G	2410	AN743A	BOLT            	CESSNA      		CESSNA	172   	172RG       	2072438	CE  										ALTERNATOR MOUNT	LOOSE           	B			PP4R	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SO	05	5493R					172RG0064				AIRCRAFT EXPERIENCED AN IN-FLIGHT ELECTRICAL FAILURE.  UPON LANDING, ALTERNATOR WAS FOUND HANGING FROM THE BELT TENSION 	BRACKET.  THE PRIMARY MOUNT BOLT, AN7-43A, WAS FOUND IN THE LOWER COWLING.  WHEN THE MOUNT BOLT FELL OUT, THE COOLING FA	N CONTACTED THE ENGINE CASE AND STOPPED THE ALTERNATOR.  WITH THE ENGINE RUNNING AND THE ALTERNATOR LOCKED UP, THE ALTER	NATOR BELT BURNED UP ON THE ALTERNATOR PULLEY.  ALTERNATOR BELT HAD RECENTLY BEEN TIGHTENED.   (X)			1	H	7	1 	3O			 	3A17    					 
2000061600329	20000616	00329	CE  	2000	6	16	20000609SH022    	1	20000524	G	3244	8293P00727	TIRE            			MTSBSI	MU2   	MU2B36A     	5780413	CE  										RIGHT MAIN	SEPARATED       	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	15	61BA		13   			729SA				THE SUBMITTER STATED, TIRE REPAIRED AND RECAPPED BY AERO WHEEL & BRAKE SERVICE CORP., NR U8SR971J. TIRE WAS INSTALLED ON	 THIS AIRCRAFT ON 4-15-00 AND HAD 13.2 HRS TT WITH 13 LANDINGS TOTAL.  DURING LANDING ROLLOUT, A 2.5 INCH WIDE BAND OF T	READ SEPARATED FROM THE CENTER AND FULL CIRCUMFERENCE OF THE TIRE RESULTING IN DAMAGE TO THE AFT MAIN GEAR DOOR WHICH WI	LL REQUIRE REPLACEMENT OF THE DOOR AND MINOR AREA OF DAMAGE TO THE LOWER SURFACE OF THE INBOARD WING, APPROXIMATELY 3 IN	CHES IN DIAMETER. NOTE: TIRE DID NOT DEFLATE.  (X)		1	H	7	2 	3T			 	A10SW   					 
2000062700134	20000627	00134	EU  	2000	6	27	20000609SH025    	1	20000519	G	6220	E1T302301	FREQ ADAPTER    			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	B			B3OR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204Y	483  				3101				DURING 500-HOUR INSPECTION, FOUND YELLOW BLADE FREQUENCY ADAPTER CRACKED AT EDGE OF KEVLAR MATING SURFACE.  THIS IS FIRS	T OCCURRENCE OF THIS TYPE ON THE 3 AIRCRAFT OF SAME TYPE OPERATED A TOTAL OF 1200 HOURS.  NO REASON FOUND FOR DEFECT.  (	X)				1	G	7	1 	3U			 	H9EU    					 
2000061600330	20000616	00330	SO  	2000	6	16	20000609SH026    	1	20000523	G	3230	4204200	BRACE           	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  										INSIDE RADIUS	CRACKED         	I			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	59764	15290				317652037				DURING A DETAILED INSPECTION OF THE LANDING GEAR, THIS PART WAS FOUND TO HAVE A SMALL CRACK.  THIS PART CONNECTS THE HYD	RAULIC ACTUATOR TO THE FORWARD SIDE BRACE WHICH EXTENDS AND RETRACTS THE LANDING GEAR.  THE WEIGHT OF THE GEAR AND THE S	PEED OF MOVING THE GEAR UP AND DOWN EVENTUALLY FATIGUES PARTS.   SUBMITTER STATED RECURRENCE CANNOT BE AVOIDED.  (X)				1	L	7	2 	3O			 	A20SO   					 
2000061600331	20000616	00331	SO  	2000	6	16	20000609SH027    	1	20000524	G	8100	LW1009685	CONTROLLER      			PIPER 	PA31  	PA31350     	7103110	SO  											DEFECTIVE       	I			WVBA	O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	3582P	268  				318052103				ON POST-FLIGHT INSPECTION, PILOT NOTICED OIL ON UNDER SIDE OF ENGINE COWLING AND NOTIFIED MAINTENANCE PERSONNEL.  FURTHE	R INVESTIGATION REVEALED OIL DRIPPING FROM INDUCTION HOUSING DRAIN AND WAS DETERMINED TO BE COMING FROM THE SENSE LINE O	UT OF THE DIFFERENTIAL PRESSURE CONTROLLER.  (X)				1	L	7	2 	3O			 	A20SO   					 
2000061600334	20000616	00334	CE  	2000	6	16	20000609SH028    	1	20000422	G	3252	08424008	SHIMMY DAMPENER 			CESSNA	172   	172         	2072402	CE  										NOSE	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	03	6331E					46431				AFTER LANDING, THE PIC WAS TAXIING TO THE RAMP WHEN THE NOSE WHEEL STARTED TO SHIMMY.  HE APPLIED BRAKES AND THE AIRCRAF	T MADE A HARD RIGHT TURN CAUSING THE AIRCRAFT TO TOP OVER TO THE LEFT/FRONT SIDE AND THE LEFT WING TIP AND PROPELLER MAD	E CONTACT WITH THE GROUND.  INSPECTIONS OF THE AIRCRAFT REVEALED THE NOSE GEAR SHIMMY DAMPER AND BOTH STEERING RODS WERE	 BROKEN.  (X)			1	H	7	1 	3O			NT	3A12    					 
2000061600408	20000616	00408	CE  	2000	6	16	20000613SH001    	1	20000511	G	7820	70120	MUFFLER         			BEECH 	35    	V35B        	1151548	CE  	CONT  	O550  	IO550B      	 	SO  					LEFT	BULGED          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	24161					D10103	297079R			DURING A BASIC VISUAL INSPECTION OF THE ENGINE, THE LEFT MUFFLER WAS NOTED AS HAVING SEVERAL BULGES.  UPON REMOVAL OF TH	E MUFFLER AND HEAT SHIELD, THE MUFFLER HAD SEVERAL LARGE HOLES THAT WERE NOT VISIBLE UNTIL THE HEAT SHIELD WAS REMOVED. 	 CAUSE UNKNOWN.  SUBMITTER SUGGESTED HEAT SHIELD BE REMOVED FOR CLOSER INSPECTION OF MUFFLER DURING 100 HOUR/ANNUAL INSP	ECTIONS.  (X)			1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2000061600409	20000616	00409	SO  	2000	6	16	20000613SH002    	1	20000308	G	3250	9652200	SPRING          	PIPER       		PIPER 	PA34  	PA34200     	7103405	SO  										NOSE GEAR ASSY	BROKEN          	B			PP4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	1230T	5163 				347250268				DURING A 50-HOUR OIL CHANGE, THE AIRCRAFT WAS JACKED UP IN ORDER TO CHANGE BOTH MLG TIRES.  WHILE SPOT-CHECKING NLG TIRE	, EXCESSIVE PLAY WAS FOUND IN THE NLG STEERING LINKAGE.  CLOSER EXAMINATION REVEALED THE STEERING STOPS WERE DAMAGED AND	 THE NLG CENTERING SPRING WAS BROKEN.  NORMALLY, THE CENTERING SPRING TRAVEL IS GREATER THAN THE STEERING STOPS.  SUBMIT	TER SUSPECTED THE STEERING STOPS WERE DAMAGED DURING TOWING ALLOWING THE STEERING TRAVEL TO EXCEED THE STOPS AND BREAK T	HE CENTERING SPRING.  (X)		1	L	7	2 	3O			 	A7SO    					 
2000061600410	20000616	00410	SW  	2000	6	16	20000613SH003    	1	20000515	G	5510	3010610	ATTACH FITTING  			AIRTRC	AT400 	AT401       	0390204	SW  										HORIZ STAB STRUT	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	4545W	5253 				4010790				INTERNAL CORROSION CAUSED FAILURE OF HORIZONTAL STABILIZER STRUT AT LOWER ATTACH FITTING.  SUBMITTER RECOMMENDED LOWER A	TTACH POINT DESIGNED SIMILAR TO UPPER FITTING AND LINSEED OIL APPLIED TO INSIDE OF STRUT.  (X)					1	L	7	1 	3R			 	A17SW   					 
2000071900003	20000719	00003	SO  	2000	7	19	20000613SH004    	1	20000531	G	3240	1159SC15403	BRAKE           		AHA2163     	GULSTM	GV    	GV          	       	SO  										NR 2 MLG	DAMAGED         	H				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	83M	595  				557				WHILE REMOVING NR 2 MAIN WHEEL ASSY FOR A TIRE CHANGE, NOTED ON THE BRAKE INSPECTION THAT THE OUTBOARD ROTOR KEYWAY SLOT	 CLIPS WERE BREAKING AWAY FROM THE ROTOR.  WHEEL ASSY HAD SOME DAMAGE FOR LOOSE CLIPS.  BRAKE AND WHEEL ASSYS WERE BOTH 	REPLACED.  (X)				2	L	7	2 	4F			RT	A12EA   					 
2000101200142	20001012	00142	SW  	2000	10	12	20000613SH006    	1	20000523	G	7810	649264	INTAKE PIPE     			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360SB   	 	SO  					NR 4 CYL ATT	CRACKED         	B			DY1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	48LW	434  				252021	321763			DISCOVERED HEAVY STAIN AT FLANGE END OF INDUCTION TUBE DURING ROUTINE OIL CHANGE.  REMOVED FLANGE RETAINER AND FOUND PIP	E CRACKED APPROXIMATELY ONE-HALF DIAMETER.  CONTINENTAL HAS RECENTLY ISSUED SB 98-8 WHICH RECOMMENDS REPLACEMENT OF ONE 	PIECE PIPES FOR CYLINDERS 1 AND 3.  THIS PIPE WAS FOR CYLINDER NR 4.  SUBMITTER RECOMMENDED REPLACEMENT OF CYLINDERS 2 A	ND 4 PIPES WITH 2 PIECE STYLE AS WELL.  LENGTH OF PIPE IS TOO MUCH FOR FLANGE STRENGTH.  (X)			1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2000061400301	20000614	00301	EU  	2000	6	14	20000613SH007    	1	20000510	G	2710		PUSHROD TUBE    			GROB  	103TWN	G103ATWINII 	1660206	EU  										96 INCH OUT BD	FAILED          	B			L1MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	103MG	7775 				33983K216				LEFT WING AILERON PUSH ROD FOUND MISSING PLASTIC BEARING CAUSING RIVETS TO WEAR THROUGH PUSH ROD IN 2 PLACES.  (X)						1	K	0	0 	3O			0	G39EU   					 
2000061400302	20000614	00302		2000	6	14	20000613SH008    	4	20000525	G	6122	B41832	FLYWEIGHT       			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  						CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2947E				E103U	327940222				RELEVANT INDICATION  OF CRACK IN FLYWEIGHT ASSY.						1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000061400303	20000614	00303	CE  	2000	6	14	20000613SH011    	1	20000613	G	5510	1732010	BRACKET         	CESSNA      		CESSNA	177   	177RG       	2073709	CE  										BEND RADIUS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	545PZ	5000 				177RG1023				THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS.  CRACKS WERE 1.25 INCHES, 1.50 INCHES,	 AND 1.75 INCHES ON EACH.  THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT.  	SUBMITTER RECOMMENDED FREQUENT INSPECTIONS.  UNKNOWN CAUSE.   (X)				1	H	7	1 	3O			 	A20CE   					 
2000062000227	20000620	00227	CE  	2000	6	20	20000613SH012    	1	20000613	G	5510	17320311	BRACKET         	CESSNA      		CESSNA	177   	177RG       	2073709	CE  										BEND RADIUS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	545PZ	5000 				177RG1023				THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS.  CRACKS WERE 1.25 INCHES, 1.50 INCHES,	 AND 1.75 INCHES ON EACH.  THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT.  	SUBMITTER RECOMMENDED FREQUENT INSPECTIONS.  UNKNOWN CAUSE.  (X)				1	H	7	1 	3O			 	A20CE   					 
2000061400304	20000614	00304	CE  	2000	6	14	20000613SH013    	1	20000613	G	5510	17320312	BRACKET         	CESSNA      		CESSNA	177   	177RG       	2073709	CE  										BEND RADIUS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	545PZ	5000 				177RG1023				THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS.  CRACKS WERE 1.25 INCHES, 1.50 INCHES,	 AND 1.75 INCHES ON EACH.  THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT.  	SUBMITTER RECOMMENDED FREQUENT INSPECTIONS.  UNKNOWN CAUSE.  (X)				1	H	7	1 	3O			 	A20CE   					 
2000061400305	20000614	00305	CE  	2000	6	14	20000613SH014    	1	20000525	G	3230	508103437	PIN             			BEECH 	200   	B200        	1152922	CE  										MLG DOWNLOCK	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	529NA					BB1091				THE RELEASE LINKS AND PINS IN BOTH  MAIN LANDING GEAR DOWNLOCKS WERE REMOVED FROM AIRCRAFT FOR INSPECTION.  INSPECTION R	EVEALED BOTH PINS WERE WORN APPROX .002 INCH BEYOND LIMITS AND BOTH LINK PIN HOLES HAD CIRCUMFERENTIAL SCRATCHES INDICAT	ING THAT PINS HAD AT SOME TIME ROTATED IN LINK.  PINS AND LINKS WERE REPLACED.  ACFT TIME:  8,933.1 HOURS, 5,559 LANDING	S.  SUBMITTER SUGGESTED THAT HOOK AND LINK ASSYS BE DISASSEMBLED AND INSPECTED AT EACH 6 YEAR 8,000 LANDING INSPECTION O	F DRAG BRAKE ASSY.  (X)		1	L	7	2 	4T			 	A24CE   					 
2000061400306	20000614	00306	WP  	2000	6	14	20000613SH021    	2	20000601	G	7250	30747522	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					POST FIR TREE	OUT OF TOLERANCE	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE IN POST FIR TREE AREA.  NICK MORE THAN .001 INCH IN DEPTH ON FORWARD SIDE. 	 LOT NUMBER 00P0130.  (X)										4	F			E6WE				 
2000061400307	20000614	00307		2000	6	14	20000613SH023    	4	20000525	G	6122	B41832	FLYWEIGHT       	HARTZL      		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  						CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					A3858T					RELEVANT CRACK INDICATION AT BASE OF FLYWEIGHT.  (X)						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2000061400308	20000614	00308	SO  	2000	6	14	20000613SH024    	1	20000509	G	2410	75536	BUSHING         	LYC         		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  						FAILED          	B			PAIR	K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			SO	05	61CG					31P30	L47262			PILOT EXPERIENCED ALTERNATOR FAILURE ON LT ENGINE IN-FLIGHT.  UPON INSPECTION AFTER LANDING, FOUND LT SIDE OF AIRCRAFT C	OVER IN OIL AND LT ALTERNATOR LYING INSIDE OF COWLING.  SUSPECT FAILURE OF GOVERNOR ADAPTER ASSY.  BUSHING, PN 75539, CA	USED MIS-ALIGNMENT OF ALT DRIVESHAFT WHICH CAUSED COUPLING, PN LW-14464, TO FAIL IN SUCH A MANNER THAT CAUSED ALTERNATOR	 ADAPTER ASSY, PN LW-10259, TO FAIL. (X)			1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2000061400309	20000614	00309	CE  	2000	6	14	20000613SH025    	1	20000525	G	7810	NH10010910	COUPLING        			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  						CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4243C	100  				4140539				***TONY, LAST SENTENCE?????***WASTEGATE ELBOW COUPLING INSTALLED ON RAM SERIES VII C-340 AND 414, IAW STC SA4331SW.  FOU	ND CRACKED AND REPLACED EACH 50 - 100 HOURS FOR 150 HOURS.  (X)					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2000061400310	20000614	00310	CE  	2000	6	14	20000613SH026    	1	20000525	G	3230	508103961	LINK            			BEECH 	200   	B200        	1152922	CE  											OUT OF TOLERANCE	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	529NA					BB1091				THE RELEASE LINKS AND PINS IN BOTH  MAIN LANDING GEAR DOWNLOCKS WERE REMOVED FROM AIRCRAFT FOR INSPECTION.  INSPECTION R	EVEALED BOTH PINS WERE WORN APPROX .002 INCH BEYOND LIMITS AND BOTH LINK PIN HOLES HAD CIRCUMFERENTIAL SCRATCHES INDICAT	ING THAT PINS HAD AT SOME TIME ROTATED IN LINK.  PINS AND LINKS WERE REPLACED.  ACFT TIME:  8,933.1 HOURS, 5,559 LANDING	S.  SUBMITTER SUGGESTED THAT HOOK AND LINK ASSYS BE DISASSEMBLED AND INSPECTED AT EACH 6 YEAR 8,000 LANDING INSPECTION O	F DRAG BRAKE ASSY.  (X)		1	L	7	2 	4T			 	A24CE   					 
2000061600488	20000616	00488	SO  	2000	6	16	20000615SH001    	1	20000615	G	5711	62015	SPAR            			PIPER 	PA28  	PA28160     	7102806	SO  											CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	5158W					28189				FORWARD LOWER EDGE OF MAIN SPAR INBOARD BEHIND FUEL TANK BADLY CORRODED.  DEFOLIATED BY ABOUT 50 PERCENT OF THICKNESS.  	MICE NESTS AND FECAL MATTER FOUND.  SUBMITTER RECOMMENDED FUEL TANK REMOVAL FOR INSPECTION AT LEAST EVERY 5 YEARS.  ALSO	, INSTALL INSPECTION HOLE BEHIND TANKS FOR BETTER INSPECTION ACCESS.  (X)				1	L	7	1 	3O			 	2A13    					 
2000072600253	20000726	00253	NE  	2000	7	26	20000615SH002    	2	20000605	G	7230	UL27681	COMPRESSOR WHEEL								RROYCE	RB211 	RB211535E4  	54555	NE  					COOLING HOLES	CRACKED         	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		16222					31374			CRACK INDICATIONS FOUND DURING ACCOMPLISHMENT OF ROLLS-ROYCE SB RB211-72-C817.  (X)											4	F			E12EU				 
2000062600125	20000626	00125	NE  	2000	6	26	20000615SH003    	1	20000511	G	5302		TAIL BOOM       			SKRSKY	S55   	S55         	8141602	NE  										TAIL CONE	CRACKED         	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	17754	396  				V55398T				UPPER TAIL CONE SKIN AT STA 181.9 CRACKED APPROXIMATELY 12 INCHES IN LENGTH.  (X)						1	G	7	1 	3R			 	1H4     					 
2000070600229	20000706	00229	WP  	2000	7	6	20000615SH005    	1	20000602	G	3246	152058	WHEEL           		1542511     	DOUG  	DC8   	DC8*        	       	WP  										SPOKE AREA OTBD	UNSERVICEABLE   	B			INWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										NDT INSPECTION SHOWED CRACK INDICATION AT SPOKE AREA. (X)						2	L	7	4 	4J			F	4A25    					 
2000061900240	20000619	00240		2000	6	19	20000615SH007    	4	20000523	G	3424	1394T10054	GEAR            			PIPER 	PA38  	PA38112     	7103812	SO  										TURN AND BANK	INOPERATIVE     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	4265E	1846 				3878A0513				TURN COORDINATOR NOT WORKING, FLAG WAS INDICATING PROPER OPERATION, BUT RATE OF TURN NOT INDICATED. OCCURED UNDER NORMAL	 CONDITONS.  THE CAUSE IS INTERNAL DAMAGE TO GEARINGS OR PART MALFUCTNION.  SUBMITTER STATED TO PREVENT, TAXI AROUND AND	 YAW BACK AND FOURTH AND CHECK FOR PROPER OPERATION.  (X)				1	L	7	1 	3O			 	A18SO   					 
2000062000228	20000620	00228	EA  	2000	6	20	20000615SH008    	2	20000605	G	8530	LW12892	PLUG            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	O540C4B5    	41532	EA  					ROCKER SHAFT	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	17WE					277854118	L1811048A			FOUND IN BOTH ENGINES DURING ANNUAL WHILE PERFORMING LYC 400-HOUR ROCKER ARM INSP, SEVERAL OF THE ROCKER SHAFT THRUST BU	TTONS WERE FOUND DETERIORATING.  A COUPLE OF THEM WERE FOUND BROKEN OFF AND OUT OF THE ROCKER SHAFT.  THE OIL SCREEN WAS	 FOUND TO CONTAIN SOME BITS OF PLASTIC.  ALL THE THRUST BUTTONS WERE REMOVED AND SEVERAL OF THEM CRUMBLED WHEN SQUEEZED.	  ENGINES HAD JUST OVER 1,600 HRS SMOH IN 1982.  A FEW HRS AFTER INSPECTION, ONE OF THE ENGINES DEVELOPED HIGH OIL PRESS	URE PROBLEMS, POSSIBLY DUE TO PLUGGED OIL PASSAGES.  ALL OF THE THRUST BUTTONS REPLACED AT INSP, BUT THERE STILL COULD B	E PLASTIC BITS IN THE ENGINE WHICH COULD PLUG PASSAGES.  (X)	1	L	7	2 	3O	3	O	 	1A10    	E295				 
2000062000229	20000620	00229	EA  	2000	6	20	20000615SH009    	2	20000605	G	8530	LW12892	PLUG            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ROCKER SHAFT	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	17WE					277854118	L1815148A			FOUND IN BOTH ENGINES DURING ANNUAL WHILE PERFORMING LYC 400-HOUR ROCKER ARM INSP, SEVERAL OF THE ROCKER SHAFT THRUST BU	TTONS WERE FOUND DETERIORATING.  A COUPLE OF THEM WERE FOUND BROKEN OFF AND OUT OF THE ROCKER SHAFT.  THE OIL SCREEN WAS	 FOUND TO CONTAIN SOME BITS OF PLASTIC.  ALL THE THRUST BUTTONS WERE REMOVED AND SEVERAL OF THEM CRUMBLED WHEN SQUEEZED.	  ENGINES HAD JUST OVER 1,600 HRS SMOH IN 1982.  A FEW HRS AFTER INSPECTION, ONE OF THE ENGINES DEVELOPED HIGH OIL PRESS	URE PROBLEMS, POSSIBLY DUE TO PLUGGED OIL PASSAGES.  ALL OF THE THRUST BUTTONS REPLACED AT INSP, BUT THERE STILL COULD B	E PLASTIC BITS IN THE ENGINE WHICH COULD PLUG PASSAGES.  (X)	1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2000061900277	20000619	00277	EA  	2000	6	19	20000615SH010    	2	20000412	G	7320	3027974	TUBE            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FCU	BROKEN          	E			AOBA	O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			EA	11	369GA	7845 	5    			LJ934	PCE24685			WHILE APPLYING POWER FOR TAKEOFF, THE LEFT ENGINE WOULD NOT RESPOND. INSPECTED AND FOUND THE PY LINE CRACKED AT THE FUEL	 CONTROL UNIT.  (X)					1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2000061900278	20000619	00278	CE  	2000	6	19	20000615SH011    	1	20000524	G	2510	0514090	SEAT            	CESSNA      		CESSNA	172   	172M        	2072418	CE  											FAILED          	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	64427	60541				17265219				WHEN SEAT CRANK IS TURNED, PIN RUBS ON VERTICAL ADJUST SCREW ASSY.  IT CATCHES AT MAX ADJUSTMENT AND PREVENTS FULL SEAT 	ADJUST PIN ENGAGEMENT.  SUBMITTER SUGGESTED A POSSIBLE MANUFACTURER DEFECT.  (X)					1	H	7	1 	3O			NT	3A12    					 
2000071800505	20000718	00505	WP  	2000	7	18	20000615SH030    	1	20000418	G	5320	991073417	WEB             			DOUG  	DC9   	DC933F      	302207A	WP  										FUSELAGE	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	945F					47279				DURING C-CHECK, FOUND NUMEROUS CRACKS AND ELONGATED HOLES IN CUSP WEB AT BS 218 TO BS 237, LBL 44.5.  CAUSE UNKNOWN. (X)						2	L	7	2 	4F			 	A6WE    					 
2000062700135	20000627	00135	SW  	2000	6	27	20000619SH004    	1	20000428	G	6300	412340102101	BOOT            	BELL        		BELL  	412   	412         	1182202	SW  										RUBBER	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	412FH	93   				36027				THE RUBBER PART OF THE BOOT HAD COME LOOSE FROM THE METAL RING THAT HOLDS THE BOOT.  NOTE:  BOOT MFG DATE, MARCH 1999.  	(X)					1	G	7	2 	4U			 	H4SW    					 
2000062700136	20000627	00136	SW  	2000	6	27	20000619SH005    	1	20000428	G	6310	212040176101	BOOT            			BELL  	412   	412         	1182202	SW  										ENGINE/TRANS	TORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										THIS BOOT WAS REMOVED FROM STOCK AND FOUND THE RUBBER IN BAD CONDITION.  HAD SEVERAL PLACES WHERE IT COULD TEAR.  NOTE: 	 BOOT MFG DATE JULY 21, 1999.  (X)					1	G	7	2 	4U			 	H4SW    					 
2000062700137	20000627	00137	SW  	2000	6	27	20000619SH006    	1	20000428	G	6310	212040176101	BOOT            	BELL        		BELL  	412   	412         	1182202	SW  										ENGINE/TRANS	TORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	555BA	286  				36015				TEAR ON RUBBER PART OF THE BOOT.  NOTE: BOOT MFG DATE DECEMBER 11, 1998. (X)						1	G	7	2 	4U			 	H4SW    					 
2000062700138	20000627	00138	SW  	2000	6	27	20000619SH007    	1	20000502	G	6310	212040176101	BOOT            			BELL  	412   	412         	1182202	SW  										ENGINE/TRANS	TORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	555BA	38   				36015				TEAR ON RUBBER PART OF BOOT.  NOTE: BOOT MFG DATE JULY 21, 1999.  (X)						1	G	7	2 	4U			 	H4SW    					 
2000072000007	20000720	00007	NE  	2000	7	20	20000619SH019    	2	20000609	G	7250	811935	SUPPORT BRACKET 								PWA   	JT8   	JT8*        	52044	NE  					NR 5 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART FAILED FMPI CRACK TEST IN SERVERAL LOCATIONS.  (X)											4	F			E2EA				 
2000072000008	20000720	00008	NE  	2000	7	20	20000619SH020    	2	20000609	G	7250	811935	SUPPORT BRACKET 								PWA   	JT8   	JT8*        	52044	NE  					NR 5 BEARING	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03										PART FAILED FMPI CRACK TEST IN SEVERAL LOCATIONS.  (X)											4	F			E2EA				 
2000062000232	20000620	00232	CE  	2000	6	20	20000619SH026    	1	20000430	G	2823	520220940625	ROLL PIN        			BEECH 	35    	K35         	1151524	CE  										FUEL SEL VALVE	MISSING         	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	09	3095C	3600 				D5774				FUEL STARVATION, OFF AIRPORT LANDING.  PILOT REPORTED THAT WHEN HE SWITCHED TANKS HE DID NOT FEEL POSITIVE DETENT.  APPR	OX 12 MINUTES LATER, ENGINE QUIT.  AGAIN ATTEMPTED TO SWITCH TANKS AND SELECTOR HANDLE CAME DETACHED FROM SELECTOR VALVE	 SHAFT.  EMERG LANDING MADE AND ON ROLL-OUT, ACFT STRUCK A FENCE CAUSING NOSE GEAR COLLAPSE, HEAVY DAMAGE TO ACFT.   INV	EST REVEALED THE ROLL PINS WERE MISSING FROM FUEL SELECTOR VALVE SHAFT, UPPER AND LOWER.  SUBMITTER STATED SAFETY WIRING	 THROUGH ROLL PIN AND SHAFT WOULD HAVE ELIMINATED DEFECT.  (X)		1	L	7	1 	3O			 	3A15    					 
2000062000233	20000620	00233	CE  	2000	6	20	20000619SH028    	1	20000530	G	5510	07122071	ATTACH FITTING  			CESSNA	182   	182A        	2072704	CE  										LT SIDE EMPENNAG	CRACKED         	B			PP4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	5890B					33890				DURING ANNUAL INSP, LT SIDE HORIZONTAL STABILIZER ATTACH BRACKET WAS FOUND CRACKED NEXT TO A MOUNT BOLT.  APPROX ONE YEA	R PRIOR, THE HORIZ STAB HAD BEEN REBUILT.  THE SPAR, STRINGERS, AND SKIN HAD BEEN REPLACED.  VERY FEW OF THE ORIGINAL PA	RTS WERE RETURNED TO SERVICE.  IT IS BELIEVED THE STABILIZER AND MOUNT BRACKET WERE DAMAGED DURING OR BY GROUND HANDLING	 THE ACFT BY THE TAIL.  THE SMALL CRACK NEXT TO ONE OF THE TWO BOLTS THAT ATTACH IT TO THE ACFT WAS OVERLOOKED.  (X)			1	H	7	1 	3O			NT	3A13    					 
2000062000234	20000620	00234	EA  	2000	6	20	20000619SH029    	2	20000525	G	7300		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  						POWER LOSS      	A			BSYA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			GL	07	35453					318052006	L167861A			GRR - RIGHT ENGINE WOULD NOT COME ABOVE 2,000 RPM''S ON TAKEOFF.  MAINTENANCE TROUBLESHOT, NO PROBLEM FOUND.  GROUND RUN	 CHECKED GOOD.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000062000235	20000620	00235	SO  	2000	6	20	20000620SH001    	1	20000519	G	3230		ROD             			PIPER 	PA31  	PA31350     	7103110	SO  										DOWN AND LOCK	BINDING         	A			BSYA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	35551					318052063				 - RT MAIN GEAR NO DOWN AND LOCK INDICATION.  FOUND ROD AND BINDING NOT LETTING THE HOOK DROP INTO PLACE.  CLEANED AND L	UBED, OPS CHECKED GOOD.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000062000236	20000620	00236	CE  	2000	6	20	20000620SH002    	1	20000525	G	3230	99100023	MOTOR           			CESSNA	310   	310R        	2074245	CE  										LANDING GEAR	FAILED          	A			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	5113J					310R0233				BUR - LANDING GEAR CIRCUIT BREAKER TRIPS WHEN GEAR SELECTED UP.  REMOVED AND REPLACED GEAR MOTOR.  OPS CHECKED GOOD.  (X	)					1	L	7	2 	3O			 	3A10    					 
2000062000237	20000620	00237	SO  	2000	6	20	20000620SH003    	2	20000525	G	7300		ENGINE          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  						SURGES          	A			BSYA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			GL	07	5215C					310R1515	277772R			CMH - RIGHT ENGINE ON APPROACH STARTED SURGING BETWEEN 2,200 RPM AND 2,600 RPM.  CHECKED ENGINE OUT COMPLETELY, COULD NO	T DUPLICATE.  OPS CHECKED GOOD. (X)					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2000062000238	20000620	00238	CE  	2000	6	20	20000620SH004    	1	20000516	G	5610		WINDSHIELD      			CESSNA	310   	310R        	2074245	CE  											BIRD STRIKE     	A				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	07	6121C					310R1288				OMA - PILOT HEARD LOUD BANG ON APPROACH INTO OMAHA.  NOTIFIED OMA TOWER AND LANDED, NO PROBLEM.  ON THE GROUND, FOUND TH	AT A BIRD HIT TOP OF WINDSHIELD.  NO DAMAGE TO AIRCRAFT, RETURNED TO SERVICE.  (X)					1	L	7	2 	3O			 	3A10    					 
2000062000239	20000620	00239	EA  	2000	6	20	20000620SH005    	2	20000505	G	7314	5006050	COUPLER         	PESCO       		BEECH 	90    	65A901      	       	CE  	PWA   	PT6   	PT6A20      	52043	EA  					CASE TO PUMP	SHEARED         	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	99	7089Q		516  		5489	LM77	21043			EXPERIENCED AN ENGINE FAILURE DURING CRUISE AT 4,500 FEET.  AFTER SOME TROUBLESHOOTING ON THE GROUND, FOUND IT TO BE THE	 HIGH PRESSURE FUEL PUMP, PARTICULARLY THE DRIVE COUPLING.  THE SPLINES WERE DAMAGED (SHEARED) ENOUGH THAT IT ALLOWED TO	O MUCH PLAY AND THE PUMP QUIT PUMPING.  THE POSSIBLE CAUSE COULD HAVE BEEN INSUFFICIENT LUBRICATION TO THE DRIVE COUPLIN	G.  THE PUMP ITSELF HAS NOT YET BEEN TORN ALL THE WAY DOWN TO SEE IF THERE WERE INTERNAL PROBLEMS THAT MAY HAVE CONTRIBU	TED.  (X)		1	L	7	2 	3T	3	T	 	3A20    	E4EA				 
2000062800189	20000628	00189	CE  	2000	6	28	20000620SH008    	1	20000605	G	3230	6046H39B	RELAY           			BEECH 	95    	95B55       	1152729	CE  										LDG MOTOR	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	01	41TG	2900 				TC1581				PILOT REPORTED LANDING GEAR MOTOR CIRCUIT BREAKER WOULD TRIP WHEN SELECTING GEAR DOWN.  TRIED EMERG EXTENSION HANDLE AND	 FOUND TIGHT.  AFTER SEVERAL TRIES, PILOT WAS ABLE TO EXTEND L/G GEAR WITH THE EMERG EXTENSION HANDLE AND LANDED WITHOUT	 PROBLEMS.  WHEN MAINTENANCE INSPECTED ACFT, THEY FOUND THE LANDING GEAR TRANSMISSION BINDING.  LANDING GEAR APPEARED TO	 BE IN RIG. FURTHER INVESTIGATION REVEALED THE L/G MOTOR DYNAMIC BRAKE RELAY NOT REVERSING THE CURRENT TO STOP MOTOR AND	 LANDING GEAR TRANSMISSION WHICH ALLOWED THE MOTOR TO DRIVE THE SECTOR GEAR AGAINST THE INTERNAL TRANS STOP.  FOUND SECT	OR GEAR BADLY DAMAGED AT ONE END.  RE-INSTALLED TRANSMISSION AFTER O/H, INSTALLED NEW RELAY.  RE-RIGGED GEAR PER MM. (X)	1	L	7	2 	3O			RT	3A16    					 
2000062100160	20000621	00160	CE  	2000	6	21	20000620SH009    	1	20000601	G	2822	5100001RX	PUMP            			CESSNA	182   	182S        	2072701	CE  											LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	01	664PB		511  			18280156				SEAL BETWEEN PUMP AND MOTOR LEAKING SEVERELY OUT DRAIN TUBE.  THE ONLY WAY TO STOP IT FROM LEAKING IS TO TURN THE FUEL S	ELECTOR VALVE TO THE OFF POSITION.  THE ORIGINAL PUMP WAS REPLACED FOR THE SAME PROBLEM AT 81.9 HOURS.  INSTALL OVERHAUL	ED PUMP P/N 5100-00-3RX.  AIRCRAFT TT, 593.2 HRS.  SUBMITTER STATED THEY HAVE EXPERIENCED SAME PROBLEM WITH OTHER CESSNA	 182S MODELS.  (X)			1	H	7	1 	3O			NT	3A13    					 
2000062100161	20000621	00161	CE  	2000	6	21	20000620SH010    	1	20000529	G	3222	1243400200	STRUT           			CESSNA	210   	210B        	2073410	CE  										NOSE	BROKEN          	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	07	3222	3083 				21057842				NOSE FORK ASSY BREAKAGE AT SHOCK STRUT MATING SURFACE.  DURING ROLL-OUT AFTER LANDING, A SHIMMY WAS ENCOUNTERED FOLLOWED	 BY NOSE FORK ASSY BREAKAGE.  AD 71-22-02 NOT APPLICABLE TO CESSNA 210 SERIES, BUT REFERENCED DIRECTIVE SL 63-31 INCORPO	RATES THIS AIRCRAFT MODEL.  REVISE AD TO INCORPORATE SL REFERENCED AIRCRAFT.  (X)				1	H	7	1 	3O			 	3A21    					 
2000062100162	20000621	00162	EA  	2000	6	21	20000620SH015    	2	20000530	G	7250	3013102	BLADE           			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A27      	52043	EA  					PT DISK	MISSING         	B			TIMA	O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			NM	11	99TH					U155	PCE40840100			ON TAKEOFF, PILOT FELT AIRCRAFT SHUDDER, RETURNED TO FIELD WITHOUT ANY DAMAGE TO AIRCRAFT.  UPON INVESTIGATION ON ENGINE	, FOUND 2 INCH SQUARE AREA MISSING FROM EXHAUST.  UPON FURTHER INVESTIGATION, FOUND PORTION OF POWER TURBINE BLADE MISSI	NG.  THIS ENGINE HAD 339.1 HOURS SINCE POWER SECTION WAS DISASSEMBLED FOR POWER TURBINE BLADE INSPECTION.  (X)				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000062100163	20000621	00163	EA  	2000	6	21	20000620SH016    	2	20000317	G	7310	125099016	LINE            			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					FUEL PRESS	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	950HP					20608002	L2667948A			**ISAAC, NADA, PART NAME, ETC.***FOUND FUEL PRESSURE LINE, PN 1250990-16, AND OIL PRESSURE LINE, PN 1250990-15, RUBBING 	IN ENGINE COMPARTMENT.  THESE LINES RUN FROM FUEL DISTRIBUTOR MANIFOLD TO RT REAR BAFFLE AND RT FRONT OIL PASSAGE TO RT 	REAR BAFFLE. OIL PRESSURE LINE IS CLAMPED TO PUSH ROD TUBES TWO PLACES.  BOTH LINES WERE WORN THROUGH TO THE POINT OF LE	AKING AT ANY TIME.  THIS IS A NEW AIRCRAFT WITH 450 TOTAL HOURS.  LINES NEED TO BE BENT SLIGHTLY AND REPOSITIONED TO PRE	VENT THIS PROBLEM.  NOTE:  THIS COULD HAVE CAUSED A FIRE IN THE ENGINE COMPARTMENT AS SOON AS THE NEXT FLIGHT.  (X)		1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000062100164	20000621	00164	SO  	2000	6	21	20000620SH017    	1	20000530	G	7120	6711957	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  										RT DRAG BRACE	BROKEN          	B			OG5R	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	21	175ND	8696 				2837029				PILOT REPORTED GEAR UNLOCKED INDICATION WITH GEAR RETRACTED.  INVESTIGATION FOUND ENGINE MOUNT TUBE BROKEN JUST ABOVE RI	GHT DRAG BRACE MOUNT.  WHEN GEAR WAS RETRACTED, MOUNT FLEXED NOT ALLOWING UPLOCK SWITCH CONTROL.  (X)					1	L	7	1 	3O			 	2A13    					 
2000072000138	20000720	00138	SO  	2000	7	20	20000620SH018    	1	20000508	G	7921	8535311	COOLER          			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENG OIL SYS	FAILED          	D				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CE	07	7436L	4600 	120  			317400994	L1028561A			AS AIRCRAFT ROTATED DURING TAKEOFF, MANIFOLD PRESSURE DROPPED, PILOT FOUND LOW OIL RPESSURE, AND RETURNED TO AIRPORT AND	 SECURED ENGINE AFTER LANDING.  ON INSPECTION, FOUND OIL COOLER BOWED OUTWARD AND INNER COILS BULGED WITH 2.5 INCH SPLIT	.  OIL COOLER WAS OVERHAULED APPROXIMATELY 120 HRS.  NO APPARENT DAMAGE OTHER THAN LISTED FOUND ON COOLER.  FOUND NO REA	SON FOR COOLER RUPTURE.  ON ENGINE GROUND TEST, ALL ENGINE PRESSURES NORMAL.  (X)			1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
2000062900124	20000629	00124	SW  	2000	6	29	20000620SH030    	1	20000602	G	6200	MS3116FB4S	CONNECTOR       			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R TRANSMISSION	READS HIGH      	B			CYXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	407LG	635  				53143	CAE847161			*****MICKEY****,PART LOCATION:  TRANSMISSION OIL PRESSURE MANIFOLD*****PILOT REPORTED A HIGH OIL PRESSURE INDICATION (11	0 PSI) ON THE TRANSMISSION OIL PRESSURE INDICATOR.  THIS READING WAS CAUSED BY DIRT/CORROSION INSIDE OF AN ELECTRICAL CO	NNECTOR ON THE SYSTEMS PRESSURE TRANSDUCER.  CONNECTOR WAS CLEANED AND SYSTEM WAS CHECKED GOOD WITH AN EXTERNAL CALIBRAT	ED GAUGE.  OPERATOR:  ST LUKES HOSPITAL, CEDAR RAPIDS, IOWA. 			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2000062800190	20000628	00190		2000	6	28	20000620SH031    	4	20000607	G	6113	D3291	BULKHEAD        			BEECH 	33    	35C33       	1151408	CE  						MCAULY	2A36C	2A36C23     	GL  		CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	6134V	100  				CD864		705098		CRACKS FORMED AROUND 4 OF ATTACHING BOLTS IN BULKHEAD IN USE LESS THAN 100 HOURS.  ATTACHING FLANGE APPEARS TO BE RUBBIN	G AGAINST HUB.  FLANGE IS MISFORMED.  MANUFACTURING DEFECT.  (X)					1	L	7	1 	3O			 	3A15    		5	C	P880	 
2000062900125	20000629	00125	NE  	2000	6	29	20000621SH002    	2	20000223	G	7313	430167601	MANIFOLD        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUEL NOZZLE	DEFECTIVE       	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911VU					7141	LE45583EFA			IMPROPER NOZZLE SPRAY PATTERN. REQUIRED 6000-HOUR INSPECTION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2000100200014	20001002	00014	NE  	2000	10	2	20000621SH005    	2	20000201	G	7313	430167601	MANIFOLD        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NOZZLE	IMPROPER        	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117BK	653  				7229	LE45753EFA			IMPROPER NOZZLE SPRAY PATTERN.  REQUIRES 600 HOUR INSPECTION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2000100200015	20001002	00015	NE  	2000	10	2	20000621SH006    	2	20000420	G	7412	9550176020	EXCITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HE GENERATOR	INOPERATIVE     	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	151AC	107  				1173	415			HE GENERATOR INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000100200016	20001002	00016	EU  	2000	10	2	20000621SH007    	1	20000414	G	2612	0301037070	HARNESS         			SNIAS 	350   	AS350B2     	8680813	EU  										FIRE DETECTION	INOPERATIVE     	A			R7MA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	93LG	221  				2654				T4 HARNESS INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000072600168	20000726	00168	WP  	2000	7	26	20000621SH008    	2	20000313	G	7250	30747522	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					POST FIR TREE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED WITH DAMAGE IN POST FIR TREE AREA ON BOTH FORWARD AND AFT SIDE.  RE:  LOT NUMBER:  OOPO14.  (X)											4	F			E6WE				 
2000072600077	20000726	00077	WP  	2000	7	26	20000621SH009    	2	20000309	G	7250	30720705	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					POST FIR TREE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										NEW PART RECEIVED WITH DAMAGE ON AFT SIDE IN POST FIR TREE AREA.  LOT NUMBER:  99P348.  (X)											4	F			E6WE				 
2000072400078	20000724	00078	WP  	2000	7	24	20000621SH014    	1	20000607	G	3246	152058	WHEEL           			DOUG  	DC8   	DC8*        	       	WP  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										NDT INSPECTION SHOWED CRACK INDICATION AT BEAD SEAT AREA. (X)						2	L	7	4 	4J			F	4A25    					 
2000100200252	20001002	00252	EA  	2000	10	2	20000622SH002    	1	20000622	G	3230	269A3170	DAMPER          			SCWZER	269   	269D        	8059501	EA  										LANDING GEAR	CRACKED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	296RL	1862 				0020				BOTH OF THE FORWARD LANDING GEAR DAMPERS WERE FOUND WITH A COMPLETE CRACK ON THE UPPER CAP THE CRACK EXTENDS FROM  THE B	EARING BORE TO THE TOP OF THE CAP.  (X)					1	G	7	1 	3U			0	4H12    					 
2000101200165	20001012	00165	SO  	2000	10	12	20000622SH011    	2	20000606	G	8530		CYLINDER        			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  						FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	231B		155  			D4651	36361D7388R			ENGINE WAS REMOVED 3 TIMES FOR LOW OIL PRESSURE, AND IT HAD NEW CYLINDERS AT OVERHAUL.  SUBMITTER REMOVED ALL 6 CYLINDER	S AT 89.9 TSO FOR LOW COMPRESSION LEAKING BY EXHAUST VALVES, 3 CYLINDERS REMOVED AT 154.3 TSO WHICH IS 64.4 HOURS FROM T	HE LAST REMOVAL AND REPAIRED.  (X)				1	L	7	1 	3O	3	O	 	A777    	E267				 
2000100200245	20001002	00245	GL  	2000	10	2	20000622SH012    	2	20000201	G	7250	23038229	GEAR SHAFT      	ALLSN       		AROFAL	OH58  	OH58C       	1181580	SW  	ALLSN 	250C  	250C20C     	03013	GL  					GAS PRODUCER	SHEARED         	B			HEFR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	38FA	1312 				7015448	AE405837			ENGINE WAS REMOVED FROM AIRCRAFT BECAUSE IT WAS GENERATING METAL IN THE OIL.  AFTER DISASSEMBLY, IT WAS VIEWED THAT THE 	GEAR SHAFT IN QUESTION HAD SHEARED.  THE SHAFT HAD SHEARED FROM WHERE IT MATES WITH THE MAIN GEAR PORTION OF THE PART.  	NO PROBLEMS WITH RELATED GEARS, BEARINGS, ETC., WERE FOUND TO SUBSTANTIATE A CAUSE FOR THE FAILURE.  PART WAS RETURNED T	O ALLISON FOR FAILURE ANALYSIS PER ALLISON REF CN0099F-REH 0200.  (X)			1	G	7	1 	3U	3	U	NC	H22NM   	E4CE				 
2000101200168	20001012	00168		2000	10	12	20000622SH015    	4	20000127	G	2200	KA132	ACCELEROMETER   	KING        		PIPER 	PA31  	PA31350     	7103110	SO  										FWD RADIO RACK	FAULTY          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	3536B					317952205				ACCELERATION SWITCH - WHEN SUBJECTED TO VIBRATION (ENGINE AT HIGH POWER OR IN FLIGHT), SERVOS ENGAGE, BUT WILL NOT DRIVE	, COMMAND BARS FUNCTION PROPER.  AP LIGHT VARIES FROM FULL BRIGHTNESS TO HALF BRIGHT AT A CONSTANT RATE.  REPLACED ACCEL	ERATION SWITCH AGAIN WITH NEW.  A/P WORKS NORMAL.  (X)				1	L	7	2 	3O			 	A20SO   					 
2000071800521	20000718	00521	CE  	2000	7	18	20000622SH016    	1	20000210	G	3230	6070843004	RETAINER        			BEECH 	200   	B200        	1152922	CE  										PILOT SUB-PANEL	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3127K					BB1293				LANDING  GEAR DOWN AND LOCKED ANNUNCIATOR BULB LOST ELECTRICAL POWER DUE TO WORN ANNUNCIATOR CAP RETAINING PINS ALLOWING	 CAP TO SEPARATE FROM ANNUNCIATOR ASSEMBLY.  REF:  B200 WIRING MANUAL 32-61-00, PAGE 2.  (X)					1	L	7	2 	4T			 	A24CE   					 
2000071800012	20000718	00012	CE  	2000	7	18	20000622SH018    	2	20000425	G	7322	654353	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					TOP ENGINE (AFT)	GOUGED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4161D				70196810	3449141	322031			FUEL SERVO GOUGED AT BASE BY SHOCK MOUNT ATTACHED TO ENGINE.  SUBMITTED STATED SHOCK MOUNT DOES NOT COVER COMPLETE BASE 	OF SERVO.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000101200006	20001012	00006	SO  	2000	10	12	20000622SH019    	1	20000513	G	2823	6965422	ARM             			PIPER 	PA32  	PA32R301    	7103218	SO  										FUEL SELECTOR ST	BENT            	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	07	4148R	1800 				3246129				DURING FLIGHT, THE STUDENT PILOT INADVERTENTLY SHUT THE FUEL OFF CAUSING AN EMERGENCY LANDING AND DAMAGE TO THE RIGHT WI	NG.  INVESTIGATION REVEALED THE FUEL SELECTOR COULD BE MOVED TO THE OFF POSITION WITH LITTLE RESISTANCE.  THE STOP IS AT	TACHED TO THE CENTER PANEL AND ITS SPRING STEEL ARM WAS FOUND BENT ALLOWING THE SELECTOR HANDLE TO BYPASS THE STOP.  (X)				1	L	7	1 	3O			 	A3SO    					 
2001020200006	20010202	00006	SW  	2001	2	2	20000622SH021    	1	20000209	G	5510	407023002117	SLAT            			BELL  	407   	407         	       	SW  										HORIZONTAL	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	369  				532027				REPLACED WITH NEW SLATS FROM BELL HELICOPTER.  C/W BELL ASJ 407-99-32.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200007	20010202	00007	SW  	2001	2	2	20000622SH022    	1	20000209	G	2840	407375016101	SIGNAL COND UNIT			BELL  	407   	407         	       	SW  										FUEL SYSTEM	INTERMITTENT    	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	369  				532027				REPLACED WITH NEW FUEL SIGNAL CONDITIONER FROM BELL HELICOPTER.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200010	20010202	00010	GL  	2001	2	2	20000622SH025    	2	20000224	G	7320	23072725	FUEL CONTROL    			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					HMU	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	407CR	1058 	433  			53254				START PROBLEMS, I.E., (NON-STARTS, ERRATIC STARTS).  CHANGED HMU.  OPS NORMAL PER MM (ALLISON).  (X)						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001020200011	20010202	00011	SW  	2001	2	2	20000622SH026    	1	20000317	G	3530		GAUGE           			BELL  	407   	407         	       	SW  										OXYGEN BOTTLE	LEAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	407CR	481  				53254				OXYGEN GAUGE LEAKING AT CONNECTION PIPE THREADS.  SUBMITTER SUGGESTED INSTALLING FLARED OR BRASS FITTINGS TO SEAL BETTER	.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000062800192	20000628	00192	CE  	2000	6	28	20000622SH027    	2	20000518	G	7322	RSA5AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					FUEL INJECTOR	FAILED          	B			VJ3R	O				OTHER                   				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			WP	07	4142N	923  	450  			3449128	322265LN			LEFT ENGINE DIED ON ROLL-OUT AFTER LANDING.  THIS SERVO HAS 923 HOURS TT SINCE NEW AND 450 HOURS FROM REPAIR OF MIXTURE 	PLATE.  ENGINE RAN ROUGH AT IDLE AND AT LOW POWER SETTINGS.  THE MIXTURE WAS ON THE RICH SIDE AND UNABLE TO ADJUST MIXTU	RE.  SERVO REMOVED AND A NEW ONE INSTALLED IAW TCM AND PIPER MM.   (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000062800193	20000628	00193	EA  	2000	6	28	20000622SH028    	2	20000506	G	8530		SEAT            			AMRGEN	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 1 CYLINDER	MISALIGNED      	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	5437L	92   				AA50337	L133339A			ANNUAL INSPECTION FOUND NO COMPRESSION ON NR 1 CYLINDER.  REMOVED CYLINDER, SENT FOR REPAIR.  FOUND INTAKE VALVE SEAT IN	STALLED WRONG (AT ANGLE) HAD BENT INTAKE VALVE.  ALSO, ENGINE HAD NOT BEEN DE-SLUDGED AT OVERHAUL CAUSING PITS.  FOUND A	T AD INSPECTION AFTER 20 HOURS.  (X)				1	L	7	1 	3O	3	O	 	A16EA   	E274				 
2000062700140	20000627	00140	SW  	2000	6	27	20000622SH031    	1	20000609	G	2720	500012265	CONTROL CABLE   			GULSTM	690TP 	690B        	7630516	SW  										RT RUDDER	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	489GA					11530				RIGHT RUDDER CABLES FRAYED.  (X)						1	H	7	2 	3T			 	2A4     					 
2000062700142	20000627	00142		2000	6	27	20000622SH034    	4	20000622	G	2300	CM35895059825010	SWITCH          			CESSNA	414   	414A        	2075907	CE  											FAILED          	B			QFYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	643WM	2480 				414A1205				DURING TROUBLESHOOTING, FUEL FLOW INDICATION PROBLEM.  TECHNICIAN NOTED THE AVIONICS SWITCH FELT ''ABNORMAL''.  DID NOT 	HAVE ''POSITIVE FEEL''.  NEW SWITCH INSTALLED.  NOTE:  REMOVED SWITCH TOTALLY FAILED DURING OPERATION CHECK AFTER REMOVA	L.  SWITCH LEVER SEIZED.   (X)				1	L	7	2 	3O			 	A7CE    					 
2000062700143	20000627	00143	SO  	2000	6	27	20000622SH035    	1	20000104	G	2432	AN33701	CONTACTOR       			PIPER 	PA23  	PA23250     	7102308	SO  										BATTERY	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	6913A	1795 				277954108				DURING ROUTINE MAINTENANCE FOR 100-HOUR INSPECTION, NOTED CORROSION AFTER FAILURE OCCURRED.  DISASSEMBLED AND FOUND UNIT	 FULL OF RUST AND CORROSION CAUSING TOTAL ELECTRICAL SYSTEM FAILURE.  (X)					1	L	7	2 	3O			 	1A10    					 
2000062700144	20000627	00144	EA  	2000	6	27	20000622SH036    	2	20000404	G	7322	MA4SPA	CARBURETOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  						SEPARATED       	D				O				OTHER                   				W	R		INADEQUATE Q C            	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			EA	07	6212G	764  				17273579	RL515876T			AIRCRAFT ENGINE RAN ROUGH DURING FLIGHT.  WAS UNABLE TO SHUT ENGINE DOWN  USING MIXTURE CONTROL.  FOUND CARBURETOR BOWL 	SEPARATING FROM CARBURETOR BODY.  ALL SCREWS WERE SECURED BY SAFETY TABS AND FACTORY TORQUE SEAL, BUT SCREWS WERE LOOSE.	  SUBMITTER SUSPECTED IMPROPER TORQUE OF SCREWS DURING OVERHAUL. CARBURETOR REPLACED W ITH OVERHAULED UNIT.  FUNCTIONS N	ORMAL.  (X)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000062700145	20000627	00145	CE  	2000	6	27	20000622SH040    	1	20000531	G	8100	LW15550	ROTOR           	LYC         		CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					OIL PUMP	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NM	07	738FN		287  			R18200921				ENGINE TURBO SCAVENGING PUMP FAILED.  THIS ALLOWED THE ENGINE TO PUMP ALL THE ENGINE OIL OVERBOARD THROUGH THE TURBO.  E	MERGENCY OFF AIRPORT LANDING CAUSED SUBSTANTIAL DAMAGE TO AIRCRAFT.  (X)					1	H	7	1 	3O	3	O	 	3A13    	E295				 
2000062700151	20000627	00151	SW  	2000	6	27	20000623SH007    	1	20000419	G	8120	30503505	MOUNT           			MOONEY	M20   	M20K        	5870220	SW  										TURBO	CRACKED         	B			DY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9801Y	882  				250526				DURING ANNUAL INSPECTION, FOUND TURBO SUPPORT MOUNT UPPER FOOT CRACKED AND LOWER FOOT AREA WHICH IS CLOSER TO TURBO EXHA	UST SCROLL VERY RUSTY.  REPLACED WITH NEW MOUNT WHICH HAS IMPROVED PLATING PROCESS.  AIRCRAFT HAS BEEN MODIFIED IAW STC 	SA5691MM AND HAS A TSIO520 SERIES INSTALLED.  THE PROXIMITY OF THE TURBOCHARGER TO THE ENGINE MOUNT AND TURBO SUPPORT TU	BES REQUIRED CONSTANT INSPECTIONS FOR HEAT DAMAGED COMPONENTS.  AD 95-17-06 IS NOT AVAILABLE TO THE TURBO SUPPORT TUBE F	OUND CRACKED.  SUBMITTER RECOMMENDED EXAMINATION OF THE AREA AROUND THE TURBO EXHAUST WHENEVER THE COWLING IS REMOVED.  	(X)	1	L	7	1 	3O			 	2A3     					 
2000062800194	20000628	00194		2000	6	28	20000623SH009    	4	20000512	G	2370	066011550201	AUDIO PANEL     			CESSNA	172   	172S        	2072439	CE  											INTERMITTENT    	B			ACOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	971SP	72   				172S8173				COPILOT''S TRANSMISSION INTERMITTENT.  KMA26 WAS NEW WHEN INSTALLED ON AIRCRAFT.  (X)						1	H	7	1 	3O			NT	3A12    					 
2000082800001	20000828	00001	NE  	2000	8	28	20000623SH010    	2	20000623	G	7230	772568QQ	BOLT            								PWA   	JT8   	JT8D7B      	52053	NE  					HEAD	FAILED          	B			WG4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	19							657618			PMA BOLT PN 772568QQ, REPLACEMENT FOR OEM BOLT, PN 772568, FAILED AFTER 1.548.5 HOURS AND 932 CYCLES IN SERVICE.  BOLT F	RACTURED CAUSING HEAD TO BE INGESTED INTO THE N-2 COMPRESSOR DRIVE TURBINE WHERE EXTENSIVE DAMAGE WAS INFLICTED.  BOLT W	AS FROM AFFECTED BATCHES AS DESCRIBED IN FLIGHT STANDARDS INFORMATION BULLETIN FOR AW NR FSAW 00-07.  (X)									4	F			E2EA				 
2000062700152	20000627	00152	WP  	2000	6	27	20000623SH013    	2	20000609	G	7230	30752272	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					CURVIC	INADEQUATE      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED  WITHOUT HIGH SPOT ON CURVIC BEING MARKED ON EITHER SIDE.  LOT NR:  00P159.  (X)											4	F			E6WE				 
2000100200053	20001002	00053	EU  	2000	10	2	20000623SH014    	1	20000608	G	2500	C533C	DOOR            			UROCOP	EC120 	EC120B      	8680987	EU  										SLIDEUPPER HINGE	SEPARATED       	H				K				NONE                    				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SW	09	182TA	862  				1001				DURING PHOTO FLIGHT MISSION, SLIDING DOOR, STD EQUIP (STOWED IN THE AFT LOCKED POSITION BEFORE TAKEOFF), AIRSPEED AT OR 	BELOW FLIGHT MANUAL LIMITATIONS FOR SLIDING DOOR OPEN, EXITED ACFT.  THE AIRSTREAM PULLED THE SLIDING DOOR FROM LOWER LT	 CORNER AWAY FROM THE SLIDING DOOR RAIL, BENDING UPPER LT HINGE POINT ROLLER OUT OF THE RAIL, HINGING AFT UPPER AND LOWE	R HINGE POINTS, SWINGING BACK TO CONTACT THE AIRFRAME STRUCT IMMEDIATELY BEHIND SLIDING DOOR ASSY, FINALLY BREAKING THE 	UPPER AND LOWER SLIDING ASSYS AWAY FROM FRAME RAILS.  SUBMITTER RECOMMENDED TO PREVENT RECURRENCE, CLOSE UP TOLERANCE ON	 FRAME RAILS AGAINST SLIDING DOOR ROLLERS, AND ENHANCE STOPS AT ENDS OF EACH FR RAIL (4 POINTS).  DOOR ASSY RECOVERED.	1	G	7	2 	3U			NC	R0001RD 					 
2000062700153	20000627	00153	SW  	2000	6	27	20000623SH015    	1	20000520	G	7920	31014284	FITTING         			MTSBSI	MU2   	MU2B30      	5780410	SW  	GARRTT	TPE331	TPE3316     	01514	WP  					COOLER	DETERIORATED    	C			DKBA	E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			SO	09	13RR	8000 	4000 			682	P20478			OIL SUPPLY LINE FOR OIL COOLER, FITTING THREADS IN CASE DETERIORATED ALLOWING FITTING TO BLOW OUT.  THIS ALLOWED ENGINE 	OIL TO PUMP OUT.  PILOT SHUT ENGINE DOWN WITHOUT DAMAGE TO ENGINE.  (X)					1	H	7	2 	3T	4	T	 	A2PC    	E4WE				 
2000062700154	20000627	00154	CE  	2000	6	27	20000623SH016    	1	20000425	G	5620	010A31890	WINDOW          			MTSBSI	MU2   	MU2B25      	5780409	CE  										LEFT CABIN	SEPARATED       	B			IZ2R	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			SW	15	10BK	6477 				272				IN-FLIGHT, APPROXIMATELY 18,000 FEET, AIRCRAFT LOST PRESSURIZATION.  AFTER LANDING, INSPECTION OF THE AIRCRAFT REVEALED 	LEFT CABIN WINDOW HAD FAILED.  DAMAGE WAS LIMITED TO THE WINDOW, NO OTHER AIRFRAME PARTS WERE DAMAGED.  WINDOW HAD BEEN 	POLISHED 8 MONTHS EARLIER. (X)				1	H	7	2 	3T			 	A2PC    					 
2000062700155	20000627	00155		2000	6	27	20000623SH017    	4	20000607	G	6122	A20066	GEAR            	MCAULY      		MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360LB   	17025	SO  						CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	231MS	462  			794319	250313				RELEVANT CRACK INDICATION.  (X)						1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2000062800195	20000628	00195	CE  	2000	6	28	20000623SH018    	1	20000609	G	3222	07421801	BUSHING         			CESSNA	180   	180K        	2072624	CE  										TAIL WHEEL SPRIN	ERODED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	2879K	8    				18053115				RECENTLY INSTALLED TAILSPRING BUSHINGS FOUND EXTRUDED AFTER ONLY 8 HOURS OF OPERATION.  SUBMITTER KNOWS OF ONE OTHER LOW	 TIME FAILURE OF THESE BUSHINGS.  (X)					1	H	7	1 	3O			 	5A6     					 
2000082100160	20000821	00160	CE  	2000	8	21	20000626SH002    	1	20000613	G	5740	08112761	FITTING         			CESSNA	310   	310J        	2074226	CE  										RT REAR SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	3079L	3000 				310J0079				EXFOLIATION CORROSION AT LEAST .01 INCH TO .1250 INCH DEEP AND GROWING.  SUBMITTER STATES THAT AIRCRAFT WAS BASED IN SAN	 FRANCISCO BAY AREA AND SALT AIR MAY HAVE CONDENSED INSIDE THE AIRCRAFT INSULATION AND DRIPPED DOWN ON THE FITTINGS.  HO	WEVER, SUBMITTER BELIEVED THE ORIGINAL CORROSION MAY HAVE BEEN INTERGRANULAR THAT PROGRESSED.  (X)				1	L	7	2 	3O			 	3A10    					 
2000082100165	20000821	00165	CE  	2000	8	21	20000626SH003    	1	20000613	G	5711	08112763	SPAR            			CESSNA	310   	310J        	2074226	CE  										UPER INSIDE CABI	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	310J	3000 				310J0079				EXFOLIATION CORROSION AT LEAST .01 INCH TO .1250 INCH DEEP AND GROWING.  SUBMITTER STATES THAT AIRCRAFT WAS BASED IN SAN	 FRANCISCO BAY AREA AND SALT AIR MAY HAVE CONDENSED INSIDE THE AIRCRAFT INSULATION AND DRIPPED DOWN ON THE FITTINGS.  HO	WEVER, SUBMITTER BELIEVED THE ORIGINAL CORROSION MAY HAVE BEEN INTERGRANULAR THAT PROGRESSED.  (X)				1	L	7	2 	3O			 	3A10    					 
2000082100182	20000821	00182	CE  	2000	8	21	20000626SH005    	1	20000519	G	5312	24122013	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										BS 108.00 LT	CRACKED         	B			EBVD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5169V	6935 				172RG0458				DURING INSPECTION, THE LEFT AND RIGHT BULKHEADS AT BS 108.00 WERE FOUND CRACKED.  THE CRACKS EMANATED FROM THE BULKHEAD 	FLANGE THAT IS RIVETED TO THE HAT RACK SKIN.  BOTH BULKHEADS WERE REPLACED WITH NEW.  RECOMMEND CLOSE INSPECTION OF THIS	 AREA.  ALL BAGGAGE AREA TRIM MUST BE REMOVED IN ORDER TO INSPECT THIS AREA.  SUBMITTER STATED INSPECT ESPECIALLY IF HAT	 RACK IS USED FREQUENTLY.  (X)			1	H	7	1 	3O			 	3A17    					 
2000082100183	20000821	00183	CE  	2000	8	21	20000626SH006    	1	20000519	G	5312	24120014	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  										BS 108.00 RT	CRACKED         	B			EBVD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5169V	6935 				172RG0458				DURING INSPECTION, THE LEFT AND RIGHT BULKHEADS AT BS 108.00 WERE FOUND CRACKED.  THE CRACKS EMANATED FROM THE BULKHEAD 	FLANGE THAT IS RIVETED TO THE HAT RACK SKIN.  BOTH BULKHEADS WERE REPLACED WITH NEW.  RECOMMEND CLOSE INSPECTION OF THIS	 AREA. ALL BAGGAGE AREA TRIM MUST BE REMOVED IN ORDER TO INSPECT THIS AREA.  SUBMITTER STATED INSPECT ESPECIALLY IF HAT 	RACK IS USED FREQUENTLY.  (X)			1	H	7	1 	3O			 	3A17    					 
2000082100184	20000821	00184	CE  	2000	8	21	20000626SH008    	1	20000523	G	2450	ATC30	FUSE            	LAMAR       		CESSNA	172   	172S        	2072439	CE  										F2	BROKEN          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	508ER	1571 			80111810	172S8008				AIRCRAFT LOST POWER TO NR 1 BUSS, TAB, NR 1 COMM, ETC.  FOUND F2 PUSH IN TYPE 30-AMP FUSE IN ELECTRICAL DISTRIBUTION BOX	 INTERMITTANT.  FUSE WAS NOT BLOWN, BUT PUSHING ON IT MADE CONTACT WITH A+.  TRYING TO REMOVE FUSE, IT BROKE A TAB OFF. 	 THERE WAS ARCING ON THE TAB THAT CAUSED THE INTERMITTANT. (X)				1	H	7	1 	3O			NT	3A12    					 
2000082800017	20000828	00017	EA  	2000	8	28	20000626SH009    	2	20000615	G	8520		CRANKSHAFT      			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  						BROKEN          	D				A				UNSCHED LANDING         				R	W		PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            		NR	NOT REPORTED   	1			EA	05	6715U	908  				2447	L942436A			AIRCRAFT INVOLVED IN AN ACCIDENT BECAUSE OF AN ENGINE FAILURE.  THE ENGINE WAS DISASSEMBLED BY THE MANUFACTURER WITH THE	 FOLLOWING FINDINGS.  THE WRONG  PART NUMBER CRANKSHAFT WAS INSTALLED IN THE ENGINE.  THE SLUDGE TUBES, P/N 71577, WERE 	NOT INSTALLED ON THE CRANK PINS.  THE SLUDGE TUBES AID IN THE LUBRICATION OF THE CRANKSHAFT AND RODS.  IN THE CASE OF TH	IS ENGINE, THE NR 2 ROD CAP FAILED CAUSING THE ROD TO BREAK THROUGH THE CASE RESULTING IN THE ENGINE FAILING.  (X)			1	L	7	1 	3O	3	O	 	2A3     	E286				 
2000082100186	20000821	00186	SO  	2000	8	21	20000626SH010    	1	20000523	G	7160	DETAIL4	GASKET          			MAULE 	MX7   	MX7180      	5460185	SO  	LYC   	O360  	O360C1F     	41514	EA  					HEAT BOX	LOOSE           	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	25	5661P					11006C	L3112036A			THE DIAMETER OF HEAT BOX THROAT IS LARGER THAN SEALING SURFACE OF CARBURETOR GASKET ALLOWING CARBURETOR BASKET TO REMAIN	 LOOSE.  COULD BE SUCKED INTO CARBURETOR.  NOTED DURING ENGINE CHANGE.  (X)					1	H	7	1 	3O	3	O	NC	3A23    	E286				 
2000082100187	20000821	00187	CE  	2000	8	21	20000626SH011    	1	20000626	G	2410	A144666	ALTERNATOR      			CESSNA	210   	210M        	2073450	CE  										ENGINE	LOOSE           	D			DKBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	761PS		800  			21062415				FOUND GROUND STUD TO BE LOOSE ON BACK OF ALTERNATOR.  (X)						1	H	7	1 	3O			 	3A21    					 
2000082100188	20000821	00188	CE  	2000	8	21	20000626SH012    	1	20000522	G	2437		WIRE            			MTSBSI	MU2   	MU2B26A     	5780414	CE  											CHAFED          	B			IZ2R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SW	15	741MA					355SA				PILOT REPORTED TO MAINTENANCE THAT THE LEFT AMP GAUGE WENT TO ZERO AMPS, BUT LEFT GENERATOR STAYED ON-LINE.  INVESTIGATI	ON REVEALED CHAFED WIRE BUNDLE IN LEFT MIB AT GROUND ATTACH POINT E253.  REPAIRED 7 CHAFED WIRES AND PROTECTED AS NEEDED	.  SYSTEM OPS CHECKED SATISFACTORY.  (X)				1	H	7	2 	3T			RT	A10SW   					 
2000082100189	20000821	00189	CE  	2000	8	21	20000626SH013    	1	20000613	G	5510	7321014	BRACKET         			CESSNA	182   	182Q        	2072732	CE  										LT AFT HORIZ STA	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	951CC	13427				18266998				DURING 100-HOUR ANNUAL INSPECTION, THE HORIZONTAL STABILIZER ATTACHMENT POINT REINFORCEMENT ON LEFT SIDE WAS FOUND CRACK	ED.  SUSPECTED CAUSE WAS PART HIGH TIME.  ALTHOUGH THE RIGHT REINFORCEMENT WAS NOT CRACKED, IT WAS REPLACED DUE TO HIGH 	TIME.  (X)				1	H	7	1 	3O			NT	3A13    					 
2000082200036	20000822	00036	SO  	2000	8	22	20000626SH014    	2	20000613	G	8530	65465044	CYLINDER        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 6	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	951CC	1380 				18266998	813325R			CYLINDER NR 6 WAS REMOVED BECAUSE THE COMPRESSION WAS 50/80 DUE TO LEAKAGE PAST THE INTAKE VALVE.  AFTER INSPECTION OF T	HE CYLINDER, THE CYLINDER ASSY WAS REPLACED DUE TO A WEAR STEP AT THE TOP OF THE CYLINDER BARREL.  (X)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000082200037	20000822	00037	CE  	2000	8	22	20000626SH015    	1	20000613	G	7713	0700099138	LINE            			CESSNA	182   	182Q        	2072732	CE  										MANIFOLD/FIREWAL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	951CC	13359				18266998				MANIFOLD PRESSURE LINE WAS FOUND BROKEN AFTER PILOT REPORTED GAUGE READING AMBIENT PRESSURE.  POSSIBLE CAUSE, HIGH PART 	TOTAL TIME.  (X)					1	H	7	1 	3O			NT	3A13    					 
2000082200038	20000822	00038	SO  	2000	8	22	20000626SH017    	2	20000525	G	7322	RSA5AD	FUEL CONTROL    			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  						FAILED          	H			VJ3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			WP	07	9299E	54   				3449043				ENGINE DIED ON LANDING ROLL-OUT.  AIRCRAFT WAS TAKEN TO MAINTENANCE AND A GROUND RUN PERFORMED.  THE FUEL SERVO ON THIS 	ENGINE WAS RICH AT IDLE AND UNABLE TO ADJUST MIXTURE.  SERVO WAS REMOVED FROM ENGINE AND SENT FOR REPLACEMENT.  TOTAL TI	ME ON UNIT WAS 54 HOURS. FROM NEW, THIS IS A -5 SERVO.  (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000062700156	20000627	00156	GL  	2000	6	27	20000626SH019    	1	20000529	G	3240	Y139APU7	VALVE           			YAKLEV	YAK   	YAK52       	9830220	GL  										PNEUMATIC BRAKE	INOPERATIVE     	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	07	208YA	435  				8910009				BRAKE SYSTEM  FAILED WHILE TAXIING FROM HANGAR TO RAMP.  FOUND ''REDUCING VALVE'' DEFECTIVE.  (REF:  BLK NR 5).  (X)						1	L	7	1 	3R			RT	EXPA1L71					 
2000082200039	20000822	00039	CE  	2000	8	22	20000626SH020    	1	20000614	G	5312		BULKHEAD        			BEECH 	55    	E55         	1152732	CE  											CRACKED         	B			NT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3085W	2206 				TE954				INSTALLED KIT, PN 55-4030-5S, SI 0090 REV II.  INSPECTED FOR POSSIBLE CRACKS.  FOUND CRACKS ON BOTH LT AND RT SIDES OF B	ULKHEAD.   CRACK .75 INCH  LT SIDE.  CRACK .3750 INCH RT SIDE, SAME LOCATION.  (X)					1	L	7	2 	3O			 	3A16    					 
2000062800223	20000628	00223	CE  	2000	6	28	20000626SH021    	1	20000514	G	2430	23AT2T2	SWITCH          			CESSNA	414   	414         	2075908	CE  										STANDBY/MAIN REG	FAILED          	H				O				OTHER                   				A			FLAME/FIRE                			IN	INSP/MAINT     	1			SW	99	313RW					4140010				THE STANDBY/MAIN VOLTAGE REGULATOR SWITCH FAILED INTERNALLY CAUSING THE NOISE FILTERS, PN CM221, TO SHORT AND CATCH ON F	IRE.  (X)					1	L	7	2 	3O			RT	A7CE    					 
2001020500174	20010205	00174	NE  	2001	2	5	20000626SH023    	2	20000308	G	7230	1A9642	LOCK            								PWA   	2037  	F117PW100   	 	NE  					ENGINE	UNSECURE        	B			WA2D	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03		2191 					P170090			IMPROPER ASSEMBLY.  WING BORESCOPE INSPECTION DISCLOSED ONE 7TH STAGE BLADE LOCK NOT CRIMPED.  DIS-ASSEMBLY INSPECTION V	ERIFIED ON WING FINDINGS.  REVIEW OF PAST BUILD AND PROCEDURES BEING PERFORMED TO DETERMINE ROOT CAUSE.  LAST BUILD PERF	ORMED AT CRS WA2D259L.  (X)									4	T			E17NE				 
2000082300003	20000823	00003	GL  	2000	8	23	20000626SH026    	3	20000406	G	6110		SEAL            			CESSNA	206   	206H        	2073301	CE  						MCAULY	3D36C	B3D36C432   	GL  	PROP	LEAKING         	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	2312V	298  				20608046		991143		DURING PRE-FLIGHT INSPECTION OF THE AIRCRAFT IN A HANGAR, PILOT FOUND A LARGE POOL OF RED OIL ON THE FLOOR BENEATH THE P	ROPELLER.  UPON REMOVAL OF THE SPINNER, DETERMINED THE FLUID WAS LEAKING FROM UNDER A PROPELLER BLADE ROOT.  THE PROPELL	ER WAS REMOVED AND SENT OUT FOR REPAIR.  (X)				1	H	7	1 	3O			RT	A4CE    		5	C	P58GL	 
2000082300005	20000823	00005	SO  	2000	8	23	20000627SH005    	1	20000509	G	7120	86212002	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  										LEFT	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	28721					447995296				DURING 100-HOUR INSPECTION, FOUND LT ENGINE MOUNT CRACKED AND BROKEN.  FAILURE WAS LOCATED BETWEEN THE UPPER AND LOWER O	UTBOARD LORD MOUNT LOCATION.  TUBULAR MEMBER WAS FOUND COMPLETELY SEVERED WITH SMALL PIECE OF MATERIAL MISSING.  PIPER S	B 937 AND SL 719, WHICH DEAL WITH MOUNT REINFORCEMENT HAD NOT BEEN COMPLIED WITH.  OVERHAULED MOUNT INCORPORATING BULLET	INS WAS INSTALLED.  (X)			1	L	7	2 	3O			 	A19S0   					 
2000082300006	20000823	00006	CE  	2000	8	23	20000627SH006    	1	20000619	G	2450	ANL325	CURRENT LIMITER 			BEECH 	200   	200BEECH    	1152920	CE  										MAIN BUSS TIE	FAILED          	B			DBCR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			GL	19	204JS	4695 				BB842				SBM - UPON LEFT ENGINE START-UP, PILOT NOTED ZERO VOLTS ON RIGHT BUSS.  TROUBLESHOT TO FAILED CURRENT LIMITER.  REPLACED	 CURRENT LIMITER, PN ANL-M-325.  OPS CHECK OK.  (X)					1	L	7	2 	4T			 	A24CE   					 
2000082300007	20000823	00007	SO  	2000	8	23	20000627SH007    	1	20000619	G	7120	3802000	MOUNT           			PIPER 	PA32  	PA32R300    	7103213	SO  										FRONT LOWER END	CRACKED         	B			DECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	38911	3366 				32R7780488				SUPPORT TUBE AT LOWER CURVED TUBE BEHIND STEERING ARM FOUND CRACKED AT WELD.  (X)						1	L	7	1 	3O			 	A3SO    					 
2000082300008	20000823	00008	EA  	2000	8	23	20000627SH008    	2	20000620	G	8520	78027	BOLT            	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ROD CAP NR 4	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	33LJ		6826 			15282023	L1867515			CONNECTING ROD CAP BOLT FAILED RESULTING IN ROD FAILURE WHICH BROKE OUT A 6 INCH BY 4 INCH HOLE IN THE CASE.  THIS WAS A	N IN-FLIGHT FAILURE.  THE AIRCRAFT MADE A SAFE ON AIRPORT LANDING.  (X)					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000062900176	20000629	00176	SO  	2000	6	29	20000627SH009    	1	20000427	G	3230	6390128	HOSE            			PIPER 	PA34  	PA34200T    	7103406	SO  											CONTAMINATED    	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	21	47611	7264 				347770418				P/N 63901-28 AND P/N 63901-70 HOSES (TT 7,264.3 HRS) CAUSED CONTAMINATION TO BE INJECTED INTO ORFICE FITTING OF NOSE GEA	R ACTUATOR CAUSING NOSE TO NOT COME OUT OF WHEELWELL MAKING FOR A NOSE GEAR UP LANDING.  (X)					1	L	7	2 	3O			 	A7SO    					 
2000082300009	20000823	00009	SO  	2000	8	23	20000627SH010    	1	20000427	G	3233	6390170	HOSE            			PIPER 	PA34  	PA34200T    	7103406	SO  											DETERIORATED    	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	47611	7264 				347770418				P/N 63901-28 AND P/N 63901-70 HOSES (TT 7,264.3 HRS) CAUSED CONTAMINATION TO BE INJECTED INTO ORFICE FITTING OF NOSE GEA	R ACTUATOR CAUSING NOSE TO NOT COME OUT OF WHEELWELL MAKING FOR A NOSE GEAR UP LANDING.  (X)					1	L	7	2 	3O			 	A7SO    					 
2000082300011	20000823	00011	SO  	2000	8	23	20000627SH011    	1	20000616	G	5540		HORN            			PIPER 	PA28  	PA28140     	7102802	SO  										RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4887T					287225230				RUDDER STEEL CONTROL HORN IS MATED TO THE ALUMINUM CONTROL SURFACE BY RIVETS.  THE MATING SURFACES OF THE RUDDER WERE CO	RRODED TO THE POINT OF REPLACEMENT OF THE LOWER RIB.  THERE WAS NO EXTERIOR EVIDENCE OF POTENTIAL FAILURE EXCEPT THAT 2 	OF THE RIVET HEADS COULD BE FLIPPED OFF WITH A FINGER NAIL.  CROSS SECTION THE RIVETS SHOWED DETERIORATION CAUSED BY ELE	CTROLYSIS.  THIS ELECTROLYSIS WAS CAUSED BY DISSIMILAR METALS (STEEL & ALUM) IN PRESENCE OF MOISTURE.  UPON DISASSSEMBLY	 OF  RUDDER COMPONENTS, FOUND CORROSION.		1	L	7	1 	3O			 	2A13    					 
2000082400001	20000824	00001	CE  	2000	8	24	20000627SH012    	1	20000613	G	3230	YZ2RN7T	SWITCH          			CESSNA	210   	T210N       	2073456	CE  										PLUNGER	MISSING         	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SO	16	5515Y					21064233				PILOT REPORTED AFTER TAKEOFF AND NORMAL CLIMB, NOTICED THE GEAR UP AND LOCKED LIGHT WAS NOT ILLUMINATED.  THE PUSH TO TE	ST FUNCTION OPERATED NORMALLY.   UPON LANDING, MAINTENANCE DISCOVERED THE NOSE GEAR UPLIMIT SWITCH HAD FAILED.  THE PLUN	GER ASSY WAS COMPLETELY MISSING FROM THE SWITCH.  DURING RIGGING OF NEW SWITCH IAW CESSNA SM D2057-3-13 PARA 5A-85 AND F	IG 51-14, AND MANUALLY RETRACTING THE GEAR, WAS UNABLE TO ACQUIRE THE DIMENSION SHOWN IN FIG 5A-14, BUT ONCE HYD POWER A	PPLIED TO GEAR, THE DIMENSION SHOWN WAS RECEIVED.  SUSPECT THAT THESE SWITCHES MAY BE IMPROPERLY ADJUSTED IF ONLY ADJUST	ED DURING MANUAL OPER AND NOT RE-CHECKED USING HYD PRESSURE.  (X)	1	H	7	1 	3O			 	3A21    					 
2000082400002	20000824	00002	CE  	2000	8	24	20000627SH013    	1	20000617	G	7160	05521641	AIR BOX         	FACET       		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					FLAPPER SEAL	MISSING         	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			EA	11	734TB	4925 			CK11816	17269091	RL655176T			ENGINE DEVELOPED VIBRATION IN-FLIGHT AND LOSS OF POWER.  MAINTENANCE REMOVED CARBURETOR AIR BOX AND CARBURETOR.  FOUND P	IECE OF SEAL FROM AIR BOX FLAPPER VALVE BROKEN OFF AND LODGED IN THE VENTURI.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000082400003	20000824	00003	CE  	2000	8	24	20000628SH002    	1	20000616	G	5280	3581501G7	HINGE           	RAYTHN      		BEECH 	58    	58P         	1152744	CE  										REAR ARM	FAILED          	H				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EU	01	79AP	3799 				TJ206				REAR HINGE CASTING FAILED HALFWAY ALONG ARM OF RADIUS, PN 35/815016/7 WHILE APPROACH TO LAND:  POSSIBLE CAUSE IS WEAR IN	 THE FRONT HINGE PIVOT BRACKET BOLT HOLES WHICH COULD CAUSE VIBRATION.  INSPECT BOTH FRONT AND REAR BOLT HOLES FOR WEAR 	ALIGNMENT BY DISCONNECTING THE ACTUATING ROD, REPLACE AS NECESSARY.  (X)				1	L	7	2 	3O			 	A23CE   					 
2000082400004	20000824	00004	EA  	2000	8	24	20000628SH003    	2	20000615	G	8530	73806	PUSHROD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  						CRACKED         	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	86SA		948  			A1520950	L2146215			AIRCRAFT INSPECTED 33 HRS FOLLOWING ANNUAL (1 MONTH) PRIOR TO PUTTING ON LINE FOR FLIGHT TRAINING.  LAST REF TO LYC SI 1	068A VALVE TAPPET CLEARANCE CHK FROM LOGS WAS 552.3 HRS PRIOR (100 HR INSP).  FOUND 3 TIGHT VALVES.  NR 2 EXH WAS TIGHT,	 PUSHROD CRACKED .5625 INCH LONGITUDINALLY, VISIBLE ON OTBD END.  CRACK CONTINUED 180 DEGREES AROUND CIRCUMFERENTIALLY. 	 PUSHROD END LOOSE.  REMOVED ALL PUSHRODS, 7 OUT OF 8 CRACKED.  MOST .3750 INCH LONGITUDINALLY ON INBD END.  REPLACEMENT	 PART LYC 15F22200/S673806 IS NOW STEEL.  ORIG 73806 WAS ALUM.  LYC SI 1068A SUPPLEMENT NR 1 NOW APPLIES FOR STEEL PUSHR	ODS.  (X)	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000082400005	20000824	00005	CE  	2000	8	24	20000628SH005    	1	20000613	G	5511	1232105	RIB             			CESSNA	182   	182Q        	2072732	CE  										HORIZ STABILIZER	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	951CC	13427				18266998				DURING ANNUAL/100 HOUR INSPECTION, THE SECOND RIB OUTBOARD OF CENTER ON THE RT SIDE OF THE HORIZONTAL STABILIZER WAS FOU	ND BENT THROUGH THE LIGHTENING HOLES.  POSSIBLE CAUSE OF THIS DAMAGE, IMPROPER GROUND HANDLING (SITTING ON STABILIZER TO	 TURN AIRCRAFT).  (X)				1	H	7	1 	3O			NT	3A13    					 
2000082200035	20000822	00035	SW  	2000	8	22	20000628SH006    	1	20000624	G	5540	14524401	RUDDER HORN     			NAVION	NAVION	L17A        	6150106	SW  	CONT  	E225  	E2254       	17015	SO  	HARTZL	HC12V	HC12V20*    	GL  	RUDDER	CORRODED        	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	8818H	4557 				NAV4818				DURING INSPECTION FOR AD 68-20-06, FOUND CORRISION HAD CAUSED DELAMINATION AND SWELLING OF ONE SIDE OF RUDDER HORN, P/N 	145-24401.  LAST ANNUAL 1992.  (I)					1	L	7	1 	3O	3	O	 	A782    	E267	5	C	P46GL	 
2000083000035	20000830	00035	CE  	2000	8	30	20000629SH001    	1	20000623	G	2823	1093890027	VALVE           			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					FIREWALL	LEAKING         	E				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	15	15		100  			LA138				INTERNAL LEAK OF FUEL THROUGH GATE VALVE, WITH SHUT-OFF VALVE IN CLOSED POSITION.  (I)						1	L	7	2 	4T	4	T	 	A31CE   	E4EA				 
2000092100007	20000921	00007	SO  	2000	9	21	20000707SH001    	2	20000523	G	8530	649264	PIPE            			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360SB   	 	SO  					ATT FLANGE NR 4	CRACKED         	B			DY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	48LW	434  				252021	321763			DISCOVERED HEAVY STAIN AT FLANGE END OF INDUCTION TUBE DURING ROUTINE OIL CHANGE.  REMOVED FLANGE RETAINER AND FOUND PIP	E CRACKED APPROXIMATELY ONE-HALF DIAMETER.  CONTINENTAL HAS RECENTLY ISSUED SB 98-8 WHICH RECOMMENDED REPLACEMENT OF ONE	-PIECE PIPES FOR CYLINDERS NR 1 AND NR 3.  THIS PIPE WAS FOR CYLINDER NR 4.  SUBMITTER RECOMMENDED REPLACEMENT OF CYLIND	ERS NR 2 AND NR 4 PIPES WITH 2-PIECE STYLE AS WELL.  LENGTH OF PIPE IS TOO MUCH FOR FLANGE STRENGTH.			1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2001020200014	20010202	00014	EA  	2001	2	2	20000707SH002    	2	20000620	G	7414	10357586	GEAR            	CONT        		BELL  	47    	47G         	1181002	SW  	FRNKLN	6AV350	6V350A      	27043	EA  					MAGNETO	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	950B		5    		C200014DR	693	E60073			AIRCRAFT LANDED AT REMOTE FIELD LOCATION ON ISLAND.  SEVERAL HOURS LATER, AIRCRAFT STARTED.  RIGHT MAGNETO COMPLETELY FA	ILED.  ON RPM MAG CHECK, MAGNETO REMOVED AND TAKEN APART.  NYLON DISTRIBUTOR GEAR LOST 3 TEETH.  GEAR USED WAS NOT NEW, 	CHECKED WITH TELEDYNE CONTINENTAL.  THEY CONFIRMED DISTRIBUTOR GEARS ARE ROUTINELY REUSED.  SINCE THERE IS NO WAY TO ZYG	LO OR MAGNAFLUX NYLON DISTRIBUTOR GEARS, SUBMITTER RECOMMENDED ROUTINE REPLACEMENT OF ALL DISTRIBUTOR GEARS AT FACTORY O	VERHAUL.  (X)		1	G	7	1 	3O	3	O	 	H1      	E9EA				 
2000102400180	20001024	00180	SO  	2000	10	24	20000707SH003    	2	20000623	G	8520	642396	CRANKSHAFT      			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RIGHT ENGINE	BROKEN          	B				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NM	05	1920E	60   				340A0669	813713R			RIGHT ENGINE CRANKSHAFT BROKE IN CRUISE FLIGHT 15,000 FEET, 2,300 RPM.  NR 1 PISTON NOT MOVING WHEN PROPELLER IS TURNED.	  NR 5 CYLINDER, NO COMPRESSION.  METAL FOUND IN OIL FILTER AND GOVERNOR GASKET SCREEN.  (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2000102400007	20001024	00007		2000	10	24	20000707SH005    	4	20000621	G	2561	KS9P0101125	LIFE VEST       																	FLOTATION CELL	DEFECTIVE       	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										CELL FAILED MFG RECOMMENDED 2 PSI PRESSURE TEST IAW 25-60-1.  DATE OF MFG:  MAY 1983.  (X)																			 
2000102400008	20001024	00008		2000	10	24	20000707SH006    	4	20000621	G	2561	KS9P0101125	LIFE VEST       																	FLOTATION CELL	DEFECTIVE       	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										CELL FAILED MFG RECOMMENDED 2 PSI PRESSURE TEST IAW 25-60-1.  DATE OF MFG:  FEB 1984.  (X)																			 
2000102400013	20001024	00013	SO  	2000	10	24	20000707SH007    	1	20000614	G	2460	E303	CONNECTOR       			PIPER 	PA31  	PA31350     	7103110	SO  										OVERHEATED	MELTED          	B			R2JR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	21	13FS	3542 				318352024				WHILE COMPLETING PIPER MANDATORY SB 1004, FOUND PLUG E303 AND  WIRING BADLY BURNT.  REPLACED PLUG AND WIRING AND RAN WIR	ING PER SB INSTRUCTIONS.  CREW HAD REPORTED STRONG BURNING SMELL ON ONE PREVIOUS FLIGHT.  PLUG IS LOCATED BEHIND COCKPIT	 UPHOLSTERY AND COULD HAVE CAUSED FIRE.  SUBMITTER SUGGEST MSB 1004 BE MADE AN AD NOTE.  (X)				1	L	7	2 	3O			 	A20SO   					 
2000102400014	20001024	00014	SO  	2000	10	24	20000707SH008    	1	20000614	G	2823	492114	SHUTOFF VALVE   			PIPER 	PA31  	PA31350     	7103110	SO  										INTERNAL FAILURE	FAILED          	B			R2JR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	13FS	3542 				318352024				DURING INSPECTION, FOUND RIGHT FIREWALL SHUT-OFF VALVE FAILED TO RIG PROPERLY.  FUEL STILL FLOWED IN AFT POSITION.  FOUN	D VALVE HAD FAILED INTERNALLY.  AD 80-18-10 AND PIPER SB 648A APPLIES TO AIRCRAFT WITH LOWER SERIAL NUMBERS, BUT NOT THI	S AIRCRAFT.  SUBMITTER SUGGESTED SB AND AD BE APPLIED TO ALL SERIAL NUMBERED AIRCRAFT.  NEW VALVE WAS INSTALLED AND SYST	EM TESTED PROPERLY.  LEFT VALVE WAS ALSO TESTED.  (X)			1	L	7	2 	3O			 	A20SO   					 
2001011100927	20010111	00927		2001	1	11	20000707SH010    	1	20000614	G	2431	BS19747	SWITCH          	MARATHON    																OVERHEAT	IMPROPER PART   	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21					9702895					BATTERY RECEIVED FOR SERVICE AT THIS STATION WITH P/N BS 19747 FAA-PMA OVERHEAT SWITCH INSTALLED.  RESEARCH SHOWED THIS 	BATTERY IS NOT LISTED ON PMA HOLDERS ELIGIBILITY LIST, ALTHOUGH IT IS LISTED IN THE HOLDERS PRODUCT SUPPORT CATALOG AS T	HE PROPER SENSOR FOR THIS SP910D BATTERY.  PMA HOLDER WAS NOTIFIED.  (AD NOTE REQUIRES SENSOR).																	 
2000102400056	20001024	00056	NE  	2000	10	24	20000707SH013    	2	20000126	G	7421	CH34682	IGNITER         								PWA   	305   	PW305       	 	NE  						FAILED          	B			R14R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										RECEIVED 2 EACH IGNITERS.  THE THIRD IGNITER OPS CHECKED OK.  BATCH NUMBER UNKNOWN.  THE IGNITER USED NORMALLY IS INSTAL	LED IN PWA 305 SERIES ENGINES.  (P/N CH34682).  (X)										4	F			E35NE				 
2000102400057	20001024	00057	NE  	2000	10	24	20000707SH014    	2	20000209	G	7421	CH34682	IGNITER         								PWA   	305   	PW305       	 	NE  						DEFECTIVE       	B			R14R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										RECEIVED 3 EACH IGNITERS.  THE 4TH IGNITER OPS CHECKED OK.  BATCH NUMBER UNKNOWN.  THE IGNITER USED NORMALLY IS INSTALLE	D IN P&W 305 SERIES ENGINES.  (PN 34682).  (X)										4	F			E35NE				 
2000102400058	20001024	00058		2000	10	24	20000707SH015    	4	20000619	G	6122	D20887	DRIVE GEAR      	MCAULY      							CONT  	O520  	IO520*      	17032	SO  					GOVERNOR	DEFECTIVE       	C			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					760751					LONG LINEAR INDICATION ON SHAFT, POSSIBLE INCLUSION. (X)											3	O			E5CE				 
2000080200067	20000802	00067	SO  	2000	8	2	20000707SH018    	1	20000626	G	3240	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 2 POSITION	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1019 			0072A					BRAKE ASSEMBLY, P/N 2-1585, FAILED PREMATURELY.  NR 2 STATOR CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVEN WEAR	.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2000102400020	20001024	00020	GL  	2000	10	24	20000710SH006    	1	20000429	G	5743	5310006	BULKHEAD        			AMTR  	SEAREY	SEAREY      	05625X5	GL  										LEFT SIDE	BROKEN          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	05	4293S	165  				1MK026				DURING TAXI, THE LEFT LANDING GEAR COLLAPSED.  INSPECTION REVEALED THE TWO LEFT LG BULKHEAD UPRIGHT SUPPORT TUBES BROKEN	 AT THE LG ATTACH POINT.  IT IS SUSPECTED THE PARTS MAY HAVE BEEN OVERSTRESSED DURING ASSY OF MINIMAL STRENGTH OR THE RE	SULT OF FATIGUE CAUSED BY AN UNREPORTED HARD LANDING(S).  (X)				1	H	7	1 	3I			RC	1H71EXPA					 
2001020200016	20010202	00016	SW  	2001	2	2	20000710SH008    	1	20000520	G	6420	209040177101	FLANGE          			BELL  	412   	412EP       	1182205	SW  										TAIL ROTOR	LOOSE           	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	22PP	469  				36219				DISC TO FLANGE INTERFACE FOUND LOOSE DURING ROTOR BRAKE QUILL SEAL CHANGE.  REPLACED BOTH DISC AND FLANGE WHICH WERE MEA	SURED AND FOUND WORN BEYOND LIMITS.  (X)					1	G	7	2 	4U			 	H4SW    					 
2001020200017	20010202	00017	SW  	2001	2	2	20000710SH009    	1	20000520	G	6420	94404911	DISC PACK       			BELL  	412   	412EP       	1182205	SW  										TAIL ROTOR	LOOSE           	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	22PP	469  				36219				DISC TO FLANGE INTERFACE FOUND LOOSE DURING QUILL SEAL CHANGE.  REPLACED BOTH DISC AND FLANGE WHICH WAS MEASURED AND FOU	ND BEYOND LIMITS.  (X)					1	G	7	2 	4U			 	H4SW    					 
2001020200018	20010202	00018	NE  	2001	2	2	20000710SH010    	1	20000225	G	5330	7620305001123	SKIN            			SKRSKY	S76   	S76A        	8143006	NE  										PYLON	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	22BF	6173 				760216				CORROSION.  SKIN REMOVED FROM PYLON AND TREATED IAW SA 4047-76-8, CORROSION CONTROL MANUAL.  THE CORROSION WAS CLASSIFIE	D AS MINOR CORROSION.  THE CORROSION APPEARED AS PAINT BLISTERS AROUND SKIN FASTENERS.  (X)					1	G	7	2 	3U			 	H1NE    					 
2001020200019	20010202	00019	NE  	2001	2	2	20000710SH011    	1	20000225	G	5312	7620104009	BULKHEAD        			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	MISDRILLED      	B			EGRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	22BF	6173 				760216				THE VERTICAL PYLON FORWARD BULKHEAD AT STA 458 HAD DOUBLE DRILLED HOLES AT THE FASTENER AREA.  THE BULKHEAD IS BETWEEN T	HE UPPER AND LOWER DECKS.  THERE WAS A CRACK FOUND AT THE LEFT CORNER OF THE BULKHEAD WEB.  (X)					1	G	7	2 	3U			 	H1NE    					 
2001020200020	20010202	00020	EU  	2001	2	2	20000710SH012    	1	20000225	G	7120	365A51103300	MOUNT           			AEROSP	AS365 	AS365N2     	8680815	EU  										ENGINE	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	272NE	3235 				6435				AIRFRAME ENGINE MOUNT IS CRACKED IN TWO PLACES BEYOND LIMITS FOR REPAIR IAW MANUFACTURER''S MM.  CRACKS OCCURRED AT FAST	ENING HOLE AREAS.  REPLACED WITH NEW PART.  (X)					1	G	7	2 	3U			RT	H10EU   					 
2001020200022	20010202	00022	NE  	2001	2	2	20000710SH014    	1	20000614	G	5320	7620105002114	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				36085				CAP ANGLE FOUND CRACKED.   PART WILL BE REPLACED WITH NEW ASSY IAW MANUFACTURERS MM AND REPAIR PROCEDURES.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200023	20010202	00023	NE  	2001	2	2	20000710SH015    	1	20000621	G	5320	7608020041101	PLATE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				PLATE CORRODED.  CORRODED PART WILL BE REPLACED WITH NEW PART.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200024	20010202	00024	NE  	2001	2	2	20000710SH016    	1	20000621	G	5320	7608020041103	DOUBLER         			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				DOUBLER SHOWED SIGNS OF CORROSION.  CORRODED PART WILL BE REPLACED WITH NEW PART.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200025	20010202	00025	NE  	2001	2	2	20000710SH017    	1	20000621	G	5320	7608020041102	DOUBLER         			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				36085				DOUBLER CORRODED.  THE CORRODED PART WILL BE REPLACED WITH NEW PART. (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200026	20010202	00026	NE  	2001	2	2	20000710SH018    	1	20000619	G	5320	7620204002114	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				ANGLE FOUND CORRODED.  PART WILL BE REPLACED WITH A NEW UNIT.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200027	20010202	00027	NE  	2001	2	2	20000710SH019    	1	20000619	G	5320	RMLH257780	NUT             			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				BARREL NUT FOUND CRACKED IN SEVERAL PLACES.  REPLACED WITH NEW PART.  C/W ASB 76-66-30.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200028	20010202	00028	NE  	2001	2	2	20000710SH020    	1	20000619	G	5320	7620204002107	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				ANGLE FOUND CORRODED.  PART WILL BE REPLACED WITH A NEW UNIT.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001030200003	20010302	00003	NE  	2001	3	2	20000710SH021    	1	20000608	G	5321	7620204002117	FLOOR PANEL     			SKRSKY	S76   	S76B        	8143007	NE  										CABIN	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				DECK CRACKED.						1	G	7	2 	4U			 	H1NE    					 
2001020200029	20010202	00029	NE  	2001	2	2	20000710SH022    	1	20000608	G	5320	7620105002101	WEB             			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				WEB CRACKED.						1	G	7	2 	4U			 	H1NE    					 
2001020200030	20010202	00030	NE  	2001	2	2	20000710SH023    	1	20000608	G	5320	7620105002115	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				ANGLE CRACKED.						1	G	7	2 	4U			 	H1NE    					 
2001020200031	20010202	00031	NE  	2001	2	2	20000710SH024    	1	20000608	G	5320	7607020532101	STRAP           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				STRAP CRACKED.						1	G	7	2 	4U			 	H1NE    					 
2001020200032	20010202	00032	NE  	2001	2	2	20000710SH025    	1	20000608	G	5320	7620204002124	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				ANGLE CRACKED.						1	G	7	2 	4U			 	H1NE    					 
2001020200033	20010202	00033	NE  	2001	2	2	20000710SH026    	1	20000608	G	5320	7620105002117	ANGLE           			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	280TR	3951 				760344				ANGLE CRACKED.						1	G	7	2 	4U			 	H1NE    					 
2001020200034	20010202	00034	EU  	2001	2	2	20000711SH001    	1	20000611	G	6320	4638001001	TRANSMISSION    			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	MAKING METAL    	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	17	5417J		1105 			S798				MAIN ROTOR CHIP LIGHT CAME ON IN-FLIGHT AND WOULD NOT PULSE OFF.  AFTER REMOVAL OF MAIN ROTOR CHIP DETECTOR AND MAIN ROT	OR OIL FILTER, FOUND STEEL SLIVERS AND CHIPS, BRONZE IN THE FILTER, AND OIL DRAINED.  TRANSMISSION REMOVED AND SHIPPED T	O EUROCOPTER CANADA FOR REPAIR.  TBO FOR THIS UNIT IS 3,000 HOURS. PART FAILED AT 1,104.5 HOURS SINCE OVERHAUL.   (X)				1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2000101600308	20001016	00308	EA  	2000	10	16	20000711SH002    	2	20000614	G	8520	LW12186	NUT             	LYC         		GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  						SEPARATED       	E				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	15	524HW		1380 			1533191	L210748			LEFT ENGINE LOST OIL PRESSURE.  FEATHERED IN-FLIGHT.  DISASSEMBLED ENGINE.  ROD, P/N 75061, ON NR 4 CYLINDER BROKEN AND 	IT LOOKS AS IF ONE NUT CAME LOOSE CAUSING THE FAILURE.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000101600309	20001016	00309	SO  	2000	10	16	20000711SH004    	1	20000605	G	5310	1713444	FRAME           			PIPER 	PA23  	PA23250     	7102308	SO  											CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	250MC					277305142				FUSLAGE FRAME TUBES FOUND BADLY CORRODED ON ANNUAL INSPECTION.  WATER SOAKED INSULATION FOUND IN CONTACT WITH AFFECTED T	UBES.  SUBMITTER SUSPECTED WATER INGRESS FROM BADLY FITTING CABIN DOOR AND PV WINDOW SEALS.   SUBMITTER RECOMMENDED THE 	UNDER FLOOR AREA BELOW THE CABIN DOOR AND PV WINDOW BE INSPECTED ON ALL AIRCRAFT OF A SIMILAR DESIGN TO THE PA23 FOR WAT	ER INGRESS, AND CORROSION.  DAMAGED AND WATER SOAKED INSULATION BLANKETS BE REPLACED.  EXTRA WATER DRAINS BE INSTALLED T	O LOWER FUSELAGE AREA IN ORDER TO MINIMIZE THE RISK OF WATER PUDDLES FORMING.  (X)		1	L	7	2 	3O			 	1A10    					 
2000101600311	20001016	00311	SO  	2000	10	16	20000711SH006    	1	20000603	G	3232	758440	ROD END         	WIEBEL      		PIPER 	PA42  	PA421000    	7104225	SO  										RT MAIN GEAR	BROKEN          	B			SO5R	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			NE	03	325KW	4083 				425527025				RIGHT MAIN LANDING GEAR ACTUATOR ROD END BROKE IN HALF WHERE PIVOT BALL IS RETAINED.  NOT SURE WHETHER IT BROKE ON UP OR	 DOWN CYCLE.  AFTER FAILURE, GEAR WOULD NOT COMPLETELY LOCK.  BLOW DOWN SYSTEM AND HAND PUMP WERE NOT ABLE TO WORK WITH 	ROD END BROKEN.  GEAR WAS EXTENDED, BUT SLOWLY COLLAPSED UPON LANDING.  FAILURE MAY HAVE BEEN CAUSED BY MACHINING MARKS 	ON ROD END OR BY LACK OF PROVISION FOR A DOWN-CYCLE STOP NUT ON THE ACTUATOR SHAFT.    (X)			1	L	7	2 	4T			RT	A23SO   					 
2000101600312	20001016	00312	SO  	2000	10	16	20000711SH007    	1	20000615	G	2434	ES4032	ALTERNATOR      			PIPER 	PA28  	PA28181     	7102807	SO  											BROKEN          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	354MR	147  				2843315				HOLES DISCOVERED IN LOWER AND UPPER ENGINE COWLING ON LEFT SIDE.  REMOVED COWL AND FOUND ALTERNATOR COOLING FAN BROKEN C	AUSING DAMAGE TO COWL.  REPAIRED COWL AND REPLACED FAN ASSY WITH NEW PART.  SUBMITTER STATED IT APPEARED THAT THE ''DISH	ED'' FRONT PLATE WAS ON BACKWARDS.  (X)				1	L	7	1 	3O			 	2A13    					 
2000101600313	20001016	00313	WP  	2000	10	16	20000711SH008    	1	20000602	G	3240		BRAKE ASSY      			SUPAC 	LA    	LFA         	8730208	WP  											SEIZED          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	11	34783					239				UPON DEPARTURE, PILOT LOST DIRECTIONAL CONTROL DUE TO THE LEFT BRAKE SEIZING.  AIRCRAFT RECEIVED SUBSTANTIAL DAMAGE.  AT	 INSPECTION, BROKEN ASSY WAS FOUND DRAGGING, BUT WHEN CHECKED A SECOND TIME, IT ROTATED FREELY.  NO CAUSE WAS FOUND.  (X	)				1	L	7	1 	3O			 	A730    					 
2000101600314	20001016	00314	CE  	2000	10	16	20000712SH001    	1	20000712	G	2800	112054E	VENT LINE       			BEECH 	100   	A100        	1152915	CE  										LEFT & RIGHT WIN	FAILED          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	102FG	150  	150  			B131				OPERATIONAL CHECKS AT INSPECTION INTERVALS TYPICALLY FIND THE VENT HEATS INOPERATIVE DUE TO THE ELECTRICAL CONNECTION ON	 THE TUBE ITSELF.  USING A PROBE AND INSERTING IN THE HOLE WHERE THE HEATING COIL TERMINATES PRODUCES A SPARK AND THEN T	HE COIL WILL HEAT PROPERLY AFTER THE CONNECTION IS MADE. THIS DEFECT IS FOUND NEARLY EVERY INSPECTION ON TWO KING AIRS. 	 SUBMITTER STATED A REDESIGN OF THE TERMINATION WOULD MOST LIKELY CURE THE EXISTING POOR CONNECTION.  (X)			1	L	7	2 	3T			 	A14CE   					 
2001020200036	20010202	00036	NE  	2001	2	2	20000712SH007    	1	20000404	G	6510		DRIVE SHAFT     			SKRSKY	S76   	S76B        	8143007	NE  										TAIL ROTOR	CORRODED        	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	421MK	5285 				760354				SUSPECTED CORROSION ON SHAFT TUBE AREA, BLISTERING.  REPLACED SHAFT WITH A NEW UNIT IAW SIKORSKY MM.  (X)						1	G	7	2 	4U			 	H1NE    					 
2001020200037	20010202	00037	EU  	2001	2	2	20000712SH008    	1	20000301	G	2910		LINE            			SNIAS 	350   	AS350B3     	8680954	EU  										MO4 TO MO5	LEAKING         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5226R	500  				3144				THE MO4 TO MO5 FLEX LINE STARTED LEAKING AT 500 HOURS.  THE LEAK WAS IN THE AREA OF THE FLEX BRAID AND COULD NOT DETECT 	ANY EXTREME DAMAGE OF THE FLEX LINE.  REPLACED WITH NEW FLEX LINE AND PERFORMED LEAK CHECK OK.  (X)					1	G	7	1 	3U			 	H9EU    					 
2000101600315	20001016	00315	SO  	2000	10	16	20000712SH011    	1	20000622	G	5553	AN311	BOLT            			PIPER 	PA28  	PA28140     	7102802	SO  										STABILATOR	DAMAGED         	D				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	23	6467R					281655				DURING ANNUAL INSPECTION, THE CONTROL SURFACES WERE FOUND TO HAVE NEVER BEEN RE-BALANCED AFTER THE AIRCRAFT HAD BEEN RE-	PAINTED SOMETIME PRIOR.  WHEN REMOVING THE STABILATOR, IT WAS FOUND THAT THE MOUNTING BOLTS COULD NOT BE REMOVED WITHOUT	 BEING CUT OFF.  ON CLOSER INSPECTION UPON REMOVAL, THE BOLTS HAD BEEN DEFORMED WITH A JOGGLE/BEND FORMED IN THE SHANK. 	 AFTER REMOVING PAINT FROM THE BOLT HEADS, FOUND THAT AN3 BOLTS WERE INSTALLED INSTEAD OF THE STRONGER NAS1104-17 AS SPE	CIFIED IN THE PARTS MANUAL.  PRIOR TO REMOVAL, THE BOLTS APPEARED NORMAL AND UNDAMAGED.  HIGH LOADS ON THE STABILATOR AN	D  INCORRECT HARDWARE WERE POSSIBLE CAUSES.  (X)	1	L	7	1 	3O			 	2A13    					 
2000100300253	20001003	00253	CE  	2000	10	3	20000712SH012    	1	20000615	G	2434	DOFF10300J	HOUSING         			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  					ALT BOLTS	LOOSE           	A			WVBA	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			AL	01	756DJ		96   			U20604005	812407R			PILOT REPORTED ALTERNATOR INOPERABLE AT TAKEOFF POWER.   AT IDLE, ALTERNATOR APPEARED TO OPERATE NORMALLY.  UPON EXAMINA	TION, FOUND THE COARSE THREAD INTERNAL WRENCHING BOLTS HOLDING THE ALTERNATOR CASE HALVES WERE LOOSE, WHICH AT HIGH ENGI	NE RPM, CAUSED THE CASE TO FLOAT ON THE ARMATURE DRIVING THE ALTERNATOR OFF-LINE.  SUBMITTER SUGGESTED MANUFACTURER OR O	VERHAUL FACILITY SHOULD CONSIDER A HIGHER TORGUE VALUE ON THESE BOLTS TO CURTAIL FURTHER RROBLEMS.  THIS WAS THE SECOND 	OCCURRENCE ON THIS AIRCRAFT WITHIN A  100-HOUR TIME FRAME.  (X)		1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001020200039	20010202	00039	NE  	2001	2	2	20000712SH014    	1	20000614	G	5320	RMLH257780	NUT             			SKRSKY	S76   	S76B        	8143007	NE  										FUSELAGE	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	9NJ	347  				760345				BARREL NUT IS CRACKED.  THE PART HAS BEEN IN SERVICE FOR 346.7 HOURS.  ALL BARREL NUTS WILL BE REPLACED WITH NEW UNITS. 	 ALL WORK DONE IAW MFG MM.  (X)					1	G	7	2 	4U			 	H1NE    					 
2001020200040	20010202	00040	NE  	2001	2	2	20000712SH015    	1	20000613	G	6320		CASE            			SKRSKY	S76   	S76B        	8143007	NE  										TRANSMISSION	CRACKED         	B			EGRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	9NJ		1013 		A23100024	760345				MAIN TRANSMISSION HAS CRACK ON THE UPPER CASE IN THE AREA OF THE RIGHT REAR MOUNT LEG.  (X)						1	G	7	2 	4U			 	H1NE    					 
2000101800112	20001018	00112	CE  	2000	10	18	20000712SH020    	1	20000424	G	5711	122210630	SPAR            			CESSNA	206   	U206G       	2073356	CE  										RT WS 126	CRACKED         	B			SMTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	783	2750 				U20606524				DURING ROUTINE INSP, NOTED THE RT WING AFT SPAR WEB CRACKED IN 5 PLACES AND THE ROLL SERVO ATTACH BRACKET 60931 CRACKED 	AT THE OTBD SERVO ATTACH HOLE.  ALL CRACKS ARE IN VICINITY OF S-TEC ROLL SERVO BRACKET ATTACHMENT BOLTS.  S-TEC TWO AXIS	 AUTOMATIC FLIGHT GUIDANCE SYS, MODEL ST-208-50 INSTALL IS APPROVED VIA S-TEC CORP STC SA5216SW-D AND ELIGIBLE TO BE INS	TALLED ON ACFT WHEN MODIFIED PER R/STOL SYS.   STC SA1513WE (ROBERTSON STOL) WHICH THIS ACFT HAS BEEN MODIFIED OR STC SA	3634SW, WHICH ACFT HAS NOT BEEN MODIFIED.  SPAR REPLACED WITH NEW CESSNA P/N 1222106-30.  NEW SPAR INSTALLED AND NOT MOD	IFIED WITH ROLL SERVO ATTACHMENT HOLES.  S-TEC AUTOPILOT DISABLED IAW FAR REG PART 91.213.  TT SINCE STC''S, 1,348.2 HRS	1	H	7	1 	3O			 	A4CE    					 
2000101800114	20001018	00114	WP  	2000	10	18	20000712SH022    	1	20000623	G	3246	152059	WHEEL           	BENDIX      		DOUG  	DC8   	DC8*        	       	WP  										SPOKE AREA	CRACKED         	B			INWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										NDT INSPECTION SHOWED CRACK INDICATION AT SPOKE AREA.						2	L	7	4 	4J			F	4A25    					 
2000101800115	20001018	00115	CE  	2000	10	18	20000712SH023    	1	20000620	G	5610	531126111	WINDOW          			CESSNA	340   	340CESSNA   	2076404	CE  											DEPARTED        	H				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	09	69554					3400369				AT FLIGHT LEVEL 11,500 FEET, WINDOW BLEW OUT.  DETERMINED THAT CESSNA SB HAD NOT BEEN DONE (SK340-26).  (X)						1	L	7	2 	3O			 	3A25    					 
2000101800118	20001018	00118	CE  	2000	10	18	20000712SH029    	1	20000712	G	7921	1E1337652660	COOLER          			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520*      	17032	SO  					OIL TUBE	LEAKING         	B			RF3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23										COOLER HAD RECEIVED PREVIOUS EPOXY REPAIRS.  EPOXY FAILED DURING NORMAL USE. SUBMITTER RECOMMENDED ELIMINATING EPOXY USE	 IN OIL COOLERS AS EPOXY FAILURE IS COMMON OCCURRENCE WHEN USED TO REPAIR LEAKS IN OIL COOLERS.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000101800074	20001018	00074	CE  	2000	10	18	20000712SH033    	1	20000621	G	7921	8524295	COOLER          	CONT        		CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  					CORE	LEAKING         	B			RF3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23										PART HAD BEEN REPAIRED USING EPOXY TO STOP A LEAK.  DURING NORMAL SERVICE, EPOXY FAILED CAUSING THE OIL COOLER TO LEAK A	T POINT OF ORIGINAL REPAIR.  SUBMITTER RECOMMENDED ELIMINATING USE OF EPOXY IN OIL COOLERS AS EPOXY FAILURE IS COMMON.  	(X)				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001020500028	20010205	00028	NE  	2001	2	5	20000712SH044    	2	20000628	G	7250		BLADE           	GE          							GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	FRACTURED       	B			EX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		712  					299091			TWO EACH STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAGE	 BLADES AND AFT FAN SECTION.  SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS I N THE ENGINE MANUAL TO DETEC	T THINNING/NECKING OF THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION.  THINNING OF THE BLADE AIRFOIL C	ROSS-SECTION RESULTS IN BLADE FRACTURE.  (X)								4	F			E7EA				 
2001020500029	20010205	00029	NE  	2001	2	5	20000712SH045    	2	20000628	G	7250		BLADE           	GE          							GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	FRACTURED       	B			EX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15			712  				299091			TWO EACH STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAGE	 BLADES AND AFT FAN SECTION.  SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS I N THE ENGINE MANUAL TO DETEC	T THINNING/NECKING OF THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION.  THINNING OF THE BLADE AIRFOIL C	ROSS-SECTION RESULTS IN BLADE FRACTURE.  (X)								4	F			E7EA				 
2000101800044	20001018	00044		2000	10	18	20000712SH047    	4	20000622	G	6122	G210569	GOVERNOR        	WOODWARD    		BNORM 	BN2   	BN2         	1520202	EU  	LYC   	O540  	IO540*      	41532	EA  						MALFUNCTIONED   	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										RELEVANT INDICATION ON GOVERNOR BODY. (X)						1	H	7	2 	3O	3	O	 	A17EU   	1E4				 
2000101800045	20001018	00045	EA  	2000	10	18	20000712SH048    	2	20000628	G	8520	LW17060	CRANKSHAFT      	LYC         		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 3 THROW	BROKEN          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SW	99	8189T	5487 	1281 			288016309	L1330539A			DURING TAKEOFF, ENGINE QUIT WHEN AIRCRAFT WAS AT 200 FEET AGL.  AIRCRAFT CRASHED INTO A SWAMP.  AIRCRAFT WAS DESTROYED, 	OCCUPANTS RECEIVED MINOR INJURIES.  DURING POST-CRASH INVESTIGATION, THE ENGINE CRANKSHAFT WAS FOUND BROKEN AT THE NR 3 	ROD BEARING JOURNAL FORWARD THROW AT THE ENTER MAIN BEARING JOURNAL.  ENGINE TT IS 5,487 HRS AND TSO IS 1,281 HRS.  NOTE	D IN THE MAINTENANCE RECORDS FOR THE ENGINE THAT A PROP STRIKE OCCURRED WITH APPROX 1,500 HRS TT.  AT THAT TIME, ONLY A 	FLANGE RUN-OUT CHECK WAS ACCOMPLISHED.  SUBMITTER SUGGESTED THAT THE CRANKSHAFT BE REPLACED AFTER ANY SUDDEN STOPPAGE OR	 PROP STRIKE.  (X)	1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000080700097	20000807	00097	NE  	2000	8	7	20000713SH001    	2	20000711	G	7421	ER400	SPARK PLUG      	PWA         	AN1         	AYRES 	S2    	S2RRESTD    	0970101	SO  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	ENGINE	BROKEN          	G			KIIG	A	 			UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	15	82494				7P102181	1541R	7P102181	SW2837		SPARK PLUG FAILED INTERNALLY.  COMBUSTION GASSES BURNT OFF THE SPARK PLUG LEAD AND VENTED EXTERNALLY, RESULTING IN LOST 	COMPRESSION AND POWER OUTPUT.  (INT)					1	L	7	1 	3R	3	R	 	A4SW    	5E2	5	C	P257	 
2000101800048	20001018	00048	CE  	2000	10	18	20000713SH005    	1	20000609	G	2450		CIRCUIT BREAKER 			CESSNA	172   	172M        	2072418	CE  										ALTERNATOR OUTP	FAILED          	G				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NE	03	12766	4622 				17262240				ALTERNATOR OUTPUT BREAKER FAILED IN IFR FLIGHT.  BREAKER HAD NO CONTINUITY IN CLOSED (NOT TRIPPED) CONDITION.  ORIGINAL 	CIRCUIT BREAKER FROM DATE OF MFG 9/73.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001030200004	20010302	00004	CE  	2001	3	2	20000713SH006    	1	20000626	G	7160		PAINT           			CESSNA	208   	208B        	2073701	CE  										INERTIAL SEPARAT	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1289Y	198  				208B0818				DURING THE FIRST PHASE 1 INSPECTION, AN AREA APPROXIMATELY 3 INCHES SQUARE ON THE INSIDE BOTTOM OF THE INERTIAL SEPARATO	R HAD LOOSE EPOXY PAINT PEELING LOOSE.  15 GRAMS OF CHIPS REMOVED WITH FINGERNAIL.  AN UNKNOWN MOUNT WAS MISSING AND PRE	SUMABLY WENT THROUGH THE ENGINE.  NO DAMAGE WAS NOTED DURING INSPECTION OF NR 1 COMPRESSOR WHEEL.  SUBMITTER RECOMMENDED	 THAT AFTER THIS PART IS DIP PAINTED, IT BE DRIED IN AN UPRIGHT POSITION TO ALLOW EXCESS PAINT TO DRAIN.  (X)			1	H	7	1 	3T			 	A37CE   					 
2000120700004	20001207	00004	SO  	2000	12	7	20000713SH009    	2	20000713	G	8520		CASE            			BEECH 	58    	58TC        	1152746	CE  	CONT  	O520  	TSIO520L    	17040	SO  						CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1865L	1084 	764  			TK14	227668R			CASE FOUND CRACKED AT NR 5 CYLINDER STUD NR 3, NUT ON STD NR 7 LOOSE AND STUD NR 8 PULLED FROM CASE AND RESTING ON CYLIN	DER COOLING FINS.  (X)					1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001020500041	20010205	00041	SO  	2001	2	5	20000713SH010    	2	20000222	G	8520	SA10200A1	CASTING         			LUSCOM	8     	8A          	8190104	SO  	CONT  	C90   	C908F       	17009	SO  					ENGINE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	1970B	100  				6397	4685098			DURING ANNUAL INSPECTION, OIL WAS FOUND LEAKING NEAR BOTTOM OF ROCKER COVERS.  THE LEAK WAS TRACKED TO THE CASTING LINE 	BETWEEN THE VALVE GUIDES IN THE FIN AREA.  LOCATION OF THE PROBLEM IS THE SAME ON ALL 4 CYLINDERS.  LEAK SEEMED TO BE CA	USED BY POROSITY IN CASTING LINE.    (X)				1	H	7	1 	3O	3	O	 	A694    	E252				 
2000102600001	20001026	00001	CE  	2000	10	26	20000713SH023    	1	20000514	G	3230	HEIMHML6	ROD END         			BEECH 	35    	J35         	1151522	CE  										N/G RETRACT ROD	BROKEN          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	03	263AA					D5581				PILOT WAS TAXIING OUT FOR TAKEOFF WHEN NOSE GEAR SUDDENLY RETRACTED CAUSING SUDDEN STOPPAGE OF ENGINE.  FOUND ROD END BR	OKEN AT AFT END OF NOSE GEAR RETRACT ROD WHERE IT ATTACHES TO GEAR ACTUATOR.  SUBMITTER RECOMMENDED CLOSER INSPECTION AT	 ANNUAL.  (X)				1	L	7	1 	3O			 	3A15    					 
2000102600002	20001026	00002	EA  	2000	10	26	20000713SH024    	2	20000613	G	8530		PLUG            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					IN PISTON	FAILED          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	40258	163  				277305068				PISTON PIN PLUG FAILED AND FILLED THE ENGINE WITH ALUMINUM.  THESE ARE THE SEPARATE PUSH IN LARGE DIAMETER PLUGS.  INSTA	LLATION DATE:  7/98.  (X)					1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2000102600003	20001026	00003		2000	10	26	20000713SH025    	4	20000510	G	3416	5932A3	ALTIMETER       			PIPER 	PA32  	PA32300     	7103212	SO  										INSTR PANEL	DEFECTIVE       	B			GCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4210R					3240575				PERFORMED PITOT/STATIC CERTIFICATION IAW FAR 91.411 AND TRANSPONDER CERTIFICATION IAW FAR 91.413.  FOUND DEFECTIVE ALTIM	ETER AND REPLACED WITH NEW INSTRUMENT.  PERFORMED CORRESPONDENCE TEST IAW FAR PART 43 APP E PARA (C).  NO FURTHER PROBLE	MS SEEN.  (X)				1	L	7	1 	3O			 	A3SO    					 
2000102600005	20001026	00005	CE  	2000	10	26	20000714SH008    	1	20000304	G	2730	053200135	ADAPTER         			CESSNA	172   	172F        	2072414	CE  										RT ELEVATOR	FRETTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	5320R	4020 				17252844				DURING ANNUAL CONDITION INSP, RT ELEVATOR WAS FOUND LOOSE ON THE TORQUE TUBE. FURTHER INVESTIGATION REVEALED THE RIVETS 	 HOLDING THE TORQUE TUBE ADAPTER (PN 0532001-35) WERE FRETTING AND IT WAS DETERMINED TO BE THE CAUSE OF THE LOOSE CONDIT	ION.  SUBMITTER STATED THIS IS THIRD CONDITION FOUND ON CESSNA ACFT.  POSSIBLY CAUSED BY HIGH WINDS AND/OR VIBRATION CAU	SED BY PROP WASH.  (X)			1	H	7	1 	3O			NT	3A12    					 
2000120700005	20001207	00005	GL  	2000	12	7	20000714SH024    	3	20000616	G	6111	V84334R	BLADE           	HARTZL      		BEECH 	35    	S35         	1151532	CE  	CONT  	O520  	IO520BA     	17032	SO  	HARTZL	HCA3V	PHCA3VF4    	GL  	V-GROOVE SHANK	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	87K					D7607		BL137		PROPELLER SUBMITTAL FOR AD 97-18-02 INITIAL INSPECTIONS.  S/N A69152 (BLADE NR 1) FOUND CRACKED IN AREA OF A/O?????? USI	NG EDDY CURRENT INSPECTION EQUIPMENT.  NOTE:  A/O??????WAS OVERDUE.  SUBMITTER STATED SHOULD HAVE BEEN COMPLETED NO LONG	ER THAN SEPT, 1999.  (X)				1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P6EA	 
2000071800130	20000718	00130	EA  	2000	7	18	20000714SH029    	2	20000714	G	8530		VALVE SEAT      			CESSNA	206   	T206H       	       	CE  	LYC   	O540  	TIO540AF1A  	41532	EA  					EXHAUST	LOOSE           	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	2638U					T20608061	L1018861A			AIRCRAFT HAD ENGINE FAILURE AT 79 FLIGHT HOURS. THE NR 1 CYLINDER EXHAUST VALVE SEAT CAME LOOSE FROM THE CYLINDER AND CA	USED SIGNIFICANT DAMAGE TO THE ENGINE.  THE OUTSIDE DIAMETER OF THE EXHAUST VALVE SEAT WAS FOUND UNDERSIZED.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2000071800131	20000718	00131	NE  	2000	7	18	20000714SH030    	2	20000627	G	7412	CH346593	IGNITER         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					CENTER ELECTRODE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	37WP	148  				5600259	PCE108497			DURING PHASE 2 INSPECTION, LEFT ENGINE INBOARD IGNITER PLUG WAS FOUND TO HAVE APPROXIMATELY .6250 INCH OF THE CENTER ELE	CTRODE MISSING ON THE FIRING END.  IT APPEARS THE ELECTRODE DEPARTED SHORTLY AFTER IGNITER PLUG INSTALLATION DUE TO VERY	 SLIGHT WEAR ON THE FIRING END OF PLUG.  THE HP TURBINE BLADES BORESCOPED BY PRATT & WHITNEY REP WITH NO DISCREPANCIES N	OTED.   (X)			2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2000071800132	20000718	00132	SW  	2000	7	18	20000714SH031    	1	20000601	G	2121	19A2501	BLOWER MOTOR    			BELL  	412   	412         	1182202	SW  											INOPERATIVE     	A			XSFA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	412SA					33210				BLOWER MOTOR INOPERATIVE.  (X)						1	G	7	2 	4U			 	H4SW    					 
2000071800133	20000718	00133	CE  	2000	7	18	20000714SH032    	1	20000625	G	2820	RSA5AD1	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	O360*       	41514	EA  					FUEL ENG	VAPOR LOCK      	D				O				OTHER                   				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			NM	03	567JW	590  				172S8187				ACFT WAS ON NIGHT FLIGHT AND COMPLETED 5 LANDINGS.  FULL STOP ON RUNWAY, THEN TAKING OFF.  ON THE 6TH LANDING WHEN THROT	TLE WAS RETARDED OVER THE RUNWAY THRESHOLD, ALTERNATOR LIGHT ILLUMINATED AND ON ROLL-OUT, ENGINE QUIT.  ATTEMPTS WERE MA	DE TO RESTART, BUT  WOULD NOT RESTART.   ACFT TOWED TO PARKING.  MAINTENANCE INSPECTED AND STARTED ENG WITH NO DIFFICULT	IES.  ALL OPERATING PERIMETERS NORMAL, IDLE SPEED, AND MIXTURE STRENGTH NORMAL.  UPON RETURN HOME, ACFT DIVERTED FOR 1 H	R DUE TO THUNDERSTORMS, THEN TOOK OFF, RETURNED HOME.  UPON ARRIVAL, ENG IDLE WAS ROUGH, IDLE SPEED ERRATIC.  ENG SHUT D	OWN, RESTART ATTEMPTED, VAPOR LOCKED.   RESTARTED END, NO DIFFICULTIES.  FUEL SERVO SENT TO CESSNA FOR EXAMINATION.  (X)	1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2000071800134	20000718	00134	CE  	2000	7	18	20000714SH033    	1	20000629	G	2600		SWITCH          	CESSNA      		CESSNA	208   	208B        	2073701	CE  										INST PANEL	SHORTED         	C			AWHA	A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			WP	17	790FE					208B0288				PILOT REPORTED AFTER REPEATED ACTUATIONS OF FIRE DETECTION WARNING TEST SWITCH, SWITCH BUTTON DETACHED FROM SWITCH BODY 	CAUSING SWITCH TO SHORT AND ACTIVATE WARNING HORN.  PILOT DECLARED AN EMERGENCY AND DIVERTED TO BUR AIRPORT WITHOUT INCI	DENT.  (X)				1	H	7	1 	3T			 	A37CE   					 
2000071800196	20000718	00196	CE  	2000	7	18	20000714SH034    	1	20000622	G	3250	2609	CLIP            	MAULE       		BBAVIA	11    	11AC        	0191102	CE  										STEERING SPRING	SEPARATED       	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	07	85861					11AC284				CONNECTOR CLIP PULLED OPEN ALLOWING STEERING SPRING TO COME LOOSE OF TAIL WHEEL STEERING HORN RESULTING IN A LOSS OF LEF	T STEERING CONTROL.  (X)					1	H	7	1 	3O			 	A761    					 
2000071800002	20000718	00002	CE  	2000	7	18	20000717SH007    	1	20000627	G	7120	045100336	MOUNT           			CESSNA	150   	152         	2071835	CE  										LOWER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	89433	6203 				15282743				LOWER WELD AT LOWER NLG STRUT SLEEVE BROKEN ON ENGINE MOUNT.  SUSPECT FATIGUE OR OVERTORQUING OF LOWER STRUT MOUNT BOLT 	AS CAUSE OF CRACK.  POSSIBLE NOSE HARD LANDING CONTRIBUTED TO PROBLEM.  (X)					1	H	7	1 	3O			NT	3A19    					 
2000071800004	20000718	00004	CE  	2000	7	18	20000717SH008    	1	20000627	G	7120	05510231	MOUNT           			CESSNA	172   	172N        	2072434	CE  											BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	733VS	3586 				17268588				DURING 100-HOUR INSPECTION, FOUND LOWER CROSSOVER TUBE ON ENGINE MOUNT BROKEN ON RT SIDE AND CRACKED ON LT SIDE (BOTH AT	 WELDS).  POSSIBLE CAUSES ARE WORN SHOCK MOUNTS CAUSING EXCESS VIBRATION OR FATIGUE.  SUBMITTER RECOMMENDED MAKING SURE 	MOUNT IS CLEAN TO  FACILITATE THOROUGH INSPECTION.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000071800007	20000718	00007	EA  	2000	7	18	20000717SH010    	2	20000610	G	8520		CRANKSHAFT      			UNIVAR	108   	1082        	9230406	NM  	FRNKLN	6A4165	6A4165B3    	27025	EA  						FAILED          	G				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	21	9830K					1082830				ENGINE BEGAN RUNNING ROUGH AND THEN THE PROPELLER LOCKED IN THE VERTICAL POSITION.  POST-INCIDENT INSPECTION OF THE ENGI	NE REVEALED THE CRANKSHAFT HAD FAILED.  (X)					1	H	7	1 	3O	3	O	 	A767    	E238				 
2001020700102	20010207	00102	NE  	2001	2	7	20000717SH012    	2	20000629	G	7250		BLADE           	GE          							GE    	CJ610 	CJ6109      	30006	NE  					ENGINE	FRACTURED       	B			EX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		4709 	1917 		GATWZA0442		222060			TWO EACH, STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAG	E BLADES.  SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS IN THE ENGINE MANUAL TO DETECT THINNING/NECKING O	F THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION.  THINNING OF THE BLADE AIRFOIL CROSS-SECTION RESULTS	 IN BLADE FRACTURE.  (X)								4	J			1E16				 
2001020700114	20010207	00114	NE  	2001	2	7	20000717SH013    	2	20000628	G	7250		BLADE           	GE          							GE    	CJ610 	CJ6109      	30006	NE  					ENGINE	FRACTURED       	B			EX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		4709 	1917 		GATWZA00442		222060			TWO EACH, STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAG	E BLADES.  SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS IN THE ENGINE MANUAL TO DETECT THINNING/NECKING O	F THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION.  THINNING OF THE BLADE AIRFOIL CROSS-SECTION RESULTS	 IN BLADE FRACTURE.  (X)								4	J			1E16				 
2001012900031	20010129	00031	EU  	2001	1	29	20000717SH014    	1	20000416	G	6320		CONNECTOR       			SNIAS 	350   	AS350B2     	8680813	EU  										GEARBOX	CORRODED        	A			XSFA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	964SA	4905 				2931				CORRODED PINS AT DIFFERENT CANNON PLUGS AND CORRODED WIRES THROUGHOUT HARNESS.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900032	20010129	00032	EU  	2001	1	29	20000717SH015    	1	20000419	G	6410	350A332115300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DELAMINATED     	A			XSFA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	964SA	256  				2931				BEARING DELAMINATING.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900033	20010129	00033	EU  	2001	1	29	20000717SH016    	1	20000517	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE OIL	READS LOW       	A			XSFA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	964SA	4971 				2931				TRANSMITTER READING TOO LOW, NOT ACCURATE.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001012900034	20010129	00034	EU  	2001	1	29	20000717SH018    	1	20000606	G	6320		SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR INPUT	LEAKING         	A			XSFA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	13	985SA					3111				INPUT SEAL, MAIN ROTOR GEARBOX, LEAKING POST LIP.   (X)						1	G	7	1 	3U			 	H9EU    					 
2000100300050	20001003	00050	SW  	2000	10	3	20000718SH001    	1	20000608	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  											FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	524  			A283	53381				DURING IN-SHOP REPAIR, FOUND ROUGH BEARINGS.  INSTALLED SELF-CENTERING BEARINGS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200050	20010202	00050	SW  	2001	2	2	20000718SH002    	1	20000608	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	524  			A283	53381				DURING IN-SHOP REPAIR, FOUND ROUGH BEARINGS.  INSTALLED SELF-CENTERING BEARINGS.  REPLACED 2 EACH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200051	20010202	00051	SW  	2001	2	2	20000718SH003    	1	20000505	G	6420	406312100101	BEARING         	BELL        		BELL  	407   	407         	       	SW  										T/R YOKE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	644  			A487	53381				DURING DAILY SERVICE CHECK, FOUND INBOARD FEATHER BEARING WEAR, CAUSING THE OUTER RACE OF FEATHER BEARING TO SHIFT IN YO	KE CAUSING BORE TO WEAR BEYOND LIMITS.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020200052	20010202	00052	EU  	2001	2	2	20000718SH004    	1	20000628	G	7603	961305A57105300	BALL JOINT      			SNIAS 	350   	AS350B1     	8680811	EU  										POWER LEVER	DETACHED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	2127S					2213				DURING STARTING SEQUENCE, PILOT ATTEMPTED TO SHUT DOWN THE ENGINE DUE TO SLOW START.  ENG KEPT RUNNING, PILOT WENT TO EM	ERG SHUT OFF.  UPON INSP, POWER LEVER ''END'' HAD COME OFF OF ''BALL JOINT'' WHICH IS ATTACHED TO FUEL CONTROL.  THE SAF	ETY PIN THAT SAFTIES THE ''END'' RELEASE WAS IN PLACE.  NOTED THE ''END'' WOULD COME OFF THE ''BALL JOINT'' WHEN RELEASE	 WAS PRESSED INSPITE OF SAFETY PIN BEING IN PLACE.  IT IS RECOMMENDED THAT INSP CRITERIA FOR PARTS IN QUESTION (BALL JOI	NT AND THE END) BE ADDED TO APPROPRIATE MAINT WORK CARDS AND PROCEDURE BE ADDED AS WELL.  COPY OF THIS MDR WILL BE SENT 	TO AMERICAN EUROCOPTER.  (X)	1	G	7	1 	3U			 	H9EU    					 
2001020200053	20010202	00053	SW  	2001	2	2	20000718SH005    	1	20000706	G	6310	206040047001	NUT             			BELL  	206   	206L3       	1182108	SW  										INPUT ADAPTER	OVERTORQUED     	B			NKVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	206DB	608  				52127				MECHANIC REPORTED THE M/R TRANSMISSION INPUT SHAFT ADAPTER RETAIING NUT SEEMED TO BE OVERTORQUED ON INSTALL OR PREVIOUS 	MAINTENANCE.  ESTIMATED TORQUE WAS AT LEAST TWICE THE BHT M.M. SPEC FOR THAT PART.  ADAPTER AND NUT MAGNAFLUXED FOR DEFE	CTS, NONE FOUND.  SUBMITTER RECOMMENDED SAME ACTION IF OTHER OPERATORS ENCOUNTED THIS PROBLEM.  (X)				1	G	7	1 	3U			 	H2SW    					 
2001020200054	20010202	00054	SW  	2001	2	2	20000718SH006    	1	20000403	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27545	2444 				45234				INSPECTION OF AIRCRAFT DURING REFURBISHING, FOUND INTERGRANULAR CORROSION OF LEADING EDGE OF MAIN ROTOR BLADES.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020200055	20010202	00055	SW  	2001	2	2	20000718SH007    	1	20000403	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27545	2699 				45234				INSPECTION OF AIRCRAFT DURING REFURBISHING FOUND INTERGRANULAR CORROSION OF LEADING EDGE OF MAIN ROTOR BLADES.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001012900039	20010129	00039	EU  	2001	1	29	20000718SH008    	1	20000621	G	6730	SC8032	SERVO           			AEROSP	SA365 	SA365N      	8680669	EU  										MAIN ROTOR	DAMAGED         	A			ZYWA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	09	365SJ	2718 				6018				SERVO LIGHT INTERMITTENT.  REMOVED AND REPLACED SERVO.  (X)						1	G	7	2 	3U			 	H10EU   					 
2001012900040	20010129	00040	EU  	2001	1	29	20000718SH009    	1	20000612	G	5260	14860011	ACTUATOR        			AEROSP	AS365 	AS365N2     	8680815	EU  										STOP	INOPERATIVE     	A			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM	34   				6429				STOP ACTUATOR MOTOR INOPERATIVE.  REMOVED AND REPLACED MOTOR.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001012900041	20010129	00041	EU  	2001	1	29	20000718SH010    	1	20000615	G	6230	365A3118SP02	ADAPTER         			AEROSP	AS365 	AS365N2     	8680815	EU  										MAIN ROTOR	TORN            	A			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM					6429				ONE EACH ADAPTER TORN AFTER 218.1 HOURS IN SERVICE.  REMOVED AND REPLACED FREQUENCY ADAPTERS.    REPLACED 2 EACH.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001012900042	20010129	00042	EU  	2001	1	29	20000718SH011    	1	20000615	G	6230	365A3118SP02	ADAPTER         			AEROSP	AS365 	AS365N2     	8680815	EU  										MAIN ROTOR	TORN            	A			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM	218  				6429				ONE EACH ADAPTER TORN AFTER 218.1 HOURS IN SERVICE.  REMOVED AND REPLACED FREQUENCY ADAPTERS.    REPLACED 2 EACH.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001012900043	20010129	00043	EU  	2001	1	29	20000718SH012    	1	20000622	G	6730	SC8031	SERVO           			AEROSP	SA365 	SA365N      	8680669	EU  										MAIN ROTOR	DAMAGED         	A			ZYWA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	09	365SJ	2149 				6018				SERVO LIGHT ILLUMINATING.  REMOVED AND REPLACED SERVO.  (X)						1	G	7	2 	3U			 	H10EU   					 
2001020200056	20010202	00056	SW  	2001	2	2	20000718SH013    	1	20000611	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3174Y	3428 				51038				DURING DAILY INSPECTION, FOUND HEAVY INTERGRANULAR CORROSION ON TRAILING EDGE EXTRUSION.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001012900044	20010129	00044	NE  	2001	1	29	20000718SH014    	1	20000508	G	3230		CONNECTOR       			SKRSKY	S76   	S76A        	8143006	NE  										PROX SWITCH	DIRTY           	A			ALGA	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			SW	03	376AL					760002				ON TAKEOFF, LANDING GEAR WOULD NOT RETRACT.  FOUND ''UP'' PROXIMITY SWITCH CANNON PLUG ON NOSE GEAR ACTUATOR DIRTY.  CLE	ANED AND REINSTALLED.  (X)					1	G	7	2 	3U			 	H1NE    					 
2001020200057	20010202	00057	SW  	2001	2	2	20000718SH015    	1	20000621	G	6320	407040006107	TRANSMISSION    			BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL	2487 			A327	53247				AT DISASSEMBLY FOR TRANSMISSIONS FIRST OVERHAUL, FOUND CORROSION IN BORE OF MOUNTING SPLINDLE.  CORROSION IN BORE OF CHI	P DETECTOR ASSY.  CORROSION ON INPUT FLANGE.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001012900045	20010129	00045	SW  	2001	1	29	20000718SH016    	1	20000614	G	6510	407340340101	DISC PACK       	BELL        		BELL  	407   	407         	       	SW  										T/R DRIVE	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467AL	1209 	25   		A457	53190				DURING 25-HOUR AD INSPECTION, FOUND THE LAST DISC IN THE COUPLING CRACKED (WITH PACK FACING FORWARD) MID-SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200058	20010202	00058	SW  	2001	2	2	20000718SH017    	1	20000527	G	6220	407310101101	BEARING         	BELL        		BELL  	407   	407         	       	SW  										MAIN ROTOR HUB	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	3185 	690  		A190	53172				DURING DAILY SERVICE CHECK, FOUND ELASTOMERIC SEPARATED FROM SPINDLE.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001012900046	20010129	00046	EA  	2001	1	29	20000718SH018    	2	20000622	G	7414	10357424	BEARING         			ROBSIN	R22   	R22BETAII   	7640110	NM  	LYC   	O360  	O360J2A     	41514	EA  					DIST BLOCK	FAILED          	A			MKWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	441MM	95   			L049915E	3057	L3727236A			LEFT MAGNETO FAILED. UPON DISASSEMBLY AND INSPECTION, FOUND THE BUSHING IN THE DISTRIBUTOR BLOCK WHERE THE DISTRIBUTOR G	EARSHAFT RIDES, HAD COME LOOSE.  THE LOOSE BUSHING HAD BADLY DAMAGED THE DISTRIBUTOR BLOCK ASSY.  (X)					1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2001013000037	20010130	00037	SW  	2001	1	30	20000719SH001    	1	20000501	G	6510	407340340101	DISC PACK       	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	607AL		25   		A1128	53264				DURING 25-HOUR AD INSPECTION, TAIL ROTOR DRIVESHAFT FOUND CRACKED.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200059	20010202	00059	SW  	2001	2	2	20000719SH002    	1	20000427	G	6510	407340339103	HOUSING         			BELL  	407   	407         	       	SW  										T/R BEARING	CRACKED         	C			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	331  			AFS1204	53284				DURING DAILY INSPECTION AND BEARING LUBRICATION, FOUND HOUSING CRACKED AND BLACK GREASE EXPELLED FROM AROUND THE  SEAL D	ETERMINING BEARING DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001013000038	20010130	00038	SW  	2001	1	30	20000719SH003    	1	20000427	G	6510	206061	HOUSING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	331  			AFS1204	53284				DURING DAILY INSPECTION AND BEARING LUBRICATION, FOUND HOUSING CRACKED AND BLACK GREASE EXPELLED FROM AROUND THE  SEAL D	ETERMINING BEARING DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020200060	20010202	00060	SW  	2001	2	2	20000719SH004    	1	20000416	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										SHAFT HANGER	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL	907  			A1669	53366				RECURRING 25-HOUR INSPECTION AND BEARING LUBRICATION (PER ASB 407-00-35 AND AD 2000-02-01), FOUND ACCUMULATED GREASE EXP	ELLED FROM AROUND THE SEAL IS BLACK DETERMINING BEARING IS DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020200061	20010202	00061	GL  	2001	2	2	20000719SH006    	2	20000601	G	7260	23007248	GEAR SHAFT      	ALLSN       		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEAR BOX	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	710AL	113  			CAG90802	760279	890266S			UPON ASSEMBLY OF GEARBOX  WHEN INSTALLING COUPLING , FOUND COUPLING WOULD NOT SIT COMPLETELY, STAYED COCKED.  REMOVED CO	UPLING AND INSPECTED.  FOUND IMPROPER MACHINING OF COUPLING MATING SURFACE TO F/C GEAR WITH PIECES OF ROLLED METAL.  FUE	L CONTROL GEAR HAD IMPROPER MACHINING AT COUPLING MATING SURFACE.  (X)				1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2000103100015	20001031	00015	SO  	2000	10	31	20000719SH008    	2	20000217	G	8530	SA52000A20P	GUIDE           								CONT  	O520  	IO520*      	17032	SO  						INACCURATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INTAKE GUIDE VARIANCE, 0.0020 INCH.  (X)											3	O			E5CE				 
2000103100016	20001031	00016	SO  	2000	10	31	20000719SH009    	2	20000217	G	8530	SA52000A20P	GUIDE           								CONT  	O520  	IO520*      	17032	SO  						INACCURATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INTAKE GUIDE VARIANCE, 0.0016 INCH.  (X)											3	O			E5CE				 
2000103100017	20001031	00017	SO  	2000	10	31	20000719SH010    	2	20000217	G	8530	52L9915	GUIDE           								CONT  	O520  	IO520*      	17032	SO  						INACCURATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INTAKE GUIDE VARIANCE, 0.0015 INCH.  (X)											3	O			E5CE				 
2000103100023	20001031	00023	SO  	2000	10	31	20000719SH011    	2	20000217	G	8530	SA52000A20P	GUIDE           								CONT  	O520  	IO520*      	17032	SO  						INACCURATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INTAKE GUIDE VARIANCE, 0.0016 INCH.  (X)											3	O			E5CE				 
2000110100030	20001101	00030	SO  	2000	11	1	20000719SH012    	2	20000217	G	8530	SA52000A20P	GUIDE           								CONT  	O520  	IO520*      	17032	SO  						INACCURATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INTAKE GUIDE VARIANCE, 0.0018 INCH.  (X)											3	O			E5CE				 
2000110100031	20001101	00031	SO  	2000	11	1	20000719SH013    	2	20000227	G	8530	SA52000A20P	GUIDE           								CONT  	O520  	IO520*      	17032	SO  						INACCURATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03										INTAKE GUIDE VARIANCE, 0.0020 INCH.  (X)											3	O			E5CE				 
2000073100207	20000731	00207	SO  	2000	7	31	20000719SH014    	2	20000519	G	8520	649134	CRANKSHAFT      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  						FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3469Y	63   				18502888	559906			PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2000091400001	20000914	00001	SO  	2000	9	14	20000719SH015    	2	20000519	G	8510	649134	CRANKSHAFT      			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  						FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9728B	19   				50026	506161			PER TCM MSB 00-5, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	5A6     	E273				 
2000091400002	20000914	00002	EU  	2000	9	14	20000719SH016    	1	20000705	G	3230	TB2061238001	PRESSURE SWITCH 		LANDINGGEAR 	SOCATA	TB20  	TB21        	8680697	EU  										HYDRAULIC SYSTEM	FAILED          	H				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			EA	07	30582	128  			W51148	1618				PILOTS REPORTED LANDING GEAR WOULD NOT RETRACT, CHECKED FUSES, ALL OK.  BYPASSED PRESSURE SWITCH.  GEAR RETRACTED, INSTA	LLED NEW PRESSURE SWITCH, PN TB206138001, SYSTEM CHECKED OK.  NOTE: SEVERAL PRESSURE SWITCHES HAVE BEEN REPLACED.  PART 	TT 128.1 HOURS, SWITCH WAS INSTALLED 3-16-00. (X)				1	L	7	1 	3O			RT	A51EU   					 
2000091400003	20000914	00003	EA  	2000	9	14	20000719SH017    	2	20000621	G	8520	SL74644	ROD BOLT        	LYC         		GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  						BROKEN          	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	780SP	1400 				1362133	L88148			ROD CAP CAME OFF NR 2 CYLINDER AS A RESULT OF EITHER SL74644 BREAKING OR SL128186 NUT BACKING OFF.  (X)						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000091400004	20000914	00004	EA  	2000	9	14	20000719SH018    	2	20000621	G	8530	SL12186	NUT             			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  						FAILED          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	780SP	1400 				1362133	L88248			INTAKE GUIDE VARIANCE, 0.0020 INCH.  (X)						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000091400006	20000914	00006	CE  	2000	9	14	20000720SH001    	1	20000613	G	2711	99130011	TRIM TAB        			BEECH 	99    	99          	1154002	CE  										LT AILERON	CRACKED         	A			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	95WA	35294				U6				THE AILERON TRIM TAB DID NOT PASS A VISUAL SURFACE INSPECTION DURING A CHECK OF THE FREE PLAY DURING A DETAILED INSPECTI	ON.  REMOVED ENTIRE AILERON ASSY AND INSTALLED A SERVICEABLE AILERON ASSY.  THE INSPECTION PROCESS WORKED IN THIS CASE A	S DESIGNED SO AN INCREASE IN FREQUENCY IS NOT WARRANTED.  THE INSPECTION/CHECK IS FOR FREE-PLAY AND THE DISCREPANCY WAS 	FOR BOTH FREE-PLAY IN EXCESS OF THE MFG''S RECOMMENDATIONS AND CRACKS IN THE SKIN.  CRACKS IN THE SKIN APPEAR TO BE THE 	RESULT OF IMPROPER GROUND HANDLING.  (X)		1	L	7	2 	3T			 	A14CE   					 
2000091400007	20000914	00007	CE  	2000	9	14	20000720SH002    	1	20000613	G	2720	50524327	BELLCRANK       			BEECH 	99    	B99         	1154004	CE  										RUDDER	CORRODED        	E			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	99TH	33111				U155				DURING A ROUTINE INSPECTION, THE RUDDER WAS FOUND TO HAVE SOME FREE-PLAY AT THE TOP PIVOT BEARING SUPPORT.  IT WAS NECES	SARY TO REMOVE THE RUDDER TO INSPECT FOR HIDDEN DAMAGE.  UPON REMOVAL, NOTICED THE RUDDER BELLCRANK CORRODED AT THE BOLT	 HOLES THAT SECURE THE RUDDER TO THE BELLCRANK.  THE DEFECTIVE BELLCRANK WAS REPLACED WITH A SERVICEABLE BELLCRANK.  FUT	URE INSPECTION TECHNIQUES WILL INCLUDE MINOR DISASSEMBLY IN THIS AREA TO INSPECT FOR CORROSION.  (X)			1	L	7	2 	3T			 	A14CE   					 
2000091400008	20000914	00008	EA  	2000	9	14	20000720SH003    	2	20000621	G	8520	SL74644	ROD BOLT        	LYC         		GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  						BROKEN          	E				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	15	304JT	60   				1494175	L13048			NR 5 CYLINDER ROD CAP CAME OFF.  BOTH ROD BOLTS WERE BROKEN.  THE CYLINDER WAS BROKEN AND SEPARATED FROM CRANKCASE AT IT	S FLANGE.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000091400009	20000914	00009	EA  	2000	9	14	20000720SH004    	2	20000621	G	8520	SL12186	NUT             	LYC         		GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  						BROKEN          	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	304JT	60   				1494175	L13048			NR 5 CYLINDER ROD CAP CAME OFF.  BOTH ROD BOLTS WERE BROKEN.  THE CYLINDER WAS BROKEN AND SEPARATED FROM CRANKCASE AT IT	S FLANGE.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000091400010	20000914	00010	CE  	2000	9	14	20000720SH006    	1	20000706	G	5550	50610015	FITTING         			BEECH 	80    	65A80       	1152808	CE  											CRACKED         	B			XA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	70348					LD246				FOUND CRACK RUNNING FROM .25 INCH MOUNTING HOLE TO EDGE OF PART.  POSSIBLE CAUSE WAS OVERTORQUE OF FITTING TO ELEVATOR B	ELLCRANK ATTACH BOLT.  FITTING TIES ELEVATOR TORQUE TUBE TO BELLCRANK ASSEMBLY.  (X)					1	L	7	2 	3O			 	3A20    					 
2000091400011	20000914	00011	EA  	2000	9	14	20000720SH007    	2	20000622	G	7414	E0080155	MOUNT           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					LT POSITION	CRACKED         	B			BCBR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	03	3480Q	3841 	2464 			287725299	L4714327A			PILOT REPORTED A SLIGHT ENGINE OIL LEAK.  PROBLEM TRACED TO LEFT MAGNETO, PULLED TO REPLACE MOUNTING GASKET AND NOTED MO	UNTING FLANGE WAS CRACKED IN RADIUS APPROXIMATELY 2 INCHES AROUND.  MAGNETO WAS REPLACED.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000091400013	20000914	00013	CE  	2000	9	14	20000720SH008    	1	20000207	G	3230	08421201	TUBE            			CESSNA	310   	310L        	2074230	CE  										L/G, GEARBOX	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	867MF					310L0123				ON APPROACH AFTER LOWERING GEAR, PILOT NOTICED NOSE GEAR NOT DOWN AND LOCKED.  PILOT MADE NOSE-UP LANDING.    FURTHER IN	SPECTION REVEALED EYELET OF TUBE ASSY HAD FAILED.  (X)					1	L	7	2 	3O			 	3A10    					 
2000091400014	20000914	00014	CE  	2000	9	14	20000720SH009    	1	20000207	G	3230	08421211	TUBE            			CESSNA	310   	310L        	2074230	CE  										L/G GEARBOX	FAILED          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	07	867MF					310L0123				ON APPROACH AFTER LOWERING GEAR, PILOT NOTICED NOSE GEAR NOT DOWN AND LOCKED.  PILOT MADE NOSE-UP LANDING.    FURTHER IN	SPECTION REVEALED EYELET OF TUBE ASSY HAD FAILED.  (X)					1	L	7	2 	3O			 	3A10    					 
2000091400015	20000914	00015	SO  	2000	9	14	20000720SH010    	1	20000703	G	3233	41789000	FORK            			PIPER 	PA31  	PA31350     	7103110	SO  											BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	766CF		5998 			317305102				BOLT BROKE ON SHAFT.  POSSIBLE CORROSION.  FORK BOLT BROKE WHERE HYDRAULIC ACTUATOR ATTACHES.  IT BROKE WHERE IT APPEARE	D TO BE SCRATCHED.  SUBMITTER STATED THIS MAY BE FROM INSTALLATION.					1	L	7	2 	3O			 	A20SO   					 
2000092100014	20000921	00014	EA  	2000	9	21	20000720SH011    	2	20000608	G	8530	LW11775	PLUG            	LYC         		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALL CYLINDERS	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	688  				172S8135				PERFORMED LYC SI 1492B.  DURING THE PHASE 2 INSPECTION, OIL FILTER REMOVED AND CUT OPEN FOR INSPECTION.  AN EXCESSIVE AM	OUNT OF ALUMINUM FLAKES WERE DISCOVERED.  ALL 4 CYLINDERS REMOVED ENOUGH TO INSPECT AND REPLACED 8 WORN PISTON PIN PLUGS	 WITH P/N 60828 PLUGS.  RE-INSTALLED CYLINDERS WITH NEW CYLINDER BASE SEALS, INTAKE GASKETS, PUSHROD SEALS AND VALVE COV	ER GASKETS.  PERFORMED OPERATIONAL CHECK, CHECKED SATISFACTORY.  (X)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000110100009	20001101	00009	SO  	2000	11	1	20000720SH012    	1	20000712	G	7920	LW13366	GASKET          			PIPER 	PA31  	PA31350     	7103110	SO  										FILTER CONV PLTE	DETERIORATED    	I			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	35270	177  				317952141	L161068A			AFTER REPORT FROM ANOTHER OPER ABOUT OIL FILTER CONVERTER PLATE GASKET POSSIBLY FAILING, TECH WERE INSPECTING THE AREAS 	AROUND OIL FILTER CONVERTER PLATES FOR SIGNS OF GASKET EXTRUDING PAST PLATE ON ACCY HOUSING OIL FILTER PAD.  ON HEAVY IN	SP OF ENG, NOTICED A .0312 INCH TO .0625 INCH OF GASKET MATERIAL EXTRUDING PAST CONVERTER PLATE.  FOR SAFETY, OLD GASKET	 REMOVED.  NOTED OLD GASKET WIDER, THINNER, AND BRITTLE (COMP TO NEW).  DURING REMOVAL, GASKET CAME OUT IN SMALL PIECES.	  NOTED THE BRAKE AWAY TORQUE WAS IN EXCESS OF 50-60 FEET/POUNDS REQ BY SI 1453.  THIS SI IS REFERRED TO IN SSP 493, PC-	315-5 DATED OCT 1991 FOR TIO, LTIO-540 SERIES TEXTRON LYC.  (X)	1	L	7	2 	3O			 	A20SO   					 
2001013000042	20010130	00042	EU  	2001	1	30	20000720SH013    	1	20000426	G	5550	1053040212	FITTING         			BOLKMS	117   	BK117A3     	5626015	EU  										VERTICAL FIN	CRACKED         	E			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	163BK	502  				7063				UPON INSPECTION, NOTICED A CRACK BEHIND UPPER LEFT BOLT HOLE EXTENDING TO RIVET HOLE.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001013000043	20010130	00043	EU  	2001	1	30	20000720SH014    	1	20000202	G	6210	117150071	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	DEBONDED        	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	163BK	6034 				7063				LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROX BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, B	OTH UPPER/LOWER SURFACES.  (X)					1	G	7	2 	3U			 	H13EU   					 
2000110100011	20001101	00011	SO  	2000	11	1	20000720SH015    	2	20000714	G	8520		CRANKSHAFT      			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FLANGE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	73100		10   			20700559				CRANKSHAFT CRACKED AND FAILED JUST AFT OF FLANGE AND PROPELLER SEPARATED FROM AIRCRAFT WHILE IN-FLIGHT.  (X)						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2000110700001	20001107	00001	CE  	2000	11	7	20000720SH016    	1	20000503	G	2800		FUEL LINE       			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  						CONTAMINATED    	E				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AL	03	7254H					20609036	L2688948A			PILOT REPORTED ENGINE SURGING ON TAKEOFF WITH SIGNIFICANT FUEL FLOW FLUCTUATION WHICH WAS CORRECTED WITH A DECREASE IN E	NGINE POWER BY ADJUSTMENT OF THE PROP CONTROL AND ACTIVATION OF THE STANDBY ELECTRIC FUEL PUMP.  POST-GROUND RUNS COULD 	NOT DUPLICATE THE PROBLEM.  FOLLOW-UP TEST FLIGHT COULD NOT DUPLICATE THE PROBLEM.  INSPECTION OF THE AIRCRAFT FUEL SYST	EM DID NOT FIND ANY CONTAMINATION, OBSTRUCTIONS, OR LEAKAGE.  (X)			1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000110700002	20001107	00002	SO  	2000	11	7	20000720SH017    	2	20000517	G	7322		CARBURETOR      			CESSNA	180   	180J        	2072622	CE  	CONT  	O520  	IO520F      	17032	SO  						INACCURATE      	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AL	05	4406R					18052670	818812R			NOTE:  ACFT IS CONFIGURED ON AEROCET FLOATS AND INCORPORATES TEXAS SKYWAYS, INC. STC NR SE09017SC.  INSTALL OF CARBURETE	D IO520F ENGINE.  PILOT REPORTED ENGINE RUNS ROUGH AT ALL POWER SETTINGS.  THE STC HOLDER ADVISED ACFT SHOULD BE OPERATE	D BY ''''LEANING WITH MIXTURE CONTROL AGGRESSIVELY FOR OPERATION'''' AS THE ENGINE IS CONFIGURED WITH A LARGER JET IN TH	E CARBURETOR DESIGNED TO RUN RICH TO ACCOMMODATE COOLING OF THE LARGER ENGINE, AS WELL AS SETTING THE IDLE RPM AT 1000, 	WELL ABOVE THE NORMAL IDLE OF 575-625 RPM.  THE FLIGHT SUPPLEMENT SUPPLIED WITH THE STC DOES NOT ADDRESS THESE OPERTIONA	L DEVIATIONS NOR DOES THE STANDARD PILOT''''S OPERATING HANDBOOK, AND COULD POTENTIALLY CAUSE A SAFETY OF FLIGHT ISSUE. 	1	H	7	1 	3O	3	O	 	5A6     	E5CE				 
2000092500002	20000925	00002	EA  	2000	9	25	20000720SH018    	2	20000425	G	8500		ENGINE          			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  						FAILED          	E				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AL	05	7281M					20606048	L2497448A			PILOT REPORTED ENGINE SURGING ON TAKEOFF WITH SIGNIFICANT FUEL FLOW FLUCTUATION WHICH WAS CORRECTED WITH A DECREASE IN E	NGINE POWER BY ADJUSTMENT OF THE PROP CONTROL AND ACTIVATION OF THE STANDBY ELECTRIC FUEL PUMP.  POST-GROUND RUNS COULD 	NOT DUPLICATE THE PROBLEM. FOLLOW-UP TEST FLIGHT COULD NOT DUPLICATE THE PROBLEM.  INSPECTION OF THE AIRCRAFT FUEL SYSTE	M DID NOT FIND ANY CONTAMINATION, OBSTRUCTIONS, OR LEAKAGE. (X)			1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000092500003	20000925	00003	EA  	2000	9	25	20000720SH019    	2	20000605	G	8500		ENGINE          			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  						FAILED          	E				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AL	05	7281M					20608048	L2497448A			PILOT REPORTED ENGINE SURGING ON TAKEOFF WITH SIGNIFICANT FUEL FLOW FLUCTUATION WHICH WAS CORRECTED WITH A DECREASE IN E	NGINE POWER BY ADJUSTMENT OF THE PROP CONTROL AND ACTIVATION OF THE STANDBY ELECTRIC FUEL PUMP.  POST-GROUND RUNS DUPLIC	ATED THE PROBLEM, BUT NORMAL SYSTEMS CHECKS SATISFACTORY.  THREE FOLLOW-UP TEST FLIGHTS PERFORMED, PROBLEM RECURRED IN O	NLY 2 OF THE FLIGHTS, BOTH DURING TAKEOFF ROLL.  INSPECTION OF THE AIRCRAFT FUEL SYSTEM DID NOT REVEAL ANY CONTAMINATION	, OBSTRUCTIONS, OR LEAKAGE.  MANUFACTURER RECOMMENDED SWAPPING FUEL SERVOS WITH ANOTHER SAME AIRCRAFT TO DETERMINE IF TH	E PROBLEM FOLLOWED THE SERVO.  ACCOMPLISHED RECOMMENDATION, AND PROBLEM DID NOT RECUR IN EITHER AIRCRAFT.  (X)	1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000092500004	20000925	00004	CE  	2000	9	25	20000720SH020    	1	20000516	G	2842	C6680501108	TRANSMITTER     			CESSNA	208   	208B        	2073701	CE  										LEFT WING	SHORTED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	1275N	3494 				208B0756				LEFT FUEL QUANTITY INDICATOR INACCURATE AND ERRATIC.  REPLACED DEFECTIVE CENTER OUTBOARD FUEL SENDING UNIT.  (X)						1	H	7	1 	3T			 	A37CE   					 
2000110700003	20001107	00003	CE  	2000	11	7	20000720SH021    	1	20000613	G	2782	99105863	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  										CABIN CEILING	SHEARED         	E				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AL	05	1275N	349  				208B0756				STANDBY FLAP MOTOR INOPERATIVE.  ACTUATOR SHAFT ROLL PIN SHEARED. JACKSCREW CONTAMINATED WITH METAL PARTICLES, MOTOR INO	PERATIVE.  UPON REPLACEMENT OF TRANSMISSION ASSY, ALSO DISCOVERED ELECTRICAL PIN IN PRIMARY FLAP MOTOR POWER CONNECTOR P	ARTIALLY DISENGAGED CAUSED BY PIN LOCKING TABS NOT EXTENDED.  (X)				1	H	7	1 	3T			 	A37CE   					 
2000112800016	20001128	00016	NE  	2000	11	28	20000720SH022    	2	20000516	G	7532	304903802	BLEED VALVE     			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE	FAILED          	E				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05	1275N	321  				208B0756				MANUFACTURER RECALLED THIS SPECIFIC COMPRESSOR BLEED VALVE FOR TESTING OF INTERNAL PACKING FOR DEFECTS.  BLEED VALVE SER	IAL NUMBER FELL OUTSIDE OF ANY AD OR SB.  (X)					1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000111600001	20001116	00001	CE  	2000	11	16	20000720SH024    	1	20000707	G	2730	187504	CONTROL ARM     			BEECH 	18    	C45H        	1151018	CE  										CNTRLCOLUMN ASSY	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	9532Z	7529 				AF448				AIRCRAFT SUBJECTED TO HELICOPTER ROTOR WASH WHILE PARKED.  ELEVATOR SUBJECTED TO VIOLENT MOVEMENT STOP TO STOP.  AD 77-1	9-07 WAS PERFORMED.  INSPECTION REVEALED A CRACK IN ELEVATOR CONTROL ARM.  CRACK ORIGINATES ON AFT LEFT TAPER PIN HOLE A	ND PROCEEDS OFF LEFT SIDE OF CASTING.    (X)				1	L	7	2 	3R			 	A765    					 
2000111600002	20001116	00002	CE  	2000	11	16	20000720SH026    	1	20000705	G	2400	W31X104450	CIRCUIT BREAKER 			CESSNA	414   	414A        	2075907	CE  										AVIONICS SYSTEM	BURNED OUT      	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	4573V					414A0300				AFTER TAKEOFF,THERE WAS A SMELL OF SMOKE IN THE COCKPIT.  THE SMELL WAS COMING FROM THE AREA OF AVIONICS MASTER BREAKER/	SWITCH.  DISCOVERED THE POTTER & BRUMFIELD BREAKER/SWITCH, PN W31-X1000-50, HAD OVERHEATED AND THE BREAKER POINTS HAD WE	LDED SHUT.  THIS RENDERED THE SWITCH PORTION OF THE BREAKER/SWITCH INOPERATIVE.  THIS BREAKER/SWITCH HAD FAILED BEFORE O	N THER AIRCRAFT, BUT NEVER IN FLIGHT. THE FAILURES USUALLY OCCURRED ON THE GROUND DURING GROUND OPERATION OR PRE-FLIGHT.	  THE AVIONICS SYSTEM IS PROTECTED BY A SECOND CIRCUIT BREAKER, PN 7815-15-50, LOCATED IN THE LEFT WING ROOT FWD OF THE 	BATTERY BOX WHICH WILL TRIP IF THERE IS AN OVERLOAD.  (X)	1	L	7	2 	3O			 	A7CE    					 
2000112800150	20001128	00150	CE  	2000	11	28	20000720SH027    	1	20000707	G	2910	551700863	HYDRAULIC LINE  			CESSNA	501   	551         	2076605	CE  											LEAKING         	B				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03	242WT					5510066				THE LT MLG PRESSURE LINE RUNNING JUST OVER THE FLIGHT CONTROL CABLES IN THE TAIL CONE SECTION OF THE A/C WAS BEAT DOWN I	NTO THE PATH OF ONE OF THE CABLES.  AFTER A LIMITED TIME, THE CABLE WORE THROUGH THE HYDAULIC LINE DUMPED THE RESERVOIR 	INTO THE TAIL CONE.  TO PREVENT RECURRENCE OF THIS INCIDENT, SUBMITTER SUGGESTED THE HYDRAULIC LINE SHOULD BE ROUTED BEL	OW THE FLIGHT CONTROL CABLES.  (X)			1	L	7	2 	4F			 	A27CE   					 
2000112800361	20001128	00361	EA  	2000	11	28	20000720SH028    	2	20000509	G	7414	M3333	IMPULSE COUPLING			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					PINS	LACK OF LUBE    	E			LABA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	3957X	500  				327640003	RL137854SA			OCCURRED UNDER NORMAL WORKING CONDITIONS - LACK OF LUBRICATION IN CHAMBER IS ONE PROBLEM.						1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000112800362	20001128	00362	CE  	2000	11	28	20000720SH029    	1	20000623	G	2750	1216346331	FLEX COUPLING   			BEECH 	36    	A36         	1151604	CE  										LT FLAP	UNSERVICEABLE   	H				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SO	05	1565X	857  				E2853				OWNER REPORTED FLAP SPLIT DURING FLIGHT.  INSPECTION REVEALED LT FLAP FLEX CABLE DRIVE SPLINE CRIMP TO BE LOOSE WHICH AL	LOWED CABLE CORE TO SLIP.  LT FLAP DID NOT EXTEND AS MUCH AS RT FLAP.  WHEN FLAPS WERE RETRACTED, LT FLAP CONTACTED UPLI	MIT SWITCH; THUS, STOPPING FLAP RETRACTION.  RT FLAP WAS STILL EXTENDED 15 DEGREES - 25 DEGREES CAUSING SPLIT.  THIS APP	EARED TO BE A MANUFACTURING DEFECT.  SUBMITTER SUGGESTED RAYTHEON ISSUE AN EMERGENCY SB TO REQUIRE FIELD INSPECTIONS OF 	FLAP DRIVE SYSTEM.  (X)		1	L	7	1 	3O			 	3A15    					 
2000112800363	20001128	00363	CE  	2000	11	28	20000720SH030    	1	20000623	G	2750	99124238EX	CONTROL VALVE   			CESSNA	525   	525         	2076601	CE  										FLAP UNIT	DEFECTIVE       	B			EBVR	O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	525KA					5250019				ORDERED AND RECEIVED NEW HYDRAULIC FLAP CONTROL VALVE.  INSTALLED VALVE AND RAN AIRCRAFT.  FOUND FLAPS WOULD ONLY OPERAT	E INTERMITTENTLY.  CHECKED ALL ELECTRICAL CIRCUITS, ALL CHECKED GOOD.  RE-INSTALLED OLD VALVE AND FLAPS OPERATED NORMALL	Y.  RE-ORDERED A NEW VALVE.  (X)				1	L	7	2 	4F			RT	A1WI    					 
2000112800364	20001128	00364	SO  	2000	11	28	20000720SH031    	1	20000601	G	2910		B-NUT           			PIPER 	PA32  	PA32R301    	7103218	SO  										RT GEAR	LOOSE           	B				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			SO	13	9236V					3213069				GEAR WOULD NOT EXTEND.  CIRCUIT BREAKER TRIPPED.  RE-SET, BUT NO HELP.  GEAR FREE FALL FAILED TO LOCK ALL GEAR DOWN.  RI	GHT MAIN COLLAPSED UPON LANDING.  FOUND B-NUT ON RIGID LINE BELOW HYDRAULIC POWER PACK LOOSE AND LEAKING HYDRAULIC FLUID	.  GEAR OPERATED NORMAL AFTER FIXING LEAK AND SERVICING RESERVOIR.  (RESISTANCE WAS NOTED IN GEAR SYSTEM WHEN RECOVERY F	ROM RUNWAY UNTIL EMERGENCY EXTEND RESET).  (X)			1	L	7	1 	3O			 	A3SO    					 
2000112800365	20001128	00365	GL  	2000	11	28	20000720SH032    	1	20000604	G	2822		PUMP            			AMTR  	300   	SX300       	05675EK	GL  											MISINSTALLED    	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	2H	984  				SA2966				AFTER RUNNING LEFT WING TANK DRY, PILOT SWITCHED TO RIGHT WING TANK.  ELECTRIC FUEL PUMP FAILED TO PICK UP FUEL AGAIN.  	INVESTIGATION REVEALED ELECTRIC PUMP HAD BEEN INSTALLED ON FIREWALL INSTEAD OF IN NOSE WHEELWELL AS PLANS INDICATED.					1	L	7	1 	3O			RT	EXPA1L71					 
2000112800393	20001128	00393	EA  	2000	11	28	20000720SH034    	2	20000626	G	8530	LW16475KLIO	SPRING          	LYC         		BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720A1B    	41546	EA  					EXHAUST	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15			530  							EXHAUST VALVE SPRING RETAINING CAP BROKE IN HALF AND BURNED EXHAUST VALVE.  (X)						1	L	7	2 	3O	3	O	 	3A20    	1E15				 
2000112800395	20001128	00395	SO  	2000	11	28	20000720SH036    	2	20000628	G	7414	10349276	CAPACITOR       	CONT        		BEECH 	35    	35BEECH     	1151502	CE  	CONT  	O520  	IO520*      	17032	SO  					MAGNETO	FAILED          	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	03		8    								CUSTOMER REPORTED THE RIGHT MAGNETO FAILED.  INVESTIGATION REVEALED THE POINTS WERE NOT OPENING.  TCM SB 651 DESCRIBES O	NE CAUSE FOR THIS TO BE CAPACITOR FAILURE CAUSING POINTS TO ARC, HEAT UP, AND MELT THE NYLON CAM FOLLOWERS.  BECAUSE SHO	P HAD JUST REPLACED THE CAPACITOR AND SET THE POINTS, SUBMITER BELIEVES THE NEW CAPACITOR FAILED.  (X)				1	L	7	1 	3O	3	O	 	A777    	E5CE				 
2000112800396	20001128	00396	CE  	2000	11	28	20000720SH037    	1	20000619	G	5511		STABILIZER      			CESSNA	150   	150J        	2071820	CE  										INBOARD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		1500 				15070260				BOTH STABILIZER SPARS FOUND CRACKED IN THE UPPER BEND RADIUS FOR THE FLANGE AT THE INBOARD PAD ABOUT 2 INCHES FROM THE P	ADS.  THIS AREA IS CONCEALED UNDER STIFFENER 0432001-15 (ALSO CRACKED).  THIS WAS DISCOVERED DURING INSPECTION FOR AD 80	-11-04, ALSO SPAR REINFORCMENT, PN 0432001-15, WAS CRACKED.  (X)				1	H	7	1 	3O			 	3A19    					 
2001011103993	20010111	03993		2001	1	11	20000720SH038    	2	20000626	G	7414	10349276	CAPACITOR       	CONT        																	OPEN            	B			NQ2R	O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	05										OPEN CONDITION TO PRIMARY TERMINAL WHICH WOULD CAUSE MAGNETO TO BE ''HOT'' EVEN THOUGH SWITCH IN OFF POSITION.  THIS IS 	A NEW PART ABOUT TO BE INSTALLED DURING OVERHAUL.  DATE CODE ON PART IS 99-43.  TCM BUL CSB 641 AND AD 94-06-09 SPEAKS T	O THIS PROBLEM, BUT THIS ONE IS OUTSIDE THE 93-40 AND 93-42 DATE CODES CALLED OUT IN THE BULLETIN AND AD.  (X)																	 
2000112800397	20001128	00397	SO  	2000	11	28	20000720SH039    	1	20000518	G	3250	8362507	ARM             			PIPER 	PA46  	PA46350P    	       	SO  										FRONT OP NOSE ST	BENT            	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	17	9250B					4622161				AFTER TOUCHDOWN, PILOT HAD NO NOSE STEERING.  AFTER CONTACT WITH DIRT, NOSE STRUT BROKE AT ENGINE MOUNT HARD POINTS AND 	COLLAPSED.  POSSIBLE CAUSE:  NOSE STEERING ARM WAS BROKEN.  REASON:  UNKNOWN.  (X)					1	L	7	1 	3O			RT	A25SO   					 
2001013000044	20010130	00044	NE  	2001	1	30	20000720SH040    	2	20000604	G	7310	1VN02523	MANIFOLD        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE FUEL	MALFUNCTIONED   	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5194C	593  				7169	LE45382EA			FUEL MANIFOLD ASSY CAUSES ENGINE TO RUN HOT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001013000045	20010130	00045	EU  	2001	1	30	20000721SH001    	1	20000202	G	6210	117150071	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	DEBONDED        	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			nm	07	163BK					7063				LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING 	EDGE, BOTH UPPER/LOWER SURFACES.  (X)					1	G	7	2 	3U			 	H13EU   					 
2001013000046	20010130	00046	EU  	2001	1	30	20000721SH002    	1	20000202	G	6210	117150071	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	DEBONDED        	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	163BK					7063				LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING 	EDGE, BOTH UPPER/LOWER SURFACES.  (X)					1	G	7	2 	3U			 	H13EU   					 
2001013000047	20010130	00047	EU  	2001	1	30	20000721SH003    	1	20000202	G	6210	117150071	BLADE           			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	DEBONDED        	A			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	163BK					7063				LEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING 	EDGE, BOTH UPPER/LOWER SURFACES.  (X)					1	G	7	2 	3U			 	H13EU   					 
2001013000048	20010130	00048	NE  	2001	1	30	20000721SH004    	2	20000602	G	7310	430167601	MANIFOLD        			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE FUEL	MALFUNCTIONED   	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	163BK	573  				7063	LE45332EA			FUEL MANIFOLD ASSY CAUSES ENGINE TO RUN HOT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001013000049	20010130	00049	NE  	2001	1	30	20000721SH005    	2	20000518	G	7310	430163701	MANIFOLD        			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE FUEL	MALFUNCTIONED   	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	420MB	119  				7077	LE45218EA			FUEL MANIFOLD ASSEMBLY CAUSES ENGINE TO RUN HOT.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001013000050	20010130	00050	NE  	2001	1	30	20000721SH006    	2	20000327	G	7310	430167601	MANIFOLD        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE FUEL	MALFUNCTIONED   	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	10UM	555  				7231	LE45806EFA			FUEL MANIFOLD ASSY CAUSES ENGINE TO RUN HOT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001013000051	20010130	00051		2001	1	30	20000721SH007    	4	20000620	G	3457	0110028000	GPS             			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	MALFUNCTIONED   	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	392LG					3252				UNIT INOPERATIVE.  CRSR WILL NOT SCROLL PAGES.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020100005	20010201	00005		2001	2	1	20000721SH009    	4	20000525	G	3160	B19030MB01	DISPLAY         			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INTERMITTENT    	A			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	104LN	804  				3134				VEMD UNIT INOPERATIVE.  T4.5 SPLIT BETWEEN FADE AND VEMD CAUSES LFI PAGE TO GO OFF-LINE.  INTERMITTENT 20 TO 80 DEGREES.	  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001013100005	20010131	00005	NE  	2001	1	31	20000721SH010    	2	20000407	G	7310	430167601	MANIFOLD        			BOLKMS	117   	BK117A1     	5626010	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE FUEL	LEAKING         	A			R7MA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	128HH	569  				7036	LE4515EA			FUEL MANIFOLD ASSY LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED UNIT.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020700195	20010207	00195	SO  	2001	2	7	20000721SH011    	1	20000713	G	3242	1331317	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1271 			1561A					BRAKE ASSY, PN 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVEN	 WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT 	BRAKE CONFIGURATION, PN 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001022100079	20010221	00079	SO  	2001	2	21	20000721SH012    	1	20000713	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1650 			1246A					BRAKE ASSY, PN 2-1584-T, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEV	EN WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED TO BRAKE ASSY.  	(X)				2	L	7	2 	4T			RT	A31SO   					 
2001020600106	20010206	00106	SW  	2001	2	6	20000721SH013    	1	20000526	G	2622	RTA600	EXTINGUISHER    			BELL  	407   	407         	       	SW  										CABIN	LEAKING         	B			FKFR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	03	24156					53415				FIRE EXTINGUISHER, BELL P/N 40000, TRADE NAME ''RIGHT-OUT'' TM IS STANDARD EQUIPMENT FROM THE BELL FACTORY.  THE NEW OWN	ER PICKED UP NEW HELICOPTER AT THE COMPLETION CENTER.  ON THE FLIGHT TO  HOME BASE, THE FIRE EXTINGUISER SLOWLY DISCHARG	ED IN-FLIGHT.  ESTIMATE AIRCRAFT TT, 15.0 HOURS.  (X)				1	G	7	1 	3U			O	H2SW    					 
2001020600107	20010206	00107	SW  	2001	2	6	20000721SH014    	1	20000721	G	2622	RTA600	EXTINGUISHER    			BELL  	407   	407         	       	SW  										CABIN	LEAKING         	B			FKFR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	03	98JT					53286				FIRE EXTINGUISHER, BELL PN 40000, TRADE NAME ''RIGHT-OUT'' TM, IS STANDARD EQUIPMENT FROM THE BELL FACTORY.  SHIP CAME I	N FOR AN ANNUAL INSPECTION.  THE FIRE EXTINGUISHER WEIGHT WAS FOUND 56 GRAMS LIGHT AND UNAIRWORTHY.   (X)					1	G	7	1 	3U			O	H2SW    					 
2000110600131	20001106	00131		2000	11	6	20000721SH015    	4	20000705	G	6113	D6199	SPINNER         			MOONEY	M20   	M20M        	5870222	SW  						MCAULY	3D32C	B3D32C417   	GL  		CRACKED         	B			FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	10KG	473  				270249		980209		FOUND SPINNER BULKHEAD SEVERELY CRACKED DURING ROUTINE MAINTENANCE.  SUBMITTER STATED THIS IS THE SECOND M20M WITH LESS 	THAN 500 HOURS THAT THE BULKHEAD HAS FAILED.  SPINNER BULKHEAD HAS CRACKS AT ATTACHEMNT HOLES AND AT FIRST BEND RADIUS. 	 SEVERAL PIECES MISSING.  (X)				1	L	7	1 	3O			RT	2A3     		5	C	P58GL	 
2000110600132	20001106	00132	EA  	2000	11	6	20000721SH016    	2	20000622	G	8530	73555	PUSHROD         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 4 CYLINDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	120DM					327340122	RL930748			ENGINE USING EXCESSIVE OIL AFTER RECENT OVERHAUL (200 HRS).  CYL REMOVED FOR RE-OVERHAUL.   UPON RE-INSTALL OF NEWLY O/H	 CYLINDERS, DISCOVERED NR 4 CYL PUSHROD WAS MODIFIED BY APPARENT ATTEMPT TO SHORTEN LENGTH BY CUTTING AND DOWELING ROD O	N ONE END.  ROD ESTIMATED TO HAVE AT LEAST 200 HRS TIS.  ROD STARTING TO FAIL SHOWING MUSHROOMING.  TIP COULD BE PULLED 	APART BY HAND PRESSURE.  NOTE:  PN 73555 IS SUPERCEDED TO PN 15F21362-21.  THIS IS WRONG P/N FOR ENG MODEL.  THE CORRECT	 PUSHROD PN IS 73455 S/S TO 15F19957-55.  (X)		1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000110600133	20001106	00133		2000	11	6	20000721SH017    	4	20000427	G	2562	AK450	ELT             			CESSNA	180   	180H        	2072618	CE  											INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	180PR					18052186				DURING ANNUAL INSPECTION, CHECKED ELT FOR OPERATION AND CONDITION.  ELT DID NOT OPERATE.  EITHER INERTIA SWITCH OR MANUA	L SWITCH.  CHANGED BATTERY, AS SUGGESTED BY MFG.  NO CHANGE.  SENT UNIT TO MFG FOR REPLACEMENT.  PART TT:  18 MONTHS.   	(X)				1	H	7	1 	3O			 	5A6     					 
2000110600134	20001106	00134	SO  	2000	11	6	20000721SH018    	2	20000609	G	8530	642594CP	CYLINDER HEAD   			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					NR 3 POSITION	CRACKED         	B			JZRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	17825		1698 			CE711	562770			CYLINDER NR 3 CRACKED FROM BOTTOM SPARK PLUG HOLE THROUGH EXHAUST PORT EXTENDING  INTO EXTERNAL FINDS.  FOUND DURING COM	PRESSION CHECK FOR ANNUAL INSPECTION. CHANNEL CHROME CYLINDER, EXACT HOURS ON CYLINDER UNKNOWN (CHROME PLATED 9/86).  SU	BMITTER RECOMMENDED LIFE LIMIT ON CYLINDER HEAD SHOULD NOT EXCEED 1,800 HOURS.  (X)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2000110600135	20001106	00135	WP  	2000	11	6	20000721SH019    	1	20000711	G	3260	820014196	LIGHT           	CVAC        		CVAC  	440   	440         	2422902	WP  										ANNUNCIATOR PNL	OPEN            	C			OGCB	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	23	161FL	15000				430				CREW EN ROUTE FROM MMCS TO ELP.  CREW LOWERED LANDING GEAR AND DID NOT RECEIVE A DOWN/LOCKED LIGHT FOR LT MAIN GEAR (INT	RANSIT).  LIGHT WAS NOT ILLUMINATED NOR DID THEY RECEIVE GEAR HORN.  OPTED TO MAKE FLYBY.  TOWER WOULD NOT CONFIRM GEAR 	DOWN.  CREW PERFORMED HIGH ''''G'''' MANEUVER, DID NOT RECEIVE GEAR DOWN LOCKED INDICATION.  CREW MADE FLYBY AND TOWER T	HEN INDICATED GEAR APPEARED TO BE DOWN AND LOCKED.  CREW LANDED PLANE WITHOUT INCIDENT.  INSP OF ACFT REVEALED LIGHT ASS	Y WAS DEFECTIVE.  REPLACED LIGHT.  ACFT RETURNED TO SERVICE.  (X)		2	L	7	2 	4R			 	6A6     					 
2000110600136	20001106	00136	CE  	2000	11	6	20000721SH020    	1	20000612	G	3246	3680025	WHEEL           	RAYTHN      		BEECH 	95    	95B55       	1152729	CE  										NOSE GEAR	CRACKED         	C				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	216RW					TC1956				A CRACK APPEARED ON NOSE WHEEL 3 INCHES TO 4 INCHES LONG ON THE OUTER HALF OF THE WHEEL.  AS THE WHEEL IS INSTALLED, THE	 CRACK IS ON THE HORIZONTAL SURFACE BETWEEN THE HUB AND THE WHEEL FLANGE.  THE CRACK WAS DISCOVERED BEFORE FAILURE OCCUR	RED. THE WHEEL WAS REPLACED WITH CLEVELAND ASSY P/N 40-87D.				1	L	7	2 	3O			RT	3A16    					 
2000110600140	20001106	00140	EU  	2000	11	6	20000721SH021    	1	20000622	G	5330		SKIN            			AMD   	FALC50	FALCON900   	2700160	EU  										FUSELAGE	CORRODED        	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	26LB2					51				CORROSION OF FUSELAGE SKIN AT TOWER FRAME 10 UNDER FORWARD END OF PANEL 130A.  THE DOMED NUTPLATES ARE RETAINING WATER. 	 THIS PANEL IS REMOVED ONLY AT 2C INSPECTION.  SUBMITTER RECOMMENDED REMOVAL AT EACH C-INSPECTION TO INSPECT FOR CORROSI	ON.  ACTT:  4,868.6 HRS.  (X)				2	L	7	3 	4F			RT	A46EU   					 
2000110600142	20001106	00142	EU  	2000	11	6	20000721SH022    	1	20000626	G	5330		SKIN            			AMD   	FALC50	FALCON900   	2700160	EU  										FUSE	CORRODED        	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	26LB					51				AIRCRAFT FUSELAGE SKIN AT APU EXHAUST BETWEEN FRAMES 33 AND 34 CORRODED.  DAMAGED AREA WAS REMOVED AND SKIN REPLACEMENT 	REPAIR DONE.  (X)					2	L	7	3 	4F			RT	A46EU   					 
2000110600144	20001106	00144	NE  	2000	11	6	20000721SH023    	2	20000531	G	7310	37E501248P101	MANIFOLD        			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					MAIN FITTING	LEAKING         	B				O				OTHER                   				K	A		FLUID LOSS                	FLAME/FIRE                		NR	NOT REPORTED   	1			SW	99	239CA					25B149	251332A			FUEL MANIFOLD STARTED TO LEAK AT THE SILVER SOLDER JOINT BY THE LARGE B-NUT.  FUEL CAUGHT FIRE AND BURNED ENGINE COWL ON	 TAKEOFF.  (X)					2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2000110600145	20001106	00145	SO  	2000	11	6	20000721SH024    	1	20000623	G	3230	405452	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										LANDING GEAR	SHEARED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	17	35LK					277654059				AFTER LANDING, A BOLT IN THE LEFT LINK (PIPER PARTS CATALOG PG 283, ITEM 52, PARA 405, 452) SHEARED COLLAPSING THE GEAR 	AND WHEEL ASSY AFT AND RESTING TIRE ON THE FLAP.  OWNER OPERATOR RECOMMENDED AT LEAST A 1,000 HOUR INSPECTION.  (X)					1	L	7	2 	3O			 	1A10    					 
2001020600115	20010206	00115	SW  	2001	2	6	20000721SH028    	1	20000705	G	2913	8505261	GEAR            			BELL  	206   	206B3       	1181506	SW  										HYD PUMP	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	50Q		433  		BDO113	3419				INTERNAL SPLINES ON HYDRAULIC PUMP WORN EXCESSIVELY CAUSING HYDRAULIC PUMP TO START TO FAIL.  PUMP OVERHAULED 432.8 HOUR	S PRIOR TO FAILURE.  REASON FOR FAST SPLINE WEAR UNKNOWN.  (X)					1	G	7	1 	3U			 	H2SW    					 
2001020600116	20010206	00116	NE  	2001	2	6	20000721SH029    	2	20000610	G	8550		ENGINE          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2	MAKING METAL    	B			TI1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	05	527MB	6473 	107  			7103	LE45157			INSPECTED NR 2 ENGINE CHIP DETECTOR AND FOUND NO SIGN OF CHIPS OR DEBRIS.  CLEARED CHIP PLUG AND REINSERTED INTO HOUSING	.  PILOT PERFORMED A GROUND RUN OF THE NR 2 ENGINE AND THE CHIP LIGHT DID NOT ILLUMINATE.  PILOT SHUT ENGINE DOWN, RE-CH	ECKED CHIP PLUG AND FOUND NO EVIDENCE OF CHIPS.  ADJUSTED NR 2 ENGINE FLOW FENCE ACTUATOR AND PERFORMED AN OPERATIONAL C	HECK FLIGHT TO VERIFY ENGINE TORQUE INDICATIONS.  TORQUE INDICATIONS WERE DEEMED TO BE WITHIN MBB LIMITS AND ACFT RELEAS	ED FOR RETURNED TO SERVICE.  (X)		1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000110600147	20001106	00147	CE  	2000	11	6	20000721SH031    	1	20000630	G	2730	2213063203	BRACKET         			CESSNA	182   	182S        	2072701	CE  										ELEV CABLE PULLE	INADEQUATE      	B			FCPR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	6870L					18280097				****PART LOC:  ELEV CABLE PULLEY BRACKET*****WHILE TRYING TO C/W CESSNA MANDATORY SB 00-27-01, REPLACEMENT OF ELEVATOR C	ONTROL CABLE SUPPORT BRACKET, FOUND NEW BRACKET PN 2213063-203 WAS IMPROPERLY MANUFACTURED AND WILL NOT PERFORM ITS INTE	NDED FUNCTION.  (X)				1	H	7	1 	3O			NT	3A13    					 
2000110600148	20001106	00148	CE  	2000	11	6	20000721SH032    	1	20000605	G	3230	51420025	DRAG BRACE      			CESSNA	402   	402C        	207590R	CE  										NOSE GEAR	CRACKED         	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	69SC	1737 				402C0041				ON PRE-FLIGHT, CREW FOUND SUSPECTED CRACK AT DRAG BRACE TO ACTUATOR ATTACH LUG AREA.  MAINTENANCE PERFORMED NDT.  FOUND 	TO BE CRACKED AT SUSPECTED AREA.  REMOVED AND REPLACED DRAG BRACE AND ROD END (PN ADNE4JW) WITH NEW AND RETURNED AIRCRAF	T TO SERVICE.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000110600149	20001106	00149	EA  	2000	11	6	20000721SH035    	2	20000630	G	8530	75413	PISTON          			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					NR 1	FAILED          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	02	6887W	1600 				2821043	L1539727A			THE AIRCRAFT  WAS AT 6,500 FEET MSL, ABOUT 30 MINUTES INTO A FLIGHT.  (VFR) RPM STARTED TO DROP.  THERE WAS NO WARNING O	R UNUSUAL SOUND.  AIRCRAFT WAS DESTROYED DURING EMERGENCY LANDING ON A ROAD.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000110600150	20001106	00150	EA  	2000	11	6	20000721SH036    	2	20000626	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  						MAKING METAL    	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			EA	05	79GA					BB556	PCE81261			PILOT EXPERIENCED OIL PRESSURE AND TORQUE FLUCTUATION.  THIS ENGINE SHUT DOWN IN-FLIGHT.  INSPECTION OF OIL FILTER SHOWE	D METAL CONTAMINATION.  THIS ENGINE HAS BEEN OPERATED FOR 714.9 HOURS ON THE MORE PROGRAM.  THE EXACT REASON FOR THIS FA	ILURE IS NOT KNOWN AT THIS TIME.  (X)				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000110600155	20001106	00155	SW  	2000	11	6	20000721SH037    	1	20000706	G	2900	70053H000A100A	HOSE            			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	LEAKING         	B			LX5R	A				UNSCHED LANDING         				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19	721LL					51164				HOSE LEAKED, FLUID EMPTIED.  LANDED AT BLOOMINGTON, ILL AIRPORT.  (X)						1	G	7	1 	3U			 	H2SW    					 
2000110600156	20001106	00156	CE  	2000	11	6	20000721SH038    	1	20000707	G	3710	442CW12	PUMP            			BEECH 	58    	58          	1152740	CE  											FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	25	7353R		222  			TH486				VACUUM PUMP FAILED UNDER NORMAL ENGINE OPERATING CONDITIONS.  THE INTERNAL DRIVE COUPLING AND ASSOCIATED INTERNAL SPLINE	 ASSY SEPARATED FROM THE ROTOR.  (NOT TO BE CONFUSED WITH THE NORMAL BREAK AWAY FLEXIBLE COUPLING.)     (X)					1	L	7	2 	3O			 	3A16    					 
2001020600118	20010206	00118	SW  	2001	2	6	20000721SH039    	1	20000721	G	2622	RTA600	EXTINGUISHER    			BELL  	407   	407         	       	SW  										CABIN	LEAKING         	B			FKFR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	03	888DJ					53408				FIRE EXTINGUISHER, BELL PN 40000, TRADE NAME ''RIGHT-OUT''TM IS STANDARD EQUIPMENT FROM THE BELL FACTORY.  THIS ONE LEAK	ED DOWN ON A FLIGHT TO THE REPAIR STATION.  AIRCRAFT TT 38.8 HOURS.  THE HELICOPTER WAS DELIVERED IN MAY, 2000, AT 16.0 	HRS.  HAPPENED DURING NICE HOT SUMMER WEATHER.  (X)				1	G	7	1 	3U			O	H2SW    					 
2000110600158	20001106	00158	NE  	2000	11	6	20000721SH040    	2	20000519	G	7310	S2495880000520	HOSE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  						LEAKING         	A			HSYA	A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			NM	05	903FE					208B0003				HNL - FLT 8666 - ON CLIMB-OUT, PILOT REPORTED ''FUEL FUMES IN COCKPIT''.  AIR TURNBACK TO HNL.  FUEL ACCUMULATION IN ENG	INE COWL DUE TO LOOSE FUEL LINE CONNECTION AT FIREWALL FUEL FILTER.  TIGHTENED THE NOSE FITTING, FLUSHED COWLING WITH SO	AP AND WATER.  PERFORMED GROUND RUN-UP LEAK CHECK.  AIRCRAFT RETURNED TO SERVICE.  (X)				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000110600186	20001106	00186	CE  	2000	11	6	20000724SH004    	1	20000624	G	2720		CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  										UNDER AFT FLRBD	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	17EA	465  				E3092				DURING ANNUAL INSPECTION, FOUND LT RUDDER CABLE RUBBING ON EDGE OF HOLE WHERE IT PASSES THROUGH BULKHEAD UNDER AFT FLOOR	BOARDS.  NO DAMAGE TO CABLE.  APPEARS TO RUB ONLY WHEN RUDDER IS FULLY DEFLECTED TO EITHER SIDE.  SUBMITTER SUGGESTED IN	SPECTION OF ALL CABLES WHERE THEY PASS THROUGH HOLES.  (X)				1	L	7	1 	3O			 	3A15    					 
2000110600187	20001106	00187	EA  	2000	11	6	20000724SH005    	2	20000705	G	8530		VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					EXHAUST	SEIZED          	G				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	733FF	5635 	1200 			17268256	L31676T			NR 1 CYLINDER EXHAUST VALVE SEIZED IN GUIDE, DESTROYED PISTON.  RESULTANT OIL SYSTEM CONTAMINATION HUNG NR 2 CYLINDER IN	TAKE LIFTER, BROKE CONNECTIN ROD, AND FAILED CASE.  LYC MANDITORY SB NR 388B DATED MAY 13, 1992, ADDRESSES SCHEDULED VAL	VE TO GUIDE CLEARANCE INSPECTIONS.  C/W THIS INSPECTION MAY PRECLUDE POTENTIAL SIMILAR INCIDENTS.  (X)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000110600188	20001106	00188	SO  	2000	11	6	20000724SH007    	1	20000714	G	2750	486631	SHAFT           	DUKES       		PIPER 	PA31  	PA31350     	7103110	SO  										CABLE END	FAILED          	I			FWRA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	01	100GW	210  				317305046				FLT 178 - AFTER  LANDING, PILOT RETRACTED FLAPS.  RT FLAP CAME UP, LT DID NOT.  A FAILURE OF THE LT FLAP FLEX SHAFT, PN 	486-631, THRUST OR RETAINING WASHER AT TRANSMISSION END ALLOWED DRIVE END OF CABLE TO PULL OUT OF TRANSMISSION INSIDE CA	BLE HOUSING CAUSING TRANSMISSION NOT TO ACTUATE AND THE LT FLAP NOT TO RETRACT.  SPLIT FLAP PROTECTION SYS FAILED DUE TO	 A FAILURE OF THE TIME DELAY RELAY ALLOWING A 40-DEGREE SPLIT CONDITION.  REPLACED LT FLAP FLEX SHAFT.  REPLACED TIME DE	LAY RELAY WITH SERVICABLE UNIT.  MOTOR REPLACED WITH OVERHAULED UNIT.  (X)		1	L	7	2 	3O			 	A20SO   					 
2001020600119	20010206	00119	NE  	2001	2	6	20000724SH008    	1	20000710	G	2435	200SGL115QZ	STARTER GEN     			SKRSKY	S76   	S76C        	8143008	NE  										ENGINE	DAMAGED         	B			EGRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	165ML		813  			760471				COOLING FANS ON BOTH UNITS ARE LOOSE.  (X)						1	G	7	2 	3U			NC	H1NE    					 
2001020600120	20010206	00120	NE  	2001	2	6	20000724SH009    	1	20000710	G	2435	2000SGL115QZ	STARTER GEN     			SKRSKY	S76   	S76C        	8143008	NE  										ENGINE	DAMAGED         	B			EGRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	165ML		813  			760471				COOLING FANS ON BOTH UNITS ARE LOOSE.  (X)						1	G	7	2 	3U			NC	H1NE    					 
2000110600190	20001106	00190	GL  	2000	11	6	20000724SH010    	3	20000707	G	6114		PROPELLER       	HARTZL      		PIPER 	PA36  	PA36300     	7103612	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	HUB	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	CCCFR	542  				7760020		CH30810A		DURING PROPELLER OVERHAUL, HUB, PN D-22-1-17, PROP ASSY, SN CH30810A, FACTORY HUB, PN A20277A, WAS DISCOVERED CRACKED.  	CRACK IS LOCATED IN BOTTOM HUB HALF, NR 2 BLADE SOCKET, T/E SIDE, CRACKED FROM INSIDE TO OUTSIDE ABOUT 3.5 INCHES AROUND	 BULKHEAD HUB HALF BOLT HOLE AND OUTER HUB HALF BOLT HOLE.  CRACK DOES NOT GO THROUGH BOLT HOLES, CRACK STOPS INBD OF OU	TER HUB HALF BOLT HOLE.  NOTE:  CRACK IS VISIBLE WITHOUT USE OF 10X GLASS.  HUB FALLS OUTSIDE S/N RANGE OF AD NOTE 90-02	-23.  PROP O/H WITH REPLACEMENT HUB AND RETURNED TO SERVICE 1-12-98. (X)		1	L	7	1 	3O			 	A10SO   		5	C	P920	 
2000110900001	20001109	00001	CE  	2000	11	9	20000724SH011    	1	20000630	G	5280	24130832	DOOR            			CESSNA	172   	172RG       	2072438	CE  										NOSE GEAR	FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	6313R					172RG0161				DURING ATTEMPT OF EXTENSION OF LANDING GEAR, MLG EXTENDED NORMALLY, NLG WOULD NOT EXTEND.  REPEATED ATTEMPTS WERE MADE T	O EXTEND NOSE GEAR WITH NO SUCCESS.  ACFT MADE SUCCESSFUL GEAR UP LANDING IN GRASS.  UPON LIFTING ACFT TO EXTEND GEAR, F	OUND RT NOSE GEAR DOOR OUTER SKIN WRINKLED AND DISTORTED.  PRIED SKIN ON DOOR AWAY FROM AIRFRAME SKIN AND NOSE GEAR FELL	 OUT OF WELL TO A DOWN AND LOCKED POSITION.  INVEST FOUND SPOT WELDS THAT HOLD INNER AND OUTER SKIN TOGETHER ON NOSE GEA	R DOOR HAD FAILED CAUSING DOOR SKIN TO BIND ON GEARWELL SKIN.  THIS INTERFERENCE WOULD NOT ALLOW GEAR TO EXTEND.   (X)		1	H	7	1 	3O			 	3A17    					 
2000080100138	20000801	00138	SO  	2000	8	1	20000724SH014    	1	20000615	G	3060		BOOT            			PIPER 	PA34  	PA34220T    	7103420	SO  						MCAULY	3AF34C	3AF34C*     	GL  	PROP DE-ICE	SEVERED         	D			IPMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	224BD					348133186				FOUND ALL 3 DEICE BOOT LEADS SEVERED AT CONNECTOR MOUNT BRACKET.  DETERMINED PROPELLER OVERHAUL SHOP INSTALLED INCORRECT	LY.  RECOMMEND INSTALLATION PROCEDURES OUTLINED IN PIPER MM AND BFG SB 3-84070 DATED OCT 1989 FOR PROPER BOOT INSTALLATI	ON.  SUBMITTER STATED THIS HAS BEEN A REPETITIVE PROBLEM.  (X)				1	L	7	2 	3O			 	A7SO    		5	C	P22EA	 
2000121800001	20001218	00001	GL  	2000	12	18	20000724SH015    	1	20000628	G	3222	NG01	STRUT           			AMTR  	EUROPA	XSTRIGEAR   	05607JV	GL  										WELDMENTS	FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	912EA					EA003XS				NOSE WHEEL FELL FROM AIRCRAFT DURING TOUCH AND GO''S.  AIRCRAFT LANDED ON REMAINDER OF NOSE STRUT.  INVESTIGATION SHOWS 	THAT WELD POINTS ON NOSE LANDING GEAR ASSY ARE POSSIBLY DEFECTIVE.  ALL WELD POINTS HAD EITHER CRACKED OR BROKEN ENTIREL	Y.  LANDINGS, 45.  (X)				1	L	7	1 	3O			NC	EXPA1L71					 
2000073100210	20000731	00210	SO  	2000	7	31	20000724SH016    	1	20000605	G	3230	2108303	HANDLE          	PIPER       		PIPER 	PA24  	PA24260     	7102406	SO  										 EMER LANDING GR	WORN            	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	9070P					244538				WHILE PERFORMING EMERG LANDING GEAR EXTENSION CHK DURING ANNUAL INSP, FOUND EMERG RELEASE MECH WOULD NOT DISENGAGE L/G  	FROM TRANSMISSION ASSY WHEN FLOORBOARDS AND RUGS WERE INSTALLED.  THIS PREVENTED LANDING GEAR FROM BEING EXTENDED USING 	MANUAL/EMERG MODE.  RELEASE LANDING GEAR/ARM PN 21083-03 WOULD HIT ON FORWARD EDGE OF ACCESS CUT-OUT IN CABIN FLOORBOARD	, PN 22720-00.  RELEASE MECH WOULD FUNCTION NORMALLY WITH FLOORBOARD REMOVED.  INSP REVEALED EXCESSIVE WEAR AT PIVOT POI	NTS FOR P/N 21083-03 RELEASE HANDLE ALLOWING EXCESS PLAY AND LOST MOTION IN RELEASE MECH.  THIS REQUIRED RELEASE HANDLE 	TO HAVE TO BE MOVED FURTHER FWD TO RELEASE LANDING GEAR WITH FLOORBOARD IN PLACE, HANDLE TRAVEL WAS RESTRICTED.	1	L	7	1 	3O			 	1A15    					 
2000073100211	20000731	00211	SO  	2000	7	31	20000724SH017    	1	20000713	G	2820		FUEL LINE       			PIPER 	PA22  	PA22150     	7102210	SO  										WING	DETERIORATED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	5785D					224461				A MECHANIC PERFORMING ANNUAL INSP, REPORTED  THE FUEL SYSTEM WOULD NOT FLOW FOR THE FUEL STRAINER TEST AND CLEANING.  T/	S FUEL SYS, FOUND BOTH RUBBER FUEL LINES IN BOTH WINGS WHERE THE TANK OUTLET FITTING IS CONNECTED TO THE FUSELAGE ALUMIN	UM FUEL LINE HAD DETERIORATED.  MECH REMOVED BOTH RUBBER HOSES AND FOUND INTERIOR RUBBER HAD COLLAPSED COMPLETELY STOPPI	NG ALL FUEL FLOW.  THE MARKING ON BOTH HOSES SHOWED MIL-H-6000 MFG DATE OF 3Q72.  ALSO, ACFT HAS BEEN OPERATED UNDER AN 	STC FOR AUTOFUEL FOR MANY YEARS AND HAD SET IDLE IN HANGAR FOR 2 YRS.  IT WAS MECHANIC''S OPINION THAT SOME ADDITIVE IN 	AUTOFUEL HAD SOFTENED INNER RUBBER LINING ALLOWING IT TO COLLAPSE AND SEAL LINE.	1	H	7	1 	3O			 	1A6     					 
2000073100212	20000731	00212	CE  	2000	7	31	20000724SH018    	1	20000616	G	2841		GAUGE           			CESSNA	182   	182Q        	2072732	CE  										INTERIOR	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11										PILOT REPORTED RT FUEL GAUGE STUCK ON APPROX ONE-THIRD FULL, NO MATTER WHAT ACTUAL LEVEL WAS.  REMOVED GAUGE AND FOUND P	IECE OF FOAM INSULATION THAT IS GLUED TO UNDERSIDE OF GLARE SHIELD HAD BECOME LODGED AROUND NEEDLE, PREVENTING IT FROM M	OVING.  THIS INSULATION WAS FALLING APART AND COVERING COOLING HOLES IN AVIONICS, ETC.				1	H	7	1 	3O			NT	3A13    					 
2000073100213	20000731	00213	CE  	2000	7	31	20000724SH019    	1	20000714	G	7820	075016189	MUFFLER         			CESSNA	185   	A185F       	2072821	CE  										OUTLET PIPE	SEPARATED       	G				A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			AL	03	71R					18503942				MUFFLER OUTLET PIPE FELL OFF AFTER TAKEOFF.  AIRCRAFT RETURNED.  MUFFLER AND SHROUD WERE REPLACED. AIRCRAFT RELEASED TO 	SERVICE.   (X)					1	H	7	1 	3O			 	3A24    					 
2000073100214	20000731	00214	EA  	2000	7	31	20000724SH020    	1	20000706	G	5540	RCM334TC10Z	HINGE           		MS2124254K  	WACO  	YMF   	YMF         	9600412	EA  										RUDDER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	90B	276  				F5033				FOUND ON ANNUAL INSPECTION, LOWER RUDDER HINGE BROKEN.  CAUSE UNKNOWN.  PART TT: 275.9 HOURS.  (X)						1	Q	7	1 	3R			 	ATC542  					 
2000073100215	20000731	00215	CE  	2000	7	31	20000724SH021    	1	20000606	G	3250	1243405200	SHAFT           			CESSNA	210   	210C        	2073412	CE  										NOSE GEAR  STRUT	BROKEN          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	23	3681Y	2634 				21058181				DURING LANDING, NOSE GEAR BEGAN TO SHAKE AND FORK ASSY BROKE CAUSING A PROP STRIKE AND DAMAGE TO NOSE GEAR DOORS.  INVES	TIGATION  FOUND NOSE GEAR STEERING SHAFT BROKEN, SHAFT FOUND TO BE PREVIOUSLY WELDED BY UNKNOWN PARTIES.  (X)					1	H	7	1 	3O			 	3A21    					 
2000073100216	20000731	00216	CE  	2000	7	31	20000724SH022    	1	20000701	G	3242	3063A	BRAKE ASSY      			CESSNA	182   	182E        	2072712	CE  										RT  MAIN	FAILED          	B			EIPR	O				OTHER                   				A			FLAME/FIRE                			LD	LANDING        	1			WP	07	3049Y					18254049				AIRCRAFT BRAKED VERY HARD TO CLEAR RUNWAY FOR AIRLINER ON SHORT FINAL.  ON TAXI BACK TO RUNWAY FOR TAKEOFF, PILOT NOTICE	D RT WHEEL ASSY ON FIRE.  THE FIRE DEPT FOAMED AIRCRAFT.   NOTE:  AIRCRAFT HAS ''STC'' SPEED FAIRINGS.  SUBMITTER BELIEV	ED THE DESIGN OF THE SPEED FAIRINGS DID NOT ALLOW HEAT TO ESCAPE.  THE EXCESSIVE HEAT CAUSED THE BRAKE CALIPER PACK TO P	OP OUT CAUSING A HYDRAULIC LEAK WHICH CAUGHT FIRE.  THE BOTTOM SKIN OF CABIN WAS WARPED BY THE FIRE.  BRAKE CALIPER WAS 	NOT FOUND.  (X)		1	H	7	1 	3O			NT	3A13    					 
2000073100217	20000731	00217		2000	7	31	20000724SH023    	4	20000531	G	6113	055032110	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  											BROKEN          	B			UKJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	538SP	41   				172S8395				DURING POST-FLIGHT INSPECTION, FOUND AFT EDGE OF PROPELLER SPINNER NEAR BLADE BENT OUTWARD.  FOUND AFT SPINNER BULKHEAD 	BROKEN AROUND THE FLOATING NUTPLATE.  REPLACED BULKHEAD WITH NEW.  WITH SUCH LOW TIME SINCE NEW ON THIS AIRCRAFT, IT IS 	POSSIBLE THIS BULKHEAD WAS IMPROPERLY FABRICATED.  THE NEW PART WAS INSPECTED AND POSSIBLY THIS ONE WILL ALSO FAIL DUE T	O THE WAY IT WAS FABRICATED AT THE RADIUS.  SUBMITTER SUGGESTED THE MFG INSPECT THE BULKHEADS IN THE AREA OF THE RADIUS 	AND CORRECT THIS PROBLEM.  (X)		1	H	7	1 	3O			NT	3A12    					 
2000073100218	20000731	00218	SO  	2000	7	31	20000724SH025    	2	20000614	G	8530	SA539467	PISTON PIN      			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					CYLINDER/PISTON	BROKEN          	B			NJ1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	22BS	140  				TC1928	454832			PORTION OF THE NR 6 CYLINDER PISTON PIN PLUG BROKE OFF AND CAUSED THE PISTON TO DISINTEGRATE.  THIS CAUSED DAMAGE TO THE	 CONNECTING ROD ON THE NR 5 CYLINDER AND DAMAGE TO THE CRANKCASE.  NO RECOMMENDATION TO PREVENT THIS AT THIS TIME.  (X)					1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2000073100219	20000731	00219	CE  	2000	7	31	20000724SH026    	1	20000714	G	7160	165201325	AIR BOX         	CESSNA      		CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	IO470F      	17026	SO  					HINGE PIN	DETACHED        	H				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			WP	23	6305F	33   				18264152	089945R			DURING T/S OF ROUGH ENG OPERATION FOLLOWED BY NOTED REDUCTION IN AVAILABLE POWER, THE ALTERNATE-AIR DOOR PN 1652013-25 W	AS FOUND LOOSE IN THE INDUCTION BOX.  THE HINGE PIN HAD SLID OUT OF THE HINGE ALLOWING THE DOOR TO PARTIALLY OBSTRUCT TH	E AIR FLOW TO  HE ENGINE.  UPON INSP OF THE HINGE, DETERMINED STACKING PROCEDURE DURING MFG WAS INADEQUATE TO RETAIN  HI	NGE PIN.  FURTHER ENG DAMAGE RESULTED FROM INGESTION OF THE HINGE SPRING THAT WAS FND LODGED IN THE EXH MUFFLER BAFFLE. 	AIR-BOX ASSY, PN 1652013-38 WAS INSTALLED IN CONJUNCTION WITH STC NR SA3825SW IN FACTORY NEW CONDITION; 32.6 HRS BEFORE.		1	H	7	1 	3O	3	O	NT	TA13    	3E1				 
2000073100220	20000731	00220	SO  	2000	7	31	20000724SH027    	2	20000714	G	7322	666916	FLOAT           	MARVELSCHEBX		CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  						SEPARATED       	H				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	104PM	1000 				18258085				FUEL SEEP AT CARBURETOR.  FOUND BOTH BELLOWS SEPARATED FROM FLOAT ARM. CONDITION EXISTED FOR SOME TIME AS SOLDER JOINTS 	WERE WORN SMOOTH.  (X)					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000121800002	20001218	00002	CE  	2000	12	18	20000728SH001    	1	20000727	G	2100		LINE            			CESSNA	210   	T210N       	2073456	CE  										CONDENSATION	LEAKING         	B			B30R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	5515Y					21064233				STC SA01194NY WAS INSTALLED IN THIS AIRCRAFT. THIS IS AN ELECTRIC AIR CONDITIONING SYSTEM.  PILOT HAD A NEW DEVICE, A TO	XIBEE ELECTRONIC CO DETECTOR. DURING FLIGHT, DETECTOR ALARM ACTUATED INDICATING AN UNSAFE LEVEL OF CO. MAINTENANCE INSPE	CTED AIRCRAFT AND FOUND THE CONDENSATION DRAIN LINE RAN THROUGH THE AIRFRAME IN THE MAIN GEAR WHEELWELL. THE LINE WAS AB	OUT .50 INCH OD GOING THROUGH A HOLE ABOUT 2 INCHES IN DIAMETER. THE MECHANIC SEALED THE HOLE AROUND DRAIN LINE WITH ALU	MINUM TAPE AND RTV AND A TEST FLIGHT WAS PERFORMED WITH NO CO DETECTED.  STC MANUFACTURER WAS CONTACTED AND HE SAID HE W	OULD PROVIDE REPAIR TO AREA TO MAKE A PERMENANT SEAL.	1	H	7	1 	3O			 	3A21    					 
2000121800003	20001218	00003	CE  	2000	12	18	20000728SH002    	1	20000727	G	2100		LINE            			CESSNA	210   	T210N       	2073456	CE  										CONDENSATIONS	LEAKING         	B			B30R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	5515Y					21064233				STC SA01194NY WAS INSTALLED IN THIS AIRCRAFT. THIS IS AN ELECTRIC AIR CONDITIONING SYSTEM.  PILOT HAD A NEW DEVICE, A TO	XIBEE ELECTRONIC CO DETECTOR. DURING FLIGHT THE DETECTOR ALARM ACTUATED INDICATING AN UNSAFE LEVEL OF CO. MAINTENANCE IN	SPECTED AIRCRAFT AND FOUND THAT THE CONDENSATION DRAIN LINE RAN THROUGH THE AIRFRAME IN THE MAIN GEAR WHEELWELL. THE LIN	E WAS ABOUT .50 INCH OD GOING THROUGH A HOLE ABOUT 2 INCHES IN DIAMETER.  THE MECHANIC SEALED THE HOLE AROUND DRAIN LINE	 WITH ALUMINUM TAPE AND RTV AND A TEST FLIGHT WAS PERFORMED WITH NO CO DETECTED.  STC MANUFACTURER WAS CONTACTED AND HE 	SAID HE WOULD PROVIDE REPAIR TO AREA TO MAKE A PERMENANT SEAL.	1	H	7	1 	3O			 	3A21    					 
2000073100222	20000731	00222	EA  	2000	7	31	20000728SH004    	2	20000703	G	8520	75458	CRANKSHAFT      	LYC         		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 4 CNTRWEIGHT	BROKEN          	B			EKIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	252MA	1095 	248  			31P33	L25562			NR 4 COUNTERWEIGHT DEPARTED CRANKSHAFT AND PUNCHED HOLE IN TOP OF CASE AFTER TAKEOFF.  RETURNED TO PHI AND LANDED SAFELY	.  SUBMITTER STATED THIS APPEARS TO BE A CONTINUING PROBLEM WITH THIS ENGINE.  (X)					1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2000073100223	20000731	00223	SO  	2000	7	31	20000728SH010    	1	20000608	G	2731	96003000	BUSHING         			PIPER 	PA34  	PA34220T    	7103420	SO  										TAIL	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	550ST	2957 				348533008				EXCESSIVE PLAY IN ELEVATOR TRIM TABS.  HOLES IN UPPER LINK, PN 96003-000, WORN OUT.  NEW PARTS HAVE BRASS BUSHINGS INSTA	LLED IN THESE HOLES, BUT IT IS NOT CALLED OUT IN THE PARTS MANUAL OR BY A SERVICE BULLETIN.  (X)					1	L	7	2 	3O			 	A7SO    					 
2000080800170	20000808	00170	CE  	2000	8	8	20000728SH011    	1	20000710	G	2100		A/C PACK        			CESSNA	210   	T210N       	2073456	CE  										DRAIN LINE MLGWW	MISINSTALLED    	B			B3OR	O				OTHER                   				J	W		WARNING INDICATION        	INADEQUATE Q C            		CR	CRUISE         	1			SW	03	5515Y					21064233				DURING ROUTINE FLIGHT, PILOTS WERE TRYING OUT A NEW ELECTRONIC CO DETECTOR, TOXIBEE, AND THE UNIT REGISTERED 50 PPM OF C	O (MAXIMUM THAT IT WILL REGISTER). THIS AIRCRAFT JUST HAD AN AIR CONDITIONING SYSTEM INSTALLED PER STC SA01194NY. MAINTE	NANCE INVESTIGATED THE INSTALLATION AND FOUND THAT CONDENSATION DRAIN LINE EXITED CABIN INTO REAR WHEELWELL AREA THROUGH	 A LARGE DIAMETER HOLE (NOTE: TUNE OD IS .50 INCH ,  HOLE IS ABOUT 2 INCHES). THIS HOLE WAS SEALED OFF WITH ALUMINUM TAP	E AND RTV AND AIRCRAFT WAS TEST FLOWN WITH NO INDICATION OF CO AT ALL ON THE TOXIBEE. THE AIRCRAFT WILL RETURN TO STC IN	STALLER WHO WILL PERFORM PERMANENT REPAIR TO DRAIN EXIT.	1	H	7	1 	3O			 	3A21    					 
2000073100225	20000731	00225	EA  	2000	7	31	20000731SH001    	2	20000710	G	7414	6351	MAGNETO         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					CAM FOLLOWER	FAILED          	A			LABA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05		200  								DUE TO NOT HAVING AN OIL FELT WIPER, A VERY HIGH NUMBER OF NEW OR OVERHAULED SLICK MAGS ARE HAVING EXCESSIVE WEAR ON POI	NTS CAM FOLLOWER, AND POINTS ARE SLOWLY CLOSING.  SUBMITTER STATED  E-GAP MUST NOT ONLY BE CHECKED EVERY 100-HOURS, BUT 	IN MOST CASES ADJUSTED.   (X)				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000110600090	20001106	00090	SW  	2000	11	6	20000731SH002    	1	20000706	G	3211	19805	BOLT            			BBAVIA	7     	7GCBC       	1220601	SW  										LANDING GEAR	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	17						33472				LEFT SIDE, LANDING GEAR DEPARTED AIRCRAFT.  (X)						1	H	7	1 	3O			NC	A759    					 
2000073100226	20000731	00226	SW  	2000	7	31	20000731SH003    	1	20000706	G	3211	MS2000532	BOLT            			BBAVIA	7     	7GCBC       	1220601	SW  										LANDING GEAR	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	10989					33472				LEFT SIDE, LANDING GEAR DEPARTED AIRCRAFT.  (X)						1	H	7	1 	3O			NC	A759    					 
2000110600091	20001106	00091	SO  	2000	11	6	20000731SH004    	1	20000720	G	7920	LW13388	GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ACCY HOUSING	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	200AK	342  				318052180	L79368A			OIL FILTER CONVERTER PLATE REMOVED FOR SEAL INSPECTION.  SEAL FOUND TO BE SOFT AND EXTRUDED.  THIS IS THE SECOND SEAL FO	UND TO EXHIBIT THIS CONDITION.  ENGINE WAS A FACTORY OVERHAUL WITH OVERHAUL DATE OF 3-27-00.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000110600092	20001106	00092	EA  	2000	11	6	20000731SH005    	2	20000717	G	8510	AEL36001Y	CRANKSHAFT      			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  						FAILED          	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	25	2265M	243  				287890238	L2417636A			CRANKSHAFT FAILED IN-FLIGHT, FORWARD CHEEK OF NR 4 CONROD JOURNAL.  AIRCRAFT LANDED AT AIRPORT.  NO DAMAGE.  (X)						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000110600099	20001106	00099	SO  	2000	11	6	20000731SH007    	1	20000710	G	7810	403109	EXHAUST PIPE    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ATTACH FLANGE	CRACKED         	I			LABA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	3523Y					317952115				ATTACH FLANGE (TURBO END) OF NR 2 ENGINE OUTBOARD EXHAUST CRACKED AND PIPE DISCONNECTED FROM TURBO.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000110600101	20001106	00101	SO  	2000	11	6	20000731SH008    	1	20000719	G	5541	6106200	RUDDER          			PIPER 	PA25  	PA25        	7102502	SO  	LYC   	O320  	O320A1A     	41508	EA  					RUDDER POST	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6220Z	5900 				25263	L292227			RUDDER TAIL POST CORRODED AND BROKE JUST ABOVE LOWER RUDDER MOUNTING PIN AND FORMING TUBE BROKE OFF AT RUDDER  POST.  (X	)					1	L	7	1 	3O	3	O	 	2A10    	E274				 
2000110600102	20001106	00102	SO  	2000	11	6	20000731SH009    	1	20000629	G	2820	GL06049	HOSE            			BALWKS	FIREFY	FIREFLY9    	1050124	SO  										CRIMP END/HOSE	SPLIT           	B			FJ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	90660					F9037				OUTER COVERING OF FUEL HOSES SPLIT AT CRIMP END FITTING.  10 BAD HOSES.  (X)						1	B	0	0 	  			 	A14SO   					 
2000110600103	20001106	00103	SO  	2000	11	6	20000731SH010    	1	20000620	G	2810	462056	GASKET          			PIPER 	PA28  	PA28181     	7102807	SO  										FUEL CAP	TORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	926PA	9    				2843289				THE FUEL CAP GASKET DETERIORATES AND TEARS AFTER PUTTING THE FUEL CAP ON AND OFF A FEW TIMES.  APPROXIMATELY 10 TIMES OF	 TAKING THE FUEL CAP ON AND OFF.  (X)					1	L	7	1 	3O			 	2A13    					 
2000110600104	20001106	00104	EA  	2000	11	6	20000731SH011    	2	20000712	G	8530	74541	EXHAUST VALVE   	LYC         		PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					VALVE FACE	BROKEN          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	8914J	1885 				282929				PILOT REPORTED DURING CRUISE OPERATION ENGINE BECAME ROUGH AND LOST PARTIAL POWER.  PRECAUTIONARY LANDING WAS MADE AT RU	SH CITY, MN, REGIONAL AIRPORT. INVESTIGATION DISCLOSED APPROX 50 PERCENT OF NR 2 EXHAUST VALVE FACE MISSING, AND EVIDENC	E OF PIECES IMPACTING THE PISTON CYL HEAD AND SPARK PLUGS.   UPON REMOVAL OF CYLINDER, 3 PIECES OF THE VALVE WERE RECOVE	RED FROM THE EXHAUST SYS.  NO DEBRIS OR DAMAGE WAS FOUND INSIDE THE ENG OR OIL FILTER.  NO ADVANCE SYMPTOMS REPORTED.  A	NNUAL INSP 20 HOURS PRIOR.  COMPRESSION WAS 32/80 AT THAT TIME.  USED CYL INSTALLED FOR FLIGHT TO OVERHAUL SHIP.  NORMAL	 OPERATION REPORTED.  (X)	1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000110600105	20001106	00105	SO  	2000	11	6	20000731SH012    	2	20000731	G	8520	A239610N	CRANKSHAFT      			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					FLANGE	CRACKED         	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	73100		10   			20700559	818889R			CRANKSHAFT CRACKED AND FAILED JUST AFT OF FLANGE AND PROPELLER SEPARATED FROM AIRCRAFT WHILE IN-FLIGHT.  (X)						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2000110600106	20001106	00106	CE  	2000	11	6	20000731SH013    	1	20000710	G	3222	1243400201	FORK            			CESSNA	210   	210B        	2073410	CE  										NOSE GEAR	BROKEN          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	01	9661X					21057961				WHILE TAXIING OFF RUNWAY, NOSE GEAR FORK BROKE OFF AT OLEO.  RIGHT FORK SHOWED SIGNS OF OLD SEPARATION OR CRACK.  (X)						1	H	7	1 	3O			 	3A21    					 
2000110600107	20001106	00107	EA  	2000	11	6	20000731SH014    	2	20000710	G	7322		SERVO           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  						FAILED          	I			LABA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	95C					327804118				REBUILT SERVO ON ZERO TIMEOVERHAUL FROM FACTORY  (LYC).  BOTH RAN LEAN, REPLACEMENT SERVO CORRECTED PROBLEM.  (X)						1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000110600108	20001106	00108	EA  	2000	11	6	20000731SH015    	2	20000710	G	7322		SERVO           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  						FAILED          	I			LABA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	18C					327640049				REBUILT SERVO ON ZERO TIME OVERHAUL FROM FACTORY (LYC).  BOTH RAN LEAN, REPLACMENT SERVO CORRECTED PROBLEM.  (X)						1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000110600109	20001106	00109	GL  	2000	11	6	20000731SH016    	3	20000713	G	6111	S82NC55	BLADE           			CESSNA	310   	T310R       	2074246	CE  						MCAULY	3AF32C	3AF32C93    	GL  	THREADS	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5466J					310R0264		805686		THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150.   (X)						1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2000110700004	20001107	00004	GL  	2000	11	7	20000731SH017    	3	20000713	G	6111	S82NC55	BLADE           			CESSNA	310   	T310R       	2074246	CE  						MCAULY	3AF32C	3AF32C93    	GL  	THREADS	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5466J					310R0264		805686		THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2000110700005	20001107	00005	GL  	2000	11	7	20000731SH018    	3	20000713	G	6111	S82NC55	BLADE           			CESSNA	310   	T310R       	2074246	CE  						MCAULY	3AF32C	3AF32C93    	GL  	THREADS	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5466J					310R0264		805686		THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2000110700006	20001107	00006	GL  	2000	11	7	20000731SH019    	3	20000713	G	6111	S82NC55	BLADE           			CESSNA	310   	T310R       	2074246	CE  						MCAULY	3AF32C	3AF32C93    	GL  	THREADS	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5466J					310R0264		961060		THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2000110700007	20001107	00007	GL  	2000	11	7	20000731SH020    	3	20000713	G	6111	S81NC55	BLADE           			CESSNA	310   	T310R       	2074246	CE  						MCAULY	3AF32C	3AF32C93    	GL  	THREADS	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5466J					310R0264		961060		THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2000110700008	20001107	00008	GL  	2000	11	7	20000731SH021    	3	20000713	G	6111	S82NC55	BLADE           			CESSNA	310   	T310R       	2074246	CE  						MCAULY	3AF32C	3AF32C93    	GL  	THREADS	SCRATCHED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5466J					310R0264		961060		THE BLADE WAS REJECTED DUE TO SCRATCHES IN THREADS PER MCAULEY SB 150.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P22EA	 
2000110700009	20001107	00009	CE  	2000	11	7	20000731SH024    	1	20000731	G	2822	1C712	PUMP            			CESSNA	500   	500CESSNA   	2076602	CE  										INTERNAL SEAL	LEAKING         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17										BOOST PUMP WAS CAUSING CIRCUIT BREAKER TO TRIP.  FURTHER INVESTIGATION REVEALED UNIT WOULD PUMP FUEL UP THROUGH THE ELEC	TRICAL MOTOR THEN THROUGH THE WIRE PROTECTIVE COVERING FINALLY COMING OUT OF THE BACK OF THE CANNON PLUG AND WOULD SHORT	 THE WIRES TOGETHER CAUSING THE CIRCUIT BREAKER TO TRIP. (X)				1	L	7	2 	4F			 	A22CE   					 
2000110700010	20001107	00010	NM  	2000	11	7	20000731SH025    	1	20000510	G	5311		FRAME           			BOEING	727   	727232      	1384082	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	33785					20640				DURING A C-CHECK, CORROSION WAS NOTED ON FRAME UPPER FLANGE AT STA 1010, RIGHT.  (X)						2	L	7	3 	4F			 	A3WE    					 
2001020600122	20010206	00122	SW  	2001	2	6	20000731SH027    	1	20000616	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	387  				532027				WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH.  SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING	S AS REFERENCED IN AD 2000-02-12. (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600123	20010206	00123	SW  	2001	2	6	20000731SH028    	1	20000616	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	387  				532027				WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH.  SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING	S AS REFERENCED IN AD 2000-02-12. (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600124	20010206	00124	SW  	2001	2	6	20000731SH029    	1	20000616	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R  DRIVESHAFT	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	387  				532027				WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH.  SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING	S AS REFERENCED IN AD 2000-02-12. (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600125	20010206	00125	SW  	2001	2	6	20000731SH030    	1	20000616	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	387  				532027				WHILE C/W BELL A3B-407-00-35, FOUND 4 EACH BEARINGS TO BE ROUGH.  SUBMITTER STATED THESE WERE NOT THE OIL COOLER BEARING	S AS REFERENCED IN AD 2000-02-12. (X)					1	G	7	1 	3U			O	H2SW    					 
2000121800004	20001218	00004	NM  	2000	12	18	20000731SH032    	1	20000510	G	5330		SKIN            			BOEING	727   	727231      	1384079	NM  										STA 480-500	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24343					21630				DURING A C-CHECK, CORROSION WAS NOTED ON SKIN BETWEEN STR 27 - STR 28L OF STA 480 - STA 500.  (X)						2	L	7	3 	4F			 	A3WE    					 
2000121800005	20001218	00005	NM  	2000	12	18	20000731SH033    	1	20000510	G	5311		FRAME           			BOEING	727   	727231      	1384079	NM  										STA 970-990	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24343					21630				DURING A C-CHECK, CORROSION WAS NOTED ON FRAME AT STA 970 - STA 990, STR 29L.  OUTBOARD FLANGE, ALSO NOTED ON STR 29R.  	(X)					2	L	7	3 	4F			 	A3WE    					 
2000121800006	20001218	00006	NM  	2000	12	18	20000731SH034    	1	20000510	G	2510		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										STA 1030 - 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24343					21630				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK, INBOARD, LEFT STA 1030 - STA 1110, AND OUTBOARD TRACK.  (X)						2	L	7	3 	4F			 	A3WE    					 
2000121800007	20001218	00007	NM  	2000	12	18	20000731SH035    	1	20000510	G	5320		SILL            			BOEING	727   	727231      	1384079	NM  										L-2 DOOR/MOPSILL	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24343					21630				DURING A C-CHECK, CORROSION WAS NOTED ON L-2 DOOR MOP SILL.  (X)						2	L	7	3 	4F			 	A3WE    					 
2000121800008	20001218	00008	NM  	2000	12	18	20000731SH036    	1	20000510	G	5315		FLOOR SUPPORT   			BOEING	727   	727231      	1384079	NM  										STA 400-420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24343					21630				DURING A C-CHECK, CORROSION WAS NOTED ON FLOOR SUPPORT, STA 400 - STA 420, BETWEEN BL ZERO AND RBL 24.75. (X)						2	L	7	3 	4F			 	A3WE    					 
2000121800009	20001218	00009	NM  	2000	12	18	20000731SH037    	1	20000510	G	5315		FLOORBEAM       			BOEING	727   	727231      	1384079	NM  										STA 380	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	24343					21630				DURING A C-CHECK, CORROSION WAS NOTED ON FLOORBEAM AT STA 380 FROM RT MOPSILL AND R-1 DOOR TO BL ZERO.  (X)						2	L	7	3 	4F			 	A3WE    					 
2000101000340	20001010	00340	CE  	2000	10	10	20000802SH008    	1	20000322	G	5712	07221892	RIB             	CESSNA      		CESSNA	206   	206H        	2073301	CE  										RT WING	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	2312V	294  				20808046				DURING 100-HOUR INSPECTION, DISCOVERED THE RT WING LEADING EDGE NOSE RIB LOCATED AT STA 136.00 CRACKED AT THE LIGHTENING	 HOLE.  SUBMITTER SUSPECTED PART WAS DAMAGED DURING INITIAL INSTALL AT THE FACTORY ASSY LINE. (X)					1	H	7	1 	3O			RT	A4CE    					 
2000101000341	20001010	00341	CE  	2000	10	10	20000802SH009    	1	20000322	G	2810	121640752	TANK            	CESSNA      		CESSNA	206   	206H        	2073301	CE  										RT SUBFLOOR	LEAKING         	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	2312V	294  				20608046				DURING 100-HOUR INSPECTION, DISCOVERED THE RT AUXILIARY FUEL TANK LEAKING FROM A JOINT WELD LOCATED ON THE TOP LEFT SIDE	, AND LEAKING FROM THE AFT SIDE OF THE TANK WHERE THERE WAS EVIDENCE OF THE ELECTRODE TOUCHING THE TANK DURING ITS PRODU	CTION, AND BURNING A HOLE THROUGH THE SIDE.  NOTE:  SUBMITTER STATED THIS HOLE WAS NOT LOCATED ON AN EXISTING WELD OR NE	AR A FITTING.  (X)			1	H	7	1 	3O			RT	A4CE    					 
2000101000342	20001010	00342		2000	10	10	20000802SH010    	4	20000322	G	6122	C1610310121	GOVERNOR        			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					POWERPLANT	LEAKING         	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	2312V	294  				20608046	L269848A			DURING 100-HOUR INSPECTION, DISCOVERED PROPELLER GOVERNOR LEAKING FROM PLUG LOCATED ON THE TOP OF THE GOVERNOR.  (X)						1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000101000343	20001010	00343	CE  	2000	10	10	20000802SH011    	1	20000313	G	2820	1200406249	LINE            			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					HEADER TANK	DAMAGED         	E				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	7254H	267  				20608036	L2688948A			DURING A 100-HOUR INSPECTION, FOUND FUEL LINE FROM FUEL BOOST PUMP TO LT HEADER TANK LEAKING AT THE HEADER TANK FITTING.	  UPON REMOVAL OF LINE, DISCOVERED DAMAGED FLARE.  AIRCRAFT TT 288.7 HOURS.  (X)					1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000101000346	20001010	00346	EA  	2000	10	10	20000802SH014    	2	20000714	G	7324	25765561	FLOW DIVIDER    	PRECISION   		CESSNA	206   	T206H       	       	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  						FAILED          	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	2467X	11   			70194901	T20608155	L1040461A			WHILE C/W TEXTRON-LYC SA 55-550 ENG RECALL, FUEL FOUND IN CRANKSCASE MIXED WITH OIL.  TEXTRON CHECKED FUEL SYS, FOUND NO	 PROBLEMS.  TECH REP INSPECTED INSTALL AND FOUND NO PROBLEMS WITH INSTALL, BUT NOTED FUEL DRIPPING FROM FUEL INJECTOR LI	NES WITH MIX AND THROTTLE CONTROLS IN FWD POSITION WITH NO FUEL BOOST PUMP ON AND FUEL SEL ON.  CONDITION CONSIDERED NOR	MAL BY TEXTRON AND SUGGESTED TO SHUT OFF FUEL SEL AT EACH ENG SHUT DOWN.  TEXTRON RELAYED FUEL SERVO WAS NOT POSITIVE SH	UT-OFF TYPE, FUEL FLOW DIVIDER HAS BLEED HOLE FOR ENG TO BE ABLE TO IDLE AND THIS IS WHY FUEL KEEPS DRIPPING.		1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2000101000347	20001010	00347	EA  	2000	10	10	20000802SH015    	2	20000717	G	8530	MS139973	KEEPER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CYLINDER	FAILED          	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	4822G					17273370	L678276T			MAJOR DAMAGE TO THE ENGINE CAUSED AS A RESULT OF THE VALVE KEEPERS BREAKING AND ALLOWING THE EXHAUST VALVE TO FALL INTO 	THE COMBUSTION CHAMBER FOR CAUSE APPEARS TO BE KEEPERS BROKE WHILE WEARING ON THE VALVE UNTIL RELEASE.  THE VALVE BROKE 	AWAY FROM THE HEAD OF THE VALVE AND WAS DRIVEN THROUGH THE TOP OF THE CYLINDER AND ENDED UP INSIDE THE MUFFLER ALONG WIT	H LARGE CHUNKS OF THE PISTON WHICH BROKE OFF AND EXITED THROUGH THE NOW EMPTY EXHAUST PORT.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000101000348	20001010	00348	EA  	2000	10	10	20000802SH016    	2	20000717	G	8530	SL54017	VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					CYLINDER	FAILED          	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	4822G					17273370	L678276T			MAJOR DAMAGE TO THE ENGINE CAUSED AS A RESULT OF THE VALVE KEEPERS BREAKING AND ALLOWING THE EXHAUST VALVE TO FALL INTO 	THE COMBUSTION CHAMBER FOR CAUSE APPEARS TO BE KEEPERS BROKE WHILE WEARING ON THE VALVE UNTIL RELEASE.  THE VALVE BROKE 	AWAY FROM THE HEAD OF THE VALVE AND WAS DRIVEN THROUGH THE TOP OF THE CYLINDER AND ENDED UP INSIDE THE MUFFLER ALONG WIT	H LARGE CHUNKS OF THE PISTON WHICH BROKE OFF AND EXITED THROUGH THE NOW EMPTY EXHAUST PORT.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000110700012	20001107	00012	SO  	2000	11	7	20000802SH017    	1	20000626	G	2700	82836002	ROD END         			PIPER 	PA46  	PA46310P    	7104605	SO  										AT BOTTOM TUBE	CORRODED        	B			SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6910T	3181 				468508067				DURING ANNUAL INSPECTION, TUBE WAS FOUND WITH EXTERIOR CORROSION ON BOTTOM AFT SURFACE.  FLAKED OFF LOOSE PAINT FOUND A 	DEEP PIT.  ABLE TO PASS THIS TUBE WITH AN AWL.   WAS ABLE TO PUSH THROUGH A SECOND AREA OF TUBE THAT DID NOT HAVE SIGNS 	OF CORROSION EXTERNALLY.  POSSIBLY CAUSE IS WATER GETTING INTO THE INSIDE OF ROD ASSY FROM THE FORWARD ROD END.  SUBMITT	ER RECOMMENDED INSPECTION FOR CORROSION AND SPRAYING A CORROSION PREVENTIVE INSIDE OF TUBE.  (X)			1	L	7	1 	3O			RT	A25SO   					 
2000110700013	20001107	00013	EA  	2000	11	7	20000802SH018    	2	20000628	G	8530		EXHAUST VALVE   			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					LEFT, NR 2 CYL	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	8219Y					301347				DURING FLIGHT, PILOT HEARD BANG AND NOTICED DIMINISHED  POWER.  PILOT LANDED WITH BOTH ENGINES RUNNING.  ON GROUND, INSP	ECTION FOUND ''O'' COMPRESSION ON LEFT ENGINE, NR 2 CYLINDER.  ON FURTHER INSPECTION, TOP OF EXHAUST VALVE WAS SHEARED O	FF STEM.  STEM WAS STILL IN PLACE, VALVE WAS GONE, CYLINDERS AND PISTONS WERE BADLY GOUGED.  (X)				1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2000110900002	20001109	00002	NE  	2000	11	9	20000802SH021    	2	20000717	G	8530	399359	CYLINDER        			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R134059     	52016	NE  					SPARK PLUG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	7502Y		1070 			821B	19771			THE NUMBER SEVEN CYLINDER HEAD IS CRACKED STARTING AT THE FORWARD SPARK PLUG BOSS RADIATING UP OVER THE TOP OF THE HEAD 	AND STOPS AT THE AFT SPARK PLUG BOSS.  THE CRACK IS OPEN TO AS MUCH AS .0625 INCH, AND EXHAUST GAS RESIDUE IS PRESENT.  	TOTAL TIME OF CYLINDER IS UNKNOWN.  (X)				1	Q	7	1 	3R	3	R	 	1A16    	5E2				 
2000110700017	20001107	00017	CE  	2000	11	7	20000802SH024    	1	20000622	G	2711		CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  										AILERON	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	581SA	46   				TH1942				FOUND ONE OF THE AILERON TRIM CABLES CUTTING INTO A FREON LINE UNDER THE FLOOR ON THE LEFT SIDE OF AIRCRAFT BETWEEN STA 	100.00 - STA 118.5, P/N 58-555028-13.  LINE NEEDS TO FORM DIFFERENTLY TO PROVIDE CLEARANCE FROM THE CABLES.  (X)					1	L	7	2 	3O			 	3A16    					 
2000110700018	20001107	00018	CE  	2000	11	7	20000802SH025    	1	20000717	G	2820	10192000015	TUBE            			BEECH 	200   	200BEECH    	1152920	CE  										LT WHEELWELL	CHAFED          	B			T4OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	1115F	5981 				BB324				SMALL HOLE CHAFED IN TUBE.  INSTALLED NEW TUBE, POSITIONED FOR PROPER CLEARANCE.  (X)						1	L	7	2 	4T			 	A24CE   					 
2000110700020	20001107	00020	SO  	2000	11	7	20000802SH027    	1	20000720	G	7920	LW13904	PLATE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					HOUSING SEAL	DISTORTED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	200AK	342  				318052180	L79368A			OIL FILTER CONVERER PLATE REMOVED FOR SEAL INSPECTION.  SEAL FOUND SOFT AND EXTRUDED.  THIS IS THE SECOND SEAL FOUND TO 	EXHIBIT THIS CONDITION.  ENGINE WAS A FACTORY OVERHAUL WITH OVERHAUL DATE OF 3-27-00. (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000110700021	20001107	00021	CE  	2000	11	7	20000802SH028    	1	20000610	G	3233	12810012	ACTUATOR        			CESSNA	210   	T210N       	2073456	CE  										BROKEN BODY	BROKEN          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4673Y	11299				21063978				RIGHT MAIN GEAR DID NOT FULLY RETRACT.  GEAR WAS EXTENDED AND AIRCRAFT LANDED WITHOUT PROBLEMS.  FOUND THE RT MLG ACTUAT	OR BODY BROKEN JUST FORWARD OF THE ROLLER BEARING.  THIS ALLOWED THE RACK AND PINION GEARS TO ''''JUMP A TOOTH''''.  THE	 ACTUATOR BODY, P/N 128101-2, WAS REPLACED.  (X)				1	H	7	1 	3O			 	3A21    					 
2000110700022	20001107	00022	CE  	2000	11	7	20000802SH029    	1	20000721	G	3221	NAS464P426	BOLT            			CESSNA	421   	421B        	2076014	CE  										RT MLG	BROKEN          	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	5987M	7775 				421B0329				HEAD OF BOLT BROKE OFF ALLOWING THE REMAINDER OF THE BOLT TO SLIDE OUT.  WHEN THE BOLT SLID OUT AND WAS ONLY ON ONE OF T	HE LUGS ON THE MAIN GEAR TRUNNION, THE LUG FAILED.  (THERE ARE TWO LUGS ON THE TRUNNION).    (X)					1	L	7	2 	3O			 	A7CE    					 
2000110700023	20001107	00023	CE  	2000	11	7	20000802SH030    	1	20000714	G	7603	565549011	THROTTLE CABLE  			CESSNA	172   	172P        	2072436	CE  											INACCURATE      	B			DYCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07	54356					17274961				OWNER REQUESTED THROTTLE CABLE BE CHANGED DUE TO CABLE CREEPING.  WHEN CABLE WAS COMPARED TO ORIGINAL CABLE, NEW CABLE W	AS FOUND TO HAVE MANY DIFFERENCES:  LENGTH WAS LONGER; FIREWALL SLEEVE IN DIFFERENT LOCATION; LARGER DIAMETER; ENGINE MO	UNT ATTACHMENT COMPLETELY OFF.  CESSNA NOTIFIED.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000080300223	20000803	00223	SW  	2000	8	3	20000803SH001    	1	20000705	G	7332	407075024103	INDICATOR       			BELL  	407   	407         	       	SW  										FUEL PRES.	ERRATIC         	B			GS1R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407WH	389  				532027				REPLACED FUEL PRESSURE INDICATOR WITH NEW FROM BELL HELICOPTER.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001011104087	20010111	04087		2001	1	11	20000803SH004    	1	20000720	G	3350	37815001	BATTERY PACK    																	CELL TAPS/SPOT W	FAILED          	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										CELL TAG SPOT WELDS BROKEN AND TABS DISTORTED AT ELECTRICAL CENTER OF PACK., AND AT ONE ADDITIONAL LOCATION.  DAMAGE OCC	URRED DURING SHIPPING/HANDLING OF PACK BETWEEN FACTORY AND END USER.  POSSIBLE CAUSE IS INADEQUATE ADHESIVE USED DURING 	MANUFACTURING OF PACK.   NOTE:  THIS PACK DOES HAVE SMALL AMOUNT OF ADHESIVE BETWEEN PACK HALVES, BUT IS NOT ADEQUATE TO	 SUPPORT HANDLING STRESSES.  SUBMITTER RECOMMENDED MORE EXTENSIVE USE OF ADHESIVE AND PERHAPS APPLICATOR NOZZLES TO REAC	H CORE OF PACK AND BETWEEN CELLS.  (X)															 
2001011104088	20010111	04088		2001	1	11	20000803SH005    	1	20000719	G	3350	37815001	BATTERY PACK    																	CELL TABS 10&11	FAILED          	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										CELL TAB  SPOT WELDS BROKEN AT ELECTRICAL CENTER OF BATTERY PACKS (BETWEEN CELLS NR 10 AND NR 11).  DAMAGE TO TABS/SPOT 	WELDS IS OCCURRING DURING SHIPPING/HANDLING OF THESE PACKS BETWEEN FACTORY AND END USER.  POSSIBLE CAUSE IS LACK OF ADHE	SIVE BETWEEN  CELLS AND PACK HALVES WHICH ONCE WAS, BUT NO LONGER USED DURING MANUFACTURE OF PACKS.  SUBMITTER RECOMMEND	ED USE OF ADHESIVE IN ASSEMBLY.  (X)																 
2000112800062	20001128	00062	GL  	2000	11	28	20000803SH007    	3	20000620	G	6110	6506709	BRUSH BLOCK     													ALLSN	A6441	A6441FN606  	GL  		CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										CRACK IN METAL, PN 6506709, IN BRUSH BLOCK LEAF ASSEMBLY.  (X)																6	C	P898	 
2000112800063	20001128	00063	SO  	2000	11	28	20000803SH009    	1	20000714	G	2410	635796	COUPLING        	PRESTOLITE  		PIPER 	PA34  	PA34200T    	7103406	SO  										COUPLES ALT/ENG	FAILED          	B			HE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	345HK	380  			0070545	347870359				SUBMITTER STATED THIS IS THIRD FAILURE EXPERIENCED, TWO PREVIOUS ON RIGHT ENGINE.  BOND BETWEEN RUBBER SLEEVE AND ACCESS	ORY DRIVE GEAR AND ALTERNATOR COUPLE FAILED WITH GEAR SLIPPING RELATIVE TO COUPLE, CAUSED ALTERNATOR TO FAIL UNDER LOAD.	  (X)				1	L	7	2 	3O			 	A7SO    					 
2000112800064	20001128	00064	EA  	2000	11	28	20000803SH010    	2	20000707	G	7250	3032651	VANE            	PWA         		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  					VANE T/E REPAIR	INACCURATE      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	24BH		176  		10471	U67	PCE51931			A TREND HAS DEVELOPED INDICATING PROCEDURES, TECHNIQUES, OR WORKMANSHIP OF OVERHAULED VANE RINGS IS RESULTING IN PREMATU	RE FAILURE OF PN 3032651 WHICH RESULTS IN UNSATISFACTORY ENGINE PERFORMANCE AND POSSIBLE ENGINE FAILURE.  (X)					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000112800065	20001128	00065	SO  	2000	11	28	20000803SH011    	1	20000607	G	7920	13388	GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ACCESSORY CASE	ERODED          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	01	3536B	734  	367  			317952205	L54361A			GASKET UNDER OIL FILTER CONNECTOR PLATE FAILED RESULTING IN LARGE OIL LEAK AND ENGINE FIRE.  UPON REMOVAL, GASKET APPEAR	ED TO HAVE UNUSUALLY SOFT CONSISTENCY AND EXTENDED BEYOND NORMAL DIMENSIONS.  REPLACED WITH NEW.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000112800067	20001128	00067	SO  	2000	11	28	20000803SH013    	1	20000717	G	3222	6773500V	TRUNNION        			PIPER 	PA28  	PA28R180    	7102809	SO  										LH WEB AREA	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	3293R					28R31264				DURING ANNUAL INSPECTION, FOUND LEFT MAIN GEAR TRUNNION, P/N 67735-00V, CRACKED THROUGH WEB AREA AND INTO CASTING APPROX	 .75 INCH.  PIPER SL 616 ALLOWS FOR THE EXISTING .191 INCH HOLE TO BE ENLARGED TO .500 INCH IN DIAMETER TO REMOVE CRACKE	D AREA, BUT THIS CRACK HAD ALREADY EXTENDED TOO FAR UP INTO THE CASTING.  REPLACED WITH A SERVICEABLE, NEW STYLE TRUNNIO	N WHICH INCORPORATES A MUCH THICKER WEB.  AIRCRAFT TT:  3,352 HOURS.  (X)			1	L	7	1 	3O			 	2A13    					 
2000112800068	20001128	00068	SW  	2000	11	28	20000803SH014    	1	20000719	G	7120	6200421	BRACKET         			GULSTM	690TP 	690A        	0141722	SW  										LEFT ENGINE	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690DB	8440 				11226				AFT ENGINE MOUNT SUPPORT BRACKET TO LEFT ENGINE CRACKED AT INBOARD WEB.  (X)						1	H	7	2 	3T			 	2A4     					 
2001020600078	20010206	00078	SW  	2001	2	6	20000804SH001    	1	20000517	G	6710	2060103605	PITCH LINK      			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	732H					51607				PC LINK FOUND CRACKED AT LOWER END (CRACK - .250 INCH LONG).  FOUND ON DAILY INSPECTION.  AIRCRAFT TT, 5,271:10 HOURS.  	POSSIBLE CAUSE UNKNOWN, PREVIOUS PROBLEMS WITH PART ARE ON RECORD AT BHT.   (X)					1	G	7	1 	3U			 	H2SW    					 
2001020600001	20010206	00001	WP  	2001	2	6	20000804SH003    	1	20000804	G	2450		TAB             			ROBSIN	R22   	R22ALPHA    	7640104	WP  										CAP	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	22HF	300  				0386				FOUND SEVERAL CAPS WITH BROKEN AND BENT LOCKING TABS.  ALSO, CORRODED/STUCK SPRUNG IN CAP - EITHER WILL CAUSE DISRUPTION	 OF POWER TO CLUTCH MOTOR PREVENTING PROPER ACTUATOR FUNCTION WHICH COULD CAUSE  PILOT TO MAKE PRECAUTIONARY LANDING.  S	UBMITTER RECOMMENDED MAKING THE CAPS OF A MORE DURABLE MATERIAL.  (X)				1	G	7	1 	3O			 	H10WE   					 
2001020100033	20010201	00033	NE  	2001	2	1	20000804SH004    	2	20000724	G	7314	02527730007	PUMP            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2 ENGINE	BROKEN          	A			HEAA	A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	11	214KA	1570 				30827	CPPS60002			NR 2 ENGINE SHUT DOWN IN-FLIGHT.  PILOT MADE NORMAL LANDING.  INVESTIGATED PROBLEM.  PULL FUEL PUMP OFF.  FOUND INTERNAL	 SPLINES OF PUMP GROUND OFF.  SPLINES MISSING DUE TO ABNORMAL WEAR ON SPLINES.  INSTALLED NEW PUMP.  GROUND RAN ENGINE. 	 ENGINE FUNCTIONED PROPERLY.  (X)				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001020600002	20010206	00002	SW  	2001	2	6	20000804SH005    	1	20000711	G	6710	251401501299	BEARING         	GLOBE       		BELL  	206   	206B        	1181511	SW  										ENGINE BAY	BINDING         	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2193X					3506				LINEAR ACTUATAORS, PN 206-062-721-001 AND 721-109 FAILED PREMATURELY DUE TO OVERSTAKING OF BEARING ROD END P/N 251401501	299 CAUSING BEARING TO BE TIGHT AND BINDING WHERE ADJUSTMENTS ARE MADE.  ACTUATOR MOTOR IS NOT STRONG ENOUGH TO OVERCOME	 BEARING STIFFNESS.  SUBMITTER SUGGESTED USING BRG WITH LESS BREAK FREE FORCE,THAT IS NOT STAKED SO TIGHT TO ALL FREE MO	VEMENT OF BRG AND LINEAR ACTUATOR.			1	G	7	1 	3U			 	H2SW    					 
2001020600003	20010206	00003	SW  	2001	2	6	20000804SH006    	1	20000711	G	6710	251401501299	BEARING         	GLOBE       		BELL  	206   	206L1       	1182107	SW  										ENGINE BAY	BINDING         	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2150M					45703				LINEAR ACTUATORS, P/N 206-062-721-001, AND 721-109, FAILED PREMATURELY DUE TO OVERSTAKING OF BEARING ROD END P/N 2514015	01299 CAUSING BEARING TO BE TIGHT AND BINDING WHERE ADJUSTMENTS ARE MADE.  ACTUATOR MOTOR IS NOT STRONG ENOUGH TO OVERCO	ME BEARING STIFFNESS.  SUBMITTER SUGGESTED USING BRG WITH LESS BREAK FREE FORCE THAT IS NOT STAKED SO TIGHT TO ALLOW FRE	E MOVEMENT OF BRG AND LINEAR ACTUATORS.  (X)			1	G	7	1 	3U			 	H2SW    					 
2001020600004	20010206	00004	SW  	2001	2	6	20000804SH007    	1	20000726	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407JR					53245				TAIL ROTOR HANGER BEARINGS,  P/N 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING 	INSPECTIONS.  THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTA	TING IMPELLER (FAN).  SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RET	AIN GREASE IN BEARING.  (X)			1	G	7	1 	3U			O	H2SW    					 
2001020600005	20010206	00005	SW  	2001	2	6	20000804SH008    	1	20000726	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AK					53269				TAIL ROTOR HANGER BEARINGS, PN 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING IN	SPECTIONS.  THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTATI	NG IMPELLER (FAN).  SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RETAI	N GREASE IN BEARING.  (X)			1	G	7	1 	3U			O	H2SW    					 
2001020600008	20010206	00008	SW  	2001	2	6	20000804SH009    	1	20000726	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PR					53232				TAIL ROTOR HANGER BEARINGS, P/N 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING I	NSPECTIONS.  THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTAT	ING IMPELLER (FAN).  SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RETA	IN GREASE IN BEARING.  (X)			1	G	7	1 	3U			O	H2SW    					 
2001020600009	20010206	00009	SW  	2001	2	6	20000804SH010    	1	20000726	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	517R					53231				TAIL ROTOR HANGER BEARINGS, PN 407-340-339-103, HAVE BEEN FOUND ROUGH AND FAILED PREMATURELY ON MANY OCCASIONS DURING IN	SPECTIONS.  THE GREASE USED TO LUBRICATE THESE BEARINGS IS BEING FORCED OUT BY SUCTION CREATED BY THE OIL COOLERS ROTATI	NG IMPELLER (FAN).  SUBMITTER SUGGESTED THE MFG OF THESE BEARINGS DEVELOP A HIGHER QUALITY OF SEAL MORE DURABLE TO RETAI	N GREASE IN BEARING.  (X)			1	G	7	1 	3U			O	H2SW    					 
2001020600010	20010206	00010	SW  	2001	2	6	20000804SH011    	1	20000804	G	5210	2060315723S	HINGE           			BELL  	206   	206B        	1181511	SW  										CREW DOOR	WRONG PART      	B			UK7R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	26EA					2175				HINGES REMOVED BECAUSE OF POOR DOOR FIT.  FURTHER INSPECTION AND INVESTIGATION REVEALED NON-COMPLIANCE WITH IPB.  PART N	UMBER NOT APPLICABLE TO 206B SERIES, POSSIBLY OH58 SERIES.  REMOVED FROM SERVICE.					1	G	7	1 	3U			 	H2SW    					 
2001020600011	20010206	00011	NE  	2001	2	6	20000804SH012    	1	20000629	G	2422	SPC75B	INVERTER        			SKRSKY	S76   	S76A        	8143006	NE  										E/E BAY	INOPERATIVE     	B			ALGR	O				OTHER                   				J	B		WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			SW	03	164AG					760290				AFTER TAKEOFF, NR 1 INVERTER LIGHT ILLUMINATED.  NR 1 INVERTER WAS INOPERATIVE, AND CREW AND PASSENGERS SMELLED SMOKE.  	(X)					1	G	7	2 	3U			 	H1NE    					 
2001020100034	20010201	00034	SW  	2001	2	1	20000804SH014    	1	20000630	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL				A244	53107				DURING 25-HOUR AD INSPECTION, FOUND DISC PACK CRACKED IN 3 PLACES FACING AFT AND 1 CRACK FORWARD.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600013	20010206	00013	SW  	2001	2	6	20000804SH015    	1	20000703	G	6510		FRAME           			BELL  	407   	407         	       	SW  										TRANSMISSION	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL				KC312	53107				DURING DAILY SERVICE CHECK, FOUND TRANSMISSION SIDE OF MDS, FORWARD FLEX FRAME CRACKED FROM ATTACHMENT BOLT TO OUTER EDG	E OF FLEX FRAME.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600014	20010206	00014	SW  	2001	2	6	20000804SH016    	1	20000614	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467AL					53190				UPON DAILY INSPECTION, FOUND CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600015	20010206	00015	SW  	2001	2	6	20000804SH017    	1	20000716	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467AL	132  				53190				UPON DAILY INSPECTION, CRACKED IN CORNERS CAUSED BY INHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020100035	20010201	00035	SW  	2001	2	1	20000804SH018    	1	20000715	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL				A823	53054				DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS THE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600017	20010206	00017	SW  	2001	2	6	20000804SH019    	1	20000531	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL					53054				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY IHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600018	20010206	00018	SW  	2001	2	6	20000804SH020    	1	20000708	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	487AL	1666 				53204				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600019	20010206	00019	SW  	2001	2	6	20000804SH021    	1	20000713	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	1244 				53203				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600056	20010206	00056	GL  	2001	2	6	20000804SH022    	2	20000218	G	7210	6893672	PINION GEAR     		CAG47276    	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	1985 			CAG47276	53203	CAE847125			PINION GEAR HAS EXCESSIVE GALLING ON GEAR TEETH, POSSIBLY DUE TO EXCESSIVE TORQUE ON ENGINE, GEAR CANNOT SUSTAIN LOAD.  	(X)					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001020600057	20010206	00057	SW  	2001	2	6	20000804SH023    	1	20000710	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										NR 6	CRACKED         	B			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	00	437AL				A932	53141				DURING PHASE INSPECTION, VISUAL INSPECTION OF TAILROTOR DRIVESHAFT FOUND ONE SEGMENT OF DISC PACK OF NR 6 DRIVESHAFT CRA	CKED.  FORWARD SEGMENT CRACKED ACROSS THE SPAN.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600058	20010206	00058	SW  	2001	2	6	20000804SH024    	1	20000712	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										NR 3	CRACKED         	B			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL				AFS932	53247				DURING 25-HOUR AD INSPECTION, FORWARD SEGMENT CRACKED ACROSS TWO SPANS.  180 DEGREES OPPOSITE EACH OTHER.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600072	20010206	00072	SW  	2001	2	6	20000804SH025    	1	20000717	G	6322	406040320101	SHAFT           			BELL  	407   	407         	       	SW  										OIL COOLER	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL	550  			AFS932	53247				ON FINAL APPROACH, PILOT FELT A GRINDING IN THE FLIGHT CONTROLS.  POST-FLIGHT INSPECTION REVEALED FORWARD OIL COOLER BLO	WER BEARING FAILURE.  FORWARD BEARING DISINTEGRATED (FAILED) AND DAMAGED SHAFT.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600073	20010206	00073	SW  	2001	2	6	20000807SH001    	1	20000717	G	6322	406040322101	HANGER ASSY     			BELL  	407   	407         	       	SW  										OIL COOLER	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL		550  		AFS932	53247				ON FINAL APPROACH, PILOT FELT A GRINDING IN THE FLIGHT CONTROLS.  POST-FLIGHT INSPECTION REVEALED FORWARD OIL COOLER BLO	WER BEARING FAILURE.  FORWARD BEARING DISINTEGRATED (FAILED) IN THE HANGER AND THE HANGER WAS DAMAGED.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600074	20010206	00074	SW  	2001	2	6	20000807SH002    	1	20000717	G	6322	407340339103	BEARING         			BELL  	407   	407         	       	SW  										COOLER BLOWER	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL	550  			AFS932	53247				ON FINAL APPROACH,  PILOT FELT A GRINDING IN THE FLIGHT CONTROLS.  POST-FLIGHT INSPECTION REVEALED FORWARD OIL COOLER BL	OWER BEARING FAILURE.  BEARING DISINTEGRATED (FAILED).  (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600080	20010206	00080	SW  	2001	2	6	20000807SH003    	1	20000522	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	587AL	2536 				53248				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600082	20010206	00082	SW  	2001	2	6	20000807SH005    	1	20000707	G	6310	406340102101	SEAL            			BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	LEAKING         	A			ALGA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	627AL	621  			A4199	53284				DURING DAILY INSPECTION, FORWARD SEAL LEAKING, CARBON PORTION PITTED.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600083	20010206	00083	SW  	2001	2	6	20000807SH006    	1	20000520	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	2274 				53284				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATION.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600084	20010206	00084	SW  	2001	2	6	20000807SH007    	1	20000712	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL				A1199	53284				DURING 25 HOUR AD INSPECTION, FORWARD SEGMENT CRACKED ACROSS THE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600085	20010206	00085	SW  	2001	2	6	20000807SH008    	1	20000712	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	184  			A1173	53284				DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS THE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600086	20010206	00086	SW  	2001	2	6	20000807SH009    	1	20000713	G	6710		BUSHING         			BELL  	407   	407         	       	SW  										SWASHPLATE LINK	WORN            	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL				AFS1179	53284				DURING REPAIR FOR WORN BUSHINGS AND SPACERS, EXCESSIVE CORROSION AROUND AND UNDER BUSHINGS, P/N 206-010-338-3.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600105	20010206	00105	SW  	2001	2	6	20000807SH010    	1	20000707	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	153  			AFS1027	53284				AFT COUPLING OF NR 2 TAILROTOR DRIVESHAFT HAS A CRACK ACROSS THE SPAN ON THE FORWARD AND AFT SEGMENTS OF THE DISC PACK. 	   (X)					1	G	7	1 	3U			O	H2SW    					 
2001020600088	20010206	00088	SW  	2001	2	6	20000807SH011    	1	20000623	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	87   			A1199	53284				DURING 25-HOUR AD INSPECTION, DSIC PACK CRACKED IN TWO PLACES ACROSS THE SPAN OF THE FORWARD SEGMENT.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600089	20010206	00089	SW  	2001	2	6	20000807SH012    	1	20000606	G	6510	407340340101	DISC PACK       		NR5         	BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL				A1178	53284				DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS THE SPAN. (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600090	20010206	00090	SW  	2001	2	6	20000807SH013    	1	20000608	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL				A765	53284				DURING 25-HOUR AD INSPECTION, AFT SEGMENT CRACKED ACROSS SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600091	20010206	00091	SW  	2001	2	6	20000807SH014    	1	20000628	G	6220	407010103101	PITCH HORN      			BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	2486 			A305	53284				AT FIRST OVERHAUL OF MAIN ROTOR HUB ASSEMBLY, CORROSION PITTING UNDER BUMPER PLATES.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600092	20010206	00092	SW  	2001	2	6	20000807SH015    	1	20000628	G	6220	407010103101	PITCH HORN      			BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	2486 			A305	53284				AT FIRST OVERHAUL OF MAIN ROTOR HUB ASSEMBLY, CORROSION PITTING UNDER BUMPER PLATES.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600093	20010206	00093	SW  	2001	2	6	20000807SH016    	1	20000713	G	6710		BUSHING         			BELL  	407   	407         	       	SW  										SWASHPLATE	CORRODED        	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL				AFS1788	53284				DURING REPAIR FOR WORN BUSHINGS AND SPACERS, EXCESSIVE CORROSION AROUND AND UNDER BUSHINGS, PN 206-010-338-3.						1	G	7	1 	3U			O	H2SW    					 
2001020600094	20010206	00094	SW  	2001	2	6	20000807SH017    	1	20000404	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	770  			A1199	53284				DURING 25-HOUR AD INSPECTION, ONE LAMINATE IS CRACKED (AFT LAMINATE).  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600095	20010206	00095	SW  	2001	2	6	20000807SH018    	1	20000628	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL	388  			A469	53366				DURING REPAIR/REPLACEMENT OF CRACKED HOUSING, BEARINGS ROUGH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600096	20010206	00096	SW  	2001	2	6	20000807SH019    	1	20000628	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL	388  			A469	53366				DURING REPAIR/REPLACEMENT OF CRACKED HOUSING, BEARINGS ROUGH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600097	20010206	00097	SW  	2001	2	6	20000807SH020    	1	20000619	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	607AL					53264				DURING 50-HOUR VISUAL INSPECTION, NR 3 TAILROTOR DRIVESHAFT DISC PACK IS CRACKED ON AFT SIDE. (X)						1	G	7	1 	3U			O	H2SW    					 
2000091400113	20000914	00113	CE  	2000	9	14	20000808SH001    	1	20000801	G	3260	V31	SWITCH          			CESSNA	401   	401         	207590C	CE  										NOSE GEAR	FAILED          	E			MHJA	O				OTHER                   				J	L	N	WARNING INDICATION        	NO TEST                   	FALSE WARNING             	LD	LANDING        	1			SW	05	401PW					5010269				THE PILOT REPORTED HE DID NOT HAVE A NOSE GEAR DOWNLOCK INDICATION.  THE PILOT DECLARED AN EMERGENCY, AND LANDED WITHOUT	 INCIDENT.  THE CAUSE OF THE PROBLEM WAS A DOWNLOCK MICROSWITCH ON THE NOSE GEAR THAT FAILED AND A BROKEN WIRE ON THE DO	WNLOCK GEAR INDICATOR.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000091400115	20000914	00115	CE  	2000	9	14	20000808SH002    	1	20000726	G	2434	9522R	ALTERNATOR      			CESSNA	401   	401         	207590C	CE  										RT ENGINE	FAILED          	E			MHJA	O				OTHER                   				J	S	O	WARNING INDICATION        	AFFECT SYSTEMS            	OTHER                     	TX	TAXI/GRND HDL  	1			SW	05	3208Q					4010008				RIGHT ALTERNATOR WAS INOPERTIVE ON RUN-UP BEFORE DEPARTURE.  CAUSE OF PROBLEM WAS A DEFECTIVE ALTERNATOR.  REPLACED THE 	ALTERNATOR AND CHECKED THE CHARGING SYSTEM, OK.					1	L	7	2 	3O			 	A7CE    					 
2001020600098	20010206	00098	SW  	2001	2	6	20000808SH003    	1	20000522	G	6730	41002979103	SLEEVE          	TEXTRON     		BELL  	407   	407         	       	SW  										BYPASS SPOOL	CONTAMINATED    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	617AL	1331 			HR811	53265				ATTEMPTED TAKEOFF, COLLECTIVE LEVER MOVEMENT WAS RESTRICTED.  TAKEOFF ABORTED, COLLECTIVE SERVO REPLACED.  SHOP INSPECTI	ON REVEALED SERVO BYPASS SPOOL WAS BINDING IN BYPASS SPOOL SLEEVE.  THIS CAUSED PRIMARY CONTROL SPOOL HYDRAULIC NULL TO 	SHIFT LIMITING SERVO ACTUATOR MOVEMENT.  SPOOLS AND SLEEVE CONTAMINATED WITH SOME TYPE OF COATING.  THIS COATING COULD N	OT BE SEEN, BUT WAS WASHED OFF.  NORMAL SPOOLS AND SLEEVE OPERATION RESTORED.  CAUSE UNKNOWN.  (X)			1	G	7	1 	3U			O	H2SW    					 
2001020600099	20010206	00099	SW  	2001	2	6	20000808SH004    	1	20000608	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	787  				53381				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS. (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600100	20010206	00100	SW  	2001	2	6	20000808SH005    	1	20000703	G	6310	406340102101	SEAL            			BELL  	407   	407         	       	SW  										CAP ASSY	LEAKING         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	907  			A4747	53381				DURING DAILY INSPECTION, FOUND LEAKING, NO OBVIOUS DEFECTS. (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600101	20010206	00101	SW  	2001	2	6	20000808SH006    	1	20000705	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	130  			A318	53381				DURING DAILY INSPECTION, HOUSING IS CRACKED AND BEARINGS ARE ROUGH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600102	20010206	00102	SW  	2001	2	6	20000808SH007    	1	20000705	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	130  			A318	53381				DURING DAILY INSPECTION, HOUSING IS CRACKED AND BEARINGS ARE ROUGH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600103	20010206	00103	SW  	2001	2	6	20000808SH008    	1	20000703	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917AL	120  				53381				UPON DAILY INSPECTION, CRACKS IN CORNERS CAUSED BY INHERENT VIBRATIONS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000091400125	20000914	00125	CE  	2000	9	14	20000808SH010    	1	20000611	G	3233	508202085	NUT             			BEECH 	100   	100BEECH    	1152916	CE  										NOSE GEAR	STRIPPED        	I			VNWA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	11JJ		1918 			B2				THE NET ASSEMBLY, P/N 90-820015-1, INSTALLED IN NOSE LANDING GEAR ACTUATOR, P/N 50-820208-5, WAS FOUND VOID OF THREADS C	AUSING THE NOSE GEAR TO FAIL TO EXTEND.  REQUIRED OVERHAUL IS 8,000 CYCLES, PART HAD 2,516 CYCLES SINCE OVERHAUL.  (X)					1	L	7	2 	3T			 	A14CE   					 
2000091400126	20000914	00126		2000	9	14	20000808SH011    	4	20000725	G	2300	CM358950	SWITCH          	AMF         		CESSNA	441   	441         	2076020	CE  										AVIONICS	BURNED          	A			VE7A	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	07	988AE					441075				SWITCH FAILED INTERNALLY CAUSING SMOKE IN THE COCKPIT.  DUE TO THE FACT THE SWITCH WAS AT FAULT, IT DID NOT TRIP AND CON	TINUED TO SMOKE UNTIL SHUT OFF BY THE PILOT.  (X)					1	L	7	2 	3T			RT	A28CE   					 
2000091400128	20000914	00128	CE  	2000	9	14	20000808SH014    	1	20000712	G	3242	06900400	PIN             	PARKERHANFIN		CESSNA	402   	402C        	207590R	CE  										BRAKE SYSTEM	DESTROYED       	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	01	771EA					402C0046				ON LANDING, AFT BRAKE LOCKED UP, AND MAIN WHEEL SEIZED.  MAINTENANCE FOUND ONE CALIPER ANCHOR PIN SHEARED.  REMOVED AND 	REPLACED MAIN WHEEL ASSY, BRAKE CALIPER, AND BRAKE BACKPLATE ASSY, THEN RETURNED AIRCRAFT TO SERVICE.  AT THIS TIME, ALL	 ANCHOR PINS ARE BEING CHANGED IN THE OPERATOR''S FLEET.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000091400129	20000914	00129	CE  	2000	9	14	20000808SH015    	1	20000727	G	7120	J124532	MOUNT           			CESSNA	210   	210M        	2073450	CE  										LT FORWARD	MISSING         	A			FPIA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	7660E					21062692				PART MANUFACTURED DEFECT.  MISSING REINFORCEMENT WASHER ON UPPER HALF.  (X)						1	H	7	1 	3O			 	3A21    					 
2000092100019	20000921	00019	CE  	2000	9	21	20000808SH016    	1	20000327	G	2497		WIRE            			CESSNA	182   	182Q        	2072732	CE  										ALT BREAKER	SHORTED         	H				A				UNSCHED LANDING         				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			WP	05	735MS	1917 				18265536				PILOT WAS FORCED TO LAND DUE TO SMOKE IN COCKPIT.  INSP REVEALED ALTERNATOR POWER WIRE (WIRE NR PB-10) FROM ALT TO THE A	LT OUTPUT CIRCUIT BREAKER TO BE HEAT DAMAGED.  WIRE IS AN EIGHT-GAUGE SHIELDED WIRE WITH ALTERNATOR OUTPUT POWER IN THE 	CENTER CONDUCTOR AND THE SHIELDING GROUNDED TO AIRFRAME GROUND.  FOR AN UNKNOWN REASON, SHIELDING CHAFED THROUGH TO POWE	R CONDUCTOR AND CAUSED A DIRECT SHORT TO GROUND.  APPROX 6 INCHES OF THE WIRE SHOWED DAMAGE, INSULATION MELTED OFF BETWE	EN POWER CONDUCTOR AND SHIELDING AND MUCH OF THE SHIELDING MISSING DUE TO ARCING.  DAMAGED SECTION OF WIRE REPLACED WITH	 MIL-W-22759/16-8, AND SHIELDING INSPECTED ADJACENT TO DAMAGED AREA.  NO OTHER CHAFING OR DEFECTS NOTED.  (X)	1	H	7	1 	3O			NT	3A13    					 
2000091400135	20000914	00135	CE  	2000	9	14	20000808SH017    	1	20000724	G	7120	505401033	RIVET           			CESSNA	421   	421C        	2076016	CE  										OUTBOARD	FRETTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	942SW	4609 				421C1025				DURING ROUTINE INSPECTION, LOOSE RIVETS WERE FOUND IN THE TOP PLATE CURBED AREA AFT OF THE ENGINE IN BOTH MOUNT BEAMS OF	 LEFT ENGINE.  SOME RIVET HEADS HAD FRETTED INTO THE SURFACE OF THE PLATE.  THE SUSPECTED CAUSE WOULD BE A VIBRATION IN 	THIS AREA.  AN ENGINEERING APPROVED REPAIR WAS MADE AND AIRCRAFT RETURNED TO SERVICE.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000091400136	20000914	00136	CE  	2000	9	14	20000808SH018    	1	20000724	G	7160	515402031	RIVET           			CESSNA	421   	421C        	2076016	CE  										INBOARD	FRETTED         	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	942SW	4609 				421C1025				DURING ROUTINE INSPECTION, LOOSE RIVETS WERE FOUND IN THE TOP PLATE CURBED AREA AFT OF THE ENGINE IN BOTH MOUNT BEAMS OF	 LEFT ENGINE.  SOME RIVET HEADS HAD FRETTED INTO THE SURFACE OF THE PLATE.  THE SUSPECTED CAUSE WOULD BE A VIBRATION IN 	THIS AREA.  AN ENGINEERING APPROVED REPAIR WAS MADE AND AIRCRAFT RETURNED TO SERVICE.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000092100020	20000921	00020	CE  	2000	9	21	20000808SH019    	1	20000131	G	3010	1H374	CHECK VALVE     			CESSNA	310   	310R        	2074245	CE  										ENGINE COMPART	FAILED          	B			DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90FC	705  				310R1838				DURING ROUTINE MAINTENANCE, DISCOVERED 2 UNSERVICEABLE CHECK VALVES, PN''S 1H37-4, FOR THE PNEUMATIC DEICE SYSTEM.  BOTH	 VALVES HAVE 21 MONTHS AND 705.1 HOURS SINCE NEW.  THESE VALVES CALL FOR YEARLY INSPECTIONS STARTING AT 5 YEARS FROM NEW	 THOUGH 10 YEARS REPLACEMENT.  THE MANUFACTURER HAS BEEN NOTIFIED AND ONE VALVE HAS BEEN SENT FOR THEIR EVALUATION.  (X)				1	L	7	2 	3O			 	3A10    					 
2001020600104	20010206	00104	SW  	2001	2	6	20000808SH020    	1	20000718	G	6310	406340102101	SEAL            			BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	LEAKING         	B			EH1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	175P	106  			A4504	53316				REPLACED ORIGINAL SEAL AT 383.1 HOURS SINCE NEW.  REPLACED SECOND SEAL AFTER 106.1 HOURS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020600108	20010206	00108	EU  	2001	2	6	20000808SH022    	1	20000721	G	3340	G62504	MOTOR           			SNIAS 	350   	AS350B3     	8680954	EU  										SEARCH LIGHT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52281	15   				3249				SEARCH LIGHT UNIT INOPERATIVE.  FAILED TO EXTEND.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020600109	20010206	00109	NM  	2001	2	6	20000808SH023    	1	20000519	G	6230	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	746  				90000012				MAIN ROTOR BEARING ASSY DEBONDING.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001020700207	20010207	00207	NM  	2001	2	7	20000808SH024    	1	20000519	G	6230	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	752  				90000012				MAIN ROTOR CENTER BEARING ASSEMBLY DEBONDING.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001020700190	20010207	00190	NM  	2001	2	7	20000808SH025    	1	20000628	G	6230	900C2010183107	LINK            			DOUG  	MD900 	MD900       	3027375	NM  										DRIVE SCISSORS	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	283  				90000012				HINGE AND SHIMS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001020700208	20010207	00208	EU  	2001	2	7	20000808SH026    	1	20000623	G	2450	430121402	HARNESS         			BOLKMS	117   	BK117A4     	5626017	EU  										ELECTRICAL SYS	SHORTED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	118LF	512  				7137				CABLE, ELECTRICAL, AFT HAD INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000091400141	20000914	00141	CE  	2000	9	14	20000808SH028    	1	20000720	G	7820	14550171	BRACE           			CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  					LOWER TUBE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	793DS	4294 				33701376	60466R			DURING INSPECTION, P/N 1455017-1 AND P/N 1455017-2 BRACE ASSYS WERE FOUND CHAFING ON THE PN 629671A2 OIL SUMP.  THE P/N 	1555001-1 MUFFLER CAN MOVE FWD AND AFT DUE TO ENG VIBRATION AS THERE ARE NO DOWL PINS IN P/N 1555001-1 CLAMPS TO MAINTAI	N POSITION OF MUFFLER.  SUBMITTER RECOMMENDED UPGRADING MUFFLER SYS TO DUAL MUFFLERS LIKE FRONT ENGINE INSTALL OF THIS A	CFT, OR AT LEAST THE INSTALL OF DOWL IN P/N 1555002-1 CLAMPS.  THIS IS THE THIRD OCCURRANCE ON THE ACFT IN THE LAST 5 YE	ARS.  (X)		1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2000091400142	20000914	00142	CE  	2000	9	14	20000808SH029    	1	20000720	G	7820	14550172	BRACE           			CESSNA	337   	337E        	2075721	CE  	CONT  	O360  	IO360C      	17025	SO  					LOWER TUBE	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	793DS	4294 				33701376	60466R			DURING INSPECTION, P/N 1455017-1 AND P/N 1455017-2 BRACE ASSYS WERE FOUND CHAFING ON THE PN 629671A2 OIL SUMP.  THE P/N 	1555001-1 MUFFLER CAN MOVE FWD AND AFT DUE TO ENG VIBRATION AS THERE ARE NO DOWL PINS IN P/N 1555001-1 CLAMPS TO MAINTAI	N POSITION OF MUFFLER.  SUBMITTER RECOMMENDED UPGRADING MUFFLER SYS TO DUAL MUFFLERS LIKE FRONT ENGINE INSTALL OF THIS A	CFT, OR AT LEAST THE INSTALL OF DOWL IN P/N 1555002-1 CLAMPS.  THIS IS THE THIRD OCCURRANCE ON THE ACFT IN THE LAST 5 YE	ARS.  (X)		1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2000091400144	20000914	00144	CE  	2000	9	14	20000808SH030    	1	20000724	G	2460	70H10A	DIODE           			BEECH 	99    	C99         	1154006	CE  										ELECTRICAL BUSS	SHORTED         	A			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	239AL					U239				DIODE 70 H10 A - 4 EACH IN A/C ELEC BUSS SYS.  2 EACH LEFT, 2 EACH RIGHT WHICH CONTROL ANNUNCIATOR PANEL AND SOME ENGINE	S PLUS LANDING GEAR.  FOUND 2 EACH DIODES SHORTED OUT ON RIGHT SIDE, NO SHORTS FOUND IN ELECTRICAL SYSTEM.  (X)					1	L	7	2 	3T			 	A14CE   					 
2000101000354	20001010	00354	CE  	2000	10	10	20000808SH031    	1	20000707	G	3220	358250545	ARM             			BEECH 	99    	99          	1154002	CE  										BELOW COCKPIT	LOOSE           	A			TIMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	24BH	25936				U67				NOSE STEERING REPORTED LOOSE AND INSPECTION REVEALED NOSE STEERING TORQUE ARM HOLE TO ACTUATOR ELONGATED.  REPLACED NOSE	 STEERING TORQUE ARM WITH SERVICEABLE ARM.  THE ELONGATION COULD HAVE BEEN PREVENTED WITH THE ADDITION OF SHIMS BETWEEN 	THE CLEVIS ARM AND THE ROD END OF THE ACTUATING ROD.  (X)				1	L	7	2 	3T			 	A14CE   					 
2000101000355	20001010	00355	CE  	2000	10	10	20000808SH032    	1	20000707	G	3220	5052432519	ARM             			BEECH 	99    	99          	1154002	CE  										PILOTS RIGHT	WORN            	A			TIMA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	24BH	25936				U67				NOSE STEERING WAS REPORTED TO BE LOOSE.  INSPECTION REVEALED RUDDER PEDAL ARM PIVOT HOLES ELONGATED.  REPLACED RUDDER AR	M ASSY WITH NEW COMPONENT AND NEW HARDWARE AS NECESSARY.  LACK OF LUBRICATION IN THIS AREA POSSIBLY ACCELERATED THE WEAR	 OF THE PIVOT HOLES.  THE BE99 MM DOES NOT SPECIFICALLY REFERENCE THIS PARTICULAR AREA FOR LUBRICATION.  (CHAP 12).  MAI	NT DEPT HAS BEEN USING EITHER LPS 2 OR 3.  (X)			1	L	7	2 	3T			 	A14CE   					 
2000101000356	20001010	00356	SW  	2000	10	10	20000809SH001    	1	20000725	G	3230	560028951	BRACKET         			MOONEY	M20   	M20J        	5870219	SW  											CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	4182H	2458 				240656				DURING ANNUAL INSPECTION, THE LEFT RETRACT (LANDING GEAR) SPRING BRACKET WAS FOUND CRACKED AT THE SPRING ATTACH HOLE.  B	RACKET WAS REPLACED.  (X)					1	L	7	1 	3O			 	2A3     					 
2000101000357	20001010	00357	NE  	2000	10	10	20000809SH002    	2	20000713	G	8520	10992	ROD             			AIRTRC	AT400 	AT401       	0390204	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					MASTER ROD	FRACTURED       	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	21	4508Y		447  			4010751	ZP102256			DURING AGRICULTURAL SPRAYING OPERATION, NR 7 ROD ASSY FAILED FORCING AIRCRAFT TO EMERGENCY LANDING AND SUBSEQUENT SUBSTA	NTIAL AIRCRAFT DAMAGE.  REF:  ACCIDENT REPORT NR LAX00LA271.  (X)					1	L	7	1 	3R	3	R	 	A17SW   	5E2				 
2000101000358	20001010	00358	SO  	2000	10	10	20000809SH003    	1	20000714	G	2810	462056	FUEL CAP        			PIPER 	PA28  	PA28181     	7102807	SO  										GASKET	TORN            	B			FQAS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	910PA	28   				2843300				THESE GASKETS APPEAR NOT TO BE COMPATIBLE WITH 100LL FUEL.  ALSO COMPOSITION IS WEAK MATERIAL.  SOFT AND BREAKS EASY.  S	UBMITTER STATED OTHERS ON FLEET HAVE SAME PROBLEM.  (X)					1	L	7	1 	3O			 	2A13    					 
2000101000359	20001010	00359	SO  	2000	10	10	20000809SH004    	2	20000801	G	7414	6324	MAGNETO         			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360E    	17025	SO  					LEFT	FAILED          	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	07	4128M	645  				3449068	321449			TEST RUN SHOWED MAGNETO TO BE DEAD.  REMOVED AND DISASSEMBLED MAGNETO.  FOUND WIPER TAB FOR DISTRIBUTOR GEAR TO BE SHEAR	ED OFF OF GEAR.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000101000360	20001010	00360	SO  	2000	10	10	20000809SH005    	1	20000709	G	2810	462056	GASKET          			PIPER 	PA28  	PA28181     	7102807	SO  										LT GAS CAP	TORN            	C			FQAS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	917PA	20   				2843306				GASKET TEARS AFTER A SHORT USAGE.  TIME, APPROXIMATELY 2 WEEKS USAGE.  (X)						1	L	7	1 	3O			 	2A13    					 
2000101000361	20001010	00361	SO  	2000	10	10	20000809SH006    	1	20000713	G	2810	462056	FUEL CAP        			PIPER 	PA28  	PA28181     	7102807	SO  										GASKET	SWOLLEN         	C			FQAS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PA	21   				2843277				THESE GASKETS APPEAR NOT TO BE COMPATIBLE WITH 100LL FUEL.  THE MATERIAL USED CONTINUED TO SWELL AND RIP AFTER ONLY A SH	ORT PERIOD OF TIME.   (X)					1	L	7	1 	3O			 	2A13    					 
2000101000362	20001010	00362	GL  	2000	10	10	20000809SH007    	1	20000605	G	2900	6658531	LINE            			NAMER 	T6    	SNJ5        	6400418	GL  										RT L/G WELL	FRACTURED       	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	23	62724					43724				ALUMINUM LINE FRACTURED (SPLIT) APPROXIMATELY .50 INCH IN LENGTH LONGITUDINALLY NEXT TO UNION.  CAUSE UNKNOWN.  (X)						1	L	7	1 	3R			 	A2575   					 
2000111500001	20001115	00001	SO  	2000	11	15	20000809SH008    	1	20000711	G	2810	462056	GASKET          			PIPER 	PA28  	PA28181     	7102807	SO  										RT FUEL CAP	TORN            	C			FQAS	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	926PA	25   				284389				AFTER SHORT PERIOD OF USE, GASKET HAD DETERIORATED AND TORN.  SUBMITTER STATED HAVING SEEN NUMEROUS CASES OF THIS IN FLE	ET OF ARCHER III''S.  (X)					1	L	7	1 	3O			 	2A13    					 
2000111500002	20001115	00002	SO  	2000	11	15	20000809SH009    	1	20000707	G	2810	462056	GASKET          			PIPER 	PA28  	PA28181     	7102807	SO  										RT FUEL CAP	TORN            	C			FQAS	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	928PA	25   				2843298				AFTER SHORT PERIOD OF USE, GASKET HAD DETERIORATED AND TORN.  SUBMITTER STATED HAVING SEEN NUMEROUS CASES OF THIS IN FLE	ET OF ARCHER III''S.  (X)					1	L	7	1 	3O			 	2A13    					 
2000111500003	20001115	00003	SO  	2000	11	15	20000809SH010    	1	20000610	G	2810	462056	GASKET          			PIPER 	PA44  	PA44180     	7104402	SO  										FUEL CAP	TORN            	C			FQAS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	971PA	11   				4496031				GASKET TEARS AND BREAKS APART AFTER A FEW TIMES OPENING THE GAS CAP.  (X)						1	L	7	2 	3O			 	A19S0   					 
2000111500004	20001115	00004	EA  	2000	11	15	20000809SH011    	2	20000613	G	7323	210624V	GOVERNOR        			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	OVERSPEED	LEAKING         	E			TIMA	O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	99TH	35110				U155				RIGHT ENGINE LEAKING OIL AT FRONT SECTION.  PROBLEM DETERMINED TO BE CRACKED HOUSING ON AUTOFEATHER DUMP SOLENOID.  REPL	ACED ENTIRE OVERSPEED GOVERNOR WITH SERVICEABLE OVERSPEED GOVERNOR.  PART POSSIBLY CRACKED AS A RESULT OF MATING TWO UNE	VEN SURFACES.  (X)				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2000111500005	20001115	00005	SO  	2000	11	15	20000809SH012    	1	20000616	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4122F	2342 				2843118				LEFT AILERON BALANCE CABLE FRAYED LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000111500006	20001115	00006	SO  	2000	11	15	20000809SH013    	1	20000719	G	2740	62701080	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	1165 				3449112				LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED AT FRAME  ASSEMBLY, STA 222.43.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000111500007	20001115	00007	SO  	2000	11	15	20000809SH014    	1	20000713	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4130W	1345 				2843204				RIGHT AILERON BALANCE CABLE FRAYED LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000111500008	20001115	00008	SO  	2000	11	15	20000809SH015    	1	20000710	G	2740	62701080	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	990  				3449128				LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED LOCATED AT STA 222.43.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000111500009	20001115	00009	SO  	2000	11	15	20000809SH016    	1	20000705	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4149Y	1741 				2843128				LEFT AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000111500010	20001115	00010	SO  	2000	11	15	20000809SH017    	1	20000705	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4161Z	2141 				2843129				LEFT AILERON BALANCE CABLE FRAYED. LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000111500011	20001115	00011	SO  	2000	11	15	20000809SH018    	1	20000719	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4163W	1541 				2843127				LEFT AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000111500012	20001115	00012	SO  	2000	11	15	20000809SH019    	1	20000715	G	2740	62701080	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	2193 				3449046				LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED AT FRAME ASSEMBLY, STA 222.43.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000111500013	20001115	00013	SO  	2000	11	15	20000809SH020    	1	20000719	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299B	2141 				2843116				LEFT AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS.    (X)						1	L	7	1 	3O			 	2A13    					 
2000111500014	20001115	00014	SO  	2000	11	15	20000809SH021    	1	20000630	G	2740	62701080	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	1942 				3449043				LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED AT FRAME ASSY, STA 222.43.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000081000141	20000810	00141	SO  	2000	8	10	20000809SH022    	1	20000725	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										UND REAR SEAT	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4132D	1144 				2843234				RIGHT AILERON BALANCE CABLE FRAYED.  LCOATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000081000142	20000810	00142	SO  	2000	8	10	20000809SH023    	1	20000725	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										UND REAR SEAT	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4144P	1943 				2843121				RIGHT AILERON BALANCE CABLE FRAYED.  LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000081000143	20000810	00143	SO  	2000	8	10	20000809SH024    	1	20000724	G	2740	62701080	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										LOWER AFT	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	1640 				3449042				LOWER AFT STABILATOR DOWN CONTROL CABLE FRAYED.  FRAYING OCCURRED AT STA 222.43.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000081000144	20000810	00144	SO  	2000	8	10	20000809SH025    	1	20000724	G	2710	62701126	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										WING ROOT PULLY	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	1041 				3449128				RIGHT AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000111500015	20001115	00015	CE  	2000	11	15	20000809SH026    	1	20000727	G	2842	S33312	TRANSMITTER     			CESSNA	172   	172S        	2072439	CE  										LT FUEL CELL	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	768  				172S8135				LEFT FUEL QTY WENT TO EMPTY, LT LOW FUEL ANNUNCIATOR LIGHT ILLUMINATED IN-FLIGHT. MAINT FOUND THE FUEL QTY TRANSMITTER I	NOP.  WHEN XMITTER REMOVED FROM FUEL CELL, THE FLOAT AND RETAINER WASHER ON OTBD END OF THE FLOAT ARM WERE MISSING.  FUE	L CELL OPENED AND THE FLOAT AND WASHER RETRIEVED.  SUBMITTER STATED FUEL QTY XMITTER MFG INCORRECTLY, WIRE ARM THAT RUNS	 THRU FLOAT WAS NOT CRIMPED ON EITHER SIDE OF THE FLOAT DURING MFG ALLOWING IT TO FALL OFF THE ARM.  FOUND LT AND RT FUE	L QTY XMITTERS INSTALLED BACKWARDS IAW CESSNA C-172R/S PM.  THE S3331-2 TRANSMITTER IS REQUIRED TO BE INSTALLED IN THE R	T FUEL CELL AND THE S3331-1 XMITTER IS REQUIRED TO BE INSTALLED IN THE LT FUEL CELL.  BOTH TRANSMITTERS REPLACED.  (X)	1	H	7	1 	3O			NT	3A12    					 
2000111500016	20001115	00016	CE  	2000	11	15	20000809SH027    	1	20000714	G	2410	31M22045	SUPPORT BRACKET 			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					POWERPLANT	INCORRECT       	H				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05	7254H	498  				20608036	L2688948A			DURING ROUTINE INSPECTION, FOUND THE ALTERNATOR BELT DRIVE SUPPORT MISALIGNED WITH THE ALTERNATOR PULLEY CAUSING THE BEL	T TO SLIP PARTIALLY OFF OF THE ALTERNATOR PULLEY.  FURTHER INVESTIGATION DETERMINED THE INCORRECT STARTER RING GEAR SUPP	ORT, PN 31M22045, WAS INSTALLED WHICH POSITIONED THE BELT SUPPORT FWD OF THE ALTERNATOR DRIVE PULLEY.  SUBMITTER STATED 	THE INCORRECT PART WAS INSTALLED AT THE FACTORY DURING PRODUCTION.  (X)			1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000111500017	20001115	00017	CE  	2000	11	15	20000809SH028    	1	20000714	G	2914	9148D27	PUMP            			CESSNA	208   	208         	2073702	CE  										EMERGENCY SYS	LEAKING         	H				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	05	1273E	87   				20800319				EMERGENCY GEAR HAND PUMP SEEPING HYDRAULIC FLUID.  DETERMINED METAL SHAVINGS PRODUCED DURING ACTUATOR PRODUCTION HAD LOD	GED UNDER AN O-RING.  NO GALLING OR DAMAGE WAS FOUND INSIDE THE ACTUATOR.  DEBRIS REMOVED AND NEW SEALS INSTALLED.  (X)					1	H	7	1 	3T			NT	A37CE   					 
2000111500018	20001115	00018	CE  	2000	11	15	20000809SH029    	1	20000801	G	5740	50110231	FITTING         			CESSNA	414   	414A        	2075907	CE  										AFT WING ATTACH	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	414FC	5076 				414A0039				EXTENSIVE INTERGRANULAR CORROSION FOUND ON THE BOTTOM OF THE UPPER AFT WING ATTACH FITTING ON THE LEFT WING.  THE SAME F	ITTING ON THE RIGHT WING STUB WAS CORRODED TO A LESSER DEGREE.  MOISTURE ENTRAPMENT IS BELIEVED TO CONTRIBUTE. (X)					1	L	7	2 	3O			 	A7CE    					 
2000111500019	20001115	00019	SO  	2000	11	15	20000809SH030    	2	20000718	G	8520	539937	SUMP            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  						CRACKED         	B			BXSA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	09	931E	223  				TC1009	1553646L			FOUND THE SUMP CRACKED, CENTER FORWARD SECTION.  CRACK OVERALL LENGTH, 2.75 INCHES.  TWO SHORT SPUR CRACKS CAME OFF THE 	MAIN CRACK. (X)					1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2000112900001	20001129	00001		2000	11	29	20000810SH001    	4	20000801	G	2562	CIR10	ELT             			BEECH 	60    	A60         	1153604	CE  										CABIN	INOPERATIVE     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	811DN					P224				ALKALINE BATTERY PACK LEAKED AND CORRODED ELT MONITOR.  REPLACED ELT WITH NEW ELT NOT REQUIRING A LITHIUM BATTERY PACK. 	 (X)					1	L	7	2 	3O			 	A12CE   					 
2000081800082	20000818	00082	WP  	2000	8	18	20000810SH002    	1	20000712	G	6410	369D2161531	BLADE           			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	504MP	6195 			0022220312	O523E				PILOT FOUND TAIL ROTOR BLADE ROOT FITTING CRACKED ON A PRE-FLIGHT INSPECTION.  THIS IS THE SECOND OCCURRENCE ON THIS AIR	CRAFT.  THE LAST BLADE, S/N 009999-1489, ONLY TWO SERIAL NUMBERS DIFFERENCE.  (X)					1	G	7	1 	3U			 	H3WE    					 
2000081800083	20000818	00083	WP  	2000	8	18	20000810SH003    	1	20000309	G	6410	369D2161531	BLADE           			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	504MP	5700 			0022220312	O523E				CRACKED BLADE WAS FOUND ON POST-FLIGHT AFTER THE PILOT FELT AN IN-FLIGHT VIBRATION.  THE TAIL ROTOR BLADE WAS CRACKED FR	OM THE INBOARD ROOT FITTING, 1.5 INCHES LONG WITH A 90-DEGREE TURN FOR ANOTHER .5 INCH.  (X)					1	G	7	1 	3U			 	H3WE    					 
2000112900002	20001129	00002	SO  	2000	11	29	20000810SH009    	1	20000802	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 1 POSITION	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1050 			0478A					BRAKE ASSEMBLY, P/N 2-1585-R, FAILED PREMATURELY.  NR 1 STATOR IS EXCESSIVELY WARPED.  HEAT STACK WARPED AND UNEVEN WEAR	.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2000081800087	20000818	00087	NE  	2000	8	18	20000810SH014    	1	20000731	G	2612	7630607902103	DETECTOR        			SKRSKY	S76   	S76C        	8143008	NE  										RT FWD ENG COMPT	FAILED          	A			N9WA	K				NONE                    				N			FALSE WARNING             			AP	APPROACH       	1			EA	11	986AH					760438				ISP - WHILE ON APPROACH, NR 2 ENGINE FIRE WARNING ACTIVATED FOR APPROXIMATELY 2 SECONDS.  WARNING ACTIVATED AGAIN APPROX	IMATELY 2 MINUTES LATER, STAYED ON FOR APPROXIMATELY 2 MINUTES AND WENT OUT BY ITSELF.  THERE WERE NO CONFIRMING ENGINE 	INDICATIONS.  LANDED NORMALLY.  REPLACED RIGHT FORWARD FLAME DETECTOR IAW S-76 MM 26-11-01.  OPS CHECKED NORMAL.  (X)				1	G	7	2 	3U			NC	H1NE    					 
2000081800088	20000818	00088	NE  	2000	8	18	20000810SH015    	1	20000713	G	2612	473205	DETECTOR        			SKRSKY	S76   	S76C        	8143008	NE  										LT AFT ENG COMPT	FAILED          	A			N9WA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	986AH					760438				CDW - WHILE ON GROUND FOR APPROXIMATELY 5 TO 7 MINUTES, NR 1 ENGINE FIRE DETECTOR ACTIVATED.  REPLACED NR 1 ENGINE AFT F	LAME DETECTOR, SYSTEM OPS CHECKED NORMAL.  (X)					1	G	7	2 	3U			NC	H1NE    					 
2000112900003	20001129	00003	CE  	2000	11	29	20000810SH019    	1	20000723	G	2810	3189	ADAPTER         			CESSNA	182   	182Q        	2072732	CE  										WING FUEL CAPS	INADEQUATE      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	08	759HT					18266013				AS SUPPLIED WITH THE STC NR SA2326NM, THE DOCUMENTED INSTRUCTIONS, AND DRAWINGS ARE LIMITED IN SCOPE AND POOR IN DETAILS	.  THE PART USES A SIMPLE SYSTEM TO SECURE THE ADAPTER TO THE ORIGINAL LARGE SIZE FUEL CAP OPENING WITH THE SELF-LOCKING	 SINGLE LUG ANCHOR NUTS (SIMILAR TO NAS1025-3).  THE SINGLE LUG HAS TWO HOLES IN IT AS MANUFACTURED AND IN APPEARANCE, I	T IS EASY TO INSTALL THE CAP ADAPTER ASSEMBLY WITH THE ROLL PINS INSTALLED THROUGH THE INSIDE HOLE OF THIS PLATE.  SUBMI	TTER STATED IF THIS ERROR IS  MADE, THE ADAPTER MAY EASILY BE DISLODGED, AND AIRCRAFT FUEL MAY BE LOST IN-FLIGHT CAUSING	 ENGINE STOPPAGE.  (X)	1	H	7	1 	3O			NT	3A13    					 
2000112900005	20001129	00005		2000	11	29	20000811SH001    	4	20000810	G	6113		SPINNER         	CESSNA      		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200*       	17020	SO  						CRACKED         	C				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										SPINNER BACKING PLATE HAS CRACKS RADIATING FROM THE BOLT HOLE AREAS.  AN UNAUTHORIZED REPAIR WAS MADE.THE REPAIR WAS MAD	E BY MAKING A CIRCULAR FLAT SHEET METAL SAME THICKNESS AS THE ORIGIANL MATERIAL,THEN RIVETED TO THE BACKING PLATE.  BOLT	 HOLES WERE DRILLED AT THE CORRECT LOCATION.  IT WAS NOT CONCENTRICALLY ROUND AND IT WAS NOT CENTERED TO THE BACKING PLA	TE.  THE PLATE WAS OUT OF BALANCE.  AFTER A NEW ONE WAS INSTALLED, THE OWNER REPORTS A MUCH SMOOTHER ENGINE-PROPELLER PE	RFORMANCE.  PART TIME UNKNOWN. OWNER INDICATES THAT ANOTHER 150 IS FLYING WITH THE SAME REPAIR.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000112900006	20001129	00006	SO  	2000	11	29	20000811SH002    	1	20000809	G	2910		LINE            			PIPER 	PA42  	PA42720     	7104212	SO  											LEAKING         	B				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			GL	15	31GA					425501009				AFTER TAKEOFF THE LANDING GEAR WOULD NOT PROPERLY RETRACT AND RED FLUID WAS SEEN EXITING RT ENGINE/WING AREA.  CREW RETU	RNED TO BASE.  HYD LEAK FOUND UNDER THE ENGINE NACELLE TO WING ROOT FAIRING.  CAUSED BY AN EXCESSIVELY LONG FAIRING SCRE	W WHICH HAD CHAFED AND PENETRATED THE ALUMINUM HYDRAULIC LINE.  A NEW LINE WAS FABRICATED, PRESSURE TESTED, INSTALLED, A	ND OPERATIONALLY TESTED.  LINE WAS REROUTED SLIGHTLY AND CORRECT PANEL SCREWS INSTALLED.  AS A PRECAUTION, INSPECTED THE	 LINES IN THE LEFT WING ROOT AND FOUND TWO CHAFED HYDRAULIC LINES WHICH WERE REPLACED.  SUBMITTER RECOMMENDED INBOARD WI	NG LEADING EDGE BE REMOVED PERIODICALLY TO INSPECT THE INSTALLATION OF ALL HYDRAULIC, DEICE, AND ELETRICA.	1	L	7	2 	4T			 	A23SO   					 
2000112900007	20001129	00007	SO  	2000	11	29	20000811SH003    	1	20000725	G	7603	MS203651032C	NUT             			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					THROTTLE	FAILED          	B			JAVR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	526JM	1    	1    			4622166	RL10599			INSTALLED LYCOMING FACTORY REBUILT ENGINE IAW PIPER PA-46-310/350 MM 71-00-00, PG 19-22(A) (8).  SECURED ENGINE CONTROL 	WITH SELF-LOCKING NUTS PER PIPER PRACTICES.  AFTER LANDING, ON FIRST FLIGHT, THROTTLE CONTROL WAS LOST DUE TO LOSS OF HA	RDWARE AT THROTTLE TO INJECTOR CONTROL.  MS20365-1032C SELF-LOCKING NUT BACKED OFF AND LOST.  CASTLE NUT/COTTER KEY AND 	BOLT INSTALLED ON THROTTLE, MIXTURE AND PROPELLER GOVERNOR.  (X)			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000112900008	20001129	00008	SO  	2000	11	29	20000811SH004    	1	20000609	G	3221	4032700	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  											CRACKED         	B			QE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										THE MAIN LANDING GEAR TRUNNION WAS BROUGHT TO THIS STATION FOR INSPECTION AND POSSIBLE REPAIR.  THE TRUNNION HAD DEVELOP	ED A CRACK ALONG THE BARREL AND NEXT TO THE FORGING SEAM.  THE OWNER OF THIS TRUNNION HAD TAKEN IT TO A LOCAL WELDING SH	OP AND HAD IT WELDED.  WELDING SHOP HAD NO APPROVED DATA TO PERFORM ANY WELDING ON THIS COMPONENT, THEREFORE, THE COMPON	ENT WAS REJECTED.  IN ADDITION, REPAIRS WERE ACCOMPLISHED BY AN UNAUTHORIZED FACILITY.  (X)			1	L	7	2 	3O			 	A20SO   					 
2000120700006	20001207	00006	CE  	2000	12	7	20000811SH005    	1	20000717	G	3222	998201213	GEAR            			BEECH 	99    	C99         	1154006	CE  										DRAG BRACE	DEFECTIVE       	A			TIMA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	236AL					U236				THE PART WAS ORDERED NEW FROM BEECHCRAFT WITH THE TOP HOLES DRILLED INCORRECTLY.  THE TOP LEFT HOLE IS SUPPOSED TO BE 1.	75 INCHES AND IT WAS DRILLED ON THIS UNIT 1.50 INCHES.  (X)					1	L	7	2 	3T			 	A14CE   					 
2000111500021	20001115	00021	SW  	2000	11	15	20000811SH006    	1	20000811	G	3222		TRUNNION        			SPARTN	7W    	7W          	8430302	SW  										CASTING	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	25	17613					12				LEFT LANDING GEAR DEPARTED UPON LANDING.  STRUT ASSY BROKE FROM TRUNNION, LEFT WING TIP IMPACTED RUNWAY, DIRECTIONAL CON	TROL LOST.  POROUS CASTING, INADEQUATE.   (X)					1	L	7	1 	3R			 	TC628   					 
2000111500023	20001115	00023	CE  	2000	11	15	20000811SH007    	1	20000727	G	7120	J124532	MOUNT           			CESSNA	210   	210L        	2073448	CE  										LT FORWARD	DEFECTIVE       	A			FPIA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2437S					21061281				PART LABELLED/MANUFACTURED WRONG.  NOTICED LT FORWARD ENGINE MOUNT SAGGING.  UPON FURTHER INSPECTION, FOUND PART LABELLE	D ''TOP FORWARD MTG'', BUT DID NOT HAVE REINFORCEMENT WASHER BUILT IN.  CHECKED ALL OTHER P/N J-12453-2 MOUNTS IN STOCK,	 ALL LABELLED ''TOP FORWARD MOUNTING'' AND HAVE REINFORCEMENT WASHER BUILT IN. (X)				1	H	7	1 	3O			 	3A21    					 
2000111500024	20001115	00024	EA  	2000	11	15	20000811SH009    	2	20000811	G	7421		PLUG            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  						FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			NM	08	734QM					17269031	L317676			ENGINE DOES NOT HAVE T-MOD\ WHEN CHANGING VALVE COVERS.  FOUND LYC PN LW-LW15316 EXHAUST (GASKETS) VALVE CAP LAYING IN B	OTTOM OF VALVE COVER, LIFTER P/N LW-16586, WAS NOT PUMPED UP WITH OIL AND WAS BLED DOWN.  THIS MAY HAVE ALLOWED THE CAP 	TO FALL OUT.  ENGINE DID HAVE 3 BROKEN SPARK PLUGS.  RHM-40E CERAMIC INSERTS WERE BROKEN LOOSE AND ENGINE RUN ROUGH AT S	TART-UP, BUT THEN SMOOTHED UP SOMEWHAT.  SUBMITTER DID NOT SUSPECT A LIFTER PROBLEM.   (X)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000111500025	20001115	00025	CE  	2000	11	15	20000811SH010    	1	20000724	G	3233		ROD END         	BEECH       		BEECH 	58    	58P         	1152744	CE  										RT RETRACT ROD	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	133Z					T367				DURING LANDING GEAR INSPECTION, PORTION OF PHASE INSPECTION, AN AMOUNT OF BRASS SHAVINGS WERE OBSERVED UNDER THE RT MAIN	 GEAR BRAKE ASSY ROD END WHERE IT ATTACHES TO THE ACTUATOR ASSY.  THE ROD END WAS DISCOVERED TO BE SEVERELY WORN.  BOTH 	(ACTUATOR END) ROD ENDS WERE REPLACED AND OPS CHECK GOOD.  (X)				1	L	7	2 	3O			 	A23CE   					 
2000111500026	20001115	00026	CE  	2000	11	15	20000811SH011    	1	20000724	G	2410	646655	COUPLING        			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520LB   	17040	SO  					RT ENG ALTERNATO	SEPARATED       	H				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			NM	11	120Z	990  				TJ426	274308R			UPON INVESTIGATION OF AN ALTERNATOR FAILURE, DISCOVERED THE ELASTOMER COUPLING HAD COME APART SENDING A LARGE AMOUNT OF 	RED RUBBER PARTICLES INTO THE ENGINE CRANKCASE AND OIL SYSTEM.  THE OIL FILTER WAS INSPECTED AND FOUND TO BE CONTAMINATE	D WITH THIS DEBRIS.  THE ALTERNATOR WAS NOT SEIZED.  THE ENGINE WAS REMOVED FOR TEAR DOWN, PROP, AND OIL LINES FLUSHES. 	 ENGINE INSTALLED IN 1995.  (X)			1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2000111500027	20001115	00027	SO  	2000	11	15	20000811SH012    	2	20000721	G	7314	35328800	PUMP            			PIPER 	PA28  	PA28181     	7102807	SO  	CONT  	O360  	TSIO360*    	17025	SO  					FIREWALL	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	91075					288690021				PILOT REPORTED WHEN ELECTRIC FUEL WAS TURNED ON, THE ELECTRIC FUEL PUMP AND ALTERNATOR FIELD CIRCUIT BREAKERS TRIPPED.  	INSPECTED FUEL PUMP AND FOUND LEAD-IN WIRE TO ELECTRIC PUMP HAD PULLED OUT OF HOUSING AND WAS SHORTING TO GROUND.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E9CE				 
2000122900002	20001229	00002	EA  	2000	12	29	20000811SH013    	2	20000724	G	8530	74541	EXHAUST VALVE   			AMRGEN	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					VALVE HEAD	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	28384	1052 				AA5B0583	L2362336A			EXHAUST VALVE BROKE ON NR 1 CYLINDER.  HALF OF VALVE HEAD CAME OFF CAUSING DAMAGE TO NR 1 CYLINDER AND THEN BROKE INTO 3	 PIECES.  TWO PIECES LODGED IN THE MUFFLER.  ONE SMALL PIECE TRAVELLED THROUGH THE INTAKE SYSTEM TO NR 4 CYLINDER WHERE 	IT DID DAMAGE TO THE HEAD AND PISTON, ALSO BREAKING THE LOWER SPARK PLUG.  TWO SERVICEABLE CYLINDERS WERE INSTALLED ON T	HE ENGINE.  THE ENGINE WAS RUN FOR 1.5 HOURS WITH ALL GAUGE INDICATIONS NORMAL.  A COMPRESSION TEST SHOWED NORMAL READIN	GS OF NR 1 - 78, NR 2 - 74, NR 3 - 72, NR 4  - 79 AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (X)		1	L	7	1 	3O	3	O	 	A16EA   	E286				 
2000111500029	20001115	00029	EU  	2000	11	15	20000811SH014    	1	20000731	G	8100	58B19497	TANK            			SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					AT WELD	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	159DM	17   				2005	L1041261A			FOUND WELD AT TURBO BEND OF OIL DRAIN TANK CRACKED.  UPON REMOVAL, TUBE CAME OUT OF TANK.  LOOKING AT WELD, IT APPEARED 	TO BE A BAD WELD.  SUBMITTER STATED THAT HAD THIS GONE UNDETECTED, IT COULD HAVE BEEN A DISASTER.  (X)					1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
2000111500030	20001115	00030		2000	11	15	20000811SH016    	4	20000627	G	6122	C210569	GOVERNOR        	WOODWARD    																	DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1481260K					REVELVANT INDICATION INSIDE GOVERNOR BODY.  (X)																			 
2000111500031	20001115	00031		2000	11	15	20000811SH017    	4	20000627	G	6122	210658	MOUNT           	WOODWARD    																	LEAKING         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1481058B					INDICATION AROUND GOVERNOR BODY FACE.  (X)																			 
2000112900009	20001129	00009		2000	11	29	20000811SH018    	4	20000622	G	6122	G210659	HOUSING         	WOODWARD    		BNORM 	BN2   	BN2         	1520202	EU  											DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										RELEVANT INDICATION ON GOVERNOR BODY.  (X)						1	H	7	2 	3O			 	A17EU   					 
2000112900010	20001129	00010		2000	11	29	20000811SH019    	4	20000717	G	6122	4030064	HOUSING         	WOODWARD    																	DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										RELEVANT INDICATION (PT/ET) ON TOP OF GOVERNOR BODY.  (X)																			 
2000112900011	20001129	00011		2000	11	29	20000811SH020    	4	20000714	G	6122	211952	HOUSING         	WOODWARD    		BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	TSIO520C    	17040	SO  						DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1451415N					RELEVANT INDICATION ON SIDE OF GOVERNOR BASE.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E8CE				 
2000111500022	20001115	00022	GL  	2000	11	15	20000811SH021    	1	20000811	G	3230		BOLT            			AMTR  	LANCAR	LANCAIR235  	05626K4	GL  										NOSE GEAR	MISALIGNED      	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	09	67MW	118  				95				NOSE GEAR ALIGNING STRAP BOLT CAUGHT ON NOSE GEAR DOOR PIVOT HINGE ASSEMBLY.  RESULTED IN GEAR UP LANDING.  (X)						1	L	7	1 	3O			RT	EXPA    					 
2000111500028	20001115	00028	CE  	2000	11	15	20000811SH022    	1	20000811	G	7160	589100287	DUCT            			BEECH 	58    	58          	1152740	CE  											CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11		286  				TH1881				INLET DUCT, CRACKED OUT AT NUTPLATE AT FORWARD MIDDLE SCREW OF DOOR PN 58-910028-17 THAT IS ATTACHED TO THE INLET DUCT. 	 NOTE:  BOTH LEFT AND RIGHT ENGINES INLET DUCTS BROKEN AT THE SAME TIME.  THE CAUSE COULD BE VIBRATION INDUCED BY THE AI	R STREAM.  SUBMITTER RECOMMENDED ADDING A FOURTH SCREW FOR DOOR TO LESSEN VIBRATION.  (X)				1	L	7	2 	3O			 	3A16    					 
2000112900012	20001129	00012		2000	11	29	20000814SH001    	4	20000714	G	6122	B210710	HOUSING         			BEECH 	55    	E55         	1152732	CE  											DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	CTEXT									RELEVANT INDICATION ON TOP OF GOVERNOR BODY.  (X)						1	L	7	2 	3O			 	3A16    					 
2000112900013	20001129	00013	CE  	2000	11	29	20000814SH002    	1	20000727	G	2842	S33312	TRANSMITTER     			CESSNA	172   	172S        	2072439	CE  										LT FUEL CELL	DEFECTIVE       	B				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			NM	03	789EP	768  				172S8135				LEFT FUEL QUANTITY WENT TO EMPTY AND LT LOW FUEL ANNUNCIATOR LIGHT ILLUMINATED IN-FLIGHT.  MAINT FOUND THE FUEL QUANTITY	 TRANSMITTER INOPERATIVE.  WHEN THE XMITTER WAS REMOVED FROM FUEL CELL, THE FLOAT WAS MISSING ALONG WITH THE RETAINER WA	SHER ON THE OTBD END OF THE FLOAT ARM.  THE FUEL CELL WAS OPENED AND THE FLOAT AND WASHER RETRIEVED.  FUEL QTY XMITTER M	FG INCORRECTLY, THE WIRE ARM THAT RUNS THROUGH THE FLOAT WAS NOT CRIMPED ON EITHER SIDE OF THE FLOAT DURING MFG ALLOWING	 IT TO FALL OFF THE ARM.  ALSO FOUND LT AND RT FUEL QTY XMITTERS INSTALLED BACKWARDS IAW CESSNA C-172R/S PARTS MANUAL.  	S331-2 TRANSMITTER IS REQUIRED TO BE INSTALLED IN THE RT FUEL CELL AND S331-1 XMITTER IN LT.  REPLACED BOTH XMITTERS.	1	H	7	1 	3O			NT	3A12    					 
2000112900014	20001129	00014	SO  	2000	11	29	20000814SH003    	1	20000814	G	7160		GASKET          			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2B5    	41532	EA  						INADEQUATE      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	8785L					255471	L628440			THIS AIRCRAFT HAS THE SAME AIR FILTER AND LANDING LIGHT ASSY AS THE PA28140 150-150 WITH BAD GASKETS.  SUBMITTER FEELS A	D96-10-01-R1 SHOULD APPLY.  (X)					1	L	7	1 	3O	3	O	 	2A10    	E295				 
2000112900015	20001129	00015	SO  	2000	11	29	20000814SH004    	1	20000716	G	5280		HINGE FITTING   			EMB   	120   	EMB120RT    	       	SO  										RMLG	BROKEN          	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	236AS					120049				RIGHT MAIN LANDING GEAR AFT INBOARD DOOR, AFT HINGE FITTING WAS FOUND BROKEN DURING C-CHECK INSPECTION.  POSSIBLE CAUSE:	  FATIGUE.  SUBMITTER RECOMMENDED REPLACING MONITOR AT REGULAR INTERVALS.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2000112900016	20001129	00016	SO  	2000	11	29	20000814SH005    	1	20000727	G	3242	1331317	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										NR 2 POSITION	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1477 			0185					BRAKE ASSEMBLY, PN 2-1661, FAILED PREMATURELY.  NR 2 STATOR CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVEN WEAR.	  SUBMITTER STATED  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT B	RAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2000112900017	20001129	00017	CE  	2000	11	29	20000814SH006    	1	20000727	G	7120	J124532	SHOCK MOUNT     			CESSNA	210   	210         	2073402	CE  										ENGINE	MISMANUFACTURED 	A			FPIA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										PART LABELED/MANUFACTURED WRONG.  PART LABELED ''''TOP FORWARD MOUNTING'''', BUT AT INSTALLATION, DID NOT HAVE REQUIRED 	REINFORCEMENT WASHER PUT IN AT MANUFACTURE.  PART CURE DATE:  3/99.  (X)					1	H	7	1 	3O			RT	3A21    					 
2000112000001	20001120	00001	CE  	2000	11	20	20000814SH012    	1	20000725	G	7920		ENGINE          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  						MAKING METAL    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3699B	740  	100  			BE107	P27219			DURING A PHASE INSPECTION, THE LEFT ENG OIL FILTER WAS FOUND TO HAVE EXCESSIVE METAL IN OIL FILTER.  ANALYSIS ON OIL AND	 FILTER WAS COMPLETED.  METAL WAS FOUND TO BE MAGNESIUM.  (X)					1	L	7	2 	4T	4	T	 	A14CE   	E4WE				 
2000112000002	20001120	00002	EA  	2000	11	20	20000814SH014    	2	20000807	G	7260	3021459	SHAFT           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ACCESSORY GRBX	SHEARED         	E			TVMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	79GA		3715 			BB556	PCE81261			FAR 135 OPERATOR HAD TO CONDUCT AN EMERGENCY LANDING DUE TO A LEFT ENGINE FAILURE.  THE ENGINE WAS BEING MAINTAINED UNDE	R THE MORE PROGRAM STC SE0000EN.  THE ENGINE FAILED.  TEAR-DOWN REPORT SHOWED THE ACCESSORY GEARBOX INPUT DRIVSHAFT AND 	DRIVESHAFT BEARINGS FAILED.  THIS ENGINE EXCEEDED THE RECOMMENDED OVERHAUL TIME OF 3,000 HOURS BECAUSE IT WAS MAINTAINED	 UNDER THE MORE STC  (3,714.9 HRS).  (X)			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000112000003	20001120	00003	EA  	2000	11	20	20000814SH015    	2	20000807	G	7260	3010674	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ACCESSORY GRBX	SHEARED         	E			TVMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	79GA		3715 			BB556	PCE81261			FAR 135 OPERATOR HAD TO CONDUCT AN EMERGENCY LANDING DUE TO A LEFT ENGINE FAILURE.  THE ENGINE WAS BEING MAINTAINED UNDE	R THE MORE PROGRAM STC SE0000EN.  THE ENGINE FAILED.  TEAR-DOWN REPORT SHOWED THE ACCESSORY GEARBOX INPUT DRIVSHAFT AND 	DRIVESHAFT BEARINGS FAILED.  THIS ENGINE EXCEEDED THE RECOMMENDED OVERHAUL TIME OF 3,000 HOURS BECAUSE IT WAS MAINTAINED	 UNDER THE MORE STC  (3,714.9 HRS).  (X)			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000112000004	20001120	00004	CE  	2000	11	20	20000814SH016    	1	20000814	G	6100		PROPELLER       			CESSNA	182   	182S        	2072701	CE  						MCAULY	3D36C	B3D36C431   	GL  	OIL SERVICE PLUG	LEAKING         	B			WIWR	O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			WP	07	7267Z	106  				18280525		990085		PILOT/OWNER REPORTED OIL ON PROPELLER BLADES, WINDSHIELD.  INSPECTION OF PROPELLER HUB FOUND RED DYE LEAKING FROM HUB SE	RVICE PLUG.  SUBMITTER STATED THIS IS THE SECOND 182S MCCAULEY PROPELLER WITH A LEAK FROM PLUG.  ALSO, A CESSNA 206H MCC	AULEY PROPELLER WAS NOTED AND REPAIRED.  ALL AIRCRAFT HAD LESS THAN 160.0 HOURS SINCE NEW.  NO GUIDE LINES HAVE BEEN EST	ABLISHED FOR THIS PROP IN REGARDS TO ACCEPTABLE STANDARDS FOR RETURN TO SERIVCE CRITERIA.  (X)			1	H	7	1 	3O			NT	3A13    		5	C	 	 
2001011104170	20010111	04170		2001	1	11	20000816SH001    	1	20000804	G	6410	31038382	BLADE           								GARRTT	TPE331	TPE331*     	01514	WP  					3RD ROTOR ASSY	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH DAMAGE ON ONE BLADE.  LOT NR:  4,685.  (X)											3	T			E2WE				 
2000081800166	20000818	00166	EU  	2000	8	18	20000816SH012    	1	20000108	G	7720	430150102	THERMOCOUPLE    			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	SHORTED         	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV					7089				INTERNAL SHORT.  REPLACED THERMOCOUPLE WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000081800167	20000818	00167	NE  	2000	8	18	20000816SH013    	2	20000108	G	7240	430150601	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2 BEARING	LEAKING         	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV	870  				7089	LE45078EA			SEAL LEAKING BEYOND SERVCIEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000081800168	20000818	00168	NE  	2000	8	18	20000816SH014    	2	20000108	G	7240	430144801	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 3 BEARING	LEAKING         	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV	870  				7089	LE45078EA			SEAL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000081800169	20000818	00169	EU  	2000	8	18	20000816SH015    	1	20000108	G	7712		TUBE            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					TORQUEMETER	LEAKING         	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV	870  				7089	LE45078EA			TORQUEMETER FEED LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000082100218	20000821	00218	NE  	2000	8	21	20000816SH018    	2	20000108	G	7250	411100720	SHROUD          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					GAS PROD	BINDING         	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV					7089	LE45078EA			EXCESSIVE GP BLADE TIP RUB.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000082100224	20000821	00224	NE  	2000	8	21	20000816SH020    	2	20000108	G	7240	410106701	RING            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					FIRST TURBINE SH	WORN            	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MV					7089	LE45078EA			SEAL RING WORN BEYOND SEVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000082100225	20000821	00225	NE  	2000	8	21	20000816SH021    	2	20000406	G	7250	411100720	SHROUD          			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					GP TURBINE ROTOR	BINDING         	B			R7MR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117CW	384  				7125	LE45273EA			EXCESSIVE GP BLADE TIP RUB.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800968	20010208	00968	NE  	2001	2	8	20000816SH022    	2	20000406	G	7230	410115013	DIFFUSER        			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	MISMANUFACTURED 	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117CW					7125	LE45273EA			OUTER DIAMETER OF VANE SUPPORT RING IS TOO LARGE (10.221 INCHES).  IMPROPER MANUFACTURE.  REPLACED WITH NEW UNIT, CORREC	TED PROBLEM.  (X)					1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000112000005	20001120	00005	SO  	2000	11	20	20000816SH023    	1	20000807	G	2912	28108	HOUSING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HYD FILTER	CRACKED         	I			WVBA	O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	27755					317852148	RL826861A			PILOT REPORTED GEAR WOULD NOT CYCLE DOWN.  GEAR WAS PUMPED DOWN MANUALLY.  FLUID WAS OBSERVED LEAKING FROM LEFT HYDRAULI	C FILTER HOUSING.  HOUSING WAS REMOVED AND IT WAS DISCOVERED THAT THE LAST FEW THREADS ON THE HOUSING SIDE HAD CRACKED T	HROUGH.  HOUSING AND O-RING WERE REPLACED AND SYSTEM SERVICED AND FUNCTIONALLY TESTED.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000112000006	20001120	00006	SO  	2000	11	20	20000816SH025    	2	20000725	G	8530	652451	PUSHROD         			CESSNA	180   	180F        	2072614	CE  	CONT  	O470  	O470R       	17026	SO  						PLUGGED         	D				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	2163Z	190  				18051263	815845R			C/W TCM SB MSB00-5B, (REPLACING CRANKSHAFT), FOUND PUSH ROD TUBE FOR NR 6 EXHAUST VALVE PLUGGED.  THIS APPARENTLY WAS MI	S-MANUFACTURED.  FROM THE VALVE END IN APPROXIMATELY .1250 INCH FOR AN ADDITIONAL .3750 INCH.  THE TUBE IS SOLID, SO NO 	OIL MAY PASS THROUGH.  THIS CAUSED MATERIAL FROM THE ROCKER ARM BUSHING TO TRANSFER TO THE ROCKER ARM SHAFT FROM LACK OF	 PROPER LUBRICATION.  THIS NECESSITATED REPLACEMENT OF THE PUSH ROD, ROCKER ARM ASSY AND ROCKER ARM SHAFT.  IT APPEARS T	HAT IN MANUFACTURING, THE TUBE BECAME PLUGGED WHEN THE BALL END WAS INSTALLED.  (X)		1	H	7	1 	3O	3	O	 	5A6     	E273				 
2000112000007	20001120	00007	CE  	2000	11	20	20000816SH026    	1	20000802	G	3210	40172	WHEEL           			BEECH 	99    	C99         	1154006	CE  											CRACKED         	B			TIMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	239AL					U239				WHEEL HALF FOUND CRACKED DURING A ROUTINE INSPECTION.  (X)						1	L	7	2 	3T			 	A14CE   					 
2000112000008	20001120	00008	GL  	2000	11	20	20000816SH027    	3	20000731	G	6114	C4716C98	HUB             			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	D2A34C98    	GL  	2ND & 3RD THREAD	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07								983984		HUB, SN 950456, CRACKED ALL THE WAY THROUGH HUB AT 2ND AND 3RD THREAD IN BLADE SOCKET APPROXIMATELY 3.50 INCHES LONG.  R	ED DYE LEAKING FROM PROPELLER.  CAUSE OF CRACK UNKNOWN.  PROPELLER USED IN AG OPERATION.  REPLACED HUB WITH SN 983984.  	(X)				1	L	7	1 	3O			 	A9CE    		5	C	P3EA	 
2000112000009	20001120	00009	GL  	2000	11	20	20000816SH028    	3	20000731	G	6114	D5904C90	HUB             			CESSNA	188   	T188        	2073011	CE  						MCAULY	3A32C	D3A32C90    	GL  	BLADE SOCKETS	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07								7710026		PROPELLER CAME IN LEAKING RED DYE.  ALL THREE BLADE RETENTION NUTS CRACKED AND HUB CRACKED IN NR 2 BLADE SOCKET.  BLADE,	 SN K62431YS, HAD EXCESSIVE CORROSION IN BLADE THREADS (SCRAP).  PROPELLER USED IN AG OPERATIONS.  TWO GOOD BLADES RETUR	NED TO CUSTOMER.  EXACT CAUSE OF CRACK UNKNOWN.  (X)				1	L	7	1 	3O			 	A9CE    		5	C	P21EA	 
2001030100003	20010301	00003	GL  	2001	3	1	20000816SH029    	3	20000731	G	6114	D6447C23	HUB             													MCAULY	2A36C	2A36C23     	GL  	PROPELLER	CORRODED        	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								821846		HUB, SN 673713, SCRAPPED DUE TO EXCESSIVE CORROSION THROUGHOUT (INSIDE/OUTSIDE) AND IN BLADE THREADS.  HUB REPLACED WITH	 SN 821846.  CAUSE OF EXCESSIVE CORROSION POSSIBLY AGE (DEFECTIVE HUB WAS 33 YEARS OLD). (X)															5	C	P880	 
2001030100004	20010301	00004	GL  	2001	3	1	20000816SH030    	3	20000731	G	6111		BLADE           													HARTZL	HC12X	HC12X207    	GL  	PROPELLER	CORRODED        	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07								6757N		HUB (SN 6757N) AND BOTH BLADES (SN A2545 AND A3412) SCRAP DUE TO CORROSION.  SUBMITTER STATED:  CAUSE DUE TO NEGLECT OVE	R THE LAST 53 YEARS.  (X)															5	C	P845	 
2000121800012	20001218	00012	GL  	2000	12	18	20000816SH031    	3	20000731	G	6114	C5480C66	HUB             			CESSNA	182   	182J        	2072722	CE  						MCAULY	2A34C	2A34C66     	GL  	NR 2 HUB SOCKET	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07								725308		HUB, SN 697045, CRACKED IN NR 2 HUB SOCKET ON BACK SIDE.  RED DYE LEAKING FROM PROPELLER.  CAUSE OF CRACK UNKNOWN.  REPL	ACED HUB WITH SN 725308.  (X)					1	H	7	1 	3O			NT	3A13    		5	C	P3EA	 
2000121800013	20001218	00013	GL  	2000	12	18	20000816SH032    	3	20000731	G	6111	90DHA4	BLADE           			CESSNA	188   	188CESSNA   	2073002	CE  						MCAULY	2A34C	B2A34C205   	GL  	2.50 INCHES/BUTT	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07								841770		PROPELLER LEAKING RED DYE.  TEAR-DOWN INSPECTION REVEALED BLADE CRACKED ALL THE WAY THROUGH INTO THE WEIGHT HOLE.  DYE C	OMING FROM BLADE PATCH.  CAUSE UNKNOWN.  PROPELLER USED IN AG OPERATION.  (X)					1	L	7	1 	3O			 	A9CE    		5	C	P3EA	 
2001020700112	20010207	00112	EU  	2001	2	7	20000816SH033    	1	20000706	G	6220	365A31185802	ADAPTER         			AEROSP	AS365 	AS365N2     	8680815	EU  										MAIN ROTOR	TORN            	B			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM					6429				FREQUENCY ADAPTER, SN 17143, TORN.  REMOVED AND REPLACED FREQUENCY ADAPTER PAIR.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001020100036	20010201	00036	EU  	2001	2	1	20000816SH034    	1	20000706	G	6220	365A31185802	ADAPTER         			AEROSP	AS365 	AS365N2     	8680815	EU  										MAIN ROTOR	TORN            	A			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM	314  				6429				FREQUENCY ADAPTER TORN.  REMOVED AND REPLACED FREQUENCY ADAPTER PAIR.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2000121800014	20001218	00014	CE  	2000	12	18	20000816SH035    	1	20000726	G	3213	07416321	BUSHING         			CESSNA	182   	182S        	2072701	CE  										LT MLG	DEFORMED        	C			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	321HW	163  				18280264				DURING A ROUTINE INSPECTION OF THE AIRFRAME, THE LEFT MAIN LANDING GEAR BUSHING WAS FOUND DEFORMED.  THE INSIDE BUSHING 	MATERIAL WAS PROTRUDING FROM THE EDGE OF THE BUSHING.  THE BUSHING WAS FURTHER INSPECTED AFTER REMOVAL FROM THE AIRCRAFT	 AND CONTAINED STRESS CRACKS ALONG THE INSIDE OF THE BUSHING.  POSSIBLE CAUSE WAS A DEFECTIVE BUSHING PRIOR TO INSTALLAT	ION IN THE AIRCRAFT.  SUBMITTER SUGGESTED BETTER QUALITY CONTROL AND NEW PARTS PRIOR TO INSTALLATION TO PREVENT RECURREN	CE.  (X)		1	H	7	1 	3O			NT	3A13    					 
2000121800015	20001218	00015	CE  	2000	12	18	20000817SH003    	1	20000630	G	7920	17374	STRAINER        			CESSNA	414   	414A        	2075907	CE  										OIL LINE/WASTEGA	RESTRICTED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	414P	10   				414A0507				OIL STRAINER ELEMENT P/N EK9052V INSTALLED UNDER STC BY RAM WHEN AIRCRAFT WAS MODIFIED TO SERIES VII.  ELEMENT PLUGS UP 	AND HAS NO BYPASS AND LIMITS OIL FLOW TO WASTEGATE AND AIRCRAFT DOES NOT DEVELOP FULL POWER ON TAKEOFF OR AT ALTITUDE.  	WITH NEW ELEMENT, AIRCRAFT OPERATES NORMAL.  ELEMENT LASTS ONLY BETWEEN 5 TO 15 HOURS.   (X)				1	L	7	2 	3O			 	A7CE    					 
2000121800016	20001218	00016	NE  	2000	12	18	20000817SH004    	2	20000804	G	8530	116733CP	CYLINDER        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 1	CRACKED         	H				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	11	5831B		685  			421008822	354578			WHILE EN ROUTE, LEFT ENGINE STARTED TO RUN ROUGH.  PILOT FEATHERED PROPELLER AND SECURED ENGINE.  AN UNEVENTFUL LANDING 	WAS MADE.  MAINTENANCE FOUND NR 1 CYLINDER CRACKED.  CYLINDER REPLACED WITH AN OVERHAULED UNIT.  ENGINE GROUND RUN AND R	ETURNED TO SERVICE.  (X)				2	L	7	2 	4R	4	R	 	A669    	5E4				 
2000121800017	20001218	00017	SO  	2000	12	18	20000817SH005    	2	20000719	G	8530	649168	CYLINDER        			CESSNA	310   	310D        	2074212	CE  	CONT  	O470  	IO470D      	17026	SO  					NR 2/EXH VLV	FAILED          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	03	674FT	3668 	935  			39041	R7914200			LEFT ENGINE WOULD NOT DEVELOP FULL POWER AT TAKEOFF.  AIRCRAFT CRASH LANDED DUE TO POOR PERFORMANCE.  INSPECTION OF ENGI	NE REVEALED THAT NR 2 CYLINDER HAD ''ZERO'' COMPRESSION.  FURTHER INSPECTION REVEALED THE EXHAUST VALVE FACE WAS NOT SEA	LING ON HALF OR MORE OF THE SURFACE OF THE VALVE SEAT.  LAST ANNUAL INSPECTION C/W 11-12-99.  COMPRESSION CHECK ALL CYLI	NDERS NORMAL.  ENGINE TIME SINCE MAJOR OVERHAUL, 934.7 HOURS.  VALVE, EXHAUST P/N 646286.  INSERT, EXHAUST VALVE SEAT, P	/N 35967.  (X)		1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2000112900019	20001129	00019	NM  	2000	11	29	20000817SH010    	1	20000712	G	2730	35274001	HORN            			CHRIS 	HUSKY 	A1          	221020X	NM  										TAIL OF FUSELAGE	MISALIGNED      	B			AWKR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	8XJ	390  				1388				P/N 50025 (AN3-5) BOLT AND P/N 53875 (AN 1115-21), CLEVIS ATTACHED TO THE ELEVATOR TRIM HORN LINE, P/N 3-5274-001, CHAFE	D ON TAIL STRUCTURE TUBING.  THE LINK SHOULD HAVE A JOGGLE BUILT IN TO DEFLECT THE TRIM CABLE INBOARD FOR CLEARANCE.  AN	TI-CHAFE TAPE WAS APPLIED.  SUBMITTER STATED PER PHONE CALL TO AVIAT FACTORY, HORN LINK WAS BENT INWARD TO CLEAR FUSELAG	E TUBING.  (X)			1	H	7	1 	3O			NC	A22NM   					 
2000112900020	20001129	00020	GL  	2000	11	29	20000817SH012    	3	20000731	G	6114		HUB             			CESSNA	310   	310J        	2074226	CE  						MCAULY	2AF34C	D2AF34C81   	GL  	BLADE SOCKET	CRACKED         	B			M71R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	3141L					310J0141		787504		HUB CRACKED IN BOTH THREADED BLADE SOCKETS.  PROPELLER WAS LEAKING, IN FOR RE-SEAL.  (X)						1	L	7	2 	3O			 	3A10    		5	C	P5EA	 
2000112900022	20001129	00022	EU  	2000	11	29	20000817SH014    	1	20000808	G	8100	LW19107	LINK            			SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					TURBO END	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	678TB	23   				1925	L1041161A			LINK FOUND BROKEN; ANOTHER LINK FOUND BROKEN ON ANOTHER AIRCRAFT.  (X)						1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
2000112900023	20001129	00023	EU  	2000	11	29	20000817SH015    	1	20000808	G	8100	LW19107	LINK            			SOCATA	TB20  	TB21        	8680697	EU  	LYC   	O540  	TIO540AB1A  	41533	EA  					TURBO END	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	678TB	23   				2005	L1041261A			DURING 25-HOUR INSPECTION, FOUND BROKEN LINK.  (X)						1	L	7	1 	3O	3	O	RT	A51EU   	E14EA				 
2000112900024	20001129	00024	SO  	2000	11	29	20000817SH016    	2	20000817	G	8520	535661	CAMSHAFT        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  						MAKING METAL    	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	7138Q	1947 	213  			U20603074	247849R			FERROUS MATERIAL FOUND IN OIL FILTER.  ENGINE DIS-ASSEMBLED, PROBLEM FOUND TO BE FAILED CAMSHAFT AND LIFTER BODIES.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000112900025	20001129	00025	SO  	2000	11	29	20000817SH017    	2	20000817	G	8520	535661	CAMSHAFT        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470L       	17026	SO  						MAKING METAL    	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	9269T	2039 	80   			50769	808530L4			FERROUS MATERIAL FOUND IN OIL FILTER.  ENGINE DIS-ASSEMBLED, PROBLEM FOUND TO BE FAILED CHAMSHAFT AND LIFTER BODIES.  (X	)					1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2000112900026	20001129	00026		2000	11	29	20000817SH018    	4	20000801	G	6122	320268	HOUSING         	MCAULY      							CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  		DEFLATED        	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										RELEVANT PT/ET INDICATION ON GOVERNOR BODY.  (X)											3	O			E8CE	5	C	P47GL	 
2000112900027	20001129	00027	SO  	2000	11	29	20000817SH019    	1	20000809	G	3213	65319004	CYLINDER        			PIPER 	PA28  	PA28151     	7102805	SO  										LINK ATTACH, LOW	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1195X	11100				287515324				DURING OTHER MAINTENANCE TO LANDING GEAR, THE TORQUE LINKS WERE REMOVED AND UPPER STRUT CYLINDER CLEANED.  CRACKS WERE F	OUND AT THE BOTTOM OF THE MACHINED AREA FOR THE TORQUE LINK ATTACHMENT BOTH SIDES.  SUBMITTER SUSPECTED AGE IN HOURS AND	 NUMBER OF LANDINGS AS CAUSE.  (X)				1	L	7	1 	3O			 	2A13    					 
2000112900028	20001129	00028	SO  	2000	11	29	20000817SH020    	2	20000606	G	8520	646623	CRANKSHAFT      			CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550*      	 	SO  						INADEQUATE      	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	61599	126  				U20602350	284915			PER TCM MSB 00-5B, CRANKSHAFT WAS REJECTED BY TELEDYNE CONTINENTAL MOTORS.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2001011104171	20010111	04171		2001	1	11	20000817SH021    	2	20000817	G	7322	HW6106019	CARBURETOR      	PRECISION   																	SATURATED       	B			FUXR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										CHAMBER OF FLOAT NEXT TO FULLRUN POINT IS APPROXIMATELY 75 PERCENT FULL OF AVGAS.  THE CARBURETOR WAS SENT FOR OVERHAUL.	  FLOAT STICKING.  SUBMITTER STATED THIS IS A RECURRING PROBLEM WITH THIS FLOAT AS THIS IS THE THIRD SUBMITTED BY THIS R	EPAIR STATION.  SUBMITTER RECOMMENDED RECALL OF THIS 30-800 FLOAT TO REMEDY THIS PROBLEM.  (X)																	 
2000082800180	20000828	00180	SO  	2000	8	28	20000817SH022    	2	20000817	G	8520	SA535661	CAMSHAFT        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470S       	17026	SO  						FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	79JP	2142 	118  			18267081	469049			FERROUS MATERIAL FOUND IN OIL FILTER.  ENGINE DISASSEMBLED, PROBLEM FOUND TO BE FAILED CAM AND LIFTER BODIES.  (X)						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000082800181	20000828	00181	SO  	2000	8	28	20000817SH023    	2	20000222	G	7314	6482121	PUMP            			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  						LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05	207DF		253  			20700728	818805R			FUEL PUMP FOUND LEAKING FUEL FROM SEAL AT THE DRIVE END OF PUMP HOUSING.  (X)						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2000082800182	20000828	00182	CE  	2000	8	28	20000817SH024    	1	20000211	G	8011	643259A18	ADAPTER         			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  					STARTER	SLIPPED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	207EX		171  			20700100	812380R			STARTER CLUTCH SLIPS.  (X)						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2000082800183	20000828	00183	SO  	2000	8	28	20000817SH025    	2	20000712	G	8530	MILLENIUM	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  						FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	45624		200  			15076995	253134			DURING A 100-HOUR INSPECTION, FOUND THE MILLININUM CYLINDER ASSY WHICH WAS INSTALLED IN THE NR 3 POSITION WOULD ONLY HOL	D A COMPRESSION OF 32 PSI AFTER 200 HOURS OF SERVICE.  POSSIBLE CAUSE UNKNOWN AT THIS TIME.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000082800184	20000828	00184	SO  	2000	8	28	20000817SH026    	2	20000615	G	7322		BUSHING         	CONT        		CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  					THROTTLE SHAFT	WORN            	H				O				OTHER                   				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			AL	03	1581U		310  		J179716AR	20700181	812349R			AIRCRAFT HAD FUEL FLOW FLUCTUATIONS AND POWER SURGES (2-4 GPH).  OCCURRED ON TAKEOFF AND WAS PROGRESSIVELY MORE NOTICEAB	LE AS ENGINE WARMED UP.  POSSIBLE CAUSE WAS THE BUSHINGS THAT THE THROTTLE SHAFT GOES THROUGH BEING WORN CAUSING PLAY IN	 THROTTLE TO MIXTURE ADJUSTMENT AND SUBSEQUENT CHANGES IN FUEL/AIR RATIO AND INDUCTION LEAKAGE THROUGH WORN BUSHINGS.  (	X)			1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001020700125	20010207	00125	GL  	2001	2	7	20000818SH001    	2	20000524	G	7261	369A8010681	LINE            			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					PLENUM CHAMBER	FAILED          	B			ZR4R	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	11	91DK	151  				0187E	835702			COMPRESSION FITTING PROVIDED WITH PLASTIC LINE FAILED IN ENGINE PLENUM CHAMBER AT FULL POWER DURING FLIGHT CAUSING OIL I	NGESTION INTO ENGINE CAUSING TURBINE OUTLET TEMPERATURE AND TORQUE SURGE WHEN OIL IGNITED WITH FUEL AIR MIXTURE IN BURNE	R CAN.  FOUR QUART OIL SYSTEM, OIL REMAINING IN SYSTEM LESS THAN ONE PINT.  PILOT ABLE TO SAFELY LAND MACHINE.  STRONGLY	 SUGGEST METAL LINES IN PLENUM CHAMBER INSTEAD OF PLASTIC.  MANUFACTURER IS AWARE OF PREVIOUS PROBLEMS WITH PLASTIC LINE	S.  (X)		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000121800018	20001218	00018	SO  	2000	12	18	20000821SH001    	2	20000808	G	8530	646678	SEAL            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					INTAKE VALVE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	1278H	372  				347770118				372 HOURS TOTAL TIME SINCE NEW.  RETAINER SPRINGS FELL OFF OF SEAL AND INTO THE OIL SYSTEM.  NO DAMAGE CAUSED.  THEY WER	E CAUGHT IN OIL SCREEN.  UPON REMOVAL OF VALVE COVERS AND VALVE SPRINGS, ALL SEALS WERE FOUND WORN AND SPRINGS READY TO 	WEAR THROUGH.   (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000121800019	20001218	00019	NE  	2000	12	18	20000821SH002    	3	20000627	G	6111	6607132886	BLADE           													ROTOL	R389	R3894123F25 	NE  	ROOT END OUTER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		25152	3194 					DRG179287		PROPELLER RECEIVED FOR REPAIR WITH CUSTOMER COMPLAINT OF EXCESSIVE BLADE TIP MOVEMENT.  DISASSEMBLED PROPELLER AND FOUND	 THAT BLADE, S/N 1193, HAD A CRACK 360 DEGREES AROUND OUTER SLEEVE ON ROOT END.  BLADE REJECTED FROM SERVICE.  (X)															6	C	P30NE	 
2000082800187	20000828	00187	CE  	2000	8	28	20000821SH003    	1	20000808	G	5540	07126161	BULKHEAD        			CESSNA	182   	182F        	2072714	CE  										LT RUDDER CABLE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	3171U	4039 				18254571				DURING ANNUAL INSPECTION, CRACK FOUND UPPER PORTION OF LEFT RUDDER CABLE CUT OUT ON TAIL BULKHEAD.  AD 72-07-09 CRACKS A	ND LOOSE BOLTS RUDDER/FIN LAST C/W 4/94 AT ACFT TOTAL TIME 3,845 HOURS BY DYE PENETRANT AND VISUAL INSPECTION.  NO DEFEC	TS WERE NOTED AT THAT TIME.  BULKHEAD REMOVED ALSO FOUND CRACK AT TIE-DOWN LOOP HOLE.  POSSIBLE TAIL STRIKE FROM LANDING	 AND/OR WIND DAMAGE.  (X)			1	H	7	1 	3O			NT	3A13    					 
2000082800188	20000828	00188	SO  	2000	8	28	20000821SH004    	1	20000629	G	2434		COOLING FAN     	ELECTROSYS  		PIPER 	PA38  	PA38112     	7103812	SO  											BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	958SC	294  			9070089	3878A0233				DURING 100-HOUR INSPECTION, NOTED ALL OF THE BLADES OF THE COOLING FAN HAD BROKEN FROM THEIR MOUNTING PLATE AND SEPARATE	D FROM THE ALTERNATOR.  ALTERNATOR WAS STILL PROPERLY FUNCTIONING.  THE COOLING FAN BLADES WERE ATTACHED TO AN ALUMINUM 	PLATE.  THE BLADES HAD BROKEN AT THE POINT THEY WERE WELDED TO THE PLATE.  (X)				1	L	7	1 	3O			 	A18SO   					 
2000082800189	20000828	00189	CE  	2000	8	28	20000821SH005    	1	20000628	G	7160	P198281	AIR FILTER      			CESSNA	172   	172R        	2072401	CE  										INDUCTION	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	4206K	300  				17280751				AIR FILTER IS LISTED AS A 500-HOUR REPLACEMENT ITEM.  AT 100-HOUR INSPECTION, MADE AT 300 HOURS, NOTED THE INSPECTION AT	 200 HOURS AND THE INSPECTION AT 300 HOURS THE PAPER ELEMENT OF THE FILTER ASSY HAD BADLY ERODED ON APPROXIMATELY 40 PER	CENT OF THE FORWARD FACING SURFACE TO A DEPTH THAT PENETRATED THE ACCORDIAN FOLDS OF THE PAPER.  WHEN THE FILTER WAS HEL	D UP TO THE LIGHT, IT APPEARED THE ELEMENT HAD LOST 40 PERCENT OF ITS FILTERING CAPACITY.  THIS AIRCRAFT HAS BEEN USED F	OR PRIMARY TRAINING AND RENTAL AND HAD BEEN OPERATED FROM PAVED FIELDS ONLY.   SUBMITTER SUGGESTED INSPECTING ON A 50-HO	UR INTERVAL.  (X)	1	H	7	1 	3O			NT	3A12    					 
2000082800190	20000828	00190	SO  	2000	8	28	20000821SH007    	1	20000804	G	3233	65319004	CYLINDER        			PIPER 	PA28  	PA28151     	7102805	SO  										ATTACH FLANGE	ELONGATED       	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1195X	11100				287515324				ON SEVERAL OCCASIONS DURING INSPECTIONS, THE LT LANDING GEAR TO WING SPAR CAP LOWER BOLTS WAS FOUND BROKEN, USUALLY ONE 	BOLT.  LESS FREQUENTLY, AN UPPER BOLT COULD BE FOUND BROKEN.  THE MOUNT HOLES IN BOTH THE SPAR CAPS AND GEAR CYLINDER WE	RE FOUND ELONGATED.  AIRCRAFT MANUFACTURER HAD NO AUTHORIZED REPAIR FOR THIS CONDITION.  AIRCRAFT WAS REPAIRED BY DER AP	PROVAL.  FOR SEVERAL YEARS, THIS AIRCRAFT HAD MADE A TIGHT LEFT 180 DEGREE TURN INTO ITS PACKING AREA AS A TRAINING AIRC	RAFT.  (X)		1	L	7	1 	3O			 	2A13    					 
2000082800191	20000828	00191	SO  	2000	8	28	20000821SH008    	2	20000811	G	7414	6320	MAGNETO         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520R    	17040	SO  					INTERNAL	CORRODED        	B			AI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	94203	760  				21060537	29358R			PRESSURIZED SLICK MAGNETOS ON CESSNA T210L.  DURING ANNUAL, INSPECTED MAGS INTERNALLY FOR CONDITION.  FOUND SEVERE MOIST	URE-CASED CORROSION ALL AROUND INSIDE.  MAGNETO MANUAL CALLS FOR INSPECTION OF 6200 SERIES EACH 100 HOURS, NOTHING FOUND	 FOR INSPECTION OF 6300 SERIES.  MANUAL SAYS TO CLEAN CORROSION AND RE-INSTALL.  CORROSION SO EXTENSIVE, MAGS REPLACED. 	 SLICK AD 88-25-04 ADDRESSES THIS PROBLEM, BUT THESE MAGS, 6320 SERIES, ARE NOT IN THE APPLICABILITY SECTION.  SUBMITTER	 STATED AD SHOULD BE REVISED TO INCLUDE 6300 SERIES PRESSURIZED MAGNETOS.  (X)		1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000082800192	20000828	00192	SO  	2000	8	28	20000821SH009    	2	20000811	G	7414	6320	MAGNETO         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520R    	17040	SO  					INTERNAL	CORRODED        	B			AI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	94203	760  				21060537				PRESSURIZED SLICK MAGNETOS ON CESSNA T210L.  DURING ANNUAL, INSPECTED MAGS INTERNALLY FOR CONDITION.  FOUND SEVERE MOIST	URE-CASED CORROSION ALL AROUND INSIDE.  MAGNETO MANUAL CALLS FOR INSPECTION OF 6200 SERIES EACH 100 HOURS, NOTHING FOUND	 FOR INSPECTION OF 6300 SERIES.  MANUAL SAYS TO CLEAN CORROSION AND RE-INSTALL.  CORROSION SO EXTENSIVE, MAGS REPLACED. 	 SLICK AD 88-25-04 ADDRESSES THIS PROBLEM, BUT THESE MAGS, 6320 SERIES, ARE NOT IN THE APPLICABILITY SECTION.  SUBMITTER	 STATED AD SHOULD BE REVISED TO INCLUDE 6300 SERIES PRESSURIZED MAGNETOS.  (X)		1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000082800193	20000828	00193	CE  	2000	8	28	20000821SH010    	1	20000814	G	2720	S100343A	BEARING         			CESSNA	172   	172R        	2072401	CE  										COPILOT LT PEDAL	LOOSE           	B			VDNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	172GH					17280192				COPILOT''S LEFT RUDDER PEDAL FOUND EXCESSIVLEY LOOSE AT DUAL BRAKE TUBE DURING 100-HOUR INSPECTION.  FURTHER INVESTIGATI	ON REVEALED BEARING, PN S1003-43A, NOT INSTALLED.  INSTALLED NEW BEARING.  SUBMITTER SUSPECTED BEARING NOT INSTALLED AT 	FACTORY.  AIRCRAFT TT:  1,398.2 HOURS.  SUBMITTER STATED THIS IS THE SECOND TIME THIS CONDITION HAS BEEN NOTED AND REPOR	TED.  (X)			1	H	7	1 	3O			NT	3A12    					 
2000082800194	20000828	00194	CE  	2000	8	28	20000821SH011    	1	20000803	G	5510	AN1767A	BOLT            			BEECH 	60    	B60         	1153605	CE  										HORIZ STABILIZER	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	7BB	1629 				P402				DURING ANNUAL INSPECTION, FOUND THE HORIZONTAL STABILIZERS TO CREAK WHEN FORCED UP OR DOWN.  DURING INVESTIGATION, NOTIC	ED MOVEMENT IN THE AFT ATTACH FITTING FOR BOTH SIDES.  REMOVED THE BOLTS FROM THEIR CLOSE TOLERANCE HOLES TO DISCOVER TH	EY WERE TOO SHORT.  THE DUKE PARTS CATALOG SHOWED THAT AN AN176-11A SHOULD BE INSTALLED.  SUBMITTER VERIFIED THAT TO BE 	TRUE BASED ON LENGTH OF THE HOLE.  PART REMOVED WAS AN AN176-7A AND SUBMITTER STATED THIS PART LOOKED TO BE A FACTORY IN	STALLATION.  (X)		1	L	7	2 	3O			 	A12CE   					 
2000082800195	20000828	00195	SO  	2000	8	28	20000821SH013    	1	20000821	G	3245	TR67	TUBE            			PIPER 	PA28  	PA28R200    	7102811	SO  										SCHRADER VALVE	LEAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	2311T	165  				28R7135197				FAILURE OF SCHRADER VALVE ASSY ON GOODYEAR TUBE: 500-5 TR67 LY23930A MANUFACTURED SEP 25 1998.  THE TUBE LOST PRESSURE -	 FAILED AT THE T LETTER STAMPING ON THE VALVE STEM ITSELF, THE STAMPING TOO DEEP INTO THE METAL VALVE STEM RESULTING IN 	COMPLETE AIR PRESSURE LOSS.  (X)				1	L	7	1 	3O			 	2A13    					 
2000082800196	20000828	00196	SW  	2000	8	28	20000825SH001    	1	20000824	G	5320	590000001011	BRACKET         			MOONEY	M20   	M20K        	5870220	SW  										LOWER BELLY	FRACTURED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1162D	1612 				250730				DURING COURSE A OF ANNUAL INSPECTION, FOUND HAT SECTION P/N 590000-001/11 CRACKED.						1	L	7	1 	3O			 	2A3     					 
2000082800197	20000828	00197	SO  	2000	8	28	20000825SH002    	2	20000824	G	8520	631716	CRANKSHAFT      	CONT        		PIPER 	PA28  	PA28150     	7102804	SO  	CONT  	O520  	TSIO520P    	17040	SO  						FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	01	5256W	3054 	1254 			28276	513691			ENGINE FAILED AFTER TAKEOFF RESULTING IN FORCED LANDING.  INSPECTION OF ENGINE REVEALED CRANKSHAFT FAILED BETWEEN THE NR	 2 AND NR 3 JOURNALS.					1	L	7	1 	3O	3	O	 	2A13    	E8CE				 
2001011104195	20010111	04195		2001	1	11	20000825SH003    	2	20000811	G	7322	30800	FLOAT           	PRECISION   																	STUCK           	B				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	09					75059703					CARBURETOR  FLOAT DEFECTIVE.  THE TWO CHAMBERS CLOSEST TO THE FULCRUM ARE APPROXIMATELY 75 PERCENT FULL OF 100LL FUEL.  	THIS CREATED A STICKING FLOAT SYNDROME AND CAUSED EXTREMELY RICH CONDIITION.  THE POSSIBLE CAUSE IS THE INTEGRITY OF THE	 WELD/GLUE OR WHATEVER IS BEING USED TO PLACE THE TOP  ON THE FLOAT IS COMPROMISED CAUSING THE FUEL TO SEEP INTO THE FLO	AT CHAMBERS.  (X)																 
2000121800020	20001218	00020	CE  	2000	12	18	20000825SH004    	1	20000726	G	5752	58341206	HINGE           	CESSNA      		CESSNA	425   	425         	2076018	CE  										TRIM TAB AREA	CRACKED         	B			QB7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07					0176					DURING INITIAL INSPECTION OF THE AILERON, A SLIGHT BUCKLING WAS OBSERVED IN THE UPPER HINGE AREA.  UPON REMOVAL OF THE U	PPER SKIN, A CRACK WAS DISCOVERED IN THE UPPER HINGE BRACKET AREA (P/N 5834120-6).  THE CRACK EXTENDED FROM RIBS 5834110	-90 TO 5834110-98, WHICH WAS MEASURED AT 12.25 INCHES LONG.   (X)				1	L	7	2 	3T			RT	A7CE    					 
2000121800021	20001218	00021	NM  	2000	12	18	20000825SH005    	2	20000801	G	7210	3588941	BEARING         			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					TORQUE SENSOR	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	CGFPP	2591 			P598	11032	P06068			ENGINE DISASSEMBLED, INSPECTED,  A BEARING IN THE DIRECT-DRIVE GEAR TRAIN FAILED.  BEARING IS INSTALLED IN THE TORQUE SE	NSOR ASSY.  ALLIED SIGNAL SB 331-72-0360 ADDRESSES THIS BEARING BY OFFERING A BEARING WITH INCREASED FATIGUE LIFE.  C/W 	THIS SB IS LISTED AS OPTIONAL.  SB 33172-0555 SPECIFICALLY ADDRESSES THIS ISSUE BY REPLACING THE TORQUE SENSOR ASSY WITH	 AN IMPROVED UNIT.  C/W THIS BULLETIN IS LISTED AS RECOMMENDED.  ALLIED SIGNAL NOW REQUIRES ENGINES OPERATING TO THE EXT	ENDED 5400 HR TBO, TO INCORPORATE THE MODIFICATIONS.  THE FAILED TORQUES SENSOR INSTALLED IN 1989, SEE AD 95-16-08.  (X)		1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2001021600019	20010216	00019	SO  	2001	2	16	20000825SH006    	1	20000818	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1663 			1405A					BRAKE ASSY, P/N 2-1585-R, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNE	VEN WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.   NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSY.	  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001021600020	20010216	00020	SO  	2001	2	16	20000825SH007    	1	20000817	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1674 			0437A					BRAKE ASSY, P/N 2-1585-R, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT OUTER RELIEF HOLES.  HEAT STACK WARPED A	ND UNEVEN WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE 	ASSY.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001021600021	20010216	00021	SO  	2001	2	16	20000825SH008    	1	20000819	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		131  			0393A					BRAKE ASSY, P/N 2-1585, FAILED PREMATURELY.  NR 1 STATOR CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVEN WEAR.  S	UBMITTER STATED THIS IS CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBLY.  (X)					2	L	7	2 	4T			RT	A31SO   					 
2001021600022	20010216	00022	SO  	2001	2	16	20000825SH009    	1	20000814	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1948 			0547A					BRAKE ASSY, P/N 2-1585, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVE	N WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.   NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE ASSEMBL	Y.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001021600023	20010216	00023	SO  	2001	2	16	20000825SH010    	1	20000814	G	3242	RFS2010	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1326 			0051A					BRAKE ASSEMBLY, P/N 2-1585-R, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND	 UNEVEN WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  RAPCO FLEET SUPPORT PARTS INSTALLED IN BRAKE AS	SY.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001021600024	20010216	00024	SO  	2001	2	16	20000825SH011    	1	20000817	G	3242	1331317	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		981  			1438A					BRAKE ASEMBLY, P/N 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UN	EVEN WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST REC	ENT BRAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001011100952	20010111	00952		2001	1	11	20000825SH012    	1	20000825	G	2822		SHAFT           	DUKES       							LYC   	O540  	IO540D4A5   	41532	EA  					FUEL PUMP	SHEARED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	5788						L402648			THE ELECTRIC FUEL PUMP WOULD RUN, BUT WOULD NOT PUMP FUEL.  DURING DISASSEMBLY, FOUND ONE OF THE FOUR VANES MISSING, THE	 VANE HOUSING TO SHAFT RETAINING PIN HAD COME OUT, AND THE SHAFT HAD SHEARED. THE CONCERN IS THAT THERE IS NO FILTER OR 	SCREEN BETWEEN THE ELECTRIC PUMP AND THE ENGINE DRIVEN PUMP TO STOP THE DEBRIS FROM THE FAILED ELECTRIC PUMP CAUSING CAT	ASTROPHIC DAMAGE TO THE ENGINE DRIVEN PUMP.  SUBMITTER RECOMMENDED THAT CLOSE ATTENTION BE PAID TO THE PRESSURE OUT OF T	HE ELECTRIC PUMP AND NOT TRUSTING SOLELY IN THE SOUND OF THE PUMP.  ALSO, SOME TYPE OF SAFETY SHOULD BE INSTALLED TO PRE	VENT ELECTRIC PUMP DEBRIS FROM MIGRATING TO THE ENGINE DRIVEN PUMP.  (X)						3	O			1E4				 
2000112900029	20001129	00029	GL  	2000	11	29	20000828SH002    	3	20000727	G	6114	C23	HUB             			BEECH 	45    	A45         	1152006	CE  						MCAULY	2A36C	2A36C23     	GL  		CRACKED         	B			FR6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03			1500 					802034		SUBMITTER STATED AT LAST ASSEMBLE, IMPROPER USE OF SILICONE WAS USED TO SEAL THREADS OF RETENTION NUT TO HUB.  HUB SOCKE	TS WERE BOTH CRACKED.  EARLY CRACK DETECTION FROM ROD DYE OIL LEAKING OUT COULD NOT HAPPEN BECAUSE THREADS WERE FILLED W	ITH SILICONE DURING ASSEMBLY.  (X)				1	L	7	1 	3O			 	5A3     		5	C	P880	 
2000112900030	20001129	00030	SW  	2000	11	29	20000828SH018    	1	20000812	G	3230	1433316510	BRACE           	RYAN        		TMPSON	NAVION	NAVIONB     	6150112	SW  										LMLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	10894	4468 				NAV42333B				DURING ANNUAL INSPECTION, FOUND RIGHT AND LEFT MAIN GEAR RETRACT SIDEBRACE LINKS CRACKED AT WELD WHERE TUBE ATTACHES TO 	YOKE.  ALL 3 LINKS (INCLUDING NOSE GEAR) WERE REPLACED WITH NEW DESIGN.  STRONGER UNITS PURCHASED.  (X)					1	L	7	1 	3O			 	A782    					 
2000112900031	20001129	00031	SO  	2000	11	29	20000828SH020    	2	20000804	G	8520	537296	SHROUD          			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					PUSH ROD ENGINE	CRACKED         	B				A				UNSCHED LANDING         				K	Y		FLUID LOSS                	ENGINE STOPPAGE           		CR	CRUISE         	1			SW	01	1830V					E3087	682616			PUSHROD SHROUD CRACKED AT INSIDE OF SPRING RETAINING CRIMP, AND ALLOWED THE OIL TO LEAVE ENGINE CAUSING ENGINE TO SEIZE.	  (X)					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2000112900032	20001129	00032	CE  	2000	11	29	20000828SH021    	1	20000727	G	3230	1153800025	MOTOR           			BEECH 	200   	B200        	1152922	CE  										CENTER FUSELAGE	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			EA	03	152C		260  			BB1132				AGC, AIRCRAFT DEPARTED, UPON RETRACTION, FLIGHT CREW NOTICED GEAR OPERATION SOUNDED SLUGGISH.  APPROX HALF WAY UP ON RET	RACTION, THE GEAR STOPPED FOR A SECOND OR SO, THEN CONTINUED TO RETRACT.  PILOTS NOTICED A RED LIGHT IN THE GEAR HANDLE.	  CREW SELECTED GEAR DOWN, GOT 3 GREEN LIGHTS AND LANDED ACFT BACK AT AGC.  AFTER JACKING ACFT IN HANGAR, RETRACTED GEAR	 24 TIMES WITHOUT FAILURE.  REPLACED GEAR MOTOR.  THERE WAS A SLIGHT DIFFERENCE IN THE SPEED OF THE NEW GEAR MOTOR.  NO 	EVIDENCE OF MECHANICAL BINDING IN SYSTEM.  FAILED MOTOR WAS O/H.  (X)		1	L	7	2 	4T			 	A24CE   					 
2000112900033	20001129	00033	CE  	2000	11	29	20000828SH022    	1	20000722	G	2100	MS20364624C	NUT             			BEECH 	58    	58P         	1152744	CE  										FREON COMP BRACK	MISSING         	B			FC6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	163Z					TJ247				WHILE PERFORMING A VISUAL INSPECTION OF LEFT ENGINE, DISCOVERED THE FREON COMPRESSOR BRACKET ASSY MISSING THE NUT THAT R	ETAINS THE IDLER SHEAVE ARM RETAINING BOLT.  THE SHEAVE ASSY WAS BEING HELD TO THE COMPRESSOR BRACKET BY BELT TENSION ON	LY AND EVENTUALLY WOULD HAVE FAILED.  BOLT THREADS WERE INSPECTED, A NEW WASHER AND NUT CALLED OUT FOR IN THE ENGINE PAR	TS CATALOG WERE INSTALLED AND TORQUED PER THE ENGINE O/M.  (X)			1	L	7	2 	3O			 	A23CE   					 
2000112900034	20001129	00034	CE  	2000	11	29	20000828SH023    	1	20000722	G	3710		LINE            			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  						MISALIGNED      	B			FC6R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			NM	05	163Z					TJ247				PILOT WAS UNABLE TO OBTAIN FULL RICH FUEL MIXTURE ON LEFT ENGINE.  UPON INSPECTION BY MAINTENANCE, THE MIXTURE CONTROLLE	R LINKAGE WAS FOUND OBSTRUCTED FROM REACHING FULL TRAVEL BY THE DRY AIR PUMP PRESSURE AIR LINE.  THE PRESSURE AIR LINE W	AS CORRECTLY ROUTED SO THAT THE MIXTURE CONTROL HAD COMPLETE FREEDOM OF MOVEMENT.  (X)				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001011100775	20010111	00775	SO  	2001	1	11	20000828SH024    	1	20000801	G	3340	AL5112	POWER SUPPLY    			GULSTM	G1159 	G1159       	3953505	SO  										UPWASH LIGHT SYS	DEFECTIVE       	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	03	154C	1735 				253				WHILE PERFORMING A ROUTINE POST-FLIGHT INSPECTION, SMOKE WAS FOUND COMING FROM BEHIND THE VALANCE PANEL AREA NEAR FWD LT	 EMERG EXIT WINDOW.  FOUND PROTECTED POWER SUPPLY (PPU) FOR ONE OF THE UPWASH FLUORESCENT LIGHT BULBS HAD BEEN DEFECTIVE	.  SIMILAR OCCCURRENCE ON 9-99 ON SAME ACFT WITH SAME P/N PPU (AL-5112), SN 2526.  (X)				2	L	7	2 	4F			RT	A12EA   					 
2001011100799	20010111	00799	CE  	2001	1	11	20000828SH025    	1	20000808	G	3221	NAS51736	SCREW           			CESSNA	500   	550         	2076604	CE  										NOSE WW	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	26496	4783 				5500607				ON THIS ACFT AND SEVERAL OTHERS (4614N, 26494) THE SCREWS HOLDING THE LT AND RT UPPER NOSE AND TRUNNION IN PLACE HAVE BE	EN FOUND LOOSE.  THERE IS NO INSPECTION PROCEDURE OR TIME FRAME CALLED OUT IN THE MM.  (X)					1	L	7	2 	4F			 	A22CE   					 
2000112900035	20001129	00035	EA  	2000	11	29	20000828SH026    	2	20000815	G	7322	2539559F	DIAPHRAGM       	BENDIX      	RSA5AD1     	AMTR  	SH2R  	SH2R        	05601P2	GL  	LYC   	O360  	IO360B1E    	41514	EA  					BUSHINGS	WORN            	B			X9PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	26PB	1000 			239709	585R	RL70651A			SERVO HAD WORN THROTTLE SHAFT BUSHINGS AND IDLE LINK LEVER HOLES.  COMPONENT APPEARED TO HAVE BEEN SUBJECTED TO ABNORMAL	 VIBRATION INPUT.  TIME SINCE LAST OVERHAUL - MAY 1965.  ALL INSPECTION DATA IS AVAILABLE ON JWO 2705.  (X)					1	L	7	1 	3O	3	O	RT	EXPA1L71	1E10				 
2001020700189	20010207	00189	EA  	2001	2	7	20000828SH027    	2	20000808	G	8530	73938	INTAKE VALVE    	LYC         		HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	GOUGED          	B				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	03	2039B	44   				0111	L3748136A			AIRCRAFT EXPERIENCED A ROUGH RUNNING ENGINE ACCOMPANIED BY A LOSS OF POWER.  SUSPECTING A STICKING VALVE, AN EXHAUST VAL	VE WIGGLE CHECK WAS PERFORMED IAW LYC SB SB388B.  SINCE EXHAUST VALVE CLEARANCES WERE FOUND WITHIN LIMITS, AN INSP OF TH	E INTAKE VALVES WAS PERFORMED.  INSP OF THE NR 2 CYLINDER INTAKE VALVE REVEALED SEVERE GOUGING AND SCORING ON VALVE STEM	.  MARKS WERE CONSISTENT WITH TOOL JAWS AND BELIEVED TO BE PRODUCED DURING MFG OR ASSY.  CYLINDER WAS REMOVED AND REPLAC	ED.  (X)		1	G	7	1 	3O	3	O	O	4H12    	E286				 
2000121800022	20001218	00022	CE  	2000	12	18	20000828SH029    	1	20000702	G	3220		NUT             	PIPER       		CESSNA	206   	U206B       	2073322	CE  										YOKE NOSE GEAR	DAMAGED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	08	3488L				594	U2060788				DURING LANDING TOUCHDOWN, THE AIRCRAFT''S NOSE WHEEL DEPARTED AIRCRAFT.   LOCAL PEOPLE, AT THE SITE, FOUND THE NOSE WHEE	L AND ATTACHMENT BOLT ALONG WITH OTHER ATTACHMENT HARDWARE.  (THE AN6-58A NOSE WHEEL BOLT REVEALS NO SIGNS TO THREAD DAM	AGE.  ADDITIONALLY, IN THE HARDWARE FOUND AT THE SITE, IS AN AN363-6 SELF-LOCKING NUT, ALTHOUGH THERE IS NO WAY TO POSIT	IVELY IDENTIFY THIS NUT AS THE ACTUAL ONE THAT WAS INSTALLED ON THE NOSE WHEEL BOLT; BUT IT MAY HAVE BEEN.  NOTE:  THE N	UT IS EASILY INSTALLED BY HAND ONTO THE BOLT TO WHERE THE NUT IS FLUSH WITH END OF THE BOLT.  (X)		1	H	7	1 	3O			 	A4CE    					 
2000121800023	20001218	00023	SO  	2000	12	18	20000828SH030    	1	20000803	G	5751	3721400	HINGE           			PIPER 	PA34  	PA34200T    	7103406	SO  										RT AILERON	CRACKED         	A			HEBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	304CW					347870153				RIGHT AILERON CENTER HINGE CRACKED FROM CORROSION INSIDE THE RIGHT AILERON.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000121800024	20001218	00024	CE  	2000	12	18	20000828SH031    	1	20000803	G	3211	AN425A	BOLT            			CESSNA	177   	177RG       	2073709	CE  											SHEARED         	B			SMTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	33224					177RG0928				LANDING GEAR RIGGING WAS BEING CHECKED.  DISCOVERED BOLT SHEARED AT MOUNT ATTACH POINT, MAIN LANDING GEAR SUPPORT ASSEMB	LY.  REPLACED BOTH BOLTS.  AC TT:  6,552.00 HOURS.   (X)					1	H	7	1 	3O			 	A20CE   					 
2001020700193	20010207	00193	EU  	2001	2	7	20000828SH034    	1	20000804	G	3340	H102	ADAPTER         			SNIAS 	350   	AS350B2     	8680813	EU  										STROBE LIGHT	DETACHED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4035W	2373 				2912				AFTER A FLIGHT AND ON THE POST-FLIGHT INSPECTION, THE TAIL STROBE BEACON WAS FOUND HANGING ON THE SIDE OF THE VERTICAL F	IN.  THE CLAMP WAS STILL IN PLACE BUT LOOSE ALLOWING THE STROBE LENS TO WEAR AWAY THE HOLDING ADAPTER FOR THE STROBE.  W	HEN ENOUGH MATERIAL WAS LOST, THE STROBE BROKE OFF.  THIS COULD HAVE BEEN A LOT WORSE IF THE WIRES HAD BROKEN AND ALLOWE	D THE STROBE TO CONTACT THE TAIL ROTOR.  THIS IS THE SECOND TIME ON TWO AIRCRAFT IN FLEET.  BOTH AIRCRAFT HAD ABOUT THE 	SAME AMOUNT OF TIME.  (X)		1	G	7	1 	3U			 	H9EU    					 
2000083101064	20000831	01064	NE  	2000	8	31	20000829SH001    	2	20000719	G	8550	33019	DRIVE GEAR      			FRCHLD	22    	22C7A       	3370104	EA  	PWA   	R2000 	R20007M2    	52023	NE  					NR 2 OIL PUMP	FRACTURED       	B			G2OC	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AL	03	2225C		240  			215	P105274			LOSS OF OIL PRESSURE (ENGINE) IN FLIGHT.  FOUND MAIN OIL PUMP, PN 33019, DRIVESHAFT SHEARED JUST BELOW THE SCAVENGE VANE	S.  THE CAUSE APPEARS TO BE A FATIGUE FRACTURE.  THE ENGINE ASSY WILL BE REPLACED DUE TO OIL STARVATION.  THE OIL PUMP A	SSY WILL BE SENT TO THE OVERHAUL FACILITY FOR TDR.  (X)				1	H	7	1 	3I	4	R	 	ATC438  	5E5				 
2000083101065	20000831	01065	GL  	2000	8	31	20000829SH002    	1	20000707	G	2710		ROD END         			AMTR  	S300  	S300D2      	       	GL  										AILERON HINGE	DESTROYED       	G				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			GL	13	112KG	393  				22				WHILE PERFORMING AEROBATICS (1/2 SNAP TO LEFT) THE LEFT AILERON DEPARTED AIRCRAFT.  INVESTIGATION REVEALED CENTER AILERO	N HINGE HAD FAILED.  LOW CYCLE FATIGUE.  AIRCRAFT DESIGNER TO PERFORM A RE-EVALUATION OF THE HINGE DESIGN.  AIRCRAFT IS 	LICENSED ''EXPERIMENTAL EXHIBITION''.  (X)				1	L	7	1 	3O			NC	EXPA1L71					 
2000083101066	20000831	01066	CE  	2000	8	31	20000829SH004    	1	20000126	G	2434	5488	ALTERNATOR      	LAMAR       		CESSNA	172   	172S        	2072439	CE  										JUNCTION BOX	INOPERATIVE     	B			BF8R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			WP	07	508ER	1100 				172S8008				ALTERNATOR FAILURE REPORTED BY PILOT DURING FLIGHT.  INSPECTION OF CHARGING SYSTEM FOUND HIGH RESISTANCE ACROSS ALTERNAT	OR CONTACTOR TERMINALS.  POSSIBLE CAUSE, TURNING ON ALTERNATOR WITH HIGH LOAD.  SUBMITTER SUGGESTED CHANGING START-UP PR	OCEDURE SO ALTERNATOR IS ON DURING STARTING AND INSTALL HEAVY DUTY CONTACTOR.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000083101067	20000831	01067	EA  	2000	8	31	20000829SH008    	2	20000322	G	8530	LW11633	CYLINDER        	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER WALLS	UNSERVICEABLE   	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69186	460  				15282536	L2389615			DURING A 100-HOUR INSPECTION, ALUMINUM SHAVINGS WERE FOUND IN THE OIL FILTER.  SUBMITTER STATED THIS 5TH TIME THIS SHOP 	HAS HAD THIS PROBLEM IN THE LAST 18-24 MONTHS).  ALUMINUM IS FROM PISTON PIN PLUGS RUBBING AGAINST THE LOWER PART OF THE	 CYLINDER WHICH, AFTER 400-500 HOURS, DEVELOPED SEVERE PITTING THEN CREATED A WEAR STOP IN THE CYLINDER WALLS.  ONE ENGI	NE LOST COMPRESSION IN ALL 4 CYLINDERS BELOW ACCEPTABLE LIMITS.  (X)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000083101068	20000831	01068	CE  	2000	8	31	20000829SH009    	1	20000715	G	3210	07410094	GEAR            			CESSNA	182   	182         	2072702	CE  										MOUNTING AREA	FAILED          	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	01	6473A	14306				33273				DURING TAXI, LANDING GEAR SPRING FAILED AT MATING AREA OF P/N 0541121-2 SUPPORT.  CAUSED SUBSTANTIAL DAMAGE TO RIGHT CAB	IN AFT OF CREW DOOR, RIGHT SIDE OF HORIZONTAL STABILIZER AND ELEVATOR, AND OUTBOARD SECTION OF RIGHT WING.  (X)					1	H	7	1 	3O			NT	3A13    					 
2000083101069	20000831	01069	EA  	2000	8	31	20000829SH010    	2	20000724	G	8550		GASKET          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					OIL SUMP PAN	IMPROPER PART   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	61541	620  				17264626	L4068727A			THE LOWER RIGHT ENGINE ISOLATION MOUNT IS BECOMING RUPTURED DUE TO CHAFING CAUSED BY THE PROTRUSION OF THE OIL SUMP PAN 	GASKET.  THIS GASKET, WHEN DRIED OUT DUE TO HEAT, SEEMS TO ACT LIKE A KNIFE AGAINST THE ISOLATION MOUNT.  TRIMMING THE G	ASKET STOPS THIS.  SUBMITTER STATED THIS IS 3RD OCCURRENCE ON 3 DIFFERENT AIRCRAFT.  (X)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000083101070	20000831	01070	SO  	2000	8	31	20000829SH011    	1	20000714	G	8100	654237	DUCT            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					LEFT ENGINE	CRACKED         	A				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	01	8063L	78   				348233067	811371R			PILOT REPORTED THOTTLE SPLIT AND UNABLE TO OBTAIN RATED POWER ON LEFT ENGINE.  INSPECTION OF LEFT ENGINE REVEALED EXHAUS	T V-DUCT ASSY AT TURBOCHARGER CRACKED.  THIS PART WAS INSTALLED NEW AS A COMPONENT OF A FACTORY RE-MANUFACTURED ENGINE. 	 TOTAL TIME SINCE INSTALLED WAS 78 HOURS.  CAUSE OF CRACKING IS UNDER INVESTIGATION.  (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000083101071	20000831	01071	CE  	2000	8	31	20000829SH012    	1	20000810	G	7603	5122218	THROTTLE        			CESSNA	206   	P206C       	2073312	CE  	CONT  	O520  	IO520A      	17032	SO  					CENTRAL ASSY	BROKEN          	A			DKBA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	09	8630Z	126  				P2060430	112751R			PILOT STARTED TO REDUCE POWER IN ORDER TO LOSE ALTITUDE.  AT THIS TIME, THE THROTTLE CABLE BROKE CAUSING A LOSS IN ENGIN	E POWER.  PILOT MADE SAFE LANDING IN A REMOTE FIELD.  UPON INSPECTION, MAINTENANCE PERSONNEL FOUND THROTTLE CABLE BROKEN	 JUST ABOVE THE CABLE SUPPORT BRACKET.  SUBMITTER SUSPECTED CAUSE AS IMPROPER HARDWARE USED ON SUPPORT BRACKET ALLOWING 	IT TO FLEX AS THROTTLE AND MIXTURE CONTROLS WERE CYCLED.   SUBMITTER SUGGESTED TO PREVENT RECURRENCES, CLOSER INSPECTION	 OF FLIGHT CRITICAL ITEMS SHOULD BE PERFORMED IAW MANUFACTURER''S MM.  (X)		1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000083101072	20000831	01072	EA  	2000	8	31	20000829SH013    	2	20000811	G	7414	4381	MAGNETO         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					LEFT	FAILED          	B			WIWR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	07	95615	2070 				15285938	L2391215			HIT/DVT - WHILE EN ROUTE PILOT REPORTED A SEVERE LOSS OF ENGINE POWER.  ACFT MADE UNEVENTFUL LANDING IN THE DESERT ON AN	 UNCHARTED DIRT STRIP.  ACFT HAD TO BE TRUCKED BACK TO DVT.  FOUND MAGNETOS PARTIALLY FAILED.  BOTH COILS SHOWED SIGNS O	F OVERHEATING AND WERE OUT OF LIMITS PER MFG SPECS.  BOTH SETS OF POINTS WERE FOUND UNSERVICABLE, BOTH DISTRIBUTORS SHOW	ED SIGNS OF CARBON TRACKING ONE OF WHICH WAS ARCING/GROUNDING OUT ON THE MOUNTING SCREW THROUGH THE CAP.  ONE MAG WAS FO	UND WITH LARGE AMOUNTS OF OIL INSIDE CASE.  POSSIBLY, EXTREMELY HIGH OUTSIDE AIR TEMPS (BETWEEN 110 DEGREES AND 121 DEGR	EES) WERE CAUSE OF COILS OVERHEATING.  MAINT RECORDS SHOWED NO EVIDENCE OF 500-HR INSP BEING PERFORMED ON EITHER MAG.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000083101073	20000831	01073	EA  	2000	8	31	20000829SH014    	2	20000811	G	7414	4381	MAGNETO         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					RIGHT	FAILED          	B			WIWR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	07	95615	2070 				15285938	L2391215			HIT/DVT - WHILE EN ROUTE PILOT REPORTED A SEVERE LOSS OF ENGINE POWER.  ACFT MADE UNEVENTFUL LANDING IN THE DESERT ON AN	 UNCHARTED DIRT STRIP.  ACFT HAD TO BE TRUCKED BACK TO DVT.  FOUND MAGNETOS PARTIALLY FAILED.  BOTH COILS SHOWED SIGNS O	F OVERHEATING AND WERE OUT OF LIMITS PER MFG SPECS.  BOTH SETS OF POINTS WERE FOUND UNSERVICABLE, BOTH DISTRIBUTORS SHOW	ED SIGNS OF CARBON TRACKING ONE OF WHICH WAS ARCING/GROUNDING OUT ON THE MOUNTING SCREW THROUGH THE CAP.  ONE MAG WAS FO	UND WITH LARGE AMOUNTS OF OIL INSIDE CASE.  POSSIBLY, EXTREMELY HIGH OUTSIDE AIR TEMPS (BETWEEN 110 DEGREES AND 121 DEGR	EES) WERE CAUSE OF COILS OVERHEATING.  MAINT RECORDS SHOWED NO EVIDENCE OF 500-HR INSP BEING PERFORMED ON EITHER MAG.	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000083101074	20000831	01074	NM  	2000	8	31	20000829SH015    	1	20000816	G	2820	1086221101	HOSE            			UNIVAR	108   	1081        	9230404	NM  	FRNKLN	6A4150	6A4145A3    	27024	EA  					FUEL SUMP/CARB	RESTRICTED      	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CE	07	9442K					1082442	30093			AIRCRAFT LOST POWER DUE TO FUEL STARVATION.  AIRCRAFT LANDED DOWN WIND ON GRASS STRIP MORE THAN HALF WAY DOWN THE STRIP.	  AIRCRAFT WAS PUT IN A PARTIAL SKID AT TIME OF IMPACT.  RIGHT LANDING GEAR COLLAPSED CAUSING PROPELLER TO HIT GROUND AN	D RIGHT WING DAMAGED.  PILOT WAS NOT INJURED.  FOUND FUEL LINE P/N 108-6221101 HAD SWIVELLED UP FROM LOW PRESSURE MIL H-	6000 3Q85 .50 INCH INNER LINING OF HOSE HAS SWIVELLED UP NEAR THE FITTING CAUSING A RESTRICTION.  POSSIBLE CAUSE, AIRCRA	FT HAD STC FOR AUTOFUEL.  AUTOFUEL USED MOSTLY FOR SEVERAL YEARS.  (X)		1	H	7	1 	3O	3	O	 	A767    	E238				 
2001020700191	20010207	00191	EU  	2001	2	7	20000829SH016    	1	20000801	G	6320	350A32030004	GEARBOX         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN	MAKING METAL    	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	13	971H	3137 	137  			2955	4548			WHILE PILOT WAS FLYING ON TOUR FLIGHT, NOTICED MAIN GEARBOX CHIP LIGHT ILLUMINATED.  PILOT MADE PRECAUTIONARY LANDING.  	INSPECTED MAIN GEARBOX CHIP PLUG, FOUND A SMALL METAL FLAKE.  CLEANED CHIP PLUG AND PERFORMED OPERATIONAL CHECK, FUNCTIO	NALLY CHECKED GOOD.  AIRCRAFT RETURNED TO SERVICE.  AIRCRAFT TT:  6,706.2 HOURS.  (X)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001020700192	20010207	00192	SW  	2001	2	7	20000829SH017    	1	20000731	G	6220	12NH8EB080	NUT             	BELL        		BELL  	222   	222U        	1182140	SW  										M/R PTICH HORN	UNSERVICEABLE   	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	911ED	506  			A44	45771				NUT P/N 12NH-8 AND P/N EB080.  LOOSE TORQUE IF INSTALLED IAW ASB 222U-98-54, ASB HAS NO WASHER INSTALLED UNDER THE HEAD 	OF THE NUT.  THE NUT BECOMES DEFORMED AND LOSES TORQUE.  CORRECTED ASB 222U-98-54 TO SHOW A WASHER P/N 140-007-33-28=3, 	AND NEW NUT P/N 7594S820.  (X)				1	G	7	2 	3U			 	H9SW    					 
2000112900036	20001129	00036	WP  	2000	11	29	20000830SH001    	2	20000821	G	7230	30723961	DISK            	HONEYWELL   							GARRTT	TFE731	TFE7313D    	 	WP  					FWD RIM DV TAIL	CRACKED         	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		7526 	6255 				P76227			C/W NDT INSPECTION AND FOUND FORWARD RIM CRACKED IN 7 EACH PLACES AND 1 EACH DOVE TAIL CRACKED.  (X)											4	F			E6WE				 
2000112900038	20001129	00038	CE  	2000	11	29	20000830SH025    	1	20000821	G	3230	1068100111	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  										LT MAIN GEAR	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	1057C	601  				TH1777				FOUND LEFT MAIN GEAR DOWNLOCK CABLE FRAYED OVER 50 PERCENT THROUGH AT SWAGED TERMINAL ATTACHING TO LANDING GEAR ACTUATOR	.  NO EVIDENCE OF BEND OF OTHER DAMAGE TO CABLE.  DAMAGE APPEARS TO HAVE OCCURRED DURING MANUFACTURE.  INSTALLED AND RIG	GED NEW CABLE ASSY.  (X)				1	L	7	2 	3O			 	3A16    					 
2001020700209	20010207	00209	SW  	2001	2	7	20000830SH026    	1	20000815	G	6510	222044006109A	COUPLING        			BELL  	222   	222U        	1182140	SW  										DRIVE SHAFT	CORRODED        	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	111DS	85   				47554				REPLACED WITH RECONDITIONED LEFT DRIVESHAFT FROM BELL HELICOPTER.  (X)						1	G	7	2 	3U			 	H9SW    					 
2000112900039	20001129	00039	CE  	2000	11	29	20000830SH028    	1	20000804	G	3246	50300010133	WHEEL           			BEECH 	90    	C90A        	1152911	CE  										LT WHEEL BEARING	FAILED          	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	09	3220L					LJ1420				WHEN AIRCRAFT LANDED, THE RT WHEEL WABBLED ON AXLE.  JACKED AIRCRAFT AND REMOVED WHEEL WITHOUT REMOVING NUT.  FOUND SMAL	L OUTER BEARING FROZEN AND DISSINTEGRATED, AND THE INNER (LARGER) RACE SPUN IN WHEEL.  FURTHER INVESTIGATION FOUND ALL W	HEEL HALF BOLTS FINGER LOOSE.  (X)				1	L	7	2 	3T			RT	3A20    					 
2000112900040	20001129	00040	SO  	2000	11	29	20000830SH029    	1	20000721	G	3260		SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  											LACK OF LUBE    	A			BSYA	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			GL	07	35453					318052006				CLE - GOING INTO CLEVELAND AIRPORT, RT MAIN GEAR DOWN AND LOCK INOPERABLE.  CYCLED GEAR SEVERAL TIMES, LIGHT CAME ON.  C	LEANED AND LUBED DOWN AND LOCK SWITCH.  OPS CHECKED GOOD.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000112900037	20001129	00037	EA  	2000	11	29	20000830SH031    	2	20000627	G	8520	LW13212	BEARING         	LYC         		PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					NR 6	FAILED          	G				B				EMER. DESCENT           				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	01	92939	106  				4636119	L1044361A			ENGINE (106.6 HOURS SINCE NEW) FAILED WHILE AT CRUISE RESULTING IN AN EMERGENCY DESCENT AND LANDING AT ALB.  RESULTS OF 	ENGINE SERVICE TEARDOWN INSPECTION AND TECHNICAL REPORTS DATED 7/5/2000 AND 7/27/2000 FROM TEXTRON LYCOMING FOUND THE CR	ANKSHAFT ROD JOURNAL AND CONNECTING ROD BROKEN AT NR 6 CRANKPIN WITH NR 6 ROD BEARING EXTRUDED.  FACTORY TECHNICAL REPOR	T CONCLUDED THAT PRIMARY FAILURE WAS MOST LIKELY DUE TO NR 6 CONNECTING ROD BEARING FAILURE.  (THIS WAS THE 3RD FACTORY 	NEW ENGINE INSTALLED ON THIS AIRFRAME).		1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000112900041	20001129	00041	EA  	2000	11	29	20000831SH001    	2	20000830	G	7310		FUEL LINE       	PRECISION   		BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					FUEL SYSTEM	DETERIORATED    	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	11	18981	3320 	30   			MC545	L1805851A			IN CRUISE FLIGHT ENGINE RAN ROUGH, HAD LOW EGT 900DG ON NR  2 CYLINDER.  AFTER LANDING AND TROUBLESHOOTING FOUND DEBRIS 	IN FUEL LINE FROM SERVO TO FLOW DIVIDER.  REPLACED RUBBER FUEL LINE WITH TEFLON LINE P/N LW12784-4-172 IAW LYCOMING SI12	74B.  SUBMITTER SUGGESTED REPLACING  ALL FUEL AND OIL LINES WITH TEFLON TYPE.  SUSPECT FUEL LINE HAD 30 HRS SMOH.				1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2000112900042	20001129	00042	SO  	2000	11	29	20000831SH002    	1	20000718	G	3260		BULB            			PIPER 	PA31  	PA31350     	7103110	SO  											FAILED          	A			BSYA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	07	4079Y					318152079				IND - GOING INTO IND COULD NOT GET THE RIGHT GEAR LIGHT TO COME ON.  REMOVED AND REPLACED LIGHTBULB.  OPS CHECKED GOOD. 	 (X)					1	L	7	2 	3O			 	A20SO   					 
2000112900043	20001129	00043	SO  	2000	11	29	20000831SH003    	2	20000512	G	8530		INTAKE VALVE    	LYC         		PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					NR 2 CYLINDER	FRACTURED       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AL	01	5633V	649  				32R7780349	L1648648A			DURING FLIGHT, ENGINE BEGAN TO RUN ROUGH.  PILOT POWERED BACK AND MADE PRECAUTIONARY LANDING.  INSPECTION REVEALED FAILU	RE OF THE VALVE STEM ON NR 2 CYLINDER INTAKE VALVE.  THE FRACTURE IS LOCATED APPROXIMATELY .6250 INCH FROM THE TOP OF TH	E VALVE STEM NEAR THE VALVE KEEPERS.  SOME WEAR WAS DETECTED AT THE VALVE GUIDE.  (X)				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000112900044	20001129	00044	GL  	2000	11	29	20000831SH004    	1	20000723	G	5540	93004	HINGE           			AMTR  	KITFOX	KITFOXSPEEDS	05623DZ	GL  										RUDD HINGE BOLTS	FAILED          	D				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			CE	09	525PP	360  				JBS009				ALL 4 RUDDER HINGE BOLTS FAILED ON LANDING RESULTING IN LOSS OF CONTROL OF AIRCRAFT ON THE RUNWAY.  AIRCRAFT WENT OFF RU	NWAY INTO THE GRASS (LEFT SIDE RUNWAY).  AIRCRAFT THEN TAXIED TO PARKING WHERE FAILED RUDDER HINGES DISCOVERED.   REPAIR	ED BROKEN BOLTS.  (X)				1	H	7	1 	3I			NC	EXPA1H71					 
2000112900045	20001129	00045	SO  	2000	11	29	20000831SH005    	1	20000704	G	2910		B-NUT           			PIPER 	PA31  	PA31350     	7103110	SO  											LOOSE           	A			BSYA	O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			GL	07	525AA					318052111				OWB - GOING INTO OWB, COULD NOT GET LANDING GEAR DOWN.  PILOT HAND PUMPED GEAR DOWN, LANDED NO PROBLEMS.  SERVICED HYDRA	ULIC FLUID, TIGHTENED LOOSE B-NUT BACK SIDE OF HYDRAULIC SERV. PORT.  (X)					1	L	7	2 	3O			 	A20SO   					 
2001020700210	20010207	00210	SW  	2001	2	7	20000831SH006    	1	20000815	G	6510	214040659005	COUPLING        			BELL  	412   	412EP       	1182205	SW  										DRIVESHAFT	WORN            	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6379E	117  				36247				COUPLING FOUND WORN.  REPLACED WITH NEW COUPLING FROM BELL HELICOPTER.  (X).						1	G	7	2 	4U			 	H4SW    					 
2000112900046	20001129	00046	SO  	2000	11	29	20000831SH012    	2	20000803	G	7322		PUMP            			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  						LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	8260Z		46   		F189902BR	2050249	10242125			DURING POST-FLIGHT SECURING OF ACFT, PILOT NOTICED FUEL DRIPPING FROM LT COWL FLAP OPENING.  INVEST REVEALED FUEL COMING	 FROM ENGINE DRAIN LINE TRACED TO THE FUEL INJECTION PUMP.  SELECTING THE OFF POSITION OF THE FUEL SELECTOR VALVE RELIEV	ED THE FUEL TANK HEAD PRESSURE FROM THE SYSTEM AS THIS WOULD CAUSE THE LEAK TO STOP.  BEFORE REPLACING THE PUMP, A GROUN	D RUN WAS PERFORMED TO SEE IF FUEL WAS BEING LOST IN-FLIGHT.  NONE WAS OBSERVED.  THE PILOT INDICATED THE ENGINE PERFORM	ED NORMALLY DURING THE LAST FLIGHT, SO THE QUESTION AS TO WHETHER OR NOT AIR WAS BEING DRAWN INTO THE SYSTEM REMAINED UN	ANSWERED.  FUEL INJECTION PUMP REPLACED.  (X)	1	H	7	1 	3O	3	O	 	3A21    	3E1				 
2000112900047	20001129	00047	SO  	2000	11	29	20000831SH015    	2	20000831	G	8500		ENGINE          			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  						FAILED          	A			SX0A	A				UNSCHED LANDING         				J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			SO	33	165R		584  			32R7885217	L2500448A			AIRCRAFT WAS IN-FLIGHT WHEN ENGINE LOST ALL OIL PRESSURE, AND HAD A CATASTROPHIC FAILURE.  AIRCRAFT WAS ABLE TO MAKE A S	AFE OFF-FIELD LANDING WITH NO STRUCTURAL DAMAGE.  ENGINE WAS OVERHAULED ENGINE FROM LYCOMING.  ENGINE SHOPPED TO LYC FOR	 INSPECTION.  (X)				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001011104196	20010111	04196	GL  	2001	1	11	20000831SH016    	1	20000714	G	7920	632072	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					OIL FILTER CLAMP	BROKEN          	B			HBKR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	22	107CT	17   				C0107	806184			BRACKET BROKEN AT BAND.  CAUSE MAY HAVE BEEN DUE TO MISALIGNMENT WITH  MATING STRAP AT LOCATION A.  (X)						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2000112900048	20001129	00048	SO  	2000	11	29	20000831SH017    	2	20000810	G	8520	631845	CAM             			BEECH 	95    	95B55       	1152729	CE  	CONT  	O520  	IO520E      	17032	SO  					INTERNAL GEAR	STRIPPED        	B			H8AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	05	22EW					TC1058	556217			ENGINE FAILURE CAUSED BY TEETH BEING STRIPPED OFF OF CAMGEAR.  ONE TOOTH APPEARS TO HAVE BEEN FRACTURED AND THE FOLLOWIN	G 6 TEETH WERE STRIPPED.   GEAR WAS STILL PROPERLY FASTENED TO CAMSHAFT.  THE CRANKSHAFT GEAR WAS NOT DAMAGED.  NO FOREI	GN MATERIALS WERE FOUND IN CRANKCASE.  ALSO, NO RECENT WORK PERFORMED IN THIS AREA.  CAUSE OF FAILURE NOT DETERMINED.  (	X)			1	L	7	2 	3O	3	O	RT	3A16    	E5CE				 
2000112900049	20001129	00049	EA  	2000	11	29	20000831SH018    	2	20000816	G	8520	LW13885M06	BEARING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					FWD THRUST	MAKING METAL    	A			FWRA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	31657	180  				327840139	L1800548A			FOUND METAL IN OIL FILTER AND SCREEN.  FOUND FORWARD THRUST BEARING HALVES OUTER COATING ON THE INSIDE HALVES FLAKING OF	F.  (FLAKES AND CHUNKS).  PART NUMBER ON BOTH HALVES IS LW-13885-M06 1-97.  (X)					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000112900050	20001129	00050	CE  	2000	11	29	20000831SH019    	1	20000808	G	8011	643259A40	ADAPTER         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					STARTER SHAFT TE	WORN            	B			CSLR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	41106	781  				421B0589	267421			REMOVED STARTER ADAPTER FROM RIGHT POSITION FOR VISUAL INSPECTION PER TCM CRITICAL SB NR CSB94-4C, PART 3.  FOUND UNACCE	PTABLE HEAVY WEAR, SPALLING AND PITTING FULL TOOTH WIDTH.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2000112900051	20001129	00051	CE  	2000	11	29	20000831SH020    	1	20000808	G	8011	643259A40	ADAPTER         			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					SHAFT GEAR TEETH	WORN            	B			CSLR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	41106	781  				421B0589	267420R			REMOVED STARTER ADAPTER FROM LEFT POSITION FOR VISUAL INSPECTION PER TCM CRITICAL SB NR CSB94-4C, PART 3.  FOUND UNACCEP	TABLE HEAVY WEAR, SPALLING AND PITTING FULL TOOTH WIDTH PER FIGURE 6.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2000112900052	20001129	00052	CE  	2000	11	29	20000831SH021    	1	20000731	G	2820	1118	HOSE            			AYRES 	S2    	S2R         	7630202	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					FUEL SOV TO PUMP	RESTRICTED      	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4925X					2124R	P34014			HOSE INTER RUBBER EXPANDED TO RESTRICT FUEL FLOW AT FUEL SHUT-OFF VALVE.  PART TIME IN SERVICE:  281 HOURS.  REF:  S-2R 	ILLUSTRATED PARTS CATALOG FIG 2-7, ITEM 15, P/N 111-312-312-8-0070.  (X)					1	L	7	1 	3R	3	T	NC	A4SW    	E2WE				 
2001011104197	20010111	04197		2001	1	11	20000831SH024    	3	20000701	G	6110	AN660	BOLT            			AMTR  	VANSAC	RV3         	05608T7	GL  										PROPELLER	FAILED          	G				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	470RV					470				OWNER REPORTED 5 OF 6 AN 6-60 PROPELLER BOLTS FAILED IN-FLIGHT.  BOLTS SENT TO MFG, FOUND IN SPEC REASON FOR FAILURE DUE	 TO BOLTS BEING TOO LONG PREVENTING PROPER CLAMP-UP OF CRUSHPLATE AND SPINNER BULKHEAD TO CAMSHAFT FLANGE EXTENSION.  FA	ILED BOLTS SHOWED 4 TO 5 THREADS PROTRUDING FROM NUTS WITH 2 WASHERS UNDER EACH NUT.  SUBMITTER STATED TO CAUTION MECHAN	ICS NOT TO ALLOW MORE THAN 2 THREADS TO SHOW BEYOND THE NUT.  (X)			1	L	7	1 	3O			NC	EXPA1L71					 
2000101200127	20001012	00127	SO  	2000	10	12	20000831SH025    	1	20000802	G	2810	461698	FUEL CELL       			PIPER 	PA44  	PA44180     	7104402	SO  										RT WING NACELLE	LEAKING         	B			WIWR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	4144C	61014				4496020				PILOT REPORTED ON PRE-FLIGHT, FUEL WAS DRIPPING FROM THE RIGHT WING NACELLE BEHIND THE ENGINE.  UPON INSPECTION, THE FUE	L OUTLET NIPPLE HAD A SMALL HOLE.  POSSIBLE CAUSE WAS MAIN FUEL LINE IS NOT SUPPORTED IN THAT AREA AND THE GROMMET USED 	BY PIPER WAS TOO SMALL WHERE THE FUEL LINE WENT THROUGH A RIB.  VIBRATIONS FROM ENGINE POSSIBLY WORKED THE NIPPLE UNTIL 	IT DEVELOPED A HOLE.  FUEL BLADDER WAS REPLACED WITH NEW.  (X)			1	L	7	2 	3O			 	A19S0   					 
2000101200136	20001012	00136	SO  	2000	10	12	20000906SH001    	1	20000831	G	2710	6271105	PULLEY          			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	WING ROOT	FROZEN          	B				O				OTHER                   				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	15	773FT	92   				2844030	L2885451A	000220		LEFT REAR AILERON CABLE RUNNING ALONG THE OUTSIDE OF CABLE PULLEY AT WING ROOT.  NO WEAR PATTERN APPARENT ON PULLEY SLOT	 INDICATING THAT THE CABLE WAS NEVER ON THE PULLEY SINCE MANUFACTURE. THE PULLEY WAS ALSO FROZEN.  SUBMITTER STATED THEY	 HAVE FOUR NEW PA28R201 AND ONE PA44-180 ALL WITH LESS THAN 200 HOURS TIME AND ALL HAVING ASSORTED RIGGING PULLEYS THAT 	WERE FROZEN FROM THE FACTORY.  ALL OF WHICH HAVE BEEN REPLACED DURING THE FIRST 100 HOUR INSPECTION.  (X)			1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2000090800155	20000908	00155	EU  	2000	9	8	20000906SH002    	1	20000901	G	7830	MS178257	NUT             			AMD   	FALC90	FALCON900EX 	2730009	EU  										UPPER RT T/R	IMPROPER PART   	C				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	404A	300  			TRO58SL060	56				UPPER RT T/R DOOR HINGE BOLT, P/N NAS6307U-23D, HAD AN ALTERNATE PART NUMBER NUT INSTALLED, P/N MS17825-7.  THIS P/N NUT	 WAS NOT LISTED IN THE IPC (REF IPC78-30-10-10 ,ITEM 60, F12NE4753-070).  ONLY THE UPPER RT T/R HINGE BOLT HAD THE ALTER	NATE P/N NUT INSTALLED.  DURING THE FIRST ACCESS TO THIS AREA , (REMOVAL OF BOLT FOR LUBRICATION) DAMAGE WAS OBSERVED ON	 THE AFT BODY SKIN BELLOW SUPPORT ASSEMBLY P/N FGFB583842150D2.  DAMAGE APPEARED TO HAVE BEEN CAUSED BY NUT ROTATION DUR	ING INSTALLATION.  DAMAGED AREA MEASURED .60 INCH IN DIAMETER AND .030 TO .050 INCH IN DEPTH.  SUBMITTER SUGGESTED MANUF	ACTURER MAY HAVE ALLOWED DAMAGE TO BE BLENDED (REF DASSAULT STRUCTURES PROJECT NR 3557).  (X)	2	L	7	3 	4F			RT	A46EU   					 
2001020700194	20010207	00194	SW  	2001	2	7	20000907SH008    	1	20000815	G	6310	406340102101	SEAL            			BELL  	206   	206L4       	1182110	SW  										FREEWHEEL UNIT	LEAKING         	B			GS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	208FC	400  				52044				FREEWHEELING UNIT OUTPUT SEAL, BETWEEN ENGINE AND TRANSMISSION,  REPLACED WITH NEW SEAL FROM BELL HELICOPTER.  (X)						1	G	7	1 	3U			NC	H2SW    					 
2001010200001	20010102	00001	CE  	2001	1	2	20000907SH010    	1	20000822	G	5551		MOUNT           			CESSNA	172   	172R        	2072401	CE  										HORIZ STAB	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	263RE	923  				17280572				DURING ANNUAL INSPECTION, FOUND HORIZONTAL STABILIZER LOOSE AT FORWARD MOUNT BOLTS, PLAY VISIBLY NOTICEABLE AND ACCOMPAN	IED BY LOUD CREAKING NOISE.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001020700196	20010207	00196	SW  	2001	2	7	20000907SH013    	1	20000815	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAILROTOR DRIVE	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	52AZ	161  				53380				BEARING REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER.  REPLACED IAW ASB 407-00-35, NDT PER AD 2000-02-12.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020700257	20010207	00257	SW  	2001	2	7	20000907SH014    	1	20000815	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAILROTOR DRIVE	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	52AZ	161  				53380				REPLACED WITH NEW BEARINGS FROM BELL HELICOPTER.  REPLACED IAW ASB 407-00-35, NDT PER AD 2000-02-12.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020700258	20010207	00258	SW  	2001	2	7	20000907SH015    	1	20000815	G	6230	214040659005	COUPLING        			BELL  	412   	412EP       	1182205	SW  										MAIN DRIVESHAFT	WORN            	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6379E	117  				36247				REPLACED COUPLING WITH NEW FROM BELL HELICOPTER. (X)						1	G	7	2 	4U			 	H4SW    					 
2001022000165	20010220	00165	GL  	2001	2	20	20000907SH016    	3	20000822	G	6110	1A101DCM6948	FLANGE          			CESSNA	150   	150H        	2071818	CE  						MCAULY	1A101	1A101DCM    	GL  	PROPELLER	DAMAGED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6665S					15067465		G1691		PROPELLER SUBMITTER FOR REPAIR.  DURING INSPECTION, DISCOVERED THE PROPELLER MOUNTING SURFACE WAS NOT FLAT AND APPEARED 	TO HAVE BEEN NOT SEATING PROPERLY ON THE ENGINE CRANKSHAFT.  SUBMITTER STATED IT APPEARED THE PROPELLER FLANGE HAD BEEN 	HEAVILY GROUND OR SANDED DURING PREVIOUS MAINTENANCE.  (X)				1	H	7	1 	3O			 	3A19    		5	N	P918	 
2001020700259	20010207	00259	GL  	2001	2	7	20000907SH017    	2	20000829	G	7510	23064620	LINE            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE ANTI-ICE	BROKEN          	B			HY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	739NM	7879 				51124	CAE895175			WHEN TROUBLESHOOTING THE ENGINE ANTI-ICE SYSTEM, FOUND THE AIR LINE BETWEEN THE SOLENOID VALVE AND AIR VALVE HAD A BROKE	N FLARE AT THE AIR VALVE END.  THE BROKEN PIECE OF THE FLARE CAME OFF WHEN THE AIR LINE B-NUT WAS REMOVED.  7,879.4 HOUR	S ACTT.  (X)				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001010200002	20010102	00002	SO  	2001	1	2	20000907SH018    	1	20000808	G	2100	134A	COMPRESSOR      			PIPER 	PA31  	PA31310     	7103103	SO  										A/C CABIN	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	01	9007Y	3661 	1976 		5300610200	3111				PILOT DEPARTED RUNWAY AND DURING CLIMB-OUT HAD SMOKE ENTERING CABIN.  HE RETURNED TO AIRPORT AND MADE A SAFE LANDING.  A	FTER INVESTIGATION, FOUND AIR CONDITIONER BELT BURNED AND WAS A CAUSE OF THE COMPRESSOR LOCKING UP.  SERVICED WITH FREON	, OPS CHECKED, TEST FLOWN, CHECKED OK.  A NEW BELT, PN ES200333, WAS ALSO INSTALLED.  ALL TIMES ARE AIRCRAFT HOURS NOT A	CTUAL TIME ON COMPONENT.  (X)			1	L	7	1 	3O			RT	A20SO   					 
2001010200003	20010102	00003	GL  	2001	1	2	20000907SH022    	1	20000717	G	7910	632072	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					OIL FILTER TUBE	BROKEN          	B			HBKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	996CT	16   				C0096	806163			BRACKET/CLAMP BROKEN AT BOND.  SUBMITTER STATED MAY HAVE BEEN DUE TO MISALIGNMENT AT JOINT.  (X)						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2001010200004	20010102	00004	CE  	2001	1	2	20000907SH023    	1	20000802	G	7120	50910279	MOUNT           			BEECH 	99    	B99         	1154004	CE  										LT/RT ENGINE	WORN            	E			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	99CA	33953				U127				DURING ENGINE CHANGES, BOTH ENGINE TUBE FRAME MOUNTS WERE FOUND TO HAVE WEAR ON TORSION BARS BEYOND LIMITS.  THIS IS OCC	URRING DUE TO THE AFT LOWER STAINLESS FIRE SHIELD RESTING ON THE MOUNT.  THE LOCATION IS CONCEALED DUE TO THE RUBBER SEC	TION OF THE FIRE SHIELD IN THIS AREA. SUBMITTER STATED, NORMALLY, THERE IS ADEQUATE CLEARANCE BETWEEN THE FIRE SHIELD AN	D THE TORSION TUBE, BUT IF THE FIRE SHIELD IS BENT FORWARD SUCH AS DURING AN ENGINE INSTALLATION, THEN SUCH A CONDITION 	IS LIKELY TO RESULT IN CHAFING.  (X)		1	L	7	2 	3T			 	A14CE   					 
2001010200005	20010102	00005	GL  	2001	1	2	20000907SH024    	1	20000714	G	7910	632072	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  										OIL FILLER BRKT	BROKEN          	B			HBKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	904CT	17   				C0104				BRACKET BROKEN AT BAND.  SUBMITTER STATED  CAUSE MAY HAVE BEEN DUE TO MISALIGNMENT WITH MATING STRAP.  (X)						1	L	7	1 	3O			NT	TA4CH   					 
2001010200006	20010102	00006	GL  	2001	1	2	20000907SH025    	3	20000802	G	6111	B3204	SCREW           	HARTZL      		BEECH 	200   	200BEECH    	1152920	CE  						HARTZL	HCD4N3	HCD4N3A     	GL  	SET SCREW	FAILED          	B			EK2D	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	81WU					BB576		FY2131		BLADE PRELOAD ADJUSTMENT SCREW FAILED AT JAM NUT ALLOWING THE NUT TO FLOAT FREELY WITHIN THE HUB.  PILOT REPORTED OCCASI	ONAL STICKING OF THE PROPELLER.  THE CONDITION WAS CAUSED BY THE JAM NUT HANGING BETWEEN THE HUB AND THE BETA PICK-UP PL	ATE.  THE RESULTING DAMAGE TO THE HUB WAS CAUSE FOR RETIREMENT OF THE HUB.  (X)				1	L	7	2 	4T			 	A24CE   		5	C	STC	 
2001010200007	20010102	00007	SO  	2001	1	2	20000907SH026    	1	20000815	G	2421	3656624	ALTERNATOR      			PIPER 	PA28  	PA28R201    	7102816	SO  											FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			WP	05	5145W					28R7837098				NO ELECTRICAL OUTPUT.  ALTERNATOR END BELL CRACKED COMPLETELY THROUGH ONE SIDE.  ONE DIODE COPPER LEAD BROKEN IN TWO.  R	OTOR RUBBING.  ALTERNATOR OVERHAULED 3-26-90.  TOTAL TIME SINCE O/H:  920 HOURS.  (X)					1	L	7	1 	3O			 	2A13    					 
2000122000002	20001220	00002	CE  	2000	12	20	20000907SH033    	1	20000524	G	2822	476411	TRANSFER PUMP   			CESSNA	402   	402B        	207590P	CE  										TIP TANK	INOPERATIVE     	E			MHJA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	402PJ	159  				402B0591				SUBMITTER STATED THIS MODEL NUMBERED TRANSFER PUMP IS CONSISTENTLY FAILING AT 300 HOURS OR LESS CAUSING A DANGEROUS COND	ITION FOR PILOTS.  INSTALLED ON 4-5-00.  FAILED ON 5-24-00.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000122000003	20001220	00003	CE  	2000	12	20	20000907SH034    	1	20000417	G	2822	476411	TRANSFER PUMP   			CESSNA	401   	401         	207590C	CE  										TIP TANK	FAILED          	E			MHJA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3208Q	368  				4010008				SUBMITTER STATED THIS IS ONLY ONE OF MANY INCIDENTS.  THESE PUMPS ARE REPEATEDLY FAILING AROUND 300 OR LESS HOURS.  INST	ALLED ON 11-15-99.  FAILED ON 4-17-00.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000122000004	20001220	00004	CE  	2000	12	20	20000907SH035    	1	20000810	G	2822	476411	TRANSFER PUMP   			CESSNA	401   	401         	207590C	CE  										TIP TANK	INOPERATIVE     	E			MHJA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3208Q	211  				4010008				SUBMITTER STATED THIS MODEL NUMBERED TRANSFER PUMP IS CONSISTENLY FAILING AT 300 HOURS OR LESS CAUSING A DANGEROUS CONDI	TION FOR PILOTS AND INCREASED MAINTENANCE.  INSTALLED ON 5-19-00.  FAILED ON 8-10-00.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000122000005	20001220	00005	CE  	2000	12	20	20000907SH036    	1	20000803	G	2822	476411	TRANSFER PUMP   			CESSNA	402   	402B        	207590P	CE  										TIP TANK	INOPERATIVE     	E			MHJA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PJ	76   				402B0591				SUBMITTER STATED THIS MODEL NUMBERED TRANSFER PUMP IS CONSISTENTLY FAILING AT 300 HOURS OR LESS CAUSING A DANGEROUS COND	ITION FOR PILOTS AND INCREASED MAINTENANCE.  INSTALLED ON 5-22-00.  FAILED ON 6-3-00.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000122000006	20001220	00006	SO  	2000	12	20	20000907SH037    	1	20000817	G	2720	6345100	SUPPORT BRACKET 			PIPER 	PA28  	PA28140     	7102802	SO  										CROSSBAR	CRACKED         	B			JZRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	1692T	5960 				287125009				BRACKET ATTACHMENT HOLES CRACKED IN SEVERAL DIRECTIONS (4 HOLES TOTAL).  FOUND RUDDER PEDAL CROSSBAR MOVEMENT DURING ANN	UAL.  METAL FATIGUE AND LIGHT WEIGHT STEEL (.035 INCH) MAY BE CAUSE OF FAILURE.  SUBMITTER RECOMMENDED GUSSETS WELDED AT	 HOLES OF PART CONSTRUCTED FROM THICKER MATERIAL.  (X)				1	L	7	1 	3O			 	2A13    					 
2000122000007	20001220	00007		2000	12	20	20000907SH038    	4	20000512	G	6122		BEARING         	MCAULY      		CESSNA	402   	402C        	207590R	CE  										INSIDE GOVERNOR	DESTROYED       	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			EA	07	548GA	1299 			791519	402C0653				PILOT REPORTED LOSS OF POWER ON TAKEOFF.  MAINTENANCE FOUND PROPELLER GOVERNOR LEAKING OIL AND CONFIRMED POWER LOSS.  CH	ANGED GOVERNOR AND RETURNED AIRCRAFT TO SERVICE.  TEAR DOWN OF GOVERNOR REVEALED INTERNAL FAILURE CAUSED BY BEARING FAIL	URE.  (X)				1	L	7	2 	3O			 	A7CE    					 
2001010200008	20010102	00008	CE  	2001	1	2	20000907SH039    	1	20000814	G	3244	650108PLY	TIRE            			CESSNA	402   	402C        	207590R	CE  										LEFT MAIN	UNSERVICEABLE   	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	07	4652N		99   		62140615	402C0011				CREW REPORTED UNUSUAL NOISE ON TAXI.  FOUND CHUNK OF AFT TIRE MISSING.  MAINTENANCE DISPATCHED TO CHANGE TIRE.  FOUND LA	RGE PORTION OF RECAP HAD SEPARATED FROM CORE TIRE.  MAINTENANCE REMOVED AND REPLACED TIRE AND RELEASED AIRCRAFT BACK INT	O SERVICE.  (X)				1	L	7	2 	3O			 	A7CE    					 
2001022000260	20010220	00260		2001	2	20	20000907SH040    	4	20000810	G	6122	D20591	DRIVE GEAR      	MCAULY      		CESSNA	180   	180         	2072602	CE  										PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					70634					RELEVANT MT INDICATION AROUND GEAR TEETH.  (X)						1	H	7	1 	3O			NC	5A6     					 
2000101200003	20001012	00003	SO  	2000	10	12	20000908SH001    	1	20000907	G	2842		SENSOR          			PIPER 	PA28  	PA28161     	7102803	SO  											MISINSTALLED    	H			OG5S	K				NONE                    				W			INADEQUATE Q C            			CR	CRUISE         	1			GL	21	275ND					2842097				PILOT REPORTED FUEL SELECTOR DRAW WAS FROM OPPOSITE TANK SELECTED.  TROUBLESHOOTING BY MAINTENANCE FOUND THE WIRES FROM 	THE FUEL TANK SENDER WERE SWAPPED AT THE INDICATORS.  WIRES WERE REMOVED AND REINSTALLED PER THE MANUFACTURER''S WIRE DI	AGRAM.  SYSTEM FUNCTIONED NORMALLY.  (SUBMITTED BY FAR-FSDO FROM FORM 8010-4 SUPPLIED BY OPERATOR).  (X)				1	L	7	1 	3O			 	2A13    					 
2000101900117	20001019	00117	SO  	2000	10	19	20000908SH002    	1	20000907	G	7603	554528	THROTTLE CABLE  			PIPER 	PA44  	PA44180     	7104402	SO  										RIGHT	SEPARATED       	B			OG5S	D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			GL	21	292ND	1311 				4496023				AFTER TAKEOFF DURING POWER REDUCTION, RIGHT THROTTLE WOULD NOT DECREASE BELOW 20 INCHES MANIFOLD PRESSURE. AIRCRAFT RETU	RNED TO BASE UNEVENTFULLY.  INSPECTION REVEALED THROTTLE CABLE SEIZED AT ENGINE SIDE WHERE CABLE EMERGES FROM OUTER SHEA	TH. THE OUTER SHEATH HAD SEPARATED AT FLEXIBLE SWEDGE THAT ALLOWED INCREASE OF THROTTLE POSTION BUT LIMTED RETARDING TO 	20 INCHES MANIFOLD PRESSURE. CABLE REPLACED AND AIRCRAFT RETURNED TO SERVICE.  (SUBMITTED BY FAR-FSDO FROM INFORMATION O	N FORM 8010-4 SUPPLIED BY OPERATOR).  (X)		1	L	7	2 	3O			 	A19S0   					 
2000122000008	20001220	00008	EA  	2000	12	20	20000908SH003    	2	20000817	G	8530	LW11625	PLUG            	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	67719	728  				15281981	L2438215			AN EXCESSIVE AMOUNT OF ALUMINUM WAS FOUND IN THE OIL SCREEN DURING A 50-HOUR INSPECTION.  THE METAL WAS SENT TO LYCOMING	 FOR EVALUATION AND IT WAS DETERMINED TO BE FROM THE PISTON PIN PLUGS.  ALL CYLINDERS WERE REMOVED AND ALL PLUGS SHOW EX	CESSIVE WEAR TO VARYING DEGREES.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS A DEFECT IN THE METAL USED TO FABRICATE THE END 	PLUGS.  (X)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000122000009	20001220	00009	SO  	2000	12	20	20000908SH004    	1	20000908	G	8100	AM52192037	CLAMP           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					VOSS CLP THREADS	STRIPPED        	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	84859	1500 				317305043				CLAMP AND NUT THREADS SEPARATED CAUSING CLAMP TO SPRING OPEN.  THUS, HIGH PRESSURE TURBO AIR LEAKED OVERBOARD CAUSING MA	NIFOLD PRESSURE TO DROP TO 25 POUNDS (NATURALLY ASPIRATED).  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000122000010	20001220	00010	CE  	2000	12	20	20000908SH005    	1	20000802	G	2410	S159660L	CIRCUIT BREAKER 			CESSNA	172   	172M        	2072418	CE  										BREAKER PANEL	INOPERATIVE     	D				A				UNSCHED LANDING         				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		NR	NOT REPORTED   	1			NM	11	9912Q	5673 				17265856				PILOT DEPARTED BOISE, NOTICED SMOKE IN THE COCKPIT AND RETURNED FOR LANDING.  ALTERNATOR CIRCUIT BREAKER FAILED (DUE TO 	AGE).  NO OTHER DAMAGE FOUND.  (X)					1	H	7	1 	3O			NT	3A12    					 
2000122000011	20001220	00011	CE  	2000	12	20	20000908SH006    	1	20000814	G	2750	0510105122	CONTROL CABLE   			CESSNA	185   	A185F       	2072821	CE  										TE FLAPS	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	4892E	2500 				18503897				CABLE PARTED .25 INCH AFT OF MS20668-3 SWAGED TERMINAL EYE END FITTING, IN AN AREA VERY DIFFICULT TO INSPECT VISUALLY, C	AUSING SUDDEN FLAP RETRACTION.  SUBMITTER RECOMMENDED PERIODIC INSPECTION EVEN IF IT REQUIRES REMOVAL OF THE CABLE.  SUB	MITTER STATED DESIGN OF INSTALLATION MAY CAUSE BEND IN CABLE IMMEDIATELY ADJACENT TO RIGID END FITTING.  (X)				1	H	7	1 	3O			 	3A24    					 
2000122000012	20001220	00012	SO  	2000	12	20	20000908SH008    	2	20000815	G	7414	TCM10382584	POINTS          			CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  						FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	527NR	184  				U2060278				DURING PRE-INSPECTION RUN-UP BY MECHANIC, FOUND UNUSUAL MAG DROP ON RIGHT MAGNETO REMOVED FOR TROUBLESHOOTING.  FOUND TH	E POINT ASSY CONTACT LOOSE AND FALLING OUT OF SPRING ARM.  REPLACED CONTACT ASSY.  OPS CHECKED GOOD.  THIS MAG HAD 184 H	OURS SINCE A TCM OVERHAUL.  THE MAGNETOS CAME ON A RECENTLY OVERHAULED TCM IO520 ENGINE.  (X)				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000122000013	20001220	00013	CE  	2000	12	20	20000908SH009    	1	20000827	G	2810		FUEL CAP        			BEECH 	18    	D18S        	1151004	CE  	GARRTT	TPE331	TPE33110    	01514	WP  						LEAKING         	E			KKFA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	502CK	14825	12165			A366	P93049C			RIGHT ENGINE SLOWLY ROLLED BACK AND SHUT-DOWN.  REMOVED WATER CONTAMINATION FROM FUEL SYSTEM AND TANKS.  REPLACED ENGINE	 FUEL FILTER WITH NEW.  REPLACED RIGHT MAIN TANK FUEL CAP WITH NEW.  PEFORMED GROUND RUN, LEAK AND PERFORMANCE CHECK IAW	 GARRETT RUN-UP FORM TTF-0052.  (X)				1	L	7	2 	3R	4	T	 	A765    	E4WE				 
2000122000014	20001220	00014		2000	12	20	20000908SH010    	4	20000815	G	6122	B20908	FLYWEIGHT       	MCAULY      							CONT  	O520  	IO520*      	17032	SO  						FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					790153					RELEVANT INDICATION ACROSS FLYWEIGHT BODY.  (X)											3	O			E5CE				 
2001010200009	20010102	00009	SO  	2001	1	2	20000908SH011    	2	20000731	G	7414	1052948	ROTOR           		S6RN201     	CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470L       	17026	SO  					ROTOR BEARINGS	OVERHEATED      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	9103X		467  		K279618ER	18253503	819441L4			MAGNETO DISASSEMBLED FOR 500-HOUR MAINTENANCE, BALL BEARINGS, PN 1081806 AND PN 2202, FROM ROTATING MAGNET ASSY WERE OBS	ERVED TO HAVE A SMOKY-BLUE CAST.  ROTOR WAS RE-ASSEMBLED IN CASE HALVES TO FACILITATE SHAFT END PLAY CHECK WITH DIAL IND	ICATOR.  PER SERVICE MANUAL, 30 POUNDS OF FORCE WAS EXERTED ON ROTOR SHAFT IN EACH DIRECTION - NO PERCEPTIBLE NEEDLE REF	LECTION RESULTED.  SM SPECIFIES INITIAL ROTOR SHAFT END PLAY SHOULD BE FROM 0.0005 INCH TO 0.0015 INCH LOOSE TO OBTAIN P	ROPER BEARING PRELOAD.  BY REMOVING SHIMS AND RE-CHECKING END PLAY, IT WAS DETERMINED ROTOR BEARINGS WERE UNDER A COMPRE	SSION LOAD OF APPROXIMATELY 0.003 INCHES.  (X)	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001011104203	20010111	04203		2001	1	11	20000908SH012    	1	20000821	G	2560	EAMT46	LIFE RAFT       																		MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EU	01	OCVYD									TEMPORARY PACKING TIE HAD BEEN LEFT ON THE PACKED LIFE RAFT.  SUBMITTER STATED THIS WOULD HAVE PREVENTED DEPLOYMENT.  DI	SCOVERED WHEN RAFT WAS RECEIVED FOR OVERHAUL.  THE MANUFACTURE DATE WAS NOVEMBER, 1998,																		 
2001020700260	20010207	00260	EU  	2001	2	7	20000908SH013    	1	20000831	G	6710		BUSHING         			SNIAS 	350   	AS350B3     	8680954	EU  										MAIN ROTOR	SEIZED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	392LG					3252				FOUND BUSHINGS LOCKED UP CAUSING DAMAGE TO THE SCISSORS HOUSING, PN 350A37-1126-02.  FOUR NEW PARTS DID THE SAME THING. 	 PARTS FROM ANOTHER AIRCRAFT WORKED OK.  THE NEW PARTS WERE DAMAGED IN 2-5 HOURS.  POSSIBLE CAUSE IS BUSHINGS IN THE NEW	 PARTS MAY HAVE BEEN MISALIGNED.  (X)				1	G	7	1 	3U			 	H9EU    					 
2001020700262	20010207	00262	SW  	2001	2	7	20000911SH003    	1	20000619	G	6320	206040221003	SHAFT           			BELL  	206   	206B3       	1181506	SW  										FREEWHEEL UNIT	WORN            	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	GPGH	2976 				4022				DURING OVERHAUL INSPECTION, DISCOVERED BEARING OUTBRACE HAD ROTATED IN HOUSING.  EXCESSIVE WEAR IN HOUSING INSIDE DIAMET	ER.  WILL C/W BELL TECH BULLETIN 206-95-155 THAT INSTALLS SLOTTED OUTER SHAFT WITH KEYED BEARING WHICH IS TO CORRECT THE	 BEARING ROTATION PROBLEM.  (X)				1	G	7	1 	3U			 	H2SW    					 
2001030100005	20010301	00005	EA  	2001	3	1	20000911SH004    	2	20000821	G	7414	4271	MAGNETO         								LYC   	O320  	O320B2B     	41508	EA  					ENGINE	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09		590  					L345027			ENGINE WOULD NOT START NORMALLY.  COIL IN MAGNETO SHOWING OPEN.  THIS LEFT MAG OPENED AND REPLACED, FAULTY COIL (NUMBER 	ON COIL, M3525 0310).										3	O			E274				 
2001030100006	20010301	00006	EA  	2001	3	1	20000911SH005    	2	20000821	G	7414	4270	MAGNETO         								LYC   	O320  	O320B2B     	41508	EA  					ENGINE	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09		590  					L345027			ENGINE RAN OKAY.  MAGNETO DISASSEMBLED AS PRECAUTIONARY.  FOUND COIL OUT OF LIMITS WITH VERY HIGH RESISTANCE ON SECONDAR	Y CIRCUIT.  (COIL NR 5, M3525 011989).  (X)										3	O			E274				 
2001030100007	20010301	00007	EA  	2001	3	1	20000911SH010    	2	20000828	G	8500	C4170	GEAR            	HARTZL      							LYC   	O540  	IO540*      	41532	EA  					IDLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6100				E244U					RELEVANT MAG PARTICLE INDICATION ON GEAR TEETH.  (X)											3	O			1E4				 
2001030100008	20010301	00008	EA  	2001	3	1	20000911SH011    	2	20000828	G	8500	C4170	GEAR            	HARTZL      							LYC   	O540  	IO540*      	41532	EA  					IDLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B440U					RELEVANT MAG PARTICLE INDICATION ON IDLER GEAR TEETH.  (X)											3	O			1E4				 
2001030100009	20010301	00009	EA  	2001	3	1	20000911SH012    	2	20000828	G	8500	B41832	FLYWEIGHT       	HARTZL      							LYC   	O540  	IO540*      	41532	EA  					GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B4401U					RELEVANT MAG PARTICLE INDICATION ON FLYWEIGHT TOE.  (X)											3	O			1E4				 
2001020700263	20010207	00263	SW  	2001	2	7	20000911SH013    	1	20000809	G	5302	206033412121A	BRACKET         			BELL  	206   	206L1       	1182107	SW  										TAIL BOOM	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WHILE FITTING NEW BEARING SUPPORT BRACKET ON TAILBOOM, DISCOVERED CONTOUR WAS NOT CORRECT, TABS WERE OVER BENT AND UNDER	 BENT.  (X)					1	G	7	1 	3U			 	H2SW    					 
2001020700264	20010207	00264	SW  	2001	2	7	20000911SH014    	1	20000809	G	5302	206033412119A	BRACKET         			BELL  	206   	206L1       	1182107	SW  										TAIL BOOM	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DURING FITTING NEW BEARING SUPPORT BRACKET ON TAILBOOM, DISCOVERED CONTOUR WAS NOT CORRECT, THE TABS WERE OVER BENT AND 	UNDER BENT.  (X)					1	G	7	1 	3U			 	H2SW    					 
2001020700265	20010207	00265	SW  	2001	2	7	20000911SH015    	1	20000809	G	5302	206033412001A	BRACKET         			BELL  	206   	206L1       	1182107	SW  										TAIL BOOM	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DURING FITTING BEARING SUPPORT BRACKET ON TAILBOOM, DISCOVERED CONTOUR WAS NOT CORRECT, THE TABS WERE OVER BENT AND UNDE	R BENT.  (X)					1	G	7	1 	3U			 	H2SW    					 
2001030100010	20010301	00010	GL  	2001	3	1	20000911SH017    	3	20000823	G	6111		HUB             	MCAULY      												MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	DAMAGED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17								738532		RELEVANT ET INDICATION, 4TH THREAD UP.  (X)																5	C	P3EA	 
2000120600002	20001206	00002	SO  	2000	12	6	20000911SH018    	1	20000829	G	3244	175X625610P	TIRE            			PIPER 	PA42  	PA42        	7104202	SO  										NOSE	SHEARED         	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	11	112BC	82   				428001027				TIRE SHREADED ON LANDING.  (X)						1	L	7	2 	4T			 	A23SO   					 
2000120600003	20001206	00003	EA  	2000	12	6	20000911SH019    	2	20000816	G	8500		ENGINE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  						MAKING METAL    	B			AMYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	12KW	139  				4636255	L1040961A			DURING OIL CHANGE AND OIL FILTER INSPECTION, FOUND METAL IN THE OIL FILTER AND METAL WAS FOUND IN THE SUCTION SCREEN.  5	0 TO 60 PIECES WERE FOUND IN OIL FILTER AND TWO FLAKES WERE FOUND IN THE SUCTION SCREEN.  (X)					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000120600004	20001206	00004	NE  	2000	12	6	20000911SH020    	2	20000821	G	7220	3018018	RIVET           	PWA         		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT ENGINE INLET	MISSING         	A			UG8A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	225J					5500283	PCE70878			RIVET MISSING IN LEFT ENGINE INLET AND ONE FAN BLADE HAD SMALL CURL AT LEADING EDGE TIP.  REPLACED MISSING RIVET, INSPEC	TED AND REPAIRED FAN ASSEMBLY.  (X)					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000120600005	20001206	00005	SO  	2000	12	6	20000911SH021    	1	20000826	G	2400	A002581	SWITCH          			PIPER 	PA38  	PA38112     	7103812	SO  										UNDER RT VNT PNL	SHORTED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2408L					3879A0696				DURING LEVEL FLIGHT WITH NORMAL ELECTRICAL LOAD, ALTERNATOR INOP SWITCH INTERNALLY SHORTED.  THE UNIT WAS SEALED.  CAUSE	 IS MOST LIKELY THE AGE OF PART AND NORMAL DEGRADATION OF INTERNAL CIRCUITRY.  (X)					1	L	7	1 	3O			 	A18SO   					 
2000120600006	20001206	00006	SO  	2000	12	6	20000911SH022    	1	20000823	G	3230	2075209	HOUSING         			PIPER 	PA30  	PA30        	7103002	SO  										RT GEAR	BROKEN          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	07	282P					30508				AFT SUPPORTING PORTION OF THE RIGHT GEAR HOUSING BROKE AND ALLOWED THE POSITION TO SHIFT WHICH CAUSED IT TO HANG UP IN T	HE WHEELWELL.  AIRCRAFT LANDED GEAR UP BECAUSE GEAR COULD NOT BE EXTENDED USING ELECTRIC MOTOR OR MANUAL LEVER.  HAD TO 	PRY GEAR OUT OF WHEELWELL DURING RECOVERY.  (X)				1	L	7	2 	3O			 	A1EA    					 
2000120600008	20001206	00008	SO  	2000	12	6	20000911SH024    	1	20000812	G	7921	20006A	OIL COOLER      			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  						LEAKING         	D				K				NONE                    				K	A		FLUID LOSS                	FLAME/FIRE                		CR	CRUISE         	1			GL	23	38984					32R7780495	L1688448A			PILOT DEPARTED AIRPORT.  DURING CLIMB APPROXIMATELY 2 MINUTES INTO FLIGHT, NOTICED NO OIL PRESSURE INDICATION.  QUICKLY 	RETURNED TO DEPARTURE AIRPORT.  ENGINE FAILED ON FINAL DUE TO OIL STARVATION.  A SAFE LANDING WAS MADE.  ENGINE SEIZED A	ND THREW PARTS THROUGH CRANKCASE.  UPON INVESTIGATION, OIL COOLER WAS FOUND TO HAVE PIN-HOLE IN BOTTOM.  THIS COOLER WAS	 NEW 1 YEAR AND 117 HOURS PRIOR.  INSTALLED IAW LO-PRESTI COWLING MODIFICATION.  (X)			1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000120600009	20001206	00009	CE  	2000	12	6	20000911SH025    	2	20000813	G	7322	RSA5AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						FAILED          	B			VJ3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			WP	07	4128X					3449112	819255R			ON LANDING , LEFT ENGINE LAGGED POWER TO LANDING.  THE RPM DROPPED FROM 2,400 TO 1,800.  THROTTLE POWER TO 22 INCHES.  (	X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000120600010	20001206	00010	SO  	2000	12	6	20000911SH026    	1	20000815	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	VJ3R	1341 				2843207				AILERON BALANCE CABLE FRAYED.  LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600011	20001206	00011	SO  	2000	12	6	20000911SH027    	1	20000821	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										AILERON	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4139A	2142 				2843115				AILERON BALANCE CABLE FRAYED.  LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600012	20001206	00012	SO  	2000	12	6	20000911SH028    	1	20000821	G	2740	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4139A	5142 				2843115				STABILATOR CONTROL CABLE FRAYED.  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600013	20001206	00013	SO  	2000	12	6	20000911SH029    	1	20000824	G	2710	62701125	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	2297 				3449046				LEFT HAND BALANCE CABLE FRAYED, NEW CABLE INSTALLED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000120600014	20001206	00014	SO  	2000	12	6	20000911SH030    	1	20000823	G	2750	87765041	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										TE FLAPS	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	2292 				3449046				FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLYS AT THE FLAP SELECTOR.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000120600015	20001206	00015	SO  	2000	12	6	20000911SH031    	1	20000823	G	2740	62701047	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4166H					2843119				AFT STABILATOR TRIM CABLE FRAYED.  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600016	20001206	00016	SO  	2000	12	6	20000911SH032    	1	20000821	G	2700	6270147	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4144P	1990 				2843121				TRIM CABLE FRAYED AT REAR DRUM.  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600017	20001206	00017	SO  	2000	12	6	20000911SH033    	2	20000821	G	7322	RSA5AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						FAULTY          	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	41   				3449128	322021RN			ENGINE RUNNING RICH AND BLOWING BLACK SMOKE.  UNABLE TO ADJUST MIXTURE.  REMOVED AND SENT BACK TO TCM.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000120600018	20001206	00018	CE  	2000	12	6	20000911SH034    	2	20000727	G	7322	RSA3AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						FAULTY          	B			VJ3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			WP	07	4128X	158  				3449112	819255R			WILL NOT IDLE UNLESS BOOST PUMP IS ON, MIXTURE TOO LEAN.  SERVO REMOVED AND SENT BACK TO TCM.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000120600019	20001206	00019	SO  	2000	12	6	20000911SH035    	1	20000825	G	2740	62701104	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STAB TRIM	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4132D	1242 				2843234				TRIM CABLE FRAYED (FRONT CABLE AT TRIM WHEEL).  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600020	20001206	00020	SO  	2000	12	6	20000911SH036    	1	20000725	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4132D	1144 				2843234				RIGHT HAND AILERON BALANCE CABLE FRAYED.  LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000120600021	20001206	00021	SO  	2000	12	6	20000911SH037    	1	20000815	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	1694 				3449042				RIGHT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000120600022	20001206	00022	SO  	2000	12	6	20000911SH038    	1	20000815	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	1694 				3449042				LEFT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000120600023	20001206	00023	SO  	2000	12	6	20000911SH039    	1	20000815	G	2750	8776541	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										SELECTOR FLAP	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	1694 				3449042				FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLEYS AT THE FLAP SELECTOR.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000120600024	20001206	00024	CE  	2000	12	6	20000911SH040    	2	20000821	G	7322	RSA5AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						FAULTY          	B			VJ3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			WP	07	4123C					3449042	819258R			UNABLE TO ADJUST FUEL FLOW AT IDLE.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000120600001	20001206	00001	SO  	2000	12	6	20000911SH041    	2	20000828	G	8540	35016	GEAR            	TELEDYNECNTL		PIPER 	PA18  	PA18        	7101802	SO  	CONT  	C90   	C908F       	17009	SO  					CRANK SHAFT	FRACTURED       	G				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y	Z		ENGINE STOPPAGE           	SIGNIFICANT FAILURE REPORT		IN	INSP/MAINT     	1			EA	01	3357A	3418 	25   			183004	4065788			AIRCRAFT MADE AN EMERGENCY LANDING FOLLOWING SUDDEN ENGINE FAILURE DURING CRUISE FLIGHT.  UPON INSPECTION, THE CRANKSHAF	T GEAR HAD 5 OR 6 TEETH MISSING AND THE REMAINING TEETH WERE ROUNDED AND EXHIBITED GALLING-LIKE DAMAGE SIMILAR TO THAT F	OUND ON THE MAGNETO DRIVE GEARS.  ALSO THERE WAS SOME GOUGING IN THE REAR HOUSING AREA, ADJACENT TO THE CRANKSHAFT GEAR.	  AN ENGINE OVERHAUL WAS COMPLETED DURING THE LAST ANNUAL INSPECTION ON 2/5/2000, AND SINCE HAD ACCUMULATED ONLY 25.3 HO	URS.  (X)		1	H	7	1 	3O	3	O	 	1A2     	E252				 
2000120600025	20001206	00025		2000	12	6	20000911SH042    	4	20000824	G	6122	A153A2	FLYWEIGHT       	HARTZL      							LYC   	O540  	IO540*      	41532	EA  						DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B2405U					RELEVANT MAG PARTICLE INSPECTION INDICATION AT BOTTOM OF FLYWEIGHT BASE.  (X)											3	O			1E4				 
2000120600026	20001206	00026	EA  	2000	12	6	20000911SH044    	2	20000816	G	8520	LW13383	BAFFLE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					FWD VERT DEFLECT	MISALIGNED      	B			AMYR	O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	05	4170K	26   				4636297	L1056061A			ENGINE OIL QUICK DRAIN WOULD NOT SHUT OFF DUE TO ONE SHEARED OFF RIVET HEAD, MS 20470-4, BLOCKING HOLE IN DRAIN VALVE.  	REF LYC SB 489A.  OIL SUMP BAFFLE ASSY HAD THE VERTICAL DEFLECTOR FLANGE MISALIGNED TO BAFFLE PLATE AND THE TENSION LOAD	 POPPED THE RIVET HEAD OFF.  RIVET LOCATED AT AFT END OF FORWARD VERTICAL DEFLECTOR.  (X)				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001011104205	20010111	04205	CE  	2001	1	11	20000911SH045    	1	20000821	G	3411	10220001812	ALTIMETER       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550*      	 	SO  					INSTRUMENT PANEL	STUCK           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	4805					18504432				ALTIMETER STICKING EXCESSIVELY 500-600 FEET.  THIS AIRCRAFT WAS PITOT STATIC TESTED THE DAY BEFORE THE  FLIGHT FROM PLAC	ERVILLE CA TO WHITEMAN AIRPARK.  THIS ALTIMETER HAS AN INTERNAL ENCODER.  THE PITOT STATIC CASE WAS ORDERED TO BE C/W PR	IOR TO CLOSURE OF THE SALE OF THIS ACFT.  THE ANNUAL WAS SIGNED OFF WITH NO PITOT STATIC TEST C/W.  (X)				1	H	7	1 	3O	3	O	 	3A24    	E3SO				 
2000120600027	20001206	00027	CE  	2000	12	6	20000911SH046    	1	20000831	G	3250	051010552	CONTROL CABLE   			CESSNA	185   	185F        	2072820	CE  										TAIL WHEEL STEER	WRONG PART      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	4805					18504432				AIRCRAFT WAS SOLD WITH TWO DIFFERENT SIZED TAILWHEEL STEERING CABLES (LEFT CABLE WAS 60 INCHES LONG AND THE RIGHT CABLE 	WAS 58.50 INCHES LONG), AND THE .1250 INCH CABLE STAYS WERE REPLACED WITH .0625 INCH DIAMETER SOFT COTTER KEYS WHICH CAU	SED EXCESSIVE TAIL WHEEL SHIMMY UPON THE FIRST LANDING OF THIS AIRCRAFT BY THE NEW OWNER.  THIS AIRCRAFT WAS SOLD WITH A	 NEW ANNUAL.  (X)			1	H	7	1 	3O			 	3A24    					 
2000100300046	20001003	00046	CE  	2000	10	3	20000912SH001    	1	20000731	G	3230	S217840096	HOSE            			CESSNA	182   	R182        	2072734	CE  										NOSE GEAR	SEPARATED       	D				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			GL	09	4629S					R18201361				HOSE SEPARATED AT SWAGED END CAUSING LOSS OF FLUID AND NOSE GEAR TO FALL INTO AIRSTREAM.  CESSNA INSPECTION CHECKLIST CA	LLS OUT FOR THIS HOSE ALONG WITH REST OF LANDING GEAR HOSES TO BE REPLACED ON CONDITION FOR THIS AIRCRAFT.  SUBMITTER RE	COMMENDED CHANGING REQUIREMENT TO 5 TO 8 YEAR LIFE ON THESE HOSES.  (X)				1	H	7	1 	3O			RT	3A13    					 
2001020100044	20010201	00044	SW  	2001	2	1	20000912SH002    	1	20000614	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467AL	126  			A263	53190				TAIL ROTOR DRIVESHAFT IN FOR REPAIR OF RIVET MISSING FROM OIL COOLER BLOWER HOUSING.  FOUND BEARING ROUGH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020100045	20010201	00045	SW  	2001	2	1	20000912SH003    	1	20000614	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467AL	126  			A263	53190				TAIL ROTOR DRIVESHAFT IN FOR REPAIR OF RIVET MISSING FROM OIL COOLER BLOWER HOUSING.  FOUND BEARING ROUGH.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020100046	20010201	00046	SW  	2001	2	1	20000912SH004    	1	20000729	G	5302		STRUCTURE       			BELL  	407   	407         	       	SW  										TAIL BOOM	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	2747 	1406 		53207	53172				DURING DAILY SERVICE CHECK AND AD 2000-06-10/ASB 407-99-29 REVISION A, FOUND CRACK IN TAILBOOM SKIN FROM UNDER THE HORIZ	ONTAL STABILIZER SUPPORT TO THE FIRST RIVET ABOVE THE SUPPORT.  LOCATION LEFT AFT OF THE HORIZONTAL STABILIZER AT THE FO	RMER BOOM STA 120.75.  (X)				1	G	7	1 	3U			O	H2SW    					 
2001020700266	20010207	00266	SW  	2001	2	7	20000912SH005    	1	20000721	G	2810	206362002103	FUEL CAP        			BELL  	407   	407         	       	SW  										FUEL CELL	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	427AL	4309 				53107				DURING DAILY INSPECTION, FOUND FUEL CAP LEAKING, CRACKED AT LOCKING MECHANISM.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020700267	20010207	00267	SW  	2001	2	7	20000912SH006    	1	20000808	G	6322	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	587AL	272  				53248				DURING DAILY INSPECTION, FOUND A CRACK IN THE CORNER.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020100047	20010201	00047	EU  	2001	2	1	20000912SH007    	1	20000806	G	2612		WIRE            			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 ENGINE	BROKEN          	A			ALGA	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			SW	03	501AL					S58				IN CRUISE FLIGHT, NR 1 ENGINE FIRE LIGHT ILLUMINATED.  FOUND AND REPAIRED BROKEN WIRE.  (X)						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001020100048	20010201	00048	NE  	2001	2	1	20000912SH008    	1	20000815	G	3260		WARNING LIGHT   			SKRSKY	S76   	S76A        	8143006	NE  										MLG	ILLUMINATED     	A			ALGA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	519AL					760058				BEFORE LANDING, UNSAFE GEAR INDICATION, (LEFT MAIN, NO GREEN, RED STAYED ON).  RECYCLED GEAR AND ALL GREEN LIGHTS ILLUMI	NATED.  VISUALLY CHECKED GEAR AND SWITCHES.  NO DEFECTS WERE NOTED.  (X)					1	G	7	2 	3U			 	H1NE    					 
2001021600036	20010216	00036	SO  	2001	2	16	20000912SH009    	2	20000824	G	8520	631716	CRANKSHAFT      			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					ENGINE	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			EA	01	5256W	3054 	1254 			P21000664	51391			ENGINE FAILED AFTER TAKEOFF RESULTING IN FORCED LANDING.  INSPECTION OF ENGINE REVEALED CRANKSHAFT FAILED BETWEEN THE NR	 2 AND NR 3 JOURNALS.  (X)					1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001021600037	20010216	00037	SO  	2001	2	16	20000912SH010    	1	20000828	G	2910	3152700	HYDRAULIC LINE  			PIPER 	PA23  	PA23250     	7102308	SO  										LT OF PILOT SEAT	CHAFED          	B			HI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	500KW					277405264				UPON INSP, FOUND THE LEFT RUDDER CABLE CHAFING ON HYD LINE ATTACHED TO THE LEFT LANDING GEAR SEQ VALVE .  THE CABLE HAD 	CHAFED THRU APPROX 50 PERCENT OF THE HYD LINE OVER A 2 INCH AREA.  LOCATION OF AREA IS BEHIND THE PANEL ON THE LEFT SIDE	 OF THE PILOT SEAT.  THE LINE IS ON THE BOTTOM OF A GROUP OF LINES WHICH ARE SECURED TOGETHER BY STAND-OFF LACING.  RUDD	ER CABLE IS ROUTED SLIGHTLY DIAGONALLY BELOW HYD LINE.			1	L	7	2 	3O			 	1A10    					 
2001020100049	20010201	00049	SW  	2001	2	1	20000912SH011    	1	20000720	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL	396  			A1729	53366				DURING 25-HOUR AD INSPECTION, FOUND AFT SEGMENT CRACKED IN 3 PLACES ACROSS THE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020700268	20010207	00268	SW  	2001	2	7	20000912SH012    	1	20000802	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL				A1673	53366				DURING 25-HOUR AD INSPECTION, FOUND AFT SEGMENT CRACKED ACROSS THE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020700269	20010207	00269	SW  	2001	2	7	20000912SH013    	1	20000809	G	6320	406040029101	SUN GEAR        			BELL  	407   	407         	       	SW  										TRANSMISSION	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	607AL	2158 			A273	53264				TRANSMISSION ASSEMBLY MAKING  METAL.  SUN GEAR UPPER TEETH PITTED (BREAKING DOWN).  SUN GEAR SCRAPPED.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020100050	20010201	00050	SW  	2001	2	1	20000912SH014    	1	20000806	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL	124  			A1176	53284				DURING 25-HOUR AD INSPECTION, FOUND AFT SEGMENT IS CRACKED ACROSS THE SPAN IN TWO PLACES 180 DEGREES APART.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020100051	20010201	00051	SW  	2001	2	1	20000912SH015    	1	20000722	G	5754	407023801133	BRACKET         			BELL  	407   	407         	       	SW  										SLATS	CRACKED         	A			ALGA	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	03	647AL	554  				53357				PILOT NOTICED THE LEFT CENTER SLAT MISSING AFTER LANDING AND SHUT-DOWN AT OFFSHORE PLATFORM MC268.  MOUNTING BRACKETS FO	R THE LEFT CENTER SLAT WERE CRACKED AND BROKEN ALLOWING SLAT TO DEPART THE AIRCRAFT.  LEFT VERTICAL FINLET WAS DAMAGED B	Y THE MISSING SLAT.  (X)				1	G	7	1 	3U			O	H2SW    					 
2001020100052	20010201	00052	SW  	2001	2	1	20000912SH016    	1	20000722	G	5754	407023801131	BRACKET         	BELL        		BELL  	407   	407         	       	SW  										SLATS	CRACKED         	A			ALGA	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	03	647AL	554  				53357				AFTER LANDING AND SHUT-DOWN AT OFFSHORE PLATFORM MC268.  MOUNTING BRACKETS FOR THE LEFT CENTER SLAT WERE CRACKED AND BRO	KEN ALLOWING SLAT TO DEPART THE AIRCRAFT.  LEFT VERTICAL FINLET WAS DAMAGED BY THE MISSING SLAT.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001021600038	20010216	00038	CE  	2001	2	16	20000912SH017    	1	20000822	G	2822	DO299038R	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	LEAKING         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	6311Z	1036 				CE997	813765R			WHEN HOT, THERE WAS NO PRESSURE, AND FUEL LEAKED OUT OF DRAIN.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001020800969	20010208	00969	SW  	2001	2	8	20000912SH018    	1	20000731	G	6730	41002979103	SLEEVE          	TEXTRON     		BELL  	407   	407         	       	SW  										BYPASS SPOOL	BINDING         	B			ALGR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	587AL	2780 			HR763	53248				PILOT REPORTED AN INTERMITTENT BIND.  INTERMITTENT BIND IN SERVO ACTUATOR.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001010200010	20010102	00010	EA  	2001	1	2	20000912SH019    	2	20000912	G	7414	10382807F	CAPACITOR       	BENDIX      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO COVER	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	734HZ	691  			I029912GR	17268878	L141676			OPEN ''P'' LEAD CIRCUIT.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001010200011	20010102	00011	CE  	2001	1	2	20000912SH020    	1	20000726	G	2821	07560052	STRAINER        			CESSNA	172   	172N        	2072434	CE  										FUEL STRAINER	MALFUNCTIONED   	B			DINR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	734JS	2824 				17268895				BOTH AD2000-06-01 AND SEB97-9 DID NOT APPLY TO THIS AIRCRAFT.  (STRAINER HAD NOT BEEN SWAPPED OUT).  DURING ROUTINE MAIN	TENANCE, SHOP INSPECTS THE STANDPIPE OF THESE STRAINERS SINCE IT IS A VERY EASY PROCEDURE.  DURING MAINTENANCE OF THE FU	EL STRAINER, FOUND THE STANDPIPE WAS EXTENDED TOO FAR AND ACTUALLY PULLED OUT OF THE TOP ASSY WITH FINGER PRESSURE ONLY.	  STRAINER WAS REPLACED WITH SERVICEABLE UNIT.  (X)			1	H	7	1 	3O			NT	3A12    					 
2001010200012	20010102	00012	CE  	2001	1	2	20000912SH021    	1	20000625	G	3230	S20496FG	ROD END         			CESSNA	177   	177RG       	2073709	CE  											FAILED          	B				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	17	7520V	4580 				177RG0817				WHEN PILOT SELECTED GEAR DOWN, HE HEARD A POP/BANG UNDER THE FLOOR AND THE MAIN GEAR FAILED TO EXTEND.  ACFT WAS LANDED 	GEAR UP WITH MINIMAL AIRFRAME DAMAGE.  INVEST REVEALED MAIN GEAR ACTUATOR ROD END BEARING PN S2049-6FG HAD FAILED AND SP	LIT APART AT THE SPHERICAL END.  FAILURE APPEARS TO HAVE STARTED AT THE HOLE IN THE ROD END USED FOR GREASING.  AREA INS	P APPROX 8 HRS PRIOR, DURING ANNUAL, WITH NO VISUAL DEFECTS.  FOUND OLD CESSNA SI LETTER SE79-37 RECOMMENDING ROD END RE	PLACEMENT WITH PN S2426-6, WHICH IS NOW SUPERCEDED TO PN S3469-1.  NEW P/N IS A SEALED UNIT WITH NO GREASER HOLE.  SUBMI	TTER RECOMMENDED CESSNA RE-ADDRESS THIS AS A SERVICE BULLETIN WITH HIGHER PRIORITY.  (X)	1	H	7	1 	3O			 	A20CE   					 
2001020800970	20010208	00970	NE  	2001	2	8	20000912SH022    	1	20000811	G	7603	7630101015001	ROLLER          			SKRSKY	S76   	S76B        	8143007	NE  										THROTTLE	DETACHED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	780P	3680 				760359				THE PIN THAT HOLDS THE ROLLER FOR POSITIVE THROTTLE DETENTS FAILED COMPLETELY AND THE ROLLER AND PIN ASSEMBLY FELL INTO 	THE THROTTLE QUADRENT.  SINCE THE QUADRENT IS IN AN OVERHEAD POSITION, THERE WAS NO THROTTLE RESTRICTION WITH THIS FAILU	RE.  (X)				1	G	7	2 	4U			 	H1NE    					 
2001020800971	20010208	00971	SW  	2001	2	8	20000912SH023    	1	20000710	G	6510	407040320101	SHAFT           	BELL        		BELL  	407   	407         	       	SW  										NR 2	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	847AL	1146 			A166	53150				DURING PHASE INSPECTION, FOUND SPLINES WORN BEYOND LIMITS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000092100501	20000921	00501	CE  	2000	9	21	20000912SH024    	1	20000825	G	3213	5141001212	TRUNNION        			CESSNA	310   	310Q        	2074242	CE  										BELLCRANK ATTACH	FAILED          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	15	8403F	5123 				310Q0640				AFTER LANDING AND WHILE TURNING LEFT OFF OF RUNWAY ONTO TAXIWAY, RIGHT GEAR COLLAPSED.  FOUND RIGHT GEAR TRUNNION UPPER 	BARREL TO BELLCRANK CASTING FAILED AND THE LOWER SIDE LINK SEPARATED AT ADJUSTMENT BOLT.  POSSIBLE CAUSE:  LOWER SIDE LI	NK ADJUSTMENT BOLT SEPARATED AS GEAR COLLAPSED AS EVIDENT BY BEND IN BOLT.  EXACT CAUSE OF FAILURE IS NOT KNOWN, POSSIBL	Y THE UPPER BARREL FITTING FAILED.  (X)			1	L	7	2 	3O			 	3A10    					 
2000092100502	20000921	00502	SO  	2000	9	21	20000912SH025    	2	20000824	G	7314	654351A1	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	86   				3449043	819507R			WITH TOP END FUEL PRESSURE SET IAW SPEC, AT IDLE, THE PUMP PRESSURE DROPS TO LOW.  LESS THAN 25 PSI TO OPERATE FUEL SERV	O AT IDLE.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000092100503	20000921	00503	SO  	2000	9	21	20000912SH026    	2	20000725	G	7314	F2899168R	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E					3449043	819507R			IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER.  PRESSURE WAS ALSO ERRATIC.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000092100504	20000921	00504	SO  	2000	9	21	20000912SH027    	1	20000823	G	2710	62701126	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										WING ROOT	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	2091 				3449043				RIGHT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000092100505	20000921	00505	CE  	2000	9	21	20000912SH028    	1	20000426	G	2730	50934032	TAPER PIN       			CESSNA	421   	421C        	2076016	CE  										TORQ TUBE COLLAR	LOOSE           	B			GICA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	88EQ					421C0821				ELEVATORS IN ACFT ARE ATTACHED TO A FLANGED COLLAR WITH TAPER PIN, PN 5035017-1.  TAPER PIN WORKED LOOSE WHICH OVALED OU	T THE HOLES IN THE COLLAR AND TORQUE TUBE.  AT INSP, COULD HOLD ONE ELEV RIGID, MOVE OTHER ELEV APPROX 1 INCH ON BOTH SI	DES.  CESSNA TECH REPS ACKNOWLEDGED THIS HAS BEEN A PROBLEM ON THE 421.  THE ONLY APPROVED CESSNA REPAIR IS TO REPLACE C	OLLAR WITH NEW STYLE COLLAR  TWICE AS LONG, ALLOWS A HOLE TO BE DRILLED THRU TORQUE TUBE OTBD.  NEW COLLAR INSTALLED ON 	ACFT DURING PREV REPAIR OF SAME CONDITION.  ONLY APPROVED REPAIR TO 2ND OCCURRENCE IS TO INSTALL A NEW TORQUE TUBE ASSY 	THAT COMES WITH SHORTER COLLAR.  ALLOWS CYCLE TO BEGIN AGAIN INSTEAD OF A FIX. (CANNOT PURCHASE SHORT COLLAR SEPARATE).	1	L	7	2 	3O			 	A7CE    					 
2000092100506	20000921	00506	CE  	2000	9	21	20000912SH029    	1	20000202	G	7931	1013890233	TRANSDUCER      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENG COMPARTMENT	FAILED          	B			UGIR	A				UNSCHED LANDING         				N	Y		FALSE WARNING             	ENGINE STOPPAGE           		CR	CRUISE         	1			SW	03	68TW	4790 				LJ1200	PCE25424			RIGHT ENGINE OIL PRESSURE INDICATION FAILED IN-FLIGHT.  ENGINE SHUT DOWN.  UNEVENTFUL LANDING.  (X)						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2000092100507	20000921	00507	EA  	2000	9	21	20000912SH030    	2	20000531	G	8520	72877	LIFTER          			CESSNA	185   	A185E       	2072818	CE  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 2 EXH LIFTER	FAILED          	B			YB3R	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	07	694BK					1851582	L474361A			THE FAILURE OCCURRED IN-FLIGHT RESULTING IN A FORCED LANDING.  POSSIBLE CAUSE FROM FRACTURE OF LIFTER BODY.  (X)						1	H	7	1 	3O	3	O	 	3A24    	E14EA				 
2001011105093	20010111	05093	CE  	2001	1	11	20000912SH031    	1	20000830	G	2800		FUEL LINE       	PREAIR      		BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					FUEL SYSTEM	DETERIORATED    	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	11	18981	3320 	30   			MC545	L1805851A			IN CRUISE FLIGHT, ENGINE RAN ROUGH HAD LOW EGT 900 DEGREES.  ON NR 2 CYLINDER. AFTER LANDING AND TROUBLESHOOTING, FOUND 	DEBRIS IN FUEL LINE FROM SERVO TO FLOW DIVIDER.  REPLACED RUBBER FUEL LINE WITH TEFLON LINE P/N LW12784-4-172 IAW LYCOMI	NG SI 1274B.  SUBMITTER SUGGESTED REPLACING ALL FUEL AND OIL LINES WITH TEFLON TYPE LINES.  TT ON RUBBER FUEL LINE 30 HO	URS.  (X)			1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2001011101150	20010111	01150	CE  	2001	1	11	20000912SH032    	1	20000830	G	2810		FUEL LINE       	PREAIR      		BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					FUEL SYSTEM	DETERIORATED    	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			GL	11	18981	3320 	30   			MC545	L1805851A			IN CRUISE FLIGHT, ENGINE RAN ROUGH HAD LOW EGT 900 DEGREES.  ON NR 2 CYLINDER.AFTER LANDING AND TROUBLESHOOTING, FOUND D	EBRIS IN FUEL LINE FROM SERVO TO FLOW DIVIDER.  REPLACED RUBBER FUEL LINE WITH TEFLON LINE P/N LW12784-4-172 IAW LYCOMIN	G SI 1274B.  SUGGESTED SUGGESTED REPLACING ALL FUEL AND OIL LINES WITH TEFLON TYPE LINES.  TT ON RUBBER FUEL LINE 30 HOU	RS.  (X)			1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2001010200014	20010102	00014	CE  	2001	1	2	20000913SH007    	1	20000829	G	2822	6467682A1	PUMP            			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520C    	17040	SO  						LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	08	1953U	55   				U20602306	178573R			REPLACEMENT (FOR REBUILT) BRAND NEW FUEL PUMP FOUND LEAKING FUEL FROM PORT SIDE ENGINE COWL BEFORE FLIGHT.  POSSIBLE CAU	SE, BROKEN DIAPHRAGM.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001010200015	20010102	00015	CE  	2001	1	2	20000913SH008    	1	20000829	G	2822	6467682A1	PUMP            			CESSNA	206   	TU206F      	2073353	CE  											LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	08	1953U		96   			U20602306				FUEL CONTINUOUSLY LEAKING FROM PORT SIDE ENGINE COWL.  FOUND AT END OF FLIGHT.  POSSIBLE CAUSE, BROKEN DIAPHRAGM.  (X)						1	H	7	1 	3O			 	A4CE    					 
2001010300002	20010103	00002	SO  	2001	1	3	20000913SH009    	2	20000830	G	8530		CYLINDER HEAD   			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BA     	17032	SO  					CYLINDER ASSY	DEPARTED        	E			XGNA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	05	1096W	1033 				CE436	249271A			CYLINDER HEAD DEPARTED BARREL WHILE AIRCRAFT IN-FLIGHT.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001010300003	20010103	00003	EU  	2001	1	3	20000913SH011    	1	20000828	G	5740	D22200361	FITTING         			WSK   	M18A  	M18A        	       	EU  										RIGHT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	2297L	5155 				01730				AIRCRAFT WAS INSPECTED IAW SPECIAL AIRWORTHINESS INFO BULLETIN NR CE-00-27, DATED ULY 11, 2000.  MAG PARTICAL INSPECTION	 REVEALED CRACK IN RIGHT BOTTOM FITTING, BACK SIDE.  (X)					1	L	7	1 	3O			NC	A47EU   					 
2001010300004	20010103	00004	EU  	2001	1	3	20000913SH012    	1	20000828	G	5740	D22200241	BRACKET         			WSK   	M18A  	M18A        	       	EU  										RIGHT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	2297L	5155 				1Z01730				AIRCRAFT WAS INSPECTED IAW SPECIAL AIRWORTHINESS INFO BULLETIN NR CE-00-27 DATED JULY 11, 2000.  VISUAL INSPECTION REVEA	LED CRACKS IN UPPER AND LOWER CUT-OUT SLAT.  (X)					1	L	7	1 	3O			NC	A47EU   					 
2001010300006	20010103	00006	CE  	2001	1	3	20000913SH014    	1	20000821	G	3220	98600661	LOCK            			CESSNA	185   	185F        	2072820	CE  										CABIN/TAIL WHEEL	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	4805					18504432				TAIL WHEEL LOCK ASSEMBLY MISSING EVERYTHING BUT THE LOCK ITSELF WHICH IS MOUNTED ON THE TAIL WHEEL.  NR 337 SHOWING REMO	VAL OF THESE PARTS.  AIRCRAFT WAS ORIGINALLY MOUNTED ON FLOATS.  AIRCRAFT WAS SOLD WITH WHEEL GEAR INSTALLED AND ANNUALE	D IN THIS CONDITION.  SALES PEOPLE CONVINCED THE NEW OWNER THAT THE TAIL LOCK ASSY WAS NOT NECESSARY ON THIS AIRCRAFT.  	TAIL WHEEL LOCK LEVER ALSO MISSING.  (X)			1	H	7	1 	3O			 	3A24    					 
2001010200016	20010102	00016	CE  	2001	1	2	20000913SH015    	1	20000827	G	2741	12606041	INDICATOR       			CESSNA	206   	206H        	2073301	CE  										ELEV TRIM IND	MALFUNCTIONED   	B			FTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	631AF	206  				20608070				PILOT REPORTED CONTINUOUS TRIM INDICATOR MALFUNCTION.  AFTER NUMEROUS ATTEMPTS TO RESET INDICATOR, A NEW PART WAS RECEIV	ED.  THE TANG WHICH RIDES IN THE TRIM WHEEL WAS FOUND TO BE SHORT BY 50 PERCENT.  NEW INDICATOR INSTALLED WITH NO FURTHE	R PROBLEMS.  (X)				1	H	7	1 	3O			RT	A4CE    					 
2001010300007	20010103	00007	CE  	2001	1	3	20000913SH016    	1	20000821	G	2822	120040663	LINE            			CESSNA	210   	T210F       	2073422	CE  										LINE TO AUX PUMP	LEAKING         	B			FTKR	A				UNSCHED LANDING         				K	Y		FLUID LOSS                	ENGINE STOPPAGE           		CR	CRUISE         	1			GL	19	6777R	2205 				T2100177				PILOT REPORTED ENGINE STARTED SURGING THEN CUTTING OUT PRIOR TO COMPLETING THE APPROACH TO LANDING.  THE PILOT WAS FORCE	D TO LAND SHORT OF THE AIRPORT RESULTING IN DAMAGE TO THE AIRCRAFT.  INVESTIGATION RESULTED AN IN-FLIGHT FUEL LEAK FROM 	THE RIGHT MAIN TANK.  ADDITIONALLY, EVIDENCE THAT FUEL WAS BEING LOST IN THE WHEELWELL.  THE OUTLET LINE FROM THE AUXILI	ARY FUEL PUMP WAS FOUND BARELY SNUG AND EVIDENCE OF FUEL STAINING ON AND AROUND THE FITTING AREA.  SUBMITTER SUPPOSED FU	EL EXHAUSTION TO ENGINE TO BE CAUSE OF INCIDENT.  SUBMITTER SUGGESTED SOME TYPE OF SAFETY/LOCKING DEVICE FOR THOSE LINES	 THAT COULD BE MOUNTING VIBRATION.  (X)	1	H	7	1 	3O			 	3A21    					 
2001010300008	20010103	00008	SO  	2001	1	3	20000913SH017    	1	20000713	G	3242	1690010	DRUM            			PIPER 	PA22  	PA22150     	7102210	SO  										BRAKE DRUM	WARPED          	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	1940P	3092 				222691				INNER WHEEL HALF ASSEMBLY CAUSING BRAKE DRUMS TO WARP.  FOUND EXCESSIVE BRAKE DRAGGING WHEN PERFORMING ANNUAL INSPECTION	.  SINCE NO SPECIFIC KEY POSITION, ASSEMBLY CAN BE TAKEN OFF AND RE-ASSEMBLED IN DIFFERENT POSITIONS.  WHEN TORQUING, WA	RPING CAN OCCUR IN BRAKE ASSEMBLY.  CAUSE IS DUE TO INACCURACY OF CASTING AT ALL CONTACT POINTS.  SUBMITTER SUGGESTED ST	AMPING ON THE INNER HALF OF WHEEL AND BRAKE ASSY AS REFERENCE MARK CAN HELP PREVENT WARPING.  (X)			1	H	7	1 	3O			 	1A6     					 
2001010300009	20010103	00009	EA  	2001	1	3	20000913SH018    	1	20000831	G	3244	275K221	TIRE            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										RETREAD LEVEL 5	SEPARATED       	H			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	715					1517				NOSE TIRE TREAD SEPARATION FROM CARCASS.  SUBMITTER SUSPECTED FOD.  (X)						1	H	7	1 	3R			 	A806    					 
2001010300010	20010103	00010	CE  	2001	1	3	20000913SH019    	1	20000721	G	5210		SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  											MISRIGGED       	D				O				OTHER                   				P			NO WARNING INDICATION     			CR	CRUISE         	1			WP	23	113GW	6887 				BB541				CABIN DOOR WAS NOT COMPLETELY LOCKED BEFORE FLIGHT.  DOOR BLEW OPEN DURING PRESSURIZED FLIGHT AT 12,500 FEET.  CABIN DOO	R WARNING LIGHT MICROSWITCH WAS MISRIGGED TO ALLOW THE WARNING LIGHT TO BE OUT, BUT THE DOOR NOT COMPLETELY LOCKED.  SUB	MITTER RECOMMENDED TO CLOSELY INSPECT THE DOOR LATCHING RIGGING DURING PHASE 3 INSPECTION TO INSURE THE MICROSWITCH DOES	 NOT CLOSE BEFORE THE DOOR HANDLE GOES OVERCENTER TO THE LOCKED POSITION.  (X)			1	L	7	2 	4T			 	A24CE   					 
2001022000123	20010220	00123	SO  	2001	2	20	20000913SH021    	1	20000802	G	2823	11383004	SELECTOR KNOB   			PIPER 	PA22  	PA22108     	7102204	SO  										LT CABIN WALL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4689Z					228227				FUEL SELECTOR VALVE IS HARD TO SET IN THE DESIRED POSITION WITHOUT LOOKING AT IT.  THE DETENTS ARE NOT POSITIVE ENOUGH A	ND THE SELECTORS GET STIFF IF NOT USED ENOUGH.  (X)					1	H	7	1 	3O			 	1A6     					 
2001022000124	20010220	00124	SO  	2001	2	20	20000913SH022    	1	20000802	G	2823	492014	SELECTOR KNOB   			PIPER 	PA22  	PA22108     	7102204	SO  										LT CABIN WALL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4689Z					228227				FUEL SELECTOR VALVE IS HARD TO SET IN THE DESIRED POSITION WITHOUT LOOKING AT IT.  THE DETENTS ARE NOT POSITIVE ENOUGH A	ND THE SELECTORS GET STIFF IF NOT USED ENOUGH.  (X)					1	H	7	1 	3O			 	1A6     					 
2001030100011	20010301	00011	SW  	2001	3	1	20000913SH027    	1	20000830	G	7160	88021719	PLENUM          			GULSTM	690TP 	690A        	0141722	SW  										INLET	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	500TS	5174 				11209				INLET PORTION OF PLENUM ASSEMBLY CRACKED AT WELD AREA.  (X)						1	H	7	2 	3T			 	2A4     					 
2001022100041	20010221	00041	CE  	2001	2	21	20000913SH028    	1	20000913	G	7160	16991007721	ALT AIR DOOR    			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	BROKEN          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	07	397RC	30008				MC631				DURING A FLIGHT LESSON, ENGINE LOST POWER AND AN EMERGENCY LANDING WAS MADE, NO INJURIES OR DAMAGE.  DURING INSPECTION A	FTER LANDING, ENGINE DEVELOPED POWER WHEN COLD.  REMOVED AIR FILTER ELEMENT, DISCOVERED HEAT DAMAGE TO FILTER ELEMENT AN	D FOUND ALT AIR DOOR HAD BROKEN AWAY FROM ITS HINGE AND HAD BECOME LODGED IN THE INTAKE OF THE FUEL SERVO.  AIRCRAFT INS	PECTED 81 HOURS PREVIOUSLY WITH NO DEFECTS NOTED.  SUBMITTER RECOMMENDED PAYING CLOSE ATTENTION TO THE ALT AIR DOOR DURI	NG INSPECTION, INSTALLING A SCREEN TO PREVENT A TOTAL BLOCKING OF THE INTAKE IF DOOR FAILS, AND INSTALLING A DOUBLER OVE	R THE DOOR WHERE IT ATTACHES TO THE HINGE.  (X)	1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2001022100058	20010221	00058	SO  	2001	2	21	20000913SH029    	1	20000831	G	2731	62701104	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STABILATOR TRIM	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4181M	2041 				2843120				TRIM CABLE FRAYED (FRONT CABLE AT TRIM WHEEL).  (X)						1	L	7	1 	3O			 	2A13    					 
2001022100059	20010221	00059	SO  	2001	2	21	20000913SH030    	2	20000830	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUEL INJECTOR	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4138X					3449112	321749R			UNABLE TO ADJUST FUEL FLOW AND IDLE MIXTURE.  NEW SERVO.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022100061	20010221	00061	SO  	2001	2	21	20000913SH031    	2	20000830	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUEL INJECTOR	MALFUNCTIONED   	B			VJ3R	E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			WP	07	4128X					3449112	32179R			FUEL FLOW RIGHT ENGINE DROP 3 GALLONS PER HOUR.  IN-FLIGHT, CHT AND TIT TEMP WENT HIGHER THAN THE OTHER ENGINE.  ENGINE 	STARTED TO RUN ROUGH.  ENGINE WAS SHUT DOWN IN-FLIGHT AND A SAFE LANDING ON ONE ENGINE WAS MADE.  INSPECTION OF ENGINE F	OUND THE RIGHT FUEL SERVO WAS LEAN AT ALL POWER SETTINGS.  SERVO REPLACED.  (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022100062	20010221	00062	SO  	2001	2	21	20000913SH032    	1	20000828	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										LT AILERON	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	1340 				3449112				LEFT AILERON FORWARD CABLE FRAYED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2001022100063	20010221	00063	SO  	2001	2	21	20000913SH033    	1	20000828	G	2710	62701124	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										RT AILERON	FRAYED          	B			XJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4133D	2241 				2843117				CABLE FRAYED AT FUSELAGE.  RIGHT AILERON BALANCE CABLE.  (X)						1	L	7	1 	3O			 	2A13    					 
2001022100066	20010221	00066	SO  	2001	2	21	20000913SH034    	1	20000828	G	2730	6270113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										LT STABILATOR	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4133D	2241 				2843117				LEFT FORWARD STABILATOR CONTROL CABLE FRAYED.  (X)						1	L	7	1 	3O			 	2A13    					 
2001022100067	20010221	00067	SO  	2001	2	21	20000913SH035    	1	20000828	G	2731	62701104	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STABILATOR TRIM	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4133D	2241 				2843117				TRIM CABLE FRAYED (FORWARD TRIM CABLE).  (X)						1	L	7	1 	3O			 	2A13    					 
2001030100012	20010301	00012	NE  	2001	3	1	20000914SH004    	2	20000818	G	8550	59500347	FITTING         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					ENGINE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	1295G					208B0841				AIRCRAFT ARRIVED WITH OIL LEAK.  ACFT LOST 1/2 QUART OF OIL DURING A 3.5 HOUR FLIGHT.  T/S REVEALED OIL LEAKING FROM THE	 TOP OF THE TORQUE LINE ADAPTER, PN 5950034-7, MOUNTED AT THE FRONT OF THE ENG.  INSP REVEALED FITTING, PN 5950034-7, HA	D DRILLED TO ALLOW A .1250 INCH PIPE THREAD FITTING TO BE INSTALLED.  HOLE DRILLED, BUT THE .1250 INCH PIPE THREADS WERE	 NOT CUT.  THE .1250 INCH PIPE THREAD FITTING WAS INSTALLED, TORQUED AT THE FACTORY.  FITTING ASSY LEAKED ONLY WHEN ENG 	WAS RUN AT HIGH POWER SETTINGS.  AT HIGH POWER SETTINGS, TORQUE FITING HAD PRESS IN RANGE OF 30/60 PSI.  TECH REMOVED TH	E FITTING, CUT .1250 INCH PIPE THREADS AND REINSTALLED ASSY.  ENG TAKEOFF POWER RUNS, LEAK CHECKS OK.  HOBBS:  22.0. (X)	1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2001022100072	20010221	00072		2001	2	21	20000914SH005    	4	20000829	G	3416	AK350	ENCODER         			CESSNA	172   	172M        	2072418	CE  										INSTRUMENT PNL	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	20466	1460 				17261310				ENCODER SHOWED PROPER PRESSURE ALTITUDE FOR APPROXIMATELY 25 MINUTES.  AFTER THAT TIME, ENCODER STARTED TO REPORT (PLUS)	 100 FOOT ERROR EVERY 2 MINUTES UNTIL THE ERROR BECAME ABOUT 600 FEET.  AFTER THAT, THE ENCODER WANDERED UP AND DOWN ABO	UT 200 FEET.  UNIT WAS REPLACED WITH NEW ENCODER.  (X)				1	H	7	1 	3O			NT	3A12    					 
2001022100073	20010221	00073	SO  	2001	2	21	20000914SH006    	1	20000823	G	2810	2722100	FUEL CAP        			PIPER 	PA30  	PA30        	7103002	SO  										FUEL TANKS	LEAKING         	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	3JM					30144				DURING TROUBLESHOOTING FOR FUEL CONTAMINATION PROBLEMS, NOTED WATER LEAKING FROM FUEL CAP.  UPON DISASSEMBLY OF CAPS, FO	UND EVIDENCE OF MOISTURE INSIDE CAPS.  CAPS ARE TYPICAL, OLDER PIPER ''THREADS BOTTLE'' CAPS.  DESIGN ALLOWS WATER TO EN	TER INTERIOR OF CAP THROUGH LOCKING LEVER SHAFT.  IF BOTTOM METAL PORTION OF CAP IS DISTORTED OR ATTACH HARDWARE IS CORR	ODED, WATER CAN DIRECTLY ENTER TANK, ESPECIALLY IF TANK FILLER SCUPPER DRAINS ARE PLUGGED.  TIME SINCE LAST INSPECTION, 	25 HOURS.  AIRCRAFT TOTAL TIME APPROXIMATELY 4,800 HOURS.  (X)		1	L	7	2 	3O			 	A1EA    					 
2001022100074	20010221	00074	SW  	2001	2	21	20000914SH007    	1	20000815	G	3210	71461R	GEAR            			BBAVIA	8     	8GCBC       	1220803	SW  										RT MLG	BROKEN          	B			AW4R	K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	11	8638V	4900 				16275				UPON LANDING, RT GEAR LEG, PN 7-1461-R, FAILED AT AREA OF U-BOLT ATTACH CLAMP.  FAILURE RESULTED IN DAMAGE TO RT WING, P	ROPELLER, ENGINE AND COWLING.  AIRCRAFT IS USED FOR GLIDER TOWING FROM AN UNPAVED RUNWAY AND AVERAGES 3-5 TAKEOFFS AND L	ANDINGS PER HOUR.  TOTAL CYCLES ON GEAR LEG ARE ESTIMATED TO BE BETWEEN 15,000 TO 20,000.  CRACK APPEARS TO BE FATIGUE R	ELATED AND IS BEING INVESTIGATED BY THE NTSB LABORATORIES.  SUBMITTER RECOMMENDED A LIFE-LIMIT BE ESTABLISHED FOR THESE 	GEAR LEGS.  TIME SINCE LAST INSPECTION IS APPROXIMATELY 170 HOURS.  (X)		1	H	7	1 	3O			 	A21CE   					 
2001022100075	20010221	00075	EA  	2001	2	21	20000914SH008    	2	20000823	G	7414	106B2016	GEAR            			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540J3C5    	41532	EA  					MAGNETO	BROKEN          	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	63BD		170  		B119801GR	R18201067				PILOT REPORTED RT PORTION OF MAGNETO INOPERATIVE (TCM DOUBLE MAG).  INVESTIGATION REVEALED SEVERAL TEETH BROKEN FROM RT 	DISTRIBUTOR GEAR (PN 10-682016) ALLOWING GEAR NOT TO ROTATE.  INSPECTION OF LT GEAR SHOWED ONE TOOTH BROKEN, HOWEVER, GE	AR WAS STILL ABLE TO TURN.  CAUSE OF FAILURE UNKNOWN, IT IS SUSPECTED THAT GEAR TOOTH FAILURE OF ONE GEAR CAUSED FAILURE	 OF THE OTHER GEAR DUE TO FAILED PART JAMMING OTHER GEAR.  (X)			1	H	7	1 	3O	3	O	 	3A13    	E295				 
2001022100099	20010221	00099	CE  	2001	2	21	20000914SH009    	1	20000908	G	7810	AN3C15	BOLT            			BEECH 	58    	58          	1152740	CE  										TAIL PIPE	MISSING         	B			VG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	35	3MU					TH1864				AIRCRAFT IN FOR MAINTENANCE WITH MISSING FLANGE BOLTS, BOLTS NOT OF STAINLESS STEEL  INSTALLED CAUSING FLANGE BOLT HOLES	 TO ELONGATE AND POSSIBLE PIPE SEPARATION.  NEW AIRCRAFT RECEIVED WITH STANDARD BOLTS INSTALLED.  NO INSTALL INSTRUCTION	S IN MM.  (X)				1	L	7	2 	3O			 	3A16    					 
2001022100076	20010221	00076	EA  	2001	2	21	20000914SH010    	2	20000719	G	7314	AE40296C	PUMP            			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	FAILED          	B			GETA	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NM	09	3832Q		13   			274	L2310651A			53 MINTUES AFTER TAKEOFF, AT A FLIGHT ALTITUDE 1,500 MSL, 5 MILES WEST OF EVERETT, WA, LEFT ENGINE QUIT.  RESTARTED WITH	 AUXILIARY FUEL PUMP AND LANDED.  REPLACED ENGINE DRIVEN PUMP WITH OVERHAULED PUMP FROM LYC.  PUMP HAD BEEN NEWLY OVERHA	ULED.  REPAIR STATION YV4R88M PMI WAS NOTIFIED.  (X)				1	H	7	2 	3O	3	O	 	A31EU   	1E10				 
2001022100077	20010221	00077	CE  	2001	2	21	20000914SH011    	1	20000828	G	2120	0570331	DIFFUSER        			CESSNA	172   	172N        	2072434	CE  										RT RADIO RACK	OUT OF POSITION 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	734KU					17268921				PILOT COMPLAINED THE ELEV CONTROL WAS JAMMED, RESTRICTING UP ELEV TRAVEL.  INSP FOUND THE RT SIDE RADIO COOLING DIFFUSER	 CESSNA PN 057033-1 HAD FALLEN AND WAS PINNED BETWEEN THE YOKE TUNNEL AND THE RADIO STACK.  WHEN UP ELEV ATTEMPTED, COPI	LOT''S YOKE AILERON SPROCKET PINNED THE DIFFUSER AGAINST THE FWD SIDE OF INSTRUMENT PANEL.  SINCE THE DIFFUSER WAS DOUBL	E-WALLED ALUMINUM AND THE SPACE BETWEEN THE RADIO STACK AND THE YOKE TUNNEL WAS ONLY A FEW INCHES,  PILOT WAS NOT ABLE T	O OVERCOME THE RESISTANCE.  THE DIFFUSER SHOULD BE HELD IN PLACE BY 4 SPRINGS, CESSNA PN 1470221-2, WHICH ATTACH IT TO A	N IDENTICAL DIFFUSER ON THE LT SIDE OF THE RADIO STACK.  LT DIFFUSER HAD BEEN PREVIOUSLY REMOVED.  ONLY 1 SPRING INTACT.	1	H	7	1 	3O			NT	3A12    					 
2001022100081	20010221	00081	GL  	2001	2	21	20000914SH012    	3	20000824	G	6110	D4991	MOUNT           													HARTZL	HCD4N3	HCD4N3A     	GL  	HUB	CRACKED         	B			F3PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		2729 	1800 					FY1049		DURING OVERHAUL INSPECTION, VISUAL CRACK IN BOTTOM OF MOUNTING HOLE DETECTED.  CONFIRMED WITH ZYGLO INSPECTION, EDDY CUR	RENT DEFLECTION DETECTED.  (X)															5	C	STC	 
2001022100100	20010221	00100	CE  	2001	2	21	20000914SH013    	1	20000814	G	3231		DOOR            			BEECH 	200   	B200        	1152922	CE  										LT MLG	OUT OF RIG      	B			EBVR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	09	55FJ	5434 				BB1297				WHILE CONDUCTING A TRAINING EXERCISE, CREW SIMULATED AN ENGINE OUT WITH THE LANDING GEAR DOWN.  DURING COURSE OF THE SCE	NARIO, THE GEAR WAS RETRACTED.  THE CREW NOTED THE HYDRAULIC PUMP STAYED ON UNUSUALLY LONG.  THE GEAR WAS PUT BACK DOWN 	AND AIRCRAFT SOON AFTER LANDED.  UPON INSP, LT INBOARD GEAR DOOR EDGE WAS FOUND BENT UP.  SUBSEQUENT INSP FOUND THE OVER	CENTER CONDITION OF THE GEAR DOOR RIGGING WAS NOT RIGGED PROPERLY AND THE YAW CONDITION DURING GEAR UP OPS CAUSED THE WH	EEL TO CATCH THE DOOR.  ACFT GEAR DOOR RIGGING HAD JUST BEEN DONE AT RECENT INSPECTION.  (X)		1	L	7	2 	4T			 	A24CE   					 
2001022100078	20010221	00078	EA  	2001	2	21	20000914SH014    	2	20000914	G	7322	MA3A	NEEDLE SEAT     			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	OBSTRUCTED      	G				A				UNSCHED LANDING         				C	R		F.O.D.                    	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			GL	09	2545N		400  			3879A0908				LOSS OF POWER AND SUBSEQUENT OFF-AIRPORT LANDING OCCURRED AFTER DARK.  REMOVABLE ''''TANG'''' FROM A HELICOIL WAS FOUND 	IN THE FINGER SCREEN CAVITY STUCK IN THE HOLE OF THE SEAT (OF THE NEEDLE AND SEAT) STOPPING FUEL FLOW TO THE FLOAT BOWL.	  (X)				1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2001022100082	20010221	00082	CE  	2001	2	21	20000914SH016    	1	20000824	G	2121	09040022	FAN BLADE       			CESSNA	425   	425         	2076018	CE  										CABIN	BROKEN          	B			EBVR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	09	5PP	294  				4250198				DURING FLIGHT, CREW SMELLED BURNING PLASTIC.  UPON INVESTIGATION BY MAINTENANCE, FOUND THAT ALL OF THE FAN BLADES HAD BR	OKEN OFF AND WERE LAYING IN THE AUXILIARY HEATER ASSY.  ONE BLADE MADE IT INTO THE HEATER COILS AND WAS BEING MELTED.  I	NSTALLED NEW FAN BLADE ASSY.  POST OPS CHECK WAS NORMAL.  NO REASON OR CAUSE FOR BLADES COMING OFF WAS FOUND.  (X)				1	L	7	2 	3T			RT	A7CE    					 
2001022100101	20010221	00101	CE  	2001	2	21	20000914SH017    	1	20000907	G	2720	5038017027	CHECK VALVE     			BEECH 	200   	200BEECH    	1152920	CE  										RUDDER BOOST	INOPERATIVE     	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	551JL	4885 				BB788				LEFT RUDDER BOOST INOPERATIVE.  FOUND RIGHT RUDDER BOOST CHECK VALVE NOT CHECKING-FLOWING BOTH DIRECTIONS CAUSING LEFT E	NGINE BLEED PRESSURE TO BE FELT ON BOTH SIDES OF RUDDER BOOST DIFFERENTIAL PRESSURE SWITCH CAUSING NO PRESSURE DIFFERENC	E TO BE FELT CAUSING LT RUDDER BOOST TO FAIL.  (X)				1	L	7	2 	4T			 	A24CE   					 
2001022100088	20010221	00088	GL  	2001	2	21	20000914SH018    	3	20000903	G	6111		SEAL            			CESSNA	182   	182S        	2072701	CE  						MCAULY	3D36C	B3D36C431   	GL  	PROPELLER	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	913CT	166  				18280391		982654		PROPELLER OIL LEAKING FROM SERVICE PLUG, AND BLADE SEALS.  NO INSTRUCTIONS PROVIDED FOR APPROVAL FOR RETURN TO SERVICE. 	 (X)					1	H	7	1 	3O			NT	3A13    		5	C	 	 
2001020800972	20010208	00972	EU  	2001	2	8	20000918SH001    	1	20000825	G	2913		SHAFT           			SNIAS 	350   	AS350BA     	8680817	EU  										HYD PUMP ASSY	WORN            	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	13	4064F					3087				HYDRAULIC PUMP SHAFT SPLINE WORN MAKING HYDRAULIC SYSTEM INOPERATIVE.  THIS HAPPENED ON A FERRY FLIGHT.  INSPECTION REQU	IREMENTS ARE EVERY 500 HOURS.  THE LAST INSPECTION ON THIS UNIT WAS ABOUT 390.2 HOURS AGO.					1	G	7	1 	3U			NC	H9EU    					 
2001020800973	20010208	00973	EU  	2001	2	8	20000918SH005    	1	20000206	G	7714	430106202	PICKUP          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NG SPEED	ERRATIC         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	117BK	109  				7229	LE45753EFA			NGP ERRATIC.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001020800974	20010208	00974	NE  	2001	2	8	20000918SH006    	2	20000628	G	7420	430111202	IGNITION LEAD   			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	SHORTED         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	163BK	543  				7063	LE45144EA			IGNITION HAD INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800975	20010208	00975	NE  	2001	2	8	20000918SH007    	2	20000412	G	7420	430111202	IGNITION LEAD   			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	SHORTED         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	158BK	998  				7058	LE45291EA488			IGNITION HAD INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800976	20010208	00976	NE  	2001	2	8	20000918SH008    	2	20000412	G	7420	430111202	IGNITION LEAD   			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	SHORTED         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	158BK	998  				7058	LE45291EA			INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800977	20010208	00977	EU  	2001	2	8	20000918SH009    	1	20000611	G	6210	L621M1010054	BLADE           			UROCOP	EC135 	EC135P1     	8680990	EU  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	1260 				0054				PROTECTION PLATE DEBONDING.  REPLACED WITH NEW UNITS, CORRECTED PROBLEM.  DAMPERS REMOVED:  LK0888, LK0894.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001020800978	20010208	00978	EU  	2001	2	8	20000918SH010    	1	20000611	G	6210	L621M1010054	BLADE           			UROCOP	EC135 	EC135P1     	8680990	EU  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	1260 				0054				PROTECTION PLATE DEBONDING.  REPLACED WITH NEW UNITS, CORRECTED PROBLEM.  DAMPERS REMOVED:  LK0670, LK0771.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001020800979	20010208	00979		2001	2	8	20000918SH011    	4	20000802	G	3421	066030460007	INDICATOR       			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	103LN	653  				3128				HSI - EXCESSIVE DEVIATION, LOOSE FACE PLATE.  UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020800980	20010208	00980		2001	2	8	20000918SH012    	4	20000805	G	3160	B19030MB01	DISPLAY         			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	104LN	147  				3134				UNIT INOPERATIVE.  NR 1 LANE FAILED.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020800981	20010208	00981	EU  	2001	2	8	20000918SH013    	1	20000717	G	2110	SD505	COMPRESSOR      			SNIAS 	350   	AS350B2     	8680813	EU  										AIR CONDITIONING	LEAKING         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	102LN					3065				LEAKING OIL FROM FRONT SEAL.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020800982	20010208	00982	EU  	2001	2	8	20000918SH014    	1	20000611	G	6210	L621M1010054	BLADE           			UROCOP	EC135 	EC135P1     	8680990	EU  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	1260 				0054				PROTECTION PLATE DEBONDING.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  DAMPERS REMOVED:  LK0911, LK0878.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001030100013	20010301	00013	EU  	2001	3	1	20000918SH015    	1	20000901	G	6710	1174120101	JACKSHAFT       			BOLKMS	117   	BK117A1     	5626010	EU  										M/R CONTROLS	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117LF	7928 				7013				DURING INSPECTION, FOUND MASSIVE AMOUNTS OF CORROSION INSIDE CYCLIC JACKSHAFT.  SAME LOCATION AS FOUND AND REPORTED PREV	IOUSLY ON ANOTHER AIRCRAFT 12-8-99.  MANUFACTURER ALLOWS .4 MM ALMOST IMPOSSIBLE TO MEASURE.  IT APPEARS LITTLE OR NO PA	INT TREATMENT ON INTERIOR OF STEEL TUBE.  THE TUBE HAS CASTINGS ON EACH END ANGLED UP AT 45 DEGREES WHICH INCREASES CHAN	CE OF GETTING FLUIDS INSIDE.  THERE ARE NO PROVISIONS FOR DRAINAGE.  SUBMITTER SUGGESTED MFG TREAT INTERIOR AND PROVIDE 	DRAINAGE.  THE LAST TIME THIS OCCURRED IT TOOK 3 MONTHS FOR THIS FLIGHT CRITICAL PART OF AN AIRCRAFT STILL IN PRODUCTION	 TO BE DELIVERED.  (X)	1	G	7	2 	3U			 	H13EU   					 
2001020800983	20010208	00983	NE  	2001	2	8	20000918SH017    	2	20000617	G	7323	430121204	GOVERNOR        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE	ERRATIC         	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	214AE	1106 				7206	LE45714			GOVERNOR CAUSED ERRATIC POWER OUTPUT RESULTING IN LOSS OF POWER AND SHUT DOWN.  REPLACED GOVERNOR.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001020800984	20010208	00984		2001	2	8	20000918SH019    	4	20000810	G	2311	TFM500G	TRANSCEIVER     			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	MALFUNCTIONED   	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	392LG	212  				3252				UHF 155 TX FEEDBACK TO CREW.  NEED M5 REVISION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020800985	20010208	00985	EU  	2001	2	8	20000918SH021    	1	20000808	G	7712		TRANSMITTER     			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ENGINE TORQUE	DAMAGED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	106LN	283  				3251	22097			TORQUE TRANSMITTER LOST ROLL PIN.  REPLACED 2 AND 3 MODULES DUE TO TURBINE RUB.  REPLACED WITH NEW UNIT, CORRECTED PROBL	EM.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2001020800986	20010208	00986	EU  	2001	2	8	20000918SH022    	1	20000717	G	6230	350A37112602	SCISSORS        			SNIAS 	350   	AS350B3     	8680954	EU  										M/R SWASHPLATE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	392LG	92   				3252				BUSHINGS LOCKED UP CAUSING DAMAGE TO SCISSOR HOUSING.  FOUR NEW PARTS DID SAME THING.  INSTALLED PART FROM ANOTHER AC AN	D WORKED FINE.  NEW PARTS DAMAGED IN 2.5 HOURS.  SUBMITTER SUSPECTED BUSHINGS IN NEW PARTS TO BE MISALIGNED.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001022100109	20010221	00109	SW  	2001	2	21	20000918SH023    	1	20000901	G	2510	49205503	SEAT            			GULSTM	112   	114         	7630314	SW  										PILOT SEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5879N	1990 				14424				SEAT FRAME TUBE FAILED AT LOCATIONS RESULTING IN SEAT BACK GOING TO A FULL RECLINE POSITION.  SEAT FRAME HAD BEEN MODIFI	ED PER SB 114-21A, REF AD 85-03-04R2.  (X)					1	L	7	1 	3O			 	A12SO   					 
2001020800987	20010208	00987	EU  	2001	2	8	20000918SH028    	1	20000119	G	7714	430106202	PICKUP          			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NG SPEED	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	7059N	536  				7154	LE45755EFA			UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2001020800988	20010208	00988	NE  	2001	2	8	20000918SH030    	2	20000811	G	7321	0164248850	FUEL CONTROL    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	96LG	29   				2817	9362			FUEL CONTROL ASSY LEAKING FUEL BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001020800989	20010208	00989	EU  	2001	2	8	20000918SH031    	1	20000127	G	7714	430106202	PICKUP          			BOLKMS	117   	BK117B1     	5626012	EU  										NG SPEED	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911VU	80   				7141				UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001020800990	20010208	00990		2001	2	8	20000919SH001    	4	20000731	G	3160	900A3720002111	DISPLAY         			DOUG  	MD900 	MD900       	3027375	NM  										COCKPIT	INOPERATIVE     	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	313  				90000012				UNIT INOPERATIVE.  PARTS OF DIGITAL READOUTS AND FUEL QUANTITY BARS INTERMITTENTLY DISAPPEAR.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001020800991	20010208	00991	NM  	2001	2	8	20000919SH002    	1	20000525	G	6720	900F2421545105	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										NOTAR THRUSTER	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	246  				90000012				DIVITS RESULTING FROM BEARING WEAR BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001020800992	20010208	00992	NE  	2001	2	8	20000919SH004    	2	20000229	G	7260	230307203	SEAL            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					CSD	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800993	20010208	00993	NE  	2001	2	8	20000919SH006    	2	20000229	G	7250	410106701	SEAL            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					1ST TURBINE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			SEAL WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800994	20010208	00994	NE  	2001	2	8	20000919SH007    	2	20000229	G	7250	410106802	SEAL            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					WORN	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800995	20010208	00995	EA  	2001	2	8	20000919SH008    	2	20000229	G	7230	410115013	DIFFUSER        			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	O540  	LTIO540*    	41533	EA  					ENGINE	CRACKED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127				DIFFUSER ASSY CRACKED BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	O	 	H13EU   	E14EA				 
2001020800996	20010208	00996	NE  	2001	2	8	20000919SH009    	2	20000229	G	7250	411100720	SHROUD          			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					GAS PRODUCER	DAMAGED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			EXCESSIVE GP BLADE TIP RUB.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800997	20010208	00997	NE  	2001	2	8	20000919SH010    	2	20000229	G	7240	413102002	CURL            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					COMBUSTION CHAMB	BURNED          	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			EXCESSIVE BURN IN SOME AREAS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800998	20010208	00998	NE  	2001	2	8	20000919SH011    	2	20000229	G	7250	430144801	SEAL            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 3 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020800999	20010208	00999	NE  	2001	2	8	20000919SH012    	2	20000229	G	7250	430150601	SEAL            			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	911BY	604  				7127	LE45385EA			LEAKING BYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001020801000	20010208	01000	EU  	2001	2	8	20000919SH014    	1	20000329	G	7714	430106202	PICKUP          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NGP SPEED	ERRATIC         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911VU	136  				7141	LE45583EFA			NGP SPEED ERRATIC.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001020100053	20010201	00053	EU  	2001	2	1	20000919SH016    	1	20000829	G	2435		WIRE            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					STARTER GEN	SHORTED         	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911KB				96288	0013	BB0017			BRUSH WIRE CONTACTED HOUSING AFTER A BRUSH INSPECTION.  EXTREME CARE SHOULD BE TAKEN DURING RE-ASSEMBLY AFTER INSPECTION	.  (X)					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001030200006	20010302	00006	CE  	2001	3	2	20000919SH019    	1	20000721	G	7333	99121942	SWITCH          			CESSNA	441   	441         	2076020	CE  										FUEL SYSTEM	INTERMITTENT    	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	8970N					4410092				FLOW SWITCH UNIT INOPERATIVE.  BENCH CHECKED AND FOUND UNIT TO OPERATE INTERMITTENTLY.  REPLACED WITH NEW UNIT, CORRECTE	D PROBLEM.  (X)					1	L	7	2 	3T			RT	A28CE   					 
2001022100169	20010221	00169	SO  	2001	2	21	20000919SH020    	2	20000808	G	7314	F289916BR	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					ENGINE	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	841  				3449046	819506R			IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022100170	20010221	00170	CE  	2001	2	21	20000919SH021    	2	20000808	G	7314	G189916BR	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					ENGINE	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	VJ3R	841  				3449046	819257R			IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022100171	20010221	00171	SO  	2001	2	21	20000919SH022    	2	20000727	G	7314	F289912BR	PUMP            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					ENGINE	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	158  				3449112	321749			IDLE PRESSURE WAS LOW AND UNABLE TO ADJUST HIGHER.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022100172	20010221	00172	EA  	2001	2	21	20000919SH023    	2	20000804	G	8550	LYL10	GASKET          			AVIAT 	A1    	A1B         	       	GL  	LYC   	O360  	O360*       	41514	EA  					FILTER ADAPTER	MISSING         	B			V2AR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	58TD	192  				2017				FILTER ADAPTER WAS MISSING PN MS28773-08 GASKET.  (X)						1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2001022100173	20010221	00173	EA  	2001	2	21	20000919SH024    	2	20000804	G	8550	LYC10	GASKET          			AVIAT 	A1    	A1B         	       	GL  	LYC   	O360  	O360*       	41514	EA  					FILTER ADAPTER	MISSING         	B			V2AR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	475MA	49   				2074				FILTER ADAPTER WAS MISSING PN MS28773-08 GASKET.  AN6289-8D.  NUT WAS NOT TORQUED.  OIL FILTER  ADAPTER WAS LEAKING.  (X	)					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2001022100174	20010221	00174	SO  	2001	2	21	20000919SH025    	1	20000919	G	2731	6841403	CONTROLLER      			PIPER 	PA32  	PA32R300    	7103213	SO  										ELEV TRIM CNTRL	WORN            	B			PP4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	10WW	2441 				32R7680319				DATE OF OCCURRENCE:  12-11-90PILOT REPORTED THAT ATTEMPT TO MANUALLY ADJUST STABILATOR TRIM FAILED.  EXAMINATION REVEALE	D THAT PLASTIC TRIM CONTROL WHEEL WAS WORN IN AREA OF DETENT RECEPTACLE THAT ENGAGES BALL SWAGED ON CONTROL CABLE.  CONT	ROL WHEEL WAS REPLACED WITH NEW AND TRIM CONTROL WAS RIGGED PER PIPER PA-32 SERIES SERVICE MANUAL.  SUBMITTER SUSPECTED 	THAT DUE TO RELATIVELY LOW TIME OF PART/AIRCRAFT, DAMAGE POSSIBLY OCCURRED DUE TO ATTEMPT TO OVERRIDE FAILED OR LOCKED U	P ELECTRIC TRIM SYSTEM BY APPLYING EXCESSIVE FORCE TO CONTROL.  (X)		1	L	7	1 	3O			 	A3SO    					 
2001022100175	20010221	00175	NE  	2001	2	21	20000919SH026    	2	20000602	G	7260	30727841	CARBON SEAL     	HONEYWELL   		AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					ACCESSORY GRBX	LEAKING         	B			BICR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	55AS					214	P76785			ENGINE NEW ON 6-5-90 WITH SB TFE731-72-3124 AND TFE731-72-3289 INCORPORATED.  ENGINE HAS HAD SEAL REPLACED ON THE FOLLOW	ING DATES AND ENGINE TIMES:  TSN 2603.9, 4/5/96;TSN 2720.1, 7-8-96; TSN 2978.6, 1-24-97; TSN 3725.9, 6/26/98; TSN 3962.3	, 12/1/98; TSN 3983.0, 12/21/98; TSN 3992.2, 1/4/99; TSN 4000.5, 1/9/99.  (X)				2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2001022100176	20010221	00176	NE  	2001	2	21	20000919SH027    	2	20000602	G	7260	30727841	CARBON SEAL     	HONEYWELL   		AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					ACCESSORY GRBX	LEAKING         	B			BICR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	55AS					214	P76787			ENGINE NEW ON 7/16/90 WITH SB TFE731-72-3124 AND TFE731-72-3289 INCORPORATED.  ENGINE HAS HAD SEAL REPLACED ON THE FOLLO	WING DATES AND ENGINE TIMES:  TSN 1718.6, 10/24/94; TSN 2815.8, 10/24/96; TSN 3646.4, 6/25/98; TSN 4004.7, 11/12/98; TSN	 4126.4, 6/25/99; TSN 4279.5, 10/27/99; TSN 4373.0, 1/3/00.  (X)				2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2001022100177	20010221	00177	NE  	2001	2	21	20000919SH028    	2	20000620	G	7260	30727841	CARBON SEAL     	HONEYWELL   		AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					ACCESSORY GRBX	LEAKING         	B			BICR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	250AS					182	P76628			ENGINE NEW ON 8/83 WITH SB TFE731-72-3124 AND TFE731-72-3289 INCORPORATED.  ENGINE HAS HAD SEAL REPLACED ON THE FOLLOWIN	G DATES AND ENGINE TIMES:  TSN 2219.8, 12/11/92; TSN 3666.5, 5/31/96; TSN 4819.8, 10-30-98, TSN 5574.4, 4/10/00.  (X)					2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2001022100006	20010221	00006	CE  	2001	2	21	20000920SH001    	1	20000714	G	2810		VENT LINE       			BEECH 	77    	77          	1153007	CE  										RT WING	BENT            	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			NM	11	3809Y	3997 				WA212				INITIAL FLIGHT INFORMATION REVEALED RIGHT FUEL TANK WOULD RUN DRY LONG BEFORE LEFT.  AFTER MANY LEAK TESTS, THE FUEL VEN	TS WERE SET TO FACTORY SPECS.  NEXT FLIGHT INDICATED THE REVERSE OF TANKS.  THE FOLLOWING FLIGHTS AND ADJUSTMENTS OF FUE	L VENTS LEFT AND RIGHT HAD PRODUCED FAIRLY EVEN FUEL TANK FLOW.  (X)				1	L	7	1 	3O			 	A30CE   					 
2001022100007	20010221	00007	CE  	2001	2	21	20000920SH002    	1	20000731	G	2434	649304A1	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  										ENGINE	MALFUNCTIONED   	B			AWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	458JG	60   				TH1908				ALTERNATOR DROPS OFF LINE.  (X)						1	L	7	2 	3O			 	3A16    					 
2001022100008	20010221	00008	CE  	2001	2	21	20000920SH003    	1	20000609	G	2434	649304	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  										ENGINE	INOPERATIVE     	B			ZWKR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	25	3196W	173  				TH1913				ALTERNATOR INOPERATIVE.  (X)						1	L	7	2 	3O			 	3A16    					 
2001022100009	20010221	00009	CE  	2001	2	21	20000920SH004    	1	20000831	G	2434	649305A1	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  										ENGINE	FAILED          	B			AWKR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	25	3196W	313  				TH1913				ALTERNATOR HAD NO OUTPUT.  (X)						1	L	7	2 	3O			 	3A16    					 
2001022100010	20010221	00010	CE  	2001	2	21	20000920SH005    	1	20000920	G	7810		BOLT            			BEECH 	100   	B100        	1152919	CE  										EXHAUST	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	120MG					BE70				DURING ROUTINE INSPECTION, FOUND THE RETAINING HARDWARE FOR THE EXHAUST DUCT WITHIN BOTH ENGINE COWLINGS WAS CORRODED BE	YOND SERVICEABLE LIMITS.  BOLTS AN4-4A AND NUTS MS21042L4.  THIS INSPECTION TOOK PLACE AT 310.5 HOURS FROM OVERHAUL OF B	OTH ENGINES.  (X)				1	L	7	2 	4T			 	A14CE   					 
2001022100011	20010221	00011	CE  	2001	2	21	20000920SH006    	1	20000831	G	8011		DRIVE SHAFT     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					LT ENG STARTER	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	120MG		311  			BE70	P27142			DURING ROUTINE INSPECTION, STARTER DRIVESHAFT WAS FOUND WORN BEYOND SERVICEABLE LIMITS AT 310.5 HOURS  AFTER ENGINE OVER	HAUL.  (X)					1	L	7	2 	4T	4	T	 	A14CE   	E4WE				 
2001022100016	20010221	00016	CE  	2001	2	21	20000920SH007    	1	20000908	G	5751		HINGE           			BEECH 	58    	58P         	1152744	CE  										AILERON	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	249CR					TJ249				OUTER HINGE ATTACHMENT SCREWS ON THE LOWER SIDE WERE HOT.  INSTALLED THROUGH THE HINGE ASSEMBLY, BUT THROUGH THE SKIN ON	LY.  SCREWS WERE HELD IN BY THE SKIN AND BACKSIDE OF COCKED HINGE.  PROBLEM WAS DISCOVERED FROM RESPONSE TO BEECH MAINTE	NANCE ALERT MA00-03, DATED 8-31-00.  (X)				1	L	7	2 	3O			 	A23CE   					 
2001020801001	20010208	01001	SW  	2001	2	8	20000920SH008    	1	20000829	G	5320	206031314037	CHANNEL         	BELL        		BELL  	206   	206L4       	1182110	SW  										FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	406MP	4700 				52086				FOUND .8750 INCH CRACK ON LEFT UPPER TAILBOOM ATTACHMENT CHANNEL DURING A ROUTINE 100 HOUR INSPECTION.  THE CRACK WAS ON	LY VISIBLE WITH REMOVAL OF THE TAILBOOM ACCESS PANEL AND THE USE OF AN INSPECTION MIRROR.  THE CAUSE OF THE CRACK IS NOT	 YET DETERMINED.  (X)				1	G	7	1 	3U			NC	H2SW    					 
2001022100182	20010221	00182	CE  	2001	2	21	20000920SH009    	1	20000912	G	2434	DOFF10300B	ALTERNATOR      			CESSNA	182   	TR182       	2072735	CE  										ENGINE	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	4928S					R18201467				ALTERNATOR 60-AMP CIRCUIT BREAKER TRIPPED.  JUMP STARTED AIRCRAFT.  ENGINE GROUND RUN.  ALTERNATOR CHARGED BATTERY WITH 	RADIO MASTER SWITCH ON.  AS LANDING TAXI LIGHTS WERE TURNED ON, 60-AMP CIRCUIT BREAKER TRIPPED.  INSTALLED TROUBLESHOOTI	NG EQUIPMENT,  INDICATIONS OF INTERNAL ALTERNATOR FAULT.  REMOVED AND REPLACED ALTERNATOR.   (X)				1	H	7	1 	3O			 	3A13    					 
2001022100183	20010221	00183	SO  	2001	2	21	20000920SH010    	2	20000512	G	8530		INTAKE VALVE    	LYC         		PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					NR 2 CYLINDER	FRACTURED       	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AL	01	5633V	649  				32R7780349	L1648648A			DURING FLIGHT, ENGINE BEGAN TO RUN ROUGH.  PILOT POWERED BACK AND MADE PRECAUTIONARY LANDING.  INSPECTION REVEALED FAILU	RE OF THE VALVE STEM ON NR 2 CYLINDER INTAKE VALVE.  THE FRACTURE IS LOCATED APPROXIMATELY .6250 INCH FROM THE TOP OF TH	E VALVE STEM NEAR THE VALVE KEEPERS.  SOME WEAR WAS DETECTED AT THE VALVE GUIDE.  (X)				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001022100184	20010221	00184	SO  	2001	2	21	20000920SH011    	1	20000603	G	3700		GASKET          			AMRGEN	AA1   	AA1A        	0630710	SO  	LYC   	O235  	O235C2C     	41505	EA  					VACUUM/PUMP	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	11	7C					AA1A0345	L1080415			REPLACED VAC/PUMP OIL SEAL STD-208 AND GASKET SL-61183 (2 TIMES SL-61183).  OIL WOULD LEAK OUT IN GREAT AMOUNT.  SEAL/GA	SKET DOES NOT HOLD OIL PRESSURE.  THE ALUM/BODY HAD A SHAFT AND GEAR DRIVING THE VAC/PUMP.  THERE IS A BORED/HOLE TO FEE	D OIL UNDER PRESSURE TO THE SHAFT.   (X)				1	L	7	1 	3O	3	O	 	A11EA   	E223				 
2001022100185	20010221	00185	GL  	2001	2	21	20000920SH012    	1	20000905	G	2821	2228215100	GASCOLATOR      			DIAMON	DA20  	DA20C1      	2990001	GL  										FUEL TANK	LEAKING         	B			HBKR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	899CT	110  				C0099				GASCOLATOR BOWL CANNOT BE SECURED TO PREVENT LEAKING AT BOWL GASKET AREA.  ANY SIDE LOAD CAUSES EXCESSIVE LEAKING.  LEAK	S AT JOINT OF HOUSING AND BOWL.  (X)					1	L	7	1 	3O			NT	TA4CH   					 
2001022100190	20010221	00190	CE  	2001	2	21	20000920SH015    	1	20000830	G	3710	HP006	HOSE            			CESSNA	182   	182R        	2072731	CE  										AIR FILTER	DETERIORATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	9386X	1608 				18268508				FOUND HOSE MADE BY IMPERIAL EASTMAN HYTYON YP006 250 PSI W.P.  FOUND OUTSIDE OF HOSE CRACKED AND COMING APART.  FOUND IN	SIDE OF HOSE RED IN COLOR VERY BRITTLE, CRACKING.  HOSE USED FOR INSTRUMENT VACUUM SERVICE.  HOSE ROUTED FROM INSTRUMENT	 AIR FILTER TO ARTIFICIAL HORIZON.  NOTE:  OTHER CESSNA AIRCRAFT HAVE HAD THIS TYPE HOSE PROBLEM WITH SAME TOTAL TIMES. 	 TACK 1,667.5 HOURS.  TTAC 1,607.5 HOURS.  (X)			1	L	7	1 	3O			NT	3A13    					 
2001022100191	20010221	00191	CE  	2001	2	21	20000920SH016    	1	20000901	G	2571	07120591	SUPPORT BRACKET 			CESSNA	182   	182R        	2072731	CE  										BATTERY BOX	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	9386X	1608 				18268508				ON INSPECTION OF AIRCRAFT, FOUND LEFT AND RIGHT BATTERY BOX SUPPORTS CRACKED IN BEND RADIUS, P/N  0712059-1.  24V BATTER	Y LOCATED IN TAIL SECTION OF AIRCRAFT.  NOTE:  THIS PROBLEM HAS BEEN FOUND IN OTHER 182R''S.  (X)					1	L	7	1 	3O			NT	3A13    					 
2001022600001	20010226	00001	EA  	2001	2	26	20000920SH017    	2	20000905	G	8530	05K22756	TUBE            			PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540*     	41532	EA  					INTAKE SYSTEM	DISCONNECTED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	9288X	215  				3257027	L9908861A			C/W PIPER SB 1030A AIR INLET TUBE REPLACEMENT AND DRAIN IMPROVEMENT AND LYC SB 538A AIR INLET TUBE.  REPLACEMENT ON 10-2	6-99 PER PIPER AND LYC SB''''S AND NOW, 215 HOUR LATER, THE INLET DRAIN SNIFFLE VALVE FALLS OUT.  (X)					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001011101151	20010111	01151	NM  	2001	1	11	20000920SH018    	1	20000920	G	5300	693535214	STRINGER CLIP   			BOEING	737   	7372B7      	1384560	NM  										FUSELAGE	CRACKED         	B			D8LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										PARTS PURCHASED NEW FROM BOEING STOCK, FOUND CRACKED IN OUTSIDE RADII OF CLIP IN EXTERNAL LAMINATE.  (X)						2	L	7	2 	4F			 	A16WE   					 
2001020801002	20010208	01002	SW  	2001	2	8	20000920SH026    	1	20000831	G	6520	47645205	SHAFT           			BELL  	47    	47G2        	1181008	SW  										T/R GEARGOX	SHEARED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	67083					2280				PILOT HAD JUST ARRIVED AT A FIELD TO SPRAY AND WAS DOING A 180 DEGREE TURN WHEN HE LOST TAIL ROTOR FUNCTION.  SHAFT FAIL	ED IN TAIL ROTOR GEARBOX.  (X)					1	G	7	1 	3O			 	H1      					 
2001011101152	20010111	01152	GL  	2001	1	11	20000921SH001    	3	20000911	G	6114		HUB             	HARTZL      		PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER ASSY	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	325CD	4441 	10   			447995243		AU1734		DURING PREFLIGHT, PILOT NOTICED GREASE ON BLADES.  MECHANIC REMOVED SPINNER AND FOUND HUB CRACKED ON RADIUS OF HUB.  THE	 CRACK STARTS WHERE THE CYLINDER ATTACHES TO HUB, GOES THROUGH ZERK FITTING HOLE TO MATING SURFACE OF HUB.  THE CRACK IS	 THROUGH THE ENTIRE HUB.  (X)				1	L	7	2 	3O			 	A19S0   		5	C	P920	 
2001030100014	20010301	00014		2001	3	1	20000925SH004    	4	20000911	G	2330	22840302	POWER SUPPLY    																	VIDEO UNIT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										POWER SUPPLY RETURNED FOR REPAIR AFTER REPORTED THAT UNIT WAS SMOKING DURING FLIGHT SEGMENT.  DURING TEAR-DOWN, FOUND ''	SCORCHED & MELTED'' CAPACITORS AND COMPONENTS WITHIN POWER SUPPLY.  INVESTIGATION OF ROOT CAUSE STILL ONGOING.  A NIC MF	G CAPACITOR IS SUSPECTED.  FINAL FIX STILL BEING WORKED.  AS A PRECAUTION, NIC CAPACITORS HAVE BEEN PURGED FROM REPAIR S	TATION STOCK AND COORDINATED PRODUCTION.  AIRLINE AND BOEING COORDINATION ONGOING.  (X)																 
2001030100015	20010301	00015		2001	3	1	20000925SH005    	4	20000911	G	2330	22840303	POWER SUPPLY    																	VIDEO UNIT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										POWER SUPPLY RETURNED FOR REPAIR AFTER REPORTED THAT UNIT WAS SMOKING DURING FLIGHT SEGMENT.  DURING TEAR-DOWN, FOUND ''	SCORCHED & MELTED'' CAPACITORS AND COMPONENTS WITHIN POWER SUPPLY.  INVESTIGATION OF ROOT CAUSE STILL ONGOING.  A NIC MF	G CAPACITOR IS SUSPECTED.  FINAL FIX STILL BEING WORKED.  AS A PRECAUTION, NIC CAPACITORS HAVE BEEN PURGED FROM REPAIR S	TATION STOCK AND COORDINATED PRODUCTION.  AIRLINE AND BOEING COORDINATION ONGOING.  (X)																 
2001030100016	20010301	00016		2001	3	1	20000925SH006    	4	20000911	G	2330	232840304	POWER SUPPLY    																	VIDEO UNIT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23										POWER SUPPLY RETURNED FOR REPAIR AFTER REPORTED THAT UNIT WAS SMOKING DURING FLIGHT SEGMENT.  DURING TEAR-DOWN, FOUND ''	SCORCHED & MELTED'' CAPACITORS AND COMPONENTS WITHIN POWER SUPPLY.  LABORATORY INVESTIGATION OF ROOT CAUSE STILL ONGOING	.  A NIC MFG CAPACITOR IS SUSPECTED.  FINAL FIX STILL BEING WORKED.  AS A PRECAUTION, NIC CAPACITORS HAVE BEEN PURGED FR	OM REPAIR STATION STOCK AND COORDINATED PRODUCTION.  AIRLINE AND BOEING COORDINATION ONGOING.  (X)																 
2001030100017	20010301	00017	NM  	2001	3	1	20000925SH007    	1	20000908	G	6720	500N53673	PITCH SLIDER    			DOUG  	600N  	600N        	3027377	NM  										NOTAR FAN	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	603BP	601  				RN029				DURING REMOVAL OF NO TAIL ROTOR (NOTAR) FAN BEARING, DISCOVERED THE FAN PITCH SLIDER, P/N 500N5367-3, AND FAN SUPPORT SH	AFT, P/N 500N5357-11, HAD PITTING CORROSION.  A NEW SUPPORT SHAFT AND SLIDER WERE INSTALLED.  WITH NEW PARTS INSTALLED, 	A CONDITION OF EXCESSIVE BINDING OF THE FAN PITCH SLIDER EXISTED.  IN CONJUNCTION WITH MD HELICOPTERS TECH REPS, DETERMI	NED THE TORQUE APPLIED TO THE PITCH SUPPORT SHAFT LOCKNUT P/N NAS1493-6F (60 TO 70 FEET/POUNDS AS SPECIFICIED IN THE HAN	DBOOK OF MAINTENANCE INSTRUCTIONS) WAS EXCESSIVE AND WAS THE MAJOR CONTRIBUTING FACTOR OF THE BINDING OF THE PITCH SLIDE	R.  (X)	1	G	7	1 	3U			NC	H3WE    					 
2001022200179	20010222	00179	CE  	2001	2	22	20000925SH008    	1	20000925	G	3710		LINE            			CESSNA	182   	182R        	2072731	CE  										INSTRUMENT PNL	DETERIORATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	6545E					18268373				WHILE CERTIFYING THE STATIC SYSTEM, DISCOVERED THE VACUUM LINES WERE DETERIORATING.  AFTER FURTHER INVESTIGATION, FOUND 	THE VACUUM LINES WERE THE LINES THAT HAD AD ISSUED AGAINST THEM.  REMOVED ALL VACUUM LINES AND REPLACED WITH NEW HOSES. 	 POSSIBLE CAUSE FOR THE PROBLEM IS FAULTY ENGINEERING AND AGE OF THE HOSE.  SUBMITTER RECOMMENDED ACTION WOULD BE TO REP	LACE ALL EASTMAN HOSES FOUND ON CESSNAS.  SEB96-10.  (X)			1	L	7	1 	3O			NT	3A13    					 
2001022200001	20010222	00001	CE  	2001	2	22	20000925SH009    	1	20000811	G	7602	5038901021	CONTROL CABLE   			BEECH 	95    	95B55       	1152729	CE  										RT ENG	BROKEN          	B			AIHR	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	11	18273					TC2065				PILOT REPORTED THAT ON CLIMB, RIGHT ENGINE WOULD NOT LEAN OUT.  PILOT THEN TURNED BACK TO AIRPORT AND AN UNEVENTFUL LAND	ING WAS MADE.  PILOT THEN DISCOVERED RIGHT ENGINE WOULD NOT SHUT DOWN WHEN MIXTURE CONTROL WAS PULLED BACK TO IDLE CUT-O	FF.  UPON INSPECTION BY MAINTENANCE, RIGHT ENGINE MIXTURE CABLE WAS FOUND WITH END PULLED OUT OF SWAGE AT FUEL CONTROL E	ND.  (X)			1	L	7	2 	3O			RT	3A16    					 
2001022200167	20010222	00167		2001	2	22	20000925SH012    	4	20000907	G	3452	RT359A	TRANSPONDER     	ARC         		CESSNA	182   	182R        	2072731	CE  										COCKPIT	INOPERATIVE     	H				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	05	9910H	82   			28853	18268106				TRANSPONDER REPORTED INOPERATIVE.  BENCH TEST REVEALED CAVITY TRANSMITTING AT 2,012 MEGAHERTZ AND IT COULD NOT BE ADJUST	ED INTO TOLERANCE.  FOUND TUBE INSTALLED WAS PC2080A, DATE CODE 99-13.  INSTALLED BY FAA CRS AJVR135C, PRESENT MANUFACTU	RER (SIGMA-TEK) DOES NOT AUTHORIZE THE USE OF THE PC2080A IN THE TRANSPONDER.  (X)				1	L	7	1 	3O			NT	3A13    					 
2001022200168	20010222	00168	EA  	2001	2	22	20000925SH014    	2	20000911	G	8550	77808	RELIEF VALVE    			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE CRANKCASE	DIRTY           	B			AW4R	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			WP	11	193PM					4622143				FOLLOWING TAKEOFF, PILOT NOTED DECREASE IN OIL PRESSURE.  PILOT ELECTED TO RETURN TO AIRPORT.  UPON LANDING AND TAXI BAC	K TO RAMP, PILOT KEPT RPM AT APPROX 1,500 RPM TO KEEP OIL PRESS ABOVE READING (LOW END).  DUE TO TAXIING AT HIGH RPM, BR	AKES WERE OVERHEATED WITH THE RT BRAKE CATCHING FIRE BY THE TIME ACFT RETURNED TO RAMP.  FIRE EXTINGUISHED.  DAMAGE CONF	INED TO BRAKE AND TIRE.  INVEST REVEALED SEVERAL SMALL PIECES OF WHAT APPEARED TO BE DIRT OR SAND ON RELIEF VALVE SEAT A	LLOWING OIL TO BYPASS THRUST THE RELIEF VALVE RESULTING IN LOWERED PRESSURE.  (X)		1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001020500189	20010205	00189	CE  	2001	2	5	20000925SH018    	1	20000831	G	5311	994400201	FRAME           			BEECH 	99    	99A         	1154003	CE  										FUSELAGE	CRACKED         	A			HSYA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	199CA		24624			U96				CPR - FUSELAGE FRAME CRACKED .75 INCH IN LENGTH AT STA 409 JUST RIGHT OF CENTER BELLY OF AIRCRAFT.  SUBMITTER SUSPECTED 	CAUSED BY FOD.   PERFORMED DOUBLER REPAIR; STOP DRILLED THE CRACK, FABRICATED DOUBLER WITH .032 INCH 2024T3 ALUMINUM AND	 INSTALLED WITH MS20470AD4 RIVETS.  COMPLETED FAA FORM 337.  (X)				1	L	7	2 	3T			 	A14CE   					 
2001022200169	20010222	00169	NE  	2001	2	22	20000925SH021    	2	20000925	G	7322	P13773	SCREW           	BENDIX      		WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985AN1     	52008	NE  					CARBURETOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	90303					1641				CARBURETOR FLOAT FULCRUM SCREW WAS FOUND LOOSE ON ANNUAL INSPECTION.  BRASS THREADS WERE FOUND WORN.  REPLACED FULCRUM S	CREW, PROPERLY INSTALLED NEW SCREW AND SAFTIED.  BELIEVE SCREW WAS NOT PROPERLY INSTALLED BY MANUFACTURER.  SUBMITTER RE	COMMENDED AN AD OR SA1B BE ISSUED TO INSPECT FULCRUM SCREW FOR PROPER INSTALLATION.  (X)				1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2001022200173	20010222	00173	EA  	2001	2	22	20000925SH024    	2	20000828	G	8520		STUD            			CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  					NR 1 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	12970	416  				17262415	RL2202336A			LYC WORK ORDER NR LB 1027207 FACTORY ZERO TIME ASSEMBLED 11-10-92 INSTALLED 12-28-92 IAW  PEN YAN STC.  18 HOURS SINCE L	AST ANNUAL.  FOUND NR 1 CYLINDER TOP RIGHT .50 INCH THROUGH STUD BROKEN FLUSH WITH CASE.  ALL OTHER STUDS ON NR 1 OK.  R	ESEARCH SEEMS TO INDICATE A FATIGUE FAILURE.  (X)				1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2000100200271	20001002	00271	CE  	2000	10	2	20000925SH029    	2	20000813	G	7322	RSA5AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						FAILED          	B			VJ3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			WP	07	4128X					3449112	819255R			ON LANDING AT GOODYEAR AIRPORT IN AZ, THE LEFT ENGINE LAGGED POWER TO LANDING.  THE RPM DROPPED FROM 2,400 TO 1,800.  TH	ROTTLE POWER TO 22 INCHES.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200001	20001002	00001	SO  	2000	10	2	20000925SH030    	1	20000815	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	1694 				3449042				RIGHT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000100200003	20001002	00003	SO  	2000	10	2	20000925SH031    	1	20000815	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	1694 				3449042				LEFT HAND AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.   (X)						1	L	7	2 	3O			 	A7SO    					 
2000101300107	20001013	00107	SO  	2000	10	13	20000925SH032    	2	20000817	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4123C	323  				3449042	321676R			THROTTLE HARD TO MOVE IN FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED.  OVER FOUR POUNDS TO MOVE CONTROL.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200007	20001002	00007	SO  	2000	10	2	20000925SH033    	2	20000817	G	8530	649262	TUBE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					INTAKE NR2	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	800  				3449046	819506R			NR 2 INTAKE TUBE ON RIGHT ENGINE CRACKED AT THE FLANGE WHERE IT MOUNTS TO THE CYLINDER .  INTAKE TUBE WAS REPLACED AND T	CM HAS BEEN INFORMED.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200008	20001002	00008	SO  	2000	10	2	20000925SH034    	2	20000817	G	8530	649262	TUBE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					INTAKE	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	800  				3449046	819506R			NR 6 INTAKE TUBE ON RIGHT ENGINE CRACKED AT THE FLANGE WHERE IT MOUNTS TO THE CYLINDER.  INTAKE TUBE WAS REPLACED AND TC	M HAS BEEN INFORMED.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200009	20001002	00009	CE  	2000	10	2	20000925SH035    	2	20000816	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						FAILED          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R					3449046	819256R			THROTTLE END PLAY ON SHAFT.  NEW FROM TCM.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200050	20001002	00050	SO  	2000	10	2	20000925SH036    	2	20000816	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						FAILED          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	90   				3449046	819506R			STIFF THROTTLE ARM, OVER 4 POUNDS TO MOVE CONTROL.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200051	20001002	00051	CE  	2000	10	2	20000925SH037    	2	20000817	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						FAILED          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	442  				3449046	819257R			THROTTLE HARD TO MOVE IN FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED.  OVER FOUR POUNDS TO MOVE CONTROL.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200052	20001002	00052	SO  	2000	10	2	20000925SH038    	1	20000815	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										AILERON	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142Q	1341 				2843207				AILERON BALANCE CABLE FRAYED.  LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2000100200267	20001002	00267	SO  	2000	10	2	20000925SH039    	2	20000817	G	8530	649264	TUBE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					INTAKE	CRACKED         	B			VJ3R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	07	4142N	1195 				3449128	322021R			THE PILOT REPORTED THE RIGHT ENGINE RUNNING ROUGH AND VIBRATION.  THE ENGINE WAS SHUT DOWN AND A SAFE LANDING WAS MADE. 	 AIRCRAFT WAS TAKEN TO MAINTENANCE AND INSPECTION WAS DONE ON THE ENGINE, NR 4 INTAKE TUBE WAS FOUND CRACKED AT THE FLAN	GE OF TUBE WHERE IT MOUNTS TO THE CYLINDER.  NEW INTAKE TUBE INSTALLED.  (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200268	20001002	00268	SO  	2000	10	2	20000925SH040    	2	20000817	G	7322	RSA5AD225765405	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						FAILED          	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9299E	11   				3449043	819507R			WHEN BOOST PUMP IS TURNED ON, FUEL FLOW DROPS, ENGINE RUNS ON THE LEAN SIDE.  REPLACED SERVO.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000100200231	20001002	00231	SO  	2000	10	2	20000927SH001    	1	20000926	G	5312	9512103	BULKHEAD        	PIPER       		PIPER 	PA34  	PA34200T    	7103406	SO  										BS 49.5	CRACKED         	B				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA		2900S	4480 			7970344	7970344				STA 49.5 BULKHEAD CRACKED AT UPPER NOSE GEAR ATTACH AREA - ALSO WINDSHIELD BRACE BUCKLED AT LOWER ATTACH AREA - NOTE: BR	ACE INSTALLED AS PART OF STC SA 1434AT.  (X)					1	L	7	2 	3O			 	A7SO    					 
2000120600028	20001206	00028	CE  	2000	12	6	20000927SH002    	1	20000908	G	6123	1D41701	COUNTERWEIGHT   	MCAULY      		BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  	MCAULY	2A34C	D2AF34C30   	GL  		DEPARTED        	E			VLGA	C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			GL	15	830Q		828  			TH368	298938	725050		DURING THE TAKEOFF ROLL, THE PILOT EXPERIENCED A SEVERE VIBRATION.  THE PILOT ABORTED THE TAKEOFF AND SHUT DOWN THE ENGI	NES.  AN INSPECTION OF THE AIRCRAFT REVEALED THAT A FEATHERING COUNTERWEIGHT ON THE LEFT PROPELLER HAD FAILED, DEPARTING	 THE AIRCRAFT AND DAMAGED THE SPINNER AND OPPOSITE BLADE.  THE SEARCH FOR THE COUNTERWEIGHT IN THE SURROUNDING AREA HAS 	BEEN UNSUCCESSFUL  (X).			1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2000100200058	20001002	00058	CE  	2000	10	2	20000927SH003    	1	20000926	G	2710	12601121	PULLEY          	CESSNA      		CESSNA	182   	182S        	2072701	CE  										QUADRANT	BURRED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	543MC	79   				18280548				WHILE PERFORMING SB 00-27-02, DATED AUGUST 14, 2000, TO INSPECT FOR PROPER RADIUS WHERE INTERCONNECT CABLE IS ATTACHED T	O QUADRANT, AILERON CABLE 0510105-328 WAS FOUND SEVERELY WORN.  CABLE WEAR WAS WHERE CABLE CONTACTED PULLEY GROOVE (OUTE	R SECTION OF 1260112-1 PULLEY) OVER HOLE DRILLED FOR NAS561-6-32 PIN (INNER SECTION OF PULLEY) WHICH ATTACHES PULLEY TO 	AILERON CONTROL TUBE ASSEMBLY, FORWARD OF YOKE.(DIGITAL PICTURES AVAILABLE ON REQUEST).  REF:  OPER CONTROL NR 200002.  	(X)		1	H	7	1 	3O			NT	3A13    					 
2001011101153	20010111	01153	SO  	2001	1	11	20001010SH001    	2	20000929	G	8550		SUMP            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	LOOSE           	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	13	18640					15074008				ON PREFLIGHT, PILOT NOTICED OILY RESIDUE ON OIL SUMP.  DURING A SCHEDULED OIL CHANGE, OWNER/PILOT DISCOVERED ONE OF THE 	FOUR BRACES THAT EXTEND FROM THE SOIL SUMP FLANGE TO THE SUMP BODY HAD CRACKED PLACING ADDITIONAL STRESS ON THE REMAININ	G BRACES.  THIS FAILURE INCREASED STRESS ON THE OTHER OIL SUMP BRACES AND CREATED A CRACK IN THE OIL TANK ADJACENT TO TH	E OVER STRESSED MEMBER.  SUMP WAS REMOVED, OVERHAULED AND RETURNED TO SERVICE.  (X)			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000113000038	20001130	00038	EA  	2000	11	30	20001011SH001    	2	20000703	G	8500		CAMSHAFT        								LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  		MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	HBKDO	1400 					51A	CH31018A		DURING 50-HOUR INSPECTION, FOUND A FEW CHIPS IN OIL FILTER. 10 HOURS LATER, NO CHIPS FOUND.  DURING 100-HOUR INSPECTION,	 AGAIN, SOME CHIPS.  ENGINE CONTROLLED WITH A MORE DETAILED INSPECTION.  FOUND CAMSHAFT CYLINDERS 3 AND 4 WORN OUT EXTRE	MELY.  AIRPLANE WAS USED FREQUENTLY FOR GLIDER TOWING.  (X)									3	O			1E10	5	C	P920	 
2000101800087	20001018	00087		2000	10	18	20001011SH002    	4	20001006	G	6122		GOVERNOR        	ALIDSG      		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  						MALFUNCTIONED   	B				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SO	15	84LJ				P337C	4410084	P31437C			PILOT REPORTED THAT AFTER ENGINE SHUT-DOWN OF A NORMAL FLIGHT, OIL WAS NOTICED LEAKING PROFUSELY FROM THE RIGHT COWLING.	  FURTHER INVESTIGATION REVEALED  THE OIL LEAK WAS ORIGINATING FROM THE PROP GOVERNOR BASE FLANGE SEAM.   IT WAS VERIFIE	D BY A MECHANIC THAT THE FLANGE GASKET WAS NOT THE SOURCE OF THE LEAK, BUT THE SEAM ON THE GOVERNOR WAS.  GOVERNOR TIME 	IN SERVICE: 17.8 HOURS.  (X)			1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2000101800085	20001018	00085		2000	10	18	20001011SH003    	4	20001006	G	6122		GOVERNOR        	ALIDSG      		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  						MALFUNCTIONED   	B				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	15	84LJ				P1482	4410084	P31437C			A MECHANIC INSTALLED A NEW PROP GOVERNOR, P/N 897160-9, ON THE RIGHT ENGINE OF A CESSNA 441. WHILE PERFORMING ROUTINE GR	OUND RUNS AND LEAK CHECKS IT WAS NOTED THAT OIL WAS LEAKING FROM THE TORQUE MOTOR, SPECIFICALLY THE EXIT POINT FOR THE W	IRES.  GOVERNOR TIME IN SERVICE 0.0 HOURS SINCE NEW, GROUND RUN TIME ONLY.  THIS PART NUMBER GOVERNOR HAS HAD A HISTORY 	OF VARIOUS OUT-OF-BOX FAILURES THROUGHOUT THE CESSNA 441 INDUSTRY.  SUBMITTER SUGGESTED THAT WHEN THESE GOVERNORS ARE BE	ING BENCH CHECKED AFTER ASSEMBLY, THE MANUFACTURER AND/OR OVERHAUL FACILITY SHOULD USE PREHEATED OIL ON THE TEST BENCH A	ND OPERATE THE GOVERNORS FOR A LENGTH OF TIME.  (X)	1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2000101800086	20001018	00086	CE  	2000	10	18	20001011SH004    	1	20001004	G	3233	99810057604	ACTUATOR        			BEECH 	200   	B200        	1152922	CE  										LT MAIN GEAR	SHEARED         	B				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SO	13	27LJ	5164 	984  			BB1040				UNSAFE GEAR INDICATION.  INSPECTION REVEALED LT MAIN GEAR ACTUATOR JACKSCREW FAILURE INVOLVING SEPARATION OF SPLINES INT	ERNALLY.  FAILURE REPORTED TO FSDO-13 OF COLUMBIA, SC.  FAA INSPECTOR  PRESENT DURING ARRIVAL AND LANDING.  AIRCRAFT LAN	DED WITHOUT INCIDENT.  (X)				1	L	7	2 	4T			 	A24CE   					 
2000101800168	20001018	00168	CE  	2000	10	18	20001011SH005    	1	20001007	G	2822	476411	PUMP            			CESSNA	310   	310Q        	2074242	CE  										POWER LEAD	FAILED          	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	25	69572	100  				310Q0790				DURING FLIGHT, PILOT NOTICED LEFT LANDING LIGHT CIRCUIT BREAKER OPEN.  AFTER LANDING, INSP FOUND LEFT TIP TANK FUEL TRAN	SFER PUMP P/N 476411 FAILED ELECTRICALLY.  PUMP SHOWED SIGNS OF HEAT AND ARCING ON OUTSIDE OF CASE FROM INTERNAL FAILURE	.   THIS PUMP IS WIRED BY MFG THROUGH LANDING LIGHT CIRCUIT.  SUBMITTER STATED THESE PUMPS HAVE HAD A HIGH FAILURE RATE.	  THE PUMP ON THIS ACFT IS THE FIFTH ONE INSTALLED IN 14 MONTHS. TIME BETWEEN FAILURES HAS BEEN 64 HRS, 21.4 HRS, 15.2 H	RS, 100.8 HRS.  PUMP IS REQUIRED EQUIPMENT FOR AD NOTE MANDATED EQUIPMENT ON ALL SUCH INSTALLATIONS AND IS REQUIRED FOR 	FLIGHT OPERATIONS.  ELECTRICAL FAILURE OF FUEL PUMPS CONSTITUTES A SIGNIFICANT FIRE/EXPLOSION HAZARD.  (X)	1	L	7	2 	3O			 	3A10    					 
2000101800169	20001018	00169	CE  	2000	10	18	20001011SH006    	1	20001007	G	2822	476411	PUMP            			CESSNA	310   	T310R       	2074246	CE  										POWER LEAD	FAILED          	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	25	310BA	95   				310R0065				DURING FLIGHT, PILOT NOTICED RIGHT LANDING LIGHT CIRCUIT BREAKER OPEN.  AFTER LANDING, INSP FOUND LEFT TIP TANK FUEL TRA	NSFER PUMP P/N 476411 FAILED ELECTRICALLY.  PUMP SHOWED SIGNS OF HEAT AND ARCING ON OUTSIDE OF CASE FROM INTERNAL FAILUR	E.   THIS PUMP IS WIRED BY MFG THROUGH LANDING LIGHT CIRCUIT.  SUBMITTER STATED THESE PUMPS HAVE HAD A HIGH FAILURE RATE	. THE PUMP ON THIS AIRCRAFT IS THE THIRD ONE INSTALLED IN 10 MONTHS. TIME BETWEEN FAILURES HAS BEEN 48 HRS, 10.3 HRS, 95	.7 HRS.   PUMP IS REQUIRED EQUIPMENT FOR AD NOTE MANDATED EQUIPMENT ON ALL SUCH INSTALLATIONS AND IS REQUIRED FOR FLIGHT	 OPERATIONS.  ELECTRICAL FAILURE OF FUEL PUMPS CONSTITUTES A SIGNIFICANT FIRE/EXPLOSION HAZARD.  (X)	1	L	7	2 	3O			 	3A10    					 
2000101800096	20001018	00096	NE  	2000	10	18	20001012SH004    	3	20000821	G	6114	660714214	HUB             													ROTOL	R390	R3904123F27 	NE  	REAR FACE	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21		11794	4321 					DAP0009		CRACK FOUND IN HUB REAR HALF AT NR 4 THREADED, MOUNTING INSERT.  CRACK IS APPROXIMATELY 3.5 INCHES LONG TRAVELING TOWARD	 NR 2 BLADE PORT OPENING.  HUB REJECTED FROM SERVICE.  (X)															6	C	P31NE	 
2000101900285	20001019	00285	CE  	2000	10	19	20001012SH005    	2	20000901	G	8500		BEARING         								CONT  	IO360 	IO360*      	17025	CE  					ENGINE	MAKING METAL    	B			EDER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	35										FOUND METAL IN FILTER.  SENT SAMPLE OF FILTER TO LYCOMING.  THEY SAID IT WAS BEARING MATERIAL AND RECOMMENDED TAKING OUT	 OF SERVICE.  (X)										3	O			E1CE				 
2000101800097	20001018	00097	CE  	2000	10	18	20001012SH006    	1	20001012	G	5521	033422013	SPAR            			CESSNA	195   	195A        	2073110	CE  										OUTBOARD TIP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	1010D					7618				BOTH ELEVATOR SPARS CRACKED VERTICALLY INITIATING IN BEND RADIUS OF FLANGE TO MOUNT TIP RIB.  THIS APPEARS TO BE FROM TO	RSIONAL FLEXING DUE TO THE HEAVY COUNTERWEIGHT OPPOSING AIR LOADS.  (X)					1	H	7	1 	3R			 	A790    					 
2000101800098	20001018	00098	CE  	2000	10	18	20001012SH007    	1	20001012	G	5751	0322709	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  										LT & RT INBOARD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4339V					7245				FOUND BOTH INBOARD AILERON HINGE BRACKETS CRACKED COMPLETELY THROUGH THE BEARING BOSS.  THESE BRACKETS WERE MADE FROM MA	GNESIUM AND SUFFER CORROSION PROBLEMS.  APPROXIMATELY 40 POUNDS OF PRESSURE SEPARATED THE AILERON FROM ITS HINGE/ATTACH 	ON THE INBOARD END.  (X)				1	H	7	1 	3R			NC	A790    					 
2000101800099	20001018	00099	CE  	2000	10	18	20001012SH008    	1	20001012	G	5751	03227091	HINGE BRACKET   			CESSNA	190   	190         	2072902	CE  										LT & RT AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4339V					7245				FOUND BOTH INBOARD AILERON HINGE BRACKETS CRACKED COMPLETELY THROUGH THE BEARING BOSS.  THESE BRACKETS WERE MADE FROM MA	GNESIUM AND SUFFER CORROSION PROBLEMS.  APPROXIMATELY 40 POUNDS OF PRESSURE SEPARATED THE AILERON FROM ITS HINGE/ATTACH 	ON THE INBOARD END.  (X)				1	H	7	1 	3R			NC	A790    					 
2000101800100	20001018	00100	CE  	2000	10	18	20001012SH009    	1	20000925	G	2781		HORN            			CESSNA	421   	421C        	2076016	CE  											MALFUNCTIONED   	G			IBUA	O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			WP	07	6793V					421C1022				LANDING GEAR WARNING HORN SOUNDED WITH GEAR EXTENDED WHEN FLAPS WERE MOVED FROM 15 DEGREES TO 30 DEGREES.  AFTER CYCLING	 GEAR AND FLAPS 2-3 TIMES, SYSTEM FUNCTIONED PROPERLY.  AIRCRAFT LANDED WITHOUT INCIDENT.  FLAP SWITCH, THROTTLE SWITCH,	 AND WIRING WERE INSPECTED WITH NO FAULTS NOTED.  PERFORMED FUNCTIONAL CHECK OF SYSTEM IAW CESSNA SERVICE MANUAL.  SYSTE	M FUNCTION NORMAL.  (X)			1	L	7	2 	3O			 	A7CE    					 
2000101800101	20001018	00101	CE  	2000	10	18	20001012SH010    	1	20000922	G	5540	07126161	BULKHEAD        			CESSNA	182   	182E        	2072712	CE  										BS 230.187	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01										NEW PART AS RECEIVED FROM CESSNA.  RE-INSTALLATION INSPECTION FOUND THE .3750 INCH DIAMETER BOLT HOLES ELONGATED AND OVE	RSIZED, EXCEEDING THE ACCEPTABLE LIMITS FOR BOLT HOLES LISTED IN AD 7207-09 PARA C)2)B) AND CESSNA SL SE 72-3.  DETERMIN	ED THE FINISHING PROCESS USED IN AREA OF RUDDER CABLE CUT-OUTS WOULD BE HIGHLY CONDUCIVE TO CRACKING.  THIS INCLUDED SCO	RING, GOUGING IN THE CORNER RADII, AND THINNING OF THE MATERIAL THICKNESS, AT ONE POINT PRODUCING A KNIFE EDGE.  THESE D	EFECTS WERE MADE WITH A SANDER OR SIMILAR TOOL.  RUDDER CABLE CUT-OUTS ARE WITHIN THE CRITICAL AREAS FOR POTENTIAL CRACK	ING AND INSPECTION REFERRED TO IN AD 72-07-09 AND CESSNA SL SE72-3 AND SE27-29.  (X)	1	H	7	1 	3O			NT	3A13    					 
2000101800102	20001018	00102	CE  	2000	10	18	20001012SH011    	1	20001012	G	5540	07126161	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  										BS 230.187	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	21268					18261528				NEW PART AS RECEIVED FROM CESSNA.  RE-INSTALLATION INSPECTION FOUND THE .3750 INCH DIAMETER BOLT HOLES ELONGATED AND OVE	RSIZED, EXCEEDING THE ACCEPTABLE LIMITS FOR BOLT HOLES LISTED IN AD 7207-09 PARA C)2)B) AND CESSNA SL SE 72-3.  DETERMIN	ED THE FINISHING PROCESS USED IN AREA OF RUDDER CABLE CUT-OUTS WOULD BE HIGHLY CONDUCIVE TO CRACKING.  THIS INCLUDED SCO	RING, GOUGING IN THE CORNER RADII, AND THINNING OF THE MATERIAL THICKNESS, AT ONE POINT PRODUCING A KNIFE EDGE.  THESE D	EFECTS WERE MADE WITH A SANDER OR SIMILAR TOOL.  RUDDER CABLE CUT-OUTS ARE WITHIN THE CRITICAL AREAS FOR POTENTIAL CRACK	ING AND INSPECTION REFERRED TO IN AD 72-07-09 AND CESSNA SL SE72-3 AND SE27-29.  (X)	1	H	7	1 	3O			NT	TA13    					 
2000101800103	20001018	00103	CE  	2000	10	18	20001012SH012    	1	20000922	G	5540	07126161	BULKHEAD        			CESSNA	182   	182J        	2072722	CE  										BS 230.187	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	3120F	3186 				18257220				AFT BULKHEAD AT BS 230.187 WAS FOUND CRACKED DURING VISUAL INSPECTION IN THE AREA OF THE LEFT RUDDER CABLE CUT-OUT RADIU	S AND THE BULKHEAD FLANGE.  THESE CRACKS CAN BE VERY FINE AND HARD TO SEE.  THEY USUALLY CAN BE VERIFIED BY VIEWING THE 	BULKHEAD FROM THE FRONT AND BACK.  A COMMON AREA FOR CRACKS IS THE LOWER END OF THE OUTSIDE UPPER RADIUS.  THIS IS ONE O	F THE CRITICAL AREAS LISTED FOR INSPECTION IN AD 72-07-09 AND CESSNA SL SE72-3.  REF:  ALERTS 215 JUNE 1996 AND ALERTS 2	28 JULY 1997.  (X)		1	H	7	1 	3O			NT	3A13    					 
2001022200015	20010222	00015	SO  	2001	2	22	20001012SH013    	1	20000914	G	3242	1331317	STATOR          			EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1681 			0205					BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVE	N WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT	 BRAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001011101170	20010111	01170	SO  	2001	1	11	20001012SH014    	1	20000909	G	3240	1331317	STATOR          			EMB   	120   	EMB120      	3260201	SO  										NR 1 & NR 2	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1555 			1253A					BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVE	N WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT	 BRAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001011101171	20010111	01171	SO  	2001	1	11	20001012SH015    	1	20000914	G	3240	1331317	STATOR          			EMB   	120   	EMB120      	3260201	SO  										NR 1 & NR 2 POS	DEFECTIVE       	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1689 			1179A					BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVE	N WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY, AND THE MOST RECEN	T BRAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001022200016	20010222	00016	SO  	2001	2	22	20001012SH016    	1	20000911	G	3242	1331317	STATOR          			EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1600 			0096					BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVE	N WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY, AND THE MOST RECEN	T BRAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001022200017	20010222	00017	SO  	2001	2	22	20001012SH017    	1	20000921	G	3242	1331317	STATOR          			EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1785 			1560A					BRAKE ASSY, P/N 2-1661, FAILED PREMATURELY.  NR 1 AND NR 2 STATORS CRACKED AT RELIEF HOLES.  HEAT STACK WARPED AND UNEVE	N WEAR.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY, AND THE MOST RECEN	T BRAKE CONFIGURATION, P/N 2-1661.  (X)				2	L	7	2 	4T			RT	A31SO   					 
2001011101172	20010111	01172		2001	1	11	20001012SH018    	4	20000915	G	6122	B20908	FLYWEIGHT       	MCAULY      																GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					770751					RELEVANT MAGNETIC PARTICLE INDICATION IN CORNER OF FLYWEIGHT HEAD.  (X)																			 
2001011101173	20010111	01173	NE  	2001	1	11	20001012SH019    	1	20000718	G	6320		STRUCTURE       	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  										M/R GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	194AC	3402 	1560 		A6084	64017				DURING TEARDOWN, MGB, PN 6435-20400-063, SN 16-084, FOR O/H, 5 CRACKS VISUALLY NOTICED IN 5 OF 9 LIGHTENING HOLES IN LOW	ER PLATE OF 2ND STAGE PLANETARY PLATE ASSY, P/N 6435-20231-014, SN EAC 3691.  FLUORESCENT MAGNETIC PARTICLE INSPECT(FMPI	) REVEALED 8 CRACKS. LONGEST, 3.500 INCHES WHICH EXTENDS INTO THE .500 INCH RADIUS OF CENTER HUB.  7 OF 8 CRACKS BEGAN O	N INBD SIDE OF LIGHTENING HOLES EXTENDING AT A 45 DEGREE ANGLE TOWARDS TO .500 INCH RADIUS.  1 CRACK BEGAN AT OTBD SIDE 	OF LIGHTENING HOLE, BUT DID NOT EXTEND OVER EDGE RADIUS OF THE HOLE.  THIS IS THE SAME LIGHTENING HOLE CONTAINING 3.500 	INCH CRACK.  2ND STAGE PLANETARY ASSY, PN 6435-20231-014, SN EAC 3681, TT 1936.9 HRS.  PERFORMED 62.8 FLT HRS PREVIOUS.	2	G	7	2 	4U			 	H4EA    					 
2001022200018	20010222	00018	CE  	2001	2	22	20001012SH021    	1	20000818	G	2612	47790008	CONTROL BOX     			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					FIRE DETECTION	FAILED          	E				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	99	1273E	175  				20800319	PCEPO0759			FIRE ALARM PUSH-TO-TEST FAILED TO ACTIVATE AUDIBLE HORN.  DETERMINED THE FIRE DETECTION CONTROL BOX HAD FAILED.  (X)						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2001030100018	20010301	00018	CE  	2001	3	1	20001012SH022    	1	20000728	G	7110	2652026200	ANGLE           			CESSNA	208   	208B        	2073701	CE  										NOSE CAP	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	12813	403  				208B0808				FORWARD ANGLE ON LEFT NOSE CAP FOR INDUCTION AIR PLENUM ATTACHMENT CRACKED.  (X)						1	H	7	1 	3T			 	A37CE   					 
2001030100019	20010301	00019	CE  	2001	3	1	20001012SH023    	1	20000801	G	7110	2652026200	ANGLE           			CESSNA	208   	208B        	2073701	CE  										NOSE CAP	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1275N	593  				208B0756				FORWARD ANGLE ON LEFT NOSE CAP FOR INDUCTION AIR PLENUM ATTACHMENT CRACKED.  (X)						1	H	7	1 	3T			 	A37CE   					 
2001030100020	20010301	00020	SO  	2001	3	1	20001012SH025    	2	20000822	G	8530		PISTON          			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					NR 3 CYLINDER	STUCK           	B				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			IN	INSP/MAINT     	1			EA	21	1015E	17   				TH1776	815431			ENGINE LOST OIL PRESSURE, STARTED RUNNING ROUGH, AND OWNER SHUT ENGINE DOWN AND FEATHERED IT.  AFTER FURTHER EVALUATION,	 NR 3 CYLINDER PISTON WAS NOT MOVING IN CYLINDER.  ENGINE REMOVED AND SENT TO TCM FOR TEAR DOWN.  NO DAMAGED SUSTAINED T	O AIRCRAFT, PILOT LANDED WITH NO INCIDENT.  (X)				1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2000120700106	20001207	00106	EU  	2000	12	7	20001012SH026    	1	20000814	G	7800	PC02596RH	HEAT SHIELD     			RHNFLU	EXT300	EA300L      	70218DG	EU  											FAILED          	B			UV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	13PR	5    				115				EXHAUST HEAT SHIELD FAILED ITS CLAMP ATTACH TABS.  SUBMITTER STATED THIS CONDITION COULD BE CONSIDERED SERIOUS IN THE EV	ENT A PART FAILS AND BECOMES LOOSE IN THE ENGINE COMPARTMENT.  (X)					1	M	7	1 	3O			NC	EA67U   					 
2000120700107	20001207	00107	EU  	2000	12	7	20001012SH027    	1	20000925	G	2730	PC00423	GRIP            			RHNFLU	EXT300	EA300L      	70218DG	EU  										BALL GRIP ELEV	DISLODGED       	B			UV4R	O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SO	15	13PR	28   				115				ELEVATOR TRIM BALL GRIP CAME OFF IN-FLIGHT.  OWNER COMMENTED HE NOTICED RED MARKS ON HIS RIGHT PANTS LEG JUST ABOVE THE 	KNEE ON SEVERAL OCCASIONS.  SUBMITTER SUGGESTED ALL EXTRA OWNERS CHECK THEIR TRIM KNOBS FOR LOOSENESS AS THIS IS A POTEN	TIALLY LIFE THREATENING DEFECT.  (X)				1	M	7	1 	3O			NC	EA67U   					 
2000101800128	20001018	00128	CE  	2000	10	18	20001012SH028    	1	20000915	G	2810	051600918	RESERVOIR       			CESSNA	172   	172R        	2072401	CE  										LOWER, L/E	CRACKED         	B			DYCR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	07	172QS					17280440				PILOT REPORTED FUEL DRIPPING FROM UNDER ACFT.  MECH DETERMINED IT WAS DRAIN VALVE.  DRAIN VALVE REPLACED.  FUEL CONTINUE	D TO DRIP FROM THE VALVE.  INVEST SHOWED THE LEAK WAS COMING FROM THE LOWER LEADING EDGE SEAM OF THE RESERVOIR TANK.  AF	TER REMOVAL, 2 INCH CRACK IN THE WELD WAS VISIBLE UPON INSP.  NO OBVIOUS CAUSE OF THE FRACTURE WAS VISIBLE.  POSSIBLE CA	USE MAY BE FROM RESERVOIR TANK FLEXING FROM BUILT-UP VENT PRESSURE AND THE WEIGHT OF THE FUEL.  INSP OF THIS ITEM ON A S	CHEDULED BASIS SHOULD BE ACCOMPLISHED TO DETERMINE CONDITION.  SUBMITTER STATED IF SEAM WOULD FAIL DURING FLIGHT, ALL FU	EL ONBOARD WOULD BE LOST AND ENGINE WOULD STARVE FOR FUEL.  (X)	1	H	7	1 	3O			NT	3A12    					 
2000101800129	20001018	00129	CE  	2000	10	18	20001012SH029    	1	20000918	G	7130	0553006209	FIREWALL        			CESSNA	172   	172P        	2072436	CE  										LOWER	CRACKED         	B			IKBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	100SU					17275001				FIREWALL CRACKS WHERE ENGINE COWLING SHOCK MOUNTS ARE ATTACHED TO THE LOWER FIREWALL AND FIREWALL REINFORCEMENTS.  CRACK	S APPEAR TO BE DUE TO THE AGE OF THE AIRCRAFT.  AIRCRAFT TT, 12,705 HOURS.  REPAIRS WERE MADE IAW CESSNA STRUCTURAL REPA	IR MANUAL.  THIS IS A WELL MAINTAINED AIRCRAFT AND IS USED IN A FLIGHT TRAINING ENVIRONMENT.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000101800009	20001018	00009	CE  	2000	10	18	20001012SH030    	1	20000904	G	2730	50934042	TUBE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					INSIDE TUBE	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	1361G					402C0270				REMOVED RIGHT ELEVATOR FROM AIRCRAFT TO REPLACE HINGE BEARINGS.  CLEANED INSIDE TUBE AND NOTICED 3 RUSTED HOLES THROUGH 	TUBE.  REPLACED TUBE WITH NEW AND LUBED INSIDE TUBE.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2000101800109	20001018	00109	SO  	2000	10	18	20001013SH001    	1	20000914	G	2810	6399816	FUEL TANK       			PIPER 	PA28  	PA28235     	7102810	SO  										CTR LT WING TANK	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	15219					287310024				DURING ANNUAL INSPECTION, THE MAIN FUEL SUMP SCREEN WAS FOUND ALMOST COMPLETELY BLOCKED WITH A REDDISH/BROWN MATTER.  TH	E FUEL TANKS'' INTERIOR WAS INSPECTED AND FOUND TO HAVE BEEN SLUSHED  AT UNKNOWN DATE AND TIME.  THE SLUSHING COMPOUND W	AS DISINTEGRATING AND FLAKING OFF.  THE TANKS WERE DRAINED AND SENT TO A REPAIR FACILITY FOR REMOVAL OF THE SLUSHING COM	POUND AND RESEALED WITH STC APPROVED FFCS-100.  NOTE:  AIRCRAFT IS BEING USED WITH AUTO FUEL AND IS STC''D FOR AUTO FUEL	 USE.  (X)		1	L	7	1 	3O			 	2A13    					 
2000101800110	20001018	00110	SO  	2000	10	18	20001013SH002    	1	20000914	G	2810	6399817	FUEL TANK       			PIPER 	PA28  	PA28235     	7102810	SO  										CTR RT WING TANK	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	15219					287310024				DURING ANNUAL INSPECTION, THE MAIN FUEL SUMP SCREEN WAS FOUND ALMOST COMPLETELY BLOCKED WITH A REDDISH/BROWN MATTER.  TH	E FUEL TANKS'' INTERIOR WAS INSPECTED AND FOUND TO HAVE BEEN SLUSHED  AT UNKNOWN DATE AND TIME.  THE SLUSHING COMPOUND W	AS DISINTEGRATING AND FLAKING OFF.  THE TANKS WERE DRAINED AND SENT TO A REPAIR FACILITY FOR REMOVAL OF THE SLUSHING COM	POUND AND RESEALED WITH STC APPROVED FFCS-100.  NOTE:  AIRCRAFT IS BEING USED WITH AUTO FUEL AND IS STC''D FOR AUTO FUEL	 USE.  (X)		1	L	7	1 	3O			 	2A13    					 
2000101800108	20001018	00108	SO  	2000	10	18	20001013SH003    	1	20001010	G	2740	6270197	CONTROL CABLE   			PIPER 	PA34  	PA34200T    	7103406	SO  										AFT FUSELAGE	BROKEN          	C				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	07	810JP	4415 				347670088				STABILATOR TRIM CABLE (P/N 62701-97) BROKE AT THE ELECTRIC TRIM DRIVE WHEEL ASSEMBLY WHILE DOING STEEP TURNS IN PT FOR C	OMML (ME). AIRCRAFT PITCHED UP 10-20 DEGREES BUT WAS CONTROLLABLE BY SLOWING AND LOWERING FLAPS TO FIRST NOTCH FOR SLOW 	RETURN AND LANDING WITHOUT FURTHER PROBLEM.  ABOVE PART WAS REPLACED. SUSPECT OVER-STRESS OF TRIM CABLE (P/N 62701-73) A	ND THAT WAS ALSO REPLACED.  ALL CONTROL/TRIM FUNCTIONS RESTORED TO NORMAL.  FORM 337 ISSUED 11 OCT AND MAILED TO SCOTTSD	ALE FSDO.   (X)		1	L	7	2 	3O			 	A7SO    					 
2000101800111	20001018	00111	CE  	2000	10	18	20001013SH004    	1	20000930	G	7932	633233W	CAP             			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520BA     	17032	SO  						BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	18287					D10032	562885			AFTER CHECKING THE ENGINE OIL QUANTITY, THE ROD-OIL-GAUGE CAP FAILED TO SECURELY LOCK IN PLACE WHEN IT WAS REINSTALLED. 	 UPON INVESTIGATION, FOUND ONE OF THE TWO LOCKING TABS HAD BENT 90 INCHES UP INTO THE FILLER CAP''S ROD-PLATE SPRING COM	PARTMENT.  OVER TIME, THE TAB HAD WORN VERY THIN FROM REPEATED USE.  WHILE ON THE BENCH FOR INSPECTION, THIS BENT LOCKIN	G TAB DID BREAK OFF.  THE LOCKING TAB COULD HAVE FALLEN INTO THE CRANKCASE.  SUBMITTER RECOMMENDED CLOSE VISUAL INSPECTI	ON OF THIS ROD-OIL-GAUGE CAP ASSY EACH TIME THE ENGINE OIL QUANTITY IS CHECKED.  IMPROVED ROD-OIL-GAUGE, TCM P/N 652171-	1, WAS INSTALLED.  (X)	1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2000101800140	20001018	00140	CE  	2000	10	18	20001013SH005    	1	20000921	G	2510	201101510	SEAT TRACK      			CESSNA	177   	177RG       	2073709	CE  											CORRODED        	B			X0FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1597H					177RG0771				INTERGRANULAR CORROSION FOUND ON VERTICAL LEG OF SEAT TRACK STARTING AT LAST SEAT ADJUSTMENT PIN HOLE (APPROX 20.25 INCH	ES FROM MOST FORWARD HOLE).  CORROSION STARTED AT AFT EDGE OF HOLE AND PROGRESSED AFT ONE INCH.  SURFACE METAL ON RIGHT 	SIDE OF VERTICAL LEG WAS FOUND EXFOLIATING APPROXIMATELY 2.5 PERCENT OF TOTAL THICKNESS.  POSSIBLE CAUSE IS EXPLAINED IN	 AC 43.13-1B, PAGES 6-17 AND 6-18, PROPER PERIODIC INSPECTIONS.  (X)			1	H	7	1 	3O			 	A20CE   					 
2000101800141	20001018	00141	SO  	2000	10	18	20001013SH006    	1	20000901	G	3230	105476	MOTOR           			PIPER 	PA28  	PA28R200    	7102811	SO  										EMPENNAGE	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	11	1334T		62   			28R7235263				LANDING GEAR MOTOR WOULD NOT OPERATE IN THE DOWN POSITION.  ON JACKS, THE GEAR MOTOR IS GETTING VOLTAGE, TAPPING MOTOR W	ITH HAMMER WILL CAUSE MOTOR TO OPERATE.  (X)					1	L	7	1 	3O			 	2A13    					 
2000101800142	20001018	00142	SW  	2000	10	18	20001013SH007    	1	20000912	G	5280		LINK            			GULSTM	690TP 	690A        	0141722	SW  										MAIN GEAR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690SM	7077 				11337				LINK ARM ASSY LOCATED ON RIGHT MAIN GEAR TO DOOR LINK FOUND CRACKED AT LINK TO ARM ATTACH AREA.  (X)						1	H	7	2 	3T			 	2A4     					 
2000101800144	20001018	00144	CE  	2000	10	18	20001013SH008    	1	20000921	G	5530	04310093	FITTING         	CESSNA      		CESSNA	150   	152         	2071835	CE  											CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	4713B	5099 				15283593				TEE SHAPED FITTING ON THE TRAILING EDGE OF THE FIN WAS CRACKED ON THE RIGHT SIDE IN THE RADIUS.  (X)						1	H	7	1 	3O			NT	3A19    					 
2000101800088	20001018	00088	EA  	2000	10	18	20001013SH009    	2	20000918	G	8520	LW13521	CONNECTING ROD  			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					BEARING FACE	FLAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	2589Z	764  				278154006	RL1888548A			DURING ROUTINE OIL CHANGE, FOUND ABUNDANT METAL PARTICLES IN OIL FILTER AND FINGER SCREEN.  AFTER CONFERRING WITH LYCOMI	NG, ALL CYLINDERS WERE PULLED TO CHECK PILOTED PISTON PIN PLUGS, NO ABNORMAL WEAR WAS NOTED.  SENT OIL FILTER AND FINGER	 SCREEN METAL TO LYCOMING FOR ANALYSIS, FOUND ALL METAL WAS BEARING INSERT MATERIAL.  OVERHAUL SHOP NOTED THAT CONNECTIN	G ROD BEARING INSERT WAS FLAKING APART.  TOTAL TIME ON FACTORY REMANUFACTURED, 763 HOURS, DATE COMPLETED 10-25-96, POSSI	BLE CAUSE:  UNKNOWN.  (X)		1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001011101174	20010111	01174	EU  	2001	1	11	20001013SH010    	1	20000802	G	6710	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										LT/RT CONTROL	LEAKING         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	102LN	755  				3065				SERVO LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020801003	20010208	01003	EU  	2001	2	8	20001013SH011    	1	20000805	G	6710	SC5083	SERVO           			SNIAS 	350   	AS350B3     	8680954	EU  										MAIN ROTOR	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	104LN	954  				3134				SERVO LEAKING BEYOND SERVICEABLE LIMITS.  REPALCED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001011101175	20010111	01175	EU  	2001	1	11	20001013SH012    	1	20000801	G	7931	DK040	TRANSMITTER     			BOLKMS	105   	BO105CBS    	5626008	EU  										ENGINE OIL	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	105LC					S789				PRESSURE TRANSMITTER UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			NC	H3EU    					 
2001011101176	20010111	01176	EU  	2001	1	11	20001013SH013    	1	20000513	G	7931	DK040	TRANSMITTER     			BOLKMS	105   	BO105CBS    	5626008	EU  										ENGINE OIL	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	105LC	47   				S789				TRANSMITTER UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H3EU    					 
2001011101177	20010111	01177	EU  	2001	1	11	20001013SH014    	1	20000523	G	7931	DK042M0D01	TRANSMITTER     			BOLKMS	105   	BO105CBS    	5626008	EU  										OIL PRESSURE	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	105LC	665  				S789				TRANSMMITTER UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			NC	H3EU    					 
2001011101178	20010111	01178	EU  	2001	1	11	20001013SH015    	1	20000629	G	6230	1051011305	BELLOWS         			BOLKMS	117   	BK117B1     	5626012	EU  										MAIN ROTOR	TORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117BK	751  				7229				BELLOWS IS TORN AROUND CLAMP AND FOLD AREAS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			 	H13EU   					 
2000101600452	20001016	00452	CE  	2000	10	16	20001013SH017    	1	20000913	G	2820	560010631	FUEL LINE       			CESSNA	340   	340CESSNA   	2076404	CE  										NACELLE/FIREWALL	WORN            	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	10MF	6300 				3400198				DURING INSTALLATION OF FUEL LINE CROSSFEED KIT NR SK340-31-6, REMOVAL OF THE OLD LINES REVEALED THAT TWO LINES HAD NEARL	Y BEEN WORN THROUGH DUE TO CONTACT WITH INSPECTION PANEL SCREWS.  THE ORIGINAL TUBING WAS PROTECTED BY THE ABRASION CUSH	IONS, BUT THE EXTENT OF DAMAGE WAS NOT EVIDENT UNTIL THE CUSHION WAS PEELED OFF.  VERY LITTLE CLEARANCE IS AVAILABLE AT 	THIS POINT, AND NEARLY IMPOSSIBLE TO DETECT ANY DAMAGE DURING INSPECTIONS.  IF THIS CONDITION GOES UNDETECTED, THE NEW T	UBING WILL ALSO BE DAMAGED.  NUTPLATE/SCREW CLEARANCE FROM FUEL TUBING MUST BE VERIFIED.  (X)		1	L	7	2 	3O			 	3A25    					 
2000101600453	20001016	00453	CE  	2000	10	16	20001013SH019    	1	20000914	G	5540	MS289135	BEARING         			BEECH 	200   	200BEECH    	1152920	CE  										RUDDER	LOOSE           	B			BXSR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	8238 				BB832				BEARING FOUND TO HAVE EXCESSIVE RADIAL FREE PLAY.  AFTER REMOVAL FROM THE AIRCRAFT, THE BEARING WAS DISASSEMBLED.  FOUND	 THE INTERNALS WERE DRY.  THE LUBRICATION WAS HARD. THIS BEARING SHOULD HAVE A LUBRICATION FITTING OR A CALENDAR REPLACE	MENT INTERVAL.  (X)				1	L	7	2 	4T			 	A24CE   					 
2000101600454	20001016	00454	CE  	2000	10	16	20001013SH020    	1	20001013	G	7130	12536072	FIREWALL        			CESSNA	206   	T206H       	       	CE  										LWR RT DIAG STRP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	206VW	92   				T20608064				DURING FIRST ANNUAL INSPECTION, FOUND CRACK IN DIAGONAL SUPPORT ACROSS LOWER RIGHT FIREWALL.  CRACK APPEARS TO BE CAUSED	 BY A MANUFACTURING DEFECT.  (X)					1	H	7	1 	3O			 	A4CE    					 
2000101600455	20001016	00455	SW  	2000	10	16	20001013SH021    	1	20000907	G	6100	D20887	DRIVE GEAR      	MCAULY      		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  						FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	201JY	1100 			820251	24318				REVELANT MAG PARTICLE INDICATION IN TEETH AREA.  (X)						1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2000101600456	20001016	00456		2000	10	16	20001013SH022    	4	20000907	G	6122	D20271	GOVERNOR        	MCAULY      		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  						CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	201JY	1100 				241318				RELEVANT EDDY CURRENT AND PENETRANT TESTING INDICATION AROUND HEAD OF GOVERNOR BODY.  (X)						1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2000101600457	20001016	00457	CE  	2000	10	16	20001013SH023    	1	20000814	G	3710	216CW	PUMP            			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					RIGHT SIDE	SHEARED         	E				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	2312V	50   				20608046	L2695848A			RIGHT VACUUM PUMP FAILED, DRIVESHAFT SHEARED.  (X)						1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000101600458	20001016	00458	CE  	2000	10	16	20001013SH024    	1	20000908	G	5540	0532104	BUSHING         			CESSNA	172   	172M        	2072418	CE  										RUDDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	20299	4943 				17261172				DURING INSPECTION, FOUND THE RUDDER HINGE BUSHINGS SEVERELY WORN.  VISUAL INSPECTION OF THE BUSHINGS DID NOT REVEAL ANY 	NOTICEABLE WEAR.  GENTLY PUSHING THE RUDDER AGAINST ITS STOPS WHILE WATCHING THE HINGE ALIGNMENT SHOWED ADDITIONAL MOVEM	ENT.  THE FULL EXTENT OF WEAR BECAME APPARENT AFTER REMOVAL OF THE RUDDER.  CABLE TENSION MUST BE REMOVED TO DETECT WEAR	.  THE AIRCRAFT WAS RETURNED TO SERVICE WITH NEW BUSHINGS.  (X)			1	H	7	1 	3O			NT	3A12    					 
2000101600459	20001016	00459	CE  	2000	10	16	20001013SH026    	1	20000809	G	8100	12509981	LANYARD         			CESSNA	206   	T206H       	       	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  						MISSING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	206VW	92   				T20608064	L1021361A			LANYARD AND ALL ATTACHING HARDWARE FOUND MISSING AND NO SIGN OF EVER BEING INSTALLED DURING FIRST ANNUAL INSPECTION.  SU	BMITTER STATED THIS DEFECT COULD CAUSE AN IN-FLIGHT FIRE.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2000101600460	20001016	00460	CE  	2000	10	16	20001013SH027    	1	20001013	G	3500		OXYGEN BOTTLE   			CESSNA	206   	T206H       	       	CE  											MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	206VW	92   				T20608064				OXYGEN BOTTLE APPEARS TO BE INSTALLED ON WRONG SIDE OF AIRCRAFT.  REF:  CESSNA SERVICE MANUAL INSIDE OF AIRCRAFT TAILCON	E.  (X)					1	H	7	1 	3O			 	A4CE    					 
2000101600461	20001016	00461	CE  	2000	10	16	20001013SH028    	1	20001013	G	7160		BOLT            	LYC         		CESSNA	206   	T206H       	       	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  						MISSING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	206VW	92   				T20608064	L1021361A			FOUND FORWARD SECURING BOLT MISSING FROM INTAKE PLENUM.  SUBMITTER STATED THERE WAS NO SIGN OF EVER BEING INSTALLED.  (X	)					1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2001020801004	20010208	01004	EU  	2001	2	8	20001016SH001    	1	20001004	G	2121	0500846	BLOWER          			SNIAS 	350   	AS350BA     	8680817	EU  										COCKPIT FAN	FAILED          	D			LBGA	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	13	87EW	126  				2116				DURING FLIGHT, SMOKE FILLED INTO THE CABIN.  FIRST, TURNED ALL ELEC OFF SWITCH.  VENTED THE CABIN BY OPENING THE FRONT V	ENT AND WINDOW (PILOT SIDE).  AFTER DETERMINING THERE WAS NO DANGER TO THE SAFE OPERATION OF THE AIRCRAFT, CONTINUED TO 	ALTERNATE AIRPORT, THEN TURNED ON PRIMARY INSTRUMENTS AND LATER THE AIRCRAFT FAN, THEN DETERMINED IT WAS THE AIRCRAFT 7 	INCH FAN.  BECAUSE OF THE NATURE OF THE FAILURE, RETURNED TO THE PRIMARY A/P WITHOUT INCIDENT.  (X)			1	G	7	1 	3U			NC	H9EU    					 
2001022200004	20010222	00004	SO  	2001	2	22	20001016SH003    	2	20001002	G	7314	6429324	PUMP            	CONT        		BEECH 	36    	36BEECH     	1151602	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	05	7883R	182  				E138	297118R			AT 80 HRS TT, FWD SEAL VENT LINE STARTED DISCHARGING SMALL AMTS OF OIL IRREG.  OIL ON OUTSIDE OF LT COWL SUSPECTED TO BE	 RESIDUAL OIL VENTING FROM HEAT.  NO BLUE FUEL STAINS EVIDENT.  THERE WAS A LOW PRESSURE WHEN PRIMING WITH BOOST PUMP, N	OT OUT OF NORMAL RANGE.  EGT CONFIRMED MIXTURE SO LEAN, IT WOULD DESTROY ENG BEFORE DEVELOPING POWER FOR TAKEOFF.  VERIF	IED FUEL PUMP LEAKING BY OPERATING BOOST PUMP WITH ENGINE OFF.  FUEL FLOWED OUT VENT.  (X)			1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2000120700109	20001207	00109	EU  	2000	12	7	20001016SH004    	1	20000725	G	7800	PC02596RH	HEAT SHIELD     			RHNFLU	EXT300	EA300L      	70218DG	EU  											LOOSE           	H			UV4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	278SJ	15   				113				EXHAUST HEAT SHIELD FAILED ITS CLAMP ATTACH TABS.  THIS CONDITION COULD BE CONSIDERED SERIOUS IN THE EVENT A PART FAILS 	AND BECOMES LOOSE IN THE ENGINE COMPARTMENT.  (X)					1	M	7	1 	3O			NC	EA67U   					 
2001022300003	20010223	00003	SO  	2001	2	23	20001016SH007    	1	20000918	G	3233	484373	SOLENOID        			PIPER 	PA32  	PA32RT300T  	7103216	SO  										MLG	MALFUNCTIONED   	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SO	33	21423					32R7887205				ACFT MADE GEAR UP LANDING AFTER ALTERNATE GEAR EXTENSION PROCEDURES FAILED TO EXTEND GEAR.  PILOT REPORTED HEARING GEAR 	HYD PUMP RUNNING AT ALL TIMES.  JUST PRIOR TO TOUCHDOWN, PILOT TURNED OFF MASTER POWER, AND GEAR ATTEMPTED TO EXTEND.  T	WO DC POWER SOLENOIDS CONTROL PUMP DIRECTION (GEAR UP/GEAR DOWN).  FOUND ''UP'' SOLENOID HAD ARCED CONTACT, SENDING DC P	OWER TO ''UP'' DIRECTION OF HYD PUMP.  SUBMITTER SUSPECTED SOLENOID HAD STUCK, KEEPING GEAR RETRACTED.  SUBMITTER RECOMM	ENDED PERIODIC REPLACEMENT OF SOLENOIDS, PIPER PN 484-373, TO PRECLUDE POSSIBILITY OF GEAR UP LANDINGS.  (X)		1	L	7	1 	3O			 	A3SO    					 
2000101900286	20001019	00286	CE  	2000	10	19	20001016SH012    	1	20000914	G	3231	55421029	TORQUE TUBE     			CESSNA	500   	550         	2076604	CE  										AT WELD	CRACKED         	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	361DB	187  				5500884				OPERATOR REPORTED THE NOSE LANDING GEAR DOORS ARE NOT CLOSED TIGHT.  INVESTIGATION FOUND THE NOSE LANDING GEAR DOORS TOR	QUE TUBE DAMAGED.  THE RIGHT END PLATE ON TORQUE TUBE HAD ONE WELD BROKEN AND THE OTHER WELD CRACKED.  REPLACED TORQUE T	UBE AND RIGGED NLG DOORS.   (X)				1	L	7	2 	4F			 	A22CE   					 
2000101900287	20001019	00287	CE  	2000	10	19	20001016SH013    	1	20001016	G	3230	4582507239	BRACE           			BEECH 	58    	58          	1152740	CE  										RT AFT RETRACT	CRACKED         	E			FPIA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	329H	9694 				TH219				FOUND ITEM CRACKED DURING ROUTINE INSPECTION.  CRACK LOCATED ON LOWER SIDE OF RIGHT TUBE WHERE RETRACT ROD ATTACH POINT 	AND BRACE PIVOT POINT ARE WELDED TOGETHER.  SECOND INCIDENT IN NINETY DAYS.  FIRST INCIDENT PART FAILED AND CAUSED GEAR 	COLLAPSE ON LANDING.  AIRCRAFT N NR 103GA, S/N JH-213.  (X)				1	L	7	2 	3O			 	3A16    					 
2000101900288	20001019	00288	CE  	2000	10	19	20001016SH014    	1	20000830	G	3340		SWITCH          			BEECH 	58    	58          	1152740	CE  										TAXI LIGHT	SHORTED         	A			BSYA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			GL	07	33WC					TH170				BWI - TAXIING OUT FOR TAKEOFF, SMELLED SMOKE, RETURNED TO BASE.  FOUND TAXI LIGHT SWITCH SHORTED TO WIRING HARNESS SUPPO	RT CLAMP.  REMOVED AND REPLACED TAXI LIGHT SWITCH AND BURNED WIRES.  RETURNED AIRCRAFT TO SERVICE.  (X)					1	L	7	2 	3O			 	3A16    					 
2000101900289	20001019	00289	CE  	2000	10	19	20001016SH015    	1	20000913	G	2742	31350012	SCREW           			LEAR  	35    	31          	5170530	CE  										THREADS	CORRODED        	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	331N					022				SCREW ASSEMBLY BAD FROM STOCK.  SCREW ASSEMBLY, S/N K138L, WAS FOUND CORRODED WHEN REMOVED FROM WRAPPING.   (X)						2	L	7	2 	4F			RT	A10CE   					 
2000101900290	20001019	00290	CE  	2000	10	19	20001016SH016    	1	20000913	G	2742	31355402	SCREW           	LEAR        		LEAR  	35    	31          	5170530	CE  										STAB ACTUATOR	NICKED          	B			JGVR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	331N					022				SCREW ASSEMBLY BAD FROM STOCK.  SCREW ASSEMBLY, S/N K320L, HAD TWO NICKS ON THREAD SURFACE.  (X)						2	L	7	2 	4F			RT	A10CE   					 
2000101900291	20001019	00291	CE  	2000	10	19	20001016SH017    	1	20000911	G	5610	51116052	WINDOW          			CESSNA	421   	421C        	2076016	CE  										EMERGENCY EXIT	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	3237U	4520 				421C0112				WHILE REPLACING PRESSURIZATION SEAL ON EMERGENCY EXIT, UPHOLSTERY WAS REMOVED.  FOUND OUTER WINDOW BROKEN BETWEEN FASTEN	ER HOLES.  PIECES WERE GLUED IN WITH RTV.  CAUSE OF FAILURE BELIEVED TO BE IMPROPER INSTALLATION.  NEW WINDOW INSTALLED 	ALONG WITH METAL RETAINER RING REQUIRED BY CESSNA SB MEB 87-4.   (X)				1	L	7	2 	3O			 	A7CE    					 
2000101900292	20001019	00292	CE  	2000	10	19	20001016SH018    	1	20000911	G	7120	505403042	BEAM            			CESSNA	421   	421C        	2076016	CE  											CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	3237U	4520 				421C0112				WHILE PERFORMING ANNUAL INSPECTION, FOUND LEFT ENGINE BEAM WITH 1.50 INCH CRACK ON UPPER CAP.  CRACK HAD BEEN STOP DRILL	ED, BUT THIS IS NOT A LEGAL REPAIR.  BEAM MUST BE REPLACED WITH NEW.  CESSNA FIELD SERVICE HAD TO ASSIST TO OBTAIN NEW P	ARTS THAT WOULD FIT.  CAUSE OF CRACK SUSPECTED TO BE IMPROPER FIT AT MANUFACTURE.  SUBMITTER SUGGESTED CLOSE VISUAL INSP	ECTION OF THESE BEAMS AT REGULAR INTERVALS.  (X)			1	L	7	2 	3O			 	A7CE    					 
2000101900293	20001019	00293	CE  	2000	10	19	20001016SH019    	1	20000911	G	2520	MEB003	SEAT            			CESSNA	421   	421C        	2076016	CE  										CABIN	MISINSTALLED    	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	3237U	4520 				421C0112				UPON C/W CESSNA MANDATORY SB MEB 00-3, FOUND ALL 4 CABIN SEATS INSTALLED IN WRONG POSITIONS.  PLACARDED AND REINSTALLED 	SEATS FOR SB.  SUBMITTER SUGGESTED A RECURRING AD NOTE BE ISSUED TO REQUIRE C/W THIS BULLETIN.  IMPROPER INSTALLATION OF	 FORWARD AND AFT FACING SEATS NEGATE ANY CRASHWORTHINESS DESIGNED IN THE SEAT.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000101900294	20001019	00294	CE  	2000	10	19	20001016SH020    	1	20000911	G	3230	5141200	UPLOCK          			CESSNA	421   	421C        	2076016	CE  											WORN            	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	3237U	4520 				421C0112				OPERATOR COMPLAINED OF HYDRAULIC SYSTEM STAYING ON AFTER LANDING GEAR RETRACTION.  COULD NOT DUPLICATE ON JACKS.  CESSNA	 FIELD SERVICE SUGGESTED INSTALLING NEW IMPROVED PARTS FOR UPLOCK HOOKS AND SWITCHES PER CESSNA SI LETTER NR M81-2.  NEW	 PARTS WERE MORE SUBSTANTIAL AND HIGHER QUALITY.  SOLVED PROBLEM.  ORIGINAL PARTS BADLY WORN.  SUBMITTER SUGGESTED COMPL	IANCE ON ALL EARLY SERIAL NUMBERED AIRCRAFT.  (X)			1	L	7	2 	3O			 	A7CE    					 
2001022100084	20010221	00084	CE  	2001	2	21	20001016SH021    	1	20000911	G	5730	SA2872SW	SKIN            			CESSNA	421   	421C        	2076016	CE  										WING	DAMAGED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	3237U					421C0112				DURING AIRCRAFT INSPECTION, FOUND RT STC''ED BAGGAGE LOCKER 28 GAL - FUEL TANK HOLD-DOWNS PULLING THROUGH UPPER WING SKI	N.  337 FORMS FOUND, BUT NO STC CERTIFICATE.  FURTHER INSPECTION REVEALED THIS ENTIRE INSTALLATION DOES NOT SEEM TO MEET	 INDUSTRY STANDARDS.  STC UNAVAILABLE AT THIS TIME AND WILL BE REQUIRED TO CONDUCT CONFORMITY INSPECTION BEFORE AIRCRAFT	 MAY BE APPROVED FOR RETURN TO SERVICE.  AWAITING DRAWINGS FROM STC HOLDER.  (X)			1	L	7	2 	3O			 	A7CE    					 
2000121500008	20001215	00008	CE  	2000	12	15	20001016SH022    	1	20000911	G	2820	510011075	LINE            			CESSNA	421   	421C        	2076016	CE  										COLLET	CRACKED         	B			R2JR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	3237U	4520 				421C0112				WHILE CHANGING DEFECTIVE FUEL TANK SELECTOR VALVE (LEFT), FOUND MAIN FUEL LINE TO BOOST PUMP HAD A CRACKED COLLET.  NEW 	LINE INSTALLED.  SUBMITTER STATED LEAK OR FAILURE OF THIS LINE COULD CAUSE ENGINE FAILURE AND/OR FIRE.  CAUSE OF FAILURE	 UNKNOWN.  (X)				1	L	7	2 	3O			 	A7CE    					 
2001022300006	20010223	00006	EA  	2001	2	23	20001016SH024    	2	20001003	G	8520	LW19340	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	DAMAGED         	I			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	3527U		1786 			317952141	L836861A			DURING INSPECTION, LOW CYLINDER COMPRESSION WAS DETECTED DURING THE COMPRESSION CHECK.  THE CYLINDER WAS REMOVED AND A V	ISUAL INSPECTION PEFORMED ON THE CAMSHAFT.  DETERMINED BOTH NR 3 AND NR 4 INTAKE LOBES AND TAPPET FACES WERE DAMAGED.  S	UBMITTER STATED THIS IS THE FOURTEENTH SUCH OCCURRENCE IN APPROXIMATELY 2-1/2 YEARS FOR THIS OPERATOR.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001020500142	20010205	00142	EU  	2001	2	5	20001016SH025    	1	20000831	G	7332	642100021	TRANSMITTER     			AEROSP	SA365 	SA365N      	8680669	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					FUEL PRESSURE	INTERMITTENT    	I			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365SJ					6018	2256			FUEL PRESSURE INTERMITTENT.  REMOVED AND REPLACED TRANSMITTER.  (X)						1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2001030100021	20010301	00021	GL  	2001	3	1	20001016SH026    	3	20000912	G	6111	V10133	BLADE           			HELIO 	H391  	H391B       	4300106	CE  						HARTZL	HC82V	HC82V201    	GL  	PROPELLER	DAMAGED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4120D					044		7682N		PROPELLER WAS BEING SERVICED DURING AN ANNUAL 100-HOUR INSPECTION.  WHILE ATTEMPTING TO GREASE THE PROPELLER, WATER WAS 	FOUND STREAMING FROM THE BLADE CLAMPS.  PROPELLER WAS DISASSEMBLED AND LIGHT RUST AND CORROSION WAS FOUND THROUGHOUT THE	 PROPELLER ESPECIALLY IN THE BLADE BALANCE HOLES.  ALTHOUGH THE CORROSION WAS LIGHT, THE BALANCE HOLES WERE ALREADY WELL	 OVER THE MAXIMUM INSIDE DIAMETER FOR REPAIR.  THE AIRCRAFT HAD NOT FLOWN AT ALL DURING THE PREVIOUS YEAR.  (X)			1	H	7	1 	3O			 	1A8     		5	C	P23EA	 
2001030100022	20010301	00022	GL  	2001	3	1	20001016SH027    	3	20000912	G	6111	V10133	BLADE           			HELIO 	H391  	H391B       	4300106	CE  						HARTZL	HC82V	HC82V201    	GL  	PROPELLER	DAMAGED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4120D					044		7682N		PROPELLER WAS BEING SERVICED DURING AN ANNUAL 100-HOUR INSPECTION.  WHILE ATTEMPTING TO GREASE THE PROPELLER, WATER WAS 	FOUND STREAMING FROM THE BLADE CLAMPS.  PROPELLER WAS DISASSEMBLED AND LIGHT RUST AND CORROSION WAS FOUND THROUGHOUT THE	 PROPELLER ESPECIALLY IN THE BLADE BALANCE HOLES.  ALTHOUGH THE CORROSION WAS LIGHT, THE BALANCE HOLES WERE ALREADY WELL	 OVER THE MAXIMUM INSIDE DIAMETER FOR REPAIR.  THE AIRCRAFT HAD NOT FLOWN AT ALL DURING THE PREVIOUS YEAR.  (X)			1	H	7	1 	3O			 	1A8     		5	C	P23EA	 
2001022300007	20010223	00007	EA  	2001	2	23	20001017SH001    	2	20000921	G	7322	30802	FLOAT           	PRECISION   		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A2F     	41514	EA  					CARBURETOR	LEAKING         	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	4419F	200  			7501826	287790027				CUSTOMER SUBMITTED CARBURETOR FOR REPAIR FOR A ''STUMBLE IN ACCELERATION''.  SPLIT CARBURETOR AND FOUND FUEL IN BOTH PON	TOONS ON NEW STYLE ADVANCED POLYMER FLOAT.  ALSO, FOUND SCREWS LOOSE HOLDING THROTTLE PLATE TO SHAFT.  PLATE MOVED FREEL	Y IN SHAFT SLOT.  (X)				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001022300008	20010223	00008	SO  	2001	2	23	20001017SH002    	1	20000914	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										AILERON	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145X	1472 				2843152				DURING A ROUTINE INSPECTION, THE LEFT AILERON BALANCE CABLE WAS FOUND FRAYED BY THE LEFT WING ROOT RIB.  (X)						1	L	7	1 	3O			 	2A13    					 
2000101900295	20001019	00295	SO  	2000	10	19	20001017SH003    	1	20000906	G	2780	829132	PUSHROD TUBE    			PIPER 	PA46  	PA46350P    	       	SO  										INBD FLAP WELL	BINDING         	B			AMYR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	41518	28   				4636302				BOTH FLAPS BINDING IN TRACKS WHILE EXTENDING FROM FULL UP POSITION TO APPROXIMATELY FIVE DEGREES.  FOUND PUSH ROD P/N 82	913-2 THE WRONG LENGTH PER MM, CHAPTER 27-509-00 PAGE 8, PARA (69).  THIS MEASUREMENT OF 5.26 INCHES WILL NOT ALLOW BOLT	 TO BE INSTALLED.  (X)				1	L	7	1 	3O			RT	A25SO   					 
2000101900296	20001019	00296	SO  	2000	10	19	20001017SH004    	1	20000831	G	3234		SELECTOR KNOB   			PIPER 	PA31  	PA31350     	7103110	SO  											MALFUNCTIONED   	A			BSYA	O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			GL	07	4UE					318152061				GRR - HAD 3 GREEN DOWN AND LOCK LIGHTS, HANDLE WOULD NOT RETURN TO NEUTRAL.  HAD MAINTENANCE JACK AIRCRAFT, CYCLE GEAR M	ANY TIMES, COULD NOT DUPLICATE.  HYDRAULIC RESERVOIR FULL, BOTH PUMPS CHECKED OK.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000101900297	20001019	00297	SO  	2000	10	19	20001017SH005    	1	20000810	G	3230		UPLOCK          			PIPER 	PA31  	PA31350     	7103110	SO  											MALFUNCTIONED   	A			BSYA	O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	07	4UE					318152061				CMH - AFTER TAKEOFF, COULD NOT GET GEAR UP AND LOCKED INDICATION, RETURNED TO CMH.  JACKED AIRCRAFT CHECKED ALL UPLOCK A	DJUSTMENTS AND OPERATION, CLEANED AND LUBED ALL UPLOCK ATACHMENTS, CYCLED GEAR SEVERAL TIMES.  OPS CHECKED GOOD.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000101900298	20001019	00298	SO  	2000	10	19	20001017SH006    	1	20000808	G	3230	4878621CH214	DOWNLOCK        			PIPER 	PA31  	PA31350     	7103110	SO  										MAIN GEAR	MALADJUSTMENT   	A			BSYA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	4079Y					318152079				CMH - LEFT GEAR DID NOT INDICATE DOWN AND LOCK.  RECYCLED GEAR, THEN CAME ON.  MAINTENANCE JACKED AIRCRAFT, REMOVED AND 	REPLACED LEFT GEAR DOWN AND LOCK SWITCH.  OPS CHECKED GOOD.  (X)					1	L	7	2 	3O			 	A20SO   					 
2000101900299	20001019	00299	SO  	2000	10	19	20001017SH007    	1	20000906	G	2730	5698102	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  										SPRING ATTACH	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4095L					318152178				C/W AD 98-08-18 (SB626C) ELEVATOR DOWN SPRING REPLACEMENT.  SB CALLS FOR REPLACEMENT OF SPRING, PN 71056-03, AND LINK, P	/N 71086-03, BUT DOES NOT ADDRESS THE LINK (P/N 56981-02) AT THE OTHER END OF THE SPRING WHICH IS WORN AT THE ATTACH HOL	E.  (X)				1	L	7	2 	3O			 	A20SO   					 
2000101900300	20001019	00300	SO  	2000	10	19	20001017SH008    	2	20000920	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					LINKAGE	LOOSE           	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	4128X					3449112				EXCESS PLAY IN ARM TO LINKAGE.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000101900301	20001019	00301	SO  	2000	10	19	20001017SH009    	2	20000920	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						MALADJUSTMENT   	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	1428 				3449112	321749R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000101900302	20001019	00302	CE  	2000	10	19	20001017SH010    	2	20000614	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						MALFUNCTIONED   	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4128X	30   				3449112	819255R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000101900303	20001019	00303	SO  	2000	10	19	20001017SH011    	1	20000928	G	2700	62701126	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	1448 				3449112				RIGHT HAND BALANCE CABLE FRAYED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000101900304	20001019	00304	CE  	2000	10	19	20001017SH012    	2	20000922	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						MALFUNCTIONED   	B			XC4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4177R	218  				3449046	819257R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000101900305	20001019	00305	CE  	2000	10	19	20001017SH013    	2	20000404	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						MALFUNCTIONED   	B			XC4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4177R	181  				3449046	819257R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001020801005	20010208	01005	EU  	2001	2	8	20001017SH014    	1	20000818	G	2432	RG355	CASE            			SNIAS 	350   	AS350B2     	8680813	EU  										BATTERY	CRACKED         	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4035W	395  				2912				DURING 100-HOUR INSPECTION, LEAD ACID BATTERY WAS FOUND WITH A CASE CRACK IN  ALL THE LOWER BOX CORNERS.  ALL OF THE CRA	CKS ARE 1 INCH TO 2 INCHES LONG.  BATTERY IS INSTALLED IN THE TAIL BOOM UNDER AN AEC STC.  AT APPROX 119.48 STA, THE LEA	D ACID BATTERY IS 4 POUNDS AND THE NICAD, IS 38 POUNDS.  TIME ON BATTERY 395 HOURS.  WITH THE INCREASED WEIGHT OF BATTER	Y AND LOCATION, POSSIBLY THE CASE OF THE BATTERY CANNOT STAND UP TO THE VIBRATIONS.  ATTACH BRACKET WHERE THE BATTERY CL	AMPS DOWN IS SQUARE CUT NOT ROUNDED.  SUBMITTER STATED SECOND ACFT IN FLEET AT THIS SITE WITH THIS CONDITION.  TO-DATE, 	SUBMITTER HAS HAD 6 CASES OF BATTERY BOX CASE CRACKING.  (X)	1	G	7	1 	3U			 	H9EU    					 
2000101900306	20001019	00306	SO  	2000	10	19	20001017SH015    	1	20000825	G	2740	62701047	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STAB	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4130W	1592 				2843204				TRIM CABLE FRAYED AT THE REAR TRIM DRUM.  (X)						1	L	7	1 	3O			 	2A13    					 
2000101900307	20001019	00307	GL  	2000	10	19	20001017SH016    	3	20000906	G	6114	D2AF34C30NP	HUB             	MCAULY      		BEECH 	58    	58          	1152740	CE  						HARTZL	HC92Z	HC92ZK1     	GL  	BLADE RET THREAD	CRACKED         	B			B2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	4183A					TH21				PROPELLER RECEIVED TO INVESTIGATE CAUSE OF DYED OIL LEAKING FROM HUB CAVITY.  PROPELLER WAS DISASSEMBLED AND UPON INSPEC	TION, SEVERAL CRACKS WERE FOUND IN THE BLADE RETENTION THREADS.  CRACKS WERE VERIFIED USING EDDY CURRENT INSPECTION.  (X	)				1	L	7	2 	3O			 	3A16    		5	C	P892	 
2001020900012	20010209	00012	EU  	2001	2	9	20001017SH017    	1	20000622	G	7110	1172312001	COWLING         			BOLKMS	117   	BK117A3     	5626015	EU  										FUSELAGE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	420MB	510  				7077				CATCHER/CREST COWLING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001020900013	20010209	00013	EU  	2001	2	9	20001017SH018    	1	20000801	G	7930	6607190A	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESSURE	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	485EC	476  				S754				OIL PRESSURE WARNING SWITCH UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H3EU    					 
2001022300009	20010223	00009	SO  	2001	2	23	20001017SH019    	2	20000908	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUEL SYSTEM	STUCK           	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	393  				3449128	322021R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022300010	20010223	00010	SO  	2001	2	23	20001017SH020    	2	20000915	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUEL INJECTOR	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	716  				3449128	322021R			ENGINE DIED AT IDLE, UNABLE TO ADJUST MIXTURE.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001030100023	20010301	00023	SO  	2001	3	1	20001017SH021    	1	20000914	G	2700	67701073	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										FLIGHT CONTROL	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	1290 				3449128				REAR TRIM CABLE FRAYED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2001020900014	20010209	00014	SW  	2001	2	9	20001017SH022    	1	20000918	G	6710	369H7024	NUT             	HUGHES      		HUGHES	500N  	500N        	3027374	SW  										UNILOCK	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	520PM	24   			0245985326	LN059				AT ACTT:  23.5 HOURS, THE UNILOCK, PN 369A7010501 SN 024598-5326, WAS INSTALLED IN NEW CONDITION TO REPLACE A LEAKING UN	ILOCK.  AFTER 23.6 HRS OF OPERATION, PILOT RETURNED STATING THE CYCLIC CONTROL HAD PLAY LONGITUDINALLY.  THE GRIP WOULD 	MOVE SEVERAL INCHES BEFORE THE INPUT WOULD BE SENT TO THE ROTOR SYSTEM.  FOUND NUT, PN 269H7024, WAS LOOSE ALLOWING THE 	INPUT ROD END TO MOVE.  IF THE NUT COMPLETELY LOOSENED, THE ROD END MAY SEPARATE FROM THE UNILOCK LEAVING PILOT WITH NO 	LONGITUDINAL CONTROL.  (X)		1	G	7	1 	3U			NC	H3WE    					 
2001022300011	20010223	00011	EA  	2001	2	23	20001017SH024    	2	20000828	G	8520	SL75060	ROD BOLT        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	56213	820  				347350304	L80367A			NR 3 CONNECTING ROD BOLT PN SL-75060 BROKE CAUSING THE CONNECTING ROD CAP TO SEPARATE RESULTING IN COMPLETE ENGINE FAILU	RE.  AIRCRAFT LANDED WITHOUT INCIDENT.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2001020900015	20010209	00015	EU  	2001	2	9	20001017SH028    	1	20000919	G	6210	10514101111	BOLT            			BOLKMS	117   	BK117B1     	5626012	EU  										M/R BLADE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	601EH	728  			050042	7181				AGC/CJI - DURING POST-FLIGHT FOUND MAIN ROTOR BLADE SECONDARY BOLT PROTRUDING UP 1 INCH OUT OF BOLT HOLE.  NUT AND REMAI	NING PART OF BOLT MISSING.  (COMPLETELY CRACKED IN HALF).  POSSIBLE CAUSE:  UNDER INVESTIGATION.  (X)					1	G	7	2 	3U			 	H13EU   					 
2001020900016	20010209	00016	SW  	2001	2	9	20001017SH029    	1	20000919	G	3213	20505015249	CROSSTUBE       			BELL  	204   	UH1H        	1181407	SW  										LANDING GEAR	CRACKED         	B			SXHL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6257P					6308807				DURING REFUEL, FOUND FORWARD CROSSTUBE AT RIGHT SADDLE CRACKED.  POSSIBLE CAUSE, WEAR.  (X)						1	G	7	1 	4U			 	EXPA1G71					 
2001020900017	20010209	00017	SW  	2001	2	9	20001017SH030    	1	20000901	G	5302	2050307121	ANGLE           			BELL  	204   	UH1H        	1181407	SW  										TAILBOOM MOUNT	CRACKED         	B			SXHL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	6257P					6308807				FOUND ANGLE CRACKED AT LEFT LOWER TAILBOOM MOUNT.  POSSIBLE CAUSE IS STRESS TORQUE OF TAILBOOM TO FUSELAGE.  (X)						1	G	7	1 	4U			 	EXPA1G71					 
2001022300013	20010223	00013	CE  	2001	2	23	20001017SH031    	1	20000904	G	5330		SKIN            			BEECH 	200   	200BEECH    	1152920	CE  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	60PD	15615				BB58				DURING EVENT NR 1 INSPECTION AND SPECIAL STRUCTURAL, BELOW FLOORBOARD FROM FORWARD PRESSURE BULKHEAD TO AFT PRESSURE BUL	KHEAD, A 1.50 INCH LATERAL CRACK WAS FOUND IN THE LOWER SKIN PANEL AT APPROXIMATE CENTERLINE OF AIRCRAFT ABOUT .50 INCH 	FORWARD OF BS 167.625.  SUBMITTER STATED THIS WILL REQUIRE DOUBLER REPAIR.  (X)				1	L	7	2 	4T			 	A24CE   					 
2001020900018	20010209	00018	EU  	2001	2	9	20001017SH032    	1	20000524	G	7712	G555674	TRANSDUCER      			BOLKMS	117   	BK117B1     	5626012	EU  										ENGINE TORQUE	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	62LF	380  				7163				PRESSURE TRANSDUCER UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2000101900308	20001019	00308	CE  	2000	10	19	20001017SH033    	1	20000918	G	2436	VR515G	REGULATOR       			CESSNA	210   	P210N       	2073454	CE  											SHORTED         	G				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	13	734JV					P21000604				PILOT EXPERIENCED ELECTRICAL POWER FAILURE.  NEW ALTERNATOR INSTALLED.  PILOT DEPARTED EN ROUTE HOME WHEN ELECTRICAL POW	ER WAS LOST AGAIN 9-19-2000.  MAINT REPLACED VOLTAGE REGULATOR.  THIS IS THE SECOND INCIDENT.  IN TWO YEARS, BOTH TIMES 	THE INDIVIDUAL COMPONENTS WERE REPLACED AT DIFFERENT TIMES.  SUBMITTER SUGGESTED ANY ALTERNATOR FAILURE OF THIS SYSTEM, 	BOTH THE ALTERNATOR AND REGULATOR, SHOULD BE REPLACED TOGETHER.  (X)			1	H	7	1 	3O			 	3A21    					 
2000101900309	20001019	00309		2000	10	19	20001017SH034    	4	20000906	G	6122	A20107	GEAR            	MCAULY      		CESSNA	402   	402B        	207590P	CE  											DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	768WC		1400 		740086	402B1066				RELEVANT MAG PARTICLE INDICATION AROUND TEETH AREA.  (X)						1	L	7	2 	3O			 	A7CE    					 
2000101900310	20001019	00310	CE  	2000	10	19	20001017SH035    	1	20000819	G	3710	216CW	PUMP            			CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					RIGHT SIDE SHAFT	SHEARED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7273Q	181  				20608045	L2694348A			RIGHT VACUUM PUMP FAILED, DRIVESHAFT SHEARED.  (X)						1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2000101900311	20001019	00311	SO  	2000	10	19	20001017SH036    	1	20000817	G	2823	491497	VALVE           			PIPER 	PA28  	PA28180     	7102808	SO  										CABIN SIDEWALL	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	7846W					281864				FUEL SELECTOR WAS FOUND STIFF AND HAD NO DETECTABLE DETENTS.  IN ADDITION, WHILE EXERCISING THE SELECTOR, IT WOULD OCCAS	IONALLY SEIZE UP IN RANDOM POSITIONS.  TEAR DOWN OF VALVE SHOWED THE DETENT RING HAD DEFORMED AND BROKEN IN TWO PIECES. 	 INTERNAL VALVE WEAR WAS MINIMAL.  AIRCRAFT RETURNED TO SERVICE WITH A NEW VALVE.  (X)				1	L	7	1 	3O			 	2A13    					 
2001020900019	20010209	00019	GL  	2001	2	9	20001017SH037    	1	20000916	G	7410	MILT7928	TERMINAL        			AMTR  	RF2000	RAF2000     	13017MN	GL  	AMTR  	SUBARU	EA81        	59050	GL  					IGNITION WIRE	BROKEN          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			LD	LANDING        	1			WP	25	86523	1124 				H2934104				AIRCRAFT FORCED TO EMERGENCY LAND AFTER ENGINE QUIT DURING LANDING.  AIRCRAFT IS AN AMATEUR BUILT GYRO PLANE.  THE ENGIN	E WAS A SUBURU WITH SINGLE COIL IGNITION SYSTEM.  POST-LANDING INSPECTION REVEALED THE COIL WIRE TERMINAL LUG BROKE OFF 	THE COIL WHICH TERMINATED IGNITION.  OPERATOR STATED HE ALWAYS CHECKS THESE CONNECTIONS DURING PRE-FLIGHTS BY GRASPING T	HEM FOR SECURITY CHECK.			1	G	7	1 	3O	3	O	NT	EXPA1G71	EXPA				 
2000101900312	20001019	00312	CE  	2000	10	19	20001017SH038    	1	20000912	G	7331	910532P	INDICATOR       			BEECH 	60    	A60         	1153604	CE  										FUEL FLOW	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	81AG					P219				INSTALLED SHADIN FUEL FLOW INDICATOR SYSTEM.  PROCESSOR LOCKED UP AND WOULD NOT FUNCTION ON SECOND TEST.  RETURNED TO FA	CTORY FOR SERVICE.  (X)					1	L	7	2 	3O			 	A12CE   					 
2000101900313	20001019	00313	CE  	2000	10	19	20001017SH039    	1	20000823	G	7810		PIPE            			CESSNA	172   	172C        	2072408	CE  	CONT  	O300  	O300D       	17022	SO  					MUFFLER ASSY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	8414X					17248914	34410D6D			COWL REMOVED FOR ANNUAL INSP, MASSIVE EXHAUST LEAKS APPARENT AT NR''S 2, 3, AND 4 EXHAUST FLANGES.  NR 2 WAS MISSING INB	D ATTACH NUT, NR''S 2 AND 4 INLET STACKS IMPROPERLY ORIENTED AND CAUSED FAILURE OF FLANGE GASKET, HAIRLINE CRACK IN MUFF	LER AT NR 4 INLET.  EXH LEAKAGE AT NR 3 CYL ERODED PORT AND MAY HAVE CAUSED WARPED EXH VALVE IN CYL.  ENG HAD 11.0 HRS T	SO, 31.0 HRS TSI.  REMOVAL OF MUFFLERS FOUND INTERNAL BAFFLES IN BOTH MUFFLERS BURNED AWAY.  (X)			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2000101900314	20001019	00314	SO  	2000	10	19	20001017SH040    	2	20000914	G	8550	7429322	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	LEAKING         	B			VJ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	8240T	1274 				CE1542	813973R			OIL LEAKING FROM VENT.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2000101900315	20001019	00315	SO  	2000	10	19	20001017SH041    	2	20000925	G	8530		CYLINDER HEAD   			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  					NR 5	DESTROYED       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			EA	21	8139Q	2756 	1356 			4140039	218930H			OFP - AFTER TAKEOFF IN VFR CONDITIONS, PILOT REPORTED ENGINE FIRE ON RIGHT ENGINE.  AFTER SAFE LANDING, AND INSPECTION O	F THE ENGINE REVEALED A 1.75 INCH HOLE IN THE SIDE OF NR 5 CYLINDER HEAD EXHAUST CHAMBER.  UPON TEAR-DOWN INSPECTION OF 	THE ENGINE AND ACCESSORIES, NO OTHER DEFECTS WERE NOTED.  POSSIBLE CAUSE TO HEAD FAILURE WAS DETERMINED TO BE AGE OF UNI	T AND CRACKING IN THIS HIGH STRESS AREA.  (X)			1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2000101900316	20001019	00316	SO  	2000	10	19	20001017SH042    	1	20000907	G	2434	4111809	ALTERNATOR      			PIPER 	PA28  	PA28181     	7102807	SO  										SOLDER TAB LNGTH	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	17	8366Z		53   			288190206				DURING TRAINING FLIGHT, PILOT NOTICED SEVERAL HIGH AMPERAGE SPIKES FOLLOWED BY A TOTAL LOSS OF ELECTRICAL OUTPUT FROM TH	E ALTERNATOR.  ALSO DAMAGED ELECTRICALLY WERE THE VOLTAGE REGULATOR AND OVERVOLTAGE RELAY.  POSSIBLE CAUSE FOUND DURING 	A BENCH CHECK OF AFFECTED ALTERNATOR, AN ARCING FROM FIELD TERMINAL LUG TO THE TIP OF THE REAR COOLING FAN.  ABRASIONS F	OUND ON ALL OF THE COOLING FAN TIPS INDICATED A CONTINUOUS ARCING HAD BEEN OCCURRING.  THE MATTER HAS BEEN BROUGHT TO TH	E ATTENTION OF THE ELECTROSYSTEMS, INC.  (X)		1	L	7	1 	3O			 	2A13    					 
2001020900020	20010209	00020	EU  	2001	2	9	20001017SH043    	1	20000818	G	2432	RG355	BATTERY         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL BOOM	CRACKED         	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	896WD	441  				2926				DURING 100-HR INSP, LEAD ACID BATTERY FOUND WITH A CASE CRACK IN THE LEFT FORWARD LOWER CORNER.  CRACK IS APPROX 1 INCH 	LONG.  BATTERY IS INSTALLED IN THE TAIL BOOM UNDER AN AEC STC AT APPROX 119.48 STA.  THE LEAD ACID BATTERY IS 41 POUNDS,	  NICAD IS 38 POUNDS.  TIME ON BATTERY IS 440 HOURS.  SUBMITTER SUGGESTED INCREASED WEIGHT OF THE BATTERY AND THE LOCATI	ON, THAT THE CASE OF THE BATTERY CANNOT STAND UP TO THE VIBRATIONS PUT ON IT IN THIS LOCATION.  THE ATTACHMENT BRACKET W	HERE THE BATTERY CLAMPS DOWN IS SQUARE CUT, NOT ROUNDED.  THIS MAY ALSO PUT UNDUE STRESS ON THE BATTERY BOX IN THE CORNE	RS.  STC SH5117NM BATT RELOC, STC SR09185RC NICAD LEAD ACID CONV, FIELD APPROVAL, COMBINED BOTH STC''S ON SAME ACFT.  (X	1	G	7	1 	3U			 	H9EU    					 
2000102500170	20001025	00170	CE  	2000	10	25	20001017SH045    	1	20000915	G	8011	MZ4222	STARTER         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					FRONT BEARING	DEFECTIVE       	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	9627Q		119  			17265711				FRONT BEARING WORKED OUT OF HOUSING IN 199 HOURS TIME IN SERVICE DUE TO INCORRECT BUSHING NOT PROPERLY FITTED IN HOUSING	.  INCORRECT PART SIZE, INCORRECT INSTALLATION.  OHC WOH 467690 6/10/00.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001022300015	20010223	00015	CE  	2001	2	23	20001018SH001    	1	20000831	G	3246	EDO688652	FLOAT           			CESSNA	175   	175         	2072502	CE  										RT FRONT STRUT	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	9366B					55166				RIGHT FRONT STRUT FLOATS CRACKED.  (X)						1	H	7	1 	3O			NT	3A17    					 
2001022300016	20010223	00016	CE  	2001	2	23	20001018SH003    	1	20000827	G	5312	07126261	BULKHEAD        			CESSNA	182   	182E        	2072712	CE  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	9327					18253727				VISUAL INSPECTION OF BULKHEAD REVEALED A HAIRLINE CRACK .25 INCH LONG AT THE LEFT RUDDER CABLE CUT-OUT IN THE OUTER RADI	US NEAREST THE BULKHEAD FLANGE.  AD 72-07-09 AND SL SE 72.3 REQUIRE INSPECTION OF THIS AREA AND BULKHEAD REPLACEMENT IF 	FOUND CRACKED.  SUBMITTER STATED THIS BULKHEAD WAS A REPLACEMENT AND IS THE SECOND ONE INSTALLED ON THIS AIRCRAFT.  (X)				1	H	7	1 	3O			NT	3A13    					 
2001021300001	20010213	00001	SW  	2001	2	13	20001018SH005    	1	20000822	G	5312		BULKHEAD        			BELL  	206   	206B        	1181511	SW  										FUSELAGE	CRACKED         	A			HSYA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	991FE					208B0127				BIL - DISCOVERED RIGHT BULKHEAD AT STA 385.6 CRACKED WHILE PERFORMING OTHER MAINTENANCE.  CRACKED APPROXIMATELY 80 PERCE	NT THROUGH INBOARD TO OUTBOARD NEAR LOWER ATTACH TO THE LEFT BULKHEAD.  REMOVED AND REPLACED THE RIGHT BULKHEAD, PN 2612	052-6, AT STA 385.6 PER THE IPC AND SRM.  INITIATED FAA FORM 337.  (X)				1	G	7	1 	3U			 	H2SW    					 
2001022300018	20010223	00018	CE  	2001	2	23	20001018SH006    	1	20000821	G	2820		FUEL LINE       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	VAPOR LOCK      	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	948SP					172S8144	L2812651A			AFTER 3RD SORTIE OF THE DAY, AIRCRAFT SAT FOR 45 MINUTES BEFORE NEXT FLIGHT.  ENGINE START WAS DIFFICULT USING HOT START	ING PROCEDURES WITH ENGINE RUNNING RPM WAS INCREASING AND DECREASING 200 RPM AND ENGINE OPERATION WAS ROUGH AND ERRATIC.	  AN ATTEMPT WAS MADE TO PURGE VAPORS IAW LYC''S PROCEDURE WITH NO EFFECT.  WHEN THROTTLE WAS RETURNED TO IDLE, ENGINE Q	UIT.  MAINTENANCE ATTEMPTED AN ENGINE START APPROX 15 MINUTES LATER AND WITH MIXTURE FULL OPEN AND BOOST PUMP ON, NO FUE	L FLOW INDICATED.  ENGINE VAPOR LOCKED.  RUN-UP NEXT MORNING NORMAL, NO VAPORIZATION PROBLEMS, SUBSEQUENT TEST FLIGHT SA	TISFACTORY.  MAINT COULD FIND NOTHING DEFECTIVE WHEN ENGINE INSPECTED.  (X)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000102500171	20001025	00171	SO  	2000	10	25	20001018SH007    	1	20000914	G	2710	62701125	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	2138 				3449043				LEFT AILERON BALANCE CABLE FRAYED AT WING ROOT PULLEY.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000102500172	20001025	00172	SO  	2000	10	25	20001018SH008    	1	20000915	G	2700	62701125	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	2138 				3449043				REAR TRIM CABLE FRAYED AT REAR DRUM.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000102500173	20001025	00173	CE  	2000	10	25	20001018SH009    	2	20000705	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					PISTON	STUCK           	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	9299E	156  				3449043	809256R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000102500174	20001025	00174	CE  	2000	10	25	20001018SH010    	2	20000921	G	7322	6493623	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  						STUCK           	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	9299E	674  				3449043				THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000102500175	20001025	00175	CE  	2000	10	25	20001018SH011    	2	20000510	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					PISTON	STUCK           	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	9299E	320  				3449043	819256R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000102500176	20001025	00176	SO  	2000	10	25	20001018SH012    	2	20000915	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					FUEL INJECTOR	DEFECTIVE       	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	4128X	120  				3449112	321749R			THROTTLE HARD TO MORE IN-FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED.  OVER FOUR POUNDS TO MOVE CONTROL.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000102500177	20001025	00177	CE  	2000	10	25	20001018SH013    	2	20000915	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					FUEL INJECTOR	DEFECTIVE       	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	120  				3449112	819255R			THROTTLE HARD TO MOVE IN-FLIGHT, SERVO REMOVED AND A NEW ONE INSTALLED.  OVER FOUR POUNDS TO MOVE CONTROL.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001020900021	20010209	00021	EU  	2001	2	9	20001018SH014    	1	20000726	G	6340	IPT20RT1100080G	TRANSMITTER     			BOLKMS	117   	BK117B1     	5626012	EU  										MAIN ROTOR	FLUCTUATES      	B			R7MR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	07	911VU	280  				7141				PRESSURE TRANSMITTER UNIT CAUSED PRESSURE GAUGE TO FLUCTUATE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001020900022	20010209	00022	EU  	2001	2	9	20001018SH015    	1	20000727	G	3340	2LA00162500	LIGHT           			BOLKMS	117   	BK117A4     	5626017	EU  										TAIL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911BY	512  				7127				CLEAR TAIL LIGHT WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001020900023	20010209	00023	EU  	2001	2	9	20001018SH016    	1	20000606	G	7931	DK042M0D01	TRANSMITTER     			BOLKMS	105   	BO105CBS    	5626008	EU  										OIL PRESSURE	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	911BH	117  				685				OIL PRESSURE TRANSMITTER UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H3EU    					 
2001022300019	20010223	00019	SO  	2001	2	23	20001018SH017    	1	20000828	G	7120	6711957	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  										ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	941NZ	7673 				28R7737172				ENGINE MOUNT CRACKED LOWER LEFT SIDE OF CENTER CROSS TUBE.  REQUIRED ENGINE REMOVAL.  VISUALLY SEEN DURING ANNUAL INSPEC	TION.  PAINT WAS STRIPPED IN THE CRACKED AREA AND A DYE CHECK WAS DONE TO CONFIRM THE CRACK.  (X)					1	L	7	1 	3O			 	2A13    					 
2001030200008	20010302	00008		2001	3	2	20001018SH024    	4	20000926	G	6122	20609	LEVER           	MCAULY      																GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					810290					RELEVANT MAGNETIC PARTICLE INDICATION ON LEVER ARM.  (X)																			 
2001022300021	20010223	00021		2001	2	23	20001018SH025    	4	20000928	G	6122	4030145	GOVERNOR        			BNORM 	BN2   	BN2         	1520202	EU  	LYC   	O540  	O540*       	41532	EA  					PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										RELEVANT PENETRANT INDICATION ON TOP OF GOVERNOR BODY.  RETIRED FROM SERVICE, UNAIRWORTHY.  (X)						1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2001022300022	20010223	00022	GL  	2001	2	23	20001018SH026    	3	20000921	G	6111	82NC55	BLADE           			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CORRODED        	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	401PC					401A0088		783251		PROPELLER BLADE CORRODED.  (X)						1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2001022300023	20010223	00023	GL  	2001	2	23	20001018SH027    	3	20000921	G	6111	82NC55	BLADE           			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CORRODED        	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	401PC					401A0088		952511		PROPELLER BLADE CORRODED.  (X)						1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2001030100025	20010301	00025	GL  	2001	3	1	20001018SH028    	3	20000925	G	6111	D7067	COUNTERWEIGHT   			CESSNA	401   	401A        	207590D	CE  						MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	401PC					401A0088		952511		RELEVANT MAGNETIC PARTICLE INDICATION.  (X)						1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2001020900024	20010209	00024	NE  	2001	2	9	20001018SH029    	1	20000816	G	6320	643520411102	GEAR            	SKRSKY      		SKRSKY	S64   	S64F        	       	NE  										M/R GEARBOX	FAILED          	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	163AC	3109 	699  		A6165	64093				1ST STAGE PLANETARY PINION GEAR, PN 6435-20411-102, SN 1524, UNKNOWN TT, FAILED IN MAIN GEARBOX, PN 6435-20500-049, SN A	6-165, LEAVING LARGE FRAGMENT OF FERROUS METAL IN SUMP, SUMP SCREEN.  TEARDOWN INSP REVEALED ENTIRE TOOTH FRACTURED AT J	UNCTION OF CASE TO CORE.  SECONDARY DAMAGE FOUND ON 3 EACH 2ND STAGE PLANETARY PINION GEARS, PN 6435-20057-012, RING GEA	R, PN 6435-20165-012, AND 1ST STAGE SUN GEAR, PN 6435-20412-102, ALL OF WHICH WERE BLENDED, RETURNED TO SERVICE.  DURING	 OPERATION, CREW HEARD A LOUD NOISE AND EXPERIENCED A VIBRATION PRIOR TO REGISTERING A CHIP LIGHT.  A PREVIOUS MDR WAS S	UBMITTED 4-20-00, SAME PN GEAR FRACTURED A GEAR TOOTH AT 697.0 HRS ON DIFFERENT GEARBOX.  (X)	2	G	7	2 	4U			 	H6EA    					 
2001020100054	20010201	00054	EU  	2001	2	1	20001018SH030    	1	20000830	G	6730	AC67244	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					MAIN ROTOR	BINDING         	A			HLXA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	126TV	1792 				2944	9447			SERVO CONTROL REMOVED DUE TO CYCLIC BINDING.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001022300020	20010223	00020	CE  	2001	2	23	20001018SH031    	1	20001015	G	7110	J744436	MOUNT           			CESSNA	172   	172R        	2072401	CE  										COWLING	TORN            	H				K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			SW	99	869CP	1388 				17280641				CONDITION: COWLING MOUNT TORN.  CORRECTIVE ACTION:   REPLACED WITH NEW.  (X)						1	H	7	1 	3O			NT	3A12    					 
2001022300024	20010223	00024	SO  	2001	2	23	20001019SH001    	2	20000908	G	7314	7429322	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	DEFECTIVE       	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1569P	673  				CE1300	820276R			UNABLE TO ADJUST FUEL FLOW TOP END AND IDLE MIXTURE.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001020900025	20010209	00025	EU  	2001	2	9	20001019SH002    	1	20000925	G	6220	350A37124420	BOLT            			SNIAS 	350   	AS350B1     	8680811	EU  										MAIN ROTOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	13HF	980  				2267				BROKEN BOLT FOUND ON PRE-FLIGHT INSPECTION.  HELICOPTER IS USED FOR MULTIPLE ROLES INCLUDING PERSONNEL TRANSPORT, EXTERN	AL LOAD, WATER DROPPING, AND RECONNAISSANCE.  CAUSE IS UNKNOWN AT THIS TIME, BUT IS BEING DETERMINED.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001020900026	20010209	00026	SW  	2001	2	9	20001019SH003    	1	20000720	G	6310	70061G00DX116	LINE            			BELL  	206   	206B        	1181511	SW  										FREEWHEEL UNIT	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	59617					1517				FOUND SEEPAGE ON POST-FLGIHT INSPECTION, VERY HOT DAY.  REPLACED HOSE.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900027	20010209	00027	GL  	2001	2	9	20001019SH004    	2	20000825	G	7200		ENGINE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENG BAY	MAKING METAL    	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	15	1585W	2286 				2516	CAE831404			ENGINE PRODUCED CHIP LIGHTS.  REMOVED CHIP DETECTOR, CLEANED, RE-INSTALLED.  RAN ENGINE 30 MINUTES AND FOUND MORE CHIPS.	  REMOVED ENGINE AND SENT FOR REPAIR.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001020900028	20010209	00028		2001	2	9	20001019SH006    	4	20000922	G	3421	4021541671	GYRO            			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	MISREPAIRED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	13	217MC					7195				GYRO HORIZON WAS RETURNED FROM REPAIR STATION WITH 8130-3 TAG INDICATING ''REPAIRED''.  AFTER INSTALLATION AND FUNCTIONA	L TEST, THE UNIT WAS DETERMINED TO HAVE SAME SYMPTOMS AS ORIGINAL.  THE UNIT SHOWED NO EVIDENCE THAT IT WAS EVER REPAIRE	D.  NO ''DO NOT BREAK SEAL'' STICKER, ETC.  (X)				1	G	7	2 	3U			 	H13EU   					 
2001022300026	20010223	00026	SO  	2001	2	23	20001019SH007    	2	20000901	G	8550	LW13388	SEAL            			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					OIL FILTER	FAILED          	H				O				OTHER                   				M	Y		OVER TEMP                 	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CE	05	28WC	373  				32RT7885055	L1574648A			SEAL SOFTENED, SWELLED, RUPTURED.  NIGHT, PART 135 FLIGHT LOST OIL, ENGINE SEIZED.  SEAL MATERIAL NOT OIL PROOF.  SUBMIT	TER SUGGESTED RETURNING TO ORIGINAL MATERIAL.  (X)					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001022300028	20010223	00028	CE  	2001	2	23	20001019SH009    	1	20000922	G	3230	50410011	BOLT            			CESSNA	402   	402B        	207590P	CE  										LT MLG BELLCRANK	SHEARED         	E				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	3131K					402B0248				BOLT, P/N NAS464P4, SHEARED CAUSING SIDE LOAD ON THE BELLCRANK BREAKING THE ATTACH POINT AT THE GEAR LIGHT SAFETY SWITCH	.  (X)					1	L	7	2 	3O			 	A7CE    					 
2001022300029	20010223	00029	CE  	2001	2	23	20001019SH011    	1	20001002	G	3250	50420101	BELLCRANK       			CESSNA	401   	401         	207590C	CE  										NLG STEERING	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3260Q	9000 				4010060				DURING 100-HOUR INSPECTION, FOUND CRACK IN THE RADIUS OF THE CENTER ATTACH POINT AT BELLCRANK.  CAUSE UNKNOWN.  (X)						1	L	7	2 	3O			 	A7CE    					 
2001022300030	20010223	00030	GL  	2001	2	23	20001019SH012    	3	20000927	G	6110		PROPELLER       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	325SP	944  				172S8251		TF047		PROPELLER SUBMITTED FOR SB 233A COMPLIANCE.  PROPELLER FOUND CRACKED AS INDICATED IN THE SERVICE BULLETIN, IN THE PILOT 	BORE, FACE SIDE OF THE PROPELLER.  PROPELLER IS TO BE RETURNED TO MANUFACTURER FOR DISPOSITION.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001022300031	20010223	00031	EA  	2001	2	23	20001019SH013    	2	20000711	G	7414	ES10349276	CONDENSER       	BENDIX      		CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  					MAGNETO	INOPERATIVE     	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SO	13	34194	1    				17701692	L1633536A			THE AIRCRAFT MADE AN EMERGENCY LANDING IN A FIELD AFTER A LOSS OF ENGINE POWER.  INSPECTION BY A MECHANIC REVEALED THE P	OINTS WERE BURNED AND THE CONDENSER WERE PART OF A NEWLY INSTALLED FACTORY REMANUFACTURED MAGNETO.  THE POINTS AND CONDE	NSER WERE REPLACED, AND THE MAGNETO REINSTALLED AND RETURNED TO ENGINE.  ENGINE PERFORMED SATISFACTORILY.  (X)				1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2001022300032	20010223	00032	SO  	2001	2	23	20001019SH014    	1	20000831	G	3211		CASTING         			LKHEED	12A   	12A         	5261402	SO  										RT WW	FAILED          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	09	33RA					1239				RIGHT FLANGE OR GEAR DRIVE CASTING FAILED UNDER LOAD DURING LANDING.  THIS CAUSED THE JACK SCREW TO BEND ALLOWING THE RI	GHT MAIN LANDING GEAR TO COLLAPSE.  (X)					1	L	7	2 	3R			 	TC616   					 
2001022300033	20010223	00033	SO  	2001	2	23	20001019SH015    	1	20001011	G	2722	480735	ROLL PIN        			PIPER 	PA31  	PA31350     	7103110	SO  										ACTUATOR	BACKED OUT      	I			WVBA	K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AL	01	42WP					318252038				PILOT RETURNED FROM FLIGHT, REPORTED RUDDER TRIM INOPERABLE.  FOUND ONE OF THE TWO ROLL PINS THAT SECURE THE ROD END THA	T CONNECTS THE ACTUATOR SCREW TO THE TRIM TAB PUSH/PULL TUBE HAD MIGRATED ALMOST COMPLETELY OUT, THE OTHER ROLL PIN WAS 	MISSING.  THIS CAUSED ROD END TO DISCONNECT FROM ACTUATOR SCREW RENDERING THE TRIM INOPERABLE.  TWO NEW PINS INSTALLED, 	SAFTIED WITH .032 INCH WIRE.   REF:  AC65-9A, PG 145; AC43.13-1B, PG 7-17 (7-104).  (X)			1	L	7	2 	3O			 	A20SO   					 
2001022300034	20010223	00034	CE  	2001	2	23	20001019SH016    	2	20000908	G	8530	649264	TUBE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					INTAKE	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	1241 				3449128	322265L			INSPECTION OF INTAKE FOUND NR 2 INTAKE TUBE CRACKED AT THE FLANGE.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022300035	20010223	00035	SO  	2001	2	23	20001019SH017    	2	20000921	G	7322	RSA5AD	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUEL INJECTOR	MALFUNCTIONED   	B			VJ3R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			WP	07	4128X					3449112	321749R			IN-FLIGHT, WHEN MIXTURE WAS LEANED TO CRUISE SETTING AT ABOUT 9 GALLON/HOUR, THE MIXTURE WENT UP TO 3 GALLONS PER HOUR. 	 SERVO REMOVED AND A NEW ONE INSTALLED IAW PIPER MANUAL.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022300036	20010223	00036	SO  	2001	2	23	20001019SH018    	1	20000918	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										AILERON	FRAYED          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4177R	2345 				3449046				LEFT AILERON BALANCE CABLE FRAYED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2001022300037	20010223	00037	SO  	2001	2	23	20001019SH019    	1	20000918	G	2710	62701123	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										AILERON	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4175V	2340 				2843126				LEFT HAND AILERON BALANCE CABLE FRAYED, LOCATED UNDER THE REAR SEATS.  (X)						1	L	7	1 	3O			 	2A13    					 
2001022300038	20010223	00038	SO  	2001	2	23	20001019SH020    	1	20000918	G	2740	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STABILATOR	FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4134T	1540 				2843208				FORWARD STABILATOR CABLE FRAYED.  (X)						1	L	7	1 	3O			 	2A13    					 
2001022300039	20010223	00039	SO  	2001	2	23	20001019SH021    	2	20000908	G	7322	6493623	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUAL CONTROL	STUCK           	B			VJ3R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			WP	07	4142N	1241 				3449128	322021R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022300040	20010223	00040	CE  	2001	2	23	20001019SH022    	1	20000917	G	3230	NAS5055J	BEARING         			BEECH 	95    	95B55       	1152729	CE  										LT MLG	SEIZED          	G				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			EA	21	4464S					TC1878				INCIDENT INVESTIGATION AFTER LEFT MAIN GEAR FAILED TO EXTEND (BOTH NORMAL AND EMERGENCY), FOUND UPLOCK ROLLER BEARING SE	IZED.  WOULD NOT ROTATE.  AD 72-22-01 IS NOT APPLICABLE PER SERIAL NUMBER OF AIRCRAFT.  THE UPLOCK ROLLER CLEARANCE BETW	EEN BEARING (NAS505-5J) AND UPLOCK BLOCK (35-815077-4) WAS FOUND TO BE INSUFFICIENT PER MM SPEC''S.  THE (35-815156-4) I	CE BOOT WAS FOUND TORN AND WEDGED BETWEEN THE WING SHIM AND UPLOCK ASSY WITH THE GEAR RETRACTED.  LAST ANNUAL INSPECTION	 COMPLETED 11/99.  SUBMITTER RECOMMENDED TO CLOSELY FOLLOW MANUFACTURER''S INSPECTION GUIDE TO ENSURE PROPER GEAR RIGGIN	G AND LUBRICATION.  (X)	1	L	7	2 	3O			RT	3A16    					 
2001022300041	20010223	00041	CE  	2001	2	23	20001019SH023    	1	20001004	G	2720		NUT             			CESSNA	172   	172S        	2072439	CE  										RUDDER PEDAL	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	571SP	195  				172S8496				DURING A 100-HOUR INSPECTION, THE COPILOT''S LEFT PEDAL LOWER BOLT AND NUT WERE FOUND LOOSE.  THE NUT WAS STILL IN NEW C	ONDITION AND HAD NEVER BEEN PROPERLY TORQUED.  THE PLASTIC SELF-LOCKING FEATURE OF THE NUT HAD NEVER BEEN ENGAGED AND NO	 TORQUE SEAL HAD BEEN APPLIED.  (X)				1	H	7	1 	3O			NT	3A12    					 
2001022300044	20010223	00044	EA  	2001	2	23	20001019SH027    	2	20000929	G	8550	LW13388	GASKET          			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  					OIL FILTER	LEAKING         	B			BF8S	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	66340	1707 				ME241	L29471A			DURING ROUTINE MAINTENANCE, FOUND OIL FILTER CONVERTER GASKET LEAKING.  AD 2000-18-53 DID NOT APPLY DUE TO INSTALLATION 	DATE OF GASKET (12-18-97 OVERHAUL DATE).  GASKET REPLACED WITH CHAMPION GASKET PN CH48211.  RUN AND LEAK CHECK GOOD.  OL	D GASKET DID NOT APPEAR TO HAVE EXTRUDED.  (X)				1	L	7	2 	3O	3	O	 	A29CE   	1E10				 
2001022300045	20010223	00045	EA  	2001	2	23	20001019SH028    	2	20000825	G	8550		PLUG            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE SUMP	MISSING         	D				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			SW	15	82149	3953 	557  			17267692	L132076			AIRCRAFT WAS FLYING FROM TULSA/SILOAM SPRINGS, 8 MILES FROM SILOAM SPRINGS AIRPORT, PILOT REPORTED THE ENGINE OIL PRESSU	RE WAS FLUCTUATING FROM ZERO TO 60 PSI.  ENGINE THEN STARTED TO VIBRATE SEVERELY BEFORE ENGINE COMPLETELY STOPPED.  UPON	 INSPECTION OF AIRCRAFT, FOUND THE OIL QUICK DRAIN MISSING WHICH OBVIOUSLY CAUSED ENGINE TO LOSE OIL PRESSURE.  SUBMITTE	R STATED QUICK DRAIN INSTALLED DID NOT HAVE A PROVISION FOR SAFETY WIRE.   (X)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001022300046	20010223	00046	EA  	2001	2	23	20001019SH029    	2	20000928	G	7230	3013340	CASE            			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  					LEFT ENGINE	CRACKED         	B			TIMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	899CA	34511				U104				DURING PROPELLER CHANGE ON LEFT ENGINE, A SERIES OF CRACKS WERE FOUND ON THE INBOARD EXHAUST FLANGE.  THE FLANGE IS A PA	RT OF THE POWER SECTION, SO FIELD REPAIR WAS NOT POSSIBLE.  THE AFFECTED POWER SECTION WAS REPLACED WITH A SERVICEABLE P	OWER SECTION.  A POSSIBLE CAUSE FOR THE CRACKED FLANGE MAY HAVE BEEN THE RESULT OF OVERTORQUING THE HARDWARE ATTACHING T	HE EXHAUST STACKS TO THE FLANGE.  (X)			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001022300047	20010223	00047	CE  	2001	2	23	20001019SH030    	2	20000921	G	7322	RSA5AD2	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					FUEL INJECTION	FAULTY          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	130  				3449043	819507R			THROTTLE HARD TO MOVE, CHECKED FORCE TO MOVE THROTTLE ON THE GROUND AND FOUND OVER SPECS.  SERVO REMOVED AND A NEW ONE I	NSTALLED IAW PIPER MANUAL.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001020900029	20010209	00029	SW  	2001	2	9	20001019SH031    	1	20000710	G	6220	204011110005	BEARING         			BELL  	212   	212         	1181420	SW  										M/R HUB	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	911KW	1929 			A60	30592				DURING A POST-FLIGHT INSPECTION, DARK BLACK GREASE WAS FOUND ON THE M/R TRUNNION.  REMOVED AND DISASSEMBLED M/R TRUNNION	.  ONE TRUNNION BEARING HAD TOTALLY FAILED.  INNER AND OUTER  RACES WERE BROKEN.  (X)					1	G	7	1 	4U			 	H4SW    					 
2001020900030	20010209	00030	SW  	2001	2	9	20001019SH032    	1	20000928	G	6220	2040111105	BEARING         	BELL        		BELL  	212   	212         	1181420	SW  										M/R TRUNNION	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	911VR	1842 			ADA01108	30998				DURING MAINTENANCE CHECKS, WHITE M/R BLADE TRUNNION BEARING GREASE WAS FOUND TO BE DARKER THAN RED BLADE.  GRAY/RED IN C	OLOR.  REMOVED AND REPLACED M/R TRUNNION BEARINGS WITH NEW BEARINGS.  WHILE BLADE BEARING SHOWS SIGNS OF ADVANCED BRINNE	LLING.  SUBMITTER STATED THIS IS THE SECOND OCCURRENCE THIS YEAR ON FLEET, PLUS ONE OTHER FROM ANOTHER OPERATOR.   REF: 	 OPER CNTRL NR 20001019SH031.  (X)			1	G	7	1 	4U			 	H4SW    					 
2001022300048	20010223	00048	SO  	2001	2	23	20001023SH001    	1	20000828	G	2913	HYC5005	MOTOR           			PIPER 	PA28  	PA28RT201   	7102818	SO  										POWERPACK	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	366LC		208  			28R8218005				MOTOR QUIT.						1	L	7	1 	3O			 	2A13    					 
2001022300049	20010223	00049	CE  	2001	2	23	20001023SH002    	2	20000908	G	8530	649264	TUBE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					NR 2 INTAKE	CRACKED         	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	1282 				3449128	322265L			INSPECTION OF INTAKE FOUND NR 2 INTAKE TUBE CRACKED AT THE FLANGE.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000102400278	20001024	00278	GL  	2000	10	24	20001023SH004    	3	20000921	G	6110	B3490	LINK            	MCAULY      		CESSNA	402   	402CESSNA   	207590K	CE  						MCAULY	3AF32C	3AF32C87    	GL  	BLADE & PCR	DAMAGED         	B				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	11								803995		DURING PREFLIGHT INSPECTION, OPERATOR FOUND BLADE TO BE LOOSE.  THE PROPELLER WAS REMOVED FROM AIRCRAFT AND SENT FOR REP	AIR.  DURING DISASSEMBLY, THE BLADE LINK SNAP RING WAS NOT INTACTED.  THE PROPELLER RECEIVED A COMPLETE OVERHAUL WITH RE	PLACEMENT OF ALL UNAIRWORTHY PARTS.  (X)				1	L	7	2 	3O			 	A7CE    		5	C	P22EA	 
2001011101194	20010111	01194	NE  	2001	1	11	20001024SH001    	2	20000829	G	7320	4050582G02	VALVE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581402    	30011	NE  					NR 2 ENGINE	BROKEN          	A			ERAA	B	A	E		EMER. DESCENT           	UNSCHED LANDING         	ENGINE SHUTDOWN         		K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AL	03	563EH	12474	89   			61808	295246			DEPARTED MC822 EN ROUTE TO VENICE.  DURING LETDOWN TO VENICE, A SLIGHT FUEL ODOR DETECTED.  AS POWER INCREASED TO LEVEL 	AT 500 FEET, NR 2 ENGINE CAME OFF-LINE.  N1 NOTED AT APPROX 60 PERCENT, TORQUE AT 20-30 PERCENT, NF HAD SPLIT FROM NR 1 	NF.  A STRONG FUEL ODOR NOTED.  NR 2 ENGINE SECURED PER EMERGENCY ACTION CHECKLIST.  A RUNNING LANDING PERFORMED, ACFT L	ANDED WITH NO DAMAGE.  SUBSEQUENT PRELIMINARY INSP REVEALED FLOW DIVIDER FAILED CAUSING LOSS OF FUEL TO ENGINE.  RECOMME	NDATION TO PRECLUDE RECURRENCE:  FOLLOW UP 9-19-00.  FLOW DIVIDERS ON ALL ENGINES WERE REMOVED AND THE TEMP VALVES NDT I	NSPECTED AND RE-ASSEMBLED.  NO DEFECTS NOTED, SERVICEABLE UNITS REINSTALLED.  (X)	2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001020900045	20010209	00045	SW  	2001	2	9	20001024SH002    	1	20000816	G	6510	407340340101	DISC PACK       	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	184  			A823	53054				DURING 25-HOUR AD INSPECTION, FOUND FORWARD SEGMENT CRACKED ACROSS ONE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001022600003	20010226	00003	NE  	2001	2	26	20001024SH004    	2	20000927	G	7230	1711M20P08	SEAL            								GE    	GE90  	GE9090B     	 	NE  					HP INTERSTAGE	CRACKED         	B			QEMY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	9KAOA						900211			SEAL EXHIBTS TWO SHORT CRACKS, 0.150 INCH LENGTH EACH, IN THE FORWARD ARM OUTSIDE DIAMETER AT THE STAGE 1 BLADE INTERFAC	E.  THIS PART HAD ACCUMULATED 954 CSN.  (X)										4	F			E00049EN				 
2001022300050	20010223	00050	CE  	2001	2	23	20001024SH005    	1	20000920	G	2810	509215873	GASKET          			BEECH 	200   	B200        	1152922	CE  										FUEL GASKET	SPLIT           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	14		529  				BB1194				GASKET SPLITTING AND FUEL LEAKING FROM NACELLE AND AUXILIARY TANKS INTO ENGINE EXHAUST PATH.  AIRCRAFT N NR YV0988CP.   	(X)					1	L	7	2 	4T			 	A24CE   					 
2001022600004	20010226	00004	CE  	2001	2	26	20001024SH006    	1	20000920	G	2810	509215875	GASKET          			BEECH 	200   	B200        	1152922	CE  										FUEL GASKET	SPLIT           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	14		529  				BB1194				GASKET SPLITTING AND FUEL LEAKING FROM NACELLE AND AUXILIARY TANKS INTO ENGINE EXHAUST PATH.  AIRCRAFT N NR YV-988CP.  (	X)					1	L	7	2 	4T			 	A24CE   					 
2001030200009	20010302	00009		2001	3	2	20001024SH012    	4	20001002	G	2562	P3030029010	ELT             	BFGOODRICH  																LIFE RAFT	FAILED          	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	19					10R437					ELT FAILED, UNABLE TO TRANSMIT SIGNALS.  ELT PACKED IAW OEM MANUAL INSTRUCTIONS.  ELT MODEL SRB-10.  (X)																			 
2001030200010	20010302	00010		2001	3	2	20001024SH013    	4	20000902	G	2562	P3030029010	ELT             	BFGOODRICH  																LIFE RAFT	FAILED          	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R427					ELT FAILED, UNABLE TO TRANSMIT SIGNALS.  ELT PACKED IAW OEM MANUAL INSTRUCTIONS.  ELT MODEL SRB-10.  (X)																			 
2001030200011	20010302	00011		2001	3	2	20001024SH014    	4	20000829	G	2562	P3030029010	ELT             	BFGOODRICH  																LIFE RAFT	FAILED          	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R215					ELT FAILED, UNABLE TO TRANSMIT SIGNALS.  ELT PACKED IAW OEM MANUAL INSTRUCTIONS.  ELT MODEL SRB-10.  (X)																			 
2001030200012	20010302	00012		2001	3	2	20001024SH015    	4	20000608	G	2562	P3030029010	ELT             	BFGOODRICH  																LIFE RAFT	FAILED          	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R210					ELT FAILED, UNABLE TO TRANSMIT SIGNALS.  ELT PACKED IAW OEM MANUAL INSTRUCTIONS.  ELT MODEL SRB-10.  (X)																			 
2001030200020	20010302	00020		2001	3	2	20001024SH023    	4	20001018	G	2562	SRB10	ELT             	BFGOODRICH  																LIFE RAFT	FAILED          	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R214					DURING THE FUNCTIONAL TESTING OF THE ELT, IT DID NOT TRANSMIT ANY SIGNALS.  THE BATTERY WAS REPLACED WITH A BATTERY THAT	 TESTED OKAY ON OTHER ELT''S, BUT THE ELT WOULD STILL NOT TRANSMIT.  (X)																		 
2001030200021	20010302	00021		2001	3	2	20001024SH024    	4	20001015	G	2562	SRB10	ELT             	BFGOODRICH  																LIFE RAFT	FAILED          	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R211					DURING THE FUNCTIONAL TESTING OF THE ELT, IT DID NOT TRANSMIT ANY SIGNALS.  THE BATTERY WAS REPLACED WITH A BATTERY THAT	 TESTED OKAY ON OTHER ELT''S, BUT THE ELT WOULD STILL NOT TRANSMIT.  (X)																		 
2001011101195	20010111	01195	CE  	2001	1	11	20001025SH001    	1	20001024	G	2721	556544060	ROD             			CESSNA	500   	550         	2076604	CE  										RUDDER TRIM	SPLIT           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	71GA					5500444				AIRCRAFT STRIPPED FOR PAINT.  AFTER P/N 5565440-60 RUDDER TRIM ROD (LOWER) PAINTED, BUBBLES APPEARED UNDER PAINT, PAINT 	CRACKED, SPLIT ABOUT 2 INCHES LONG IN ROD, VISUALLY SEEN.  (X)					1	L	7	2 	4F			 	A22CE   					 
2000103100114	20001031	00114	CE  	2000	10	31	20001025SH002    	1	20000906	G	2810	509215873	GASKET          			BEECH 	90    	F90         	1152909	CE  										FUEL GASKET	SPLIT           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	14	333WT					LA91				GASKET SPLITTING AND FUEL LEAKING FROM NACELLE INTO ENGINE EXHAUST PATH.  (X)						1	L	7	2 	4T			 	A31CE   					 
2001030100026	20010301	00026	EU  	2001	3	1	20001025SH003    	1	20000901	G	6710	1174120101	JACKSHAFT       			BOLKMS	117   	BK117A1     	5626010	EU  										M/R CONTROLS	CORRODED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117LF	7928 				7013				DURING INSPECTION, FOUND MASSIVE AMOUNTS OF CORROSION INSIDE CYCLIC JACKSHAFT.  MANUFACTURER ALLOWS .4MM.  IT APPEARS LI	TTLE OR NO PAINT TREATMENT ON INTERIOR OF STEEL TUBE.  THE TUBE HAS CASTINGS ON EACH END ANGLED UP AT 45 DEGREES WHICH I	NCREASES CHANCE OF GETTING FLUIDS INSIDE.  THERE ARE NO PROVISIONS FOR DRAINAGE.  SUBMITTER SUGGESTED MANUFACTURER TREAT	 INTERIOR AND PROVIDE DRAINAGE. (X)			1	G	7	2 	3U			 	H13EU   					 
2000103100113	20001031	00113	CE  	2000	10	31	20001025SH004    	1	20000825	G	2810	509215873	GASKET          			BEECH 	90    	C90         	1152913	CE  										FUEL	SPLIT           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	14	34CE					LJ932				GASKET SPLITTING AND FUEL LEAKING FROM NACELLE INTO ENGINE EXHAUST PATH.  (X)						1	L	7	2 	3T			 	3A20    					 
2000103100139	20001031	00139	SO  	2000	10	31	20001025SH005    	1	20001018	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  										LT MAIN GEAR	BROKEN          	A			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	300ED					317852008				PILOT REPORTED GEAR DOOR BROKEN.  DISCOVERED FORWARD HINGE ON LEFT MAIN GEAR DOOR BROKEN IN HALF AND GEAR DOOR BENT FROM	 CONTACT WITH MAIN GEAR WHEEL.  A NEW DOOR INSTALLED AND AIRCRAFT RETURNED TO SERVICE.  SUBMITTER RECOMMENDED THESE HING	ES BE STRIPPED OF PAINT PRIOR TO INSTALLATION TO FACILITATE PROPER INSPECTION OF THE LARGE INNER RADIUS OF THE HINGE FOR	 CRACKING.  NOTE:  BROKEN HINGE PN 47529-32 IS CORRECT.  PART IAW AD 80-2605.  (X)			1	L	7	2 	3O			 	A20SO   					 
2000103100025	20001031	00025	CE  	2000	10	31	20001025SH006    	1	20001005	G	3230	50450101	TORQUE TUBE     			CESSNA	401   	401         	207590C	CE  										RT WW	SEPARATED       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3260Q					4010060				PUSH/PULL ROD PN 5045213-2, PULLED OUT OF TORQUE TUBE ASSY, PN 50450104.  CAUSE UNKNOWN.  (X)						1	L	7	2 	3O			 	A7CE    					 
2000103100026	20001031	00026	EA  	2000	10	31	20001025SH007    	2	20000921	G	8530	77569	SEAL            			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					INTAKE MANIFOLD	MISSING         	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NE	05	47985	44   				28R7837021	RL2171851A			AIRCRAFT OWNER, PILOT, COMPLAINED OF PROGRESSIVELY WORSENING BAD IDLE, ABNORMALLY HIGH MANIFOLD PRESSURE AT REDUCED POWE	R SETTINGS AND AFTERFIRING ON THROTTLE REDUCTION AND HIGH EGT READY ON NR 3 CYLINDER.  AFTER CHECKING COMPRESSION AND FU	EL NOZZLES, THE COWL WAS REMOVED, NR 3 AND NR 1 INTAKE SEALS WERE FOUND PARTIALLY INGESTED.  NO PIECES HAD SEPARATED AND	 WENT INTO THE MANIFOLD.  THE SEALS AND GASKETS ON THE FLANGES WERE REPLACED AND THE ENGINE RAN-UP NORMALLY.  (X)			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2000103100102	20001031	00102	CE  	2000	10	31	20001025SH008    	1	20000901	G	2916	511700712	SIGHT GAUGE     			CESSNA	402   	402C        	207590R	CE  										HYDRAULIC TANK	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			SW	07	402GR					402C0035				HOLE IN SIGHT GAUGE (TUBE) APPEARS TO BE CAUSED BY HEAT, LOST FLUID.  NOSE GEAR DID NOT EXTEND.  LANDING WAS MADE WITH N	OSE GEAR UP.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000103100030	20001031	00030	CE  	2000	10	31	20001025SH009    	1	20001009	G	2810	509215873	GASKET          			BEECH 	90    	C90A        	1152911	CE  											SPLIT           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	14	488XJ	753  				LJ1527				GASKET SPLITTING AND FUEL LEAKING FROM NACELLE INTO ENGINE EXHAUST PATH.  (X)						1	L	7	2 	3T			RT	3A20    					 
2000103100031	20001031	00031	SO  	2000	10	31	20001025SH010    	1	20000929	G	2750	8776541	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										FLAP SELECTOR	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	1392 				3449128				FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLEYS AT THE FLAP SELECTOR.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000103100032	20001031	00032	SO  	2000	10	31	20001025SH011    	1	20000929	G	2710	62701127	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  											FRAYED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	1392 				3449128				RIGHT AILERON CABLE FRAYED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000103100033	20001031	00033	SO  	2000	10	31	20001025SH012    	1	20001003	G	2740	62701104	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STAB TRIM	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4141U	2440 				2843125				TRIM CABLE FRAYED (FORWARD).  (X)						1	L	7	1 	3O			 	2A13    					 
2000103100034	20001031	00034	SO  	2000	10	31	20001025SH013    	1	20001003	G	2740	62701104	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										STAB RIM	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4141U	2440 				2843125				TRIM CABLE FRAYED (FORWARD).  (X)						1	L	7	1 	3O			 	2A13    					 
2000103100035	20001031	00035	SO  	2000	10	31	20001025SH014    	1	20000929	G	2750	8776541	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										TE FLAPS	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	1445 				3449112				FLAP SELECTOR CABLE FRAYED WHERE THE CABLE GOES AROUND THE PULLEYS AT THE FLAP SELECTOR.  (X)						1	L	7	2 	3O			 	A7SO    					 
2000103100024	20001031	00024	SO  	2000	10	31	20001025SH015    	1	20001003	G	2710	62701125	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										AILERON	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4128X	1447 				3449112				AILERON CONTROL CABLE FRAYED.  (X)						1	L	7	2 	3O			 	A7SO    					 
2001020900048	20010209	00048	SW  	2001	2	9	20001025SH016    	1	20000905	G	6510	407340340101	DISC PACK       	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL	170  			A657	53247				DURING 25-HOUR AD INSPECTION, FOUND FORWARD SEGMENT CRACKED ACROSS THE SPAN.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001022300051	20010223	00051	CE  	2001	2	23	20001025SH019    	1	20000909	G	2810	509215873	GASKET          			BEECH 	200   	B200        	1152922	CE  										FUEL GASKET	SPLIT           	B			VG4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	35	523GM					BB1598				GASKET SPLITTING AND FUEL LEAKING FROM NACELLE AND AUXILIARY TANKS INTO ENGINE EXHAUST PATH.  (X)						1	L	7	2 	4T			 	A24CE   					 
2001022600005	20010226	00005	SO  	2001	2	26	20001025SH020    	1	20001013	G	3222	6332906	FORK            			PIPER 	PA28  	PA28140     	7102802	SO  										NLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5926U	5848 				2826739				DURING ANNUAL INSPECTION, DISCOVERED EXFOLIATION CORROSION ON INNER SURFACE OF FORK.  AREA OF CORROSION WAS .50 INCH WID	E, 3.50 INCHES LONG, AND .10 INCH KEEP.  STARTING FROM UPPER ANCHOR NUT ON LT SIDE AND EXTENDING UPWARD AROUND UPPER/INN	ER CURVE.  REPLACED FORK ASSEMBLY.  FORK IS ALUMINUM AND ANCHOR NUT IS STEEL, POSSIBLE DISSIMILAR METAL CORROSION IN ADD	ITION TO EXFOLIATION/INTERGRANULAR.  (X)			1	L	7	1 	3O			 	2A13    					 
2001022600006	20010226	00006	CE  	2001	2	26	20001025SH021    	1	20001025	G	2810		LINER           	RAYTHN      		BEECH 	35    	J35         	1151522	CE  										FUEL BLADDER	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	8233D	6254 				D5335				REMOVED BOTH MAIN FUEL BLADDERS DUE TO LEAKAGE.  FOUND CORROSION UNDER FUEL BLADDERS.  ATTEMPTED TO CLEAN CORROSION USIN	G ACID ETCHING, LT BAY LINER HAD EXTENSIVE PITTING AND BLISTERING WHILE WORKING CORROSION WITH ABRASIVE WHEEL.  FOUND CO	RROSION HAD EATEN THROUGH LINER IN ONE SPOT.  TANKS APPEAR TO BE ORIGINALS, BOTH HAD 1957 DATES OF MFG STAMPED ON THEM. 	 WATER APPEARED TO HAVE ENTERED AROUND MAIN FUEL CAP ACCESS PLATE THEN COLLECTED BETWEEN BLADDER AND BAY LINER.  AFT WAL	L OF MAIN FUEL BAY IS THE WING SPAR.  SUBMITTER RECOMMENDED SEALING PANEL WITH SEALING COMPOUND ON INSTALLATION, REMOVIN	G BLADDERS AND INSPECTING BAY IF TANKS HAVE NOT BEEN REPLACED.  (X)	1	L	7	1 	3O			 	3A15    					 
2001020900052	20010209	00052	SW  	2001	2	9	20001026SH001    	1	20000602	G	6320	6893673	GEAR            	ALLSN       	C47B        	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	BROKEN          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	687AL	3100 	2958 		CAG47017	53366	CAE847018			CHIP LIGHT WAS DETECTED ON AIRCRAFT.  CHIP DETECTORS WERE PULLED AND INSPECTED.  LARGE PIECE OF GEAR TOOTH WAS FOUND ON 	PLUG.  LARGE PIECE OF GEAR TOOTH BROKE OFF DURING FLIGHT.  CAUSE FOR BROKEN GEAR TOOTH WAS DUE TO EXCESSIVE GALLING EXTE	NDING UP TO FORWARD END OF SMALL GEAR TEETH.  (X)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001020200063	20010202	00063	SW  	2001	2	2	20001026SH002    	1	20000824	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	A			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	697AL	534  			A1778	53374				DURING 25-HOUR AD INSPECTION, TIME SINCE LAST INSPECTION IS 16.6 HOURS.  FORWARD SEGMENT OF THE DISC PACK IS CRACKED ACR	OSS THE SPAN.  (X)					1	G	7	1 	3U			O	H2SW    					 
2000103100179	20001031	00179	CE  	2000	10	31	20001026SH003    	1	20000926	G	8000	99103971	RELAY           			CESSNA	402   	402C        	207590R	CE  										LEFT STAB WING	FAILED          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	770CA					402C0432				WHEN AIRCRAFT BATTERY MASTER SWITCH WAS TURNED ON, LEFT ENGINE MOTORED OVER.  MAINTENANCE REMOVED AND REPLACED LEFT STAR	TER RELAY AND RELEASED THE AIRCRAFT BACK TO SERVICE.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000103100180	20001031	00180	CE  	2000	10	31	20001026SH004    	1	20000920	G	2710	12601121	CABLE HOUSING   			CESSNA	206   	206H        	2073301	CE  										AILERON QUADRANT	INADEQUATE      	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7281M	3121 				20608048				DURING INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANTS (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DETER	MINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT.  SUBSEQUENT I	NSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STRANDS BROKEN.  THE CABLE TENSIONS BEFORE REMOVA	L WERE WITHIN LIMITS.  THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS.  (X)			1	H	7	1 	3O			RT	A4CE    					 
2000103100103	20001031	00103	CE  	2000	10	31	20001026SH005    	1	20000920	G	2710	12601122	CABLE GUARD     			CESSNA	206   	206H        	2073301	CE  										AILERON QUADRANT	INADEQUATE      	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7281M	3121 				20608048				DURING INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANTS (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DETER	MINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT.  SUBSEQUENT I	NSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STRANDS BROKEN.  THE CABLE TENSIONS BEFORE REMOVA	L WERE WITHIN LIMITS.  THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS.  (X)			1	H	7	1 	3O			RT	A4CE    					 
2000103100104	20001031	00104	CE  	2000	10	31	20001026SH006    	1	20000925	G	2710	12601121	CABLE GUARD     			CESSNA	206   	206H        	2073301	CE  										AILERON QUADRANT	INADEQUATE      	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7273Q	405  				20608045				DURING INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANTS (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DETER	MINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT.  SUBSEQUENT I	NSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STRANDS BROKEN.  THE CABLE TENSIONS BEFORE REMOVA	L WERE WITHIN LIMITS.  THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS.  (X)			1	H	7	1 	3O			RT	A4CE    					 
2000103100105	20001031	00105	CE  	2000	10	31	20001026SH007    	1	20000925	G	2710	12601122	CABLE GUARD     			CESSNA	206   	206H        	2073301	CE  										AILERON QUADRANT	INACCURATE      	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7273Q	406  				20608045				DURING THE INITIAL INSPECTION OF THE AILERON INTERCONNECT CABLE QUADRANT (RT AND LT) IAW CESSNA SB SB00-27-02, IT WAS DE	TERMINED THE REQUIRED RADIUS AROUND THE EDGE OF THE HOLE WHERE THE INTERCONNECT CABLE PASSES WAS NOT PRESENT.  SUBSEQUEN	T INSPECTION OF THE INTERCONNECT CABLE FOUND ONLY MINIMAL CHAFING WITH NO STANDS BROKEN.  THE CABLE TENSIONS BEFORE REMO	VAL WERE WITHIN LIMITS.  THE QUADRANTS WERE MODIFIED AND REINSTALLED PER THE INSTRUCTIONS.  (X)			1	H	7	1 	3O			RT	A4CE    					 
2000103100116	20001031	00116	SW  	2000	10	31	20001026SH008    	1	20001002	G	3231	330094505	ARM             			GULSTM	690TP 	690B        	7630516	SW  											CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	771BA					11429				ARM ASSY CRACKED AT LANDING GEAR DOOR ATTACH AREA.  (X)						1	H	7	2 	3T			 	2A4     					 
2001022600007	20010226	00007	EA  	2001	2	26	20001026SH010    	2	20001026	G	7414	6361	MAGNETO         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299X	440  				3257021				OWNER REPORTED ENGINE GETTING HARDER TO START, LAST START TOOK 20 MINUTES, WOULD NOT START AT NEXT FUEL STOP.  REMOVED S	PARK PLUG LEADS TO CHECK FOR SPARK, NONE NOTED ON EITHER MAGNETO.  REMOVED BOTH MAGS AND OPENED FOR INSP.  FOUND BOTH MA	GS FULL OF MELTED GREASE.  GREASE APPEARS TO HAVE COME FROM MAGNETO BEARINGS.   RT MAG SHOWED SIGNS OF HIGHER HEAT AS GR	EASE WAS MORE LIQUID WHEN COMPARED TO LT MAG.  INSTALLED 2 NEW SLICK MAGS OF SAME MODEL NUMBERS.  OPER CHECK NORMAL WITH	 NO DIFFICULT STARTING.  (X)		1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001022600008	20010226	00008	EA  	2001	2	26	20001026SH011    	2	20001026	G	7414	6360	MAGNETO         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299X	440  				3257021				OWNER REPORTED ENGINE GETTING HARDER TO START, LAST START TOOK 20 MINUTES, WOULD NOT START AT NEXT FUEL STOP.  REMOVED S	PARK PLUG LEADS TO CHECK FOR SPARK, NONE NOTED ON EITHER MAGNETO.  REMOVED BOTH MAGS AND OPENED FOR INSP.  FOUND BOTH MA	GS FULL OF MELTED GREASE.  GREASE APPEARS TO HAVE COME FROM MAGNETO BEARINGS.   RT MAG SHOWED SIGNS OF HIGHER HEAT AS GR	EASE WAS MORE LIQUID WHEN COMPARED TO LT MAG.  INSTALLED 2 NEW SLICK MAGS OF SAME MODEL NUMBERS.  OPER CHECK NORMAL WITH	 NO DIFFICULT STARTING.  (X)		1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001022600009	20010226	00009	CE  	2001	2	26	20001026SH012    	1	20000915	G	5751		SKIN            			BEECH 	90    	C90         	1152913	CE  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	901JA	8475 				LJ694				ON 5-15-00, LEFT AILERON SKIN FOUND CRACKED AT OUTBOARD AFT EDGE UNDERSIDE.  UPON FURTHER INSPECTION, FOUND THE SKIN TO 	BE VERY BRITTLE.  ON 9-10-00, FOUND RIGHT AILERON SKIN CRACKED AT SKIN LAP AFT OF CENTER ATTACH POINT BOTH UPPER AND LOW	ER.  SKIN FOUND TO BE BRITTLE.  CRACK WAS DIFFICULT TO IDENTIFY AS IT APPEARED TO BE A NATURAL SEPARATION OF AGING PAINT	 SEPARATION AT THE LAP JOINT.  SUBMITTER SUSPECTED WORKING SURFACES AND/OR DISSIMILAR METAL CORROSION.  THERE WERE NO OB	VIOUS SIGNS OF A CRACK NOR OF WORKING SURFACES OR CORROSION.  (X)		1	L	7	2 	3T			 	3A20    					 
2001022600010	20010226	00010	CE  	2001	2	26	20001026SH013    	1	20001004	G	2820		FUEL LINE       			CESSNA	208   	208B        	2073701	CE  										FUEL RESERVOIR	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	914FE	7440 				208B0014				BOLT HOLDING SEAL TO LONGERON HAD THE END RUBBING AGAINST THE FUEL LINE THAT FEEDS THE RESERVOIR.   (X)						1	H	7	1 	3T			 	A37CE   					 
2001022600012	20010226	00012	SO  	2001	2	26	20001026SH015    	1	20001002	G	7602	653657	CONTROL CABLE   			PIPER 	PA34  	PA34220T    	7103420	SO  										MIXTURE CONTROL	BINDING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9299E	2140 				3449043				RIGHT HAND MIXTURE CABLE (HARD TO MOVE IN-FLIGHT).  (X)						1	L	7	2 	3O			 	A7SO    					 
2001020900053	20010209	00053	EU  	2001	2	9	20001026SH018    	1	20000729	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B3     	8680954	EU  										EXTERIOR LIGHTS	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	103LN	647  				3128				POWER SUPPLY BOX UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900054	20010209	00054		2001	2	9	20001026SH019    	4	20000726	G	3414	3502001105	INDICATOR       			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	103LN	27   				3128				IPC DOES NOT DISTINGUISH BETWEEN LIGHTED AND UNLIGHTED INDICATORS.  AIRCRAFT REQUIRES LIGHTED INDICATOR.  REPLACED WITH 	NEW UNIT, CORRECTED PROBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001020900055	20010209	00055	EU  	2001	2	9	20001026SH020    	1	20000421	G	5220	350A25109521	ROD             			SNIAS 	350   	AS350B3     	8680954	EU  										JETTISON DOOR	WEAK            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	527  				3128				JETTISON DOOR ROD WEAK.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900056	20010209	00056		2001	2	9	20001026SH021    	4	20000707	G	3413	3502011111	INDICATOR       			SNIAS 	350   	AS350B3     	8680954	EU  										VERTICAL SPEED	FLUCTUATES      	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	619  				3128				VERTICAL SPEED INDICATOR HAD EXCESSIVE NEEDLE FLUCTUATION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900057	20010209	00057	EU  	2001	2	9	20001026SH022    	1	20000829	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B3     	8680954	EU  										PITCH CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	104LN	61   				3134				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900058	20010209	00058	EU  	2001	2	9	20001026SH023    	1	20000726	G	3340	A490ATSCF1428	POWER SUPPLY    			UROCOP	EC135 	EC135P1     	8680990	EU  										STROBE LIGHT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	372  				EC1350054				STROBE POWER SUPPLY UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001020900059	20010209	00059	EU  	2001	2	9	20001026SH024    	1	20000727	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  										FUEL PUMP	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	137  				EC1350054				FUEL PUMP CARTRIDGE INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001020900060	20010209	00060	EU  	2001	2	9	20001026SH025    	1	20000718	G	6710	10545371	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	664  				7527				ROD END ASSY WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001020900061	20010209	00061	EU  	2001	2	9	20001026SH026    	1	20000819	G	7714	117902111	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRIPLE TACH	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	117SU	32   				7527				TRIPLE TACH INDICATOR UNIT INOPERATIVE.  N2 SPLIT OF 2 PERCENT INDICATED IN ERROR.  REPLACED WITH NEW UNIT, CORRECTED PR	OBLEM.  (X)					1	G	7	2 	3U			NC	H13EU   					 
2001020900062	20010209	00062	EU  	2001	2	9	20001026SH027    	1	20000807	G	7714	117902111	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRIPLE TACH	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	117SU	713  				7527				TRIPLE TACH INDICATOR UNIT INOPERATIVE.  NR 1 POINTER INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001020900063	20010209	00063	EU  	2001	2	9	20001026SH028    	1	20000808	G	6320	IPT20RT1100080G	TRANSMITTER     			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRANS OIL PRESS	ERRATIC         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	117SU	713  				7527				PRESSURE TRANSMITTER HAD ERRATIC READINGS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001022600019	20010226	00019	CE  	2001	2	26	20001030SH014    	1	20001013	G	2752	C1452501S	MOTOR           			CESSNA	172   	172N        	2072434	CE  										FLAP	FAILED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	737XM	54   				17269755				FLAP MOTOR BURNED OUT.  SUBMITTER STATED THEY PUT 2 NEW UNITS IN FROM CESSNA, CHECK OF ACTUATOR AND GEARBOX FOUND NO DEF	ECTS.  TURNS FREELY.  CHECKED WIRES, NO DEFECTS.  UNKNOWN CAUSE OF FAILURES.  DATE OF MANUFACTURE OF MOTOR NR 2 IS 7/99.	  (X)				1	H	7	1 	3O			NT	3A12    					 
2001022600020	20010226	00020	CE  	2001	2	26	20001030SH015    	1	20001013	G	2752	C1452501S	MOTOR           			CESSNA	172   	172N        	2072434	CE  										FLAP	FAILED          	B			ZKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	737XM	205  				17269755				FLAP MOTOR BURNED OUT.  SUBMITTER STATED THEY PUT 2 NEW UNITS IN FROM CESSNA, CHECK OF ACTUATOR AND GEARBOX FOUND NO DEF	ECTS.  TURNS FREELY.  CHECKED WIRES, NO DEFECTS.  UNKNOWN CAUSE OF FAILURES.  DATE OF MANUFACTURE OF MOTOR NR 2 IS 7/99.	  (X)				1	H	7	1 	3O			NT	3A12    					 
2001022600021	20010226	00021	SO  	2001	2	26	20001030SH016    	1	20001013	G	2821		FUEL FILTER     			PIPER 	PA34  	PA34200T    	7103406	SO  										FUEL SYSTEM	CONTAMINATED    	B			ZKGR	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NE	05	4516F					347670340				ACFT FLYING AT 13,000 FEET AROUND ZERO DEGREES FAHRENHEIT, RT ENGINE POWER FLUX AND LOST POWER.  ACFT LANDED WITHOUT INC	IDENT.  INSPECTION OF FUEL SYSTEM AROUND 18 HOURS LATER AND AFTER RUN-UP CHECK ABOUT 1 HR LATER, FOUND WATER DROPLET IN 	FUEL FILTER BOWL, PILOT HAD HAD ACFT SERVICED WITH FUEL BEFORE FUEL TRUCK RAN OUT OF FUEL IN TANK.  WHILE FUELING, RT WI	NG, DRAINED FUEL AND FLUSHED TANKS.  SUBMITTER STATED PILOT WAS USING ANTI-ICING ADDITIVE FOR FUEL AT THIS TIME TO PREVE	NT IT FROM HAPPENING AGAIN WHEN WEATHER CONDUCIVE TO FREEZING.  CAUSE OF TROUBLE MAY HAVE BEEN FROZEN WATER IN FUEL STRA	INING BOWL.  RECHECKED BOWL 5 HRS LATER, NO WATER.  (X)	1	L	7	2 	3O			 	A7SO    					 
2001020900068	20010209	00068	EU  	2001	2	9	20001030SH017    	1	20000813	G	3340	A490ATSCF1428	POWER SUPPLY    			UROCOP	EC135 	EC135P1     	8680990	EU  										STROBE LIGHT	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	135SJ	48   				EC1350054				STROBE POWER SUPPLY INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001020900069	20010209	00069		2001	2	9	20001030SH018    	4	20000921	G	3160	B19030MA	DISPLAY         			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INTERMITTENT    	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	392LG	247  				3252				UNIT OPERATES INTERMITTENTLY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900070	20010209	00070	EU  	2001	2	9	20001030SH019    	1	20000802	G	6230	350A37112701	SCISSORS        			SNIAS 	350   	AS350B3     	8680954	EU  										MAIN ROTOR LINK	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	392LG	63   				3252				BUSHINGS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900071	20010209	00071	EU  	2001	2	9	20001030SH020    	1	20000713	G	6230	704A33640021	SPACER          			SNIAS 	350   	AS350B3     	8680954	EU  										SWASHPLATE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	392LG	13   				3252				BUSHINGS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900072	20010209	00072	EU  	2001	2	9	20001030SH021    	1	20000713	G	6230	704A33640021	SPACER          			SNIAS 	350   	AS350B3     	8680954	EU  										SWASHPLATE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	392LG	13   				3252				BUSHINGS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900073	20010209	00073	EU  	2001	2	9	20001030SH022    	1	20000713	G	6230	350A37112602	SCISSORS        			SNIAS 	350   	AS350B3     	8680954	EU  										MAIN ROTOR LINK	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	00	392LG	8    				3252				BUSHINGS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900074	20010209	00074		2001	2	9	20001030SH023    	4	20000914	G	3160	B19030MB01	DISPLAY         			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	397LG	29   				3268				UNIT INOPERATIVE.  BRIGHTNESS FAILURE CODE ON NEARLY ALL LIGHTS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900075	20010209	00075	EU  	2001	2	9	20001030SH024    	1	20000826	G	6520	350A33200406	SPIDER          			SNIAS 	350   	AS350B3     	8680954	EU  										TAIL ROTOR	LOOSE           	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52281	328  				3249				EXCESSIVE PLAY ON TR SHAFT ASSY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900076	20010209	00076	EU  	2001	2	9	20001030SH025    	1	20000826	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B3     	8680954	EU  										PITCH CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52281	328  				3249				ROD, PITCH CONTROL WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900077	20010209	00077		2001	2	9	20001030SH026    	4	20000902	G	3452	KT70	TRANSPONDER     			SNIAS 	350   	AS350B3     	8680954	EU  										ATC	SHORTED         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	52281	345  				3249				TRANSPONDER, KT70 MODE S ATC,  HAD INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900078	20010209	00078	EU  	2001	2	9	20001030SH027    	1	20000817	G	7930	ZRA25500	TRANSMITTER     			SNIAS 	350   	AS350B3     	8680954	EU  										OIL PRESSURE	INTERMITTENT    	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	52285	287  				3251				OIL PRESSURE TRANSMITTER UNIT OPERATED INTERMITTENTLY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900079	20010209	00079	EU  	2001	2	9	20001030SH029    	2	20001030	G	7200		BLADE           			AEROSP	SA316 	SA315B      	8680615	EU  	TMECA 	ARTST2	ARTOUSTE2B1 	60002	EU  					ENGINE	MISSING         	B			LH3D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	65185	7050 				2288	400			EXCESSIVE VIBRATION DURING ENGINE RUN-UP.  REMOVED ENGINE FOR TEAR-DOWN INSPECTION.  FOUND ONE EACH MISSING BLADE AND SE	VERAL OTHERS DAMAGED ON 2 INCH STAGE TURBINE WHEEL.  CAUSE UNKNOWN AT THIS TIME.  (X)					1	G	7	1 	4U	3	U	 	H1IN    	E300				 
2001020900080	20010209	00080	NM  	2001	2	9	20001030SH030    	1	20000908	G	6710	900C2010214101	PITCH LINK      			DOUG  	MD900 	MD900       	3027375	NM  										ROTOR CONTROL	WORN            	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	901CF	505  				90000012				PITCH LINK ASSY, ROTOR CONTROL, WORN BEYOND SERVICEABLE LIMITS.  EXCESSIVE WEAR INTO ROD END ASSY.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001022600018	20010226	00018	CE  	2001	2	26	20001030SH032    	1	20001030	G	2730	RI106	CONTROL BOX     			CESSNA	501   	501         	2076603	CE  										COCKPIT	CHAFED          	B			PJYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15						0075				ELEVATOR TRIM CHAIN IN PEDESTAL CHAFED ON SPERRY RI-106 REMOTE CONTROL BOX.  CASE OF CONTROL BOX WAS SEVERLY WORN.  IT W	AS EVIDENT THIS CONDITION EXISTED FOR SOME TIME. THIS COULD HAVE POSSIBLY LED TO JAMMING OF THE ELEVATOR TRIM SYSTEM.  U	NIT WAS REMOVED AND AIRCRAFT WAS FERRIED TO A CITATION SERVICE CENTER FOR REPAIR.  (X)				1	L	7	2 	4F			 	A27CE   					 
2001011101203	20010111	01203	SO  	2001	1	11	20001030SH033    	2	20001030	G	8530		CYLINDER        								CONT  	O520  	IO520*      	17032	SO  					ENGINE	DELAMINATED     	C				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SW	17		1831 	82   				291457R			CERMINIL COATING DELAMINATED FROM ONE STEEL CYLINDER BORE AT 82.2 HOURS TSO.  POSSIBLE CAUSE, SOME INDIVIDUAL POSSIBLY T	OUCHED CYLINDER BORE JUST BEFORE PROCESSING.  TOUCHING THE CYLINDER BORE AFTER FINAL CLEANING AND/OR DURING PROCESSING I	S STRICTLY PROHIBITED IN SPECIFICATION FOR THE PROCESS BECAUSE  CONTAMINATION FROM A PERSON'S HAND CAN CAUSE ADHERENCE P	ROBLEMS.  THE AUTOMATED PRE-TREAT PROCESS WAS POSSIBLY INTERRUPTED THROUGH SOME ELECTRICAL OR COMPUTER ANOMALY AND THE R	EQUIRED PRE-TREATMENTS WERE NOT SATISFACTORLY COMPLETED.  THE PLATING PROCESS IS PRIMARILY ACCOMPLISHED THROUGH COMPUTER	 AND ROBOTIC MANIPULATION.  SUBMITTER STATED THE COMPUTER REPORTED PROCESSING PROBLEMS.  (X)						3	O			E5CE				 
2001022600024	20010226	00024	SO  	2001	2	26	20001031SH003    	2	20001005	G	8530		CYLINDER        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  					ENGINE	SEPARATED       	B				A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			GL	15	9248C					31347	4610463			DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE.  INSPECTION REVEALED ONE CYLINDER HAD	 SEPARATED BETWEEN BARREL AND HEAD.  THESE 6 CYLINDERS HAD APPROXIMATELY 400 HOURS SINCE BEING CHROMED.  OWNER REPLACED 	ALL CYLINDERS WITH NEW SUPERIOR MILLENIUM SET.  (X)				1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2001022600025	20010226	00025	EA  	2001	2	26	20001031SH004    	2	20001005	G	7414		MAGNETO         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	DAMAGED         	H			IK8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	6669Y					273986	L95545			MAGNETOS REMOVED FOR OVERHAUL.  UPON EXAM OF LT MAG DRIVE GEAR AND ROTATING MAGNET THREAD END, NOTED NUT, PN 10-163178, 	WAS LOOSE.  ALSO, DRIVE BUSHING, PN 10-357193 WAS LOOSE ALLOWING PLATE DRIVE, PN 10-163216 TO SHIFT ALIGNMENT OF DRIVE G	EAR WHICH ATE INTO BACK OF ENG CASE.  THIS MISALIGNMENT CREATED A LOT OF DAMAGE THAT COULD NOT BE REPAIRED.  ALSO DISCOV	ERED A WASHER WAS LEFT OUT WHEN MAG O/H''''D.  IT GOES BTWN DRIVE NUT PN 10-163178 AND BUSHING PN 10-357193.  WITH THIS 	WASHER, PN 10-116860 OUT, PROPER TORQUE COULD NOT BE OBTAINED.  SUBMITTER STATED NO HISTORY AS TO WHEN MAGS O/H''''D, AN	D NO HISTORY OF TIME WHEN INSTALLED.  (X)	1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001022600026	20010226	00026	SO  	2001	2	26	20001031SH007    	1	20000913	G	3211		BOLT            			PIPER 	PA28  	PA28151     	7102805	SO  										LT MLG	MISSING         	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CE	09	41558	3121 				287415270				AIRCRAFT CONTROL LOST ON LANDING.  AIRCRAFT BOUNCED AND STRUT FELL OUT.  SCISSOR BOLT WAS MISSING.  (X)						1	L	7	1 	3O			 	2A13    					 
2001022600027	20010226	00027	CE  	2001	2	26	20001031SH008    	1	20001010	G	5510	9562001085	CHANNEL         			BEECH 	58    	58          	1152740	CE  										HORIZONTAL STAB	CRACKED         	B			VY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	3713N	1729 				TH1196				FOUND RIGHT STABILIZER, FORWARD SPAR ATTACH CHANNEL CRACKED IN LOWER RADIUS.  AREA VERY HARD TO ACCESS WITH MIRROR AND F	LASHLIGHT.  FOUND A CRACK IN A BARON IN THE SAME LOCATION PREVIOUSLY.  CRACK IS FOUND WHERE THE MOUNTING CHANNEL PASSES 	THROUGH THE FUSELAGE.  STABILIZER MUST BE REMOVED TO REPLACE THIS CHANNEL.  SUBMITTER SUGGESTED THIS ARM BE INSPECTED RE	GULARLY.  (X)			1	L	7	2 	3O			 	3A16    					 
2001022600028	20010226	00028	EU  	2001	2	26	20001031SH010    	1	20000914	G	2752	951D1009	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  										TE FLAP	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		171  								TWO SHAFT SUPPORT BEARINGS WERE NOT INSTALLED AT THE TIME OF ORIGINAL ASSEMBLY.  THE OMISSION OF THESE BEARINGS SA13589-	1 AND SA13588-1 CAUSED PREMATURE WEAR OF THE WORN SHAFT RESULTING IN EXCESSIVE GEAR BACKLASH.  (X)					1	L	7	1 	3T			RT	A78EU   					 
2001022100186	20010221	00186	NM  	2001	2	21	20001031SH011    	1	20001031	G	5753		SPAR            			BOEING	737   	737*        	       	NM  										TE FLAPS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					BN495					ONE EACH CRACK EXITS ON THE UPPER AFT T-SPAR MEASURING 1.5 INCHES LONG, LOCATED AT THE INBOARD END OF THE OUTBOARD MID-F	LAP.  (X)					2	L	7	2 	4F			RT	A16WE   					 
2001022100187	20010221	00187	NM  	2001	2	21	20001031SH012    	1	20001031	G	5753	6540406	SPAR            			BOEING	737   	737300      	1384610	NM  										TE FLAPS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										737300/737400/737500 WERE FOUND WITH A CRACK IN THE UPPER AFT SPAR T-CAP OF THE OUTBOARD MIDFLAP.  CRACK IS LOCATED ON T	HE VERTICAL LEG OF THE SPAR NEAR THE EXHAUST GATE HINGE.  EACH OF THE LAST FOUR 737 OTBD MIDFLAPS EVALUATED WERE CRACKED	 IN THE DESCRIBED LOCATION.  DETAILS OF THESE 737 OTBD MIDFLAPS ARE:  PN 65C263201, SN BN444, 6 INCHES LONG, ON 10-5-99;	 PN 65C263201, SN BN479, 4.5 INCHES LONG, ON 11-15-99; PN 65C263201, SN BN461, 5 INCHES LONG, ON 1-8-00; PN 65C263203, S	N BN495, 1.5 INCHES LONG (W/STOP HOLE), ON 1-11-00.  DAMAGE DISCOVERED ON FLAPS DETACHED FROM ACFT DURING EVAL FOR REPAI	R/OVERHAUL, POSSIBLE CAUSE CANNOT BE DETERMINED BY SUBMITTER.  NOTE: 5TH OTBD MIDFLAP FOUND WITH CRACK SIMILAR LOCAL.(X)	2	L	7	2 	4F			RT	A16WE   					 
2001022100021	20010221	00021	NM  	2001	2	21	20001031SH014    	1	20001031	G	5753	6540406	SPAR            	BOEING      		BOEING	737   	737400      	       	NM  										TE FLAPS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										737300/737400/737500 WERE FOUND WITH A CRACK IN THE UPPER AFT SPAR T-CAP OF THE OUTBOARD MIDFLAP.  CRACK IS LOCATED ON T	HE VERTICAL LEG OF THE SPAR NEAR THE EXHAUST GATE HINGE.  EACH OF THE LAST FOUR 737 OTBD MIDFLAPS EVALUATED WERE CRACKED	 IN THE DESCRIBED LOCATION.  DETAILS OF THESE 737 OTBD MIDFLAPS ARE:  PN 65C263201, SN BN444, 6 INCHES LONG, ON 10-5-99;	 PN 65C263201, SN BN479, 4.5 INCHES LONG, ON 11-15-99; PN 65C263201, SN BN461, 5 INCHES LONG, ON 1-8-00; PN 65C263203, S	N BN495, 1.5 INCHES LONG (W/STOP HOLE), ON 1-11-00.  DAMAGE DISCOVERED ON FLAPS DETACHED FROM ACFT DURING EVAL FOR REPAI	R/OVERHAUL, POSSIBLE CAUSE CANNOT BE DETERMINED BY SUBMITTER.  NOTE: 5TH OTBD MIDFLAP FOUND WITH CRACK SIMILAR LOCAL.(X)	2	L	7	2 	4F			RT	A16WE   					 
2001022100188	20010221	00188	NM  	2001	2	21	20001031SH015    	1	20001031	G	5753	6540406	SPAR            	BOEING      		BOEING	737   	737500      	       	NM  										TE FLAPS	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										737300/737400/737500 WERE FOUND WITH A CRACK IN THE UPPER AFT SPAR T-CAP OF THE OUTBOARD MIDFLAP.  CRACK IS LOCATED ON T	HE VERTICAL LEG OF THE SPAR NEAR THE EXHAUST GATE HINGE.  EACH OF THE LAST FOUR 737 OTBD MIDFLAPS EVALUATED WERE CRACKED	 IN THE DESCRIBED LOCATION.  DETAILS OF THESE 737 OTBD MIDFLAPS ARE:  PN 65C263201, SN BN444, 6 INCHES LONG, ON 10-5-99;	 PN 65C263201, SN BN479, 4.5 INCHES LONG, ON 11-15-99; PN 65C263201, SN BN461, 5 INCHES LONG, ON 1-8-00; PN 65C263203, S	N BN495, 1.5 INCHES LONG (W/STOP HOLE), ON 1-11-00.  DAMAGE DISCOVERED ON FLAPS DETACHED FROM ACFT DURING EVAL FOR REPAI	R/OVERHAUL, POSSIBLE CAUSE CANNOT BE DETERMINED BY SUBMITTER.  NOTE: 5TH OTBD MIDFLAP FOUND WITH CRACK SIMILAR LOCAL.(X)	2	L	7	2 	4F			RT	A16WE   					 
2001022600029	20010226	00029	SO  	2001	2	26	20001031SH016    	2	20000926	G	7314	6467661A1	PUMP            			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	FAILED          	D				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	33	8170D	135  				E2600	297181R			INTERNAL FAILURE, PUMP STOPPED BEFORE TAKEOFF.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2001030100027	20010301	00027	SO  	2001	3	1	20001031SH017    	2	20000925	G	8550		SPRING          			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					OIL SYSTEM	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	13AG		1394 			347770115	807270R			PILOT REPORTED THAT OIL PSI WAS LOW AS HE REDUCED POWER FOR LANDING.  THE SPRING BROKE DUE TO RUBBING ON THE INSIDE OF T	HE RELIEF VALVE PISTON.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022600030	20010226	00030	SO  	2001	2	26	20001031SH018    	2	20000519	G	7313	63274814	INJECTOR        			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520WB   	17040	SO  					CYLINDERS	LEAKING         	H				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	03	144Z	35   				TJ211	274454R			WHILE IN-FLIGHT, A FUEL SMELL ENTERED THE CABIN.  FUEL WAS LEAKING AT ALL 6 INJECTORS BETWEEN PIPE THREADS AND CYLINDER.	  ALL INJECTORS WERE SEALED PER CONTINENTAL SM.  NEXT FLIGHT STILL LEAKING.  INJECTORS RESEALED WITH LOCTITE 569 PER CON	TINENTAL.  (X)				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001030100028	20010301	00028	CE  	2001	3	1	20001031SH019    	1	20001003	G	2436	DGR72850	REGULATOR       			CESSNA	310   	310H        	2074220	CE  										COPILOT SEAT	MISMARKED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1029Q					310H0029				BOTH REGULATORS ARE OF THE PARALLELING TYPE.  THE PARALLELING TERMINAL ON THE REGULATOR IS MARKED GRD FOR GROUND, AND SH	OULD BE PAR FOR PARALLEL.  IF THIS TERMINAL IS GROUNDED TO THE PARALLELING RELAY, THE WIRES WILL SMOKE REPRESENTING A FI	RE HAZARD UNDER THE COPILOT''S  SEAT.  (X)				1	L	7	2 	3O			 	3A10    					 
2001030100029	20010301	00029	CE  	2001	3	1	20001031SH020    	1	20001003	G	2436	DGR72850	REGULATOR       			CESSNA	310   	310H        	2074220	CE  										COPILOT SEAT	MISMARKED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1029Q					310H0029				BOTH REGULATORS ARE OF THE PARALLELING TYPE.  THE PARALLELING TERMINAL ON THE REGULATOR IS MARKED GRD FOR GROUND, AND SH	OULD BE PAR FOR PARALLEL.  IF THIS TERMINAL IS GROUNDED TO THE PARALLELING RELAY, THE WIRES WILL SMOKE REPRESENTING A FI	RE HAZARD UNDER THE COPILOT''S  SEAT.  (X)				1	L	7	2 	3O			 	3A10    					 
2001022600031	20010226	00031	SO  	2001	2	26	20001031SH022    	2	20001016	G	7322		SHAFT           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	WORN            	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	27	18601					15073976				POWER LOSS CAUSED AN OFF AIRPORT LANDING.  EXAMINATION OF THE CARBURETOR REVEALED THE THROTTLE SHAFT WAS SEVERELY WORN. 	 ADDITIONALLY, THE ACCELERATOR PUMP SHAFT SEAL WAS ALSO WORN.  THE THROTTLE ARM WAS STILL OF THE ORIGINAL TYPE AS IN AD 	72-06-05R2.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001022600032	20010226	00032	SW  	2001	2	26	20001031SH023    	1	20000910	G	8120	3AT6EE10J2	TURBOCHARGER    			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	SEIZED          	H				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			GL	21	205MN	213  				243019	2443351A			TURBO LOCKED UP.  THE PILOT LANDED THE A/C UNEVENTFULLY.  NO DAMAGE TO A/C.    TURBOCHARGER P/N 3AT6EE10J2  CF600573-000	0.  (X)					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001022600033	20010226	00033	SO  	2001	2	26	20001031SH024    	1	20000816	G	3244	1159SCL20633	TIRE            			GULSTM	G1159 	G1159       	3953505	SO  										LT INBD MLG	SEPARATED       	B				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			NE	01										TIRE SHED OUTER TREAD DURING TAKEOFF.  TREAD SEPARATED FROM TIRE IN LARGE PIECES AND SHEETS.  TIRE CASING REMAINED INTAC	T WITH NO LOSS OF AIR PRESSURE.  MOUNTED ON LT INBOARD POSITION.  TOTAL TIME ON TIRE, 139 HOURS TSN.  123 LANDINGS TSN. 	 (X)				2	L	7	2 	4F			RT	A12EA   					 
2001022600034	20010226	00034	WP  	2001	2	26	20001031SH025    	1	20001016	G	3246	9550328	WHEEL           			DOUG  	DC8   	DC8*        	       	WP  										NLG	CORRODED        	B			INWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										NOSE WHEEL ASSY HEAVILY CORRODED AT BEAD SEAT AREA.  ALSO, BOLT HOLES AREA HEAVILY CORRODED.  (X)						2	L	7	4 	4J			F	4A25    					 
2001022600035	20010226	00035	SO  	2001	2	26	20001031SH026    	1	20001031	G	3230	AN625	BOLT            			PIPER 	PA28  	PA28R200    	7102811	SO  										DRAG BRACE	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	2781R					28R35272				BOLTS IN UPPER NOSE GEAR DRAG BRACE ASSY, SECURING TO ENGINE MOUNT ARE INSTALLED BACKWARDS.  LARGE DIAMETER STEEL WASHER	S, TEFLON WASHERS ARE ALSO INSTALLED INCORRECTLY PER PAC DRAWING, IPC, AND SM.  (X)					1	L	7	1 	3O			 	2A13    					 
2001022600036	20010226	00036	CE  	2001	2	26	20001031SH027    	1	20000921	G	3230	504501033	TORQUE TUBE     			CESSNA	421   	421B        	2076014	CE  										LT MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	3372Q	424  				421B9256				LEFT MAIN LANDING GEAR WOULD NOT RETRACT.  FOUND LARGE CRACK AT LEFT MAIN LANDING GEAR TORQUE TUBE.  NOTHING ABNORMAL WI	TH GEAR RIGGING, CRACKED FROM STRESS OF CONTINUED USE.  REPLACED TORQUE TUBE WITH NEW FROM FACTORY.  RECHECKED LANDING G	EAR RIGGING PER CESSNA MM.  (X)				1	L	7	2 	3O			 	A7CE    					 
2001022600037	20010226	00037	CE  	2001	2	26	20001031SH028    	1	20001018	G	2571	0024000133	DRAIN MAST      			BEECH 	58    	58          	1152740	CE  										FWD FUSELAGE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	4456T	19   				TH1946				SUBMITTER STATED BATTERY DRAIN MASTS HAVE BEEN CRACKED OR BROKEN OFF OF A LARGE NUMBER OF NEW B-58 AIRCRAFT.  TIME VARIE	S FROM 20 HOURS TO SEVERAL HUNDRED HOURS.  (X)					1	L	7	2 	3O			 	3A16    					 
2001022600038	20010226	00038	SO  	2001	2	26	20001031SH029    	1	20001012	G	3230	AN625	BOLT            	PIPER       		PIPER 	PA28  	PA28R201T   	7102813	SO  										DRAG BRACE	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	5907V					28R7703165				BOLTS ON UPPER NOSE GEAR DRAG BRACE ASSY, SECURING TO ENGINE MOUNT, ARE INSTALLED BACKWARDS.  THE PN 62833-43 LARGE  DIA	METER STEEL WASHER, TEFLON WASHERS, ARE ALSO INSTALLED INCORRECTLY PER PAC DRAWING, FAC AND SM.  (X)					1	L	7	1 	3O			 	2A13    					 
2001022600039	20010226	00039	CE  	2001	2	26	20001101SH001    	1	20000919	G	2400	S337711	MASTER SWITCH   			CESSNA	172   	172R        	2072401	CE  										INSTRUMENT PANEL	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	718EH	1283 				17280061				WHEN AVIONICS MASTER SWITCH STARTS TO FAIL, IT WILL ONLY TURN ON THE NR 1 COM.  ALL OTHER AVIONIC COMPONENTS ARE CONTROL	LED BY THE BATTERY MASTER.   (X)					1	H	7	1 	3O			NT	3A12    					 
2001022600040	20010226	00040	GL  	2001	2	26	20001101SH003    	3	20000906	G	6111	C32941	BLADE           			MTSBSI	MU2   	MU2B35      	5780411	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NR 2 ENG PROP	BROKEN          	H				E	K			ENGINE SHUTDOWN         	NONE                    			E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	15	770MA		223  			625		BVA7037		AIRCRAFT AT CRUISE, ALT 11,000 FEET, NR 1 PROPELLER BLADE BROKE APPROXIMATELY 10 INCHES FROM HUB ON NR 2 ENGINE.  BLADE 	DID NOT CONTACT AIRCRAFT.  DAMAGE TO COWLING, NACELLE, REAR ENGINE MOUNT, OUTBOARD FLAP, WING TRAILING EDGE.  ENGINE REM	AINED ON WING.  CREW MADE NORMAL LANDING.  REMAINING PORTION OF BLADE REMOVED FROM PROP HUB AND SENT TO NTSB LAB FOR INS	PECTION.  (X)			1	H	7	2 	3T			RT	A10SW   		6	C	P15EA	 
2000111500244	20001115	00244	SO  	2000	11	15	20001101SH004    	2	20001002	G	8530	642399	CONNECTING ROD  			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					INSIDE ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NE	01	770CA	518  				402C0432	816179			CLIMBING THROUGH 2,000 FEET ON TAKEOFF, LEFT ENGINE QUIT.  AIRCRAFT RETURNED TO THE GATE WHERE MAINTENANCE FOUND NR 1 CO	NNECTING ROD HAD SEPARATED FROM THE CRANKSHAFT PUNCTURING THE CASE HALVES AND KNOCKING BOTH MAGNETOS AFT OF MOUNTING FLA	NGES.  MAINTENANCE REMOVED AND REPLACED ENGINE AND RELEASED AIRCRAFT BACK TO SERVICE.  (X)				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2000111500245	20001115	00245	SO  	2000	11	15	20001101SH005    	2	20001009	G	7414	6310	MAGNETO         			CESSNA	207   	T207        	2073612	CE  	CONT  	O520  	IO520F      	17032	SO  					RIGHT	DEFECTIVE       	D				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	01	7405	534  				20700147	818866R			ON INITIAL POWER-UP FOR THE FLIGHT''S TAKEOFF ROLL, THE ENGINE LOST SUBSTANTIAL POWER.  THE PILOT ROLLED OFF TO A TAXIWA	Y AND SHUT DOWN.  AFTER TROUBLESHOOTING THE IGNITION SYSTEM, THE RIGHT MAGNETO WAS FOUND DEFECTIVE AND REPLACED WITH NEW	.  RUN-UP SATISFACTORY.  (X)				1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2000111500246	20001115	00246	GL  	2000	11	15	20001101SH006    	1	20000802	G	8000		SOLENOID        			BLANCA	17    	1730A       	1220433	GL  	CONT  	O520  	IO520K      	17032	SO  						FAILED          	D				O				OTHER                   				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CE	01	8223R					30407	20914871K			PRIOR TO TAKEOFF ON ENGINE RUN-UP, AIRCRAFT LOST ALL ELECTRICAL POWER, STARTER SOLENOID STAYED ENGAGED.  THE ENGINE RAN 	THE STARTER, CAUSED A REVERSE CURRENT FLOW TO THE BATTERY.  BATTERY FAILED, SMOKE FROM UNDER THE COWLING.  STARTER SOLEN	OID LOCATED ON THE FIRE WALL.  SUBMITTER STATED AIRCRAFT IS FABRIC COVERED.  THERE WAS NO DAMAGE IN THE ENGINE AREA.  (X	)			1	L	7	1 	3O	3	O	 	A18CE   	E5CE				 
2000111500247	20001115	00247	CE  	2000	11	15	20001101SH007    	1	20000825	G	7900		VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENG SUMP DRAIN	MISSING         	D				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	15	82149	3953 	557  			17267692	L132076			THE AIRCRAFT WAS FLYING FROM TULSA TO SILOAM SPRINGS AND 8 MILES FROM SILOAM SPRINGS AIRPORT, PILOT REPORTED THE ENGINE 	OIL PRESSURE WAS FLUCTUATING FROM ZERO TO 60 PSI.  THE ENGINE THEN STARTED TO VIBRATE SEVERELY BEFORE THE ENGINE COMPLET	ELY STOPPED.  UPON INSPECTION OF AIRCRAFT, FOUND THE OIL QUICK DRAIN WAS MISSING WHICH OBVIOUSLY CAUSED THE ENGINE TO LO	SE OIL PRESSURE.  THE QUICK DRAIN INSTALLED DID NOT HAVE A PROVISION FOR SAFETY WIRE.  SUBMITTER RECOMMENDED TO PREVENT 	FUTURE PROBLEM WOULD BE TO CHANGE ALL PMA QUICK DRAINS TO BE REQUIRED TO HAVE A SAFETY HOLE IN THE VALVE.  (X)		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000111500248	20001115	00248	GL  	2000	11	15	20001101SH008    	1	20001016	G	7160	19165910	ALT AIR DOOR    			BLANCA	17    	1731A       	1220435	GL  										IND AIR BOX	FAILED          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			EA	05	9643E	600  				7732169				PILOT REPORTED LOSS OF POWER ON TAKEOFF CLIMB.  AFTER RETURNING TO THE AIRPORT, INVESTIGATION REVEALED A FAILED ALTERNAT	E AIR DOOR.   (X)					1	L	7	1 	3O			 	A18CE   					 
2000111500249	20001115	00249	CE  	2000	11	15	20001101SH009    	1	20000916	G	3230		TUBE            			CESSNA	310   	310H        	2074220	CE  										DRIVE NLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	09	99JT	6167 				310H0136				NOSE GEAR WOULD NOT LOCK DOWN AND COLLAPSED ON LANDING.  FOUND NOSE GEAR DRIVE TUBE BROKEN.  (X)						1	L	7	2 	3O			 	3A10    					 
2000111500250	20001115	00250	EA  	2000	11	15	20001101SH010    	2	20000818	G	7414	M3158	ROTOR SHAFT     			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ROTOR GEAR SLOT	CRACKED         	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CE	07	9812C	1885 				287890445	L2342636A			MAGNETO HAD A 250 RPM DROP DURING PRE-FLIGHT RUN UP.  A CHECK OF THE TIMING OF MAGNETO TO ENGINE SHOWED IT TO BE APPROX 	10 DEGREES RETARDED.  MAG WAS NOT FOUND LOOSE AT ITS MOUNT, SO IT WAS REMOVED FOR INSPECTION.  UPON DISASSEMBLY, DISCOVE	RED A CRACK ON THE ''EAR'' OF THE SLOT IN THE ROTOR SHAFT THAT HOLDS THE CAM FOR OPENING THE POINTS.  NO RUST OR OTHER O	UTSIDE FACTOR WAS VISIBLE AS A CAUSE FOR THIS FAILURE.  (X)			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000111500251	20001115	00251	EA  	2000	11	15	20001101SH011    	2	20000928	G	7322	25765362	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  						FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	03	948SP	824  				172S8144	L2812651A			ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS.  FUEL FLOW BELOW 1700 RPM IS TOO HIGH, AT IDLE RPM IS ERRATIC, 	AND THE IDLE SPEED AND IDLE MIXTURE CANNOT BE SET TO SPECIFICATION WITH SATISFACTORY ENGINE OPERATION.  FUEL SERVO REMOV	ED, SENT FOR REPAIR.  MAJOR REPAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 1-5-00.  REIN	STALLED FUEL SERVO, ADJUSTED IAW SPECS, OPERATIONAL CHECKED SATISFACTORY.  SUBMITTER RECOMMENDED ANY RSA-5AD1 FUEL SERVO	 NOT FLOWED TO PRECISION FLOW SHEET 30075-02, BE REMOVED IMMEDIATELY AND SENT TO APPLICABLE REPAIR STATION FOR REPAIR.  	(X)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001020900083	20010209	00083	EU  	2001	2	9	20001101SH014    	1	20000726	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	97LG	488  				2917				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROB	LEM.  FOUR HALF SHELLS EQUALS ONE KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001020900084	20010209	00084	EU  	2001	2	9	20001101SH015    	1	20000831	G	6410	704A33633171	HINGE           			SNIAS 	350   	AS350B2     	8680813	EU  											WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	93LG					2654				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A33-2153-00 CORRECTED PROBLE	M.  TWO TEETERING BEARINGS EQUALS ONE KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001020900085	20010209	00085	EU  	2001	2	9	20001101SH016    	1	20000914	G	6310	350A35105901	COUPLING        			SNIAS 	350   	AS350B3     	8680954	EU  										ENGINE/TRANS	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5224R	986  				2968				COUPLING DISC HAD BROKEN INSERTS.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001020900086	20010209	00086	EU  	2001	2	9	20001101SH017    	1	20000901	G	6310		FREEWHEEL UNIT  			SNIAS 	SA330 	SA330J      	8680612	EU  										M/R GEARBOX	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	330J	1089 				1647				MAIN GEARBOX FREEWHEEL FAILURE.  (X)						2	G	7	2 	4U			 	H4EU    					 
2001020900087	20010209	00087	EU  	2001	2	9	20001101SH018    	1	20000901	G	6310	330N34400102	FREEWHEEL UNIT  			SNIAS 	SA330 	SA330J      	8680612	EU  										M/R GEARBOX	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	330J					1647				MAIN GEARBOX FIREEWHEEL FAILURE CAUSING OVERTORQUE TO INTERMEDIATE GEARBOX.  (X)						2	G	7	2 	4U			 	H4EU    					 
2001020900088	20010209	00088	EU  	2001	2	9	20001101SH019    	1	20000129	G	6310	330A33000008	FREEWHEEL UNIT  			SNIAS 	SA330 	SA330J      	8680612	EU  										T/R GEARBOX	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	330J	333  				1647				MAIN GEARBOX FREEWHEEL FAILURE CAUSING OVERTORQUE TO TAILROTOR GEARBOX.  (X)						2	G	7	2 	4U			 	H4EU    					 
2001020900089	20010209	00089	EU  	2001	2	9	20001101SH020    	1	20000823	G	6720	31605333006001	BEARING         			AEROSP	SA316 	SA316B      	8680207	EU  										TAIL ROTOR	BRINELLED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	31660	326  				1981				MAJOR BRINELLING ON INNER AND OUTER RACE.  AIRCRAFT WAS REPORTED TO HAVE LOST TAIL ROTOR CONTROL IN-FLIGHT.  NO INJURIES	 OR MAJOR DAMAGE.  (X)					1	G	7	1 	4U			 	H1IN    					 
2001022600043	20010226	00043	EA  	2001	2	26	20001101SH022    	2	20001017	G	7314	02532330002	PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	BROKEN          	B			AHDR	A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			EA	13	561SS		873  			BB464	PCE80897			LEFT ENGINE FLAMED OUT IN-FLIGHT, RESTART PROCEDURES TRIED, BUT ENGINE WOULD NOT START.  EMERGENCY DECLARED, AIRCRAFT LA	NDED WITHOUT INCIDENT.  TROUBLESHOOTING FOUND DRIVESHAFT FOR HIGH PRESSURE FUEL PUMP BROKEN.  ENGINE OIL FILTER CHECKED 	FOR METAL CONTAMINATION, NONE FOUND.  DRAINS FOR FCU CHECKED FOR LEAKAGE, NONE FOUND.  CAUSE FOR FAILURE IS STILL UNDER 	INVESTIGATION.  (X)			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001022100036	20010221	00036	CE  	2001	2	21	20001101SH024    	1	20001017	G	2822	64621219A1	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					LT FUEL BOOST	FAILED          	B			R14R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	258DM	124  				TH1938	684599			PILOT REPORTED LEFT ENGINE EXHIBITING A DROP IN FUEL PRESSURE AT TAKEOFF POWER.  PILOT ALSO REPORTED THAT AFTER LANDING,	 BOTH ENGINES WOULD EXHIBIT AN UNCONTROLLABLE ROLLBACK OF FUEL PRESSURE FOLLOWED BY ENGINE STALL.  TROUBLESHOOTING REVEA	LED LOW UNMETERED FUEL PRESSURE BEING DELIVERED BY THE ENGINE DRIVEN FUEL PUMPS ON BOTH ENGINES.  BOTH FUEL PUMPS WERE R	EMOVED AND REPLACED (SUBMITTER STATED THIS IS THE 2ND RAYTHEON MODEL 58 TO BE SERVICED AT THIS FACILITY WITHIN 2 WEEKS F	OR THE SAME DISCREPANCY.)  (X)		1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2001022100039	20010221	00039	CE  	2001	2	21	20001101SH025    	1	20001017	G	2822	64621219A1	PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					RT FUEL BOOST	FAILED          	B			R14R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	258DM	124  				TH1938	684603			PILOT REPORTED LEFT ENGINE EXHIBITING A DROP IN FUEL PRESSURE AT TAKEOFF POWER.  PILOT ALSO REPORTED THAT AFTER LANDING,	 BOTH ENGINES WOULD EXHIBIT AN UNCONTROLLABLE ROLLBACK OF FUEL PRESSURE FOLLOWED BY ENGINE STALL.  TROUBLESHOOTING REVEA	LED LOW UNMETERED FUEL PRESSURE BEING DELIVERED BY THE ENGINE DRIVEN FUEL PUMPS ON BOTH ENGINES.  BOTH FUEL PUMPS WERE R	EMOVED AND REPLACED (SUBMITTER STATED THIS IS THE 2ND RAYTHEON MODEL 58 TO BE SERVICED AT THIS FACILITY WITHIN 2 WEEKS F	OR THE SAME DISCREPANCY.)  (X)		1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2001020900090	20010209	00090	SW  	2001	2	9	20001101SH026    	1	20000914	G	6410	206011809107	PITCH HORN      	BELL        		BELL  	206   	206L3       	1182108	SW  										T/R BLADE	LOOSE           	B			C68R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	288JB					51288				DURING A 100-HOUR INSPECTION, ONE OF THE MECHANICS FOUND THE STUD PN 206-010-744-105 LOOSE IN THE PITCH HORN, PN 206011-	809-107.  THE POSSIBLE CAUSE IS UNKNOWN AT THIS TIME.  (X)					1	G	7	1 	3U			 	H2SW    					 
2001030200022	20010302	00022	NE  	2001	3	2	20001101SH028    	2	20001016	G	7200	P2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FOR PENETRANT INSPECTION IAW THE IAE V2500 PROPULSION SYSTEM ENGINE SYSTEM MANUAL, REV 44, SECT 70-23-01, 	TASK 70-23-01-230-501.  PART REJECTED DUE TO CRACKS ON TOP SURFACE.  (X)										4	F			E311NE				 
2001020900091	20010209	00091	SW  	2001	2	9	20001101SH030    	1	20001016	G	6720	407001026101	TUBE            			BELL  	407   	407         	1182206	SW  										BELLCRANK	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	52AZ	290  				53380				FOUND DURING SCHEDULED INSPECTION, MECHANICAL DAMAGE FROM AFT BOLTHEAD AT AFT BELLCRANK.  REPLACED WITH NEW CONTROL TUBE	 FROM BELL HELICOPTER.					1	G	7	1 	3U			O	H2SW    					 
2000111500252	20001115	00252	SO  	2000	11	15	20001101SH031    	2	20001012	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  						STUCK           	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	4123C	244  				3449042				THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000111500253	20001115	00253	NE  	2000	11	15	20001102SH001    	3	20001011	G	6114	660714259	HUB             													ROTOL	R389	R3894123F25 	NE  	MATING FACE	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		8669 	965  					DRG876984		HUB ASSEMBLY FOUND CRACKED AT NR 10 AND NR 4 BLADE OPENING AT BEARING ABUTMENT FACE AND SPLIT LINE FACE.  HU8 REJECTED F	ROM SERVICE.  (X)															6	C	P30NE	 
2000112000218	20001120	00218	SO  	2000	11	20	20001102SH002    	2	20001012	G	7322	63338811	CONTROLLER      			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  						STUCK           	B			VJ3R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	4123C	162  				3449042	819505R			THE CONTROLLER PISTON STICK IN.  A SPLIT IN POWER SETTING IN-FLIGHT AND ON THE GROUND.  CONTROLLER REPLACED.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000111500254	20001115	00254	SO  	2000	11	15	20001102SH003    	2	20001011	G	7322	25765405	SERVO           	PRECISION   		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					FUEL INJECTOR	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142N	56   			70207608	3449128	322021			UNABLE TO ADJUST MIXTURE AND IDLE WILL NOT STAY SET.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2000111500255	20001115	00255	CE  	2000	11	15	20001102SH004    	2	20001011	G	7322	25765405	SERVO           	PRECISION   		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					FUEL INJECTOR	INOPERATIVE     	B			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9299E	160  			70211310	3449043	819256R			UNABLE TO ADJUST MIXTURE AND IDLE.  WILL NOT STAY SET.  ENGINE QUITS WITH BOOST PUMP ON.  (X)						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022100140	20010221	00140	NM  	2001	2	21	20001102SH005    	1	20000908	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										MLG	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4005A					HOUSING IS CRACKED INSIDE THE MOUNTING HOLE.  FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100144	20010221	00144	NM  	2001	2	21	20001102SH007    	1	20000908	G	2782		VALVE           	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					123					BLOCKING VALVE ASSY HAD A CRACKED SLEEVE.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100145	20010221	00145	NM  	2001	2	21	20001102SH008    	1	20000914	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										MLG	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3633					HOUSING IS CRACKED INSIDE THE MOUNTING HOLE.  FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100056	20010221	00056	NM  	2001	2	21	20001102SH009    	1	20000914	G	2910	654468311	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										HYD SYSTEM	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		24699			2030					HOUSING IS CRACKED AT PORT NR 1 CAUSING UNIT TO LEAK WHEN HYDRAULIC PRESSURE IS APPLIED.  POSSIBLE CAUSE:  FATIGUE.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100149	20010221	00149	NM  	2001	2	21	20001102SH010    	1	20000912	G	2730	401606223	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										CHECK VALVE	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					596D					HOUSING ASSY IS CORRODED ON THE SEAL PLATE SURFACES, BOLT HOLES, AND CHECK VALVE PORTS.  HOUSING ASSY IS MADE FROM MAGNE	SIUM ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS.  (X)					2	L	7	3 	4F			RT	A3WE    					 
2001022100150	20010221	00150	NM  	2001	2	21	20001102SH011    	1	20000912	G	2730	401606223	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										CHECK VALVE	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					675R					HOUSING ASSY CORRODED ON THE SEAL PLATE SURFACES, BOLT HOLES, AND CHECK VALVE PORTS.  HOUSING ASSY IS MADE FROM MAGNESIU	M ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS.  (X)					2	L	7	3 	4F			RT	A3WE    					 
2001022100151	20010221	00151	NM  	2001	2	21	20001102SH012    	1	20000829	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										MLG	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					603					HOUSING HAD A CRACKED MOUNT BOLT HOLE.  OVERTORQUING OF MOUNT BOLT IN INSTALLATION.  FLAW IN CASTING OF THE HOUSING.  (X	)					2	L	7	2 	4F			RT	A16WE   					 
2001022100152	20010221	00152	NM  	2001	2	21	20001102SH013    	1	20000823	G	2782	108010	HOUSING         	ROTOL       		BOEING	727   	727*        	       	NM  										SLAT ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4390ADEK					BODY HAD CRACKS IN BOTH THE EXTEND AND RETRACT PORTS.  STRESS AND FATIGUE, TIME IN SERVICE UNKNOWN.  (X)						2	L	7	3 	4F			RT	A3WE    					 
2001022100153	20010221	00153	NM  	2001	2	21	20001102SH014    	1	20000828	G	2782	69358521	SLEEVE          	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					360					BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED.  SUBMITTER STATED APPEARED CRACKS OCCURRING UNDER NORMAL USE.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100154	20010221	00154	NM  	2001	2	21	20001102SH015    	1	20000828	G	2782	69358791	SLEEVE          	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					360					BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED.  SUBMITTER STATED APPEARED CRACKS OCCURRING UNDER NORMAL USE.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100155	20010221	00155	NM  	2001	2	21	20001102SH016    	1	20000828	G	2782	69358521	SLEEVE          	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					384					BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED.  SUBMITTER STATED APPEARED CRACKS WERE OCCURRING UNDER NORMAL USE.  	(X)					2	L	7	2 	4F			RT	A16WE   					 
2001022100156	20010221	00156	NM  	2001	2	21	20001102SH017    	1	20000828	G	2782	69358791	SLEEVE          	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					384					BLOCKING VALVE SLEEVES ITEMS 31 AND 32 ARE CRACKED.  SUBMITTER STATED APPEARED CRACKS WERE OCCURRING UNDER NORMAL USE.  	(X)					2	L	7	2 	4F			RT	A16WE   					 
2001022100157	20010221	00157	NM  	2001	2	21	20001102SH018    	1	20000908	G	7830	65445329	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										CONTROL VALVE	ERODED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					146593					PORT ''D'' HAD EROSION.  POSSIBLE CAUSE:  ANGLE OF PORT ''D'' IN THE HOUSING IS APPROXIMATELY 90 DEGREES.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100158	20010221	00158	NM  	2001	2	21	20001102SH019    	1	20000926	G	2782	65447582	STUD            	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CHIPPED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					0048					LOCKING STUD IS CHIPPING WHERE LOCKING SEGMENTS CONTACT.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100159	20010221	00159	NM  	2001	2	21	20001102SH020    	1	20000926	G	7830	122510	HOUSING         	ROTOL       		BOEING	737   	737*        	       	NM  										SOLENOID VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		7581 			2017					BODY IS CRACKED NEXT TO PORT NR 3.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100160	20010221	00160	NM  	2001	2	21	20001102SH021    	1	20000926	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										SHUTTLE VAVLE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4224					HOUSING IS CRACKED INSIDE THE THREADED AREA OF THE PLUG HOLE.  FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100161	20010221	00161	NM  	2001	2	21	20001102SH022    	1	20000921	G	5513	69778551	SPRING          	BOEING      		BOEING	737   	737*        	       	NM  										HORIZONTAL STAB	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KEO0893					SPRINGS, PN 69-77855-1, ARE BROKEN IN THE AUXILIARY BRAKE SYSTEM CAUSING THE UNIT TO BOND AND JAM.  IMPROPER HEAT-TREATI	NG, AUSTENITE, FATIGUE AND INCREASED SPRING COIL STRESSES.  SUBMITTER STATED SPRINGS PN 69-77855-1 ARE TO BE REPLACED WI	TH PN 69-77855-2 SPRINGS ON ACTUATOR ASSEMBLIES MFG PRIOR TO S/N KEO1730 PER BOEING SL 737-SL-27-090-B.  (X)				2	L	7	2 	4F			RT	A16WE   					 
2001022100102	20010221	00102	NM  	2001	2	21	20001102SH023    	1	20001010	G	2923	654468311	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										HYD SYSTEM	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		16065			2013					HOUSING ASSY HAD MULTIPLE CRACKS IN THE AREA OF PORT NR 1.  WEAK POINT OF HOUSING, POSSIBLE OVERTORQUING OF FITTING UPON	 INSTALLATION.  (X)					2	L	7	2 	4F			RT	A16WE   					 
2001022100103	20010221	00103	NM  	2001	2	21	20001102SH024    	1	20001010	G	2782	65447417	SLEEVE          	BOEING      		BOEING	737   	737*        	       	NM  										SLAT ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1756T					SLEEVE (145) OF THE BLOCKING VALVE ASSY WAS FOUND CRACKED DURING NDI.  REMOVED AND REPLACD SLEEVE (145).  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100104	20010221	00104	NM  	2001	2	21	20001102SH025    	1	20000928	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737*        	       	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		8731 			3867					HOUSING CRACKED INSIDE THE MOUNTING HOLE.  FATIGUE AND/OR DEFECT IN THE CASTING OF THE HOUSING.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001022100105	20010221	00105	NM  	2001	2	21	20001102SH026    	1	20001011	G	3210	65446925	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										MLG SYSTEM	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		56579			1033					HOUSING CRACKED IN THE ''D'' PRIORITY AND ''U'' RESTRICTOR PORTS.  POSSIBLE CAUSE:  FATIGUE, HIGH TSO.  (X)						2	L	7	2 	4F			RT	A16WE   					 
2001030200023	20010302	00023		2001	3	2	20001102SH027    	4	20001003	G	2561		CELL            																	LIFE VEST	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										ONE CELL FAILED THE MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-12.  DATE OF MFG:  OCT 1986.  (X)																			 
2001030200024	20010302	00024		2001	3	2	20001102SH028    	4	20001003	G	2561		CELL            																	LIFE VEST	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										ONE CELL FAILED THE MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-12.  DATE OF MFG OCT 1986.  (X)																			 
2001020900092	20010209	00092	EA  	2001	2	9	20001102SH029    	2	20001016	G	7322		RETAINER        			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					GASCOLATOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	1118N	3873 	1874 			1780				DURING A 100-HOUR INSPECTION, THE GASCOLATOR BOWL RETAINING WIRE BROKE WHILE BEING ASSEMBLED.  THE BREAK OCCURRED AT THE	 FLATTENED PART UNDER THE SCREW.  IF THE BREAK HAD OCCURRED DURING FLIGHT, IT WOULD HAVE CAUSED A MASSIVE FUEL LEAK.  (X	)				1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001022600046	20010226	00046	CE  	2001	2	26	20001102SH030    	1	20001102	G	2752	505211958	ACTUATOR        	RAYTHN      		BEECH 	B300  	B300        	1159232	CE  										LT FLAP	CRACKED         	B			CGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	CGC5L	1426 			378E92	FL87				NOTED DURING REMOVAL OF ACTUATOR FOR ROUTINE 1,200-HOUR LUBE THAT ACTUATOR PISTON WAS CRACKED FOR ENTIRE LENGTH IN AN AP	PROXIMATELY STRAIGHT LINE.   A NEW P/N''D ACTUATOR AND ACTUATOR SHAFT WAS INCORPORATED ON AIRCRAFT, SN R-129, AND UP.  R	EPLACED ACTUATOR WITH SUPERSEDING P/N 129-521050-1.  DAMAGE MAY HAVE OCCURRED FROM FREEZING OF TRAPPED WATER EXPANDING P	ISTON INTERNALLY, OR, BRITTLE METAL CONDITION.  (X)			2	L	7	2 	4T			RT	A24CE   					 
2001030100031	20010301	00031	EU  	2001	3	1	20001102SH031    	1	20001002	G	3246		BOLT            			BRAERO	1000  	BAE1251000A 	1500104	EU  										WHEEL ASSY	FAILED          	B			VG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	35	204R					259017				DUNLOP WHEEL CMM TIE BOLT RUNNING TORQUE CHECK DOES NOT CHECK FULL LENGTH OF THE THREADS.  THE TIE BOLTS APPEAR TO BE ST	RETCHING FARTHER TOWARD THE SHANK OF THE BOLT.  WHEN RUNNING TORQUE WAS CHECKED OVER, THE FULL LENGTH OF THE THREAD, 5 B	OLTS FAILED.  (X)				2	L	7	2 	4F			RT	A3EU    					 
2001022600047	20010226	00047	NE  	2001	2	26	20001102SH032    	2	20000806	G	7250		TURBINE         			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5079S					3010116	2P103762			ENGINE DISASSEMBLED 10/4/00.  EXTENSIVE DAMAGE TO POWER SECTION OF ENGINE DUE TO ENGINE OPERATION AFTER FIRST KNOWLEDGE 	OF MALFUNCTION.  POSSIBLE CAUSE, LINK ROD BROKE AT LINK PIN AND DUE TO METAL FATIGUE.  (X)					1	L	7	1 	3R	3	R	 	A9SW    	5E2				 
2001020900093	20010209	00093	SW  	2001	2	9	20001102SH033    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB	9553 			0022221970	LN001				FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX.  APPEARED THAT M/R 	TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001021300005	20010213	00005	SW  	2001	2	13	20001102SH034    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	523FB	8355 			0022221992	LN003				FOUND PAINT SEALANT INSIDE M/R MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX.  APPEARED THAT M/R TRANSMI	SSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001021300006	20010213	00006	SW  	2001	2	13	20001102SH035    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	8397 			0022221999	LN004				FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX.  APPEARED THAT M/R 	TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001021300007	20010213	00007	SW  	2001	2	13	20001102SH036    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	525FB	7947 			0022222004	LN005				FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX.  APPEARED THAT M/R 	TRANSMISSION OIL MOBIL SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001021300008	20010213	00008	SW  	2001	2	13	20001102SH037    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	526FB	8121 			0022221998	LN006				FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX.  APPEARED THAT M/R 	TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001021300009	20010213	00009	SW  	2001	2	13	20001102SH038    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	527FB	7576 			0022222003	LN007				FOUND PAINT SEALANT INSIDE MAST TUBE BLISTERED AND FALLING INTO M/R TRANSMISSION GEARBOX.  APPEARED THAT M/R TRANSMISSIO	N OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF M/R MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001021300010	20010213	00010	SW  	2001	2	13	20001103SH001    	1	20001013	G	6230		MAST            			HUGHES	500N  	500N        	3027374	SW  										MAIN ROTOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	522FB	8505 			0022221949	LN002				FOUND PAINT SEALANT INSIDE MAIN ROTOR MAST TUBE BLISTERED AND FALLING INTO MAIN ROTOR TRANSMISSION GEARBOX.  APPEARED TH	AT MAIN ROTOR TRANSMISSION OIL MOBILE SHC 626 IS NOT COMPATIBLE WITH SEALANT PAINT ON INSIDE OF MAIN ROTOR MAST.					1	G	7	1 	3U			NC	H3WE    					 
2001022600048	20010226	00048	CE  	2001	2	26	20001103SH005    	1	20000925	G	5711		SPAR            			BEECH 	23    	C23         	1151242	CE  										LT AND RT WING	CORRODED        	B			T9ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7694R	2924 				M1294				INSPECTION OF LEFT AND RIGHT WINGS DUE TO ACCIDENT.  EXFOLIATION CORROSION IN LOWER SPAR CAP WAS FOUND IN THE SAME AREA 	ON LEFT AND RIGHT WING SPARS.  CORROSION IS LOCATED JUST OUTBOARD OF SPAR SPLICE CONTINUING ON TO WING TIP OR SPAR END. 	 DAMAGE IS EXTREMELY VISIBLE AND SHOULD BE FOUND DURING ROUTINE INSPECTION.  WING LEADING EDGE IS FACTORY GLUED TO SPAR 	IN THIS LOCATION.  WING SPAR JUNK.  (X)			1	L	7	1 	3O			 	A1CE    					 
2001022600050	20010226	00050		2001	2	26	20001103SH008    	4	20001016	G	3422	102620422	GYRO            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					INSTRUMENT PNL	FLUCTUATES      	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	19	9550Q	916  				17280517	L2758651A			DIRECTIONAL GYRO PRECESSES ABOUT 5 DEGREES EVERY 10 MINUTES IN-FLIGHT.  WITH VACUUM SYSTEM TEST KIT INSTALLED, DG PRECES	SES ABOUT ONE-HALF DEGREE EVERY 15 MINUTES.  ON THE NEW CESSNA AIRCRAFT, THE INSTRUMENTS AS WELL AS THE INSTRUMENT PANEL	 ARE HARD MOUNTED TO THE AIRFRAME.  SUBMITTER SUSPECTED THE VIBRATIONS CAUSED BY THE RUNNING ENGINE ARE TRANSMITTED DIRE	CTLY TO THE INSTRUMENTS AND ARE THE CAUSE OF THE PROBLEM.  (X)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001022600054	20010226	00054	SW  	2001	2	26	20001106SH084    	1	20001017	G	3710		PUMP            			MOONEY	M20   	M20J        	5870219	SW  										VACUUM PUMP	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	CGPKE					240071				PUMP FAILED, 170.5 HOURS.  X)						1	L	7	1 	3O			 	2A3     					 
2001021400004	20010214	00004	SW  	2001	2	14	20001106SH085    	1	20001015	G	6720		CONTROL ROD     			HUGHES	500N  	500N        	3027374	SW  										TAIL ROTOR	CHAFED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	954SD	3103 				LN079				PILOT REPORTED, DURING THROTTLE ADVANCE ON RUN-UP, A LOUD RUMBLING NOISE AND SEVERE VIBRATION STARTED ABRUPTLY AS TORQUE	 APPROACHED 40 PERCENT TORQUE.  INSP OF ALL SYS BY MECH FOUND NO PROBLEM AREA.  TWO SUBSEQUENT RUNS PRODUCED NO REPEAT O	F PROBLEM THIRD RUN, SHIP START VIBRATION AGAIN, VERY SEVERE, LOUD NOISE.  AFTER SHUT DOWN, TEAR DOWN OF DRIVETRAIN AND 	CONTROLS, DISCOVERED FAN AFT CONTROL TUBE FOR ANTI-TORQUE CONTROL HAD RUBBED IN 2 PLACES.  RUB FND ON FWD PART OF ROD TH	AT PASSES THRU FAN GRBX, OUTPUT GEARSHFT ID, REAR CNTRL TUBE, MINOR RUB CENTER OF CNTRL TUBE.  SUBMITTER FOUND NO CAUSE 	FOR THIS CONDITION.  MD HELICOPTERS INFORMED.  (X)	1	G	7	1 	3U			NC	H3WE    					 
2001022600055	20010226	00055	CE  	2001	2	26	20001106SH086    	1	20001012	G	5753	052390114	SUPPORT FITTING 			CESSNA	172   	172R        	2072401	CE  										RT FLAP	GROOVED         	B			EBVD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	992CP	842  				17280284				DURING INSPECTION, FOUND RT FLAP, INBOARD HINGE, INBOARD FLAP SUPPORT ARM WAS GROOVED BY THE AFT BEARING CHAFING ON IT. 	REPLACED BOTH THE INBOARD AND OUTBOARD SUPPORT A;RMS.  SEB 95-3 ADDRESSES INSPECTING THESE AREAS.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001022600056	20010226	00056	CE  	2001	2	26	20001106SH087    	1	20001012	G	5753	052390113	SUPPORT FITTING 			CESSNA	172   	172R        	2072401	CE  										RT FLAP	GROOVED         	B			EBVD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	992CP	842  				17280284				DURING INSPECTION, FOUND RT FLAP, INBOARD HINGE, INBOARD FLAP SUPPORT ARM WAS GROOVED BY THE AFT BEARING CHAFING ON IT. 	 SUBMITTER STATED THIS CONDITION IS USUALLY FOUND AT THE FORWARD BEARING AREA.  FIRST TIME THIS FACILITY HAS SEEN IT IN 	THE AFT BEARING AREA.  REPLACED BOTH THE INBOARD AND OUTBOARD SUPPORT ARMS.  SEB 95-3 ADDRESSES INSPECTING THESE AREAS. 	 (X)			1	H	7	1 	3O			NT	3A12    					 
2001021400005	20010214	00005	NE  	2001	2	14	20001107SH001    	2	20000525	G	7313	430167601	NOZZLE          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUEL MANIFOLD	MALFUNCTIONED   	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	61LF	507  				7230	LE45988EFA			IMPROPER NOZZLE SPRAY PATTERN.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021400006	20010214	00006	NE  	2001	2	14	20001107SH002    	2	20001005	G	7250	414129011	TURBINE WHEEL   			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					PT SECTION	DAMAGED         	B			R7MR	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	07	62LF					7163	LE45753EFA			LOSS OF TORQUE RETENTION.  REPLACED WITH NEW ROTOR, CORRECTED PROBLEM.  ROTOR ASSY, INSERTABLE BLADED, POWER TURBINE.  (	X)					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021400007	20010214	00007	NE  	2001	2	14	20001107SH003    	2	20000720	G	7313	430167601	NOZZLE          			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					FUEL MANIFOLD	MALFUNCTIONED   	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	62LF	651  				7163	LE45508EFA			IMPROPER NOZZLE SPRAY PATTERN.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021400008	20010214	00008		2001	2	14	20001107SH004    	4	20000920	G	3457	069010250025	GPS             			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	OUT OF TOLERANCE	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	103LN	708  				3128				VHF COMMUNCIATION TRANSCEIVER/NAVIGATION RECEIVER; GPS OFF COURSE, SOMETIMES BY AS MUCH AS 15 DEGREES.  REPLACED WITH NE	W UNIT, CORRECTED PROBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021400009	20010214	00009	EU  	2001	2	14	20001107SH005    	1	20001021	G	2450	45023500	CONTROL BOX     			UROCOP	EC135 	EC135P1     	8680990	EU  										ELECTRICAL SYS	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	135N	2    				EC1350086				ELECTRICAL MASTER BOX, RT FULL OPT, UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001021400010	20010214	00010	EU  	2001	2	14	20001107SH006    	1	20001009	G	3340	02471131	LIGHT           			SNIAS 	350   	AS350B3     	8680954	EU  										SEARCH LIGHT	SHORTED         	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	397LG	71   				3268				SEARCH LIGHT ASSEMBLY (SX-5) HAD INTERNAL SHORT.  WILL NOT LIGHT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021400011	20010214	00011	NE  	2001	2	14	20001107SH007    	2	20000603	G	7320		TUBE            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					FUEL MANIFOLD	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			TUBE-START ASSIST TO MANIFOLD FEED WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400012	20010214	00012	NE  	2001	2	14	20001107SH008    	2	20000603	G	7230	430124203	BEARING         			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					COMPRESSOR	CORRODED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			BEARING - ANNULAR BALL, COMPRESSOR, EXCESSIVE PITTING REPLACED WITH NEW UNIT, CORRECTED. PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400013	20010214	00013	NE  	2001	2	14	20001107SH009    	2	20000603	G	7250	410106701	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					1ST TURB SHROUD	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			SEAL RING - FIRST TURBINE SHROUD, WORN BEYOND SERVICEABLE LIMITS.  REPLACED 2 EACH WITH NEW UNITS, CORRECTED PROBLEM.  (	X)					1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400014	20010214	00014	NE  	2001	2	14	20001107SH010    	2	20000603	G	7250	410106802	SPRING          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					SEAL RING	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			SPRING - SEAL RING EXPANDER, WORN BEYOND SERVICEABLE LIMITS.  REPLACED 2 EACH WITH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400015	20010214	00015	NE  	2001	2	14	20001107SH011    	2	20000603	G	7230	430151801	BEARING         			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			BEARING - CYLINDER ROLLER NR 2, WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400016	20010214	00016	NE  	2001	2	14	20001107SH012    	2	20000603	G	7240	413102002	CURL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					COMBUST CHAMBER	DAMAGED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			CURL ASSY - COMBUSTION CHAMBER, EXCESSIVE BURN IN SOME AREAS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400017	20010214	00017	NE  	2001	2	14	20001107SH013    	2	20000603	G	7250	430144801	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 3 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058	LE45291EA			SEAL - NR 3 BEARING, LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400018	20010214	00018	EU  	2001	2	14	20001107SH014    	1	20000603	G	7720	430150102	THERMOCOUPLE    			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	SHORTED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058				THERMOCOUPLE HAD INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001021400019	20010214	00019	EU  	2001	2	14	20001107SH015    	1	20000603	G	7720	430150102	THERMOCOUPLE    			BOLKMS	117   	BK117A3     	5626015	EU  										ENGINE	SHORTED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	158BK	702  				7058				THERMOCOUPLE HAD INTERNAL SHORT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001021400020	20010214	00020	NM  	2001	2	14	20001107SH016    	1	20001001	G	6220	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	33   				90000012				CENTER BEARING ASSY, MAIN ROTOR, DEBONDING.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400021	20010214	00021	NM  	2001	2	14	20001107SH017    	1	20001016	G	6220	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	39   				90000012				CENTERING BEARING ASSY, MAIN ROTOR, DEBONDING.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400022	20010214	00022		2001	2	14	20001107SH020    	4	20000809	G	3160	764B04	BATTERY         			DOUG  	MD900 	MD900       	3027375	NM  										DISPLAY	FAULTY          	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	10   				90000012				BMS FAULTS 2 AND 4 TRIGGERED REGULARLY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.   (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400023	20010214	00023	NM  	2001	2	14	20001107SH021    	1	20000911	G	7810	900P2630115102	EXHAUST PIPE    			DOUG  	MD900 	MD900       	3027375	NM  										ENGINE	CRACKED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	321  				90000012				RIGHT PRIMARY EXHAUST NOZZLE CRACKED BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400024	20010214	00024	NM  	2001	2	14	20001107SH022    	1	20000908	G	6710	900C2010214101	PITCH LINK      			DOUG  	MD900 	MD900       	3027375	NM  										ROTOR CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	505  				90000012				PITCH LINK ASSY, ROTOR CONTROL, WORN BEYOND SERVICEABLE LIMITS.  REPLACED 5 EACH WITH NEW UNITS, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400025	20010214	00025	NM  	2001	2	14	20001107SH023    	1	20000912	G	6720	900F2421545105	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										THRUSTER	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	308  				90000012				BEARING RACE, THRUSTER, WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400026	20010214	00026	NM  	2001	2	14	20001107SH024    	1	20000912	G	6720	900R2441017101	SLEEVE          			DOUG  	MD900 	MD900       	3027375	NM  										NOTAR FAN HUB	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	584  				90000012				SLEEVE, NOTAR FAN HUB, WORN BEYOND SERVICEABLE LIMITS.  REPLACED 13 EACH WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400027	20010214	00027	NM  	2001	2	14	20001107SH025    	1	20000916	G	6710	900C3010002105	FRICTION RING   			DOUG  	MD900 	MD900       	3027375	NM  										COLLECTIVE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	2650 				90000012				COLLECTIVE FRICTION UNIT LOST FRICTION CONTROL.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400028	20010214	00028	NM  	2001	2	14	20001107SH026    	1	20000309	G	6321	431373	BOLT            			DOUG  	MD900 	MD900       	3027375	NM  										ROTOR BRAKE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	625  				90000012				BOLT - ROTOR BRAKE, WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400029	20010214	00029	NM  	2001	2	14	20001107SH027    	1	20000809	G	6321	900D3403006101	LINER           			DOUG  	MD900 	MD900       	3027375	NM  										ROTOR BRAKE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	625  				90000012				ROTOR BRAKE LINING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEMS.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021400030	20010214	00030	NE  	2001	2	14	20001107SH028    	2	20000610	G	7250	410106802	SPRING          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					SEAL RING	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	163BK	389  				7063	LE45115EA			SPRING - SEAL RING EXPANDER, WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400031	20010214	00031	NE  	2001	2	14	20001107SH029    	2	20000610	G	7250	410106701	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					1ST TURB SHROUD	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	163BK	389  				7063	LE45115EA			SEAL RING - FIRST TURBINE SHROUD, WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400032	20010214	00032	NE  	2001	2	14	20001107SH030    	2	20000907	G	7313	430167601	NOZZLE          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					FUEL MANIFOLD	MALFUNCTIONED   	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	951AM					7017	LE45111EA			FUEL MANIFOLD ASSY HAD IMPROPER NOZZLE SPRAY PATTERN.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021400033	20010214	00033	NM  	2001	2	14	20001108SH002    	1	20000813	G	6220	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DEBONDED        	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	687  				90000012				MAIN ROTOR CENTER BEARING ASSEMBLY IS DEBONDING.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001011101205	20010111	01205		2001	1	11	20001108SH003    	4	20001016	G	6122	B20908	FLYWEIGHT       	MCAULY      							CONT  	O520  	IO520*      	17032	SO  					GOVERNOR	DAMAGED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					781836					RELEVANT MAGNETIC PARTICLE INDICATION IN ALL FOUR CORNERS OF FLYWEIGHT DISC.  REF:  CESSNA.  (X)											3	O			E5CE				 
2000120700117	20001207	00117	CE  	2000	12	7	20001108SH019    	1	20001027	G	3213	07416301	SPRING          			CESSNA	182   	182P        	2075816	CE  										STEP BRACKET	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	1933M					18264487				THREE YEARS AFTER REPAIR OF CRACKS IN MAIN LANDING GEAR LEG FAIRING USING A RIVETED PATCH, FOUND THAT HEADS OF RIVETS HA	D WORN 7 HOLES (DEPRESSIONS) ABOUT .010 INCH DEEP IN GEAR LEG.  CONSULTED CESSNA TECH SERVICE WHO STATED LEG MUST BE REP	AIRED OR REPLACED DUE TO DAMAGE THROUGH SHOT PEENED LAYER.  REPAIR IMPOSSIBLE LOCALLY BECAUSE NO FACILITY TO SHOT PEEN A	REA THAT HAD TO BE GROUND AND POLISHED OUT.  SUBMITTER RECOMMENDED THAT ANY PATCHING OF FAIRING BE COVERED WITH ANTI-ABR	ASION TAPE.  ALSO A GOOD IDEA TO REMOVE FAIRING PERIODICALLY TO EXAMINE GEAR LEG FOR WEAR AND TO RENEW ANTI-ABRASION TAP	E.  (X)	1	H	7	1 	3O			NT	TA13    					 
2000120700118	20001207	00118	SW  	2000	12	7	20001108SH020    	1	20001023	G	5753	210104	HINGE           	MOONEY      		MOONEY	M20   	M20J        	5870219	SW  										RT WING INBD HNG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	191ER	9255 				243252				DURING A PRE-FLIGHT INSPECTION, AN INSTRUCTOR NOTICED THE RIGHT FLAP HAD PLAY OR EXCESSIVE TRAVEL WITH FLAPS DOWN.  UPON	 INSPECTION, THE HINGE, P/N 210104-000, WAS FOUND BROKEN JUST BELOW THE AFT HINGE (BOLT).  THE BREAK APPEARED TO BE A FR	ESH BREAK.  (X)				1	L	7	1 	3O			 	2A3     					 
2000120700119	20001207	00119	EA  	2000	12	7	20001108SH021    	2	20001010	G	8520	LW19341	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 1&2 CAMSHAFTS	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	200AK	535  				318052180	L79368A			STEEL WAS FOUND IN BOTH SPIN-ON FILTER AND OIL SUCTION SCREENS.  CAMSHAFT SUSPECTED FAILING, AND PROVEN WITH VISUAL INSP	ECTION AND CHECKING THE LIFT OF ALL OF THE LOBES.  NR 1 AND NR 2 LOBES WERE ONLY GIVING HALF THE LIFT FROM THE OTHER LOB	ES.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000120700120	20001207	00120	SW  	2000	12	7	20001108SH022    	1	20001018	G	3710		PUMP            			MOONEY	M20   	M20J        	5870219	SW  										VACUUM PUMP	FAILED          	B			L9PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	201DB	58   				240026				VACUUM PUMP (215CC) FAILED, 58.1 HOURS.  (X)						1	L	7	1 	3O			 	2A3     					 
2000120700121	20001207	00121	SW  	2000	12	7	20001108SH023    	1	20001015	G	3710		PUMP            			MOONEY	M20   	M20J        	5870219	SW  										VACUUM PUMP	FAILED          	B			L9PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	201DB	39   				240026				PUMP (215CC) FAILED AFTER 39 HOURS.  (X)						1	L	7	1 	3O			 	2A3     					 
2000120700122	20001207	00122	CE  	2000	12	7	20001108SH026    	1	20001010	G	7430	C2925010109	IGNITION SWITCH 			CESSNA	172   	172S        	2072439	CE  											STUCK           	B			BF8R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	508ER	1843 				172S8008				PILOT SQUAWK:  IGNITION KEY STICKS IN OFF POSITION.  MAINTENANCE REMOVED IGNITION SWITCH AND FOUND BURNED CONTACTS.  THI	S IS THE SAME SWITCH COVERED BY AD 83-05-06.  HOWEVER, THE 172S MODEL IS NOT INCLUDED IN THE AD LIST.  SUBMITTER STATED 	THE 172R''''S MODEL AIRCRAFT SHOULD BE INCLUDED IN AD.  ACS KIT NR A3600 INSTALLED.  OPERATIONAL CHECK GOOD.  AIRCRAFT R	ELEASED.  (X)			1	H	7	1 	3O			NT	3A12    					 
2001021400034	20010214	00034	SW  	2001	2	14	20001108SH027    	1	20001013	G	6320	369D25100507	GEAR            			HUGHES	500N  	500N        	3027374	SW  										M/R TRANSMISSION	SPALLED         	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	07	526FB	4603 	1935 			2N006				MAIN ROTOR CHIP DETECTORS PICKING UP MAJOR METAL.  OPENED GEARBOX AND INSPECTED.  FOUND SPALLING OF ALL GEARS.  SUBMITTE	R SUGGESTED OIL NOT LUBRICATING UNDER LOADS.  USING MOBIL SHC 626 PER MDHC NOTICE NL.001.1.  (X)					1	G	7	1 	3U			NC	H3WE    					 
2000120700123	20001207	00123	GL  	2000	12	7	20001108SH028    	3	20001016	G	6110		PROPELLER       			PIPER 	PA24  	PA24180     	7102402	CE  						MCAULY	3D36C	B3D36C424   	GL  	PROP ASSEMBLY	VIBRATION       	B			PC7R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	09	5785P					24864		000624		NEW MCAULEY STC PROPELLER KIT INSTALLED, ACFT FLOWN FOR BRIEF FLIGHT.  AIRCRAFT HAD SUCH VIOLENT VIBRATION, PILOT NO LON	GER WILLING TO FLY IT.  INSPECTION OF BLADE ANGLES WITH PROP ON ACFT, SHOWED ANGLES WERE NOT IN COMPLIANCE WITH MFG SPEC	S BETWEEN BLADES AND COULD CAUSE VIBRATION.  MCAULEY REPLACEMENT PROPELLER CHECKED, WHILE NOT PERFECT, WAS INSTALLED.  S	TILL THERE WAS VIBRATION.  BOTH 3-BLADED PROPS WERE DYNAMICALLY BALANCED TO REDUCE VIBRATION.  NEW MOTOR MOUNTS INSTALLE	D.  TEST FLOWN, STILL VIBRATION.  FINAL EFFORT, ORIG 2-BLADED HARTZL PROP RE-INSTALLED AND FLOWN TO ITS DESTINATION.  SU	BMITTER STATED STC NR SA360CH DOES NOT INDICATE RESTRICTIONS ON ACFT MODEL OR SERIAL NUMBER.   (X)	1	L	7	1 	3O			NT	1A15    		5	C	P58GL	 
2000120700124	20001207	00124	GL  	2000	12	7	20001108SH029    	3	20001016	G	6110		PROPELLER       			PIPER 	PA24  	PA24180     	7102402	CE  						MCAULY	3D36C	B3D36C424   	GL  	PROP ASSY	VIBRATION       	B			PC7R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	09	5785P					24864		000624		NEW MCAULY STC PROPELLER KIT INSTALLED, ACFT FLOWN FOR BRIEF FLIGHT.  AIRCRAFT HAD SUCH VIOLENT VIBRATION, PILOT NO LONG	ER WILLING TO FLY IT.  INSPECTION OF BLADE ANGLES WITH PROP ON ACFT, SHOWED ANGLES WERE NOT IN COMPLIANCE WITH MFG SPECS	 BETWEEN BLADES AND COULD CAUSE VIBRATION.  MCAULEY REPLACEMENT PROPELLER CHECKED, WHILE NOT PERFECT, WAS INSTALLED.  ST	ILL THERE WAS VIBRATION.  BOTH 3-BLADED PROPS WERE DYNAMICALLY BALANCED TO REDUCE VIBRATION.  NEW MOTOR MOUNTS INSTALLED	.  TEST FLOWN, STILL VIBRATION.  FINAL EFFORT, ORIG 2-BLADED HARTZL PROP RE-INSTALLED AND FLOWN TO ITS DESTINATION.  SUB	MITTER STATED STC NR SA360CH DOES NOT INDICATE RESTRICTIONS ON ACFT MODEL OR SERIAL NUMBER.   (X)	1	L	7	1 	3O			NT	1A15    		5	C	P58GL	 
2001020200067	20010202	00067	NE  	2001	2	2	20001108SH030    	2	20001013	G	7200	70BM031070	ENGINE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE BAY	STALLED         	E			HWVA	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	13		8103 	2015 				4463			PILOT COMPLAINT WAS SMALL COMPRESSOR STALLS ''POPPING SOUND'' OCCURRING WHEN THEY WOULD DROP COLLECTIVE.  THIS WAS AN IN	FREQUENT OCCURRENCE THAT WAS HAPPENING OVER A PERIOD OF DAYS PRIOR TO INSPECTION OF THE TURBINE SECTION.  FULL INSPECTIO	N OF THE COMPRESSOR, BLEED VALVE, AND RELATED SYSTEM WERE CONDUCTED, WITHOUT SUCCESS.  INSPECTION OF THE HOT END WAS CON	DUCTED AND DISCOVERY OF BROKEN TURBINE BLADES WAS DISCOVERED.  ENGINE WAS REMOVED AND SHIPPED TO ACRO FOR INSPECTION.  (	X)		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001022600058	20010226	00058	CE  	2001	2	26	20001108SH031    	1	20000816	G	2820		FUEL LINE       			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL DISTRIBUTE	VAPOR LOCK      	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NM	07	567JW	662  				172S8187	L2822651A			PILOT REPORTED AT 2,400 RPM, NO CLIMB POWER.  TRIED ADJUSTING  MIXTURE SETTINGS, NOTHING WORKED.  ENGINE COUGHED ON DOWN	WIND, ACFT WOULD NOT CLIMB.  MAINT ATTEMPTED ENGINE START AFTER PARKING ACFT.  ENGINE WAS VAPOR LOCKED, WITH ELEC BOOST 	PUMP ON AND MIXTURE IN FULL RICH, NO FUEL FLOW COULD BE ATTAINED, NO FUEL WOULD FLOW FROM DRAIN.  AFTER ENG COOLED, APPR	OX 1 HOUR, ENGINE WAS STARTED, OIL TEMP INDICATED 150 DEGREES FAHRENHEIT.  ENGINE OPERATION WAS NORMAL, FULL POWER COULD	 BE DEVELOPED, AND MAGNETO CHECK NORMAL.  ADJ MADE TO THE IDLE MIXTURE TO ENRICH IT, AND THE IDLE SPEED RE-ADJUSTED.  AI	RCRAFT TEST FLOWN, RELEASED FOR FLIGHT WITH NO ABNORMALTIES NOTED.  ENGINE FUEL SERVO REPLACED IN JULY, SAME PROBLEM.(X)	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000120700125	20001207	00125	CE  	2000	12	7	20001108SH032    	1	20001023	G	3213	12414231	SADDLE          			CESSNA	210   	T210F       	2073422	CE  											CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6780R	1548 				T2100180				DURING ANNUAL INSPECTION AND C/W AD 76-14-07, R2 VISUAL INSPECTION AND DYE PENETRANT INSPECTION OF THE APPROVED P/N 1241	423-1 AND P/N 1241423-2, LANDING  GEAR SADDLES SHOWED CRACKS IN THE FORWARD INBOARD RADIUS OF EACH SADDLE.  TOTAL TIME O	N EACH PART 1,547.89 HOURS IN 23 YEARS OF SERVICE.  REPLACED SADDLES WITH NEW P/N 1294151-1 AND P/N 1294151-2 SADDLES.  	(X)			1	H	7	1 	3O			 	3A21    					 
2000120700126	20001207	00126	CE  	2000	12	7	20001108SH033    	1	20001023	G	3213	12414232	SADDLE          			CESSNA	210   	T210F       	2073422	CE  											CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6780R	1548 				T2100180				DURING ANNUAL INSPECTION AND C/W AD 76-14-07, R2 VISUAL INSPECTION AND DYE PENETRANT INSPECTION OF THE APPROVED P/N 1241	423-1 AND P/N 1241423-2, LANDING  GEAR SADDLES SHOWED CRACKS IN THE FORWARD INBOARD RADIUS OF EACH SADDLE.  TOTAL TIME O	N EACH PART 1,547.89 HOURS IN 23 YEARS OF SERVICE.  REPLACED SADDLES WITH NEW P/N 1294151-1 AND P/N 1294151-2 SADDLES.  	(X)			1	H	7	1 	3O			 	3A21    					 
2000120700127	20001207	00127	CE  	2000	12	7	20001108SH034    	1	20000913	G	2750	052390138	FLAP            			CESSNA	172   	R172E       	2072413	CE  										RT INBOARD	DESTROYED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	7899N	13495				R1720290				AIR LOADS MOVED THE RIGHT FLAP OUTBOARD SO THAT, WHEN RETRACTED, THE INBOARD RIB ASSY - FLAP SUPPORT ARM LEFT, P/N 05239	01-8, WAS BLOCKED BY THE FLAP TRACK SUPPORT STRUCTURE.  BOTH FLAP SUPPORT ARMS WERE BENT BACKWARD BY THE FORCE OF THE FL	AP MOTOR, FINALLY JAMMING AT ABOUT FIVE DEGREES DOWN.  SUBMITTER RECOMMENDED INSTALLATION OF CESSNA SERVICE KIT SK180-44	-1.  (X)			1	H	7	1 	3O			 	3A17    					 
2001021400035	20010214	00035	EU  	2001	2	14	20001108SH035    	1	20001004	G	5302	350A23101920	BULKHEAD        			SNIAS 	350   	AS350B2     	8680813	EU  										TAILBOOM	CRACKED         	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6103X	3262 				2723				DURING SCHEDULED INSPECTION WITH HORIZONTAL STABILIZER REMOVED, NOTICED 2 LOOSE RIVETS THAT ATTACH RT AFT GUSSET OF BATT	ERY SHELF TO BULKHEAD LOCATED AT BOOM STATION 119.0.  THIS IS AN STC RELOCATING THE BATTERY TO THE TAILBOOM.  STC NR SH5	117NM, HELD AND INSTALLED BY AMERICAN EUROCOPTER PRIOR TO DELIVERY.  RIVET TYPE:  CR3212-4.  ON ANOTHER OCCASION, 2 OF T	HESE 3 ATTACH RIVETS WERE FOUND SHEARED.  BELIEVE VIBRATION COULD BE SOURCE OF PROBLEM AS BATTERY IS HELD DOWN BY FWD AN	D AFT HOLD-DOWN BRACKETS AT BASE OF BATTERY.  NO FEATURE TO HOLD BATTERY DOWN FROM TOP.  ALTHOUGH BATTERY FELT SECURE PR	IOR TO REMOVAL, FRETTING WAS NOTICED ON THE RT UNDERSIDE AFT HOLD-DOWN BRACKET.  (X)	1	G	7	1 	3U			 	H9EU    					 
2001022600060	20010226	00060	CE  	2001	2	26	20001108SH037    	1	20001008	G	3211	2082900	STUD            			PIPER 	PA24  	PA24180     	7102402	CE  										LANDING GEAR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	8170P		453  			243426				LANDING GEAR STUD IS TO BE INSPECTED EVERY 1,000 HOURS PER AD 97-01-01.  CRACKED STUD IN QUESTION HAD ONLY 453 HOURS SIN	CE LAST MAGNAFLUX INSPECTION.  (X)					1	L	7	1 	3O			NT	1A15    					 
2001020900094	20010209	00094	CE  	2001	2	9	20001108SH038    	1	20000918	G	5347		PIN             			CESSNA	208   	208B        	2073701	CE  										CARGO TIE DOWN	SHEARED         	E			T0DA	K				NONE                    				O			OTHER                     			UK	UNKNOWN        	1			CE	03	806BF					208B0806				THE ROLL PIN THAT HOLDS THE LOCK MECHANISM FOR THE CARGO TIE-DOWN FITTING, PN 22555-71, SHEARED CAUSING THE CARGO STRAP 	TO COME LOOSE AND THE LOAD TO SHIFT.  THE LOAD SHIFT CAUSED THE AIRCRAFT IN QUESTION TO FALL ONTO THE TAIL TIE-DOWN AFTE	R THE ENGINE WAS SHUT DOWN.  (X)				1	H	7	1 	3T			 	A37CE   					 
2001030100032	20010301	00032	SO  	2001	3	1	20001108SH039    	2	20001005	G	8530		CYLINDER        			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  					ENGINE	SEPARATED       	B			AW0R	A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			GL	15	9248C					31347	461046J			DURING WATER TAKEOFF, EXPERIENCED MODERATE ROUGH RUNNING ENGINE, RETURNED TO LAKE.  INSPECTION REVEALED ONE CYLINDER HAD	 SEPARATED BETWEEN BARREL AND HEAD.  THESE 6 CYLINDERS HAD APPROX 400 HOURS SINCE BEING CHROMED.  OWNER REPLACED ALL CYL	INDERS WITH NEW SUPERIOR MILLLENIUM SET.  (X)				1	H	7	1 	3O	3	O	NC	5A6     	E273				 
2001021400036	20010214	00036	GL  	2001	2	14	20001108SH040    	2	20000922	G	7250		TURBINE WHEEL   			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					NR 1	DAMAGED         	B				O				OTHER                   				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	07	905MC	2242 	378  			53214	CAE847242			DURING APPROACH TO LAND, PILOT EXPERIENCED A LOUD CONTINUOUS NOISE COMING FROM THE ENGINE.  ALL ENGINE INSTRUMENTS WERE 	NORMAL.  ENGINE WAS INSPECTED BY MAINT, NO OBVIOUS MALFUNCTIONS WERE NOTED.  DURING ENGINE RUN-UP TO ISOLATE ENGINE NOIS	E, THE ENGINE CHIP DETECTOR CAUTION LIGHT ILLUMINATED.  CHROME SLIVERS WERE FOUND ON BOTTOM PLUG.  TEAR-DOWN INSPECTION,	 FOUND NR 1 TURBINE WHEEL BLADE MISSING AND OTHER BLADES DAMAGED.  (X)			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001021400037	20010214	00037	SW  	2001	2	14	20001108SH041    	1	20001018	G	8000	M835366025M	RELAY           			BELL  	407   	407         	       	SW  										STARTER	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	911FS	312  				53424				START DELAY FAILED/INTERMITTENT.  DURING START SEQUENCE, REPLACED PART PER BHT TECH REP.  (X)						1	G	7	1 	3U			O	H2SW    					 
2000120700116	20001207	00116	SO  	2000	12	7	20001108SH042    	1	20001027	G	7120	6711949	MOUNT           			PIPER 	PA28  	PA28R200    	7102811	SO  										ENGINE MOUNT	BROKEN          	G				O				OTHER                   				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			EA	23	9392N					28R35102				DURING THE COURSE OF A 100 HR INSPECTION, MAINTENANCE DISCOVERED THE ENGINE MOUNT, P/N 67119-49, COMPLETELY BROKEN AT TH	E TOP RIGHT HAND SIDE OF THE COMPONENT. THIS WAS NOT SIMPLY A CRACK, BUT RATHER, THE TUBE WAS COMPLETELY BROKEN THROUGH.	  THIS FAILURE IS THE SUBJECT OF PIPER SERVICE LETTER 568.  THE NATURE OF THIS FAILURE IS SUCH THAT IT COULD LEAD TO SEP	ARATION OF THE ENGINE AND SUBSEQUENT LOSS OF CONTROL OF THE AIRCAFT.  A SEARCH OF THE SDR DATABASE REVEALED THAT SEVEN O	THER FAILURES ARE ON RECORD FOR THIS SAME PART NUMBER.  SUBMITTER RECOMMENDS THESE MOUNTS BE CLOSELY INSPECTED AT EACH 1	00 HOURS AS STIPULATED BY THE SERVICE LETTER.  FOR A COPY OF THIS SERVICE LETTER, CONTACT THE NEW PIPER AIRCRAFT. (X)	1	L	7	1 	3O			 	2A13    					 
2001011101225	20010111	01225	SO  	2001	1	11	20001108SH043    	1	20001108	G	7120	6711949	MOUNT           			PIPER 	PA28  	PA28R200    	7102811	SO  										ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	9330N					28R35030				DURING THE COURSE OF A 100 HR INSPECTION, MAINTENANCE DISCOVERED THE ENGINE MOUNT P/N 67119-49, WAS CRACKED AT THE TOP L	EFT SIDE OF THE COMPONENT. THIS FAILURE IS THE SUBJECT OF PIPER SERVICE LETTER 568. THE NATURE OF THIS FAILURE IS SUCH T	HAT IT COULD LEAD TO SEPARATION OF THE ENGINE AND SUBSEQUENT LOSS OF CONTROL OF THE AIRCRAFT.  A SEARCH OF THE SDR DATAB	ASE REVEALED THAT SEVERAL OTHER SIMILAR FAILURES ON ENGINE MOUNTS HAVE OCCURRED.  IN FACT, THE OPERATOR OF THIS AIRCRAFT	 EXPERIENCED THE SAME FAILURE ON ANOTHER PIPER ARROW JUST WEEKS EARLIER. THE TWO AIRCRAFT ARE ONLY SEVERAL SERIAL NUMBER	S APART.  SUBMITTER RECOMMENDS THAT THESE ENGINE MOUNTS BE CLOSELY INSPECTED EVERY 100 HRS AS STIPULATED IN PIPER SM.(X)	1	L	7	1 	3O			 	2A13    					 
2001011104470	20010111	04470		2001	1	11	20001109SH004    	1	20001017	G	7922	639305	VERNATHERM      								CONT  	O520  	TSIO520CE   	17040	SO  					OIL TEMP VALVE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		335  					268574R			THE VERNATHERM SHAFT WAS BENT AND UPON INVESTIGATION, FOUND BROKEN AT THE ROLL PIN HOLE.  ONLY A COUPLE THREADS OF THE S	HAFT INTO THE RETAINING NUT WAS HOLDING THE UNIT TOGETHER.  ENGINE REBUILT ON 10-17-97.  (X)										3	O			E8CE				 
2001011104471	20010111	04471		2001	1	11	20001109SH005    	1	20001006	G	7920	F07K311	OIL FILTER      																	FILTER BASE	CRACKED         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21										DURING AN INCOMING MATERIAL INSPECTION, A REPAIR STATION NOTED WHAT APPEARED TO BE A MANUFACTURING INDUCED CRACK ON THE 	INSIDE PORTION OF THE FILTER BASE RING WHICH RETAINS THE RUBBER GASKET.  THIS CRACK IS APPROXIMATELY .0625 INCH IN LENGT	H AND APPEARED TO HAVE BEEN FORMED WHEN THE RING WAS CRIMPED TO THE BASE.  THE REPAIR STATION CHECKED THEIR STOCK OF FIL	TERS AND FOUND NO FURTHER INSTANCES OF THIS CONDITION.  (X)																 
2000111600179	20001116	00179	CE  	2000	11	16	20001109SH006    	1	20001101	G	3240	5100106159	LINE            			CESSNA	421   	421C        	2076016	CE  										UNDER RT CREW ST	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	748CA					421C0905				RIGHT BRAKE INOPERATIVE.  BRAKES WERE SERVICED AND BLED, THEN MECHANIC FOUND HYDRAULIC FLUID LEAKING FROM BOTTOM OF AIRC	RAFT.  ON FURTHER INSPECTION, LINE PN 5100106-159 WAS FOUND TO HAVE PIN HOLES IN IT.  SUBMITTER RECOMMENDED:  INSPECT TH	IS LINE IN MORE DETAIL DURING 100-HOUR INSPECTION.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000111600180	20001116	00180	CE  	2000	11	16	20001109SH007    	1	20001026	G	5510	16962000165	STABILATOR      			BEECH 	23    	B24R        	1151253	CE  										AFT	CRACKED         	A			BIKA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	1991L	2000 				MC431				DURING INSPECTIONS OF UNDERSIDES OF STABILATORS ON BEECH SIERRAS, SUNDOWNERS, HAVE FOUND DEFECTS RANGING FROM WORKING RI	VETS TO CRACKS IN LOWER SKINS.  PROBLEM IS CENTERED APPROX 6 INCHES OUT FROM FUSELAGE ON BOTH SIDES.  MECHANICS HAVE INS	TALLED OVERSIZED RIVETS, ADDITIONAL RIVETS, PATCHES.  BEECH ADDRESSES THIS PROBLEM IN SI 1167, OFFERS A P/N FOR IMPROVED	 AFT CENTER SPAR CALLING FOR NEW SPAR TO BE BONDED TO SKINS.  REPLACED AFT CENTER SPARS, AFT LOWER SKINS ON 2 SIERRAS, I	N ONE, SPARS CRACKED WEAKENED BY 0.250 INCH CHERRY MAX RIVETS AND TRIPPLING OF RIVETS.  ORIG SPAR DOES NOT OFFER ENOUGH 	SUPPORT TO CONTROL OIL CANNING EVEN THOUGH EXISTING SPAR MAY NOT BE CRACKED, WORKING, OR OVERSIZED.  (X)	1	L	7	1 	3O			 	A1CE    					 
2000111600181	20001116	00181	CE  	2000	11	16	20001109SH008    	1	20001026	G	5510	16962000165	STABILATOR      			BEECH 	23    	C24R        	1151254	CE  										AFT	CRACKED         	A			BIKA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	6710D	2000 				MC709				DURING INSPECTIONS OF UNDERSIDES OF STABILATORS ON BEECH SIERRAS, SUNDOWNERS, HAVE FOUND DEFECTS RANGING FROM WORKING RI	VETS TO CRACKS IN LOWER SKINS.  PROBLEM IS CENTERED APPROX 6 INCHES OUT FROM FUSELAGE ON BOTH SIDES.  MECHANICS HAVE INS	TALLED OVERSIZED RIVETS, ADDITIONAL RIVETS, PATCHES.  BEECH ADDRESSES THIS PROBLEM IN SI 1167, OFFERS A P/N FOR IMPROVED	 AFT CENTER SPAR CALLING FOR NEW SPAR TO BE BONDED TO SKINS.  REPLACED AFT CENTER SPARS, AFT LOWER SKINS ON 2 SIERRAS, I	N ONE, SPARS CRACKED WEAKENED BY 0.250 INCH CHERRY MAX RIVETS AND TRIPPLING OF RIVETS.  ORIG SPAR DOES NOT OFFER ENOUGH 	SUPPORT TO CONTROL OIL CANNING EVEN THOUGH EXISTING SPAR MAY NOT BE CRACKED, WORKING, OR OVERSIZED.  (X)	1	L	7	1 	3O			 	A1CE    					 
2000111600183	20001116	00183	GL  	2000	11	16	20001109SH010    	3	20000904	G	6110	C4451	FERRULE         	MCAULY      		CESSNA	206   	U206F       	2073333	CE  						MCAULY	3A32C	D3A32C90    	GL  	BLADE	CRACKED         	B			MFNY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	OONRJ		318  		CA318YS	3579		860281		PROPELLER SENT FOR REPAIR OF OIL LEAK.  AFTER INVESTIGATION OF THE PROPELLER AND DISASSEMBLY, FOUND THE OIL LEAK OCCURRE	D BECAUSE ONE BLADE FERRULE HAD BEEN CRACKED IN THE BEARING AREA.  (X)					1	H	7	1 	3O			 	A4CE    		5	C	P21EA	 
2000111600184	20001116	00184	CE  	2000	11	16	20001109SH011    	1	20001030	G	5712	57222082	RIB             			CESSNA	441   	441         	2076020	CE  										LT WING	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	185GA	4375 				4410066				DURING A PHASE INSPECTION, FOUND A 1.1 INCH CRACK IN LEFT WING CANTED RIB.  CRACK STARTING AFT OF THE FORWARD SPAR AND E	XTENDED AFT ALONG THE RIB RADIUS.  SUBMITTER STATED CESSNA NO LONGER WILL ALLOW STOP DRILLING OF THIS CRACK, SO THE RIB 	WAS REPLACED.  (X)				1	L	7	2 	3T			RT	A28CE   					 
2000111600185	20001116	00185	CE  	2000	11	16	20001109SH012    	1	20001020	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	185GA	4375 				4410066				DURING A PHASE INSPECTION, FOUND A .9 INCH CRACK IN RIGHT WING CANTED RIB TOP CAP.  CRACK STARTS AFT OF FORWARD SPAR AND	 EXTENDS AFT.  FOR MANY YEARS, CESSNA HAS ALLOWED THESE CRACKS TO BE STOP DRILLED, BUT NO LONGER WILL ACCEPT THIS REPAIR	.  NO PARTS ARE AVAILABLE TO REPLACE THIS RIB.  STOP DRILLED CRACK IAW 8110-3 DATED 10-19-00 WHICH WILL ALLOW 100 HOURS 	BEFORE PERMANENT REPAIR.  (X)			1	L	7	2 	3T			RT	A28CE   					 
2000111600186	20001116	00186	SO  	2000	11	16	20001109SH013    	2	20001006	G	8530		HOSE            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  						MISINSTALLED    	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	99	11955					15075733	251631			INTAKE BOOT SLID OFF INTAKE TUBE, MOST LIKELY CAUSED BY IMPROPER POSITIONING OF WORM GEAR HOSE CLAMP.  THIS CAUSED EXCES	SIVE LEAN MIXTURE.  THE RESULT WAS PISTON FAILURE, WRIST PIN FAILURE, AND CYLINDER FAILURE.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000111600187	20001116	00187	EA  	2000	11	16	20001109SH014    	2	20001030	G	8530	SL3600WA20P	CYLINDER        			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  					NR 2	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	13472					17702425	L2112736A			THE PUSH ROD TUBE RETAINER CLIPS, SL 14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS.  DET	ECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER.  SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT.  (X	)				1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2000111600188	20001116	00188	EA  	2000	11	16	20001109SH015    	2	20001030	G	8530	SL3600WR20P	CYLINDER        			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  					NR 3	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	13472	283  				17702425	L2112736A			THE PUSH ROD TUBE RETAINER CLIPS, PN SL14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS.  D	ETECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER.  SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT.  	(X)				1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2000111600189	20001116	00189	EA  	2000	11	16	20001109SH016    	2	20001030	G	8530	SL3600WA20P	CYLINDER        			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360A1F6    	41514	EA  					NR 4	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	13472	283  				17702425	L2112736A			THE PUSH ROD TUBE RETAINER CLIPS, PN SL14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS.  D	ETECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER.  SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT.  	(X)				1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2000111600190	20001116	00190	CE  	2000	11	16	20001109SH020    	1	20001019	G	5300		STRINGER        			CESSNA	500   	550         	2076604	CE  										AILERON BELLCK	CORRODED        	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	387SC	7566 				5500142				WHILE INVESTIGATING A PROBLEM OF FUEL IN THE CABIN, AN AREA OF SEVERE CORROSION WAS FOUND.  THE CORROSION WAS LOCATED IN	 A STRINGER UNDER THE AILERON BELLCRANK UNDER THE AFT CABIN FLOOR.  THE CORRODED STRINGER IS IN THE SAME LOCATION OF A S	IMILARLY CORRODED STRINGER FOUND ON AN S550 AIRCRAFT, 5500024.  SUBMITTER STATED IT SHOULD BE NOTED THE AREA IN QUESTION	 IS NOT EASILY SEEN.  (X)			1	L	7	2 	4F			 	A22CE   					 
2000111600191	20001116	00191	CE  	2000	11	16	20001109SH024    	1	20001020	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	445AE	8990 				4410043				DURING A PHASE INSPECTION, FOUND THE CRACK IN THE RIGHT CANTED RIB HAD PROGRESSED BEYOND THE PREVIOUSLY INSTALLED STOP D	RILLS.  AIRCRAFT WAS RETURNED TO THE OPERATOR WITH A ''FERRY PERMIT'' FOR REPAIR.  (X)					1	L	7	2 	3T			RT	A28CE   					 
2000111600192	20001116	00192	SW  	2000	11	16	20001109SH025    	1	20001017	G	7922	639305	VERNATHERM      			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					OIL TEMP VALVE	BENT            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	252DX	1088 				250580	279249R			RETAINING NUT ROLL PIN TO SECURE THE NUT.  THE SHAFT ON WHICH THE NUT IS INSTALLED WAS BENT JUST BEHIND THE NUT.  SUBMIT	TER HAS SEEN SEVERAL NOW WITH THIS CONDITION AND THEY ARE ALL FROM FACTORY REMAINS OR NEW ENGINES FROM RECENT YEARS.  TH	IS ONE REBUILT 2-8-95.  THE BEND IS IN THE DIRECTION OF THE ROLL PIN.  IT COULD BE CAUSED AT MANUFACTURE WHEN THE PIN IS	 INSTALLED.  IT APPEARED THE END OF THE BRASS SHAFT WAS MACHINED.  IT COULD OCCUR AT THAT TIME, IF SHAFT IS NOT SUPPORTE	D.  SUBMITTER HAS ADVISED TCM.  (X)		1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2000111600193	20001116	00193	CE  	2000	11	16	20001109SH026    	1	20001017	G	6100		NUT             			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	LOOSE           	B			W59R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	2181X					3370081		760428		THE REAR PROPELLER WAS SUBMITTED FOR REPAIR OF A LOOSE BLADE FOUND DURING AN ANNUAL INSPECTION.  UPON DISASSEMBLY, FOUND	 THE RED DYE OIL REQUIRED BY AD 91-15-04 HAD BEEN REMOVED AND THE PROPELLER WAS HAND PACKED WITH GREASE.  THE LOOSE BLAD	E CONTAINED A CRACKED BLADE RETENTION NUT, AND THE BLADE BEARING HAD FAILED ALLOWING THE STEEL ROLLERS END BEARING SPACE	R TO ROLL LOOSE IN THE HUB.  (X)			1	H	7	2 	3O			 	A6CE    		5	C	P5EA	 
2000111600194	20001116	00194	SO  	2000	11	16	20001109SH027    	1	20001014	G	8120	46C19836D	BEARING         			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540A1A   	41532	EA  						FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	289JG	641  				3257030	L992261A			THE TURBO WAS HUNG UP ON THE BEARINGS AND COULD NOT ROTATE UNTIL FORCE WAS APPLIED TO THE COMPRESSOR.  THEN THERE WAS DR	AGGING ON THE BEARINGS AND TURBINE AGAINST THE HOUSING.  THERE WAS A LOT OF END-PLAY IN THE TURBINE SHAFT.  (X)					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2000111600195	20001116	00195	EA  	2000	11	16	20001109SH028    	2	20001017	G	8520	11754	CAMSHAFT        			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ONE LOBE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	3327M		580  			28R7837112	L1839751A			AFTER FINDING FINE FERROUS METAL IN OIL FILTER , FURTHER INVESTIGATION LED TO THE FAILED CAMSHAFT AND TAPPETS.  BOTH TAP	PETS RIDE ON THE SAME LOBE.   SUBMITTER STATED THESE WERE RECONDITIONED PARTS.  (X)					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001011104473	20010111	04473		2001	1	11	20001109SH029    	2	20001017	G	8520	72877	LIFTER          			PIPER 	PA28  	PA28R201    	7102816	SO  										FACES	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	3327M		580  			28R7837112				AFTER FINDING FINE FERROUS METAL IN OIL FILTER , FURTHER INVESTIGATION LED TO THE FAILED CAMSHAFT AND TAPPETS.  BOTH TAP	PETS RIDE ON THE SAME LOBE.   SUBMITTER STATED THESE WERE RECONDITIONED PARTS.  (X)					1	L	7	1 	3O			 	2A13    					 
2001022600061	20010226	00061	CE  	2001	2	26	20001109SH032    	1	20001012	G	7160	145720210	VALVE           			CESSNA	172   	R172G       	2072421	CE  	CONT  	O360  	IO360DB     	17025	SO  					INDUCT AIR BOX	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	7751L					R1720427				ON ENGINE TBO CHANGE BEFORE INSTALLING THE INDUCTION AIR BOX, DISCOVERED THAT ONE HALF OF THE FLASHBACK VALVE HAD BROKEN	 AND WAS BACK IN THE AIR BOX.  BOTH HALVES AND SPRING WERE REPLACED.  (X)					1	H	7	1 	3O	3	O	 	3A17    	E1CE				 
2001022700001	20010227	00001	NM  	2001	2	27	20001109SH033    	2	20001017	G	7321	254911842	FUEL CONTROL    			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					LT ENGINE	FLUCTUATES      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	81446		1521 			11327	P79653			DURING THE RUN AND ADJUSTMENT AFTER THE INSTALLATION OF THE FUEL CONTROL, WHEN THE POWER LEVER WAS ADVANCED ABOVE THE FL	IGHT IDLE GATE WITH THE CONDITION LEVER IN THE HIGH POSITION, THE ENGINE GOES TO FULL POWER WITHIN A .50 INCH ABOVE THE 	FLIGHT GATE.  WHEN THE MAX POWER SCREW WAS ADJUSTED OUT, THE POWER LEVER RESPONSE WAS STILL TOO QUICK AND ENGINE FAILED 	TO MAKE MORE THAN 650 SHP.  THIS ENGINE ALSO SURGED WHEN THE POWER LEVER WAS RETARDED TO GROUND IDLE.  (X)			1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2001022600062	20010226	00062	SO  	2001	2	26	20001109SH034    	1	20001002	G	8120	LW16858	WASTEGATE VALVE 			PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					TURBOCHARGER	MISSING         	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	09	81573					328024004	L837961A			PILOT REPORTED UNABLE TO DEVELOP NORMAL POWER AT ALTITUDE.  INSPECTION REVEALED 30 PERCENT - 40 PERCENT OF WASTEGATE BUT	TERFLY VALVE MISSING.  UNIT REMOVED, REPAIRED AND REINSTALLED.  ENGINE HAD APPROX 730 HOURS SINCE FACTORY OVERHAUL.  BUT	TERFLY WAS NORMAL AT THAT TIME.  AIRFRAME TT, APPROX 3,600 HOURS.  UNABLE TO DETERMINE IF WASTEGATE ASSY HAD BEEN REPAIR	ED OR REPLACED PREVIOUSLY.  NO DAMAGE WAS DONE TO TURBINE, SO POSSIBLY BUTTERFLY MUST HAVE DISINTEGRATED SLOWLY OVER A P	ERIOD OF TIME.  (X)		1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001022600063	20010226	00063	CE  	2001	2	26	20001109SH036    	1	20001009	G	3230	MS244615	BEARING         			CESSNA	414   	414         	2075908	CE  										N/G DRAG BRACE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	8HM					4140620				FOUND NOSE GEAR DRAG BRACE BEARINGS LOOSE.  NOTE:  MOST NEEDLE BEARINGS WERE MISSING.  DRAG BRACE P/N 5042020-3.  (X)						1	L	7	2 	3O			RT	A7CE    					 
2001022600064	20010226	00064	CE  	2001	2	26	20001109SH037    	1	20001010	G	3250	12430714	TUBE            			CESSNA	210   	210         	2073402	CE  										NLG	BROKEN          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	09	9660T	2342 				57460				THE TUBE WELDED ASSY WHICH STEERS NOSE GEAR, ARM BROKE THE WELD ON THE TUBE WHICH ALOWED THE NOSE WHEEL TO SWIVEL AND CO	LLAPSED THE NOSE WHEEL ON LANDING.  (X)					1	H	7	1 	3O			RT	3A21    					 
2001020900096	20010209	00096	CE  	2001	2	9	20001109SH038    	1	20001022	G	5330	26110002	SKIN            			CESSNA	208   	208B        	2073701	CE  										FUSELAGE	CORRODED        	A			HSYA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	904FE	6433 				208B0004				HNL - MAINTENANCE FOUND FUSELAGE SKIN PANEL, UPPER CENTER FORWARD, CORRODED.  PANEL CORRODED BEYOND LIMITS FOR 2024T3, .	032 INCH THICK.  REMOVED AND REPLACED PANEL ASSEMBLY IAW C208 SRM 53-10-10 AND SRM 51-40-00.  (X)					1	H	7	1 	3T			 	A37CE   					 
2001022600065	20010226	00065	CE  	2001	2	26	20001109SH039    	1	20001024	G	5513	115610010231	SKIN            			BEECH 	99    	99A         	1154003	CE  										LT STABILATOR	CRACKED         	B			TIMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	955AA	30472				U128				DURING ROUTINE INSPECTION, A CRACK WAS FOUND ON THE LEFT STABILATOR LOWER SKIN.  (X)						1	L	7	2 	3T			 	A14CE   					 
2001022600067	20010226	00067	EA  	2001	2	26	20001113SH002    	2	20000930	G	7322	CF30766	FLOAT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320B2B     	41508	EA  					CARBURETOR	MISALIGNED      	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	23	9372C	55   			75065519	287816467				COMPLETE ENGINE FAILURE WITH FORCED LANDING.  DISCOVERED CARBURETOR FLOODING ENGINE.  UPON DISASSEMBLY OF CARBURETOR WIT	H FAA REP, FOUND FLOAT HANGING UP SIDE OF BOWL.  FLOAT APPEARS TO BE MISALIGNED DURING ASSSEMBLY AND SOLDERING OF FLOAT.	  (X)				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001021400038	20010214	00038	WP  	2001	2	14	20001113SH006    	1	20001027	G	6220	5143711	HUB             			HILLER	UH12  	UH12E       	4360122	WP  										MAIN ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		1451 								PRIOR TO THE INSTALLATION OF MAIN ROTOR HEAD ASSY, SN 493, AD 73-20-03 WAS ACCOMPLISHED.  THE MAIN ROTOR HUB, SN 493, WA	S FOUND CRACKED INSIDE THE HUB IN THE AREA OF THE CONTROL ROTOR STUDS.  METHOD OF INSPECTION WAS DYE PENETRANT.  THE ASS	Y RECORDS INDICATE THE ASSY HAD ZERO HOURS SINCE OVERHAUL.  (X)				1	G	7	1 	3O			 	4H11    					 
2001021400039	20010214	00039	GL  	2001	2	14	20001113SH007    	2	20001024	G	7310		B-NUT           			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL CONTROL	LOOSE           	G				A				UNSCHED LANDING         				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	NR	NOT REPORTED   	1			SW	03	58SN					52119				AIRCRAFT WAS LEVEL FLIGHT WHEN ENGINE DECELERATED AND QUIT.  PRELIMINARY INSPECTION FOUND PC LINE B-NUT AT FUEL CONTROL 	LOOSE.  LINE WAS REMOVED, INSPECTED, AND RE-INSTALLED.  ENGINE GROUND RUN.  (X)					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2001020200068	20010202	00068	SW  	2001	2	2	20001113SH008    	1	20001009	G	7910	206061505109	DRAIN LINE      			BELL  	206   	206L1       	1182107	SW  										ENGINE OIL TANK	CRACKED         	E			TUSA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	911SA	6964 				45383				OIL TANK DRAIN VALVE DISCOVERED WET DURING 100-HR INSP.  NO STATIC LEAKS NOTED AFTER CAREFUL INSP, ALTHOUGH A SMALL SEEP	 WAS FOUND DURING ACFT RUN-UP.  SMALL STRESS CRACKS FOUND WITH 10X MAGNIFYING GLASS WITHIN THE RADIUS BETWEEN DRAIN FITT	ING AND TANK BOTTOM SHEET METAL ADJACENT TO WELDED AREA.  SUBSEQUENT PRESS TEST ON THIS TANK SHOWED THE LEAK WOULD OCCUR	 WITH LESS THAN 3 POUNDS OF PRESSURE.  THESE STRESS CRACKS POSSIBLY WERE CAUSED BY 20 YEARS OF OIL CHANGES, AND THE CLOS	E PROXIMITY OF SCAVENGE OIL FILTER TO THE DRAIN VALVE.  SUBMITTER RECOMMENDED VERYIFYING OIL TANK DRAIN HOSE DOES NOT CO	ME IN CONTACT WITH SCAVENGE FILTER HOUSING, AND CARE USED DURING REMOVAL OF AIRFRAME MOUNTED SCAVENGE FILTER.  (X)	1	G	7	1 	3U			 	H2SW    					 
2001021400040	20010214	00040	GL  	2001	2	14	20001113SH010    	2	20000819	G	7210	6893672	PINION GEAR     	ALLSN       		BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					GEARBOX	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	591  			CAG47188	53054	CAE847188			DISASSEMBLED GEARBOX DUE TO METAL IN OIL.  CLEANED AND INSPECTED, FOUND EXCESSIVE GALLING ON PINION GEAR AND TORQUEMETER	 GEAR TEETH.  PINION GEAR HAD EXCESSIVE GALLING ON GEAR TEETH DUE TO IMPROPER MESHING OF T/M AND PINION GEARS.  SECONDAR	Y DAMAGE:  T/M GEAR PN 23071895, SN NN146407, TT 591.3 HOURS, SPALLING AND GALLING ON GEAR TEETH.  (X)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001021400041	20010214	00041	SW  	2001	2	14	20001113SH011    	1	20000830	G	7920	206061432121	HOUSING         	BELL        		BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	810  			A382	53107				DURING DAILY INSPECTION, FOUND HOUSING CRACKED AND RIVETS MISSING DUE TO HIGH VIBRATION, HOUSING SCRAPPED.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001020200069	20010202	00069	NE  	2001	2	2	20001113SH012    	1	20000831	G	6700	7640701106102	SUPPORT BRACKET 			SKRSKY	S76   	S76A        	8143006	NE  										PILOTS CYCLIC	BROKEN          	E			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	519AL					760058				DURING COMPLIANCE OF ASB 76-67-44, FOUND CYCLIC SUPPORT NOT TO BE THE CORRECT CONFIGURATION.  (X)						1	G	7	2 	3U			 	H1NE    					 
2001021400042	20010214	00042	NE  	2001	2	14	20001113SH013    	1	20000120	G	3233	SS49MC90J420R	RESTRICTOR VALVE	CLEVELANDPNU	1944        	SKRSKY	S76   	S76A        	8143006	NE  										NLG ACTUATOR	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	PTHOR	6607 			CPC0118ADER	760003				LANDING  GEAR ACTUATOR WOULD NOT LOCK IN DOWN POSITION.  ACTUATOR RESTRICTOR ASSEMBLY FILTER AND ORIFICE DISPLACED FROM 	RESTRICTOR AND FORCED INTO ACTUATOR TERMINAL.  THIS PREVENTED DOWNLOCK KEEPER FROM MOVING INTO LOCKED POSITION.  (X)					1	G	7	2 	3U			 	H1NE    					 
2000120400195	20001204	00195	CE  	2000	12	4	20001114SH027    	1	20001114	G	5520	NAS464P4A23	BOLT            			BEECH 	200   	200BEECH    	1152920	CE  										RT ELEV HINGE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	8225 				BB832				RIGHT ELEVATOR CENTER HINGE BOLT WAS FOUND BROKEN DURING A ROUTINE AIRCRAFT INSPECTION.  IT LOOKED INTACT, BUT UPON A TO	RQUE CHECK, IT WAS FOUND THAT THE BOLT WAS BROKEN.  THERE IS NO HISTORY OF UNUSUAL STRESSES ON THIS PART.  (X)					1	L	7	2 	4T			 	A24CE   					 
2001021400043	20010214	00043	EU  	2001	2	14	20001117SH003    	1	20001117	G	6500	593404	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R DRIVE	SEIZED          	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		NR	NOT REPORTED   	1			WP	01	6095U	941  				2699				SMOKE IN COCKPIT, TAIL VIBRATION.  REF:  OPERATOR CONTROL NR 010270.  (X)						1	G	7	1 	3U			 	H9EU    					 
2000120700199	20001207	00199	EA  	2000	12	7	20001117SH004    	2	20001017	G	7414	103571651	COIL            			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  						OPEN            	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	917GT		93   		G270012ER	500113777	L1456548			PILOT REPORTED LEFT MAGNETO, LEFT ENGINE, INOPERATIVE.  ON PREFLIGHT MAGNETO CHECK,  REVEALED COIL WIRE BROKEN AT SPADED	 CONNECTOR TO MAIN CONTACTS.  FACTORY OVERHAULED MAGNETO.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000120700200	20001207	00200	CE  	2000	12	7	20001120SH001    	1	20001119	G	8011	PM240131B22207	STARTER         			CESSNA	172   	172S        	2072439	CE  										POWERPLANT	OPEN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	916CP	226  				172S8336				STARTER FAILED, FAULT TRACED POWER THROUGH CONTACTOR, POWER AT STARTER LUG,  NO CURRENT DRAW.  NO REASON FOR FAULT COULD	 BE DETERMINED AS DISASSEMBLY WAS NOT AVAILABLE.  NO RECOMMENDATIONS AVAILABLE TO PREVENT RECURRENCE.  (X)					1	H	7	1 	3O			NT	3A12    					 
2000120700201	20001207	00201	SO  	2000	12	7	20001120SH003    	2	20001015	G	8530	652956	VALVE           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					CYLINDER ASSY	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	967CC	253  				21064534	294133R			CYLINDER NR 4 REMOVED FOR LOW COMPRESSION DUE TO LEAKAGE PAST THE EXHAUST VALVE.  THE REPAIR STATION THAT REPAIRED THE C	YLINDER ASSY REPLACED THE INTAKE AND EXHAUST VALVES, EXHAUST VALVE GUIDE, AND ASSOCIATED PARTS.  THE INTAKE VALVE''S FAC	E WAS CUPPED, EXHAUST VALVE WAS STRETCHED, AND THE EXHAUST VALVE GUIDE WAS WORN PAST SERVICEABLE LIMITS.  (X)				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000120700202	20001207	00202	SO  	2000	12	7	20001120SH004    	2	20000920	G	8530	646283	VALVE           			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					CYLINDER ASSY	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	967CC	404  				21064534	294133R			CYLINDER NR 2 REMOVED FOR LOW COMPRESSION DUE TO LEAKAGE PAST THE INTAKE VALVE.  THE REPAIR STATION THAT REPAIRED THE CY	LINDER ASSEMBLY REPLACED THE INTAKE AND EXHAUST VALVES, EXHAUST GUIDE, AND ASSOCIATED PARTS.  THE INTAKE VALVE''S FACE W	AS CUPPED, EXHAUST VALVE WAS STRETCHED .0045 INCH, AND THE EXHAUST VALVE GUIDE WAS WORN OVERSIZED.  (X).				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000120700203	20001207	00203	CE  	2000	12	7	20001120SH005    	1	20000913	G	2750	50000084	CONTROL CABLE   			CESSNA	402   	402B        	207590P	CE  										FLAP SYSTEM	BROKEN          	C				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			SW	11	5040Q	10   				402B0347				CPS/LIT - WHILE ON FINAL, THE FLAP SYSTEM FAILED.  IT WAS DETERMINED THE UPPER FLAP EXTEND CABLE ON THE RIGHT SIDE HAD B	ROKEN APPROXIMATELY A FOOT OUTBOARD OF THE ACTUATOR CHAIN ATTACH POINT.  THE CABLE COULD HAVE BEEN INCORRECTLY ROUTED/RI	GGED AND/OR THE CABLE TENSION COULD HAVE BEEN INCORRECTLY SET.  THE CABLE WAS REPLACED ABOUT 10 HOURS PRIOR TO FAILURE. 	 (X)			1	L	7	2 	3O			 	A7CE    					 
2000120700204	20001207	00204	EA  	2000	12	7	20001120SH006    	2	20001025	G	7414	10349276G	CAPACITOR       	CONT        		GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					WIRE CONN END	BROKEN          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	15	524HW		245  		B010004ER	1533191	L2076548			PILOT COMPLAINT, SEVERE MAG DROP ON PRE-FLIGHT RUN UP.  REPLACED MAGNETO AND PROBLEM WAS FIXED.  INSPECTION OF OLD MAGNE	TO REVEALED BROKEN WIRE ON CAPACITORS AND POINTS BURNT.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001022600068	20010226	00068	NE  	2001	2	26	20001120SH007    	3	20001016	G	6111	6607132886	BLADE           													ROTOL	R389	R3894123F26 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21		25625	24951					DRG202388		PROPELLER RECEIVED FOR REPAIR OF SLINGING GREASE AND LIGHT BLADE DAMAGE.  BLADE, SN 784, WAS FOUND TO HAVE A CRACK RUNNI	NG FROM PTFE FACE TO BLADE BEARING FACE ON OUTER SLEEVE AT ROOT END.  BLADE REJECTED FROM SERVICE.  (X)															6	C	P30NE	 
2001022600069	20010226	00069	NE  	2001	2	26	20001120SH008    	3	20001016	G	6111	6607132896	BLADE           													ROTOL	R389	R3894123F26 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		20288	7428 					DRG728486		PROPELLER RECEIVED FOR ROUTINE OVERHAUL.  AT DISASSEMBLY FOR OVERHAUL, NOTED BLADE, SN SC340-132/2239 WAS CRACKED IN OUT	ER SLEEVE AT ROOT END.  BLADE REJECTED FROM FURTHER SERVICE.  (X)															6	C	P30NE	 
2001022600071	20010226	00071		2001	2	26	20001120SH011    	4	20001024	G	6122	210100	SHAFT           	WOODWARD    		BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  					PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	102GA				1445291S	TE771				RELEVANT MAGNETIC PARTICLE INDICATION ON GEAR TOE.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001022600073	20010226	00073	SW  	2001	2	26	20001120SH022    	1	20001106	G	2913		POWERPACK       	POINTER     		GULSTM	112   	112         	0144701	SW  										HYDRAULIC SYSTEM	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	1169J					169				LANDING GEAR HYDRAULIC POWER PACK BUILDS UP 16 PSI.  (AFTER GEAR EXTENSION) IN THE ''UP'' SIDE OF HYDRAULIC CIRCUIT CONT	RARY TO COMMANDER 112 SM.  POWER PACK VENDOR STATES THE OVERHAUL IS IAW COMMANDER SPECS AND COMMANDER STATES PROBLEM IS 	WITH POWER PACK VENDOR.  SUBMITTER STATED, NO RESOLUTION.  (X)				1	L	7	1 	3O			 	A12SO   					 
2001011101198	20010111	01198	CE  	2001	1	11	20001120SH023    	1	20000607	G	3230	101810000651	DRAG BRACE      			BEECH 	200   	A200        	1152921	CE  										MLG	MISOVERHAULED   	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	21	1547					BC50				MAIN GEAR ASSEMBLY RECEIVED IN OVERHAULED CONDITION.  DURING INSTALLATION PROCESS, NOTED AND VERIFIED THE DRAG LINK ATTA	CHMENT LUG SLEEVE WAS APPROXIMATELY .010 INCH OVERSIZE FROM SPECS CALLED OUT IN THE RAYTHEON BEECHCRAFT COMPONENT MM.  R	EF:  FAA FORM 8130-3.  (X)				1	L	7	2 	4T			 	A24CE   					 
2001021400044	20010214	00044	EU  	2001	2	14	20001120SH025    	1	20001106	G	3246	1090500163	WHEEL           			AGUSTA	A109  	A109        	0260109	EU  										LT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	168BH	4367 				7256				THE LEFT MAIN TIRE WAS LOW, AS THE MECHANIC WAS GOING TO SERVICE THE TIRE, NOTED A CRACK PROPAGATING FROM A BOLT HOLE OU	TWARD.  (X)					1	G	7	2 	3U			 	H7EU    					 
2001022600074	20010226	00074	SW  	2001	2	26	20001120SH026    	1	20000925	G	3710		PUMP            			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					VACUUM SYSTEM	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	231MY					250152	309262			THIS AIRCRAFT HAD A 211 CC VACUUM PUMP FROM 7/93 UNTIL 5/99.  WHEN THE PART FAILED, IT WAS REPLACED WITH A 215 CC, SN 5A	R2833.  THIS LASTED 4 MONTHS (19 HOURS) AND WAS REPLACED WITH A 215 CC, SN 11AP4226.  THIS LASTED 6 MONTHS (57 HOURS) AN	D WAS REPLACED IN 5/00 WITH A 215 CC, SN S-2AT1103.  THIS FAILED IN 8/00 AFTER 3 MONTHS, AND 64 HOURS AND WAS REPLACED W	ITH 215 CC, SN 4AR2358.  THIS LASTED ONE MONTH AND 22 HOURS AND FAILED 9/19/00.  SUBMITTER THINKS THERE IS A PROBLEM WIT	H THIS PUMP TYPE.  (X)		1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2001022600075	20010226	00075	CE  	2001	2	26	20001120SH027    	1	20001106	G	7112	35910067635	BAFFLE          			BEECH 	36    	B36TC       	1151609	CE  										ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	376RH	202  				EA612				BAFFLE ABOVE OIL COOLER CRACKED OUT FROM PRESS FILTER HOLE.  (X)						1	L	7	1 	3O			 	3A15    					 
2001022600076	20010226	00076	CE  	2001	2	26	20001120SH028    	1	20001110	G	8120	643816	BRACKET         			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					TURBOCHARGER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	376RH	202  				EA612	527393			TURBO CONTROLLER SUPPORT BRACKET BROKEN AT CASE ATTACHMENT POINT.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2001022600077	20010226	00077	SO  	2001	2	26	20001120SH029    	1	20001103	G	3211	452575	BEARING         			PIPER 	PA44  	PA44180T    	7104404	SO  										STRUT HOUSING	WRONG PART      	B			DPOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	227ST	2000 				448107042				DURING COMPLIANCE WITH AD 94-13-11 AMDT 79-8952, STRUT HOUSING CHANGE.  BEARING HAD NARROW GROOVE AND NO HOLE FOR GREASE	 TO ENTER THE BEARING (MFG DEFECT).  (X)					1	L	7	2 	3O			 	A19SO   					 
2001020200081	20010202	00081	EU  	2001	2	2	20001120SH032    	1	20001102	G	6420	704A33640046	ADAPTER         			AEROSP	AS365 	AS365N2     	8680815	EU  										TAIL ROTOR	TORN            	E			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM	167  				6429				FREQUENCY ADAPTER, SN 18495, TORN.  REMOVED AND REPLACED MATCHED PAIR FREQUENCY ADAPTERS.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001020200082	20010202	00082	EU  	2001	2	2	20001120SH033    	1	20001102	G	6420	704A33640046	ADAPTER         			AEROSP	AS365 	AS365N2     	8680815	EU  										TAIL ROTOR	TORN            	E			ZYWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	365WM	167  				6429				FREQUENCY ADAPTER, SN 18495, TORN.  REMOVED AND REPLACED MATCHED PAIR FREQUENCY ADAPTERS.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001021300013	20010213	00013	EU  	2001	2	13	20001120SH034    	1	20001026	G	2911	08233901102	ACCUMULATOR     			AEROSP	AS365 	AS365N2     	8680815	EU  										HYD SYSTEM	FAILED          	E			ZYWA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	365WM	7198 				6429				ACCUMULATOR FAILED TO HOLD CHARGE, SLOWLY DROPPED PRESSURE.  REMOVED AND REPLACED ACCUMULATOR.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001020200083	20010202	00083	EU  	2001	2	2	20001120SH035    	1	20001018	G	2844	81071370010	TRANSMITTER     			AEROSP	AS365 	AS365N2     	8680815	EU  										FUEL PRESSURE	FLUCTUATES      	E			ZYWA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	365WM	1815 				6429				PRESSURE TRANSMITTER IS FLUCTUATING.  (X)						1	G	7	2 	3U			RT	H10EU   					 
2001022600078	20010226	00078	SO  	2001	2	26	20001120SH036    	1	20001031	G	2140	A23D04	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	4112K					318353006				FUEL REGULATOR ON JANITROL HEATING SYSTEM (FORWARD) LEAKED AT CASE PARTING SURFACES.  (X)						1	L	7	2 	3O			 	A20SO   					 
2001022600079	20010226	00079	SO  	2001	2	26	20001120SH037    	1	20000911	G	8011	MHB23995	ARMATURE        	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					STARTER	DEFECTIVE       	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4147K				8031187	2843169	L3623336A			THE ARMATURE DRIVE SPLINE WAS FOUND ALMOST COMPLETELY STRIPPED AWAY LEAVING SHARDS OF STEEL IN THE GEAR HOUSING THAT CON	TAMINATED THE BEARINGS.  THE BENDIX DRIVE END WAS UNDAMAGED AND THE SHEAR PIN DID NOT SHEAR.   THE ARMATURE DRIVE END MA	Y NOT BE PROPERLY HEAT TREATED OR SHEAR PIN MAY BE TOO HARD.  SUBMITTER STATED THIS IS THE SEVENTH ARMATURE FOUND IN THI	S CONDITION.  (X)			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001020200084	20010202	00084	SO  	2001	2	2	20001120SH038    	1	20001115	G	2140	A23D0475	VALVE           	JANITROL    		PIPER 	PA31  	PA31350     	7103110	SO  										FUEL REGULATOR	LEAKING         	A			FFSA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4501B	164  			5954723	318052168				FUEL WAS OBSERVED LEAKING FROM DRAIN TUBE.  INVESTIGATION REVEALED VALVE TO BE LEAKING FROM DIAPHRAGM PARTING SURFACE.  	VALVE BODY SCREWS WERE FOUND TO HAVE LOOSENED OVER TIME.  SUBMITTER SUGGESTED SELECTION OF ALTERNATE LOCKING DEVICE TO P	REVENT RECURRENCE.  (X)				1	L	7	2 	3O			 	A20SO   					 
2001022600080	20010226	00080	CE  	2001	2	26	20001120SH039    	1	20001105	G	5220	52111302	ESCAPE HATCH    			CESSNA	402   	402B        	207590P	CE  										FUSELAGE	DEPARTED        	B				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			EA	13	4537Q	10771				402B0343				ESCAPE HATCH DEPARTED AIRCRAFT AT 2,200 FEET, SIX MILES WEST OF LANCASTER AIRPORT.  NO DAMAGE WAS FOUND ON THE AIRCRAFT.	  INSPECTION OF THE FRAME, OF THE ESCAPE HATCH OPENING, FOUND NOTHING BROKEN IN THE RETAINING SYSTEM.  IT APPEARED THE R	ETAINING PINS VIBRATED OUT ENOUGH TO ALLOW THE HATCH TO BE PULLED OUT BY THE WIND.  (X)				1	L	7	2 	3O			 	A7CE    					 
2001030100034	20010301	00034	CE  	2001	3	1	20001120SH040    	1	20000717	G	8010	643259A	DRIVE SHAFT     			CESSNA	185   	A185F       	2072821	CE  										ENGINE	DEFECTIVE       	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	6JV	989  				18502397				STARTER DRIVE STARTED MAKING NOISE WHEN CRANKING ENGINE.  WHEN STARTER WAS REMOVED, LOWER FLANGE OF STARTER DRIVE WAS FO	UND TO BE BROKEN.  WHEN ''STARTER DRIVE'' SHAFT WAS TURNED AFTER REMOVAL FROM ENGINE, IT WAS VERY NOISY LIKE A VERY BAD 	BEARING OR SOMETHING.  THE ABOVE IS NOT PART OF THE STARTER.  (X)				1	H	7	1 	3O			 	3A24    					 
2001021400046	20010214	00046	EU  	2001	2	14	20001120SH051    	1	20001104	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350BA     	8680817	EU  										ENGINE	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	1188P	906  				2347				STARTER/GENERATOR INOPERABLE.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021400047	20010214	00047	EU  	2001	2	14	20001120SH052    	1	20001030	G	7712	305731366	INDICATOR       			SNIAS 	350   	AS350BA     	8680817	EU  										TORQUE	ERRATIC         	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	180EH					2337				TORQUE INDICATOR ERRATIC.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021400048	20010214	00048	EU  	2001	2	14	20001120SH053    	1	20001105	G	7714	0177555170	TACHOMETER      			SNIAS 	350   	AS350BA     	8680817	EU  										ENGINE	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	270SH					1864				TACHOMETER BOX INOPERABLE.  BLEED VALVE WILL NOT CLOSE.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021500001	20010215	00001	EU  	2001	2	15	20001120SH055    	1	20001023	G	7332	704A37643000	INDICATOR       			SNIAS 	350   	AS350BA     	8680817	EU  										FUEL PRESSURE	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	37SH					2300				FUEL PRESSURE INDICATOR IS INOPERATIVE.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021500002	20010215	00002	SW  	2001	2	15	20001120SH056    	1	20001025	G	7722	12444412	GAUGE           			BELL  	206   	206B        	1181511	SW  										TOT	FLUCTUATES      	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	667JM					3444				TOT GAUGE FLUCTUATES IN-FLIGHT.  SPIKES FROM 0 - 800 THEN NORMAL OPS.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001021500003	20010215	00003		2001	2	15	20001120SH057    	4	20001025	G	3422	206075606103	GYRO            			BELL  	206   	206B        	1181511	SW  										COCKPIT	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	73DP					2513				DIRECTIONAL GYRO INOPERABLE.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001022600081	20010226	00081	EA  	2001	2	26	20001120SH058    	2	20000802	G	8530	60828	PLUG            			AMRGEN	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320E2G     	41508	EA  					CYLINDER NR 2	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	6084L	800  				AA50184	L3216327A			PISTON PIN PLUG IN CYLINDER NR 2 FAILED CATASTROPHICALLY ENLARGING PISTON BOSS AND WEARING INTO LOWER RING.  ENGINE WAS 	800 SMOH, CYLINDERS .010 INCH OS (PLAIN STEEL).  SCREEN LAST CHECKED 48 HOURS PREVIOUSLY.  PRESSURE SCREEN BECAME PLUGGE	D WITH ALUMINUM FLAKES, OIL PRESSURE DROPPED AND PILOT NOTICED CHANGE.  ALL OTHER CYLINDERS REMOVED.  TWO OTHER PLUGS WO	RN BEYOND LIMITS.  REPLACED ALL PISTON PIN PLUGS WITH LYC PN 72198.  (X)			1	L	7	1 	3O	3	O	 	A16EA   	E274				 
2001022600082	20010226	00082	SW  	2001	2	26	20001120SH059    	1	20001101	G	5414		SKIN            			GULSTM	690TP 	690A        	0141722	SW  										LT/RT NACELLE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	62366	4042 				11141				DURING 100-HOUR INSPECTION, AIRCRAFT NACELLE AREA FOUND THE UPPER ENGINE MOUNT ATTACH STRUCTURE STEEL STRAPS HEAVILY COR	RODED.  UPON REMOVAL OF THE UPPER NACELLES ON THE LEFT AND RIGHT SIDES OF THE AIRCRAFT, FOUND HEAVY PITTING AND WIDE SPR	EAD CORROSION OVER THE TOP SURFACE OF THE WING AS WELL AS CORROSION AND PITTING EXTENDING UNDER THE STEEL STRAPS.  (X)				1	H	7	2 	3T			 	2A4     					 
2001022700002	20010227	00002	SO  	2001	2	27	20001120SH060    	1	20001027	G	3230	AN643	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										NOSE GEAR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	6855Y					273891				FOUND UPPER BOLT (AN6-43) IN NOSE GEAR DRAG LINK BROKEN WHERE DRAG LINK ATTACHES TO AIRFRAME STRUCTURE.  AIRCRAFT HAD 8,	600 HOURS TOTAL TIME.  TOTAL TIME IN SERVICE OF BOLT UNKNOWN.  AIRCRAFT OPERATED FROM TURF AND PAVED RUNWAYS.  (X)					1	L	7	2 	3O			 	1A10    					 
2001022700003	20010227	00003	EA  	2001	2	27	20001120SH062    	2	20001025	G	8530		ROCKER BOSS     			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  					CYLINDER	OUT OF POSITION 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	83296					187609068	L4503827A			CYLINDER HAD LOW COMPRESSION.  WHEN ROCKER BOSS COVER WAS REMOVED, THE EXHAUST SIDE OF ROCKER SHAFT BOSS WAS FOUND IN BO	TTOM OF COMPARTMENT.  CHROME CYLINDER WAS OVERHAULED 226 HOURS PRIOR.  (X)					1	H	7	1 	3O	3	O	 	1A2     	E274				 
2001022700004	20010227	00004	EA  	2001	2	27	20001120SH063    	2	20000922	G	8550		PLUG            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE SUMP	MISSING         	D				O				OTHER                   				E	M	Y	VIBRATION/BUFFET          	OVER TEMP                 	ENGINE STOPPAGE           	IN	INSP/MAINT     	1			SW	15	82149	3953 	557  			17267692	L132076			AIRCRAFT WAS FLYING FROM TULSA TO SILOAM SPRINGS, 8 MILES FROM SILOAM SPRINGS AIRPORT, PILOT REPORTED THE ENGINE OIL PRE	SSURE WAS FLUCTUATING FROM ZERO TO 60 PSI.  THE ENGINE THEN STARTED TO VIBRATE SEVERELY BEFORE THE ENGINE COMPLETELY STO	PPED.  UPON INSPECTION OF THE AIRCRAFT, FOUND THE OIL QUICK DRAIN WAS MISSING WHICH OBVIOUSLY CAUSED THE ENGINE TO LOSE 	OIL PRESSURE.  THE QUICK DRAIN INSTALLED DID NOT HAVE A PROVISION FOR SAFETY WIRE. (X)			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001030100035	20010301	00035	SO  	2001	3	1	20001121SH001    	1	20001108	G	3110	770052	DISPLAY         			PIPER 	PA32  	PA32301T    	7103209	SO  										INSTRUMENT PANEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	9288X	223  				3257027				CODE ONE FAILURE MODE; SECOND TIME IN THIS AIRCRAFT.  SUBMITTER STATED FAX''''S TO PIPER, THEIR TECH REPS SAY THAT IT HA	S THE ONLY AMPS AND VOLT READINGS ON THIS INSTRUMENT, SO IT IS REQUIRED.   (X)					1	L	7	1 	3O			 	A3SO    					 
2001030100036	20010301	00036	SO  	2001	3	1	20001121SH002    	1	20001108	G	3110	770052	DISPLAY         			PIPER 	PA32  	PA32301T    	7103209	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					INSTRUMENT PANEL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	9288X	128  				3257027	L990861A			CODE ONE FAILURE MODE; THIRD TIME IN THIS AIRCRAFT.  SUBMITTER STATED FAX''S TO PIPER, THEIR TECH REPS SAY THAT IT HAS T	HE ONLY AMPS AND VOLT READINGS ON THIS INSTRUMENT, SO IT IS REQUIRED.  (X)					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001022700007	20010227	00007	CE  	2001	2	27	20001121SH004    	1	20001017	G	5412	05530313	FIREWALL        			CESSNA	172   	172S        	2072439	CE  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	74GW	559  				172S8143				FIREWALL HAD CRACK APPROXIMATELY .75 INCH STARTING AT LOWER LEFT COWL MOUNT TOWARDS BATTERY BOX MOUNT.  CESSNA SB 98-53-	02.  PERTAINS TO THIS SITUATION, BUT IS ONLY ON 172R MODEL.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001022700008	20010227	00008	CE  	2001	2	27	20001121SH005    	1	20001017	G	3340	1212010791	CONNECTOR       			CESSNA	182   	182S        	2072701	CE  										TAILCONE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	23735	407  				18280458				AT 100-HOUR INSPECTION, REMOVED TAILCONE AND FOUND IT FILLED WITH APPROXIMATELY 1.50 INCHES OF WATER.  WATER HAD CORRODE	D CONNECTOR FOR TAIL NAVIGATION LIGHT.  CONNECTOR WAS REPLACED AND LOWER ATTACH SCREW FOR TAILCONE WAS NOT RE-INSTALLED 	TO ALLOW FOR FUTURE WATER DRAIN.  TAILCONE HAD SUFFICIENT SCREWS (14) TO RETAIN IT SAFELY WITH LOWER SCREW OMITTED.  (X)				1	H	7	1 	3O			NT	3A13    					 
2001021500004	20010215	00004		2001	2	15	20001127SH001    	4	20001110	G	3422	5050010902	GYRO            			SNIAS 	350   	AS350B1     	8680811	EU  										COCKPIT	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	53SH					2009				DIRECTIONAL GYRO INOPERATIVE.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500005	20010215	00005		2001	2	15	20001127SH004    	4	20001109	G	3422	103002201	GYRO            			SNIAS 	350   	AS350BA     	8680817	EU  										COCKPIT	OUT OF TOLERANCE	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	350SH					2957				DIRECTIONAL GYRO, FLAG OUT OF CALIBRATION, POSSIBLY DUE TO ROTOR BEARINGS STARTING TO FAIL.  SENT FOR OVERHAUL.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021500006	20010215	00006	NE  	2001	2	15	20001127SH006    	2	20000614	G	7250	410106701	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					TURBINE  SHROUD	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	420MB	423  				7077	LE45218EA			FIRST TURBINE SHROUD, SEAL RING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021500007	20010215	00007	NE  	2001	2	15	20001127SH007    	2	20000614	G	7250	410106802	SPRING          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					SEAL RING EXPAND	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	420MB	523  				7077	LE45218EA			SEAL RING EXPANDER - SPRING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001030200027	20010302	00027		2001	3	2	20001127SH008    	4	20001109	G	2561	KS9P0101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07	A									LIFE VEST FAILED MFGS TWO PSI INFLATION TESTS IAW 25-60-1.  LIFE VEST DATE OF MFG, JUNE 1980.  FAIR WEAR AND TEAR.  (X)																			 
2001022700010	20010227	00010	CE  	2001	2	27	20001127SH010    	1	20000811	G	5341	0512122	FITTING         			CESSNA	172   	172M        	2072418	CE  										WING ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	137FS	57980				17266030				CRACK FOUND DURING AN ANNUAL INSPECTION.  (X)						1	H	7	1 	3O			NT	3A12    					 
2001022700011	20010227	00011	SO  	2001	2	27	20001127SH011    	1	20001108	G	7430	IO3572001	IGNITION SWITCH 			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					COCKPIT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2234Z	1200 				287911160				AD 76-07-12 DOES NOT APPLY TO THIS IGNITION SWITCH BY MANUFACTURE CODE DATE (8408), HOWEVER, SWITCH FAILED THE ''OFF CHE	CK'' SPECIFIED IN THE AD.  INSTALLATION OF CONTACT KIT P/N 10-357510, WAS REQUIRED.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E295				 
2001022700012	20010227	00012	CE  	2001	2	27	20001127SH012    	1	20001027	G	3221	16981001127	HOUSING         			BEECH 	23    	C23         	1151242	CE  										NLG	BROKEN          	G				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			EA	07	450BA	500  				M2342				NOSE GEAR ASSEMBLY FELL OFF THE AIRCRAFT ON TAKEOFF.  FOUND THE HOUSING HAD CRACKED OUT WHERE THE STEERING ASSY ATTACHES	.  THIS AREA SHOWED SIGNS OF BEING CRACKED FOR SOME TIME.  (X)					1	L	7	1 	3O			 	A1CE    					 
2001011101201	20010111	01201	CE  	2001	1	11	20001127SH013    	1	20001101	G	5520	50610000546	BRACKET         			BEECH 	90    	C90         	1152913	CE  										ELEVATOR	DAMAGED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	6732V	1745 				LJ0899				WHILE RE-INSTALLING THE RIGHT ELEVATOR, THE MECHANIC NOTICED THE BOLT THAT HOLDS THE ELEVATOR OUTBOARD BRACKET TO THE HO	RIZONTAL BEARING BRACKET PN 50-620001-69 WAS SLOPPY.  AFTER REMOVING BOLT, FOUND IT SEVERELY WORN AND BRACKET 50-61000-5	46 HAD SEVERELY ELONGATED HOLES WHERE THE BOLT PASSES THROUGH IT.  SUBMITTER STATED PREVIOUS BOLT WAS INSTALLED WITH THI	N WASHERS AND THE NUT WAS SHANKED OUT LEAVING THE BOLT LOOSE TO RATTLE IN THE BRACKET.  INSTALLED NEW BRACKET AND PROPER	 SIZE WASHERS ON NEW BOLT.  (X)		1	L	7	2 	3T			 	3A20    					 
2001022700013	20010227	00013	SO  	2001	2	27	20001127SH015    	1	20001127	G	5341		RIVET           			PIPER 	PA24  	PA24250     	7102404	SO  										WING ATTACH	SHEARED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	7456P					242646				DURING ANNUAL INSPECTION, FOUND SHEARED RIVETS AT BOTH REAR WING ATTACH FITTINGS AS FOLLOWS:  BS 136 RT SIDE, ALL RIVETS	 SHEARED THRU PLATE PN 23662-00, FITTING ASSY P/N 23663-00, DOUBLER P/N 23664-02.  EXTENSIVE MOVEMENT BETWEEN PLATE AND 	FITTING ASSY CAUSED ANGLE P/N 20554-16 TO SHEAR IN TWO.  LT SIDE MUCH THE SAME EXCEPT 2 RIVETS REMAINING, ANGLE HAS NOT 	COMPLETELY SHEARED THROUGH.  AIRFRAME TT 6,342 HRS.  (X)			1	L	7	1 	3O			 	1A15    					 
2001022700014	20010227	00014	SO  	2001	2	27	20001127SH017    	1	20001110	G	3030	587954	SWITCH          			PIPER 	PA34  	PA34200T    	7103406	SO  										INSTRUMENT PANEL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	8514C					347670147				PILOT REPORTED AIRCRAFTS PITOT HEAT SYSTEM TO BE INOPERATIVE.  INSPECTION REVEALED THE SWITCH ASSY TO HAVE CORROSION IN 	THE CONTACTS.  THE CORROSION APPEARED TO BE CAUSED BY MOISTURE SUCH AS RAIN WATER. (X)					1	L	7	2 	3O			 	A7SO    					 
2001022700015	20010227	00015	EA  	2001	2	27	20001127SH018    	2	20001014	G	8500		ENGINE          			PIPER 	PA24  	PA24260     	7102406	SO  	LYC   	O540  	O540E4A5    	41532	EA  					ENGINE	FAILED          	H				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	17	9005P	2035 	35   			244466	L2414040A			ENGINE FAILED CATASTROPHICALLY IN-FLIGHT AND SUBSEQUENTLY AIRCRAFT LANDED GEAR UP NEXT TO CANAL.  INITIAL INSPECTION IND	ICATED ROD BEARING OR ROD CAP FAILURES.  MANUFACTURER''S INSPECTION RESULTS ARE PENDING.  (X)					1	L	7	1 	3O	3	O	 	1A15    	E295				 
2001030100038	20010301	00038	CE  	2001	3	1	20001128SH001    	1	20001102	G	5510	1694400173	HINGE           			BEECH 	23    	A24R        	1151252	CE  										HORIZONTAL STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8022R					MC14				THE PAINT WAS CRACKED AROUND THE HINGE PLATE ON THE RT SIDE.  A  FINGERNAIL WOULD GO UNDER A COUPLE OF THE RIVETS.  WHEN	 THE RIVETS WERE DRILLED OUT, SEVERAL SPUN AND BROKE BEFORE THE BIT WENT THROUGH.  THE BACK SIDE OF THE HINGE PLATES WAS	 RUSTED AND BLACK GALLING APPEARED ON THE ALUMINUM UNDERNEATH INDICATING MOVEMENT.  SUBMITTER STATED THIS IS A 25-HOUR A	D INSPECTION THAT IS DIFFICULT TO ASSESS UNTIL REMOVED.  (X)			1	L	7	1 	3O			 	A1CE    					 
2001011101202	20010111	01202	SO  	2001	1	11	20001129SH001    	1	20001128	G	2822	LW5473	PUMP            			PIPER 	PA32  	PA32300     	7103212	SO  										ENGINE FUEL	FAILED          	E			FPXA	C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			SO	25	2835W	1522 				327940148	L1330348A			DURING TAKEOFF, THE ENGINE MOMENTARILY LOST POWER WHEN FUEL BOOST PUMP WAS SHUT OFF. FUEL FLOW REDUCED BY 8 GPH. AFTER A	 COUPLE OF SECONDS, THE FUEL FLOW RETURNED TO NORMAL AND THE ENGINE RECOVERED POWER. THE AIRCRAFT LANDED WITHOUT INCIDEN	T. GROUND TESTING REVEALED THE ENGINE DRIVEN PUMP WAS SUPPLYING PROPER PRESSURE DURING ALL OPERATIONS EXCEPT FOR FULL PO	WER AFTER ELECTRIC PUMP SHUT DOWN.  INTERUPTION OF FUEL FLOW WAS ONLY MOMENTARY AND DID NOT OCCUR AT LOWER POWER SETTING	S.  ENGINE DRIVEN PUMP WAS REPLACED AND ENGINE OPERATES NORMALLY.  (X)		1	L	7	1 	3O			 	A3SO    					 
2001030200029	20010302	00029	NE  	2001	3	2	20001129SH003    	2	20001030	G	7200	P2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FOR FLUORESCENT PENETRANT INSPECTION IAW IAE V2500 PROPULSION SYSTEM ENGINE MANUAL, REV 44, SECTION 70-23-	01, INSPECTION CHECK-01, TASK 70-23-01-230-501.  PART REJECTED AT FPI DUE TO TWO CRACKS ON OUTSIDE DIAMETER OF PART (ARE	AS MARKED ON PART).  (X)									4	F			E311NE				 
2001011101229	20010111	01229		2001	1	11	20001129SH007    	4	20001102	G	6122	B4169	IDLER GEAR      	HARTZL      							LYC   	O360  	LO360A1G6   	41514	EA  					GOVERNOR	DAMAGED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					1384S					RELEVANT MAGNETIC PARTICLE INDICATION AROUND GEAR TEETH AREA.  (X)											3	O			1E10				 
2001020900101	20010209	00101	EU  	2001	2	9	20001129SH008    	1	20001108	G	3246	AHA1236	WHEEL           			STBROS	SD3   	SD360       	8100606	EU  										LT MLG	FAILED          	E			DATA	K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	13	151CA		272  			SH3653				UPON LANDING IN MLI, THE LEFT MAIN WHEEL BLEW OUT.  THE MLI MECHANIC REMOVED AND REPLACED THE LT MAIN WHEEL ASSY.  THERE	 WAS NO DAMAGE TO THE BRAKE AND STRUT.  OPS CHECKED GOOD.  (X)					2	H	7	2 	4T			 	A41EU   					 
2001022700021	20010227	00021	SO  	2001	2	27	20001129SH014    	2	20001115	G	7314	634053	PUMP            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	DAMAGED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	222MB					TC654	297985R			ALT BRACKET CONTACTING FUEL INLET FITTING DUE TO FITTING ''CLOCKING'' AND BRACKET LOCATION.  FACTORY ZERO TIMED ENGINE. 	 BOTH COMPONENTS FACTORY INSTALLED CAUSED LOSS OF FUEL IN-FLIGHT.  ENGINE PUMP REPLACED WITH CONTINENTAL SUPPLIED O/H UN	IT AND FOUND NEW PUMP FITTING TO CONTACTING ARM AS WELL.  MODIFY ALT BRACKET PER CONTINENTAL REPS REQUEST.  ALSO, FOUND 	FITTING MILL SHAVINGS IN FITTING BLOCKING FLOW ON NEW PUMP.  (X)			1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2001022700022	20010227	00022	SO  	2001	2	27	20001129SH016    	1	20001017	G	2730	400053AN36	BOLT            			PIPER 	PA31T 	PA31T       	7103124	SO  										ELEVATOR CABLE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	47SF					31T8020031				UPPER AND LOWER BOLTS THAT ATTACH BOTH THE MAIN ELEVATOR CABLES AND AUTOPILOT BRIDLE CABLES.  (X)						1	L	7	2 	3T			 	A8EA    					 
2001022700023	20010227	00023		2001	2	27	20001129SH017    	4	20001017	G	2200	400056AN311	BOLT            			PIPER 	PA31T 	PA31T       	7103124	SO  										AUTO PILOT CABLE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	47JF					31T8020031				UPPER AND LOWER BOLTS THAT ATTACH BOTH THE MAIN ELEVATOR CABLES AND AUTOPILOT BRIDLE CABLES.  (X)						1	L	7	2 	3T			 	A8EA    					 
2001022700024	20010227	00024	SO  	2001	2	27	20001129SH018    	1	20001114	G	3213	2075212	STRUT           			PIPER 	PA24  	PA24260     	7102406	SO  										LT MLG	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	4960	6763 				244025				INSPECTION OF LEFT MAIN LANDING GEAR FOUND STRUT JAMMED.  HOUSING CRACKED AND LEAKING FLUID.  AIRCRAFT TT, 6,763.2 HOURS	.  (X)					1	L	7	1 	3O			 	1A15    					 
2001022700025	20010227	00025	SO  	2001	2	27	20001129SH019    	1	20001013	G	7820		MUFFLER         			MAULE 	M7    	M7235B      	5460109	SO  										LEFT EXHAUST	CRACKED         	B			UM9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	4279L	151  				23058C				DURING ANNUAL INSPECTION, NOTED THE LEFT MUFFLER WAS CRACKED AT THE END PLATE WHERE IT HAD BEEN WELDED DURING ASSY.  THE	 CRACKS RAN PARALLEL TO WELDS AND SHOWED EVIDENCE OF EXHAUST LEAKAGE.  (X)					1	H	7	1 	3O			NC	3A23    					 
2001022700026	20010227	00026	SO  	2001	2	27	20001129SH020    	1	20001013	G	7810		TAILPIPE        			MAULE 	M7    	M7235B      	5460109	SO  										LT EXHAUST	CRACKED         	B			UM9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	4279L	151  				23058C				DURING ANNUAL INSPECTION, NOTED THE LEFT TAILPIPE CRACKED AT THE MOUNTING SUPPORT TAB APPROXIMATELY 95 PERCENT OF PIPE D	IAMETER.  CRACK HAD ORIGINATED FROM WELD ON TAB.  PART FAILED ON REMOVAL.  (X)					1	H	7	1 	3O			NC	3A23    					 
2001030200030	20010302	00030	CE  	2001	3	2	20001129SH022    	1	20000927	G	3150		LIGHT           			CESSNA	206   	206H        	2073301	CE  										INSTRUMENT PANEL	INOPERATIVE     	B			IC1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	23	7266Y	188  			1808	20608059				OIL PRESSURE LIGHT IN ANNUNCIATOR PANEL IS OUT.  SUBMITTER SUSPECTED BAD BULB.  REMOVED AND REPLACED ANNUNCIATOR PANEL I	AW CESSNA MM.  OPERATIONAL TEST GOOD.  (X)					1	H	7	1 	3O			RT	A4CE    					 
2001030200031	20010302	00031	CE  	2001	3	2	20001129SH023    	1	20000915	G	7933	S23351	TERMINAL        			CESSNA	206   	206H        	2073301	CE  										OIL TEMP BULB	BROKEN          	B			IC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	7266Y	188  				20608059				OIL TEMPERATURE BULB CENTER WIRE TERMINAL POST SPINS IN HOUSING.  SUBMITTER SUSPECTED FAULTY UNIT.  REPLACED WITH SERVIC	EABLE UNIT FROM CESSNA, GROUND RAN ENGINE.  OPERATION AND LEAK CHECKS GOOD.  (X)					1	H	7	1 	3O			RT	A4CE    					 
2001030200032	20010302	00032	EA  	2001	3	2	20001129SH024    	2	20001031	G	7414	10349276REVG	WIRE            			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					CAPACITOR	BROKEN          	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	99	780SP		315  		BF210007ER	1362133	L853948			PRE-FLIGHT RUNUP SHOWED SEVERE MAGNETO DROP.  POST-REPLACEMENT INSPECTION SHOWED BURNED CONTACTS AND CAPACITOR WIRE BROK	EN.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001011101230	20010111	01230		2001	1	11	20001129SH027    	4	20000928	G	8300	67542	BEARING         			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					ACCESSORY SECT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	904VL	8806 	1012 			3014	L1807440A			DURING ROUTINE INSPECTION, REMOVED OIL FILTER AND FOUND EXCESSIVE PARTICLES ON OIL SCREEN.  REMOVED ENGINE FOR SENDING T	O OVERHAUL.  PRELIMINARY VIEW FOUND LEFT MAGNETO CASE BEARING DISINTEGRATED AND CASE GEAR WEAR.  (X)					1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2001030200033	20010302	00033	SW  	2001	3	2	20001129SH028    	1	20001103	G	2432	413S34LN2	CIRCUIT BREAKER 			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					INSTRUMENT PANEL	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	9140X					243245	L2568451A			WHILE INSTALLING NEW J. P. INSTRUMENT, REMOVAL OF CIRCUIT BREAKER PANEL REVEALED THE BATTERY BREAKER LINE LEAD WAS CONTA	CTING THE INSTRUMENT PANEL SUPPORT STRUCTURE AND HAD BURNED A PENCIL SIZED HOLE IN STRUCTURE.  IT APPEARED THIS WAS FACT	ORY INSTALLED.  RELIEVED PANEL STRUCTURE AND INSTALLED SMALLER DIMENSION BREAKER, AND PLASTIC SHIELD.  (X)				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001030200034	20010302	00034	SO  	2001	3	2	20001130SH001    	2	20001013	G	7414	6310	MAGNETO         			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE	FAILED          	B			UM9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	9912N	5    				18052567				MAGNETO FAILED TO OPERATE.  AFTER 4.5 HOURS OF OPERATION.  DISASSEMBLY REVEALED THAT DISTRIBUTOR BLOCK TAB NEXT TO COIL 	HAD BURNED AND MELTED CAUSING MAGNETO TO BECOME INOPERATIVE.  DEFECT WAS REPORTED TO SLICK TECHNICAL SERVICES DEPARTMENT	.  SUBMITTER SUSPECTED COIL WAS CRACKED OR LEAKING AND CAUSED THIS FAILURE.  (X)				1	H	7	1 	3O	3	O	 	5A6     	E273				 
2001030200035	20010302	00035	SW  	2001	3	2	20001130SH003    	1	20001109	G	5347		SEAT TRACK      			GULSTM	690TP 	690B        	7630516	SW  										PILOT SEAT	CORRODED        	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9LV	6088 				11550				PILOT INBOARD SEAT RAIL LOCATED AT THE FLOOR ATTACHMENT HAD EVIDENCE OF CORROSION AT THE AFT ATTACHMENT SCREWS.  (X)						1	H	7	2 	3T			 	2A4     					 
2001030200036	20010302	00036	CE  	2001	3	2	20001130SH004    	1	20001101	G	3240	AN313A	BOLT            			CESSNA	172   	172S        	2072439	CE  										PARK BRAKE	BACKED OUT      	D				K				NONE                    				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			NM	03	949SP	823  				172S8145				DURING PHASE 2 INSPECTION, PARKING BRAKE CROSSOVER CABLE, BELLCRANK BOLT WAS BACKED OUT AND RESTRICTING PILOT''S R-RUDDE	R PEDAL, FWD TRAVEL.  WITH THE BOLT BACKED OUT OF THE BELLCRANK, PARKING BRAKE INOP.  THE FIBERLOCK NUT WAS FOUND DOWN U	NDER THE RUDDER PEDALS AND THE BOLT WAS BENT SLIGHTLY.  NO PREVIOUS WORK ACCOMPLISHED ON PARKING BRAKE OR RUDDER PEDALS.	  IT IS ASSUMED THE NUT WAS NOT TIGHTENED ON INSTALL.  THE ONLY WRITE-UP ON ACFT ENTERING PHASE INSPECT WAS  PARKING BRA	KE INOP.  SUBMITTER RECOMMENDED THE AN3-13A BOLT SECURING THE PARKING BRAKE CROSSOVER CABLE BELLCRANK PN 0713070-9 BE IN	STALLED FROM RT TO LT INSTEAD OF PRESENT INSTALL LT TO RT.  (X)	1	H	7	1 	3O			NT	3A12    					 
2001011101231	20010111	01231	SO  	2001	1	11	20001204SH001    	1	20001018	G	7160	3808016	ALT AIR DOOR    			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	BROKEN          	E			FPXA	C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SO	25	2891U	8056 	57   			327940184				IMMEDIATELY AFTER THROTTLE UP FOR TAKEOFF, ENGINE LOST SIGNIFICANT POWER.  PILOT TRIED TO RETARD THROTTLE TO ABORT, BUT 	LEVER WOULD ONLY GO ABOUT HALF WAY BACK.  HE THEN SLIGHTLY ADVANCED THROTTLE AND THEN WAS ABLE TO PULL THROTTLE ALL THE 	WAY BACK TO IDLE POSITION.  THE ENGINE DEVELOPED SUFFICIANT POWER TO TAXI BACK TO THE RAMP, BUT WAS RUNNING VERY ROUGH. 	 INSPECTION OF THE INDUCTION SYSTEM REVEALED THAT BOTH ALTERNATE AIR DOOR DISCS HAD BROKEN AND LARGE PIECES INGESTED INT	O THE ENGINE.  ONE HAD LODGED IN THE FUEL SERVO RESTRICTING THE MOVEMENT OF THE AIR VALVE.  SEVERAL PIECES MADE IT INTO 	THE CYLINDERS AND MELTED OVER THE BOTTOM SPARK PLUGS.  THE DEBRIS WAS REMOVED, THE INDUCTION SYSTEM CLEANED.	1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2000121800227	20001218	00227	EA  	2000	12	18	20001204SH010    	2	20001115	G	7310		LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 6 CYLINDER	BROKEN          	E				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	19	600EE					317952158	L464861A			THE NR 1 ENGINE QUIT EN ROUTE.  THE PILOT ATTEMPTED TO RESTART THE DEAD ENGINE WITH NO SUCCESS.  A FORCED LANDING WAS SU	CCESSFULLY MADE.  THE LEFT ENGINE WAS LATER REMOVED FROM THE AIRCRAFT AND INSTALLED ON A TEST STAND.  THE NR 6 CYLINDER 	MANIFOLD TO NOZZLE, TUBE ASSY WAS FOUND BROKEN.  A SERVICEABLE TUBE ASSY WAS INSTALLED FOR A TEST RUN.  THE ENGINE START	ED AND RAN WITH NO APPARENT PROBLEM.  THE BROKEN FUEL LINE WAS APPARENTLY THE REASON THE ENGINE QUIT, AND WHY THE PILOT 	COULD NOT GET IT RE-STARTED.  AS 93-02-05 WAS C/W 23.7 HOURS PRIOR TO THE ENGINE FAILURE.  (X)		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000121800228	20001218	00228	SO  	2000	12	18	20001204SH011    	1	20001128	G	2140	A23D0475	REGULATOR VALVE 			PIPER 	PA31  	PA31350     	7103110	SO  										FWD HEATER	LEAKING         	H				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	4501B	17   				318052168				FUEL OBSERVED DRIPPING FROM DRAIN LINE AFTER GROUND RUN OF ENGINE WITHOUT HEATER BEING USED.  VALVE WAS REMOVED FROM AIR	CRAFT AND 30 PSI SHOP AIR WAS APPLIED TO INLET WITHOUT POWER TO OPEN VALVE.  LEAK CHECK FLUID WAS APPLIED TO VALVE BODY 	AND LEAK WAS FOUND TO BE COMING FROM UNUSED MOUNTING HOLE ON VALVE BODY.  (X)				1	L	7	2 	3O			 	A20SO   					 
2000121800229	20001218	00229	SO  	2000	12	18	20001204SH012    	1	20001128	G	2140	AD23D0475	REGULATOR VALVE 			PIPER 	PA31  	PA31350     	7103110	SO  										FWD HEATER	LEAKING         	H				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	4501B					318052168				INSTALLED NEW FUEL REGULATOR SHUT-OFF VALVE.  AFTER SEVERAL MINUTES OF OPERATION, VALVE BEGAN LEAKING AT BODY HALF.  REM	OVAL AND INSPECTION REVEALED ALL FOUR SCREWS THAT HOLD BODY VALVE TOGETHER TO BE LOOSE WITH TORQUE SEAL IN PLACE.  TIGHT	ENED SCREWS AND RETESTED.  VALVE STILL LEAKED.  REPLACED VALVE WITH NEW UNIT.  SUBMITTER SUSPECTED IMPROPER TORQUE USED 	AS ASSEMBLY.  (X)			1	L	7	2 	3O			 	A20SO   					 
2000121800230	20001218	00230	SO  	2000	12	18	20001204SH013    	1	20001018	G	7810	2109217	STACK           			PIPER 	PA24  	PA24        	7102402	SO  	LYC   	O360  	O360A1D     	41514	EA  					INSIDE HEAT MUFF	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	7644P					242858	L494536			THE PIPER COMANCHE BROKE THE RT REAR EXHAUST STACK INSIDE THE CARBURETOR HEAT MUFF.  THE PIPE BROKE INSIDE THE CUFF THAT	 IS WELDED TO THE STACK FOR THE MUFF TO ATTACH TO CAUSING THE STACK TO DROP AND ERODE ITS WAY THROUGH THE MUFF.  THE HEA	T BEING DIRECTED INSIDE THE ENGINE COWLING CAUSED THE INSULATION ON THE MAG P-LEAD WIRES TO MELT AND GROUND TO THE METAL	 HOUSING OF THE TACH CABLE THEY WERE SECURED TO, GROUNDING OUT THE MAGS AND SHUTTING DOWN THE ENGINE.  AN UNEVENTFUL OFF	 AIRPORT LANDING OCCURRED WITH NO OTHER DAMAGE.  (X)		1	L	7	1 	3O	3	O	 	1A15    	E286				 
2000121800231	20001218	00231	CE  	2000	12	18	20001204SH014    	1	20001115	G	2510	07140594	SEAT            	CESSNA      		CESSNA	182   	R182        	2072734	CE  										REAR POINT	BROKEN          	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	11130	6272 				R18201940				REAR ATTACH POINT ON LOWER SEAT WHERE IT ATTACHES TO THE PEDESTAL ASSEMBLY.  ONE SIDE BROKEN OFF THE OTHER SIDE IS CRACK	ED.  BROKE AT CUT-OUT FOR SEAT PIVOT BRACKET PN 0514060-5.  (X)					1	H	7	1 	3O			RT	3A13    					 
2000121800232	20001218	00232	CE  	2000	12	18	20001204SH015    	1	20001018	G	2140	26405	SEAL            			CESSNA	402   	402C        	207590R	CE  										RT SUB WING	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	2611X	295  				402C0072				AFTER DEPARTURE, CREW SMELLED FUEL AND RETURNED TO LAND, LANDING WITHOUT INCIDENT.  MAINTENANCE FOUND HEATER FUEL FILTER	S LEAKING.  REMOVED AND REPLACED GASKET.  OPS AND LEAK CHECKED OK. AIRCRAFT RELEASED FOR RETURN TO SERVICE.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000121800233	20001218	00233	CE  	2000	12	18	20001204SH016    	1	20001019	G	3230	51420025	DRAG BRACE      			CESSNA	402   	402C        	207590R	CE  										NOSE GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6837Y	932  				402C0467				UPON ROUTINE INSPECTION OF THE NOSE GEAR AREA, MAINTENANCE DETERMINED THE NOSE GEAR DRAG WAS CRACKED AT THE AREA JUST AF	T OF THE ACTUATOR ATTACH LUG.  MAINTENANCE REMOVED AND REPLACED THE DRAG BRACE AND RELEASED AIRCRAFT BACK TO SERVICE.  (	X)				1	L	7	2 	3O			 	A7CE    					 
2000121800234	20001218	00234	EA  	2000	12	18	20001204SH018    	2	20001120	G	7414	16171	CASE            	BENDIX      		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					THREADED HOLES	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	739GQ	3660 	500  		16171	17270535	L352776			ABOVE 2,100 RPM, ENGINE WOULD HAVE ROUGHNESS.  LEFT MAG WOULD CHECK GOOD, BUT RIGHT WOULD RUN ROUGH AND CAUSE AFTERFIRIN	G, SOMETIMES VERY LOUDLY.  BELOW 2,100 RPM, MAG CHECKS WERE NORMAL.  PROBLEM TRACED TO POOR CONTACT ASSY GROUND CAUSED B	Y CORROSION IN MAGNESIUM CASE THREADS WHERE DIST BLOCK RETAINING SCREWS (PN 10-35937-20) GROUND CONTACTORS.  THREADS WER	E BLACK IN COLOR, BUT RESTORED TO BRIGHT METAL BY RUNNING A TAP IN.  OHMMETER TESTS RESULTED IN 3 TO 10 OHMS RESISTANCE 	BEFORETHREADS WERE CLEANED.  (X)		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000121800235	20001218	00235	CE  	2000	12	18	20001204SH019    	1	20001114	G	5210	05170392	HANDLE          			CESSNA	185   	A185F       	2072821	CE  										CABIN INTERIOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	61301	100  				18504144				THE HANDLE SPLINE BUSHING STRIPED CAUSING HANDLE FAILURE.  (X)						1	H	7	1 	3O			 	3A24    					 
2000121900203	20001219	00203	CE  	2000	12	19	20001205SH009    	1	20001103	G	5210	52113492	PIN             			CESSNA	402   	402C        	207590R	CE  										LATCH UP CABN DR	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NE	01	548GA					402C0653				DURING FLIGHT, UPPER CABIN DOOR OPENED.  AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE FOUND FORWARD LATCH PIN BROKEN A	T BELLCRANK ATTACH POINT.  REPLACED LATCH PIN AND ASSIST SPRINGS AND RELEASED THE AIRCRAFT BACK TO SERVICE.  (X)					1	L	7	2 	3O			 	A7CE    					 
2000121900204	20001219	00204	EA  	2000	12	19	20001205SH010    	2	20001107	G	8530	60828	PLUG            			AMTR  	MSTG2 	MUSTANG2    	       	GL  	LYC   	O320  	O320E2D     	41508	EA  					NR 1 CYLINDER	ERODED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	54JL	1700 				1776	RL04219027A			NOTED LOW COMPRESSION.  REMOVED NR 1 CYLINDER, NOTED 1 EACH PISTON PIN PLUG MISSING.  OTHER PISTON PIN PLUGS WORN TO TAP	ERED SIZE.  PISTON PIN HOLE IN PISTON SEVERELY ELONGATED AND MELTED.  ALUMINUM NUGGETS FOUND INSIDE OF PISTON PIN.  OIL 	FILTER CONTAINED LARGE AMOUNTS OF METAL.  SUCTION SCREEN HAD METAL.  OTHER CYLINDER PISTON PIN PLUGS SHOWED SIMILAR WEAR	.  OPERATOR USING PHILLIPS 20/50 OIL AND 89 OCTANE AUTOGAS AND 100LL AVGAS.  (X)			1	L	7	1 	3O	3	O	 	EXPA1L71	E274				 
2000121900206	20001219	00206	CE  	2000	12	19	20001205SH012    	1	20001006	G	3245	40135	WHEEL           			CESSNA	414   	414A        	2075907	CE  										LT OTBD RIM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	414SF					414A0488				UPON AN ANNUAL INSPECTION, THE LEFT MAIN WHEEL WAS REMOVED AND CLEANED.  AFTER CLEANING, A 4 INCH CRACK WAS NOTICED NEXT	 TO RIM ON THE OUTBOARD WHEEL.  AIR WAS REMOVED AND WHEEL DISASSEMBLED.  THE CRACK WAS ALL THE WAY THROUGH.  ALSO, THE O	NE BRAKE PAD WAS MISSING.  NO OTHER DAMAGE FOUND.  SUBMITTER SUSPECTED HARDER THAN NORMAL LANDING.  (X)				1	L	7	2 	3O			 	A7CE    					 
2000121900207	20001219	00207	SO  	2000	12	19	20001205SH013    	1	20001110	G	3030	587954	PIVOT           			PIPER 	PA34  	PA34200T    	7103406	SO  										PILOTS CNTRL PNL	CORRODED        	E			GAYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	8514C					347670147				PILOT REPORTED THE AIRCRAFT''S PITOT HEAT SYSTEM TO BE INOPERATIVE.  INSPECTION REVEALED THE SWITCH ASSY TO HAVE CORROSI	ON IN THE CONTACTS.  THE CORROSION APPEARED TO BE CAUSED BY MOISTURE SUCH AS RAINWATER.  (X)					1	L	7	2 	3O			 	A7SO    					 
2001021500021	20010215	00021	EU  	2001	2	15	20001205SH027    	1	20001117	G	8012		VALVE           			SNIAS 	350   	AS350BA     	8680817	EU  										START DRAIN	LEAKING         	E			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	270SH					1864				START DRAIN VALVE LEAKING.  REPLACED.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021500022	20010215	00022	EU  	2001	2	15	20001205SH028    	1	20001115	G	8012	0174078010	VALVE           			SNIAS 	350   	AS350B      	8680801	EU  										START DRAIN	LEAKING         	E			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	37SH					2300				START DRAIN VALVE LEAKING.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500023	20010215	00023	EU  	2001	2	15	20001205SH029    	1	20001115	G	7722	56265220	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										ENGINE T-4	DAMAGED         	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	37SH					2300				T-4 GAUGE UNSERVICEABLE.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001011101256	20010111	01256	NE  	2001	1	11	20001206SH001    	1	20000926	G	6210	7615009100041A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL	10072	264  			760280				DISCOVERED DURING POST-FLIGHT INSPECTION (VIBRATION WAS FELT DURING FLIGHT).  EXTENSIVE UPPER SURFACE SKIN DISBOND.  (X)						1	G	7	2 	3U			 	H1NE    					 
2001011101257	20010111	01257	SW  	2001	1	11	20001206SH002    	1	20000724	G	7810	407062021101	DUCT            			BELL  	407   	407         	       	SW  										EXHAUST	CRACKED         	B			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	527AL					53211				DURING DAILY INSPECTION FOUND DUCT ASSY CRACKED IN CORNERS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001011101258	20010111	01258	SW  	2001	1	11	20001206SH003    	1	20000922	G	6310	406040516101	SHAFT           			BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	557AL	1389 			A4013	53243				DURING SEAL REPAIR, FOUND WORN SPLINES.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001011101259	20010111	01259	NE  	2001	1	11	20001206SH004    	1	20001013	G	3212	7625100702042	EXPLOSIVE LINK  			SKRSKY	S76   	S76A        	8143006	NE  										RT MLG DOOR	DISCHARGED      	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL					760280				AIRCRAFT FLOATS WERE INADVERTENTLY DISCHARGED.  MALFUNCTION WAS DISCOVERED DURING REMOVAL OF RT MAIN GEAR DOOR.  EXPLOSI	VE CHARGE DISCHARGED WHEN FLOATS TRIPPED, BUT LINK DID NOT SEPARATE.  (X)					1	G	7	2 	3U			 	H1NE    					 
2001011101260	20010111	01260	GL  	2001	1	11	20001206SH005    	2	20001113	G	7240	23062752	NOZZLE          	RROYCE      	C47         	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					1ST STAGE	BROKEN          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	487AL	1890 			CAT44414	53204				TURBINE RECEIVED IN SHOP TO PERFORM 2000 HOUR OVERHAUL.  UPON REMOVAL OF OUTER COMBUSTION CASE AND COMBUSTION LINER, FOU	ND A HOLE IN DOME OF 1ST STAGE SHIELD.  ALSO, FOUND THE BROKEN PIECE LODGED ON 1ST STAGE NOZZLE VANE.  POSSIBLE IMPROPER	 METAL USED TO MAKE DOME.  PART WAS SCRAPPED, UNABLE TO REPAIR.  (X)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001011101261	20010111	01261	SW  	2001	1	11	20001206SH006    	1	20001025	G	7921	407062021101	DUCT            			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					OIL COOLER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL					53107				DURING DAILY INSPECTION, FOUND OIL COOLER BLOWER CRACKED.  (X)						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001021500024	20010215	00024	SW  	2001	2	15	20001206SH007    	1	20000808	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	587AL	603  			AFS1204	53248				DURING DAILY INSPECTION, FOUND OCB HOUSING CRACKED DUE TO VIBRATION.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001021500025	20010215	00025	SW  	2001	2	15	20001206SH008    	1	20001029	G	6510	206340300105	DRIVE SHAFT     			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					TRANSMISSION	FAILED          	B			ALGR	A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	687AL	1806 				53366				IN-FLIGHT, PILOT HEARD A LOUD POP.  LANDED AT THE NEAREST PLATFORM AND AFTER SHUT DOWN, FOUND FORWARD FLEXURE ON INPUT D	RIVESHAFT HAD FAILED.  ONE OF THE FORWARD FLEXURES FAILED AT THE BOLT HOLE AND A PORTION OF THE FLEXURE WENT THROUGH THE	 TRANSMISSION DECK/CABIN ROOF.  (X)				1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001021500026	20010215	00026	EU  	2001	2	15	20001206SH009    	1	20001107	G	6510	350A34021006	DRIVE SHAFT     			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DAMAGED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	486  				3118				DURING 500-HOUR INSPECTION, FOUND INNER SLEEVE OF AFT MOST BEARING SLIPPING ON T/R DRIVESHAFT.  IT APPEARED TO HAVE BEEN	 SPINNING FOR SOME TIME AND RUBBER HAD ACTUALLY TRANSFERRED FROM SLEEVE TO SHAFT.  SHAFT ITSELF WAS NOT DAMAGED.  REPLAC	ED ENTIRE SHAFT ASSEMBLY DUE TO WARRANTY AND REPAIR DIFFICULTY.  (X)				1	G	7	1 	3U			 	H9EU    					 
2001021500027	20010215	00027	EU  	2001	2	15	20001206SH010    	1	20001107	G	6220	350A31185421	BOLT            			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	486  				3118				DURING 500-HOUR INSPECTION, FOUND CORROSION ON SLEEVE ATTACHING BOLTS.  NOTED MASTINOX WAS NOT USED AT THE TIME OF ASSEM	BLY.  REF:  S/NS 6327, 6329, 6339, 6343, 6370, AND 6380.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500028	20010215	00028	EU  	2001	2	15	20001206SH011    	1	20001107	G	6220	350A31185003	FLANGE          			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	486  				3118				DURING 500-HOUR INSPECTION, FOUND CORROSION ON UPPER SLEEVE FLANGE HOLES.  NOTED MASTINOX WAS NOT USED AT THE TIME OF AS	SEMBLY.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500029	20010215	00029	EU  	2001	2	15	20001206SH012    	1	20001107	G	6220	350A31185002	FLANGE          			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	486  				3118				DURING 500-HOUR INSPECTION, FOUND CORROSION ON LOWER SLEEVE FLANGE.  NOTED MASTINOX WAS NOT USED AT THE TIME OF ASSEMBLY	.  REF:  S/N M4413, M4415, M4417.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500030	20010215	00030	EU  	2001	2	15	20001206SH013    	1	20001107	G	6220	704A33640046	ADAPTER         			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	486  				3118				DURING 500-HOUR INSPECTION, FOUND CORROSION IN BOLT HOLES OF FREQUENCY ADAPTER.  NOTED MASTINOX WAS NOT USED AT THE TIME	 OF ASSEMBLY.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500031	20010215	00031	EU  	2001	2	15	20001206SH014    	1	20001107	G	6220	704A33633208	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5204J	486  				3118				DURING 500-HOUR INSPECTION, FOUND CORROSION ON THE SPHERICAL THRUST BEARING HOLES.  NOTED MASTINOX WAS NOT USED AT THE T	IME OF ASSEMBLY.  REF:  S/N''S LK3520, LK3544, LK3678.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500032	20010215	00032	SW  	2001	2	15	20001206SH018    	1	20001116	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVE	ROUGH           	E			R6LA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	1116H					53046				C/W THE INTENT OF AD 2000-02-12 BY INSPECTING OIL COOLER BLOWER DRIVESHAFT BEARINGS.  AFT BEARING FOUND ROUGH RUNNING.  	(X)					1	G	7	1 	3U			O	H2SW    					 
2001030200038	20010302	00038	CE  	2001	3	2	20001206SH019    	1	20001201	G	5523	9661000668	ATTACH FITTING  			BEECH 	55    	E55         	1152732	CE  										ELEV TRIM TAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1025T	3475 				TE950				STEEL HORN WITH BRAZED BUSHING CRACK ON HORN ONLY, NOT INTO BUSHING.  CAUSE UNKNOWN.  (X)						1	L	7	2 	3O			 	3A16    					 
2001030200039	20010302	00039	CE  	2001	3	2	20001206SH020    	1	20001118	G	3233	35380094	MOTOR           			BEECH 	35    	V35B        	1151548	CE  										MLG	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	15	1825L					D9877				DURING RETRACT TEST, LANDING GEAR MOTOR TRIPPED CIRCUIT BREAKER.  TROUBLESHOOTING REVEALED EMERGENCY DOWN CRANK IMPOSSIB	LE TO TURN.  REPLACEMENT OF MOTOR RESOLVED PROBLEM.  CONCERN THAT FAILED GEAR MOTOR COULD RENDER EMERGENCY CRANK INOPERA	TIVE RESULTING IN A WHEELS UP LANDING.  (X)				1	L	7	1 	3O			 	3A15    					 
2001030200040	20010302	00040	SO  	2001	3	2	20001206SH022    	2	20001114	G	8520	652832	CRANKSHAFT      			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	11NP	1570 				421C0093	272362R			CRANKSHAFT BROKEN AFT ON NR 2 ROD JOURNAL AT NR 2 MAIN BEARING.  ENGINE HAD 401.0 HOURS SINCE RE-MANUFACTURE.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001021500033	20010215	00033		2001	2	15	20001206SH024    	4	20001127	G	3416	D120P2T	ENCODER         			SNIAS 	350   	AS350BA     	8680817	EU  										ALTIMETER	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	180EH					2337				ENCODER IS BAD.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021500034	20010215	00034	SW  	2001	2	15	20001206SH025    	1	20000814	G	6220	222011114103	SUPPORT BRACKET 			BELL  	222   	222U        	1182140	SW  										M/R HEAD	FRACTURED       	E			STRA	A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			WP	27	222UT	3058 				47559				PILOT EXPERIENCED A MAIN ROTOR VIBRATION WHICH SUBSEQUENTLY BECAME SEVERE DURING CRUISE FLIGHT.  PILOT MADE A LANDING AT	 NEAREST AIRPORT, DURING SHUT DOWN OF ENGINES, VIBRATION WENT AWAY.  INVESTIGATION OF MAIN ROTOR SYS NOTED THE LOWER PEN	DULUM OF ONE OF THE BLADES WAS MISSING.  FURTHER INSP REVEALED A SLIGHT NICK TO THE T/E OF THE M/R BLADE.  UPON EXAMINAT	ION OF THE PENDULUM AFTER REMOVAL, SHOWED THE TANGS HAD FRACTURED AND THERE WERE SIGNS OF A PREVIOUS CRACK.  PART SENT T	O BHT FOR EVALUATION.  (X)		1	G	7	2 	3U			 	H9SW    					 
2000121500186	20001215	00186	EA  	2000	12	15	20001206SH026    	2	20001030	G	8520		CRANKSHAFT      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					PROP/BUSHING	FAILED          	B			QRQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	2269S	7    				17280955	L2911051A			THIS ACFT RECEIVED NEW FROM CESSNA FACTORY.  UPON REMOVAL OF PROPELLER TO FACILITATE INSTALL OF AFTERMARKET AIR CONDITIO	NERS, NOTED THAT 2 OF THE 4 PROPELLER ALIGNMENT BUSHINGS THAT ARE PRESSED INTO THE CRANKSHAFT FLANGE WERE EXTRUDED FROM 	THE BACKSIDE OF THE FLANGE APPROX .375 INCH.  THE APPARENT CAUSE OF THIS DEFECT WAS THE IMPROPER CLOCKING OF THE PROP TO	 THE CRANKSHAFT.   (X)			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001030200041	20010302	00041	CE  	2001	3	2	20001206SH027    	1	20001117	G	2810		SEALANT         			CESSNA	140   	140         	2071602	CE  										LT MAIN FUEL TNK	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	279W	7980 	556  			9976				LARGE PARTICLES OF SLOSHING TYPE FUEL TANK SEALANT WERE FOUND ON THE FUEL TANK FINGER SCREEN DURING A POST-ACCIDENT INSP	ECTION.  THE SUBJECT ACFT HAD AN AUTOFUEL STC WHICH MAY NOT HAVE BEEN COMPATIBLE WITH THE SEALANT WHICH WAS APPLIED IN 1	957.  (X)				1	H	7	1 	3O			NC	A768    					 
2001030200042	20010302	00042		2001	3	2	20001206SH028    	4	20001117	G	3416		WIRE            			CESSNA	320   	320D        	2074512	CE  										ALTIMETER	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	254KB					320D0103				A/F TOTAL TIME, 11,510.2 HOURS.  INTERMITTENT ERRONEOUS ALTITUDE MODE C INDICATION.  FOUND CHAFED WIRE FROM ENCODING ALT	IMETER TO TRANSPONDER.  REPAIRED WIRING AND SECURE.  (X)					1	L	7	2 	3O			 	3A25    					 
2001030200043	20010302	00043	EA  	2001	3	2	20001206SH029    	2	20001023	G	7322		CARBURETOR      			PIPER 	PA23  	PA23150     	7102303	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	ICED            	C				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			NM	01	3127P					231050				ENGINE FAILURE DUE TO CARBURETOR ICE.  FAILURE OCCURRED WITHIN 15 SECONDS OF SELECTING FUEL TRANSFER.  ASSUMPTION THAT P	ROBLEM WAS WITH FUEL TRANSFER DELAYED APPLICATION OF CARBURETOR HEAT.  (X)					1	L	7	2 	3O	3	O	RT	1A10    	E274				 
2001030200044	20010302	00044	CE  	2001	3	2	20001206SH030    	1	20001114	G	7930		LINE            			CESSNA	206   	TU206A      	2073318	CE  										INSTRUMENT PANEL	CORRODED        	B			IC1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	4801F	4258 				U2060501				LINE SHOWS SIGNS OF INTERGRANULAR CORROSION.  OIL LINE IN COCKPIT BEHIND INSTRUMENT PANEL SUPPLYING OIL PRESSURE GAUGE R	UPTURED CAUSING APPROXIMATELY 3 QUARTS OF OIL TO ENTER CABIN PRIOR TO AIRCRAFT LANDING.  REPLACED LINE ASSEMBLY, NO LEAK	S NOTED.  (X)				1	H	7	1 	3O			 	A4CE    					 
2001020900103	20010209	00103	SO  	2001	2	9	20001206SH031    	2	20001116	G	8520		CONNECTING ROD  			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 5 CYLINDER	FAILED          	E			P6VA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			EA	07	410AJ		1216 			421C1093	610473			AIRCRAFT WAS CLIMBING AFTER TAKEOFF, LOUD NOISE HEARD BY PILOT, OIL PRESSURE STARTED TO DROP, ENGINE FEATHERED.  AIRCRAF	T LANDED WITHOUT INCIDENT.  FOUND NR 5 CYLINDER CONNECTING ROD FAILED, KNOCKED HOLE  IN UPPER CRANKCASE.  ENGINE TOTAL T	IME 2,768.7 HOURS, 1,215.7 HOURS SMOH.  (X)				1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001020900104	20010209	00104	CE  	2001	2	9	20001206SH032    	1	20001120	G	8120	MILH60004	LINE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					LT ENGINE	LOOSE           	E			DYVA	O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			NM	07	4119M					421C1029	277163R			THE LEFT ENGINE TURBOCHARGER COMPRESSOR DISCHARGE REFERENCE LINE CAME OFF AT CRUISE POWER AT 15,500 FEET CAUSING THE ENG	INE TO DIE WITH AN EXCESSIVELY RICH MIXTURE.  THE PILOT DID NOT ATTEMPT LEANING DURING TROUBLESHOOTING AND FEATHERED THE	 ENGINE, LANDED SAFELY WITH NO FURTHER INCIDENT.  THE REFERENCE LINE WAS SECURED AND ENGINE OPERATION CHECKED NORMAL.  (	X)			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001011101264	20010111	01264	CE  	2001	1	11	20001207SH001    	1	20001205	G	5730	MS24694C51	SCREW           	CESSNA      		CESSNA	500   	550         	2076604	CE  										WING SKIN	IMPROPER PART   	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	1200N					5500681				UPON INSPECTION OF AREA UNDER HEATED LEADING EDGE (TOP FORWARD SCREW), IT WAS FOUND THAT THE SCREW HAD CONTACTED THE SKI	N SURFACE.  THE SCREW HAD PENETRATED PART OF A RIVET HEAD ON THE LEFT WING AND EXTENDED INTO THE SKIN APPROXIMATELY 0.03	2 INCH.  THE SCREW ON THE RIGHT WING HAD NOT CONTACTED A RIVET HEAD BUT HAD PENETRATED THE SKIN BY APPROXIMATELY 0.028 	INCH. THE CORRECT HARDWARE WAS USED PER THE AIRCRAFT MANUFACTURERS PARTS CATALOGUE.  REPAIR OR REPLACEMENT OF THE WING	 SKIN OVERLAYING THE FUEL CELL WILL BE REQUIRED TO RETURN THE AIRCRAFT TO SERVICE.  (X)		1	L	7	2 	4F			 	A22CE   					 
2001011101265	20010111	01265	CE  	2001	1	11	20001207SH002    	1	20001205	G	5730	MS24694C51	SCREW           	CESSNA      		CESSNA	500   	550         	2076604	CE  										WING SKIN	IMPROPER PART   	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	4614N					5500659				UPON INSPECTION OF AREA UNDER HEATED LEADING EDGE (TOP FORWARD SCREW), IT WAS FOUND THAT THE SCREW HAD CONTACTED THE SKI	N SURFACE.  THE SCREW HAD PENETRATED PART OF A RIVET HEAD ON THE LEFT WING AND EXTENDED INTO THE SKIN APPROXIMATELY 0.05	0 INCH (POSSIBLY A COMBINATION OF PENETRATION AND DIMPLING).  THE SCREW ON THE RIGHT WING HAD CONTACTED A RIVET HEAD DE	AD CENTER AND PENETRATED THE RIVET APPROXIMATELY 0.030 INCH.  THE CORRECT HARDWARE WAS USED PER THE AIRCRAFT MANUFACTUR	ERS PARTS CATALOGUE.  THE LEFT WING WILL REQUIRE REPAIR OR REPLACEMENT OF THE WING SKIN OVERLAYING THE FUEL CELL, THE R	IGHT WING WILL REQUIRE REPLACEMENT OF THE RIVET IN THE FUEL CELL IN ORDER TO RETURN THE AIRCRAFT TO SERVICE.  (X)	1	L	7	2 	4F			 	A22CE   					 
2001020900105	20010209	00105	SO  	2001	2	9	20001207SH003    	1	20001115	G	2140	A23D0475	REGULATOR       	JANITROL    		PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	A			FFSA	O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	4501B	164  			5954723	318052168				FUEL WAS OBSERVED LEAKING FROM DRAIN TUBE.  INVESTIGATION REGVEALED VALVE TO BE LEAKING FORM DIAPHRAGM PARTING SURFACE. 	 VALVE BODY SCREWS WERE FOUND LOOSENED OVER TIME.  SUGGESTED SELECTION OF ALTERNATE LOCKING DEVICE TO PREVENT RECURRENCE	.  (X)				1	L	7	2 	3O			 	A20SO   					 
2001021500035	20010215	00035	SW  	2001	2	15	20001207SH004    	1	20001116	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										T/R DRIVE	ROUGH           	E			R6LA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	58236					53069				C/W THE INTENT OF HD 2000-02-12 BY INSPECTING OIL COOLER BLOWER D/S BEARINGS.  AFT BEARING FOUND ROUGH RUNNING.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001030200045	20010302	00045	CE  	2001	3	2	20001207SH005    	1	20001114	G	2436	DGR3	REGULATOR       			CESSNA	172   	172P        	2072436	CE  										ALTERNATOR	FAILED          	B			IC1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	23	65003					17275666				ALTERNATOR CONTROL UNIT FAILED INTERNALLY EMITTING SMOKE ODOR.  REPLACED ACU AND INSPECTED CHARGING SYSTEM FOR OPERATION	 IAW CESSNA MM.  (NO DEFECTS NOTED).  (X)					1	H	7	1 	3O			NT	3A12    					 
2001030200046	20010302	00046	CE  	2001	3	2	20001207SH006    	1	20001024	G	2751	45AS61015021	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  										LT FLAP	OUT OF ADJ      	B				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			GL	23	695BK	577  				RK235				FLAP ASYMMETRY LIGHT ILLUMINATED DURING LANDING.  ADJUSTED LEFT FLAP FOLLOW-UP SWITCH OUTPUT VOLTAGE TO ASYMMETRY DETECT	OR IAW WITH THE RAYTHEON 400/400A MM.  OPERATIONAL CHECK GOOD.  (X)					2	H	7	2 	4F			RT	A16SW   					 
2001030200047	20010302	00047	EA  	2001	3	2	20001207SH007    	2	20001127	G	7322	105193	CARBURETOR      	PRECISION   		CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			AQ2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	65516	651  			75056408	17275769	L3557336A			FOUND CRACKS IN FLOAT BOWL ON LOWER THROUGH-BOLT BOSS.  APPEARED TO BE A FORGING PROBLEM.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001030200048	20010302	00048	EA  	2001	3	2	20001207SH008    	2	20001109	G	7414	10349276H	WIRE            			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					CAPACITOR	BROKEN          	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CE	07	724LH		182  		F070005ER	1613211	RL112048			PILOT REPORT MAGNETO INOPERATIVE.  POST-REPLACEMENT INSPECTION REVEALED POINTS BURNT, CAPACITOR WIRE BROKEN AT CAPACITOR	 END.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000121500191	20001215	00191	CE  	2000	12	15	20001207SH009    	1	20001101	G	7603	63255535	THROTTLE ARM    			BEECH 	58    	58          	1152740	CE  										RIGHT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	7279R					TH587				RIGHT THROTTLE ARM, PN 632555-35, FAILED PER DRAWING.  THIS IS AT LEAST 10 TIMES ON 10 DIFFERENT AIRPLANES IN PAST 8 YEA	RS THIS PART OR SAME P/N MIXTURE ARM HAD FAILED.  NEEDS SB OR AD.  (X)					1	L	7	2 	3O			 	3A16    					 
2001030200049	20010302	00049	CE  	2001	3	2	20001207SH010    	1	20001127	G	2823		SELECTOR VALVE  			CESSNA	172   	172B        	2072406	CE  										COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	7752X	4035 				17248252				DURING ANNUAL INSPECTION, NOTED THE FUEL SELECTOR VALVE WOULD NOT SHUT OFF FUEL.  THIS COULD BE A HAZARD IF AN IN-FLIGHT	 FIRE OCCURRED.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001030200050	20010302	00050		2001	3	2	20001207SH011    	4	20001127	G	2562	7A1132	ELT             			CESSNA	172   	172B        	2072406	CE  										TAIL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	7752X					17248252				DURING ANNUAL INSPECTION, ELT WAS FOUND NOT TO MEET FAR 91.207(D).  IT FAILED G-TEST AND WAS MOUNTED IMPROPERLY IN AIRCR	AFT.  IT WAS MOUNTED WITH VELCRO AND A DETERIORATED STRAP.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001030200051	20010302	00051	CE  	2001	3	2	20001207SH012    	1	20001127	G	7920		HOSE            			CESSNA	172   	172B        	2072406	CE  										OIL PRESSURE	BROKEN          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	13	7752X					17248252				DURING ANNUAL INSPECTION, OIL PRESSURE HOSE WAS FOUND WET WITH OIL.  AFTER REMOVING HOSE, HOSE CRACKED AND BROKE WHEN TW	ISTED.  FUEL HOSE WAS CHECKED AND WAS IN THE NEAR SAME CONDITION.  NO LOG ENTRY FOUND AS TO WHEN AND IF THESE HOSES HAD 	BEEN REPLACED.  (X)				1	H	7	1 	3O			NT	3A12    					 
2001030200052	20010302	00052	CE  	2001	3	2	20001207SH013    	1	20001102	G	5712		RIB             			CESSNA	172   	172K        	2072430	CE  										LT WING	DAMAGED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7122G	1457 				17258822				DURING A HIDDEN DAMAGE INSP, LT WING ASSY PN 0523005-83 FOUND LIGHT DAMAGE TO MID L/E SKIN AND 1 NOSE RIB, UNAPPROVED RE	PAIR FOUND TO AFT INBD SPAR ASSY.  ALMOST ALL NOSE RIBS IN WING FOUND DAMGED, 10 IN ALL.  A T/E RIB WAS CUT BY A FLAP CO	NTROL CABLE.  4 SKINS FOUND DAMAGED, OTBD L/E SKIN.  RECORDS CHK BY OWNER SHOWED ACFT WING WAS REPAIRED AND RETURNED TO 	SERVICE.  THE SPAR SPLICE WAS NOT DONE IAW CESSNA SM.  RT WING INSP, FOUND RT WING WITH 7 DAMAGED NOSE RIBS 2 EACH L/E S	KINS DAMAGED, AFT SPAR SPLICED, DAMAGE TO SEVEN OTHER SKINS.  (X)		1	H	7	1 	3O			NT	3A12    					 
2001030200053	20010302	00053	CE  	2001	3	2	20001207SH014    	1	20001024	G	8011		TAB             			CESSNA	210   	210         	2073402	CE  										SOLENOID	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	7431E	247  				57131				MOUNTING TABS BROKE OFF ON BOTH SIDES OF THE STARTER SOLENOID BREAKING GROUND CONNECTION SO STARTER WAS INOP.  SOLENOID 	IS MOUNTED DIRECTLY ON THE STARTER.  MOUNTING BRACKET IS SPOT WELDED TO SOLENOID HOUSING.  FAILURE POSSIBLY DUE TO VIBRA	TION.  REPLACED SOLENOID.  (X)				1	H	7	1 	3O			RT	3A21    					 
2001030200054	20010302	00054	GL  	2001	3	2	20001207SH015    	3	20001127	G	6110	83037L	LOCK            			GULSTM	690TP 	690C        	7630517	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	BROKEN          	B			V5SR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	840V	117  				11727		BUA22884		START-LOCK BROKE AND PIN FELL OUT BECAUSE RETAINING COTTER PIN WAS TOO WEAK.  (X)						1	H	7	2 	3T			 	2A4     		6	C	P15EA	 
2001030200055	20010302	00055	CE  	2001	3	2	20001207SH016    	1	20001121	G	3230	504501019	TORQUE TUBE     			CESSNA	310   	310Q        	2074242	CE  										LT MLG	CRACKED         	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	03	8TC					310Q0264				AFTER TAKEOFF, PILOT ADVISED BY GROUND OBSERVERS, LT MLG STILL DOWN.  GEAR CYCLED SEVERAL TIMES, GROUND OBSERVERS REPORT	ED LT MAIN GEAR STILL DOWN.  GEAR SELECTED DOWN, SAFE LANDING.  INSP SHOWED LT M/G TORQUE TUBE, PN 5045010-19, CRACKED, 	FAILED.  CRACK APPEARED TO ORIG BTWN THREADED BOSS WHERE FORK BOLT PN 5141052-1 LATCHES, AND AFT FLANGE OF AFT PIVOT BOL	T MOUNTING BRACKET.  AREA OF BOSS, CRACK RUSTED FOR APPROX 1.5 INCHES INDICATING PRE-EXISTING CONDITION.  CRACK EXTENDS 	AXIALLY AFT FOR 2 INCHES, THEN EXTENDS RADIALLY FWD OF BOSS FOR APPROX 5 INCHES TO 6 INCHES SPIRALLING AROUND TUBE.  INS	P OF INTERIOR OF TORQUE TUBE SHOWED NUMEROUS SPOTS OF CORROSION WITH A CONCENTRATION OF RUST AT THREADS BOSS.  (X)	1	L	7	2 	3O			 	3A10    					 
2001030200056	20010302	00056	SW  	2001	3	2	20001207SH017    	1	20001120	G	3230	ES12404	DRAG BRACE      			GULSTM	690TP 	690B        	7630516	SW  										MLG	CRACKED         	B			MV5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9LV	6088 				11550				UPPER PORTION OF DRAG BRACE CRACKED.  CRACK EXTENDED APPROXIMATELY .50 INCH.  (X)						1	H	7	2 	3T			 	2A4     					 
2001030100044	20010301	00044	SW  	2001	3	1	20001208SH010    	1	20001208	G	5330		SKIN            			MOONEY	M20   	M20J        	5870219	SW  										FUSELAGE	CRACKED         	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	58135	698  				241567				DURING INSPECTION, A CRACK WAS FOUND AT THE LEFT LOWER FUSELAGE SKIN AT BS -5.375 WHERE THE FUSELAGE SKIN ENDS AT THE FI	REWALL AREA.  THE CRACK EMANATED FROM THE EDGE OF THE SKIN, EXTENDED THROUGH A RIVET HOLE AND BACK OUT, ANGLING BACK TOW	ARDS THE SKIN EDGE AGAIN.  THE CRACK WAS APPROXIMATELY 1.5 INCHES LONG WHEN DISCOVERED.  A PROPER SKIN REPAIR WAS ACCOMP	LISHED.  RECOMMEND A CLOSE LOOK IN THIS AREA DURING SCHEDULED INSPECTIONS.   NO DEFINITE CAUSE WAS FOUND TO HAVE CAUSED 	THIS PARTICULAR DEFECT.  (X)		1	L	7	1 	3O			 	2A3     					 
2001030100051	20010301	00051	NE  	2001	3	1	20001212SH010    	2	20001113	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FOR FPI IAW IAE V2500 PROPULSION SYSTEM ENGINE MANUAL, REV 45, SECTION 70-23-01, INSPECTION CHECK-01, TASK	 70-23-01-230-501.  PART REJECTED AT FPI DUE TO CRACKS IN TWO AREAS ON OUTSIDE DIAMETER OF PART.  (X)										4	F			E311NE				 
2001030100052	20010301	00052	NE  	2001	3	1	20001212SH011    	2	20001109	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FOR FPI IAW IAE V2500 PROPULSION SYSTEM ENGINE MANUAL, REV 45, SECTION 70-23-01, INSPECTION CHECK-01, TASK	 70-23-01-230-501.  PART REJECTED AT FPI FOR CRACKS IN TWO AREAS ON OUTSIDE OF PART.  (X)										4	F			E311NE				 
2001030100049	20010301	00049	CE  	2001	3	1	20001214SH001    	1	20001212	G	2400		HARNESS         			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE	BURNED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	773TP	183  				BB1722				WIRE BUNDLE SPIRAL WRAP MELTED AND CHAFING AGAINST THE BRAKE DE-ICE HEAT LINE WHERE IT MAKES THE TURN TO COME INTO THE F	ORWARD INBOARD PART OF WHEELWELL AT WS 85, ACCESS PANEL NR  13 AS SEEN ON CHAP 12-20-00 PAGE 249, FIG. 205 OF MM.  (X)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000121800237	20001218	00237	CE  	2000	12	18	20001214SH006    	1	20001030	G	5531	16962000161	SPAR CAP        	BEECH       		BEECH 	23    	C23         	1151242	CE  										INTERNAL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	6717K	7191 				M2266				DURING ANNUAL INSPECTION, ''CREAKING'' WAS HEARD WHEN FORCE WAS APPLIED TO STABILATOR TIP TO CHECK FOR BEARING PLAY.  SO	URCE OF SOUND WAS FOUND TO BE WORKING RIVETS AND CRACKED SPAR CAP INSIDE CENTER SPAR BOX ASSY IN THE LOOSE RIVETS OR CRA	CK COULD BE SEEN BY EXTERIOR INSPECTION OF THE STABILATOR ONLY.  THE BALANCE WEIGHT TUBE HAD TO BE REMOVED TO INSPECT TH	E INTERIOR OF THE SPAR BOX.  WHEN CHECKED AGAIN THE NEXT MORNING, AFTER COOLING OFF ALL NIGHT, THE CREAKING COULD NOT BE	 DUPLICATED.  SUBMITTER RECOMMENDED PERIODIC INSPECTION OF THE SPAR BOX INTERIOR BY REMOVAL OF THE BALANCE WEIGHT TUBE A	NNUALLY AND AT SOME INTERVAL.  (X)	1	L	7	1 	3O			 	A1CE    					 
2000121800240	20001218	00240	EA  	2000	12	18	20001214SH010    	2	20001122	G	8530	EC75362EC101	CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NR 5	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	900TS	975  				277405429	L634048			AIRCRAFT ON 135 FLIGHT, PILOT NOTICED BLUE FLAME IN COWLING, RIGHT ENGINE.  LANDED AT COLUMBIA, MO ON A SCHEDULED STOP. 	 FOUND NR 5 CYLINDER HAD EXHAUST HOLE BURNED THROUGH CYLINDER FORWARD SIDE, .25 INCH BY 1 INCH.  HOLE STARTED ON INSIDE 	EXHAUST PART BY EXHAUST SEAT AND WORKED OR BURNED FORWARD FRONT OF ENGINE.  CRACKS WERE NOTED FROM BOTH SPARKPLUG HOLES 	TO BURNED HOLE.  THE CYLINDERS WERE NEW, ECI INSTALLED 2-18-99 AND HAD 974.6 HOURS ON CYLINDER, OCCURRED 11-20-00.  (X)			1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2000121800242	20001218	00242	CE  	2000	12	18	20001214SH016    	1	20001129	G	3233	99810057652	ACTUATOR        			BEECH 	100   	100BEECH    	1152916	CE  											FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	23	153JW		2744 			B53				LEFT LANDING GEAR FAILED TO EXTEND FOR LANDING.  PILOT UNSUCCESSFULLY ATTEMPTED TO LOWER LANDING GEAR (WHILE IN CONTACT 	WITH MAINTENANCE) SEVERAL TIMES.  PILOT LANDED AIRCRAFT WITH GEAR RETRACTED.  AIRCRAFT SUSTAINED DAMAGE TO THE LOWER FUS	ELAGE, LOWER RIGHT NACELLE AND PROPELLERS.  INITIAL INSPECTION REVEALED LEFT TORQUE SHAFT SHEARED INBOARD OF LANDING GEA	R ACTUATOR ATTACH POINT DUE TO LEFT LANDING GEAR ACTUATOR INTERNAL FAILURE.  NO DISASSEMBLY OF ACTUATOR PERFORMED.  CAUS	E OF FAILURE UNDETERMINED.  (X)		1	L	7	2 	3T			 	A14CE   					 
2000121800243	20001218	00243	CE  	2000	12	18	20001214SH017    	1	20001122	G	3250	05430221	BUNGEE CYLINDER 			CESSNA	172   	172R        	2072401	CE  										NOSE GEAR	WEAK            	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	07	24468	440  				17280863				PILOT EXPERIENCED POOR STEERING, RAN OFF RUNWAY IN CROSSWIND CONDITION.  FOUND LEFT AND RIGHT STEERING BUNGEES WEAK.  PU	LLED TESTED BOTH ORIGINAL BUNGEES, ACTUATOR STARTED ABOUT 20 - 25 POUNDS PULL.  NEW BUNGEES PULL TESTED 60 - 65 POUNDS P	ULL.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000121800244	20001218	00244	CE  	2000	12	18	20001214SH018    	1	20001204	G	3250	05430222	BUNGEE CYLINDER 			CESSNA	172   	172R        	2072401	CE  										NOSE GEAR	WEAK            	B				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	07	24468	440  				17280873				PILOT EXPERIENCED POOR STEERING, RAN OFF RUNWAY IN CROSSWIND CONDITION.  FOUND LEFT AND RIGHT STEERING BUNGEES WEAK.  PU	LLED TESTED BOTH ORIGINAL BUNGEES, ACTUATOR STARTED ABOUT 20 - 25 POUNDS PULL.  NEW BUNGEES PULL TESTED 60 - 65 POUNDS P	ULL.  (X)				1	H	7	1 	3O			NT	3A12    					 
2000121800245	20001218	00245	CE  	2000	12	18	20001214SH019    	1	20001121	G	7500	C1B0021	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  										INSIDE ENG NAC	WORN            	H			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	280SC	139  				BB664				HOSES ARE WEARING ON COWLING LATCHES.  THIS CAUSES DAMAGE TO HOSES AND TO THE LATCHES.  HOSES ARE TOO LARGE, OR INSTALLE	D AT THIS WRONG ANGLE.  HOSES WERE INSTALLED UNDER STC SA 8986SW.  (X)					1	L	7	2 	4T			 	A24CE   					 
2000121800246	20001218	00246	CE  	2000	12	18	20001214SH020    	1	20001121	G	7500	C1B0022	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  										INSIDE ENG NAC	WORN            	H			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	280SC	139  				BB664				HOSES ARE WEARING ON COWLING LATCHES.  THIS CAUSES DAMAGE TO HOSES AND TO THE LATCHES.  HOSES ARE TOO LARGE, OR INSTALLE	D AT THIS WRONG ANGLE.  HOSES WERE INSTALLED UNDER STC SA 8986SW.  (X)					1	L	7	2 	4T			 	A24CE   					 
2000121800247	20001218	00247	CE  	2000	12	18	20001214SH021    	1	20001201	G	5600	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  										PILOT	CRACKED         	B			JEMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	300HB					BB566				WINDSCREEN SPIDER WEB CRACKED IN-FLIGHT.  (X)						1	L	7	2 	4T			 	A24CE   					 
2000121800248	20001218	00248	SO  	2000	12	18	20001214SH022    	2	20001101	G	8530		EXHAUST VALVE   			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					NR 1 CYLINDER	GROOVED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	36TU	264  				EA273	248926R			DUE TO LOW COMPRESSION READING, CYLINDER WAS BORESECOPED.  EXTREME OVERHEATING OF EXHAUST VALVE WAS NOTED.  WEAR GROOVE 	WAS CUT INTO VALVE FACE BY SEAT.  REMOVED CYLINDER.  UPON INSPECTION, UNUSUAL WEAR WAS DUE TO MISALIGNMENT OF VALVE GUID	E OR VALVE SEAT.  CYLINDER SENT FOR INSP.  LOWER END OF GUIDE WAS BELL MOUNTED.  VALVE SEAT CHECKED WITH MASTER SEAT GAU	GE AND FOUND TO SHOW HEAVIER CONTACT ON OTBD SIDE, LESS ON INBD SIDE.  CAUSE NOT OFFICIALLY DETERMINED.  SUBMITTER BELIE	VED CAUSE ORIGINATED DURING MFG.  PART CAME FROM FACTORY MISALIGNED.  (X)		1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2000121800249	20001218	00249	CE  	2000	12	18	20001214SH025    	1	20001120	G	5510	C12326242	BRACKET         			CESSNA	210   	T210N       	2073456	CE  										HORIZ STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	6509N					21063113				DURING ANNUAL INSPECTION, MECHANIC FOUND REINFORCEMENT BRACKET LOCATED CENTER AFT ON HORIZONTAL STABILIZER WAS CRACKED. 	 POSSIBLE CAUSE, MOVING AIRCRAFT VIA HORIZONTAL STABILIZER AND NOT WITH TOW POINTS.  INSTALLED NEW AND IMPROVED BRACKETS	 PER SEB00-10.  (X)				1	H	7	1 	3O			 	3A21    					 
2000121800250	20001218	00250	SW  	2000	12	18	20001214SH027    	1	20001005	G	3220	540015001	LINK            			MOONEY	M20   	M20L        	5870221	SW  										NOSE GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	78MP	816  				260010				DURING ANNUAL INSP, NOTICED PAINT ON OUTSIDE OF THE SHOCK LINK SHOWED SIGNS OF METAL UNDERNEATH CRACKING.  PAINT REMOVED	, PART VISUALLY AND DYE PENETRANT INSPECTED.  NO CRACKS FOUND.  NOTICED SHOCK DISCS COMPRESSED OUT OF LIMITS. UPON REMOV	AL, NOTICED SHOCK LINK CRACKED ON INSIDE.  IN JUNE, 2000 A MOONEY M20K HAD AN ACCIDENT UPON LANDING.  N/G COLLAPSED ON T	OUCHDOWN RESULTING IN PROP STRIKE, LOSS OF DIRECTIONAL CONTROL OF ACFT.   UPON INVEST, FOUND SHOCK LINK ON N/G HAD CRACK	ED, SLOWLY WOBBLED OUT THE INSIDE OF SHAFT.  M20K AND M20L HAVE SAME PART NUMBER FOR SHOCK LINK.  PART IS INSTALLED IN N	/G, USED TO COMPRESS, HOLD RUBBER SHOCK DISCS.  IF PART BREAKS, UPON LANDING, PUSHES ITSELF INTO N/G WELL.  (X)	1	L	7	1 	3O			RT	2A3     					 
2000121800251	20001218	00251	CE  	2000	12	18	20001214SH028    	1	20001125	G	2820	RG34720A	PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENG ACCY CASE	LEAKING         	E				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			GL	15	847BA		2019 			BB847	PCE85099			DURING FLIGHT, THE FUEL FLOW DROPPED OFF UNTIL THE ENGINE TORQUE DROPPED ENOUGH TO FEATHER THE PROPELLER.  THE CREW THEN	 SHUT THE ENGINE OFF WITH THE FUEL CONDITION LEVER.  MAINTENANCE FOUND THE 4 SCREWS (THAT WERE SAFTIED) HOLDING THE PRES	SURE RELIEF ADJUSTMENT PLATE ONTO THE LOW PRESSURE FUEL PUMP LOOSE, AND FUEL LEAKING, SUSPECT AIR WAS BEING INTRODUCED I	NTO THE FUEL SYSTEM HERE AND CAVITATED THE HIGH PRESSURE PUMP CAUSING LOSS OF FUEL TO FCU.  (X)			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001021500037	20010215	00037	EU  	2001	2	15	20001214SH029    	1	20001130	G	8012	B666B	VALVE           			SNIAS 	350   	AS350B2     	8680813	EU  										START DRAIN	LEAKING         	E			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	09	53SH					2009				START DRAIN VALVE LEAKING INTERNALLY.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500038	20010215	00038	EU  	2001	2	15	20001214SH030    	1	20001201	G	3110	704A47270101	INDICATOR       			SNIAS 	350   	AS350BA     	8680817	EU  										TEMPERATURE	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	270SH					1864				TEMPERATURE GAUGE INOPERATIVE.  (X)						1	G	7	1 	3U			NC	H9EU    					 
2001021500039	20010215	00039	NE  	2001	2	15	20001214SH031    	2	20001130	G	7321	BB56B	FUEL CONTROL    			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	LEAKING         	E			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	2273A					2273				DECELERATION UNIT ON FCU LEAKING.  (X)						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001021500041	20010215	00041	EU  	2001	2	15	20001214SH035    	1	20000901	G	6240	614764021	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										TACHOMETER	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	101LN	406  				3038				TACHOMETER UNIT INOPERATIVE.  NTL NEEDLE VIBRATED EXCESSIVELY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500042	20010215	00042	NE  	2001	2	15	20001214SH037    	2	20000406	G	7250	410106701	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					TURBINE SHROUD	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117MA	449  				7107	LE45266EA			FIRST TURBINE SHROUD SEAL RING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021500043	20010215	00043	NE  	2001	2	15	20001214SH038    	2	20000912	G	7250	414129011	TURBINE WHEEL   			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					POWER TURBINE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	10UM	2308 	1319 			7231	LE45610EFA			ROTOR ASSY, INSERTABLE BLADED, POWER TURBINE RETENTION PLUG WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, COR	RECTED PROBLEM.  (X)					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021500044	20010215	00044	EU  	2001	2	15	20001214SH039    	1	20001002	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350B3     	8680954	EU  										HYDRAULIC SYS	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	721  				3128				HYDRAULIC PUMP HAD EXCESSIVE SPLINE WEAR.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500045	20010215	00045	EU  	2001	2	15	20001214SH040    	1	20001106	G	2841	9550171990	SWITCH          			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					LOW FUEL	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	103LN					3128	22032			LOW FUEL SWITCH UNIT INOPERATIVE.  MASTER CAUTION LIGHT GOES OUT PERMANENTLY BEFORE ENGINE START.  REPLACED WITH NEW UNI	T, CORRECTED PROBLEM.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2001021500046	20010215	00046	EU  	2001	2	15	20001214SH041    	1	20001122	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  										FUEL PUMP	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135N	3    				EC1350086				FUEL PUMP CARTRIDGE UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001021500047	20010215	00047	EU  	2001	2	15	20001214SH042    	1	20001122	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  										FUEL PUMP	INOPERATIVE     	A			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135N	3    				EC1350086				FUEL PUMP CARTRIDGE UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001021500048	20010215	00048	EU  	2001	2	15	20001214SH043    	1	20000922	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B3     	8680954	EU  										TAIL ROTOR	DELAMINATED     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	104LN	705  				3134				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM ONE EACH KIT, P/N 355A09-1036-01, CORRECTED PR	OBLEM.  4 HALF SHELLS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500049	20010215	00049	EU  	2001	2	15	20001214SH044    	1	20001008	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B3     	8680954	EU  										EXTERIOR LIGHTS	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	104LN	1053 				3134				POWER SUPPLY BOX UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500050	20010215	00050		2001	2	15	20001214SH045    	4	20000805	G	3454	071010520000	TRANSMITTER     			SNIAS 	350   	AS350B3     	8680954	EU  										VOR SYSTEM	INOPERATIVE     	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	104LN	534  				3134				MAGNETIC AZIMUTH TRANSMITTER UNIT INOPERATIVE.  5 TO 60 DEGREE DEVIATION WHILE ON SAME HEADING IN SLAVE MODE.  REPLACED 	WITH NEW UNIT, CORRECTED PROBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500051	20010215	00051	NE  	2001	2	15	20001214SH046    	2	20000706	G	7260	230093304	BEARING         			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	127HH	901  				7060	LE45083EA			ANNULAR BALL BEARING WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021500052	20010215	00052	NE  	2001	2	15	20001214SH047    	2	20000706	G	7250	430150601	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 2 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	127HH	901  				7060	LE45083EA			NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021500053	20010215	00053	NE  	2001	2	15	20001214SH048    	2	20000706	G	7250	430144801	SEAL            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 3 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	127HH	901  				7060	LE45083EA			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021500054	20010215	00054	EU  	2001	2	15	20001214SH049    	1	20000706	G	8011		GEAR            	HONEYWELL   		BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					STARTER	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	127HH	901  			A342	7060	LE45083EA			STARTER, GEAR ASSY, EXCESSIVE SPLINE WEAR.  REPLACED WTIH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001021500055	20010215	00055	EU  	2001	2	15	20001215SH001    	1	20001008	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  										FUEL PUMP	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	127  				EC1350054				FUEL PUMP CARTRIDGE UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			O	H88EU   					 
2001021500056	20010215	00056	NE  	2001	2	15	20001215SH002    	2	20000326	G	7310	L717M1009801	TUBE            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					FUEL CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	1444 				EC1350054				TUBE ASSY WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001021500057	20010215	00057	EU  	2001	2	15	20001215SH003    	1	20001106	G	3340	02471131	LIGHT           			BOLKMS	BK117 	BK117C1     	5626025	EU  										SEARCHLIGHT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	921  				7527				SERACHLIGHT UNIT INOPERATIVE.  PIN B-D ONLY 20 VAC, SHOULD BE 48 VAC.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001021500058	20010215	00058	EU  	2001	2	15	20001215SH004    	1	20001031	G	3030	PR6123	ELEMENT         			BOLKMS	BK117 	BK117C1     	5626025	EU  										PITOT HEAT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	622  				7527				PITOT TUBE HAD INOPERATIVE HEATING ELEMENT.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001021500059	20010215	00059	EU  	2001	2	15	20001215SH005    	1	20001025	G	2913	40165	PUMP            			BOLKMS	BK117 	BK117C1     	5626025	EU  										HYDRAULIC SYSTEM	DAMAGED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	902  				7527				DRIVESHAFT WAS TORQUED TOO TIGHTLY IN PLACE AT THE FACTORY.  WHILE MECHANIC WAS REMOVING THE PUMP FOR INSPECTION, THE SH	AFT PULLED LOOSE.  REPLACED WITH USED UNIT, CORRECTED PROBLEM.  (X)					1	G	7	2 	3U			NC	H13EU   					 
2001021500060	20010215	00060	EU  	2001	2	15	20001215SH006    	1	20000627	G	6710	10513141	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	617  				7527				ROD END ASSY WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001021500061	20010215	00061	EU  	2001	2	15	20001215SH007    	1	20000627	G	6710	10513142	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	617  				7527				ROD END ASSY WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001021500062	20010215	00062	EU  	2001	2	15	20001215SH008    	1	20000822	G	6320	4639302037	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R TRANSMISSION	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	117SU	751  				7527				SEALING RING LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H13EU   					 
2001021500063	20010215	00063	NE  	2001	2	15	20001215SH009    	2	20000326	G	7250	430144801	SEAL            			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 3 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	7060G	490  				7173	LE45756EFA			NR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021500064	20010215	00064	NE  	2001	2	15	20001215SH010    	2	20000826	G	7250	430150602	SEAL            			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 2 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	7060G	490  				7173				NR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021500065	20010215	00065	NE  	2001	2	15	20001215SH011    	2	20000826	G	7230	430404701	SEAL            			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 1 BEARING	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	7060G	490  				7173	LE45756EFA			NR 1 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021500066	20010215	00066	EU  	2001	2	15	20001215SH012    	1	20001101	G	2435	524031	STARTER GEN     			SNIAS 	350   	AS350B3     	8680954	EU  										ENGINE	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG					3268				STARTER/GENERATOR UNIT INOPERATIVE.  BRUSH SPRING BROKE RESULTING IN FAN DAMAGE.  REPLACED WITH NEW UNIT, CORRECTED PROB	LEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500067	20010215	00067	NE  	2001	2	15	20001215SH013    	2	20001101	G	7261	350A54113800	VENT LINE       			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL SYSTEM	CRACKED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	102  				3268				TUBE, AIR VENT - OIL, CRACKED BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001021500068	20010215	00068	EU  	2001	2	15	20001215SH014    	1	20001030	G	6321	350A32501000	SUPPORT BRACKET 			SNIAS 	350   	AS350B3     	8680954	EU  										ROTOR BRAKE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	102  				3268				BRAKE LINING SUPPORT WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500069	20010215	00069	NE  	2001	2	15	20001215SH015    	2	20001101	G	7310	350A54113720	COUPLING        			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					P2 LINE	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	102  				3268				P2 UNION WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001021500070	20010215	00070	NE  	2001	2	15	20001215SH016    	2	20001101	G	7310	9996660	LINE            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					P2	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	102  				3268				P2 HOSE WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001021500071	20010215	00071	EU  	2001	2	15	20001215SH017    	1	20001107	G	2432	RG355	BATTERY         			SNIAS 	350   	AS350D      	8680803	EU  										BATTERY BOX	DISCHARGED      	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	350RM	356  				1024				LEAD ACID BATTERY WILL NOT HOLD CHARGE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500072	20010215	00072	EU  	2001	2	15	20001215SH018    	1	20000810	G	6420	35A33214501	CONTROL ROD     			SNIAS 	350   	AS350B3     	8680954	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52285	283  				3251				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500073	20010215	00073	EU  	2001	2	15	20001215SH019    	1	20000731	G	3340	025453	RESISTOR        			SNIAS 	350   	AS350B3     	8680954	EU  										LIGHT BALLAST	BROKEN          	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	52285					3251				BALLAST RESISTOR ASSEMBLY BROKEN AND WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500074	20010215	00074	EU  	2001	2	15	20001215SH020    	1	20000613	G	7933	RP26800	PROBE           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					OIL TEMPERATURE	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52285	170  				3251				TEMPERATURE PROBE UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001021500075	20010215	00075	EU  	2001	2	15	20001215SH021    	1	20001031	G	2432	350A62250120	BATTERY         			SNIAS 	350   	AS350B3     	8680954	EU  										BATTERY BAY	CRACKED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52285	427  				3251				BATTERY FIXING 350B3, CRACKED BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500076	20010215	00076	EU  	2001	2	15	20001215SH022    	1	20001103	G	6720	704A34240015	ACCUMULATOR     			SNIAS 	350   	AS350B3     	8680954	EU  										T/R CONTROL	LEAKING         	B			R7MR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	52285					3251				ACCUMULATOR LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500077	20010215	00077	EU  	2001	2	15	20001215SH023    	1	20001020	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	DELAMINATED     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	58045					1602				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL	EM.  4 HALF SHELLS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500078	20010215	00078	EU  	2001	2	15	20001215SH024    	1	20001025	G	6410	704A33633171	HINGE           			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	58045	437  				1602				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A33-2153-00, CORRECTED PROBL	EM.  TWO TEETERING BEARINGS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500079	20010215	00079	EU  	2001	2	15	20001215SH025    	1	20001012	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B3     	8680954	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52281	432  				3249				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL	EM.  FOUR HALF SHELLS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500080	20010215	00080	EU  	2001	2	15	20001215SH026    	1	20001008	G	3340	025453	RESISTOR        			SNIAS 	350   	AS350B3     	8680954	EU  										LIGHT BALLAST	BROKEN          	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	52281	430  				3249				BALLAST RESISTOR ASSEMBLY BROKEN AND WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500081	20010215	00081		2001	2	15	20001215SH027    	4	20001009	G	3454	071010520000	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  										VOR SYSTEM	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	5771C	845  				1369				MAGNETIC AZIMUTH TRANSMITTER UNIT INOPERATIVE.  10 TO 15 DEGREE DEVIATION FROM EAST TO WEST.  REPLACED WITH NEW UNIT, CO	RRECTED PROBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500082	20010215	00082		2001	2	15	20001215SH028    	4	20001110	G	2211	7004206901	COMPUTER        			BOLKMS	117   	BK117B1     	5626012	EU  										CSAS	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	62LF	42   				7163				CSAS-COMPUTER PITCH INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001021500083	20010215	00083	NM  	2001	2	15	20001215SH029    	1	20001107	G	6710	900C3010002105	FRICTION RING   			DOUG  	MD900 	MD900       	3027375	NM  										COLLECTIVE	ROUGH           	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	129  				90000012				COLLECTIVE FRICTION UNIT ROUGH AND RATCHETY.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021500084	20010215	00084	NM  	2001	2	15	20001215SH030    	1	20001013	G	6220	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DELAMINATED     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	29   				90000012				MAIN ROTOR ENTERING BEARING ASSY, DELAMINATION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021500085	20010215	00085	NM  	2001	2	15	20001215SH031    	1	20001117	G	6220	900R3101001107	BEARING         			DOUG  	MD900 	MD900       	3027375	NM  										MAIN ROTOR	DELAMINATED     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	684  				90000012				MAIN ROTOR CENTERING  BEARIN  ASSY , DELAMINATION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			NC	H19NM   					 
2001021500086	20010215	00086	NE  	2001	2	15	20001215SH032    	2	20001028	G	7261	900P3650108103	BREATHER TUBE   			DOUG  	MD900 	MD900       	3027375	NM  	PWA   	PW206 	PW206A      	 	NE  					ENGINE OIL	DAMAGED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	4225 				90000012	PCE206042			HOSE, ENGINE OIL BREATHER, INSIDE OF HOSE IS BUBBLED.  REPLACED WITH NEW UNIT, CORRECTED UNIT.  (X)						1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2001021500087	20010215	00087		2001	2	15	20001215SH033    	4	20001027	G	3160	900A3720002111	DISPLAY         			DOUG  	MD900 	MD900       	3027375	NM  										COCKPIT	MALFUNCTIONED   	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	259  				90000012				INTEGRATED INSTRUMENT DISPLAY SYSTEM ASSEMBLY, MRB BALANCE DISPLAY ONLY SHOWS PARTIAL CHARACTERS.  INCORRECT CALCULATION	S.  (X)					1	G	7	2 	3U			NC	H19NM   					 
2001021500088	20010215	00088	EU  	2001	2	15	20001215SH034    	1	20000919	G	6410	704A33633171	HINGE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	96LG	474  				2817				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A33-2153-00, CORRECTED PROBL	EM.  TWO TEETERING BEARINGS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500089	20010215	00089	EU  	2001	2	15	20001215SH035    	1	20000919	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	96LG	474  				2817				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL	EM.  FOUR HALF SHELLS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500090	20010215	00090	EU  	2001	2	15	20001215SH036    	1	20000809	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	284  				2575				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500091	20010215	00091		2001	2	15	20001215SH037    	4	20000719	G	3454	071010520000	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										VOR SYSTEM	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	92LG	380  				2575				MAGNETIC AZIMUTH TRANSMITTER UNIT INOPERATIVE.  12 DEGREE NORTH HEADING DEVIATION.  REPLACED WITH NEW UNIT, CORRECTED PR	OBLEM.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500092	20010215	00092	EU  	2001	2	15	20001215SH038    	1	20001108	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	93LG	385  				2654				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT FROM 1 EACH KIT P/N 355A09-1036-01, CORRECTED PROBL	EM.  4 HALF SHELLS EQUALS 1 KIT.  (X)					1	G	7	1 	3U			 	H9EU    					 
2001021500093	20010215	00093	EU  	2001	2	15	20001215SH039    	1	20000914	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	93LG	295  				2654				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	1 	3U			 	H9EU    					 
2001021500094	20010215	00094	NE  	2001	2	15	20001215SH040    	1	20001013	G	3212	7625100702042	LINK            			SKRSKY	S76   	S76A        	8143006	NE  										MLG FLOATS	FAILED          	E			ALGA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	712AL	10392				760280				FLOATS WERE INADVERTENTLY INFLATED.  LINK DID NOT SEPARATE AT SHEAR POINT.   (X)						1	G	7	2 	3U			 	H1NE    					 
2001021500095	20010215	00095	NE  	2001	2	15	20001215SH041    	1	20001030	G	6230	7635109030044	MAST            	SKRSKY      		SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	E			ALGA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	717AL	477  			A08100240	760221				WHILE INVESTIGATING AN OIL LEAK AND SUBSEQUENT REMOVAL OF THE MAIN GEARBOX, THE MAST WAS FOUND CRACKED ALMOST HALFWAY AR	OUND ITS CIRCUMFERENCE.  THE CRACK IS LOCATED BELOW THE LOWER MAIN ROTOR HUB MOUNTING FLANGE.  THE CRACK MEASURES ALMOST	 HALFWAY AROUND THE MAST.  THE MAJORITY OF THE CRACK WAS HIDDEN BY THE SWASHPLATE GUIDE SHIELD RUBBER SEAL.  MAIN GEARBO	X  SENT FOR EVALUATION.  (X)			1	G	7	2 	3U			 	H1NE    					 
2001021500096	20010215	00096	NE  	2001	2	15	20001218SH001    	1	20000721	G	6210	641520201049	BLADE           			SKRSKY	S64   	S64E        	8142604	NE  										MAIN ROTOR	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	176AC	5881 				64003				THE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY .360 INCH AT A 7 O	''CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN).  THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFOR	MED IN THE FIELD.  (X)				2	G	7	2 	4U			 	H4EA    					 
2001021500097	20010215	00097	NE  	2001	2	15	20001218SH002    	1	20000710	G	3213	646550152103	HOUSING         			SKRSKY	S64   	S64E        	8142604	NE  										MLG	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	218AC					64033				MAIN  LANDING GEAR PN 6425-50100-013, -014 WAS REMOVED FOR OVERHAUL.  DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTIO	N PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREME	NTS OF .093 INCH TO .036 INCH IN LENGTH.  THE INDICATIONS ARE LOCATED AT THE LIGHTENING HOLES WITH SOME BREAKING THE EDG	E OF THE HOLE.  A SECOND MLG WAS ALSO INSPECTED AND 7 LINEAR INDICATIONS NOT VISIBLE TO THE NAKED EYE WITH MEASUREMENTS 	OF .171 INCH TO .531 INCH IN LENGTH WERE FOUND ON THE LOWER COLLAR HOUSING.  (X)		2	G	7	2 	4U			 	H4EA    					 
2001021500098	20010215	00098	NE  	2001	2	15	20001218SH003    	1	20000710	G	3213	646550152101	HOUSING         			SKRSKY	S64   	S64E        	8142604	NE  										MLG	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	218AC					64033				MAIN  LANDING GEAR PN 6425-50100-013, -014 WAS REMOVED FOR OVERHAUL.  DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTIO	N PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREME	NTS OF .093 INCH TO .036 INCH IN LENGTH.  THE INDICATIONS ARE LOCATED AT THE LIGHTENING HOLES WITH SOME BREAKING THE EDG	E OF THE HOLE.  A SECOND MLG WAS ALSO INSPECTED AND 7 LINEAR INDICATIONS NOT VISIBLE TO THE NAKED EYE WITH MEASUREMENTS 	OF .171 INCH TO .531 INCH IN LENGTH WERE FOUND ON THE LOWER COLLAR HOUSING.  (X)		2	G	7	2 	4U			 	H4EA    					 
2001021500099	20010215	00099	WP  	2001	2	15	20001218SH004    	1	20000707	G	6220	369A10045	PIN             			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR HUB	BROKEN          	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	502CH	5885 				180252D				VISUAL INSPECTION REVEALED BROKEN PIN.  (X)						1	G	7	1 	3U			 	H3WE    					 
2001021500100	20010215	00100	SW  	2001	2	15	20001218SH005    	1	20000613	G	2822	P49389	RELIEF VALVE    	AIRBORNE    		BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					FUEL BOOST PUMP	FAILED          	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	407AR	197  			2AR27	53363	CAE847397			DURING ANNUAL INSPECTION, HARDWARE WAS FOUND IN AIRFRAME ANTI-ICE FUEL FILTER.  AFTER CONSULATION WITH BELL PRODUCT SUPP	ORT, IT WAS THOUGH TO HAVE COME FROM THE FILTER BOWL.  INSPECTION OF THE FILTER BOWL AND FILTER HEAD FOUND NO DISCREPANC	IES.  INSPECTED AFT FUEL BOOST PUMP ASSY, FOUND LEFT THERMAL RELIEF VALVE HAD COME APART SENDING A NUT AND ANOTHER PIECE	 INTO THE FILTER.  FURTHER INSPECTION FOUND A SPRING IN THE FUEL LINE TO THE FILTER AND ANOTHER PIECE IN THE CANNISTER W	ITH SOME ALUMINUM SHAVINGS.  THE LEFT VALVE THREADS WERE ALSO PARTIALLY STRIPPED.  THE BOOST PUMP ASSY WAS INSPECTED WIT	H NO DISCREPANCIES FOUND.  (X)	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001021500101	20010215	00101	NE  	2001	2	15	20001218SH006    	1	20000629	G	6420	6511207101041	ARM             	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  										TAIL ROTOR	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	164AC		1432 		A9028	64034D				ARM ASSEMBLY HAD CRACK INDICATION ON OUTBOARD MOUNTING LUG EXTENDING FROM .256 INCH/.252 INCH DIAMETER THROUGH HOLE TO .	34 INCH RADIUS.  CIRCUMSTANCES UNDER WHICH CRACKING OCCURRED ARE UNKNOWN.  POSSIBLE CAUSE IS FROM FRETTING MOVEMENT BETW	EEN SLEEVE MOUNTING EARS, AND ARM ASSY MOUNTING LUGS.  ALL THROUGH HOLES OF BOTH SLEEVE AND ARM ASSY MET BLUEPRINT REQUI	REMENTS .256 INCH/.252 INCH DIAMETER.  (X)			2	G	7	2 	4U			 	H4EA    					 
2001011104198	20010111	04198	SO  	2001	1	11	20001218SH007    	2	20001030	G	8530	CLASS71	CYLINDER        								CONT  	O520  	IO520*      	17032	SO  					ENGINE	DELAMINATED     	B			AG2R	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SW	17		1831 	82   				291457R			CERMINIL COATING DELAMINATED FROM ONE STEEL CYL BORE AT 82.2 HRS TSO.  POSSIBLE CAUSE, SOME INDIVIDUAL POSSIBLY TOUCHED 	CYL BORE JUST BEFORE PROCESSING.  TOUCHING CYL BORE AFTER FINAL CLEANING AND/OR DURING PROCESSING IS STRICTLY PROHIBITED	 IN SPECS FOR PROCESS BECAUSE CONTAMINATION FROM PERSON'S HAND CAN CAUSE ADHERENCE PROBLEMS.  THE AUTOMATED PRE-TREAT PR	OCESS WAS POSSIBLY INTERRUPTED THROUGH SOME ELECTRIC OR COMPUTER ANOMALY AND REQUIRED PRE-TREATMENTS WERE NOT COMPLETED.	  PLATING PROCESS ACCOMPLISHED THROUGH COMPUTER, ROBOTIC MANIPULATION.  COMPUTER REPORTS PROCESSING PROBLEMS, BUT THERE 	WERE NO REPORTS ASSOCIATED WITH THIS PARTICULAR CYLINDER.  (X)						3	O			E5CE				 
2001021400056	20010214	00056	CE  	2001	2	14	20001218SH011    	1	20001004	G	5510	12326241	BRACKET         			CESSNA	210   	T210N       	2073456	CE  										HORIZ STABILIZER	CRACKED         	B			VT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	1766U	5541 				21064741				DURING PRE-FLIGHT INSPECTION, PILOT NOTED LEFT STABILIZER BRACKET BROKEN.  SUBMITTER RECOMMENDED CLOSE INSPECTION OF THI	S AREA DURING PRE-FLIGHT, 100-HOUR, ANNUAL INSPECTIONS, AND TO C/W CESSNA SE 84-17.  (X)					1	H	7	1 	3O			 	3A21    					 
2001021400057	20010214	00057	NE  	2001	2	14	20001218SH012    	1	20001204	G	2612	7630607902103	FIRE DETECTOR   			SKRSKY	S76   	S76B        	8143007	NE  										NR 1 ENG	MALFUNCTIONED   	D				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			EA	25	22CP	3132 				760425				AN ERRONEOUS NR 1 ENGINE FIRE INDICATION (FIRE LIGHT) CAME ON IN-FLIGHT WITH NO OTHER SUPPORTING INDICATIONS OF A FIRE. 	 REPLACED NR 1 FORWARD ENGINE FLAME DETECTOR WITH A NEW SERVICEABLE PART AS DETERMINED BY TROUBLESHOOTING OF FIRE DETECT	ION SYSTEM.  CHECKED OUT SYSTEM, OK.  SUBSEQUENT FLIGHTS, SYSTEM NORMAL.  (X)				1	G	7	2 	4U			 	H1NE    					 
2001010200131	20010102	00131	SO  	2001	1	2	20001218SH015    	2	20001110	G	8530	654961A7BP	CYLINDER        			BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  						FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	3181U	368  				EA563				CYLINDER HAD LOW COMPRESSION.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E8CE				 
2001010200146	20010102	00146	CE  	2001	1	2	20001218SH017    	1	20001115	G	3230	08411103	LINK            			CESSNA	401   	401A        	207590D	CE  										ADJUSTING SCREW	WORN            	B			AK6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	6296Q	6799 				401A0096				UPON C/W AD 76-13-07, REPLACEMENT OF FORK BOLTS, PLAY WAS NOTICED AT ADJUSTING SCREW/DOWNLOCK SWITCH LOCK LINK.  UPON FU	RTHER INSPECTION, THREADS WERE SHOWN TO BE WORN AND PART WAS ALLOWED ABOUT 5 THOUSANDS OF AN INCH IN PLAY.  THIS IS THE 	SECOND REPORT FILED ON THIS PART NUMBER AND SECOND RECOMMENDATION OF MANDATORY AD OF 2,500-HOUR REPLACEMENT.  THIS IS TH	E ONLY DOWNLOCK LOAD ON THE GEAR SIDE BRACE AND UPON FAILIURE, IS GUARANTEED GEAR FAILURE/COLLAPSE.  (X)			1	L	7	2 	3O			 	A7CE    					 
2001021400061	20010214	00061	CE  	2001	2	14	20001218SH018    	1	20001129	G	2434	649304	ALTERNATOR      			CESSNA	310   	310R        	2074245	CE  										ENGINE	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	6832Y					310R2121				FOUND WORN BRUSH IN ALTERNATOR CAUSING SPRING OF BRUSH TO COME OUT OF POSITION TO SHORT ALTERNATOR FIELD.  (X)						1	L	7	2 	3O			 	3A10    					 
2001021500102	20010215	00102	NE  	2001	2	15	20001218SH019    	1	20001201	G	6510	7630807952105	BLOWER          			SKRSKY	S76   	S76B        	8143007	NE  										OIL COOLER	INTERMITTENT    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	61CP					760427				DURING A HELICOPTER GROUND RUN, MECHANIC WAS MOVING AND SHAKING THE WIRE BUNDLE LEADING FROM THE HELICOPTER MAIN GEARBOX	 NR SENSOR ROUTED ALONG LEFT SIDE OF NR 1 ENG OIL COOLER BLOWER BASE, TRYING TO STIMULATE COCKPITS INTERMITTENT INDICATI	ON.  ENGINES OIL COOLER BLOWERS ARE ACTIVE WHEN MAIN ROTORS ARE TURNING.   MECHANIC LOST THE TIPS OF TWO FINGERS OF LEFT	 HAND BY RUNNING HIS HAND PAST BASE OF ENG OIL COOLER BLOWER CONTACTING THE AIR INLET IMPELLER.			1	G	7	2 	4U			 	H1NE    					 
2001021500103	20010215	00103	NM  	2001	2	15	20001218SH020    	1	20001127	G	5320		STIFFENER       			DOUG  	600N  	600N        	3027377	NM  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	609BP	903  				RN038				DURING AN INSPECTION OF THE AIRCRAFT, A STIFFENER WAS FOUND CRACKED, P/N 369D23022-5.  THE CRACK IS LOCATED ON THE INBOA	RD SIDE WHERE THE TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK.  (X)					1	G	7	1 	3U			NC	H3WE    					 
2001021500104	20010215	00104	NM  	2001	2	15	20001218SH021    	1	20001127	G	5320		STIFFENER       			DOUG  	600N  	600N        	3027377	NM  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	609BP	903  				RN038				DURING AN INSPECTION, A STIFFENER WAS FOUND CRACKED, P/N 369D23022-6.  THE CRACK IS LOCATED ON THE INBOARD SIDE WHERE TH	E TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK.  (X)					1	G	7	1 	3U			NC	H3WE    					 
2001021500105	20010215	00105	NM  	2001	2	15	20001218SH022    	1	20001127	G	5320		STIFFENER       			DOUG  	600N  	600N        	3027377	NM  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	610BP	1002 				RN040				DURING AN INSPECTION, A STIFFENER WAS FOUND CRACKED, PN 369D23022-5.  THE CRACK IS LOCATED ON THE INBOARD SIDE WHERE THE	 TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK.  (X)					1	G	7	1 	3U			NC	H3WE    					 
2001021500106	20010215	00106	NM  	2001	2	15	20001218SH023    	1	20001127	G	5320		STIFFENER       			DOUG  	600N  	600N        	3027377	NM  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	610BP	1002 				RN040				DURING AN INSPECTION, A STIFFENER WAS FOUND CRACKED, P/N 369D23022-6.  THE CRACK IS LOCATED ON THE INBOARD SIDE WHERE TH	E TWO RIVETS THAT HOLD THE STIFFENER TO THE UPPER MAST DECK.  (X)					1	G	7	1 	3U			NC	H3WE    					 
2000122800396	20001228	00396	CE  	2000	12	28	20001218SH026    	1	20000830	G	3233	11581002917	NUT             	RAYTHN      		BEECH 	200   	200BEECH    	1152920	CE  										LT LDG ACTUATOR	SEPARATED       	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	80WM				512G81	BB863				THREADED INSERT SEPARATED FROM LANDING GEAR ACTUATOR ROD CAUSING AN UNSAFE LANDING  GEAR INDICATION IN COCKPIT.  THE ACT	UATOR NUT WAS INSTALLED NEW IN THE LANDING GEAR ACTUATOR.  POSSIBLE CAUSE:  MANUFACTURING DEFECT.  (X)					1	L	7	2 	4T			 	A24CE   					 
2000122800397	20001228	00397	CE  	2000	12	28	20001218SH029    	2	20001205	G	7414	K3823	DISTRIBUTOR     	SLICK       		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					GRSHFT HSNG BASE	WORN            	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9284R	587  			97101129	3449005	321440			DURING SCHEDULED 500-HOUR INSPECTION OF MAGNETO, FOUND DISTRIBUTOR GEARSHAFT AND BLOCK BEARINGS WORN.  THIS WEAR HAD ALL	OWED BRUSH TO WEAR WHICH CAUSED METAL CONTACT AND WEARING OF THE COIL,  THE MAGNETO WAS REPLACED.  GEAR AND BLOCK ASSY, 	PN K-3823.  (X)				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022300052	20010223	00052	GL  	2001	2	23	20001218SH030    	3	20001205	G	6112	755379	LEAD            			PIPER 	PA34  	PA34220T    	7103420	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER HUB	SEVERED         	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9284R	823  				3449005				DURING SCHEDULED INSPECTION, FOUND 2 PROPELLER BULKHEADS TO SLIP, RING LEADS SEVERED DUE TO CONTACT WITH THE ENGINE COWL	.  THREE FAULTS WERE FOUND WHICH POSSIBLY CONTRIBUTED TO THIS.  ENGINE VIBRATION, MOUNTS WERE SAGGED.  MFG RECOMMENDED R	EPLACEMENT AT APPROX ENGINE MID-OVERHAUL.  FORWARD TY WRAP HOLDING LEAD TO HUB HAD SHIFTED AFT.  SPINNER BULKHEAD GROMME	TS WERE DETERIORATED (ONE MISSING).  PARTS REPLACED, CONTRIBUTING FACTORS REPLACED.  GROUND TEST SATISFACTORY.  (X)			1	L	7	2 	3O			 	A7SO    		5	C	P920	 
2001022300053	20010223	00053	SO  	2001	2	23	20001218SH031    	1	20001204	G	2140	75775694E423	SWITCH          			PIPER 	PA34  	PA34220T    	7103420	SO  										COCKPIT	MALFUNCTIONED   	B			RMMR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	01	928AR	368  			A96070023	3449005				DURING SCHEDULED INSPECTION WHEN HEATER SWITCH SELECTED ON, HEATER DID NOT IGNITE.  FUEL WAS DRAINING FROM DRAIN.  TROUB	LESHOOTING DETERMINED NO COMBUSTION AIR FLOW AND CONTINUITY BETWEEN THE TERMINALS OF P/N 94E42-3, (PIPER P/N 757-756) CO	MBUSTION AIR SENSE SWITCH.  COMBUSTION AIR BLOWER MOTOR BRUSHES WERE SHORT, AND WERE REPLACED.  COMBUSTION AIR SWITCH WA	S REPLACED WITH NEW.  GROUND OPERATIONAL TEST WAS SATISFACTORY.  (X)			1	L	7	2 	3O			 	A7SO    					 
2001022300054	20010223	00054	CE  	2001	2	23	20001218SH032    	2	20001205	G	7414	K3823	DISTRIBUTOR     	SLICK       		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					MAGNETO	WORN            	B			RMMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9284R	587  			97101123	3449005	321440			DURING SCHEDULED 500-HOUR INSPECTION OF MAGNETO, FOUND DISTRIBUTOR GEARSHAFT AND BLOCK BEARINGS WORN.  PARTS WERE REPLAC	ED.  P/N M3828 GEAR REPLACED AND MAGNETO INSTALLED AND TIMED.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001022300055	20010223	00055		2001	2	23	20001218SH033    	4	20001004	G	3422	S33302	GYRO            			CESSNA	172   	172R        	2072401	CE  										COCKPIT	INOPERATIVE     	B			VT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	9513R	32   				17280619				DIRECTIONAL GYRO REPORTED INOPERATIVE BY PILOT.  DURING REPLACEMENT OF DG, NOTED THE CASE UNDER THE DATA PLATE WAS DENTE	D IN.  SUSPECT THAT THE SERIAL NUMBER WAS STAMPED ON DATA PLATE RESULTING IN DENTED CASE.  (X)					1	H	7	1 	3O			NT	3A12    					 
2001022300056	20010223	00056	CE  	2001	2	23	20001218SH034    	1	20001110	G	8120	63272913	TURBOCHARGER    			BEECH 	36    	B36TC       	1151609	CE  										ENGINE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	25	978JG	149  				EA637				TURBOCHARGER LEAKING OIL.  (X)						1	L	7	1 	3O			 	3A15    					 
2001022300057	20010223	00057	CE  	2001	2	23	20001218SH035    	1	20000619	G	3221	07421802	BUSHING         			CESSNA	185   	A185F       	2072821	CE  										TAILWHEEL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	267  				18503173				TAILWHEEL TO AFT BULKHEAD SUPPORT BUSHINGS FOUND SEVERELY WORN.  SUBMITTER STATED NEW PARTS OBTAINED FROM CESSNA APPEAR 	TO BE MADE FROM INFERIOR MATERIALS.  (X)					1	H	7	1 	3O			 	3A24    					 
2001022300058	20010223	00058	CE  	2001	2	23	20001218SH036    	1	20000624	G	3221	07421802	BUSHING         			CESSNA	185   	A185F       	2072821	CE  										TAILWHEEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	93055	40   				18503173				ON INSPECTION OF TAILWHEEL SUPPORT BUSHINGS, FOUND NEWLY INSTALLED BUSHINGS SEVERELY WORN, EXTRUDED AND CRACKED.  THESE 	BUSHINGS, OBTAINED FROM CESSNA, ARE MADE OF INFERIOR MATERIALS.  (X)					1	H	7	1 	3O			 	3A24    					 
2001021400066	20010214	00066	CE  	2001	2	14	20001219SH011    	1	20001201	G	5523	9661000668	ATTACH FITTING  			BEECH 	55    	E55         	1152732	CE  										ELEV TRIM TAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1025T	3475 				TE950				STEEL HORN WITH BRAZED IN BUSHING CRACK ON HORN ONLY NOT INTO BUSHING.  CAUSE UNKNOWN.  (X)						1	L	7	2 	3O			 	3A16    					 
2001022300059	20010223	00059	SO  	2001	2	23	20001219SH013    	1	20001128	G	2140	AD23D0475	REGULATOR       	JANITROL    		PIPER 	PA31  	PA31350     	7103110	SO  										FWD HEATER	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	4501B					318052168				INSTALLED NEW FUEL REGULATOR SHUT-OFF VALVE.  AFTER SEVERAL MINUTES OF OPERATION, VALVE BEGAN LEAKING AT BODY HALF.  REM	OVAL AND INSPECTION REVEALED ALL FOUR SCREWS THAT HOLD BODY HALF TOGETHER TO BE LOOSE WITH TORQUE SEAL IN PLACE.  TIGHTE	NED SCREWS AND RE-TESTED.  VALVE STILL LEAKED.  REPLACED VALVE WITH NEW UNIT.  SUBMITTER SUSPECTED IMPROPER TORQUE USED 	AT ASSEMBLY.  (X)			1	L	7	2 	3O			 	A20SO   					 
2001021400068	20010214	00068	SO  	2001	2	14	20001219SH014    	1	20001128	G	2140	A23D0475	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4501B	17   				318052168				FUEL OBSERVED DRIPPING FROM DRAIN LINE.  AFTER GROUND RUN OF ENGINE WITHOUT HEATER BEING USED.  VALVE WAS REMOVED FROM A	IRCRAFT AND 30 PSI SHOP AIR WAS APPLIED TO INLET WITHOUT POWER TO OPEN VALVE.  LEAK CHECK FLUID WAS APPLIED TO VALVE BOD	Y AND LEAK WAS FOUND COMING FROM UNUSED MOUNTING HOLE ON VALVE BODY.  (X)				1	L	7	2 	3O			 	A20SO   					 
2001021400069	20010214	00069	NE  	2001	2	14	20001219SH015    	2	20001204	G	7323	430121204	GOVERNOR        			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 1 ENGINE	FAILED          	G			RMXA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	05	460H	1815 				7142	LE45700			IN CRUISE FLIGHT, NR 2 ENGINE TORQUE DROPPED TO 20 PERCENT, N1 STABILIZED AT 82 PERCENT.  BEEPED NR 2 ENGINE UP, CONTINU	ED FLIGHT, LANDED WITHOUT INCIDENT.  FOUND THE NR 1 ENGINE HIGH SIDE GOVERNOR HAD FAILED.  (X)					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001021400070	20010214	00070	CE  	2001	2	14	20001219SH016    	1	20001207	G	2720	24670013	TORQUE TUBE     			CESSNA	172   	172RG       	2072438	CE  										LT PEDAL UPRIGHT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4802R	6237 				172RG0035				PILOT''S LEFT RUDDER PEDAL REPORTED AS ''NOT WORKING''.  FOUND RUDDER PEDAL SUPPPORT POST BROKEN OFF RUDDER PEDAL TORQUE	 TUBE.  MAINTENANCE REMOVED AND REPLACED ENTIRE TORQUE TUBE ASSEMBLY, LINKAGES, BEARING BLOCKS, AND HARDWARE (BOTH SIDES	).  (X)				1	H	7	1 	3O			 	3A17    					 
2001021500107	20010215	00107	NE  	2001	2	15	20001219SH019    	1	20000629	G	6420	6511207101041	ARM             	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  										TAIL ROTOR HEAD	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	164AC		1432 		A9028	64034D				ARM ASSEMBLY HAD CRACK INDICATION ON OUTBOARD MOUNTING LUG EXTENDING FROM .256 INCH/.252 INCH DIAMETER THROUGH-HOLE TO .	34 INCH RADIUS.  CIRCUMSTANCES UNDER WHICH CRACKING OCCURRED ARE UNKNOWN.  POSSIBLE CAUSE IS FROM FRETTING MOVEMENT BETW	EEN SLEEVE MOUNTING EARS, AND ARM ASSEMBLY MOUNTING LUGS.  ALL THROUGH-HOLES OF BOTH SLEEVE AND ARM ASSEMBLY MEET BLUEPR	INT REQUIREMENTS OF .256 INCH/.252 INCH DIAMETER.  (X)			2	G	7	2 	4U			 	H4EA    					 
2001021500108	20010215	00108	NE  	2001	2	15	20001219SH020    	1	20000721	G	6210	641520201049	BLADE           			SKRSKY	S64   	S64E        	8142604	NE  										MAIN ROTOR	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	176AC	5881 				64003				THE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY 360 DEGREES AT A 7	 O CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN).  THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFO	RMED IN THE FIELD.  (X)				2	G	7	2 	4U			 	H4EA    					 
2001021500109	20010215	00109	NE  	2001	2	15	20001219SH021    	1	20000710	G	3213	646550152103	HOUSING         	SKRSKY      		SKRSKY	S64   	S64E        	8142604	NE  										MLG	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	218AC					64033				MAIN LANDING GEAR, PN 6425-50100-013, -014, WAS REMOVED FOR OVERHAUL.  DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTI	ON PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREM	ENTS OF .093 INCH TO .360 INCH IN LENGTH.  THE INDICATIONS ARE LOCATED AT THE LIGHTENING HOLES WITH SOME BREAKING THE ED	GE OF THE HOLE.  A SECOND MLG WAS ALSO INSPECTED AND 7 LINEAR INDICATIONS NOT VISIBLE TO THE NAKED EYE WITH MEASUREMENTS	 OF .171 INCH TO .531 INCH IN LENGTH, WERE FOUND ON THE LOWER COLLAR HOUSING.  (X)		2	G	7	2 	4U			 	H4EA    					 
2001021400072	20010214	00072		2001	2	14	20001219SH023    	4	20001010	G	2211	7004206901	COMPUTER        			BOLKMS	117   	BK117B1     	5626012	EU  										CSAS	MALFUNCTIONED   	B			R7MR	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			NM	07	62LF	129  				7163				COMPUTER GOES OFF-LINE DURING FLIGHT.  PILOT IS ABLE TO RESET.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  (X)						1	G	7	2 	3U			 	H13EU   					 
2001021400073	20010214	00073	SW  	2001	2	14	20001219SH024    	1	20001116	G	6310	406040516101	SHAFT           			BELL  	407   	407         	       	SW  										FWU	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	607AL	2492 			A4230	53264				DURING 2,500 HOUR OVERHAUL, SPLINES WERE WORN BELOW LIMITS.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001021500110	20010215	00110	SW  	2001	2	15	20001220SH001    	1	20001204	G	6510	206040320015	SHAFT           			BELL  	206   	206L3       	1182108	SW  										COOLER BLOWER	DAMAGED         	B			C68R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	288JB					51288				PILOT REPORTED AIRCRAFT MAKING UNUSUAL NOISE.  ON INSPECTION, FOUND FORWARD BEARING RETAINING NUT ON OIL COOLER BLOWER S	HAFT HAD LOST TORQUE.  LOCKING WASHER WAS FULLY ENGAGED AND INTACT, ON DISASSEMBLY, FOUND AFT FACE OF BEARING INNER RACE	 GROOVED AND DAMAGED BEYOND LIMITS.  BOARING INNER RACE HAD ROTATED ON SHAFT CAUSING WEAR ON SHAFT JOURNAL IN EXCESS OF 	LIMITS.  REPLACED SHAFT, BEARING, NUT AND LOCKING WASHER.  (X)			1	G	7	1 	3U			 	H2SW    					 
2001021400076	20010214	00076	EA  	2001	2	14	20001220SH005    	2	20000923	G	7414	6351	GEAR            	SLICK       		GULSTM	114   	114B        	O145001	SW  	LYC   	O540  	IO540T4B5   	41532	EA  					MAGNETO	WORN            	G			HUNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	664H	595  				14664				NYLON DRIVE GEAR WORN AND DECOMPOSED DUE TO WATERY CHEMICAL WITHIN MAGNETO CASE.  COULD HAVE BEEN CAUSED BY A PRESSURE W	ASHER AFTER AN OIL CHANGE OR OTHER SERVICE OR MAINTENANCE.  (X)					1	L	7	1 	3O	3	O	RT	A12SO   	1E4				 
2001020900121	20010209	00121	CE  	2001	2	9	20001220SH006    	1	20001130	G	2400	604H193	RELAY           			CESSNA	310   	310R        	2074245	CE  										BATTERY BOX	FAILED          	E			BGJA	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			GL	27	6832Y					310R2121				UPON DESCENT, A HEAVY LOAD WAS APPLIED TO THE ELECTRICAL SYSTEM CAUSING THE MASTER RELAY TO FAIL.  SUBSEQUENT PARTIAL PO	WER LOSS TO THE CABIN RESULTED.  THIS REPORT IS FOR C/W FAR 135.415 AND AFS OPS MANUAL 5.9.					1	L	7	2 	3O			 	3A10    					 
2001021400077	20010214	00077	CE  	2001	2	14	20001220SH007    	1	20001214	G	5330		SKIN            			CESSNA	206   	TU206A      	2073318	CE  										FUSLEAGE	CORRODED        	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	81608					U2060652				DURING AVIONICS RETROFIT, CORROSION NOTICED IN THE HORIZONTAL STABILIZER.  FURTHER INSPECTION FOUND 85 PERCENT OF THE RU	DDER ASSY WITH MAJOR CORROSION AND CABIN ROOF AREA AND MAIN WING SPAR ATTACHMENT POINTS. THIS AIRCRAFT SPENT MOST OF ITS	 LIFE IN FLORIDA AND PUERTO RICO.  NO PROVISION IS MADE BY MANUFACTURER TO INSPECT MANY OF THESE AREAS.  SUBMITTER SUGGE	STED SMALL INSPECTION HOLES BE MADE AND BORESCOPED.  (X)			1	H	7	1 	3O			 	A4CE    					 
2001021500111	20010215	00111	GL  	2001	2	15	20001220SH008    	2	20001201	G	7323	355A57247221	SPRING          			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					GOV RETENTION	BROKEN          	B			SZTR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	911NW					5082	CAE840415			DURING ROUTINE FLIGHT, PILOT EXPERIENCED A RAPID YAW TO THE RIGHT.  NR 2 ENGINE, SN CAE-840415, SPOOLED DOWN TO FLIGHT I	DLE AS THE RESULT OF THE NR 2 ENGINE GOVERNOR RETENTION SPRING FAILURE.  GOVERNOR RETENTIONS SPRING WAS REPLACED.  AIRCR	AFT RETURNED TO SERIVCE.  (X)				1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001021300017	20010213	00017	EA  	2001	2	13	20001222SH001    	2	20001107	G	7322	666943	FLOAT           								LYC   	O540  	O540J3C5    	41532	EA  					CARBURETOR	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11			142  		75058101		L2121140A			CARBURETOR FLOAT FILLED UP PART WAY WITH AVIATION FUEL CAUSING VERY RICH FUEL MIXTURE REDUCING ENGINE POWER.  (X)											3	O			E295				 
2001021300018	20010213	00018	SW  	2001	2	13	20001222SH005    	1	20001211	G	2910		FITTING         			GULSTM	112   	112TCA      	7630307	SW  										RT MLG	BROKEN          	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	4590W					13180				RIGHT MAIN GEAR INBOARD HYDRAULIC FITTING BROKE.  COMPLETE LOSS OF HYDRAULIC FLUID, FITTING WAS RUBBING ON WING SPAR SUP	PORT BRACKET.  THIS FAILURE HAPPENED AT 20 INCHES BELOW AIR TEMP.  (X)					1	L	7	1 	3O			 	A12SO   					 
2001021300019	20010213	00019		2001	2	13	20001222SH006    	4	20001206	G	6122	B20107	GEAR            	MCAULY      																PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										RELEVANT MAGNETIC PARTICLE INDICATION ON TEETH AREA OF IDLER GEAR.  (X)																			 
2001021300020	20010213	00020	CE  	2001	2	13	20001222SH007    	1	20001214	G	2110		SEAL            	GODFREY     		BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  					SUPERCHARGER	LEAKING         	E			IJAA	C				ABORTED TAKEOFF         				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		TX	TAXI/GRND HDL  	1			CE	07	777KU	1884 			35493	LJ377	PCE21609			PILOT ABORTED FLIGHT DUE TO SMELL OF SMOKE IN CABIN.  FOUND SUPERCHARGER SEAL LEAKING OIL INTO AIRCRAFT SILENCER.  THIS 	MIXTURE OF OIL AND BLEED AIR CAUSED SMOKE TO ENTER CABIN.  (X)					1	L	7	2 	3T	3	T	 	3A20    	E4EA				 
2001021300021	20010213	00021	GL  	2001	2	13	20001222SH008    	3	20001110	G	6114	B32811	SPRING          			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER HUB	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	13916		600  			274551		901		PROPELLER WAS LEAKING GREASE. DURING TEAR DOWN FOUND WATER IN HUB.  WATER HAD CORRODED SPRING.  SPRING SUBSEQUENTLY BROK	E INTO FOUR PIECES.  ALSO, FOUND BOTH BLADE SHANKS SERIOUSLY CORRODED IN AREA ADDRESSED BY AD 77-12-06.  LAST DOCUMENTED	 OVERHAUL ON PROP WAS 10/85.  (X)				1	L	7	2 	3O			 	1A10    		5	C	P9EA	 
2001021300022	20010213	00022	NE  	2001	2	13	20001222SH009    	2	20000912	G	8530	287177	CYLINDER        			CVAC  	340   	34032       	2422706	WP  	PWA   	R2800 	R280083A    	52026	NE  					NR 5	CRACKED         	H				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			SW	17	3427		257  			90	30890			PILOT NOTED DROP IN BMEP AND ROUGHNESS ON DESCENT.  INSPECTION DISCOVERED NR 5 CYLINDER CRACKED 1.50 INCHES FROM  SPARK 	PLUG BOSS OUTWARD TOWARD CENTER OF HEAD.  (X)					2	L	7	2 	4R	4	R	 	6A6     	5E8				 
2001021300023	20010213	00023	NE  	2001	2	13	20001222SH010    	2	20001205	G	8530	11876	PUSHROD TUBE    			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 3 CYL EXH	BROKEN          	B			MU2R	E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CE	09	3629D	5187 	182  			743B	17718			AIRCRAFT WAS BEING TEST RUN FOLLOWING ENGINE FAILURE.  UPON RUN-UP, ENGINE STARTING MISSING AND WOULD NOT HOLD RPM OVER 	600.  AIRCRAFT WAS SHUT DOWN.  ALL ROCKER BOX COVERS WERE PULLED AND INSPECTION REVEALED THE NR 3 CYLINDER EXHAUST ROCKE	R PLAY WOULD GO FROM .010 INCH TO APPROXIMATELY .125 INCH AND A RATTLE WAS ALSO HEARD.  UPON REMOVAL OF THE PUSH ROD TUB	E, FOUND THE TOP END OF THE ASSY HAD BROKEN IN THE AREA WHERE THE TUBE SLIDES INTO THE END FITTING CAUSING THE ENGINE TO	 MALFUNCTION.  (X)		1	Q	7	1 	3R	3	R	 	1A16    	5E2				 
2001021300024	20010213	00024	SO  	2001	2	13	20001222SH011    	1	20001220	G	3230	105476	POWERPACK       			PIPER 	PA28  	PA28R200    	7102811	SO  										EMPENAGE	FAILED          	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SO	01	4875T		399  			28R7235129				GEAR WOULD NOT RETRACT IN AIR, AND WOULD NOT GO DOWN AND LOCKED.  PUT AIRCRAFT ON JACKS, AND GEAR WOULD NOT CYCLE.  FOUN	D CIRCUIT BREAKER TRIPPED.  RESET BREAKER, GEAR COULD COME UNLOCKED, BUT WOULD NOT GO UP, AND GEAR WOULD NOT LOCK DOWN. 	 PUMP DID NOT HAVE PRESSURES IAW PIPER MANUAL.  REMOVED POWER PACK FOR OVERHAUL, REINSTALLED AFTER OVERHAUL, GEAR CYCLED	 NORMAL.  (X)			1	L	7	1 	3O			 	2A13    					 
2001020900122	20010209	00122	EA  	2001	2	9	20001222SH012    	2	20001222	G	8520	13S19648	GEAR            	LYC         		CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540AC1A5  	 	EA  					CRANKSHAFT	SPALLED         	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7273Q	438  				20608045	L2694348A			DURING INSP C/W AD 91-14-22 AND LYC SB 475 REV A, NO DAMAGE FOUND TO CRANKSHAFT COUNTERBORE RECESS, ALIGNMENT DOWEL, RET	AINING BOLTS AND THREADS.  UPON INSP OF CRANKSHAFT GEAR TEETH, SEVERAL WERE FOUND TO HAVE LINEAR PTTING WHICH APPEARED T	O BE CAUSED BY PLATING BREAKDOWN DEFECTS RESEMBLING FRETTING/SPALLING.  NO CRITERIA EXISTED IN BODY OF AD, MFG O/H MANUA	L, OR SB TO IDENTIFY SERVICEABLE LIMITS FOR DAMAGE FOUND ON TEETH, SO GEAR REPLACED.  IT NOTE:  THIS ENGINE MAINTAINED U	SING 50-HR OIL CHANGES/SAMPLE INTERVALS WITH NO EVIDENCE OF INTERNAL PROBLEMS TO THIS POINT.   RECOMMEND ADDITIONAL CRIT	ERIA BE ADDED TO SUPPORT  PARA (A) OF AD, SO A/W OF GEAR, SHOULD ANY DAMAGE BE FOUND, CAN BE DETERMINED.  (X)	1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2001021300015	20010213	00015	CE  	2001	2	13	20001227SH001    	1	20001222	G	3221		TRUNNION        			CESSNA	425   	425         	2076018	CE  										NLG	GROOVED         	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	111SU	2791 				4250205				FOUND TWO SMALL GROOVES WORN INTO THE NOSE GEAR UPPER TRUNNION WHERE THE DRAG BRACE ATTACH LINK CONNECTS TO THE UPPER TR	UNNION.  THE FORWARD END OF THE ATTACH LINK WAS MAKING CONTACT WITH THE UPPER TRUNNION DURING NORMAL OPERATION.  FOUND B	EARING IN ATTACH LINK WAS GOOD.  NO PLAY WAS EVIDENT.  REMOVED NOSE GEAR.  REMOVED UPPER TRUNNION AND PERFORMED NDT INSP	ECTION OF AFFECTED AREA.  NO DEFECTS WERE NOTED.  BLENDED OUT SMALL GROOVES,  TREATED AND PRIMED AREA.  RECOMMEND INSPEC	TING THIS AREA ANYTIME THE DRAG BRACE IS DISCONNECTED FROM THE UPPER TRUNNION.  (X)		1	L	7	2 	3T			RT	A7CE    					 
2001021300016	20010213	00016	SW  	2001	2	13	20001227SH002    	1	20001222	G	8120	4078109001	TURBOCHARGER    			MOONEY	M20   	M20K        	5870220	SW  										ENGINE	FAILED          	B			EBVR	B	A			EMER. DESCENT           	UNSCHED LANDING         			R	K		PARTIAL RPM/PWR LOSS      	FLUID LOSS                		CR	CRUISE         	1			GL	09	5269R					251188				OPERATOR WAS CRUISING AT FL 210 WHEN A LOUD NOISE OCCURED FOLLOWED BY AN IMMEDIATE PARTIAL REDUCTION IN POWER.  THE OPER	ATOR BEGAN IMMEDIATE DESCENT AND VECTORED TO NEAREST AIRPORT FOR LANDING.  UPON INVESTIGATING PROBLEM, THE TURBO SHAFT W	AS FOUND TO HAVE FAILED AND THE TURBO IMPELLER MOVED AGAINST THE HOUSING AND SHEARED SEVERAL BLADES.  MOST OF THE AIRCRA	FT''''S OIL WAS LOST OVERBOARD.  FOUND METAL IN THE INTERCOOLERS AND FILTER ASSEMBLY.  TURBO ASSEMBLY WAS REMOVED AND SE	NT TO OEM.  ENGINE WAS REMOVED AND SENT OUT FOR INSPECTION.  NO DEFINITE CAUSE FOR THE FAILURE HAS BEEN DETERMINED AT TH	IS WRITING.  (X)	1	L	7	1 	3O			 	2A3     					 
2001011101324	20010111	01324	CE  	2001	1	11	20001227SH003    	1	20001222	G	2571	0553022	RACK            			CESSNA	172   	172S        	2072439	CE  										BATTERY	CRACKED         	B			EIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	428SA	194  	49   			172S8547				THE BATTERY MOUNT RACK WAS FOUND CRACKED AND BROKEN AT ITS LOWER, OUTBOARD ATTACH POINT WHERE IT IS SECURED TO THE FIREW	ALL.  THE CRACK OCCURRED AT THE BEND RADIUS OF THE LOWER SINGLE FLANGE OR TAB.   SUBMITTER SUGGESTED CAUSE FOR THE CRACK	 IS THE FIREWALL IS NOT REINFORCED IN THAT AREA.   THERE IS A STIFFENER ANGLE ON THE AFT SIDE OF THE FIREWALL THAT RUNS 	DIAGONALLY FROM THE LOWER, INBOARD TO UPPER, OUTBOARD OF THE BATTERY RACK ATTACHMENT AREA, AND THE UPPER, INBOARD, FORWA	RD CORNER OF THE BATTERY RACK IS SUPPORTED BY THE ENGINE MOUNT TUBE WITH AN ADEL CLAMP, BUT THERE IS NOTHING TO HELP THE	 OUTBOARD LOWER RACK ATTACH AREA SUPPORT THE LOAD DURING LANDING OR TURBULENCE.  THE BATTERY RACK WAS REPLACED.  (X)	1	H	7	1 	3O			NT	3A12    					 
2001021300026	20010213	00026	EA  	2001	2	13	20001227SH007    	2	20001119	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					NR 4 CYLINDER	FAILED          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	27	6772W	601  				2820899	L1514627A			STUDENT PILOT SOLD X-C - ENGINE FAILURE.  LANDED SAFELY IN FIELD.  NR 4 CYLINDER EXHAUST VALVE STEM FOUND BROKEN NEXT TO	 VALVE FACE.  PISTON PIN PLUG ALSO FOUND WORN APPROXIMATELY .050 INCH.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001021300027	20010213	00027	CE  	2001	2	13	20001227SH008    	1	20000801	G	3230	1693800573	UPLOCK          			BEECH 	23    	C24R        	1151254	CE  										LT MLG	CORRODED        	H				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			SO	15	1831N	2323 				MC763				PILOT ATTEMPTED EXTENDING THE LANDING GEAR AFTER A NORMAL FLIGHT; WHEN THE LT MAIN LANDING GEAR WOULD NOT EXTEND, PILOT 	MADE SEVERAL ATTEMPTS WITH BOTH THE NORMAL AND THE EMERGENCY SYSTEMS TO BRING DOWN THE GEAR.  THE PILOT MADE A GEAR UP L	ANDING.  AFTER LIFTING THE AIRCRAFT FROM THE RUNWAY, FOUND THE LT GEAR UPLOCK WOULD NOT RELEASE.  PRYING THE UPLOCK ARM 	AWAY FROM THE GEAR ALLOWED THE GEAR TO FREEFALL INTO THE GEAR DOWN AND LOCKED POSITION.  A GEAR DOWN OF THE UPLOCK WAS P	ERFORMED.  SHAFT WAS FOUND RUSTED AND CYL HEAD, WHICH THE SHAFT RUNS THROUGH, TO BE CORRODED CAUSING THE UPLOCK CYLINDER	 TO SEIZE.  (X)	1	L	7	1 	3O			 	A1CE    					 
2001022000128	20010220	00128	EA  	2001	2	20	20001227SH010    	2	20001206	G	7414	1052947	MAGNETO         			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	15	127KH		16   		F280010ER	500B102738	L20548			PRE-FLIGHT RUN UP MAGNET CHECK REVEALED MAGNETO DEAD.  POST-REPLACEMENT INSPECTION REVEALED EXCESSIVE.  RADIAL AND END P	LAY ON ROTATING MAGNET SHAFT POINTS WOULD NOT OPEN.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001021300029	20010213	00029	EA  	2001	2	13	20001227SH011    	2	20001205	G	7414	10349276REVG	CAPACITOR       			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					MAGNETO	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	1153C		372  		B12004ER	1474169	RL32948			PRE-FLIGHT RUN UP REVEALED EXCESS RPM DROP ON MAG CHECK.  POST-REPLACEMENT INSPECTION REVEALED POINTS BURNED AND CAPACIT	OR WIRE BROKEN AT CONNECTOR END.  (X)					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001021300030	20010213	00030	CE  	2001	2	13	20001227SH012    	1	20001207	G	2810	070009977	VENT LINE       			CESSNA	182   	182B        	2072706	CE  										CABIN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2711G	3776 				52011				DURING AN ANNUAL INSPECTION, THE FUEL TANK VENT CARRY-THROUGH WAS FOUND CORRODED THROUGH AT SEVERAL POINTS ALONG THE TUB	INGS LENGTH.  FUEL STAINS WERE ALSO VISIBLE.  THE VENT LINE WAS HIDDEN BEHIND A LAYER OF FIBERGLASS INSULATION.  THIS PA	RT CAN ONLY BE INSPECTED BY REMOVAL OF THE HEADLINER AND ANY INSULATION AT THIS LOCATION.  12				1	H	7	1 	3O			NT	3A13    					 
2001021300038	20010213	00038	GL  	2001	2	13	20001227SH030    	1	20000929	G	5540	AN43B	BOLT            			AMTR  	AEROCP	COMPMONST145	05602RF	GL  										RUDDER HINGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	6162A	206  				96107				HINGE BOLTS WERE FOUND LOOSE DURING ANNUAL INSPECTION.  REMOVED RUDDER AND HINGE BOLTS, ROTATED.  CALLED COMP AIR PER PR	OCEDURE TO TIGHTEN TORQUE ETC.  CUT HOLES IN RUDDER TO ACCESS NUTS.  FOUND RUST AND CORROSION.  REMOVED NUTS AND AN43B H	INGE BOLTS.  TOP BOLT MINIMAL RUST AND CORROSION, CENTER AND LOWER, FOUND SEVERE RUST AND CORROSION ON SHANKS AND NUTS. 	 (X)			1	H	7	1 	30			NC	EXPA1H71					 
2001021300040	20010213	00040	GL  	2001	2	13	20001227SH032    	1	20000902	G	3213		AXLE            			AMTR  	F2SPEC	F2SPECIAL   	05604C5	GL  										LT WHEEL	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	17	521S	47   				002GM				ON LANDING, LEFT AXLE FAILED CAUSING AIRCRAFT STRUT TO DIG INTO GRASS FIELD.  AIRCRAFT FLIPPED ON ITS BACK CAUSING SUBST	ANTIAL DAMAGE.  PRELIMINARY INSPECTION INDICATED A FAILED WELD ON THE AXLE TO STRUT BRACKET.  (X)					1	H	7	1 	  			 	EXPA1H71					 
2001021300041	20010213	00041	SW  	2001	2	13	20001227SH033    	1	20001211	G	7920		HOSE            			MOONEY	M20   	M20A        	5870204	SW  										OIL COOLER	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	13	6099X	300  				1700A				OPERATOR REQUESTED MECHANIC TO TRY AND LOCATE AN OIL LEAK IN ENGINE COMPARTMENT.  AFTER INVESTIGATING, THE OIL COOLER HO	SE WAS FOUND TO HAVE A SMALL HOLE IN THE EXTERIOR AROUND MIDWAY OF THE HOSE.  (X)					1	L	7	1 	3O			 	2A3     					 
2001021300042	20010213	00042	EA  	2001	2	13	20001227SH034    	2	20001211	G	8520		CAMSHAFT        			AMRGEN	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	26993	1317 				AA5A0866	L4876327A			CYLINDERS 2 AND 4 REMOVED DUE TO LOW COMPRESSION.  AT THIS TIME, THE CAMSHAFT WAS FOUND SEVERELY PITTED, ONE LOBE WAS FL	AT.  LIFTER BODIES WERE ALSO PITTED.  1,317.0 HOURS, TOTAL TIME.  (X)					1	L	7	1 	3O	3	O	 	A16EA   	E274				 
2001021300043	20010213	00043	SO  	2001	2	13	20001228SH001    	1	20001211	G	7820		MUFFLER         			AMRGEN	AA5   	AA5A        	3960106	SO  										EXHAUST	DETERIORATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	26993	1317 				AA5A0866				DURING AN ANNUAL INSPECTION, THE MUFFLER ASSY WAS FOUND TO HAVE ITS WALLS SEVERELY DETERIORATED AND THE BAFFLES LOOSE.  	(X)					1	L	7	1 	3O			 	A16EA   					 
2001021300044	20010213	00044	SO  	2001	2	13	20001228SH002    	2	20001211	G	7310		HOSE            			CESSNA	140   	140         	2071602	CE  	CONT  	C85   	C8512       	17008	SO  					CARBURETOR	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	13	1888V					14068				DURING ANNUAL INSPECTION, THE FLEXIBLE FUEL HOSE WAS FOUND WET WITH FUEL NEAR ONE OF THE FITTINGS.  THE HOSE WAS NOT THA	T OLD AND WAS MADE IN THE FIELD.  (X)					1	H	7	1 	3O	3	O	NC	A768    	E233				 
2001021300045	20010213	00045		2001	2	13	20001229SH001    	4	20001214	G	2561	AV8AS2100	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOTATION DEVICE FAILED THE MANUFACTURER''S RECOMMENDED 2 PSI CELL TEST IAW 25-60-33.  ITEM DATE OF MFG:  AUG	 1987.  FAIR WEAR AND TEAR.  (X)																		 
2001021300046	20010213	00046		2001	2	13	20001229SH002    	4	20001214	G	2561	AV8AS2100	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										INDIVIDUAL FLOTATION DEVICE FAILED MANUFACTURER''S RECOMMENDED TWO PSI CELL TEST IAW 25-60-33.  ITEM DATE OF MFG:  AUG 1	987.  FAIR WEAR AND TEAR.  (X)																		 
2001021300047	20010213	00047	GL  	2001	2	13	20001229SH003    	3	20001201	G	6111		BLADE           			MULTEC	D16   	D16A        	9230604	WP  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			FR6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	708T					TTN77		K1428N		DISASSEMBLY OF PROPELLER FOR O/H AND AD COMPLIANCE REVEALED BLADE, SN 106993, IS SCRAP BECAUSE BALANCE HOLE TOO DEEP.  M	AX DEPTH IS 6.5 INCHES.  BLADE, SN A27681, IS SCRAP BECAUSE IT IS CRACKED IN THE SHANK.  BREAKAWAY TEST PERFORMED TO PUS	H THE TUBE BACK IN THE HUB.  TEST ONLY NEEDED 2200 PSI TO BREAK IT AWAY.  6000 PSI IS THE MIN PRESSURE REQUIRED FOR THE 	TEST AND IF TUBE MOVES, IT MUST BE REMOVED AND NEW TUBE INSTALLED.  BLADE THRUST BEARINGS PN A14B THAT WERE INSTALLED FO	R THE BLADES HAD WRONG RETAINERS PN A159.  S/B REPLACED WITH PN A969.  COULD HAVE CAUSED BLADE SEPARATION.  RETAINER PN 	A159 S/B REPLACED WITH A159N PER AD 59-01-03.  (X)	1	L	7	2 	3O			 	2A1     		5	C	P23EA	 
2001021300048	20010213	00048	GL  	2001	2	13	20001229SH004    	3	20001201	G	6111		BLADE           			MULTEC	D16   	D16A        	9230604	WP  						HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			FR6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	708T					TTN77		K2013N		PROPELLERS REMOVED FOR OVERHAUL AND AD COMPLIANCE.  BLADE SN 93464 IS SCRAP BECAUSE IT IS CRACKED IN THE SHANK.  ONE OF 	THE BLADE THRUST BEARINGS PN A14B INSTALLED FOR THE BLADES HAD WRONG RETAINERS PN A159.  S/B REPLACED WITH PN A969.  COU	LD CAUSE BLADE SEPARATION.  THE OTHER BLADE THRUST BEARING IS PN A14A WHICH IS STILL GOOD.  SHOULD HAVE HAD RETAINER PN 	A159N INSTALLED.  THRUST BEARINGS A14A AND A14B BOTH SERVICEABLE BEARINGS, BUT SHOULD BE ALL THE SAME IN PROP ASSY (RETA	INER PN A159 SHOULD HAVE BEEN REPLACED WITH A159N PER AD 59-01-03).  (X)		1	L	7	2 	3O			 	2A1     		5	C	P23EA	 
2001021300049	20010213	00049	SO  	2001	2	13	20001229SH005    	1	20001207	G	3211	6704204	TRUNNION        			PIPER 	PA34  	PA34200     	7103405	SO  										LT MLG	BROKEN          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	09	1390T					347250274				NO LOG BOOKS WITH A/C.  RT TACH:  1,993.5 HRS.  HM-2,232.1 HRS.  LEFT MAIN GEAR SEPARATED FROM A/C WHILE BEING TAXIED AF	TER LANDING.  FAILURE BELIEVED TO BE CAUSED BY REAR TRUNNION ASSY WITH CRACKS/BREAKS AT 3 OF 4 ATTACH AREAS.  WHEN FINAL	 ATTACH AREA FAILED, THIS ALLOWED GEAR TO DAMAGE FORWARD ATTACH AND GEAR TO SEPARATE A/C.  RECOMMEND FORWARD AND AFT TRU	NNIONS BE INSPECTED AS MM REQUIRES DURING INSPECTION.  (X)			1	L	7	2 	3O			 	A7SO    					 
2001021300050	20010213	00050	EA  	2001	2	13	20001229SH006    	2	20001220	G	7230		COMPRESSOR      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENGINE	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CE	01	366EA	4421 	925  			BB841	PCE85097			JUST AFTER TAKEOFF, COPILOT REPORTED SPARKS COMING FROM RT ENGINE INBOARD AND OUTBOARD EXHAUST STACKS.  POWER WAS REDUCE	D AND AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT.  INSPECTION THROUGH THE HIGH AND LOW BLEED VALVE OPENINGS REVEALED 	MASSIVE COMPRESSOR FAILURE.  ENGINE REMOVED AND SENT FOR REPAIR.  (X)				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001021300052	20010213	00052	SO  	2001	2	13	20001229SH008    	2	20001218	G	8520	630826	BEARING         			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470L      	17026	SO  					CONNECTING ROD	DELAMINATED     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	349Y	8    				TC389	297805RCS			ENGINE WAS DISASSEMBLED FOR PROPELLER STRIKE INSPECTION, FOUND NR 6 ROD BEARING SURFACE MATERIAL DELAMINATING FROM BEARI	NG EXPOSING BABBITT MATERIAL AND REMAINING BEARINGS SHOWING SIGNS OF THIS CONDITION FORMING ON THEM.  ALL BEARINGS WERE 	SENT TO TELEDYNE CONTINENTAL MOTORS FOR ANALYTICAL INSPECTION.  THESE BEARINGS WERE REMOVED FROM A TELEDYNE CONTINENTAL 	MOTORS FACTORY REMANUFACTURED WITH 8.3 TOTAL HOURS AND 12 MONTHS FROM INSTALLATION DATE.  (X)			1	L	7	2 	3O	3	O	 	3A16    	3E1				 
2001030600018	20010306	00018	CE  	2001	3	6	20001229SH010    	1	20001229	G	3230	12810331	ACCUMULATOR     			CESSNA	210   	210L        	2073448	CE  										MLG	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	60617					21060595				FOUND ACCUMULATOR LEAKING.  CLEANED AND CYCLED GEAR.  FOUND ACCUMULATOR LEAKING FROM CRACK IN MACHINED CASTING SEAM.  CR	ACK IS ONLY VISIBLE WITH 10X MAGNIFICATION.  CAUSE - POSSIBLE CASTING FLAW.  (X)					1	H	7	1 	3O			 	3A21    					 
2001030600019	20010306	00019	EA  	2001	3	6	20001229SH011    	2	20001214	G	7322	30766	FLOAT           			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235C1      	41505	EA  					CARBURETOR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	9699S	472  			Y202371	430	L890015			CARBURETOR WAS OVERFILLING.  UPON DISASSEMBLY, FOUND CARBURETOR GASKET, PN 16-B85, SAGGING AND THE METAL FLOAT, WHERE TH	E NEEDLE SEAT RUBS, WORN EXCESSIVELY AT THE FLOAT LEVER ADJUSTMENT TAB.  (X)					1	H	7	1 	3O	3	O	 	A759    	E223				 
2001030600020	20010306	00020	CE  	2001	3	6	20001229SH012    	1	20000925	G	3213	2500404511	STRUT           			HELIO 	H295  	H295        	4300802	CE  										RT MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	03	993PT					1451				UPON LANDING, THE AIRCRAFT EXPERIENCED SOME VIBRATION AND SHORTLY AFTER, THE RIGHT MAIN LANDING GEAR STRUT BROKE.  THE F	AILURE OCCURRED HALF WAY DOWN THE LEG, A 2.25 INCH SQUARE CONSTRUCTED OF 0.132/4130 STEEL.  THE LANDING GEAR IS BEING EV	ALUATED.  (X)				1	H	7	1 	3O			 	1A8     					 
2001021500112	20010215	00112	SW  	2001	2	15	20001229SH014    	1	20001206	G	6410	406016100119	BLADE           	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2778 			A95	53044				DURING DAILY INSPECTION, BLADE CRACKED AT WEEP HOLE, ON THE INBOARD LEADING EDGE.  CRACK EXTENDED AFT FOR ABOUT 1.50 INC	HES.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001021500113	20010215	00113	SW  	2001	2	15	20001229SH015    	1	20001205	G	6410	406016100119	BLADE           			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	E			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	2720 	278  			53172				DURING DAILY INSPECTION, BLADE CRACKED AT WEEP HOLE, ON THE INBOARD LEADING EDGE.  CRACK EXTENDED AFT FOR ABOUT 1.25 INC	HES.  (X)					1	G	7	1 	3U			O	H2SW    					 
2001021500116	20010215	00116	EU  	2001	2	15	20001229SH019    	1	20001214	G	2432		BRACKET         			SNIAS 	350   	AS350B2     	8680813	EU  										BATTERY BOX	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4035W	441  				2912				DURING A 100-HOUR INSPECTION, FOUND THE FORWARD BATTERY HOLD-DOWN BRACKET PN G10110 AND THE AFT BATTERY HOLD-DOWN BRACKE	T PN G10115 WERE BADLY WORN AT THE SLOTS THAT HOLD THE BATTERY IN PLACE.  THERE ARE 3 AIRCRAFT WITH THE SAME STC INSTALL	ING THE BATTERY IN THE TAIL BOOM AND ALL SHOW THE SAME PROBLEM WITH THE BRACKET WEAR.  WHEN ORDERING REPLACEMENT BRACKET	S, THE HOLES DO NOT MATCH THE ATTACH POINTS IN THE AIRCRAFT.  EVEN THROUGH ALL AIRCRAFT HAVE THE SAME STC, AEC SAYS THER	E ARE AT LEAST 2 CHANGES TO THE DRAWINGS AND THAT THEY ARE WORKING ON THE PROBLEM OF HOW TO FIGURE OUT WHAT PART GOES TO	 WHAT CHANGE IN AIRCRAFT.  TT:  2,571.3 HOURS.  (X)	1	G	7	1 	3U			 	H9EU    					 
2000011500646	20000115	00646	EA  	2000	1	15	2000ZZZX117      	2	20000113	G	7322		ID PLATE        	DONALDSON   	P107172     	MAULE 	M4    	M4220       		SO  	FRNKLN	6AV350	6A350C1     	27043	EA  					CARBURETOR	LOOSE           	B		A		O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			WP	25	11EN				C2945100301	2037				IDENTIFICATION STICKER CAME LOOSE AND LODGED AGAINST CARBURETOR VENTURI.  STICKER WAS STUCK IN CARBURETOR HEAT BOX AND W	AS NOT SEEN WHEN NEW FILTER WAS INSTALLED.  SUBMITTER RECOMMENDED THAT IDENTIFICATION OF FILTER BE STAMPED ON OR ETCHED.					1	H	7	1 	3O	3	O		3A23    	E9EA				 
2000011500661	20000115	00661	EA  	2000	1	15	2000ZZZX132      	2	20000103	G	7310	LW127844274	MANIFOLD        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					FUEL INJECTION	LOOSE           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	14268					274828	L612148			FOUND FUEL LINE FITTING ON FUEL INJECTOR LOSE CAUSING FUEL STARVATION TO FUEL MANIFOLD.  TIGHTENED FITTING AND RETURNED 	TO SERVICE.					1	L	7	2 	3O	3	O		1A10    	1E4				 
2000011500666	20000115	00666	CE  	2000	1	15	2000ZZZX137      	1	20000114	G	2434	649304	ALTERNATOR      			BEECH 	36    	A36         	1151604	CE  										ENGINE	FAILED          	B			W45R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	07	3222B	143  				E3222				ALTERNATOR BOUND UP AND CAUSED THE DRIVE COUPLING TO SEIZE.  STRONG SMELL OF BURNED ELECTRICAL.						1	L	7	1 	3O				3A15    					 
2000012200355	20000122	00355	CE  	2000	1	22	2000ZZZX172      	1	20000106	G	3230	24411091	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  										LT MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	5284V	7365 				172RG0494				A 1 1/4 ALUMINUM SHAFT THT ATTACHES THE ACTUATOR TO THE LEFT MAIN GEAR STRUT FAILED UPON RETRACTION.  THIS RESULTED IN A	 CONDITION IN WHICH THE GEAR WAS HANGING OUT AND COULD NOT BE RETRACTED OR EXTENDED.  THE INSTRUCTOR HAD STUDENT HANG OU	T THE DOOR OF THE AIRCRAFT AND PULL THE GEAR FORWARD UNTIL IT LOCKED IN THE DOWN POSITION.  THE AIRCRAFT LANDED WITHOUT 	FURTHER INCIDENT.  THE ENDS OF THE BROKEN PART APPEAR TO HAVE FAILED IN FATIGUE.  THOUGH I AM NO METALURGIST, I THINK I 	SEE BEACH MARKS ON THE BROKEN SURFACE.		1	H	7	1 	3O				3A17    					 
2000012200384	20000122	00384	SW  	2000	1	22	2000ZZZX200      	1	20000103	G	2432		BATTERY         	GILLBATT    		MTSBSI	MU2   	MU2B        	5780404	SW  										BATTERY BAY	DISCHARGED      	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	36G					035				WHILE PERFORMING PERIODIC INSPECTION, FOUND MAIN BATTERIES HAD CASE DAMAGE CAUSED BY OVERHEATING.  ALSO, ELECTROLYTE MOS	TLY BOILED OUT.  AIRCRAFT ELECTRICAL SYSTEM TESTED OK.  BATTERIES SERVICED AND CHECKED 97 HRS PREVIOUSLY, OK PER MANUAL.	  FAILURE POSSIBLY DUE TO AGE. SUBMITTER SUGGESTED TIME CHANGE REQUIREMENTS BE REQUIRED OR MORE DETAILED IN-SERVICE INSP	ECTION CRITERIA BE REQUIRED (I.E., LOAD TEST) IN ORDER TO DETECT PENDING FAILURES.			1	H	7	2 	3T				A2PC    					 
2000012200385	20000122	00385	NM  	2000	1	22	2000ZZZX201      	1	20000104	G	3242	2445902	CARRIER         	BFGOODRICH  	21565       	DHAV  	DHC8  	DHC8*       		NM  										BRAKE	BROKEN          	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1012					BRAKE ASSY P/N 2-1565 FAILED PREMATURELY.  NR 1 CARRIER AND LINING ASSY BROKEN IN HALF.  THIS IS A CONTINUAL DISCREPANCY	.  OEM PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION P/N 2-1565.					2	H	7	2 	4T			RT	A13NM   					 
2000012200394	20000122	00394		2000	1	22	2000ZZZX210      	4	20000103	G	2215	40005238501	SERVO           			MTSBSI	MU2   	MU2B        	5780404	SW  										AUTOPILOT	FAILED          	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	36G				5463	035				AFTER REINSTALLING BENDIX AUTOPILOT SERVOS AFTER FACTORY OVERHAUL BY ALLIED SIGNAL CRS, ROLL CHANNEL INOPERABLE.  TROUBL	ESHOOTING REVEALED BAD SERVO.  TEAR DOWN SHOWED CLUTCHES CROSS-WIRES; THEREFORE, SERVO RAN THE OPPOSITE DIRECTION IT WAS	 SUPPOSED TO.				1	H	7	2 	3T				A2PC    					 
2000012200396	20000122	00396	CE  	2000	1	22	2000ZZZX212      	1	20000103	G	7830	L2020001A	LUG             			CESSNA	500   	550         	2076604	CE  										THRUST REVERSER	BROKEN          	B			R2JR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	24E	2927 				5500651				ON PRE-FLIGHT, CREW FOUND LEFT LOWER THRUST REVERSER DOOR HANGING DOWN.  MAINTENANCE FOUND LUGS BROKEN ON BLOCKER DOOR '	BIRDCAGE' ASSEMBLY.  FAILURE DUE TO IMPROPER BOLT ANTI-ROTATION DEVICE INSTALLATION PREVIOUSLY C/W.  BLOCKER DOOR POSSIB	LY WOULD HAVE LEFT AIRCRAFT ON NEXT FLIGHT.  THRUST REVERSER ASSY CHANGED.				1	L	7	2 	4F				A22CE   					 
2000012200397	20000122	00397	WP  	2000	1	22	2000ZZZX213      	2	20000103	G	7250	30720141	TURBINE BLADE   		30720152    	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	FAILED          	B			IY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	CGRIS	10452			LOT159	002	P73114			ONE EACH, THIRD STAGE LOW PRESSURE TURBINE BLADE FAILED DUE TO STRESS RUPTURE.  AIRCRAFT LANDED SAFELY.  POSSIBLE CAUSE 	WAS THE OPERATION OF BLADE IN EXCESS OF RECOMMENDED HOURS AS SET IN ALLIED SB 72-3494.  RECOMMEND ENGINE MFG INCLUDE TUR	BINE BLADES IN SB 72-300, 'SERVICE LIFE LIMITED OF CRITICAL LIFE LIMITED COMPONENTS' AS THIS BULLETIN IS THE ONLY MANDAT	ORY SB LISTED IN ENGINE TYPE CERTIFICATE DATA SHEET.			2	L	7	2 	4F	4	F		A33EU   	E6WE				 
2000012900233	20000129	00233		2000	1	29	2000ZZZX219      	1	20000106	G	3242	7010FS9545708	SEAL            		50105201    															BRAKE	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1704 			APR981278					BRAKE ASSEMBLY P/N 5010520-1 FAILED PREMATURELY.  THREE EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASS	EMBLY AND THE MOST RECENT BRAKE CONFIGURATION P/N 5010520-1.																	 
2000012900235	20000129	00235	GL  	2000	1	29	2000ZZZX221      	3	20000104	G	6110	B36634	COUNTERWEIGHT   			WSK   	M18A  	M18A        		EU  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	CRACKED         	B	S		M3PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	2296Y	2000 				1201827		BVA6450		FOUND DURING ROUTINE INSPECTION, CRACKED COUNTERWEIGHT.						1	L	7	1 	3O			NC	A47EU   		6	C	P15EA	 
2000012900237	20000129	00237	GL  	2000	1	29	2000ZZZX223      	3	20000104	G	6110	B36634	COUNTERWEIGHT   			WSK   	M18   	M18DROMADER 	9810102	EU  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	CRACKED         	B	S		M3PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	5168J	1345 				1200719		BVA6452		FOUND DURING MAINTENANCE INSPECTION, CRACKED COUNTERWEIGHT.						1	L	7	1 	3O				A47EU   		6	C	P15EA	 
2000012900244	20000129	00244	CE  	2000	1	29	2000ZZZX230      	1	20000125	G	2434	649304	ALTERNATOR      			BEECH 	36    	A36         	1151604	CE  										ENGINE	FAILED          	B			W45R	O				OTHER                   				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			WP	07	4486X	10   				E3286				ELECTRICAL FAILURE DUE TO INTERNAL ALTERNATOR FAILURE WITH STRONG SMELL OF ELECTRICAL.						1	L	7	1 	3O				3A15    					 
2000012900250	20000129	00250		2000	1	29	2000ZZZX236      	1	20000111	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1030 			JUN981391					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  ONE EACH PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSEM	BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000012900251	20000129	00251		2000	1	29	2000ZZZX237      	1	20000104	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1701 			AUG971057					BRAKE ASSEMBLY, P/N 5020520-1, FAILED PREMATURELY,  FIVE EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY F	ILLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INST	ALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000012900252	20000129	00252		2000	1	29	2000ZZZX238      	1	20000108	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		2174 			JAN981176					BRAKE ASSEMBLY, P/N 5010520-1 FAILED PREMATURELY.  ONE EACH PISTON LEAKING FROM INSULATOR AREA.  EVIDENCE OF T-SEAL FAIL	URE.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECEN	T BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000012900253	20000129	00253		2000	1	29	2000ZZZX239      	1	20000110	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1652 			APR981293					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSE	MBLY.																	 
2000012900254	20000129	00254		2000	1	29	2000ZZZX240      	1	20000107	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE	LEAKING         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1953 			JUN971000					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  THREE EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY 	FILLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  SUBMITTER STATED THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INS	TALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000012900260	20000129	00260	SW  	2000	1	29	2000ZZZX246      	1	20000107	G	6420	406312103101	PITCH LINK      			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	B			UNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		751  			NHF03257					BEARINGS WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2000012900261	20000129	00261	SW  	2000	1	29	2000ZZZX247      	1	20000107	G	6420	406312103101	PITCH LINK      			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	B			UNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		751  			NHF03235					BEARINGS WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2000020500923	20000205	00923	CE  	2000	2	5	2000ZZZX258      	1	20000202	G	5320	CM35753	SEAL            			CESSNA	500   	560CESSNA   	2076750	CE  										CABIN	DAMAGED         	B			JSNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	208PC	600  				5605005				DURING A SCHEDULED INSPECTION, THE TWO AFT MOISTURE DRAINS/SEALS, P/N CM3575-3, WERE FOUND DAMAGED AND TORN AND NOT DOIN	G A PROPER JOB DURING PRESSURIZATION.  FIRST TIME THE DRAIN SEALS HAD BEEN INSPECTED.  SEALS AND RETAINERS WERE REPLACED	.				2	L	7	2 	4F			RT	A22CE   					 
2000020500924	20000205	00924	CE  	2000	2	5	2000ZZZX259      	1	20000202	G	2621	661420027	TUBE            			CESSNA	500   	560CESSNA   	2076750	CE  										FIRE EXTINGUISH	LOOSE           	B	P		JSNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	207PC	573  				5605008				DURING SCHEDULED INSPECTION, B-NUT ON P/N 6614200-27 TUBE ASSY WAS BACKED OFF WITH ONLY ONE THREAD ENGAGED.  THIS IS THE	 FIRE EXTINGUISING TUBE FOR THE RIGHT ENGINE.  THIS IS FIRST INSPECTION SINCE AIRCRAFT LEFT FACTORY.  B-NUT RETORQUED.					2	L	7	2 	4F			RT	A22CE   					 
2000020500930	20000205	00930	EA  	2000	2	5	2000ZZZX265      	2	20000114	G	8530	SL36000	CYLINDER        								LYC   	O360  	O360A4K     	41514	EA  					ENGINE	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99										PORT DOES NOT ALIGN WITH EXHAUST GASKET.  ON RECEIPT OF CYLINDERS, THEY ARE CHECKED FOR CONFORMITY.  ONE OF THE CHECKS I	S PLACING A GASKET ON THE EXHAUST STUDS TO CHECK FOR CONCENTRICITY WITH THE PORT. ANOTHER CHECK IS TO SEE IF THE CYLINDE	R HEAD TEMPERATURE DRILLING IS CENTERED IN ITS BOSS.  IF THE DRILLING IS OFF, THEN THE EXHAUST PORT WILL BE ALSO.  THIS 	HAS BEEN LEARNED THROUGH TRIAL AND ERROR.  IT APPEARS THAT SUPERIOR IS USING A SLIGHTLY LARGER EXHAUST PORT DIMENSION TH	AN LYCOMING WHICH GIVES LESS TOELRANCE TO GASKET PLACEMENT.							3	O			E286				 
2000020500943	20000205	00943	CE  	2000	2	5	2000ZZZX274      	1	20000103	G	5320	991503553	STIFFENER       			CESSNA	500   	560CESSNA   	2076750	CE  										BS 440	DAMAGED         	B			JSNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	207PC	573  				5605008				DURING A SCHEDULED INSPECTION, NOTED THAT P/N 9915035-53, EXTRUDED STIFFENER, HAD A RIVET CIRCLED IN RED FROM THE MANUFA	CTURER.  THE RIVET WAS NOT BUCKED.  THE HOLE WAS EGGSHAPED WHEN RIVET WAS REMOVED.  AN OVERSIZED RIVET WAS USED TO 'COMP	LETE' THE JOB.				2	L	7	2 	4F			RT	A22CE   					 
2000020500944	20000205	00944		2000	2	5	2000ZZZX275      	4	20000103	G	2562	4523050	ELT TRAY        	ARTEX       	1104        	CESSNA	500   	560CESSNA   	2076750	CE  										TAIL	MISMANUFACTURED 	B	P		JSNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	207PC	573  				5605008				DURING SCHEDULED MAINTENANCE INSPECTION FOR FUNCTIONAL CHECK OF ARTEX ELT 110-4, SEVERAL DISCREPANCIES WERE NOTED.  AIRF	RAME MANUFACTURER DID NOT PROVIDE ANY CHAFE PROTECTION FOR WIRES AND ANTENNA CABLE COMING THROUGH HOLE IN UPPER FUSELAGE	 SKIN IN FRONT OF THE ELT TRANSMITTER.  THE WIRING WAS SHOWING SIGNS OF CHAFING.  THE ELT MOUNTING TRAY ASSY, P/N 452-30	50, RETAINING CAP HAD ONLY ONE OF TWO SCREWS ENGAGED.  IT WAS IMPOSSIBLE TO FASTEN THE SECOND SCREW.  ON EXAMINATION, TH	E INNER TAG OF THE SOUTHCO SCREW CLIP WOULD NOT ENGAGE THE HOLE IN THE MOUNTING TRAY DUE TO THE HOLE CENTER DRILLED TOO 	LOW ON THE TRAY FOR THE SCREW CLIP.	2	L	7	2 	4F			RT	A22CE   					 
2000021200252	20000212	00252	WP  	2000	2	12	2000ZZZX277      	1	20000207	G	5311		FRAME           			DOUG  	DC9   	DC932F      	3022067	WP  										BS 695	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	935F					47220				MAIN CARGO COMPARTMENT STA 695 AT CENTER LINE LONGITUDINAL FRAME HAS AN AREA WITH SEVERE INTERGRANULAR CORROSION.  REPAI	RED BY FABRICATING AND INSTALLING BRACKETS AND INSTALLING A REPAIR DOUBLER.  DER APPROVED ON FAA FORM 8110-3 DATED 99-12	-15 ECRA 935-53-055-2.				2	L	7	2 	4F				A6WE    					 
2000021200253	20000212	00253	WP  	2000	2	12	2000ZZZX278      	1	20000207	G	5330		SKIN            			DOUG  	DC9   	DC932F      	3022067	WP  										BS 996-1019	DENTED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	935F					47220				TWO LARGE DENTS IN SKIN AT STA 996 - STA 1019, L3-L5, RIGHT.  REPLACED INTERCOSTAL WEBS AND BY SHIMMING THE SMALLER GAP 	DER APPROVED ON FAA FORM 8110-3 DATED 99-12-02.					2	L	7	2 	4F				A6WE    					 
2000021200254	20000212	00254	WP  	2000	2	12	2000ZZZX279      	1	20000207	G	5520		FASTENER        			DOUG  	DC9   	DC932F      	3022067	WP  										ELEVATOR	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	935F					47220				FASTENER HEAD COMING OFF/BENDING BACK, LOWER SIDE OF RIGHT ELEVATOR 23.50 INCHES INBOARD OF OUTBOARD TIP.  REPAIRED PER 	SRM 53-03, FIG 14.  DER APPROVED ON FORM 8110-3 DATED 99-11-18.  ECRA 935-55-047-2.					2	L	7	2 	4F				A6WE    					 
2000021200255	20000212	00255	WP  	2000	2	12	2000ZZZX280      	1	20000207	G	5532		SKIN            			DOUG  	DC9   	DC932F      	3022067	WP  										VERTICAL STAB	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	935F					47220				SCREW HOLE COUNTERSUNK SURFACE AREA DRILLED THROUGH NUMEROUS TIMES ON UPPER LEFT SIDE OF VERTICAL STABILIZER LEADING EDG	E PANEL.  REPAIRED WITH REPAIR BUSHINGS.  DER APPROVED ON FORM 8110-3 DATED 9-11-23 ECRA 935-55-050-2.					2	L	7	2 	4F				A6WE    					 
2000021200256	20000212	00256	WP  	2000	2	12	2000ZZZX281      	1	20000207	G	5330		SKIN            			DOUG  	DC9   	DC932F      	3022067	WP  										BS 47 AND 53	DENTED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	935F					47220				DENT IN SKIN PLATING RIGHT SIDE OF FUSELAGE NOSE SECTION AT BS 47 AND BS 53.  REPAIRED BY FABRICATING 2 EACH FRAMES PER 	DRAWING AND INSTALLING FILLER AND FINGER AND INTERNAL DOUBLER DER APPROVED ON FAA FORM 8110-3 DATED 99-12-07 ECRA 935-53	-045-2.				2	L	7	2 	4F				A6WE    					 
2000021200257	20000212	00257	WP  	2000	2	12	2000ZZZX282      	1	20000207	G	5330		SKIN            			DOUG  	DC9   	DC932F      	3022067	WP  										BS 133.425	MISREPAIRED     	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	935F					47220				PREVIOUS FUSELAGE SKIN PANEL REPAIR AT FS 133.425 NOT PER SRM 53-04, FIG 12B, SHEET 2.  REPAIR ASLO HAS NUMEROUS GOUGES 	IN REPAIR.  REPAIRED PER SRM 53-04 FIG 12B DER APPROVED ON FORM 8110-3 DATED 99-11-19, ECRA 935-53-048-2.					2	L	7	2 	4F				A6WE    					 
2000021200258	20000212	00258	WP  	2000	2	12	2000ZZZX283      	1	20000207	G	5330		SKIN            			DOUG  	DC9   	DC932F      	3022067	WP  										FUSELAGE	MISREPAIRED     	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	935F					47220				FORWARD LOWER CARGO DOOR FORWARD LOWER CORNERS SKIN REPAIR NOT TO DRAWING.  SRO9530117 PER EO 53-DC9-905-98 REV A.  REPA	IRED BY EXPANDING AND INSTALLING FILLER, DOUBLER, AND TRIPLER.  DER APPROVED ON FAA FORM 8110-3 DATED 99-11-29 AND FAA L	ETTER DATED DEC 12, 1999, ECRA 935-53-046-2.				2	L	7	2 	4F				A6WE    					 
2000021200259	20000212	00259	WP  	2000	2	12	2000ZZZX284      	1	20000207	G	5711		SPAR            			DOUG  	DC9   	DC933F      	302207A	WP  										WS 267	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				RIGHT WING REAR SPAR VERTICAL LEG AT STA 267.0 HAS HEAVY CORROSION.  REPAIRED BY TRIMMING UPPER CAP BETWEEN XRS 180.1 AN	D XRS 319.5.  NEW SECTION SPLICED IN PER SB 57-179 AND ECRA 941-57-015-2.					2	L	7	2 	4F				A6WE    					 
2000021200260	20000212	00260	WP  	2000	2	12	2000ZZZX285      	1	20000207	G	5320		WEB             			DOUG  	DC9   	DC932F      	3022067	WP  										BS 370 AND 427	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	935F					47220				FORWARD PIT, RIGHT FLOOR WEB BETWEEN BS 370 AND BS 427 ABOVE PIT DOOR HAS SURFACE CORROSION AT FLOOR BEAM.  REPAIRED BY 	INSTALLING NEW CUSP WEB AT STA 313 TO STA STA 389 AND STA 389 TO STA 503.  DER APPROVED ON FAA FORM 8110-3 DATED 99-11-1	9, ECRA 935-53-C43-2.				2	L	7	2 	4F				A6WE    					 
2000021200261	20000212	00261	WP  	2000	2	12	2000ZZZX286      	1	20000207	G	5230		PAN             			DOUG  	DC9   	DC933F      	302207A	WP  										CARGO DOOR	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CRACK DAMAGE ON THE LOWER AFT CARGO DOOR INNER AND OUTER PAN.  REPAIRED LOWER AFT CARGO DOOR INNER AND OUTER PAN PER EIA	 ECRA 941-52-102-2.					2	L	7	2 	4F				A6WE    					 
2000021200262	20000212	00262	WP  	2000	2	12	2000ZZZX287      	1	20000207	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 58.75	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				APPROVAL FOR AN EXISTING REPAIR ON THE FUSELAGE SKIN AT STA 58.750 L19L.  REPAIR REMOVED A CRACK COMMON TO THE SKIN AT T	HE STA 58.750 FRAME.  REPAIRED FUSELAGE SKIN EXTERNAL DOUBLER AT STA 58.750 L18L TO L19L PER EIA ECRA 941-53-005-2.					2	L	7	2 	4F				A6WE    					 
2000021200263	20000212	00263	WP  	2000	2	12	2000ZZZX288      	1	20000207	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 320	DENTED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				DENT DAMAGE FOUND BELOW THE MAIN DECK CARGO DOOR, FORWARD AND ABOVE THE PRESSURE RELIEF VALVES.  REPAIRED FUSELAGE SKIN 	DENT AT STA 320 BETWEEN L18L TO L19L PER EIA ECRA 941-53-014-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200264	20000212	00264	WP  	2000	2	12	2000ZZZX289      	1	20000207	G	5320		WEB             			DOUG  	DC9   	DC933F      	302207A	WP  										BS 452-455	PUNCTURED       	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				PUNCTURE DAMAGE COMMON TO THE CUSP MEMBRANE BETWEEN STA 452 TO ST 455.  REPAIRED RT FUSELAGE CUSP MEMBRANE/WEB PUNTURE B	ETWEEN STA 452 TO STA 456 PER EIA ECRA 541-53-012-2.					2	L	7	2 	4F				A6WE    					 
2000021200265	20000212	00265	WP  	2000	2	12	2000ZZZX290      	1	20000207	G	5230		FITTING         			DOUG  	DC9   	DC933F      	302207A	WP  										CARGO DOOR	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				ELONGATED HOLE IN MAIN DECK CARGO DOOR TORQUE TUBE FITTING.  REPAIRED UPPER CARGO DOOR TORQUE TUBE AT STA 380 BETWEEN L4	L TO L5L PER EIA ECRA 941-53-072-2.					2	L	7	2 	4F				A6WE    					 
2000021200266	20000212	00266	WP  	2000	2	12	2000ZZZX291      	1	20000207	G	5244		DOOR            			DOUG  	DC9   	DC933F      	302207A	WP  										RT WING	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				DAMAGE ON THE RIGHT WING NR 4 LEADING EDGE SLAT DOOR AT WS X0S 240.081.  REPAIRED DAMAGE ON THE RT WING NR 4 L/E SLAT DO	OR AT WS X05 240.081 PER DIA ECRA 941-57-089-2.					2	L	7	2 	4F				A6WE    					 
2000021200267	20000212	00267	WP  	2000	2	12	2000ZZZX292      	1	20000207	G	5730		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										WS 575.5	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				REPAIRED THE PREVIOUS REPAIR ON THE LT WING LEADING EDGE AT XFS 575.5.  REPAIRED PREVIOUS FLUSH REPAIR ON THE LT WING LE	ADING EDGE AT XFS 575.5 PER EIA ECRA 941-57-009-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200268	20000212	00268	WP  	2000	2	12	2000ZZZX293      	1	20000207	G	5220		STRUCTURE       			DOUG  	DC9   	DC933F      	302207A	WP  										EMERGENCY DOOR	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				PREVIOUSLY PLUGGED HOLE WITH SHORT EDGE DISTANCE AND GOUGE ON THE RT FORWARD EMERGENCY EXIT DOOR.  REPAIRED PREVIOUSLY P	LUGGED HOLE WITH SHORT EDGE DISTANCE AND GOUGE ON THE RT FORWARD EMERGENCY EXIT DOOR PER EIA ECRA 941-52-058-2.					2	L	7	2 	4F				A6WE    					 
2000021200269	20000212	00269	WP  	2000	2	12	2000ZZZX294      	1	20000207	G	5320		RIVETS          			DOUG  	DC9   	DC933F      	302207A	WP  										BS 256-945	MISINSTALLED    	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				OVERLAPPING RIVETS ON THE INTERCOSTALS AT VARIOUS LOCATIONS.  REPAIRED OVERLAPPING RIVETS ON THE INTERCOSTALS AT LT STA'	S 617, 465, 945, 927, 908, 889, 851, 832, 813, 794 775, 756, 737, 718, 699, 639, 560, 541, AND 256 L6L.  RT STA'S 639, 6	17, 313, 699, 484, 465, 256, 541, 560, 237, 408, 756, 775, 794, 813, 832, 851, 927, AND 945 L6R PER EIA ECRA 941-53-018-	2.			2	L	7	2 	4F				A6WE    					 
2000021200270	20000212	00270	WP  	2000	2	12	2000ZZZX295      	1	20000207	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 908	MISDRILLED      	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				MISDRILLED HOLE AT RT FRAME STA 908.00 L6R.  REPAIRED MISDRILLED HOLE AT RT FRAME STA 908 L6R PER EIA ECRA 941-53-039-2.						2	L	7	2 	4F				A6WE    					 
2000021200271	20000212	00271	WP  	2000	2	12	2000ZZZX296      	1	20000207	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 332	MISDRILLED      	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				MISDRILLED HOLE AT RIGHT FRAME STA 332.00 L6R.  REPAIRED MISDRILLED HOLE AT RT FRAME STA 332 L6R PER EIA ECRA 941-53-064	-2.					2	L	7	2 	4F				A6WE    					 
2000021200272	20000212	00272	WP  	2000	2	12	2000ZZZX297      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 718	MISDRILLED      	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				MISDRILLED HOLE AT RIGHT FRAME STA 718, L6R.  REPAIRED MISDRILLED HOLE AT RIGHT FRAME STA 718, L6R PER EIA ECRA 941-53-0	23-2.					2	L	7	2 	4F				A6WE    					 
2000021200273	20000212	00273	WP  	2000	2	12	2000ZZZX298      	1	20000208	G	5347		CARGO RACK      			DOUG  	DC9   	DC933F      	302207A	WP  										BS 522	PUNCTURED       	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				PUNCTURE IN THE DUAL CARGO TRACK AT LEFT STA 522.00, LBL 24.00.  REPAIRED A PUNCTURE IN THE DUAL CARGO TRACK AT STA 522,	 LBL 24 PER EIA ECRA 941-53-048-2.					2	L	7	2 	4F				A6WE    					 
2000021200274	20000212	00274	WP  	2000	2	12	2000ZZZX299      	1	20000208	G	5320		WEB             			DOUG  	DC9   	DC933F      	302207A	WP  										BS 343.6	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CRACK IN THE FASTENER HOLE ON THE CUSP WEB AT RIGHT STA 343.60, RBL 42.  REPAIRED FASTENER HOLE ON CUSP WEB AT RIGHT STA	 343.60, RBL 42 PER ECRA 941-53-057-2.					2	L	7	2 	4F				A6WE    					 
2000010800177	20000108	00177		2000	1	8	2000ZZZX30       	4	20000104	G	3444	031002220008	SWITCH          			CESSNA	500   	550         	2076604	CE  										COCKPIT	FAILED          	B			CNQ6	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	814CB					5500824				BOTH TRANSPONDERS OPERATE SIMULTANEOUSLY.  OPERATOR HAD SELECTED NR 1 TRANSPONDER AND PUT NR 1 IN STANDBY WITH 7700 CODE	 SELECTED.  BOTH MODE A CODES SEEN BY RADAR.  POSSIBLE CAUSE WAS TRANSPONDER SELECT SWITCH NOT FALLING IN UP POSITION. S	ITUATION CAN BE MOST LIKELY TO OCCUR IF THERE IS NOT ENOUGH CLEARANCE BETWEEN SWITCH AND OVERLAY PANEL CAUSING BINDING O	F SWITCH MOVEMENT.  SWITCH SHOULD BE REPLACED WITH A 'BREAK BEFORE MAKE' TYPE SWITCH.  ALSO, ENLARGE HOLE IS OVERLAY PAN	EL IF REQUIRED.		1	L	7	2 	4F				A22CE   					 
2000021200275	20000212	00275	WP  	2000	2	12	2000ZZZX300      	1	20000208	G	5311		DOOR FRAME      			DOUG  	DC9   	DC933F      	302207A	WP  										FUSELAGE	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				A 0.5 INCH CRACK WAS FOUND IN THE RADIUS OF THE SERVICE DOOR FRAME.  DURING REPAIR, A FASTENER WAS FOUND WITH A 0.15 INC	H EDGE MARGIN MEASURED FROM THE CENTER OF THE FASTENER HOLE TO THE EDGE OF THE FITTING.  REPAIRED FORWARD GALLEY SERVICE	 DOOR NR 2 HORIZONTAL BEAM FORWARD UPPER CORNER PER EIA ECRA 941-52-076-2.				2	L	7	2 	4F				A6WE    					 
2000021200276	20000212	00276	WP  	2000	2	12	2000ZZZX301      	1	20000208	G	5312		BULKHEAD        			DOUG  	DC9   	DC933F      	302207A	WP  										BS 996	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				ELONGATED FASTENER HOLES, GOUGE AND CRACK DAMAGE ASSOCIATED WITH THE AFT PRESSURE BULKHEAD TEE CHORD SPLICE AT L6L TO L8	L.  REQUIRED AFT PRESSURE BULKHEAD TEE CHORD AT STA 996 BETWEEN L6L TO L8L PER EIA ECRA 941-53-077-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200277	20000212	00277	WP  	2000	2	12	2000ZZZX302      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 870	MISDRILLED      	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				MISDRILLED HOLE AT RT FRAME STA 870.00  L6R.  REPAIRED MISDRILLED HOLE AT RIGHT FRAME STA 870 L6R PER EIA ECRA 941-53-01	9-2.					2	L	7	2 	4F				A6WE    					 
2000021200278	20000212	00278	WP  	2000	2	12	2000ZZZX303      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 870	MISDRILLED      	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				MISDRILLED HOLE AT LEFT FRAME STA 870.00 L6L.  REPAIRED  MISDRILLED HOLE AT LEFT FRAME STA 870, L6L PER EIA ECRA 941-53-	020-2.					2	L	7	2 	4F				A6WE    					 
2000021200279	20000212	00279	WP  	2000	2	12	2000ZZZX304      	1	20000208	G	3210		FITTING         			DOUG  	DC9   	DC933F      	302207A	WP  										LT AND RT MLG	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CORROSION DAMAGE FOUND IN 5 BOLT HOLES COMMON TO THE LT AND RT MAIN LANDING GEAR FITTINGS.  REPAIRED LT AND RT MAIN LAND	ING GEAR FITTINGS PER EIA ECRA 941-57-065-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200280	20000212	00280	WP  	2000	2	12	2000ZZZX305      	1	20000208	G	5511		RIB             			DOUG  	DC9   	DC933F      	302207A	WP  										HORIZ STABILIZER	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				DAMAGE TO THE XHS 86.00 RIB IN THE RT HORIZONTAL STABILIZER FORWARD UPPER END WHILE GAINING ACCESS TO AN UNCONFIRMED CRA	CK.  CRACK WAS LATER FOUND TO BE AN ANOMALIE ONLY.  REPAIRED RT HORIZONTAL STABILIZER RIB DAMAGE AT XHS 86 PER EIA ECRA 	941-55-013-2 REV A.				2	L	7	2 	4F				A6WE    					 
2000021200281	20000212	00281	WP  	2000	2	12	2000ZZZX306      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 927-936	MISREPAIRED     	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				NON-DOCUMENTED DOUBLERS AT FUSELAGE RIGHT STA 927 AND STA 936.  REPAIRED RT FUSELAGE SKIN AT STA 927 AND STA 936, BETWEE	N L14R AND L15R PER EIA ECRA 941-53-083-2 REV B.					2	L	7	2 	4F				A6WE    					 
2000021200282	20000212	00282	WP  	2000	2	12	2000ZZZX307      	1	20000208	G	5511		STRINGER        			DOUG  	DC9   	DC933F      	302207A	WP  										HORIZ STABILIZER	MISREPAIRED     	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				TWO EXISTING UNAPPROVED REPAIR CHANNELS ON THE LT HORIZONTAL STABILIZER UPPER PANEL AT STR 6 AT XHS 25 AND XHS 37.  REPA	IRED LT HORIZONTAL STABILIZER UPPER PANEL STRINGER AT XHS 25 AND XHS 37, L6 PER EIA ECRA 941-55-059-2.					2	L	7	2 	4F				A6WE    					 
2000021200283	20000212	00283	WP  	2000	2	12	2000ZZZX308      	1	20000208	G	5320		INTERCOSTAL     			DOUG  	DC9   	DC933F      	302207A	WP  										FUSELAGE	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				FORWARD ENTRY DOOR LOWER SILL 9957838-3 INTERCOSTAL FOUND CORRODED AT THE NUTPLATE LOCATIONS.   WHILE GAINING ACCESS THR	OUGH THE UPPER CUSP ANGLE, THE LOWER CUSP ANGLE WAS DAMAGED.  REPAIRED FORWARD ENTRY DOOR LOWER SILL UPPER AND LOWER CUS	P ANGLES PER EIA ECRA 941-53-075-2.				2	L	7	2 	4F				A6WE    					 
2000021200284	20000212	00284	WP  	2000	2	12	2000ZZZX309      	1	20000208	G	5320		WEB             			DOUG  	DC9   	DC933F      	302207A	WP  										BS 579	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CRACK DAMAGE ON THE CUSP WEB AT LEFT AFT STA 579, LBL 54.00.  REPAIRED LEFT AFT CUSP WEB AT STA 579, LBL 54, PER EIA ECR	A 941-53-052-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200285	20000212	00285	WP  	2000	2	12	2000ZZZX310      	1	20000208	G	5530		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										VERTICAL STAB	MISDRILLED      	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				DOUBLE-DRILLED HOLE TO THE VERTICAL STABILIZER FRAME AT STA YV 247.750, ZV 140.825.  REPAIRED DOUBLE-DRILLED HOLE ON VER	TICAL STABILIZER FRAME AT STA YV 247.750, ZV 140.825 PER EIA ECRA 941-52-053-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200286	20000212	00286	WP  	2000	2	12	2000ZZZX311      	1	20000208	G	3210		FITTING         			DOUG  	DC9   	DC933F      	302207A	WP  										RT MLG	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				THREE OVERSIZED HOLES IN THE RT MAIN LANDING GEAR FITTING.  REPAIRED RIGHT MAIN LANDING GEAR FITTING OVERSIZED HOLES PER	 EIA ECRA 941-57-055-2.					2	L	7	2 	4F				A6WE    					 
2000021200287	20000212	00287	WP  	2000	2	12	2000ZZZX312      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 1037	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CRACK IN THE LEFT FRAME AT STA 1037.  REPAIRED FUSELGE FRAME AT STA 1037 BETWEEN L12L TO L13L PER EIA ECRA 941-53-053-2.						2	L	7	2 	4F				A6WE    					 
2000021200288	20000212	00288	WP  	2000	2	12	2000ZZZX313      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 1810	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CRACKED AREA OF FUSELAGE SKIN NEAR STA 1810, L23L.  REPAIRED FUSELAGE SKIN DOUBLER AT STA 1018, L23L PER EIA ECRA 941-53	-062-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200289	20000212	00289	WP  	2000	2	12	2000ZZZX314      	1	20000208	G	5320		INTERCOSTAL     			DOUG  	DC9   	DC933F      	302207A	WP  										BS 180	GOUGED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				GOUGE IN INTERCOSTAL AT STA 180.00, RBL 21.  REPAIRED INTERCOSTAL GOUGE AT STA 180, RBL 21 PER EIA ECRA 941-53-079-2.						2	L	7	2 	4F				A6WE    					 
2000021200290	20000212	00290	WP  	2000	2	12	2000ZZZX315      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 160-200	GOUGED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				GOUGES ON THE FUSELAGE SKIN BELOW THE AIRSTAIR DOOR.  REPAIRED LEFT FUSELAGE EXTERNAL SKIN AT STA 160 TO STA 200 UNDER T	HE AIRSTAIR DOOR PER EIA ECRA 941-53-078-2.					2	L	7	2 	4F				A6WE    					 
2000021200291	20000212	00291	WP  	2000	2	12	2000ZZZX316      	1	20000208	G	5320		WEB             			DOUG  	DC9   	DC933F      	302207A	WP  										BS 427	DENTED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				TRIMMED OUT DENT ON FORWARD CARGO COMPARTMENT WEB AT STA 427.00 BETWEEN L24R TO L26R.  REPAIRED FORWARD CARGO COMPARTMEN	T WEB AT STA 427 BETWEEN L24R TO L26R PER EIA ECRA 941-53-080-2.					2	L	7	2 	4F				A6WE    					 
2000021200292	20000212	00292	WP  	2000	2	12	2000ZZZX317      	1	20000208	G	5244		DOOR            			DOUG  	DC9   	DC933F      	302207A	WP  										WS 294	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				EXISTING EXTRA JOINT IN THE RIGHT WING BUTTE DOOR AT XRS 294.  REPAIRED RT WING BUTTE DOOR HINGE AT XRS 294 PER EIA ECRA	 941-57-082-2.					2	L	7	2 	4F				A6WE    					 
2000021200293	20000212	00293	WP  	2000	2	12	2000ZZZX318      	1	20000208	G	5320		CHORD           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 319	GOUGED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				TEE CHORD AT STA 319, L19L HAS A GOUGE AND DENT DAMAGE.  REPAIRED GOUGED TEE CHORD AT STA 319, L19L PER EIA ECRA 941-53-	093-2.					2	L	7	2 	4F				A6WE    					 
2000021200294	20000212	00294	WP  	2000	2	12	2000ZZZX319      	1	20000208	G	5320		WEB             			DOUG  	DC9   	DC933F      	302207A	WP  										BS 313 AND 323	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				DAMAGE ON THE CUSP WEB BETWEEN RT STA 313 AND STA 323 AT RBL 54.  REPAIRED DAMAGED CUSP WEB BETWEEN RT STA 313 TO STA 32	3 AT RBL 54 PER EIA ECRA 941-53-087-2.					2	L	7	2 	4F				A6WE    					 
2000021200295	20000212	00295	WP  	2000	2	12	2000ZZZX320      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 996	MISREPAIRED     	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				CLASS 2 SKIN REPAIR AT RT STA 996, L28R AND L29R.  REPAIRED EXISTING CLASS 2 SKIN REPAIR AT RIGHT STA 996, L28R AND L29R	 TO A CLASS 1 REPAIR PER EIA ECRA 941-53-051-2.					2	L	7	2 	4F				A6WE    					 
2000021200296	20000212	00296	WP  	2000	2	12	2000ZZZX321      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 168.750	MISREPAIRED     	B			ERKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	941F					47193				FUSELAGE SKIN REPAIR ON RIGHT OF FUSELAGE AT FS 168.750 OVERLAPPING SKIN PANEL BUTT JOINT ON LONGERON 26 NEEDS TO BE CHA	NGED FROM A CLASS 2 REPAIR TO A CLASS 1 REPAIR.  REPAIRED PER ECRA 941-53-081-2.					2	L	7	2 	4F				A6WE    					 
2000021200297	20000212	00297	WP  	2000	2	12	2000ZZZX322      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 229-588	MISDRILLED      	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				RIGHT SKIN AT STA 229 - STA 588 HAS A LOT OF DAMAGE AND INTERNAL DOUBLER HAS A HOLE FROM PREVIOUS REPAIR.  REMOVED AND R	EPLACED SKINS AND INTERNAL DOUBLER PER ECRA 94-53-0003-3.					2	L	7	2 	4F				A6WE    					 
2000021200298	20000212	00298	WP  	2000	2	12	2000ZZZX323      	1	20000208	G	5320		SPLICE          			DOUG  	DC9   	DC933F      	302207A	WP  										BS 718	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				FUSELAGE STA 715 RIGHT BUTT LINE 58.  CORROSION ON WEB.  CORROSION ON FORWARD, LOWER SURFACE OF FRAME 718, SPLICE UNDER 	CABIN FLOOR.  REPLACED FRAME STA 781, REPLACED WEB PER SB 53-131 REV 4 AND SRM 53-2, 51-30-5.					2	L	7	2 	4F				A6WE    					 
2000021200299	20000212	00299	WP  	2000	2	12	2000ZZZX324      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 699	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				FUSELAGE STATION 699 RIGHT AFT SIDE OF FRAME IN MID-POCKET.  FRAME HAS THREE CRACKS LOCATED BENEATH FLOOR.  REPLACED FRA	ME PER SB 53-131 REV 4.					2	L	7	2 	4F				A6WE    					 
2000021200300	20000212	00300	WP  	2000	2	12	2000ZZZX325      	1	20000208	G	5522		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										ELEVATOR	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				RIGHT ELEVATOR LOWER SURFACE OUTBOARD END HAS A HOLE.  REPLACED SKIN PER DOUGLAS DRAWING ECRA 942-55-083-2 REV A AND DC9	 SRM.					2	L	7	2 	4F				A6WE    					 
2000021200301	20000212	00301	WP  	2000	2	12	2000ZZZX326      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 718	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				FRAME 718 RIGHT CRACKED ON FORWARD SIDE OF INTERMEDIATE POCKET, LOWER AFT RADIUS FROM FASTENER HOLE TO FASTENER HOLE UND	ER CABIN FLOOR.  REPLACED FRAME 718 RIGHT SIDE PER SB 53-131 AND ECRA 941-53-067-2.					2	L	7	2 	4F				A6WE    					 
2000021200302	20000212	00302	WP  	2000	2	12	2000ZZZX327      	1	20000208	G	5311		FRAME           			DOUG  	DC9   	DC933F      	302207A	WP  										BS 185.0	GOUGED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				INSIDE L-2 DOOR STA 185.0 LBL 44.5, TEE CHORD HAS .50 INCH LONG DEEP GOUGE ON TOP SIDE.  REPAIR PER ECRA 941-53-088-2.						2	L	7	2 	4F				A6WE    					 
2000021200303	20000212	00303	WP  	2000	2	12	2000ZZZX328      	1	20000208	G	5330		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										BS 737	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				REMOVED EXISTING REPAIR DOUBLER AT STA 737 BETWEEN L17-L18 RT SIDE FOR INSPECTION AND MEASURING BLENDED AREA PER ENGINEE	RING.  REPAIRED PER ECRA 941-53-061-2.					2	L	7	2 	4F				A6WE    					 
2000021200304	20000212	00304	WP  	2000	2	12	2000ZZZX329      	1	20000208	G	5320		DOOR  JAMB      			DOUG  	DC9   	DC933F      	302207A	WP  										FUSELAGE	CRACKED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				CRACK FOUND ON AFT LOWER CORNER OF THE FORWARD SERVICE DOOR.  DOOR JAMB CRACK COMING OUT OF AFT UPPER SCREW HOLE FOR SCU	FF PLATE AND CORROSION UNDER SCUFF PLATE.  REPAIRED PER ECRA 941-53-098-2 REV A.					2	L	7	2 	4F				A6WE    					 
2000021200305	20000212	00305	WP  	2000	2	12	2000ZZZX330      	1	20000208	G	5230		SKIN            			DOUG  	DC9   	DC933F      	302207A	WP  										CARGO DOOR	GOUGED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				FORWARD PIT DOOR, DOOR EDGE, LOWER AFT, AND UPPER END FORWARD, HAS A GOUGE.  INSTALLED REPAIR PER SRM 52-01 FIG 01 AND E	CRA 941-52-091-2.					2	L	7	2 	4F				A6WE    					 
2000021200306	20000212	00306	WP  	2000	2	12	2000ZZZX331      	1	20000208	G	5315		FLOORBEAM       			DOUG  	DC9   	DC933F      	302207A	WP  										BS 917	CHAFED          	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				AFT CARGO PIT STA 917 BL ZERO FLOORBEAM CHAFED.  REPAIRED PER ECRA NR 941-53-094-2.						2	L	7	2 	4F				A6WE    					 
2000021900078	20000219	00078	SO  	2000	2	19	2000ZZZX361      	1	20000117	G	7603	554051	CONTROL CABLE   		6932403     	PIPER 	PA32  	PA32R301    	7103218	SO  										ENGINE BAY	BENT            	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	8024A	4687 				32R83103008				NOSE GEAR FAILED TO EXTEND.  FOUND THE ALTERNATE AIR CABLE (PIPER P/N 554051) NOT ROUTED CORRECTLY IN ENGINE COMPARTMENT	 AND TY WRAP BROKEN WHICH ALLOWED ALTERNATE AIR CABLE TO BECOME ENTANGLED TO THE NOSE GEAR LOWER DRAG LINK (PIPER P/N 38	040-02) AND BOLT (PIPER P/N 402938).  RECOMMENDED SOLUTION THAT PIPER REVIEW MANUAL AND IPC CLARIFING ROUTING AND CLAMPI	NG OF ALTERNATE AIR CABLE AND OWNERS THEN ARE PROVIDED WITH THAT, TO PREVENT RECURRENCE.			1	L	7	1 	3O			 	A3SO    					 
2000021900079	20000219	00079	WP  	2000	2	19	2000ZZZX362      	1	20000210	G	5330		DOUBLER         			DOUG  	DC9   	DC933F      	302207A	WP  										BS 376	TEMPORARY       	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				REMOVED THE EXISTING CLASS 2 REPAIR AND INSTALLED A CLASS 1 REPAIR AT LT STA 376.00 BETWEEN L22L AND L24L.  REMOVED CLAS	S 2 REPAIRS AND INSTALLED CLASS 1 REPAIRS FROM LT STA 376.00 TO STA 395.00 BETWEEN L22L TO L24L PER EIA ECRA 941-53-090-	2.				2	L	7	2 	4F				A6WE    					 
2000021900080	20000219	00080	WP  	2000	2	19	2000ZZZX363      	1	20000110	G	5330		DOUBLER         			DOUG  	DC9   	DC933F      	302207A	WP  										FUSELAGE	TEMPORARY       	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	941F					47193				REPLACED A TEMPORARY REPAIR WITH A PERMANENT REPAIR.  TEMPORARY REPAIR IS FOR DENT AND CRACK DAMAGE AT THE LOWER AFT COR	NER OF THE MAIN DECK CARGO DOOR.  REPAIRED MAIN DECK CARGO DOOR AFT LOWER CORNER DAMAGE PER EIA ECRA 941-52-046-2.					2	L	7	2 	4F				A6WE    					 
2000021900083	20000219	00083	CE  	2000	2	19	2000ZZZX366      	1	20000121	G	3310	C6130010101	INVERTER        			CESSNA	310   	T310R       	2074246	CE  										COCKPIT	FAILED          	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			SW	01	828P	243  			9817	310R0681				DURING FINAL FOR ARTESIA, NM (ATS) PILOT REPORTED SMOKE IN COCKPIT.  ON INSPECTION, FOUND ENGINE SWITCH AND PANEL LIGHTS	 CIRCUIT BREAKER TRIPPED.  TROUBLESHOT SYSTEM AND FOUND 28VDC TO 115VAC INVERTER BURNED OUT AND SEALANT DRIPPING.  INVER	TER WAS REPLACED 8-25-98.  AFTT:  1,982 HOURS.  FOUND BREAK IN INSULATION ON WIRE NR L329K20 (28VDC IN) THAT WAS SHORTIN	G TO GROUND AND CAUSED THE INVERTER FAILURE.  REPAIRED WIRE AND REPLACED INVERTER PACK WITH NEW P/N C613001-0101.			1	L	7	2 	3O				3A10    					 
2000021900086	20000219	00086	EA  	2000	2	19	2000ZZZX369      	2	20000103	G	7314	02532310102	PUMP            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LT ENGINE	DEFECTIVE       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	982FA					LJ1000	PCE24449			SERIAL NUMBERS ARE THE UNITS THAT REPLACED THE DEFECTIVE UNITS.  S/N 7848.  SHAFT IN ENGINE FUEL CONTORL SHEARED CAUSING	 ENGINE TO SHUT DOWN.					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2000021900087	20000219	00087	EA  	2000	2	19	2000ZZZX370      	2	20000103	G	7321	82447452	FCU             			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LT ENGINE	DEFECTIVE       	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	982FA					LJ1000	PCE24449			SERIAL NUMBERS ARE THE UNITS THAT REPLACED THE DEFECTIVE UNITS.  S/N 72779.  SHAFT IN ENGINE FUEL CONTROL SHEARED CAUSIN	G ENGINE TO SHUT DOWN.					1	L	7	2 	3T	4	T		3A20    	E4EA				 
2000021900088	20000219	00088	CE  	2000	2	19	2000ZZZX371      	1	20000113	G	2810		BAFFLE          			BBAVIA	8     	8KCAB       	2110612	CE  										FUEL CELL	LOOSE           	B		A	OG5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	68ND	2564 				66892				AIRCRAFT WAS WRITTEN UP FOR HAVING A ROLL TENDENCY.  INVESTIGATION BY MAINTENANCE FOUND INTERNAL BAFFLING ON LEFT FUEL T	ANK HAD COME LOOSE CAUSING TANK HAD COME LOOSE CAUSING TANK TO BUDGE INCREASING THE CAMBER ON THAT WING.  FURTHER INSPEC	TION OF RT TANK FOUND ONE INTERNAL BAFFLE COMPLETELY SEPARATED AND LOOSE IN THE TANK.  BOTH TANKS ARE BEING REPLACED.  R	T TANK P/N 71537-2.  LT TANK P/N 715371.			1	H	7	1 	3O				A21CE   					 
2000021900092	20000219	00092	CE  	2000	2	19	2000ZZZX373      	1	20000120	G	7830		ROD END         			LEAR  	35    	35A         	5170602	CE  										THRUST REVERSER	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	10AH					657				DURING A 1,200 HOUR T/R INSPECTION, FOUND WORN ACTUATOR ROD END BUSHING BRACKET.  THE BRACKETS ARE ACTUALLY PART OF THE 	THRUST REVERSER DOOR.  THEY ARE CAST INTO THE DOOR.					2	L	7	2 	4F				A10CE   					 
2000021900093	20000219	00093	EA  	2000	2	19	2000ZZZX374      	2	20000103	G	8550		LINE            			AMRGEN	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					OIL BREATHER	FROZE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	26456					AA5A0600				ENGINE AIR BREATHER PINCH HOLE HAD B EEN ELIMINATED BY PARTIES UNKNOWN.  BREATHER LINE FROZE SHUT AT 15,000 FEET.  EXCES	SIVE CRANKCASE PRESSURE CAUSED THE CRANKSHAFT OIL SEAL TO LEAK OIL.  BREATHER LINE WAS REPOSITIONED AND A PINCH HOLE WAS	 DRILLED.				1	L	7	1 	3O	3	O		A16EA   	E274				 
2000021900096	20000219	00096	SW  	2000	2	19	2000ZZZX377      	1	20000107	G	6310	2060401561	SEAL            			BELL  	407   	407         		SW  										TRANSMISSION	LEAKING         	B			UNFR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	19	147CF	757  				53281				SEAL LEAKING IN TRANSMISSION.						1	G	7	1 	3U			O	H2SW    					 
2000021900098	20000219	00098	CE  	2000	2	19	2000ZZZX379      	1	20000111	G	6120	68668	SPRING          			BEECH 	95    	95          	1153402	CE  										RELIEF VALVE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	2051C		1475 			TD238				LOW OIL PRESSURE DURING FLIGHT CAUSING PROPELLER TO GO TO LOW PITCH AND EVENTUALLY FEATHER.  AIRCRAFT LANDED SAFELY AND 	AFTER TROUBLESHOOTING PROBLEM, FOUND BROKEN SPRING IN OIL PRESSURE RELIEF VALVE.  INSTALLED NEW SPRING, ADJUSTED OIL PRE	SSURE AND RETURNED TO SERVICE.				1	L	7	2 	3O				3A16    					 
2000021900102	20000219	00102		2000	2	19	2000ZZZX383      	4	20000107	G	2561	KS9P0101	LIFE VEST       	EAAEROMARINE																CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					B40352					LIFE VEST FAILED MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-1.  ITEM DATE OF MFG JUNE 1980.																			 
2000021900103	20000219	00103		2000	2	19	2000ZZZX384      	1	20000115	G	3240	7010FS9545708	SEAL            		501052001   															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		2377 			SEP971104					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASS	EMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900104	20000219	00104		2000	2	19	2000ZZZX385      	1	20000111	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1990 			APR981288					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  ONE EACH PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY 	AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900105	20000219	00105		2000	2	19	2000ZZZX386      	1	20000117	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1540 			DEC981557					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OEM	 PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900106	20000219	00106		2000	2	19	2000ZZZX387      	1	20000118	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1330 			FEB991604					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  THREE EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY 	FILLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSY.  NOTE:  OEM P	ARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION P/N 5010520-1.																	 
2000021900107	20000219	00107		2000	2	19	2000ZZZX388      	1	20000112	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1049 			AUG981445					BRAKE ASSY, P/N 5010520-1, FAILED PREMATURELY.  THREE EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSEM	BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900108	20000219	00108		2000	2	19	2000ZZZX389      	1	20000113	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1615 			OCT981541					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  ONE EACH PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OEM P	ARTS INSTALLE DIN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900109	20000219	00109		2000	2	19	2000ZZZX390      	1	20000121	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1977 			OCT981543					BRAKE ASSY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FILLED	 WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSY.  NOTE:  OEM PARTS I	NSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900110	20000219	00110		2000	2	19	2000ZZZX391      	1	20000118	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1712 			APR981290					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  THREE EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY 	FILLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSY.  NOTE:  OEM P	ARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900111	20000219	00111		2000	2	19	2000ZZZX392      	1	20000120	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1269 			MAY981314					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OEM	 PARTS INSTALLED IN BRAKE ASSY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900113	20000219	00113		2000	2	19	2000ZZZX394      	1	20000124	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE SYSTEM	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1292 			APR991673					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OEM	 PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000021900114	20000219	00114	NE  	2000	2	19	2000ZZZX395      	3	20000126	G	6114		BEARING         													HARTZL	HCC3Y	HCC3YR2     	NE  	HUB	CORRODED        	B			ZN1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13		1916 						CK2830		HAD EXCESSIVE RUST IN BEARING RACES AND ON BALLS.  SOME CORROSION O INSIDE OF HUB.																5	C	P25EA	 
2000021900115	20000219	00115	EU  	2000	2	19	2000ZZZX396      	1	20000124	G	7931	11346AA	TRANSMITTER     			AMD   	FALC20	FALCON      	2720302	EU  										ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	99	213LS		1140 			107				OIL PRESSURE INDICATOR IN RIGHT ENGINE FLUCTUATED THEN INDICATED ZERO.  SECURED ENGINE FOR PRECAUTION.  DECLARED PRECAUT	IONARY EMERGENCY WITH ATC AND RETURNED TO HOME BASE (SBN).  TRANSMITTER REPLACED WITH OVERHAULED UNIT.  OPS/MAINT CHECKE	D GOOD.  RETURNED AIRCRAFT TO SERVICE.				2	L	7	2 	4F				A7EU    					 
2000021900118	20000219	00118	CE  	2000	2	19	2000ZZZX399      	1	20000107	G	3221	504100081	TRUNNION        			CESSNA	310   	310P        	2074238	CE  										LT MLG	DAMAGED         	B	L		QE5R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	5768M	3315 				310P0068				COMPONENT SENT TO REPAIR STATION FOR EVALUATION AS TO WHETHER IT WAS REPAIRABLE.  ACFT HAD EXPERIENCED A NLG FAILURE AND	 IT WAS THOUGHT THE NLG FAILURE MAY HAVE CAUSED THE DAMAGE TO LT MLG ASSY.  UPON INSP AND REFERENCING MM SECTIONS, THE M	LG ASSY IS NON-REPAIRABLE.   THE REPAIR WAS ACCOMPLISHED BY DRILLING OUT AND INSERTING A BUSHING.  LUG DRILLED TO AN APP	ROX SIZE OF .750 INCHES.  A BUSHING WITH A .500 ID BY .750 OD WAS INSTALLED.  RE MM, BUSHINGS ARE NOT USED AT THIS LOCAT	ION AND A CLOSE TOLERANCE PIN, .500 INCH DIA, REF PAGE 2-178 OF MM, SECURE ASSY.  DUE TO EXCESSIVE REMOVAL OF BASE MATER	IAL, IT IS OPINION OF THIS REPAIR STATION THIS COMPONENT WOULD NOT BE AIRWORTHY; NO REPAIR SHALL BE ATTEMPTED.	1	L	7	2 	3O				3A10    					 
2000021900119	20000219	00119	SO  	2000	2	19	2000ZZZX400      	1	20000103	G	3220	400910	CLEVIS BOLT     			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG	CHAFED          	G		A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	25	47686	456  				347770427				NOSE GEAR FAILED TO EXTEND ON APPROACH TO CAK, AIRCRAFT LANDED WITH NOSE GEAR RETRACTED RESULTING IN DAMAGE THE AIRCRAFT	.  SUBSEQUENT INVESTIGATION REVEALED THE NOSE GEAR CENTERING ATTACH BOLT (PIPER P/N 400-910), HAD COME IN CONTACT WITH N	OSE GEAR DOOR ACTUATION-AFT TUBE ASSY, (PIPER P/N 95771-0), PREVENTING EXTENSION OF THE GEAR.  SUBMITTER STATED BASED ON	 THE MARKS CONTAINED ON THE TUBE ASSY, IT APPEARED THAT CONDITION HAD EXISTED FOR A PERIOD OF TIME PRIOR TO THIS OCCURRE	NCE.		1	L	7	2 	3O				A7SO    					 
2000021900123	20000219	00123	CE  	2000	2	19	2000ZZZX405      	1	20000104	G	2710		PULLEY          			CESSNA	172   	172N        	2072434	CE  										ALERON	SEPARATED       	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	75803	5400 				17267962				WHILE REPLACING AILERON PUSH/PULL ROD, SLACKNESS IN AILERON CABLE LED TO DISCOVERY THAT AILERON PULLEY, P/N S378-4 (LOCA	TED UPPER STARBOARD POSITION IN REAR DOORPOST BULKHEAD ASSY), WAS NO LONGER BOLTED IN POSITION.  NUT HAD WORKED OFF BOLT	, BOLT HAD BACKED OUT OF PULLEY, AND PULLEY HAD FALLEN OUT OF POSITION.  INSTALLED PULLEY BOLT WAS DISCOVERED TO BE AN4-	14A RATHER THAN SPECIFIED AN4-15A.  SUBMITTER SUSPECTED BOLT FACTORY INSTALLED.			1	H	7	1 	3O			NT	3A12    					 
2000021900124	20000219	00124	CE  	2000	2	19	2000ZZZX406      	1	20000128	G	7800		SLIP JOINT      			ZINAIR	CH2000	CH2000      	9950100	CE  										EXHAUST	LEAKING         	H	P	A		O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			SW	99	32ZA	375  								PILOT REPORTED EXHAUST SMELL IN THE COCKPIT.  UPON INVEST, FOUND A SLIP JOINT ABOVE AND FWD OF HEATER  MUFF ALLOWING EXH	AUST TO ENTER HEAT MUFF.  AREA HAD EXCESSIVE EXHAUST STAINS AND SCAT HOSE ON  INTAKE SIDE OF THE MUFF WAS BRITTLE AND HE	AT DAMAGED.   FACTORY INFORMED THERE IS A LOWER PRESSURE IN THE COWLING THAN IN THE HEAT MUFF AND EXHAUST SHOULD NOT ENT	ER THE MUFF.  THIS THEORY DOES NOT HOLD UP IN THE FIELD.  THE OPERATION OF CABIN VENTS, SLOW FLIGHT, FAST FLIGHT, AND CR	UISE MAY CHANGE THESE PRESSURES.  FACTORY STATED THEY HAVE A NEW DESIGN EXHAUST SYSTEM WITH DIFFERENT STYLE JOINTS AND C	LAMPS.  SUBMITTER SUGGESTED FACTORY MAKE ALL OWNERS AWARE OF POTENTIAL PROBLEM AND OFFER NEW STYLE EXHAUST.	1	L	7	1 	3O			NT	TA5CH   					 
2000021900125	20000219	00125	WP  	2000	2	19	2000ZZZX407      	1	20000120	G	3246	26088851	WHEEL           		26088911    	DOUG  	DC9   	DC9*        		WP  										MLG	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B1161					BROKEN HUB.  UNDER INVESTIGATION.						2	L	7	2 	4F				A6WE    					 
2000021900126	20000219	00126	NM  	2000	2	19	2000ZZZX408      	1	20000120	G	3246	2609811	TIE BOLT        			DOUG  	MD11  	MD11        	3023602	NM  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09										BROKEN TIE BOLT.  UNDER INVESTIGATION.						2	L	7	3 	4F			RT	A22WE   					 
2000021900128	20000219	00128	SO  	2000	2	19	2000ZZZX410      	1	20000103	G	7120	6299173	CLAMP           			GULSTM	G1159 	GIV         	3980115	SO  										ENGINE	CRACKED         	B			EC3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	71RP				BN75458	1222				AEROQUIP VEE BAND CLAMP CRACKED STRAP BENEATH 'TEE' BOLT.  CLAMP SECURED 12TH STAGE DUCT BLANKING PLATE.  CRACK ALLOWED 	CLAMP TO FLEX THEN FAIL.  CLAMP AND PLATE EXITED EXHAUST THROUGH BYPASS SECTION.  DAMAGE TO BYPASS CASE OUTBOARD OF 12TH	 STAGE.				2	L	7	2 	4F			RT	A12EA   					 
2000021900129	20000219	00129	CE  	2000	2	19	2000ZZZX411      	1	20000120	G	8097	31B22207	WIRE            			CESSNA	172   	172S        	2072439	CE  										STARTER	FAILED          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	498SP	435  			85009816	172S8039				FIFTH FLIGHT OF THE DAY, ENGINE WOULD NOT START.  MAINTENANCE FOUND STARTER WOULD NOT MOTOR.  REMOVED STARTER AND REMOVE	D END CAP, FOUND TWO BRUSH LEADS MELTED WHERE THEY ATTACH TO THE BRUSHES.  REPLACED STARTER, OPERATIONAL CHECKED SATISFA	CTORY.				1	H	7	1 	3O			NT	3A12    					 
2000021900130	20000219	00130	WP  	2000	2	19	2000ZZZX412      	1	20000120	G	3246	26088851	WHEEL           		26088911    	DOUG  	DC9   	DC983       	3022083	WP  										MLG	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	598AA				B0172	53288				BROKEN HUB.  UNDER INVESTIGATION.						2	L	7	2 	4F			RT	A6WE    					 
2000021900131	20000219	00131	NM  	2000	2	19	2000ZZZX413      	1	20000120	G	3244		TIRE            			BOEING	737   	737*        		NM  										MLG	FAILED          	B			A3L2	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09										PARTIAL SEPARATION OF TIRE TREAD FROM THE CAUCUS.  UNDER INVESTIGATION.						2	L	7	2 	4F			RT	A16WE   					 
2000021900132	20000219	00132	CE  	2000	2	19	2000ZZZX414      	1	20000120	G	7810	HS783820041	BRACKET         			RAYTHN	DH125 	HAWKER800XP 		CE  										ENG TAILPIPE	CHAFED          	B	S		G1FR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	501F					258286				CHAFE DAMAGE OCCURRED TO BOTH ENGINE TAILPIPE V-CLAMPS, P/N 234-559-9019 (IPC REF 78-10-01, FIG 1, ITEM 15) AND INNER CO	RE COWL CHAFE BRACKET, P/N HS7838200-41 (IPC REF 78-30-05-05A, ITEM 245).  EACH ENGINE CONTAINS 8 BRACKETS AND 1 V-CLAMP	.  DAMAGE HAS OCCURRED AT SOME OR ALL BRACKET MOUNT  LOCATIONS WITH APPROXIMATE .020 INCH TO .090 INCH DEPTH WITH TOTAL 	EDGE SPAN OF 0.375 INCH ON THE BRACKETS AND APPROXIMATE .010 INCH TO .025 INCH DEPTH AT CONTACT LOCATIONS ON V-CLAMP.  T	HIS DAMAGE DISCOVERED DURING DISASSEMBLY AND REMOVAL OF ENGINE FOR 2100 HOUR HOT SECTION INSPECTION.  ACFT TT:  2,003.3 	HRS.  LANDINGS:  1,146.  LT ENG, SN 107124 TTSN 1,803.5 HRS, CSN 1,045.  RT ENG SN 107125 TTSN 2,003.3 HRS, CSN 1,161.	2	L	7	2 	4F			RT	A3EU    					 
2000021900135	20000219	00135	CE  	2000	2	19	2000ZZZX417      	1	20000121	G	3222	CPS6502	SEAL            			CESSNA	650   	650         	2076802	CE  										NLG STRUT	LEAKING         	A			CNQ3	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	13	97AL				259	6500155				UPON TAKEOFF, LANDING GEAR WOULD NOT RETRACT BECAUSE SQUAT SWITCH WAS NOT MADE FOR AIR MODE.  ADDITIONALLY, NOSE WHEEL W	AS DEFLECTED TO THE LEFT.  CAUSE WAS DETERMINED TO BE OLEO STRUT NOT EXTENDING COMPLETELY WHICH PREVENTED THE NOSE WHEEL	 FROM CENTERING, THEREBY, NOT ALLOWING THE SQUAT SWITCH TO MAKE FOR AIR MODE.  FOUND OLEO SEALS LEAKING BETWEEN AIR AND 	FLUID CHAMBERS.  REPACKED STRUT WITH NEW SEALS, AIRCRAFT FLIGHT CHECKED GOOD.			2	L	7	2 	4F				A9NM    					 
2000021900136	20000219	00136	WP  	2000	2	19	2000ZZZX418      	1	20000129	G	3244		TIRE            			DOUG  	DC9   	DC982       	3022082	WP  										MLG	DAMAGED         	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09										SEPARATION OF TIRE TREAD FROM TIRE CAUCUS.  UNDER INVESTIGATION.						2	L	7	2 	4F				A6WE    					 
2000021900137	20000219	00137	WP  	2000	2	19	2000ZZZX419      	1	20000120	G	3240		LINING          		26088921    	DOUG  	DC9   	DC982       	3022082	WP  										BRAKE ASSY	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B0978					BRAKE LININGS FAILURE.  CAUSE:  UNDETERMINED.						2	L	7	2 	4F				A6WE    					 
2000030100001	20000301	00001		2000	3	1	2000ZZZX488      	1	20000204	G	6123	C6536	COUNTERWEIGHT   													MCAULY	5JFR	C5JFR36C1104	GL  	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		11324	5878 							COUNTERWEIGHT CRACKED ON LOCATING RIDGE OF PROPELLER.																5	C	P15NE	 
2000030100002	20000301	00002		2000	3	1	2000ZZZX489      	1	20000202	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		2456 	1308 		MAY981325					BRAKE ASSEMBLY, PN 5010520-1, FAILED PREMATURELY.  ONE EACH, PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSEM	BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000030100003	20000301	00003		2000	3	1	2000ZZZX490      	1	20000203	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1478 			AUG981444					BRAKE ASSEMBLY, PN 5010520-1, FAILED PREMATURELY.  ONE EACH, PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSEM	BLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000030100005	20000301	00005	NM  	2000	3	1	2000ZZZX492      	1	20000129	G	2823	287N33009	CONDUIT         			BOEING	757   	75724APF    	1384969	NM  										NR 2 ENGINE	DAMAGED         	B	P		HN6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	419UP					23906				NR 2 ENGINE FUEL SHUT-OFF VALVE (SOV) CONDUIT IS DAMAGED AT FORWARD END AND WIRING INSULATOR IS PEELED OFF.						2	L	7	2 	4F			RT	A2NM    					 
2000030200002	20000302	00002		2000	3	2	2000ZZZX495      	4	20000113	G	2300	C23PU696701	REEL            	HUGHES      	C23PB620001 	BOEING	767   	767         	UTILUSE	NM  										PHONE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	CTEXT				135910122	339				PHONE REEL MELTED.						2	L	7	2 	4F			RT	A1NM    					 
2000030200005	20000302	00005	SO  	2000	3	2	2000ZZZX498      	1	20000117	G	5313		LONGERON        			PIPER 	PA18  	PA18        	7101802	SO  										FUSELAGE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										DURING LAST 6 AIRCRAFT RECOVERED BY FACILITY, 5 OF THESE AIRCRAFT HAD TO HAVE THE TOP LONGERON REPLACED BECAUSE OF CORRO	SION DUE TO WATER BEING TRAPPED UNDER THE SLIDING WINDOW CHANNEL ON THE LEFT SIDE.  IN ALL CASES, THE SLIDING CHANNELS I	N LONGERON AREA WERE SEVERELY CORRODED BEYOND JUST CLEANING AND HAD TO BE REPAIRED.				1	H	7	1 	3O				1A2     					 
2000030300012	20000303	00012		2000	3	3	2000ZZZX499      	1	20000202	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		2339 								BRAKE ASSEMBLY, PN 5010520-1, FAILED PREMATURELY.  ONE EACH, PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID. EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSY A	ND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.																	 
2000030300013	20000303	00013	SO  	2000	3	3	2000ZZZX500      	1	20000117	G	5320		CHANNEL         			PIPER 	PA18  	PA18        	7101802	SO  										FUSELAGE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										DURING RECOVERING OF AIRCRAFT, FOUND THE REAR WINDOW CHANNELS LEFT AND RIGHT WERE CORRODED BEYOND REPAIR AND HAD TO BE R	EPLACED.					1	H	7	1 	3O				1A2     					 
2000030900064	20000309	00064	GL  	2000	3	9	2000ZZZX564      	3	20000121	G	6111		BLADE           			PIPER 	PA30  	PA30        	7103002	SO  						HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	MISOVERHAULED   	B			M71R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	7887Y	3995 	219  			30973		BG3404		AIRCRAFT WAS IN GEAR UP LANDING IN 1995.  PROPELLER WAS OVERHAULED BY KANSAS PROPELLER AND AVIATION.  WO NR 1008.  SUBMI	TTER STATED DAMAGE IN PRELOAD SHOULD HAVE BEEN REJECTED IN 1995.					1	L	7	2 	3O				A1EA    		5	C	P9EA	 
2000030900065	20000309	00065	SO  	2000	3	9	2000ZZZX565      	1	20000121	G	5720	35770802	WEIGHT ASSY     			PIPER 	PA28  	PA28R201    	7102816	SO  										WING	CORRODED        	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	9436C	4177 				28R7837198				FOUND EXTENSIVE CORROSION ON BOTH STEEL PARTS OF THIS ASSEMBLY DURING 100-HOUR INSPECTION.						1	L	7	1 	3O				2A13    					 
2000030900066	20000309	00066	CE  	2000	3	9	2000ZZZX566      	1	20000306	G	3200	99121033	BOTTLE          	PACIFICSCIEN	18225901    	CESSNA	500   	500CESSNA   	2076602	CE  										MLG	LEAKING         	B			IBER	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	05	4918B				2543	5000102				NEW EMERGENCY BLOW DOWN BOTTLE LEAKING.  APPROXIMATELY 500 PSI IN 24-HOUR PERIOD.						1	L	7	2 	4F				A22CE   					 
2000030900067	20000309	00067	SO  	2000	3	9	2000ZZZX567      	2	20000111	G	8520		GEAR            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					CRANKSHAFT	DAMAGED         	B			TUPR	O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			NM	09	421PJ		1229 			421C0860	608138			ON ROLL-OUT AFTER LANDING, PILOT OBSERVED THE ENGINE HAD SHUT DOWN.  ON ATTEMPTED START, THERE WAS NO PROPELLER MOVEMENT	.  STARTER WAS CHECKED ON THE BENCH, AND STARTER ADAPTER WAS REMOVED FOR ENGINE TO REVEAL SEVERE GEAR DAMAGE TO THE MAIN	 CRANKSHAFT GEAR AND STARTER ADAPTER GEAR.  OTHER GEARS WERE DAMAGED DUE TO FOD FROM THE CRANK GEAR.  INITIAL OBSERVATIO	N INDICATED THE STARTER ADAPTER BEARINGS IN THE REAR OF ADAPTER AND THE FORWARD NEEDLE BEARING IN THE CRANKCASE WERE INT	ACT AND SECURE.		1	L	7	2 	3O	3	O		A7CE    	E7CE				 
2000030900069	20000309	00069	CE  	2000	3	9	2000ZZZX568      	1	20000124	G	3240	12801111	SWIVEL          			CESSNA	182   	R182        	2072734	CE  										BRAKE ASSY	LEAKING         	B			AMVR	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	05	4135C	8654 				R18200326				SWIVEL IS FOR BRAKE LINE AT MAIN GEAR.  PILOT SQUAWK OF PEDAL FOR RT BRAKE BLEEDS OFF, BRAKE FLUID ON BELLY.  INSPECTION	 OF SYSTEM UNDER PRESSURE SHOWED LEAK AT SWIVEL.  REPLACED SWIVEL.  SUBMITTER SUGGESTED CAUSE, AGE.					1	H	7	1 	3O			RT	3A13    					 
2000030900070	20000309	00070	CE  	2000	3	9	2000ZZZX569      	1	20000111	G	3230	08411132	ADJUST SCREW    			CESSNA	340   	340CESSNA   	2076404	CE  										RT MLG	FAILED          	B			AK6R	D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	19	5910M	3622 				3400067				UPON TAXI OFF OF THE RUNWAY AFTER AN UNEVENTFUL LANDING, THE PART SPECIFIED (0841113-2) FAILED CAUSING THE RIGHT MAIN GE	AR TO FOLD.  THE AIRCRAFT ROTATED AROUND CAUSING THE LEFT GEAR TO COLLAPSE.					1	L	7	2 	3O				3A25    					 
2000030900071	20000309	00071	SO  	2000	3	9	2000ZZZX570      	1	20000307	G	5720	2366200	FITTING         			PIPER 	PA24  	PA24250     	7102404	SO  										WS136	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5457P	3017 				24513				RIGHT WING ATTACHMENT FITTING STA 136 UNDER AFT BAGGAGE COMPARTMENT FLOOR.  PLATE, P/N 23662-00, AND FITTING, P/N 23663-	00, RIVETS GONE.					1	L	7	1 	3O				1A15    					 
2000030900073	20000309	00073	GL  	2000	3	9	2000ZZZX572      	3	20000117	G	6110	LW13335	BEARING         	LYC         	LW13081     	PIPER 	PA31  	PA31P       	7103120	SO  						HARTZL	HCC3Y	HCC3YN      	GL  	PROPELLER	FAILED          	B			EKIR	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			WP	07	7652L	521  				31P730012		D6237		OIL PRESSURE DROPPED TO UPPER YELLOW  AREA ON APPROACH TO LANDING.  FOUND FERROUS AND NON-FERROUS  METAL IN FILTER.  ENG	INE TORN DOWN, FOUND THRUSTBEARING BEARING BROKEN.  SUBMITTER SUSPECTED PIECES WENT THROUGH PROPELLER DRIVE AND DRIVE GE	ARS CAUSING DAMAGE TO BOTH GEARS.				1	L	7	2 	3O				A8EA    		5	C	P25EA	 
2000030900074	20000309	00074	NE  	2000	3	9	2000ZZZX573      	3	20000128	G	6111	D5133	EROSION SHIELD  		E10950PK    											HARTZL	HCE4A	HCE4A3A     	NE  	NR 1 PROPELLER	DAMAGED         	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01					2540			HJ717		REMOVED EROSION SHIELD PAD BOOT FROM NR 1 BLADE, SN 2540, BECAUSE MISSING .1250 INCH BY .50 INCH PIECE OF EROSION SHIELD	.  INSTALLED NEW EROSION SHIELD AND DE-ICE BOOT WITH EA9330 LOT NR 9228-1 IAW PROCEDURE 001, AND HARTZELL M 135F 61-13-3	5.  BALANCED IAW HARTZELL MM 143A 61-10-16.														5	C	P10NE	 
2000030900075	20000309	00075	NE  	2000	3	9	2000ZZZX574      	3	20000125	G	6111	D5133	EROSION SHIELD  		E10950PK    											HARTZL	HCE4A	HCE4A3A     	NE  	NR 2 PROPELLER	CRACKED         	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01					2315			HJ691		REMOVED EROSION SHIELD AND DE-ICE BOOT FROM NR 2 BLADE, S/N 2315, BECAUSE OUT OF LIMITS FOR CRACKS.  INSTALLED NEW EROSI	ON SHIELD AND DE-ICE BOOT IAW PROCEDURE 001 AND HARTZELL MM 135F 61-13-35 AND BALANCED IAW 143A 61-10-16.  USED HYSOL EA	9330 LOT NR 9228-1.														5	C	P10NE	 
2000030900076	20000309	00076	CE  	2000	3	9	2000ZZZX575      	1	20000111	G	3230	08411011	FITTIN          			CESSNA	340   	340CESSNA   	2076404	CE  										RT MLG	FAILED          	B			AK6R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	19		3622 				3400067				UPON TAXI OFF OF THE RUNWAY AFTER AN UNEVENTFUL LANDING, THE PART SPECIFIED (0841101-1) FAILED CAUSING THE RIGHT MAIN GE	AR TO FOLD.  THE AIRCRAFT ROTATED AROUND CAUSING THE LEFT GEAR TO COLLAPSE.					1	L	7	2 	3O				3A25    					 
2000030900077	20000309	00077	EA  	2000	3	9	2000ZZZX576      	2	20000107	G	8530		CYLINDER        			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					RT ENGINE	SEPARATED       	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	6892R					600887816125	L2082548A			BGM - RIGHT ENGINE, NR 2 CYLINDER, SEPARATED.  SUBMITTER STATED CAUSE UNKNOWN AT THIS TIME.  WILL REMOVE AND REPLACE ENG	INE, FLUSH PROPELLER, AND PROPELLER GOVERNOR BEFORE FLIGHT.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000030900079	20000309	00079	SW  	2000	3	9	2000ZZZX578      	1	20000209	G	7714	407375002103	INDICATOR       			BELL  	407   	407         		SW  										ENGINE NG	MALFUNCTIONED   	B			GS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	407WH	369  			0039	532027				NG INDICATOR MALFUNCTIONED.  REPLACED WITH NEW INDICATOR FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW    					 
2000030900080	20000309	00080	SO  	2000	3	9	2000ZZZX579      	2	20000125	G	8500		ENGINE          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LEFT	MAKING METAL    	H				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	07	58TA					TH596	299134R			ELM - LEFT ENGINE SHUT DOWN BY ITSELF IN-FLIGHT.  ENGINE HAD PLENTY OF OIL, NO EXTERNAL LEAKS OR CRACKS, OIL FILTER FULL	 OF METAL.  SUBMITTER STATED CAUSE UNKNOWN AT THIS TIME.					1	L	7	2 	3O	3	O		3A16    	E5CE				 
2000030900081	20000309	00081	SO  	2000	3	9	2000ZZZX580      	1	20000201	G	2731		PULLEY          			PIPER 	PA12  	PA12        	7101202	SO  										ELEVATOR	WORN            	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	3168M	3100 				121847				FOUND TRIM PULLEY AND SHAFT HAD WORN EXCESSIVELY INTO BRACKETS.  WELDED TO AIRCRAFT (THIS IS TRIM CRANK IN COCKPIT) CAUS	ED TRIM TO BIND UP.					1	H	7	1 	3O				A780    					 
2000031700001	20000317	00001	EU  	2000	3	17	2000ZZZX581      	1	20000211	G	2800	B97E51254	VALVE           			AMD   	FALC20	FALCON20F5  	2730105	EU  										RT WING	MALFUNCTIONED   	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	SUAYD					361				RIGHT WING REFUEL VENT VALVE OPERATES INCORRECTLY AFTER OVERHAUL.  WHEN POWER IS APPLIED TO THE 'OPEN' CIRCUIT, VALVE RU	NS TO THE CLOSED POSITION AND THE VALVE POSITION INDICATOR (MECHANICAL INDICATES CLOSED.  ELECTRICALLY, THE VALVE INDICA	TES OPEN.				2	L	7	2 	4F			RT	A7EU    					 
2000031700002	20000317	00002	WP  	2000	3	17	2000ZZZX582      	2	20000103	G	7250	30723515	DISK            								GARRTT	TFE731	TFE7313R1H  	29001	WP  					LP TURBINE	FAILED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		2419 	2148 		103229852		P80131C			ENGINE RECEIVED WITH TURBINE DAMAGE.  FIELD REPORT REVEALED THIS ENGINE EXPERIENCED AN IN-FLIGHT SHUT DOWN AT FL 350.  D	URING TEAR DOWN, THE LPT1 ROTOR ASSY HAD ALL BLADES BROKEN OFF JUST ABOVE THE FIR TREE AREA.  ONE LPT1 BLADE COULD NOT B	E FOUND.  DISK GROWTH MEASURED 0.060 INCH.  SUBMITTER SUSPECTED BLADE RELEASE.  (X)									4	F			E6WE				 
2000031700003	20000317	00003	CE  	2000	3	17	2000ZZZX583      	1	20000207	G	5320		RIVET           			LEAR  	55    	55C         	5170706	CE  											MISINSTALLED    	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	PTGMN	2261 				139				SIX RIVETS MISSING FROM RT FUSELAGE BETWEEN MIDDLE AND AFT WING ATTACH POINTS.  BS 401.92 AND BS 410.30.  THESE RIVETS D	O NOT GO THROUGH THE PRESSURE VESSEL, BUT DO GO THROUGH RT FUSELAGE OVERWING LONGERON.  THREE RIVETS MISSING FROM AFT SI	DE OF MIDDLE ATTACH FITTING AND THREE RIVETS MISSING FROM AFT SIDE OF AFT ATTACH POINT.  (X)				2	L	7	2 	4F			RT	A10CE   					 
2000031700004	20000317	00004		2000	3	17	2000ZZZX584      	1	20000223	G	2810		CELL            	DURACELL    	PORAPREFI   																CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25										FUEL CELLS CRACKING INTERNALLY IF TANKS ARE NOT TOPPED OFF.  HAVE RECEIVED 28 OF SUCH CELLS SINCE 11-30-99.  CELLS ARE O	F FAA APPROVED MATERIAL, ETC.  SUBMITTER CONCERNED ABOUT THEIR RELIABILITY IN THE FUTURE IN THAT THERE ARE A LOT OF THES	E CELLS OUT THERE.  HAVE ADVISED MANUFACTURING INSPECTOR IN ATLANTA, GA OF THE PROBLEM TODAY, 2-24-00, AFTER FINDING RET	URNS IN LOG BOOK.  (X)																 
2000031700005	20000317	00005		2000	3	17	2000ZZZX585      	1	20000217	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1719 			DEC981559					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  TWO EACH, PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY F	ILLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OE	M PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.  (X)																	 
2000031700006	20000317	00006		2000	3	17	2000ZZZX586      	1	20000224	G	3240	7010FS9545708	SEAL            		50105201    															BRAKY ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1292 			APR991672					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  ONE EACH, PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FIL	LED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OEM 	PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.  (X)																	 
2000031700007	20000317	00007		2000	3	17	2000ZZZX587      	1	20000224	G	3240	7010FS9545708	SEAL            		50105201    															BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		2195 			APR981272					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  FIVE EACH, PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY 	FILLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE A	SSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.  (X)																	 
2000031700008	20000317	00008	WP  	2000	3	17	2000ZZZX588      	2	20000207	G	7250	30720695	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322903007					NEW PART RECEIVED FROM HONEYWELL WITH NICKS AND SCRATCHES IN POST FIR TREE AREA, TWO PLACES ON EACH SIDE.  (X)											4	F			E6WE				 
2000031700009	20000317	00009	WP  	2000	3	17	2000ZZZX589      	2	20000204	G	7250	30720695	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322903661					NEW PART RECEIVED FROM HONEYWELL WITH STEP IN WEB AROUND CURVIC AREA ON FORWARD SIDE OF DISK; ALSO, HAS NICKS IN FIR TRE	E AREA ON BOTH SIDES OF DISK.  (X)										4	F			E6WE				 
2000031700010	20000317	00010	WP  	2000	3	17	2000ZZZX590      	2	20000204	G	7250	30720695	DISK            								GARRTT	TPE331	TPE331*     	01514	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH ROUGH SPOTS IN WEB AREA ROUND DISK ON FORWARD SIDE; ALSO, NICKS IN POST FIR TREE A	REA ON AFT SIDE.  (X)										3	T			E2WE				 
2000031700011	20000317	00011	WP  	2000	3	17	2000ZZZX591      	2	20000208	G	7250	30720695	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH SCRATCHES IN WEB AREA THAT CAN BE FELT WITH AN .080 INCH STYLIST ON FORWARD SIDE; 	ALSO, ONE NICK IN POST FIR TREE AREA ON FORWARD SIDE.  (X)										4	F			E6WE				 
2000031700012	20000317	00012	WP  	2000	3	17	2000ZZZX592      	2	20000120	G	7261	31032173	SHAFT           								GARRTT	TPE331	TPE33112UA  	01514	WP  					OIL PUMP	SHEARED         	B			UO2R	O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	19			2568 		9714075319		P66184			ENGINE EXPERIENCED AN IN-FLIGHT SHUT DOWN CAUSED BY OIL PUMP SHAFT SHEARED.  (X)											4	T			E4WE				 
2000031700013	20000317	00013	WP  	2000	3	17	2000ZZZX593      	2	20000125	G	7250	30723515	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	DAMAGED         	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322902774					NEW PART RECEIVED FROM HONEYWELL WITH DISK WEB DAMAGE.  (X)											4	F			E6WE				 
2000031700014	20000317	00014	WP  	2000	3	17	2000ZZZX594      	2	20000128	G	7250	30723163	DISK            								GARRTT	TPE331	TPE331*     	01514	WP  					HP TURBINE	NICKED          	B			UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19					990322900255					NEW PART RECEIVED FROM HONEYWELL WITH CURVIC NICKS AT FIR TREE AREA.  (X)											3	T			E2WE				 
2000031700015	20000317	00015	WP  	2000	3	17	2000ZZZX595      	2	20000128	G	7230	30724434	PLENUM          								GARRTT	TPE331	TPE331*     	01514	WP  					COMPRESSOR	MISMANUFACTURED 	B			UO2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19		5991 			OP51825					REPAIRED PART FROM HONEYWELL.  DIM. C OUT OF LIMITS.  (X)											3	T			E2WE				 
2000031700016	20000317	00016	WP  	2000	3	17	2000ZZZX596      	2	20000209	G	7250	30720695	DISK            								GARRTT	TFE731	TFE731*     	01518	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322903684					NEW PART RECEIVED FROM HONEYWELL WITH NICKS IN BORE REGION ON AFT SIDE.  (X)											4	F			E6WE				 
2000031700017	20000317	00017	WP  	2000	3	17	2000ZZZX597      	2	20000125	G	7250	30723515	DISK            								GARRTT	TPE331	TPE331*     	01514	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19										NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS. (X)											3	T			E2WE				 
2000031700018	20000317	00018	WP  	2000	3	17	2000ZZZX598      	2	20000125	G	7250	30723515	DISK            								GARRTT	TPE331	TPE331*     	01514	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322902797					NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS.  (X)											3	T			E2WE				 
2000031700019	20000317	00019	WP  	2000	3	17	2000ZZZX599      	2	20000125	G	7250	30723515	DISK            								GARRTT	TPE331	TPE331*     	01514	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322902992					NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS.  (X)											3	T			E2WE				 
2000031700020	20000317	00020	WP  	2000	3	17	2000ZZZX600      	2	20000125	G	7250	30723515	DISK            								GARRTT	TPE331	TPE331*     	01514	WP  					LP TURBINE	NICKED          	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19					990322902819					NEW PART RECEIVED FROM HONEYWELL WITH CURVIC TEETH DAMAGE, NICKS.  (X)											3	T			E2WE				 
2000031700021	20000317	00021	GL  	2000	3	17	2000ZZZX601      	3	20000207	G	6111	8433	BLADE           			TEMCO 	11A   	11A         	8890402	CE  						HARTZL	HCD2X	HCD2X207    	GL  	V SHANK	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B68357			AV128		PROPELLER BLADE CRACKED IN V SHANK.  (ADP)						1	H	7	1 	3O				TC804   		5	C	P917	 
2000031700022	20000317	00022		2000	3	17	2000ZZZX602      	1	20000210	G	3230	23171025	PISTON          	LEAR        																MLG	MISMANUFACTURED 	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09					RH0249					RECEIVED NEW PISTON INSTALLED BALL HOUSING AND BALLS.  INSTALLED PLUNGER, BUT WAS UNABLE TO GET IT INTO LOCKING POSITION	.  FOUND BALL LOCK GROOVE .015 INCH BELOW FROM THE OLD PISTON.  (X)																		 
2000031700023	20000317	00023	SO  	2000	3	17	2000ZZZX603      	2	20000217	G	7414	6320	MAGNETO         	SLICK       		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					ENGINE	FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	21	198PS	449  			97110674	3449051				MAGNETO FAILED IN-FLIGHT.  FOUND SEVERE DAMAGE TO DISTRIBUTOR FROM ARCING.  ARCING APPEARED TO HAVE STARTED BEWEEN COIL 	AND REAR BEARING HOUSING.  SUBMITTER STATED CAUSE UNKNOWN.  (X)					1	L	7	2 	3O	3	O		A7SO    	E9CE				 
2000031700025	20000317	00025	CE  	2000	3	17	2000ZZZX605      	1	20000217	G	5540	96630000333	RUDDER MAST     			BEECH 	58    	58TC        	1152746	CE  										RUDDER	DAMAGED         	B	P	A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	23712	3194 				TK67				WHILE INSPECTING AIRCRAFT, FOUND RUDDER WAS LOOSE AT THE ATTACHMENT TO RUDDER CABLE BELLCRANK.  REMOVED BOLTS AND FOUND 	2 EACH BOLT HOLES ELONGATED.  SUBMITTER STATED CAUSE UNKNOWN, BOLTS WERE TIGHT.  SUBMITTER SUGGESTED CLOSE INSPECTION OF	 THIS AREA AT INSPECTION TIME.  FREE PLAY WAS SLIGHT AND COULD BE EASILY MISSED, BUT COULD CAUSE FLIGHT CONTROL FLUTTER.	   (X)			1	L	7	2 	3O				A23CE   					 
2000031700026	20000317	00026	CE  	2000	3	17	2000ZZZX606      	1	20000217	G	5540	0025240761	BELLCRANK       			BEECH 	58    	58TC        	1152746	CE  										RUDDER	DAMAGED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	23712	3194 				TK67				WHILE INSPECTING AIRCRAFT, FOUND RUDDER WAS LOOSE AT THE ATTACHMENT TO RUDDER CABLE BELLCRANK.  REMOVED BOLTS AND FOUND 	2 EACH BOLT HOLES ELONGATED.  SUBMITTER STATED CAUSE UNKNOWN, BOLTS WERE TIGHT.  SUBMITTER SUGGESTED CLOSE INSPECTION OF	 THIS AREA AT INSPECTION TIME.  FREE PLAY WAS SLIGHT AND COULD BE EASILY MISSED, BUT COULD CAUSE FLIGHT CONTROL FLUTTER.	  (X)			1	L	7	2 	3O				A23CE   					 
2000031700027	20000317	00027	SW  	2000	3	17	2000ZZZX607      	1	20000105	G	3233		BOLT            			MOONEY	M20   	M20J        	5870219	SW  										MLG ACTUATOR	MISINSTALLED    	H		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	1077V					243160				A SITUATION OCCURRED WHERE THE PILOT NOTICED A HIT IN THE CONTROL SYSTEM WHEN THE LANDING GEAR WAS RETRACTED.  IT WAS DE	TERMINED THE FORWARD GEAR ACUTATOR BOLT HAD BEEN INSTALLED INCORRECTLY, HAD CONTACTED THE RUDDER INTERCONNECT PIVOT POIN	T, AND HAD DEFORMED THE ATTACH POINT THAT WHENEVER THE GEAR WAS RETRACTED IT HIT IT.  IT IS RECOMMENDED THAT INSPECTION 	BE MADE WHENEVER THE ACTUATOR AREA IS ACCESSED TO CONFIRM THE ACTUATOR BOLT IS INSTALLED CORRECTLY.  (BOLT HAD FACING LE	FT).		1	L	7	1 	3O				2A3     					 
2000031700028	20000317	00028	NM  	2000	3	17	2000ZZZX608      	1	20000124	G	3230		CAM             			BOEING	767   	767332      	1382001	NM  										MLG	DAMAGED         	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	174DN					24802				PARTS WERE RECEIVED AT B. F. GOODRICH AEROSPACE LOCATED IN OPA-LOCKA, FLORIDA.  THE INTERNAL PARTS ARE DAMAGED BEYOND RE	PAIR.  SUBMITTER STATED THE DAMAGES TO UPPER AND LOWER CAMS COULD HAVE BEEN A RESULT OF A DISLODGED SUPPORT PIN LOCATED 	I THE LOWER CAM.  (X)				2	L	7	2 	4F			RT	A1NM    					 
2000031700029	20000317	00029	GL  	2000	3	17	2000ZZZX609      	3	20000207	G	6114		HUB             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	BLADE SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2744B		188  			340A0940		797794		PROPELLER HUB CRACKED IN BLADE SOCKET. (ADP)						1	L	7	2 	3O				3A25    		5	C	P22EA	 
2000031700030	20000317	00030	GL  	2000	3	17	2000ZZZX610      	3	20000207	G	6114	C7036	NUT             			CESSNA	340   	340A        	2076405	CE  						MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER HUB	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2744B		188  			349A9849		797794		LOCK NUT CRACKED IN THREADED AREA OF PROPELLER HUB.  (X)						1	L	7	2 	3O				3A25    		5	C	P22EA	 
2000031700031	20000317	00031		2000	3	17	2000ZZZX611      	4	20000208	G	3416	KEA346	ALTIMETER       	BENDIX      		BEECH 	1900  	1900D       	1154162	CE  										COCKPIT	INOPERATIVE     	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	254GL		848  		2857	UE254				ENCODER INOPERATIVE.  (X)						2	L	7	2 	4T			RT	A24CE   					 
2000031700032	20000317	00032		2000	3	17	2000ZZZX612      	4	20000208	G	3416	KEA346	ALTIMETER       	BENDIX      		BEECH 	1900  	1900D       	1154162	CE  										COCKPIT	INOPERATIVE     	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	201YQ		790  		4510	UE201				ALTIMETER FLAGGED AT 4,200 FEET AND REMAINED INOPERABLE.  VERIFIED ON BENCH.  (X)						2	L	7	2 	4T			RT	A24CE   					 
2000031700033	20000317	00033		2000	3	17	2000ZZZX613      	4	20000208	G	3416	KEA346	ALTIMETER       	BENDIX      		BEECH 	1900  	1900D       	1154162	CE  										COCKPIT	READS HIGH      	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	257GL		107  		1381	UE257				ENCODER READS 200 FEET HIGH.  PROBLEM VERIFIED ON BENCH.  (X)						2	L	7	2 	4T			RT	A24CE   					 
2000031700034	20000317	00034	CE  	2000	3	17	2000ZZZX614      	1	20000224	G	3252		SHIMMY DAMPENER 		17430213    	CESSNA	177   	177B        	2073708	CE  										MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	35033	100  				177022169				AFTER REPLACING AN OLD SHIMMY DAMPENER WITH A NEW ONE AT APPROXIMATELY 100 HOURS IN SERVICE, THE NEW PART BROKE AT THE O	UTER C-CLAMP RING SPLITTING THE OUTER CYLINDER CASE.  THIS HAPPENED AS THE AIRCRAFT STOPPED SHIMMING.  THE END PLUG, C-C	LAMP AND ALL FLUID WERE LOST.  NO INJURIES TO OCCUPANTS.  THIS IS THE NEW STYLE CYLINDER.  SUBMITTER STATEDTHIS CYLINDER	 MAY NEED MORE END DISTANCE OR THICKNESS.  PART TOTAL TIME, 100 HOURS.  (X)			1	H	7	1 	3O				A13CE   					 
2000031700077	20000317	00077	CE  	2000	3	17	2000ZZZX615      	1	20000204	G	5210	NAS130534H	BOLT            			BEECH 	MU300 	400A        	1155402	CE  										DOOR HINGE	LOOSE           	B			QMZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	295FA	2660 				RK68				AT AN A-INSPECTION, TECHNICAN FOUND DOOR HINGE WASHERS OUT OF ALIGNMENT, AND THEY COULD BE REMOVED BY HAND.  GAINED ACCE	SS TO HINGE BOLTS.  FOUND SAFETY WIRE AND TORQUE SEAL BROKEN ON BOTH BOLTS, AND BOLTS WERE BACKING OUT OF CAPTIVE NUTS. 	 REMOVED BOLTS, INSPECTED, RE-INSTALLED, AND SAFETIED.				2	H	7	2 	4F			RT	A16SW   					 
2000031700078	20000317	00078	EA  	2000	3	17	2000ZZZX616      	2	20000204	G	8520	LW10545S	PISTON          			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	2336V					31135	RL472661A			ENGINE WAS 438 HOURS FROM FACTORY REMANUFACTURE.  REMOVED LONER PLUG FROM NR 3 CYLINDER AND FOUND CYLINDER HAD EXCESSIVE	 OIL IN PLUG.  REMOVED CYLINDER AND FOUND THE OIL CONTROL RING LAND AND PISTON PIN HOLE WERE EXCESSIVELY PITTED AND CORR	ODED.  ENGINE WAS REPORTED AS NEEDING TO 'CLEAR ITS THROAT' BEFORE IT WOULD RUN SMOOTH.				1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
2000031700079	20000317	00079	CE  	2000	3	17	2000ZZZX617      	1	20000105	G	3233	1CH16	SWITCH          			LEAR  	35    	35A         	5170602	CE  										LT MLG ACTUATOR	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	15WH					85				GOING INTO BWI, HAD TO CYCLE GEAR 3 TIMES TO LET LEFT GEAR TO SHOW DOWN AND LOCK INDICATION.  FERRIED AIRCRAFT BACK TO C	MH.  REMOVED AND REPLACED LEFT GEAR ACTUATORS SWITCH.  OPS CHECKED GOOD.					2	L	7	2 	4F				A10CE   					 
2000031700081	20000317	00081	SO  	2000	3	17	2000ZZZX619      	2	20000210	G	8530		EXHAUST VALVE   			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	STUCK           	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	11	11567		738  			15075527	2047329A			AIRCRAFT LOST POWER WHEN PERFORMING 'TOUGH AND GOES'.  AIRCRAFT LANDED APPROXIMATELY 150 FEET FROM THE END OF THE RUNWAY	.  AN INVESTIGATION HAS DETERMINED THE MOST POSSIBLE CAUSE OF THE ENGINE'S POWER LOSS WAS AN EXHAUST VALVE THAT WAS INTE	RMITTENTLY STUCK 'OPEN'.  AIRCRAFT WAS SUBSTANTIALLY DAMAGED.				1	H	7	1 	3O	3	O		3A19    	E252				 
2000010800520	20000108	00520	EA  	2000	1	8	2000ZZZX62       	2	20000105	G	7322	1552113	AIRBOX          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	MISREPAIRED     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	13613					17262885				AIRCRAFT LANDED WITH A ROUGH RUNNING ENGINE WITH BLACK SMOKE EXITING FROM THE EXHAUST PIPE.  UPON INSPECTION OF THE AIRB	OX, NOTED THERE WAS SEAL MATERIAL MISSING FROM THE DIVERTER SEAL AND THAT A NUMBER OF AUTOMOTIVE STYLE POP RIVETS WERE M	ISSING FROM A PREVIOUS REPAIR ON THE AIRBOX.  THE SEAL WAS ALSO ADJUSTED WRONG SO THERE WAS PARTIAL CARBURETOR HEAT BEIN	G APPLIED WHEN THE DASH CONTROL WAS IN THE CLOSED POSITION.  THE CESSNA MM WAS USED AS A TROUBLESHOOTING GUIDE AND IT WA	S DETERMINED THAT WITH PARTIAL CARBURETOR HEAT, THERE WAS LOW STATIC RPM RUN-UP, 2,050 RPM, MAG TIMING WAS OFF, RT MAG W	AS SET FOR 30 - 31 DEGREES BTDC AND THE LT MAG WAS SET FOR 24 DEGREES BTDC, FACTORY SPEC IS 25 BTDC ON BOTH.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000031700082	20000317	00082		2000	3	17	2000ZZZX620      	1	20000203	G	2460		HARNESS         																	FUSELAGE	CHAFED          	B			XE5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	21		292  								CHAFING OF WIRE BUNDLES IS OCCURRING WHERE BUNDLES PASS THROUGH THE FUME SEALS INTO THE EFC BOX.  SB 71-C716 ADDRESSES T	HIS ISSUE.																		 
2000031700083	20000317	00083		2000	3	17	2000ZZZX621      	4	20000120	G	2562	DURACELLD	BATTERY         	ACK         	E01         	PIPER 	PA32  	PA32RT300T  	7103216	SO  										ELT	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	2172B				013496	32R7987034				REMOVED ELT TO PERFORM INSPECTION PER FAR 91.2079D0.  ELT WAS FOUND INOPERATIVE.  DISASSEMBLY FOUND FOUR OF THE EIGHT BA	TTERIES SPLIT.  REPLACEMENT DATE WAS 3/03.					1	L	7	1 	3O				A3SO    					 
2000031700084	20000317	00084	CE  	2000	3	17	2000ZZZX622      	1	20000119	G	5710	5368R	STRUT           			BBAVIA	8     	8KCAB       	2110612	CE  										RT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	2962Z	1548 				37978				DURING ANNUAL INSPECTION, FOUND RT WING FORWARD LIFT STRUT, LOWER MOUNT AREA (ON STRUT) SEVERELY CORRODED (EXFOLIATION) 	AND CRACKED APPROXIMATELY 3 INCHES LONG FROM MOUNT BOLT HOLE UPWARD.  AREA IS HIDDEN UNDER FAIRING.  SPECIFIC CAUSE IS U	NKNOWN.  REPLACED PART WITH FACTORY NEW ITEM.  SUBMITTER RECOMMENDED CLOSE ATTENTION TO COVERED AREAS DURING INSPECTIONS	.			1	H	7	1 	3O				A21CE   					 
2000031700085	20000317	00085	EU  	2000	3	17	2000ZZZX623      	1	20000201	G	2121	10089782105	COOLING FAN     			AMD   	FALC50	FALCON900   	2700160	EU  										E/E BAY	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	03	14NA	1902 			AFJ813	124				TWO HOURS AFTER TAKEOFF, A HEAVY ELECTRICAL ODOR AND SMELL WAS NOTICED BY THE CREW IN THE CENTER PEDESTAL AREA.  A PRECA	UTIONARY LANDING WAS EXECUTED.  MAINTENANCE FOUND THE SOURCE OF THE SMOKE FROM THE NR 3 IRS COOLING FAN INVERTER.  THE D	EFECTIVE INVERTER AND FAN WERE REPLACED AND AN OPERATION CHECK OF THE SYSTEM PERFORMED.  HONEYWELL TECH NEWSLETTER M23-3	341-011-00 ADDRESSES THIS PROBLEM AND SUGGESTS REPLACING THIS KIT.  SUBMITTER STATED THE NEW KIT IS NOT ELIGIBLE FOR INS	TALLATION ON THIS MODEL AIRCRAFT.		2	L	7	3 	4F			RT	A46EU   					 
2000031700086	20000317	00086	EU  	2000	3	17	2000ZZZX624      	1	20000201	G	2121	10089782105	COOLING FAN     			AMD   	FALC50	FALCON900   	2700160	EU  										E/E BAY	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	03	14NA	1902 			AFG863	124				TWO HOURS AFTER TAKEOFF, A HEAVY ELECTRICAL ODOR AND SMELL WAS NOTICED BY THE CREW IN THE CENTER PEDESTAL AREA.  A PRECA	UTIONARY LANDING WAS EXECUTED.  MAINTENANCE FOUND THE SOURCE OF THE SMOKE FROM THE NR 3 IRS COOLING FAN INVERTER.  THE D	EFECTIVE INVERTER AND FAN WERE REPLACED AND AN OPERATION CHECK OF THE SYSTEM PERFORMED.  HONEYWELL TECH NEWSLETTER M23-3	341-011-00 ADDRESSES THIS PROBLEM AND SUGGESTS REPLACING THIS KIT.  SUBMITTER STATED THE NEW KIT IS NOT ELIGIBLE FOR INS	TALLATION ON THIS MODEL AIRCRAFT.		2	L	7	3 	4F			RT	A46EU   					 
2000031700087	20000317	00087	SO  	2000	3	17	2000ZZZX625      	2	20000314	G	8520	633945	MANIFOLD        			CESSNA	421   	421         	2076010	CE  	CONT  	O520  	GTSIO520D   	17032	SO  					ENGINE	CRACKED         	B	S		MI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3121K					42100102				DURING ANNUAL INSPECTION, A CRACK EXTENDING ABOUT 2 INCHES EACH SIDE OF THE THREADED BOSS.  THE BOSS HAD BEEN DRILLED AN	D TAPPED FOR A HELICOIL.  THREADED BOSS IS FOR ATTACHING THE INTERCOOLER.					1	L	7	2 	3O	3	O	RT	A7CE    	E7CE				 
2000031700088	20000317	00088	CE  	2000	3	17	2000ZZZX626      	1	20000314	G	5410	505403033	BEAM            			CESSNA	421   	421         	2076010	CE  										LT NACELLE	CRACKED         	B			MI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	3121K					42100102				THE LEFT ENGINE AFT BEAM ASSEMBLY IS CRACKED.  CRACK IS AT THE OUTBOARD BEAM ASSEMBLY (P/N 5054030-13) ATTACHMENT POINT 	AT THE TOP SIDE, AFT END, EXTENDING 1.1250 INCHES.  THE OUTBOARD BEAM ASSEMBLY (5054030-13) ALSO HAD 3 RIVETS WITH HEADS	 MISSING ON THE INBOARD ROW OF RIVETS.  THESE RIVETS ARE THE 7TH, 8TH, AND 9TH RIVETS COUNTING FORWARD FROM THE AFT BEAM	 ASSEMBLY.			1	L	7	2 	3O			RT	A7CE    					 
2000031700091	20000317	00091	EA  	2000	3	17	2000ZZZX629      	2	20000208	G	8530	SL14995	RETAINER CUP    		SLC36100B   	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					PUSH ROD HOUSING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	3659R	346  				285762	L1480036A			ON ANNUAL INSPECTION, ROCKER COVERS REMOVED FOR GASKET LEAKS.  FOUND PUSH ROD RETAINERS ON NR 1 AND NR 2 CYLINDERS BROKE	N.  THESE WERE SUPERIOR MILLENIUM CYLINDERS WITH 346 HRS SINCE NEW.  SUBMITTER STATED PROBLEM IS BELIEVED TO BE INSUFFIC	IENT SURFACE AREA FOR THE RETAINER TO SEAT AGAINST.				1	L	7	1 	3O	3	O		2A13    	E286				 
2000031700092	20000317	00092		2000	3	17	2000ZZZX630      	4	20000208	G	2561	VS357017211	LIFE VEST       	SWITLIK     																CABIN	FAILED          	B			KQ1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED MANUFACTURER'S RECOMMENDED 2 PSI TEST.  DOM:  MAY 1981.																			 
2000031700093	20000317	00093	EA  	2000	3	17	2000ZZZX631      	1	20000214	G	3240	7010FS9545708	SEAL            		50105201    	CNDAIR	CL600 	CL6002B19   		EA  										BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1236 			JUN981360					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. ONE EACH PISTON  LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FILL	ED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  FACTORY NEW BRAKE ASSEMBLY.  NOTE:  OEM P	ARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.				2	L	7	2 	4F			RT	A21EA   					 
2000031700094	20000317	00094	EA  	2000	3	17	2000ZZZX632      	1	20000214	G	3240	7010FS9545708	SEAL            		50105201    	CNDAIR	CL600 	CL6002B19   		EA  										BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		1842 			APR981284					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY. TWO EACH, PISTONS LEAKING FROM INSULATOR AREA.  PISTONS INTERNALLY FI	LLED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASS	EMBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.				2	L	7	2 	4F			RT	A21EA   					 
2000031700095	20000317	00095	SO  	2000	3	17	2000ZZZX633      	1	20000125	G	2140	764340	SHUT OFF VALVE  			PIPER 	PA30  	PA30        	7103002	SO  										HEATER	WORN            	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	23	8486Z	850  				30227				VALVE FOUND LEAKING AFTER LANDING.  FUEL HAD TRAVELED DOWN FORWARD BULKHEAD IN NOSE SECTION AND FOUND ITS WAY INSIDE AIR	CRAFT BETWEEN BELLY SKINS AND GATHERED IN GEAR TRANSMISSION COMPARTMENT.  O-RING IS EXPECTED TO HOLD BACK DIRECT FUEL PR	ESSURE OF 26 POUNDS WHEN VALVE IS OPEN.  VALVE SHOULD BE REPLACED WITH MORE MODERN DESIGN.  HAVE FOUND OTHERS WHERE PACK	ING NUT WAS NOT DRILLED FOR SAFETY WIRE.  PACKING NUT SUBJECT TO ROTATION.			1	L	7	2 	3O				A1EA    					 
2000031700096	20000317	00096	WP  	2000	3	17	2000ZZZX634      	1	20000203	G	7120	777111232	BOLT            			DOUG  	DC8   	DC871F      	302199D	WP  										ENGINE MOUNT	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	828BX					45993				DURING INSTALLATION AND TIGHTENING OF BOLTS THAT SECURE THE FORWARD ENGINE MOUNT TO THE PYLON, ONE BOLT BROKE IN TWO AND	 ANOTHER BOLT STRIPPED.  THIS OCCURRED PRIOR TO THE BOLTS REACHING FINAL TORQUE.  THIS IS CURRENTLY BEING INVESTIGATED B	Y BOEING AND IS ALSO BEING TRACKED BY GEES SAFETY PRODUCT MANAGEMENT TEAM (SPMT).				2	L	7	4 	4F			RT	4A25    					 
2000031700097	20000317	00097	SO  	2000	3	17	2000ZZZX635      	1	20000212	G	7922	53E19600	BYPASS VALVE    	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  										OIL COOLER	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	202HF	2000 			56713	317405437				LYCOMING SB 518C, DATED 5-2-95, STATES THAT THERMOSTATIC BYPASS VALVES (TBV), P/N 53E19600 WITH S/N/S 53788 AND HIGHER A	RE NOT SUBJECT TO THE SB INSPECTION.  DURING ENGINE REMOVAL, THE TBV (P/N 53E19600, S/N 56713) RETAINING NUT WAS FOUND S	EPARATED FROM THE TBV AND LOCATED IN THE OIL COOLER.  SUBMITTER RECOMMENDED TO REQUIRE HIGHER SERIAL NUMBERED TBV'S TO T	HE INSPECTION REQUIREMENT OF THE SERVICE BULLETIN.			1	L	7	2 	3O				A20SO   					 
2000031700099	20000317	00099	CE  	2000	3	17	2000ZZZX637      	1	20000120	G	2820	0700147137	LINE            			CESSNA	185   	A185F       	2072821	CE  										FUEL SYSTEM	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	714QK	140  				18504410				FUEL PRESSURE LINE BROKEN AT FITTING (FIREWALL TO ENGINE).						1	H	7	1 	3O				3A24    					 
2000031700100	20000317	00100	CE  	2000	3	17	2000ZZZX638      	1	20000314	G	3230	508202043	DRAG BRACE      			BEECH 	90    	65A90       	1152908	CE  										NLG	CRACKED         	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	615AA					LJ298				DURING AN AFTER-FLIGHT INSPECTION OF THE NOSE WHEEL BAY AREA, A CRACK WAS NOTICED EXTENDING FROM THE LUBRICATOR UPON THE	 NLG BRACE.  UPON INSPECTION, NOTED THIS NLG BRACE WAS OF THE OLDER STYLE.					1	L	7	2 	3T				3A20    					 
2000031700115	20000317	00115	CE  	2000	3	17	2000ZZZX640      	1	20000203	G	2140	721526	PUMP            			CESSNA	310   	310R        	2074245	CE  										HEATER	FAILED          	B			BXSR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	123RA	2    				310R0221				PILOT REPORTED THE HEATER WAS INOPERATIVE.  TROUBLESHOOTING FOUND THE HEATER FUEL PUMP HAD FAILED, AND THAT IT WAS PUMPI	NG FUEL OUT AROUND THE PUMP SHAFT.  (X)					1	L	7	2 	3O				3A10    					 
2000031700116	20000317	00116	EA  	2000	3	17	2000ZZZX641      	1	20000208	G	3240	7010FS9545708	SEAT            		50105201    	CNDAIR	CL600 	CL6002B19   		EA  										BRAKE ASSY	LEAKING         	B			XC4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		821  			JUN981357					BRAKE ASSEMBLY, P/N 5010520-1, FAILED PREMATURELY.  ONE EACH, PISTON LEAKING FROM INSULATOR AREA.  PISTON INTERNALLY FIL	LED WITH FLUID.  EVIDENCE OF T-SEAL FAILURE.  THIS IS A CONTINUAL DISCREPANCY.  NOTE:  OEM PARTS INSTALLED IN BRAKE ASSE	MBLY AND THE MOST RECENT BRAKE CONFIGURATION, P/N 5010520-1.  (X)				2	L	7	2 	4F			RT	A21EA   					 
2000031700117	20000317	00117	CE  	2000	3	17	2000ZZZX642      	1	20000203	G	7820	WO7501612989	MUFFLER         			CESSNA	185   	A185F       	2072821	CE  										EXHAUST	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	1164Q	131  				18503465				MUFFLER TAILPIPE BROKEN LOSE FROM BODY.  DEFECT NOTED TO BE CRACKS IN A VERY UNUSUAL AREA.  NOT A WELD OF BODY AND TAILP	IPE.  SUSPECT MUFFLER SHELL/BODY MATERIAL PROBLEM PART WAS NEW MANUFACTURE WITH 131 HOURS TOTAL TIME.  SHOWED NO SIGN OF	 ADVERSE STRESS.  (X)				1	H	7	1 	3O				3A24    					 
2000031700118	20000317	00118	CE  	2000	3	17	2000ZZZX643      	1	20000114	G	5610	10138402516	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  										COCKPIT	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	63791	1644 			94225H2048	BB1100				1-14-00 - FLYING AT 27,000 FEET, THE RIGHT SIDE COPILOT WINDWHIELD BROKE ON THE INSIDE PORTION OF THE WINDOW.  THE OUTSI	DE PORTION OF THE WINDSHIELD REMAINED INTACT.  THE CREW DEPRESSURIZED THE CABIN PER EMERGENCY PROCEDURES AND RETURNED TO	 PDX.  1-16-00 - AFTER LANDING ON 1-14-00, THE AIRCRAFT REMAINED ON THE GROUND UNTIL TH E WINDSHIELD WAS REPLACED ON 1-1	6-00.  (X)			1	L	7	2 	4T				A24CE   					 
2000031700119	20000317	00119	CE  	2000	3	17	2000ZZZX644      	1	20000203	G	2820	30J156401	LINE            			CESSNA	500   	550         	2076604	CE  										RT ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	627L	660  				5500843				AFTER FLIGHT WHEN PILOT CHECKED RIGHT ENGINE OIL GAUGE.  PILOT FOUND FUEL AND SMOKE FUMES IN RIGHT ENGINE BOTTOM COWLING	.  REMOVED BOTTOM COWLING, FOUND PIN HOLE IN LINE.  (X)					1	L	7	2 	4F				A22CE   					 
2000031700120	20000317	00120	CE  	2000	3	17	2000ZZZX645      	1	20000202	G	2820	S1236C30350	HOSE            			CESSNA	206   	U206G       	2073356	CE  										ENGINE BAY	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	68RS					U20605503				DURING ANNUAL INSPECTION, FOUND ABOVE MENTIONED HOSE LEAKING PROFUSELY.  THE HOSE APPEARED TO BE SUPPORTED PROPERLY.  WH	EN FUEL PRESSURE WAS APPLIED WITH AIRCRAFT ELECTRIC BOOST PUMP, FUEL BEGAN COMING OUT OF BRAIDED, CRIMPED AREA NEAR THE 	END OF THE HOSE.  AD 71-24-04 DOES NOT APPLY TO THIS MODEL NUMBER AND SERIAL NUMBER OF AIRCRAFT.  SE 71-7, SUPPLEMENT 1,	 DATED 11-3-71, ENCOMPASSES ALL CESSNA SINGLE ENGINE AIRCRAFT. (X)			1	H	7	1 	3O				A4CE    					 
2000031700122	20000317	00122	EA  	2000	3	17	2000ZZZX647      	2	20000110	G	7414	10382681	CAPACITOR       		66E21576    	MAULE 	M7    	M7235       	5460170	SO  	LYC   	O540  	O540J1A5    	41532	EA  					MAGNETO	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	783SP	1    			G109900C	4101C	L2076840A			PROBLEM STARTED WITH INSTALLATION OF NEW TCM HARNESS IGNITION SYSTEM.  RESULTED IN REPEATED FAILURES IN MAGNETO ON ONE S	IDE OR OTHER (I.E., LEFT AND RIGHT).  MAGNETOS WERE REMOVED AND CHECKED. POINTS AND CAPACITORS REPLACED.  ENGINE AND AIR	FRAME ELECTRICS CHECKED OK.  CAPACITOR BATCH NR 9920 FOUND DEFECTIVE. REPLACED WITH NR 9948.  OK TO-DATE, 1-24-00.  (X)				1	H	7	1 	3O	3	O	NC	3A23    	E295				 
2000031700123	20000317	00123	CE  	2000	3	17	2000ZZZX648      	1	20000315	G	3230	22411027	PIVOT ASSY      			CESSNA	182   	R182        	2072734	CE  										MLG	CRACKED         	B	S	A	SMTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2394S	5460 				R18201336				SUBMITTER STATED FOUND FIVE OTHER PIVOTS WITH THE SAME CRACK.  ALL OTHER PIVOTS HAVE 4,500 HOURS TOTAL TIME OR MORE.  PO	SSIBLE CAUSE UNKNOWN.  (X)					1	H	7	1 	3O			RT	3A13    					 
2000031700124	20000317	00124	CE  	2000	3	17	2000ZZZX649      	1	20000110	G	2820	0700147137	LINE            			CESSNA	185   	A185F       	2072821	CE  										FUEL SYSTEM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	714SD	10   				18504418				FUEL PRESSURE LINE BETWEEN ENGINE (BAFFLE) AND FFIREWAL BROKEN AT SILVER SOLDER JOINT.  (X)						1	H	7	1 	3O				3A24    					 
2000031700125	20000317	00125	CE  	2000	3	17	2000ZZZX650      	1	20000110	G	2820	0700147137	LINE            			CESSNA	185   	A185F       	2072821	CE  										FUEL SYSTEM	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	714SD	300  				18504418				FUEL PRESSURE LINE BETWEEN ENGINE AND FIREWALL BROKEN AT SILVER SOLDER JOINT.  (X)						1	H	7	1 	3O				3A24    					 
2000031700127	20000317	00127	WP  	2000	3	17	2000ZZZX652      	1	20000211	G	5320	AEA0161	WEB             			DOUG  	DC10  	DC1010      	3022110	WP  										RT MLG WW	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	364FE					46600				DURING MAINTENANCE, 3.0 INCH CRACK WAS FOUND ON RIGHT/CENTER WHEELWELL WEB.  CRACK AFFECTED UPPER SPLICE WEB, P/N AEA016	1-1, RT SIDE, AND AEA0501-1.  (X)					2	L	7	3 	4F				A22WE   					 
2000031700128	20000317	00128	WP  	2000	3	17	2000ZZZX653      	1	20000211	G	5320	AEA0501	WEB             			DOUG  	DC10  	DC1010      	3022110	WP  										RT MLG WW	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	389FE					46623				DURING MAINTENANCE, A 3.75 INCH CRACK WAS FOUND ON RIGHT/CENTER WHEELWELL WEB.  CRACK AFFECTED KEEL WEB UPPER SPLICE ONL	Y, P/N AEA0501.  (X)					2	L	7	3 	4F				A22WE   					 
2000031700129	20000317	00129	WP  	2000	3	17	2000ZZZX654      	1	20000211	G	5320	AEA0161	WEB             			DOUG  	DC10  	DC1010      	3022110	WP  										RT MLG WW	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	374FE					46612				DURING MAINTENANCE, THREE 10 INCH CRACKS WERE FOUND ON RIGHT/CENTER WHEELWELL (Y=1386, Z=52) COMMON TO KEEL WEB, WEB DOU	BLER, AND UPER WEB SPLICE,  P/N'S, AEA0161-3, AEA0161-153, AND AEA0501 RESPECTIVELY.  DATA WAS SENT TO BOEING/DOUGLAS 5-	14-99 AND RESENT 7-9-99, WITH NO RESPONSE.  (X)				2	L	7	3 	4F				A22WE   					 
2000031700131	20000317	00131	CE  	2000	3	17	2000ZZZX656      	1	20000209	G	7931	77041	SWITCH          			CESSNA	182   	182S        	2072701	CE  										ENGINE OIL	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	9539L	1005 				18280185				OIL PRESSURE SWITCH FAILED IN-FLIGHT.  LOST 7-1/2 QUARTS OF OIL IN 20 MINUTE FLIGHT.  HAS 9 QUART SUPPLY.  SWITCH FAILED	 AT PLASTIC HOUSING.  SINCE OIL GOES UNDER AND ON BELLY, HAVE NO IDEA OF OIL LEAK IN-FLIGHT.  CESSNA SAID IT HAS HAD AT 	LEAST 4 FAILURES.  (X)				1	H	7	1 	3O			NT	3A13    					 
2000031700135	20000317	00135		2000	3	17	2000ZZZX660      	1	20000103	G	3350		POWER SUPPLY    			AMTR  		KITFOXSPEEDS												CABIN	WRONG PART      	B			R2JR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	193SC					SC47101				DURING MAINTENANCE, FOUND MODEL PS823 EMERGENCY POWER SUPPLY INCORRECTLY REPLACED WITH PS835 EMERGENCY POWER SUPPLY.  TH	OUGH SIMILAR, THESE UNITS ARE NOT DIRECT REPLACEMENTS FOR ONE ANOTHER.  WIRING CHANGES ARE REQUIRED PER JET/BF GOODRICH 	SERVICE DATA.  AIRCRAFT ALTERED PER APPROVED DATA.  (X)							0 										 
2000032300572	20000323	00572	EA  	2000	3	23	2000ZZZX713      	2	20000217	G	7313		INJECTOR NOZZLE 			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	FAILED          	H				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	498ER	848  				17280674	L2786151A			PILOT EXPERIENCED A BRIEF ROUGHNESS IN CRUISE.  THREE FUEL INJECTOR  NOZZLES WERE CHANGED.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000032300574	20000323	00574	EA  	2000	3	23	2000ZZZX715      	2	20000118	G	8550	LW15688	TUBE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					OIL SUMP	DISCONNECTED    	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	5246B		769  			15283815	RL1871015			INDUCTION TUE ATTACHED TO OIL SUMP BECAME LOOSE CAUSING ROUGH RUNNING ENGINE.  ENGINE OIL SUMP REPLACED TO CORRECT PROBL	EM.  SUBMITTER STATED THIS IS SECOND ENGINE FOUND WITH THIS CONDITION ON FACTORY OVERHAULED ENGINE.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000032300575	20000323	00575	CE  	2000	3	23	2000ZZZX716      	1	20000223	G	5280	10541000057	CHANNEL         			BEECH 	76    	76          	1153005	CE  										NLG DOOR	CRACKED         	H			BF8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6632R	9438 				ME236				THE CHANNEL AND CHANNEL SUPPORT ARE NOSE GEAR DOOR LINKAGE SUPPORT STRUCTURES.  DURING A ROUTINE INSPECTION, THESE ITEMS	 WERE FOUND TO BE CRACKED AND HAD SHIFTED POSITION WITHIN THE NOSE TUNNEL STRUCTURE.  EVEN A SMALL CHANGE IN THE POSITIO	N OF THESE PARTS CHANGES THE NOSE GEAR DOOR RIGGING CAUSING THE NOSE GEAR TO LOCK IN THE UP POSITION.  FORCE BUILD-UP FR	OM THE HYDRAULIC ACTUATOR ATTEMPTING TO  LOWER THE NOSE GEAR BROKE THE CHANNEL LOOSE FROM THE NOSE STRUCTURE AND THEN AL	LOWED THE NOSE GEAR TO COME DOWN AND LOCK.		1	L	7	2 	3O				A29CE   					 
2000032300576	20000323	00576	CE  	2000	3	23	2000ZZZX717      	1	20000223	G	5280	105410000199	SUPPORT         			BEECH 	76    	76          	1153005	CE  										NLG DOOR	CRACKED         	H			BF8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6632R	9438 				ME236				THE CHANNEL AND CHANNEL SUPPORT ARE NOSE GEAR DOOR LINKAGE SUPPORT STRUCTURES.  DURING A ROUTINE INSPECTION, THESE ITEMS	 WERE FOUND TO BE CRACKED AND HAD SHIFTED POSITION WITHIN THE NOSE TUNNEL STRUCTURE.  EVEN A SMALL CHANGE IN THE POSITIO	N OF THESE PARTS CHANGES THE NOSE GEAR DOOR RIGGING CAUSING THE NOSE GEAR TO LOCK IN THE UP POSITION.  FORCE BUILD-UP FR	OM THE HYDRAULIC ACTUATOR ATTEMPTING TO  LOWER THE NOSE GEAR BROKE THE CHANNEL LOOSE FROM THE NOSE STRUCTURE AND THEN AL	LOWED THE NOSE GEAR TO COME DOWN AND LOCK.		1	L	7	2 	3O				A29CE   					 
2000032300578	20000323	00578	CE  	2000	3	23	2000ZZZX719      	1	20000210	G	2701	605241603	YOKE            			BEECH 	36    	A36         	1151604	CE  										CONTROL COLUMN	DAMAGED         	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7231Y	2301 				E2288				UPON INSP OF CONTROL COLUMNS AND EQUIP, FOUND THE ONLY 4 RIVETS (MS20470AD5) SECURING  PILOTS CONTROL COLLAR TO THE YOKE	 WORKING IN SHEAR CAUSING SLOPPY FEEL IN THE YOKE.  SUBMITTER STATED IF RIVETS WERE TO SHEAR, COMPLETE LOSS OF PITCH AND	 ROLL CONTROL WOULD HAVE OCCURRED.  COLUMN AND YOKE REMOVED AND NEW RIVETS THE NEXT DIAMETER UP (MS20470AD6-6) INSTALLED	 AS A REPAIR UNDER A.C. 43.13 1B, SECT 4-57 PARA 4(B).  ACFT MFG NOTIFIED AND IT WAS SUGGESTED TO INSTALL ADDITIONAL RIV	ETS IN THIS COLLAR FOR FUTURE REPAIRS.  THE CONTROL WHEEL COLLAR IS ATTACHED AT OPPOSITE END WITH 8 RIVETS (MS-20470AD5)	.  SUBMITTER SUGGESTED AD BE MADE TO ADDRESS THIS ISSUE, ALL BEECH BONANZAS, BARONS WITH DUAL CONTROL COLUM INSTALLS.	1	L	7	1 	3O				3A15    					 
2000032300579	20000323	00579	CE  	2000	3	23	2000ZZZX720      	1	20000216	G	5510	NAS12918	NUT             			CESSNA	425   	425         	2076018	CE  										HORIZ STABILIZER	SPLIT           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8FR	608  				4250095				DURING A PHASE INSPECTION, THE LEFT NUT THAT RETAINS THE HORIZONTAL STABILIZER WAS FOUND SPLIT FROM TOP TO BOTTOM.  RECO	RDS SHOW THAT SB CQB 85-25 AND AD 85-25-11 WERE C/W IN 1986.  THE SB AND AD ADDRESS THIS PROBLEM.  THE NUT THAT SPLIT AP	PEARS TO HAVE BEEN THE IMPROVED REPLACEMENT CALLED OUT FOR IN THE AD AND SB.				1	L	7	2 	3T			RT	A7CE    					 
2000032300580	20000323	00580		2000	3	23	2000ZZZX721      	4	20000207	G	3416		INDICATOR       	KOLLSMAN    	671CK       	UNIVAR	415   	415C        	0420302	NM  										COCKPIT	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	99248		1    		67501	1871				DURING FIRST HOUR OF FLIGHT WITH FRESHLY OVERHAULED INSTRUMENT, THE 100 FOOT HAND STOPPED WORKING.  AFTER REMOVAL OF THE	 INSTRUMENT, NOTICED SHAFT FOR THE HAND HAD DISENGAGED INTERNALLY.   BY TILTING THE ALTIMETER, THE SHAFT COULD BE RE-ENG	AGED WITH THE INTERNAL MECHANISM, BUT WHEN TILTED TO SIMULATE A CLIMB ATTITUDE, IT WOULD ONCE AGAIN DISENGAGE AND BECOME	 INOPERATIVE.  OVERHAULED 8/99.			1	L	7	1 	3O				A718    					 
2000032300581	20000323	00581	SO  	2000	3	23	2000ZZZX722      	1	20000214	G	2140	B350091E881EL	HEATER          			PIPER 	PA34  	PA34220T    	7103420	SO  										CABIN	FAILED          	B		A	FE6R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	11	9265Q	1    			A98030046	3449077				THE PILOT ATTEMPTED TO USE THE HEATER ON A NEW AIRCRAFT WITHOUT SUCCESS.  THE CIRCUIT BREAKER TRIPPED.  REPAIRS WERE MAD	E TO OVERHEATED WIRING.  HEATER FAILED AGAIN ON NEXT FLIGHT.  MAINTENANCE REMOVED THE HEATER FROM THE AIRCRAFT FOR INVES	TIGATION, WITH A TOTAL OF .5 HOURS ON THE HEATER HOBBS SINCE NEW.  INTERNAL VENT BLOWER FAN (PIPER P/N 753-201) SEPARATE	D FROM HUB ARBOR. PRESSURE DIFFERENTIAL SWITCH (JAN AERO P/N 94E42-3).  PNEUMATIC FITTING COMPLETELY STRIPPED IN UNIT BO	DY.  LARGE DRILL SHAVING IN THE FUEL INLET LINE SOLENOID VALVE.		1	L	7	2 	3O				A7SO    					 
2000032300584	20000323	00584	CE  	2000	3	23	2000ZZZX725      	1	20000204	G	7810	1099500001	STACK           			BEECH 	90    	C90A        	1152911	CE  										EXHAUST	CRACKED         	B			BQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	600FL	33   				LJ1540				RIGHT ENGINE INBOARD EXHAUST STACK FOUND TO BE CRACKED .75 INCH APPROXIMATELY ONE-THIRD WAY AROUND CIRCUMFERENCE AT WELD	 ATTACH POINT NACELLE INLET DEICE TUBE.  A RAYTHEON REP HAS BEEN CONTACTED AND A FUTURE SERVICE BULLETIN IS PENDING RELE	ASE.				1	L	7	2 	3T			RT	3A20    					 
2000032300585	20000323	00585	CE  	2000	3	23	2000ZZZX726      	1	20000224	G	7810	1099500001	STACK           			BEECH 	90    	C90A        	1152911	CE  										EXHAUST	CRACKED         	B			BQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	600FL	206  				LJ1540				CRACKED EXHAUST STACK.  THREE OTHER M OR D REPORTS SUBMITTED FOR SAME PROBLEM.  A RAYTHEON REP HAS BEEN CONTACTED AND A 	FUTURE SERVICE BULLETIN IS PENDING RELEASE.					1	L	7	2 	3T			RT	3A20    					 
2000032300586	20000323	00586	GL  	2000	3	23	2000ZZZX727      	2	20000115	G	7323	23065121	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	B	L	A	VBVR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	09	35WH		1266 		21482	2736	CAE836154			IN CRUISE FLIGHT, THE POWER TURBINE ROTOR DROOPED TO 90 PERCENT AND WOULD NOT RECOVER.  THE PILOT LOWERED COLLECTIVE, RE	COVERED ROTOR SPEED AND DID A POWER ON RECOVERY.					1	G	7	1 	3U	3	U		H2SW    	E4CE				 
2000032300587	20000323	00587	EA  	2000	3	23	2000ZZZX728      	1	20000207	G	3230		UNIVERSAL       			ACQCOR	F22   	F22         	8850908	EA  										RT MLG	FAILED          	G		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	92K	383  				006				UNIVERSAL JOINT FAILED DURING GEAR RETRACTION PHYSICALLY SEPARATING RIGHT LANDING GEAR SCREW JACK FROM RETRACT SYSTEM. C	OULD NOT MANUALLY EXTEND GEAR DUE TO SEPARATION OF ABOVE UNIVERSAL JOINT.  UNIVERSAL JOINT HAS 2 PINS PRESSED THROUGH FO	RK INTO THE ARTICULATING PORTION OF THE JOINT.  NO PROVISION IS MADE FOR RETENTION OF PINS EXCEPT FOR PRESSURE FIT.  APP	ROXIMATELY 430 CYCLES.			1	H	7	1 	3O			NC	1A9     					 
2000041700070	20000417	00070	SW  	2000	4	17	2000ZZZX803      	1	20000223	G	5302	407023800118S	SUPPORT BRACKET 		407030801101	BELL  	407   	407         	       	SW  										TAILBOOM	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL	3773 			53185A	53247				DURING DAILY INSPECTION, FOUND CRACK IN RADIUS.						1	G	7	1 	3U			O	H2SW    					 
2000041300292	20000413	00292	SW  	2000	4	13	2000ZZZX804      	1	20000220	G	6510	407340339103	BEARING         		            	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	979  			K980828	53044				DURING DAILY INPSECTION FOUND BEARINGS WORN, AXIAL PLAY.						1	G	7	1 	3U			O	H2SW    					 
2000041300293	20000413	00293	SW  	2000	4	13	2000ZZZX805      	1	20000220	G	6510	407340339103	BEARING         		            	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	979  			K980784	53044				DURING DAILY INPSECTION FOUND BEARINGS WORN, AXIAL PLAY.						1	G	7	1 	3U			O	H2SW    					 
2000041700074	20000417	00074	SW  	2000	4	17	2000ZZZX808      	1	20000209	G	6510	206061432121	HOUSING         		407040303105	BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	627AL				AFS1013	53284				DURING DAILY INSPECTION, BLOWER HOUSING FOUND CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2000041300296	20000413	00296	SW  	2000	4	13	2000ZZZX809      	1	20000203	G	6510	407340339103	BEARING         		407040730310	BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	745  			E990600	53044				DURING DAILY INSPECTION BOTH BEARINGS FOUND ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2000041300297	20000413	00297	SW  	2000	4	13	2000ZZZX810      	1	20000203	G	6510	407340339103	BEARING         		407040730310	BELL  	407   	407         	       	SW  										TAIL ROTOR	ROUGH           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	745  			E990604	53044				DURING DAILY INSPECTION BOTH BEARINGS FOUND ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2000041300298	20000413	00298	SW  	2000	4	13	2000ZZZX811      	1	20000204	G	6210	206015001107	BLADE           		            	BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3179S	2664 			A2472	45781				DURING DAILY INSPECTION, CORROSION AND DEBONDED AT ROOT END GRIP PLATE.						1	G	7	1 	3U			 	H2SW    					 
2000041300300	20000413	00300	GL  	2000	4	13	2000ZZZX813      	2	20000131	G	7261	E23001832	NOZZLE          		            						ALLSN 	250C  	250C30      	03013	GL  					PT OIL	MISDRILLED      	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	 						CAT98100			HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF.  PART WAS NEW AND SUBMITTER STATED THIS WAS DONE 	DURING MANUFACTURING.  NOTE:  SHOULD HAVE 4 HOLES.										3	U			E1GL				 
2000041300302	20000413	00302	GL  	2000	4	13	2000ZZZX815      	2	20000131	G	7261	E23001832	NOZZLE          		            						ALLSN 	250C  	250C30      	03013	GL  					PT OIL	MISDRILLED      	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	 						CAT95221			HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF.  PART WAS NEW AND SUBMITTER STATED THIS WAS DONE 	DURING MANUFACTURING.  NOTE:  SHOULD HAVE 4 HOLES.										3	U			E1GL				 
2000041300303	20000413	00303	GL  	2000	4	13	2000ZZZX816      	2	20000131	G	7261	E23001832	NOZZLE          		            						ALLSN 	250C  	250C20      	03013	GL  					PT OIL	MISDRILLED      	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	 						CAT44377			HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF.  PARTS WAS NEW AND SUBMITTER STATED THIS WAS DONE	 DURING MANUFACTURING.  NOTE:  SHOULD HAVE 4 HOLES.										3	U			E4CE				 
2000041300304	20000413	00304	GL  	2000	4	13	2000ZZZX817      	2	20000131	G	7261	E23001832	NOZZLE          		            						ALLSN 	250C  	250C30      	03013	GL  					PT OIL	MISDRILLED      	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	 						CAT44316			HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF.  PART WAS NEW AND SUBMITTER STATED THIS WAS DONE 	DURING MANUFACTURING.  NOTE:  SHOULD HAVE 4 HOLES.										3	U			E1GL				 
2000041300305	20000413	00305	GL  	2000	4	13	2000ZZZX818      	2	20000131	G	7261	E23001832	NOZZLE          		            						ALLSN 	250C  	250C30      	03013	GL  					PT OIL	MISDRILLED      	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	 						CAT90149			HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF.  PART WAS NEW AND SUBMITTER STATED THIS WAS DONE 	DURING MANUFACTURING.  NOTE:  SHOULD HAVE 4 HOLES.										3	U			E1GL				 
2000041300306	20000413	00306	GL  	2000	4	13	2000ZZZX819      	2	20000131	G	7261	E23001832	NOZZLE          		            						ALLSN 	250C  	250C30      	03013	GL  					PT OIL	MISDRILLED      	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	 						CAT95422			HOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF.  PART WAS NEW AND SUBMITTER STATED THIS WAS DONE 	DURING MANUFACTURING.  NOTE:  SHOULD HAVE 4 HOLES.										3	U			E1GL				 
2000041300312	20000413	00312	EA  	2000	4	13	2000ZZZX827      	2	20000308	G	7414	10382681H	CAPACITOR       	BENDIX      	66E21576    	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540L3C5    	41532	EA  					MAGNETO	FAILED          	D			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	4689S	35   			F259910G	R18200591	L2225140A			NEW CAPACITOR INSTALLED TO SATISFY TCM CSB662A FAILED ON FIRST ENGINE RUN AFTER INSTALLATION.  DATE CODE ON FAILED CAPAC	ITOR IS 00-08.  FAILURE WAS INTERMITTENT DURING 15 MINUTE ENGINE RUN-UP.					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2000061600335	20000616	00335	WP  	2000	6	16	2000ZZZX828      	1	20000222	G	6520	369D2512511	PINION GEAR     	HUGHES      	369D25100505	HUGHES	369   	369D        	4470706	WP  										TRANSMISSION	FAILED          	H			S1EM	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	09	4575Z	7931 	1778 		U0215	370094D				AIRCRAFT WAS FLYING WHEN A NOISE WAS HEARD.  A PRECAUTIONARY LANDING WAS MADE.  THE PROBLEM WAS A BROKEN GEAR IN THE MAI	N TRANSMISSION.  THE BROKEN PART WAS SENT TO THE MANUFACTURER FOR EVALUATION.					1	G	7	1 	3U			 	H3WE    					 
2000041300313	20000413	00313	CE  	2000	4	13	2000ZZZX829      	1	20000219	G	2721	12606323	SPROCKET        		            	CESSNA	207   	207A        	2073604	CE  										RUDDER TRIM	MISMANUFACTURED 	E			    	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	01	7384U					20700431				AFTER INSTALLATION OF PART, OPS CHECK FOUND TRIM CHAIN TO RIDE NORMALLY FOR TWO-THIRDS OF TURN ON SPACER BEFORE RIDING U	PON TEETH OF SPROCKET AND JUMPING OFF.  INSPECTED SPROCKET AND DETERMINED SOME OF THE TEETH MISS-CUT UPON MANUFACTURE.					1	H	7	1 	3O			 	A16CE   					 
2000041300314	20000413	00314	CE  	2000	4	13	2000ZZZX830      	1	20000327	G	8011	6462751	STARTER         		            	CESSNA	207   	207A        	2073604	CE  										ENGINE	MISREPAIRED     	B			CY4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	73503		17   		R079210	20700559				UPON DISASSEMBLY OF STARTER, INCORRECT PRESTOLITE BRUSHES, PN MDL-1063B, WERE FOUND INSTALLED.  THE STARTER IS TCM, BUT 	THE BRUSHES ARE PRESTOLITE.  TCM BRUSHES ARE .50 INCH LONG.  PRESTOLITE BRUSHES ARE .75 INCH LONG.					1	H	7	1 	3O			 	A16CE   					 
2000041300315	20000413	00315	SO  	2000	4	13	2000ZZZX831      	2	20000226	G	7414	M3050	IMPULSE COUPLING	SLICK       	6310        	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					MAGNETO	FAILED          	H			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	123TM				91120142	U20601768	247629R			THE IMPULSE COUPLING ENGAGES ONLY 1 OUT OF 5 TIMES WHEN PROPELLER IS TURNED BY HAND.  THE SPRING WHICH HOLDS THE PAWL OU	T TO ENGAGE IMPULSE COUPLING HAS NOT BROKEN BUT HAS TOTALY LOST ITS SPRING EFFECT.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000041300316	20000413	00316	SW  	2000	4	13	2000ZZZX832      	1	20000124	G	6230	406010418101	SWASHPLATE      		            	BELL  	407   	407         	       	SW  										MAIN ROTOR	DAMAGED         	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407JR	1193 			A1353	53245				SWASHPLATE SEAL, PN 406-310-407-101, WORE GROOVE IN CAP, P/N 406-010-418-101, CAUSING GREASE FROM BEARINGS BELOW TO ENTE	R TOP OF SWASHPLATE OUTER EDGE UNDER BOOT.  THIS CAN ALLOW GREASE TO CONTAMINATE TEFLON LINED RACES OF UNIBALL ASSEMBLY 	RESULTING IN CHANGES OF SWASHPLATE FRICTION SETTING WHICH CAUSES STIFFNESS IN CYCLIC AND COLLECTIVE CONTROL INPUTS.  SUB	MITTER RECOMMENDED CAP BE MADE OF TOUGHER MATERIAL TO PREVENT DAMAGE FROM SEAL, P/N 406-310-407-101.			1	G	7	1 	3U			O	H2SW    					 
2000041700089	20000417	00089	SW  	2000	4	17	2000ZZZX833      	1	20000208	G	6321	D01661	PAD             			BELL  	407   	407         	       	SW  										ROTOR BRAKE	WORN            	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AK	819  			905	53269				DURING REMOVAL OF ROTOR BRAKE CALIPER ASSEMBLIES, FOUND GUIDE HOLES ON PAD ASSY AND GUIDE BOLTS WORN.  BOLT, PN D0166-1,	 WORN IN EXCESS OF 50 PERCENT OF BOLT DIAMETER. PAD ASSY, PN D0163-1, GUIDE HOLES WORN IN EXCESS OF 65 PERCENT OF WALL T	HICKNESS.  POSSIBLE CAUSE OF PREMATURE WEAR MAY BE FROM EXCESSIVE VIBRATION AND SMALL AREA OF CONTACT AT BOLT AND PAD AS	SY GUIDE HOLES.  SUBMITTER RECOMMENDED INSPECTION OF BOLTS AND PAD ASSEMBLIES EVERY 600 HOURS.			1	G	7	1 	3U			O	H2SW    					 
2000041700090	20000417	00090	SW  	2000	4	17	2000ZZZX834      	1	20000208	G	6321	D01661	PAD             			BELL  	407   	407         	       	SW  										ROTOR BRAKE	WORN            	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AK	819  			907	53269				DURING REMOVAL OF ROTOR BRAKE CALIPER ASSEMBLIES, FOUND GUIDE HOLES ON PAD ASSY AND GUIDE BOLTS WORN.  BOLT, PN D0166-1,	 WORN IN EXCESS OF 50 PERCENT OF BOLT DIAMETER. PAD ASSY, PN D0163-1, GUIDE HOLES WORN IN EXCESS OF 65 PERCENT OF WALL T	HICKNESS.  POSSIBLE CAUSE OF PREMATURE WEAR MAY BE FROM EXCESSIVE VIBRATION AND SMALL AREA OF CONTACT AT BOLT AND PAD AS	SY GUIDE HOLES.  SUBMITTER RECOMMENDED INSPECTION OF BOLTS AND PAD ASSEMBLIES EVERY 600 HOURS.			1	G	7	1 	3U			O	H2SW    					 
2000041300317	20000413	00317	EA  	2000	4	13	2000ZZZX836      	1	20000302	G	5320	MS21905	FITTING         		            	CNDAIR	CL600 	CL6001A11   	1900302	EA  										HYDRAULIC LINE	CRACKED         	C			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	751DB	7950 				1075				IN THE LAST 2 MONTHS HAVE FOUND 3 T-FITTINGS CRACKED AND LEAKING.   (TWO ON 600 CHALLENGER, ONE ON 601).  ONE DID CAUSE 	AN INTERRUPTION OF A FLIGHT.  ALL THREE ARE ALUMINUM FITTINGS THAT HAD NOT BEEN DISTURBED SINCE MANUFACTURE.					2	L	7	2 	4F			RT	A21EA   					 
2000041300318	20000413	00318	EA  	2000	4	13	2000ZZZX837      	1	20000302	G	5320	MS21905	FITTING         		            	CNDAIR	CL600 	CL6002B16   	1900305	EA  										HYDRAULIC LINE	CRACKED         	C			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	333MG	4290 				5035				IN THE LAST 2 MONTHS HAVE FOUND 3 T-FITTINGS CRACKED AND LEAKING.   (TWO ON 600 CHALLENGER, ONE ON 601).  ONE DID CAUSE 	AN INTERRUPTION OF A FLIGHT.  ALL THREE ARE ALUMINUM FITTINGS THAT HAD NOT BEEN DISTURBED SINCE MANUFACTURE.					2	L	7	2 	4F			RT	A21EA   					 
2000041300319	20000413	00319		2000	4	13	2000ZZZX838      	1	20000302	G	5320	MS178264	NUT             		            															FUSELAGE	MISMANUFACTURED 	B			WTXR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	 									PURCHASED MS17826-4 SELF-LOCKING CASTELLATED, SHEAR NUT DIRECTLY FROM CESSNA AIRCRAFT PART DEPT.  BEFORE INSTALLING ON A	 FLIGHT CONTROL BOLT, TECHNICIAN NOTICED THE CHAMFER ON THE NUT WAS SO DEEP THERE WAS ONLY ONE GRIPPING THREAD LEFT.  AF	TER CHECKING THE REST OF THE NUTS IN STOCK, FOUND 37 OUT OF 75 NUTS BAD.																	 
2000041300320	20000413	00320	CE  	2000	4	13	2000ZZZX839      	1	20000126	G	3230	509400111	TRUNNION        		            	CESSNA	340   	340CESSNA   	2076404	CE  										MLG	DAMAGED         	G			    	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	11	340WD					3400509				DURING THE LANDING PHASE OF THE FLIGHT AFTER TOUCHDOWN, THE AIRCRAFT DIPPED AND VEERED HARD TO THE LEFT.  EXAMINATION OF	 THE AIRCRAFT REVEALED A POSSIBLE CAUSE WAS A FAILURE OF THE BELLCRANK ATTACHMENT POINT OF THE MAIN LANDING GEAR TRUNNIO	N ASSEMBLY.				1	L	7	2 	3O			 	3A25    					 
2000041300321	20000413	00321	SO  	2000	4	13	2000ZZZX840      	1	20000303	G	5320	635012	RIVET           		            	PIPER 	PA34  	PA34200T    	7103406	SO  										SKIN	MISSING         	B			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4516F	6250 				347670340				FOUND MISSING AND WORKING RIVETS AND SEPARATION OF SKINS BETWEEN FIN ROOT FITTING AND OUTBOARD SKINS, BOTH SIDES.						1	L	7	2 	3O			 	A7SO    					 
2000041300322	20000413	00322	CE  	2000	4	13	2000ZZZX841      	1	20000214	G	2750	05101056	CONTROL CABLE   			CESSNA	170   	170         	2072302	CE  										TE FLAP	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3988V	4117 				18307				DURING AN ANNUAL INSPECTION, THE OUTBOARD END OF THE RIGHT FLAP CABLE WAS FOUND FRAYED .50 INCH AFT OF THE CLEVIS END.  	THIS MAY HAVE BEEN CAUSED BY WIND ON THE FLAP FLEXING THE CABLE AT THAT POINT.  SUBMITTER SUGGESTED AGE OF THE CABLE WAS	 POSSIBLY A FACTOR ALSO.				1	H	7	1 	3O			NT	A799    					 
2000041300323	20000413	00323	NE  	2000	4	13	2000ZZZX842      	3	20000306	G	6111	D5133	SHIELD          		E10950PK    											HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	 				1172			HJ254		EROSION SHIELD DEBOND BLADE NR 3, SN 1172.  REMOVED AND REPLACED EROSION SHIELD IAW PROCEDURE 001 AND HARTZELL MM.  STAT	IC BALANCED PROPELLER IAW HARTZELL CMM.															5	C	P10NE	 
2000041300324	20000413	00324	CE  	2000	4	13	2000ZZZX843      	1	20000214	G	5320	0512128	BRACKET         		            	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					BS 65.33	BROKEN          	H			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4640E	9884 				18503824	293336R			RIGHT FLAP RETRACTED AFTER PILOT SELECTED FIRST NOTCH OF FLAPS.  FOUND INBOARD MOUNTING EARS BROKEN AWAY FROM PULLEY BRA	CKET LOCATED JUST AFT OF FLAP HANDLE.  SUBMITTER STATED THIS IS THIRD BRACKET REPLACED IN FLEET OF THREE A185F'S.					1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2000042500079	20000425	00079	NE  	2000	4	25	2000ZZZX844      	3	20000327	G	6111	D5133	EROSION SHIELD  		E10950PB    											HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01					2583			HJ728		DEBOND ON NR 4 BLADE. REMOVED SHIELD TO REPAIR DEBOND AT STA 25 WHICH WAS 1 FOOT BY 1.25 FOOT IN JUST THE TOP LAYER OF G	LASS. REPAIRED IAW HARTZELL BSF. INSTALLED NEW EROSION SHIELD AND BOOT IAW PROCEDURE 001 AND HARTZELL MM 135F AND 143A, 	AND BALANCED.														5	C	P10NE	 
2000041300325	20000413	00325	CE  	2000	4	13	2000ZZZX845      	1	20000309	G	7120	40044	BRACKET         		            	CESSNA	170   	170B        	2072306	CE  										ENGINE MOUNT	BROKEN          	D			    	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	8156A	3624 				25008				BRACKET BROKEN AT THE EDGE OF THE STRAIGHT LINE OF BOLT PAD MACHINED SURFACE.  SUBMITTER RECOMMENDED VISUAL INSPECTION E	VERY 100 HOURS.					1	H	7	1 	3O			 	A799    					 
2000010800551	20000108	00551	SW  	2000	1	8	2000ZZZX88       	1	20000103	G	6420	206011810153	PLUG            		206011862101	BELL  	206   	206B        	1181511	SW  										T/R HUB	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	5008N	414  			A6541	2518				SUSPECT COMPOSIT THRUST PLUGS WERE MISMANUFACTURED OR IMPROPERLY INSTALLED ALLOWING TRUNNION TO SHIFT.  THIS CAUSED AN O	UT-OF-BALANCE CONDITION.  THE TAIL ROTOR HUB AND BLADE ASSEMBLY WAS DYNAMICALLY BALANCED ON SEVERAL OCCASIONS.  EACH TIM	E THE TAIL ROTOR VIBRATION WOULD RETURN WITHIN A FEW FLIGHT HOURS.  THE TAIL ROTOR ASSEMBLY WAS REMOVED FROM SERVICE DIS	ASSEMBLED AND THE PROBLEM IDENTIFIED.  UPON ASSEMBLY, BELL REQUIRES A .002 TO .004 THOUSANDTHS PINCH FIT.  THIS ASSEMBLY	 LOST ALL PRELOAD AND DUE TO THRUST PLUG WIRE HAD A LOOSE FIT OF .004 THOUSANDTHS.		1	G	7	1 	3U				H2SW    					 
2001022000302	20010220	00302	EA  	2001	2	20	20010123CW008    	2	20001220	G	7414	M3548	ROTOR           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	MAGNETO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149T					2843192	L3630836A	32543K		CRACK FOUND AT ROUTINE 500 HOUR INSPECTION.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2001030600067	20010306	00067	SW  	2001	3	6	20010123CW009    	1	20001219	G	6220	407310100103	HUB             			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	DEBONDED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	407BR	758  				53354				RUBBER DEBONDED IN FLIGHT, M/R HUB DAMPER ELASTOMERIC.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001030600068	20010306	00068	SO  	2001	3	6	20010123CW010    	1	20001222	G	2730	4084700	TORQUE TUBE     			PIPER 	PA31  	PA31325     	7103105	SO  										ELEVATOR	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	174BH					317612038				WHILE COMPLYING WITH AD 93-24-02 R1, THE AFT ROD END PN452658 WAS REMOVED.  CORROSION WAS DISCOVERED IN THE AFT END OF T	HE TUBE IN THE FITTING THAT IS THREADED FOR THE ROD INSTALLATION.					1	L	7	2 	3O			 	A20SO   					 
2001040900452	20010409	00452	CE  	2001	4	9	20010123CW012    	1	20001212	G	5511	503200025	SPAR            			CESSNA	402   	402B        	207590P	CE  										HORIZONTAL STAB	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	676MF					402B0106				UPON ANNUAL INSPECTION, FLAKING WAS NOTICED ON CENTER FORWARD SPAR AREA. FURTHER INSPECTION REVEALED THE SPAR WAS CORROD	ED 25 PERCENT THROUGH MAIN SURFACE.  UNIT WAS REPLACED WITH AN AIRWORTHY ITEM.					1	L	7	2 	3O			 	A7CE    					 
2001040900060	20010409	00060	CE  	2001	4	9	20010124CW001    	1	20001121	G	5210	6211282	ROD END         			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PAX DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	50EJ					650148				LOWER DOOR ROD END BROKEN IN TWO PARTS.  CAUSE WAS  IMPROPER OPERATION BY PEOPLE OPERATING DOOR.						2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2001040900064	20010409	00064	SO  	2001	4	9	20010124CW002    	1	20001227	G	3232	WTC21141	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					RT MLG DOOR	LEAKING         	G				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	35	3555B	4455 				318052056				PILOT COULD NOT EXTEND LANDING GEAR FULLY WITH EMERGENCY HAND PUMP.  FLUID LEAK AT RIGHT MAIN GEAR DOOR ACTUATOR, DEPLET	ED FLUID SUPPLY PRIOR TO COMPLETION OF GEAR DOWN CYCLE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001041000001	20010410	00001	SO  	2001	4	10	20010124CW004    	1	20001219	G	2750	4009209	BELLCRANK       			PIPER 	PA18  	PA18        	7101802	SO  										FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	9780D	8000 				186849				WHILE COMPLETELY DISASSEMBLING FOR RECOVERY, FOUND BOTH BELLCRANKS CRACKED.  ONLY  WAY TO SEE IS WITH MIRROR OR COMPLETE	 DISSASSEMBLE.  BOTTOM OF BELLCRANK NOT CRACKED.					1	H	7	1 	3O			 	1A2     					 
2001030700601	20010307	00601	SW  	2001	3	7	20010124CW005    	1	20001211	G	6320	K974120109	PUMP            			KAMAN 	K1200 	K1200       	05625F6	SW  	LYC   	T53   	T5317A      	41549	NE  					TRANSMISSION	SEIZED          	D			OWVL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99	134KA					A940006	LE81002			O.O TIME SINCE OVERHAUL, TRANSMISSION OIL PUMP SEIZED MOMENTARILY, ON FIRST STARTUP AFTER INSTALLATION.  DAMAGING TRANSM	ISSION INTERNAL OIL PUMP DRIVE GEAR.  NO SHEARSHAFT INCORPORATEN IN OIL PUMP ASSEMBLY.  TRANSMISSION HAD TO BE CHANGED, 	SECOND INSTANCE ON THIS AC.  REPORTS OF SAME PROBLEM ON OTHER AC.				1	G	7	1 	4F	4	U	NT	TR7BO   	E17EA				 
2001041800337	20010418	00337	NE  	2001	4	18	20010124CW011    	2	20001213	G	7322	2630391	DIAPHRAGM       			DOUG  	DC4   	C54BDC      	3021516	WP  	PWA   	R2000 	R2000*      	52023	NE  	HAMSTD	23E	23E50       	NE  	ACCELRATOR  PUMP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	44911	250  	250  			10461	108918	RRE182		DIAPHRAGM STILL SOFT , NOT HARD,  BUT CRACKED.						2	L	7	4 	4R	4	R	 	A762    	5E5	6	C	P603	 
2001050200003	20010502	00003	SO  	2001	5	2	20010124CW012    	2	20001222	G	8520	642396	CRANKSHAFT      			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	414WE				F344	414A0309	519783			CRANKSHAFT BROKEN IN FRONT OF NR1 ROD JOURNAL.  LESS THAN 100 HOURS SINCE OVERHAUL.ATTACHED PICTURES WITH ORIGINAL						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001050200004	20010502	00004	EA  	2001	5	2	20010125CW001    	2	20001208	G	7230		COMPRESSOR      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE	FAILED          	G			JEMA	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CE	01	366EA					BB841	PCE85097			JUST AFTER T/O COPILOT REPORTED SPARKS COMING FROM RIGHT ENGINE, INBOARD AND OUTBOARD EXHAUST STACKS.  POWER WAS REDUCED	 AND AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT.  INSPECTION THROUGH HIGH AND LOW BLEED VALVE OPENINGS REVEALED MASSI	VE COMPRESSOR FAILURE.  ENGINE REMOVED AND SENT IN FOR REPAIR				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001032000103	20010320	00103	SO  	2001	3	20	20010125CW005    	1	20001117	G	3221	89137041	MOUNT           			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ACTUATOR	MISMANUFACTURED 	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	498MM	387  				4636149	L995261A			LEFT SIDE OF ACTUATOR ATTACH BOSS NOT WELDED ALL THE WAY AROUND.  IF NOT DETECTED THIS COULD HAVE CAUSED NOSE GEAR TO CO	LLAPSE.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001050200009	20010502	00009		2001	5	2	20010125CW007    	4	20001130	G	2210	KS270	SERVO           			BEECH 	36    	A36         	1151604	CE  										AUTOPILOT SERVO	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	111LJ	3191 				E1822				FOUND PITCH SERVO INOPERATIVE DUE TO WATER CONTAMINATION.  FOUND SERVO ON TOP OF MOUNTING BRACKETT AND CLUTCH DRIVE ON T	OP OF BRACKETT.  SERVO AND CLUTCH DRIVE GEARS WERE ONLY SPLINING ABOUT .0156, AFTER SEVERAL TEST, UNIT WOULD FAIL.  INST	ALLED NEW SERVO AND CLUTCH DRIVE TOGETHER ON BOTTOM OF MOUNTING BRACKETT.				1	L	7	1 	3O			 	3A15    					 
2001050200010	20010502	00010	SO  	2001	5	2	20010125CW008    	2	20001218	G	8530	642344	CYLINDER        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8004Q		83   			421B004	219417			PILOT NOTICED RT ENGINE WAS RUNNING ROUGH.  SHUT DOWN ENGINE, DURING INSPECTION FOUND THAT NR5 CYLINDER WAS COLD,  WITH 	COMPRESSION TEST,  RESULTS WAS 0/80.  FOUND EXHST  STUD AND NUT MISSING, ALSO REVEALED BURN MARKS FROM EXHST  AND MANY C	RACKS AROUND EXHST PORT AND SPK PLUG HOLE. RMVD EXHST SYSTM AND CYL,  EXHST VLV  WAS SITTING ON TOP OF THE SEAT WITH  LO	OSE SEAT BECAUSE OF CRACKS THROUGH SEAT AREA.  POOR COND.  OF CYL  PRIOR TO O/H .  EXTENT OF RECOND REQUIRED TO REPAIR P	REVIOUS DAMAGE EVIDENT BY WELD AROUND SPK PLUG HOLES AND PORTS WAS TO MUCH FOR CYLINDER IN THIS COND.  DAMAGE AROUND EXH	ST PORT.,  IMPROPER  INSTALL OF STUD OR REPAIR OF HOLES ARE  WHERE CRKS STARTED THEN EXHST BURN THRU.	1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001041800284	20010418	00284	NM  	2001	4	18	20010125CW013    	1	20001218	G	2742	69778551	SPRING          	BOEING      		BOEING	737   	737         	UTILSYS	NM  										HORIZONTAL STAB	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KEO0361					SPRINGS ARE BROKEN IN THE AUXILIARY BRAKE SYSTEM, CAUSING THE UNIT TO BIND AND JAM.PROBABLE CAUSE/IMPROPER HEAT-TREATING	, AUSTENITE, FATIGUE AND INCREASED SPRING COIL STRESSES.					2	L	7	2 	4F			RT	A16WE   					 
2001041800286	20010418	00286	NM  	2001	4	18	20010125CW014    	1	20001218	G	3240	511531	HOUSING         	PNEUDRAULICS	5059        	BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1522					HOUSING IS BROKEN, SHEARED AT THE PRESSURE POINT.  PROBABLE CAUSE WOULD BE FATIGUE AND OR DEFECT IN THE CASTING OF THE H	OUSING.					2	L	7	2 	4F			RT	A16WE   					 
2001041800287	20010418	00287	NM  	2001	4	18	20010125CW015    	1	20001218	G	2761	654494710	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					5440					HOUSING IS CRACKED AT THE EXTERIOR OF THE RETRACT PORT.   PROBABLE CAUSE  OVERSTRESSED, FATIGUE,  AND OR POSSIBLE FLAW I	N HOUSING DESIGN.					2	L	7	2 	4F			RT	A16WE   					 
2001041800002	20010418	00002	NM  	2001	4	18	20010126CW006    	1	20001215	G	2761	654494710	HOUSING         	BOEING      		BOEING	767   	767         	UTILUSE	NM  										SPOILER ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					5408					HOUSING IS CRACKED BELOW THE RETRACT PORT. PROBABLE CAUSE:  STRESS AND OR FATIGUE.						2	L	7	2 	4F			RT	A1NM    					 
2001041800003	20010418	00003	NM  	2001	4	18	20010126CW007    	1	20001215	G	2761	654494710	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4139					HOUSING IS BROKEN AT THE BEARING LUG.PROBABLE CAUSE:  STRESS, FATIGUE AND OR HIGH TIME ON UNIT.						2	L	7	2 	4F			RT	A16WE   					 
2001041800014	20010418	00014	NM  	2001	4	18	20010126CW008    	1	20001215	G	2761	654494710	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4153					HOUSING IS BROKEN AT THE BEARING LUG.PROBABLE CAUSE:  STRESS, FATIGUE AND OR HIGH TIME ON UNIT.						2	L	7	2 	4F			RT	A16WE   					 
2001030700570	20010307	00570	NM  	2001	3	7	20010126CW009    	1	20001215	G	2923	654468311	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										HYDRAULIC SYSTEM	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					3092					HOUSING ASSEMBLY IS CRACKED AT THE NR 1 PORT.						2	L	7	2 	4F			RT	A16WE   					 
2001041800009	20010418	00009	NM  	2001	4	18	20010126CW010    	1	20001215	G	2782	65447418	SLEEVE          	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SLAT ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2501C					BLOCKING VALVE ASSEMBLY HAS A CRACKED SLEEVE  145.						2	L	7	2 	4F			RT	A16WE   					 
2001041800215	20010418	00215	CE  	2001	4	18	20010126CW011    	1	20001228	G	3610	1H1067	VALVE           			LEAR  	60    	60LEAR      	5170707	CE  										NR 1 ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	05	243F	772  				175				AIRCRAFT EXPERIENCED LOSS OF BLEEDAIR INFLIGHT,  AFTER LANDING,  INVESTIGATION REVEALED UPON OPENING LEFT ENGINE COWLING	 HAD FOUND VALVE HAD FAILED, SENT TO ENGINEERING FOR INVESTIGATION.					2	L	7	2 	4F			RT	A10CE   					 
2001041800238	20010418	00238	CE  	2001	4	18	20010126CW012    	1	20001220	G	3240	1013810125	VALVE           			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6*        	52043	EA  					LT MLG WW	STUCK           	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	981LL	560  				FL265				BRAKE DEICE LIGHT WOULD REMAIN ON WHEN ON/OFF SWITCH WAS PLACED IN OFF POSITION.   DEICE VALVE STICKING ON.						2	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2001022100044	20010221	00044	CE  	2001	2	21	20010126CW013    	1	20001229	G	6100	3156	COUNTERWEIGHT   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2A34C	D2AF34C30   	GL  	PROPELLER	BROKEN          	B			BSYA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	9189Q					TH148	810997RR	702969		MIR / DAL -  RIGHT ENGINE SURGING AFTER TAKE OFF, RETURNED TO AIRPORT.  FOUND COUNTERWEIGHT COLLAR BROKEN.  REMOVED PROP	 AND SENT TO PROP SHOP FOR INSPECTION, EDDY CURRANT INSPECTION AND REPAIR. RETURNED TO SERVICE REINSTALLED ON AIRCRAFT.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2001050200012	20010502	00012	CE  	2001	5	2	20010126CW014    	1	20001222	G	3230	583800901	MOTOR           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	MLG	INOPERATIVE     	B			HE4R	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			SW	99	1814W					TH287	298824R	EO1683		MIR  BDL   HAD NO GEAR DOWN INDICATOR GOING INTO BDL, CRANKED GEAR DOWN AND LANDED WITH NO PROBLEMS.  REMOVED AND REPLAC	ED LANDING GEAR MOTOR.  OPS CHECKS GOOD					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2001050200013	20010502	00013		2001	5	2	20010129CW001    	4	20001215	G	2210	065001782200	SERVO           			CESSNA	206   	T206H       	       	CE  										FUSELAGE	INOPERATIVE     	B			HI1R	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	99	909MA	249  				T20608097				THE PILOT INITIALLY COMPLAINED THAT THE AUTOPILOT WOULD NOT MAINTAIN CONSTANT VERTICAL SPEED.  THIS ESCALLATED INTO A FU	LL NOSE DOWN TRIM RUNAWAY.  THE PILOT RECOGNIZED THE PROBLEM AND RECOVERED FROM DIVE.  THE PITCH SERVO WAS CHANGED AND T	HE PROBLEM DID NOT RECUR.				1	H	7	1 	3O			 	A4CE    					 
2001050200014	20010502	00014	GL  	2001	5	2	20010129CW002    	2	20001130	G	7250		TURBINE         								ALLSN 	250B  	250B17F2    	 	GL  					ENGINE	MISDRILLED      	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					CAT81073		CAE881236			DURING REASSEMBLY OF THE TURBINE AFTER REPAIR, THE ANTIROTATION PIN WAS FOUND TO BE LOOSE.  UPON REMOVAL, FOUND BURRS AT	 THE BASE OF THE PIN, CAUSED BY THE PIN BEING PRESSED INTO TOO SMALL A HOLE.  MEASUREMENT OF THE PIN HOLE FOUND IT TO BE	 0.002 TO 0.003 BELOW THE PRINT LIMIT.									3	T			E10CE				 
2001050200016	20010502	00016	SO  	2001	5	2	20010129CW005    	1	20001215	G	7160	9904700	AIR BOX         			PIPER 	PA28  	PA28R201    	7102816	SO  										INTAKE SYSTEM	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	283ND	781  	781  			2844025				DURING SCHEDULED INSPECTION 2 OF 3 RIVETS HOLDING THE ALTERNATE AIR DOOR HINGE, SHEARED.  UPON REMOVAL OF AIR BOX ASSEMB	LY, A CRACK WAS FOUND EXTENDING ACROSS THE WELD AND INTO EACH TUBE FORMING THE 90 DEGREE TURN OF THE ASSEMBLY.					1	L	7	1 	3O			 	2A13    					 
2001050200017	20010502	00017	CE  	2001	5	2	20010129CW006    	1	20001221	G	2434	649304	ALTERNATOR      			BEECH 	58    	58          	1152740	CE  										ENGINE	INOPERATIVE     	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	99	158JG	304  	304  			TH1900				ALTERNATOR INOPERATIVE.						1	L	7	2 	3O			 	3A16    					 
2001041800347	20010418	00347	CE  	2001	4	18	20010129CW007    	1	20000801	G	3246	FN22A524	NUT             	DUNLOP      		RAYTHN	DH125 	HAWKER800   	7450004	CE  										MLG WHEEL	MISSING         	B			L5NR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	466CS				NN185	NAD446				NUTS CAME OFF IN SERVICE.  RECOMMEND NUTS AND BOLTS BE CHANGED AT TIRE CHANGES OR CHANGE TO A NEW TYPE NUT AND BOLT.						2	L	7	2 	4F			RT	A3EU    					 
2001050200018	20010502	00018		2001	5	2	20010129CW009    	4	20001213	G	6113	055032110	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										PROP SPINNER	BROKEN          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	796WW	143  				172S8635				FOLLOWING A ROUTINE TRAINING FLIGHT, THE STUDENT AND INSTRUCTOR RETURNED TO FIND THE SPINNER BULKHEAD BROKEN OFF AROUND 	THE NUTPLATE AND SPINNER BENT IN THAT AREA.THE PROBABLE CAUSE WAS IMPROPER SPINNER TO BULKHEAD FITTING FROM THE FACTORY,	 CREATING EXCESSIVE TENSION IN THAT AREA.  SUGGEST BETTER QUALITY CONTROL FROM THE MFG WHEN SPINNER IS INSTALLED TO PREV	ENT RECURRENCE.			1	H	7	1 	3O			NT	3A12    					 
2001050200019	20010502	00019	CE  	2001	5	2	20010129CW010    	1	20001213	G	3230	256566250	FILTER ELEMENT  			BEECH 	90    	C90A        	1152911	CE  										SUCTION LINE	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	488XJ					LJ1527				EMERGENCY LANDING, HAND PUMP SUCTION LINE FILTER ELEMENT NOT INSTALLED FROM BUILD.AIRCRAFT TOTAL TIME 799.8						1	L	7	2 	3T			RT	3A20    					 
2001050200020	20010502	00020	SO  	2001	5	2	20010129CW011    	1	20001212	G	3213	AN17413	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										RT MLG	BROKEN          	B				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	99	8VV	3100 				7554075				RIGHT M.L.G. TORQUE LINK CENTER BOLT BROKEN DURING LANDING, CAUSING RIGHT WHEEL TO ROTATE 90 DEGREE TO AIRCRAFT TRACK.  	AIRCRAFT TURNED RIGHT OFF THE RUNWAY BUT WAS NOT DAMAGED.  DUE TO M.L.G. DESIGN, THE TORQUE LINK BOLT IS PLACED IN HEAVY	 TENSION LOAD EACH LANDING.				1	L	7	2 	3O			 	1A10    					 
2001041800349	20010418	00349	CE  	2001	4	18	20010129CW012    	1	20001220	G	3297		WIRE            			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					PILOT YOKE	CHAFED          	B				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			GL	23	86VP	4830 				6500089				PILOT REPORTED THAT IN FLIGHT, THE NOSE WHEEL STEERING SYSTEM DISARMS WHEN THE YAW DAMPER SYSTEM IS DISENGAGED USING THE	 AUTOPILOT/ NWS DISCONNECT SWITCH ON THE PILOT OR COPILOTS CONTROL WHEEL.  THE TECH FOUND A CHAFFED STEERING SYSTEM WIRE	 SHORTING TO GROUND IN THE PILOTS CONTROL YOKE, BEHIND THE CONTROL WHEEL.DUE TO LIMITED WIRE HARNESS CLEARANCE IN THE YO	KE, THE WIRE PROTECTIVE SLEEV CHAFFED ON YOKE THRU BOLTS AND THE WIRE CHAFFED AND SHORTED TO GROUND.			2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2001050200023	20010502	00023	CE  	2001	5	2	20010129CW017    	1	20001218	G	2760		LINKAGE         			MTSBSI	MU2   	MU2B26A     	5780414	CE  										COCKPIT	OBSTRUCTED      	B				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	783MA					391				PILOT NOTICED BINDING IN THE SPOILER LINKAGE AND DECLARED AN EMERGENCY.  THE AC LANDED WITHOUT INCIDENT.  MAINTENANCE IN	VESTIGATED AREAS IN THE COCKPIT UNDER THE FLOOR AND FOUND TOOLS AND DEBRIS.  SOME HARDWARE WAS FOUND UNDER THE SPOILER C	HAIN.  ONE OF THE NUTS HAD SIGNS OF DAMAGE ON THE FLATS.  SUSPECT THIS NUT HAD LODGED IN THE SPOILER CHAIN, THEN FELL OU	T OF MECHANISM.  SYSTEM WAS RESTORED AND FLIGHT CHECKED.			1	H	7	2 	3T			RT	A10SW   					 
2001050200024	20010502	00024	EA  	2001	5	2	20010129CW019    	2	20001215	G	7314		WASHER          	LYC         		CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL PUMP	DISINTEGRATED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	503ER				L2780151A	008003	L2780151A			INTERNAL TO THE LW15473 FUEL PUMP, ON THE UPPER END OF THE PULL ROD, SHOWS A WASHER PN6413701 AND PN6413703.  WASHER 641	13701 WAS MISSING FROM THE PULL ROD AND BELIEVED TO BE FOUND IN THE SUMP ANDSUMP SCREEN IN PIECES.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001050200025	20010502	00025	CE  	2001	5	2	20010129CW021    	1	20001201	G	2140	CI30021	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENGINE	CHAFED          	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	280SC	138  				BB664	PCE81553			HOSE IS RUBBING AGAINST ENGINE COWLING.  RT ENGINE OUTBOARD STACK RELOCATE PICK UP TUBE LOCATION, ANGLE TOWARDS ENGINE C	ASE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001050200026	20010502	00026	CE  	2001	5	2	20010129CW022    	1	20001201	G	2140	CI30022	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENGINE	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	280SC	138  				BB664	PCE81553			HOSE IS RUBBING AGAINST ENGINE COWLING.  RT ENGINE INBOARD STACK. RELOCATE PICK UP TUBE LOCATION ANGLE TOWARDS ENGINE CA	SE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001050200027	20010502	00027	CE  	2001	5	2	20010129CW023    	1	20001201	G	2140	CI30021	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	CHAFED          	B			YXUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	280SC	138  				BB664	PCE81535			HOSE IS RUBBING AGAINST ENGINE COWLING.  LEFT ENGINE INBOARD STACK.  RELOCATE PICK UP TUBE LOCATION, ANGLE TOWARDS ENGIN	E CASE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001050200028	20010502	00028	CE  	2001	5	2	20010129CW024    	1	20001201	G	2140	CI30022	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	CHAFED          	B			YXUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	280SC	138  				BB664	PCE81535			HOSE IS RUBBING AGAINST ENGINE COWLING. LEFT ENGINE OUTBOARD STACK. RELOCATE PICK UP TUBE LOCATION.  ANGLE TOWARDS ENGIN	E CASE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001041800178	20010418	00178	NM  	2001	4	18	20010129CW026    	1	20001130	G	3233		ACTUATOR        			DOUG  	MD11  	MD11        	3023602	NM  										RT MLG	FAILED          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	03	489GX					48458				AFTER AIRBORNE,  RIGHT MAIN LANDING GEAR CAN NOT RETRACT,  AIRCRAFT TURNED BACK TO AIRPORT.   RIGHT MAIN LANDING GEAR RE	TRACT ACTUATOR REPLACED.					2	L	7	3 	4F			RT	A22WE   					 
2001030700589	20010307	00589	SW  	2001	3	7	20010130CW003    	1	20001203	G	6340	407375001105	INDICATOR       			BELL  	407   	407         	       	SW  										COCKPIT	INOPERATIVE     	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99	96JJ	419  				53364				H A S  REPLACED WITH NEW MGT INDICATOR FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW    					 
2001030700619	20010307	00619	SW  	2001	3	7	20010130CW007    	1	20001207	G	2820	3017392	FUEL LINE       	PWA         		BELL  	412   	412EP       	1182205	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR1 INLET	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99	63177	165  	165  		RET60086	36173	RET60086			NR1 INLET COWLING CHAFING FUEL INLET LINE, PN3017392, DUE TO INSTALLATION OF SHADIN FUEL FLOW, STC SE1123GL.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001041000003	20010410	00003	SO  	2001	4	10	20010205CW001    	2	20001220	G	8530	TCMCC71	CYLINDER        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520CB     	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	922DN					T4922	815282R			EXHAUST LEAK BY NR 4 CYLINDER EXHAUST GASKET.  INSPECTED, FOUND 4 CYLINDER CRACKED BY EXHAUST VALVE AREA,  INSTALLED 5-9	-00, CYLINDER OVERHAULED 7-28-98, W/O 4419.CYLINDER HAS TOTAL OF 186.3 HOURS ON IT.  INSTALLED OVERHAULD CYLINDER ASSY.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001032200115	20010322	00115	CE  	2001	3	22	20010205CW002    	1	20001221	G	3720	1HS1	VALVE           			CESSNA	320   	320C        	2074510	CE  	CONT  	O470  	TSIO470B    	17026	SO  					MANIFOLD	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	3055T	6375 				320C0055				REPLACED LEFT VACCUUM PUMP. ON OPS CHECK, BOTH RED INDICATORS WERE SUCKED IN(RT ENGINE NOT RUNNING) ADVANCE THROTTLE AND	 RIGHT SIDE POPPED OUT.  TESTED MAN VALVE, VALVED FAILED.  CORRECTIVE ACTION: REPLACE VALVE.NOTE: MFG REC 10YR REPLACEME	NT BUT DOES NOT HAVE ANY./ONE FOUND				1	L	7	2 	3O	3	O	 	3A25    	3E3				 
2001032200116	20010322	00116	CE  	2001	3	22	20010205CW003    	1	20001225	G	8010	99103971	RELAY           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					STARTER SYSTEM	FAILED          	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			NM	09	6837Y					402C0467				SHORTLY AFTER TAKEOFF, CREW NOTICED INSTRUMENTS AND RADIOS FLICKERING, FOLLOWED BY TOTAL ELECTRICAL FAILURE.  CREW RETUR	NED AND LANDED WITHOUT INCIDENT.  MECH FOUND RT START RELAY FAILED IN CLOSED POSITION, PERMANENTLY ENGAGING THE STARTER.	  MECH REMOVED AND REPLACED SART RELAY, STARTER, AND AS PRECAUTIONARY MEASURE, REMOVED AND REPLACED BATTERY AND BATTERY 	RELAY.  AC RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001050200038	20010502	00038	EA  	2001	5	2	20010205CW009    	2	20001213	G	8530	AL75060	ROD BOLT        	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR4 CYLINDER	BROKEN          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SW	03	7090B				L612061A	317752075	L612061A			CONNECTING ROD BOLT BROKEN ON NR4 CYLINDER, LT ENGINE.  DURING CRUSE FLIGHT.  NR4 CYLINDER WAS PUSHED THRU COWLING AND B	ROKE OUT LEFT UPPER CRANKCASE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030700574	20010307	00574	SO  	2001	3	7	20010205CW017    	1	20001212	G	7810	1802716	EXHAUST STACK   			PIPER 	PA23  	PA23160     	7102304	SO  										NR 3 CYLINDER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4048P					231525				DURING REPAIR OF MASSIVE OIL LEAK ON LEFT ENGINE, FOUND EXHAUST STACK MISSING ON NR3 CYLINDER.  STACK BROKEN AT FLANGE A	ND WAS LYING IN COWL.  AIRCRAFT HAD BEEN FLYING THIS WAY FOR SEVERAL HOURS.  STACK ON NR2 CYLINDER WAS CRACK MORE THAN 5	0 PERCENT AT FLANGE.  OTHER IMPROPER REPAIRS NOTED ON OTHER EXHAUST PIPES.  AC HAD JUST PREVIOUSLY BEEN ANNUALED.  NEW P	ARTS WERE INSTALLED.			1	L	7	2 	3O			 	1A10    					 
2001030700577	20010307	00577	SO  	2001	3	7	20010205CW020    	1	20001212	G	7120	1713701	TRUSS           			PIPER 	PA23  	PA23160     	7102304	SO  										RT ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4048P					231525				WHILE PERFORMING OTHER MAINTENANCE ON RT ENGINE, TECH NOTICED BROKEN ENGINE TRUSS.  TRUSS MEMBER COMPLETELY BROKEN IN HA	LF.  CAUSE OF FAILURE BELIEVED TO BE SEVERE CORROSION ON THE INSIDE OF THE STEEL TUBE CONSTRUCTED TRUSS MEMBERS.  SUGGES	T REPLACING WHOLE LANDING GEAR/ ENGINE TRUSS ASSEMBLY.  AC HAD RECIEVED RECENT INSPECTION.				1	L	7	2 	3O			 	1A10    					 
2001030700578	20010307	00578	EA  	2001	3	7	20010205CW021    	2	20001212	G	8550	0320	TUBE            			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320B3B     	41508	EA  					ENGINE	MISINSTALLED    	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	4048P					231525	L150539			AC RETURNED TO AIRPORT DUE TO NOTICEABLE OIL LEAKAGE APPEARING ON LEFT WING AND COWLING.  4 QUARTS OF OIL MISSING WHEN M	AINTENANCE CK ENGINE.  FOUND  OIL DIPSTICK TUBE HAD BEEN IMPROPERLY SAFETIED AND LOOSENED, ALLOWING OIL TO ESCAPE.  OTHE	R ENGINE TUBE WAS ALSO LOOSE, BUT NOT LEAKING AS BADLY.  RESECURED AND SAFETIED BOTH TUBES.  AC HAD RECENT INSPECTION.				1	L	7	2 	3O	3	O	 	1A10    	E274				 
2001030700579	20010307	00579	SO  	2001	3	7	20010206CW001    	1	20001212	G	2820	S220000169	PRIMER LINE     			PIPER 	PA23  	PA23160     	7102304	SO  										LT ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	4048P					231525				WHILE REPAIRING MASSIVE EXHAUST LEAK ON LEFT ENGINE THE CYLINDER PRIMER LINE WAS FOUND BROKEN IN HALF AND ANOTHER FUEL P	RIMER LINE FOUND CHAFED.  RAW FUEL AND MASSIVE EXHAUST LEAK COULD CAUSE ENGINE FIRE.  NEW LINES INSTALLED.  AC HAD RECEN	T ANNUAL.				1	L	7	2 	3O			 	1A10    					 
2001030700580	20010307	00580	EA  	2001	3	7	20010206CW002    	2	20001218	G	7200	O320E2D	ENGINE          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	FAILED          	B				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			EA	21	6802H					17265588				ENGINE HAD LOW OIL PRESSURE AND HIGH OIL TEMPERATURE IN CLIMB.  TEMP STABILIZED IN DESCENT BUT OIL PRESSURE STILL LOW.  	LANDED AIRCRAFT.  MAINTENANCE FOUND ALUMINUM ON OIL PRESSURE RELIEF VALVE.  OIL PRESSURE SCREEN COVERED WITH ALUMINUM, S	TEEL FLAKES.  SUSPECT INTERNAL FAILURE.  CUSTOMER NOTIFIED, ENGINE REPLACEMENT REQUIRED. CAUSE OF FAILURE UNKNOWN.  ENGI	NE REPLACED BY CUSTOMER.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001030700583	20010307	00583	CE  	2001	3	7	20010206CW004    	1	20001220	G	5347	07106582	SEAT TRACK      			CESSNA	182   	R182        	2072734	CE  										SEAT TRACK	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4776T	4169 				R18201762				DURING COMPLIANCE OF AD, FOUND SEAT TRACKS INSTALLED WITH CHERRY MAX BLIND FASTENERS AND OVERSIZED RIVETS, WHICH DID NOT	 MEET THE REQUIRED 2D EDGE DISTANCE REQUIREMENT.  FLOOR AND TRACKS HAD TO BE REPLACED AND SUB FLOOR REPAIRED.  CHERRY MA	X RIVETS ANRE NOT APPROVED FOR MAJOR STRUCTURAL USE.  SUGGEST CHECKING FASTENERS WHILE COMPLYING WITH AD. CALL CESSNA FO	R GUIDANCE.			1	H	7	1 	3O			RT	3A13    					 
2001041000004	20010410	00004	EU  	2001	4	10	20010206CW009    	1	20001104	G	6720	AC67032	SERVO           	DUNLOP      		AEROSP	AS355 	AS355F1     	8680810	EU  										TAIL ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					1298					CRACK DETECTED ON LOWER END OF SERVO BODY ABOVE END CAP.  EDDY CURRENT TESTING.						1	G	7	2 	3U			 	H11EU   					 
2001041000006	20010410	00006	SW  	2001	4	10	20010206CW013    	1	20001027	G	6710	41002413	BEARING         	TEXTRON     		BELL  	214   	214B        	1182100	SW  										SERVO ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					878					CRACKS DETECTED DURING OVERHAUL.						2	G	7	1 	4U			 	H6SW    					 
2001030700616	20010307	00616	EA  	2001	3	7	20010207CW003    	2	20001212	G	8520	5015P07	STUD            			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320B3B     	41508	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4048P					231525	L150539			DURING REPAIR OF MAJOR OIL LEAK ON LT ENGINE, FOUND NR1 CYLINDER HAD 3 BROKEN STUDS AND ALL BUT 2 OF THE REMAINING HOLD 	DOWN NUTS HAD BACKED OFF.  CYLINDER ASSEMBLY WOULD HAVE SOON LEFT THE CRANKCASE.  3 STUDS WERE REPLACED AND ALL CLYINDER	 HOLD DOWNS RE-TORQUED ON BOTH ENGINES ALL FOUND BELOW SPECTS.AC HAD RECENT INSPECTION.  NO LOGS AVAILABLE FOR VERIFICAT	ION.			1	L	7	2 	3O	3	O	 	1A10    	E274				 
2001030700617	20010307	00617	SO  	2001	3	7	20010207CW004    	1	20001227	G	3231	6736200	ROD             			PIPER 	PA28  	PA28R200    	7102811	SO  										NLG DOOR	BENT            	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	15	5083S	5169 				28R7135082				AIRCRAFT LANDED WITH NOSE GEAR STUCK IN THE WELL.  NOSE GEAR DOORS JAMMED SHUT.  APPEARS GEAR DOOR OVER TRAVELED DUE TO 	BENT DOOR LINKAGE.					1	L	7	1 	3O			 	2A13    					 
2001030700614	20010307	00614	SO  	2001	3	7	20010209CW001    	1	20001214	G	2730	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										ELEVATOR	FRAYED          	G			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4132D	1541 				2843234				LEFT FORWARD ELEVATOR CABLE,  FRAYED.						1	L	7	1 	3O			 	2A13    					 
2001030700640	20010307	00640	SO  	2001	3	7	20010209CW002    	2	20001227	G	7314	64621216A2	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	LEAKING         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	8268T					CE1547	820321R			ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001030700641	20010307	00641	SO  	2001	3	7	20010209CW003    	2	20001226	G	7314	64621216A	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	LEAKING         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	1556A	583  				CE1318	820275R			ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM  DRAIN.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001030700642	20010307	00642	SO  	2001	3	7	20010209CW004    	2	20001226	G	7314	64621216A2	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	LEAKING         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	1570A	707  				CE1333	820296R			ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001032700193	20010327	00193	CE  	2001	3	27	20010209CW005    	1	20001130	G	3230	1003810061	DOWNLOCK SWITCH 	BEECH       	BE76        	BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360*       	41514	EA  					LT MLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	6011U				ME101	ME101				THIS IS A TWO WAY SWITCH, ONE HALF IS FOR THE INDICATOR LIGHT WHICH WORKS, THE OTHER HALF IS FOR THE DOWN & LOCK SYSTEM.	  WHICH SHUTS OFF THE MOTOR WHEN THE GEAR IS DOWN.  THE MAINTENANCE MANUAL  TROUBLESHOOTING SECTION IS INCORRECT, IT SAY	S IF THE MOTOR KEEPS RUNNING, ONE OR MORE SWITCHES ARE OPEN. IN REALITY ONE OR MORE SWITCHES ARE CLOSED.				1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2001030700625	20010307	00625	CE  	2001	3	7	20010209CW006    	1	20001212	G	5531	51310002	SPAR            			CESSNA	402   	402B        	207590P	CE  										VERTICAL STAB	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	676MF	9676 				402B0106				UPON ANNUAL INSPECTION, FLAKING WAS NOTICED ON AFT SPAR AREA.  FURTHER INSPECTION REVEALED THE SPAR WAS CORRODED  .2500 	THROUGH MAIN SURFACE.  UNIT WAS REPLACED WITH AN AIRWORTHY ITEM.					1	L	7	2 	3O			 	A7CE    					 
2001030700594	20010307	00594	EA  	2001	3	7	20010209CW008    	2	20001207	G	7414	10382681	CAPACITOR       	BENDIX      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540*    	41533	EA  					MAGNETO	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	38KC	219  			L299903	318352033				DURING TROUBLE SHOOTING A RUFF MAG PROBLEM, WE FOUND THAT THE MAG CAPACITOR PN10-382681 WAS COMING APART, SWEGED ON TOP 	SECTION WAS LOOSE.  THIS FAILED CAPCITOR HAS A DATE CODE OF 9948.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032200122	20010322	00122	EA  	2001	3	22	20010212CW004    	2	20000921	G	8500		ENGINE          			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  		FAILED          	C				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			AL	03	453SP					172S8297	L2852351A	TG085		UNEXPECTED ENGINE FAILURE DURING LANDING FLAIR.  ON DUAL TRAINING FLIGHT, IP DEMONSTRATING A SHORT-FIELD LANDING , OVER 	AN OBSTACLE, IN THE LANDING FLAIR, THROTTLE IDLE, ENGINE QUIT, PROP STOPPED TURNING.  IP LANDED UNEVENTFULLY AND PULLED 	OFF RUNWAY.  CREW PERFORMED SHUTDOWN CHECKLIST.  ALL CONTROLS/SWITCHES WERE IN CORRECT POSITION.  CREW PERFORMED ENGINE 	START CHECKLIST, ENGINE STATED NORMALLY WITH SMOOTH 650RPM IDLE.  RUNUP & IDLE CHECKS NORMAL.  INSPECTION BY A&P AFTER F	LIGHT REVEALED NO ABNORMALITY.  IDLE AND RUNUP CHECKS NORMAL.  AC RETURNED TO SERVICE.		1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001032200125	20010322	00125	CE  	2001	3	22	20010213CW003    	1	20001213	G	7920	EK9052V10	OIL FILTER      			CESSNA	414   	414A        	2075907	CE  										LT & RT FILTER	RESTRICTED      	B			Q2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	366MC	10   				414A1005				OIL FILTER/STRAINER IN EACH ENGINE TURBOCHARGER OIL SUPPLY LINE, THESE FILTERS ARE PREMATURLY CLOGGING WITH CARBON PARTI	CLES FROM THE OIL CAUSING LOSS OF MANIFOLD PRESSURE.  RAM  VERBALLY RECOMMENDS REMOVING THIS STRAINER LELMENT TO PREVENT	 THIS OCCURANCE, NO WRITTEN NOTICE HAS BEEN PROVIDED				1	L	7	2 	3O			 	A7CE    					 
2001032700194	20010327	00194	CE  	2001	3	27	20010213CW004    	1	20001227	G	3240	S116730085	HOSE CONNECTOR  			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	O360*       	41514	EA  					BRK CYL/BLKHD	LOOSE           	B				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			GL	15	499KW	413  				172S8430	820296R			RIGHT BRAKE INOPERATIVE.  FOUND LOOSE B-NUT ON BRAKE HOSE FROM MASTER CYLINDER.  APPEARS TO HAVE BEEN LOOSE FROM FACTORY	 AS THERE IS NO RECORD OF WORK BEING PERFORMED IN THIS AREA,  AND UNBROKEN TORQUE SEAL ON FITTINGS.					1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001032700195	20010327	00195	SO  	2001	3	27	20010213CW006    	2	20001226	G	7314	H209901BR	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					FUEL PUMP	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	1570A	707  				CE1333	820296R			ENGINE DRIVEN FUEL PUMP LEAKING OIL FROM DRAIN.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001032600155	20010326	00155	CE  	2001	3	26	20010215CW008    	1	20001211	G	2823		SHUTOFF VALVE   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A60A     	52043	NE  						FAILED          	D			PS2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	550CJ					UC50				WHILE TROUBLE SHOOTING LEFT FIREWALL FUEL SHUT OFF VALVE TROUBLE, FOUND WIRE CORR. AT CONNECTOR A124P1 SOCKET NR1.  THIS	 IS THE POWER WIRE TO THE SWITCH AT THE T HANDLE, REPAIRED WIRE AT SOCKET BY REPLACEMENT OF SOCKET.  NOTE:  THE SHUT OFF	 VALVE GETS POWER FROM HOT BATTERY BUSS AND AC BUSS.  BOTH POWERS RUN TO THE ONE LOCATION.  IF THIS DOESNT WORK THE VALV	E WILL NOT SHUT. CAUSE MAY BE FLUID LEAKING IN THE STORM WINDOW AND RUNNING DOWN THE SIDE WHEN AC IS SITTING ON THE GROU	ND.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001032600341	20010326	00341	SO  	2001	3	26	20010222CW004    	2	20001217	G	7314	63815416	PUMP            			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520*      	17032	SO  					BACK OF ENGINE	LEAKING         	D				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			GL	15	2054N		1500 			D10196				SHORTLY AFTER TAKEOFF, PILOT SMELLED SMOKE IN COCKPIT AND RETURNED TO AIRPORT.  UPON INSPECTION, FOUND ENGINE DRIVEN FUE	L PUMP TO BE LEAKING BETWEEN CASE HALVES.  NO HEAT RELATED DAMAGE TO ENGINE AREA WAS NOTED.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001040900446	20010409	00446	EA  	2001	4	9	20010222CW008    	2	20001220	G	7414	10106492	HOUSING         	BENDIX      		PIPER 	PA24  	PA24180     	7102402	CE  	LYC   	O360  	O360A1D     	41514	EA  					MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	8040P				ESI805608	243286	L2366536A			DURING ANNUAL INSPECTION ,  MAGNETS  WERE FOUND TO BE OUT OF TIME TO THE ENGINE.  EXAM OF CAM / CONTACT POINT AREA, DISC	LOSED OIL AND LG AMTS OF DUST AND ALUMINUM SHAVINGS.  DISASSEMBLY OF MAGNETS DISCLOSED BEARING, OUTER RACE / CUP / LOOSE	 IN THE HOUSING.  WEAR HAD REACHED POINT OF PERMITTING MOVEMENT THE ROTARY MAGNET SUFFICIENT CAUSE OIL SEEPAGE PAST OIL 	SEAL.			1	L	7	1 	3O	3	O	NT	1A15    	E286				 
2001031400252	20010314	00252	EU  	2001	3	14	20010223CW004    	1	20001222	G	2742	5435021	ACTUATOR        			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZONTAL STAB	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	62ND		1091 			379				NORMAL PITCH SYSTEM INOPERATIVE.  AC WAS ON RAMP ALL NIGHT.  DISCREPANCY FOUND BEFORE DEPARTURE.  COLD AND DAMP WEATHER 	CONTRIBUTED TO ACTUATOR NOT WORKING.  DURING REMOVAL AND INSTALLATION OF AN O/H ACTUATOR IN HANGER SYSTEM WORKED OK.  NO	TED:  GREASE PLUGGING DRAIN HOLE IN ACTUATOR.				2	M	7	2 	4F	4	F	 	A2SW    	E6WE				 
2001032200201	20010322	00201	SO  	2001	3	22	20010227CW003    	1	20001220	G	2710	62701124	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					AILERON	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4142Q	1740 				2843207	L3644336A			AILERON BALANCE CABLE FRAYED ABOUT       8 INCHES FROM TURN BUCKLE,  NEW CABLE INSTALLED.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001040900089	20010409	00089		2001	4	9	20010227CW004    	4	20001229	G	3421	RCA26BK9	GYRO            			BEECH 	58    	58TC        	1152746	CE  										COCKPIT	DEFECTIVE       	B			UKJR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	117HS					TK21				PILOT REPORTS ELECT STANDBY GYRO HORZ, INOPERATIVE.  REMOVED INSTRUMENT, CAN HEAR LOOSE PARTS MOVING AROUND INSIDE INSTR	UMENT.  REMOVED AND RETURNED TO MFG.					1	L	7	2 	3O			 	A23CE   					 
2001050200031	20010502	00031	SO  	2001	5	2	20010227SG003    	2	20001221	G	7314	6467681A1	PUMP            		TSIO520M    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	HCBXK	440  			818076R	U20604404				FUEL LEAK FROM BETWEEN PUMP AND MOUNT						1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001032100130	20010321	00130	CE  	2001	3	21	20010228CW004    	1	20001106	G	5520	9661000612	SKIN            			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  					LWR ELEV SKIN	DEBONDED        	B			EWCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	587P	194  				TH1820				DEBOND ON ALL HONEYCOMB STIFFENERS OF RIGHT ELEVATOR.						1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2001032100131	20010321	00131	EA  	2001	3	21	20010228CW009    	2	20000506	G	8530	LW16290	CYLINDER        			PIPER 	PA44  	PA44180T    	7104404	SO  	LYC   	O360  	TO360E1A6   	41514	EA  					RKR ARM STUD/NUT	BROKEN          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	21	8295C		418  			448107028	L13973			LEFT ENGINE WAS SHUT DOWN IN CRUISE FLIGHT AFTER A MODERATE VIBARATION WAS NOTED.  POST FLIGHT INSPECTION REVEALED THAT 	NR2 CYLINDER/LT ENGINE/ EXHAUST ROCKER ARM PIVOT STUD HAD BROKEN CAUSING ROCKER ARM TO COME OFF.  EXHAUST ROCKER ARM JAM	MED THE INTAKE ROCKER ARM CAUSING THE INTAKE PUSH ROD TO BEND.  THE HOLD DOWN NUT HAD LOST ITS LOCKING ABILITY.				1	L	7	2 	3O	3	O	 	A19SO   	E26EA				 
2001040900015	20010409	00015	SO  	2001	4	9	20010301CW002    	2	20001019	G	8530	RG532451	GASKET          			BEECH 	35    	A35         	1151504	CE  	CONT  	E185  	E185*       	17014	SO  					CYLINDER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	8595A					D2033	399468			A BACKED OUT ROCKER COVER SCREW WAS NOTICED AND A CHECK OF ALL ROCKER SCREWS REVEALED THAT MOST HAD A TOTAL LOSS OF TORQ	UE, WITH THE REMAINING HAVING NEARLY A TOTAL LOSS.  GASKETS WERE INSTALLED 7 HOURS EARLIER WITH NEW SCREWS, WASHERS AND 	LOCKWASHERS.  GASKETS WERE INSTALLED AT THE TORQUE OF 25 LBS AS PER INSTALLATION INSTRUCTIONS.  INSPECTION OF THE GASKET	S SHOWED NO VISIBLE DEFECTS.  GASKETS MUST HAVE RELAXED DURING THE SHORT TIME IN SERVICE CAUSING A LOSS IN TORQUE.  LOCK	WASHERS ALONE ARE NOT ADEQUATE.		1	L	7	1 	3O	3	O	 	A777    	E246				 
2001032100134	20010321	00134	CE  	2001	3	21	20010301CW005    	1	20001114	G	2731	065001802700	SERVO           			CESSNA	182   	182C        	2072708	CE  	LYC   	O540  	IO540*      	41532	EA  					TRIM SERVO	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	360ME	50   				18280849				ELECTRIC TRIM SERVO AT ELEVATOR, FAILED.						1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001030200058	20010302	00058	GL  	2001	3	2	20010302AP002    	3	20001212	G	6111	1A170E	BLADE           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  	MCAULY	1A170	1A170E      	GL  	PROPELLER	FAILED          	G				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			GL	15	582SP	239  				172S8509	L2901051A	UC143		PROPELLER BLADE FAILED 14 INCHES FROM CENTER OF HUB.PROPELLER WAS FORWARDED TO NTSB LAB FOR FURTHER ANALYSIS.						1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001030500004	20010305	00004	EA  	2001	3	5	20010302AP004    	2	20001223	G	8500		ENGINE          			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE BAY	MALFUNCTIONED   	P				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			sw	99	23838									I AM A STUDENT PILOT AND WAS AT 3000 FT AT A LEVEL CRUISE AND THE ENGINE SHUTTERED FOR APPROX. 1-3 SECONDS.  WE NEVER LO	ST POWER AND CONTINUED ON.  APPROX. 20 MINUTES LATER AT 2000'''' THE SAME CONDITION OCCURED. MY FLIGHT INSTRUCTOR FELT T	HAT WATER HAD PASSED THRU THE FUEL SYSTEM.  I HAD PREFLIGHTED THE AIRCRAFT AND SAMPLED FUEL FROM ALL 13 SUMPS, AND FOUND	 NO EVIDENCE OF WATER OR CONTAMINENTS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001030600021	20010306	00021	SO  	2001	3	6	20010302AP006    	2	20000907	G	7414	1051324	SPRING          	BENDIX      	S6RN1225    	CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	MAGNETO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	PKMPV	11   	11   		E189909FR	U20605864	818029R	803372		TCM/BENDIX MAGNETO IMPULSE COUPLING SPRING. P/N 10-51324, PART TSN 11.6 HOURS INSTALLED ON: MAGNETO P/N 10-349350-5. S/N	 E189909FR M/N S6RN-1225 MAGNETO TSN   11.6 HOURS. THIS SPRING BROKE APPROXIMATELY 6 INCHES FROM THE OUTER DIAMETER END.	  THE MECHANIC REMOVED THE MAG BECAUSE HE HEARD NO COUPLING ENGAGEMENT.  I DO NOT KNOW THE RESULTS OF THE MAG DROP TEST,	 PERHAPS THEY NEVER GOT THAT FAR.  I WOULD GUESS IT WAS ROUGH.  THE BREAK IN THE SPRING LOOKS LIKE A METALLURGY PROBLEM.	  IT IS A CLEAN BREAK WITH A BIT OF A FLASHING ON ONE SIDE.		1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2001040900250	20010409	00250	CE  	2001	4	9	20010302CW002    	1	20001114	G	2731		SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	O360*       	41514	EA  					ELEVATOR TRIM	FAILED          	C				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	01	146ME	288  				172S8432				TRIM SERVO FAILURE.  UNIT PREVENTS USE OF AUTOPILOT AND ELECTRIC TRIM / ELEVATOR TRIM.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001040900075	20010409	00075	CE  	2001	4	9	20010305CW002    	1	20000808	G	3210	3450A	LANDING GEAR    			CESSNA	206   	T206H       	       	CE  										MAINS	COLLAPSED       	G				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	01	7255T	70   	70   			T20608065				GOT RT GEAR UNSAFE LIGHT, UNABLE TO GET LIGHT TO GO OUT.  ON LANDING, ROLL OUT RT MAIN GEAR COLLAPSED,  DAMAGING THE RT 	FLOAT.  INSPECTION FOUND RT MAIN GEAR ACTUATING CONTROL SHAFT BROKEN.  INSTALLED KIT, REPAIRED  RT FLOAT KEEL AND SKINS 	THAT WERE DAMAGED.				1	H	7	1 	3O			 	A4CE    					 
2001040900053	20010409	00053	CE  	2001	4	9	20010305CW015    	1	20001113	G	2731	065001800400	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1C    	41514	EA  					ELEVATOR TRIM	FAILED          	C				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	01	350ME	93   				172S8585				UNITS TRIM VOLTAGE LOW.  CAUSE OF FAILURE UNKNOWN.  ELEVATOR TRIM						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001040500050	20010405	00050	SW  	2001	4	5	20010312CW007    	1	20001223	G	6210	206010233005	PAD             	BELL        		BELL  	206   	206L1       	1182107	SW  										ROTOR BLADE	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03					A1525					GRIP PAD COMES WITH ADHESIVE ON IT.  TO APPLY, REMOVE PROTECTIVE TAPE, ROUGH UP PREAPPLIED ADHESIVE WITH SANDPAPER, THEN	 MIX UP ANOTHER ADHESIVE AND INSTALL GRIP PAD TO BLADE.  PROBLEM IS THAT THE PREAPPLIED ADHESIVE LAYER IS TOO THICK, AFT	ER INSTALLATION OF GRIP PADS TO BLADE, THE BLADE CANNOT BE INSTALLED INTO ROTOR HEAD.				1	G	7	1 	3U			 	H2SW    					 
2001040500115	20010405	00115	NE  	2001	4	5	20010314CW005    	1	20001202	G	6710	0301037820	HARNESS         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250B  	250B*       	 	GL  					OVERSPEED GOV	DEFECTIVE       	E			EGRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	886AH					760153				OVERSPEED SHUTDOWN.  THE OVERSPEED HARNESS ASSEMBLY PN0301037820 WAS DISASSEMBLED.  THE CONNECTOR ASSEMBLY PN9922020010 	HAD WIRES NOT PROPERLY ENGAGED INTO PIN PN9550127410 DURING THE CRIMPING PROCESS.. WIRES PULLED FROM PINS.ACTION:  CRIMP	ED ON NEW PINS, REASSEMBLED HARNESS ASSEMBLY THEN REINSTALLED IN AIRCRAFT.  RUN UP OPERATIONAL CHECK.  NORMAL				1	G	7	2 	3U	3	T	 	H1NE    	E10CE				 
2001040900252	20010409	00252	CE  	2001	4	9	20010326CW008    	1	20000929	G	5711	052300583	SPAR            			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320*       	41508	EA  					LT WING	DAMAGED         	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	7122G	1457 				17258822				DURING HIDDEN DAMAGE INSPECTION SOME LIGHT DABAGE TO MID LEADING EDGE SKIN AND ONE NOSE RIB WAS FOUND.  UNAPPROVED REPAI	R FOUND TO AFT INBD SPAR ASSY.  DAMAGE WAS FOUND ON ALMOST ALL NOSE RIBS IN WING. RECORDS CHECK BY OWNER FOUND WING WAS 	REPAIRED AND RETURNED TO SERVICE AFTER WING SPAR SPLICE.  SPLICE WAS DONE WITH TOO MANY RIVETS, TOO LONG AND BENT OVER. 	 WING SHOWED LT DAMAGE, MID LD EDGE & 1 RIB. IT IS SUSPECT REST OF DAM. WAS PREVIOUS.  RECMD SEARCH INSP FOR HIDDEN DAM.	 BE MADE WITH ANY STRUCTURAL REPAIRS.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040900543	20010409	00543	EU  	2001	4	9	20010328CW003    	1	20001026	G	3246	AN960516	WASHER          	DUNLOP      		HAWKER	BAE125	BAE125700B  	7450007	EU  										MLG WHEEL	WRONG PART      	B			NCQG	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19					5041376					WHEN THIS PART WAS ADDED TO BOLT, IT MADE THE LENGTH OF BOLT TOO SHORT.  RESULTED IN WHEEL DISASSEMBLY.						2	L	7	2 	4F			RT	A3EU    					 
2001040900544	20010409	00544	EU  	2001	4	9	20010328CW004    	1	20001025	G	3246	MS2125005016	BOLT            			HAWKER	BAE125	BAE125700B  	7450007	EU  										WHEEL ASSY	INCORRECT       	B			NCQG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										THE PART USED WAS TOO SHORT AND CAUSED THE WHEEL HALVES TO SEPARATE.						2	L	7	2 	4F			RT	A3EU    					 
2001040900248	20010409	00248	NM  	2001	4	9	20010402CW002    	1	20001214	G	3610	1H2410	MANIFOLD        			PIPER 	PA60  	PA60602P    	7106015	NM  										LT ENGINE	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	858CH	2295 				608265006				ON LT ENGINE START, RED INDICATOR BUTTON RETRACTED, GAGE DROPPED TO ZERO.  PNEUMATIC PUMP SUPPLIED PRESSURE BUT ON PRESS	URE WAS GETTING TO GYRO FLIGHT INSTRUMENTS, DOOR SEALS,  GYRO PRESSURE REGULATOR OR PRESSURE GAGE.  RIGHT ENGINE SHOWED 	NORMAL INDICATOR AND GAGE INDICATION.  LEFT ENGINE SHUT DOWN AND BOTH INDICATOR BUTTONS STAYED RETRACTED.  STICKING FLAP	PER VALVES IN MANIFOLD CAUSED PROBLEM.  THIS WOULD CAUSE A SERIOUS SITUATION AT ALTITUDE.  NO PRESSURATION ADN NO GYROS.	  MANIFOLD IN SERVICE 2295.00 HOURS.		1	M	7	2 	3O			RT	A17WE   					 
2001040900251	20010409	00251	NM  	2001	4	9	20010402CW003    	1	20000609	G	2510	4000	BUCKLE          			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	TIO540*     	41532	EA  					SEAT BELT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	90464					61P0261051				BACK SIDE, OUTER RADIUS FOR BELT CUT OUT.  CRACKS AT CORNERS OF SLOT.  BUCKLE MADE OF ALUMINUM.						1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2001040900255	20010409	00255	NM  	2001	4	9	20010402CW004    	1	20000609	G	2510	4000	BUCKLE          			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	IO540*      	41532	EA  					SEAT BELT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	858CH					608265006				ON BACK SIDE OF ALL SEAT BELT BUCKLES, LATCH PART, CRACKS AT EACH CORNER OF BELT ATTACH SLOT.  PROBABLE CAUSE- MANUFACTU	RING- JOGGLE TOO SEVERE FOR ALUMINUM BECAUSE CRACKS APPEAR AT EACH JOGGLE.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2001040900333	20010409	00333		2001	4	9	20010403CW003    	4	20000916	G	6113	B2800	SPINNER         			BLANCA	1413  	1413        	1201002	EA  	FRNKLN	6A4150	6A4150*     	27024	EA  					PROP ASSY	DESTROYED       	C				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			WP	01	74231	375  				1344				ON CLIMBOUT A VIBRATION DEVELOPED THAT CONTINUED TO INCREASE IN AMPLITUDE.  THE FLIGHT WAS ABORTED.  SUBSEQUENT INVESTIG	ATION REVEALED THAT THE FORWARD PLASTIC SPINNER BULKHEAD HAD FAILED AROUND ITS PERIPHERY ALLOWING THE SPINNER TO WOBBLE.	  CONTINUED OPERATION IN THIS CONDITION WOULD HAVE RESULTED IN FAILURE OF THE AFT BULKHEAD AND DEPARTURE OF THE SPINNER 	FROM THE AIRCRAFT.			1	L	7	1 	3O	3	O	 	A773    	E238				 
2001041000274	20010410	00274	NE  	2001	4	10	20010409CW015    	2	20001009	G	7310	500013201	MANIFOLD        								PWA   	JT8   	JT8D217     	52053	NE  					FUEL SYSTEM	FRACTURED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19							P708492			RIGHT SECONDARY FUEL MANIFOLD WAS FOUND FRACTURED.  REMOVED AND REPLACED ALL FUEL MANIFOLDS.  A PRESSURE AND LEAK CHECK 	WAS CONDUCTED,  RESULTED IN NO LEAK FOUND.										4	F			E9NE				 
2001041000276	20010410	00276	EA  	2001	4	10	20010409CW017    	2	20001212	G	8520		EXHAUST VALVE   			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					NR 2 CYLINDER	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	3922Q					60022	L3003827A			AIRCRAFT ARRIVED WITH A ROUGH ENGINE.  OPERATIONAL CHECK OF ENGINE REVEALED DANAGE IN NR 2 CYLINDER.  FOUND THAT EXHAUST	 VALVE HAD BROKEN AND DESTROYED PISTON  ALSO.  ENGINE HAD 1122.7   TIME SINCE OVERHAUL.  PREVIOUS COMPRESSION CHECK SHOU	LD  HAVE REVEALED ANY PROBLEMS WITH VALVE.  ENGINE LOG DID NOT REVEAL ANY COMPRESSION CHECKS.  ENGINE OVERHAULED AND RET	URNED TO SERVICE.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001041700225	20010417	00225	SO  	2001	4	17	20010410AP018    	1	20001204	G	7921	AE7010201K0240	HOSE            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					LT ENG OILCOOLER	CRACKED         	G				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	410CA	47   				31T8166005	PCE92300			DURING CRUSE FLIGHT THE RIGHT ENGINE OIL PRESSURE LOW WARNING ALERT SOUNDED. PILOT SECURED ENGINE AND RETURNED TO THE AI	RPORT. TECHNICAN REMOVED ENGINE COWLING AND NOTED ENGINE OIL DRIPPING FROM THE OIL COOLER HOSE FIRE SLEEVE. THE OIL LINE	 WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2001042300205	20010423	00205	GL  	2001	4	23	20010412CW003    	3	20001228	G	6110	B3663	COUNTERWEIGHT   													HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER	CRACKED         	B			FQ6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										COUNTERWEIGHT SLUG CRACKED.  LOW TIME, HAVE SLUG.																6	C	P44GL	 
2001041700074	20010417	00074	GL  	2001	4	17	20010412CW004    	3	20001211	G	6110	B36632	COUNTERWEIGHT   			AYRES 	S2    	S2R         	7630202	CE  						HARTZL	HCB4T	HCB4TN5     	GL  	PROPELLER	CRACKED         	B			FQ6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	8988Q					1488R		CDA3594		COUNTERWEIGHT SLUG CRACKED IN SLOTS. LOW TIME,  HAVE SLUG.						1	L	7	1 	3R			NC	A4SW    		6	C	P40EA	 
2001042400288	20010424	00288	EA  	2001	4	24	20010420CW010    	2	20000926	G	8530		RETAINER        			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					ROCKER PIN	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5FA					600310115	L2028948A			DEFECT OCCURED UNDER NORMAL CIRCUSTANCE ON A FRESH FACTORY OVERHAUL.  NR 4 CYL INTAKE ROCKER RETAINER, BONDED TO VALVE C	OVER, CAME LOOSE ALLOWING ROCKER PIN TO SLIDE OUT.  ROCKER JAMMED AND BY FORCE OF PUSHROD, BROKE ROCKER SHAFT HOUSING, P	ART OF CAST ALUMINUM HEAD.  ALSO NR 4 INTAKE TAPPET JAMMED IN CASE AND BROKE INTO SEVERAL PIECES.  PUSHROD DENTED VALVE 	COVER ABOUT .3750 INCH DEEP DIMPLE FROM INSIDE.  ROCKER RETAINER SHOULD BE WELDED OR RIVETED TO VALVE COVER.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2001050300109	20010503	00109	CE  	2001	5	3	20010424CW009    	1	20000928	G	5312	07126161	BULKHEAD        			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470*       	17026	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	182AZ	3938 				18259852				WHILE PERFORMING 100 HOUR INSPECTION, FOUND A CRACK IN THE UPPER RADIUS ABOVE THE RIGHT RUDDER STOP BOLT.  PROBABLE CAUS	E WOULD BE FROM THE RUDDER CONTACTING TOO HARD, POSSIBLE WIND DAMAGE.  RECOMMED A SOFT HEADED STOP BOLT.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001050300154	20010503	00154	SO  	2001	5	3	20010426CW006    	2	20001204	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03			1692 							CYLINDER HEADS CRACKED FROM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE.  CYLINDER SERIAL NUMBERS:  G98/9438, 	 (G98/9439), G98/9440,  G98/9441,  H98/9469.										3	O			E5CE				 
2001050300155	20010503	00155	SO  	2001	5	3	20010426CW007    	2	20001204	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03			1692 							CYLINDER HEADS CRACKED FORM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE.  CYLINDER SERIAL NUMBERS:  G98/9438, 	 G98/9439,  (G98/9440),  G98/9441,  H98/9469.										3	O			E5CE				 
2001050300156	20010503	00156	SO  	2001	5	3	20010426CW008    	2	20001204	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03			1692 							CYLINDER HEADS CRACKED FROM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE.  CYLINDER SERIAL NUMBERS:  G98/9438, 	 G98/9439,  G98/9440,  (G98/9441),  H98/9469.										3	O			E5CE				 
2001050300157	20010503	00157	SO  	2001	5	3	20010426CW009    	2	20001204	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03			1692 							CYLINDER HEADS CRACKED FROM THE OUTSIDE OF THE INTAKE SEAT TO THE SPARK PLUG HOLE.  CYLINDER SERIAL NUMBERS:  G98/9438, 	 G98/9439,  G98/9440,  G98/9441,  (H98/9469).										3	O			E5CE				 
2001050300242	20010503	00242	CE  	2001	5	3	20010502CW004    	1	20000719	G	5753	052390133	SKIN            			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LT WING TE FLAP	DAMAGED         	C			AKOM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	79JP	2400 				18267081	469049	891062		DURING A POST FLIGHT INSPECTION, A 10.25 INCH TEAR IN THE LEFT FLAP UPPER SKIN.   TRAILING EDGE WAS DISCOVERED.  THE UPP	ER AND LOWER FLAP SKIN TRAILING EDGES SHOWED EVIDENCE OF NEW CRACKS AROUND THE RIVETS IN THE TRAILING EDGE BEYOND THE DA	MAGED SECTION.  THE AIRCRAFT HAD BEEN ENGAGED IN GLIDER TOWING OPERATIONS PRIOR TO DAMAGE.  PROBABLE CAUSE:  PILOT IN CO	MMAND, USE OF FLAPS OUTSIDE OF MANUFACTURERS RECOMMENDATIONS.  PILOT OPERATING HANDBOOK LIMITATIONS.			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001050300324	20010503	00324	SW  	2001	5	3	20010503CW003    	1	20000508	G	7922	53E19600	VALVE           			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3D6D  	41514	EA  					OIL TEMP	FAILED          	D				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	01	923DH	679  				243368	L2671551A			PILOT REPORTS AFTER TAKEOFF OIL TEMPERATURE RED LINED.  MADE SUCCESSFUL LANDING.  DRAINED OIL SUMP, INSPECTED OIL AND OI	L FILTER FOR METAL.  FINDING WAS NORMAL.  OIL COOLER AND LINES WERE CHECKED FOR OBSTRUCTIONS AND FLOW.  FINDINGS WERE NO	RMAL.  REMOVED VARATHERM AND FIELD TESTED TEMPERATURE FUNCTION,  FAILED.  NOTED SEATING SUNCTION OF PART THRU WITNESS MA	RKS, IT WAS NOT SEATING ON ACC CASE APPROX 70 PERCENT SEATING.  NOTED, PLUNGER WAS HANGING UP ON SURCLIP BETWEEN CASE AN	D THERMAL SENSOR.  INSTALLED SUPERIOR VARATHERM, TESTED AND TEST FLOWN, ALL OPS  NORMAL.		1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001050300214	20010503	00214	EU  	2001	5	3	20010503CW006    	1	20000727	G	2910	EN63A153	HOSE            			BAC   	111   	111419EP    	1480280	EU  										HYDRAULIC SYS	RUPTURED        	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	25	999BW	9150 				BAC120				PILOT REPORTED LOW QUANTITY IN NR 1 HYDRAULIC SYSTEM.  CAUSE WAS DETERMINED TO BE A RUPTURED HOSE ON THE PRESSURE SIDE O	F THE LEFT SPOILER.					2	L	7	2 	4F			 	A5EU    					 
2001051500127	20010515	00127	NE  	2001	5	15	20010507CW009    	1	20000629	G	2140	A14D1175	REGULATOR       			LAKEAC	LAKE  	250LAKE     	5110321	NE  	LYC   	O540  	TIO540*     	41532	EA  					HEATER	LEAKING         	B				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AL	03	8549Z	4    				115				DURING A ROUTINE FLIGHT THE PILOT NOTED A FUEL SMELL DURING HEATER OPERATION.  HE SHUT OFF THE HEATER AND RETURNED TO MA	INTENANCE BASE.  THE MECHANICS NOTED THAT THE HEATER FUEL PSI REGULATOR WAS LEAKING FROM DIAPHRAGM SEAL AREA.  A NEW VAL	VE WAS INSTALLED, BUT FAILED AFTER 2 HRS OF OPERATION.   A 2ND NEW VALVE WAS INSTALLED AND WAS FOUND TO LEAK FROM DIAPHR	AGM AREA AFTER A FEW HOURS OF OPERATION.   THE THIRD VALVE WORKS NORMALLY.  NO LEAKS WERE FOUND.			1	H	7	1 	3O	3	O	NC	1A13    	E14EA				 
2001051600422	20010516	00422	CE  	2001	5	16	20010508CW010    	1	20001127	G	2820	1560016D0140	LINE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J1A5    	41532	EA  					FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	9053C	391  				00380	L2000842A			STEELE BRADED FUEL LINE FOUND SEVERLY LEAKING AT ANNUAL INSPECTION.  NOTICED ENGINE COMPARTMENT VERY WASHED FROM FUEL LE	AKING WHILE RUNNING.  FUEL LINE WAS PRESSURE LINE FROM ENGINE FUEL PUMP TO CARBURETOR.  INSTALLED 2.97  391TT VERY COMMO	N PROBLEM. TIME LIMIT NEEDED ON STEELE FUEL LINES.				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001052400001	20010524	00001	CE  	2001	5	24	20010509CW008    	1	20001020	G	2810		VENT LINE       			CESSNA	185   	185F        	2072820	CE  	CONT  	O520  	IO520*      	17032	SO  					FUEL SYSTEM	CHAFED          	B			AKOM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	61795	871  				18504256	572877			DURING AN ANNUAL INSPECTION, THE FLEXIBLE FUEL VAPOR VENT LINE WAS FOUND CHAFED AGAINST THE POSITIVE BATTERY CABLE WHICH	 SUPPLIES POWER TO THE STARTER CONTACT SOLENOID.  UPON REMOVAL, THE FUEL LINE SHOWED EVIDENCE OF ARCHING AND THE STEEL O	UTER BRAIDING WAS BURNED AWAY.  THE INSULATION ON THE BATTERY CABLE WAS WORN AWAY AND BARE WIRE WAS EXPOSED.  PROBABLE C	AUSE:  IMPROPER FUEL LINE, BATTERY CABLE ROUTING, PROTECTION, AND ENGINE TO FIREWALL CLEARANCE LIMITATIONS.			1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2001071600049	20010716	00049	CE  	2001	7	16	20010614CW001    	1	20000501	G	3211	S3461108	BOLT            			CESSNA	172   	172N        	2072434	CE  										RT MLG	BROKEN          	D			VT3R	K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	09	6360D	9601 				17272746				RIGHT GEAR LEG SPRING ROTATED IN MOUNTING (BOLT SHEARED) AFTER AIRCRAFT LOCKED UP WHEEL FROM HARD BRAKING. GEAR ROTATED 	180 DEGREES. AIRCRAFT SUFFERED BELLY DAMAGE AND ELEVATOR DAMAGE.					1	H	7	1 	3O			NT	3A12    					 
2001080100208	20010801	00208	GL  	2001	8	1	2001FA0000073    	1	20000525	G	5320	81352	ROD             			AVIAT 	A1    	A1A         	2210405	GL  										TAIL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	27HU					1359				THIS PART BROKE ON LANDING, I BELIEVE THE AIRCRAFT WAS RENDERED UNCONTROLLABLE.						1	H	7	1 	3O			NC	A22NM   					 
2001092100007	20010921	00007	EA  	2001	9	21	2001FA0000321    	1	20001122	G	2810		FUEL TANK       			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R985  	R985*       	52008	NE  					FUSELAGE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	SNAYR	700  								WATER ACCUMULATING IN FUEL TANKS WITH NO QUICK DRAINS.  TT 700 TO 900 HOURSPLUS CORROSION.						1	Q	7	1 	3R	3	R	 	1A16    	5E1				 
2002012400092	20020124	00092	SO  	2002	1	24	2002FA0000131    	2	20000828	G	8520	630393	PUSHROD         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LT ENGINE	CRACKED         	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	91284					347970111	307800	HUB792007		ON ANNUAL INSPECTION OF THE LEFT ENGINE THREE PUSHRODS WERE NOTED TO BE CRACKED ALONG WHAT LOOKS LIKE THEIR ENTIRE LENGT	HS. THE THREE DEFECTIVE PUSHRODS WERE REPLACED WITH NEW ONES, AND THE REMAINDER OF THE PUSHRODS WERE OVERHAULED FOR BOTH	 ENGINES. CAUSE OF THIS DEFECT IS UNKNOWN.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2002020800022	20020208	00022	CE  	2002	2	8	2002FA0000178    	1	20000807	G	5711		STRAP           			BEECH 	90    	C90         	1152913	CE  										SPAR	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	575C					LJ532				DEFECT IN SK SPAR STRAP SYSTEM.						1	L	7	2 	3T			 	3A20    					 
2002040400066	20020404	00066	SO  	2002	4	4	2002FA0000425    	1	20000626	G	3213	65313004	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  										MLG STRUT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2159H	11437				287916192				ATTACH EAR BROKE OFF AT WHERE THE UPPER END OF THE TORQUE LINK ATTACHES TO THE STRUT HOUSING.  NOT ORIGINALLY REMORTED, 	 AS IT WAS THOUGHT TO BE A FLUKE, CAUSED BY A STUDENT CROSS LOADING THE GEAR ON LANDING, THUS CAUSING IT TO BREAK.					1	L	7	1 	3O			 	2A13    					 
2002040400067	20020404	00067	SO  	2002	4	4	2002FA0000426    	1	20000629	G	3213	65313004	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					MLG STRUT	CRACKED         	B			C85R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2496X	7414 				288516071				CRACKS IN RADIUS OF SCISSORS EARS. POSSIBLE CAUSE FATIGUE ON HIGH TIME AIRCRAFT.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002040400068	20020404	00068	SO  	2002	4	4	2002FA0000427    	1	20000629	G	3213	65319004	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  										STRUT	CRACKED         	B			C85R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	8234D	7841 				288216027				FOUND CRACKED DURING NORMAL MAINTENANCE.  NOTED WHILE DYE CHECKING THE AREA INVOLVED, HAVING FOUND 2 PRIOR STRUTS CRACKE	D.					1	L	7	1 	3O			 	2A13    					 
2002040400069	20020404	00069	SO  	2002	4	4	2002FA0000428    	1	20000626	G	3213	65319004	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					RT MLG	CRACKED         	B			C85R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2159H	11761				287916192				CRACK WAS FOUND DURING NORMAL 100 HOUR MAINTENANCE, SINCE WE HAD ENCOUNTERED ONE BREAKING OFF EARLIER, WE WERE MORE MIND	FUL OF CHECKING THEM CLOSER.  DYE CHECK SHOWED THE CRACK IN THE EAR RADIUS AREA.  ALL THE STRUTS ARE THOUGHT TO BE ORIGI	NAL EQUIPMENT.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002112000026	20021120	00026	CE  	2002	11	20	2002FA0001302    	1	20000126	G	5551	07326015	FITTING         			CESSNA	210   	210J        	2073439	CE  	CONT  	O520  	IO520J      	17032	SO  					HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	3366S					21059166	216519R			FITTING CRACKED DUE TO FATIGUE & VIBRATION.  INSTALL IMPROVED FITTING IN HORIZONTAL STABILIZER.						1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2003050700156	20030507	00156	CE  	2003	5	7	2003FA0000395    	1	20000714	G	3230	12416307	BUMPER BLOCK    			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MLG	DEBONDED        	B			SMTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	5555S	201  				P21000417				LEFT AND RIGHT MAIN LANDING GEAR SHELL BUMPER DEBONDS,  THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKIN	G FULL DOWN TRAVEL.  THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUAT	ION, THEREFORE, AN UNSAFE CONDITION.  IT APPEARS THAT MFG MAY HAFE CHANGED THE COMPOSITION OF THE SHELL BUMPER MATERIAL 	WHICH DOES NOT HAVE GOOD BONDING QUALITIES.  RECOMMEND CHANGING COMPOSITION OF BUMPER MATERIAL.  (PHOTO)			1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2003111400052	20031114	00052	EA  	2003	11	14	2003FA0001090    	2	20000101	G	8520		FLANGE          			PITTS 	S2B   	S2B         	2210006	SO  	LYC   	O540  	AEIO540D4A5 	41532	EA  	HARTZL	HCC2Y	HCC2YR4     	GL  	CRANKSHAFT	CRACKED         	B			R6AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	87WY					5111				FOUND CRACKED CRANKSHAFT AT FLANGE RADIUS.  SUGGEST INSTALLATION OF 3 BLADE PROP TO REDUCE LOAD ON CRANKSHAFT.						1	Q	7	1 	3O	3	O	NC	A8SO    	1E4	5	C	P920	 
2003123000072	20031230	00072		2003	12	30	2003FA0001214    	4	20000218	G	8300	07900066	MOUNT           			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					RT GEARBOX	CRACKED         	B			FE4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	94204	2995 				18503289				DURING AN ANNUAL, FOUND THE RT MAIN GEAR BOX STRUCTURE TO BE CRACKED.  ALSO NOTED THAT THE RT GEAR WAS LOOSE IN CASTING.						1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2001012900064	20010129	00064	NE  	2001	1	29	AC2A0000014      	1	20000131	G	7160	7630207028060	SCREEN          			SKRSKY	S76   	S76         	8143010	NE  										INTAKE	DAMAGED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T	891  				760140				BROKEN WIRES IN SCREEN.  REPLACED SCREEN WITH LIKE ITEM.  (X)						1	G	7	2 	3U			 	H1NE    					 
2001012900065	20010129	00065	GL  	2001	1	29	AC2A0000016      	2	20000224	G	7230	6896888	SCROLL          			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					COMPRESSOR	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5403C					760141	890850			SCROLL CRACKED AT NORMAL LOCATION.  REPLACED SCROLL.  (X)						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001012900053	20010129	00053	SW  	2001	1	29	AC2A0000018      	1	20000219	G	6230	222044680101	SLEEVE          			BELL  	430   	430         	1182150	SW  										M/R DRIVE	SCORED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	277  				49037				SCORING AT THE SEALING SURFACE.  REPLACED WITH NEW PART.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900037	20010129	00037	SW  	2001	1	29	AC2A0000019      	1	20000210	G	6410	206310105101	BEARING         			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	GALLED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17237	932  				51478				BEARINGS WERE GALLING AND CAUSING STIFF PETALS AT 100 PERCENT.  INSTALLED 4 NEW BEARINGS IN THE BLADES.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001012900071	20010129	00071	GL  	2001	1	29	AC2A0000021      	2	20000225	G	7230	6896888	SCROLL          			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					COMPRESSOR	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5414X					760152	890557			CRACKED SCROLL.  INSTALLED NEW SCROLL.  (X)						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001012900047	20010129	00047	SW  	2001	1	29	AC2A0000022      	1	20000219	G	5101	430310101105	RETAINER        			BELL  	430   	430         	1182150	SW  										FUSELAGE	LOOSE           	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1908 				49037				SHEAR RESTRAINT CAME LOOSE AT PIN.  REPLACED RESTRAINT.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900048	20010129	00048	SW  	2001	1	29	AC2A0000023      	1	20000219	G	6510	430010105105	PLATE           			BELL  	430   	430         	1182150	SW  										TAIL ROTOR	CHAFED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1908 				49037				SHEAR RESTRAINT CAME UNBONDED AND WORKED AGAINST CLAMP PLATE.  REPLACED CLAMP PLATE ASSY.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900049	20010129	00049		2001	1	29	AC2A0000024      	4	20000211	G	3425	430375002105	DISPLAY         			BELL  	430   	430         	1182150	SW  										EFIS	FAILED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1690 				49037				DISPLAY SLOWLY BECAME DIM, THEN WOULD NOT DISPLAY.  REPLACED EFIS DISPLAY.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900050	20010129	00050	SW  	2001	1	29	AC2A0000026      	1	20000229	G	2510	222320828121	SEAT BELT       			BELL  	430   	430         	1182150	SW  										COCKPIT	FRAYED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1710 				49037				SHOULDER STRAPS FRAYED AT KEEPER ON TOP OF SEAT.  REPLACED RESTRAINT ASSY.  SMOOTHED EDGES OF KEEPER.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900052	20010129	00052	SW  	2001	1	29	AC2A0000029      	1	20000224	G	6420	430010433101	BEARING         			BELL  	430   	430         	1182150	SW  										ROD END	WORN            	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1710 				49037				BEARING BEYOND LIMITS.  REPLACED ROD END.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900058	20010129	00058	SW  	2001	1	29	AC2A0000030      	1	20000203	G	6720	230312001101	LINK            			BELL  	430   	430         	1182150	SW  										TAIL ROTOR PITCH	WORN            	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH					49037				WORN LINKS.  REPLACED LINKS.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900056	20010129	00056		2001	1	29	AC2A0000035      	4	20000226	G	2564	BHLCOMP1822002	LIFE RAFT       			BELL  	430   	430         	1182150	SW  										EMERGENCY EQUIP	WILL NOT TEST   	A			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	430CH	1710 				49037				JETTISONABLE LIFE RAFT WOULD NOT PASS 25 POUND PULL TEST FOR DEPLOYMENT.  FOUND TORSION SPRING BHL/COMP.1728-201 INSTALL	ED TOO TIGHT AND WASHERS ADDED TO RELEASE HANDLE AT PIVOT POINT WHICH ARE NOT CALLED OUT IN THE PARTS MANUAL OR MM.  ADJ	USTED SPRING AND REMOVED WASHERS.  RAFT RELEASED PER INSPECTION.  (X)				1	G	7	2 	3U			RT	H9SW    					 
2001013000040	20010130	00040	SW  	2001	1	30	AC2A0000036      	1	20000313	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7159H					51397				STACK CRACKED.  REMOVED AND REPLACED STACK.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001012900062	20010129	00062	SW  	2001	1	29	AC2A0000039      	1	20000321	G	3040	222325001027	ARM             			BELL  	430   	430         	1182150	SW  										WINDSHIELD WIPER	BROKEN          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1787 				49037				WINDSHIELD WIPER GUIDE ARM BROKEN AT ATTACHMENT POINT.  REPLACED GUIDE ARM.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001013000036	20010130	00036	SW  	2001	1	30	AC2A0000040      	1	20000408	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6533U	407  				51439				EXHAUST ASSEMBLY CRACKED.  REMOVED AND REPLACED.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001012900061	20010129	00061	SW  	2001	1	29	AC2A0000042      	1	20000108	G	7100	230025203101	TUBE            			BELL  	430   	430         	1182150	SW  										ENGINE BAY	CHAFED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1565 				49037				TUBE WAS CHAFED BY ENGINE COWLING.  REPLACED TUBE.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001012900067	20010129	00067	NE  	2001	1	29	AC2A0000043      	1	20000426	G	6700	SA414A	BEARING         			SKRSKY	S76   	S76         	8143010	NE  										FLIGHT CONTROLS	BINDING         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5403C	16609				760141				INTERMITTENT BINDING IN FLIGHT CONTROL WHEN ROLL INPUT IS APPLIED.  REPLACED WORN BEARING.  (X)						1	G	7	2 	3U			 	H1NE    					 
2001012900072	20010129	00072	GL  	2001	1	29	AC2A0000044      	2	20000531	G	7230	23072848	SCROLL          			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30S     	03013	GL  					COMPRESSOR	DAMAGED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5447C	254  				760180	890328			ENGINE WOULD NOT PASS LIMITING CHECK AS OUTLINED IN SIKORSKY S76 FLIGHT MANUAL.  ENG ALSO REPORTED FOR LOW POWER.  ENG R	EMOVED.  UPON DISASSEMBLY OF TURBINE, 1ST STAGE TURBINE NOZZLE AND 1ST STAGE TURBINE WHEEL WERE FOUND DAMAGED FROM FOREI	GN OBJECT PASSING THROUGH TURBINE.  BOTH NOZZLE AND WHEEL WERE REJECTED DUE TO THIS DAMAGE. COMPRESSOR DISASSEMBLED, COM	P SCROLL, PN 23072848, WAS FOUND WITH ONE PIECE OF TURNING VANE MISSING, AREA BROKEN AWAY IS .50 INCH ACROSS AND ROUGHLY	 RECTANGULAR AND THIS MISSING PIECE OF TURNING VANE IS OBJECT THAT DAMAGED TURBINE, LEADING TO LOWER POWER.  ENG REPLACE	D.  (X)	1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001012900073	20010129	00073	NE  	2001	1	29	AC2A0000045      	1	20000604	G	6320	6893672	PINION GEAR     			SKRSKY	S76   	S76         	8143010	NE  										ENGINE GEARBOX	SPALLED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5447C	633  				760180				ENGINE REMOVED FOR METAL IN OIL.  UPON DISASSEMBLY OF GEARBOX, HELICAL POWER TRAIN PINION GEAR PN 6893672 WAS FOUND TO H	AVE SPALLING ON GEAR TEETH.  HELICAL TORQUEMETER GEAR ALSO HAD SPALLING ON GEAR TEETH.  BOTH PARTS WERE REJECTED DUE TO 	SPALLING.  PINION GEAR FAILED AT LOW TOTAL TIME IN SERVICE.  632.5 HRS.  TORQUEMETER GEAR HAD 5,000 PLUS HRS IN SERVICE.	  ENGINE REPLACED.  (X)			1	G	7	2 	3U			 	H1NE    					 
2001012900070	20010129	00070	EU  	2001	1	29	AC2A0000046      	1	20000603	G	6710	10545361	CONTROL ROD     			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5366Y					S782				TUBE IS CRACKED AT COLLAR.  REPLACED TUBE.  (X)						1	G	7	2 	3U			 	H3EU    					 
2001012900066	20010129	00066	NE  	2001	1	29	AC2A0000047      	1	20000520	G	5320	7620202010108	ANGLE           			SKRSKY	S76   	S76         	8143010	NE  										FUSELAGE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5403C					760141				T-ANGLE FOUND CRACKED SIX INCHES FORWARD ON PILOTS AFT DOOR POST.  REPAIRED PER SRM.  (X)						1	G	7	2 	3U			 	H1NE    					 
2001020900044	20010209	00044		2001	2	9	AC2A0000048      	4	20000617	G	3420	060002600	GYRO            			BELL  	430   	430         	1182150	SW  										COCKPIT	FAILED          	A			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	430CH	1164 				49037				VERTICAL GYRO FAILED AT APPROX 1000 HOURS.  PART CAUSED AIRCRAFT AUTOPILOT TO PITCH UP AND ROLL RIGHT WHEN AUTOPILOT ENG	AGED.  REPLACED VERTICAL GYRO WITH SERVICEABLE VERTICAL GYRO.  (X)					1	G	7	2 	3U			RT	H9SW    					 
2001020200065	20010202	00065	SW  	2001	2	2	AC2A0000052      	1	20000615	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7159H	8665 	49   			51397				STACK IS CRACKED OUT WITH ONLY 48 HOURS.  REPLACED PART.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900043	20010209	00043	SW  	2001	2	9	AC2A0000053      	1	20000617	G	6410	222016001131	BLADE           			BELL  	430   	430         	1182150	SW  										TAIL ROTOR	SEPARATED       	A			AC2A	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	03	430CH	1085 			A405	49037				SEPARATION IN THE ROOT CLOSURE.  THIS WAS THE ORIGINAL TAIL ROTOR BLADE RECEIVED WITH THIS AIRCRAFT.  IT WAS REMOVED THE	 FIRST TIME AT AIRCRAFT TT:  589.4 HOURS FOR BEARINGS CRACKED.  REPLACED TAIL ROTOR BLADE ASSY WITH SERVICEABLE PART.  (	X)				1	G	7	2 	3U			RT	H9SW    					 
2001020200064	20010202	00064	GL  	2001	2	2	AC2A0000054      	2	20000424	G	7230	6896888	SCROLL          			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					COMPRESSOR	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7266F		801  			760273	890830			SCROLL ASSEMBLY CRACKED.  REPLACED SCROLL.  (X)						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001020900051	20010209	00051	GL  	2001	2	9	AC2A0000055      	2	20000622	G	7313	47105	METERING VALVE  			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL NOZZLE	ERODED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6533U	531  			0571	51439				PART IS ERODED AT THE METER SET CAUSING STREAKING.  REPLACED THE METER SET.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001020200062	20010202	00062	GL  	2001	2	2	AC2A0000056      	2	20000622	G	7313	47105	METER           			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					FUEL NOZZLE	CORRODED        	B			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5447C	385  			AG52992	760180				PART IS ERODED AT THE METER SET CAUSING STREAKING AND VOIDS IN THE SPRAY PATTERN.   REPLACED THE METER SET.  (X)						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001020900047	20010209	00047	GL  	2001	2	9	AC2A0000057      	2	20000622	G	7313	47105	METERING VALVE  			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					FUEL NOZZLE	ERODED          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T	143  			AG55440	760140				PART IS ERODED AT METER SET CAUSING STREAKING AND VOIDS IN THE SPRAY PATTERN.  (X)						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001020900031	20010209	00031	NE  	2001	2	9	AC2A0000063      	1	20000511	G	2612	7630607902101	FIRE DETECTOR   			SKRSKY	S76   	S76         	8143010	NE  										NR 2 ENGINE	MALFUNCTIONED   	A			AC2A	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	5447C	16030				760180				AIRCRAFT DEPARTED ICY ON 135 SERVICE FLIGHT AND APPROX 10 MILES SOUTH OF ICY, NR 2 ENGINE FIRE LIGHT ILLUMINATED AND FIR	E WARNING HORN SOUNDED.  CANCELLED TONE AND IN ABSENCE OF ANY SECONDARY INDICATIONS, RETURNED TO HELIPORT AND MADE A NOR	MAL APPROACH.  MECHANICS DETERMINED THERE WAS A PROBLEM WITH THE SENSOR SWITCH.  REMOVED AND REPLACED FLAME DETECTOR WIT	H A SERVICEABLE DETECTOR.  SYSTEM CHECKED OK.  (X) 			1	G	7	2 	3U			 	H1NE    					 
2001020100056	20010201	00056	NE  	2001	2	1	AC2A0000064      	1	20000624	G	7603	7630101910117	CONTROL CABLE   			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					THROTTLE	DAMAGED         	A				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	5447C					760180				AFTER LANDING ON SS169C, MOVED ENGINE THROTTLES TO GROUND IDLE WHILE LOADING AND UNLOADING PASSENGERS.  WHEN THROTTLES M	OVED BACK TO FLY, NR 2 THROTTLE MADE A NOTICEABLE CLICK AT THE FULL OPEN POSITION AND TRAVEL FURTHER FORWARD IN THE QUAD	RANT.  PULLED THROTTLE BACK SLIGHTLY, RPM RESPONDED.  RETURNED THROTTLE TO FULL OPEN.  CAREFULLY LIFTED TO A HOVER AND P	OWER SEEMED NORMAL.  UPON TAKEOFF, NR 2 ENG WOULD NOT PRODUCE MORE THAN 75 PERCENT TORQUE WHILE NR 1 WOULD INCREASE TO 1	00 PERCENT.  WHEN COLLECTIVE REDUCED, NR 2 ENG REMAINED AT 75 PERCENT TORQUE.  RETURNED TO ICY, MADE A SLOW RUN-ON LANDI	NG.  WHEN NR 2 ENGINE LEVER RETARDED TO IDLE, WORKED NORMAL, HOWEVER ENGINE RPM WOULD NOT GO BACK TO FLY WHEN ADVANCED.	1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001020100057	20010201	00057	EU  	2001	2	1	AC2A0000065      	1	20000622	G	6220	1051410110	BOLT            			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR HEAD	DEFECTIVE       	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5366Y				52238	S782				PART IS DEFECTIVE.  BOLT HEAD HAS SEVEN SIDES INSTEAD OF THE USUAL SIX.  PART TT IS 311.0 HOURS SINCE NEW.  REPLACED BOL	T.  (X)					1	G	7	2 	3U			 	H3EU    					 
2001020100058	20010201	00058	NE  	2001	2	1	AC2A0000066      	1	20000706	G	6220	SS40CT28A140180	HOSE            			SKRSKY	S76   	S76A        	8143006	NE  										M/R DAMPER	BINDING         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72649					760292				WHILE INSPECTING M/R DAMPERS, THE BLACK DAMPER HOSE WAS FOUND BINDING WHEN THE DAMPER WAS ROTATED.  THE INBOARD FERREL W	AS ALSO FOUND TURNING WHEN HOSE WAS ROTATED.  REPLACED HOSE, THE BAD NOSE WAS FOUND TO BE .50 INCH SOFTER THAN THE NEW H	OSE.  (X)				1	G	7	2 	3U			 	H1NE    					 
2001020100059	20010201	00059	NE  	2001	2	1	AC2A0000067      	1	20000707	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CORRODED        	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5401G					760137				DURING ZONE 1 INSPECTION, CORROSION WAS FOUND THROUGHOUT THE LOWER SURFACE OF THE YELLOW MAIN ROTOR BLADE.  THE ALUMINUM	 WIRE MESH WAS FOUND WITH NUMEROUS SMALL PITS OF CORROSION THROUGHOUT THE LOWER SURFACE OF THE BLADE.  REMOVED CORROSION	 AND SPOT PAINTED PER COMPOSITE REPAIR MANUAL.  (X)				1	G	7	2 	3U			 	H1NE    					 
2001020100060	20010201	00060	NE  	2001	2	1	AC2A0000068      	1	20000707	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CORRODED        	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5401G	3887 				760137				DURING ZONE 1 INSPECTION, CORROSION WAS FOUND THROUGHOUT LOWER SURFACE OF MAIN ROTOR BLADE.  THE ALUMINUM WIRE MESH WAS 	FOUND WITH NUMEROUS CORROSION PITS THROUGHOUT THE LOWER SURFACE OF THE BLADE.  REMOVED CORROSION AND SPOT PAINTED PER CO	MPOSITE REPAIR MANUAL.  (X)				1	G	7	2 	3U			 	H1NE    					 
2001020100061	20010201	00061	SW  	2001	2	1	AC2A0000072      	1	20000712	G	2435	230811150	DRIVE SHAFT     			BELL  	430   	430         	1182150	SW  										STARTER GEN	DEFECTIVE       	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH				97101	49037				PART IS DEFECTIVE.  SHAFT DIAMETER THAT ENGAGES THE ARMATURE IS TOO LARGE.  SUBMITTER STATED THIS IS A MANUFACTURING DEF	ECT.  REPLACED SHAFT.  (X)					1	G	7	2 	3U			RT	H9SW    					 
2001020100063	20010201	00063	SW  	2001	2	1	AC2A0000074      	1	20000521	G	5210	206033635004	HINGE           			BELL  	206   	206L3       	1182108	SW  										CREW DOOR	MISMARKED       	A			AC2A	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	7159J	8996 				51408				HINGE IS STAMPED WITH LEFT PART NUMBER, BUT IS A RIGHT PART.  REMOVED AND REPLACED WITH PROPER PART.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020100066	20010201	00066	SW  	2001	2	1	AC2A0000077      	1	20000709	G	7810	230063301102	EXHAUST PIPE    			BELL  	430   	430         	1182150	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1141 				49037				ENGINE EXHAUST DUCT FOUND CRACKED IN THE REAR AREA NEAR CENTER BOTTOM.  REPLACED ENGINE EXHAUST DUCT.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001020100067	20010201	00067	SW  	2001	2	1	AC2A0000078      	1	20000715	G	5210	222031290117	HINGE           			BELL  	430   	430         	1182150	SW  										DOOR WINDOW	BROKEN          	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	2295 				49037				COPILOT VENT WINDOW IN COPILOT DOOR WINDOW, HAD BROKEN HINGE.  REPLACED VENT WINDOW.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001020100068	20010201	00068	SW  	2001	2	1	AC2A0000079      	1	20000708	G	3246	430336437101	STRAP           			BELL  	430   	430         	1182150	SW  										LANDING SKID	DEBONDED        	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	2295 				49037				RIGHT AFT LANDING GEAR STRAP ASSY HAD RUBBER PAD DEBONDED.  REPLACED AFT STRAP ASSY.  (X)						1	G	7	2 	3U			RT	H9SW    					 
2001020900032	20010209	00032	SW  	2001	2	9	AC2A0000080      	1	20000710	G	5210	NAS5623R7A	CAM             			BELL  	430   	430         	1182150	SW  										CREW DOOR	CORRODED        	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH					49037				CAM FOLLOWERS ON HINGES FOR CABIN DOORS WERE FOUND TO HAVE CORROSION IN BEARINGS CAUSING THE BEARINGS TO SEIZE AND COME 	APART.  THE CAM FOLLOWER IS NOT PROTECTED FROM THE ENVIRONMENT AND MOISTURE CAN EINTER BEARING EASILY.  REPLACED CAM FOL	LOWERS.  (X)				1	G	7	2 	3U			RT	H9SW    					 
2001020900033	20010209	00033	SW  	2001	2	9	AC2A0000081      	1	20000726	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6533U					51439				EXHAUST ASSEMBLY IS CRACKED.  REPLACED PART.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900034	20010209	00034	SW  	2001	2	9	AC2A0000084      	1	20000718	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31079	273  				51526				EXHAUST ASSY IS CRACKED.  REPLACED WITH NEW PART.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001020900035	20010209	00035	SW  	2001	2	9	AC2A0000085      	1	20000124	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7159J	8682 				51408				EXHAUST ASSY CRACKED.  REPLACED WITH NEW PART.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900036	20010209	00036	SW  	2001	2	9	AC2A0000086      	1	20000809	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31079	7971 				51526				EXHAUST ASSY CRACKED.  REMOVED AND REPLACED DUCT.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900037	20010209	00037	NE  	2001	2	9	AC2A0000087      	1	20000822	G	6711	7640201113101	FITTING         			SKRSKY	S76   	S76         	8143010	NE  										COLLECTIVE STICK	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5403C	16921	1    			760141				FOUND SMALL CRACK IN UNDERSIDE OF FITTING.  VERIFIED CRACK WITH NDT.  REPLACED FITTING.  (X)						1	G	7	2 	3U			 	H1NE    					 
2001020900038	20010209	00038	NE  	2001	2	9	AC2A0000089      	2	20000810	G	7250	23053299	TURBINE WHEEL   			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					NR 1 ENGINE	CONTAMINATED    	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	1524 				49037	844017			FIELD MAINT REPORTED NR 1 ENGINE HAD FOREIGN OBJECT DAMAGE TO NR 1 ENG COMPRESSOR.  MECH EXAMINED TURBINE FOR DAMAGE PER	 MAINT INSTRUCTIONS.  DAMAGE FOUND ON TURBINE NR 1 WHEEL AND ENG REMOVED AND RETURNED FOR REPAIR.  UPON TEARDOWN, FOUND 	NR 1 TURB WHEEL HAD DAMAGE BEYOND REPAIR ON WHEEL BLADE TIPS DUE TO SULFIDATION CAUSING OTBD L/E OF BLADE TIPS TO ACCUMU	LATE DEPOSITS FROM CONTAMINANTS IN ATMOSPHERE, AND POSSIBLY CAUSED BY OTHER CONDITIONS.  REF RR 250/C30, CSL 3161.  AFFE	CTED TURBINE WHEEL REMOVED FROM SERVICE AND REPLACED.  TURBINE REPAIRED, RETURNED TO SERVICE.  (X)		1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2001020900039	20010209	00039	SW  	2001	2	9	AC2A0000090      	1	20000826	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17592	7307 				51535				REMOVED AND REPLACED CRACKED EXHAUST DUCT.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900040	20010209	00040	SW  	2001	2	9	AC2A0000091      	1	20000806	G	6410	206016201131	BLADE           			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	PEELING         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7159J	370  				51408				TAIL ROTOR BLADE PAINT PEELING AT 370.2 HOURS SINCE NEW.  VISUAL INSPECTED, SANDED PAINT AND REPAINTED.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900041	20010209	00041	SW  	2001	2	9	AC2A0000092      	1	20000806	G	6410	206016201131	BLADE           			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	PEELING         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7159J	370  				51408				TAIL ROTOR BLADE PAINT PEELING AND BEARINGS WORN BEYOND LIMITS.  INSPECTED, REPLACED 2 EACH BEARINGS, SANDED THE PAINT A	ND REPAINTED.  INSTALLED 2 EACH SLEEVES PN 206-010-733-003 PNAV 300549, 2 EACH BEARINGS PN 206-310-105-101 TRACKING NR 3	9858.  (X)				1	G	7	1 	3U			 	H2SW    					 
2001020200066	20010202	00066	SW  	2001	2	2	AC2A0000094      	1	20000915	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	715CC	8380 				51380				EXHAUST ASSY CRACKED.  REPLACED.  (X)						1	G	7	1 	3U			 	H2SW    					 
2001020900046	20010209	00046	NE  	2001	2	9	AC2A0000095      	1	20000926	G	6711	7640201113101	FITTING         			SKRSKY	S76   	S76         	8143010	NE  										COLLECTIVE STICK	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5402T					760140				FITTING, PILOTS COLLECTIVE STK IS CRACKED.  VERIFIED CRACK WITH NDT.  REPLACED FITTING.  (X)						1	G	7	2 	3U			 	H1NE    					 
2000103100106	20001031	00106	NE  	2000	10	31	AC2A0000096      	1	20000926	G	3210	1945E235	ROD END         			SKRSKY	S76   	S76A        	8143006	NE  										MLG	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	72649					760292				WHILE PERFORMING THE REQUIREMENTS OF ASB 76-32-26, CORROSION INSPECTION OF THE THREADED JOINT, FOUND BEARING CRACKED.  R	EPLACED POSITIONING ROD END.  (X)					1	G	7	2 	3U			 	H1NE    					 
2001020900042	20010209	00042	SW  	2001	2	9	AC2A000093       	1	20000909	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	A			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53702					51249				EXHAUST ASSEMBLY CRACKED.  REPLACED.  (X)						1	G	7	1 	3U			 	H2SW    					 
2000041300003	20000413	00003	SW  	2000	4	13	AC2A066556       	1	20000219	G	6410	206310105101	BEARING         			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	DAMAGED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17237	932  				51478				BEARINGS WERE GAULING AND CAUSING STIFF PEDALS AT 100 PERCENT.   INSTALLED 4 NEW BEARINGS IN THE BLADES.						1	G	7	1 	3U			 	H2SW    					 
2001050700570	20010507	00570	NE  	2001	5	7	AC2A072770       	1	20001017	G	6700	7640201113101	FITTING         			SKRSKY	S76   	S76A        	8143006	NE  										FLIGHT CONTROLS	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	5401G					760137				PART IS CRACKED. REPLACED CRACKED COLLECTIVE SOCKET.						1	G	7	2 	3U			 	H1NE    					 
2001050700571	20010507	00571	NE  	2001	5	7	AC2A072772       	1	20001208	G	6730	7665005801112	SERVO           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7266K	13399				760283				CRACKED MOUNTING FLANGE. REPLACED T/R SERVO.						1	G	7	2 	3U			 	H1NE    					 
2001051000128	20010510	00128	SW  	2001	5	10	AC2A072792       	1	20001022	G	7810	206064300005	EXHAUST PIPE    			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	17238	317  				51492				STACK CRACKED AS REAR WELD SEAM. REMOVED AND REMOVED STACK.						1	G	7	1 	3U			 	H2SW    					 
2001051000129	20010510	00129	SW  	2001	5	10	AC2A072793       	1	20001206	G	6300	430010124101	BUSHING         			BELL  	430   	430         	1182150	SW  										M/R DRIVE	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	589  				49037				BUSHINGS WORN BEYOND LIMITS. REPLACED BUSHINGS						1	G	7	2 	3U			RT	H9SW    					 
2001051000130	20010510	00130	SW  	2001	5	10	AC2A072794       	1	20001206	G	6230	430310450101	DUPLEX BEARING  			BELL  	430   	430         	1182150	SW  										SWASHPLATE	MAKING METAL    	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	565  				49037				METAL IN SWASHPLATE GREASE. REPLACED DUPLEX BEARING						1	G	7	2 	3U			RT	H9SW    					 
2001051000131	20010510	00131	SW  	2001	5	10	AC2A072795       	1	20001206	G	6321	5009209	LINER           			BELL  	430   	430         	1182150	SW  										ROTOR BRAKE	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	964  				49037				ROTOR BRAKE WEAK - REPLACED LININGS WITH NEW.						1	G	7	2 	3U			RT	H9SW    					 
2001051000132	20010510	00132	SW  	2001	5	10	AC2A072796       	1	20001206	G	2432	39563001	BATTERY PACK    			BELL  	430   	430         	1182150	SW  										MAIN	WEAK            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	589  				49037				BATTERY FAILED FUNCTIONAL TEST. REPLACED BATTERY.						1	G	7	2 	3U			RT	H9SW    					 
2001051000133	20010510	00133	SW  	2001	5	10	AC2A072797       	1	20001206	G	7810	230063301102	EXHAUST STACK   			BELL  	430   	430         	1182150	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	473  				49037				EXHAUST CRACKED.						1	G	7	2 	3U			RT	H9SW    					 
2001051000134	20010510	00134	SW  	2001	5	10	AC2A072798       	1	20001206	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J	634  				51408				CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001051000135	20010510	00135	SW  	2001	5	10	AC2A072799       	1	20001208	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17592	215  				51535				CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001051000136	20010510	00136	SW  	2001	5	10	AC2A072800       	1	20001208	G	2910	70053H000A100A	HOSE            			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	LEAKING         	H			AC2A	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			FS	01	715CC					51380				SMALL PIN HOLE IN HYDRAULIC FLEX LINE  CAUSED LOSS OF HYDRAULIC FLUID.  FLEX LINE IS LOCATED ON THE PRESSURE OUTLET OF T	HE HYDRAULIC PUMP. REPLACED LINE.					1	G	7	1 	3U			 	H2SW    					 
2001051000137	20010510	00137	SW  	2001	5	10	AC2A072801       	1	20001212	G	2910	70053H000A100A	HOSE            			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	LEAKING         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	8998 				51439				PILOT REPORTED GETTING FEEDBACK IN THE FLIGHT CONTROLS UPON SHUTDOWN OF THE AIRCRAFT.  AFTER COMPLETING THE SHUTDOWN, HE	 EXAMINED THE AIRCRAFT AND FOUND HYDRAULIC FLUID IN THE TRANSMISSION DECK. REPLACED HOSE ASSY.					1	G	7	1 	3U			 	H2SW    					 
2001051000138	20010510	00138	SW  	2001	5	10	AC2A072802       	1	20001214	G	2913	222380009105	PUMP            			BELL  	430   	430         	1182150	SW  										HYD SYSTEM	MALFUNCTIONED   	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	430CH	2759 				49037				PSI ABOVE 1600 AT 10 DEGS. OAT. REPLACED PUMP						1	G	7	2 	3U			RT	H9SW    					 
2000011500590	20000115	00590	WP  	2000	1	15	AGQA065532       	1	20000111	G	6510	369A76131	LINK ASSY       			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				LINK ASSEMBLY IS  WORN EXCESSIVELY.						1	G	7	1 	3U				H3WE    					 
2000011500591	20000115	00591	WP  	2000	1	15	AGQA065533       	1	20000106	G	2436	369A4652	VOLT REGULATOR  			HUGHES	369   	369E        	4470707	WP  										BATTERY BOX	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				VOLTAGE REGULATOR UNABLE TO POWER UP.						1	G	7	1 	3U				H3WE    					 
2000011500592	20000115	00592	SW  	2000	1	15	AGQA065534       	1	20000106	G	2450	MS24171D1	RELAY           			BELL  	206   	206B3       	1181506	SW  										MLG	BURNED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				RELAY IS BURNED.						1	G	7	1 	3U				H2SW    					 
2000011500593	20000115	00593	SW  	2000	1	15	AGQA065535       	1	20000106	G	2840	206075189001	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										FUEL QUANTITY	ERRATIC         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				FUEL QUANTITY INDICATOR IS ERRATIC.						1	G	7	1 	3U				H2SW    					 
2000011500594	20000115	00594		2000	1	15	AGQA065536       	4	20000106	G	3457	0110005400	GPS             			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				GPS UNABLE TO FIND SATELLITES.						1	G	7	1 	3U				H3WE    					 
2000011500595	20000115	00595	WP  	2000	1	15	AGQA065537       	1	20000106	G	6420	369A17255	HUB             			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				TAIL ROTOR HUB IS WORN EXCESSIVELY.						1	G	7	1 	3U				H3WE    					 
2000011500596	20000115	00596	SW  	2000	1	15	AGQA065538       	1	20000106	G	6240	32005007	TACH GENERATOR  			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	ERRATIC         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				TACHOMETER/GENERATOR  IS ERRATIC.						1	G	7	1 	4U				H4SW    					 
2000011500597	20000115	00597	SW  	2000	1	15	AGQA065539       	1	20000106	G	3240	MS24171D1	RELAY           			BELL  	206   	206B3       	1181506	SW  										MLG	BURNED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718					1917				RELAY IS BURNED.						1	G	7	1 	3U				H2SW    					 
2000011500598	20000115	00598	SW  	2000	1	15	AGQA065540       	1	20000106	G	2430	51509002R	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  										DC SYSTEM	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				DC CONTROL IS UNABLE TO COME ON-LINE.						1	G	7	1 	4U				H4SW    					 
2000011500599	20000115	00599	WP  	2000	1	15	AGQA065541       	1	20000106	G	3210	369D26301	DAMPER          			HUGHES	369   	369D        	4470706	WP  										MLG	WEAK            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				MLG DAMPER IS WEAK.						1	G	7	1 	3U				H3WE    					 
2000011500600	20000115	00600	WP  	2000	1	15	AGQA065542       	1	20000106	G	3210	369D26301	DAMPER          			HUGHES	369   	369D        	4470706	WP  										MLG	WEAK            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				MLG DAMPER IS WEAK.						1	G	7	1 	3U				H3WE    					 
2000022300018	20000223	00018	EA  	2000	2	23	AGQA065543       	2	20000106	G	7412	103815501	EXCITER         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				EXCITER BOX IS INOPERABLE.  WILL NOT EXCITE.						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2000011500601	20000115	00601		2000	1	15	AGQA065544       	4	20000106	G	3457	12000301	GPS             			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				GPS UNABLE TO FIND SATELLITES.						1	G	7	1 	4U				H4SW    					 
2000011500602	20000115	00602	WP  	2000	1	15	AGQA065545       	1	20000106	G	7714	389A4517	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R	4610 				1161D				TACHOMETER/GENERATOR  MAKES N1 GAUGE HANG AT ZERO..						1	G	7	1 	3U				H3WE    					 
2000011500603	20000115	00603	GL  	2000	1	15	AGQA065546       	2	20000106	G	7532	23053176	BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D	CAE822961			BLEED VALVE PRODUCES LOW POWER- HIGH N1 SPEED.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000011500604	20000115	00604		2000	1	15	AGQA065547       	4	20000106	G	2300	069102100	RADIO           			HUGHES	369   	369D        	4470706	WP  										COCKPIT	INOPERATIVE     	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				RADIO INOPERABLE UPON INSTALLATION.						1	G	7	1 	3U				H3WE    					 
2000011500605	20000115	00605	WP  	2000	1	15	AGQA065548       	1	20000106	G	6710	369A717011	MOTOR           			HUGHES	369   	369D        	4470706	WP  										LATERAL TRIM	SLOW            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				HIGH SPEED MOTOR INSTALLED DELAY IN ACTION.						1	G	7	1 	3U				H3WE    					 
2000011500606	20000115	00606	WP  	2000	1	15	AGQA065549       	1	20000106	G	2436	369A4652	VOLT REGULATOR  			HUGHES	369   	369D        	4470706	WP  										BATTERY BOX	ERRATIC         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				FIELD VOLTAGE INTERMITTENT, OVERVOLTAGE CONDITION.						1	G	7	1 	3U				H3WE    					 
2000011500607	20000115	00607	WP  	2000	1	15	AGQA065550       	1	20000106	G	6220	369A10053	DAMPENER PIN    			HUGHES	369   	369E        	4470707	WP  										M/R HEAD	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				DAMPENER PIN RIDES UP.						1	G	7	1 	3U				H3WE    					 
2000011500608	20000115	00608	WP  	2000	1	15	AGQA065551       	1	20000106	G	6520	369D2172313	BEARING         			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				BEARING WORN.						1	G	7	1 	3U				H3WE    					 
2000011500609	20000115	00609	WP  	2000	1	15	AGQA065552       	1	20000106	G	6510	369D2172313	LINK ASSY       			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				T/R LINK ASSY  IS WORN EXCESSIVELY.						1	G	7	1 	3U				H3WE    					 
2000011500610	20000115	00610	WP  	2000	1	15	AGQA065555       	1	20000106	G	6710	369A717011	MOTOR           			HUGHES	369   	369D        	4470706	WP  										LATERAL TRIM	WEAK            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				MOTOR IS SLOW AND WEAK.						1	G	7	1 	3U				H3WE    					 
2000011500611	20000115	00611	SW  	2000	1	15	AGQA065556       	1	20000106	G	7920	70010G000X116A	HOSE            			BELL  	206   	206B3       	1181506	SW  										ENGINE OIL	LEAKING         	E			AGQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	9907K					2040				HOSE ASSEMBLY LEAKING.						1	G	7	1 	3U				H2SW    					 
2000011500612	20000115	00612	SW  	2000	1	15	AGQA065557       	1	20000106	G	7714	32005007	TACH GENERATOR  			BELL  	212   	212         	1181420	SW  										ENGINE	INTERMITTENT    	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				TACHOMETER/GENERATOR CAUSES N2 GAUGE TO BE INTERMITTENT.						1	G	7	1 	4U				H4SW    					 
2000011500613	20000115	00613	WP  	2000	1	15	AGQA065558       	1	20000106	G	6420	369A21800501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	NOISY           	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				SWASHPLATE IS NOISEY, SLIGHT CLICKING NOISE WHEN ROTATING TAIL ROTOR.						1	G	7	1 	3U				H3WE    					 
2000011500614	20000115	00614		2000	1	15	AGQA065559       	4	20000107	G	2320	KY196	RADIO           			BELL  	206   	206B3       	1181506	SW  										VHF SYSTEM	INOPERATIVE     	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY					2871				FREQUENCY  WILL NOT CHANGE IN RADIO.						1	G	7	1 	3U				H2SW    					 
2000011500615	20000115	00615		2000	1	15	AGQA065560       	4	20000107	G	3457	0110005400	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718					1917				GPS UNABLE TO FIND SATELLITES.						1	G	7	1 	3U				H2SW    					 
2000011500616	20000115	00616	GL  	2000	1	15	AGQA065561       	2	20000107	G	7532	23053176	BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	STICKING        	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D	CAE833998			BLEED VALVE STICKING CAUSING COMPRESSOR STALLS.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000011500617	20000115	00617	GL  	2000	1	15	AGQA065562       	2	20000107	G	7323	23057870	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	SLOW            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D	CAE833805			GOVERNOR SLOW TO RECOVER.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000011500618	20000115	00618	WP  	2000	1	15	AGQA065563       	1	20000107	G	7720	369A45217	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										TOT	ERRATIC         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				TOT GAUGE ERRATIC.						1	G	7	1 	3U				H3WE    					 
2000011500619	20000115	00619	SW  	2000	1	15	AGQA065564       	1	20000107	G	7714	2090755265	WARINING BOX    			BELL  	212   	212         	1181420	SW  										NR 2 ENGINE	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				WARNING BOX IS INOPERATIVE.  NR 2 ENGINE LIGHT STAYS ON.						1	G	7	1 	4U				H4SW    					 
2000011500620	20000115	00620	WP  	2000	1	15	AGQA065565       	1	20000107	G	2400	369H4551	BEARINGS        			HUGHES	369   	369D        	4470706	WP  										TACH GENERATOR	DAMAGED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				BEARINGS ARE BAD AND WIRES BROKEN.						1	G	7	1 	3U				H3WE    					 
2000011500621	20000115	00621	SW  	2000	1	15	AGQA065566       	1	20000107	G	7714	2090753265	WARINING BOX    			BELL  	212   	212         	1181420	SW  										NR 2 ENGINE	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				NR 2 ENGINE OUT LIGHT INTERMITTENTLY.						1	G	7	1 	4U				H4SW    					 
2000022300019	20000223	00019	EA  	2000	2	23	AGQA065567       	2	20000107	G	7321	32447066	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FAILED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				CONTROL UNIT WOULD NOT MATCH TORQUES TORQUE SPLIT						1	G	7	1 	4U	4	U		H4SW    	E22EA				 
2000011500622	20000115	00622	SW  	2000	1	15	AGQA065568       	1	20000107	G	3340	7028511	STROBE          			BELL  	212   	212         	1181420	SW  										FUSELAGE	INTERMITTENT    	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				STROBE ASSY IS INTERMITTENT.						1	G	7	1 	4U				H4SW    					 
2000021200036	20000212	00036	WP  	2000	2	12	AGQA065668       	1	20000124	G	6520	369D21800	PITCH CONTROL   			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	CHIPPED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				SPLINE TEETH ARE BROKEN AND CHIPPED.						1	G	7	1 	3U				H3WE    					 
2000021200037	20000212	00037	GL  	2000	2	12	AGQA065669       	2	20000124	G	7532	23053176	BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	500DC					290456D	CAE831608			BLEED VALVE STALLED IN-FLIGHT.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000021200038	20000212	00038	GL  	2000	2	12	AGQA065670       	2	20000124	G	7323	252466714	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FLUCTUATED      	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J					900801D	CAE833805			GOVERNOR IS FLUCTUATING IN POWER.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000021200039	20000212	00039	WP  	2000	2	12	AGQA065671       	1	20000124	G	2430	A700ZG	RCR             			HUGHES	369   	369E        	4470707	WP  										GEN CONTROL	FAILED          	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	8330P					0330E				PART IS UNABLE TO COME ON-LINE.						1	G	7	1 	3U				H3WE    					 
2000021200040	20000212	00040	WP  	2000	2	12	AGQA065672       	1	20000124	G	7714	369A45167	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										COCKPIT	STICKING        	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5027P					611002D				TACHOMETER  IS STICKING.						1	G	7	1 	3U				H3WE    					 
2000021200041	20000212	00041	WP  	2000	2	12	AGQA065673       	1	20000124	G	6520	369D25400	GEARBOX         			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				T/R GEARBOX  IS WORN EXCESSIVELY.						1	G	7	1 	3U				H3WE    					 
2000021200042	20000212	00042	GL  	2000	2	12	AGQA065674       	2	20000128	G	7412	106149501	EXCITER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					IGNITION SYS	FAILED          	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5211R	66   				1161D				EXCITER IS POWERLESS, WILL NOT EXCITE IGNITER.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000021200043	20000212	00043	GL  	2000	2	12	AGQA065675       	2	20000128	G	7412	106149501	EXCITER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					IGNITION SYSTEM	FAILED          	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5211R	35   				1161D				EXCITER IS INOPERABLE, WILL NOT EXCITE.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000021200044	20000212	00044	WP  	2000	2	12	AGQA065676       	1	20000128	G	3310	369H64255	DIMMER CONTROL  			HUGHES	369   	369D        	4470706	WP  										COCKPIT LIGHTS	INOPERATIVE     	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J					900801D				DIMMER CONTROL IS INOPERABLE, LIGHTS WILL NOT DIM.						1	G	7	1 	3U				H3WE    					 
2000021200045	20000212	00045		2000	2	12	AGQA065677       	4	20000128	G	2312	064101900	TRANSCEIVER     			BELL  	206   	206B3       	1181506	SW  										COCKPIT	DAMAGED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718					1917				RADIO IS BROKEN, DAMAGED ANTENNA JACK.						1	G	7	1 	3U				H2SW    					 
2000021200046	20000212	00046	SW  	2000	2	12	AGQA065678       	1	20000128	G	7714	206075681003	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										DUAL TACH	INOPERATIVE     	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	90322					1736				DUAL TACHOMETER INDICATOR  IS INOPERABLE, TURBINE SIDE LOW, INSTALLED AND GROUND RUN.						1	G	7	1 	3U				H2SW    					 
2000021200047	20000212	00047	SW  	2000	2	12	AGQA065679       	1	20000128	G	6520	2040406045	COUPLING        			BELL  	204   	UH1H        	1181407	SW  										GEARBOX	CHIPPED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				COUPLING HAS CHIPPED TOOTH.						1	G	7	1 	4U				EXPA1G71					 
2000021200048	20000212	00048	SW  	2000	2	12	AGQA065680       	1	20000128	G	6510	212311009101	BEARING         			BELL  	212   	212         	1181420	SW  										T/R DRIVE	SCRATCHED       	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				INNER RACE IS SCRATCHED.						1	G	7	1 	4U				H4SW    					 
2000021200049	20000212	00049	SW  	2000	2	12	AGQA065681       	1	20000128	G	6510	212311007101	BEARING         			BELL  	212   	212         	1181420	SW  										T/R DRIVE	DAMAGED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BEARING IS DAMAGED.						1	G	7	1 	4U				H4SW    					 
2000021200050	20000212	00050	SW  	2000	2	12	AGQA065682       	1	20000128	G	6510	212311008101	BEARING         			BELL  	212   	212         	1181420	SW  										T/R DRIVE	DAMAGED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BEARING IS DAMAGED.						1	G	7	1 	4U				H4SW    					 
2000021200051	20000212	00051	SW  	2000	2	12	AGQA065683       	1	20000128	G	6510	212311010101	BEARING         			BELL  	212   	212         	1181420	SW  										T/R DRIVE	SCORED          	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				INNER RACE IS SCORED.						1	G	7	1 	4U				H4SW    					 
2000021200052	20000212	00052	SW  	2000	2	12	AGQA065684       	1	20000128	G	6320	2060401461	GEAR            			BELL  	206   	206B3       	1181506	SW  										M/R GEARBOX	FLAKING         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				GEAR IS FLAKING.						1	G	7	1 	3U				H2SW    					 
2000021200053	20000212	00053	SW  	2000	2	12	AGQA065685       	1	20000128	G	6320	2060401223	SUN GEAR        			BELL  	206   	206B3       	1181506	SW  										M/R GEARBOX	FLAKING         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				SUN GEAR IS FLAKING.						1	G	7	1 	3U				H2SW    					 
2000021200054	20000212	00054	SW  	2000	2	12	AGQA065686       	1	20000128	G	6320	2060401461	GEAR            			BELL  	206   	206B3       	1181506	SW  										M/R GEARBOX	FLAKING         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				GEAR IS FLAKING.						1	G	7	1 	3U				H2SW    					 
2000021200055	20000212	00055	SW  	2000	2	12	AGQA065687       	1	20000128	G	6320	2060401461	GEAR            			BELL  	206   	206B3       	1181506	SW  										M/R GEARBOX	FLAKING         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				GEAR IS FLAKING.						1	G	7	1 	3U				H2SW    					 
2000021200056	20000212	00056	SW  	2000	2	12	AGQA065688       	1	20000128	G	6320	2060401461	GEAR            			BELL  	206   	206B3       	1181506	SW  										M/R GEARBOX	FLAKING         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				GEAR  IS FLAKING.						1	G	7	1 	3U				H2SW    					 
2000021200057	20000212	00057	SW  	2000	2	12	AGQA065689       	1	20000128	G	5320	2040300611	SUPPORT         			BELL  	204   	UH1H        	1181407	SW  										FUSELAGE	CRACKED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				SUPPORT IS CRACKED.						1	G	7	1 	4U				EXPA1G71					 
2000021200058	20000212	00058	SW  	2000	2	12	AGQA065691       	1	20000128	G	6300	2040406235	BEARING         			BELL  	204   	UH1H        	1181407	SW  										M/R GEARBOX	LEAKING         	E			AGQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	53AG					7221588				BEARING IS LEAKING.						1	G	7	1 	4U				EXPA1G71					 
2000021200591	20000212	00591	SW  	2000	2	12	AGQA065692       	1	20000204	G	7920	700096000T302A	HOSE            			BELL  	206   	206B3       	1181506	SW  										ENGINE OIL SYS	LEAKING         	E			AGQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	90322					1736				HOSE IS LEAKING.						1	G	7	1 	3U				H2SW    					 
2000021200592	20000212	00592	GL  	2000	2	12	AGQA065693       	2	20000204	G	7412	106149501	EXCITER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	INOPERATIVE     	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				EXCITER INOPERATIVE.						1	G	7	1 	3U	3	U		H3WE    	E4CE				 
2000021200593	20000212	00593	WP  	2000	2	12	AGQA065694       	1	20000204	G	3252	369D26301131	DAMPER          			HUGHES	369   	369D        	4470706	WP  										MLG	DISCHARGED      	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				MAIN LANDING DAMPER IS LOW.						1	G	7	1 	3U				H3WE    					 
2000021200594	20000212	00594	WP  	2000	2	12	AGQA065695       	1	20000204	G	3252	369D26301231	DAMPER          			HUGHES	369   	369D        	4470706	WP  										MLG	DISCHARGED      	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				MAIN LANDING GEAR DAMPER IS LOW.						1	G	7	1 	3U				H3WE    					 
2000021200595	20000212	00595	WP  	2000	2	12	AGQA065696       	1	20000207	G	6720	369D21800501	SWASHPLATE      			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR	WORN            	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				TAIL ROTOR PITCH CONTROL'S INNER BUSHING WORN BEYOND LIMITS.						1	G	7	1 	3U				H3WE    					 
2000021900074	20000219	00074	WP  	2000	2	19	AGQA065932       	1	20000208	G	7810	369A8230503	PIPE            			HUGHES	369   	369D        	4470706	WP  										EXHUAST	CRACKED         	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				EXHAUST PIPE IS CRACKED APPROXIMATELY 4 INCHES, AFT, INBOARD CENTER.						1	G	7	1 	3U				H3WE    					 
2000021900075	20000219	00075		2000	2	19	AGQA065933       	4	20000209	G	2312	KY195B	RADIO           			HUGHES	369   	369D        	4470706	WP  										VHF	INOPERATIVE     	E			AGQA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	500DC					290456D				VHF RADIO IS INOPERATIVE.						1	G	7	1 	3U				H3WE    					 
2000021900076	20000219	00076	SW  	2000	2	19	AGQA065935       	1	20000211	G	2436	CSV115212A	VOLT REGULATOR  			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	INOPERATIVE     	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				VOLTAGE REGULATOR INOPERABLE,  WILL NOT REGULATE.						1	G	7	1 	4U				EXPA1G71					 
2000021900610	20000219	00610	SW  	2000	2	19	AGQA065942       	1	20000211	G	2436	CSV115212A	VOLT REGULATOR  			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	INOPERATIVE     	E			AGQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				VOLTAGE REGULATOR INOPERABLE.   WILL NOT REGULATE.						1	G	7	1 	4U				EXPA1G71					 
2000073100024	20000731	00024	EA  	2000	7	31	AU000068         	2	20000130	G	8540		GEARBOX         	LYC         		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  						FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 							L44162			(AUS) ENGINE GEARBOX SUSPECT FAILURE.						1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2000073100025	20000731	00025	EA  	2000	7	31	AU000070         	2	20000127	G	8500		ENGINE          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LEFT	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L17061A			(AUS) LEFT ENGINE OIL FILTER NON-FERROUS METAL CONTAMINATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000073100026	20000731	00026	EA  	2000	7	31	AU000074         	2	20000205	G	8530		VALVE SEAT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NUMBER 5	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			897  				L496861A			(AUS) LEFT ENGINE NR 5 CYLINDER EXHAUST VALVE SEAT SEPARATED FROM CYLINDER HEAD.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000073100027	20000731	00027	SO  	2000	7	31	AU000081         	1	20000207	G	3230	4204200	ARM             	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR RETRACTION ARM BROKEN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000073100028	20000731	00028	CE  	2000	7	31	AU000084         	1	20000208	G	2800		FUEL TANK       			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	AIRCRAFT FUEL SY	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM INSPECTED IAW AD/GEN/79, AD/GEN/80 AND AD/GEN/81.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P3EA9	 
2000073100029	20000731	00029	CE  	2000	7	31	AU000086         	1	20000112	G	7500	25001	VALVE           	PARKER      	25001       	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE BLEED AIR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BLEED AIR SOLENOID VALVE OPEN CIRCUITED.  MOVING PARTS CORRODED. SUSPECT WATER INGRESS.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000073100030	20000731	00030	EU  	2000	7	31	AU000087         	1	20000128	G	5730	136	RIVET           	PARTEN      		PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING PLATES/SKIN	MISALIGNED      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					136					(AUS) LEFT AND RIGHT WING INBOARD ENGINE COWL RIVETS MISALIGNED.  THE RIVETS DID NOT IMPINGE ON THE SPAR.  FOUND DURING 	INSPECTION IAWAD/P68/46.					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2000073100031	20000731	00031	EA  	2000	7	31	AU000090         	2	20000120	G	8520	LWI3885MO6	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							RL11668A			(AUS) RIGHT ENGINE FRONT BEARING PICKED UP ON CRANKSHAFT.  ENGINE SEIZED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000073100032	20000731	00032	SO  	2000	7	31	AU000091         	1	20000201	G	2810	07560106	PLUNGER         			MAULE 	M4    	M4210       	5460108	SO  	CONT  	O360  	IO360A      	17025	SO  	MCAULY	2A34C	D2A34C67    	GL  	FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							1042444			(AUS) FIREWALL MOUNTED FUEL STRAINER PLUNGER RUBBER NOT COMPATIBLE WITH FUEL PREVENTING FUEL FROM BEING DRAINED FROM STR	AINER.  PLUNGER WAS PURCHASED AND FITTED IN SEPTEMBER 1999.					1	H	7	1 	3O	3	O	 	3A23    	E1CE	5	C	P3EA	 
2000073100033	20000731	00033	SO  	2000	7	31	AU000092         	1	20000205	G	3260	MS272402	SWITCH          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR POS	INTERMITTENT    	W				K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT IN OPERATION.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2000073100034	20000731	00034	EA  	2000	7	31	AU000093         	2	20000219	G	8530	LW12427	CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170CFA    	GL  	NR 4 SPARK PLUG	CRACKED         	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			1239 				L3256136A			(AUS) NR 4 CYLINDER CRACKED FROM LOWER SPARK PLUG HOLE TO EXHAUST PORT.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857	 
2000073100035	20000731	00035	EA  	2000	7	31	AU000094         	2	20000202	G	7324	254088	DIAPHRAGM       	BENDIX      	25241783    	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL DIVIDER	WORN            	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					AGA631					(AUS) LEFT ENGINE FUEL FLOW DIVIDER DIAPHRAGM FAILED DUE TO CHAFING ON THE VALVE PLATE.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000073100036	20000731	00036	SO  	2000	7	31	AU000095         	2	20000121	G	8540	534728	STUD            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	IDLER GEAR	SHEARED         	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			1170 				276417R	960416		(AUS) IDLER GEAR SUPPORT PIN SECURING STUD SHEARED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000073100037	20000731	00037	CE  	2000	7	31	AU000101         	1	20000214	G	2800		FUEL TANK       			CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH WATER. THE FUEL SYSTEM HAD BEEN FLUSHED WITH WATER IAW AD/GEN/80A1 FOLLOWED	 BY APPROVED PURGING OF THE WATER FROM THE SYSTEM.  COMPLETE ENGINE FAILURE OCCURRED IN-FLIGHT.  WHEN THE GASCOLATOR WAS	 DRAINED AFTER LANDING, APPROXIMATELY 100 ML OF WATER WAS RECOVERED FROM THE DRAIN.  				1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL	 
2000073100038	20000731	00038	CE  	2000	7	31	AU000105         	1	20000111	G	7500	25001	VALVE           			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					ENGINE BLEED AIR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							19391			(AUS) BLEED AIR SOLENOID VALVE OPEN CIRCUITED.  MOVING PARTS CORRODED.  SUSPECT MOISTURE INGRESS.						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA				 
2000073100039	20000731	00039	SO  	2000	7	31	AU000106         	1	20000211	G	2822	421135	PUMP            	WELDON      	421135      	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL BOOST PUMP	FAILED          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 			15   		10082					(AUS) RIGHT FUEL BOOST PUMP BLADE RETAINING RING BROKEN.  PUMP HAD ONLY JUST BEEN FITTED FOLLOWING OVERHAUL AND HAD ONLY	 OPERATED FOR APPROXIMATELY FIFTEEN MINUTES.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000073100040	20000731	00040	CE  	2000	7	31	AU000109         	1	20000211	G	5520	583410121	DOUBLER         		5734100142  	CESSNA	441   	441         	2076020	CE  										ELEVATOR STRUCTU	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					0138					(AUS) LEFT AND RIGHT ELEVATOR DOUBLER PLATES CORRODED.						1	L	7	2 	3T			RT	A28CE   					 
2000073100041	20000731	00041	EU  	2000	7	31	AU000111         	1	20000125	G	7120	68120251	MOUNT           	PARTEN      	P68B        	PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE MOUNT SEC	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					136					(AUS) LEFT AND RIGHT ENGINE MOUNTS CRACKED AND CORRODED.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2000073100042	20000731	00042	SO  	2000	7	31	AU000115         	1	20000405	G	3211	AN717A	BOLT            			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	MAIN LANDING GEA	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LEFT LANDING GEAR INBOARD ATTACHMENT BOLT FAILED.  LEFT LANDING GEAR COLLAPSED.						1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045	 
2000073100043	20000731	00043	NE  	2000	7	31	AU000117         	2	20000411	G	7313	3017957	NOZZLE          	PWA         		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUEL INJECTOR NO	IMPROPER PART   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					AIJ234					(AUS) NR 13 FUEL NOZZLE TIP INCORRECT PART.  PART FITTED IS PN 3017957.  CORRECT PN 3019424.   UNAPPROVED PART.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2000081000029	20000810	00029	CE  	2000	8	10	AU000120         	1	20000413	G	7430	A3600	CONTACTOR       	LYC         		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					IGNITION SWITCHI	BURNED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) IGNITION SWITCH CONTACTS BURNT/DAMAGED.  AIRCRAFT IS NOT SUBJECT TO AD/ELECT/59.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2000081000030	20000810	00030	CE  	2000	8	10	AU000121         	1	20000328	G	5522		SKIN            			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	ELEVATOR PLATES/	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			60   							(AUS) LT AND RT ELEVATORS PN 96-61005-655 (LT) AND PN 96-61005-656 (RT) HAD CRACKS IN THE TOP AND BOTTOM SKINS.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2000062800216	20000628	00216	SW  	2000	6	28	AU000124         	1	20000410	G	6230	412010407105	RING            	BELL        		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR MAST	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1706 		RE0160					(AUS) SWASHPLATE OUTER RING CRACKED.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2000062800217	20000628	00217	NM  	2000	6	28	AU000128         	1	20000308	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETA     	       	NM  										ENGINE/TRANSMISS	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS FAILED.  LIMITED INFORMATION PROVIDED.						1	G	7	1 	3O			 	H10WE   					 
2000021900524	20000219	00524		2000	2	19	AU000128046      	4	20000103	G	2562		SWITCH          	ARTEX       	4530150A    															ELT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						25271					(AU) INTERNAL G-SWITCH FAILED TO ENABLE INTERMITTENTLY RECERTIFICATION TESTING.																			 
2000021900529	20000219	00529	SO  	2000	2	19	AU000128053      	2	20000105	G	8500		ENGINE          	CONT        	O300A       	CESSNA	170   	170B        	2072306	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1A170	1A170*      	GL  	NOSE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				479  		15335D9AR		15335D9AR	M61393		(AU) ENGINE LOST ITS OIL AND SEIZED.  OPERATOR SPECIFIED FROZEN BREATHER AS THE CAUSE.						1	H	7	1 	3O	3	O		A799    	E253	5	N	P857	 
2000081000031	20000810	00031	SO  	2000	8	10	AU000129         	1	20000104	G	3230		DOWNLOCK        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	LACK OF LUBE    	W				K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK PIVOT BOLTS STIFF DUE TO LACK OF LUBRICATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000082800002	20000828	00002	WP  	2000	8	28	AU000130         	2	20000109	G	7200		ENGINE          			DHAV  	DHC2  	DHC2*       	2800108	EA  	GARRTT	TPE331	TPE3312201A 	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E	R	X	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	DE	DESCENT        	1			AU	S 			3577 				P90202	BVA6348		(AUS) ENGINE FAILED IN-FLIGHT.						1	H	7	1 	3R	4	T	 	A806    	E3WE	6	C	P15EA	 
2000062800218	20000628	00218	EU  	2000	6	28	AU000135         	1	20000404	G	7714	0177555170	CONTROL BOX     	TMECA       		SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					ENGINE RPM INDIC	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 					903B		4223			(AUS) ENGINE TACHOMETRIC BOX FAILED. SUSPECT CAUSED BY INTERNAL COMPONENT FAILURE.                                      	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000062800219	20000628	00219	NM  	2000	6	28	AU000136         	1	20000310	G	7160		INTAKE DUCT     	LYC         		ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE AIR INTAK	CONTAMINATED    	W				K	 	 	 	NONE                    				Y		 	ENGINE STOPPAGE           			NR	NOT REPORTED   	1			AU	S 							L1813339A			(AUS) AIR INTAKE HOUSING BLOCKED BY WATER FOLLOWING LANDING IN FLOOD WATER.  ENGINE FAILURE CAUSED A HARD LANDING WHICH 	RESULTED IN DAMAGE TO THE LANDING GEAR, ENGINE FRAMES AND BELLY SKIN.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000082800003	20000828	00003	CE  	2000	8	28	AU000137         	1	20000316	G	5310		STRUCTURE       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	FUSELAGE MAIN ST	FRACTURED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR NACELLE STRUCTURE FAILED IN THE AREA OF THE UPPER ACTUATOR ATTACHMENT POINT.  NLG COLLAPSED DURI	NG LANDING CAUSING DAMAGE TO THE SURROUNDING STRUCTURE AND BOTH PROPELLERS.  SUSPECT STRUCTURE HAD BEEN DAMAGED FOR SOME	 TIME BEFORE FINAL FAILURE.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000082800004	20000828	00004	EU  	2000	8	28	AU000142         	1	20000125	G	2497		WIRE            			PILATS	PC12  	PC12        	7090550	EU  										DC POWER DISTRIB	LOOSE           	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) GENERATOR GROUND CABLE BOLT LOOSE WITH ARCING AND PITTING OF THE FRAME AND DOUBLER.						1	L	7	1 	3T			RT	A78EU   					 
2000082800005	20000828	00005	SO  	2000	8	28	AU000143         	2	20000313	G	7310		LINE            	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE FUEL DIST	MISINSTALLED    	W				K	 	 	 	NONE                    				E		 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) LEFT ENGINE UPPER DECK PRESSURE LINES NOT FITTED TO NR 4 AND NR 6 CYLINDERS.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001011105803	20010111	05803	SO  	2001	1	11	AU000147         	1	20000417	G	5531	4429400	RIB             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	VERTICAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER RIB CRACKED.  FORWARD SPAR RIVETS LOOSE.  DRAG ANGLE PN 71059-06 CRACKED.  CRACK LENGTH 20 MM 	(0.787 INCH).					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000082800006	20000828	00006	SO  	2000	8	28	AU000148         	2	20000311	G	8530	ROCKERBOSS	CYLINDER        	CONT        		CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	BROKEN          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			438  							(AUS) NR 2 CYLINDER EXHAUST VALVE ROCKER BOSS BROKEN.						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2000082800007	20000828	00007	GL  	2000	8	28	AU000152         	3	20000405	G	6110		PROPELLER       	HARTZL      		PILATS	PC12  	PC12        	7090550	EU  						HARTZL	HCE4A	HCE4A3D     	GL  	PROPELLER ASSY	DAMAGED         	W				K	 	 	 	NONE                    				C	 	 	F.O.D.                    			NR	NOT REPORTED   	1			AU	S 								HJ326		(AUS) PROPELLER STRIKE (KANGAROO).  PROPELLER AND ENGINE INSPECTED IAW MAINTENANCE MANUALS WITH NO DEFECTS FOUND.						1	L	7	1 	3T			RT	A78EU   		5	C	P210NE	 
2000082800008	20000828	00008	CE  	2000	8	28	AU000153         	1	20000327	G	5753	3516505084	RIB             			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	TE FLAP STRUCTUR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT FLAP RIBS CRACKED.  RIBS ARE LOCATED IMMEDIATELY BENEATH THE FLAP ACTUATING BRACKET.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2000082800009	20000828	00009	CE  	2000	8	28	AU000154         	1	20000321	G	5753	3516505084	RIB             			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	TE FLAP STRUCT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT FLAP RIBS CRACKED.  RIBS ARE LOCATED IMMEDIATELY BENEATH THE FLAP ACTUATING BRACKET.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2000082800010	20000828	00010	CE  	2000	8	28	AU000156         	1	20000217	G	2822	476411	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					FUEL BOOST PUMP	BURNED OUT      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							277331			(AUS) RIGHT MAIN FUEL TANK TRANSFER PUMP CONNECTOR BURNT AND BLACKENED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2000082800011	20000828	00011	CE  	2000	8	28	AU000157         	1	20000228	G	5312		BULKHEAD        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD LOCATED AT BS 346.75 CRACKED IN TWO PLACES.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000083000070	20000830	00070	CE  	2000	8	30	AU000158         	1	20000222	G	5311	207	FRAME           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 207 CRACKED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000083000071	20000830	00071	CE  	2000	8	30	AU000159         	1	20000222	G	5311	207	FRAME           			BEECH 	200   	B200T       	1152929	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 207 CRACKED.                                                                                       	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000082800012	20000828	00012	CE  	2000	8	28	AU000160         	1	20000222	G	5311	207	FRAME           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 207 CRACKED.                                                                                       	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000082100071	20000821	00071	EA  	2000	8	21	AU000164         	2	20000130	G	8540	L44162	GEARBOX         			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 							L44162			(AUS) ENGINE SUSPECT GEARBOX FAILURE.						1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2000062800220	20000628	00220	SW  	2000	6	28	AU000165         	1	20000328	G	5313	47322241173	LONGERON        	BELL        	47G         	BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  					FUSELAGE MAIN LO	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LOWER LONGERON CRACKED. FOUND DURING X-RAY INSPECTION IAW AD/BELL47/62 AMDT2.						1	G	7	1 	3O	3	O	 	2H3     	E279				 
2000082100129	20000821	00129	CE  	2000	8	21	AU000167         	1	20000228	G	5312	10144009811	BULKHEAD        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD TOP WEB CRACKED IN SEVERAL PLACES.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000082800013	20000828	00013	CE  	2000	8	28	AU000168         	1	20000210	G	3230	3581507714	UPLOCK          		ELECTRIC    	BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	LANDING GEAR RET	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR UPLOCK ACTUATING BOLT HOLE CORRODED AND WORN.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2000082300002	20000823	00002	WP  	2000	8	23	AU000170         	2	20000221	G	7322	89711014	FCU             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FUEL CONTROL/CAR	FAULTY          	W				E		 	 	ENGINE SHUTDOWN         				E	B	 	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 			271  				P31330			(AUS) RT ENGINE FUEL CONTROL UNIT FAULTY.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2000081700020	20000817	00020	CE  	2000	8	17	AU000174         	1	20000229	G	2460	507250101	CIRCUIT BREAKER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	DC POWER DISTRIB	CORRODED        	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 							8071381011	BU4983BU9782		(AUS) CIRCUIT BREAKER PANEL CORRODED DUE TO WATER INGRESS THROUGH THE COPILOT''S DV WINDOW.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000081700021	20000817	00021	CE  	2000	8	17	AU000176         	1	20000207	G	2430	DGR3	CONTROL PANEL   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	DC GENERATING SY	BURNED          	W				K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 							574090	FP1051376		(AUS) ALTERNATOR CONTROL UNIT INTERNAL FAULT.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P36EA	 
2000100300131	20001003	00131	SW  	2000	10	3	AU000179         	1	20000210	G	3211	AN423A	BOLT            			GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	MAIN LANDING GEA	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR STRUT TRUNNION PIN RETAINING BOLT CRACKED.  TRUNNION PIN ALSO WORN.						1	L	7	1 	3O	3	O	 	A12SO   	1E4	5	C	P920	 
2000081700022	20000817	00022	CE  	2000	8	17	AU000180         	1	20000223	G	3230	96820034	SHAFT           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	LANDING GEAR RET	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATING SHAFT SUSPECT ILLEGAL REPAIRS.  NLG DOOR APPEARS TO HAVE CLOSED DURING RETRACTION CAUS	ING THE NLG TO FOUL.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2000081700025	20000817	00025	NE  	2000	8	17	AU000182         	2	20000220	G	8530	27056	PISTON          			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					RING LANDS	CRACKED         	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			521  				4219276			(AUS) PISTON CRACKED FROM GUDGEON PIN HOLE, THROUGH THE RING LANDS TO THE CENTRE OF THE PISTON CROWN.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000081700026	20000817	00026	CE  	2000	8	17	AU000183         	1	20000217	G	2822	476411	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					FUEL BOOST PUMP	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							277548R			(AUS) LEFT  MAIN FUEL TANK TRANSFER PUMP FAILED.  INSPECTION FOUND BURNT CONNECTOR.						1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2000081700028	20000817	00028	EA  	2000	8	17	AU000188         	2	20000216	G	8520	LW16508	CAMSHAFT        	LYC         		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE	SPALLED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					L267775					(AUS) CAMSHAFT PN LW16508 LOBE SPALLED. CORRESPONDING TAPPET PN LW16812 ALSO SPALLED.  METAL CONTAMINATION OF OIL SYSTEM	.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2000070600234	20000706	00234	GL  	2000	7	6	AU000195         	2	20000305	G	7260		BEARING         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					TURBINE ENGINE	WORN            	W				K	 	 	 	NONE                    				O		 	OTHER                     			NR	NOT REPORTED   	1			AU	S 							89007			(AUS) ENGINE ACCESSORY GEARBOX 2.5 BEARING WORN.  METAL CONTAMINATION OF OIL SYSTEM.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2000081700033	20000817	00033	SO  	2000	8	17	AU000202         	1	20000314	G	2497		WIRE            			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	ELECTRICAL POWER	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) ELECTRICAL BURNING SMELL IN COCKPIT.  NO EVIDENCE OF FIRE DAMAGE.  TEST FLIGHT OK.  AIRCRAFT RETURNED TO SERVICE.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2000081700034	20000817	00034	GL  	2000	8	17	AU000203         	3	20000420	G	6111	A163634	RETAINER        	MCAULY      		REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	PROPELLER BLADE	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 							PCE12098	881779		(AUS) LEFT PROPELLER FEEDBACK RING RETAINING CIRCLIP DEFORMED.  PROPELLER WENT TO UNCOMMANDED FULL REVERSE ON LANDING.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2000082200026	20000822	00026	CE  	2000	8	22	AU000208         	1	20000301	G	3260	JE3	ACTUATOR        		ISE13       	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR POS	BROKEN          	W				K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOWN MICROSWITCH ACTUATOR LEAF BROKEN.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000082200027	20000822	00027	SO  	2000	8	22	AU000209         	1	20000217	G	5310	31420	STRUCTURE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUSELAGE MAIN ST	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD WING ATTACHMENT FITTING TO FUSELAGE UNDER TENSION.  THE FUSELAGE IN THIS AREA BULGING AND CRACKING. 	 INTERNAL STRESS DAMAGE AND CRACKING.  CAUSE OF DAMAGE UNKNOWN.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000082200028	20000822	00028	CE  	2000	8	22	AU000210         	1	20000317	G	5414		PANEL           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PLATE/SKIN	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT NACELLE FUEL DRAIN PANEL NOT REINSTALLED FOLLOWING MAINTENANCE.  SAFETY PLUG AND LOCKWIRE ALSO MISSING.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000082200029	20000822	00029	SO  	2000	8	22	AU000211         	1	20000222	G	2731	62701111	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	ELEVATOR TAB CON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD TRIM CABLE FRAYED.						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2000072600079	20000726	00079	SO  	2000	7	26	AU000214         	2	20000307	G	8530		EXHAUST VALVE   	CONT        	O200A       	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1340 				252651A48			(AUS) NR 4 CYLINDER EXHAUST VALVE SEIZED.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000072600087	20000726	00087	SW  	2000	7	26	AU000216         	1	20000322	G	2810	5630061502	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD INBOARD FUEL CELLS DETERIORATED AND LEAKING.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000072600088	20000726	00088	SW  	2000	7	26	AU000217         	1	20000322	G	2810	5630080502	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD AND AFT AND LT FORWARD INBOARD FUEL CELLS DETERIORATED AND LEAKING.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000072600249	20000726	00249	SW  	2000	7	26	AU000218         	1	20000322	G	2810	5630060501	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD INBOARD FUEL CELLS DETERIORATED AND LEAKING.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000072600095	20000726	00095	SO  	2000	7	26	AU000221         	1	20000316	G	2434	762489	STATOR          	CHRYSLER    	4111810     	PIPER 	PA28  	PA28151     	7102805	SO  										DC GENERATOR-ALT	LOOSE           	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 					02317					(AUS) ALTERNATOR STATOR WINDINGS LOOSE CAUSING CHAFING AND SHORT CIRCUIT.						1	L	7	1 	3O			 	2A13    					 
2000072600096	20000726	00096	EA  	2000	7	26	AU000226         	2	20000327	G	8530	74541	EXHAUST VALVE   			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	M76EMM      	EA  	ENGINE	BROKEN          	W				K	 	 	 	NONE                    				E	R	E	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          	CR	CRUISE         	1			AU	S 							L840136A			(AUS) NR 2 CYLINDER EXHAUST VALVE FAILED.  NR 2 CYLINDER AND SPARK PLUGS DAMAGED.  A FRAGMENT OF THE FAILED EXHAUST VALV	E WAS INGESTED BY NR 3 CYLINDER CAUSING INTERNAL DAMAGE.					1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA4	 
2000072600097	20000726	00097	NM  	2000	7	26	AU000227         	1	20000101	G	2820	200072001	PIPE            			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	IO540AA1A   	41532	NE  					ACFT FUEL DISTRI	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING FUEL PIPE CORRODED.						1	M	7	2 	3O	3	O	RT	A17WE   	1EA				 
2000072600252	20000726	00252	CE  	2000	7	26	AU000228         	1	20000405	G	3230	1454	BUSHING         	CESSNA      	991015403   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					LANDING GEAR RET	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) EMERGENCY LANDING GEAR BLOW DOWN BOTTLE HANDLE WOULD NOT OPERATE.  INVESTIGATION FOUND THE TEFLON BUSHING LOCATED 	BETWEEN THE FIRING PLUNGER AND THE OUTLET LINE BLOCK WAS SWOLLEN AND JAMMED PREVENTING THE BOTTLE FROM FIRING.  OIL CONT	AMINATION WAS FOUND IN THE BOTTLE HEAD.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2000072600254	20000726	00254	CE  	2000	7	26	AU000229         	1	20000426	G	3233	115380025	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR ACT	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR MOTOR FAILED TO OPERATE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000072600100	20000726	00100	CE  	2000	7	26	AU000236         	1	20000311	G	2750		FLAP            			BEECH 	200   	200CBEECH   	1152926	CE  	PWA   	PT6   	PT6A42      	52043	NE  					TE FLAP CONTROL	FAULTY          	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAPS WOULD NOT EXTEND.  INVESTIGATION COULD FIND NO FAULT AND THE FLAPS HAVE OPERATED CORRECTLY SINCE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000072600255	20000726	00255	SO  	2000	7	26	AU000237         	1	20000402	G	2840	2405105	PIPE            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	ACFT FUEL INDICA	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CL	CLIMB          	1			AU	S 										(AUS) RIGHT FUEL FLOW LINE LOCATED AT BACK OF INSTRUMENT INADEQUATELY FLARED.  FUEL LEAKING.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2000072600256	20000726	00256	SO  	2000	7	26	AU000240         	1	20000308	G	2842	550695	TRANSMITTER     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL QUANTITY SE	CORRODED        	W				K	 	 	 	NONE                    				O		 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RIGHT FUEL TANK SENDERS OPEN CIRCUITED AND CORRODED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000072600101	20000726	00101	SO  	2000	7	26	AU000241         	1	20000308	G	2842	550696	TRANSMITTER     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL QUANTITY SE	CORRODED        	W				K	 	 	 	NONE                    				O		 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RIGHT FUEL TANK SENDERS OPEN CIRCUITED AND CORRODED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000072600102	20000726	00102	SO  	2000	7	26	AU000242         	2	20000423	G	7421	RHB32E	SPARK PLUG      	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	SPARK PLUG/IGNIT	FAULTY          	W				K	 	 	 	NONE                    				E		 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							286164R			(AUS) NR 3 CYLINDER SPARK PLUGS (2 OFF) BRIDGED ACROSS ELECTRODES.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2000082800014	20000828	00014	SO  	2000	8	28	AU000243         	1	20000415	G	5101	347350298	STRUCTURE       			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	AIRCRAFT SUB-STA	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 								AU2714AU2576		(AUS) AIRCRAFT RECEIVED FOR COFA IN A DETERIORATED CONDITION.  COMPASS UNSERVICEABLE LT AND RT ENGINE MIXTURE, THROTTLE 	AND ALTERNATE AIR CONTROL ROD ENDS UNSERVICEABLE.  LT AND RT ENGINE MANIFOLD FUEL DRAINS OPEN TO ATMOSPHERE, RT MLG DOOR	 CRACKED.  RT ENGINE AIR FILTER HOUSING COVER UNSERVICEABLE.  LT ENGINE AIR FILTER HOUSING AND COVER UNSERVICEABLE.   LT	 AND RT INDUCTION HOSES COLLAPSED.  SCAT HOSES USED IN LIEU OF GENUINE PIPER AIR DUCT.  ALL BRAKE LININGS AND DISCS UNSE	RVICEABLE.  AILERON AND FLAP ROD ENDS WORN BEYOND LIMITS.  RT AILERON BALANCE WEIGHT TO AILERON CORRODED.  PILOTS CONTRO	L WHEEL UNIVERSAL COUPLING UNSERVICEABLE.  RT MLG BRAKE HOSE WORN THROUGH.	1	L	7	2 	3O			 	A7SO    		5	C	P920	 
2000072600257	20000726	00257	SO  	2000	7	26	AU000245         	2	20000412	G	7414	1050765	CLAMP           	BENDIX      	S6LN25T     	CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	MAGNETO/DISTRIBU	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			338  		898959		57083			(AUS) FRONT ENGINE RIGHT MAGNETO COIL ATTACHMENT CLAMPS BROKEN.  FOUND DURING INSPECTION IAW AD/ELECT/68.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2000073100015	20000731	00015	GL  	2000	7	31	AU000248         	1	20000307	G	8010		RELAY           	LYC         		PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE CRANKING	STUCK           	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) ENGINE STARTER SOLENOID RELAY JAMMED IN THE ON POSITION.  STARTER MOTOR WOULD NOT DISENGAGE.   (X)						1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2000072600120	20000726	00120	EA  	2000	7	26	AU000250         	2	20000406	G	7310	25243271	VALVE           	BENDIX      	RSA5        	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	ENGINE FUEL DIST	CONTAMINATED    	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							L441755A			(AUS) RIGHT ENGINE FUEL DISTRIBUTOR VALVE VENT HOLE BLOCKED BY A GREASE TYPE SUBSTANCE APPLIED TO THE DIAPHRAGM SPRING. 	  					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2000072600103	20000726	00103	SO  	2000	7	26	AU000252         	1	20000209	G	2434	762489	STATOR          	CHRYSLER    	4111810     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	DC GENERATOR-ALT	LOOSE           	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			271  		9021856					(AUS) ALTERNATOR STATOR LOOSE.  STATOR WINDINGS SHORT CIRCUITED.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000071200112	20000712	00112	SW  	2000	7	12	AU000253         	1	20000404	G	3230	ES10106	DRAG BRACE      			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	LANDING GEAR RET	FRACTURED       	W				O	 	 	 	OTHER                   				C	 	 	F.O.D.                    			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE FAILED AFTER THE AIRCRAFT STRUCK A KANGAROO ON TAKEOFF.  THE NLG COLLAPSED DURING LAN	DING.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2000072600104	20000726	00104	SW  	2000	7	26	AU000254         	1	20000404	G	3230	ES10107	DRAG BRACE      			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	LANDING GEAR RET	FRACTURED       	W				A	 	 	 	UNSCHED LANDING         				C	 	 	F.O.D.                    			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE FAILED WHEN THE AIRCRAFT STRUCK A KANGAROO ON TAKEOFF.  NLG COLLAPSED DURING LANDING.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2000071800156	20000718	00156	WP  	2000	7	18	AU000258         	1	20000412	G	6310	4474	CLUTCH          			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/TRANSMISS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			570  							(AUS) CLUTCH ASSEMBLY FREE WHEEL UNIT REAR FACE PLATE CRACKED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000072600121	20000726	00121	SO  	2000	7	26	AU000259         	2	20000407	G	8530		PISTON          	CONT        		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 										(AUS) NR 2 CYLINDER PISTON HOLED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000072700045	20000727	00045	EA  	2000	7	27	AU000262         	2	20000303	G	8520		CRANKCASE       	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 							L2161415			(AUS) CRANKCASE CRACKED IN THE AREA BETWEEN NR 2 AND NR 4 CYLINDERS.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2000073100016	20000731	00016	SO  	2000	7	31	AU000263         	1	20000217	G	5310	31420	STRUCTURE       	PIPER       		PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUSELAGE MAIN ST	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED IN AREA OF LEFT WING FORWARD ATTACHMENT FITTING. INTERNAL STRUCTURE ALSO DAMAGED IN THE SAME	 AREA.  CENTER SECTION LOWER FUSELAGE FRAMES BUCKLED AND LOWER SKIN DAMAGED.					1	L	7	1 	3O	3	O	RT	A20SO   	E14EA	5	C	P33EA	 
2000071800161	20000718	00161	NM  	2000	7	18	AU000266         	1	20000329	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETA     	       	NM  										ENGINE/TRANSMISS	FAULTY          	W				K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 										(AUS) DRIVE BELT SET FAULTY.						1	G	7	1 	3O			 	H10WE   					 
2000073100017	20000731	00017	SO  	2000	7	31	AU000267         	1	20000216	G	5730	62061002	SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	WING PLATES/SKIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SKIN CRACKED.						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2000081000003	20000810	00003	SO  	2000	8	10	AU000272         	2	20000319	G	7300		FUEL TANK       	CONT        	O200A       	CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE FUEL & CO	CONTAMINATED    	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE FUEL SYSTEM CONTAMINATED WITH EDA (ETHYLINE DIAMINE).  EVIDENCE OF EDA IN CARBURETOR AND FUEL FILTERS.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000081000004	20000810	00004	SO  	2000	8	10	AU000279         	2	20000209	G	7310	AN78022	FITTING         	CONT        	63135111    	PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE FUEL DIST	DAMAGED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					128803CR					(AUS) DISTRIBUTOR VALVE TO FUEL INJECTOR LINE FITTING LOOSE.  INVESTIGATION FOUND DAMAGED THREADS WHICH ALLOWED THE NUT 	TO LOOSEN.  FUEL LEAKING FROM FITTING.					1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2000082800015	20000828	00015	CE  	2000	8	28	AU000281         	1	20000114	G	5101		PAINT           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	EXTERIOR COLOUR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING REPAINTING, THE PRIMER WOULD NOT ADHERE TO THE AIRCRAFT.  SUSPECT ONE PART OF THE TWO PART PAINT WAS INCORR	ECT.  UNAPPROVED PART.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000081000005	20000810	00005	SW  	2000	8	10	AU000282         	1	20000322	G	2810	5630061502	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD FUEL CELLS HOLED DUE TO CELL DETERIORATION.   FUEL LEAKING FROM CELLS.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000081000006	20000810	00006	SW  	2000	8	10	AU000283         	1	20000322	G	2810	5630080502	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD FUEL CELLS HOLED DUE TO CELL D TERIORATION.   FUEL LEAKING FROM CELLS.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000081000007	20000810	00007	SW  	2000	8	10	AU000284         	1	20000322	G	2810	5360060501	FUEL CELL       			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD AND AFT AND LEFT FORWARD FUEL CELLS HOLED DUE TO CELL DETERIORATION.  FUEL LEAKING FROM CELLS.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000081000008	20000810	00008	EU  	2000	8	10	AU000285         	1	20000203	G	2800		FUEL TANK       			NOORDN	AT16  	AT16HARVARD 	       	EU  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3R	3	R	 	AR11    	5E2	5	C	P257	 
2000081000009	20000810	00009	CE  	2000	8	10	AU000286         	1	20000211	G	2800		FUEL TANK       			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED ETHYLENE DIAMINE (EDA).                                                         	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2000081000010	20000810	00010	SO  	2000	8	10	AU000287         	1	20000201	G	2800		FUEL TANK       			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2000081000011	20000810	00011	SO  	2000	8	10	AU000288         	1	20000207	G	2800		FUEL TANK       			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000081000012	20000810	00012	CE  	2000	8	10	AU000289         	1	20000201	G	2800		FUEL TANK       			BEECH 	33    	35B33       	1151406	CE  	CONT  	O470  	IO470K      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3O	3	O	 	3A15    	3E1	5	C	P880	 
2000081000013	20000810	00013	GL  	2000	8	10	AU000290         	1	20000215	G	2800		FUEL TANK       			NAMER 	T6    	AT6D        	6400416	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3R	3	R	 	A2575   	5E2	5	C	P257	 
2000081000014	20000810	00014	SO  	2000	8	10	AU000291         	1	20000301	G	2800		FUEL TANK       			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3O	3	O	 	2A13    	E295	5	N	P874	 
2000081000015	20000810	00015	GL  	2000	8	10	AU000293         	1	20000203	G	2800		FUEL TANK       			DHAV  	DHC1  	DCH1CHIPMUNK	2801704	GL  										AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3O			 	EXPA1L71					 
2000081000016	20000810	00016	CE  	2000	8	10	AU000294         	1	20000126	G	2800		FUEL TANK       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1522915	K6883		(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2000071200174	20000712	00174	CE  	2000	7	12	AU000295         	1	20000204	G	2810		FUEL TANK       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL SYSYTEM	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L821276T	Q6004		(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000081000017	20000810	00017	GL  	2000	8	10	AU000296         	1	20000203	G	2800		FUEL TANK       			NAMER 	T6    	SNJ4        	6400414	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							15558	80827		(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3R	3	R	 	A2575   	5E2	5	C	P257	 
2000070300763	20000703	00763	CE  	2000	7	3	AU000297         	1	20000201	G	2800		FUEL TANK       			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	FUEL SYSTEM	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							577217	739868		(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2000070300764	20000703	00764	CE  	2000	7	3	AU000298         	1	20000127	G	2800		FUEL TANK       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1543715	K5410		(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA)						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P9045	 
2000071100289	20000711	00289	WP  	2000	7	11	AU000299         	1	20000209	G	2800		FUEL TANK       			NANCNG	CJ6A  	CJ6A        	056183N	WP  										AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).						1	L	7	1 	3R			RT	EXPA1L71					 
2000070300765	20000703	00765	SO  	2000	7	3	AU000300         	1	20000412	G	3230	451359	BUNGEE CYLINDER 			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	LANDING GEAR RET	FAULTY          	W				K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR BUNGEE FAULTY.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2000070300766	20000703	00766	CE  	2000	7	3	AU000301         	1	20000304	G	5312		DOUBLER         			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	FWD PRESS BULKHE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD DOUBLER CRACKED.  SEALANT DETERIORATED.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2000081000018	20000810	00018	EA  	2000	8	10	AU000305         	1	20000215	G	2720	C6CFM12106	PEDAL           			DHAV  	DHC6  	DHC6100     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER CONTROL S	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT RUDDER PEDAL BRAKE CONTROL OPERATING LEVER FAILED.  PEDAL WAS FOUND TO BE A PRE-MOD TYPE.						1	H	7	2 	3T	3	T	 	A9EA    	E4EA	6	C	P15EA	 
2000081000019	20000810	00019	SO  	2000	8	10	AU000308         	1	20000313	G	5320		STRUCTURE       			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE	MISREPAIRED     	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STRUCTURE AT THE BASE OF THE COPILOT''S CONTROL COLUMN CUT AND GROUND AWAY IN THE AREA OF THE ELEVATOR PUSH-PULL R	OD ATTACHMENT. UNAPPROVED MODIFICATION.  .					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2000071200194	20000712	00194	SO  	2000	7	12	AU000312         	1	20000313	G	2710		CONTROL CABLE   			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AILERON CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING FORWARD INBOARD AILERON CABLE AND LEFT WING AFT INBOARD AILERON CABLE SEVERELY ERODED IN THE AREA WHERE	 THEY EXIT THE FUSELAGE.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2000081000020	20000810	00020	SO  	2000	8	10	AU000313         	1	20000313	G	5742		FITTING         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING, NAC/PYLON	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT INBOARD NACELLE TO FORWARD SPAR ATTACHMENT CASTING UPPER LUG CORRODED IN THE AREA AROUND HI-LOC FASTENER.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2000081000021	20000810	00021	SO  	2000	8	10	AU000314         	1	20000313	G	5552	1103216321	FITTING         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR/TAB ATT	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM FITTING AND HINGE HAD EXCESSIVE PLAY.  FURTHER INVESTIGATION FOUND THE TRIM FITTING CRACKED.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2000081000022	20000810	00022	SO  	2000	8	10	AU000315         	1	20000313	G	5347		SEAT TRACK      			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SEAT/CARGO ATTAC	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL CABIN SEAT TRACKS SEVERELY CORRODED.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105985	20010111	05985	SO  	2001	1	11	AU000316         	1	20000313	G	2520		SEAT            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN SEAT LEGS DEFORMED AND CRACKED IN THE AREA OF ATTACHMENT TO THE MAIN SEAT TUBE.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105986	20010111	05986	SO  	2001	1	11	AU000317         	1	20000313	G	2730		CONTROL CABLE   			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT ELEVATOR CABLES (4 OFF) AND AFT RUDDER CABLES CORRODED IN THE AREA LOCATED BETWEEN FRAME 19 AND FRAME 21.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105987	20010111	05987	SO  	2001	1	11	AU000318         	1	20000413	G	5554	4A3440	HINGE           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTER RUDDER HINGE BRACKET CORRODED BEYOND REPAIR.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105988	20010111	05988	SO  	2001	1	11	AU000319         	1	20000413	G	5552		HINGE           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ELEVATOR CENTER HINGE CORRODED.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105989	20010111	05989	SO  	2001	1	11	AU000320         	1	20000313	G	2730	4A321402	BELLCRANK       		4A322402    	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR CONTROL	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT ELEVATOR BELLCRANKS PN 4A-3224-02 (LT) AND PN 4A-3214-02 (RT) AND BELLCRANK STOPS PN 110-3010-26 AN	D PN 110-3010-27 CORRODED.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105990	20010111	05990	SO  	2001	1	11	AU000321         	1	20000313	G	5744	JRA7502	HINGE           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CONTROL SURFACE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT AILERON INBOARD HINGE CORRODED.                                                                                	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011105991	20010111	05991	GL  	2001	1	11	AU000322         	1	20000117	G	2720		MOUNT           			PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	RUDDER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LEFT PILOT SIDE BRAKE CALIPER MOUNT CRACKED.						1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001011106012	20010111	06012	GL  	2001	1	11	AU000323         	1	20000124	G	8010		RELAY           			PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	STARTER	STUCK           	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) STARTER RELAY JAMMED ON.                                                                                          	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2000081700001	20000817	00001	CE  	2000	8	17	AU000325         	1	20000426	G	2821		FILTER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ACFT FUEL FILTER	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRFRAME FUEL FILTER CONTAMINATED WITH AN UNKNOWN CLEAR GEL TYPE SUBSTANCE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000081700002	20000817	00002	SO  	2000	8	17	AU000326         	1	20000401	G	7160	8734902	RETAINER        	LYC         		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE AIR INTAK	MISSING         	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							RL1859739A	A54041		(AUS) FOAM AIR FILTER ELEMENT INGESTED INTO THE CARBURETTOR.INVESTIGATION FOUND ONLY ONE FILTER RETAINER WAS FITTED INST	EAD OF TWO. FURTHER CHECKING FOUND THAT THE IPC MAY BE MISLEADING INTHE NUMBER OF RETAINERS TO BE FITTED.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000081700003	20000817	00003	CE  	2000	8	17	AU000328         	1	20000504	G	2821	5092004010	FILTER          		359242307   	BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	2A36C	2A36C23     	GL  	ACFT FUEL FILTER	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRFRAME FUEL FILTER CONTAMINATED BY AN UNKNOWN WHITE SUBSTANCE.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P880	 
2000081700004	20000817	00004	CE  	2000	8	17	AU000329         	1	20000331	G	3230	S20495FG	ROD END         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR PUSH-PULL ROD END SPLIT.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000081700005	20000817	00005	SO  	2000	8	17	AU000330         	2	20000131	G	8520	643037	CRANKCASE       			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	MCAULY	3AF34C	3AF34C502   	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1800 				307706	786028L70726		(AUS) CRANKCASE CRACKED IN NUMEROUS PLACES. CRANKCASE HAD BEENPREVIOUSLY WELD REPAIRED.                                 	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2000062800221	20000628	00221	WP  	2000	6	28	AU000331         	1	20000412	G	6210	269D21100513M	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR BLADE	CRACKED         	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) MAIN ROTOR BLADE CRACKED.  BUSHING LOOSE.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000081700006	20000817	00006	SO  	2000	8	17	AU000334         	2	20000427	G	8540	537721	BEARING         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	DISINTEGRATED   	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 			870  				604802			(AUS) STARTER ADAPTER FRONT SUPPORT BEARING DISINTEGRATED.  METAL CONTAMINATION OF ENGINE OIL SYSTEM.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2000062800222	20000628	00222	CE  	2000	6	28	AU000335         	1	20000408	G	3243	8000016	SEAL            	CESSNA      	50440004    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MASTER CYL/BRAKE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) BRAKE MASTER CYLINDER LOC O SEAL'' FAILED.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2000081800007	20000818	00007	SO  	2000	8	18	AU000340         	1	20000420	G	5711	20207T902	SPAR            	AYRES       		AYRES 	S2    	S2RG10      	       	SO  	GARRTT	TPE331	TPE33110    	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	WING SPAR STRUCT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					RE201		P37100C	4HFR34C653G		(AUS) RIGHT LOWER SPAR CAP CRACKED.  FOUND DURING EDDY CURRENT INSPECTION IAW AD/ACSNOW/24 (1).  DEFECT CONFIRMED BY MPI	.					1	L	7	1 	3T	4	T	NC	A4SW    	E4WE	6	C	3PNE	 
2000081700007	20000817	00007	SO  	2000	8	17	AU000341         	1	20000505	G	2823	492239	SELECTOR VALVE  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL SELECTOR/SH	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SELECTOR VALVE SEVERELY CORRODED (RUSTED) INTERNALLY.  FOUND APPROXIMATELY 25 HOURS AFTER COMPLIANCE WITH AD/	GEN/81.  A SECOND SELECTOR VALVE WAS ALSO FOUND IN THE SAME CONDITION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000081700008	20000817	00008	SO  	2000	8	17	AU000342         	1	20000407	G	2810		FUEL TANK       			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK LEAKING.  INSPECTION FOUND FAULTY SEALANT.  FOUND FOLLOWING COMPLIANCE WITH AD/GEN/80.						1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2000081700009	20000817	00009	NM  	2000	8	17	AU000343         	1	20000407	G	2810		FUEL TANK       			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANKS LEAKING.  FOUND FOLLOWING COMPLIANCE WITH AD/GEN/81  .LEAKS WERE NOT PRESENT PRIOR TO INTRODUCTION OF W	ATER OR IPA.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000081700010	20000817	00010	SO  	2000	8	17	AU000344         	1	20000217	G	2810		FUEL TANK       			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANKS LEAKING.  FOUND FOLLOWING COMPLIANCE WITH AD/GEN/80.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2000082200014	20000822	00014	SO  	2000	8	22	AU000345         	1	20000407	G	2810		FUEL TANK       			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANKS LEAKING.  FOUND FOLLOWING COMPLIANCE WITH AD/GEN/80.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2000082200015	20000822	00015	WP  	2000	8	22	AU000346         	1	20000214	G	2800		FUEL TANK       			FUJI  	FA200 	FA200180    	       	WP  	LYC   	O360  	IO360B1B    	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L555451A			(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA)						1	L	7	1 	3O	3	O	 	A4PC    	1E10	5	C	P7EA	 
2000082200016	20000822	00016	CE  	2000	8	22	AU000352         	1	20000508	G	5730		SKIN            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING PLATES/SKIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED IN AREA OF MLG WHEELWELL CENTER RIB.  AIRCRAFT HAS A FACTORY INSTALLED RIB REINFORCEM	ENT FITTED AND IS ALSO OUTSIDE OF THE SERIAL NUMBER RANGE AS REFERENCED IN AD/CESSNA400/105 AND SERVICE LETTER MEB 76-2.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000082200017	20000822	00017	SO  	2000	8	22	AU000353         	1	20000416	G	2800		FUEL TANK       			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	M76EMM      	EA  	AIRCRAFT FUEL SY	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L569936	38002K		(AUS) FUEL SYSTEM CONTAMINATED WITH ETHYLENE DIAMINE (EDA).  FOLLOWING DECONTAMINATION WASH, WATER WOULD NOT DRAIN FROM 	THE TANKS.  A PROBE INSERTED VIA THE WATER DRAIN PORT RESULTED IN A DIAPHRAGM BEING FELT.  THE DIAPHRAGM WAS PUNCTURED T	O DRAIN THE WATER. THIS WAS CARRIED OUT NUMEROUS TIMES BEFORE THE TANKS WERE FULLY DRAINED.  DURING THE DRAIN A GREEN TR	ANSLUCENT GEL  APPEARED.  A SAMPLE WAS TAKEN BUT APPAREENTLY EVAPORATED OVER A THREE DAY  PERIOD.  ABOUT THREE TO FOUR D	AYS LATER A TREACALY BROWN SUBSTANCE WAS FOUND ON THE BOTTOM OF THE TANKS.		1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA4	 
2000082200018	20000822	00018	SO  	2000	8	22	AU000354         	2	20000510	G	8520	652541	NUT             	CONT        	IO520M      	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 			1059 		560460		560460			(AUS) RIGHT ENGINE NR 6 CYLINDER HOLDDOWN NUT CRACKED.  LOSS OF TENSION ON THROUGH BOLT.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000082200019	20000822	00019	SW  	2000	8	22	AU000355         	1	20000504	G	5311	1044841	TUBE            			AIRTRC	AT500 	AT502B      	0390307	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE VERTICAL TUBE CRACKED AT WING ANGLE ATTACHMENT POINT.						1	L	7	1 	3T	4	T	NC	A17SW   	E4EA	6	C	P15EA	 
2000082200020	20000822	00020	CE  	2000	8	22	AU000356         	1	20000401	G	5312		BULKHEAD        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOORPOST BULKHEAD CRACKED IN RELIEF HOLE.  CRACK LENGTH 12.7 MM (0.5 INCH).  FOUND DURING INSPECTION IAW A	D/C206/48.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2000082100130	20000821	00130	EU  	2000	8	21	AU000357         	1	20000401	G	5753		LINK            			PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	TE FLAP STRUCTUR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT INBOARD FLAP HANGERS CORRODED IN AREA OF BONDING WIRE ATTACHMENT.  FOUND DURING INSPECTION IAW AD/P	68/40.					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2000082100131	20000821	00131	SO  	2000	8	21	AU000358         	1	20000428	G	5730	62061002	SKIN            			PIPER 	PA28  	PA28181     	7102807	SO  										WING PLATES/SKIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SKIN CRACKED.						1	L	7	1 	3O			 	2A13    					 
2000082100132	20000821	00132	EA  	2000	8	21	AU000361         	2	20000501	G	7250		BEARING         			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							PCE81516			(AUS) ENGINE POWER SECTION FAILED.  SUSPECT CAUSED BY NR 3 BEARING FAILURE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000082100133	20000821	00133	SO  	2000	8	21	AU000364         	1	20000515	G	5311	77467009	FRAME           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	74D	74DM        	EA  	FUSELAGE MAIN FR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME REINFORCEMENT CHANNEL DISTORTED AND CRACKED ON FLANGES.  FUSELAGE FRAME DISTORTED WITH A SMALL CRAC	K WHERE ARIVET HAD PULLED OUT AT THE LOWER OUTBOARD ATTACHMENT TO THEFUSELAGE SKIN.  FOUND DURING INSPECTION IAW AD/PA38	/25.				1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P88614	 
2000082100134	20000821	00134	SO  	2000	8	21	AU000365         	1	20000505	G	2710	1430028	CONTROL CABLE   			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	AILERON CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT AILERON CONTROL CABLES WORN BEYOND LIMITS IN THE AREA OF THE OUTER GUIDES.						1	H	7	1 	3O	3	O	 	1A2     	E274	5	N	P88614	 
2000082100135	20000821	00135	SW  	2000	8	21	AU000366         	1	20000412	G	3213	ED12526	FITTING         	GULSTM      	710015      	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					MAIN LANDING GEA	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 			2205 							(AUS) RH MAIN LANDING GEAR ACTUATOR ATTACHMENT CLEVIS FITTING CRACKED.                                                  	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000062900173	20000629	00173	SW  	2000	6	29	AU000375         	1	20000213	G	6720	222012724103	SPACER          	BELL        		BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					TAIL ROTOR CONTR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) TAIL ROTOR PITCH CHANGE MECHANISM SPACER SEVERELY CORRODED.  A PIECE OF THE SPACER HAD FLAKED OFF AND JAMMED THE S	PLINE PLATE PN 222-012-725-001 ON THE OUTPUT SHAFT SPLINES.					1	G	7	2 	3U	3	U	 	H9SW    	E5NE				 
2000081700015	20000817	00015	GL  	2000	8	17	AU000383         	3	20000515	G	6111		BLADE           	MCAULY      		CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	PROPELLER BLADE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 								830133		(AUS) PROPELLER BLADES LOOSE ON FERRULE ASSEMBLIES.  LOW TORQUE.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2000071100293	20000711	00293	SW  	2000	7	11	AU000384         	1	20000515	G	6220	206011147007	STRAP           	BELL        	206011100145	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR HEAD	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					AAB51059		CAE832194			(AUS) TENSION-TORSION (TT) STRAPS DETERIORATED.  THE STRAPS WERE DISTORTED AND THE URETHANE COATING ADJACENT TO THE LATC	H BOLT BUSHINGS WAS SPLIT REVEALING THE INTERNAL WINDINGS.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000081700016	20000817	00016	GL  	2000	8	17	AU000385         	3	20000515	G	6114	D32513R	HUB             	HARTZL      		CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	PROPELLER HUB SE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 								EC1567A		(AUS) PROPELLER HUB CRACKED IN TWO PLACES FROM CRANKSHAFT BORE RADIALLY TO TWO STUD HOLES.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P25EA	 
2000081700023	20000817	00023	GL  	2000	8	17	AU000390         	3	20000419	G	6112	4E13113	BRUSH BLOCK     			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER DE-ICE	MISINSTALLED    	W				K	 	 	 	NONE                    				O	B	 	OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE DE-ICE SYSTEM CENTER BRUSH BLOCK TERMINAL INCORRECTLY INSTALLED.  PROPELLER AMMETER IN LINE TERMINALS	 MELTED.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2000070600231	20000706	00231	NM  	2000	7	6	AU000391         	1	20000224	G	5511	A0441	SPAR            	ROBSIN      		ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					HORIZ STABILIZER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					2072					(AUS) HORIZONTAL STABILIZER SPAR CRACKED THROUGH ATTACHMENT BOLT HOLES (4 OFF).  FOUND FOLLOWING TAIL ROTOR STRIKE INSPE	CTION ALTHOUGH IT IS SUSPECTED THAT THE CRACKS WERE ALREADY PRESENT.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000070600232	20000706	00232	EU  	2000	7	6	AU000392         	1	20000512	G	6210	1178016602	BRACKET         		11780166    	BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					MAIN ROTOR BLADE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE VIBRATION ABSORBER LOWER BRACKET CRACKED.                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2000070600233	20000706	00233	GL  	2000	7	6	AU000393         	2	20000420	G	7250	23062750	HEAT SHIELD     			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE SECTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAT36613		CAE832257			(AUS) FIRST STAGE TURBINE NOZZLE HEAT SHIELD CRACKED.  FOUND DURING INSPECTION IAW ROLLS ROYCE CEBA-1370.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000081700024	20000817	00024	CE  	2000	8	17	AU000394         	1	20000519	G	5753	3516505084	RIB             			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	TE FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FLAP RIB LOCATED BENEATH FLAP ACTUATING BRACKET CRACKED.						1	L	7	2 	3O			 	3A16    		5	C	P22EA	 
2000062900174	20000629	00174	EU  	2000	6	29	AU000397         	1	20000427	G	6510	593404	BEARING         	AEROSP      	350A34011004	AEROSP	AS355 	AS355F      	8680806	EU  	ALLSN 	250C  	250C20F     	03013	GL  					TAIL ROTOR DRIVE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVESHAFT BEARING SPINNING ON THE DRIVESHAFT WEARING A GROOVE INTO THE SHAFT.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2000081700027	20000817	00027	SO  	2000	8	17	AU000401         	2	20000523	G	7414	10349276TCM	CAPACITOR       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C98    	GL  	MAGNETO/DISTRIBU	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAGNETO CAPACITOR FAULTY.  CAPACITOR WAS A NEWLY FITTED ITEM.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2000081700029	20000817	00029	CE  	2000	8	17	AU000403         	1	20000525	G	2497		WIRE            			CESSNA	206   	U206F       	2073333	CE  						MCAULY	D3A34	D3A34C404   	GL  	COLLECTOR TANK	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							564231			(AUS) FIRE UNDER FUSELAGE FLOOR IN RT FUEL COLLECTOR TANK COMPARTMENT.  EXTENSIVE DAMAGE CAUSED TO WIRING LOOM LOCATED B	ETWEEN THE COLLECTOR TANK AND THE FLOOR PANEL.  SUSPECT CAUSED BY SPARKS FROM THE RIGHT EXHAUST TAILPIPE IGNITING LEAKIN	G BOOST PUMP FUEL AND LEAKING ENGINE OIL.				1	H	7	1 	3O			 	A4CE    		5	C	P47GL	 
2000081700030	20000817	00030	SO  	2000	8	17	AU000404         	1	20000517	G	3234		LEVER           			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	LANDING GEAR SEL	FOULED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR MANUAL EXTENSION SYSTEM LEVER OBSTRUCTED BY THE SEAT MOUNTED PORTABLE FIRE EXTINGUISHER IN SOME SEAT 	POSITIONS.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2000081700031	20000817	00031	SO  	2000	8	17	AU000408         	1	20000510	G	2434	ALH212851	ROTOR           		ALX842ILS   	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	DC GENERATOR-ALT	SHORTED         	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					406116		L97455AL8085	BG45824634		(AUS) LEFT ALTERNATOR SHORT CIRCUITED.  COMPLETE ELECTRICAL FAILURE.  A PROBLEM LOWERING THE LANDING GEAR RESULTED IN A 	GEAR UP LANDING CAUSING DAMAGE TO THE AIRCRAFT. SEE SDR AU000404 FOR ADDITIONAL INFORMATION.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2000082100029	20000821	00029	CE  	2000	8	21	AU000410         	1	20000306	G	2822		PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					FUEL BOOST PUMP	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 							277602R			(AUS) LEFT FUEL TRANSFER PUMP FAILED.  INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING.  L	EFT LANDING LIGHT CIRCUIT BREAKER TRIPPED.  (X)					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2000082100030	20000821	00030	CE  	2000	8	21	AU000411         	1	20000427	G	2822		PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					FUEL BOOST PUMP	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 							277564R			(AUS) LEFT FUEL TRANSFER PUMP FAILED.  INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING.  L	EFT LANDING LIGHT CIRCUIT BREAKER TRIPPED.					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2000082100056	20000821	00056	CE  	2000	8	21	AU000412         	1	20000419	G	2822		PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					FUEL BOOST PUMP	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 							277331R			(AUS) RIGHT FUEL TRANSFER PUMP FAILED.  INVESTIGATION FOUND THAT THE PUMP POSITIVE WIRE HAD BURNED OFF AT THE HOUSING.  	RIGHT LANDING LIGHT CIRCUIT BREAKER TRIPPED.					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2000082100031	20000821	00031	CE  	2000	8	21	AU000414         	1	20000525	G	3230	50452134	ROD END         		504501025   	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	FAILED          	W				K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR TORQUE TUBE ROD END FAILED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001011100337	20010111	00337	NM  	2001	1	11	AU000415         	1	20000516	G	2750	7455	WIRE ROPE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAP CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SECONDARY DRIVE OUTER CABLE SWAGED COUPLING FLANGE WORNEXCESSIVELY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000071800016	20000718	00016	NM  	2000	7	18	AU000416         	1	20000521	G	6310	A1681	RETAINER        	ROBSIN      		ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/TRANSMISS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			409  		4430					(AUS) CLUTCH SEAL PLATE CRACKED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000071800017	20000718	00017	NM  	2000	7	18	AU000417         	1	20000510	G	7820	A1696	MUFFLER         	LYC         		ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE NOISE SUP	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EXHAUST MUFFLER SPLIT.  MUFFLER WAS A NEW ITEM.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000082100032	20000821	00032	EA  	2000	8	21	AU000419         	2	20000529	G	8550	LW13388	SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		LD	LANDING        	1			AU	S 					L142368A		L142368A			(AUS) LEFT ENGINE OIL FILTER ADAPTER PLATE SEAL PROTRUDING FROM PLATE.  SEAL APPEARED TO BE SEVERED.  ENGINE NEEDED 9 LI	TRES OF OIL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000082100057	20000821	00057	SO  	2000	8	21	AU000420         	2	20000529	G	8520	652541	NUT             	CONT        		CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 5 CYLINDER THROUGH BOLT NUT SPLIT.						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2000082100033	20000821	00033	EA  	2000	8	21	AU000421         	2	20000524	G	8530		CYLINDER        	LYC         		GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							L1528448			(AUS) LEFT ENGINE NR 6 CYLINDER FAILED AND SEPARATED.  CRANKCASE HOLED IN AREA OF NR 6 CYLINDER.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2000071900172	20000719	00172	EU  	2000	7	19	AU000422         	1	20000526	G	6230	704A3364021	BUSHING         	AEROSP      	SCISSORLINK 	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR MAST	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR SWASHPLATE TOP SCISSOR LINK BUSHING BROKEN. THE BROKEN BUSHING WORE INTO THE SCISSOR LINK.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000082100038	20000821	00038	CE  	2000	8	21	AU000423         	1	20000531	G	5523	12346281	TRIM TAB        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ELEVATOR TAB STR	DISTORTED       	W				K	 	 	 	NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ELEVATOR TRIM TAB DISTORTED,  SPLIT AND BULGED.  INVESTIGATION FOUND THAT THE CORE HAD BEEN FILLED WITH EXPA	NDABLE FOAM WHICH HAD CONTINUED TO EXPAND AFTER FILLING THE AVAILABLE SPACE.  UNAPPROVED PART.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2000082100039	20000821	00039	SW  	2000	8	21	AU000424         	1	20000530	G	7921	8526250	COOLER          	LYC         		GULSTM	680   	680FL       	0141608	SW  	LYC   	O720  	IO720B1B    	41546	EA  	HARTZL	HCB3Z	HCB3Z302    	GL  	ENG OIL COOLER	CRACKED         	W				K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 							L92454A			(AUS) RIGHT ENGINE OIL COOLER LEAKING FROM PREVIOUS WELD REPAIR.						1	H	7	2 	3O	3	O	 	2A4     	1E15	5	C	P907	 
2000072000016	20000720	00016	SW  	2000	7	20	AU000425         	1	20000601	G	6220		MAIN ROTOR      	BELL        	TRUNNION    	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					SPLIT CONE HALF	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			304  							(AUS) MAIN ROTOR SPLIT CONE HALF INSTALLED UPSIDE DOWN.  MAIN ROTOR TRUNNION CHAMFER DAMAGED BY SHARP EDGE OF CONE.  MAS	T SPLIT CONE SEAT FRETTING.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000082100040	20000821	00040	CE  	2000	8	21	AU000426         	1	20000523	G	2810		FUEL TANK       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	FUEL STORAGE	FOD             	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING FUEL TANK FOD.  ON REMOVAL OF THE RIGHT WING FUEL TANK ACCESS PANEL, A PIECE OF RAG MEASURING APPROXIMA	TELY 300 MM BY 300 MM (11.8 INCHES BY 11.8 INCHES) WAS FOUND IN THE BOTTOM OF THE TANK COVERING ONE FUEL TANK FLOW VALVE	 AND THE MAIN FUEL SUCTION PORT.  THE  PANEL WAS REMOVED DUE TO A LARGE FUEL STAIN ON THE TOP SURFACE OF THE WING.  IT W	AS NOTED THAT THE PANEL HAD BEEN INCORRECTLY  INSTALLED AND NO SEALANT HAD BEEN USED.   FOD.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000082400006	20000824	00006	SO  	2000	8	24	AU000427         	1	20000524	G	2910	9515348	PIPE            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	HYDRAULIC, MAIN	CORRODED        	W				K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR ''UP'' PIPE CORRODED AND LEAKING.  LOSS OF HYDRAULIC  FLUID.  LEFT MLG DOWNLOCK STIFF TO OPERATE.  AI	RCRAFT OPERATES IN A SALT LADEN ENVIRONMENT.					1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2000082400007	20000824	00007	EA  	2000	8	24	AU000428         	2	20000214	G	8550	LW13388	SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							RL11668A			(AUS) OIL FILTER BASE PLATE GASKET LEAKING AND PROTRUDING PAST THE PLATE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000071900173	20000719	00173	WP  	2000	7	19	AU000429         	1	20000508	G	6420	B1151	BEARING         			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					TAIL ROTOR HEAD	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					DN					(AUS) TAIL ROTOR TEETER BEARINGS WEARING PREMATURELY.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000082400008	20000824	00008		2000	8	24	AU000430         	4	20000322	G	2211	BZX5111	DIODE           	CENTURY     	IC151       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AUTOPILOT COMPUT	INCORRECT       	W				K	 	 	 	NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					S205B					(AUS) ROLL AMPLIFIER POWER SUPPLY ZENER DIODE INCORRECT PART.  DIODE CAUSED DRIVER TRANSISTOR TO FAIL.  UNAPPROVED PART.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011106062	20010111	06062	NM  	2001	1	11	AU000431         	1	20000414	G	7120		MOUNT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							120153			(AUS) NR 2 ENGINE INBOARD AND OUTBOARD FORWARD MOUNTS INCORRECTLY INSTALLED (BACK TO FRONT). FURTHER INVESTIGATION FOUND	 THE TOP FORWARD MOUNT TO BE UNUSUALLY COMPRESSED AND THE RIVETS IN THE TOP SKIN OF THE HORSE COLLAR IN THE AREA OF THE 	TOP FORWARD MOUNT TO BE PULLING IN A FORWARD DIRECTION. THE ENGINE CONTROL QUADRANT SPRING STRUT FORK END APPEARS BENT A	ND THE AFT TOP ENGINE MOUNT STRUTS ARE ANGLED SLIGHTLY FORWARD.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011106063	20010111	06063	SW  	2001	1	11	AU000432         	1	20000530	G	5210	2724127077	LOCK            			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	PAX DOOR	JAMMED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER DOOR HANDLE SAFETY LOCK FAULTY. INVESTIGATION FOUND THE PIVOT BOLT BETWEEN THE ACTUATING ARM AND THE PLU	NGER WAS TOOTIGHT CAUSING THE MECHANISM TO JAM.					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011106064	20010111	06064		2001	1	11	AU000433         	4	20000528	G	3414	640608901	INDICATOR       			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	AIRSPEED	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 			10109							(AUS) RT AIRSPEED INDICATOR AND STANDBY AIRSPEED INDICATORS LOSTINDICATION. SUSPECT CAUSED BY ICING.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011106065	20010111	06065	WP  	2001	1	11	AU000434         	2	20000527	G	7313	31032359	NOZZLE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					FUEL INJECTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			74   				31032359			(AUS) FUEL INJECTOR NOZZLE INLET SHEARED IN THREADED AREA.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2001011106066	20010111	06066	EU  	2001	1	11	AU000435         	1	20000528	G	3251	104273007	VALVE           	ROTOL       	200876004   	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					STEERING UNIT	LEAKING         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR STEERING VALVE INTERNAL LEAK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000082400009	20000824	00009	CE  	2000	8	24	AU000436         	1	20000605	G	2752	261114467	BRACKET         	CESSNA      	208B        	CESSNA	208   	208B        	2073701	CE  										FUSELAGE MISC	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 					B0428					(AUS) STANDBY FLAP MOTOR SUPPORT BRACKETS PN 2611144-6 AND PN 2611144-7 FAILED.						1	H	7	1 	3T			 	A37CE   					 
2000082400010	20000824	00010	NE  	2000	8	24	AU000437         	2	20000527	G	7532	310334701	BLEED VALVE     	PWA         		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR BLEED	FAULTY          	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			390  		19308					(AUS) ENGINE BLEED VALVE DIAPHRAGM HOLED AND SEAT BADLY WORN DUE TO CHATTERING.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2001011106067	20010111	06067	NM  	2001	1	11	AU000438         	1	20000603	G	5542	85540012101	SKIN            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RUDDER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORE RUDDER SKIN CRACKED IN TOP LH CORNER. INSPECTION FOUND THAT THE LAST (REARMOST) RIVET ON THE STIFFENER PNO 85	540025-101 WAS INCORRECTLY FITTED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011106068	20010111	06068	EU  	2001	1	11	AU000439         	1	20000528	G	3234	HTE96811	SELECTOR VALVE  			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE INTERNAL LEAK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011106069	20010111	06069	EU  	2001	1	11	AU000440         	1	20000531	G	2750		CONTROLLER      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAP	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) FLAPS FAULTY. FLAPS CHECKED ON GROUND AND OPERATED WITHOUT FAULT.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011106070	20010111	06070	EU  	2001	1	11	AU000441         	1	20000206	G	3230	HTE2501	MOTOR           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					CONTROL VALVE	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR CONTROL VALVE ACTUATOR MOTOR FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011106071	20010111	06071	NM  	2001	1	11	AU000442         	1	20000519	G	5310		STRUCTURE       			BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FUSELAGE	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR INADVERTANTLY RETRACTED DURING OVERNIGHT MAINTENANCE. EXTENSIVE DAMAGE WAS CAUSED TO THE FUSELAG	ESTRUCTURE IN THE NOSE 					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000082400011	20000824	00011	CE  	2000	8	24	AU000443         	1	20000605	G	2910	520010785	PIPE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	HYDRAULIC, MAIN	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT HYDRAULIC FILTER HOUSING PRESSURE PIPE SPLIT AT OUTBOARD RADIUS OF BEND.  LOSS OF HYDRAULIC FLUID.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000082400012	20000824	00012	CE  	2000	8	24	AU000444         	1	20000414	G	2910	520010786	PIPE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	HYDRAULIC, MAIN	CRACKED         	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT HYDRAULIC FILTER PRESSURE PIPE SPLIT AND LEAKING AT OUTBOARD RADIUS.  LOSS OF HYDRAULIC FLUID.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011106081	20010111	06081	NM  	2001	1	11	AU000445         	1	20000528	G	6123	6121K5	RELAY           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) AUTO-FEATHER RELAY 6121K5 FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000082400013	20000824	00013	EA  	2000	8	24	AU000446         	2	20000320	G	8520		CRANKSHAFT      	LYC         		GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			AU	S 							RL805748C			(AUS) ENGINE FAILURE.  SUSPECT BROKEN CRANKSHAFT.						1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000082400014	20000824	00014	CE  	2000	8	24	AU000447         	1	20000603	G	2435	03601018	BEARING         	LEARSIEGLER 	230790021   	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	STARTER/GEN	FAILED          	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			AU	S 					269					(AUS) LEFT ENGINE STARTER/GENERATOR REAR BEARING FAILED.  LEFT ELECTRICAL BUS CURRENT LIMITER ALSO FAILED.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2001011106082	20010111	06082		2001	1	11	AU000448         	4	20000606	G	3414	WL604AMA26	INDICATOR       			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					AIRSPEED	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) CAPTAINS AIRSPEED INDICATOR (ASI) FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000071200161	20000712	00161	CE  	2000	7	12	AU000449         	1	20000605	G	5320	26111446	BRACKET         	CESSNA      		CESSNA	208   	208B        	2073701	CE  										FUSELAGE	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 					B0428					(AUS) FLAP MOTOR SUPPORT BRACKETS PN 2611144-6 AND PN 2611144-7 TORN FROM FUSELAGE STRUCTURE.						1	H	7	1 	3T			 	A37CE   					 
2000100300073	20001003	00073	NM  	2000	10	3	AU000450         	1	20000520	G	2822	50081761	HOUSING         	SUNDSTRANDEM	5006003C    	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FUEL BOOST PUMP	ERODED          	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 					337					(AUS) MAIN FORWARD FUEL TANK LEFT BOOST PUMP FAILED.  INVESTIGATION FOUND PIECES OF METAL SEPARATED FROM THE HOUSING INL	ET STRUTS JAMMING THE CHECK VALVE PARTIALLY OPEN.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011100632	20010111	00632	NM  	2001	1	11	AU000451         	1	20000603	G	5610	91142H2369	WINDSHIELD      			BOEING	737   	73733A      	1384673	NM  										COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) FIRST OFFICERS NO1 WINDOW OUTER PANE CRACKED.						2	L	7	2 	4F			RT	A16WE   					 
2001011100633	20010111	00633	NM  	2001	1	11	AU000452         	1	20000526	G	5320		WEB             			BOEING	747   	747338      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL WELL TORQUE BOX VERTICAL WEB CRACKED ANDFRAME DISTORTED.						2	L	7	2 	4F			RT	A20WE   					 
2001011100634	20010111	00634	NE  	2001	1	11	AU000453         	2	20000527	G	7230	13065	BLADE           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					COMPRESSOR	FAILED          	W				O	 	 	 	OTHER                   				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			41574				13065			(AUS) NO2 ENGINE HIGH PRESSURE COMPRESSOR BLADE FAILED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001011100635	20010111	00635	NM  	2001	1	11	AU000454         	1	20000523	G	2752		FITTING         			BOEING	747   	747338      	       	NM  										TE FLAP ACTUATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTBOARD RT AFT TRAILING EDGE FLAP DRIVE MECHANISM OUTBOARD FITTING CRACKED AND BOLT BADLY CORRODED. BOLT HEAD MIS	SING ANDBOLT PROTRUDING.					2	L	7	2 	4F			RT	A20WE   					 
2001011100636	20010111	00636		2001	1	11	AU000455         	4	20000523	G	2565	G126	PIN             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ESCAPE SLIDE	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ESCAPE SLIDERAFT INFLATION BOTTLE SAFETY PIN STILL FITTED. SLIDEWOULD NOT HAVE OPERATED WHEN REQUIRED.  PERSONNEL 	/ MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2000082800019	20000828	00019	CE  	2000	8	28	AU000456         	1	20000601	G	7160		HOSE            	LYC         		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENG AIR INTAKE	LOOSE           	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							L266776	731692		(AUS) ENGINE CARBURETOR HEAT SCAT HOSE CLAMP MISSING.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001011100666	20010111	00666	EU  	2001	1	11	AU000457         	1	20000610	G	7600		CONTROL UNIT    			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	ENGINE	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 							367175			(AUS) RT ENGINE CTOT WOULD NOT ENABLE. DURING FAULT FINDING ENGINEOPERATED OK UNTIL TORQUE MOTOR LOCKOUT WAS SELECTED. S	USPECTTORQUE MOTOR LOCKED OUT DURING OPERATION.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011100667	20010111	00667	EU  	2001	1	11	AU000458         	1	20000609	G	7712	7239060503	PANEL           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	TORQUE PANEL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 			5780 				785153			(AUS) CONSTANT TORQUE ON TAKEOFF (CTOT) PANEL FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001011100668	20010111	00668	SO  	2001	1	11	AU000459         	1	20000607	G	5610		SEAL            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					COCKPIT WINDOW	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) COPILOTS SIDE WINDOW SEAL OUT OF POSITION AND LEAKING.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000082800020	20000828	00020	EA  	2000	8	28	AU000460         	2	20000529	G	7210		GEARBOX         	PWA         		BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CONTAMINATED    	W				K	 	 	 	NONE                    				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							PCE81186			(AUS) PROPELLER REDUCTION GEARBOX METAL CONTAMINATION.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000082800021	20000828	00021		2000	8	28	AU000461         	4	20000609	G	3422	258719343	GYRO            			BAG   	JETSTM	JETSTM3201  	1500217	EU  										DIRECTIONAL GYRO	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 					92071948					(AUS) NR 2 DIRECTIONAL GYRO INTERNAL FAULT.						2	L	7	2 	4T			RT	A56EU   					 
2000082800022	20000828	00022	WP  	2000	8	28	AU000462         	2	20000607	G	7230	P31075	SEAL            	GARRTT      		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	LEAKING         	W				K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LEFT ENGINE CARBON SEAL ALLOWING OIL TO LEAK INTO THE BLEED AIR SYSTEM AND CONTAMINATE THE COALESCER BAG IN THE AI	R CYCLE MACHINE.  SMOKE IN THE CABIN.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2000082800023	20000828	00023	SO  	2000	8	28	AU000463         	1	20000613	G	3234	12038594001	CONTROL BOX     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					LANDING GEAR SEL	FAULTY          	W				K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 					J120046R					(AUS) LANDING GEAR CONTROL BOX FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000082800024	20000828	00024	WP  	2000	8	28	AU000464         	1	20000607	G	5743		BRACKET         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	WING, L/G	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR REAR STRUT ATTACHMENT ''Y'' BRACKETS HAD MOUNTING HOLES DRILLED OVERSIZE.  FOUND DURING INSPECTION IA	W AD/DC3/31 AMDT2.					2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001011100669	20010111	00669	WP  	2001	1	11	AU000465         	1	20000607	G	5330		SKIN            			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTER SECTION UPPER CORRUGATED SKIN CRACKED AND CORRODED IN AN AREA LOCATED NEAR THE AIRCRAFT CENTRELINE INBOARD 	OF STN 7.5 BETWEEN THE CENTRE AND REAR SPARS.					2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2000082800025	20000828	00025	EA  	2000	8	28	AU000466         	2	20000616	G	7210		GEARBOX         	PWA         		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CONTAMINATED    	W				K	 	 	 	NONE                    				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 							PCE80767			(AUS) PROPELLER REDUCTION GEARBOX METAL CONTAMINATION.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000072000030	20000720	00030	EU  	2000	7	20	AU000468         	1	20000428	G	6220	350A31190703	STARFLEX        			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					MAIN ROTOR HEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					M3308		CAE840630627			(AUS) MAIN ROTOR STARFLEX HEAD ASSEMBLY CRACKED.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2000082800026	20000828	00026	EA  	2000	8	28	AU000469         	2	20000502	G	8530	05K21114KIT	CYLINDER        	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1939415	LL034		(AUS) ENGINE SEIZED.  CYLINDERS AND PISTON RINGS RUSTED.  SURFACE CORROSION EVIDENT ON CAM FOLLOWERS AND CONNECTING RODS	.  AIRCRAFT HAD RECENTLY UNDERGONE FUEL DECONTAMINATION.  (X)					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001011104166	20010111	04166		2001	1	11	AU000470         	1	20000513	G	3500	80366201	CONTROL BOX     																	OXYGEN SYSTEM	WRONG PART      	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OXYGEN FLOW CONTROL UNITS (2 OFF) HAD UNAPPROVED SEALANT (TAPE AND PLASTICINE) APPLIED TO THE FIRST STAGE PRESSURE	 RELIEF PORTS.   UNAPPROVED PART.																		 
2001011100670	20010111	00670	EU  	2001	1	11	AU000471         	1	20000613	G	7712		SWITCH          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	FUSELAGE	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 							785512785402			(AUS) CONSTANT TORQUE ON TAKEOFF (CTOT) SWITCH LEFT IN  INCORRECT POSITION. LT AND RT ENGINE OVERTEMPERATURE OCCURRED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2000082800027	20000828	00027	SO  	2000	8	28	AU000472         	1	20000614	G	5711		SPAR CAP        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER SPAR CAP CORRODED IN WING ROOT AREA.  FOUND FOLLOWING REMOVAL OF ANTI-CHAFING TAPE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011100671	20010111	00671		2001	1	11	AU000473         	4	20000313	G	2565	7A124836	SLIDE           			BOEING	747   	747SP38     	       	NM  										PAX DOOR	MALFUNCTIONED   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT UPPER DECK ESCAPE SLIDE FAILED TO CORRECTLY DEPLOY.						2	L	7	4 	4F			RT	A20WE   					 
2000082800028	20000828	00028	CE  	2000	8	28	AU000474         	1	20000614	G	2820	52001063	PIPE            			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ACFT FUEL DISTRI	CORRODED        	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CROSSFEED PIPE CORRODED AND LEAKING.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000082800029	20000828	00029	CE  	2000	8	28	AU000475         	1	20000614	G	2820	510010877	PIPE            			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ACFT FUEL DIST	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							183445			(AUS) FUEL CROSSFEED PIPE WORN BY SPAR ANGLE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011100672	20010111	00672	SW  	2001	1	11	AU000476         	1	20000614	G	2435	03601018	BEARING         			SWRNGN	SA226 	SA226TC     	8780404	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	STARTER GEN	FAILED          	W				A	 	 	 	UNSCHED LANDING         				H	 	 	ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) LT STARTER-GENERATOR REAR BEARING FAILED AND SHAFT SHEARED.						2	L	7	2 	4T			RT	A8SW    		6	C	P15EA	 
2001011100673	20010111	00673	EU  	2001	1	11	AU000477         	1	20000609	G	2530	38512	CONNECTOR       			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	GALLEY	BROKEN          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) GALLEY COFFEEMAKER PLUG BROKEN CAUSING OVERHEATING. RT EADI HOT.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011100674	20010111	00674	EU  	2001	1	11	AU000478         	1	20000609	G	2910	137311D1576	PIPE            			BAG   	JETSTM	JETSTM3201  	1500217	EU  						ROTOL	R333	R333482F12  	GL  	HYDRAULIC SYS	RUPTURED        	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HYDRAULIC BRAKE PIPE LOCATED IN THE LANDING GEAR BAY FAILED.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T			RT	A56EU   		6	C	P61GL	 
2000082800030	20000828	00030	SO  	2000	8	28	AU000479         	2	20000607	G	8530	SA625393	SEAT            	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							291324R			(AUS) INLET VALVE SPRING SEATS ON ALL CYLINDERS CRACKED.  FURTHER INVESTIGATION FOUND THAT THE INLET VALVE GUIDES WERE N	OT FULLY SEATED IN THE CYLINDER HEAD.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001011100675	20010111	00675	SO  	2001	1	11	AU000480         	1	20000621	G	3234	12043270501	RELAY           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					MLG	INTERMITTENT    	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR RELAY BOX INTERMITTENT IN OPERATION.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2001011100676	20010111	00676	SO  	2001	1	11	AU000481         	1	20000622	G	3231	12032943001	VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					MLG	STUCK           	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) RT NOSE LANDING GEAR DOOR SEQUENCE VALVE STICKING. LANDING GEAR DOOR SOLENOID VALVE PNO SV14H1100-4 SUSPECT INTERN	AL LEAK.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000071900174	20000719	00174	SW  	2000	7	19	AU000482         	1	20000601	G	6220	206011113103	TRUNNION        	BELL        		BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR HEAD	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			304  							(AUS) MAIN ROTOR TRUNNION FAULTY.  MAST AND SPLIT CONES ALSO REPLACED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000071900175	20000719	00175	EU  	2000	7	19	AU000483         	1	20000526	G	2435	150SG10095	BRUSH BLOCK     		150SG1RZQ   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER/GEN	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					5461					(AUS) STARTER/GENERATOR BRUSHES BROKEN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000082800031	20000828	00031	EA  	2000	8	28	AU000484         	2	20000602	G	8530	68761	PIPE            	LYC         		BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	CORRODED        	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							L1327648A			(AUS) RIGHT ENGINE NR 5 CYLINDER ROCKER COVER OIL DRAIN PIPE HOLED DUE TO CORROSION.  LOSS OF ENGINE OIL.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2000082800032	20000828	00032	CE  	2000	8	28	AU000485         	1	20000612	G	2913	98807101	PRESSURE SWITCH 		12808461    	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	HYDRAULIC PUMP	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 			1000 							(AUS) LANDING GEAR POWER PACK PRESSURE SWITCH FAULTY.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2000082800033	20000828	00033	GL  	2000	8	28	AU000486         	1	20000414	G	3233	10258162	FITTING         		106580270   	AMTR  	MSTG2 	MUSTANG2    	       	GL  	PCKARD	V1650 	V16507      	49001	SO  	HAMSTD	24D	24D50       	NE  	LANDING GEAR ACT	DAMAGED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			33   		97277468		V303101	ADH9196		(AUS) RIGHT MAIN LANDING GEAR RETRACTION RAM FITTING FAILED.   INVESTIGATION FOUND THAT THE END FITTING FROM A FLAP RAM 	HAD BEEN FITTED INSTEAD OF THE CORRECT PART.  UNAPPROVED PART.					1	L	7	1 	3O	4	V	 	EXPA1L71	EXP4V	6	C	P784	 
2000082800034	20000828	00034	WP  	2000	8	28	AU000487         	2	20000612	G	8530		EXHAUST VALVE   	DHAVXX      	GIPSYMAJOR10	DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			816  				10114			(AUS) NR 1 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM.  VALVE HEAD PUNCTURED PISTON AND EXITED THE ENGINE VIA	 THE TOP RIGHT SIDE OF THE CRANKCASE.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2000082800035	20000828	00035	CE  	2000	8	28	AU000488         	1	20000616	G	3230	508102101	MOTOR           			BEECH 	80    	70          	1152807	CE  	LYC   	O480  	IGSO480A1E6 	41529	EA  	HARTZL	HCB3Z	HCB3Z302    	GL  	LANDING GEAR ACT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR MOTOR DRIVESHAFT AND GEAR TEETH STRIPPED.						1	L	7	2 	3O	3	O	 	3A20    	E284	5	C	P907	 
2000083000029	20000830	00029	SO  	2000	8	30	AU000490         	1	20000503	G	3220		GEAR            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	NOSE	COLLAPSED       	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR COLLAPSED ON LANDING.						1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2000081000032	20000810	00032	CE  	2000	8	10	AU000491         	1	20000623	G	3231	504500110	BELLCRANK       	CESSNA      	310R        	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					L/G DOOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					1681					(AUS) RIGHT MAIN LANDING GEAR DOOR BELLCRANK BROKEN.						1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2001011100708	20010111	00708	EU  	2001	1	11	AU000492         	1	20000604	G	2751	D150175	TRANSDUCER      			FOKKER	F27   	F27MK50     	       	EU  										TE FLAP POSITION	INTERMITTENT    	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) FLAP POSITION TRANSDUCER CONNECTOR LOOSE.						2	H	7	2 	4T			RT	A817    					 
2001011100709	20010111	00709	EU  	2001	1	11	AU000493         	1	20000618	G	5210	F5106043425	SEAL            			FOKKER	F27   	F27MK50     	       	EU  										PAX DOOR	CONTAMINATED    	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) CABIN DOOR SEAL CONTAMINATED WITH WATER. SUSPECT WATER FROZE AT ALTITUDE CAUSING LOSS OF PRESSURISATION.						2	H	7	2 	4T			RT	A817    					 
2001011100711	20010111	00711	EU  	2001	1	11	AU000494         	1	20000616	G	7722	321EDP32	INDICATOR       			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					ENGINE EGT/TIT	FLUCTUATES      	W				C	 	 	 	ABORTED TAKEOFF         				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE TGT SYSTEM TERMINAL LOOSE AT FORWARD PYLON BREAK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100712	20010111	00712	NE  	2001	1	11	AU000496         	2	20000623	G	7320	1103P2671	SWITCH          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	FUEL CONTROL	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE AUTO COARSEN P3 SWITCH HAD HIGH RESISTANCE ACROSS THE CONTACTS.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011100713	20010111	00713	EA  	2001	1	11	AU000497         	1	20000626	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LH FORWARD WINDSHIELD CRACKED.						2	L	7	2 	4F			RT	A21EA   					 
2001011100719	20010111	00719	SO  	2001	1	11	AU000498         	1	20000618	G	3260	12041127001	PROXIMITY SENSOR			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					MLG	INTERMITTENT    	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR POSITION PROXIMITY SENSOR INTERMITTENT INOPERATION.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000081000033	20000810	00033	CE  	2000	8	10	AU000499         	1	20000617	G	3260	ICHI6	SWITCH          			CESSNA	441   	441         	2076020	CE  						MCAULY	3G34C6	3GFR34C601  	GL  	LANDING GEAR POS	INTERMITTENT    	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR SQUAT SWITCH INTERMITTENT IN OPERATION.						1	L	7	2 	3T			RT	A28CE   		6	C	P54GL	 
2000071900176	20000719	00176	WP  	2000	7	19	AU000500         	1	20000621	G	6220	36124	CUFF            	HILLER      		HILLER	UH12  	UH12E       	4360122	WP  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR HEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			527  		10580					(AUS) MAIN ROTOR CUFF CRACKED FROM BOLT HOLE. CRACK LENGTH 10MM (0.393IN). FOUND DURING DYE PENETRANT INSPECTION IAW AD/	HIL12/17(SB 36-1).					1	G	7	1 	3O	3	U	 	4H11    	E4CE				 
2000071900177	20000719	00177	SW  	2000	7	19	AU000501         	1	20000624	G	3397		WIRE            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					PASSENGER COMPT	BROKEN          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) CABIN DOME LIGHT DIMMER POTENTIOMETER WIRE BROKEN AND SHORT CIRCUITING.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2000112800091	20001128	00091		2000	11	28	AU000502         	4	20000628	G	6122	B20897	COVER           	MCAULY      	VARIOUS     															PROP GOVERNOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CSU COVER FAULTY. THE COVER IS OVAL SHAPED AND THE BORE IS OVERSIZE BY 0.0762 MM (0.003 INCH). SUBMITTER STATED TH	E ITEM IS FAULTY AS RECEIVED FROM THE MANUFACTURER.  (X)																		 
2001011100745	20010111	00745	EU  	2001	1	11	AU000503         	1	20000616	G	2823	9401037	VALVE           			FOKKER	F28   	F28MK0100   	4990807	EU  										FUEL SELECTOR	SEIZED          	W				C	 	 	 	ABORTED TAKEOFF         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) RT FIRE/FUEL SHUTOFF VALVE MOTOR SEIZED APPROXIMATELY 75 PERCENT CLOSED.						2	L	7	2 	4F			RT	        					 
2001011100747	20010111	00747	WP  	2001	1	11	AU000504         	2	20000619	G	7322	897780	FUEL CONTROL    			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	LT ENGINE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			2176 				P66363			(AUS) LT ENGINE FUEL CONTROL UNIT FAULTY.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2001011100748	20010111	00748	EU  	2001	1	11	AU000505         	1	20000628	G	2841		INDICATOR       			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	FUEL QUANTITY	OUT OF TOLERANCE	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) FUEL QUANTITY SYSTEM OUT OF CALIBRATION.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001011100749	20010111	00749	EU  	2001	1	11	AU000506         	1	20000618	G	3412	522707	INDICATOR       			FOKKER	F27   	F27MK50     	       	EU  										TAT	FAULTY          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 					0870032					(AUS) TOTAL AIR TEMPERATURE (TAT) INDICATOR INTERNAL FAULT.						2	H	7	2 	4T			RT	A817    					 
2000082100099	20000821	00099	EA  	2000	8	21	AU000507         	1	20000628	G	2820		PIPE            			DHAV  	DHC6  	DHC6        	2802606	EA  										ACFT FUEL DIST	FOD             	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) FORWARD FUEL TANK TRANSFER PIPE BLOCKED BY BLANKING PLUG.  FOD.   (X)						1	H	7	2 	3T			RT	A9EA    					 
2000082100100	20000821	00100	CE  	2000	8	21	AU000508         	1	20000623	G	2823	5425662046	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					FUEL SELECTOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FUEL SELECTOR TELEFLEX CABLE FITTING BINDING AT SELECTOR END.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000082100101	20000821	00101	CE  	2000	8	21	AU000509         	1	20000623	G	7810	2437241	MANIFOLD        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE COLLECTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							2437241			(AUS) LEFT ENGINE EXHAUST MANIFOLDS TRANSPOSED.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000082100102	20000821	00102	SO  	2000	8	21	AU000511         	2	20000629	G	8520	646277	LIFTER          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							459310	739670		(AUS) HYDRAULIC VALVE LIFTERS (TAPPETS) WORN AND PITTED.  EVIDENCE OF PITTING ON THE CAMSHAFT.  (X)						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2000082100103	20000821	00103	EA  	2000	8	21	AU000512         	2	20000426	G	8500		ENGINE          	LYC         		PIPER 	PA24  	PA24400     	7102408	SO  	LYC   	O720  	IO720A1A    	41546	EA  	HARTZL	HCA3V	HCA3VK4     	GL  	ENGINE	DETERIORATED    	W				K	 	 	 	NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							218654C			(AUS) ENGINE IN A DETERIORATED AND POOR CONDITION.  SOME UNAPPROVED PARTS FITTED.   (X)						1	L	7	1 	3O	3	O	 	1A15    	1E15	5	C	P6EA	 
2000082100104	20000821	00104	CE  	2000	8	21	AU000513         	1	20000703	G	2710	AN443A	BOLT            	CESSNA      		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	AILERON CONTROL	LOOSE           	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					15079333					(AUS) AILERON PULLEY PN S378-4 TO CENTER CONSOLE ATTACHMENT BOLT HAD THE NUT MISSING AND THE INCORRECT WASHER SPACING UN	DER THE PULLEY GUARDS.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000082100105	20000821	00105	SO  	2000	8	21	AU000514         	1	20000621	G	3213	4550406	AXLE            	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 					317305064					(AUS) MAIN LANDING GEAR STRUT AXLE CRACKED.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011100561	20010111	00561	NM  	2001	1	11	AU000515         	1	20000613	G	2761	654494710	HOUSING         	BOEING      	65448517    	BOEING	737   	737377      	       	NM  										DRAG CONTROL ACT	CRACKED         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					4392A303103S					(AUS) LT INBOARD GROUND SPOILER OUTBOARD ACTUATOR HOUSING CRACKED.						2	L	7	2 	4F			RT	A16WE   					 
2001011100588	20010111	00588	NM  	2001	1	11	AU000516         	1	20000604	G	2760	285T0012116	CONTROLLER      			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					DRAG CONTROL SYS	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) LT WING NR 3 SPOILER VIBRATING UP TO 52.8MM (2IN) FROM THE SELECTED POSITION. WORKSHOP INVESTIGATION FOUND THE SPO	ILER CONTROL MODULE FAULTY.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011100594	20010111	00594	NM  	2001	1	11	AU000517         	1	20000527	G	5320	253T31164	WEB             			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) PARK BRAKE INPUT CRANK ASSEMBLY SUPPORT WEB CRACKED. SUSPECTPARKING BRAKE MECHANISM INCORRECTLY RIGGED CAUSING FLE	XING OF THE WEB.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011100631	20010111	00631		2001	1	11	AU000518         	4	20000616	G	2565		SLIDE           			BOEING	747   	747438      	       	NM  										PAX DOOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 LT SLIDERAFT MOORING LINE TANGLED WITH ASPIRATOR.						2	L	7	4 	4F			RT	A20WE   					 
2001011100282	20010111	00282	NM  	2001	1	11	AU000519         	1	20000618	G	3397		WIRE            			BOEING	747   	747338      	       	NM  										CABIN	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) SIDEWALL LIGHTING SYSTEM TOMBSTONE AT POSITION 40A SMOKING FROM POWER WIRE.						2	L	7	2 	4F			RT	A20WE   					 
2001011106203	20010111	06203		2001	1	11	AU000520         	4	20000618	G	2565	7A146914	SLIDE           			BOEING	747   	747438      	       	NM  										PAX DOOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR 5 RT ESCAPE SLIDE INFLATED WITH DOOR CLOSED AND LOCKED. SAFETY PIN STILL IN POSITION.						2	L	7	4 	4F			RT	A20WE   					 
2001011106204	20010111	06204	NE  	2001	1	11	AU000521         	2	20000528	G	7510	2351A000	VALVE           	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE ANTI-ICE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			17783		A8713381					(AUS) NR 2 ENGINE ANTI-ICE VALVE FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2000080700169	20000807	00169	SW  	2000	8	7	AU000523         	1	20000619	G	6220	2060111221	BOLT            	BELL        	206011100021	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR HEAD	WRONG PART      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1309 		JILM1679					(AUS) MAIN ROTOR HUB LATCH BOLTS HAD UNKNOWN HISTORY AND WERE REPLACED. THE LATCH BOLTS WERE SERIAL NUMBERED FOR USE ON 	BELL 206L TYPE AIRCRAFT AND HAVE A 1200 HOUR LIFE.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011100283	20010111	00283	EU  	2001	1	11	AU000524         	1	20000630	G	2612	2HK163	FIRE LOOP       			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FIRE DETECTION	WORN            	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE FIRE WIRE CHAFED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000082100001	20000821	00001	CE  	2000	8	21	AU000525         	1	20000701	G	3233	99101399	ACTUATOR        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	LANDING GEAR ACT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 					994					(AUS) NOSE LANDING GEAR ACTUATOR FAULTY.  SUSPECT WORN DOWNLATCH PINS.  (X)						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2001011100342	20010111	00342	NE  	2001	1	11	AU000526         	3	20000704	G	6197		WIRE            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	PROP INDICATOR	BROKEN          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 							PLE106132	GP148		(AUS) LT PROPELLER INDICATION SYSTEM WIRE BROKEN.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2001011106205	20010111	06205	EU  	2001	1	11	AU000527         	1	20000704	G	3260	A7872200	SPRING          			FOKKER	F28   	F28MK0100   	4990807	EU  										MLG	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOOR FORWARD UPLOCK PROXIMITY SENSOR RETURNSPRING BROKEN.						2	L	7	2 	4F			RT	        					 
2001011106206	20010111	06206	WP  	2001	1	11	AU000528         	2	20000630	G	7210	3583605	BOLT            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RT ENGINE	MISSING         	W				K	 	 	 	NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			1036 				P66277			(AUS) RT ENGINE PROPELLER SHAFT AFT ROLLER BEARING OUTER RACE FLANGED JOURNAL RETAINING BOLT FELL OUT AND WAS FOUND AT T	HE BOTTOM OFTHE ACCESSORY GEARBOX. THE OTHER TWO RETAINING BOLTS WERE FOUND TO BE FINGER TIGHT ONLY.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2000082100002	20000821	00002	EA  	2000	8	21	AU000529         	2	20000521	G	8520	74309	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 			835  				L80576AA			(AUS) ENGINE NR 1 CONNECTING ROD BEARING SPINNING.  METAL CONTAMINATION OF ENGINE OIL SYSTEM.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000082100158	20000821	00158	CE  	2000	8	21	AU000530         	1	20000709	G	5311		FRAME           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME NR 207 CRACKED ON LEFT SIDE.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000082100003	20000821	00003	SO  	2000	8	21	AU000531         	1	20000407	G	5230		SEAL            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					CARGO/BAGGAGE DR	LEAKING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) REAR BAGGAGE DOOR SEAL LEAKING.  INVESTIGATION COULD FIND NO FAULT ALTHOUGH MOISTURE WAS FOUND IN THE SEAL INFLATI	ON SYSTEM.  SUSPECT MOISTURE IN DOOR SEAL AIR SUPPLY LINES FROZE AT ALTITUDE.  (X)					2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2000081700072	20000817	00072	CE  	2000	8	17	AU000532         	1	20000711	G	5311	10112002117	FRAME           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FUSELAGE FRAME NR 207 CRACKED.  LEFT AND RIGHT STIFFENER PN 101-120021-17 AND PN 101-120021-18 ALSO CRACKED. 	 (X)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000081700073	20000817	00073	CE  	2000	8	17	AU000533         	1	20000612	G	3213	MS20392IC53	PIN             		76          	BEECH 	76    	76          	1153005	CE  										MLG	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR FORK CLEVIS PIN SHEARED.  (X)						1	L	7	2 	3O			 	A29CE   					 
2000081700074	20000817	00074	SO  	2000	8	17	AU000534         	1	20000710	G	5743	95299	STUD            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	WING, LANDING GR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT MAIN LANDING GEAR SIDE BRACE STUDS CRACKED.  FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AD/PA28/	91.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2001011106208	20010111	06208	SO  	2001	1	11	AU000535         	1	20000709	G	3260	12041127001	PROXIMITY SWITCH			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					MLG	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR POSITION PROXIMITY SWITCH SUSPECT FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2001011106209	20010111	06209	EU  	2001	1	11	AU000536         	2	20000619	G	7260	DRG152866	BEARING         			FOKKER	F27   	F27MK600    	4990706	EU  	RROYCE	DART  	DART5327    	54509	EU  	ROTOL	R4304	R1934304    	EU  	ENGINE GEARBOX	FAILED          	W				A	 	 	 	UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			12888							(AUS) RT ENGINE ACCESSORY GEARBOX INPUT BEARING FAILED ALLOWING OIL TOLEAK OUT OF CASE.						2	H	7	2 	4T	4	T	 	A817    	E297	6	C	P899	 
2000080700170	20000807	00170	GL  	2000	8	7	AU000537         	2	20000630	G	7250	23062750	HEAT SHIELD     	ALLSN       		HUGHES	369   	369E        	4470707	WP  	ALLSN 	25OC  	250C20R     	 	GL  					TURBINE SECTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							CAE295280			(AUS) ENGINE FIRST STAGE NOZZLE HEAT SHIELD CRACKED.  FOUND DURING INSPECTION IAW ALERT BULLETIN CEBA-72-4075.  (X)						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000080700171	20000807	00171	NE  	2000	8	7	AU000539         	1	20000521	G	6210	7615009000045	SPAR            	SKRSKY      	7615009000  	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR BLADE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					A08600119					(AUS) MAIN ROTOR BLADE SPAR CRACKED FROM OUTBOARD LOWER FORWARD BLADE ATTACHMENT BOLT HOLE.  LENGTH OF VISIBLE PORTION O	F CRACK APPROXIMATELY 44.45 MM (1.75 INCHES).  FOUND DURING INSPECTION IAW AD/S76/16 AMDT2.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2000081700075	20000817	00075	CE  	2000	8	17	AU000540         	1	20000711	G	5342	04311481	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	STABILIZER ATTAC	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIN ATTACHMENT BRACKET CRACKED.  (X)						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001011106210	20010111	06210	NM  	2001	1	11	AU000541         	1	20000713	G	2760		MOUNT           			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					DRAG CONTROL	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 SPOILER ACTUATOR MOUNT ASSEMBLY INBOARD LOWER MOUNT BOLT HOLE LUG CRACKED AND OUTBOARD LOWER MOUNT BOLT HOLE 	LUG BROKEN.INBOARD LOWER MOUNT BOLT SHEARED.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000081700076	20000817	00076	SO  	2000	8	17	AU000542         	1	20000714	G	2434	A3985T	HOUSING         	CHRYSLER    	00638       	PIPER 	PA28  	PA28161     	7102803	SO  										DC GENERATOR-ALT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					6110120					(AUS) ALTENATOR REAR HOUSING CRACKED AT ATTACHMENT POINTS.						1	L	7	1 	3O			 	2A13    					 
2000081700077	20000817	00077	EU  	2000	8	17	AU000543         	1	20000709	G	5742		RIVET           			PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING, NAC/PYLON	MISALIGNED      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							1L1819751A2L			(AUS) LEFT OUTBOARD ENGINE NACELLE COWL RIVET MISALIGNED TO SPAR CAP RIVETS BY APPROXIMATELY 3.175 MM (0.125 INCH).  FOU	ND DURING INSPECTION IAW AD/P68/46.  (X)					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2000081700078	20000817	00078	CE  	2000	8	17	AU000544         	1	20000612	G	3213	MS20392IC53	PIN             	BEECH       		BEECH 	76    	76          	1153005	CE  										MLG	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR SHOCK ABSORBER PN 105-384001-3 TO FORK PN 105-810021-9 ATTACHMENT PIN PN 105-810026-1 CLEVI	S PIN SHEARED ALLOWING ATTACHMENT PIN TO MIGRATE OUT.  (X)					1	L	7	2 	3O			 	A29CE   					 
2001011106212	20010111	06212	WP  	2001	1	11	AU000545         	2	20000630	G	7260	31028823	HOUSING         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ENGINE GEARBOX	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							P44207C			(AUS) ENGINE GEARBOX HOUSING CRACKED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001011106213	20010111	06213	NM  	2001	1	11	AU000546         	1	20000419	G	5312		BULKHEAD        			BOEING	737   	737377      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FORWARD PRESSURE BULKHEAD WEB CRACKED AT RIGHT BUTTOCK LINE 5.7 AND WATERLINE 8.3. FOUND DURING EDDY CURR	ENT INSPECTION.					2	L	7	2 	4F			RT	A16WE   					 
2001011106224	20010111	06224	NM  	2001	1	11	AU000547         	1	20000512	G	5730		SKIN            			BOEING	737   	737377      	       	NM  										LT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SKIN CONTAINED INTERGRANNULAR CORROSION IN AN AREAADJACENT TO ACCESS PANEL 7204L. CORROSION EXTENDED	 FROM THE EDGEOF THE PANEL CUTOUT IN TWO LOCATIONS FOR APPROXIMATELY 25MM (1IN).					2	L	7	2 	4F			RT	A16WE   					 
2001011106226	20010111	06226	NM  	2001	1	11	AU000548         	1	20000717	G	2910	S271T12161883	HEAT EXCHANGER  			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HYD SYSTEM	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HYDRAULIC SYSTEM HEAT EXCHANGER CORE FAILED ALLOWING THE CONTENTS OF THE RT HYDRAULIC SYSTEM TO DRAIN INTO THE 	RT FUEL TANK.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011106227	20010111	06227	NM  	2001	1	11	AU000549         	1	20000710	G	2710		PIN             			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					AILERON CONTROL	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT INBOARD AILERON LOWER HALF PCA SUMMING LEVER/INPUT ROD PIVOT LINK PIN MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011106229	20010111	06229	NM  	2001	1	11	AU000550         	1	20000711	G	5714		DRAIN LINE      			BOEING	747   	747438      	       	NM  										WING CENTER BOX	BLOCKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTRE SECTION CAVITY DRAIN BLOCKED BY WAX BUILDUP. LARGEAMOUNTS OF DEBRIS FOUND IN AREA. FOUND DURING INSPEC	TION IAWAD/B747/71.					2	L	7	4 	4F			RT	A20WE   					 
2001011106231	20010111	06231	NM  	2001	1	11	AU000551         	1	20000711	G	3040	205319EO39LL4TL	POWER CABLE     			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					WINDSHIELD	BROKEN          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) WINDOW R2 POWER CABLE BROKEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011106233	20010111	06233	NM  	2001	1	11	AU000552         	1	20000706	G	2450		CIRCUIT BREAKER 			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					AC POWER DIST	DIRTY           	W				O	 	 	 	OTHER                   				B		 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) P6-3 CIRCUIT BREAKER PANEL FOD. INSPECTION FOUND TWO SPRING WASHERS ADHERING TO A LABEL BETWEEN TWO CIRCUIT BREAKE	RS CAUSINGTHE CIRCUIT BREAKERS TO POP.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011106234	20010111	06234	NM  	2001	1	11	AU000553         	1	20000705	G	5753	6SB1754011	FITTING         			BOEING	747   	747338      	       	NM  										TE FLAP	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FOREFLAP ATTACHMENT FITTING LOCATED AT NR 5 SEQUENCE CARRIAGE BROKEN THROUGH THE LOWER BEARING LUG A	LLOWING FOREFLAP TO SEPARATE FROM THE SEQUENCE CARRIAGE. DAMAGE TO FOREFLAP TRACKS, MIDFLAP OUTBOARD UPPER LEADING EDGE 	FIBREGLASS PANEL, INBOARD UPPER TRAILING EDGE PANEL STAY ROD AND UPPER AND LOWER ATTACHMENT POINTS OF THAT STAY ROD.				2	L	7	2 	4F			RT	A20WE   					 
2001011106235	20010111	06235	NM  	2001	1	11	AU000554         	1	20000703	G	3242	26056623316B	PAD             			BOEING	747   	747338      	       	NM  										BRAKE	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NR 9 MAINWHEEL BRAKE PAD ADRIFT AND JAMMING ROTORS CAUSING THE BRAKE TO SEIZE. NR 9 MAINWHEEL TYRE BLOWN.						2	L	7	2 	4F			RT	A20WE   					 
2000081700079	20000817	00079	SW  	2000	8	17	AU000555         	1	20000229	G	3230	AN415	BOLT            			GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	LANDING GEAR RET	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION RAM TO NOSE LANDING GEAR STRUT SEPARATED DUE TO BOLT, NUT, WASHER AND SPLIT PIN SECUR	ING THE TWO ITEMS COMING LOOSE.					1	L	7	1 	3O	3	O	 	A12SO   	1E4	5	C	P920	 
2001011106244	20010111	06244	SO  	2001	1	11	AU000556         	1	20000713	G	5343	4A112222	BRACKET         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR SUPPORT BRACKET CRACKED. CRACK LENGTH28.5MM (1.125IN). FOUND DURING INSPECTION IAW SB 1	10-53-0027. CRACK COULD BE SEEN VISUALLY.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2000081700080	20000817	00080	EA  	2000	8	17	AU000557         	1	20000707	G	5720	C6WM140031	STRUT           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING MISC	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING STRUT CORRODED IN AN AREA LOCATED APPROXIMATELY 355.6 MM (14 INCHES) OUTBOARD FROM THE LOWER ATTACHMENT 	FITTING ON THE AFT WEB.  FOUND DURING INSPECTION IAW AD/DHC6/58 AND SB 6-474.  (X)					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2001011106246	20010111	06246	WP  	2001	1	11	AU000558         	2	20000701	G	7250	P90018	SHAFT           			STBROS	SC7   	SC7SERIES3  	8100512	EU  	GARRTT	TPE331	TPE3312201A 	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TURBINE	FAILED          	W				E		 	 	ENGINE SHUTDOWN         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			AU	S 							P90018			(AUS) RT ENGINE TURBINE SHAFT FAILED. SECOND STAGE AND THIRD STAGETURBINE WHEELS, REAR BEARING SUPPORT AND SCAVENGE PUMP	 MISSING.					1	H	7	2 	3T	4	T	NT	A15EU   	E3WE	6	C	P15EA	 
2000082100016	20000821	00016	EU  	2000	8	21	AU000559         	1	20000704	G	7120		MOUNT           	PWA         		REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	ENGINE MOUNT SEC	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE MOUNT CRACKED.  FOUND DURING MAGNETIC PARTICLE INSPECTION.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001011106247	20010111	06247	EA  	2001	1	11	AU000560         	1	20000505	G	2720	CF3985A	PIN             			DHAV  	DHC3  	DHC3        	2800202	EA  										RUDDER CONTROL S	BROKEN          	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RUDDER CONTROL SYSTEM PIVOT PIN CRACKED AT WELD AND THEN BROKEOFF.						1	H	7	1 	3R			 	A815    					 
2000082100022	20000821	00022	CE  	2000	8	21	AU000561         	1	20000607	G	2750	C3B18	WIRE            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	TE FLAP CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP POWER WIRE BROKEN IN AREA APPROXIMATELY 100 MM( 4 INCHES) FROM THE FLAP PRESELECT SWITCHES.  WI	RE IS ONE IN A BUNDLE OF FIVE WIRES WHICH FLEXES WHEN THE FLAPS MOVE.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000082100023	20000821	00023	SO  	2000	8	21	AU000562         	2	20000617	G	8520		CRANKSHAFT      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							814840R			(AUS) CRANKSHAFT DEFECTIVE. FOUND DURING INSPECTION AND CORE SAMPLING IAW AD/CON/80.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2000082100024	20000821	00024	EA  	2000	8	21	AU000563         	1	20000703	G	2612	1734362	FIRE DETECTOR   			DHAV  	DHC6  	DHC6200     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FIRE DETECTION	FAULTY          	W				K	 	 	 	NONE                    				B	N	 	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             		CL	CLIMB          	1			AU	S 					8552					(AUS) RIGHT ENGINE GEARBOX FIRE DETECTOR FAULTY.  LOW RESISTANCE.						1	H	7	2 	3T	3	T	 	A9EA    	E4EA	6	C	P15EA	 
2000082100025	20000821	00025	EA  	2000	8	21	AU000564         	1	20000515	G	5413	C6W151248	LONGERON        			DHAV  	DHC6  	DHC6300     	2802606	EA  										LONGERON/STR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE NACELLE RIGHT OUTBOARD LONGERON CRACKED IN AN AREA APPROXIMATELY 254 MM (10 INCHES) AFT OF THE ENGINE MOUNT	 FITTING.  CRACK LENGTH APPROXIMATELY 57.15 MM (2.25 INCHES).  FOUND DURING INSPECTION IAW AD/DHC6/51.4 (DHC6 SB 6/509).					1	H	7	2 	3T			RT	A9EA    					 
2000080700172	20000807	00172	SW  	2000	8	7	AU000565         	1	20000701	G	6230	206010451005	RING            	BELL        		BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR MAST	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					RE103					(AUS) MAIN ROTOR SWASHPLATE INNER RING CRACKED ON RIGHT INPUT ARM LOCATED APPROXIMATELY 5 MM (0.2 INCH) BEHIND THE SPHER	ICAL BEARING.  (X)					1	G	7	1 	3U			 	H2SW    					 
2000082100026	20000821	00026	EA  	2000	8	21	AU000566         	1	20000607	G	3250	7116111	COLLAR          	HEROUX      	713005      	DHAV  	DHC6  	DHC6300     	2802606	EA  										LANDING GEAR STE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					H174					(AUS) NOSE LANDING GEAR STEERING COLLAR CRACKED IN ATTACHMENT BLOCK RADIUS.  FOUND USING VISUAL INSPECTION AND CONFIRMED	 USING ULTRASONIC INSPECTION.					1	H	7	2 	3T			RT	A9EA    					 
2000091300010	20000913	00010	CE  	2000	9	13	AU000567         	1	20000612	G	5740	0411129	FITTING         			CESSNA	182   	182         	2072702	CE  										WING ATTACH FIT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ABD RIGHT WING ATTACHMENT BLOCKS CONTAIN EXFOLIATION CORROSION.						1	H	7	1 	3O			NT	3A13    					 
2000091400037	20000914	00037	EA  	2000	9	14	AU000568         	2	20000709	G	8500		ENGINE          	LYC         		CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGIN	FAILED          	W				K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			AU	S 							L2716851A			(AUS) ENGINE FAILED ON TAKEOFF RESULTING IN A FORCED LANDING. AIRCRAFT DAMAGED. GROUND RUNS ON ENGINE COULD NOT REPLICAT	E FAULT AND ENGINE RAN OK.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001011106248	20010111	06248	NM  	2001	1	11	AU000569         	1	20000713	G	2910	82950010247	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE CONTAINED A SMALL PIN HOLE LEAK ON THE INSIDE OF THE BEND RADIUS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000080700173	20000807	00173	NE  	2000	8	7	AU000570         	2	20000708	G	7323	430121204	GOVERNOR        	LYC         	430121204   	BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TURBINE GOVERNOR	FAILED          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					37422		LE48171			(AUS) RIGHT ENGINE POWER TURBINE GOVERNOR INTERNAL FAILURE.  GOVERNOR DRIVE SPLINE SHEARED WITH CORRESPONDING ENGINE OVE	RSPEED.  (X)					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2001011106250	20010111	06250	EU  	2001	1	11	AU000571         	1	20000714	G	7603		POWER LEVER     			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	LEFT	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) LH POWER LEVER OUT OF ADJUSTMENT AND LAGGING BEHIND THE RH POWERLEVER.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2000080700174	20000807	00174	GL  	2000	8	7	AU000572         	2	20000708	G	7320	68711461	PIPE            	ALLSN       		BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROLLING	LOOSE           	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 							CAE832194			(AUS) PR FUEL PIPE BETWEEN THE FUEL CONTROL UNIT AND THE POWER TURBINEGOVERNOR HAD A LOOSE B'''' NUT.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011106253	20010111	06253	SO  	2001	1	11	AU000573         	1	20000720	G	2731		WHEEL           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ELEVATOR TAB	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) RT TRIM WHEEL OUT OF ADJUSTMENT. SUSPECT INCORRECT FITMENT.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001011106254	20010111	06254	NE  	2001	1	11	AU000574         	2	20000718	G	7260	AS3209241	O-RING          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	CUT             	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			50   				120427			(AUS) RH ENGINE GENERATOR MOUNT O' RING SEAL CUT AND LEAKING. AC GENERATOR CONTAMINATED BY OIL. SUSPECT O' RING SEAL DAM	AGEDDURING INSTALLATION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011106269	20010111	06269	EU  	2001	1	11	AU000575         	1	20000719	G	5610	1379628C402	WINDSHIELD      			BAG   	JETSTM	JETSTM3201  	1500217	EU  						ROTOL	R333	R333482F12  	GL  	COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WINDSHIELD CRACKED AND DELAMINATING.						2	L	7	2 	4T			RT	A56EU   		6	C	P61GL	 
2001011106270	20010111	06270	NE  	2001	1	11	AU000576         	2	20000719	G	7210	PCE115319	GEARBOX         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					ENGINE	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							PCE115319			(AUS) RT ENGINE REDUCTION GEARBOX CHIP DETECTOR AND SCAVENGE FILTER CONTAMINATED WITH METAL.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000091400038	20000914	00038	CE  	2000	9	14	AU000577         	1	20000119	G	5540	12138871	SUPPORT BRACKET 	CESSNA      	207         	CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520G    	17040	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					00340		570008	920058		(AUS) RUDDER BAR SUPPORT ASSEMBLIES PN 1213887-1 (LEFT) AND PNO1213887-2 (RIGHT) CRACKED THROUGH BOLT HOLES.						1	H	7	1 	3O	3	O	 	A16CE   	E8CE	5	C	P47GL	 
2001011106271	20010111	06271	EU  	2001	1	11	AU000578         	1	20000630	G	2131		CONTROLLER      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					CABIN PRESSURE	BLOCKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) NO2 CABIN PRESSURE CONTROLLER PC PORT HAD A BLANKING CAP FITTED PREVENTING THE CONTROLLER FROM SENSING CORRECT CAB	IN PRESSURE.THE BLANKING CAP PNO CD-3 HAD BEEN FITTED TO THE PORT DURINGTROUBLESHOOTING AND HAD NOT BEEN REMOVED. PERSON	NEL/MAINTENANCE ERROR.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011106272	20010111	06272	NM  	2001	1	11	AU000579         	1	20000707	G	3251	3821128101	PIN             	PARKER      	3790037106  	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					STEERING UNIT	SHEARED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					00025ANSSN32					(AUS) NOSE LANDING GEAR STEERING SYSTEM RT METERING VALVE INDEXING PINSHEARED. WORKSHOP FOUND EVIDENCE OF HEAVY CORROSIO	N AROUND THEPIN LOCATION HOLE.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000091400039	20000914	00039	SO  	2000	9	14	AU000580         	2	20000721	G	8520	606507	CRANKCASE       	CONT        		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 			925  				606507			(AUS) ENGINE CRANKCASE CRACKED ADJACENT TO UPPER SPLIT LINE. FURTHER INVESTIGATION FOUND THE CAMSHAFT FORWARD JOURNAL CR	ACKED THROUGH THE OIL FEED HOLE TO THE JOURNAL  APPEARED BLOCKED.  SUBMITTER SUSPECTED HOLE HAD BEEN WELDED CLOSED.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000091400040	20000914	00040	EA  	2000	9	14	AU000582         	2	20000720	G	8550	LW13388	GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FRACTURED       	W				K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 			924  				6540761A	DJ11605A		(AUS) ENGINE OIL FILTER ADAPTER GASKET LEAKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011106273	20010111	06273	CE  	2001	1	11	AU000583         	1	20000613	G	2750		FLAP            			BEECH 	1900  	1900D       	1154162	CE  										TRAILING EDGE	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) FLAPS OUT OF ADJUSTMENT.						2	L	7	2 	4T			RT	A24CE   					 
2001011106274	20010111	06274	NE  	2001	1	11	AU000584         	3	20000719	G	6110	HJ376	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PITCH CHANGE	OUT OF RIG      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 								HJ376		(AUS) RT PROPELLER REVERSE STOP INCORRECTLY SET. PITCH CHANGE FORK CRACKED.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE	 
2001011106275	20010111	06275	NM  	2001	1	11	AU000585         	1	20000616	G	2730	85520271003	STOP            			DHAV  	DHC8  	DHC8102     	2809003	NM  										ELEVATOR	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH ELEVATOR STOP MISSING DUE TO DETERIORATION OF THE RUBBER.ELEVATOR TRAILING EDGE DAMAGED. AREA OF DAMAGE 100MM B	Y 100MM (4IN BY 4IN).					2	H	7	2 	4T			RT	A13NM   					 
2001011106278	20010111	06278	EU  	2001	1	11	AU000586         	1	20000614	G	2160	342D0200000	THERMOSTAT      			AIRBUS	320   	A320211     	3930320	EU  										ENVIRONMENT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 			27930		381					(AUS) DURING CLIMB THE NR 2 BLEED OVERHEATED. SUSEQUENTLY, THE NO1 BLEED ALSO OVERHEATED,  CABIN COULD NOT BE PRESSURISE	D. STRIP REPORT HIGH LIGHTED THAT THE NR 1 FAN AIR VALVE AND THE NR 2 TEMPERATURE CONTROL THERMOSTAT WERE BOTH FAULTY.					2	L	7	2 	4F			RT	A28NM   					 
2000091400041	20000914	00041	CE  	2000	9	14	AU000587         	1	20000707	G	7810		BOLT            	CONT        		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  					ENGINE COLLECTOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							245704R			(AUS) ENGINE EXHAUST BOLTS BROKEN, ALLOWING EXHAUST GASSES TO INITIATE BURNING A HOLE IN THE AIRFRAME.						1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2000091400042	20000914	00042	SO  	2000	9	14	AU000588         	2	20000611	G	8500		ENGINE          	CONT        		CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					ENGINE	MAKING METAL    	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			TO	TAKEOFF        	1			AU	S 							14296			(AUS) DURING CRUISE, A DROP IN INDICATED OIL PRESSURE AND A RISE IN OIL TEMPERATURE WAS OBSERVED.  A POST INSPECTION FOU	ND THE OIL FILTER CLOGGED WITH ALUMINIUM AND WHITE BEARING METAL CONTAMINATION.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2000112800059	20001128	00059	NE  	2000	11	28	AU000589         	2	20000713	G	7230		COMPRESSOR      	PWA         							PWA   	JT9   	JT9D7R4E    	52054	NE  					ENGINE	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							716931			(AUS) HP COMPRESSOR DISCS (STG 8, 10, 12 AND 14) FOUND WITH SILVER PLATE CONTAMINATION, CAUSED BY USE OF SILVER PLATED N	UTS FITTED AT TIE ROD LOCATIONS.										4	F			E3NE				 
2000112800060	20001128	00060	NE  	2000	11	28	AU000590         	2	20000713	G	7230	716913	COMPRESSOR      	PWA         							PWA   	JT9   	JT9D7R4E    	52054	NE  					TURBINE	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					716913					(AUS) HP COMPRESSOR DISCS (STG. 8, 10, 12 AND 14) FOUND WITH SILVER PLATE CONTAMINATION CAUSED BY USE OF SILVER PLATED N	UTS FITTED AT TIE ROD LOCATIONS.										4	F			E3NE				 
2001011106280	20010111	06280	NM  	2001	1	11	AU000591         	1	20000712	G	3250	3790037U	PIN             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NLG STEERING	SHEARED         	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 					SY					(AUS) DURING AIRCRAFT TAXI (TURNING) INTO BAY, THE NOSE WHEEL STEERINGWENT TO FULL LOCK UNCOMMANDED.INVESTIGATION FOUND 	THAT THE LOCATOR PIN FOR THE RT STEERING ACTUATOR ON THE RT SWIVEL VALVE HAD SHEARED.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011106300	20010111	06300	NM  	2001	1	11	AU000592         	1	20000704	G	2821		FILTER          			DHAV  	DHC8  	DHC8202     	2809007	NM  										FUEL SYSTEM	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) AT CRUISE THE NR 1 FUEL BYPASS LIGHT ILLUMINATED. DURING POST INVESTIGATION BOTH HP/LP FUEL FILTERS WERE INSPECTED	 AND REPLACED - FILTERS INDICATED SOME SLIGHT SIGNS OF FUNGUS. DURING NEXTFLIGHT THE SAME PROBLEM RE-OCCURRED. BOTH FILT	ERS WERE CHANGE DONCE AGAIN - AIRCRAFT SERVICEABLE.				2	H	7	2 	4T			RT	A13NM   					 
2000081700081	20000817	00081	SO  	2000	8	17	AU000594         	1	20000717	G	2823	12444LH12424	SEAL            	SCOTT       	236405      	PIPER 	PA34  	PA34200T    	7103406	SO  										FUEL SELECTOR	MELTED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					12444LH12424					(AUS) DURING SCHEDULED MAINTENANCE, THE FUEL COULD NOT BE TURNED OFF FULLY AND FUEL WAS CROSS-FEEDING.  THE SELECTOR VAL	VES WERE REMOVED AND FOUND THAT THE SEALS HAD DISSOLVED.  SUBMITTER SUSPECTED INCORRECT SEALS OR INCORRECT SOLVENT USED 	IN COMPLYING WITH AD/GEN/81.				1	L	7	2 	3O			 	A7SO    					 
2001011100345	20010111	00345	EU  	2001	1	11	AU000595         	1	20000721	G	3297	S320020APG	WIRE            			BAC   	146   	146200A     	1500266	EU  										MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRST POWER UP, AIRCRAFT WAS INDICATING WEIGHT ON WHEELS SENSORS IN THE 'AIR' MODE.INVESTIGATION FOUND THE LHS INB	OARD WEIGHT ON WHEELS PROXIMITY SENSOR AND HARNESS FAULTY.  BOTH WERE REPLACED,HOWEVER, THE AIRCRAFT WAS STILL IN 'AIR' 	 MODE. FURTHER INVESTIGATION FOUND THE BLUE WIRE OF GA033 (TRIPLE SHIELD) HAD LEAKAGE TO THE SHIELD CAUSING PROXIMITY SE	NSOR GA40 PCB NOT TO OPERATE.			2	H	7	4 	4F			 	A49EU   					 
2001011106301	20010111	06301	NM  	2001	1	11	AU000596         	1	20000227	G	7830	000518ANSSN30	NUT             			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					THRUST REVERSER	UNDERTORQUED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING PREFLIGHT INSPECTION, THE NR 4 BLOCKER DOOR WAS FOUND NOT FULLY STOWED ON THE NR 1 ENGINE I/B REVERSER COWL	. INVESTIGATION THEN FOUND THE BLOCKER DOORS LOWER HINGE BOLT WAS MISSING ANDTHE UPPER BOLT WAS LOOSE.  FURTHER INVESTIG	ATION FOUNDTHE NR 2  AND NR 3 BLOCKER DOORS HAD LOOSE NUTS ON THE LOWER HINGE BOLTS AND MISSING NUTS AND WASHERS ON THE 	UPPER HINGE BOLTS. SUSPECT THE  FASTENERS WERE IMPROPERLY TORQUED AT LAST BLOCKER DOOR REPLACEMENT. MAINTENANCE/PERSONNE	L ERROR.		2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001011106302	20010111	06302	NM  	2001	1	11	AU000597         	1	20000401	G	5310		STRUCTURE       			BOEING	737   	737377      	       	NM  										FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 2 CORROSION FOUND IN THE FUSELAGE STRUCTURE AS A RESULT OFAD/B737/52 AMDT 2.						2	L	7	2 	4F			RT	A16WE   					 
2001011106303	20010111	06303	NM  	2001	1	11	AU000598         	1	20000401	G	5310		STRUCTURE       			BOEING	737   	737377      	       	NM  										FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 2 CORROSION FOUND IN FUSELAGE STRUCTURE AS A RESULT OFAD/B737/52 AMDT 2.						2	L	7	2 	4F			RT	A16WE   					 
2001011106304	20010111	06304		2001	1	11	AU000599         	4	20000616	G	2565	7A146721	SLIDE           			BOEING	747   	747438      	       	NM  										PAX DOOR	MALFUNCTIONED   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING TEST, NR 1 LT SLIDE RAFT MOORING LINE TANGLED WITH THE ASPIRATOR. INVESTIGATION FOUND THAT THE SLIDE MOORIN	G LINE WAS NOT ATTACHED TO THE GIRT BAR. PERSONNEL/MAINTENANCE ERROR.					2	L	7	4 	4F			RT	A20WE   					 
2001011106305	20010111	06305		2001	1	11	AU000600         	4	20000715	G	2565	101630201	SLIDE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PAX DOOR	WRONG PART      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ON REMOVAL OF THE LT 'OFF' WING SLIDE, IT WAS DISCOVERED THAT THE SLIDE TYPE SHOULD NOT HAVE BEEN FITTED TO A -300	 SERIES AIRCRAFT- A SINGLE LANE SLIDE WAS FITTED IN LIEU OF A DUAL LANE SLIDE. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2000081700082	20000817	00082	EA  	2000	8	17	AU000601         	1	20000313	G	5210	B6MA50	DOOR            			DHAV  	DHC6  	DHC6300     	2802606	EA  										PASSENGER/CREW D	MALFUNCTIONED   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 					B070					(AUS) DURING FLIGHT, THE CABIN AIRSTAIR DOOR OPENED.  SUBMITER SUSPECTED REAR SEAT PASSENGER MAY HAVE ACCIDENTLY BUMPED 	THE DOOR HANDLE WITH KNEE.					1	H	7	2 	3T			RT	A9EA    					 
2000081700083	20000817	00083	EA  	2000	8	17	AU000602         	1	20000606	G	5413	C6W151248	LONGERON        			DHAV  	DHC6  	DHC6300     	2802606	EA  										LONGERON/STR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) A CRACK APPROXIMATELY 44.5 MM (1.75 INCHES) WAS FOUND IN THE RT OUTBOARD ENGINE NACELLE LONGERON, APPROXIMATELY 24	 CM (9.5 INCHES) AFT OF THE ENGINE MOUNT FITTING.  THE CRACK ORIGINATED FROM BENEATH STRAP P/N C6WM1712-27 WHICH WAS FIT	TED IAW DHC MOD 6/1655.				1	H	7	2 	3T			RT	A9EA    					 
2000080700175	20000807	00175	EU  	2000	8	7	AU000603         	1	20000520	G	6410	355A12003108	BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR BLADE	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			382  		2386					(AUS) AFTER APPROXIMATELY A ONE HOUR FLIGHT IN HEAVY RAIN, THE PILOT DISCOVERED THE DELAMINATION ON ONE TAIL BLADE HAD P	ROPAGATED TO APPROXIMATELY 3.5CM (1.37 INCH).  PROBLEM WAS INITIALLY FOUND ABOUT 18 HOURS EARLIER,  HOWEVER, THE DELAMIN	ATION WAS WITHIN LIMITS AND REPAIRED (SEALED) IAW MRR.				1	G	7	1 	3U			NC	H9EU    					 
2000081700084	20000817	00084	CE  	2000	8	17	AU000604         	1	20000226	G	3230		LANDING GEAR    			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520B    	17040	SO  					MLG	COLLAPSED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 							MCCOWEN3AF32			(AUS) PILOT REPORTED THAT THE LANDING GEAR RETRACTED BY ITSELF.  POST-RETRACTION/EXTENSION TESTS CARRIED OUT WITHOUT INC	IDENT.  AS A PRECAUTION, THE LG MOTOR WAS REPLACED.  SWITCHES, SETTINGS AND LIGHTS WERE CHECKED - NO DEFECTS FOUND.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2000081700085	20000817	00085	GL  	2000	8	17	AU000605         	3	20000306	G	6111	90DFA10	BLADE           			CESSNA	206   	TU206*      	       	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER BLADE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1330 					861329		(AUS) PROPELLER WOULD NOT RETURN TO FINE PITCH FROM COURSE PITCH AT ENGINE SPEEDS BELOW 2200 RPM AND WOULD REMAIN IN COU	RSE PITCH AFTER FINE PITCH SELECTED.DURING PROPELLER DISASSEMBLY, THE NR 3 BLADE WAS FOUND CRACKED AT THE BLADE ROOT ARO	UND APPROXIMATELY HALF THE BLADE''S CIRCUMFERENCE.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P47GL	 
2000081700086	20000817	00086	SO  	2000	8	17	AU000606         	1	20000719	G	5553		NUT             			PIPER 	PA32  	PA32RT300   	7103215	SO  										VERT STAB ATTACH	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ANCHOR NUT FOR RIGHT FORWARD FIN ATTACH BOLT SPLIT.						1	L	7	1 	3O			 	A3SO    					 
2000081700087	20000817	00087	GL  	2000	8	17	AU000607         	1	20000706	G	5720		SPAR            			AMTR  	F11   	JODELD11    	       	GL  										WING	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PORT WING SPAR FAILED IN COMPRESSION AT DIHEDRAL ''CRANK''.  REAR UPPER SPAR BOOM FAILED IN BOX SPAR AT TWO POINTS	:  VERTICAL PLY FACE OF BOX SPAR FAILED AT OUTER FAILURE, AND UPPER PLY FACE FAILED AT NEXT INBOARD RIB.					1	L	7	1 	3O			 	EXPA1L71					 
2001011106307	20010111	06307	EU  	2001	1	11	AU000608         	1	20000720	G	2730	602EN166B	SWITCH          			FOKKER	F28   	F28MK4000   	4990810	EU  										ELEVATOR	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				J		 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) ON APPLICATION OF TAKE-OFF POWER, THE WARNING HORN SOUNDED AND TAKE-OFF WAS ABORTED.  POST INVESTIGATION FOUND THE	 NR 2 ELEVATOR BYPASS MICROSWITCH WAS OPEN CIRCUIT.					2	L	7	2 	4F			RT	A20EU   					 
2000081700088	20000817	00088	EA  	2000	8	17	AU000609         	2	20000720	G	8530		BARREL          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	CYL	GLAZED          	W				K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 			202  				L280461A	DJ10751A		(AUS) PILOT REPORTED VIBRATION DURING ROTATION AND CLIMB.  GROUND INVESTIGATION FOUND EXCESSIVE OIL IN THE LEFT ENGINE''	S NR 3 CYLINDER.  CYLINDER WAS REMOVED AND FOUND WITH SEVERE GLAZING OF THE BORE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011106308	20010111	06308	NM  	2001	1	11	AU000610         	1	20000723	G	5330		SKIN            			DHAV  	DHC8  	DHC8102     	2809003	NM  										FUSELAGE	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIND BLEW CATERING CART INTO AIRCRAFT FUSELAGE, PUNCTURING A HOLE APPROXIMATELY 2CMS IN SIZE.						2	H	7	2 	4T			RT	A13NM   					 
2001011106310	20010111	06310	SW  	2001	1	11	AU000611         	1	20000710	G	2913		PUMP            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYD SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							P44125C			(AUS) PILOT REPORTED LOW HYDRAULIC PRESSURE. INVESTIGATION FOUND THE RT HYDRAULIC PUMP WAS DAMAGED. ON NEXT FLIGHT THE P	ILOT REPORTED THAT THE HYDRAULIC PRESSURE HAD INCREASED TO THE 'RED LINE'. THE POWER PACK WAS THEN REMOVED AS A RESULT O	F THECONTAMINATION FROM THE FAILED HYDRAULIC PUMP.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2000112800061	20001128	00061	EU  	2000	11	28	AU000612         	1	20000720	G	5552	NB310077	BRACKET         			BNORM 	BN2   	BN2A21      	1520221	EU  										ELEV/TAB ATTACH	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR BRACKET CRACKED ALONG THE BEND RADII OF ONE SIDE.						1	H	7	2 	3O			 	A17EU   					 
2001011106330	20010111	06330	NM  	2001	1	11	AU000613         	1	20000711	G	3246	300653	HUB             	BFGOODRICH  	31448       	DHAV  	DHC8  	DHC8102     	2809003	NM  										WHEEL	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					1933					(AUS) DURING A NOSE WHEEL TIRE CHANGE, FLAWS WERE OBSERVED UP TO A DEPTH OF 1.02MM (0.040IN) IN THE OUTER HUB FLANGE RAD	IUS OVER A 17.78CM (7IN) SPAN					2	H	7	2 	4T			RT	A13NM   					 
2001011106331	20010111	06331	EU  	2001	1	11	AU000614         	1	20000719	G	3020	SM15CXD4	RELAY           			SAAB  	SF340 	SF340A      	7850100	EU  										INTAKE ANTI ICE	BURNED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) AFTER TAKE-OFF WHEN ANTI-ICE WAS SELECTED 'ON', THE RH ENGINE INTAKE CAUTION LIGHT ILLUMINATED.  GROUND INVESTIGAT	ION FOUND THE RELAY WHICH CONTROLS AC POWER TO THE ELECTRICALLY HEATED ENGINE INTAKE DUCT IN A BURNT CONDITION.  IN ADDI	TION, THE CONTACTS ANDWIRING AT THE RELAY CONNECTOR WERE BURNT AND HAD TO BEREPLACED/REPAIRED.				2	L	7	2 	4T			RT	A52EU   					 
2000100300136	20001003	00136	EA  	2000	10	3	AU000615         	1	20000901	G	7722		TERMINAL        	PWA         		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A20      	52043	EA  					ENG EGT/TIT IND	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DURING CRUISE, THE ENGINE T5 INDICATOR FLUCTUATED BETWEEN 500 DEGREES CELSIUS AND 630 DEGREES CELSIUS.  INVESTIGAT	ION FOUND A DEFECTIVE WIRING JOINT AT THE ENGINE TERMINAL.  (X)					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2000100300137	20001003	00137	EA  	2000	10	3	AU000616         	1	20000901	G	5330		SKIN            			DHAV  	DHC6  	DHC6300     	2802606	EA  										FUSELAGE MAIN PL	WRINKLED        	W				K	 	 	 	NONE                    				E	C	 	VIBRATION/BUFFET          	F.O.D.                    		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR IMPACTED TWO EARTH MOUNDS ON LANDING.  GROUND INVESTIGATION FOUND SKIN RIPPLES AND LOOSE RIVETS 	IN THE LOWER FUSELAGE AREA AT STN 60. TWO LOWER STRINGER ANGLES WERE ALSO FOUND TO BE CRACKED.  (X)					1	H	7	2 	3T			RT	A9EA    					 
2000100300138	20001003	00138	EA  	2000	10	3	AU000617         	1	20000901	G	5610	C6SC10624	WINDSHIELD      			DHAV  	DHC6  	DHC6300     	2802606	EA  										FLIGHT COMPART	CRACKED         	W				K	 	 	 	NONE                    				C	 	 	F.O.D.                    			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) AIRCRAFT WAS PARKED (AWAITING DEPARTURE) BEHIND ANOTHER AIRCRAFT WHEN THE PILOT OF THE LEAD AIRCRAFT PERFORMED AN 	ENGINE POWER CHECK.  STONES WERE THROWN UP AND CRACKED THE RIGHT WINDSHIELD.  (X)					1	H	7	2 	3T			RT	A9EA    					 
2000092800094	20000928	00094	WP  	2000	9	28	AU000618         	1	20000901	G	2435	230322210	END BELL        	LEARSIEGLER 	23032027    	HUGHES	369   	369E        	4470707	WP  										STARTER/GEN	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					16326					(AUS) ON START-UP, THE ENGINE WOULD NOT ACCELERATE PAST 13 PERCENT AND TOT WAS APPROACHING A HOT START.  ON THE SECOND A	TTEMPT TO START, A GRUMBLING NOISE WAS HEARD COMING FROM THE ENGINE AREA.  INVESTIGATION FOUND THE STARTER/GENERATOR DRI	VESHAFT END BELL HAD FAILED.  (X)				1	G	7	1 	3U			 	H3WE    					 
2001011106332	20010111	06332	SO  	2001	1	11	AU000619         	1	20000901	G	7312	10718D	FUEL HEATER     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	ENGINE	LEAKING         	W				C	 	 	 	ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			3296 							(AUS) FOLLOWING ABORTED TAKEOFF THE ENGINE OIL WAS FOUND TO BE 1.9 LITRES (TWO QUARTS) BELOW THE LEVEL CHECK ON PRE-FLIG	HT INSPECTION. SUSPECT INTERNAL OIL LEAK IN THE FUEL TO OIL HEATER.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2000100300139	20001003	00139	SO  	2000	10	3	AU000620         	2	20000901	G	8530	646657	CYLINDER        	CONT        	IO520F      	CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	SEPARATED       	W				K	 	 	 	NONE                    				E	F	 	VIBRATION/BUFFET          	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 			496  		563758					(AUS) NR 6 CYLINDER HEAD SEPARATED FROM BARREL.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001011106345	20010111	06345	NM  	2001	1	11	AU000621         	1	20000901	G	3213		TORQUE LINK     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	MISINSTALLED    	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT MLG TORQUE LINKS REVERSED AT REINSTALLATION FOLLOWING BUSHING REPLACEMENT. PERSONNEL / MAINTENANCE ERROR.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011106346	20010111	06346	NM  	2001	1	11	AU000622         	1	20000901	G	3230		LANDING GEAR    			DHAV  	DHC8  	DHC8202     	2809007	NM  										NOSE	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) AFTER TAKEOFF ON THE FIRST FLIGHT OF DAY THE NLG FAILED TO RETRACT AT GEAR UP SELECTION. GROUND CHECKS FOUND THE N	OSE GEAR LOCK ENGAGED. PERSONNEL/MAINTENANCE ERROR					2	H	7	2 	4T			RT	A13NM   					 
2001011106348	20010111	06348	SW  	2001	1	11	AU000623         	1	20000901	G	7603		POWER LEVER     			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RIGHT	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AFTER TAKEOFF ERRATIC ENGINE INDICATIONS WERE OBSERVED ON THE RT ENGINE INSTRUMENTS. ENGINE WAS SHUT DOWN. SUBSEQU	ENT INVESTIGATION INCLUDED RIGGING CHECK, SPEED LEVER FRICTION CHECK AND ENGINE GROUND RUNS. FAULT COULD NOT BE DUPLICAT	ED. SUSPECT THE SPEED LEVER HAD MOVED AFT FROM THE MAXIMUM RPM POSITION TO THE POINT WHERE THE SRL SYSTEM CRUISE EGT SCH	EDULE WAS REACHED.			2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2000100300140	20001003	00140	SO  	2000	10	3	AU000624         	2	20000901	G	8520		STUD            	CONT        		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE	WRONG PART      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH PROPELLERS COULD NOT BE FITTED CORRECTLY DURING INSTALLATION TO RECENTLY OVERHAULED ENGINES.  SUBSEQUENT INVE	STIGATION FOUND THE ATTACHING STUDS WERE TOO LONG (-4 STUDS HAD BEEN FITTED INLIEU OF -3 STUDS).  (X)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2000100300141	20001003	00141	SO  	2000	10	3	AU000625         	1	20000901	G	2823	1790001	SELECTOR VALVE  			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL SELECTOR/SH	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) FUEL SELECTOR VALVE SEIZED.  INVESTIGATION FOUND WATER CONTAMINATION IN THE VALVE SPOOL CAVITY.  SUSPECT WATER FRO	ZE AND JAMMED SELECTOR.  SUBMITTER STATED FUEL SYSTEM HAD BEEN DECONTAMINATED 28 HOURS EARLIER PER AD/GEN/80 AMDT2.   (X	)				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA	5	C	P920	 
2001011106350	20010111	06350	WP  	2001	1	11	AU000626         	2	20000901	G	7250	31032794	TURBINE NOZZLE  			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RT ENGINE	SEPARATED       	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE NOZZLE GUIDE VANE SEGMENT SEPARATED. DAMAGE TO FIRST, SECOND AND THIRD STAGE NOZZLE ASSEMBLIES AND TURBI	NE WHEELS CAUSED BY FOD.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2000100300142	20001003	00142	NM  	2000	10	3	AU000627         	1	20000901	G	5341	22107001	FITTING         			CHILD 	S2    	S2BPITTS    	0110304	NM  										WING ATTACH FITT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT LOWER WING ATTACHMENT FITTING CRACKED PER PITTS SERVICE BULLETIN 25.  (X)						1	Q	7	1 	3O			 	A8SO    					 
2001011106351	20010111	06351	NM  	2001	1	11	AU000628         	1	20000901	G	3242	QF56039	STATOR          		S160T400510 	BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					BRAKE	DISINTEGRATED   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					QF56039					(AUS) NR 2 MAIN WHEEL BRAKE STATOR DISINTEGRATED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011106352	20010111	06352	NM  	2001	1	11	AU000629         	1	20000901	G	2720	AV13J5147	VALVE           			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					RUDDER CONTROL	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STANDBY RUDDER SHUTOFF VALVE INOPERATIVE. INVESTIGATION FOUND THE VALVE TO BE QUITE HOT AND THE OVERRIDE LEVER STI	FF TO OPERATE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011106354	20010111	06354	NE  	2001	1	11	AU000630         	2	20000901	G	7200		ENGINE          			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1	VIBRATES        	W				A	 	 	 	UNSCHED LANDING         				E	F	 	VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 										(AUS) NO1 ENGINE VIBRATION WITH INDICATION OF 1.5. GROUND CHECKS COULDFIND NO PROBLEMS AND AIRCRAFT RETURNED TO SERVICE.	 SUSPECT ICING.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011106355	20010111	06355	NE  	2001	1	11	AU000631         	2	20000901	G	7250		TURBINE NOZZLE  			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				X	J	 	ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 ENGINE FAILED ON TAKEOFF WITH THE TGT EXCEEDING 1000 DEGREESC. SUSPECT CAUSED BY FAILURE OF THE SECOND STAGE 	HP TURBINE NOZZLE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011106356	20010111	06356	EU  	2001	1	11	AU000632         	1	20000901	G	2910	SM601BA40A14	CIRCUIT BREAKER 			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD PUMP	STUCK           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AC HYDRAULIC PUMP REMOTE CONTROL CIRCUIT BREAKER STUCK IN THE ON' POSITION.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2000092800095	20000928	00095	NM  	2000	9	28	AU000633         	1	20000901	G	6320	A0061	TRANSMISSION    	ROBSIN      	A0061       	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR G/B	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			659  		0766					(AUS) MAIN TRANSMISSION MAKING METAL. CHIP LIGHT DID NOT ILLUMINATE.  (X)						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000100300152	20001003	00152	SO  	2000	10	3	AU000634         	1	20000901	G	2913	ESQ12S	BRUSH BLOCK     	PRESTOLITE  	9667102     	PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	B2D34C213   	GL  	HYDRAULIC PUMP	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC POWER PACK MOTOR BRUSHES WORN.  (X)						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P7EA	 
2001011106367	20010111	06367	WP  	2001	1	11	AU000635         	1	20000901	G	5554		BRACKET         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	RUDDER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER RUDDER HINGE MOUNT BRACKET CRACKED AND CORRODED.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001011106368	20010111	06368	WP  	2001	1	11	AU000636         	1	20000901	G	5730		SKIN            			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	LT & RT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING UPPER CORRUGATED SKIN LOCATED JUST INBOARD OF STN 142 CONTAINED SURFACE CORROSION AND ISOLATED EXFO	LIATION CORROSION.					2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2000100300158	20001003	00158	EA  	2000	10	3	AU000637         	2	20000901	G	8530	LW12966	CYLINDER        	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					L82B361A					(AUS) ENGINE EXHAUST VALVE SEATING INCORRECTLY.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011106369	20010111	06369	WP  	2001	1	11	AU000638         	2	20000901	G	7322	89778025	FUEL CONTROL    			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RT ENGINE	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 			2185 							(AUS) RT ENGINE FUEL CONTROL UNIT OUT OF ADJUSTMENT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2000100300159	20001003	00159	CE  	2000	10	3	AU000639         	1	20000901	G	3230	HMXL6G	ROD END         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LANDING GEAR RET	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ROD ROD END FAILED.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001011106370	20010111	06370	NM  	2001	1	11	AU000640         	1	20000901	G	2520	1108133M061	SEAT BELT       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PAX SEAT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT LIFT UP RELEASE MECHANISM SPLIT DOWN THE CENTRE. THEASSEMBLY IS MANUFACTURED FROM A PLASTIC COMPOUND. A 	TOTAL OF FIFTEEN ASSEMBLIES HAVE BEEN FOUND DAMAGED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000100300160	20001003	00160	EA  	2000	10	3	AU000641         	2	20000901	G	8530		VALVE GUIDE     	LYC         		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CARBONED        	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) NR 4 CYLINDER EXHAUST VALVE STICKING IN VALVE GUIDE DUE TO CARBON BUILD-UP.   (X)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000100300119	20001003	00119	CE  	2000	10	3	AU000642         	1	20000901	G	2910	572700223	HOSE            	CESSNA      		CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	HYDRAULIC, MAIN	FAILED          	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			DE	DESCENT        	1			AU	S 					0159					(AUS) HYDRAULIC HOSE LOCATED IN THE RIGHT WING LEADING EDGE FRACTURED ON THE BOND RADIUS.  (X)						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2001011106371	20010111	06371	NM  	2001	1	11	AU000643         	1	20000901	G	7603	TLA2	CONTROL CABLE   	PWA         	JT9D7R4E    	BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					POWER LEVER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THRUST CONTROL CABLES PN TLA2 AND PN TRA2 WORN BEYOND LIMITS. FOUND DURING INSPECTION IAW AD/B767/118.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011106372	20010111	06372	NM  	2001	1	11	AU000644         	1	20000901	G	3340		BRACKET         			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					EXTERIOR LIGHT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAXI LIGHT BRACKET CRACKED. FOUND DURING INSPECTION IAW CASAAD/B737/144 AND FAA AD 2000-08-17 AMDT 39-11703.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011106373	20010111	06373	NM  	2001	1	11	AU000645         	1	20000901	G	3340		BRACKET         			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					EXTERIOR LIGHT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAXI LIGHT BRACKET CRACKED. FOUND DURING INSPECTION IAW CASAAD/B737/144 AND FAA AD 2000-08-17 AMDT 39-11703.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011106374	20010111	06374	NM  	2001	1	11	AU000646         	1	20000901	G	3340		BRACKET         			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					EXTERIOR LIGHT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAXI LIGHT BRACKET CRACKED. FOUND DURING INSPECTION IAW CASAAD/B737/144 AND FAA AD 2000-08-17 AMDT 39-11703.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2000100300161	20001003	00161	EA  	2000	10	3	AU000647         	1	20000901	G	2100	DSC360100	SEAL            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AIR CONDITIONING	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) BLEED AIR PIPE CONNECTOR PERISEAL DETERIORATED AND LEAKING.  (X)						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2000100300162	20001003	00162	CE  	2000	10	3	AU000648         	1	20000901	G	3260	ISE13	SWITCH          			CESSNA	402   	402B        	207590P	CE  										LANDING GEAR POS	FAULTY          	W				K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOWNLOCK MICROSWITCH INTERMITTENT IN OPERATION.  (X)						1	L	7	2 	3O			 	A7CE    					 
2001011106375	20010111	06375	EU  	2001	1	11	AU000649         	1	20000901	G	7712	310703411	INDICATOR       			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE TORQUE	FAILED          	W				O	 	 	 	OTHER                   				O		 	OTHER                     			CR	CRUISE         	1			AU	S 			2105 							(AUS) NR 2 ENGINE TORQUE STRAIN GAUGE BRIDGE OPEN CIRCUITED.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2001011106376	20010111	06376	NM  	2001	1	11	AU000650         	1	20000901	G	3244	DSC429	TIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NLG	DEFLATED        	W				C	 	 	 	ABORTED TAKEOFF         				F		 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 			53   							(AUS) NOSE WHEEL TYRES DEFLATED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011106377	20010111	06377	NE  	2001	1	11	AU000651         	2	20000901	G	7230		SEAL            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 BEARING	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) ENGINE NR 1 BEARING SEAL LEAKING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000100300163	20001003	00163	SO  	2000	10	3	AU000652         	1	20000901	G	5711	6207006	SPAR            			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING MAIN SPAR CONTAINED PATCHES OF INTERGRANULAR CORROSION.  (X)						1	L	7	1 	3O	3	O	 	2A13    	1E10	5	C	P920	 
2001011106378	20010111	06378	EU  	2001	1	11	AU000653         	1	20000901	G	6120		RELAY           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R320	R3204123F1  	NE  	PROP CONTROL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) AUTO-COARSEN SYSTEM FAILED. INVESTIGATION FOUND AN INTERMITTENT RELAY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P5NE	 
2001011106401	20010111	06401		2001	1	11	AU000654         	4	20000901	G	2312	064102300	TRANSCEIVER     	KING        	VHF22A      	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	VHF COMMS	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 					UK					(AUS) NR 1 VHF TRANSCEIVER FAILED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001011106402	20010111	06402		2001	1	11	AU000655         	4	20000901	G	3445		WARNING SYSTEM  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	AIR COLLISION	FALSE ACTIVATION	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) SUSPECT ACTIVATED BY AIRCRAFT ON PARALLEL RUNWAY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011106403	20010111	06403	EU  	2001	1	11	AU000656         	1	20000901	G	2120	9303688100	DUCT            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	AIR DISTRIBUTION	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIR CYCLE MACHINE BLEED AIR SUPPLY DUCT HOLED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011106404	20010111	06404	WP  	2001	1	11	AU000658         	2	20000901	G	7261		CHIP DETECTOR   			CASA  	C212  	C212200     	2410304	EU  	GARRTT	TPE331	TPE33110    	01514	WP  					ENGINE	CONTAMINATED    	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE CHIP DETECTOR CONTAMINATED WITH METAL.						2	H	7	2 	4T	4	T	RT	A43EU   	E4WE				 
2001021400003	20010214	00003	NM  	2001	2	14	AU000659         	1	20000901	G	2400		HARNESS         	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENG ELECTRICAL	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ENGINE WIRE BUNDLES W6000 AND W6080 BADLY CHAFED IN THE AREA WHERE THEY RUN THROUGH THE NO1 STRUT KNEECAP. TH	E BUNDLES HAD BEEN CHAFING ON AN ACCESS PANEL LOCATED BENEATH THE WING LEADINGEDGE AND THE AIR DUCT ASSEMBLY.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2000100300164	20001003	00164	SO  	2000	10	3	AU000660         	1	20000901	G	2913	1213HBG310A	PUMP            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HYDRAULIC PUMP.	FAILED          	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 			2    		L462561A					(AUS) LEFT ENGINE DRIVEN HYDRAULIC PUMP DRIVESHAFT SHEARED.  PUMP HAD ONLY COMPLETED 1.7 HOURS TIS SINCE OVERHAUL.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000100300165	20001003	00165	CE  	2000	10	3	AU000661         	1	20000901	G	5311	207	FRAME           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN FR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 207 LEFT, CRACKED.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000100300166	20001003	00166	EA  	2000	10	3	AU000662         	2	20000901	G	8530	4091709001	PISTON RING     	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE OIL CONTROL PISTON RINGS BROKEN AND STUCK. TURBOCHARGER LEAKING OIL.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000101200145	20001012	00145	SO  	2000	10	12	AU000663         	1	20000901	G	8120	4091709001	TURBOCHARGER    	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	EXHAUST TURBO	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			1028 		CAN00091					(AUS) LEFT ENGINE EXHAUST TURBOCHARGER LEAKING OIL.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000101200149	20001012	00149	EA  	2000	10	12	AU000664         	2	20000901	G	8530	L913161A	PISTON RING     	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 			1045 							(AUS) LEFT ENGINE PISTON RINGS CRACKED AND STUCK.  PISTON RING GROOVES WORN.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000101200150	20001012	00150	CE  	2000	10	12	AU000665         	1	20000901	G	5740	1011100313	FITTING         	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	WING ATTACH FITT	SCORED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			36   							(AUS) LEFT UPPER FORWARD WING ATTACHMENT FITTING SCORED IN THE BORE OFTHE BARREL NUT RECESS IN THE BATHTUB FITTING.  CAU	SED BY THE BARREL NUT INSERT BEING INSERTED 90 DEGREES OUT FROM ITS CORRECT POSITION.  SUBMITTER SUSPECTED OCCURRED DURI	NG THE PREVIOUS INSPECTION IAW BEECH STRUCTURAL INSPECTION AND REPAIR MANUAL 98-39006P4 SECTION57-17-00.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001011106405	20010111	06405	NE  	2001	1	11	AU000666         	2	20000901	G	7200		ENGINE          			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					NR 2	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				E	M	J	VIBRATION/BUFFET          	OVER TEMP                 	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 ENGINE TGT EXCEEDED 900 DEGREES AND FLAMES CAME FROM THEENGINE. THE ENGINE WAS REMOVED AND SENT FOR INVESTIGA	TION AND REPAIR.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011106406	20010111	06406		2001	1	11	AU000667         	4	20000901	G	3418		STICK SHAKER    			DHAV  	DHC8  	DHC8315     	2809010	NM  										COCKPIT	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) STICK SHAKER SYSTEM FAILED. LIMITED INFORMATION PROVIDED.						2	H	7	2 	4T			RT	A13NM   					 
2000101200151	20001012	00151	EA  	2000	10	12	AU000668         	2	20000901	G	7414	6360	MAGNETO         	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MAGNETO/DIST	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					RL907161A					(AUS) LEFT AND RIGHT MAGNETOS INCORRECTLY FITTED.  SUBMITTER SUSPECTED THE MAGNETOS WERE TRANSPOSED DURING ENGINE OVERHA	UL.   (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000101200137	20001012	00137		2000	10	12	AU000669         	4	20000901	G	6122	F624Z	CSD             	WOODWARD    	F6247       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROP GOVERNOR	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 			1277 		E83T					(AUS) CONSTANT SPEED UNIT (CSU) FAULTY.  FINE PITCH STOP ADJUSTED WITH NO INCREASE IN RPM.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000101200152	20001012	00152	SO  	2000	10	12	AU000670         	2	20000901	G	8530	646657CEA7	CYLINDER        	CONT        	TSIO520N    	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE NR 2 AND NR 3 CYLINDERS CRACKED BETWEEN FUEL INJECTOR AND SPARK PLUG.  FUEL LEAKING EXTERNALLY.  (X)						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000101200153	20001012	00153	EA  	2000	10	12	AU000672         	2	20000901	G	8530		CYLINDER        	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DAMAGED         	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RIGHT ENGINE N=R 5 CYLINDER SUSPECT DETONATION.  DAMAGE TO CYLINDER HEAD, PISTON AND PISTON PIN.  TOP PISTON RING 	BROKEN CAUSING DAMAGE TO THE CYLINDER HEADM VALVES AND TURBOCHARGER TURBINE WHEEL.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011106410	20010111	06410	EU  	2001	1	11	AU000673         	1	20000901	G	3246	5009237	WHEEL           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN WHEEL ASSEMBLY CRACKED AT BEAD SEAT RADIUS. CRACK LENGTH APPROXIMATELY 93.345MM (3.675IN).						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2000090800104	20000908	00104	SO  	2000	9	8	AU000674         	2	20000901	G	7414	M3050	IMPULSE COUPLING	SLICK       	6310        	CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	MAGNETO/DIST	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					96010133LH96					(AUS) MAGNETO IMPULSE COUPLINGS (2OFF) HAD LOOSE RIVETS IN THE FLYWEIGHT ASSEMBLIES.  FOUND DURING INSPECTION IAW SLICK 	SB 1-86B.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2000090800107	20000908	00107	EA  	2000	9	8	AU000675         	2	20000901	G	8520	L1349148	CRANKSHAFT      	LYC         		GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ENGINE	BROKEN          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			1354 							(AUS) RIGHT ENGINE CRANKSHAFT BROKEN.  (X)						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2000090800108	20000908	00108	SO  	2000	9	8	AU000676         	2	20000901	G	8540	402711	STUD            	CONT        	COVER       						CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	ENGINE	MISSING         	W				K	 	 	 	NONE                    				K	E	B	FLUID LOSS                	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	TO	TAKEOFF        	1			AU	S 										(AUS) LEFT ENGINE TACHOMETER DRIVE COVER STUD MISSING.  OIL LEAKING ONTO HOT EXHAUST.  (X)											3	O			E5CE	5	C	P22EA	 
2001011106412	20010111	06412	NE  	2001	1	11	AU000677         	2	20000901	G	7250	70BM041020	TURBINE         			AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					NR 2 ENGINE	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			74   							(AUS) NR 2 ENGINE REAR BEARING MAGNETIC PLUG CONTAIN A SMALL SLIVER OF METAL. THE ENGINE WAS INSPECTED IAW THE MANUFACTU	RERS INSTRUCTIONS BEFORE BEING GROUND RUN AND FLIGHT TESTED WITH NOFURTHER PROBLEMS. AIRCRAFT RETURNED TO SERVICE.					1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2000090800109	20000908	00109	SO  	2000	9	8	AU000678         	2	20000901	G	8540	643109	SPRING          	CONT        	STARTADPTR  	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	BROKEN          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE STARTER/ ADAPTER CLUTCH SPRING BROKEN EIGHT COILS FROM THE ATTACHMENT POINT TO THE CLUTCH DRUM.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2000090800110	20000908	00110	NM  	2000	9	8	AU000679         	1	20000901	G	3230	4000833	BRACE           			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					LANDING GEAR RET	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR LOWER SIDE BRACE CRACKED.  FOUND DURING INSPECTION IAW TSA-SB600-134A.  (X)						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000090800111	20000908	00111	NM  	2000	9	8	AU000680         	1	20000901	G	3230	4000833	BRACE           			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					LANDING GEAR RET	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR LOWER SIDE BRACE CRACKED.  FOUND DURING INSPECTION IAW TSA-SB600-134A.  (X)						1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2001011100002	20010111	00002	NE  	2001	1	11	AU000681         	2	20000901	G	7250		GAS GENERATOR   			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	RT ENGINE	SEIZED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE GAS GENERATOR MODULE AND POWER SECTION SEIZED.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2001011100003	20010111	00003	WP  	2001	1	11	AU000682         	2	20000901	G	7250	310323511	TURBINE NOZZLE  			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TFE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	LT ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE FIRST STAGE NOZZLE AND INNER BAFFLE ASSEMBLY BURNED, CRACKED AND CORRODED. SEAL PLATE WARPED AND CRACKED	. FIRST STAGE TURBINE BLADE TIPS ERODED. SUSPECT CAUSED BY SULPHURISATION CORROSION OF THE NOZZLE COMPINED WITH STREAKIN	G FUEL INJECTORS.				2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2000090800112	20000908	00112	CE  	2000	9	8	AU000683         	1	20000901	G	2720	12604566	RUDDER BAR      			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RUDDER CONTROL S	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER PEDAL SEPARATED FROM RUDDER BAR AT WELD JOINT.  BRAKES HAD BEEN BLED TWELVE HOURS PREVIOUSLY.  (X)						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2001011100005	20010111	00005	NM  	2001	1	11	AU000684         	1	20000901	G	2530		HEATER          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GALLEY WATER	OVERHEATED      	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) STRONG ELECTRICAL SMELL EMANATING FROM THE AREA OF THE RT EMERGENCY CUPBOARD. INVESTIGATION COULD FIND NO SIGNS OF	 SMOKE OR FIRE. NR 2 URN WAS FOUND TO BE EMPTY OF WATER.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000090800050	20000908	00050	CE  	2000	9	8	AU000685         	1	20000901	G	7810	MVT68892250	CLAMP           	CONT        		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE COLLECTOR	INADEQUATE      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE EXHAUST CLAMPS HAD UNKNOWN HOURS IN SERVICE. CLAMPS ARE LIFED AT 500 HOURS. C LAMPS WERE IN POOR CONDITION.	  (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000090800115	20000908	00115	CE  	2000	9	8	AU000686         	1	20000901	G	2510		SEAT BELT       			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	FLIGHT COMPART	INADEQUATE      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD SEAT BELT SHOULDER HARNESSES NOT FITTED.  ITEMS HAD NOT BEEN REINSTALLED FOLLOWING INTERIOR REFURBISHMENT.	  (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000090800116	20000908	00116	CE  	2000	9	8	AU000687         	1	20000901	G	6120	991026915	CONTROL CABLE   	MCAULY      		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	PROP CONTROL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT PROPELLER OUTER CONTROL CABLES SEPARATED AT SLIDE JOINT LOCATED AT PROPELLER GOVERNOR END.  LEFT CA	BLE HAD BEEN REPAIRED BY LOCKWIRING THE ENDS TOGETHER.  CABLES P/N 9910269-15 AND P/N 9910269-16.  (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000090800117	20000908	00117	CE  	2000	9	8	AU000688         	1	20000901	G	2711		BOLT            			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	AILERON TAB CONT	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AILERON TRIM ACTUATING ROD ATTACHMENT BOLT AND NUT NOT SPLIT PINNED.   (X)						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2001011106027	20010111	06027		2001	1	11	AU000689         	4	20000901	G	3414	WL106AMA7	INDICATOR       			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AIRSPEED	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) AIR SPEED INDICATOR FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100006	20010111	00006	EU  	2001	1	11	AU000690         	1	20000901	G	5711		SPAR            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT & RT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WINGS FORWARD AND REAR SPARS CRACKED IN AREA LOCATED OUTBOARD OF RIB NR 13.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000090800119	20000908	00119	EA  	2000	9	8	AU000691         	2	20000901	G	8550	LW13388	SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 					RL11668A					(AUS) RIGHT ENGINE OIL FILTER ADAPTER PLATE SEAL FAILED.  SEAL WAS PROTRUDING FROM PLATE.  LOSS OF 9 LITRES OF ENGINE OI	L.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800120	20000908	00120	CE  	2000	9	8	AU000692         	1	20000901	G	5312		BULKHEAD        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT DOORPOST BULKHEAD CRACKED.  FOUND DURING INSPECTION IAW AD/C180/75.  (X)						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2000090800121	20000908	00121		2000	9	8	AU000693         	4	20000901	G	3416	B43E	ALTIMETER       			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  	LYC   	O320  	O320*       	41508	EA  					ALTIMETER, BAROM	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					3293					(AUS) ALTIMETER FAULTY.  (X)						1	L	7	1 	3O	3	O	RT	EXPA1L71	E274				 
2001011100007	20010111	00007	NM  	2001	1	11	AU000694         	1	20000901	G	7603	TLA2	CONTROL CABLE   			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					POWER LEVER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THRUST CONTROL CABLES TLA-2 AND TRA-2 LOCATED IN THE RHFORWARD CARGO HOLD WERE WORN BEYOND LIMITS. FOUND DU	RING INSPECTION IAW AD/B767/118.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011100008	20010111	00008	NM  	2001	1	11	AU000695         	1	20000901	G	7500	24098350	SEAL            			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					BLEED AIR SYSTEM	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BLEED AIR DUCT SEAL DETERIORATED AND BROKEN INTO PIECES. HOTBLEED AIR LEAKING ONTO CENTRE WING AND FUEL TANK.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2000090800122	20000908	00122	SW  	2000	9	8	AU000696         	1	20000901	G	2810		FUEL TANK       	MOONEY      		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FUEL TANK LEAKING FROM TOP SEAM.  AD/GEN/80 AMDT2 HAD RECENTLY BEEN CARRIED OUT.  (X)						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P920	 
2000090800123	20000908	00123	CE  	2000	9	8	AU000697         	1	20000901	G	2810	0029200344	FUEL TANK       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT INBOARD LEADING EDGE FUEL TANK LEAKING.  AIRCRAFT HAD ONLY JUST HAD AD/GEN/82 AMDT2 CARRIED OUT.  (X)						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2000090800124	20000908	00124	EA  	2000	9	8	AU000698         	2	20000901	G	8520	L575861A	STUD            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 					L575861A					(AUS) LEFT ENGINE NR 2 CYLINDER HOLD-DOWN STUDS (4OFF) FAILED.  BROKEN STUDS FOUND IN ENGINE COWL.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011100009	20010111	00009	NM  	2001	1	11	AU000699         	1	20000901	G	5755	85770068003	LEVER           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTBOARD GROUND SPOILER LEVER CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000090800125	20000908	00125	EA  	2000	9	8	AU000700         	2	20000901	G	7414	M3548	ROTOR           	SLICK       	4370        	CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	MAGNETO/DIST	BROKEN          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					9600917					(AUS) RIGHT MAGNETO ROTOR SHAFT SHEARED.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857	 
2000090800126	20000908	00126	CE  	2000	9	8	AU000701         	1	20000901	G	2700	571509665	CONTROL CABLE   			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FLIGHT CONTROLS	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) CABLE BROKEN.  (X)						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000090800127	20000908	00127	EA  	2000	9	8	AU000702         	2	20000901	G	7412	103815504	EXCITER         	PWA         		BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	EXCITER	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			623  		984OR003C					(AUS) LEFT  ENGINE IGNITION EXCITER FAILED. INVESTIGATION ALSO FOUND THAT AN ATTACHMENT POINT HAD FAILED.  (X)						1	L	7	2 	3T	3	T	 	3A20    	E4EA	6	C	P15EA	 
2001011100011	20010111	00011	NM  	2001	1	11	AU000703         	1	20000901	G	5330		SKIN            			BOEING	737   	737377      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FORWARD SERVICE DOOR AFT LOWER CORNER OUTER SKIN CRACKED. CRACK LENGTH 13MM (0.51IN). FOUND DURING EDDY CURRENT	 INSPECTION IAW ER B73-53-30-18B.					2	L	7	2 	4F			RT	A16WE   					 
2001011100012	20010111	00012	NM  	2001	1	11	AU000704         	1	20000901	G	5512		SKIN            			BOEING	737   	737377      	       	NM  										HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILISER LOWER SKIN CRACKED IN AREA OF CHEMICALLY MILLED EDGE BETWEEN STN 147.9 AND STN157.1 JUST 	FORWARD OF THE REAR SPAR. CRACK LENGTH 38.1MM (1.5IN). FOUND DURING EDDY CURRENT INSPECTION.					2	L	7	2 	4F			RT	A16WE   					 
2001011100031	20010111	00031	EU  	2001	1	11	AU000705         	1	20000901	G	5311		FRAME           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 35 CRACKED IN ALL TWELVE HOLES LOCATED BETWEEN STRINGERS 30 AND 31 ON LT AND RT SIDES. FOUND DURING	 EDDY CURRENT INSPECTION IAW AD/A320/94.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011100033	20010111	00033	EU  	2001	1	11	AU000706         	1	20000901	G	2752		JACKSCREW       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAP ACTUATOR	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAPS UNABLE TO BE MOVED FROM THE UP' POSITION. SUSPECT FAULTY RT OUTBOARD SCREWJACK.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011100034	20010111	00034	EU  	2001	1	11	AU000707         	1	20000901	G	5313		STRINGER        			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FRONT VERTICAL STRINGER CRACKED AT FRAME 36. FOUND DURING EDDY CURRENT INSPECTION IAW SB A320-57-1017.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011100036	20010111	00036	EU  	2001	1	11	AU000708         	1	20000901	G	5311		FRAME           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME CRACKED IN HOLES (2OFF) LOCATED BETWEEN FRAME 38 AND FRAME 41 AND STRINGER 12 AND STRINGER 21. FOUN	D DURING INSPECTION IAW AD/A320/89.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011100037	20010111	00037	EU  	2001	1	11	AU000709         	1	20000901	G	5311		FRAME           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 53 CRACKED. CRACK LENGTH APPROXIMATELY 2MM (0.078IN). FOUND DURING ULTRASONIC INSPECTION IAW SBA320	-52-1032.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2000090800128	20000908	00128	EU  	2000	9	8	AU000710         	1	20000901	G	3213	1095015	PIN             			GROB  	G115  	G115        	       	EU  	LYC   	O235  	O235H2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	MLG	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR AXLE PIN BROKEN BETWEEN WHEEL NUT AND SPAT RETAINER CAP.  (X)						1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045	 
2000090800129	20000908	00129	SO  	2000	9	8	AU000711         	1	20000901	G	5711	4042000	SPAR CAP        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT LOWER SPAR CAP CORRODED IN AREA BETWEEN THE FUSELAGE AND WHERE THE LOWER SKIN BEGINS. THE AREA IS COVERED BY 	AN ALUMINIUM ADHESIVE TAPE USED AS AN ANTI-CHAFING STRIP AND THE CORROSION WAS FOUND FOLLOWING REMOVAL OF THE TAPE.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800130	20000908	00130	WP  	2000	9	8	AU000712         	1	20000901	G	6210	A18910	NUT             			ROBSIN	R22   	R22         	7640102	WP  										MAIN ROTOR BLADE	MISMANUFACTURED 	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR RETENTION BOLT NUT FAULTY.  NO LEAD ON THREAD.  SUBMITTER STATED NUT WAS A NEW ITEM FROM ROBINSON.  (X)						1	G	7	1 	3O			 	H10WE   					 
2001011100039	20010111	00039	EU  	2001	1	11	AU000713         	1	20000901	G	2730	P310450002	DAMPER          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ELEVATOR	FAULTY          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR GUST DAMPER ASSEMBLY FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000090800131	20000908	00131	EA  	2000	9	8	AU000714         	2	20000901	G	8520		SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE CRANKSHAFT SEAL ADRIFT.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800132	20000908	00132	EA  	2000	9	8	AU000715         	2	20000901	G	8530		GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE NR 2, NR 4 AND NR 6 INDUCTION SYSTEM GASKETS FAULTY.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800133	20000908	00133	EA  	2000	9	8	AU000716         	2	20000901	G	8530		SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE NR 5 AND NR 6 PUSHROD GUARD TUBE SEALS LEAKING.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800134	20000908	00134	EA  	2000	9	8	AU000717         	2	20000901	G	8520		SEAL            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ENGINE CRANKSHAFT SEALS ADRIFT AND LEAKING OIL.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800135	20000908	00135	EA  	2000	9	8	AU000718         	1	20000901	G	5540		STIFFENER       			WACO  	YMF   	YMF         	9600412	EA  	JACOBP	R755  	R755B2      	35007	SW  					RUDDER STRUCTURE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER LOWER STIFFENER RUSTED AND SEPARATED FROM LOWER RUDDER BOW.  SUBMITTER SUSPECTED CAUSED BY TRAPPED WATER.  	(X)					1	Q	7	1 	3R	3	R	 	ATC542  	E237				 
2001011100040	20010111	00040	EA  	2001	1	11	AU000719         	1	20000901	G	2742	8396	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										STABILIZER TRIM	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) STABILISER TRIM ACTUATOR FAULTY.						2	L	7	2 	4F			RT	A21EA   					 
2001011100042	20010111	00042	EA  	2001	1	11	AU000720         	1	20000901	G	2613	356024310	DETECTOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										RT & LT PYLON	MALFUNCTIONED   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT PYLON BLEED LEAK DETECTOR LOOPS FAILED RESISTANCE CHECK. FOUND DURING INSPECTION IAW SB A601R-36-014.						2	L	7	2 	4F			RT	A21EA   					 
2001011100058	20010111	00058	SO  	2001	1	11	AU000722         	1	20000901	G	3242	1331096	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	BRAKE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					038OR					(AUS) RH OUTBOARD BRAKE ASSEMBLY STATOR CRACKED FROM EXPANSION SLOT TOTHE INSIDE DIAMETER AND PARTLY THROUGH ONE OF THE 	DRIVE LUGS. TWO OTHER SMALL CRACKS FOUND AT TWO OTHER EXPANSION SLOTS. FOUND WHEN BRAKE REMOVED DUE TO WEAR.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001011100060	20010111	00060	SW  	2001	1	11	AU000723         	1	20000901	G	5541	2742051037	TORQUE TUBE     			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	RUDDER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TORQUE TUBE ASSEMBLY WORN BEYOND LIMITS. CHAFING MARKS ARE APPROXIMATELY 0.254MM (0.010IN) DEEP. THE MAXIMU	M DEPTH PERMITTED IS 0.0762MM (0.003IN). SUSPECT CAUSE OF WEAR IS MISALIGNMENT OF THE PRESSURISATION SEAL AT INSTALLATIO	N ALLOWING IT TO CONTACTTHE TORQUE TUBE.				2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100061	20010111	00061	SW  	2001	1	11	AU000724         	1	20000901	G	5541	2742051037	TORQUE TUBE     			FRCHLD	SA227 	SA227DC     	3377521	SW  										RUDDER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TORQUE TUBE ASSEMBLY WORN BEYOND LIMITS. CHAFING MARKS ARE APPROXIMATELY 0.254MM (0.010IN) DEEP. THE MAXIMU	M DEPTH PERMITTED IS 0.0762MM (0.003IN). SUSPECT CAUSE OF WEAR IS MISALIGNMENT OF THE PRESSURISATION SEAL AT INSTALLATIO	N ALLOWING IT TO CONTACTTHE TORQUE TUBE.				2	L	7	2 	4T			RT	A18SW   					 
2001011100063	20010111	00063		2001	1	11	AU000725         	4	20000901	G	6122	89741016AC	GOVERNOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT PROPELLER	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 			25   							(AUS) RT PROPELLER GOVERNOR FAULTY.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2000090800142	20000908	00142	EA  	2000	9	8	AU000726         	2	20000901	G	8530	L280461A	CYLINDER        	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	GLAZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			247  		L280461A					(AUS) ENGINE SPARK PLUGS CONTAMINATED WITH OIL. INVESTIGATION FOUND NR 2, NR 4, NR 5, AND NR 6 CYLINDER BORES GLAZED WIT	H NR 5 AND NR 6 CYLINDERS ALSO CONTAINING CORROSION IN THE BORES. THE ENGINE WAS ONLY 247.9 HOURS OUT OF FACTORY OVERHAU	L.  SUBMITTER SUSPECTED GLAZING CAUSED BY INCORRECT TEST RUNNING AND CORROSION CAUSED BY INCORRECT INHIBITING FOLLOWING 	TEST RUNS AT THE FACTORY.  (X)			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000090800143	20000908	00143	EA  	2000	9	8	AU000727         	2	20000901	G	7322	1052061	CARBURETOR      	LYC         		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					FUEL CONTROL/CAR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			92   							(AUS) CARBURETOR FAULTY.  INVESTIGATION FOUND STICKY NEEDLE AND SEAT ASSEMBLY, PLUNGER O''-RING FAULTY AND CORROSION ON 	THE INSIDE OF THE CARBURETOR COVER.  (X)					1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2001011100065	20010111	00065	EU  	2001	1	11	AU000728         	1	20000901	G	2910	SA7670006155	HOSE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD SYSTEM	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 ENGINE HYDRAULIC PUMP PRESSURE HOSE FAILED. LOSS OF HYDRAULIC FLUID.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011100067	20010111	00067	EU  	2001	1	11	AU000729         	1	20000901	G	2711	HC270H0134014	CONTROL CABLE   			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AILERON TAB	CORRODED        	W				A	 	 	 	UNSCHED LANDING         				D	J	 	INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) RT UPPER AILERON TRIM CABLE CORRODED AND BROKEN IN AREA OFOUTBOARD PULLEY LOCATED AT WING RIB NR 14.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011100068	20010111	00068	SW  	2001	1	11	AU000730         	1	20000901	G	2432		RELAY           			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	BATTERY CHARGER	SHORTED         	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) BATTERY LOCKOUT RELAY FAULTY. RELAY TERMINAL SHORT CIRCUITING TOGROUND IN THE RT BATTERY BOX.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100075	20010111	00075	EU  	2001	1	11	AU000731         	1	20000901	G	7603		POWER LEVER     			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENGINE	STUCK           	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) NR 3 ENGINE THRUST LEVER STUCK AT CRUISE POWER. INVESTIGATIONCOULD FIND NO CAUSE OF DEFECT.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100076	20010111	00076	NM  	2001	1	11	AU000732         	1	20000901	G	5330		SKIN            			BOEING	737   	737377      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD SERVICE DOOR CUTOUT CONTAINED SEVEN CRACKS PROPAGATING FROM RIVET HOLES IN THE FORWARD UPPER CORNER AND SI	X OUT OF ROUND HOLES IN THE UPPER AFT CORNER. FOUND DURING EDDY CURRENTINSPECTION.					2	L	7	2 	4F			RT	A16WE   					 
2001011100077	20010111	00077	EU  	2001	1	11	AU000733         	1	20000901	G	5330		SKIN            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED IN RIVET HOLES (16OFF). FOUND DURINGINSPECTION IAW SB A320-53-1031.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011100078	20010111	00078	NM  	2001	1	11	AU000734         	1	20000901	G	5330		SKIN            			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT SKIN CORRODED BENEATH PAINT LOCATED AFT OF STN 287 AND BELOW STRINGER NR 24. AREA OF CORROSION 50MM BY 50	MM (1.968IN BY 1.968IN) AND 2.032MM (0.080IN) DEEP.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011100080	20010111	00080	NM  	2001	1	11	AU000735         	1	20000901	G	3230	113T11102	HOUSING         			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					MLG	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR SIDE STRUT SWIVEL HOUSING CORRODED IN THEAREA OF THE BUSHING FLANGE. DEPTH OF CORROSION  0.12	7MM (0.005IN).					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011104202	20010111	04202		2001	1	11	AU000736         	1	20000901	G	3520	11900301	OXYGEN MASK     																	PAX OXYGEN	FIRE            	W				O	 	 	 	OTHER                   				A		 	FLAME/FIRE                			IN	INSP/MAINT     	1			AU	S 					09238					(AUS) DURING PBE MASK DISCHARGE, THE OXYGEN MASK ACTIVATION MECHANISM SEPARATED FROM OXYGEN GENERATOR UNDER PRESSURE CAU	SING THE GENERATOR UNIT TO CATCH FIRE.  (X)																		 
2001011100397	20010111	00397	NM  	2001	1	11	AU000737         	1	20000901	G	2897		WIRE            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL INDICATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE FUL TANK FLOAT SWITCH WIRING CHAFING APPROXIMATELY 100MM (4IN) FROM END. FOLLOWING REMOVAL OF THE WIRE FUEL	 CONTAMINATIONOF THE FLOAT SWITCH WAS EVIDENT.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011100082	20010111	00082	NM  	2001	1	11	AU000738         	1	20000901	G	3230		LANDING GEAR    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NOSE	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR WOULD NOT EXTEND BY NORMAL MEANS (THREE ATTEMPTS). NLG FINALLY EXTENDED USING THE EMERGENCY SYST	EM.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000090800147	20000908	00147	CE  	2000	9	8	AU000739         	1	20000901	G	5610	531126110	WINDOW          			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	FLIGHT COMPART	SEPARATED       	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) COPILOT SIDE WINDOW SEPARATED IN-FLIGHT.  (X)						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000090800148	20000908	00148	SO  	2000	9	8	AU000740         	2	20000901	G	8520		NUT             	CONT        		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ENGINE	LOOSE           	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT ENGINE CYLINDER HOLD-DOWN NUTS LOOSE.  SUBMITTER SUSPECTED CAUSED BY INCORRECT ASSEMBLY.  ENGINES H	AD COMPLETED 210.5 HOURS SINCE BULKSTRIP.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000090800149	20000908	00149	CE  	2000	9	8	AU000741         	1	20000901	G	3246	4075D	WHEEL           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	WHEEL/SKI/FLOAT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN WHEEL INBOARD HALF CRACKED IN BEAD RADIUS WITH PARTIAL SEPARATION OF FLANGE. CRACK LENGTH 127 MM (5 INCHES). 	 (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2000090800049	20000908	00049	CE  	2000	9	8	AU000742         	1	20000901	G	2710		CONTROL CABLE   			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	AILERON CONTROL	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT AILERON CABLE SEPARATED FROM PULLEY AT RIGHT PULLEY SET LOCATED IMMEDIATELY INBOARD OF THE AILERON BELLCRANK	.  NO DAMAGE TO PULLEY OR CABLE.  (X)					1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P21EA	 
2000090800150	20000908	00150	CE  	2000	9	8	AU000743         	1	20000901	G	6120		CONTROL CABLE   	MCAULY      	D3A32C90    	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	PROP CONTROL	SEPARATED       	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PROPELLER CONTROL CABLE ROD END NOT CONNECTED TO CSU.  BOLT MISSING.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001011100083	20010111	00083	EU  	2001	1	11	AU000744         	1	20000901	G	2910	A71281421	PIPE            			FOKKER	F28   	F28MK0100   	4990807	EU  										HYD SYSTEM	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NO1 SYSTEM HYDRAULIC FROM PRESSURE REDUCING VALVE CRACKED ATFLARE. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F			RT	        					 
2001011100084	20010111	00084	NE  	2001	1	11	AU000745         	2	20000901	G	7322	78639010	HMU             			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					LT ENGINE	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE HYDROMECHANICAL METERING UNIT (HMU) FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000090800152	20000908	00152	SW  	2000	9	8	AU000746         	1	20000901	G	2910	70053H000A100A	HOSE            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					HYDRAULIC, MAIN	FAILED          	W				O	 	 	 	OTHER                   				K	F	 	FLUID LOSS                	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC HOSE LOCATED BETWEEN HYDRAULIC PUMP AND FILTER ASSEMBLY FAILED.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001011100085	20010111	00085	NE  	2001	1	11	AU000747         	2	20000901	G	7210	3107090	BEARING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					RT ENGINE G/B	SPALLED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE REDUCTION GEARBOX NR 19 BEARING FAILED. SPALLING OF THEINNER RACE CREATED METAL CONTAMINATION OF NR 18 B	EARING CAUSINGLIGHT SPALLING OF THE RACE. METAL CONTAMINATION OF THE ENGINE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000120700090	20001207	00090	NE  	2000	12	7	AU000748         	2	20000814	G	8520	4224837	LINK ROD        	PWA         		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	SEIZED          	W				K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) ENGINE FAILED.  INVESTIGATION FOUND THAT THE NR 7 LINK ROD SEIZED IN THE NR 7 LINK PIN.  (X)						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000112200003	20001122	00003	NM  	2000	11	22	AU000749         	1	20000817	G	6310	A1681	RETAINER        	ROBSIN      		ROBSIN	R22   	R22BETA     	       	NM  										ENGINE/TRANS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER SHEAVE SEAL PLATE CRACKED.  LIMITED INFORMATION PROVIDED.  (X)						1	G	7	1 	3O			 	H10WE   					 
2000112200004	20001122	00004	SW  	2000	11	22	AU000750         	1	20000821	G	6320	412040002103	TRANSMISSION    	BELL        		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					M/R GEARBOX	FAULTY          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 			3919 		ABW40279					(AUS) MAIN TRANSMISSION CHIP DETECTOR CONTAMINATED WITH METAL.  FOLLOWING INSPECTION AND GROUND RUN, THE CHIP DETECTOR A	GAIN ILLUMINATED.  (X)					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001011100086	20010111	00086	NE  	2001	1	11	AU000751         	2	20000814	G	7230	311358901	BEARING         			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 BEARING FAULTY. N1 ROTOR SEIZED.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2001011100108	20010111	00108	EA  	2001	1	11	AU000752         	1	20000821	G	7540	356024310	INDICATOR       			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					BLEED AIR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT PYLON BLEED AIR LEAK DETECTOR LOOP HAD LOW RESISTANCE. FOUND DURING INSPECTION IAW SBA601R-36-104.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001011100109	20010111	00109	SW  	2001	1	11	AU000753         	1	20000827	G	2421	300SG121Q	GCU             			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	LT GENERATOR	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			113  							(AUS) LT GENERATOR CONTROL UNIT FAULTY.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100112	20010111	00112	EU  	2001	1	11	AU000754         	1	20000825	G	5743	7257162514S515S0	FITTING         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR SUPPORT FITTINGS CORRODED IN BEARING BORES AND LINK ATTACHMENT HOLES. DEPTH OF CORROSION BETWEEN 0.15	2MM AND 1.092MM(0.006IN AND 0.043IN).					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011100114	20010111	00114	EU  	2001	1	11	AU000755         	1	20000829	G	7712		INDICATOR       			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RT ENGINE TORQUE	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE TORQUE STRAIN GAUGE BRIDGE OUT OF ADJUSTMENT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2000120700091	20001207	00091	SO  	2000	12	7	AU000756         	2	20000829	G	8520	631845	GEAR            	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					570452					(AUS) CAMSHAFT GEAR P/N 631845 CRACKED.  FUEL PUMP DRIVE GEAR P/N 535662 CRACKED AND TEETH BADLY WORN.  FUEL CONTROL UNI	T P/N 629703-2 HAD O-RING SEAL MISSING FROM MIXTURE SHAFT.   SUBMITTER SUSPECTED CAUSED BY INCORRECT MESHING OF FUEL PUM	P DRIVE GEAR P/N 535662 AND FUEL PUMP GEAR P/N 631684, AND/OR INSUFFICIENT LUBRICATION OF FUEL PUMP GEAR P/N 631684 AND 	FUEL PUMP LOWER HOUSING INSIDE DIAMETER.  (X)			1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2000120700092	20001207	00092	EA  	2000	12	7	AU000757         	2	20000901	G	8520	LW13838	CRANKCASE       	LYC         							LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			220  							(AUS) ENGINE CRANKCASE CRACKED IN AREA ADJACENT TO NR 2 CYLINDER TOP FORWARD BASE STUD.  FOLLOWING ENGINE BULK STRIP, TH	E FOLLOWING DEFECTS WERE ALSO NOTED:   CRANKCASES BADLY FRETTED ON MATING FACES .  INTERMEDIATE MAIN BEARINGS LOOSE IN M	AIN TUNNEL CAUSING WEAR TO TUNNEL.  MATERIAL CHIPPED AWAY FROM TUNNEL LOCATING DOWEL HAD DAMAGED BEARING SURFACE.  SUBMI	TTER SUSPECTED LOCATING DOWEL LOOSE IN CRANKCASE.  SIGNIFICANT TANG DAMAGE FROM BEARINGS ROTATING IN CRANKCASES.  CSU DR	IVE GEARSHAFT IN FRONT OF CRANKCASE NOT SECURED CORRECTLY AND SHAFT SPINNING IN CRANKCASE.  SEALANT USED WAS A RED SILIC	ON MATERIAL USED MEASURING 0.0035 INCHES THICK WHEN REMOVED.  (X)						3	O			1E4				 
2001011100115	20010111	00115	NM  	2001	1	11	AU000758         	1	20000831	G	2701	521314	TORQUE TUBE     			AEROCD	100   	100         	       	NM  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A105	1A105SCM    	GL  	CONTROL COLUMN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL TORQUE TUBE CRACKED IN THREE PLACES IN THE AREA ADJACENT TO THE CONTROL COLUMN PIVOT.						1	L	7	1 	3O	3	O	NT	1A21    	E252	5	N	P918	 
2001011100116	20010111	00116	NM  	2001	1	11	AU000759         	1	20000831	G	2701	521314	TORQUE TUBE     			AEROCD	100   	100         	       	NM  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A105	1A105SCM    	GL  	CONTROL COLUMN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL TORQUE TUBE CRACKED. TORQUE TUBE ALSO EXHIBITED A 10 DEGREE TWIST FROM END TO END.						1	L	7	1 	3O	3	O	NT	1A21    	E252	5	N	P918	 
2001011100118	20010111	00118	SO  	2001	1	11	AU000760         	1	20000828	G	3246	300608	WHEEL           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN WHEEL INNER HALF CRACKED IN THE TIRE BEAD SEAT AREA RESULTING IN A SECTION BREAKING AWAY AND CAUSING THE T	IRE TO DEFLATE.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001011100119	20010111	00119	CE  	2001	1	11	AU000761         	1	20000828	G	3260		SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	MLG	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR UP LIMIT MICROSWITCH OUT OF ADJUSTMENT. ABURNING SMELL IN THE CABIN WAS ATTRIBUTED TO A RECEN	T COMPRESSOR WASH.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001011100145	20010111	00145	NM  	2001	1	11	AU000762         	1	20000825	G	2731	697045521	CONTROL CABLE   			BOEING	737   	737377      	       	NM  										ELEVATOR TAB	FRAYED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER TRIM CABLE HAD AN EXCESSIVE AMOUNT OF BROKEN STRANDS. APPROXIMATELY THIRTY STRANDS BROKEN IN	 A 609.6MM(24IN) LENGTH LOCATED IN THE EMPENNAGE AREA.					2	L	7	2 	4F			RT	A16WE   					 
2001011100146	20010111	00146	NM  	2001	1	11	AU000763         	1	20000725	G	2752	MX469871	BEARING         	VICKERS     	569670      	BOEING	737   	737377      	       	NM  										TE FLAP ACTUATOR	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			605  		MX469871					(AUS) TRAILING EDGE HYDRAULIC FLAP DRIVE MOTOR DRIVE SHAFT BEARING FAILED.						2	L	7	2 	4F			RT	A16WE   					 
2001011100147	20010111	00147		2001	1	11	AU000764         	4	20000829	G	3420	6466350	INDICATOR       			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					ATTITUDE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) ARTIFICIAL HORIZON FAULTY. A TOTAL OF THREE INDICATORS HAVE FAILED IN A FEW WEEKS.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100149	20010111	00149	EU  	2001	1	11	AU000765         	1	20000829	G	2421		GENERATOR       			BAC   	146   	146200A     	1500266	EU  										NR 1	FAILED          	W				A	 	 	 	UNSCHED LANDING         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 GENERATOR FAILURE. LIMITED INFORMATION PROVIDED.						2	H	7	4 	4F			 	A49EU   					 
2001011100543	20010111	00543		2001	1	11	AU000766         	4	20000901	G	2397		WIRE            			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	2AF34C	D2AF34C71   	GL  	PTT SWITCH	SHORTED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PRESS TO TALK (PTT) SWITCH STUCK IN THE TRANSMIT' POSITION.  INVESTIGATION FOUND THE THE PVT WIRE LOCATED IN THE C	ENTRE  PEDESTAL UNDER THE THROTTLE QUADRANT WAS SHORTING OUT.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P5EA	 
2000120700093	20001207	00093	CE  	2000	12	7	AU000767         	1	20000830	G	5540	51310103	BEARING         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RUDDER STRUCTURE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER RUDDER HINGE BEARING PLATE CORRODED.  UPON REMOVAL, THE BEARING PLATE WAS FOUND TO HAVE BEEN INSTALLED UPSID	E DOWN. THE BEARING PLATE APPEARED TO BE ORIGINAL FITMENT.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011100152	20010111	00152	NM  	2001	1	11	AU000768         	1	20000714	G	5313		INTERCOSTAL     			BOEING	737   	737377      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE INTERCOSTAL / STRINGER LOCATED AT S5L AT BS 303.9 CRACKED BOTH LONGITUDINALLY AND VERTICALLY.						2	L	7	2 	4F			RT	A16WE   					 
2000120700094	20001207	00094	CE  	2000	12	7	AU000769         	1	20000828	G	5711		SPAR            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING REAR SPAR ASSEMBLY UPPER AND LOWER SPAR CAPS CORRODED.  FOUND DURING INSPECTION IAW AD/C400/40 AMDT13.  	(X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000120700095	20001207	00095	CE  	2000	12	7	AU000770         	1	20000828	G	5711	51220313	SPAR CAP        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING LOWER SPAR CAP CORRODED. SPAR CAP EXHIBITS SIGNS OF PREVIOUS UNAPPROVED REPAIRS.  FOUND DURING INSPECTIO	N IAWAD/C400/40 AMDT13.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011100153	20010111	00153		2001	1	11	AU000772         	4	20000826	G	2310	6225272020	TRANSCEIVER     			BAC   	146   	AVRO146RJ100	1500096	EU  										HF COMMS	FAULTY          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) HF TRANSCEIVER CAUSES FIRE BELL TO RING WHEN TRANSMITTER KEYED. TRANSCEIVER HAD BEEN FITTED FOLLOWING REPAIR.						2	H	7	4 	4F			RT	A49EU   					 
2001011100154	20010111	00154	NM  	2001	1	11	AU000773         	1	20000716	G	5330		SKIN            			BOEING	737   	737377      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED ON THE LT SIDE JUST AFT OF THE WING LIGHT ASSEMBLY BETWEEN STN 500C AND STN 500D LOCATED ABO	VE STRINGER NR 15. CRACK LENGTH APPROXIMATELY 50MM (1.96IN).					2	L	7	2 	4F			RT	A16WE   					 
2000120700096	20001207	00096	EU  	2000	12	7	AU000774         	1	20000812	G	7931		PIPE            	LYC         		PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE OIL PRESS	WORN            	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE OIL PRESSURE LINE LOCATED BEHIND INSTRUMENT PANEL WORN BY OPILOT ASHTRAY.  OIL LEAKING.  (X)						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2001011100155	20010111	00155	EU  	2001	1	11	AU000775         	1	20000903	G	7712		BRIDGE          			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	ENGINE TORQUE	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE TORQUE STRAIN GAUGE NR 1 BRIDGE OUTPUT FAULTY.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001011100179	20010111	00179	SO  	2001	1	11	AU000776         	1	20000831	G	7712		CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					ENGINE TORQUE	CORRODED        	W				C	 	 	 	ABORTED TAKEOFF         				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE NP PROBE PLUG AND PINS CORRODED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000120700097	20001207	00097	CE  	2000	12	7	AU000777         	1	20000827	G	5744		FITTING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CONTROL SURFACE	LOOSE           	W				K	 	 	 	NONE                    				O	F	 	OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT AILERON FOULING ON UPPER WING SKIN PREVENTING FULL AILERON MOVEMENT.  FURTHER INVESTIGATION FOUND THAT THE I	NBOARD HINGE ATTACHMENT BRACKET WAS NOT SECURED. THE TWO LOWER ATTACHMENT SCREWS WERE INSTALLED BUT NOT SECURED TO THE A	NCHOR NUTS.  (X)				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001011100181	20010111	00181	SW  	2001	1	11	AU000778         	1	20000901	G	7722	P70141	HARNESS         			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	EGT INDICATOR	FAULTY          	W				O	 	 	 	OTHER                   				E	X	 	VIBRATION/BUFFET          	ENGINE FLAMEOUT           		DE	DESCENT        	1			AU	S 					P70141					(AUS) RT ENGINE EGT FLUCTUATING DUE TO FAULTY WIRING HARNESS. RT ENGINE FLAMED OUT DURING LANDING. FCU AND FUEL PUMP CHA	NGED.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2000120600037	20001206	00037	CE  	2000	12	6	AU000779         	1	20000828	G	2710		AILERON         			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	2AF34C	D2AF34C71   	GL  	AILERON CONTROL	SEIZED          	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) AILERONS JAMMED DURING CRUISE.  AILERONS FREED DURING DESCENT.  INVESTIGATION COULD FIND NO CAUSE OF JAMMING.  SUS	PECT ICING.  (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P5EA	 
2000120600038	20001206	00038	CE  	2000	12	6	AU000780         	1	20000904	G	2810		FILLER          			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	FUEL STORAGE	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK FILLER NECK CONTAMINATED WITH WASP NEST.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600039	20001206	00039	CE  	2000	12	6	AU000781         	1	20000904	G	2800		FUEL TANK       			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	AIRCRAFT FUEL SY	UNWANTED        	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MOGAS USED IN AIRCRAFT WITHOUT AN STC.   .  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600040	20001206	00040	CE  	2000	12	6	AU000782         	1	20000904	G	2823		SELECTOR VALVE  			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	FUEL SELECTOR/SH	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SELECTOR VALVE SEIZED.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600041	20001206	00041	GL  	2000	12	6	AU000783         	3	20000904	G	6111	1AMCM	BLADE           	MCAULY      	1A100MCM    	CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	PROPELLER BLADE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			2111 							(AUS) PROPELLER BLADES CORRODED CAUSING PAINT TO LIFT.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600042	20001206	00042		2000	12	6	AU000784         	4	20000904	G	2300		VHF COMM        			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	COMMUNICATIONS S	INACCURATE      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AVIONICS FIT NOT RECORDED OR CERTIFIED IN AIRCRAFT LOG BOOK.  ITEMS NOT ACCOUNTED FOR:  1. IC-A200 VHF SNO 139702.	 KT76A ATC TRANSPONDER SNO 117656.  3. AMER-KING ENCODER SNO 35243954.  SPA-400 TSO SIGTRONICS CORP INTERCOM SNO 6055958	.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600043	20001206	00043	CE  	2000	12	6	AU000785         	1	20000904	G	3411		PITOT LINE      			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	PITOT/STATIC SYS	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PITOT/STATIC SYSTEM FAILED LEAK TEST.  INVESTIGATION FOUND THE PITOT SYSTEM CONNECTOR LOCATED AT THE LEFT WING BRE	AK WAS CROSS-THREADED AND ONLY HOLDING BY ONE TURN.  THE STATIC SYSTEM HAD BEEN REWORKED TO ACCOMMODATE THE ENCODED.  TH	E EXISTINGPLUMBING HAD BEEN CUT AND LARGER PLASTIC TUBING SLIPPED OVER IT TO FIT THE BRASS TEE.  UNAPPROVED PART.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600044	20001206	00044	CE  	2000	12	6	AU000786         	1	20000904	G	7160		HOSE            	CONT        		CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ENG AIR INTAKE	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETOR HEAT HOSE LOCATED BETWEEN FORWARD RIGHT ENGINE BAFFLE AND THE RIGHT MUFFLER MISSING.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600045	20001206	00045	CE  	2000	12	6	AU000787         	1	20000904	G	2510		SEAT BELT       			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	FLIGHT COMPARTME	MISINSTALLED    	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT SEAT BELT OUTBOARD ATTACHMENT POINTS INCORRECT.  THE BELTS WERE ATTACHED TO THE FORWARD BAGGAGE FLO	OR WITH AN3 BOLTS INSTEAD OF TO THE CORRECT POSITION BELOW THE DOOR CUTOUTS USING 6.35 MM (0.25 INCH) HARDWARE AND BUSHE	S.  UNAPPROVED PARTS.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600046	20001206	00046	CE  	2000	12	6	AU000789         	1	20000904	G	3240	7410	BRAKE ASSY      	CLEVELAND   	CFP3063     	CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	LANDING GEAR BRA	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BRAKE ASSEMBLY BACK PLATES P/N 74-10 AND PRESSURE PLATES P/N 73-11 BADLY CORRODED.  BRAKE LININGS CRACKED.  ONE BR	AKE BLEEDER SCREW BROKEN AND BOTH BRAKER BLEEDER SEAT HEXAGONALS COMPLETELY ROUNDED.  BRAKE SEALS LEAKING.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600047	20001206	00047	CE  	2000	12	6	AU000790         	1	20000904	G	3246	15315	SEAL            	CLEVELAND   	CFP4097     	CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	WHEEL/SKI/FLOAT	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WHEEL BEARING SEALS DAMAGED AND/OR FELT MISSING.  WHEEL NUT SPLIT PIN TAILS NOT BENT OVER.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600048	20001206	00048	CE  	2000	12	6	AU000791         	1	20000904	G	2810		SEAL            			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL STORAGE SYSTEM SEALS AND GASKETS DETERIORATED.  SEALS AFFECTED:  1. FUEL TANK GASKETS DETERIORATED.  2.  FUEL	 CAP SEALS DETERIORATED.  3.  LEFT AND RIGHT FUEL TANK DRAIN VALVE SEALS DETERIORATED.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600049	20001206	00049	CE  	2000	12	6	AU000792         	1	20000904	G	1100		PLATE           	CONT        	O200A       	CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ENGINE (RECIPROC	INACCURATE      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE DATA PLATE NOT STAMPED FOR COMPLIANCE WITH AD/CON/75.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600050	20001206	00050	CE  	2000	12	6	AU000793         	1	20000904	G	2510		SEAT            			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	FLIGHT COMPART	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOT AND COPILOT SEAT ROLLERS SEIZED.  COPILOT''S SEAT RELEASE ROD BENT AND FOULING ON THE STRUCTURE BENEATH THE 	SEAT PREVENTING THE SEAT FROM LOCKING.  PILOT''S SEAT LEFT SEAT RAIL CRACKED AT INBOARDFORWARD ATTACHMENT SKIN.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600051	20001206	00051		2000	12	6	AU000794         	4	20000904	G	3420		GAUGE           			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ATTITUDE AND DIR	UNSERVICEABLE   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ARTIFICIAL HORIZON, DIRECTING GYRO AND CYLINDER HEAD TEMPERATUREGAUGE UNSERVICEABLE.  UNSERVICEABLE INSTRUMENTS NO	T PLACARDED IAW CAO 20.18.10. S TANDBY COMPASS HAD 23 DEGREES ERROR ON WEST.   (X)					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600052	20001206	00052	CE  	2000	12	6	AU000795         	1	20000904	G	7110	04520026	CAP             	CONT        		CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ENGINE COWLING S	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE COWL NOSE CAP CRACKED. CRACK LENGTH 100 M (4 INCHES).  NOSE CAP HAD BEEN ILLEGALLY REPAIRED USING A FIRE EX	TINGUISHER DATE PLATE, POP RIVETS AND LIQUID NAILS.  UNAPPROVED REPAIR.  (X)					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600053	20001206	00053	CE  	2000	12	6	AU000796         	1	20000904	G	3252		DAMPER          			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	SHIMMY DAMPER	FAULTY          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SHIMMY DAMPER LOW ON FLUID.  ON FURTHER INVESTIGATION THE FOLLOWING COMPONENTS WERE FOUND TO BE DAMAGED:  1. HEAD 	BEARING P/N 0542102-3.   2.  ROLL PIN P/N NAS 561P4-143.  RING RETAINER P/N MS16625-1118.  DAMPER WAS ATTACHED BY TWO FU	LLY THREADED METRIC BOLTS.  UNAPPROVED PART.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000120600054	20001206	00054	CE  	2000	12	6	AU000797         	1	20000904	G	5740		FITTING         	CESSNA      	150F        	CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	WING ATTACH FITT	OUT OF ADJ      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT MAIN PLANE ATTACHMENT FITTING CONCENTRIC BUSHES OUT OF ADJUSTMENT CAUSING AIRCRAFT TO ROLL TO THE LEFT.  	LEFT WING WAS UNABLE TO BE ADJUSTED AS THE BUSH WAS FOUND TO BE IN THE MAXIMUM POSITION. THE ADJUSTMENT HAD TO BE CARRIE	D OUT ON THE RIGHT WING BUSH.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001011100182	20010111	00182	NM  	2001	1	11	AU000798         	1	20000828	G	5610	17180003	WINDOW          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT SIDE COCKPIT WINDOW CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000120700098	20001207	00098	SO  	2000	12	7	AU000799         	1	20000906	G	2140	461731	REGULATOR       	JANITROL    	FR65D793EL  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			7    		A92080029					(AUS) CABIN FUEL HEATER REGULATOR LEAKING.  SUBMITTER SUSPECTED HOLED DIAPHRAGM.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000120700099	20001207	00099	SO  	2000	12	7	AU000800         	2	20000805	G	7414	10106498	HOUSING         	BENDIX      	S6RN201     	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MAGNETO/DIST	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			784  		1269595ER					(AUS) MAGNETO TOP HOUSING CRACKED AROUND BEARING.  (X)						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001011100184	20010111	00184	NM  	2001	1	11	AU000801         	1	20000715	G	2782	256T21205	ACTUATOR        			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					LE FLAP	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			13773							(AUS) NR 11 LEADING EDGE SLAT INBOARD ROTARY ACTUATOR INTERNALLY CORRODED. RING GEAR SEAL MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000112200005	20001122	00005	EA  	2000	11	22	AU000802         	2	20000905	G	7414	67542	BEARING         	LYC         		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAGNETO/DIST	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAGNETO ADAPTER BEAR FAULTY.  BEARING HAD NO CAGE FITTED.  FOUND WHEN MAGNETO WAS REMOVED DUE TO BROKEN DRIVE CUSH	IONS P/N LW-13641.  (X)					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001011100186	20010111	00186	NM  	2001	1	11	AU000803         	1	20000731	G	3233	273T63002	ACTUATOR        			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					MLG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 					00056					(AUS) RT MAIN LANDING GEAR DRAG BRACE ACTUATOR PISTON ROD PN 273T6034-1 FRACTURED IN THREADED END.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011100188	20010111	00188	NM  	2001	1	11	AU000804         	1	20000621	G	2910	V643602	FUSE            			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					HYD SYSTEM	CRACKED         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			7641 							(AUS) OUTBOARD HYDRAULIC FUSE ON BRAKE MODULE CRACKED IN VALVE BODY. VALVE IS LOCATED AT THE WING TRAILING EDGE OUTBOARD	 OF THE LT MAIN LANDING GEAR. LOSS OF RT HYDRAULIC SYSTEM FLUID.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011100189	20010111	00189	EU  	2001	1	11	AU000805         	1	20000601	G	2910	SA7670006155	HOSE            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD SYSTEM	WORN            	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE HYDRAULIC PUMP PRESSURE HOSE CHAFED THROUGH BY ADEL CLAMP. LOSS OF YELLOW' SYSTEM HYDRAULIC FLUID.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011100235	20010111	00235	SO  	2001	1	11	AU000806         	1	20000907	G	2750		HANDLE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					TE FLAP CONTROL	STUCK           	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP SELECTOR HANDLE STICKING.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000120700100	20001207	00100	CE  	2000	12	7	AU000807         	1	20000905	G	7714	041108728	TACHOMETER      	CESSNA      	041108728   	CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ENGINE RPM IND	WORN            	W				K	 	 	 	NONE                    				E	I	 	VIBRATION/BUFFET          	FLT. ATTITUDE INST.       		CR	CRUISE         	1			AU	S 					13471					(AUS) TACHOMETER FAILED.  ITEM HAD BEEN LAST OVERHAULED IN 1972.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2001011100236	20010111	00236	EU  	2001	1	11	AU000808         	1	20000907	G	3244	404F63T2	TIRE            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					LT MLG	SEPARATED       	W				C	 	 	 	ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) LT MAIN LANDING GEAR NR 2 TIRE TREAD SEPARATED. DAMAGE TO LT INBOARD FLAP LEADING EDGE AND FLAP VANE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2000120700101	20001207	00101	SO  	2000	12	7	AU000809         	1	20000828	G	2810	557003	ADAPTER         		531035      	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL STORAGE	FAILED          	W				K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) RIGHT WING FUEL ADAPTER FAULTY.  FUEL CAP CAME LOOSE.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011100237	20010111	00237	EU  	2001	1	11	AU000810         	1	20000906	G	2810		FUEL TANK       			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING TANK HAD EVIDENCE OF PITTING CORROSION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000120700102	20001207	00102	SO  	2000	12	7	AU000811         	1	20000829	G	2140	A230048	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 			520  							(AUS) CABIN HEATER REGULATOR LEAKING FROM DIAPHRAGM.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000120700103	20001207	00103	SO  	2000	12	7	AU000812         	1	20000831	G	2140	A230048	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN HEATER REGULATOR LEAKING FROM DIAPHRAGM.  BASE PLATE APPEARS WARPED.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000120700104	20001207	00104	CE  	2000	12	7	AU000813         	1	20000912	G	5312	121340710	BULKHEAD        			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOORPOST BULKHEAD CRACKED ON LEFT AND RIGHT SIDES.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2000120700105	20001207	00105	CE  	2000	12	7	AU000814         	1	20000912	G	5711	07214024	ANGLE           			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING LOWER SPAR CAP ANGLE CONTAINED INTERGRANNULAR CORROSION.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2000113000025	20001130	00025	CE  	2000	11	30	AU000815         	1	20000912	G	5711	07214003	ANGLE           			CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SPAR CAP ANGLE CONTAINED EXFOLIATION CORROSION.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2001011100238	20010111	00238	EU  	2001	1	11	AU000816         	1	20000907	G	3260	JE5	ACTUATOR        			BAG   	JETSTM	JETSTM3201  	1500217	EU  						ROTOL	R333	R333482F12  	GL  	MLG	BROKEN          	W				O	 	 	 	OTHER                   				O		 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR DOOR SWITCH ACTUATOR BROKEN.						2	L	7	2 	4T			RT	A56EU   		6	C	P61GL	 
2000113000026	20001130	00026	CE  	2000	11	30	AU000817         	1	20000907	G	5341	0512122	FITTING         			CESSNA	150   	150B        	2071806	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	WING ATTACH FITT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT WING REAR ATTACHMENT FITTINGS CORRODED.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000113000027	20001130	00027	CE  	2000	11	30	AU000818         	1	20000904	G	3260	MS272401	SWITCH          			CESSNA	441   	441         	2076020	CE  						MCAULY	3G34C6	3GFR34C601  	GL  	LANDING GEAR POS	FAULTY          	W				K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR UPLOCK MICROSWITCH FAILED.  LEFT MAIN LANDING GEAR UPLOCK MICROSWITCH INTERMITTENT IN OPER	ATION.  (X)					1	L	7	2 	3T			RT	A28CE   		6	C	P54GL	 
2000113000028	20001130	00028	CE  	2000	11	30	AU000819         	1	20000907	G	3297	G12C20	WIRE            			CESSNA	441   	441         	2076020	CE  										LANDING GEAR SEL	BROKEN          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC SELECTOR VALVE WIRE BROKEN AT TERMINAL CONNECTOR.  (X)						1	L	7	2 	3T			RT	A28CE   					 
2000113000029	20001130	00029	EU  	2000	11	30	AU000820         	1	20000911	G	7603		PIN             	LYC         		BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	POWER LEVER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THROTTLE FRICTION ADJUSTER SHAFT SPLIT PIN DEFORMED AND PARTIALLY SHEARED.  (X)						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2000113000030	20001130	00030	CE  	2000	11	30	AU000821         	1	20000911	G	5521	12346501	TORQUE TUBE     		12340192    	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ELEVATOR SPAR/RI	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TORQUE TUBE CRACKED ON INBOARD END.  DISASSEMBLY FOUND SIGNIFICANT CORROSION BETWEEN THE TORQUE TUBE AND 	THE SPAR MOUNTING BRACKET.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001011100239	20010111	00239	SW  	2001	1	11	AU000822         	1	20000816	G	3213	2752529003	SHAFT           			SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	MLG	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 			664  							(AUS) LT MAIN LANDING GEAR UPPER TORQUE LINK SHAFT BROKEN.						2	L	7	2 	4T			RT	A8SW    		6	C	P61GL	 
2001011100240	20010111	00240	WP  	2001	1	11	AU000823         	1	20000903	G	2911	5133124	ACCUMULATOR     			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	HYD SYSTEM	FAULTY          	W				O	 	 	 	OTHER                   				F		 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 			4    		3545					(AUS) HYDRAULIC ACCUMULATOR FAULTY.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2000112800106	20001128	00106	WP  	2000	11	28	AU000824         	1	20000810	G	6320	269A505073	BEARING         			HUGHES	269   	269B        	4470502	WP  	LYC   	O360  	HIO360A1A   	41514	EA  					M/R GEARBOX	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			384  							(AUS) MAIN ROTOR DRIVE SHAFT THRUST BEARING WAS INCORRECTLY INSTALLED. DISCRPENCY WAS FOUND DURING INSPECTION IAW AD HU2	69/28 AMDT3.  (X)					1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2001011100242	20010111	00242	SW  	2001	1	11	AU000825         	1	20000904	G	2752	2736053003	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FLAP ACTUATOR BODY CRACKED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011100244	20010111	00244	EU  	2001	1	11	AU000826         	1	20000904	G	3020		CONNECTOR       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					INTAKE ANTI ICE	DIRTY           	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 ENGINE INTAKE LOW PRESSURE SWITCH CANNON PLUG DIRTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011104403	20010111	04403		2001	1	11	AU000827         	1	20000907	G	7732		TRANSDUCER      	LYC         	ALF502R5    			            			LYC   	ALF502	ALF502R5    	41580	NE  			            		ENGINE VIBRATION	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE VIBRATION TRANSDUCER PLUG BROKEN. PINS MISSING AND BAREWIRES SHOWING. ENGINE HAD BEEN RECEIVED FROM USA.											4	F			E6NE				 
2001011100309	20010111	00309	EU  	2001	1	11	AU000828         	1	20000905	G	3320		LIGHT           			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					CABIN	FAILED          	W				K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) LAMP HOLDERS LOCATED AT ROW 14 AND ROW 10 ON THE RT SIDE WALLS BURNED OUT.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100546	20010111	00546		2001	1	11	AU000829         	4	20000906	G	2397		WIRE            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					INTERPHONE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GROUND CALL HORN WIRE FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100363	20010111	00363	EU  	2001	1	11	AU000831         	1	20000908	G	3320	6524001	BALLAST         			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	CABIN	FAILED          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) CABIN LIGHTING BALLAST LOCATED ABOVE ROW 3 FAILED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011100364	20010111	00364		2001	1	11	AU000832         	4	20000906	G	3418		WARNING SYSTEM  			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING SY	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) STALL WARNING SYSTEM FAULT INDICATION. INVESTIGATION COULD FIND NO FAULT WITH THE SYSTEM. SUSPECT CAUSED BY GUSTIN	G CROSSWIND.					2	L	7	2 	4F			RT	A21EA   					 
2001011100365	20010111	00365	SW  	2001	1	11	AU000833         	1	20000908	G	3260		UPLOCK BRACKET  			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	MLG	STIFF           	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK HOOK STIFF IN OPERATION.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100366	20010111	00366	EU  	2001	1	11	AU000834         	1	20000907	G	3260		HARNESS         			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R320	R3204123F1  	NE  	MLG	SHORTED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LANDING GEAR EMERGENCY EXTENSION ELECTRICAL HARNESS OPEN CIRCUITED. INVESTIGATION FOUND A BROKEN WIRE IN THE HA	RNESS.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P5NE	 
2001011100367	20010111	00367	EA  	2001	1	11	AU000835         	1	20000801	G	2910	D97C00614	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FIREWALL HYDRAULIC SHUT-OFF VALVE ACTUATOR FAULTY.						2	L	7	2 	4F			RT	A21EA   					 
2001011100368	20010111	00368	EU  	2001	1	11	AU000836         	1	20000904	G	3020		SWITCH          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					INTAKE ANTI ICE	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 ENGINE INTAKE LOW PRESSURE WARNING SWITCH PLUG DIRTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2000113000031	20001130	00031	EU  	2000	11	30	AU000837         	1	20000828	G	6123	15M3	SWITCH          	MCAULY      		REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	PROP FEATHER	FAULTY          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LEFT AUTOFEATHER MICROSWITCH FAULTY.  (X)						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001011100369	20010111	00369	NM  	2001	1	11	AU000838         	1	20000908	G	2730		STOP            			DHAV  	DHC8  	DHC8202     	2809007	NM  										ELEVATOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR BUMPER STOPS FAILED ALLOWING THE ELEVATOR TO CONTACT THE RUDDER. RT ELEVATOR TRIM TAB AND RUDDER TRAILING	 EDGE DAMAGED.					2	H	7	2 	4T			RT	A13NM   					 
2000113000032	20001130	00032	NE  	2000	11	30	AU000839         	2	20000814	G	8520	NO7	PIN             	PWA         		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					4224837					(AUS) NO7 LINK PIN DISPLACED.  (X)						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000112200006	20001122	00006	SW  	2000	11	22	AU000840         	1	20000907	G	6320	7001F000X116	HOSE            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR GRBOX	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRANSMISSION OIL HOSE FAILED.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000112200007	20001122	00007	GL  	2000	11	22	AU000841         	2	20000825	G	7261	6853464	PIPE            	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	E	K	OTHER                     	VIBRATION/BUFFET          	FLUID LOSS                	IN	INSP/MAINT     	1			AU	S 					31388					(AUS) ENGINE OIL PIPE LEAKING IN AREA BENEATH P'' CLIPS.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000101100452	20001011	00452	WP  	2000	10	11	AU000842         	2	20000913	G	7250		TURBINE         	GARRTT      							GARRTT	TPE331	TPE331*     	01514	WP  					TURBINE SECTION	INACCURATE      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRST STAGE TURBINE WHEEL AND THIRD STAGE STATOR SERIAL NUMBERS DID NOT MATCH THE SERIAL NUMBERS IN THE LOGBOOK OR	 LOG CARDS.   (X)										3	T			E2WE				 
2001011100370	20010111	00370	NM  	2001	1	11	AU000844         	1	20000902	G	3260		PLUG            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					MLG	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT GROUND SHIFT PLUGS D4574P AND D4852P CONTAMINATED WITH EXCESS MOISTURE. SUSPECT MOISTURE CONTAMINATED PLUGS FOL	LOWING A WHEEL WELL WASH.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011100371	20010111	00371	EU  	2001	1	11	AU000845         	2	20000902	G	7310	737M28500011	VALVE           			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL DIST	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE FUEL VALVE FAILED TO OPEN DURING ENGINE START.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011100373	20010111	00373	NM  	2001	1	11	AU000846         	1	20000909	G	2820		VALVE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL DIST	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 SPAR VALVE FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2000101100453	20001011	00453	CE  	2000	10	11	AU000847         	1	20000913	G	5741	05233091	ANGLE           		0523309     	CESSNA	206   	U206B       	2073322	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	WING, FUSELAGE A	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT WING FORWARD ATTACHMENT FITTING ANGLES CONTAINED INTERGRANNULAR CORROSION.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2000101100454	20001011	00454	CE  	2000	10	11	AU000848         	1	20000907	G	3520	174412030	SOLENOID        	AEROSPACECMP	44021       	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PASSENGER OXYGEN	OPEN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 			548  		027					(AUS) PASSENGER OXYGEN MASKS DID NOT DEPLOY DURING TEST FLIGHT.  INVESTIGATION FOUND SOLENOID OPEN CIRCUIT.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000101100455	20001011	00455	SO  	2000	10	11	AU000849         	2	20000423	G	8530	631639	EXHAUST VALVE   	CONT        		CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ENGINE	SEIZED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) NR 4 CYLINDER EXHAUST VALVE STUCK IN VALVE GUIDE.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2001011100419	20010111	00419	NM  	2001	1	11	AU000850         	1	20000829	G	3242		NUT             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					BRAKE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO3 FRONT BRAKE EQUALISER ROD TO BRAKE ATTACHMENT PIN RETENTION NUT BACKED OFF WITH APPROXIMATELY TWO THREADS LEFT	 BEFORE THE NUT WOULD HAVE FALLEN OFF.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011100421	20010111	00421	NM  	2001	1	11	AU000851         	1	20000828	G	5210		HANDLE          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PAX DOOR	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD ENTRY DOOR HANDLE HAD EXCESSIVE FREE PLAY. DURING OPERATION THE INTERIOR HANDLE SEPARATED FROM THE SHAFT P	REVENTING THE DOOR FROM BEING OPERATED FROM THE INSIDE.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011100422	20010111	00422	NM  	2001	1	11	AU000852         	1	20000826	G	2710	252T21182	BELLCRANK       			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					AILERON CONTROL	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PCA BELLCRANK SHEAR RIVETS FAILED. FOUND DURING INSPECTION IAW EI 767-027-0112 AND FAA AD 2000 17-05.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011100423	20010111	00423	NM  	2001	1	11	AU000853         	1	20000825	G	2710		BELLCRANK       			BOEING	767   	767338      	1385151	NM  										AILERON CONTROL	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PCA BELLCRANK SHEAR RIVETS FAILED. FOUND DURING INSPECTION IAW EI 767-027-0112 AND FAA AD 2000-18-05.						2	L	7	2 	4F			RT	A1NM    					 
2001011100424	20010111	00424	NM  	2001	1	11	AU000854         	1	20000828	G	3244	161U00011	TIRE            			BOEING	747   	747438      	       	NM  										MLG	SEPARATED       	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 4 RT TIRE TREAD SEPARATED. DAMAGE TO AIRCRAFT.						2	L	7	4 	4F			RT	A20WE   					 
2001011100425	20010111	00425	NM  	2001	1	11	AU000855         	1	20000901	G	5314		KEELBEAM        			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) KEEL BEAM WEB CORRODED AT STN 950 LOCATED IN THE UPPER AFT CORNER OF THE LT WHEEL WELL. FOUND DURING CORROSION INS	PECTION.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100426	20010111	00426	NM  	2001	1	11	AU000856         	1	20000901	G	5720		WEB             			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER WEB LOCATED IN THE LT UPPER WHEEL WELL AT STN 870 BETWEEN WBL 0 AND WBL 24.75 CORRODED. FOUND DURING CORROSI	ON INSPECTION.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100427	20010111	00427	NM  	2001	1	11	AU000857         	1	20000901	G	5720		FITTING         			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					LT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SPLICE FITTING LOCATED BETWEEN STN 870 FORGING AND HORIZONTAL BEAM LOCATED IN LT WHEEL WELL CORRODED. FOUND DURING	 CORROSIONINSPECTION.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100428	20010111	00428	NM  	2001	1	11	AU000858         	1	20000901	G	5320		ANGLE           			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BULKHEAD T' ANGLE LOCATED IN RT WHEEL WELL AT STN 950 CORRODED AT KEEL BEAM ATTACHMENT. FOUND DURING CORROSION INS	PECTION.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100429	20010111	00429	NM  	2001	1	11	AU000859         	1	20000902	G	5330		SKIN            			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER CENTRE LINE FUSELAGE SKIN CORRODED AT STN 360. FOUND DURING CORROSION INSPECTION.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100430	20010111	00430	NM  	2001	1	11	AU000860         	1	20000902	G	5711		SPAR            			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR SPAR UPPER CHORD CORRODED AT UPPER SKIN INTERFACE INBOARD OF NR 4 SPOILER INBOARD HINGE. FOUND DURING CORROSI	ON INSPECTION.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100476	20010111	00476	NM  	2001	1	11	AU000861         	1	20000901	G	5711		SPAR CAP        			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR SPAR CAP CORRODED AT UPPER SKIN INTERFACE ADJACENT TOOUTBOARD FLAP OUTBOARD JACKSCREW GEARBOX. FOUND DURING C	ORROSIONINSPECTION.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001011100547	20010111	00547	SW  	2001	1	11	AU000862         	1	20000914	G	2897		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AUXILIARY BOOST PUMP WIRE WORN. LT MAIN BOOST PUMP WIRE INSULATION WORN.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100548	20010111	00548	SW  	2001	1	11	AU000863         	1	20000913	G	2897		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AUXILIARY FUEL BOOST PUMP WIRES WORN.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011100549	20010111	00549	SW  	2001	1	11	AU000864         	1	20000908	G	2897		WIRE            	SWRNGN      	3282030002  	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AUXILIARY BOOST PUMP WIRE INSULATION WORN.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100550	20010111	00550	SW  	2001	1	11	AU000865         	1	20000914	G	2897		WIRE            	SWRNGN      	32820391    	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AUXILIARY FUEL BOOST PUMP AND LT MAIN FUEL BOOST PUMP WIRING DAMAGED.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011100551	20010111	00551	SW  	2001	1	11	AU000866         	1	20000915	G	2897		WIRE            	SWRNGN      	32820301    	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN FUEL BOOST PUMP AND RT AUXILIARY FUEL BOOST PUMP WIRESWORN.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011100577	20010111	00577	SW  	2001	1	11	AU000867         	1	20000914	G	2897		WIRE            	SWRNGN      	3282030001  	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	BOOST PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUEL BOOST PUMP WIRE INSULATION WORN.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011101761	20010111	01761	NE  	2001	1	11	AU000868         	2	20000914	G	7321	70886M60G11	ECU             	GE          	CT75A2      	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	FUEL CONTROL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	M	J	VIBRATION/BUFFET          	OVER TEMP                 	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 					367249					(AUS) LT ENGINE ELECTRICAL CONTROL UNIT FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011101762	20010111	01762	EA  	2001	1	11	AU000869         	1	20000721	G	2731	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										ELEVATOR TAB	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) HORIZONTAL STABILISER TRIM ACTUATOR (HSTA) FAULTY. NR 1 CHANNEL MOTOR FAULTY.						2	L	7	2 	4F			RT	A21EA   					 
2001011101763	20010111	01763	EA  	2001	1	11	AU000870         	1	20000914	G	2910	D97C00614	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FIREWALL HYDRAULIC SHUTOFF VALVE ACTUATOR FAULTY.						2	L	7	2 	4F			RT	A21EA   					 
2000101300111	20001013	00111	SO  	2000	10	13	AU000871         	1	20000915	G	2810		FUEL CELL       			AMRGEN	AA5   	AA5A        	3960106	SO  	LYC   	O360  	O360*       	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	FUEL STORAGE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK ACCESS PANEL BONDED DOUBLER DISBONDED FROM WING SKINDUE TO CORROSION.  FUEL LEAKING THROUGH TO OUTSIDE S	KIN. FUEL TANK SEALING COMPOUND FOUND TO BE VERY SOFT AND LIFTING OFF IN SOME AREAS.  WATER CONTAMINATION OF FUEL CELLS.	  SUBMITTER SUSPECTED WATER LEFT OVER FROM FUEL CELL DECONTAMINATION IN JANUARY 2000.  SUSPECT IPA USED IN THE DECONTAMI	NATION PROCESS CAUSED THE DETERIORATION OF THE TANK SEALANT WHICH THEN LED TO THE CORROSION AND FUEL LEAKAGE.  (X)			1	L	7	1 	3O	3	O	 	A16EA   	E286	5	N	P857	 
2000101800080	20001018	00080	CE  	2000	10	18	AU000873         	1	20000821	G	3230	08411068	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR IDLER BELLCRANK FAILED.  DURING RETRACTION THE MAIN WHEEL DID NOT CLEAR THE INBOARD DOOR R	ESULTING IN THE FAILURE OF THE DOWNLOCK BELLCRANK.  (X)					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000101800002	20001018	00002	CE  	2000	10	18	AU000874         	1	20000905	G	2434	318	ALTERNATOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	DC GENERATOR-ALT	FAULTY          	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 					8070446					(AUS) ALTERNATOR FAILED.  INVESTIGATION COULD FIND NO FAULT.  SUBMITTER SUSPECTED CAUSED BY STICKING BRUSH.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000101800081	20001018	00081	CE  	2000	10	18	AU000875         	1	20000908	G	3230	HMXL6G	ROD END         			BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	LANDING GEAR RET	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR REAR ACTUATING ROD ROD END SEIZED AND FAILED ALLOWING NLG TO COLLAPSE ON LANDING.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2000101800082	20001018	00082	CE  	2000	10	18	AU000876         	1	20000908	G	5312	0024400249	BULKHEAD        		44002411    	BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR TAILCONE BULKHEAD LOCATED AT BS 271.92 CRACKED THROUGH WEB IN AREA OF RIGHT LOWER CARRY THROUGH SPAR CUT-OUT.	  (X)					1	L	7	2 	3O			 	3A16    		5	C	P22EA	 
2000101800083	20001018	00083	CE  	2000	10	18	AU000877         	1	20000913	G	5312	0024400249	BULKHEAD        		44002411    	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR TAILCONE BULKHEAD LOCATED AT BS 271.92 CRACKED THROUGH BULKHEAD AND WEB IN THE AREA OF THE LEFT LOWER CARRY T	HROUGH SPAR CUT-OUT.  CRACK LENGTH APPROXIMATELY 10.41 MM (0.41 INCH).  (X)					1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P22EA	 
2001011101764	20010111	01764	NE  	2001	1	11	AU000878         	2	20000915	G	7261	310573501	RELIEF VALVE    			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					ENGINE OIL PRESS	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE OIL PRESSURE REGULATING VALVE OUT OF ADJUSTMENT.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000101900280	20001019	00280	CE  	2000	10	19	AU000879         	1	20000915	G	3520	13240822	DIODE           			BEECH 	300   	B300C       	       	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PASSENGER OXYGEN	SHORTED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) CABIN OXYGEN CONTROL SOLENOID TRANSIENT VOLTAGE SUPPRESSION DIODE SHORT CIRCUITED.  FAILURE OF PASSENGER OXYGEN MA	SK AUTOMATIC DEPLOYMENT.  (X)					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P15EA	 
2000113000033	20001130	00033	EU  	2000	11	30	AU000880         	1	20000912	G	3250	5325012055	FLANGE          			PILATS	PC12  	PC12        	7090550	EU  										LANDING GEAR STE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL STEERING SYSTEM BEARING RETAINER AND RETAINING BOLTS LOOSE.  (X)						1	L	7	1 	3T			RT	A78EU   					 
2000113000034	20001130	00034	EU  	2000	11	30	AU000881         	1	20000810	G	2620		WIRE            			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	EXTINGUISHING SY	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 FIRE BOTTLE SQUIB WIRING INCORRECTLY WIRED TO THE BOTTLE ARM/FIRING SWITCH.  SUBMITTER STATED THIS WOULD HAVE	 PREVENTED OPERATION OF THE FIRE BOTTLE.  SUSPECT MANUFACTURING ERROR.  (X)					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2000113000035	20001130	00035	EA  	2000	11	30	AU000882         	2	20000914	G	7322	1041641	CARBURETOR      	LYC         	O360A3A     	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  	SNSNCH	76E	76EM8       	EA  	FUEL CONTROL/CAR	FAULTY          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1361 							(AUS) CARBURETOR PRIMARY VENTURI DISLODGED.  VENTURI WAS A TWO-PIECE ITEM.  (X)						1	L	7	1 	3O	3	O	 	2A13    	E286	5	N	P4EA	 
2000113000036	20001130	00036	NE  	2000	11	30	AU000883         	2	20000710	G	7200	T700	ENGINE          	GE          	T700SERIES  						GE    	TC7TS 	T700T1C     	30029	NE  					ENGINE	WRONG PART      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GENERAL ELECTRIC T700 GAS TURBINE ENGINES AS USED BY MILITARY HELICOPTERS WERE FOUND TO CONTAIN UNAPPROVED PARTS. 	GE T700 ENGINE COMES FROM THE SAME FAMILY OF ENGINES AS GE CT7 ENGINE. THIS DEFECT RECEIVED FROM ADF AS WARNING TO CIVIL	IAN OPERATORS OF GE CT7SERIES ENGINES.  FOLLOWING PARTS AFFECTED:  NUT SELF-LOCKING - NSN 5310-01-102-8856 - GE P3031T29	.  STUD SHOULDERED - NSN 5307-01-099-2481 - GE P4041T11P02.  NUT SELF-LOCKING - NSN 5310-00-129-6126 - GE P/N R1180.  ST	UD SWIRL PLATE - NSN 53 07-01-235-7902 - GE P4076T45P02.  W8 COUNTERBALANCE - NSN 2840-01-143-3372 - GE P/N 4069T98P04. 	 TUBE OIL SUMP - NSN 4710-01-089-4109 - GE P4041T52P01.  (X)						4	U			E8NE				 
2001011101766	20010111	01766	EU  	2001	1	11	AU000884         	1	20000919	G	5610	NF20216246	WINDSHIELD      			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) COPILOTS A  WINDSHIELD OUTER PANE CRACKED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011101770	20010111	01770	EU  	2001	1	11	AU000885         	1	20000527	G	5751		RIB             			BAC   	146   	AVRO146RJ70A	1500095	EU  										AILERON	DAMAGED         	W				O	 	 	 	OTHER                   				C	 	 	F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) RT AILERON DAMAGED DURING GROUND HANDLING. RIB 20 AND FAIRING DAMAGED.						2	H	7	4 	4F			RT	A49EU   					 
2001011101771	20010111	01771	EU  	2001	1	11	AU000886         	1	20000424	G	3234	HTE210014	MOTOR           			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 					190GB189H					(AUS) LANDING GEAR SELECTOR VALVE MOTOR FAULTY. WORKSHOP INVESTIGATION FOUND THE CLUTCH SLIPPING DUE TO WORN CLUTCH PADS	 AND INSUFFICIENT SPRING TENSION ON THE CLUTCH.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011101804	20010111	01804		2001	1	11	AU000887         	4	20000311	G	2370	9806005076	CVR             			BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					COCKPIT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT VOICE RECORDER (CVR) FAULTY. WORKSHOP INVESTIGATION FOUND INTERMITTENT FAILURE DUE TO TAPE DEPOSIT ON RECO	RDING HEADS CAUSING LOW AUDIO ON TRACK 2.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011101810	20010111	01810	EU  	2001	1	11	AU000888         	1	20000322	G	2450	503CA02F102Y1	CONTACTOR       			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					AC POWER DISTRIB	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AC ESSENTIAL BUS FEED SWITCH CONTACTOR 3XC FAULTY.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011101849	20010111	01849		2001	1	11	AU000889         	4	20000714	G	3460	B397BAM0513	COMPUTER        			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FLIGHT MANAGE	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 					5454ANSCCN44					(AUS) FLIGHT AUGMENTATION COMPUTER (FAC) SUSPECT FAULTY. WORKSHOP INSPECTION COULD NOT FAULT ITEM.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011101850	20010111	01850	NM  	2001	1	11	AU000890         	1	20000724	G	2721	658D1003	ACTUATOR        			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					RUDDER TAB	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) RUDDER TRIM ACTUATOR FAULTY. WORKSHOP INVESTIGATION COULD FIND NO FAULTS.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011101983	20010111	01983	NM  	2001	1	11	AU000891         	1	20000316	G	2422	7077603	INVERTER        			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					AC SYSTEM	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 			37726							(AUS) STANDBY STATIC INVERTER FAULTY. WORKSHOP INVESTIGATION FOUND THAT TRANSISTORS Q3 TO Q10 WERE SHORT CIRCUITED OR OP	EN CIRCUITED WITH THE BASE BIAS RESISTORS BLOWN OPEN.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000112100221	20001121	00221	SO  	2000	11	21	AU000892         	2	20000831	G	8520	6525396	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 			2093 		565547					(AUS) RT ENGINE CRANKCASE CRACKED IN THE AREA OF NR 1 CYLINDER UPPER FORWARD STUD.  NR 1 CYLINDER FORWARD LOWER BASE STU	D PN 646140-1 SHEARED.  THE CRACK WAS FOUND APPROXIMATELY 60 HOURS PREVIOUSLY DURING ROUTINE MAINTENANCE, BUT WAS WITHIN	 LIMITS (LESS THAN 50.8 MM OR 2 INCHES). THE CRACK HAS NOW GROWN BY APPROXIMATELY 12.7 MM (0.5 INCH) WITH ADDITIONAL CRA	CKS APPROXIMATELY 6.35 MM (0.25 INCH)CROSSING THE END OF THE MAIN CRACK.  (X)			1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000112100222	20001121	00222	EA  	2000	11	21	AU000893         	2	20000826	G	8520	25015	STUD            	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	SHEARED         	W				K	 	 	 	NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE NR 2 CYLINDER HOLD-DOWN STUDS SHEARED.  THE TWO THROUGH-BOLTS WERE INTACT.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000112100223	20001121	00223	SO  	2000	11	21	AU000894         	1	20000921	G	7920	LW13388	GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DETERIORATED    	W				K	 	 	 	NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE OIL FILTER GASKET DETERIORATED AND LEAKING.  ATTACHMENT STUD ALSO LOOSE.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000112100224	20001121	00224	CE  	2000	11	21	AU000895         	1	20000917	G	3520	1013840281	SWITCH          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					PAX OXYGEN	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) CABIN ALTITUDE SENSE SWITCH INCORRECTLY WIRED. CABIN OXYGEN MASKS FAILED TO CORRECTLY DEPLOY.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000112100225	20001121	00225	EA  	2000	11	21	AU000897         	2	20000922	G	8500		ENGINE          	LYC         	O235L2C     	CESSNA	150   	A152        	2071836	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	POWER LOSS      	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) ENGINE LOST POWER.  GROUND RUN CARRIED OUT WITH NO FAULT FOUND.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E223	5	N	P50GL	 
2001011100620	20010111	00620	EU  	2001	1	11	AU000898         	1	20000903	G	3297		WIRE ROPE       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NLG STEERING	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NOSE WHEEL STEERING CABLE FAILED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001011101985	20010111	01985	EU  	2001	1	11	AU000899         	1	20000909	G	2910	58137	MOTOR           			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					HYD SYSTEM	LEAKING         	W				D	 	 	 	RETURN TO BLOCK         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 			1595 							(AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF UTILITY HYDRAULIC SYSTEMFLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001011101986	20010111	01986		2001	1	11	AU000900         	4	20000912	G	3442	20412170413	TRANSCEIVER     			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					WEATHER RADAR	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			4452 							(AUS) WEATHER RADAR TRANSCEIVER FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001011101987	20010111	01987	EU  	2001	1	11	AU000901         	1	20000910	G	3610		DUCT            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PNEUMATIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL DUCT ASSEMBLY LEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001011101988	20010111	01988	EU  	2001	1	11	AU000902         	1	20000910	G	2910	58137	MOTOR           			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					HYD SYSTEM	LEAKING         	W				D	 	 	 	RETURN TO BLOCK         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 			1595 							(AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF HYDRAULIC FLUID FROMUTILITY SYSTEM.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2000112800267	20001128	00267	GL  	2000	11	28	AU000903         	2	20000907	G	7314	PE132	DRIVE SHAFT     	SUNDSTRANDEM	5000950D    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE FUEL PUMP	SHEARED         	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			974  		PE132					(AUS) ENGINE DRIVEN FUEL PUMP INPUT DRIVE SHAFT SHEARED.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2000112800268	20001128	00268	SW  	2000	11	28	AU000904         	1	20000812	G	5314	212030169107	PANEL           	BELL        		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUSELAGE MAIN KE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					30860					(AUS) MAIN BEAM PANEL CRACKED AT STA 166.  CRACK LENGTH 100 MM (4 INCHES). FOUND DURING INSPECTION AND REPLACEMENT OF CR	ACKED MAIN BEAM CAP IAW BHT TB 212-88-106.  (X)					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001011101989	20010111	01989	NM  	2001	1	11	AU000905         	1	20000920	G	2820	MS29513330	SEAL            			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL DIST	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 ENGINE MAIN FUEL FEED PIPE COUPLING BACKUP WASHER PROTRUDING FROM COUPLING AND O-RING SEAL DAMAGED. FUEL LEAK	ING.					2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2001011101990	20010111	01990		2001	1	11	AU000906         	4	20000918	G	3445		ANTENNA         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TCAS	MISINSTALLED    	W				K	 	 	 	NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TCAS ANTENNA MOUNTED ON THE TOP OF THE FUSELAGE LEAKING AIR THROUGH THE SEALANT. DURING REMOVAL OF THE ANTENNA IT 	WAS FOUND THAT THE TWO REAR SCREWS HAD LOOSE NUTS AND WASHERS INSTEAD OFANCHOR NUTS. THE RH FRONT SCREW WAS ALSO SPINNIN	G IN THE ANCHOR NUT. ON REASSEMBLY OF THE ANTENNA IT WAS FOUND THAT THE REARSCREWS WERE TOO LONG AND BOTTOMED OUT LEAVIN	G THE ANTENNA LOOSE ON THE MOUNT PLATE. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000112100226	20001121	00226	GL  	2000	11	21	AU000907         	1	20000916	G	3260	6409231	CONNECTOR       	AMTRNC      	LANCAIR320  	AMTR  	MK1   	MK1         	05620JY	GL  										LANDING GEAR POS	DISCONNECTED    	W				K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE SPADE CONNECTOR DISCONNECTED FROM SWITCH LUG.  (X)						1	H	7	1 	3O			NC	EXPA1H71					 
2000112100227	20001121	00227	NE  	2000	11	21	AU000908         	2	20000702	G	7260	311178001	DUCT            	PWA         							PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TURBINE DUCT ASSEMBLY CRACKED LONGITUDINALLY WITH A SECTION BROKEN OUT. SUBMITTER SUSPECTED CAUSED BY VIBRATION DU	E TO WORN SPLINE ON PROPELLER REDUCTION GEARBOX HOUSING ASSEMBLY PN 3044254-01.  (X)										4	T			E4EA	6	C	P15EA	 
2000112100228	20001121	00228	NE  	2000	11	21	AU000909         	2	20000906	G	7260	311178001	DUCT            	PWA         							PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TURBINE DUCT ASSEMBLY CRACKED.  SAME PROBLEM HAD OCCURRED 21.6 HOURS PREVIOUSLY (REF:  AU000908).  INVESTIGATION F	OUND THE FOLLOWING PROBLEMS:  1.  SECOND STAGE SUNGEAR HEAVY WEAR AND SPALLING.   2. SECOND STAGE PLANETARY GEARS (5OFF)	 HEAVY WEAR AND SPALLING.  3.  FRONT REDUCTION GEARBOX CASE NR 5 BEARING JOURNAL WORN (LOOSE  BEARING).  4.  FIRST STAGE	 CARRIED OVER LIMITS ON BALANCE.  5.  ZERO TORQUE ON NR 5 BEARING RETAINING BOLTS.  (X)								4	T			E4EA	6	C	P15EA	 
2001011101991	20010111	01991	SW  	2001	1	11	AU000910         	1	20000924	G	5730		PANEL           			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	LT WING	MISREPAIRED     	W				K	 	 	 	NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK PANEL LEAKING. INVESTIGATION FOUND THAT AN UNAPPROVED REPAIR HAD BEEN CARRIED OUT BY SPLICINGINTO WIRING	 LOOMS ON EACH SIDE OF THE PANEL WITH THE WIRING GOING THROUGH A HOLE IN THE PANEL. THE SPLICES USED WERE UNSEALED CRIMP	S USED WITHIN THE FUEL TANK WET AREA. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED REPAIR. UNAPPROVED PART.				2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011101992	20010111	01992	NM  	2001	1	11	AU000911         	1	20000608	G	3244	6442	TIRE            			BOEING	737   	73733A      	1384673	NM  										LT MLG	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT MAIN LANDING GEAR NR 2 TIRE FAILED DUE TO FATIGUE AND SEPARATION OF THE SIDEWALL AREA. LT MLG NR 1 TIRE FAILED 	DUE TO OVERLOAD AS A CONSEQUENCE OF THE FAILURE OF NR 2 TIRE.					2	L	7	2 	4F			RT	A16WE   					 
2000112100229	20001121	00229	EU  	2000	11	21	AU000912         	1	20000706	G	3222	604201011	STRUT           			REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	NOSE/TAIL LDNG	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR OLEO OVER EXTENDED ALLOWING TORQUE LINKS TO INVERT.  CAUSED BY OLEO UPPER BEARING LOOSENING FROM	 PISTON BARREL.  (X)					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001011101993	20010111	01993	EA  	2001	1	11	AU000913         	1	20000821	G	3250	DCL44299	LEVER           			CNDAIR	CL600 	CL6002B19   	       	EA  										STEERING TILLER	STUCK           	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NOSE WHEEL STEERING SYSTEM TILLER WOULD NOT RETURN TO THE DETENT POSITION AFTER RELEASE. SUSPECT CAUSED BY EXCESSI	VE FRICTION ON TILLER SHAFT.					2	L	7	2 	4F			RT	A21EA   					 
2001011101994	20010111	01994	NE  	2001	1	11	AU000914         	3	20000921	G	6114	660710325	BOLT            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER HUB	UNDERTORQUED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB BOLTS NR 2, NR 3 AND NR 6 UNDERTORQUED. FOUND DURING INSPECTION IAW DOWTY SB SF340-61-96. SUSPECT CA	USED BY EXCESSIVE SEALANT BETWEEN HUB HALVES.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2000112100230	20001121	00230	SO  	2000	11	21	AU000915         	1	20000925	G	2731	4173405	CONTROL CABLE   	PIPER       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	ELEVATOR TAB CON	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) FORWARD ELEVATOR TRIM CABLE BROKEN AT TRIM SERVO.  LOSS OF TENSION CAUSED CABLE ON TRIM CABLE DRUM TO UNWIND AND J	AM THE DRUM.  INVESTIGATION FOUND THAT THE CABLE HAD BEEN INCORRECTLY INSTALLED CAUSING THE CABLE TO BE SHORT AT THE TUR	N BARREL CONNECTION.  AN UNAPPROVED SHORT SECTION OF CABLE HAD BEEN INSTALLED TO MAKE UP THE CABLE LENGTH.  UNAPPROVED R	EPAIR/PART.  (X)			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2000112100231	20001121	00231	SO  	2000	11	21	AU000916         	1	20000927	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR POS	INTERMITTENT    	W				K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR MICROSWITCH INTERMITTENT IN OPERATION.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011101995	20010111	01995	NE  	2001	1	11	AU000918         	3	20000912	G	6111	66071328710	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R389	R3894123F25 	NE  	PROPELLER	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			4679 							(AUS) RT PROPELLER NR 1 BLADE TRAILING EDGE SPLIT FROM THE BLADE TIP. LENGTH OF SPLIT 355.6MM (14IN). 						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P30NE	 
2001011101996	20010111	01996	WP  	2001	1	11	AU000919         	2	20000926	G	7261	31039081	TUBE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT PROP GOVERNOR	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					870212					(AUS) LT PROPELLER GOVERNOR RESET TUBE CRACKED AT FLARE. LOSS OFAPPROXIMATELY THREE LITRES OF ENGINE OIL. TUBE IS A PER 	SBTPE331-A77-0072 ITEM.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011100800	20010111	00800	NE  	2001	1	11	AU000920         	3	20000922	G	6114	660710325	BOLT            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER HUB	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB BOLT INCORRECT TORQUE. FOUND DURING INSPECTION IAWDOWTY SB SF340-61-96. SUSPECT CAUSED BY EXCESSIVE 	SEALANT BETWEEN HUB HALVES.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001011100802	20010111	00802	EA  	2001	1	11	AU000921         	1	20000918	G	5230		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  										CARGO DOOR	UNLOCKED        	W				D	 	 	 	RETURN TO BLOCK         				W	 	 	INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) CARGO DOOR WARNING. ENGINEER FOUND DOOR HANDLE EXTENDED. INVESTIGATION COULD FIND NO FAULT WITH HANDLE OR WARNING 	SYSTEM.					2	L	7	2 	4F			RT	A21EA   					 
2001011100805	20010111	00805		2001	1	11	AU000922         	4	20000918	G	3444		WARNING SYSTEM  			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	GROUND PROXIMITY	FAULTY          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) GROUND PROXIMITY WARNING SYSTEM (GPWS) FALSE WARNING. INVESTIGATION COULD FIND NO FAULTS.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2000112100232	20001121	00232	SO  	2000	11	21	AU000924         	2	20000907	G	8530	630046	PISTON PIN      	CONT        		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					277299R					(AUS) LEFT ENGINE, ALL SIX PISTON PINS SEVERELY CORRODED.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000112800358	20001128	00358	SW  	2000	11	28	AU000925         	1	20001001	G	6322	209062502101	BEARING         	PWA         		BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COOLING FAN	MISALIGNED      	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					62338					(AUS) NR 2 ENGINE OIL COOLER BLOWER BEARING WAS MISALIGNED CAUSING THE BLOWER SHAFT TO SHEAR.  (X)						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2000113000069	20001130	00069	SO  	2000	11	30	AU000926         	2	20000921	G	8520	641250	SEAL            								CONT  	O520  	IO520*      	17032	SO  					RECIPROCATING EN	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CRANKSHAFT SEAL INNER LIP DAMAGED.  SEAL WAS A NEW ITEM RECEIVED FROM SUPPLIER.  (X)											3	O			E5CE				 
2000112100233	20001121	00233	CE  	2000	11	21	AU000927         	1	20000925	G	2821	07560051	FILTER          			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ACFT FUEL FILTER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL FILTER BOWL CONTAMINATED WITH ALUMINIUM HYDROXIDE. FILTER BOWL CORRODED.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000112100234	20001121	00234	EU  	2000	11	21	AU000928         	1	20000927	G	5741	D22200361	FITTING         			WSK   	M18A  	M18A        	       	EU  										WING, FUSELAGE A	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT OUTER WING BOTTOM ATTACHMENT FITTING PITTED.  (X)						1	L	7	1 	3O			NC	A47EU   					 
2000112100235	20001121	00235	EU  	2000	11	21	AU000929         	1	20000927	G	5741	D22200361	FITTING         			WSK   	M18A  	M18A        	       	EU  										WING, FUSELAGE A	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT OUTER WING BOTTOM ATTACHMENT FITTING CRACKED AND PITTED.  (X)						1	L	7	1 	3O			NC	A47EU   					 
2000112100236	20001121	00236	SO  	2000	11	21	AU000930         	2	20000920	G	7414	103493505	IMPULSE COUPLING	CONT        		CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MAGNETO/DIST	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			491  							(AUS) RIGHT MAGNETO IMPULSE COUPLING WORN EXCESSIVELY.  (X)						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2000112100237	20001121	00237	CE  	2000	11	21	AU000931         	1	20000912	G	2822	1419	PUMP            	AIRBORNE    	IC712       	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL BOOST PUMP	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					1419					(AUS) FUEL BOOST PUMP WIRES BROKEN AT BULKHEAD CANNON PLUG.  (X)						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000112100238	20001121	00238	CE  	2000	11	21	AU000932         	1	20000912	G	2810	5500347	FUEL TANK       	CESSNA      	550         	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUEL STORAGE	LEAKING         	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					5500347					(AUS) LEFT WING INBOARD HEATED LEADING EDGE ANTI-ICE PANEL ATTACHMENT SCREW HOLES LEAKING FUEL FROM TANKS.  FUEL TANK AL	SO LEAKING IN AREA BEHIND ANTI-ICE PANEL.  (X)					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000112100239	20001121	00239	SO  	2000	11	21	AU000933         	2	20000927	G	7322		O-RING          	CONT        	6405632     	PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL CONTROL/CAR	WRONG PART      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			175  		G269601NZ					(AUS) THROTTLE METERING PLATE O RING SEAL NOT USED IN THIS LOCATION.  NO REFERENCE TO THIS O RING IN THE PARTS CATALOGUE	.  UNAPPROVED PART.   (X)					1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001011100807	20010111	00807	EU  	2001	1	11	AU000934         	1	20000919	G	5610	NF20216246	WINDSHIELD      			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) WINDSHIELD CRACKED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100841	20010111	00841		2001	1	11	AU000935         	4	20000916	G	3460	1796001020012	CDU             			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FLIGHT MANAGE	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) GPS CENTRAL DATA UNIT (CDU) LOCKED UP. GPS WOULD NOT TRACK.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100844	20010111	00844	EU  	2001	1	11	AU000936         	1	20000716	G	5752		TRIM TAB        			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AILERON	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT AILERON TRIM TAB DAMAGED DURING GROUND OPERATION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100846	20010111	00846	NE  	2001	1	11	AU000937         	2	20000929	G	7260	1081	BEARING         			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT ENGINE ACCESSORY GEARBOX DEDICATED DRIVE GENERATOR BALLBEARING FAILED. METAL CONTAMINATION OF GEARBOX.						2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2001011100847	20010111	00847	EU  	2001	1	11	AU000938         	1	20000905	G	7602	82GR03291100888	CONTROL CABLE   	LYC         	O360A1F6    	GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					MIXTURE CONTROL	FAILED          	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) MIXTURE CONTROL CABLE FAILED AT SWAGED END FITTING.						1	L	7	1 	3O	3	O	NT	A57EU   	E286				 
2001011100873	20010111	00873	EU  	2001	1	11	AU000939         	1	20001001	G	2750		CIRCUIT BREAKER 			BAG   	JETSTM	JETSTM3201  	1500217	EU  						MCAULY	4HFR34	4HFR34C653  	NE  	TE FLAP CONTROL	TRIPPED         	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) FLAP CONTROL CIRCUIT BREAKER TRIPPED. INVESTIGATION COULD FIND NO FAULT.						2	L	7	2 	4T			RT	A56EU   		6	C	3PNE	 
2001011100874	20010111	00874	NM  	2001	1	11	AU000940         	1	20000926	G	3260		TARGET          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG	LOOSE           	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR PROXIMITY SENSOR TARGET LOOSE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000112100240	20001121	00240	SO  	2000	11	21	AU000941         	1	20001002	G	2434		WIRE            			PIPER 	PA30  	PA39        	7103902	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	DC GENERATOR-ALT	CRACKED         	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 										(AUS) RIGHT ALTERNATOR FIELD WIRING CRACKED ALLOWING SHORT CIRCUIT.  (X)						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2001011100876	20010111	00876	NM  	2001	1	11	AU000942         	1	20000205	G	2530	DPXAMA2634P	PLUG            			BOEING	737   	737377      	       	NM  										GALLEY	BURNED          	W				O	 	 	 	OTHER                   				B		 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 			6322 							(AUS) AFT GALLEY NR 3 OVEN TIMER POWER PINS BURNT AT TIMER MODULE PLUG.						2	L	7	2 	4F			RT	A16WE   					 
2001011100878	20010111	00878	EU  	2001	1	11	AU000943         	1	20000904	G	7722	WL706RSA4	INDICATOR       			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	FLUCTUATES      	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE EGT INDICATOR FLUCTUATING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100879	20010111	00879	NM  	2001	1	11	AU000944         	1	20001002	G	3350		CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	EMERGENCY LIGHT	UNAPPROVED PART 	W				K	 	 	 	NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT CONNECTORS USED FOR EMERGENCY LIGHTS LOCATED AT LT AND RT UNDERWING EXITS. CONNECTORS APPEAR TO BE COMME	RCIAL TELEPHONEMODULAR ITEMS. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000112100241	20001121	00241	CE  	2000	11	21	AU000945         	1	20000928	G	2150	7547511	VALVE           			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	CABIN COOLING SY	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 					FJ43426					(AUS) AIR CYCLE MACHINE BYPASS VALVE STICKING IN THE ''OPEN'' POSITION.  (X)						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2000112100242	20001121	00242	EA  	2000	11	21	AU000946         	2	20000818	G	8520	5015	STUD            	LYC         		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	SHEARED         	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 					L12061					(AUS) NR 4 CYLINDER MOUNT STUDS (3OFF) SHEARED.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000112100243	20001121	00243	CE  	2000	11	21	AU000947         	1	20000929	G	5312		BULKHEAD        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSEMAIN BULKHD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD TAIL BULKHEAD CRACKED IN THE AREA OF THE HORIZONTAL STABILIZER ATTACHMENT POINT.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001011100881	20010111	00881	EU  	2001	1	11	AU000948         	1	20000928	G	2611	7211121100	SMOKE DETECTOR  			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	CARGO BAY	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				N		 	FALSE WARNING             			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) CARGO SMOKE DETECTOR FAULTY. FIRE BOTTLE ACTIVATED. INVESTIGATION FOUND NO EVIDENCE OF FIRE.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011100883	20010111	00883	EA  	2001	1	11	AU000949         	1	20000929	G	2740		BEARING         			CNDAIR	CL600 	CL6002B19   	       	EA  										STABILIZER	STIFF           	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) HORIZONTAL STABILISER PIVOT BEARINGS BINDING CAUSING FAILURE OF THE STABILISER TRIM ACTUATOR.						2	L	7	2 	4F			RT	A21EA   					 
2001011100904	20010111	00904	NM  	2001	1	11	AU000950         	1	20000918	G	3244	319K281	TIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RT MLG	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT OUTBOARD WHEEL TIRE LEAKING FROM LOWER SIDEWALL CASING VENTS.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000113000070	20001130	00070	CE  	2000	11	30	AU000951         	1	20001002	G	3230		HYDRAULIC SYSTEM			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	L/G RETRACT	CONTAMINATED    	W				K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC SYSTEM CONTAMINATED WITH O RING AND TEFLON SEAL MATERIAL.  CONTROL VALVE CONTAMINATED.  LEF	T DOWNLOCK SWITCH FAILED.  NOSE LANDING GEAR ACTUATOR FAULTY.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000113000071	20001130	00071	NM  	2000	11	30	AU000952         	1	20000801	G	3250	450052001	COLLAR          			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					LANDING GEAR STE	WRONG PART      	W				K	 	 	 	NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR STEERING COLLAR FAILED AT ACTUATOR ATTACHMENT POINT.  CONNECTING BOLT WAS INCORRECT PART.  BOLT 	SHEARED.  UNAPPROVED PART.  (X)					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000113000072	20001130	00072	NE  	2000	11	30	AU000953         	2	20000905	G	8520	39785C	PIN             	PWA         	128502      	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					MASTER ROD	FAULTY          	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			835  							(AUS) MASTER ROD LINK PINS (8OFF) ELECTROPLATED USING AN UNAPPROVED PROCESS.  NO EVIDENCE OF UNSERVICEABILITY FOUND.   U	NAPPROVED PART. (X)					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000113000073	20001130	00073	NE  	2000	11	30	AU000954         	2	20000905	G	8520	39785C	PIN             	PWA         	128502      	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			555  		RE12449					(AUS) MASTER ROD LINK PINS (8OFF) ELECTROPLATED USING AN UNAPPROVED PROCESS.  NO EVIDENCE OF UNSERVICEABILITY FOUND.  UN	APPROVED PART.   (X)					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000113000074	20001130	00074	EA  	2000	11	30	AU000955         	2	20000824	G	8520	LW16511	CAMSHAFT        	LYC         	O320H2AD    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	SPALLED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					L258676					(AUS) CAMSHAFT LOBES AND ASSOCIATED LIFTERS SPALLED, PITTED, AND WORN.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000113000075	20001130	00075	SO  	2000	11	30	AU000956         	2	20000907	G	8530	630046	PISTON PIN      	CONT        		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					277299R					(AUS) LEFT ENGINE PISTON PINS (6OFF) SEVERELY CORRODED.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000112800359	20001128	00359	NM  	2000	11	28	AU000957         	1	20000930	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETA     	       	NM  										ENGINE/TRANS	STRETCHED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE TO TRANSMISSION DRIVE BELTS WERE STRETCHED AFTER THIRTEEN HOURS OF OPERATION.  BELTS DID NOT COME OFF PULLE	YS.  (X)					1	G	7	1 	3O			 	H10WE   					 
2000113000076	20001130	00076	EA  	2000	11	30	AU000958         	1	20000923	G	5710		FRAME           			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	WING MAIN FRAME	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LEFT WING DAMAGED DURING HEAVY LANDING.  (X)						1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2001011100906	20010111	00906	EU  	2001	1	11	AU000960         	1	20001002	G	3260	387	BULB            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	MLG INDICATOR	FAILED          	W				O	 	 	 	OTHER                   				L		 	NO TEST                   			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR LIGHT BULB BLOWN.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011100911	20010111	00911	EU  	2001	1	11	AU000962         	1	20000929	G	7712	522948	INDICATOR       			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	BMEP/TORQUE	STUCK           	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE TORQUE GAUGE FAILED. INVESTIGATION FOUND THAT THE GAUGE WAS STICKING AT APPROXIMATELY 45 PERCENT BEFORE 	GOING TO FULLSCALE INDICATION.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011100912	20010111	00912	EA  	2001	1	11	AU000963         	1	20000925	G	2421	755469D	IDG             			CNDAIR	CL600 	CL6002B19   	       	EA  										AC GENERATOR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					09192961					(AUS) NR 1 INTEGRATED DRIVE GENERATOR (IDG) FAILED.						2	L	7	2 	4F			RT	A21EA   					 
2001011100936	20010111	00936		2001	1	11	AU000964         	4	20001004	G	3418	2566A27	VANE            			FOKKER	F28   	F28MK0100   	4990807	EU  										STALL WARNING	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) LT STALL VANE FAULTY.						2	L	7	2 	4F			RT	        					 
2000113000077	20001130	00077	CE  	2000	11	30	AU000965         	1	20000920	G	3230	3682001115	ROD             	BEECH       		BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					L/G RETRACT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ROD CRACKED IN TWO POSITIONS 180 DEGREES APART AND RUNNING LENGTHWISE FROM UNDER THE 	LOCKNUT.  CRACK LENGTH 6.35 MM (0.25 INCH).   ITEM WAS ALSO IDENTIFIED AS AN UNAPPROVED PART.   (X)					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2000113000078	20001130	00078	CE  	2000	11	30	AU000966         	1	20000905	G	2932	98087	PRESSURE SWITCH 			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					HYD PRESSURE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) HYDRAULIC PRESSURE SWITCH FAULTY.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000113000079	20001130	00079	GL  	2000	11	30	AU000967         	3	20001005	G	6110		PROPELLER       	MCAULY      		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	PROPELLER ASSY	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) PROPELLER SLOW TO FEATHER. BLADE SEALS LEAKING GREASE.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011100938	20010111	00938	NM  	2001	1	11	AU000968         	1	20000927	G	5753	113T184287SP	FAIRING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					TE FLAP	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT OUTBOARD FLAP INBOARD TRAILING EDGE FAIRING MISSING. INBOARD FAIRING ATTACHMENT BRACKET MISSING. FASTENERS PULL	ED FROM FLAP.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011100939	20010111	00939	NM  	2001	1	11	AU000969         	1	20000930	G	2830	02891113A	VALVE           		6072101     	BOEING	747   	747438      	       	NM  										FUEL DUMP	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					02891113A					(AUS) NR 3 OVER-RIDE JETTISON PUMP INLET CHECK VALVE SEPARATED FROM THE HINGE POINT. INSPECTION OF THE PUMP FOUND THAT T	HE IMPELLER WAS LOOSE AND INSECURE.					2	L	7	4 	4F			RT	A20WE   					 
2001011100621	20010111	00621	EU  	2001	1	11	AU000970         	1	20001003	G	2897		WIRE            			AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					FUEL QTY IND	FAULTY          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NO2 FUEL TANK QUANTITY GAUGE OVER-READING DUE TO DEFECTIVE WIRING AT NO2 FUEL QUANTITY TRANSMITTER. NO2 ENGINE FAI	LED DUE TO FUEL EXHAUSTION.					1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2001011101107	20010111	01107	EA  	2001	1	11	AU000973         	1	20001001	G	2750	860D10018	FCU             			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAP	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAP ELECTRONIC CONTROL UNIT (FECU) FAULTY. FOLLOWING CIRCUIT BREAKER REST THE FAULT COULD NOT BE DUPLICATED.						2	L	7	2 	4F			RT	A21EA   					 
2001011101108	20010111	01108	EA  	2001	1	11	AU000974         	1	20001005	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) CAPTAINS WINDSHIELD CRACKED.						2	L	7	2 	4F			RT	A21EA   					 
2001011101063	20010111	01063	NM  	2001	1	11	AU000975         	1	20000306	G	5400	FRFOE2822PO3	CONNECTOR       			BOEING	737   	737377      	       	NM  										NR 2 PYLON	DAMAGED         	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 2 PYLON HARNESS FIREWALL CONNECTOR DAMAGED DUE TO ARCING.						2	L	7	2 	4F			RT	A16WE   					 
2000112800374	20001128	00374	SW  	2000	11	28	AU000976         	1	20001006	G	2560	206706211103	FLOATATION      			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					EMERG QUIPMENT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY FLOATS INFLATED OVERNIGHT WITH NO REASON OR CAUSE BEING FOUND.  INVESTIGATION OF THE FLOAT SYSTEM FOUND 	THAT THE SQUIB HAD BEEN FIRED ELECTRICALLY AND THAT THE SYSTEM HAD OPERATED NORMALLY.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000112800375	20001128	00375	SW  	2000	11	28	AU000977         	1	20000106	G	6310	206040015103	DRIVE SHAFT     			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE/TRANS	FAILED          	W				K	E	 	 	NONE                    	ENGINE SHUTDOWN         			O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 			599  							(AUS) ENGINE TO TRANSMISSION DRIVE SHAFT FAILED AND SEPARATED AT THE TRANSMISSION END.  SUSPECT ATTACHMENT NUTS PN MS210	43-4 HAD NOT BEEN CORRECTLY RETORQUED (LEFT FINGER TIGHT) FOLLOWING SERVICING AND GREASING OF THE SHAFT APPROXIMATELY ON	E HOUR PREVIOUSLY. TWO OF THE NUTS WERE FOUND ON THE TRANSMISSION DECK.   (X)				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011101085	20010111	01085	NE  	2001	1	11	AU000978         	2	20001010	G	7261	115175	ENGINE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					NR 1	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				J		 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE OIL PRESSURE LOW.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2000113000080	20001130	00080	SO  	2000	11	30	AU000979         	2	20000928	G	8540	631847	SHAFT           	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	STRIPPED        	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					810608R					(AUS) RH ENGINE STARTER GEAR TEETH STRIPPED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000113000081	20001130	00081	SO  	2000	11	30	AU000980         	2	20001005	G	8540	276157R	SLEEVE          	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					276157R					(AUS) LEFT ENGINE STARTER DRIVE NEEDLE ROLLER BEARING SLEEVE FAILED.  METAL CONTAMINATION OF OIL SYSTEM.  THE SLEEVE IS 	NOT AC ONTINENTAL PART.  UNAPPROVED PART.   (X).					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001011101086	20010111	01086	NM  	2001	1	11	AU000981         	1	20001001	G	2120		UNKNOWN         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					CABIN	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) ACRID OILY ODOR EVIDENT IN AIRCRAFT WITH A VISIBLE MIST OBSERVED ON THE FLIGHTDECK. ON DESCENT THE FUMES DISSIPATE	D.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011101088	20010111	01088	NM  	2001	1	11	AU000982         	1	20000924	G	4930		FUEL CONTROL    			BOEING	767   	767338      	1385151	NM  										APU	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FUEL CONTROL UNIT LEAKING. INVESTIGATION COULD FIND NO LEAKS. SUSPECT LEAK WAS RESIDUAL FUEL FROM COMBUSTION C	ASE DRAIN VALVE.					2	L	7	2 	4F			RT	A1NM    					 
2001011101089	20010111	01089	NM  	2001	1	11	AU000983         	1	20000917	G	3150	0881031006	STRUCTURE       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	ARCED           	W				D	 	 	 	RETURN TO BLOCK         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LT MASTER CAUTION RESET BASE ASSEMBLY ARCING. LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2000113000082	20001130	00082	WP  	2000	11	30	AU000984         	2	20000821	G	7250		TURBINE         	GARRTT      		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TURBINE SECTION	OVERHEATED      	W				K	 	 	 	NONE                    				E	R	M	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	OVER TEMP                 	CL	CLIMB          	1			AU	S 										(AUS) LEFT ENGINE UNCOMMANDED TORQUE REDUCTION COUPLED WITH HIGH EGT INDICATION.   HOT SECTION OVERTEMP DAMAGE.   (X)						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001011101155	20010111	01155	SW  	2001	1	11	AU000985         	1	20000907	G	2822	3282030001	HARNESS         	SWRNGN      	SB28003     	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	BOOST PUMP	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FUEL BOOST PUMP HARNESSES (2OFF) AND LT OUTBOARD BOOST PUMP HARNESS CHAFED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001011101156	20010111	01156	EU  	2001	1	11	AU000986         	1	20001007	G	2435	524031	STARTER GEN     			AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					NR 1 ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			206  							(AUS) NR 1 ENGINE STARTER-GENERATOR SHAFT HAD EXCESSIVE PLAY CAUSING HIGH VIBRATION LEVEL. IGNITER BRACKET CRACKED AS A 	RESULT.					1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2001011101157	20010111	01157	NM  	2001	1	11	AU000987         	1	20000310	G	3320	285T00976	CIRCUIT BOARD   			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					LIGHTING SYSTEM	BURNED          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) MASTER DIM AND TEST PRINTED CIRCUIT BOARD M2 IN PANEL P29 BURNED.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011101180	20010111	01180	EU  	2001	1	11	AU000988         	1	20001002	G	2701		TORQUE BOX      			GROB  	G115  	G115        	       	EU  	LYC   	O235  	O235C1B     	41505	EA  	MCAULY	1C90	1C90LM      	GL  	CONTROL COLUMN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL COLUMN TORQUE BOX CONTAINED TWO CRACKS ON THE LOWER SURFACE EMANATING FROM THE EDGES OF THE CONTROL COLUMN	 CUT-OUT.  ONE OF THE CRACKS HAD BEEN STOP DRILLED AND REINFORCED WITH A SMALL DOUBLER PATCH.  LOG BOOK ENTRY SHOWED THA	T THE CRACK HAD BEEN REPAIRED ON 29 APRIL 1989 AT 2,523 HOURS.  THIS REPAIR IS AN ILLEGAL REPAIR. AD/VAT/42 WAS LAST CAR	RIED OUT AT 3,399 HOURS.   UNAPPROVED REPAIR.  (X)			1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P842	 
2000113000083	20001130	00083	SO  	2000	11	30	AU000989         	2	20000927	G	8597	530830	PISTON PIN      	CONT        		CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1147 		669177A					(AUS) PISTON PIN FAULTY.  LIMITED INFORMATION PROVIDED.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001011101183	20010111	01183	WP  	2001	1	11	AU000990         	2	20001009	G	7261	31080281	SHAFT           		31080261    	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT ENGINE	SEIZED          	W				O	 	 	 	OTHER                   				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		LD	LANDING        	1			AU	S 										(AUS) RT ENGINE TURBINE BEARING SCAVENGE PUMP GEARSHAFT SEIZED IN THE PUMP HOUSING CAUSING THE PUMP DRIVESHAFT GEARS TO 	STRIP. METAL CONTAMINATION OF THE SCAVENGE PUMP AND REAR TURBINE BEARING.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2000113000084	20001130	00084	CE  	2000	11	30	AU000991         	1	20001012	G	7120	539914	MOUNT           	CONT        		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE MOUNT SEC	BROKEN          	W				K	 	 	 	NONE                    				C	 	 	F.O.D.                    			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT SIDE ENGINE MOUNTS BROKEN.  AIRCRAFT WAS BEING HAND STARTED AND RAN AWAY FROM THE PILOT BEFORE HITTING A FEN	CE. THE PROPELLER HIT THE FENCE AND STALLED THE ENGINE.  (X)					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001011101184	20010111	01184	NM  	2001	1	11	AU000993         	1	20001005	G	3244	H31X9751312PLY	TIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR TIRE DAMAGED ON OUTBOARD LOWER SIDEWALL BY SHARP STONE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000113000085	20001130	00085	CE  	2000	11	30	AU000994         	1	20001011	G	2150	AN737TW98	CLAMP           	HAMSTD      	H573844315  	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	CABIN COOLING SY	LOOSE           	W				K	 	 	 	NONE                    				O		 	OTHER                     			CR	CRUISE         	1			AU	S 					50794					(AUS) AIR CYCLE MACHINE TO WATER SEPARATOR DUCT CLAMP LOOSE.  INVESTIGATION FOUND THE CLAMP WAS THE INCORRECT SIZE.  COR	RECT CLAMP PN AN737TW-91. UNAPPROVED PART.  (X)					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2000113000086	20001130	00086	CE  	2000	11	30	AU000995         	1	20000928	G	5312		POST            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUSELAGE MAIN BU	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE RIGHT FORWARD LOWER DOOR POST BULKHEAD CRACKED AT RELIEF HOLE PER AD/CESSNA206/48 AMDT1.  CRACK LENGTH 8.	2 MM (0.325 INCH).  AD/CESSNA206/48 AMDT1 WAS NOT DUE FOR ANOTHER 120 HOURS.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2001011101185	20010111	01185	NM  	2001	1	11	AU000996         	1	20001016	G	3260		SENSOR          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOOR WARNING LIGHT SENSOR OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011101206	20010111	01206	NE  	2001	1	11	AU000997         	2	20001011	G	7322	78639010	HMU             	PWA         	PW118A      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					FUEL CONTROL	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			6743 		F324B					(AUS) LT ENGINE HYDRO MECHANICAL UNIT (HMU) FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2001011101207	20010111	01207	EU  	2001	1	11	AU000998         	1	20001017	G	2421		TERMINAL        			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC GENERATOR	LOOSE           	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 GENERATOR PHASE TERMINAL LOOSE. DURING TROUBLE SHOOTING FAULTS WERE ALSO FOUND IN THE BUS TRANSFER SYSTEM.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011100623	20010111	00623	EU  	2001	1	11	AU000999         	1	20000612	G	2730	27930288	WIRE            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					RT ELEVATOR	DAMAGED         	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) RT INBOARD ELEVATOR SERVO POSITION FEEDBACK TRANSDUCER WIRE PNO 2793-0288 HAD INSULATION DAMAGE. SUSPECT DAMAGE CA	USED BY FOD.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011101211	20010111	01211	NM  	2001	1	11	AU001000         	1	20000823	G	2425	119191N7	SWITCH          			BOEING	737   	737377      	       	NM  										AC POWER	FAULTY          	W				K	 	 	 	NONE                    				B		 	SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) AC POWER SELECTOR SWITCH (S3) ARCING INTERNALLY.						2	L	7	2 	4F			RT	A16WE   					 
2001011101238	20010111	01238	EU  	2001	1	11	AU001001         	1	20001019	G	3020	6124100	DUCT            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	INTAKE ANTI ICE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE INTAKE LOWER ANTI-ICE DUCT FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001030200025	20010302	00025	EU  	2001	3	2	AU001002         	1	20001017	G	2497	55T802024029	WIRE            			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION FOR AD/SF340/73 (SB 92-027) TWO WIRES WEREFOUND CHAFED THROUGH TO THE CONDUCTOR IN THE HOLE LOCA	TED IN FRAME 272.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2000113000087	20001130	00087	CE  	2000	11	30	AU001003         	1	20001019	G	2130	1013800133	VALVE           		10138001319 	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN PRESSURE C	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 					648184R					(AUS) CABIN PRESSURIZATION SYSTEM FAULTY RESULTING IN AUTO DEPLOYMENT OF THE OXYGEN MASKS.  INVESTIGATION FOUND THE RIGH	T FLOW PACK PN 101-380013-19 UNSERVICEABLE AND THE LEFT PNEUMOSTAT PN 101-380013-3 STICKING.  (X)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001011101239	20010111	01239	NM  	2001	1	11	AU001004         	1	20000826	G	5280	113T820176A	DOOR            			BOEING	767   	76733A      	1385209	NM  	PWA   	4060  	PW4060      	52119	NE  					LANDING GEAR	SEPARATED       	W				O	 	 	 	OTHER                   				D		 	INFLIGHT SEPARATION       			AP	APPROACH       	1			AU	S 										(AUS) RT MAIN LANDING GEAR STRUT AND TRUNNION DOORS MISSING.INVESTIGATION FOUND OTHER DAMAGE INCLUDING RH BRAKE LINES AN	D BOGIE TILT ACTUATOR HYDRAULIC LINES. IMPACT DAMAGE OCCURRED TOTHE WING TO BODY FAIRING (PANEL 196KR) AND UNDERWING PAN	EL 615SB. THE RH HORIZONTAL STABILISER LEADING EDGE WAS DENTED AND THREEFAN BLADES ON THE RH ENGINE HAD MINOR TIP CURL. 	SCUFF MARKS ONTHE RH FUSELAGE AND FORWARD OF THE RH MAIN WHEEL WELL SEEMS TOINDICATE THAT THE DAMAGE WAS CAUSED BY RUBBE	R DEBRIS THROWN UPDURING TAKEOFF. INSPECTION OF THE AIRCRAFT TYRES FOUND NO RUBBERMISSING WHICH INDICATES THAT THE RUBBE	R IS FROM ANOTHER AIRCRAFT.	2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2000113000088	20001130	00088	CE  	2000	11	30	AU001005         	1	20001009	G	2820		FITTING         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ACFT FUEL DIST	RUSTED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) ENGINE DRIVEN FUEL PUMP CONTAMINATED.  INVESTIGATION FOUND CONTAMINATION WAS RUST FROM THE INTERNAL BORES OF THE S	TEEL END FITTINGS OF THE FLEXIBLE HOSES AND FIREWALL FITTINGS IN THE FUEL SUPPLY SYSTEM PLUMBING.  SUBMITTER SUSPECTED R	UST PROBLEM IS ASSOCIATED WITH THE DECONTAMINATION OF THE FUEL SYSTEM WITH WATER FOLLOWING THE MOBIL FUEL CONTAMINATION 	PROBLEM.  (X)			1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2000113000089	20001130	00089	SO  	2000	11	30	AU001006         	2	20000929	G	8540	653882	SHAFT           	CONT        	ADAPTER     	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	STRIPPED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE STARTER SHAFT GEAR TEETH STRIPPED.  CRANKSHAFT GEAR DAMAGED.  (X)						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000113000090	20001130	00090	SO  	2000	11	30	AU001007         	2	20001016	G	7310	641558	PIPE            	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE FUEL DIST	DISCONNECTED    	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					276276R					(AUS) LEFT ENGINE DECK PRESSURE LINE DISCONNECTED.   (X)						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000113000091	20001130	00091	SO  	2000	11	30	AU001008         	2	20001004	G	7314		PUMP            	CONT        		BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ENGINE FUEL PUMP	CONTAMINATED    	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 										(AUS) ENGINE DRIVEN FUEL PUMP VAPOR SEPARATOR CHAMBER CONTAINED A SMALL PIECE OF UNIDENTIFIABLE CONTAMINANT.  REF:   OPE	R CNTRL NR AU001005 FOR SUSPECTED ORIGIN OF CONTAMINATION.  (X)					1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2001011101241	20010111	01241	CE  	2001	1	11	AU001009         	1	20001020	G	3213	5081032017	SOCKET          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR TORQUE LINK ATTACHMENT LUG LOCATED ON THE SOCKET ASSEMBLY CRACKED. FOUND DURING UNSCHEDULED D	OUBLE BRAKE UNIT CHANGE. AIRCRAFT HAD SUFFERED A WALLABY STRIKE ON LANDING ON THE PREVIOUS DAY.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2001011101266	20010111	01266	NE  	2001	1	11	AU001010         	2	20001020	G	7260	39705500	BEARING         			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					RT ENGINE	DISINTEGRATED   	W				O	 	 	 	OTHER                   				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) RT ENGINE ACCESSORY DRIVE GEARBOX ENGINE ELECTRONIC CONTROL (EEC) DEDICATED DRIVE GENERATOR (DDG) LINE 12 BEARING 	FAILED.					2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2000113000092	20001130	00092	CE  	2000	11	30	AU001011         	1	20001019	G	2460	7277210	CIRCUIT BREAKER 			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	DC POWER DISTRIB	FAULTY          	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) ALTERNATOR FIELD CIRCUIT POWER CIRCUIT BREAKER FAILED.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2000112800406	20001128	00406	WP  	2000	11	28	AU001012         	1	20001024	G	6310	A1882	CLUTCH          	ROBSIN      	CLUTCH      	ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE/TRANSMISS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					4112					(AUS) ENGINE TO TRANSMISSION CLUTCH SHEAVE CRACKED FROM OUTER RETAINING BOLT. SEAL RETAINING PLATES ALSO CRACKED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001011101268	20010111	01268	EU  	2001	1	11	AU001013         	1	20001018	G	3233	AE7064584	HOSE            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	MLG ACTUATOR	FAILED          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ACTUATOR HYDRAULIC HOSE FAILED.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001011101270	20010111	01270	EA  	2001	1	11	AU001014         	2	20001018	G	8520	LW11750	CONNECTING ROD  			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENGINE	MISMANUFACTURED 	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD BIGEND BOLT HOLES INCORRECTLY DRILLED. BOLT HOLESWERE DRILLED APPROXIMATELY TWO DEGREES OF CENTRE L	INE RESULTING IN A TAPERING GAP OF 0.889MM (0.035IN). MANUFACTURING ERROR.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2001011101273	20010111	01273	EU  	2001	1	11	AU001015         	1	20001010	G	3020	HE69822	CONTROL UNIT    			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	INTAKE ANTI ICE	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE AIR INTAKE ANTI-ICE CONTROL SYSTEM THERMISTOR HAD HIGH RESISTANCE.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2000112800407	20001128	00407	SW  	2000	11	28	AU001016         	1	20001009	G	6410	406016100119	BLADE           	BELL        		BELL  	407   	407         	       	SW  										TAIL ROTOR BLADE	FOD             	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR BLADE DAMAGED BY DZUS FASTENER WHICH SEPARATED FROM THE TAIL ROTOR GEARBOX COWLING.  FOD.  (X)						1	G	7	1 	3U			O	H2SW    					 
2001011101277	20010111	01277	NE  	2001	1	11	AU001018         	2	20000916	G	7532		BLEED BAND      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COMPRESSOR	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE BLEED BAND OUT OF ADJUSTMENT.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011101301	20010111	01301	EU  	2001	1	11	AU001019         	1	20000908	G	5610	NP1701022	WINDSHIELD      			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 			16880							(AUS) FIRST OFFICERS B WINDSHIELD OUTER PANE SHATTERED. CRACKING HAD  INITIATED FROM A LOCALISED HOT SPOT ALONG THE LOWE	R EDGE OF THE WINDSHIELD ADJACENT TO THE BUS BAR AREA.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011101303	20010111	01303	NM  	2001	1	11	AU001020         	1	20000922	G	5512		SKIN            			BOEING	737   	73733A      	1384673	NM  										HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILISER LOWER SKIN CRACKED IN AREA BETWEEN STN 125 AND STN 127. CRACK LENGTH 44.45MM (1.75IN).						2	L	7	2 	4F			RT	A16WE   					 
2001011101304	20010111	01304	NM  	2001	1	11	AU001021         	1	20000823	G	5512		SKIN            			BOEING	737   	737377      	       	NM  										HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILISER LOWER SKIN CRACKED AT THE CHEMICALLY MILLED EDGE BETWEEN STN 156.00 AND STN 158.00. CRACK	 LENGTH 50.8MM(2IN).					2	L	7	2 	4F			RT	A16WE   					 
2001011101305	20010111	01305	NM  	2001	1	11	AU001022         	1	20000728	G	5280	655051425	BRACKET         			BOEING	737   	737377      	       	NM  										MLG DOOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT NOSE LANDING GEAR DOOR FORWARD HINGE BRACKET CRACKED ACROSS WEB. CRACK LENGTH 23MM (0.905IN).						2	L	7	2 	4F			RT	A16WE   					 
2001011101306	20010111	01306	NM  	2001	1	11	AU001023         	1	20000920	G	2612		WARNING SYSTEM  			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FIRE DETECTION	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE FIRE WARNING. A THOROUGH INVESTIGATION OF THE FIRE WARNING SYSTEM COULD FIND NO FAULTS AND THE SYSTEM HA	S OPERATED CORRECTLY SINCE. DEFECT NOT CONFIRMED.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000113000093	20001130	00093	CE  	2000	11	30	AU001024         	1	20001025	G	2751		SWITCH          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP POSITION	STUCK           	W				K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) FLAP WARNING SYSTEM MICROSWITCH STUCK.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000113000094	20001130	00094	CE  	2000	11	30	AU001025         	1	20001017	G	2731	12600741	ACTUATOR        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELEVATOR TAB CON	CORRODED        	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) ELEVATOR TRIM ACTUATOR CORRODED INTERNALLY WITH THE LUBRICANT DRIED OUT.  AIRCRAFT HAD BEEN STRIPPED AND RE-SPRAYE	D APPROXIMATELY SIX WEEKS PREVIOUSLY WHICH MAY HAVE CONTRIBUTED TO THE PROBLEM.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001011101307	20010111	01307		2001	1	11	AU001026         	4	20001008	G	3418	EASPE8801402	CONTROL BOX     			FOKKER	F28   	F28MK0100   	4990807	EU  										STALL WARNING	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 			440  							(AUS) STALL PROTECTION ENHANCEMENT BOX FAULTY.						2	L	7	2 	4F			RT	        					 
2001011101308	20010111	01308	EU  	2001	1	11	AU001027         	1	20001024	G	3230		SELECTOR SWITCH 			FOKKER	F28   	F28MK0100   	4990807	EU  										MLG	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				J		 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR TEST SELECTOR LEFT IN GROUND ONLY' (TEST) POSITION  FOLLOWING MAINTENANCE. PERSONNEL/MAINTENANCE ERRO	R.					2	L	7	2 	4F			RT	        					 
2000121200300	20001212	00300	CE  	2000	12	12	AU001028         	1	20001010	G	2434	646655A1	HUB             	CONT        	CB12C       	BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	DC GENERATOR-ALT	FAILED          	W				K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			98   		B512914					(AUS) ALTERNATOR FLEXIBLE DRIVE COUPLING FAILED.  (X)						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2001011101309	20010111	01309	EU  	2001	1	11	AU001029         	1	20001023	G	2420		GENERATOR       			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1	FAULTY          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) NR 1 GENERATOR WENT OFF LINE. GENERATOR CONTROL UNIT AND LINE CONTACTOR CHANGED AND WIRING INSPECTED WITH NIL FAUL	TS FOUND. INVESTIGATION CONTINUING.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000121200301	20001212	00301	CE  	2000	12	12	AU001030         	1	20001018	G	3230	1313782520CL	LINK            		131378252889	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR RET	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) NOSE LANDING GEAR DRIVE CHAIN LINK ASSEMBLY SEPARATED DUE TO FAILURE OF THE RETAINING CLIP.  INSPECTION OF THE RET	AINING CLIP UNDER A 10X MAGNIFYING GLASS FOUND INDICATIONS OF FATIGUE AND CORROSION.  (X)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001011101310	20010111	01310		2001	1	11	AU001031         	4	20000901	G	2210	1311000	RELAY           			BAC   	146   	AVRO146RJ70A	1500095	EU  										AUTOPILOT SYSTEM	MISINSTALLED    	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) NAVIGATION RELAY BOX WIRES CR101 AND CR102 (HSI COURSE ERROR TO AUTOPILOT) NOT CONNECTED.						2	H	7	4 	4F			RT	A49EU   					 
2000121200302	20001212	00302	GL  	2000	12	12	AU001032         	3	20001022	G	6111		BLADE           	HARTZL      		BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  	HARTZL	HC92W	HC92WK2     	GL  	PROPELLER BLADE	SEPARATED       	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) LEFT PROPELLER BLADE SECTION SEPARATED APPROXIMATELY 200 MM (7.87 INCHES) FROM THE BLADE TIP.  FAILURE ORIGINATED 	FROM A PREVIOUS STONE STRIKE THAT HAD NOT BEEN ADEQUATELY BLENDED OUT.  (X)					1	L	7	2 	3O	3	O	 	3A16    	1E10	5	C	P16EA	 
2000121200303	20001212	00303	EA  	2000	12	12	AU001033         	2	20000925	G	8550	LW13388	GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAULTY          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) ENGINE OIL FILTER CONVERTER PLATE GASKET FAULTY.  GASKET WAS SWOLLEN AND SPONGY IN APPEARANCE.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011101311	20010111	01311	EU  	2001	1	11	AU001034         	1	20001023	G	2613		CONNECTOR       			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	OVERHEAT DETECT	SHORTED         	W				A	 	 	 	UNSCHED LANDING         				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) TAILPIPE OVERHEAT DETECTOR SHORT CIRCUITING AT CONNECTOR DUE TO CONTAMINATION.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011101331	20010111	01331	EU  	2001	1	11	AU001035         	1	20001025	G	2840	946432	INDICATOR       			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	FUEL FLOW	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RT FUEL FLOW INDICATION SYSTEM SUSPECT FAULTY (INDICATOR WENT TOFULL SCALE DEFLECTION). INVESTIGATION COULD FIND N	O FAULT WITH THE SYSTEM.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2000121200304	20001212	00304	CE  	2000	12	12	AU001036         	1	20001024	G	5313		STRINGER        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE MAIN LO	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRINGER NR 10 RT LOCATED AT FRAME 207 CRACKED.  NEW FRAME 207 AND SKIN HAD BEEN FITTED.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000121200305	20001212	00305	SO  	2000	12	12	AU001037         	2	20001022	G	7314	MS9021016	O-RING          	CONT        	6381572     	PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE FUEL PUMP	DAMAGED         	W				K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 			960  		L177307					(AUS) ENGINE DRIVEN FUEL PUMP O-G SEAL DAMAGED.  A PORTION OF THE SEAL BLOCKED THE METERING ORIFICE AT THE FCU ALLOWING 	THROUGH ONLY ENOUGH FUEL FOR IDLE POWER.  SUSPECT SEAL DAMAGED DURING PUMP ASSEMBLY AT OVERHAUL.  (X)					1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2000121200306	20001212	00306	CE  	2000	12	12	AU001038         	1	20001020	G	7810		EXHAUST PIPE    	CONT        		CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE COLLECTOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EXHAUST SLIP JOINT BURNT THROUGH ENGINE BEARER CAUSING EXTENSIVE DAMAGE TO BEARER AND WIRING.  FIRE DETECTION SYST	EM DID NOT INDICATE FAULT.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011101332	20010111	01332	SW  	2001	1	11	AU001039         	1	20000928	G	6230	206010332017	MAST            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			2906 							(AUS) MAIN ROTOR MAST CRACKED AT TOP BEARING JOURNAL.  FOUND DURING MAGNETIC PARTICLE INSPECTION.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011101333	20010111	01333	NE  	2001	1	11	AU001040         	3	20001011	G	6114	660710325	BOLT            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER HUB	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB BOLTS NR 1, NR 2, NR 3, NR 6, NR 7 AND NR 8 DID NOT MAKETHE 0.381MM (0.015IN) STRETCH LIMIT AS PER D	OWTY SB SF340-61-96.SUSPECT CAUSED BY EXCESSIVE SEALANT BETWEEN HUB HALVES.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001011101124	20010111	01124	EU  	2001	1	11	AU001041         	1	20001026	G	5610	D20543406	WINDSHIELD      			FOKKER	F28   	F28MK0100   	4990807	EU  										COCKPIT	DELAMINATED     	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RT WINDSHIELD DELAMINATED AND OUTER PANE CRACKED.						2	L	7	2 	4F			RT	        					 
2000121200307	20001212	00307	EA  	2000	12	12	AU001042         	1	20001028	G	5520		ELEVATOR        			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR STRUCTU	FOD             	W				K	 	 	 	NONE                    				O	C	 	OTHER                     	F.O.D.                    		IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ELEVATOR DAMAGED BY YACHT. TRIM TAB DAMAGED.  AIRCRAFT IS A FLOAT PLANE AND WAS MOORED AT THE TIME.  (X)						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001011101125	20010111	01125	SW  	2001	1	11	AU001043         	1	20001030	G	2752	2736053003	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAP	CRACKED         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 			7594 							(AUS) FLAP ACTUATOR HOUSING CRACKED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2000121200308	20001212	00308	SW  	2000	12	12	AU001044         	1	20000731	G	2822	A8164A	PUMP            			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C212   	GL  	FITTING	WRONG PART      	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					63229					(AUS) INCORRECT FUEL PUMP FITTED.  PUMP DEVELOPS ONLY 6 PSI WHEN THE REQUIREMENT IS FOR 14 PSI.  PUMP SERIAL NUMBER ALSO	 INCORRECTLY RECORDED.   UNAPPROVED PART.  (X)					1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2001011101126	20010111	01126	EU  	2001	1	11	AU001046         	1	20001031	G	7931		CONNECTOR       			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	OIL PRESS IND	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				K	N	 	FLUID LOSS                	FALSE WARNING             		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 ENGINE OIL PRESSURE TRANSMITTER CONNECTOR CONTAINED A BROKENDRY SOLDER JOINT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2001011101127	20010111	01127	NM  	2001	1	11	AU001047         	1	20001103	G	3150		SWITCH          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CENTRAL WARNING	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) TAKEOFF WARNING SYSTEM MICROSWITCH OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000121200309	20001212	00309	EU  	2000	12	12	AU001049         	1	20001106	G	5711	68140053	SPAR            	PARTEN      	P68B        	PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING SPAR STRUCT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT WING REAR SPAR WEBS CRACKED AT RELIEF HOLE FOR NR 3 FLAP HINGE BRACKET.  (X)						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2000121200310	20001212	00310	CE  	2000	12	12	AU001050         	1	20001101	G	3260	1SE13	SWITCH          		3500A       	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	LANDING GEAR POS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					4950					(AUS) LANDING GEAR LIMIT MICROSWITCHES PN 1SE1-3 FAILED. THE RUBBER INSERT HOLDING THE PLUNGER AND SEALING THE SWITCH HA	D EXPANDED AND DISINTEGRATED APPROXIMATELY EIGHT TO TWELVE HOURS AFTER LUBRICATION WITH LPS1 LUBRICANT AS SPECIFIED IN T	HE 3500A FLOAT SERVICE MANUAL.  A TEST WITH LPS2 LUBRICANT HAD A SIMILAR RESULT.  SUSPECT RUBBER USED IN THE MICROSWITCH	 IS INCOMPATIBLE WITH THE RECOMMENDED LUBRICANT.  THE AIRCRAFT IS FITTED WITH PK DEVOIE3500A TYPE FLOATS.  MICROSWITCH P	N 1SE1-3 IS USED IN NUMEROUS AIRCRAFT TYPES.  (X)		1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2000121200311	20001212	00311	CE  	2000	12	12	AU001051         	1	20001023	G	3260		DIODE           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	LANDING GEAR POS	FAILED          	W				K	 	 	 	NONE                    				O		 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR ANNUNCIATOR LOGIC BOARD DIODE FAILED.  (X)						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011101128	20010111	01128	EA  	2001	1	11	AU001052         	1	20001101	G	3231	400019000001	VALVE           			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG DOOR	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR MANUAL RELEASE SYSTEM NOT FULLY STOWED. INVESTIGATION FOUND THAT THE RH NOSE GEAR DOOR BYPASS VA	LVE WAS JAMMED.					2	L	7	2 	4F			RT	A21EA   					 
2000121200312	20001212	00312	CE  	2000	12	12	AU001053         	1	20001031	G	2430	08504691	RELAY           			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DC GENERATING SY	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BATTERY RELAY COIL OPEN CIRCUITED DUE TO CORROSION CAUSED BY MOISTURE INGRESS.  (X)						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000121200313	20001212	00313	CE  	2000	12	12	AU001054         	1	20001107	G	2822	476411	PUMP            			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FUEL BOOST PUMP	SHORTED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TRANSFER PUMP FAILED AFTER 287.8 HOURS OPERATION SINCE NEW.  PREVIOUS FUEL PUMP AND FUEL TANKS HAD BEEN CONTA	MINATED WITH EDA.  (X)					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000121200314	20001212	00314	NE  	2000	12	12	AU001056         	2	20001024	G	8530	40698	PISTON          	PWA         		WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	WRONG PART      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			147  		JP205253					(AUS) INCORRECT PISTONS FITTED TO NR 4 AND NR 7 CYLINDERS. THE PISTONS WERE UNDRILLED AND ARE ONLY USED IN NR 5 AND NR 6	 CYLINDERS. THE ENGINE HAD BEEN OVERHAULED IN THEUSA.  UNAPPROVED PART.  (X)					1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2000121200315	20001212	00315	CE  	2000	12	12	AU001058         	1	20001019	G	2130	1013800133	VALVE           		10138001319 	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN PRESSURE C	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 					648184R					(AUS) RIGHT FLOW PACK PN 101-380013-19 FAULTY AND LT PNEUMOSTAT PN 101-380013-3 STICKING.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2000121200316	20001212	00316	EA  	2000	12	12	AU001059         	2	20000930	G	7310	LW120980240	LINE            	LYC         	IO720A1B    	NEWZE 	FU24  	FU24954     	       	WP  	LYC   	O720  	IO720A1B    	41546	EA  					ENGINE FUEL DIST	BROKEN          	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 			944  		L163554A					(AUS) NR 2 AND NR 4 CYLINDER FUEL INJECTOR LINES PN LW-12098-0-170 AND PN LW-12098-0-240 BROKEN AT OR NEAR NIPPLE ON NOZ	ZLE END OF LINE.  (X)					1	L	7	1 	3O	3	O	 	A9PC    	1E15				 
2001011104402	20010111	04402		2001	1	11	AU001060         	1	20001108	G	8120	4066109020	TURBOCHARGER    	LYC         							LYC   	O540  	TIO540A2C   	41532	EA  					EXH TURBOCHARGER	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					L436661A					(AUS) TURBOCHARGER IMPELLER RUBBING ON HOUSING. TURBOCHARGER WAS A NEWLY OVERHAULED ITEM UNDERGOING A PREFITMENT INSPECT	ION.  (X)										3	O			E14EA				 
2001011101129	20010111	01129	SW  	2001	1	11	AU001061         	1	20001101	G	2910	2781032776	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CRACKED         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED IN RT ENGINE BAY LEAKING FROM CRACKED FLARE.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011101130	20010111	01130	EA  	2001	1	11	AU001062         	1	20001006	G	3213	170571	WASHER          			CNDAIR	CL600 	CL6002B19   	       	EA  										MLG	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR NR 2 WHEEL BEARING ANTI-ROTATION WASHER MISSING. WASHER WAS FOUND IN THE WHEEL CLEANUP BASKET DU	RING CLEANING OF THE WHEEL PRIOR TO A TIRE CHANGE. THE WHEEL HAD BEEN REMOVED TWO DAYS BEFORE AND THIS PROMPTED AN INVES	TIGATION DURING WHICH THE NEWLY FITTED WHEEL WAS REMOVED AND THE LACK OF WASHER DISCOVERED. THE WHEEL, AXLE AND BRAKE WE	RE INSPECTED FOR DAMAGE WITH NO FAULT FOUND. PERSONNEL/MAINTENANCE ERROR.			2	L	7	2 	4F			RT	A21EA   					 
2000121200317	20001212	00317	EA  	2000	12	12	AU001063         	2	20001103	G	7414	M3548	ROTOR           	SLICK       	4370        	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					MAGNETO/DIST	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					96030014					(AUS) RIGHT MAGNETO ROTOR SHAFT BROKEN AT THE MAGNET.  DURING DISASSEMBLY IT WAS NOTICED THAT THE TORQUE ON THE ROTOR SH	AFT NUT WAS VERY HIGH.  (X)					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001011101334	20010111	01334	EU  	2001	1	11	AU001064         	1	20000915	G	5720		STIFFENER       			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					WING CENTER BOX	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTRE SECTION VERTICAL STIFFENERS CRACKED IN HOLES. FOUND DURING INSPECTION IAW SB A320-57-1017.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011101335	20010111	01335	NM  	2001	1	11	AU001065         	1	20001016	G	2420	BACC63CD28A22P	CONNECTOR       			BOEING	737   	737377      	       	NM  										AC GENERATION	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 GENERATOR HARNESS CONNECTOR D5124J AND WIRES W142-001-6,W142-002-6 AND W142-003-6 LOCATED AT WING DISCONNECT 	BURNT ANDDAMAGED DUE TO ARCING. SUSPECT CAUSED BY LOOSE CONTACTS DUE TOFAULTY MANUFACTURE AND POOR RELIABILITY OF CONNEC	TORS.				2	L	7	2 	4F			RT	A16WE   					 
2001011101336	20010111	01336	NM  	2001	1	11	AU001066         	1	20000907	G	5415	311T31021	PIN             			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					LT PYLON	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE PYLON MIDSPAR INBOARD FUSE PIN CRACKED. CRACK LENGTH APPROXIMATELY 14MM (0.55IN). FOUND DURING EDDY CURR	ENT INSPECTION.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011101337	20010111	01337		2001	1	11	AU001067         	4	20000817	G	2565	60070102	SLIDE           			AIRBUS	320   	A320211     	3930320	EU  										OVERWING EXIT	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			9072 							(AUS) RT OFFWING SLIDE RAMP LEAKING IN VARIOUS LOCATIONS. DURING INVESTIGATION A SEAM OPENED UP FOR APPROXIMATELY 152.4M	M (6IN).					2	L	7	2 	4F			RT	A28NM   					 
2001011101338	20010111	01338		2001	1	11	AU001068         	4	20000817	G	2565	60070101	SLIDE           			AIRBUS	320   	A320211     	3930320	EU  										OVERWING EXIT	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			9491 							(AUS) LT OFFWING ESCAPE SLIDE RAMP SEAMS LEAKING IN VARIOUS AREAS. DURING INVESTIGATION A SEAM ON THE UPPER INBOARD RAIL	 TUBE OPENED UP FOR APPROXIMATELY 406.4MM (16IN).					2	L	7	2 	4F			RT	A28NM   					 
2000121200318	20001212	00318	CE  	2000	12	12	AU001069         	1	20000831	G	5321		PANEL           			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	FLOOR PANELS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) METAL FLOOR PANELS INTERMITTENTLY OIL CANNING DURING PHASES OF PRESSURIZATION.  (X)						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA	 
2001011101339	20010111	01339	EU  	2001	1	11	AU001070         	1	20001102	G	2150	17983211	HEAT EXCHANGER  			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					CABIN COOLING	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 1 AIRCONDITIONING PACK FAILED. LT COOLING TURBINE AND HEAT EXCHANGER REPLACED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2000121200319	20001212	00319	SO  	2000	12	12	AU001071         	2	20001108	G	8500		ENGINE          	CONT        		CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	OVERSPEED       	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE OVERSPED IN EXCESS OF 3,300 RPM.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2001011101340	20010111	01340	NE  	2001	1	11	AU001072         	2	20001106	G	7320	3029267	FILTER          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL CONTROL	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE P3 FILTER PARTIALLY BLOCKED.  AIRCRAFT IS OPERATING IN EAST TIMOR.  (X)						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001011101341	20010111	01341	NM  	2001	1	11	AU001073         	1	20000916	G	3246		BEARING         			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  						COLLAPSED       	W				C	 	 	 	ABORTED TAKEOFF         				J		 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) NR 7 MAIN WHEEL INNER BEARING COLLAPSED. INVESTIGATION FOUND THAT DURING THE LAST WHEEL CHANGE, THE INBOARD WHEEL 	SPACER WAS NOTREFITTED TO THE AXLE DUE TO THE SPACER COMING OFF WITH THE WHEEL. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001011101342	20010111	01342	NM  	2001	1	11	AU001074         	1	20001025	G	3242		BRAKE           			BOEING	737   	737377      	       	NM  										NR 2	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 BRAKE ATTACHMENT FLANGE BOLT HOLES CORRODED.  PITTING CORROSION ALSO FOUND IN THE BOLT HOLE AT THE 10 O CLOCK	 POSITION. FOUND DURING INSPECTION IAW AD/B737/140.					2	L	7	2 	4F			RT	A16WE   					 
2001011101350	20010111	01350	NM  	2001	1	11	AU001075         	1	20001102	G	3242		BRAKE           			BOEING	737   	73733A      	1384673	NM  										NR 1	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 BRAKE MOUNT HOLE LOCATED AT THE 2 O CLOCK POSITION, NR 2 BRAKE MOUNT FLANGE HOLE LOCATED AT THE 11 O CLOCK PO	SITION AND NO4BRAKE MOUNT FLANGE HOLE LOCATED AT THE 10 O CLOCK POSITION ALLCONTAINED FRETTING CORROSION. FOUND DURING I	NSPECTION IAW AD/B737/140.				2	L	7	2 	4F			RT	A16WE   					 
2001011101351	20010111	01351	WP  	2001	1	11	AU001076         	1	20001106	G	5711	RHTOPWING	SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					RT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT UPPER WING FORWARD SPAR CRACKED FROM SLAT CABLE HOLE LOCATED OUTBOARD OF THE FORWARD INTERPLANE STRUT. FOUND DU	RING INSPECTION IAW AD/DH82/11 AMDT1.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2001011101352	20010111	01352	SW  	2001	1	11	AU001077         	1	20001107	G	2752	2736053003	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAP ACTUATOR	CRACKED         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) RT FLAP ACTUATOR BODY CRACKED AND LEAKING. CRACK LENGTH 40MM(1.57IN). MANUFACTURER STATES THAT THIS ITEM IS ONE OF	 A BATCH OF ACTUATORS WITH SUSPECT INCORRECT MACHINING OF THE ACTUATOR BODY BORE.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011101353	20010111	01353	SW  	2001	1	11	AU001078         	1	20001110	G	6320	206040150	CASE            	BELL        	206B        	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			2455 		BKW11302					(AUS) MAIN ROTOR TRANSMISSION LOWER CASE CONTAINED NUMEROUS CRACKS AND WAS LEAKING IN AREA BELOW MOUNT FOR PIN ASSEMBLY 	PN 206-031-633-101.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000121200320	20001212	00320	CE  	2000	12	12	AU001079         	1	20001108	G	5711	051212443	SPAR            			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	WING SPAR STRUCT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTER SECTION SPAR TO PN 0512124-35 AND PN 0512124-36 LT AND RT DOOR POST CHANNELS HAD ATTACHMENT RIVETS COR	RODED WITH RIVET HEADS MISSING.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2000121200321	20001212	00321	GL  	2000	12	12	AU001080         	1	20001112	G	2823	AN40043	SELECTOR VALVE  			NAMER 	T6    	AT6D        	6400416	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	FUEL SELECTOR/SH	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SELECTOR STIFF IN OPERATION. SUSPECT CAUSED BY CONTAMINATED FUEL.  (X)						1	L	7	1 	3R	3	R	 	A2575   	5E2	5	C	P257	 
2000121200322	20001212	00322	CE  	2000	12	12	AU001081         	1	20001108	G	2432	7007	CONNECTOR       	CONCORDEBATT	RG380E      	BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					BATTERY/CHARGER	BURNED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					CBC368276					(AUS) BATTERY AIRCRAFT SIDE CONNECTOR POSITIVE TERMINALS BURNT AND MELTED.  (X)						2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2001011104404	20010111	04404		2001	1	11	AU001082         	1	20001116	G	3230		LANDING GEAR    	            	            			146300      					            					            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LANDING GEAR FAILED TO EXTEND. GEAR SELECTOR HANDLE RECYCLED WITH THE LANDING GEAR EXTENDING APPROXIMATELY 15 SECO	NDS AFTER THE DOWN' SELECTION.																		 
2000121200323	20001212	00323	CE  	2000	12	12	AU001083         	1	20000922	G	8010	S24432	SOLENOID        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	STARTER	FAULTY          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) STARTER SOLENOID DID NOT RELEASE ON START-UP.  (X)						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2000121200324	20001212	00324	CE  	2000	12	12	AU001084         	1	20001030	G	3230	24670036	BUNGEE CYLINDER 			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR RET	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BUNGEE ASSEMBLY INTERNAL LEFT ADJUSTMENT THREAD BROKEN.  (X)						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2000121200325	20001212	00325	CE  	2000	12	12	AU001085         	1	20001109	G	5523	12346131	TRIM TAB        			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ELEVATOR TAB STR	CRACKED         	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) ELEVATOR TRIM TAB CRACKED AND FAILED IN THE AREA AROUND THE HORN.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P25EA	 
2001011101354	20010111	01354	NM  	2001	1	11	AU001086         	1	20000901	G	5310		STRUCTURE       			BOEING	737   	737377      	       	NM  										FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEVEL 2 CORROSION INSPECTION CARRIED OUT IAW AD/B737/52 AMDT2.						2	L	7	2 	4F			RT	A16WE   					 
2000121200326	20001212	00326	CE  	2000	12	12	AU001087         	1	20001121	G	5312		BULKHEAD        			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					MAIN BULKHEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT FORWARD DOORPOST BULKHEADS CRACKED.  FOUND DURING INSPECTION IAW AD/CESSNA 180/75.  (X)						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2000121200327	20001212	00327	SO  	2000	12	12	AU001088         	1	20001116	G	5521	40075021	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR SPAR/RI	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR SPAR CRACKED. FOUND DURING INSPECTION IAW AD/PA31/126AMDT3.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011101355	20010111	01355	WP  	2001	1	11	AU001089         	1	20001113	G	2911	5133124	ACCUMULATOR     			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	HYD SYSTEM	LEAKING         	W				O	 	 	 	OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 			14   							(AUS) HYDRAULIC ACCUMULATOR DIAPHRAGM LEAKING FLUID.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001011101356	20010111	01356	WP  	2001	1	11	AU001091         	2	20001103	G	7250	3103783931038971	BLADE           			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TURBINE SECTION	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				M	J	 	OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE FIRST STAGE TURBINE BLADES  AND SECOND STAGE TURBINE NOZZLE  HEAT DAMAGED.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011101357	20010111	01357	EA  	2001	1	11	AU001092         	1	20001115	G	2751	601R930303	TRANSMITTER     			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAP POSITION	INTERMITTENT    	W				A	 	 	 	UNSCHED LANDING         				F	N	 	FLT CONT AFFECTED         	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) FLAP POSITION TRANSMITTER INTERMITTENT IN OPERATION. INVESTIGATION FOUND THAT THE TRANSMITTER CONNECTOR WERE CONTA	MINATED WITH MOISTURE DUE TO HEAVY RAIN.					2	L	7	2 	4F			RT	A21EA   					 
2001011101358	20010111	01358	WP  	2001	1	11	AU001094         	2	20001108	G	7200	P70066	ENGINE          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LEFT	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			2364 							(AUS) LT ENGINE LOW POWER. GROUND RUN CONFIRMED THE ENGINE TO BE 3 PERCENT BELOW TARGET TORQUE.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011101359	20010111	01359	EU  	2001	1	11	AU001095         	1	20001110	G	2611	72111211000	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	CARGO BAY	INTERMITTENT    	W				F	A	 	 	ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N		 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) CARGO SMOKE DETECTOR GAVE INTERMITTENT WARNINGS. FIRE EXTINGUISHER DISCHARGED. NO EVIDENCE OF SMOKE OR FIRE.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2000121200328	20001212	00328	CE  	2000	12	12	AU001096         	1	20001102	G	2510	46884689	HOOK            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	COCKPIT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT BELT HARNESS SNAP HOOK SPRING AND PIVOT PINS CORRODED. THE HOOK IS CHROME PLATED, BUT THE HOOK SPRINGS AND PI	VOT PINS ARE NOT.  THE CORRODED (RUSTY) COMPONENTS PREVENT CORRECT OPERATION OF THE HOOKS.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2000121200329	20001212	00329	EU  	2000	12	12	AU001097         	1	20001122	G	7603		PIN             			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	POWER LEVER	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			236  							(AUS) THROTTLE FRICTION ADJUSTMENT SHAFT SPLIT PIN SHEARED DURING FRICTION ADJUSTMENT.  FOUND DURING INVESTIGATION OF EX	CESSIVETHROTTLE FRICTION AND AD/BN-2/69.  (X)					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2000121200330	20001212	00330	SO  	2000	12	12	AU001098         	2	20001121	G	8540		GEAR            	CONT        		CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			80   							(AUS) VACUUM PUMP DRIVE GEAR FAILED.  (X)						1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2001011101360	20010111	01360	EU  	2001	1	11	AU001099         	2	20001013	G	7250	CFM563C1	ENGINE          			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TURBINE SECTION	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				E	X	J	VIBRATION/BUFFET          	ENGINE FLAMEOUT           	WARNING INDICATION        	CL	CLIMB          	1			AU	S 			28817							(AUS) LT ENGINE FAILED. GROUND INSPECTION FOUND MAJOR DAMAGE IN THE TURBINE AREA AND ALSO ON FOUR AREAS ON THE LEFT LOWE	R FUSELAGE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101376	20010111	01376		2001	1	11	AU001100         	4	20001016	G	2565	130104223	CYLINDER        			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ESCAPE SLIDE	UNAPPROVED PART 	W				K	 	 	 	NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OVERWING SLIDE INFLATION CYLINDER INCORRECT PART.  THE INCORRECT PNO 130104-223 INFLATION CYLINDER HAS A 750 CU	BIC INCHCAPACITY BOTTLE WHILE THE CORRECT INFLATION CYLINDER HAS A 900 CUBIC INCH CAPACITY BOTTLE. UNAPPROVED PART. 					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011101377	20010111	01377		2001	1	11	AU001102         	4	20001122	G	3445	6228973001	ANTENNA         			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER TCAS ANTENNA SPLIT. FOUND DURING REMOVAL FOR AIRFRAME CORROSION INSPECTION. ANTENNA HAD BEEN ATTACHED USING 	PRC1422.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011101378	20010111	01378	NM  	2001	1	11	AU001103         	1	20001110	G	3242	215152	BRAKE           			BOEING	747   	747438      	       	NM  										NR 10	FIRE            	W				D	 	 	 	RETURN TO BLOCK         				A		 	FLAME/FIRE                			TX	TAXI/GRND HDL  	1			AU	S 			12047							(AUS) NR 10 BRAKE UNIT FIRE. SUSPECT CAUSED BY EXCESS USE OF GREASE.						2	L	7	4 	4F			RT	A20WE   					 
2000121200331	20001212	00331	CE  	2000	12	12	AU001104         	1	20001103	G	2750	51152242	CONTROL CABLE   			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	TE FLAP CONTROL	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP FOLLOW-UP CABLE DAMAGED.   UPLIMIT SWITCH OUT OF ADJUSTMENT.  SECONDARY DAMAGE CAUSED BY FLAP OVER-RUN DUE TO	 THE UPLIMIT SWITCH INCORRECT ADJUSTMENT.  (X)					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000121200332	20001212	00332	CE  	2000	12	12	AU001105         	1	20001121	G	2760	C4A20	WIRE            		G41A20      	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ELEC WIRING	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAPS UP WIRE C4A-20 SHORT CIRCUITED TO LANDING GEAR UP WIRE G41A-20 WITHIN THE WIRING LOOM LOCATED ADJACENT TO TH	E PILOTS LEFT FOOT AREA.  SUSPECT CAUSED BY WATER INGRESS AND A CRACK IN WIRE C4A-20.  (X)					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001011101379	20010111	01379	NE  	2001	1	11	AU001106         	2	20001117	G	7200		ENGINE          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					NR 1	VIBRATES        	W				O	 	 	 	OTHER                   				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) NR 1 ENGINE VIBRATION. INSPECTION COULD FIND NO CAUSE OR DAMAGE AND IT IS SUSPECTED THAT ICE FORMATION ON THE FAN 	BLADES WAS THE CAUSE OF THE PROBLEM.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001011101380	20010111	01380	EU  	2001	1	11	AU001107         	1	20001118	G	3244		TIRE            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	LT MLG	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR TIRE BURST FOLLOWING A PRACTICE SINGLE ENGINE APPROACH AND LANDING.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2000121200333	20001212	00333	SW  	2000	12	12	AU001108         	1	20001121	G	5347	410A	HOOK            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NONSTD EQUIP	MISMANUFACTURED 	W		A		K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					047					(AUS) RESCUE HOIST HOOK ASSEMBLY THREADED ATTACHMENT SPINDLE APPROXIMATELY 0.482 MM (0.019 INCHES) UNDER SPECIFICATION S	IZE ALLOWING THE NUT TO HAVE EXCESSIVE MOVEMENT ON THE THREAD.  (X)					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001011101381	20010111	01381	EU  	2001	1	11	AU001109         	1	20001118	G	2612	51224133	FIRE LOOP       			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	RT ENGINE	CONTAMINATED    	W				O	 	 	 	OTHER                   				E	B	N	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	LD	LANDING        	1			AU	S 										(AUS) RT ENGINE FIRE WARNING. NIL EVIDENCE OF FIRE OR HOT AIR LEAKS FOUND. SUSPECT WATER CONTAMINATION OF FIRE WIRE CONN	ECTOR. AIRCRAFT HAD FLOWN THROUGH RAIN PRIOR TO FIRE WARNING.					2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2000121200334	20001212	00334	NE  	2000	12	12	AU001110         	2	20001118	G	7320	3028325	LINE            	PWA         		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL CONTROLLING	FRACTURED       	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 					60723					(AUS) ENGINE P3 LINE FRACTURED AT THE FLANGE WHERE THE LINE IS SWAGED TO THE FILTER BOWL.  (X)						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000121200335	20001212	00335	CE  	2000	12	12	AU001111         	1	20001114	G	5522	96610006618	SKIN            			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	ELEVATOR PLATES	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ELEVATOR LOWER SKIN CRACKED AND DISBONDED IN AREA OF STIFFENERS.  CRACK LENGTHS 31.75 (1.25 INCHES).  ELEVAT	ORS ARE FROM THE PERIOD SPECIFIED IN SB 27-3396 REV 1.  (X)					1	L	7	2 	3O			 	3A16    		5	C	P22EA	 
2000121200336	20001212	00336	EU  	2000	12	12	AU001112         	1	20001122	G	2800		FUEL CELL       			HWKSLY	DH104 	DH104*      	       	EU  	RROYCE	GIPSY 	GIPSY70MK2  	20007	EU  	HWKSLY	PD143	PD143312    	EU  	FUEL SYS	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL SYSTEM CONTAMINATED WITH EDA (ETHYLENE DIAMINE).  (X)						1	L	7	2 	3I	3	I	 	A807    	E310	5	C	P916	 
2001011101382	20010111	01382	WP  	2001	1	11	AU001113         	2	20001115	G	7261	P1070	FILTER          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE OIL	BROKEN          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE OIL FILTER END CAP BROKEN AWAY AT RECESS.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001011101383	20010111	01383	EU  	2001	1	11	AU001114         	1	20001025	G	3260	ZOON7143022038	CONNECTOR       			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MLG DOWNLOCK	BROKEN          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RT DOWNLOCK SWITCH CONNECTOR BROKEN AT THE BOTTOM OF THE ATTACHMENT NUT.						1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920	 
2000121200337	20001212	00337	SW  	2000	12	12	AU001115         	1	20001123	G	5711	204311	SPAR CAP        	AIRTRC      		AIRTRC	AT500 	AT502       	0390303	SW  	PWA   	PT6   	PT6A15AG    	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	WING SPAR STRUCT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					5020055					(AUS) LEFT SPAR CAP CRACKED IN AREA OF THE HOLE LOCATED 3 MM (0.118 INCHES) FORWARD ALONG THE BOTTOM FACE AND 8 MM (0.31	4 INCHES) UP THE HOLE.  FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AT/20 SL 197.   (X)					1	L	7	1 	3T	4	T	NC	A9SW    	E4EA	6	C	P15EA	 
2001011101384	20010111	01384	NM  	2001	1	11	AU001117         	1	20001111	G	2820		SEAL            			BOEING	747   	747438      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUEL DIST	MISINSTALLED    	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 PYLON FUEL LINE WIGGINS COUPLING LEAKING. INVESTIGATION FOUND THAT THE SEALS HAD BEEN INCORRECTLY FITTED. 						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2001011101385	20010111	01385	NM  	2001	1	11	AU001118         	1	20001120	G	2510		CLAMP           			BOEING	747   	747438      	       	NM  										COCKPIT	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) FIRST OFFICERS FLIGHT LIBRARY BOX BROKE FREE FROM THE RESTRAINT AND SLID BACK UNDER THE FIRST OBSERVERS TABLE. INV	ESTIGATION FOUND THAT THE BOX BROKE FREE DUE TO INADEQUATE GRIP ON THE RETAINING STRAP BY THE FORWARD LOCKING CLAMP.					2	L	7	4 	4F			RT	A20WE   					 
2001011101386	20010111	01386	NM  	2001	1	11	AU001119         	1	20001115	G	2750	65C3084618	BELLCRANK       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT OUTBOARD AFT FLAP INBOARD BELLCRANK CRACKED. THE CRACK RAN FOR ALMOST THE ENTIRE LENGTH OF THE SMALLER CRANK AR	M.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101387	20010111	01387	NM  	2001	1	11	AU001120         	1	20001031	G	3810	S417T2006	SUPPORT BRACKET 			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					POTABLE WATER	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN POTABLE WATER TANK SUPPORT RODS (3OFF) BROKEN ALLOWINGTHE TANK TO COLLAPSE ONTO THE TOILET FAN AND RUPTURE	.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001011101390	20010111	01390	NM  	2001	1	11	AU001121         	1	20001105	G	2520	908356G	SEAT            			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLIGHT ATTENDANTS FORWARD DOUBLE SEAT SEPARATED FROM WALL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101391	20010111	01391	NM  	2001	1	11	AU001122         	1	20001027	G	2731	AR7077M3	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ELEVATOR TAB CON	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			18131		Y0504					(AUS) HORIZONTAL STABILISER TRIM ACTUATOR FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2000121200338	20001212	00338	CE  	2000	12	12	AU001123         	1	20001122	G	2434	649304	ALTERNATOR      			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GENERATOR-ALT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR FAILED.  WINDINGS AND DIODES BURNT.  ALTERNATOR HAD ONLY RECENTLY BEEN OVERHAULED.  (X)						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2000121200339	20001212	00339	CE  	2000	12	12	AU001125         	1	20001108	G	3260	661011	PLUG            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	LANDING GEAR POS	BURNED OUT      	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) PILOT REPORTED LG MALFUNCTION PRIOR TO LANDING - THREE GREEN INDICATIONS AND AN INTERMITTENT RED LIGHT.  ON TOUCH 	DOWN, THE NLG COLLAPSED.  INVESTIGATION FOUND THE BULKHEAD PLUG PN 66101-1 ON THE FORWARD CABIN FIREWALL HAD AN INTERNAL	 MELT DOWN AND FUSED SOME PINS TOGETHER.  (X)				1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001011101392	20010111	01392	EU  	2001	1	11	AU001126         	1	20001106	G	3610	9303688100	DUCT            			SAAB  	SF340 	340B        	7860101	EU  										PNEUMATIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING AN ENGINE GROUND RUN THE LH 'BLEED LEAK' LIGHT ILLUMINATED. A SYSTEM CHECK DETECTED LEAKAGE FROM THE FLEXIB	LEDUCT AT THE WIND ROOT.FURTHER INVESTIGATION FOUND A STAINLESS STEEL INSERT HAD DISBONDED FROM THE SILICON FLEXIBLE DUC	T.				2	L	7	2 	4T			RT	A52EU   					 
2001011101393	20010111	01393	EU  	2001	1	11	AU001127         	1	20001122	G	2844	8346	PRESSURE SWITCH 			SAAB  	SF340 	SF340A      	7850100	EU  										PRESSURE IND	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING PRE-FLIGHT INSPECTION FUEL DEPOSITS WERE OBSERVED ON THE RT ENGINE AND NACELLE. FUEL LEAKAGE WAS TRACED TO 	A CRACKED SOLDER JOINT IN THE DIFFERENTIAL PRESSURE SWITCH FITTING.					2	L	7	2 	4T			RT	A52EU   					 
2001011101394	20010111	01394	EU  	2001	1	11	AU001128         	1	20001121	G	3610	7275031506	DUCT            			SAAB  	SF340 	SF340A      	7850100	EU  										PNEUMATIC SYSTEM	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 					J94051					(AUS) DURING CRUISE THE CREW NOTICED THE ITT DELTA T WAS 20 DEGREES HIGHER ON THE LT ENGINE COMPARED TO PREVIOUS FLIGHT.	INVESTIGATION FOUND A CRACK AROUND THE HIGH PRESSURE BLEED DUCT EXTENDING FOR APPROXIMATELY 180 DEGREES ADJACENT TO THE 	FLANGE COUPLING TO THE ENGINE.				2	L	7	2 	4T			RT	A52EU   					 
2001011101395	20010111	01395	EU  	2001	1	11	AU001129         	1	20001118	G	3610	9303688100	DUCT            			SAAB  	SF340 	340B        	7860101	EU  										PNEUMATIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING A SCHEDULED INSPECTION, EVIDENCE OF BLEED AIR LEAKAGE AT THE LT WING ROOT FLEXIBLE DUCT WAS FOUND.  FURTHER	 INVESTIGATIONFOUND A STAINLESS STEEL INSERT HAD DISBONDED FOR THE SILICONDUCT.					2	L	7	2 	4T			RT	A52EU   					 
2001011101396	20010111	01396	NM  	2001	1	11	AU001130         	1	20000814	G	2750		TORQUE TUBE     			DHAV  	DHC8  	DHC8106     	       	NM  										TE FLAP	MISINSTALLED    	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) DURING LANDING THE FLAPS WERE APPLIED TO 35 DEGREES AND FLAP DRIVE CAUTION LIGHT ILLUMINATED. INSPECTION OF THE FL	AP DRIVE SYSTEM FOUND THAT THE RT INBOARD PRIMARY DRIVE TORQUE TUBE WAS INCORRECTLY FITTED.  					2	H	7	2 	4T			RT	A13NM   					 
2001011101397	20010111	01397	NM  	2001	1	11	AU001131         	1	20001021	G	5280		NUT             			BOEING	747   	747438      	       	NM  										MLG DOOR	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING LANDING GEAR DOOR PANEL 743AB HAD EXCESSIVE PLAY. INSPECTION FOUND THE DOOR TO GEAR STRUT CONNECTING ROD N	UT AND BOLT LOOSE. NUT WAS ATTACHED BY TWO THREADS ONLY. .					2	L	7	4 	4F			RT	A20WE   					 
2001011101398	20010111	01398	CE  	2001	1	11	AU001132         	1	20001125	G	5312		BULKHEAD        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/200/67.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001011101399	20010111	01399	EA  	2001	1	11	AU001133         	3	20001102	G	6110	72CK56	BLADE           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2A     	41505	EA  	SNSNCH	72C	72CK        	EA  	PROPELLER	MISMANUFACTURED 	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER TIP EXFOLIATING. SUSPECT MANUFACTURING DEFECT/FLAW.						1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045	 
2001011101400	20010111	01400	SO  	2001	1	11	AU001134         	2	20001024	G	8520	653580	ADAPTER         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	STARTER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE CRANKSHAFT STARTER ADAPTER GEAR TEETH HAD ABNORMAL WEAR INDICATIONS.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001011101401	20010111	01401	SO  	2001	1	11	AU001135         	2	20001127	G	8540	631847	SHAFT           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	STARTER ADAPTER	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			39   							(AUS) LT ENGINE STARTER ADAPTER GEAR SHAFT SHEARED IN AN AREA 16MM(0.629IN) FROM THE PILOT BEARING END OF THE SHAFT.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001011101413	20010111	01413	NE  	2001	1	11	AU001136         	2	20001129	G	7200	CT79B	ENGINE          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	RIGHT	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			12835							(AUS) RH ENGINE CHIP DETECTOR CONTAMINATED WITH A LARGE AMOUNT OF BEARING MATERIAL.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011101414	20010111	01414	EA  	2001	1	11	AU001137         	3	20000802	G	6110	M74DM51	PROPELLER       			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	FWD	UNAPPROVED PART 	W		A		K	 	 	 	NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			1322 							(AUS) INCORRECT PROPELLER FITTED TO AIRCRAFT. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.						1	H	7	1 	3O	3	O	 	1A2     	E274	5	N	P88614	 
2001011101415	20010111	01415	CE  	2001	1	11	AU001138         	1	20001130	G	2435	1013690145	COVER           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					STARTER-GEN	SEPARATED       	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) STARTER COVER CAME OFF AND JAMMED BETWEEN THE COWL AND THE ENGINE FCU CONTROL ROD.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001011101416	20010111	01416	CE  	2001	1	11	AU001139         	1	20001129	G	2910	AE1003785G0250	HOSE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	HYD SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT ENGINE DRIVEN HYDRAULIC PUMP PRESSURE HOSE FAILED. SUSPECT HOSE WAS HEAT STRESSED.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001011101417	20010111	01417	SO  	2001	1	11	AU001140         	1	20001122	G	3520		OXYGEN MASK     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	O2 SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) PASSENGER OXYGEN MASKS FAILED TO DEPLOY AT 14,000 FEET. SUSPECT CAUSED BY DRY AND STIFF HINGES ON THE OXYGEN MASK 	DOORS DUE TOINFREQUENT USE AND SOLVENTS USED IN REPAINTING HAVING WASHED ANYLUBRICANT FROM THE HINGES. THE TOILET OXYGEN	 MASK DOOR ELECTRIC LATCH  WAS ALSO DEFECTIVE.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001011101418	20010111	01418	EU  	2001	1	11	AU001141         	1	20001127	G	5730		SKIN            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TOP SKIN PANELS CONTAINED NUMEROUS DRILL MARKED AREAS. FOUND DURING INSPECTION IAW AD/BAE146/66 AND ANSETT EN	GINEERING RELEASE BA6-57-10-9C. NO CORROSION WAS FOUND.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001011101419	20010111	01419		2001	1	11	AU001142         	4	20001201	G	3457	TNG2101	GPS             			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	COCKPIT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					6021318					(AUS) GPS SYSTEM FAULTY. RECEIVER INDICATES SPACE VEHICLES USED FOR NAVIGATION ARE BELOW THE HORIZON.						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
2001011101420	20010111	01420	CE  	2001	1	11	AU001143         	1	20001128	G	3221	5842000211	PIN             			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	NLG TRUNNION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION PINS CRACKED. FOUND DURING INSPECTIONIAW CESSNA SB 88-5R2.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011101421	20010111	01421	SW  	2001	1	11	AU001144         	1	20001128	G	3213	27515010	STRUT           	SWRNGN      	27515003BC  	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	MLG	LEAKING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 					120TD					(AUS) LT MAIN LANDING GEAR STRUT CYLINDER GLAND SEAL RETAINING RING GROOVE LOWER LAND SHEARED RELEASING THE RETAINING RI	NG AND ALLOWING THE GLAND TO SLIP DOWN THE PISTON CAUSING LOSS OF FLUID FROM THE STRUT.					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE	 
2001011101422	20010111	01422	EU  	2001	1	11	AU001145         	1	20001126	G	7722	522861	INDICATOR       			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	EGT/TIT IND	FAILED          	W				A	 	 	 	UNSCHED LANDING         				P		 	NO WARNING INDICATION     			CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE TURBINE TEMPERATURE INDICATOR FAILED.  ANALOGUE AND DIGITAL INDICATIONS WERE LOST.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001011101423	20010111	01423	EU  	2001	1	11	AU001146         	1	20001130	G	7712		CONTROL PANEL   			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	LT ENG CTOT	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE CONSTANT TORQUE ON TAKEOFF (CTOT) CONTROL PANEL SUSPECT FAULTY OR ENGINE CONTROLS SLIGHTLY MISRIGGED PRE	VENTING CTOT FROM CAPTURING THE ENGINE.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001011101424	20010111	01424	SW  	2001	1	11	AU001148         	1	20001108	G	2910	2781006	PIPE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	HYD SYSTEM	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC POWER PACK PIPE LOCATED IN LT ENGINE NACELLE LEAKING.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2001011101438	20010111	01438	NE  	2001	1	11	AU001149         	2	20001204	G	7250	PCE115413	ENGINE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					TURBINE SECTION	MAKING METAL    	W				O	 	 	 	OTHER                   				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) LH ENGINE CHIP DETECTOR METAL CONTAMINATION. FOURTH STAGE TURBINE DAMAGED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2001011101439	20010111	01439	NM  	2001	1	11	AU001150         	1	20001115	G	2913	3508806	PUMP            			BOEING	767   	767216      	1385121	NM  	GE    	CF6   	CF680A      	30025	NE  					HYD SYSTEM	CRACKED         	W				O	 	 	 	OTHER                   				F	K	 	FLT CONT AFFECTED         	FLUID LOSS                		CR	CRUISE         	1			AU	S 			10278							(AUS) RT ENGINE DRIVEN HYDRAULIC PUMP CASING CRACKED. PUMP DRIVESHAFT FAILED AT SHEAR POINT. SEVERE INTERNAL DAMAGE TO P	UMP. SUSPECTPISTON AND SHOE SUBASSEMBLY FAILED FIRST. LOSS OF HYDRAULIC FLUID.					2	L	7	2 	4F	4	F	RT	A2NM    	E13NE				 
2001011101440	20010111	01440	WP  	2001	1	11	AU001151         	1	20001205	G	6220	5143711	HUB             			HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  					MAIN ROTOR	CRACKED         	W		A		C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 			304  							(AUS) MAIN ROTOR HUB SEVERELY CRACKED IN AN AREA NOT KNOWN FOR CRACKING. FOLLOWING TAKEOFF CONTROL WAS ALMOST IMPOSSIBLE	 AND THE MASSIVE VIBRATION CAUSED THE FORE/AFT ENGINE MOUNT TO BE TORN FROM ITS HOUSING AND THE SHAFT TO CRACK. THE CRAC	K WAS OPENINGUP UNDER LOAD AND CAUSING A MASSIVE OUT OF BALANCE VIBRATION. THE  SEPARATION OF THE MAIN ROTOR BLADE WAS C	ONSIDERED IMMINENT.			1	G	7	1 	3O	3	O	 	4H11    	E304				 
2001011101441	20010111	01441	NM  	2001	1	11	AU001152         	1	20001115	G	2611	30326E1	AMPLIFIER       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SMOKE DETECTOR	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) BAGGAGE COMPARTMENT SMOKE DETECTOR AMPLIFIED FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011101442	20010111	01442	EU  	2001	1	11	AU001154         	1	20001201	G	2910	F8553048401	HOSE            			FOKKER	F27   	F27MK50     	       	EU  										HYD SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) LT MAIN LANDING GEAR RETRACTION HOSE BURST. LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T			RT	A817    					 
2001011101443	20010111	01443	CE  	2001	1	11	AU001155         	1	20001211	G	3510	51001063	PIPE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	OXYGEN SYSTEM	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OXYGEN PIPE CORRODED AND LEAKING IN AREA BEHIND PILOTS SEAT SIDELINING. PIPE CONTAINED PIN HOLE CORROSION IN THE A	REAS TOUCHING THE SCAT HOSE.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001011101444	20010111	01444	SO  	2001	1	11	AU001156         	2	20001205	G	8550		PUMP            			PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE OIL	FOD             	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 			292  							(AUS) FOREIGN OBJECT DAMAGE TO ENGINE OIL PUMP. INSPECTION FOUND THAT A SMALL LOOP OF SPRING LIKE STEEL HAD ENTERED THE 	OIL PUMP ANDJAMMED TO PUMP GEARS CAUSING THE DRIVESHAFT TO SHEAR. INSPECTIONOF THE FOREIGN MATERIAL HAS DETERMINED THAT 	IT IS NOT FROM ACOMPONENT WITHIN THE ENGINE.				1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001011101445	20010111	01445	NM  	2001	1	11	AU001157         	1	20001129	G	7920	R14	FILTER          			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE OIL	DISTORTED       	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 										(AUS) EXTERNAL ENGINE OIL FILTER MOUNT FACE WARPED AND LEAKING OIL.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001011101446	20010111	01446	EU  	2001	1	11	AU001158         	1	20001208	G	7120		BRACKET         			BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE MOUNT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT BRACKETS CRACKED ON SPAR ATTACHMENT FLANGE. FORWARD SPAR CRACKED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001011101447	20010111	01447	CE  	2001	1	11	AU001159         	1	20001207	G	2460	CM358940	CIRCUIT BREAKER 			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	DC POWER	FAILED          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) AVIONICS CIRCUIT BREAKER/SWITCH INTERNAL FAILURE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011101448	20010111	01448	CE  	2001	1	11	AU001160         	1	20001130	G	2810		FUEL CELL       			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MAIN	CONTAMINATED    	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) FUEL SYSTEM WATER CONTAMINATION. SUSPECT LEAKING FUEL TANK CAPSEALS.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001011101449	20010111	01449	EA  	2001	1	11	AU001161         	2	20001130	G	8550	LW13388	GASKET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DETERIORATED    	W				A	 	 	 	UNSCHED LANDING         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) ENGINE OIL FILTER CONVERTER PLATE GASKET DETERIORATED AND EXTRUDED. ENGINE OIL LEAKING. FOUND DURING INSPECTION IA	W AD/LYC/105.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011101464	20010111	01464	NM  	2001	1	11	AU001162         	1	20001120	G	2824	405742	ACTUATOR        			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL TRANSFER	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 					9853					(AUS) FUEL CROSSFEED VALVE ACTUATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101465	20010111	01465	NM  	2001	1	11	AU001163         	1	20001204	G	5414	196CR	PANEL           			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					RT PYLON	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT STRUT TRUNNION ACCESS PANEL SEPARATED FROM AIRCRAFT. THE PANEL CAUSED IMPACT DAMAGE TO THE RT HORIZONTAL STABIL	ISER LEADING EDGE AND TOP SKIN. FOLLOWING REMOVAL OF THE REMAINS OF THE DEPARTEDPANEL THE HOLDING TORQUE ON THE ANCHOR N	UTS WAS CHECKED WITH FOUR ANCHOR NUTS FAILING THE TORQUE CHECK.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011101466	20010111	01466	NM  	2001	1	11	AU001164         	1	20001123	G	2520	18DEF	SEAT            			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SEAT 18DEF LOOSE DUE TO THE AISLE LEG BEING OUT OF THE TRACK.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101467	20010111	01467		2001	1	11	AU001165         	4	20001117	G	2561		LIFE VEST       			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT HAD A SHORTAGE OF LIFE JACKETS ON BOARD.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101468	20010111	01468	NM  	2001	1	11	AU001166         	1	20001112	G	7830		DOOR            	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	SEPARATED       	W				O	 	 	 	OTHER                   				E	D	 	VIBRATION/BUFFET          	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 										(AUS) NR 3 ENGINE THRUST REVERSER BLOCKER DOOR SEPARATED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001011101469	20010111	01469	SW  	2001	1	11	AU001167         	1	20000918	G	5310	2700	STRUCTURE       			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT EXTENSIVELY CORRODED IN BOTH WINGS AND FUSELAGE IN NORMALLY INACCESSIBLE AREAS. AIRCRAFT HAD NO CORROSION	 PROTECTION AT MANUFACTURE.					1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P920	 
2001011101470	20010111	01470	SO  	2001	1	11	AU001168         	2	20000901	G	8520		CONNECTING ROD  			PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	NR 1 CYLINDER	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 CYLINDER CONNECTING ROD LITTLE END FAILED RESULTING IN CATASTROPHIC ENGINE FAILURE. INVESTIGATION FOUND THAT 	THE LITTLE END BUSH WAS CRACKED CAUSING THE FAILURE. SUSPECT CRACKING CAUSED BY ENGINE OVERSPEED.					1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001011101471	20010111	01471	CE  	2001	1	11	AU001169         	1	20001025	G	2731	12600741	ACTUATOR        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ELEVATOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM ACTUATOR HAD EXCESSIVE PLAY IN THE SHAFT/INTERNAL SCREW COMBINATION RESULTING IN EXCESSIVE TRIM TAB 	FREEPLAY. THE UNIT HAD ONLY 62.2 HOURS SINCE NEW.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2001011101472	20010111	01472	EA  	2001	1	11	AU001170         	2	20001208	G	8530	MS139973	KEY             			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE	DISINTEGRATED   	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO3 CYLINDER EXHAUST VALVE SPRING LOCKING KEYS SHATTERED BUT WERE STILL HOLDING THE SPRINGS IN PLACE. CAP PNO MS13	998-3 ALSO HADSEVERAL CHIPS MISSING. THE VALVE SEAT WAS DAMAGED BEYOND LIMITS.FOUND DURING INSPECTION IAW LYCOMING SB 38	8B. NO EVIDENCE OFMETAL IN THE OIL FILTERS.				1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2001011101473	20010111	01473	EA  	2001	1	11	AU001171         	1	20001211	G	3260	864807	PSEU            			CNDAIR	CL600 	CL6002B19   	       	EA  										MLG	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) PROXIMITY SENSOR ELECTRONIC UNIT (PSEU) FAULTY.						2	L	7	2 	4F			RT	A21EA   					 
2001011101474	20010111	01474	NM  	2001	1	11	AU001172         	1	20001214	G	6310	A1161	SHAFT           			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE CLUTCH	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			100  							(AUS) CLUTCH SHAFT SHEARED AND CLUTCH DISINTEGRATED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001011101475	20010111	01475	NM  	2001	1	11	AU001173         	1	20000922	G	2133		OUTFLOW VALVE   			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN PRESSURE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) CABIN PRESSURISATION SYSTEM OUTFLOW VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101492	20010111	01492	NM  	2001	1	11	AU001174         	1	20000924	G	4930		FUEL CONTROL    			BOEING	767   	767330      	       	NM  										APU	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FUEL CONTROL UNIT LEAKING FUEL.						2	L	7	2 	4F			RT	A1NM    					 
2001011101493	20010111	01493	NM  	2001	1	11	AU001175         	1	20000922	G	2133		OUTFLOW VALVE   			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN PRESSURE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) CABIN PRESSURISATION SYSTEM OUTFLOW VALVE FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001011101494	20010111	01494	EU  	2001	1	11	AU001176         	1	20000908	G	5311		FRAME           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 35 CRACKED IN AREA BETWEEN STRINGER NO30 AND STRINGER NO31.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001011101495	20010111	01495		2001	1	11	AU001177         	4	20000702	G	2370	93A10030	CVR             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT VOICE RECORDER FAILED STEPS NR1 1 AND NR 12 OF AMM23-71-00-501.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001011101496	20010111	01496	SO  	2001	1	11	AU001178         	1	20001118	G	5521	40075016	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			AU	S 										(AUS) RT ELEVATOR SPAR CRACKED AT OUTBOARD END. FOUND DURING INSPECTION IAW AD/PA31/126 AMDT3.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001011101497	20010111	01497	EU  	2001	1	11	AU001179         	1	20001204	G	2750	9450202201	DRIVE SHAFT     			PILATS	PC12  	PC12        	7090550	EU  										TE FLAP CONTROL	DAMAGED         	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) RT FLAP INBOARD DRIVESHAFT DAMAGED.						1	L	7	1 	3T			RT	A78EU   					 
2001011101498	20010111	01498	EU  	2001	1	11	AU001180         	1	20001208	G	6320	332A32100701P	TRANSMISSION    			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MAIN ROTOR G/B	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 			2423 							(AUS) MAIN TRANSMISSION MAGNETIC PLUG AND OIL FILTER CONTAMINATED WITHMETAL.						2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001011101499	20010111	01499	EU  	2001	1	11	AU001181         	1	20001209	G	3260		WARNING SYSTEM  			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MLG	FAULTY          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR WARNING LIGHTS ILLUMINATED DURING DESCENT. THE LANDING GEAR WAS CONFIRMED DOWN. INVESTIGATION OF THE 	WARNING SYSTEM COULD FIND NO FAULTS. AIRCRAFT RETURNED TO SERVICE.					2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001011101500	20010111	01500	EU  	2001	1	11	AU001182         	1	20001209	G	3230		LANDING GEAR    			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MAINS	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR WOULD NOT EXTEND. THE GEAR WAS EXTENDED USING THEEMERGENCY SYSTEM. INVESTIGATION COULD FIND NO FAULTS	 BUT THELANDING GEAR CONTROL PRINTED CIRCUIT BOARD WAS CHANGED AS A PRECAUTION.					2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001011101501	20010111	01501	EU  	2001	1	11	AU001183         	1	20001215	G	3320		SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	LAVATORY	FALSE ACTIVATION	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LAVATORY SMOKE DETECTOR OPERATED. INVESTIGATION FOUND NO EVIDENCE OF FIRE. 						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001011101502	20010111	01502		2001	1	11	AU001184         	4	20001206	G	3417	02702MOD6	ADC             			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					COCKPIT	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 					0285960					(AUS) AIR DATA COMPUTER (ADC) FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE				 
2001011101503	20010111	01503	NM  	2001	1	11	AU001185         	1	20001203	G	4920		APU             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	APU BAY	SHUTDOWN        	W				A		 	 	UNSCHED LANDING         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) APU AUTO SHUTDOWN AND OVERHEAT WARNING. INVESTIGATION COULD FINDNO FAULTS. AIRCRAFT RETURNED TO SERVICE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001011101518	20010111	01518	SO  	2001	1	11	AU001186         	1	20001210	G	2752	11595CC2127	ACTUATOR        			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					TE FLAP	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) LT OUTBOARD FLAP JACK SCREW ACTUATOR CLUTCH WEAK PREVENTING CORRECT FLAP OPERATION.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2001011101519	20010111	01519	EA  	2001	1	11	AU001188         	1	20001203	G	2910	S3250AND	PIPE            			DHAV  	DHC3  	DHC3        	2800202	EA  										HYD SYSTEM	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR BRAKE LINE BROKEN. SUSPECT CAUSED BY PROPELLER WASH DEBRIS.						1	H	7	1 	3R			 	A815    					 
2001011101520	20010111	01520	CE  	2001	1	11	AU001189         	1	20001210	G	3213	508103207	SOCKET          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					LT MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR STRUT SOCKET ASSEMBLY CRACKED IN THE AREA OF ATTACHMENT LUGS. CRACK LENGTHS INBOARD 13.2MM (0	.52IN) ANDOUTBOARD 12.7MM (0.5IN).					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001011101521	20010111	01521	CE  	2001	1	11	AU001190         	1	20001210	G	3213	5081032017	SOCKET          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					LT & RT MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR STRUT SOCKET ASSEMBLIES CRACKED INTHE AREA OF ATTACHMENT LUGS.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001011101522	20010111	01522	EA  	2001	1	11	AU001193         	1	20001208	G	2701	600591567	CAPSTAN         			CNDAIR	CL600 	CL6002B19   	       	EA  										CONTROL COLUMN	SLIPPED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) STICK PUSHER CAPSTAN SLIPPING WHEN THE ACTUATOR REACHED FULL TRAVEL ALLOWING THE CONTROL COLUMN TO RETURN FROM ITS	 FULL TRAVEL STOP AN TO BE DRIVEN TO THE STOP AGAIN. DURING REPLACEMENT OF THE CAPSTAN ONE OF THE CONTROL CABLES RUNNING	 TO THE STICK PUSH ACTUATOR WAS FOUND TO BE SEPARATED FROM THE SWAGED TERMINAL.				2	L	7	2 	4F			RT	A21EA   					 
2001011101523	20010111	01523	SW  	2001	1	11	AU001194         	1	20001129	G	2913	PVB04426	PUMP            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYD SYSTEM	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			276  							(AUS) RT ENGINE DRIVEN HYDRAULIC PUMP LEAKING FLUID FROM BETWEEN PARTING FACES. INVESTIGATION FOUND THAT A CHECK VALVE I	N THE RT HYDRAULIC PUMP BYPASS LINE WAS BLOCKED BY DEBRIS FROM PREVIOUS PUMP FAILURES CAUSING A BUILDUP OF PRESSURE ACRO	SS THE PUMP WHICH COULD NOT BE BYPASSED THERE FORE CAUSING THE PUMP TO OPEN UP AT APARTING FACE AND ALLOW HYDRAULIC FLUI	D TO BE LOST.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2001011101524	20010111	01524	NE  	2001	1	11	AU001195         	2	20001213	G	7230		COMPRESSOR      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	ENGINE	DAMAGED         	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE SURGING ABOVE 1400 FTLBS OF TORQUE. BLEED VALVE CHECKEDOK. FIRST STAGE COMPRESSOR BLADES HAD SOME LEADING E	DGE ROUGHNESS. RECOVERY WASH CARRIED OUT. STALL/SURGE AT 900 FT LBS ACCOMPANIED BY A LOUD SQUEAL FROM THE ENGINE. SUSPEC	T COMPRESSOR SECTION DISTRESS / FAILURE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001011101525	20010111	01525	EU  	2001	1	11	AU001196         	1	20001217	G	5510	2712001052901	SKIN            			FOKKER	F27   	F27MK500    	4990629	EU  						ROTOL	R4304	R1934304    	EU  	HORIZONTAL STAB	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HORIZONTAL STABILISER LEADING EDGE (LAMINATED TIMBER CONSTRUCTION) BADLY DELAMINATED , THE TIMBER SECTION ROTTE	D AND THE BONDED SECTION FULL OF WATER. RUBBER BOOT DISBONDED AND INFLATION CELLS PERISHED ON THE TOP SURFACE.					2	H	7	2 	4T			 	A817    		6	C	P899	 
2001011101526	20010111	01526	EU  	2001	1	11	AU001197         	1	20001215	G	5342	TB2034021003	BRACKET         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	STABILIZER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILISER ATTACHMENT BRACKET CONTAINED EXFOLIATION CORROSION INTHE OUTBOARD VERTICAL FACE.						1	L	7	1 	3O	3	O	RT	A51EU   	E286	5	C	P920	 
2001011101527	20010111	01527	WP  	2001	1	11	AU001201         	1	20001220	G	6220	A2035	YOKE            			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR HEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR YOKE CRACKED IN THE AREA DESCRIBED IN AD/R22/49.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001011101528	20010111	01528	CE  	2001	1	11	AU001202         	1	20001212	G	2710	08111481	BRACKET         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	AILERON CONTROL	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER AILERON BELLCRANK BRACKET WORN ON THE LOWER SIDE. THE WEAR WAS CAUSED BY THE BELLCRANK/CABLE ATTACHMENT CLEV	IS PINS RUBBING.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001011101529	20010111	01529	EU  	2001	1	11	AU001203         	1	20001220	G	2750		CONTACTOR       			PILATS	PC12  	PC12        	7090550	EU  										TE FLAP CONTROL	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP MOTOR CONTACTOR SUSPECT FAULTY.						1	L	7	1 	3T			RT	A78EU   					 
2001011101563	20010111	01563	CE  	2001	1	11	AU001204         	1	20001220	G	2710		CONTROL CABLE   			CESSNA	172   	172A        	2072404	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	RT AILERON	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD LH FLAP RETRACTION CABLE AND RH AILERON CABLES CROSSEDOVER EACH OTHER UNDER THE FLOOR BEHIND THE LANDING G	EAR BULKHEAD. FLAP AND AILERON CABLES INCORRECTLY FITTED TO BOTH LOWER OUTERAND LH AND RH PULLEYS BEHIND THE CABIN DOORS	. AILERON CABLE STRANDS WORN. PERSONNEL/MAINTENANCE ERROR.				1	H	7	1 	3O	3	O	 	3A12    	E253	5	N	P910	 
2001011101564	20010111	01564	CE  	2001	1	11	AU001205         	1	20001205	G	3213	5081032011	STRUT           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR STRUCK BY A KANGAROO. INSPECTION FOUND THE LT MAIN LANDING GEAR AXLE AND TORQUE KNEE SOCKET C	RACKED AT THE LOWER END OF THE TORQUE KNEE ATTACHMENT LUGS. CRACK LENGTH11.43MM (0.45IN).					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2001040200308	20010402	00308	NM  	2001	4	2	AU001206         	1	20001211	G	3240	215152	HEAT SHIELD     			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					MLG	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 12 BRAKE HEAT SHIELD DISTORTED AND CUT A GROOVE INTO THE WHEELHUB. THE HEAT SHIELD APPEARS TO HAVE BEEN DAMAGED	 BY IMPACT SOMETIME PREVIOUSLY.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040200309	20010402	00309	NM  	2001	4	2	AU001207         	1	20001225	G	3244	6558256281	TIRE            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LT NLG	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			211  							(AUS) LT NOSE WHEEL TYRE SHREDDED. THE TIRE WAS STILL INFLATED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200310	20010402	00310	NM  	2001	4	2	AU001208         	1	20001220	G	3510		HOSE            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CREW OXYGEN	LEAKING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) CREW OXYGEN SYSTEM HOSE LEAKING. HOSE IS LOCATED IN AN AREA BELOW THE FIRST OFFICERS OXYGEN MASK BOX.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200311	20010402	00311	EA  	2001	4	2	AU001209         	2	20001026	G	7240	PCE22284	BRACKET         			PIPER 	PA36  	PA36375     	7103620	SO  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE CASE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE GAS GENERATOR OUTER CASE BRACKET BROKE OF THE CASE LEAVING TWO HOLES OF APPROXIMATELY 9.525MM (0.375IN) IN 	THE CASE. THE BRACKET IS WELDED TO THE GAS GENERATOR CASE AND IS USED TOSUPPORT THE FORWARD FIRESEAL BULKHEAD ASSEMBLY.					1	L	7	1 	3O	3	T	 	A10SO   	E4EA	6	C	P15EA	 
2001040200312	20010402	00312	CE  	2001	4	2	AU001210         	1	20001219	G	3221	6042001	TRUNNION        			CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION CRACKED AROUND THE TRUNNION PINS.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040200313	20010402	00313	NE  	2001	4	2	AU001211         	3	20001220	G	6114	7823011	BEARING         	HAMSTD      	7827015     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROP HUB	GALLED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			8000 		860628					(AUS) PROPELLER HUB BLADE RETAINING BEARING OUTER RACE GALLED. FOUND DURING SCHEDULED BLADE CHANGE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200314	20010402	00314	CE  	2001	4	2	AU001212         	1	20001219	G	3221	6042001	TRUNNION        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION CRACKED IN AREA AROUND TRUNNION PINS.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040200315	20010402	00315	NE  	2001	4	2	AU001213         	2	20001226	G	7310	218376002	LINE            	LYC         	ALF502R5    	BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL DIST	FAILED          	W				O	 	 	 	OTHER                   				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) NR 3 ENGINE FUEL LINE LOCATED BETWEEN THE FLOW DIVIDER AND FUELMANIFOLD FRACTURED AND LEAKING FUEL. FUEL IGNITED C	AUSING DAMAGETO THE WIRING HARNESS AND TGT HARNESS.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200316	20010402	00316	NM  	2001	4	2	AU001214         	1	20001218	G	7110	2242301513	COWLING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ENGINE	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			38787							(AUS) RT ENGINE LT CORE COWL MISSING A SECTION APPROXIMATELY 254MM BY 304.8MM (10IN BY 12IN) WHICH INCLUDED THE SUPPORT 	FRAME. THEENGINE MOUNT WAS EXPOSED.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200317	20010402	00317	NM  	2001	4	2	AU001215         	1	20001027	G	2742	AR7077M3	ACTUATOR        			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					STABILIZER	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			18131							(AUS) HORIZONTAL STABILISER TRIM MOTOR FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200318	20010402	00318	NM  	2001	4	2	AU001216         	1	20001105	G	2520	908356G	SEAT            			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					CABIN	SEPARATED       	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			2281 							(AUS) FLIGHT ATTENDANT FORWARD DOUBLE SEAT SEPARATED FROM WALL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200013	20010402	00013	NM  	2001	4	2	AU001217         	1	20001031	G	3810	S417T2006	TANK            		SNO0506     	BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					POTABLE WATER	RUPTURED        	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					0506					(AUS) RT MAIN POTABLE WATER TANK SUPPORTING RODS (3OFF) BROKEN ALLOWING THE TANK TO COLLAPSE ONTO THE TOILET FAN AND RUP	TURE.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200014	20010402	00014	NM  	2001	4	2	AU001218         	1	20001211	G	2761	69B841881	BOLT            			BOEING	747   	747400      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					DRAG CONTROL	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NT 4 SPOILER ACTUATOR ROD END BOLT / NUT / BUSHING MISSING.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2001040200015	20010402	00015		2001	4	2	AU001219         	4	20001211	G	3460	6224717003	CONTROL PANEL   			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FLIGHT COMPUTER	FAULTY          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) MODE CONTROL PANEL FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200016	20010402	00016	NM  	2001	4	2	AU001220         	1	20001017	G	2810	BACB30US12K56	BOLT            			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FUEL STORAGE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR SPAR LOWER LT SPLICE PLATE / CENTER WING TANK BOLT BROKEN. THE BOLT SHANK WAS COMPLETELY SEVERED AND THE BOLT	 HEAD WAS PROTRUDING APPROXIMATELY 19.05MM (0.75IN) INTO THE CENTER WING TANK WITH SURROUNDING SEALANT DAMAGE EVIDENT. F	OUND DURING INSPECTION IAW 747-028-0019.				2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001040200017	20010402	00017	NM  	2001	4	2	AU001221         	1	20001016	G	5414		PANEL           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LT PYLON	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT PYLON PANEL 5727L REPAIR DOUBLER CRACKED. DOUBLER WAS FITTED IAW SB 7737-54-1035.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200018	20010402	00018	NM  	2001	4	2	AU001222         	1	20001016	G	7110	401B1613000059	COWLING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ENGINE	SEPARATED       	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE INBOARD TRANSLATING COWL INNER SKIN SECTION SEPARATED. SIZE OF SEPARATED SECTION APPROXIMATELY 304.8MM B	Y 609.6MM (12INBY 24IN).					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200019	20010402	00019	WP  	2001	4	2	AU001223         	1	20001222	G	5540	3115125	BRACKET         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	RUDDER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			142  							(AUS) RUDDER HINGE BRACKETS CORRODED.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001040200020	20010402	00020	EU  	2001	4	2	AU001225         	1	20001219	G	5246		LATCH           			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL PANEL	OPEN            	W				O	 	 	 	OTHER                   				W	J	 	INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) REFUEL PANEL LATCH LOCATED ADJACENT TO DOOR WARNING MICROSWITCH WAS UNLATCHED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200021	20010402	00021	EU  	2001	4	2	AU001226         	1	20001222	G	2810	N382602	CAP             			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL CELL	MISSING         	W				O	 	 	 	OTHER                   				D	K	J	INFLIGHT SEPARATION       	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) LT OVERWING FUEL CAP MISSING. LOSS OF APPROXIMATELY 230KG OF FUEL.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200022	20010402	00022	NM  	2001	4	2	AU001227         	1	20001212	G	5350	195CL	FAIRING         			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					WING TO BODY	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT WING TO BODY FAIRING PANEL 195CL MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040300011	20010403	00011	NE  	2001	4	3	AU001228         	2	20001226	G	7320	6055T19P14	HYDROMECH UNIT  			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	FUEL CONTROL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			12938							(AUS) LT ENGINE COMPRESSOR STALL (SURGE). OPERATING LIMITS EXCEEDED. SUSPECT CAUSED BY FAULTY HYDROMECHANICAL UNIT (HMU)	.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001040200023	20010402	00023	EU  	2001	4	2	AU001229         	1	20001204	G	2433		TRANSFORMER     			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RECTIFIER	FAULTY          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) SUSPECT NR 1 AND NR 2 TRANSFORMER RECTIFIER UNITS (TRU) HAD INTERMITTENT FAULTS CAUSING CIRCUIT BREAKERS TO TRIP. 	SUSPECT ALSO THAT CONTACTORS XD4 AND XD5 WERE INTERMITTENT IN OPERATION.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200024	20010402	00024	EU  	2001	4	2	AU001230         	1	20001218	G	7931	1241013	TRANSMITTER     			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	OIL PRESSURE	FAULTY          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE OIL PRESSURE TRANSMITTER FAULTY.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001040200025	20010402	00025	EU  	2001	4	2	AU001231         	1	20001224	G	2910	NAS16126	O-RING          			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					HYDRAULIC SYS	SPLIT           	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) NR 1 HYDRAULIC SYSTEM PRESSURE SWITCH O-RING SEAL SPLIT.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001040200026	20010402	00026		2001	4	2	AU001232         	4	20001217	G	3418	EASPC850340	COMPUTER        			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					STALL WARNING	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 			932  							(AUS) STALL PROTECTION COMPUTER FAULTY.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001040200027	20010402	00027	CE  	2001	4	2	AU001233         	1	20001229	G	3222	35820115	BEARING         			BEECH 	33    	E33         	1151422	CE  	CONT  	O470  	IO470K      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	NLG	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR BEARING WORN EXCESSIVELY. THE THICKNESS OF THEBEARING SURFACE WAS 1.143MM (0.045IN). WHEN NEW TH	E THICKNESS IS1.57MM (0.0625IN). TO COMPENSATE FOR WEAR A BRONZE SPACER RING2.74MM (0.108IN) WAS FITTED BETWEEN THE WORN	 BEARING AND THEBARREL RESULTING IN MISALIGNMENT OF THE SHIMMY DAMPER AND BENDING OF THE ACTUATING ROD. PERSONNEL/MAINTE	NANCE ERROR. UNAPPROVED PART.			1	L	7	1 	3O	3	O	 	3A15    	3E1	5	C	P880	 
2001040200028	20010402	00028	CE  	2001	4	2	AU001234         	1	20001229	G	7800	61199	GASKET          			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	SNSNCH	69CK	M69CK       	EA  	EXHAUST SYS	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 CYLINDER EXHAUST GASKET INCORRECTLY FITTED ON ONLY ONE STUD.DURING TIGHTENING OF THE EXHAUST THE FLANGE CRACK	ED AS WELL ASTHE WELD BETWEEN THE FLANGE AND THE PIPE. LT MUFFLER BAFFLE PIPEALSO ERODED.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P9045	 
2001040200029	20010402	00029	SO  	2001	4	2	AU001235         	2	20001229	G	8530	662200	PISTON          			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	SNSNCH	69CK	M69CK       	EA  	CYLINDER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1, NR 2 AND NR 4 CYLINDER PISTONS CRACKED BETWEEN OIL HOLES. THEPISTONS ARE MANUFACTURED BY WELLWORTH CASTING  	NUMBER A470102 AND ARE DIFFERENT TO THE CONTINENTAL MANUFACTURED PISTON IN HAVINGTEN OIL HOLES UNDER THE OIL RING WHERE 	CONTINENTAL PISTONS HAVE EIGHT HOLES BELOW THE OIL RING. LOG BOOK INDICATES THAT NO3 PISTON WAS PREVIOUSLY CRACKED AND H	AD BEEN REPLACE BY A CONTINENTAL PNO 530348.			1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P9045	 
2001040200030	20010402	00030	SO  	2001	4	2	AU001236         	1	20001219	G	2140	A98040136	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATER	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN HEATER FITTED WITHOUT USING PIPER KIT 764-005 SL 894. NO DUCTING OR AIR SHUTOFF VALVE FITTED BETWEEN AIR SCO	OP AND HEATER.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040200031	20010402	00031	NE  	2001	4	2	AU001237         	2	20001227	G	7200		ENGINE          			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1	FAILED          	W				O	 	 	 	OTHER                   				E	M	 	VIBRATION/BUFFET          	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE FAILED. A LOUD BANG WAS HEARD FROM THE ENGINE WITH THE TGT INCREASING TO 1000 DEGREES BEFORE SHUTDOWN.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200032	20010402	00032	NM  	2001	4	2	AU001239         	1	20001230	G	2910	82950010269	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	SPLIT           	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC LINE SPLIT AND LEAKING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200033	20010402	00033	CE  	2001	4	2	AU001240         	1	20001229	G	7120	S7510088	MOUNT           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT ENGINE	BROKEN          	W				O	 	 	 	OTHER                   				O		 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT ENGINE INBOARD MOUNT BROKEN. ENGINE HAD DROPPED APPROXIMATELY38.1MM (1.5IN).						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001040200034	20010402	00034	SW  	2001	4	2	AU001241         	1	20001204	G	7722		CONNECTOR       			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  					EGT/TIT INDICATO	CORRODED        	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE EGT SYSTEM CONNECTOR PLUG CORRODED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
2001040200206	20010402	00206	SW  	2001	4	2	AU001242         	1	20001206	G	7712		SIGNAL COND UNIT			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  					BMEP/TORQ IND	OUT OF ADJ      	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE TORQUE SIGNAL CONDITIONER OUT OF ADJUSTMENT.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
2001040200035	20010402	00035	SW  	2001	4	2	AU001244         	1	20001226	G	2752		GEAR            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A65R     	52043	EA  					TE FLAP ACTUATOR	WORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAP ACTUATOR FAULTY. INVESTIGATION FOUND THE WORM GEAR AND DRIVE GEAR WORN.						1	L	7	1 	3T	4	T	NC	A19SW   	E4EA				 
2001040200036	20010402	00036	EU  	2001	4	2	AU001245         	1	20001228	G	2611	FR2212	SMOKE DETECTOR  			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					CARGO BAY	FAULTY          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CR	CRUISE         	1			AU	S 					377					(AUS) BAGGAGE BAY SMOKE DETECTOR FAULTY. HEATER HOT AIR VALVE STUCK INOPEN'' POSITION.						2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001040200037	20010402	00037	CE  	2001	4	2	AU001246         	1	20001230	G	5511	553200048	SPAR            			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D1      	52060	NE  					HORIZONTAL STAB	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER REAR SPAR AND UPPER SPAR CAP CORRODED.FOUND DURING REMOVAL OF THE UPPER RH SKIN DUE TO DELAM	INATION.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2001040200038	20010402	00038	CE  	2001	4	2	AU001247         	1	20001003	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT WINDSHIELD OUTER PANE CRACKED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001040200039	20010402	00039	CE  	2001	4	2	AU001249         	1	20001219	G	2731		ACTUATOR        			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ELEVATOR TRIM	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			162  							(AUS) ELEVATOR TRIM ACTUATOR HAD EXCESSIVE END PLAY RESULTING INEXCESSIVE ELEVATOR TAB FREE PLAY. ACTUATOR HAD BEEN OVER	HAULED162 HOURS PREVIOUSLY.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040200040	20010402	00040	EA  	2001	4	2	AU001250         	1	20001018	G	2823		DIAPHRAGM       			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	FUEL SELECTOR	SPLIT           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FUEL SELECTOR VALVE DIAPHRAGM / SEAL SPLIT. SELECTOR STIFF TO OPERATE.						1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2001040200041	20010402	00041	SO  	2001	4	2	AU001251         	1	20001213	G	2434	23080013	GENERATOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	NR 2	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			1320 							(AUS) NR 2 (RT) MAIN GENERATOR FAILED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040200042	20010402	00042	NM  	2001	4	2	AU001252         	1	20001230	G	7603	38925085	CONTROL BOX     			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					POWER LEVER	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE FFR THROTTLE CONTROL BOX RACK DAMAGED.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001040200043	20010402	00043		2001	4	2	AU001253         	4	20001225	G	2565	20131	BATTERY         		20121       	BOEING	767   	767332      	1382001	NM  	GE    	CF6   	CF680C2*    	 	GL  					ESCAPE SLIDE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT ESCAPE SLIDE BATTERY PACK AND CHARGER ASSEMBLIES FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200044	20010402	00044	NM  	2001	4	2	AU001254         	1	20001230	G	2497		WIRE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ELECTRICAL POWER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GROUND SERVICE FEEDER WIRING BURNT AND DAMAGED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200045	20010402	00045	NM  	2001	4	2	AU001255         	1	20001229	G	2410	735511A	RELIEF VALVE    			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ALTERNATOR	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 			1558 							(AUS) NR 2 ENGINE CONSTANT SPEED DRIVE (CSD) INTERNAL FAILURE. INVESTIGATION FOUND THAT THE OIL PRESSURE RELIEF VALVE HA	D BLOWNOUT AND THE ATTACHMENT BOLTS HAD SHEARED. OIL LOSS THEN CAUSED CSD FAILURE.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200046	20010402	00046	NM  	2001	4	2	AU001256         	1	20001217	G	5320	EO180401	COVER           			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					FUSELAGE	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BULK CARGO VENT COVER MISSING. AD/B767/65 AND FAA AD FAD 92-02-12 REQUIRE THE COVER TO BE FITTED FOLLOWING REMOVAL	 OF THE BULK CARGO VENTILATION VALVE IAW BOEING SB 767-21A0098.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001040200047	20010402	00047	NM  	2001	4	2	AU001257         	1	20001228	G	5260		STRUCTURE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AIRSTAIR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRSTAIR COMPONENTS BROKEN AND BADLY WORN. MAIN CABIN DOOR COULD NOT BE OPENED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200207	20010402	00207	CE  	2001	4	2	AU001258         	1	20001220	G	2731	0861100164	WHEEL           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ELEVATOR TRIM	BROKEN          	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) ELEVATOR TRIM WHEEL POINTER GROOVE BROKEN.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001040200048	20010402	00048	EU  	2001	4	2	AU001259         	1	20001222	G	7603		CABLE           	LYC         	ALF502R5    	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					POWER LEVER	CONTAMINATED    	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) NR 4 ENGINE THROTTLE CABLE CONTAMINATED WITH DIRT AND STIFF IN OPERATION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200049	20010402	00049	EU  	2001	4	2	AU001260         	1	20000409	G	2752		JACKSCREW       			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TE FLAP ACTUATOR	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) RT OUTBOARD FLAP JACKSCREW SUSPECT FAULTY. INVESTIGATION COULD NOT CONFIRM THE DEFECT ALTHOUGH THE JACKSCREW WAS N	OTCHY IN OPERATION.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001040200050	20010402	00050	GL  	2001	4	2	AU001261         	2	20001201	G	7230	23057142	CASE            			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					COMPRESSOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE LOWER COMPRESSOR CASE HALF HAD DEBONDING OF THEPLASTIC BAND SECTION BETWEEN NR 3 AND NR 4 STAGES. EXCE	SSIVE SPOOL RUB EVIDENT ON THE PLASTIC SECTIONS CAUSING EXCESSIVE CRACKING. CIRCUMFERENTIAL CRACKING WAS FOUND ACROSS TH	E ENTIRE SECTION OF THE THIRD AND FOURTH STAGE BAND PLASTIC SECTION. SUSPECT CAUSED BY CORROSION.				1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001040200051	20010402	00051	NM  	2001	4	2	AU001262         	1	20001211	G	2751		TRANSMITTER     			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					TE FLAP POSITION	OUT OF ADJ      	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) LT TRAILING EDGE FLAP TRANSMITTER OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040200052	20010402	00052	CE  	2001	4	2	AU001263         	1	20001202	G	2133	903800003	REGULATOR       			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  					P3 AIR	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			11965							(AUS) PRESSURE REGULATOR LEAKING P3 AIR INTO CABIN. INTERNAL INSPECTION FOUND ALL SEALS WORN AND THE REGULATOR WORN AND 	LEAKING.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001040200066	20010402	00066	EA  	2001	4	2	AU001264         	2	20001201	G	8530	75838	VALVE GUIDE     			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1     	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 										(AUS) NR 5 CYLINDER EXHAUST VALVE GUIDE BROKEN UP. PIECES OF THE VALVE GUIDE EXITED THE CYLINDER AND JAMMED AND DAMAGED 	THE TURBOCHARGER TURBINE. NR 5 CYLINDER EXHAUST VALVE NECKED AND COLLETTS WORN.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P9EA	 
2001040200067	20010402	00067	NM  	2001	4	2	AU001265         	1	20001231	G	5330		SKIN            			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			47862							(AUS) RT SIDE FUSELAGE SKIN CONTAINED LEVEL 2 CORROSION AT STN 1420 INAREA ABOVE NR 2 ENGINE. SKIN BULGED AND FASTENERS 	SHEARED. FOUND DURING CORROSION PREVENTION AND CONTROL PROGRAM.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2001040200068	20010402	00068	CE  	2001	4	2	AU001266         	1	20001031	G	2750		SWITCH          			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	TE FLAP CONTROL	OUT OF ADJ      	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP SELECTOR SWITCHES OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040200069	20010402	00069	NM  	2001	4	2	AU001267         	1	20001227	G	2520	91012	SEAT            			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	CABIN	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) SEAT SEPARATED FROM SEAT TRACK DURING TURBULENCE. SUSPECT SEATINCORRECTLY LOCKED IN TRACK DURING FITMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200070	20010402	00070	NE  	2001	4	2	AU001268         	2	20001209	G	7250		INLET GUIDE VANE			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1 ENGINE	DAMAGED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE EXPERIENCED CONTINUOUS HIGH TEMPERATURES. INVESTIGATION FOUND THE FOLLOWING DEFECTS: HOLE BURNED IN IN	LET GUIDE VANE. FIRST STAGE NOZZLE BURNED WITH A PIECE MISSING. T5 HARNESS THERMOCOUPLE END BURNED OFF. POWER TURBINE VA	NE RING CRACKED BETWEEN ADJACENT BLADES.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001040200071	20010402	00071	SO  	2001	4	2	AU001269         	2	20001127	G	8520	6419311075	BOLT            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					CRANKCASE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER THOUGH BOLT BETWEEN NR 2 AND NR 3 CYLINDERS BROKEN 35MM (1.5IN) FROM THE LEFT END OF THE BOLT IN THE O'' RIN	G SEAL  GROOVE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001040200072	20010402	00072	SO  	2001	4	2	AU001270         	2	20001025	G	8520	6419311075	BOLT            			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER THROUGH BOLT LOCATED BETWEEN NR 2 AND NR 3 CYLINDERS BROKEN.FAILURE OCCURRED APPROXIMATELY 76.2MM (3IN) FROM	 THE LEFT END OF THE BOLT.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001040200073	20010402	00073	CE  	2001	4	2	AU001271         	1	20000504	G	3213	51411036	STRUT           			CESSNA	402   	402C        	207590R	CE  										RT MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPPER BARREL ASSEMBLY CRACKED ON THE INNER RADIUS OF THE TORQUE LINK COLLAR LUG. FOUND DURING	 FLUORESCENT MAGNETIC PARTICLE INSPECTION (MAGNAFLUX) IAW MEB89-2 R1.					1	L	7	2 	3O			 	A7CE    					 
2001040200074	20010402	00074	CE  	2001	4	2	AU001272         	1	20000504	G	3211	51227202	TRUNNION        			CESSNA	402   	402C        	207590R	CE  										RT MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR FORWARD TRUNNION CRACKED ON THE TOP WEB ADJACENT TO THE GEAR ATTACHMENT BEARING. FOUND DURING	 FLUORESCENT DYE PENETRANT INSPECTION IAW MEB85-11 R4.					1	L	7	2 	3O			 	A7CE    					 
2001040200075	20010402	00075	CE  	2001	4	2	AU001273         	1	20001012	G	3230	51420023	DRAG BRACE      			CESSNA	402   	402C        	207590R	CE  										NLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE CRACKED IN THE RADIUS OF THE ACTUATOR ATTACHMENT POINT. FOUND USING DYE PENETRANT INS	PECTION IAW MEB91-11 AND CESSNA CAP 32-20-00.					1	L	7	2 	3O			 	A7CE    					 
2001040200076	20010402	00076	CE  	2001	4	2	AU001274         	1	20000504	G	3211	51227201	TRUNNION        			CESSNA	402   	402C        	207590R	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR FORWARD TRUNNION CRACKED IN THE TOP WEB ADJACENT TO THE GEAR ATTACHMENT BEARING. FOUND DURING FL	UORESCENT DYE PENETRANT INSPECTION IAW MEB85-11 R4.					1	L	7	2 	3O			 	A7CE    					 
2001040200077	20010402	00077	EU  	2001	4	2	AU001275         	1	20001025	G	5711		SPAR            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPARS CONTAINED PITTING CORROSION IN AREA BETWEEN RIB NR 13 AND RIB NR 18.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200078	20010402	00078	EU  	2001	4	2	AU001276         	1	20001215	G	5711		SPAR            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RT & LT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPARS CONTAINED SUSPECT INTERGRANNULAR CORROSION IN AREAS LOCATED OUTBOARD OF RIB N	R 13.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200080	20010402	00080	SO  	2001	4	2	AU001278         	1	20001116	G	3260	1204112500	PROXIMITY SWITCH			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	NLG	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR SYSTEM B PROXIMITY SWITCH AND HARNESS SUSPECT FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040200208	20010402	00208		2001	4	2	AU001280         	4	20001228	G	2565	C0118	CABLE           	AIRCRUISERS 	60592101    	AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					ESCAPE SLIDE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					C0118					(AUS) ESCAPE SLIDE RESERVOIR ASSEMBLY WIRE CONTROL INTERNAL CABLE DAMAGED (KINKED) AT THE END AND AT THE ROD TO CABLE SW	AGE. DAMAGE ALSO TO THE END FITTING. FOUND DURING TESTING IAW WR 25-60/119.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001040200209	20010402	00209	EU  	2001	4	2	AU001281         	1	20001229	G	3510	MF100511	OXYGEN MASK     			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					CREW OXYGEN	LEAKING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 					58538					(AUS) FIRST OFFICERS OXYGEN MASK LEAKING.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001040200210	20010402	00210	EU  	2001	4	2	AU001282         	1	20001214	G	5610	WP1701011	WINDSHIELD      			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) LT  WINDSHIELD OUTER LAYER CRACKED. ARCING OCCURRED IN THE TOP RH CORNER OF THE SCREEN.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001040200211	20010402	00211	NM  	2001	4	2	AU001283         	1	20000615	G	2897		WIRE            			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) KAPTON WIRES LOCATED IN REFUEL PANEL HAVE DAMAGED INSULATION ALLOWING THE WIRES TO BE EXPOSED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040200212	20010402	00212	NM  	2001	4	2	AU001284         	1	20001125	G	2897		WIRE            			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) KAPTON WIRES LOCATED IN REFUEL PANEL HAVE DAMAGED INSULATION ALLOWING THE WIRES TO BE EXPOSED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040200213	20010402	00213	NM  	2001	4	2	AU001287         	1	20001117	G	2910	BACH8A06NN0336T	HOSE            			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					HYDRAULIC SYSTEM	LEAKING         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACTION ACTUATOR DOWN LINE HYDRAULIC HOSE  RUPTURED. LOSS OF SYSTEM A'' HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040300094	20010403	00094	NM  	2001	4	3	AU001288         	1	20001230	G	5754	114T310024	SLAT            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT WING  SLAT	DEBONDED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING NR 7 LEADING EDGE SLAT TRAILING EDGE WEDGE DISBONDING ON UPPER AND LOWER SURFACES.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200214	20010402	00214	EU  	2001	4	2	AU001289         	1	20000309	G	7830		VALVE           	PWA         	PW4152      	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					THRUST REVERSER	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 THRUST REVERSER PRESSURE REGULATING AND SHUTOFF VALVE (PRSOV) FAULTY.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040300095	20010403	00095	EU  	2001	4	3	AU001290         	1	20000302	G	7830		DRIVE SHAFT     	PWA         	PW4152      	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					THRUST REVERSER	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 THRUST REVERSER PNEUMATIC DRIVE UNIT FAULTY.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040200215	20010402	00215		2001	4	2	AU001292         	4	20000819	G	2300	602TR4183	RADIO           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					COMMUNICATIONS	CONTAMINATED    	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) FIRST OFFICERS RADIO SYSTEM CONTAMINATED WITH WATER. WINDOW HAD BEEN LEFT OPEN THE PREVIOUS NIGHT AND RAIN ENTERED	 THE COCKPIT.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200216	20010402	00216	EU  	2001	4	2	AU001293         	1	20001230	G	3230	BDM30003	LANDING GEAR    			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					MLG	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 					92					(AUS) LANDING GEAR WOULD NOT RETRACT WITH SYSTEM 1 SELECTION. OK USING SYSTEM 2.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040200217	20010402	00217	EU  	2001	4	2	AU001294         	1	20001110	G	2750		CIRCUIT BREAKER 			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					TE FLAPS	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAPS WOULD NOT OPERATE. CIRCUIT BREAKERS CYCLED AND FAULT CLEARED.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040200218	20010402	00218	EU  	2001	4	2	AU001295         	2	20000823	G	7321	612ECU1	FUEL CONTROL    			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 1 ENGINE	FAULTY          	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE THRUST AND N2 FLUCTUATING. TGT WARNING ILLUMINATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200219	20010402	00219		2001	4	2	AU001297         	4	20000415	G	3444	9650476088	COMPUTER        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					GROUND PROXIMITY	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) GROUND PROXIMITY WARNING SYSTEM (GPWS) COMPUTER FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200220	20010402	00220		2001	4	2	AU001299         	4	20000206	G	2210		COMPUTER        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW123D      	52152	NE  					AUTOPILOT SYSTEM	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) AUTOFLIGHT CONTROL SYSTEM (AFCS) COMPUTER FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001040200221	20010402	00221	EU  	2001	4	2	AU001303         	1	20001211	G	3260		SPRING          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG	BROKEN          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR UPLOCK MICROSWITCH SPRING BROKEN.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200222	20010402	00222	EU  	2001	4	2	AU001304         	1	20001210	G	2432	23531	BATTERY         			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					BATTERY BAY	OVERHEATED      	W				A	 	 	 	UNSCHED LANDING         				M	J	 	OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) AIRCRAFT BATTERY OVER TEMPERATURED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200223	20010402	00223	EU  	2001	4	2	AU001305         	1	20001208	G	2432	23531	BATTERY         			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					BATTERY BAY	OVERHEATED      	W				O	 	 	 	OTHER                   				J	M	 	WARNING INDICATION        	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 										(AUS) FORWARD BATTERY OVER TEMPERATURED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200224	20010402	00224	NM  	2001	4	2	AU001306         	1	20001116	G	3260		SENSOR          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW123D      	52152	NE  					MLG DOOR	DAMAGED         	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR DOOR WIRING OPEN CIRCUITED AT FILTER / INDUCTOR L4 (LT FORWARD DOOR SENSOR INPUT TO PSEU).						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001040200225	20010402	00225	EU  	2001	4	2	AU001307         	1	20001029	G	2130		A/C PACK        			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					CABIN PRESSURE	FAULTY          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) PRESSURISATION SYSTEM LEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200226	20010402	00226	EU  	2001	4	2	AU001308         	1	20001023	G	3610		DUCT            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PNEUMATIC SYS	LEAKING         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) DUCTING FROM APU TO CROSS DUCT AND GROUND AIR SUPPLY DUCT LEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200227	20010402	00227	EU  	2001	4	2	AU001309         	1	20001022	G	3230	A78712001	SPRING          			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG DOOR	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR AFT UPLOCK HOOK SPRING BROKEN.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200228	20010402	00228	EU  	2001	4	2	AU001310         	1	20001022	G	2432	23531	BATTERY         			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					BATTERY BAY	OVERHEATED      	W				O	 	 	 	OTHER                   				M	J	 	OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN BATTERIES HAD OVERTEMPERATURE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200229	20010402	00229	EU  	2001	4	2	AU001311         	2	20001017	G	7261	EU18394A	FILTER          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					ENGINE OIL	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE OIL FILTER DRAIN OUTLET LEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200230	20010402	00230	EU  	2001	4	2	AU001312         	1	20001015	G	3150		WARNING SYSTEM  			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					COCKPIT	FALSE ACTIVATION	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NR 1 BAY OVERHEAT LIGHT ILLUMINATED. AIR LEAK CHECK CARRIED OUTWITH NO LEAKS EVIDENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200231	20010402	00231	EU  	2001	4	2	AU001313         	2	20001013	G	7321	CASC211	REGULATOR       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 2 ENGINE FUEL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200232	20010402	00232	EU  	2001	4	2	AU001314         	1	20001006	G	3234		HANDLE          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG	STUCK           	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR SELECTOR HANDLE STUCK IN THE DOWN POSITION.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200233	20010402	00233		2001	4	2	AU001315         	4	20001004	G	3416	23932004	ALTIMETER       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					COCKPIT	OUT OF ADJ      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRST OFFICERS ALTIMETER OUT OF CALIBRATION. FOUND DURING COMPLIANCE WITH AD/RAD/68 AMDT2.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200234	20010402	00234	EU  	2001	4	2	AU001316         	1	20000927	G	2722	1101025	ACTUATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					RUDDER	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					FAS920821					(AUS) RUDDER ACTUATOR ASSEMBLY FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200235	20010402	00235		2001	4	2	AU001317         	4	20000912	G	3442	20412170413	TRANSCEIVER     			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					WEATHER RADAR	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) WEATHER RADAR TRANSCEIVER FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200236	20010402	00236	EU  	2001	4	2	AU001318         	1	20000910	G	2752	58137	ACTUATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					TE FLAP	LEAKING         	W				D	 	 	 	RETURN TO BLOCK         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF SYSTEM 1 HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200237	20010402	00237	EU  	2001	4	2	AU001319         	1	20000910	G	3610		DUCT            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PNEUMATIC SYSTEM	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) TAIL DUCT ASSEMBLY LOCATED AFT OF THE REAR PRESSURE BULKHEADLEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200238	20010402	00238	EU  	2001	4	2	AU001320         	1	20000909	G	2752	58137	ACTUATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					TE FLAP	LEAKING         	W				D	 	 	 	RETURN TO BLOCK         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) FLAP HYDRAULIC MOTOR LEAKING. LOSS OF UTILITY HYDRAULIC SYSTEM FLUID (SYSTEM 1).						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200239	20010402	00239	EU  	2001	4	2	AU001321         	1	20000903	G	3250		CONTROL CABLE   			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NLG STEERING	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) NOSE WHEEL STEERING CABLE BROKEN.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200240	20010402	00240	EU  	2001	4	2	AU001322         	1	20000830	G	2421	914F5696	GENERATOR       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 2 AC SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 GENERATOR DROPPED OFF LINE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200241	20010402	00241	EU  	2001	4	2	AU001323         	1	20001213	G	5740	114001021RH	FITTING         			AVIONS	R2160 	R2160       	0960101	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	RT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER 	WING SKIN PANELS ARE NONSTANDARD ACCESS PANELS.					1	L	7	1 	3O	3	O	RT	A48EU   	E274	5	N	P88614	 
2001040200242	20010402	00242	EU  	2001	4	2	AU001324         	1	20001213	G	5740	114001011LH	FITTING         			AVIONS	R2160 	R2160       	0960101	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	LT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER 	WING SKIN PANELS ARE NON STANDARD ACCESS PANELS.					1	L	7	1 	3O	3	O	RT	A48EU   	E274	5	N	P88614	 
2001040200243	20010402	00243	NM  	2001	4	2	AU001325         	1	20000928	G	2910	AN9388	FITTING         			DHAV  	DHC8  	DHC8*       	       	NM  										HYDRAULIC SYS	CRACKED         	W				O	 	 	 	OTHER                   				K	B	 	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC PIPE FITTING LOCATED IN LH NACELLE AREA CRACKED AND LEAKING. LOSS OF NR 1 SYSTEM HYDRAULIC FLUID.						2	H	7	2 	4T			RT	A13NM   					 
2001040200244	20010402	00244	EA  	2001	4	2	AU001326         	2	20001009	G	7250	PCE41063	VANE            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	DAMAGED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE POWER TURBINE VANE ASSEMBLY BROKEN AND POWER TURBINEDISC DISLODGED.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2001040200245	20010402	00245	NE  	2001	4	2	AU001327         	2	20001015	G	7261		ENGINE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  					NR 1	LACK OF LUBE    	W				A	 	 	 	UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE OIL LEVEL LOW.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001040200246	20010402	00246	NE  	2001	4	2	AU001328         	3	20001020	G	6111	SFA13M1ROAD	BLADE           			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT PROPELLER BLADE HOLED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200247	20010402	00247	NE  	2001	4	2	AU001329         	2	20001209	G	7313		NOZZLE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1 ENGINE	BURNED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE CONTINUOUS HIGH TEMPERATURE. STRIP INSPECTION FOUNDTHE FOLLOWING DEFECTS: HOLE BURNT IN INLET GUIDE VA	NE. FIRST STAGE NOZZLE BURNED AND PIECE MISSING . T5 HARNESS THERMOCOUPLE END BURNED OFF. POWER TURBINE VANE RING CRACKE	DBETWEEN ADJACENT BLADES				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001040200268	20010402	00268	NM  	2001	4	2	AU001331         	1	20001207	G	2510	8120727	SEAT BACK       			BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CAPTAINS SEAT BACK VERTICAL ADJUSTMENT TRACKS PNO 812072-7 ANDPNO 812072-8 CRACKED FROM THE UPPER EDGE OF THE AFT 	TRACK FLANGE. CRACK LENGTH 30MM (1.18IN).					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000021900503	20000219	00503	CE  	2000	2	19	AU991229075      	1	20000204	G	2820	1118	HOSE            	STRATOFLEX  		CESSNA	207   	207A        	2073604	CE  										FUEL SYSTEM	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(AU) WHILE ASSEMBLING HOSE,  FOUND THE END FITTING WOULD NOT INSTALL WITHOUT DAMAGING THE INNER HOSE LINER.  THE HOSE WA	S MEASURED AND FOUND TO BE AT THE BOTTOM RANGE OF THE MIL-H-8974 HOSE DIMENSIONAL LIMITS.					1	H	7	1 	3O				A16CE   					 
2000101800004	20001018	00004	CE  	2000	10	18	B30R200000004    	1	20001002	G	2840	AN9245D	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					WING ROOT	MISSING         	B			B3OR	O				OTHER                   				S			AFFECT SYSTEMS            			IN	INSP/MAINT     	1			SW	03	6637G	3890 				5500670				DURING A PHASE INSPECTION OF THE FUEL LOW LEVEL SWITCH, THE SWITCH WAS FOUND FAULTY.  DURING REPLACEMENT, IT WAS NOTICED	 THERE WAS ONLY ONE NUT HOLDING THE SWITCH IN PLACE.  (NO JAM NUT). THE IPC CHAPTER 28-40-01 FIG 1 ITEM 6 SHOWS TWO NUTS	. TWO OTHER AIRCRAFT, S/N'S 550-663 AND 550-666, WERE ALSO FOUND TO BE IN THE SAME CONDITION.  SUBMITTER STATED THERE IS	 NO WAY TO SAFETY JUST ONE NUT. THE SITUATION COULD POSSIBLY CAUSE A FUEL LEAK.  (X)			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000073100224	20000731	00224	CE  	2000	7	31	B3OR200000002    	1	20000726	G	5330	12112871	SKIN PANEL      			CESSNA	210   	T210L       	2073449	CE  										AFT CABIN	LOOSE           	B			B3OR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	732JF					21061543				AIRCRAFT WAS TEST FLOWN DUE TO HIGH CO LEVEL DISCOVERED IN ANOTHER 210 SERIES FLEET AIRCRAFT. PILOTS FOUND UNACCEPTABLE 	LEVEL OF CO IN CABIN USING TOXIBEE CO DETECTOR. MAINTENANCE FOUND EXHAUST GASES ENTERING TAILCONE THROUGH VENT HOLE FOR 	STC SA71RM AIR CONDITIONING SYSTEM. THIS VENT IS LOCATED ON THE BOTTOM OF THE AIRCRAFT IN THE EXHAUST STREAM. ADDITIONAL	LY, IT WAS FOUND THAT AFT BAGGAGE WALL HAD MISSING FASTENERS AND A POOR REPAIR CAUSING LEAKAGE, AND THERE WERE GAPS AROU	ND WIRE BUNDLES ENTERING THE AFT AVIONICS AREA. THE WALL WAS REPLACED WITH A NEW PART AND ALL GAPS WERE SEALED. TEST FLI	GHT REVEALED NO CO INTRUSION AT ALL INTO CABIN.	1	H	7	1 	3O			 	3A21    					 
2001011103004	20010111	03004	CE  	2001	1	11	B3OR200000003    	1	20000915	G	2841	L15H3	SWITCH          			CESSNA	500   	550         	2076604	CE  										LT WING TANK	INACCURATE      	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6637G					550670				PERFORMED FUNCTIONAL TEST OF FUEL LOW LEVEL WARNING SYSTEM, IT FAILED ON ONE SIDE, ILLUMINATING WARNING CAPSULE AT 100 P	OUNDS INSTEAD OF 200 POUNDS OF FUEL.  REPLACED FUEL LOW LEVEL WARNING FLOAT SWITCH.  SYSTEM FAILED AGAIN, DISCOVERED THA	T NEW PART WAS INTERMITTENT.  THIS SWITCH HAS BEEN A PROBLEM IN FLEET FOR YEARS, IT SEEMS EACH TIME WE DO THE FUNCTIONAL	 TEST ON THE WARNING SYSTEM WE FIND A SWITCH THAT IS BAD. AS A SIDE NOTE, WE FOUND ONLY ONE NUT SECURING EACH SWITCH IN 	THE TANK WHEN THE PARTS CATALOG SPECIFIES TWO NUTS USED TO JAM-LOCK EACH OTHER.  (X)		1	L	7	2 	4F			 	A22CE   					 
2001011103012	20010111	03012	EA  	2001	1	11	B3OR200000005    	2	20001102	G	7300	3019288	TUBE            			BEECH 	200   	A200        	1152921	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL CONTROL	CRACKED         	B			B3OR	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	03	7074G					BC17	PCE85295			PILOTS COMPLETED PRE-TAKEOFF ENGINE RUNS AND RETURNED ENGINES TO IDLE.  WHEN POWER LEVERS WERE ADVANCED FOR TAXI TO ACTI	VE, NR 1 ENGINE DID NOT RESPOND TO INPUT.  AIRCRAFT WAS RETURNED TO RAMP WHERE IT WAS DISCOVERED THAT P3 SENSE LINE TO F	CU WAS CRACKED NEAR B-NUT AT FCU CONNECTION.  THE PRESSURE LEAKAGE PREVENTED FCU FROM SCHEDULING REQUIRED FUEL FOR ENGIN	E SPOOL-UP.   SUBMITTER STATED THIS IS THE SECOND P3 LINE  THEY HAVE HAD CRACK THIS YEAR ON 200 SERIES AIRCRAFT.  (X)			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001011103013	20010111	03013	CE  	2001	1	11	B3OR200000007    	1	20001130	G	5730	652210223	SKIN            			CESSNA	500   	550         	2076604	CE  										WING	DAMAGED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5314J	3270 				5500663				WHILE REPLACING A WING DEICE BOOT, DISCOVERED ONE OF THE HEATED LEADING EDGE RETAINING SCREWS HAD MADE CONTACT WITH THE 	WING SKIN AT WS 60.  THE DAMAGE IS FAR BEYOND NORMAL LIMITS OF 10 PERCENT OF SKIN THICKNESS.  INVESTIGATION REVEALED PRO	PER P/N AND LENGTH OF SCREWS WERE INSTALLED PER CESSNA PARTS CATALOG, AND THIS SCREW DOES INDEED CONTACT LEADING EDGE SK	IN WHEN INSTALLED.  FOUND SIMILAR DAMAGE TO OTHER WING.  CHECKED OTHER AIRCRAFT ON RAMP, FOUND SAME DAMAGE.  SO FAR, 5 O	THER FLEET AIRCRAFT HAVE BEEN DISCOVERED TO HAVE CONTACT DAMAGE.  (X)		1	L	7	2 	4F			 	A22CE   					 
2001040900071	20010409	00071	CE  	2001	4	9	B3OR200000008    	1	20001204	G	5730	652210223	SKIN            			CESSNA	500   	550         	2076604	CE  										WING	DAMAGED         	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5408G	3722 				5500666				INSPECTED THIS AC FOR LING LEADING EDGE SKIN CONTACT DAMAGE FROM HEATED LEADING EDGE RETAINING SCREWS DUE TO CONTACT DAM	AGE BEING FOUND IN SISTER SHIP.  DAMAGE WAS FOUND TO WING LEADING EDGE UNDER HEATED LEADING EDGE ASSY EVEN THOUGH PROPER	 SCREWS WERE USED .  THIS DAMAGE COULD POSSIBLY CAUSE FUEL LEAKAGE INTO THE AREA COVERED BY THE HEATED LEADING EDGE ASSY	, CREATING A POTENTIAL FIRE HAZARD.  THERE IS NO ALLOWABLE FUEL LEAKAGE IN THIS AREA.  			1	L	7	2 	4F			 	A22CE   					 
2001011103014	20010111	03014	EU  	2001	1	11	B3OR200000009    	1	20001229	G	6700	CN6MEGR	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										ROD END	BINDING         	B			B3OR	C				ABORTED TAKEOFF         				O			OTHER                     			HO	HOVERING       	1			SW	03	4059W	1240 				2933				PILOT LIFTED AIRCRAFT INTO A HOVER AND FELT SOME BINDING IN THE FORE AND AFT DIRECTION OF HIS CYCLIC CONTROL. AFTER SHUT	DOWN, MAINTENANCE PERSONNEL INSPECTED CONTROL SYSTEM. BINDING WAS DUPLICATED AFTER DISCONNECTING SERVO INPUTS. INVESTIGA	TION REVEALED A FROZEN BEARING IN THE LOWER ROD END OF THE PITCH SERVO ACTUATOR INPUT ROD. REPLACEMENT OF THIS BEARING E	NDED THE BINDING AS VERIFIED BY TEST RUN.			1	G	7	1 	3U			 	H9EU    					 
2001011104226	20010111	04226	CE  	2001	1	11	B3OR20010001     	1	20001206	G	7800	121136012	BOOT ASSEMBLY   	CESSNA      		CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  					UNDER FLOOR	SMALL CUTS      	B			B3OR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	9403Y					21064498				This aircraft has an electronic carbon monoxide detector. In cruise flight, the detector registered a reading of 98 ppm 	CO. OSHA limits exposure to 50 ppm in normal circustances, avation sources suggest a much more conservative 10 to 20 ppm	 due to the elevated enviroment. The CO level dropped rapidly when air vents were opened. Investigation found that the a	ccordian style seal boots on the main landing gear downlock actuators (under cabin floor) had several cuts in them. Main	tenance sealed these with holes with RTV sealant and test flight revealed a maximan reading of 7 ppm in the cabin and 17	 ppm in the baggage area. 	1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2000121500181	20001215	00181	CE  	2000	12	15	B8RR010301       	1	20001205	G	5730	MS24694C51	SCREW           			CESSNA	500   	550         	2076604	CE  										BOTH WINGS	OVERSIZED       	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1254X					5500494				LEFT WING AND RIGHT WING LEADING EDGE SKIN HAS BEEN CHAFED BY THE UPPER SCREW OF THE OUTBOARD ROW OF SCREWS ATTACHING TH	E HEATED LEADING EDGE TO THE WING.  THE SCREWS INSTALLED WERE TOO LONG, ALTHOUGH THEY WERE THE ONES CALLED FOR IN THE PA	RTS CATALOG.  THEY CHAFED INTO THE WING LEADING EDGE SKIN ABOUT 0.020 INCH DEEP INTO THE LEFT WING AND 0.01 INCH INTO TH	E RIGHT WING.  THE SKIN IS 0.040 INCH ALUMINUM.  CESSNA HAS APPROVED A SHORTER SCREW TO BE INSTALLED AND IS CURRENTLY WO	RKING ON A PERMANENT REPAIR.  (X)		1	L	7	2 	4F			 	A22CE   					 
2000061300292	20000613	00292	EA  	2000	6	13	BJ3RE000001      	2	20000427	G	8550	AN470	RIVET           			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					BAFFLE	BROKEN          	G			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	117NJ	118  				4636168	LW13383			DURING AN OIL CHANGE, TWO RIVET HEADS (AN470) WERE FOUND IN THE OIL SUCTION SCREEN.  THE ENGINE WAS REMOVED AND THE OIL 	SUMP PULLED OFF.  TWO RIVET HEADS WERE MISSING FROM THE OIL SUMP BAFFLE.  THESE ARE MS20470AD4-4 RIVETS.  THE HOLES ON T	HE DRIVEN SIDE APPEARED TO BE COUNTERSUNK OR EXCESSIVELY DEBURRED, WHICH GAVE LITTLE BEARING SURFACE FOR THE RIVET HEAD.	  LYCOMING SB489B REFERS TO THESE RIVETS AND THEIR REPLACEMENT.  			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000061300293	20000613	00293	EA  	2000	6	13	BJ3RE000002      	2	20000427	G	8550	61298	GEAR            			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					TEETH	WORN            	G			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	117NJ	118  				4636138	RL1041561A			UPON REMOVAL OF THE OIL PUMP, TO CHECK FOR POSSIBLE DAMAGE DUE TO TWO RIVET HEADS FOUND IN THE OIL SUCTION SCREEN, IT WA	S NOTED THAT THE ALUMINUM OIL PUMP GEAR HAD EXCESSIVE WEAR ON THE DRIVEN SIDE OF EACH TOOTH, AND CHIPS MISSING ON THE OU	TER EDGE OF SEVERAL TEETH.  IT ALMOST APPEARS THAT THE HARDNESS OF THE ALUMINUM GEAR WAS NOT CORRECT.  THE STEEL DRIVING	 GEAR 61297 WAS ALSO DAMAGED, POSSIBLY DUE TO THE ALUMINUM GEAR.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000091800001	20000918	00001	EA  	2000	9	18	BJ3RE000003      	2	20000502	G	8550	LW13383	BAFFLE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					RIVET HOLES	DEFECTIVE       	G			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	117N					4636168	RL1041561A			ON RECEIPT OF A NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES, LIKE THE ONE REMOVED DUE TO FAILED RIVETS.  T	HIS IS ONE OF THE NEW DESIGN WITH 5 RIVETS PER SIDE, INSTEAD OF THE EARLIER 3 RIVET UNIT.  RIVET HOLES 1, 3, AND 5 ON EA	CH SIDE HAVE EITHER BEEN HEAVILY DEBURRED OR COUNTERSUNK, WHICH LEAVES INSUFFICIENT BEARING SURFACE FOR THE RIVET HEADS.	  SB 489B SAYS THAT MS20470AD4-4 RIVETS ARE TO BE USED.  (X)			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000091800002	20000918	00002	EA  	2000	9	18	BJ3RE000004      	2	20000508	G	8550	LW13383	BAFFLE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					RIVET HOLES	ELONGATED       	G			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	117NJ					4636168	RL1041561A			ON RECEIPT OF A SECOND NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES LIKE THE ORIGINAL UNIT AND ITS REPLACEM	ENT.  SUBMITTER STATED THIS IS THE SECOND NEW DESIGN (5 RIVETS PER SIDE) BAFFLE RECEIVED.  THE HOLES ARE ELONGATED, OVER	SIZED OR FIGURE 8 SHAPED AND ARE NO LONGER SUITABLE FOR THE MS20470AD4-4 RIVETS THAT ARE SUPPOSED TO BE INSTALLED.  ONE 	OF THE WASHERS ON THE BUCKED SIDE OF THE RIVET WAS MISSING ON ARRIVAL.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000091800003	20000918	00003	EA  	2000	9	18	BJ3RE000005      	2	20000517	G	8550	LW13383	BAFFLE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					RIVET HOLES	ELONGATED       	G			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	117NJ					4636168	RL1041561A			ON RECEIPT OF A THIRD NEW BAFFLE, IT WAS DERIVETED TO CHECK FOR DEFECTIVE HOLES LIKE THE PREVIOUS UNITS.  THIS IS ALSO O	F THE NEW (5 RIVETS PER SIDE) DESIGN.  SUBMITTER STATED THE HOLES ARE ELONGATED, OVERSIZED, AND NO LONGER SUITABLE FOR T	HE MS20470AD4-4 RIVETS CALLED FOR.  (X)				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2000110600192	20001106	00192	SO  	2000	11	6	BJ3RE000006      	1	20000720	G	7920	LW13383	BAFFLE          			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					RIVETED JOINT	BROKEN          	B			BJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	600CR	1288 				4622060	L902361A			RIVET HEAD FOUND IN OIL SUCTION SCREEN ON OIL CHANGE.  HEAD IS OF THE TYPE USED TO INSTALL THE VERTICAL BAFFLE ON THE OI	L SUMP BAFFLE.  REFERENCE LYC. SB489A.  SUBMITTER STATED AFTER RECEIVING 4 NEW DEFECTIVE OIL SUMP BAFFLES FROM LYCOMING 	OF THIS PART NUMBER, THERE IS CONCERN ABOUT THE MANUFACTURING PROCESS.  SEE SDR QC10263/BJ3RE000003,000004, AND 000005.				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001011103018	20010111	03018	NE  	2001	1	11	BTEAS76B001      	1	20000908	G	2910	SS482C2C165000	LINE            			SKRSKY	S76   	S76B        	8143007	NE  	PWA   	PT6   	PT6B36      	52043	EA  					HYD SYSTEM	BURST           	E			BTEA	E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	09	176BA	6682 				760317				NR 2 HYDRAULIC PRESSURE LINE FROM HYDRAULIC PUMP TO BULKHEAD FITTING FAILED ON AIRCRAFT START-UP.  LINE BURST FROM INSID	E WITHOUT WARNING,  (NO LEAKS NOTED ON PREFLIGHTS).  LINE WAS REPLACED, SYSTEM SERVICED AND AIRCRAFT RETURNED TO SERVICE	.  (X)				1	G	7	2 	4U	4	U	 	H1NE    	E4EA				 
2001032800114	20010328	00114	EA  	2001	3	28	CA000110066      	1	20000104	G	3244		TIRE            			CNDAIR	CL600 	CL6002B19   	       	EA  										LT MLG	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			CA											(CAN) VIBRATIONS FELT DURING TAKE-OFF, TAKE OFF ABORTED. BOTH TIRES ON LT MLG FOUND BLOWN WITH LIGHT DAMAGE TO MLG DOOR.						2	L	7	2 	4F			RT	A21EA   					 
2001032800115	20010328	00115	EA  	2001	3	28	CA000110067      	1	20000105	G	5740		WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING, WHILE TAXING, THE A/C WAS CAUGHT IN SEVERE WIND GUST. LT WING WAS LIFTED OFF THE GROUND, RT WING TI	P CONTACTED THE RUNWAY, LT COCKPIT SIDE WINDOW SHATTERED. AWAITING CREW REPORT. UPDATEAS INFO COMES AVAILABLE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000020500955	20000205	00955	CE  	2000	2	5	CA000118024      	1	20000110	G	3246	300257	WHEEL           	BFGOODRICH  	50300010133 	BEECH 	90    	E90         	1152914	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			2147 			A4262		PCE51688	FY1618		(CAN) INNER WHEEL (BRAKE HALF) CRACKED DURING TAXI AND JAMMED THE BRAKE.  FURTHER INVESTIGATION REVEALED CRACKS IN THE O	THER MAIN WHEEL HALVES.					1	L	7	2 	3T	4	T		3A20    	E4EA	5	C	STC	 
2000020500956	20000205	00956	CE  	2000	2	5	CA000118025      	1	20000110	G	3250	35660311	FITTING         			BEECH 	P35   	P35         	1151530	CE  	CONT  	O470  	IO470N      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	MLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CS955642N	663213		(CAN) DURING 100 HR INSPECTION, THE RT TORQUE FITTING WAS FOUND CRACKED AT THE ROD ATTACH POINT.  POSSIBLE CAUSE IS THAT	 THE NOSE GEAR WAS OVER-STEERED AND THE STEERING STOPS WERE NOT ADJUSTED PROPERLY AND THAT MAY HAVE PUT EXCESSIVE FORCE 	ON THE FITTING CAUSING IT TO CRACK.  DAMAGED PARTS REPLACED.  SUBMITTER STATES THAT ENGINEERS SHOULD BE AWARE THAT IF AI	RCRAFT HAS BEEN OVER-STEERED, TO CHECK AT THE UPPER YOKE AND STEERING MECHANISM BOLTS FOR DAMAGE DUE TO EXCESSIVE STRESS	.		1	L	7	1 	3O	3	O	RT	3A15    	3E1	5	C	P880	 
2001032800267	20010328	00267	EA  	2001	3	28	CA000120032      	1	20000107	G	7931		PUMP            			CNDAIR	CL604 	CL604       	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				L	 	 	NO TEST                   			CR	CRUISE         	1			CA			5    								(CAN) PRODUCTION AIRCRAFT EXPERIENCED LT ENGINE OIL PRESSURE WARNING WAS POSTED DURING FLIGHT TEST.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032800288	20010328	00288	NE  	2001	3	28	CA000128026      	2	20000128	G	7250	310976601	SHAFT           								PWA   	PT6   	PT6A42      	52043	NE  					TURBINE	FRACTURED       	W				K		 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3836 	884  							(CAN) POWER TURBINE SHAFT BROKEN. RESEARCH OF DETAILS ONGOING.											4	T			E4EA				 
2001032800301	20010328	00301		2001	3	28	CA000128046      	4	20000103	G	2562		G SWITCH        	ARTEX       	4530150A    															ELT UNIT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						25271					(CAN) INTERNAL G SWITCH FAILED TO ENABLE INTERMITANTLY RECERTIFICATION TESTING.																			 
2001032800308	20010328	00308	SO  	2001	3	28	CA000128053      	2	20000105	G	8500		ENGINE          		O300A       	CESSNA	170   	170B        	2072306	CE  	CONT  	O300  	O300A       	17022	SO  					NACELLE	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				479  							(CAN) ENGINE LOST ITS OIL AND SEIZED. OPERATOR SPECIFIED FROZEN BREATHER AS THE CAUSE.						1	H	7	1 	3O	3	O	 	A799    	E253				 
2001032800311	20010328	00311	CE  	2001	3	28	CA000128056      	1	20000108	G	3230	608100823	PIN             			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					LT MLG	MISSING         	W				A	 	 	 	UNSCHED LANDING         				D		 	INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			9350 								(CAN) DURING INITIAL RETRACTION WHEN THE GEAR WAS SELECTED UP THE LEFT GEAR STAYED DOWN. WHEN THE GEAR WAS SELECTED DOWN	 EVERYTHING WAS NORMAL ON THE INDICATOR.INSPECTION REVEALED THAT THE SHEAR PIN ON THE LEFT GEAR WAS MISSING.THE GEARS WE	RE LUBRICATED & THE BOTH LT & RT SHEAR PINS REPLACED.				1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2001032900011	20010329	00011	EA  	2001	3	29	CA000201014      	1	20000101	G	2910	82960010209	TUBE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					HYD SYSTEM	RUPTURED        	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			2221 								(CAN) ON TAKE OFF, THE AIRCRAFT EXPERIENCED A LOSS OF  NR 2 HYD SYSTEM. THE AIRCRAFT RETURNED FOR LANDING AFTER A GETTIN	G NR  2 HYD PESS AND RUDDER ISOLATE CAUTION LIGHTS. MAINTENANCE FOUND A RUPTURED HYDRAULIC LINE TO THE RUDDER LIMITER					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600275	20010326	00275	SW  	2001	3	26	CA000209005      	1	20000127	G	3213	540053	LINK            			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					NLG	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4213 								(CAN) WHILE RPLACING THE RUBBER SHOCKS ON THE NOSE GEAR SHOCK ASSEMBLY, IT WAS NOTICED THAT THERE WAS CORROSION ON THE P	OST WHERE THE RUBBER DISCS ARE PLACED.IN ORDER TO DETECT CORROSIONIN THIS AREA,THIS ASSEMBLY HAS TO BE REMOVED AND DISSA	SEMBLED.				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001032600279	20010326	00279	SO  	2001	3	26	CA000209009      	1	20000128	G	5340	JW2901R	FITTING         			LKHEED	1329  	1329        	5263102	SO  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8964 								(CAN) PART CRACKED BEYOND LIMITS.						2	L	7	4 	4J			 	2A15    					 
2001032600289	20010326	00289	EA  	2001	3	26	CA000209026      	1	20000201	G	3411	ST5122DH	PITOT TUBE      			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 2 STATIC SYS	BLOCKED         	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DUE TO CLIMATIC CONDITIONS IN FRENCH GUIANA AT THIS TIME OF YEAR, IN EFFORT TO PROTECT THE STATIC SYSTEM FROM WATE	R CONTAMINATION, THE PORTS WERE COVERED WITH TAPE WHEN THE AIRCRAFT WAS PARKED. ONE PORT WAS BLOCKED WITH A SMALL PIECE 	OF TAPE AND THE OTHER WAS BLOCKED BY THE GLUE FROM THE TAPE. THE COMPANY PROCEDURE HAS CHANGED TO ALIMINUM TAPE WITH REM	OVE BEFORE FLIGHT FLAG.			2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001022200124	20010222	00124	GL  	2001	2	22	CA000215012      	2	20000207	G	7240	6878426	NOZZLE          	ALLSN       	6898734     						ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1401 				CAT31116P			(CAN) THE 2ND STAGE NGV,FIRST STAGE BLADE PATH WAS FOUND CRACKED 50% AROUND THE CIRCUMFERENCE. THE BLADE PATH HAD BEEN R	EPLACED AND WAS JOINED AT THE SECOND NOZZLE BY A BRAZED BUT JOINT. THIS IS /WAS A DAR APPROVED REPAIR. SUSPECT NGV ARE R	EQUESTED TO BE REMOVED FROM OPERATIONS AS REQUESTED BYALERT NOTICE FROM ORENDA AEROTECH ALERT SERVICE NOTICE DATED 02/23	/00.CORRECTIVE ACTIO N ADRESSING FAA AND CANADIAN OPERATORS UNDER REVIEW.								3	U			E4CE				 
2000081000041	20000810	00041	GL  	2000	8	10	CA000215018      	3	20000105	G	6110	7998TOR7080	PROPELLER       													HARTZL	HCF3Y	HCF3YR2     	GL  	DECAL,TORQUE	MISMARKED       	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			1190 						DA1032		(CAN) WRONG PROPELLER INSTALLATION DECAL ATTACHED WHICH INDICATED AN IMPROPER TORQUE VALUE.																5	C	P31EA	 
2000071800165	20000718	00165	SW  	2000	7	18	CA000218005      	1	20000214	G	7810	222063307141	TAILPIPE        	BELL        	222063307   	BELL  	222   	222U        	1182140	SW  										X-TUBES & BRKTS	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAILPIPE FORWARDED FOR FUSION WELD REPAIR TO 4 X-TUBE SUPPORT BRACKETS. EXCESSIVE PLAY WAS NOTED.  DETAILED INSPEC	TION REVEALED WEAR THROUGH DAMAGE OF BOTH X-TUBES VISIBLE FROM ONLY INSIDE OF THE TAILPIPE WHERE WEAR WAS THEN NOTED IN 	3 AREAS.  BELL ENGINEERING WAS INFORMED AND THEY WILL CLOSELY MONITOR SUBSEQUENT FIELD REPORTS.				1	G	7	2 	3U			 	H9SW    					 
2001011104277	20010111	04277		2001	1	11	CA000222018      	4	20000204	G	2564	SA2733	REGULATOR       			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					ESCAPE SLIDE	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) SLIDE/RAFT DAH A 10 SECOND HUNG TIME ON TEST. CMM INDICATES 6 SEC MAX TIME. REGULATOR REPAIRED IN ACC WITH CMM.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011104278	20010111	04278		2001	1	11	CA000222019      	4	20000211	G	2565	SA2733	REGULATOR       			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					ESCAPE SLIDE	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) SLIDE/RAFT HAD A 10 SECOND HUNG TIME ON TEST. CMM INDICATES 6 SEC MAX TIME DELAY. REGULATER REPAIRED AS PER CMM.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011104364	20010111	04364	SO  	2001	1	11	CA000301046      	1	20000221	G	2140	10D22	IGNITER         			PIPER 	PA31  	PA31        	7103102	SO  										LEAD END	DEFECTIVE       	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) IGNITORS WERE FOUND TO BE MISSING THE CERAMIC COATING WHICH IS REQUIRED TO PREVENT THE INGNITION LEAD SPRING FROM 	ARCING INSIDE THE LEAD BARREL. (FLASH OVER). AVIALL, AIRCRAFT HEATERS, API AND ELECTRO SYSTEMS ARE AWARE OF THE QA PROBL	EM.				1	L	7	2 	3O			 	A20SO   					 
2000083000117	20000830	00117	EU  	2000	8	30	CA000310003      	1	20000222	G	6120	1530650012	SPRING          		L24278000000	ZLIN  	242   	Z242L       	9970204	EU  						MUHBR	MTV	MTV3BC      	EU  	UPPER PRT SPRING	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			31900						98471		(CAN) DURING INSPECTION IT WAS NOTICED THAT THE PROPELLER CONTROL FLAT SPRING WAS BROKEN.  THIS SPRING IS USED TO KEEP T	HE PROP CONTROL TELEFLEX SHEATH RIGID DURING PROP GOVERNOR CONTROL MOVEMENT.  THE SUBMITTER SUGGESTS THAT DURING INSTALL	ATION THEY SHOULD BE INSTALLED WITH NO STRESS ON THE SPRINGS WHICH COULD BE DETECTED BY SPRING BENDING BETWEEN THE BRACK	ET AND THE SUPPORT.  (X)			1	L	7	1 	3O			0	A76EU   		5	C	USSR	 
2000082800036	20000828	00036	CE  	2000	8	28	CA000329012      	1	20000320	G	3260	1003810061	SWITCH          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NOSE	FAULTY          	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA								PCE51107			(CAN) PILOT REPORTED LANDING GEAR UNSAFE LIGHT ON HANDLE WOULD NOT EXTINGUISH.  LANDING GEAR POSITION SWITCH ON MOTOR AD	JUSTED.  PROBLEM RECURRED WITH INDICATION LIGHT NOW BEING INTERMITTANT.  DISCOVERED MICROSWITCH INTERNALLY FAULTY.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000082800037	20000828	00037	CE  	2000	8	28	CA000329014      	1	20000321	G	2131	13034611	CONTROLLER      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	INTERNAL	FAULTY          	W				I	 	 	 	CABIN DEPRESSURIZATION  				O	 	 	OTHER                     			CR	CRUISE         	1			CA				88800				PCE81062	300783		(CAN) ON PREPARATION FOR DESCENT, CABIN PRESSURIZATION CONTROLLER RATE WAS ADJUSTED.  AFTER ADJUSTMENT WAS MADE CABIN PR	ESSURE INCREASED TO MAXIMUM DIFERENTIAL AND WAS UNCONTROLLABLE AND NONRESPONSIVE TO ANY FURTHER ADJUSTMENTS TO THE CONTR	OLLER.  CONTROLLER REPAIRED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2000083000120	20000830	00120	CE  	2000	8	30	CA000329016      	1	20000314	G	5740	817861018	BOLT            			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					LT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			89900					P27035			(CAN) CF 81-25R5 WAS BEING CARRIED OUT EARLY, 417.2 HRS.   FOUND LEFT WING TOP REAR BOLT (P/N 81786-10-18) WAS INSPECTED	 AND FOUND CRACKED AND REJECTED.  NEW BOLT INSTALLED.					1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2000083000125	20000830	00125	SO  	2000	8	30	CA000329035      	1	20000323	G	3250	401265	BOLT            	PIPER       	4438800     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					STRUT TOP	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			65200					L586361A			(CAN) AT 1,000 HR INSP, 2 BOLTS (P/N 401-265) AND BOLT (P/N 401-268) WERE REMOVED FROM NOSE GEAR STRUT ASSY FOR INSP.  O	NE 401-265 STARTING TO SHEAR AND OTHER SHOWING STRAIN.  LONGERONS 401-268 SHOWED LIGHT BENDING.  THESE BOLTS WERE REPLAC	ED 651.5 HRS AGO ON APR 20, 1999, AND THEY ARE SHOWING WEAKNESS.  SUBMITTER STATED CHIEFTAIN IS HEAVIER TO STEER THAN NA	VAJOS USING SAME SYS.  LUBRICATING SYS MORE OFTEN HELPS.  SUBMITTER SUGGESTED PIPER PUT 500 HR LIFE LIMIT ON THESE BOLTS	.  SUBMITTER CITED AN INCIDENT WITH AN OPERATOR WHERE COMPLETE STEERING ARM ASSY HAD LEFT A/C AND SUSPECTED CAUSE TO BE 	OVERSTRESSING THESE THREE BOLTS.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083000075	20000830	00075	CE  	2000	8	30	CA000329041      	1	20000317	G	3250	50420101	HORN            	CESSNA      		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	CENTER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			59300					232095R	779115		(CAN) THE STEERING HORN WAS FOUND CRACKED JUST OUTBOARD OF THE CENTER PIVOT ATTACHMENT.  THE CRACKS WERE CONFIRMED USING	 FPI.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000083000126	20000830	00126	SO  	2000	8	30	CA000329042      	1	20000328	G	2434	ALU8421LS	ALTERNATOR      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					INTERNAL	SHORTED         	W				A	 	 	 	UNSCHED LANDING         				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				55600				RL77261			(CAN) SHORTLY AFTER TAKEOFF, THE AMMETERS WERE SHOWING A DISCHARGE AND VOLTAGE REGULATOR POPPED.   ALTERNATOR FOUND TO B	E SHORTED INTERNALLY.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083000127	20000830	00127	CE  	2000	8	30	CA000330003      	1	20000131	G	3233	115380025	MOTOR           	RAYTHN      	115811020613	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					INTERNAL	WEAK            	W				O	 	 	 	OTHER                   				H	R	J	ELECT. POWER LOSS-50 PC   	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			CA				30300				PCE80590			(CAN) DURING CLIMB WHEN THE GEAR WAS SELECTED UP, THE GEAR RETRACTED ONLY HALF WAY AND THE GEAR HANDLE RED LIGHT REMAINE	D ILLUMINATED.  THE GEAR WAS LEFT IN ITS PARTIALLY RETRACTED POSITION.  WHEN ON APPROACH AND THE GEAR SELECTED TO EXTEND	, THE GEAR WOULD NOT MOVE.  THE GEAR WAS MANUALLY EXTENDED.  MAINTENANCE FOUND THE 60 AMP CIRCUIT BREAKER UNDER THE FLOO	RBOARD TO HAVE TRIPPED.  UPON RECYCLING THE GEAR IT WAS DETERMINED THAT THE MOTOR WAS WEAK AND DRAWING TOO MUCH CURRENT 	(APPROX. 53 AMPS).  BENCH TESTING FOUND EXCESSIVE SPARKING.  THE MOTOR WAS REPLACED.  THE STRIP DOWN REPORT REVEALED THA	T THE 4 BRUSH SPRINGS WERE WORN AND THE FILTER ASSY SHORTED.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000082100136	20000821	00136	CE  	2000	8	21	CA000330004      	1	20000323	G	5414	631220292	SKIN            	CESSNA      		CESSNA	525   	525         	2076601	CE  										MID SKIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1665 								(CAN) DURING SCHEDULED MAINTENANCE, A CRACK WAS FOUND ON THE LOWER PYLON SKIN. THE CRACKS WERE FOUND ON TWO RIVET ROWS P	ARALLEL TO THE C/L OF THE AIRCRAFT. THE CRACKS WERE APPROXIMATELY SIX INCHES LONG.					1	L	7	2 	4F			RT	A1WI    					 
2000082100137	20000821	00137	CE  	2000	8	21	CA000330005      	1	20000323	G	7830	6354050204	CHANNEL         	CESSNA      		CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					INBD PIVOT ATTAC	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1016 					1131			(CAN) DURING SCHEDULED MAINTENANCE, CRACKS WERE FOUND ON THE THRUST ATTENUATOR PIVOT SUPORT CHANNELS (UPPER AND LOWER, R	IGHT SIDE).  THESE CHANNELS HAD BEEN INSTALLED AS PART OF SERVICE BULLETIN 525-78-03.					1	L	7	2 	4F	4	F	RT	A1WI    	E3GL				 
2000083000134	20000830	00134	SO  	2000	8	30	CA000330006      	1	20000323	G	3710	2H2211	SOLENOID        	AIRBORNE    	2H2211      	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					VALVE	STUCK           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			45200					L81561C			(CAN) PILOT REPORTED SLUGGISH GYRO OPERATION, FOUND LOW GYRO PRESSURE (3 PSI) ON BOTH ENGINES SELECTED OR SINGLE ENGINE 	OPERATION.  UNABLE TO INCREASE PRESSURE.   REMOVED VALVES (P/N 2H22-11) AND BENCH TESTED RESPECTIVE SOLENOIDS.  SOLENOID	S FOUND TO BE PARTIALLY CLOSED AND NOT ENERGIZING ON POWER AS WELL AS LOSING PRESSURE ON LOW PRESSURE SIDE.  BOTH VALVES	 REPLACED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000073100018	20000731	00018	EA  	2000	7	31	CA000331010      	2	20000325	G	7310	3011857	LINE            	PWA         		EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					FCU	CRACKED         	W				K	 	 	 	NONE                    				B	K	 	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		LD	LANDING        	1			CA				6675 				PCE56782			(CAN) FUEL LINE CRACK AT B-NUT FOUND TO BE THE CAUSE OF FUEL ODOR, AT FCU. FEEDBACK.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2000082100138	20000821	00138	CE  	2000	8	21	CA000331013      	1	20000327	G	3240	651710018	RESERVOIR       	CESSNA      	651710018   	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AFT WELD LINE	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA								71721			(CAN) DURING INSPECTION, THE BRAKE FLUID RESERVOIR WAS FOUND LEAKING AT A CRACK ON THE AFT RIGHT CORNER WELD BEAD.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000073100019	20000731	00019	NE  	2000	7	31	CA000404001      	2	20000321	G	7314		SHAFT           	PWA         		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN1     	52008	NE  					FUEL PUMP	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				320  				4221504			(CAN) ENGINE WOULD NOT RUN WITHOUT WOBBLE PUMP OPERATING.  ENGINE DRIVEN PUMP REMOVED AND QUILL SHAFT FOUND BROKEN.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000071800168	20000718	00168	EA  	2000	7	18	CA000404002      	2	20000324	G	7314	301600	PUMP            	PWA         		BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TURB PWR SECTION	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA			11441	2916 				CPPS60876			(CAN) FUEL PUMP SHAFT WAS ROUGH TO TURN.  SENT FOR EVALUATION.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000083000135	20000830	00135	CE  	2000	8	30	CA000404005      	1	20000229	G	2612	473275	FIRE DETECTOR   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  					WIRING	SHORTED         	W				K	 	 	 	NONE                    				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE CREW REPORTED THAT DURING FLIGHT THE LEFT ENGINE FIRE WARNING CAME ON INTERMITTENTLY.  THE LIGHT INDICATION OC	CURS ONLY AFTER PRECIPITATION OR AIRCRAFT WASHING.  FOUND FIRE DETECTOR TRIGGER VOLTAGE LEAKING THROUGH WIRE INSULATION 	WHEN IT IS WET.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000083000136	20000830	00136	CE  	2000	8	30	CA000404006      	1	20000315	G	3233	993880051	RESTRICTOR VALVE			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					RESTRICTOR VALVE	SHEARED         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			CR	CRUISE         	1			CA								PCE80342			(CAN) RESTRICTOR VALVE SHEARED OFF FROM THE LEFT MAIN LANDING GEAR RETRACT/EXTEND ACTUATOR (UP LINE) CAUSING HYDRAULIC F	LUID TO BE LOST DURING FLIGHT.  RESTRICTOR VALVE REPLACED.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000071800179	20000718	00179	NE  	2000	7	18	CA000404015      	2	20000404	G	7530	0177556170	TACHOMETER      			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					INTERNAL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA				255  		2194B		840			(CAN) TACHOMETER BOX FAILED TO SEND SIGNAL TO BLEED VALVE, CAUSING VALVE NOT TO CLOSE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000082100139	20000821	00139	CE  	2000	8	21	CA000404021      	1	20000328	G	3340	S21604	SWITCH          			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					TERMINAL	LOOSE           	W				D	 	 	 	RETURN TO BLOCK         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								L1701539A			(CAN) DURING THE RUN-UP, THE PILOT NOTICED SMOKE COMING FROM BEHIND THE INSTRUMENT PANEL. THE AIRCRAFT WAS TAXIED BACK T	O THE RAMP AND SHUT DOWN.  MAINTENANCE FOUND A LOOSE/OVERHEATED CONNECTOR ON THE BACK OF THE LANDING LIGHT SWITCH.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001030800128	20010308	00128	GL  	2001	3	8	CA000404022      	3	20000317	G	6111	S90AT4	BLADE           	MCAULY      	D2A34C58    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	THREADED AREA	CRACKED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA				477  		734108		816532R	734108		(CAN) BLADE THREADS CRACKED S/N K67168YS						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2000073100020	20000731	00020	SO  	2000	7	31	CA000404025      	1	20000323	G	6120	B30012	COLLAR          	HARTZL      		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	INNER SURFACE	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				159  				PCE56682	BU10976		(CAN) DAMAGE TO INNER SURFACE OF LOW STOP COLLAR DUE TO IMPROPERLY SECURED LOCK WIRE.						1	L	7	1 	3T	4	T	 	A3SW    	E4EA	6	C	P15EA	 
2000071800183	20000718	00183	EA  	2000	7	18	CA000404031      	2	20000309	G	7322	HA61030	CARBURETOR      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				R	 	 	PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA				45   		75048907		L3486936A			(CAN) ENGINE QUIT DURING IDLE , AFTER RESTART, ENGINE WOULD NOT ACCELERATE FROM IDLE TO WARM UP RPM.  CARBURETOR REPLACE	D.					1	G	7	1 	3O	3	O	O	4H12    	E286				 
2000083000140	20000830	00140	EA  	2000	8	30	CA000404047      	2	20000327	G	7414		COIL            	BOSCH       	SFLU1410    	GRUMAV	TBM   	TBM3AIRTRD  	3950308	EA  	WRIGHT	R2600 	R260020     	67050	EA  	HAMSTD	23E	23E50       	NE  	AT STUD	BURNED OUT      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				39000		S9131		172966	P84440		(CAN) DURING ANNUAL INSPECTION IT WAS FOUND THAT THE MAGNETO COULD NOT BE TIMED PROPERLY.  FURTHER INVESTIGATION REVEALE	D THE COIL TO ROTOR CONTACT STUD WAS BROKEN AND THE COIL BURNED.					1	L	7	1 	4R	4	R	 	L82     	TC176	6	C	P603	 
2000083000142	20000830	00142	CE  	2000	8	30	CA000410008      	1	20000329	G	3213	9981002823	TRUNNION        			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					UPR TORQ KNEELUG	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE50045			(CAN) RIGHT MAIN LANDING GEAR ASSEMBLY WAS FOUND TO BE CRACKED AT THE UPPER TORQUE KNEE HOUSING.  BOTH SIDES OF THE LUG 	WERE CRACKED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000083000143	20000830	00143	CE  	2000	8	30	CA000410009      	1	20000331	G	5610	10138402521	WINDSHIELD      	BEECH       	STC200BEECH 	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					L/H SIDE	CRACKED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE81062			(CAN) WINDSHIELD DELAMINATED 2 MONTHS PRIOR TO CRACK.  DELAMINATION WAS WITHIN THE BEECH SERVICE MANUAL LIMITS.  WINDSHI	ELD CRACKED IN AREA OF DELAMINATION.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000073100021	20000731	00021	SO  	2000	7	31	CA000410010      	1	20000331	G	8120		LINE            	CONT        		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					TURBOCHARGER	BROKEN          	W				A	E	 	 	UNSCHED LANDING         	ENGINE SHUTDOWN         			E	 	 	VIBRATION/BUFFET          			AP	APPROACH       	1			CA						L473961A		L473961A			(CAN) OIL LINE FAILURE AT FITTING FEEDING TURBOCHARGER SECONDARY DAMAGE TO CONNECTING ROD BEARING CAUSING ROD FAILURE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030800055	20010308	00055	EU  	2001	3	8	CA000410015      	1	20000323	G	3297	9717516500	WIRE            			PILATS	PC12  	PC1245      	7090551	EU  										INSIDE NLG PLUG	BROKEN          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			270  								(CAN) ON APPROACH THE PILOT NOTICED THAT THE NOSE GEAR DOWN AND LOCKED LIGHT DID NOT ILLUMINATE AND THAT ALL THREE IN TR	ANSIT LIGHTS STAYED ON. LANDING GEAR WAS VERIFIED TO BE DOWN BY CONTROL TOWER PERSONNEL AND THE AIRCRAFT LANDED SAFELY. 	MAINTENANCE TRACED THE PROBLEM TO A BROKEN WIRE IN THE NOSE GEAR PROXIMITY SENSOR CANNON PLUG (P056, PIN A).				1	L	7	1 	3T			RT	A78EU   					 
2000071100294	20000711	00294	NE  	2000	7	11	CA000410036      	2	20000305	G	7310	0301007710	LINE            	TMECA       		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BELOW FLARE	CRACKED         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA								866			(CAN) ENGINE FAILED TO START, MAINTENANCE FOUND SPRAY OF FUEL BETWEEN THE LEFT HAND FITTING TO THE START INJECTOR.  THE 	LINE WAS REMOVED AND FOUND CRACKED AT BASE OF THE FLARE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2000072000054	20000720	00054	WP  	2000	7	20	CA000412001      	1	20000303	G	6510	369D25518	DRIVE SHAFT     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					DAMPER BRACKET	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9502 					CAE831949			(CAN) UPON REMOVAL OF TAIL ROTOR GEARBOX AND DRIVESHAFT, EXTENSIVE DAMAGE WAS FOUND ON TAIL ROTOR DRIVESHAFT. INVESTIGAT	ION REVEALED THAT THE DAMPER BRACKET WAS BROKEN OFF WHICH ALLOWED THE TAIL ROTOR DRIVESHAFT TO WHIP AND RESULT IN THIS D	AMAGE.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000083000149	20000830	00149	CE  	2000	8	30	CA000412002      	1	20000331	G	3233	1053840001	ACTUATOR        		1058200001  	BEECH 	76    	76          	1153005	CE  										LWR PART HOUSING	CRACKED         	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA											(CAN) NOSE GEAR FAILED TO RETRACT AFTER DOING NUMEROUS GEAR EXTENSION/RETRACTIONS DURING TRAINING.  MAINTENANCE FOUND NO	SE LANDING GEAR ACTUATOR HAD A HAIRLINE CRACK IN ITS HOUSING WHICH ALLOWED THE FLUID TO SLOWLY LEAK OUT.ACTUATOR REPLACE	D.				1	L	7	2 	3O			 	A29CE   					 
2000072600167	20000726	00167	EU  	2000	7	26	CA000412003      	1	20000403	G	6420	1053172904	BUSHING         	BOLKMS      	1053172901  	BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA						5651					(CAN) PILOT COMPLAINED THAT EXCESSIVE LEFT PEDAL WAS REQUIRED. TAIL ROTOR ASSEMBLY WAS MEASURED WITH SPRING SCALE AND FO	RCES WERE FOUND EXCESSIVE. TAIL ROTOR DISASSEMBLED TO CLEAN INNER SLEEVE BUSHINGS AND TEFLON BUSHINGS.  THE OUTBOARD SLE	EVE BUSHING WAS FOUND CRACKED.				1	G	7	2 	3U			 	H3EU    					 
2000070300767	20000703	00767	NE  	2000	7	3	CA000412004      	2	20000314	G	7261	0301037180	VENT LINE       	TMECA       	ARRIEL1D    	SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					REAR BRG VENTL	BROKEN          	W				K	 	 	 	NONE                    				O		 	OTHER                     			CR	CRUISE         	1			CA			3084 			7026		7026			(CAN) ENGINE REAR BEARING VENT LINE SNAPPED OFF DURING FLIGHT AND WAS LATER DISCOVERED THAT THE VENT LINE WENT INTO THE 	TAIL ROTOR.  THE PREVIOUS DAY THE VENT LINE CLAMP HAD BROKE AND IT WAS THEN NOTED THAT THE VENT LINE HAD CHAFE WEAR MARK	S CAUSED BY THIS CLAMP.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000083000150	20000830	00150	SW  	2000	8	30	CA000412007      	1	20000405	G	3240	332	CONTROL CABLE   		3434        	BBAVIA	7     	7EC         	2110120	SW  	CONT  	O200  	O200A       	17020	SO  					BRAKE SYSTEM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			42400					637556A			(CAN) DURING INSPECTION, NOTICED THAT THE LT AND RT BRAKE CABLES WERE BADLY FRAYED WHERE THEY PASS THROUGH THE LOWER FAI	RLEADS (P/N 1-2259) ON THE AXLE STRUTS.   FURTHER INSPECTION, REVEALED FRAYING OF THE CABLE BACK INSIDE THE SHEATHING UN	DER THE BOOT COWL.  THIS FRAYING COULD ONLY BE DETECTED BY REMOVING THE AFFECTED CABLE ASSEMBLY.   BOTH CABLES REPLACED.				1	H	7	1 	3O	3	O	 	A759    	E252				 
2000073100022	20000731	00022	CE  	2000	7	31	CA000412009      	1	20000412	G	2750	262228112	BELLCRANK       			CESSNA	208   	208B        	2073701	CE  										INPUT ARM	BROKEN          	W				L	 	 	 	ABORTED APPROACH        				F	 	 	FLT CONT AFFECTED         			AP	APPROACH       	1			CA			2392 								(CAN) DURING APPROACH ,THE FLAPS FULLY RETRACTED.  MAINTENANCE PERSONNEL FOUND THAT THE RIGHT FLAP BELLCRANK HAD BROKEN 	AT THE ARM CONNECTED TO THE INPUT DRIVE SHAFT FROM THE FLAP TRANSMISSION.  THE BREAK OCCURRED AT THE WELD WHERE THE DOUB	LER ENDS.  THE BELLCRANK HAD BEEN INSPECTED FOR CRACKS 351 LANDINGS PREVIOUSLY.				1	H	7	1 	3T			 	A37CE   					 
2000083000151	20000830	00151	CE  	2000	8	30	CA000412010      	1	20000410	G	5610	50420051255	WINDSHIELD      	BEECH       	STC99       	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					OUTER PANE	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA						U98		PCE41733			(CAN) WHILE EN ROUTE, THE CAPTAIN NOTICED THE WINDSHIELD CRACKED.   WINDSHIELD REPLACED.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000071100292	20000711	00292	EU  	2000	7	11	CA000412015      	1	20000412	G	6320	BABDRR	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										M/R TRANSMISSION	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				72   							(CAN) MAIN ROTOR TRANSMISSION INPUT SEAL LEAKING AT 71.6 HOURS SINCE INSTALLATION.   SEAL CHANGED, BUT LEAKING AGAIN AT 	101.3 HOURS.  INPUT SEAL WAS FOUND TO BE .003 THOUSANDS OF AN INCH LARGER DIAMETER.					1	G	7	1 	3U			 	H9EU    					 
2000083000152	20000830	00152	SO  	2000	8	30	CA000412016      	1	20000405	G	5743	40287KAE	ATTACH FITTING  	PIPER       	40288000    	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					TOP REINFORC RIB	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			14172					PCE51966			(CAN) DURING ROUTINE INSPECTION, A CRACK WAS FOUND ON THE LEFT AFT MAIN LANDING GEAR TRUNNION ASSEMBLY.  THE CRACKS WERE	 FOUND TO BE ON THE UPPER REINFORCEMENT RIBS.  PART WAS REPLACED.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000073100023	20000731	00023	CE  	2000	7	31	CA000414007      	1	20000329	G	3397		WIRE            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CABIN	CHAFED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA								RL462776T	728612		(CAN) DURING CLIMB, THE PILOT NOTICED A BURNING SMELL. THE PILOT TURNED OFF ALL ELECTRICS AND RETURNED FOR LANDING.  MAI	NTENANCE PERSONNEL FOUND THE WIRES TO THE LIGHT DIMMING CIRCUIT WERE SHORTING TO GROUND WHERE THEY HAD CHAFED ON THE CON	SOLE STRUCTURE. THE SHORT WAS INTERMITTANT AND DID NOT USE ENOUGH CURRENT TO CAUSE THE CIRCUIT BREAKER TO TRIP.  THE WIR	E WAS REPAIRED AND A CHAFE STRIP WAS ADDED TO THE STRUCTURE IN THE AREA OF THE WIRE DAMAGE.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000072000062	20000720	00062	SW  	2000	7	20	CA000414009      	1	20000411	G	2435	230321380	BRUSH BLOCK     	LEARSIEGLER 	23032018    	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER GENERATO	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				436  		4900		CAE832736			(CAN) POST-FLIGHT INSPECTION REVEALED THAT ONE OF THE BRUSHES WAS WORN DOWN TWICE AS MUCH AS THE OTHER VISIBLE BRUSH.  U	PON REMOVAL, IT WAS THEN NOTED THAT ONE OTHER BRUSH WAS BROKEN AND/OR BURNT OFF.  HOWEVER, THE STARTER/GENERATOR WAS STI	LL FUNCTIONING AS IT GAVE NO FAILURE WARNING INDICATION.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000071900178	20000719	00178	NE  	2000	7	19	CA000419005      	2	20000410	G	7210	103019204	SUN GEAR        	LYC         		BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					REDUCTION GEARBX	BROKEN          	W				O	 	 	 	OTHER                   				P	 	 	NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA				72500				LE07187X			(CAN) UPON FURTHER INVESTIGATION INTO WHY ENGINE WAS MAKING METAL, IT WAS FOUND THAT TWO TEETH HAD FRAGMENTED OFF THE GE	AR.  THE TEETH FRAGMENTS WERE .6250 INCH LONG AND WERE FOUND TRAPPED IN THE INTERNAL OIL SCREEN.  THE CAUSE FOR THE GEAR	 FAILURE WAS NOT EVIDENT.  AS SPECIFIED BY THE SUBMITTER AND IAW THE ENGINE MANUAL, THIS ENGINE COULD HAVE REMAINED IN S	ERVICE.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001011104480	20010111	04480	CE  	2001	1	11	CA000419009      	1	20000414	G	3246	13889	CONE            			BEECH 	1900  	1900C       	1154161	CE  										MLG WHEEL	SCORED          	W				K	 	 	 	NONE                    				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) BEARINGS RECEIVED FROM CANADIAN DISTRIBUTOR WITH NEW CERTIFICATION BUT VISUALLY INSPECTED TO BE USED PARTS.  ISSUE	 SENT TO MAINTENANCE AND MANUFACTURING FOR FOLLOW-UP.  (X)					2	L	7	2 	4T			RT	A24CE   					 
2000083000157	20000830	00157	SO  	2000	8	30	CA000419012      	1	20000406	G	3246	751489	CONE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					NOSE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L285161			(CAN) NOSE WHEEL BEARING FAILED ONLY 11.5 HOURS AFTER INSPECTION.  THE BEARINGS HAD BEEN CHECKED VISUALLY AFTER THEY WER	E CLEANED AND THEN RELUBED.  SUBMITTER IS CONCERNED THAT THE VISUAL INSPECTION METHOD IS INADEQUATE TO DETECT POSSIBLE B	EARING FAILURE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083000159	20000830	00159	EA  	2000	8	30	CA000427001      	2	20000408	G	7320	RSA10AD1	SERVO           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					FUEL INJ SERVO	FAILED          	W				K	 	 	 	NONE                    				L	W	 	NO TEST                   	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA								L58061			(CAN) FCU REQUIRED INTERNAL FUEL FLOW ADJUSTMENTS.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083000160	20000830	00160	NE  	2000	8	30	CA000427002      	2	20000403	G	8530	399354	CYLINDER        	PWA         		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					BTWN HEAD&BARREL	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA				62000				32349			(CAN) CYLINDER FOUND SEPARATED BETWEEN HEAD AND BARREL.  AD 78-08-07 COMPLIED WITH AT OVERHAUL 63 HOURS PREVIOUSLY.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000072000308	20000720	00308	SW  	2000	7	20	CA000427003      	1	20000329	G	6710	212076151007	TUBE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CYCLIC	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								CPPS61242			(CAN) DURING INSPECTION, THE RIGHT CYCLIC SERVO INPUT LEVER WAS FOUND IN AN AFT OF CENTER ORIENTATION.  SUBSEQUENT OBSER	VATION REVEALED BOTH CYCLIC BOOST TUBES HAD LOOSE CLEVIS ASSEMBLIES AT LOWER END.  THIS CAUSED THE SERVO TO ROTATE IN AN	Y POSITION AND INTERFERE WITH THE PARENT STRUCTURE.  NORMALLY, THE CLEVISES MUST BE TIGHT AND  LOCKED IN POSITION TO PRE	VENT THE SERVO FROM TURNING. THE USE OF SILICONE SEAL WAS USED TO BOND THE THREADED CLEVIS TO TUBE AS PER BELL MAINTENAN	CE MANUAL.   BELL WAS INFORMED AND STATED THAT THEY ARE MAKING THE CORRECTION TO THE MAINTENANCE MANUAL.		1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000072000208	20000720	00208	SW  	2000	7	20	CA000427004      	1	20000411	G	5302	212030447001	BEAM            	BELL        	212030100103	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					LEFT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			11193			ADW04155		CPPS61242			(CAN) DURING PRE-FLIGHT, THE LEFT HAND BEAM CAP ON THE TAILBOOM PYLON WAS FOUND CRACKED (.080 INCH).   NOTE:  THIS CRACK	 WAS FOUND IN THE SAME PLACE AS DESCRIBED IN FAA AD 99-18-02 APPLICABLE TO BELL 205 SERIES.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000083000161	20000830	00161	EA  	2000	8	30	CA000427005      	2	20000410	G	8520	STD1211	PLUG            	LYC         	LW17071     	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	EXPANSION PLUG	BACKED OUT      	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CL	CLIMB          	1			CA			28000					L1232339A	BL073		(CAN) EXPANSION PLUG AT FRONT OF CRANKSHAFT HAD COME LOOSE ALLOWING OIL TO LEAK OUT.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000082100140	20000821	00140	EU  	2000	8	21	CA000427010      	1	20000413	G	3242	9595601511	BRAKE           			PILATS	PC12  	PC1245      	       	EU  										RT GEAR	FROZEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			13   								(CAN) THE RIGHT BRAKE FROZE AND ON LANDING THE TIRE FAILED TO ROTATE AND WORE THROUGH THE CASING. THE TIRE WENT FLAT AND	 THE AIRCRAFT HAD TO BE TOWED FROM THE RUNWAY.					1	L	7	1 	3T			RT	A78EU   					 
2000083100898	20000831	00898	EU  	2000	8	31	CA000427030      	2	20000417	G	7414	996538	STATOR          	ROTAX       		DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					R/H COIL	BROKEN          	W				K	 	 	 	NONE                    				R	Y	 	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		IN	INSP/MAINT     	1			CA			58800					4380752			(CAN) AD 98..SB 912-026R3 PREVIOUSLY COMPLIED WITH.  SUBSEQUENT FAILURE OF STATOR PICK-UP COIL FOUND WITH PIECES MISSING	 AND COPPER WINDINGS SEVERED.  COMPONENT HAD  587.7 HOURS.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2000100300254	20001003	00254		2000	10	3	CA000427035      	4	20000418	G	3400	030023490004	CONNECTOR       	HONEYWELL   	KNR634066107															ELECT CONNECTOR	WRONG PART      	W				O	 	 	 	OTHER                   				O		 	OTHER                     			IN	INSP/MAINT     	1			CA						3607					(CAN) NO TEXT																			 
2000100300255	20001003	00255	NE  	2000	10	3	CA000427036      	2	20000418	G	7210	311657901	PINION GEAR     	PWA         							PWA   	120   	PW123D      	52152	NE  					2ND STG PINION	SPALLED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			33700					AG0086			(CAN) GEAR TEETH ON THE BULL GEAR AND BOTH SECOND STAGE PINIONS WERE SPALLED AND MISSING MATERIAL. THE WEAR PATTERNS OF 	THE GEARS SHOWED HEAVY WEAR ON THE FRONT HALVES AND THE SPALLED SECTIONS WERE ALL IN THE FRONT HALF OF THE GEAR TEETH.  	 NO ALIGNMENT ERRORS WERE FOUND NOR LUBRICATION OR RESIDUAL MAGNETISM SEEMED TO BE AT FAULT.  THE NR 11 BEARINGS WERE FO	UND TO HAVE MISMATCHED SERIAL NUMBERS.  SEVEN RGB''S TO DATE WITH SIMILAR PROBLEMS HAVE BEEN REPORTED BY THE SUBMITTOR A	ND THE OPI IS AWARE AND REVIEWING THE SERVICE DIFICULTIES EXPERIENCED.							4	T			E20NE				 
2001030900020	20010309	00020	NM  	2001	3	9	CA000501001      	1	20000113	G	3350	6104799	LIGHT           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	CABIN	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA								120832	860404		(CAN) BASE ASSY 3351-PS2 REPLACED BECAUSE NUMERIOUS EMERGENCY LIGHTS WOULD NOT TURN ON.  						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001030900024	20010309	00024	EU  	2001	3	9	CA000501006      	1	20000421	G	2910	HTE9531101	VALVE           			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LF05461A			(CAN) NR 2 HYD PUMP FAILED. INVESTIGATION REVEALED A LEAKING ISOLATION VALVE.  						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001030900025	20010309	00025	EA  	2001	3	9	CA000501009      	1	20000412	G	6320	23HD12004	TRANSMISSION    			BOEING	234   	234         	1385049	EA  	LYC   	AL5512	AL5512      	41581	NE  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			DE	DESCENT        	1			CA			85110	13770							(CAN) DURING DESCENT, CHIP WARNING LITE ILLUMINATED. MAINTENANCE PERSONNEL THEN CLEANED CHIP PLUG  & CHANGED FILTER. SER	VICEABILITY CHECK CARRIED OUT AS PER BOEING MAINTENANCE MANUAL SECTION 63-25-00 & 63-23-00 AND TRANSMISSION FOUND SERVIC	EABLE. HOWEVER, ROTORCRAFT WAS FERRIED TO AMO FOR PRECAUTIONARY REPLACEMENT OF TRANSMISSION.  				2	G	7	2 	4U	4	U	 	H9EA    	E4NE				 
2001030900028	20010309	00028	EA  	2001	3	9	CA000501013      	2	20000414	G	7322	LW10098	CONTROLLER      		LW1009885   	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					FUEL CONTROL	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA				569  							(CAN) PILOT NOTICED PARTIAL POWER LOSS ON CLIMB THROUGH 5-6000 FT. FAULTY DIFFERENTIAL CONTROLLER WAS FOUND.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030900029	20010309	00029	NE  	2001	3	9	CA000501014      	3	20000417	G	6114	P7900010030	HUB             			MORAVN	Z142  	Z142        	       	EU  						HAMSTD	V500	AVIAV500A   	NE  	OIL SEAL GROOVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1151 	505  					12060787		(CAN) PROP WAS SENT FOR NDT AS PER V500A/6A AND A CRACK WAS FOUND IN THE OIL SEALING RING GROVE RUNNING PARALLEL WITH TH	E GROOVE.A SECOND CRACK WAS FOUND 180 DEGREES FROM THE FIRST CRACK ON THE WALL OF THE GROOVE. NEITHER OF THESE CRACKS AR	E IN THE LOCATION SET OUT IN THE BULLETIN V500A/6A.				1	L	7	1 	3O			NT	A76EU   		5	C	P11BO	 
2001030900030	20010309	00030	WP  	2001	3	9	CA000501015      	1	20000424	G	5711		SPAR            			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	R280079     	52026	NE  					LT WING	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			3559 					FPO24759			(CAN) ON TAKEOFF THE PILOT HEARD A LOUD BANG.  A VISUAL INSPECTION REVEALED NOTHING UNUSUAL AND HE CONTINUED THE FLIGHT.	 ON LANDING THE ENGINEER DISCOVERED THE LT REAR SPAR CRACKED COMPLETELY. FLEET NDT CAMPAIGN BEING CARRIED OUT.  					2	M	7	2 	4R	4	R	 	L34     	5E8				 
2001030900031	20010309	00031	EU  	2001	3	9	CA000501017      	1	20000411	G	2742	02109703	ACTUATOR        			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					HORIZONTAL STAB	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			51300					P73113C			(CAN) ON DECENT, FOUND HORIZONTAL STAB NORMAL MODE U/S.  SELECTED EMERGENCY STAB AND LANDED.FOUND STAB ACTUATOR NORMAL M	ODE MOTOR U/S.					2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2001030900032	20010309	00032	NM  	2001	3	9	CA000501018      	1	20000415	G	2497	L51015915	WIRE            			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CABIN	OVERHEATED      	W				H				DEACTIVATE SYST/CIRCUITS				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA											(CAN) PRIOR TO PASS BOARDING WHILE FLIGHT ATTENDANTS PREPARED THE CABIN FOR FLIGHT SMOKE AND ARCING WAS NOTICED COMING F	ROM THE REAR OF THE AIRCRAFT GALLEY COFFEE MAKER CB PANEL. ELECTRICAL POWER WAS REMOVER FROM THE AIRCRAFT GALLEY AND THE	 FIRE EXTINGUISHER FIRED INTO THE COMPARTMENT. NR 2 COFFEEMAKER CB AND ATTACH WIRES HAD BEEN SEVERELY OVERHEATED AND PAR	T OF THE HOUSING AND WIRES WERE BURNED. CB AND WIRES REPLACED.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030900033	20010309	00033	NM  	2001	3	9	CA000501019      	1	20000411	G	2612		FIRE LOOP       			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT ENGINE	CHAFED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON CLIMB CREW OBSERVED ON INTERMITTENT NR 2 ENG FIRE WARNING ILLUMINATION. A/C RETURNED. WIRE UNDER RT ENGINE ANTI	 SLAVE FOUND CHAFED. WIRE REPAIRED. CRUSH WASHERS UNDER FIRE LOOP CONNECTORS MISSING, REPLACED. FIRE LOOP TOUCHING LOWER	 COWL, REPOSITIONED. SYS SERVICEABLE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030900034	20010309	00034	NM  	2001	3	9	CA000501020      	1	20000411	G	2781	188915	SENSOR          			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					LE FLAPS	INTERMITTENT    	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								648850			(CAN) ON TAXI CREW OBSERVED LE SLAT IN TRANSIT LIGHT STILL ON. NR 4 LE SLAT PROXIMITY SENSOR REPLACED. SYS SERVICEABLE. 	 					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030900035	20010309	00035		2001	3	9	CA000501021      	4	20000418	G	3416	1063701696	ALTIMETER       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					COCKPIT	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA				33   							(CAN) NEEDLES BECAME ERRATIC AND LOOSE AFTER A FEW HOURS.  ITEM RETURNED ON WARRANTY AND REPAIRED.  RE-INSTALLED.   FAIL	ED AFTER 32.5 HOURS.  INSTRUMENT REPLACED AGAIN.  OVERHAULER SAYS THAT THIS INSTRUMENT WAS WORN.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030900037	20010309	00037	EA  	2001	3	9	CA000501025      	1	20000409	G	5270		SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								807167			(CAN) EICAS MESSAGE FAILURE OF THE PASSENGER DOOR UNSAFE, AFTER TAKE OFF  FLIGHT RETURNED TO ORD. SENSOR FOUND TO BE FAR	. CLEANED SENSORS, PERFORMED SELF TEST. 					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001011104983	20010111	04983	NM  	2001	1	11	CA000501029      	1	20000331	G	5511		SPAR            			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					RT HORIZ STAB	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								P724313			(CAN) NO TEXT						2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001030900041	20010309	00041	NM  	2001	3	9	CA000501030      	1	20000404	G	2421	736664F	GENERATOR       			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LT ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA								P709683			(CAN) LT ENGINE GENERATOR FAULT DURING FLIGHT BUT RUGHT HAND GEN COULD NOT POWER LT BUSS.  APU USED TO POWER LT BUSS.  L	T INTRIGATED DRIVE GEN REPLACED, SYS SERVICEABLE. 					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030900042	20010309	00042	WP  	2001	3	9	CA000501031      	1	20000407	G	2450	5256	CONNECTOR       			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					EMERGENCY EXIT	CONTAMINATED    	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA								P653888D			(CAN) SMOKE IN CABIN.  AC OUTLET ARCING AND SMOKING AT FLOOR LEVEL UNDERNEATH LT OVERWING EMERGENCY EXIT. WATER INFILTRA	TION IN CONNECTOR FROM OVERWING EXIT. CONNECTOR REPLACED.  (ADP) 					2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001030900043	20010309	00043	NM  	2001	3	9	CA000501032      	1	20000411	G	3211	113T11113	FITTING         			BOEING	767   	767209      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LT DRAG STRUT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P709688			(CAN) ON HEAVY MAINTENANCE LT DRAG STRUT SIDE BRACE FITTING BUSHING FOR SPINDLE PIN FOUND WITH EVIDENCE OF HAVING ROTATE	D, SEALENT CUT AROUND PERIPHERY OF BUSHING FLANGE. DRAG STRUT BUSHING REMOVED AND HEAVY CORROSION FOUND ON BOTH FLANGE S	EAT AND BORE SURFACE OF FITTING. FITTING REWORKED TO REMOVE CORROSION AND OVERSIZE BUSHING FABRICATED AND INSTELLED. 				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030900044	20010309	00044	NM  	2001	3	9	CA000501033      	1	20000411	G	3211	113T11104	FITTING         			BOEING	767   	767209      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					RT DRAG STRUT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			55769					P709688			(CAN) ON HEAVY MAINTENANCE L DRAG STRUT SIDE BRACE FITTING BUSHING FOR SPINDLE PIN FOUND WITH EVIDENCE OF HAVING ROTATED	, SEALENT CUT AROUND PERIPHERY OF BUSHING FLANGE. DRAG STRUT BUSHING REMOVED AND HEAVY CORROSION FOUND ON BOTH FLANGE SE	AT AND BORE SURFACE OF FITTING. FITTING REWORKED TO REMOVE CORROSION AND OVERSIZE BUSHING FABRICATED AND INSTALLED.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030900045	20010309	00045	EA  	2001	3	9	CA000501035      	1	20000428	G	2720	26S83	STUD            			CNDAIR	CL600 	CL6002B19   	       	EA  										RUDDER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) A/C EXPERIENCED RESTRICTED MOVEMENT OF THE RUDDER PEDALS.  ONE OF THE STUDS HAD POPPED OUT OF THE RUDDER PEDELS PR	ETECTIVE PANEL RESTRICTING THE MOVEMENT IN FLIGHT.STUDS WERE REMOVED AND SENT TO BOMBARDIER FOR INVESTIGATION. 					2	L	7	2 	4F			RT	A21EA   					 
2001030900046	20010309	00046	SO  	2001	3	9	CA000501036      	1	20000414	G	7430	103572101	IGNITION SWITCH 			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					INSTRUMENT PANEL	FAILED          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA			13607					L4652527A			(CAN) SMOKE OBSERVED IN COCKPIT WHEN MAGNETO SWITCH SELECTED TO LT MAG POSITION.   INSPECTED A/C WIRE BUNDLES AND CONNEC	TIONS.  REPLACED FAULTY SWITCH.  UNSERVICEABLE SWITCH DISASSEMBLED AND STRONG ELECTRICAL BURNING SMELL WAS NOTED AS WELL	 AS SOME ELECTRICAL ARCING NOTED INSIDE THE SWITCH.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001030900047	20010309	00047	NE  	2001	3	9	CA000505002      	2	20000505	G	7200	6761005	ACTUATOR        			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			17394					LF05543A			(CAN) NR 1 ENGINE ACTUATOR CYCLING BACK AND FORTH CAUSING N1 AND TGT TO FLUCTUATE BY 2 PERCENT N1 AND 30 DEGREES TGT.TMS	 ACTUATOR REPLACED. 					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001030900051	20010309	00051	NE  	2001	3	9	CA000505006      	2	20000412	G	7321	7257256	FUEL CONTROL    			BOEING	107   	1072        	9420604	EA  	GE    	CT58  	CT581401    	30011	NE  					ENGINE	MISRIGGED       	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			CA								280319A			ENGINE FAILED TO RESPOND TO COLLECTIVE INPUT.  A/C COMPLETED TEST FLIGHT TO ISOLATE PROBLEM WITH NO POSITIVE RESULTS.  E	NGINE CHANGED OUT.  REPORT REQUESTED  .05, 15, 2000.  ENGINE RIGGING SPECIFIED TO BE THE MOST LIKELY CAUSE. 					2	G	7	2 	4U	4	U	 	1H16    	1E3				 
2001030900052	20010309	00052	EA  	2001	3	9	CA000505008      	2	20000426	G	8550	LW13388	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ACCESSORY CASE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								L147768A			(CAN) OIL LEAKING FROM FAILED SEAL BETWEEN OIL FILTER ADAPTER AND ACCESSORY CASE.  SHUT DOWN ENGINE IN-FLIGHT.  AREA CLE	ANED AND NEW SEAL INSTALLED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030900053	20010309	00053	EU  	2001	3	9	CA000505010      	1	20000414	G	3260	622800200	SWITCH          			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	NLG	DAMAGED         	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA			50800						DRG138781		(CAN) DURING APPROACH THE CREW LOWERED THE LANDING GEAR AND FAILED TO GET A SAFE (GREEN) INDICATION FOR THE NOSE GEAR.TH	HE APPROACH WAS ABORTED AND A TOWER FLY BY WAS PERFORMED IN ORDER TO VERFY THE NOSE LANDING GEAR POSITION. ATC PERSONNEL	 CONFIRMED THAT THE GEAR APPEARED TO BE DOWN AND A SAFE LANDING WAS CARRIED OUT.  MAINTENANCE PERSONNEL FOUND TWO BROKEN	 WIRES ON THE NOSE GEAR DOWNLOCK SWITCH. 			2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
2001030900054	20010309	00054	GL  	2001	3	9	CA000505011      	2	20000424	G	7240	6890040	SHIELD          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					NOZZLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				771  				CAT38320F			(CAN) WHEN COMPLETING CEB A-1370, 1ST STAGE NOZZLE SHIELD INSPECTION, FOUND AREA OF INSPECTION CRACKED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001030900055	20010309	00055	EU  	2001	3	9	CA000505012      	1	20000503	G	5270	9733024202	ARM             		552301200   	PILATS	PC12  	PC1245      	       	EU  										CARGO DOOR LATCH	BENT            	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			207  								(CAN) THE CARGO DOOR COULD BE CLOSED NORMALLY AND THE INDICATION WAS CORRECT. DURING A 100-HOUR INSPECTION,  MAINTENANCE	 PERSONNEL FOUND THE MICROSWITCH ARM ON THE LOCKING LEVER (IPC REF. 52-30-00-05 ITEM 195 - 215) BENT.  THE BENT SWITCH A	RM PREVENTED THE LOCKING LEVER FROM ENGAGING THE CATCH WHILE ALLOWING THE SWITCH TO MAKE CONTACT AND INDICATE THE DOOR T	O BE NORMALLY LOCKED.			1	L	7	1 	3T			RT	A78EU   					 
2001030800087	20010308	00087	SO  	2001	3	8	CA000505013      	2	20000420	G	8520	6492863	CRANKCASE       	CONT        	IO360G      	CESSNA	337   	337B        	2075706	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C301  	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1362 		352669					(CAN) CRANKCASE FOUND TO BE A LIGHT DUTY CASE.ENGINE SHOP DISCARDED CASE AND REPLACED IT WITH A NEW HEAVY CASE.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2000083100899	20000831	00899	EU  	2000	8	31	CA000505014      	2	20000426	G	7414	888712	STATOR          	ROTAX       	912A3       	DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					RT PICKUP COIL	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			94100			4412707		4412707			(CAN) AD 98  SB 996-538 ... REMOVE STATOR AND REPLACE WITH NEW.  UPON REMOVAL FOUND RT PICK-UP COIL PLASTIC SHROUD DISIN	TEGRATING IN PIECES, NO PERIPHERAL DAMAGE AS A RESULT.  SEE ALSO SDR 20000427030.  REFER AD98-9120026R3.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2001030900056	20010309	00056	SO  	2001	3	9	CA000505015      	1	20000426	G	3230	1742002	SUPPORT BRACKET 			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					AFT MOUNTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			30260								(CAN) AT ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RIGHT MAIN GEAR OUTBOARD TUBE ASSEMBLY OF THE DRAG LINK FITTING SUP	PORT (ITEM 13 FIG. 25 OF IPC).  THE CRACK IS LOCATED NEAR THE LOWER MOUNTING BOLT HOLE OF THE TUBE ASSEMBLY AND IS ABOUT	 1 INCH LONG.				1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001011103988	20010111	03988		2001	1	11	CA000505016      	3	20000427	G	6111	78FF0	BLADE ROOT      	MCAULY      	78FF0       															BLADE THREADS	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						C2535Y					****THIS SDR ATA NEEDS PROP MDL*****(CAN) BLADES RECEIVED FOR REWORK - SB81A.  HEAVY CORROSION FOUND DURING LPI.																			 
2000083100900	20000831	00900	GL  	2000	8	31	CA000505017      	3	20000428	G	6114	57A0285	ROLL PIN        	HARTZL      	8382        	TMPSON	NAVION	NAVIONA     	6150104	SW  	CONT  	E185  	E1859       	17014	SO  	HARTZL	HCA2V	HCA2V204    	GL  	LINK PIN & CWT	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			71000	41500		K1886		5054D	AK1345		(CAN) MAINTENANCE ISSUE.						1	L	7	1 	3O	3	O	 	A782    	E246	5	C	P24EA	 
2001030900057	20010309	00057	EA  	2001	3	9	CA000505021      	1	20000417	G	3230	AN62498	CHECK VALVE     			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	R2800*      	52026	NE  					RIGHT MLG	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA			2494 								(CAN) PILOT NOTICED A LOSS OF HYD PRESSURE BEFORE LOWERING THE LANDING GEAR. EMERGENCY LANDING GEAR EXTENSION SELECTED. 	RT CHECK VALVE WAS FOUND CRACKED AND SEPERATED IN TWO PIECES CAUSING FLUID LOSS.  S/B 215-466 INCORPARTED. 					2	H	7	2 	4R	4	R	 	A14EA   	5E8				 
2001030900058	20010309	00058	CE  	2001	3	9	CA000505023      	1	20000423	G	5610	141T480013	WINDSHIELD      			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C201    	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA								811954R	713018		(CAN) 2 HOURS INTO FLIGHT CAPTAINS WINDSHIELD OUTER PANE SHATTERED. WINDSHIELD REPLACED, HEAT CONTROLLER REPLACED AND SY	STEM CHECKS CARRIED OUT SERVICEABLE.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2001030900062	20010309	00062	EA  	2001	3	9	CA000505028      	1	20000505	G	2752	854D10012	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH A/C HAD FLAP FAIL AT 17 DEGREES.  RT O/B FLAP FOUND TWISTED. FLAP PANEL AND BOTH ACTUATORS R	EPLACED.  					2	L	7	2 	4F			RT	A21EA   					 
2001030900063	20010309	00063	EA  	2001	3	9	CA000505029      	1	20000505	G	2750	852D100012	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAP	SEIZED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) DURING FINAL APPROACH A/C HAD FLAP FAILURE AT 40 DEGREES.  						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030900064	20010309	00064	NE  	2001	3	9	CA000511001      	2	20000502	G	7200		ENGINE          			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					NR 2	LEAKING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								123113			(CAN) OIL SMELL NOTICEDTHROUGH OUTAIRCRAGFT.OIL RESIDUE FOUND IN NR 2 ACM OUTLET DUCTS. IT WAS DETERMINED  NR 4 BEARING 	SEAL LEAKING. 					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030900065	20010309	00065	NE  	2001	3	9	CA000511002      	2	20000430	G	7230	216035029	ACTUATOR        			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BLEED BAND	FAILED          	W				O				OTHER                   				M			OVER TEMP                 			CR	CRUISE         	1			CA								LF05543A			(CAN) BLEED BAND ACTUATOR FAILED CAUSING HIGHER THAN NORMAL TEMPRATURES.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001031200403	20010312	00403	NE  	2001	3	12	CA000511003      	2	20000504	G	7532	217114002	BLEED VALVE     			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COMPRESSOR	MALFUNCTIONED   	W				O				OTHER                   				M			OVER TEMP                 			CR	CRUISE         	1			CA								LF05543A			(CAN) BLEED BAND ACTUATOR FAILED CAUSING HIGHER THAN NORMAL TREMPERATURES. 						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001030900066	20010309	00066	EU  	2001	3	9	CA000511004      	1	20000501	G	6420	1053172904	BUSHING         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	LOOSE           	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								CAE835542			(CAN) PILOT STARTED AIRCRAFT AND FOUND PEDAL FORCES EXCESSIVE. AIRCRAFT WAS SHUT DOWN. T/R WAS DISASSEMBLED AND IT WAS F	OUND THAT ONE OF THE OUTBOARD BUSHING HAD SLID APPROXIMATELY .25 INCH OFF THE INNER SLEEVE AND WAS RUBBING THE OUTBOARD 	SPACER, LOCATED INSIDE THE BLADE GRIP.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001030900067	20010309	00067	EA  	2001	3	9	CA000511005      	1	20000416	G	6410	6117030201041	BLADE           			CARSON	S61   	S61LSKRSKY  	       	EA  	GE    	CT58  	CT581401    	30011	NE  					TAIL ROTOR	TORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			891  					295082			(CAN) POST FLIGHT INSPECTION REVEALED TWO TEARS IN TAIL ROTOR BLADE POCKET (19 & 16 INCH FROM TIP). IT APPEARS THAT LEAD	ING EDGE TAPE CAME LOOSE AND FLAPPED AGAINST BLADE CAUSING THE TWO TEARS.					2	G	7	2 	4U	4	U	 	H8EA    	1E3				 
2001031200404	20010312	00404	NE  	2001	3	12	CA000511007      	2	20000408	G	7260	4050T12P01	BEARING         			BOEING	107   	1072        	9420604	EA  	GE    	CT58  	CT581401    	30011	NE  					ACCESSORY DRIVE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			96   					280209A			(CAN) ENGINE CHIP PLUG INDICATED CHIPS & THEN PLUG CLEANED & INSPECTED, SHOWING NO SLIVERS, ONLY PASTE. NEXT DAY AFTER 5	0 MINS OF FLT, FLUXS OCCURRED ON FUEL & OIL PRESSURES&NG&THEN ENGINE FLAMED-OUT. SUBSEQUENTLY, SINGLE ENGINE LANDING CAR	RIED OUT AT LOGGING WORK SITE. INITIAL INDICATION IS THAT BEARING FAILED AT FRONT FRAME ACCESSORY DRIVE. POST TEARDOWN R	PT STATES THAT FFAD BEARING FAILED WHICH CAUSED BEVEL&PINION GEARS TO WEAR&LOSE CONTACT CAUSING ENGINE FLAMEOUT. METAL T	HEN CLOGGED OIL FILTER WHICH WENT INTO BYPASS&THEN CONTAMINATED ALL BEARINGS WHICH FAILED INSP. COMPRESSOR SPOOL&CASES W	ERE RED-TAGGED BECAUSE OF HOT SPOTS FROM RUBBING WHICH WERE CAUSED BY HIGH VIBRATIONS.	2	G	7	2 	4U	4	U	 	1H16    	1E3				 
2001030900068	20010309	00068	NE  	2001	3	9	CA000511008      	2	20000420	G	7310	8945682	LINE            			FRCHLD	SA227 	SA227CC     	       	SW  	GARRTT	TPE331	TPE33114    	01514	NE  					FCU	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			17743								(CAN) FUEL LINE ITEM NR 105 ON IPC 73-10-01 FOUND CRACKED DUE TO VIBRATION AND LACK OF CLAMP AS REQUIRED WITHIN IPC ITEM	 NR  110 73-10-01 FIG. 2PAGE 2B.					2	L	7	2 	4T	4	T	RT	A18SW   	E18NE				 
2001030900069	20010309	00069	NM  	2001	3	9	CA000511009      	1	20000426	G	3340	5102991	ATTACH FITTING  			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NLG	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA								P649414B			(CAN) ON APPROACH WHEN LANDING GEAR LOWERED CREW REPORTED A BANGING NOISE FROM THE AREA OF THE NOSE. INSPECTION AT THE G	ATE FOUND THE TAXI LIGHT SUPPORT HAD BROKEN AND THE TAXI LIGHT WAS TRAILING THE GEAR BY THE WIRE HARNESS. REPAIRED. 					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030900070	20010309	00070	EU  	2001	3	9	CA000511010      	1	20000330	G	2510	5000B2	LATCH           			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					SEAT BELT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10000					LE43488E			(CAN) IT WAS NOTICED THAT 2 OF THE FOUR SEAT BELT LATHCHES DO NO ALWAYS ENGAGE PROPERLY. WHEN THE BUCKLE IS INSERTED ALL	 THE WAY INTO THE LATCH, IT SOUNDS AN D LOOKS LIKE IT IS LATCHED BUT IF WE PULL THE BELT TO TIGHTEN IT, THE BUCKLE PULLS	 OUT OF THE LATCH WITH NO RESTRICTION. IT TAKES 4 TO 5 ATTEMPTS BEFORE BUCKLE LATCHES POSITIVELY. PROBLEM HAS NOW BEEN I	DENTIFIED AND REPLACEMENT PARTS ARE ON ORDER.			1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2001030900071	20010309	00071	CE  	2001	3	9	CA000511012      	1	20000428	G	5540	50600016	BELLCRANK       			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					RUDDER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6848 					P27206			(CAN) PILOT COMPLAINED OF WING ROCKING PROBLEM.  INVESTIGATION FOUND 1/4 PLAY AT RUDDER TRAILING EDGE WHILE PEDALS BEING	 HELD AT FULL DEFLECTION.  PLAY FOUND TO ORIGINATE FROM BELLCRANK FITTING (P/N 50-600016) AND LOWER SUPPORT TUBE ATTACHM	ENT POINT (RIVETS).  DISASSEMBLY FOUND THE RIVETS WORN, THE 3 BOLTS (P/N AN173-12A) CONNECTING THE RUDDER BELLCRANK AND 	BELLCRANK FITTING SLIGHTLY BENT AND THE HOLES DISTORTED  NEW BELLCRANK,  BELLCRANK FITTING AND BOLTS INSTALLED.  SUBMITT	ER SUSPECTS DAMAGE CAUSED FROM WIND GUSTS AND TOWING WITH GUST LOCK ON.		1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2000062800196	20000628	00196	CE  	2000	6	28	CA000511013      	1	20000305	G	5720	MS24694	SCREW           			CESSNA	208   	208B        	2073701	CE  										WING PLATE	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						208B0765	208B0765				(CAN) DURING A PHASE 1 INSPECTION, INCORRECT LENGTH SCREWS WERE FOUND INSTALLED AT WING ACCESS PANELS FOR THE AILERON BE	LLCRANK. THE SCREWS WERE RUBBING ON THE BELLCRANK AND THE SUBMITTER STATED THAT THE ENDS OF THE SCREWS WERE FOUND WORN O	FF.                                                                                                                     	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	H	7	1 	3T			 	A37CE   					 
2000072100922	20000721	00922	SW  	2000	7	21	CA000511015      	1	20000427	G	6230	206040536101	BEARING         	BELL        	206040014003	BELL  	206   	206L        	1181522	SW  										M/R MAST	MAKING METAL    	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			IN	INSP/MAINT     	1			CA			79800			NJF389A					(CAN) TWO TINY MARKS ON BEARING - MAKING METAL.  REPLACED WITH NEW MAST BEARING 206-040-536-101, S/N J0394-1 AND 2, NEW 	SEAL AND COMPLY WITH 1500 HOUR INSPECTION.					1	G	7	1 	3U			 	H2SW    					 
2000062800197	20000628	00197	GL  	2000	6	28	CA000511016      	2	20000504	G	7230	23009609	BEARING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					COMPRESSOR	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			32230					CAE295288			(CAN) NR 1 COMPRESSOR ROLLER BEARING MAKING METAL.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000062800198	20000628	00198	CE  	2000	6	28	CA000511018      	1	20000510	G	3297	V31001	WIRE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG SWITCH	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								PCE50717			(CAN) AIRCRAFT RETURNED WITH GEAR IN-TRANSIT LIGHT.  AFTER NUMEROUS GEAR SWINGS IT WAS DISCOVERED THAT THE WIRE WAS LOOS	E WHERE IT IS ATTACHED TO THE EMERGENCY GEAR EXTENTION MICRO-SWITCH.THIS SWITCH CUTS POWER SO THAT WHEN THE EMERGENCY SY	STEM IS USED THERE IS NO POWER.  THE INTERMITTANT POWER CAUSED THE GEAR NOT TO FULLY RETRACT AND CAUSE THE IN-TRANSIT LI	GHT TO STAY ON.  WIRE WAS SECURED.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000083000166	20000830	00166	CE  	2000	8	30	CA000511019      	1	20000510	G	5510	1154400312	BRACKET         	RAYTHN      		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					CASTING	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						B153		PCE41799			(CAN) CRACK FOUND DURING INSPECTION IN WEBBING.  SUBMITTER STATED THIS IS A COMMON AREA FOR CRACKING WITH THE UNITS.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001030900072	20010309	00072	GL  	2001	3	9	CA000511020      	2	20000315	G	7230	23056109	COMPRESSOR      			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								860787			(CAN) 1.5 INCH CRACK FOUND ON COMPRESSOR SCROLL STARTING ALONG AFT RADIUS OF SCROLL PROGRESSING TOWARD DISCHARGE ELBOW A	ND TURNING TO MIDDLE OF OUTSIDE FACE.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001030900076	20010309	00076	EU  	2001	3	9	CA000511024      	1	20000420	G	3020	5302412003	INTAKE DUCT     			PILATS	PC12  	PC1245      	       	EU  										ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28770								(CAN) DURING INSPECTION, EXHAUST RESIDUE WAS FOUND ON THE INSIDE OF THE LOWER FORWARD ENGINE COWLING.  UPON CLOSER INSPE	CTION BOTH PIPE ADAPTERS FOR THE EXHAUST INLET AND OUTLET TO THE INTAKE LIP WERE FOUND BROKEN AWAY FROM THE LIP ASSY.					1	L	7	1 	3T			RT	A78EU   					 
2000072400259	20000724	00259	SW  	2000	7	24	CA000511026      	1	20000217	G	5347		HOOK            	BELL        		BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					ON THE LANYARD	WRONG PART      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA						45146		CAE831288			(CAN) ROTORCRAFT WAS CARRYING A SKIDOO ON THE CARGO HOOK WHEN THE PILOT FELT IT RELEASE.  RETURNED TO BASE WHERE THE HOO	K AND MECHANICAL AND ELECTRICAL RELEASES WERE CHECKED.  AS A PRECAUTIONARY MEASURE, THE HOOK WAS REPLACED.  THE REMOVED 	ASSY WAS TESTED AS PER BREEZE EASTERN RECOMMENDATIONS (TWICE) AND NO DEFECTS WERE FOUND.  IT IS SUSPECTED THAT THE WRONG	 SIZE RING WAS USED ON THE LANYARD.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000082200031	20000822	00031	SO  	2000	8	22	CA000511027      	1	20000502	G	3030	30216003	PITOT TUBE      	PIPER       	DWGI6065    	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					L/H WING	BURNED OUT      	W				O	 	 	 	OTHER                   				M	P	 	OVER TEMP                 	NO WARNING INDICATION     		TO	TAKEOFF        	1			CA			71510			275476		L585248			(CAN) WHEN PITOT HEAT WAS SELECTED, CIRCUIT BREAKER TRIPPED.  UPON INVESTIGATION, FOUND HEATER ELEMENT GROUNDING OUT TO 	PITOT HEAD HOUSING.   SUBMITTER SUGGESTED CAUSE TO BE PREVIOUS USER TO SELECT HEAT WHILE ON GROUND BEYOND THE 3 MINUTE T	IME LIMIT OR NORMAL WEAR.				1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2000071200059	20000712	00059	EA  	2000	7	12	CA000511029      	1	20000310	G	7800	T10417	TRUNNION        	ORENDA      	OE600A      	DHAV  	DHC3  	DHC3        	2800202	EA  										EXHAUST ROCKER	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			63000			OE600A0016		OE600A0016			(CAN) ROCKER TRUNNION FAILED, PART RETURNED FOR INVESTIGATION.						1	H	7	1 	3R			 	A815    					 
2000062800199	20000628	00199	CE  	2000	6	28	CA000511030      	1	20000502	G	5720	082260030	FITTING         	CESSNA      	082260068   	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					TIP TANKS	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			11500					502131A			(CAN) DURING SCHEDULED INSPECTION, MOVEMENT WAS NOTICED AT THE AFT TIP TANK FITTING AS MAINTENANCE PERSONNEL APPLIED UP 	AND DOWN FORCES TO THE TIP TANK TRAILING EDGE. THE TWO MOST OUTBOARD RIVETS WHICH ATTACH THE FITTING TO THE OUTBOARD RIB	 (THROUGH THE REAR SPAR)  WERE FOUND SHEARED. THE SUBMITTER STATES THAT THIS IS THE SECOND AIRCRAFT HE HAS FOUND IN THIS	 CONDITION.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001021400001	20010214	00001	EA  	2001	2	14	CA000511031      	1	20000506	G	2740		SWITCH          			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AN AP PITCH TRIM MESSAGE APPEARED.BOTH FCC,HSTCU AND TRIM SWITCHES REPLACED.						2	L	7	2 	4F			RT	A21EA   					 
2001030900078	20010309	00078	EA  	2001	3	9	CA000511032      	1	20000506	G	2611		WARNING SYSTEM  			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					CARGO BAY	FALSE INDICATION	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA								807147			(CAN) CARGO SMOKE MESSAGE ON SHORT FINAL. FOLLOWED QRH AND BLEW BOTTLES. 						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031200405	20010312	00405	EA  	2001	3	12	CA000511033      	1	20000506	G	2752	854D10012	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) FLAPS FAIL AT 17 DEG. FLAP ACTUATOR REPLACED						2	L	7	2 	4F			RT	A21EA   					 
2001030900079	20010309	00079	EA  	2001	3	9	CA000511034      	1	20000506	G	5210		DOOR            			CNDAIR	CL600 	CL6002B19   	       	EA  										PAX	NOT CLOSED      	W				A				UNSCHED LANDING         				W	J		INADEQUATE Q C            	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) PAX DOOR HANDLE MESSAGE APPEARED ON EICAS DURING CLIMB. THEY REPORTED THAT THE DOOR WAS NOT SHUT ALL THE WAY. 						2	L	7	2 	4F			RT	A21EA   					 
2001031200406	20010312	00406	EA  	2001	3	12	CA000511035      	1	20000506	G	2760		PANEL           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON SHORT FINAL FLT SPOILER DEPLOYED UNCOMMANDED ABOUT 25 DEG UP ON THE RT WING AND APPROX 10 DEGREES UP ON THE LT 	WING.  SPOILER PANEL, INBOARD PCU AND O/B PCU REPLACED. 					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031200407	20010312	00407	EA  	2001	3	12	CA000511036      	1	20000506	G	4990		APU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU BAY	OVERSERVICED    	W				B				EMER. DESCENT           				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								807435			(CAN) SMOKE TOILET MESSAGE APPEARED ON EICAS AFTER TRANSFERING PACKS TO APU BLEED  AIR.  APU FOUND OVERSERVICED BY APPRO	X. 1/2 QT. 					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000062800200	20000628	00200	CE  	2000	6	28	CA000511038      	1	20000504	G	5753	052323113	FLAP TRACK      	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					TE FLAP	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA								L3234327A			(CAN) FOLLOWING A SIMULATED FORCED APPROACH, THE INSTRUCTOR AND STUDENT HEARD A LOUD BANG AS THE FLAPS WERE RETRACTING. 	 THE FLAPS CONTINUED TO RETRACT TO THE FULL UP POSITION AND THE FLIGHT CONTINUED BACK TO BASE AND LANDED UNEVENTFULLY.MA	INTENANCE PERSONNEL FOUND THAT THE LEFT INBOARD FLAP TRACK (RIB ASSY) HAS CRACKED.                                      	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000072400260	20000724	00260	SW  	2000	7	24	CA000511040      	1	20000506	G	5302	206032409001P	BOLT            	BELL        	206033004011	BELL  	206   	206L        	1181522	SW  										TAIL BOOM	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						AOKP00649					(CAN) CRACKED TAILBOOM ATTACHMENT BOLT FITTING.						1	G	7	1 	3U			 	H2SW    					 
2001031200408	20010312	00408	SW  	2001	3	12	CA000511041      	1	20000502	G	2710	KP16B	BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	AILERON	ROUGH           	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA									DRG294783		(CAN) THE FLIGHT CREW REPORTED THAT THE AILERON MOVEMENT WAS ROUGH AND WAS MAKING A ROUGH SOUND. MAINTENANCE FOUND A ROU	GH BEARING IN THE AILERON TORQUE TUBE HOUSING SUPPORT. THE BEARINGS WERE REPLACED WITH NEW.					2	L	7	2 	4T			RT	A8SW    		6	C	P61GL	 
2000062800201	20000628	00201		2000	6	28	CA000511042      	4	20000417	G	2562	E01	SWITCH          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELT	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L3197827A	726767		(CAN) ELT FALSE ALARM - EVIDENCE OF MOISTURE ON REMOTE SWITCH PLUG END.  						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000062800202	20000628	00202	SO  	2000	6	28	CA000511043      	1	20000418	G	7603	554546	CABLE           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					PEDESTAL	SEPARATED       	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA								L43472			(CAN) DURING TAKEOFF, THE LEFT ENGINE REMAINED AT MAXIMUM RPM WHEN CLIMB POWER WAS SELECTED FOR BOTH ENGINES.  MAINTENAN	CE FOUND THE LEFT THROTTLE CABLE BROKEN WITHIN THE PEDESTAL AREA  AT THE POINT WHERE THE CABLE ENTERS THE HOUSING. CABLE	 REPLACED.				1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2000062800203	20000628	00203	EA  	2000	6	28	CA000511044      	2	20000418	G	8530	3116	STUD            	LYC         	LW15322     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					NR 3 CYLINDER	BROKEN          	W				C	 	 	 	ABORTED TAKEOFF         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA			94000	20940				L32872T			(CAN) INTAKE ROCKER STUD FOUND BROKEN ON #3 CYLINDER.  CYLINDER SENT FOR EVALUATION WHERE IT WAS DETERMINED THAT STRESS 	TO THE THREADED PORTION OF THE STUD WAS THE CAUSE OF ITS FAILURE.                                                       	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2000083000168	20000830	00168	CE  	2000	8	30	CA000511045      	1	20000427	G	5345	08119031	MOUNT BRACKET   			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	SUPPORT ASSY	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			59600				310R0927	235587R	779115		(CAN) DURING A 200-HOUR INSPECTION, LOOSENESS WAS FOUND AT THE CABIN STEP ATTACHMENT.  THE STEP AND SUPPORT WERE REMOVED	 FOR RE-BUSHING.  THE SUPPORT ASSEMBLY WAS INSPECTED AND FOUND CRACKED.  THE CAUSE OF THE LOOSENESS IN THE STEP WAS CORR	OSION AND WEAR IN THE STEP MOUNTING HOLES.  A NEW SUPPORT ASSEMBLY WAS INSTALLED.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001031200409	20010312	00409	NM  	2001	3	12	CA000511046      	1	20000503	G	2510	5110013033	SEAT BACK       			ISRAEL	1125  	1125        	       	NM  	ALIDSG	TFE731	TFE7313AR   	 	WP  					CAPTAINS SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			31710					P96208			(CAN) PILOTS SEAT BACK REST FOUND CRACKED. 						2	L	7	2 	4F	4	F	RT	A16NM   	E6WE				 
2000072400261	20000724	00261		2000	7	24	CA000516001      	4	20000510	G	2562	BS2166	BATTERY         	NARCO       	ELT10       	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ELT BATTERY	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						C10317		CAE830913			(CAN) ELT WAS REMOVED FOR ANNUAL INSPECTION AND IT WAS NOTED THAT WHITE POWDER WAS ON OUTSIDE OF BATTERY AND ELT CASE.  	UPON INSPECTION AFTER BATTERY REMOVAL, A LEAK WAS DETECTED.  BATTERY STILL HAD 5 MONTHS LEFT ON ITS LIFE.   EXPIRATION, 	SEPT 2000.  BATTERY WAS REPLACED AND ELT WAS TESTED SERVICEABLE.  NO INTERNAL DAMAGE OCCURRED.  OWNER DID NOT NOTICE LEA	KAGE UNTIL ELT WAS REMOVED FROM BRACKET.  ELT BATTERY LOT NR 1S 44181.  MANUFACTURE DATE IS AUGUST 1998.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000062800204	20000628	00204		2000	6	28	CA000516002      	4	20000505	G	2562	0010009	BATTERY         	NARCO       	ELT10       	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ELT	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						71322		3877627A	82493		(CAN) LOOSE BATTERY CELLS IDENTIFIED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000062800205	20000628	00205	EA  	2000	6	28	CA000516003      	2	20000509	G	8550	62817	SCREEN          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	OIL SYSTEM	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L4429127A	732270		(CAN) DURING INSPECTION, THE OIL SCREEN WAS FOUND TO BE DETERIORATING AND BEGINNING TO FRAY IN ONE AREA.  THE SUBMITTER 	SUGGESTS THAT THE SCREEN WAS DETERIORATING DUE TO OLD AGE AND REPEATED CLEANINGS.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000062800206	20000628	00206	CE  	2000	6	28	CA000516005      	1	20000504	G	7120	05510171	MOUNT           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L4429127A	E18147		(CAN) DURING SCHEDULED MAINTENANCE, THE ENGINE MOUNT LOWER HORIZONTAL BRACE WAS FOUND CRACKED AT BOTH ENDS.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000062800207	20000628	00207	CE  	2000	6	28	CA000516006      	1	20000403	G	5510	1156100181	SUPPORT FITTING 			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					TORQUE TUBE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			82080					50078			(CAN) ON 1000 HOUR INSPECTION, NDT FOUND CRACK IN TAPER PIN ATTACH HOLE.  SUSPECT OVERTORQUING OF PIN.  NEW TORQUE ASSY.	 REPLACED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000062800208	20000628	00208	EU  	2000	6	28	CA000516007      	1	20000420	G	3260	9733033111	PROXIMITY SWITCH			PILATS	PC12  	PC1245      	       	EU  										MLG	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			10490								(CAN) THE CREW RECEIVED A CAWS WARNING LIGHT FOR AIR/GROUND (AIRGND).  THE MAINTENANCE CREW DIAGNOSED A FAILED PROXIMITY	 SWITCH.					1	L	7	1 	3T			RT	A78EU   					 
2000062800209	20000628	00209	EU  	2000	6	28	CA000516008      	1	20000414	G	2752	951D10011	GEAR            			PILATS	PC12  	PC1245      	       	EU  										FLAP ACTUATOR	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			25900								(CAN) DURING SCHEDULED INSPECTION, THE FLAP ACTUATOR WAS FOUND WORN BEYOND SERVICE LIMITS.						1	L	7	1 	3T			RT	A78EU   					 
2000072600060	20000726	00060	EU  	2000	7	26	CA000516009      	1	20000425	G	3010	9598901035	BOOT            			PILATS	PC12  	PC1245      	       	EU  										L/H STAB	UNBONDED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28400								(CAN) DURING PREFLIGHT INSPECTION, THE PILOT NOTICED THE DE-ICE BOOT HAD BECOME UNGLUED ON THE TOP FOR A DISTANCE OF ABO	UT TWO FEET.  THE BOOT WAS REPLACED WITH A NEW UNIT . THE SUBMITTER STATES THAT THE OLD BOOT WAS EASILY REMOVED AND DID 	NOT APPEAR TO BE PROPERLY ADHERING TO THE STABILIZER SURFACE.				1	L	7	1 	3T			RT	A78EU   					 
2000072600061	20000726	00061	EU  	2000	7	26	CA000516010      	1	20000519	G	2752	951D10011	ACTUATOR        			PILATS	PC12  	PC1245      	       	EU  										WORM GEAR	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			17800								(CAN) DURING SCHEDULED INSPECTION OF THE FLAP ACTUATORS, THREE OUT OF FOUR ACTUATORS WERE FOUND WORN BEYOND SERVICE LIMI	TS.					1	L	7	1 	3T			RT	A78EU   					 
2000071800135	20000718	00135	GL  	2000	7	18	CA000516012      	2	20000410	G	7250	6878426	NOZZLE          	ALLSN       		BELL  	206   	206BELL     	1181502	SW  	ALLSN 	250C  	250C20      	03013	GL  					1 BLADE PATH CIR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						CAT31780D		CAT31780P			(CAN) A GROUP OF 2ND STAGE NOZZLES ARE IN THE PROCESS OF RECALL.  IT WAS FOUND THAT REPAIRS MADE TO SOME NOZZLES;  WHICH	 WAS AN APPROVED REPAIR , HAVE FAILED TO REACH O/H AND ARE CRACKING WHERE THE FIRST STAGE BLADE PATH WAS JOINED TO THE 2	ND STAGE NOZZLE. TRANSPORT CAW CORRECTIVE ACTION GROUP IS ADRESSSING THIS ISSUE.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001031200411	20010312	00411	GL  	2001	3	12	CA000516014      	2	20000502	G	7250	689784	ADAPTER         								ALLSN 	250C  	250C20B     	03013	GL  					OUTER SPLINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			323  								(CAN) EXCESSIVE DAMAGE TO SPLINES OF ADAPTER AND INNER SPLINES OF THE COMPRESSOR TO TURBINE COUPLING SHAFT. IN SOME CASE	A SPLINE TOOTH IS COMPLETELY SHEARED OFF.										3	U			E4CE				 
2001031200412	20010312	00412	EA  	2001	3	12	CA000516016      	1	20000508	G	2910	2156401521	LINE            			CNDAIR	CL215 	CL2151A10   	       	EA  										HYD SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BETWEEN FS 52.00 AND LWS 60.8 WHERE LEFT FUEL TUBE ASSY AND HYD TUBE ASSY GO THROUGH THE WING ROOT.  IT WAS FOUND 	THAT THE HYD PRESSURE TUBE WAS CHAFING AGAINST LT FUEL TUBE ASSY.  					2	H	7	2 	4R			 	A14EA   					 
2000072600062	20000726	00062	CE  	2000	7	26	CA000516017      	1	20000505	G	3233	99810057652	ACTUATOR        			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RT MLG INTERNAL	SEIZED          	W				O	 	 	 	OTHER                   				J		 	WARNING INDICATION        			LD	LANDING        	1			CA								24134			(CAN) THE CREW ON A TRAINING FLIGHT NOTICED, AFTER A NUMBER OF TIMES CYCLING THE GEAR, THE GEAR HANDLE RED LIGHT REMAINI	NG ON.  AS THE AIRCRAFT LANDED, THE RIGHT LANDING GEAR COLLAPSED  .MAINTENANCE FOUND THE RIGHT LANDING GEAR ACTUATOR SEI	ZED IN THE PARTIALLY RETRACTED POSITION. THE ACTUATOR IS BEING SENT OUT FOR EVALUATION.				1	L	7	2 	3T	3	T	 	A14CE   	E4EA				 
2001032000002	20010320	00002	SW  	2001	3	20	CA000516018      	1	20000508	G	6320	269A54979	SHAFT           			HUGHES	269   	269C1       	8059504	SW  										MAIN ROTOR	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				E		 	VIBRATION/BUFFET          			AP	APPROACH       	1			CA			1286 								(CAN) FOLLOWING 1.8 HOUR FLIGHT AND AT BEGINNING OF APPROACH TO AIRFIELD, A BANG WAS HEARD AND A LOW POWER AUTOROTATION 	WAS CARRIED OUT. ROTORCRAFT WAS LEFT RUNNING FOR ENGINEER TO INSPECT. A VIBRATION WAS FELT THROUGHOUT THE CABIN (MOSTLY 	IN THE FLOOR) & LOWER PULLEY WAS VIBRATING. INSPECTION AFTER  SHUT-DOWN REVEALED A VISUAL CRACK ON THE FORWARD PART OF S	HAFT LOCATED  UNDER THE BEARING (SHAFT IS STAINLESS). THE CRACK WAS 1.5 INCH LONGITUDINAL AND 2 ING AROUND THE SHAFT CIR	CUMFERENCE.		1	G	7	1 	3O			O	4H12    					 
2001011104172	20010111	04172	WP  	2001	1	11	CA000516020      	1	20000504	G	2821	66547775940	BOLT            	PUROLATOR   	6815922     	CVAC  	580   	580         	       	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441*      	GL  	FILTER ASSY	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CR	CRUISE         	1			CA						6		501698	HC183		(CAN) CREW OBSERVED A REDUCTION OF HP, FF, TIT AND LOW PRESS FUEL LIGHT ON NR 1 ENGINE.  ALSO NOTICED RAPID LOSS OF FUEL	 IN LEFT WING TANK.  ENGINE SHUT DOWN AND FUEL TANK S/O CLOSED.  LP FUEL BOWL FAILED DUE TO CENTER BOLT BROKEN AT END OF	 THREADS.  BOLT REPLACED.				2	L	7	2 	4T	4	T	RT	        	E282	6	C	P898	 
2000072600063	20000726	00063	EA  	2000	7	26	CA000516021      	2	20000508	G	8520	7380685	PUSHROD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					AT 1 BALL END	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				R	 	 	PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				21960				RL1627815			(CAN) STEEL ENDS OF PUSH RODS DAMAGING ALUMINUM TUBES.  LYCOMING SB 453 ADDRESSES ISSUE.  LYCOMING HAS SINCE SWITCHED TO	 ALL STEEL PUSH RODS.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000072600064	20000726	00064	CE  	2000	7	26	CA000516022      	1	20000508	G	3222	AN5	BOLT            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	NLG AXLE BOLT	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			36000					L2827936A	815095		(CAN) AFTER LANDING, THE PILOT EXPERIENCED DIFFICULTY STEERING THE AIRCRAFT. THE AIRCRAFT WAS STOPPED ON THE RUNWAY AND 	IT WAS NOTICED THAT THE NOSEWHEEL WAS SITTING CROOKED ON THE NOSE GEAR FORK. FURTHER INSPECTION REVEALED THAT THE NOSE W	HEEL AXLE BOLTAND ONE AXLE FERRULE WERE MISSING FROM THE NOSE GEAR. THE SUBMITTER SUSPECTS THAT THE NUT MAY HAVE COME OF	F THE BOLT OR THE BOLT MAY HAVE BROKEN.			1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2000072600070	20000726	00070	SO  	2000	7	26	CA000516023      	1	20000508	G	2120	8124402	TUBE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					FWD PRT OF TUBE	DISCONNECTED    	W				G	B	 	 	O2 MASK DEPLOYED        	EMER. DESCENT           			W	 	 	INADEQUATE Q C            			CR	CRUISE         	1			CA			85000					PCE51623			(CAN) AIRCRAFT MADE AN IN-FLIGHT RAPID DECOMPRESSION.  THE FORWARD PART OF THE  FRESH AIR DISTRIBUTION TUBE WAS FOUND TO	 BE DISCONNECTED.  THE CLAMPS WERE REMOVED,  INSPECTED, REINSTALLED, AND LOC WIRED TO PREVENT SLIPPAGE.  THE SUBMITTER S	TATES THAT ALTHOUGH LOCKWIRING THE CLAMPS IS NOT IN THE MAINTENANCE MANUAL, LOCKWIRING GIVES BETTER SECURITY.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000072600071	20000726	00071	SO  	2000	7	26	CA000516024      	1	20000508	G	3243	492152	VALVE           			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					PARKING BRAKE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			48090					PCE80156			(CAN) PILOTS CHECKED FOR BRAKE PRESSURE DURING CRUISE FLIGHT AT 33,000 FEET.  BRAKES WERE VERY SOFT.  PARKING BRAKE VALV	E FOUND TO HAVE LEAKING O-RINGS.  SEALS REPLACED.					1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2000072600072	20000726	00072	EU  	2000	7	26	CA000516026      	1	20000505	G	3250	Z4242170001	SPRING          	MORAVN      	L24242370000	ZLIN  	242   	Z242L       	9970204	EU  										AFT END	BROKEN          	W				K	 	 	 	NONE                    				O	D	 	OTHER                     	INFLIGHT SEPARATION       		IN	INSP/MAINT     	1			CA			36530								(CAN) WHILE HAND TOWING THE AIRCRAFT, A NOISE WAS HEARD WHILE TURNING TO THE RIGHT.  INVESTIGATION REVEALED THAT THE LEF	T STEERING SPRING HAD BROKEN.  THE SPRING WAS REPLACED USING THE MINIMUM DISTANCE SETTINGS ON THE LT AND RT STEERING SPR	INGS.  SUBMITTER STATED  TURNING THE NOSE GEAR SHOULD BE DONE WHILE MOVING AND MONITORING TURN LIMITS DURING HAND TOWING	  WOULD HELP REDUCE SIMILAR OCCURENCES.			1	L	7	1 	3O			0	A76EU   					 
2000072600078	20000726	00078	EU  	2000	7	26	CA000516027      	1	20000510	G	3010	9598901014	TIMER           	BFGOODRICH  		PILATS	PC12  	PC1245      	       	EU  										INTERNAL	FAILED          	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA			40900			U0058					(CAN) WHILE ON APPROACH, THE PILOT SELECTED DE-ICE ON.  AFTER 8 SECONDS, A DE-ICE FAIL WARNING WAS OBSERVED.  SELECTING 	THE DE-ICE OFF DID NOT CANCEL THE WARNING LIGHT SO THE PILOT SECURED THE CIRCUIT BREAKER.  MAINTENANCE LATER DETERMINED 	THAT THE DE-ICE TIMER HAD FAILED AND HAD STUCK IN THE HORIZONTAL STABILIZER POSITION.				1	L	7	1 	3T			RT	A78EU   					 
2000083000169	20000830	00169	EA  	2000	8	30	CA000516031      	3	20000426	G	6111	1774017060	PROPELLER       	SNSNCH      		PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	FACE  AND CAMBER	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				31700				L400327	K30334		(CAN) NO TEXT						1	H	7	1 	3O	3	O	 	1A6     	E274	5	N	P88614	 
2001031200415	20010312	00415	NE  	2001	3	12	CA000516033      	2	20000411	G	7270		FAN             			CNDAIR	CL600 	CL6001A11   	1900302	EA  	LYC   	ALF502	ALF502L     	41580	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			CA								3068			(CAN) FOLLOWING A/C ROTATIONAT 100AGL THE NUMBER 2 ENGINE AUTOMATICALLY SHUTDOWN WITH AN OVERSPEED INDICATION. N1 FAN WO	ULD NOT ROTATE. ENGINE REPLACED. 					2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2001031200416	20010312	00416	NM  	2001	3	12	CA000516034      	1	20000501	G	3246	2607047	WHEEL           			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								648850			(CAN) WHILE TAXING MAINT NOTED NR 2 MAIN WHEEL ASSY WAS FLAT. FURTHER INVESTIGATION REVEALED 1/3 OF THE OUTBOARD WHEEL H	ALF HAD BROKEN OFF AND THE TIRE WAS CUT AT THE WALL EDGE. DAMAGE WAS FOUND ON THE WING BODY FAIRING, LT IB FORE FLAP AND	 THE LT UPPER WING TRAILING EDGE. ALL EXCEDED SRM LIMITS.  NR 2 MAIN WHEEL REPLACED AND A/C FERRIED FOR MAINTENANCE. 				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000072400263	20000724	00263	NM  	2000	7	24	CA000516035      	1	20000313	G	6322	A1874	CONE            	ROBSIN      	B1741       	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					CIRC OF CONE	CHAFED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L1581339A			(CAN) THE LENGTH OF THE SCREW THAT ATTACHES INSPECTION PLATE P/N D229-4 TO SCROLL SET P/N R7156 WAS EXTENDED THROUGH SCR	OLL SET TO A DEPTH THAT IT CONTACTED CONE P/N A187-4 CAUSING IT TO CHAFE AS THE FAN WHEEL ROTATED.  UNABLE TO DETERMINE 	AT THIS TIME THE P/N OF THE SCREW THAT WAS INSTALLED.  THE CORRECT P/N FROM ROBINSON R2 ILLUSTRATED PARTS CATALOG IS MS3	5206-227.  IT IS SUSPECTED THAT AN OVERLY LONG SCREW WAS INSTALLED DURING THE ROTORCRAFT''S  OVERHAUL.			1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2000082200032	20000822	00032	SW  	2000	8	22	CA000516036      	1	20000509	G	5101		STRUCTURE       			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  					AIRFRAME	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28440					RL954336A			(CAN) SEVERE CORROSION FOUND DURING ANNUAL INSPECTION.  EXFOLIATION CORROSION FOUND AT LT FLAP 3 AND 4 HINGE BRACKET. IN	TERGRANULAR CORROSION FOUND AT LT MAIN GEAR LINK ATTACHMENT TO MAIN WING SPAR BRACKET.  AT THE LT AND RT FUSELAGE TUBING	 ATTACHMENT TO MAIN WING LOWER SPAR, THE STEEL TUBING IS RUSTED RIGHT THROUGH.   ALSO, GENERAL SURFACE CORROSION WAS DIS	COVERED IN THE CABIN FLOOR AREA.			1	L	7	1 	3O	3	O	 	2A3     	E286				 
2000081000023	20000810	00023	NE  	2000	8	10	CA000518001      	2	20000503	G	8530		CONNECTING ROD  	PWA         		GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985AN14B   	52008	NE  					CONNECTING ROD	BROKEN          	W				A	E	 	 	UNSCHED LANDING         	ENGINE SHUTDOWN         			B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				12430				225627			(CAN) CONNECTING RODS FOR NR 8 AND NR 9 CYLINDERS BROKEN.						1	H	7	2 	3R	3	R	 	TC654   	5E1				 
2000062800211	20000628	00211	SW  	2000	6	28	CA000518007      	1	20000216	G	6320	212040001059	PLANETARY GEAR  	BELL        	212040001059	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TRANSMISSION	CHIPPED         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA				56030		ABW40017		CPPS61014			(CAN) METAL FOUND ON THE PLANETARY CHIP DETECTOR (.040 INCH  - .060 INCH). TRANSMISSION WAS REMOVED SHORT OFF AND SENT F	OR REPAIR.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000062800213	20000628	00213	NE  	2000	6	28	CA000518009      	2	20000301	G	7530	0177555170	TACHOMETER      	TMECA       	0177555170  	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					INTERNAL	UNSERVICEABLE   	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA						1338B		290			(CAN) ENGINE BLEED VALVE WHICH IS CONTROLLED BY THE TACHOMETER BOX INADVERTENTLY OPENED TWICE AT 98 PERCENT NG.  OPERATO	R WAS NOT ABLE TO DUPLICATE.  POSSIBLE CAUSE WAS A SHORT IN THE TACHOMETER BOX.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000072600245	20000726	00245	EU  	2000	7	26	CA000518010      	1	20000301	G	7712	9580113720	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TORQUE INDECATOR	INCORRECT       	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA				30000		1451		451			(CAN) TORQUE TRANSMITTER WAS INSTALLED THE DAY BEFORE AND SET TO PROPER PRESSURE.  CHECKED LATER AND FOUND TO BE OFF BY 	3% PERCENT.  UNIT RE-ADJUSTED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000062800214	20000628	00214	EU  	2000	6	28	CA000518011      	1	20000229	G	7921	RH2125	COOLER          		RH2125      	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENG OIL COOLER	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA						457		290			(CAN) EXTERNAL SEAM ON THE OIL COOLER LEAKING PROGRESSIVELY WORSE, UNIT REPLACED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000062800215	20000628	00215	EU  	2000	6	28	CA000518012      	1	20000302	G	2140	350A72100509	HEATER          		350A72100509	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					UNION FITTING	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								834			(CAN) LINE FOUND TO BE CORRODED AND CRACKED BY THE UNION.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000072600161	20000726	00161	EU  	2000	7	26	CA000518013      	1	20000411	G	6720	1053178201	PITCH LINK      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEAR BOX	UNSERVICEABLE   	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						512519		CAE836046			(CAN) DURING A TAILROTOR (T/R) GEARBOX CHANGE,THE T/R PITCH CHANGE BELLCRANK WAS FOUND DAMAGED.  THE DAMAGE WAS CAUSED F	ROM THE SAFETY WIRE CHAFING NEAR THE PIVOT BEARING.  SAFETY WIRE IS FASTENED TO PIVOT BEARING STUD FROM THE T/R GEARBOX.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2000072600246	20000726	00246	NE  	2000	7	26	CA000518014      	2	20000329	G	7532	9550158260	BLEED VALVE     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	STUCK           	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			CA				13780				347			(CAN) UNIT STICKS CLOSED INTERMITTENTLY.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000081000024	20000810	00024	CE  	2000	8	10	CA000518015      	1	20000517	G	3260	V3100	SWITCH          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					WIRE CONNECTION	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				J	S	 	WARNING INDICATION        	AFFECT SYSTEMS            		CL	CLIMB          	1			CA								PCE40975			(CAN) DURING CLIMB, THE GEAR WAS SELECTED UP AND THE GEAR DID NOT RETRACT. THE SELECTION WAS ATTEMPTED SEVERAL TIMES WIT	H THE GEAR RETRACTING ON THE LAST SELECTION.  MAINTENANCE FOUND A LOOSE WIRE ON THE EMERGENCY EXTENSION MICROSWITCH LOCA	TED BY THE GEAR TRANSMISSION.  THE CONNECTION WAS RESECURED.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000083000170	20000830	00170	CE  	2000	8	30	CA000518016      	1	20000511	G	5510	04320049	BRACKET         	CESSNA      	043200159   	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RH UP NUTPLATE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			80640					L1942015			(CAN) DURING INSPECTION FOR AD 80-11-04, THE STEEL BRACKET THAT THE SUBJECT NUTPLATES ARE ATTACHED TO WAS FOUND TO BE CR	ACKED.   THE CRACK COMPLETELY ENCIRCLED THE RIGHT UPPER NUTPLATE.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001031200420	20010312	00420	CE  	2001	3	12	CA000518017      	1	20000516	G	3297		WIRE            			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					LT MLG	CUT             	W				A				UNSCHED LANDING         				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) LT MLG HAD NO LIGHT INDICATION. EMERG GEAR USED. BROKEN WIRE AT CR73 LT EQUIPMENT TRAY.						2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2000081000025	20000810	00025	EA  	2000	8	10	CA000519001      	1	20000414	G	2710	C2WA159AWD	BRACKET         	DHAV        	C2WA155A    	DHAV  	DHC2  	DHC2*       	2800108	EA  	WSK   	PZL   	PZL3S       	67204	EU  	WSK	US132	US132000A   	NE  	REAR VERT TUBE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								9502022CS	AO27038		(CAN) WHILE CONDUCTING CF-61-12, AILERON MASS BALANCE WT INSPECTION.  A CRACK WAS FOUND IN SUPPORT BRACKET.						1	H	7	1 	3R	3	R	 	A806    	E18EU	5	C	P4NE	 
2001031200422	20010312	00422		2001	3	12	CA000519004      	4	20000505	G	3417	700700975	COMPUTER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AIR DATA	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			57280	52500				120164	910442		(CAN) NR 2 ADC FAILED DURING TAXI.MULTIPLE INSTRUMENTS FAILED. 						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001031200423	20010312	00423	NE  	2001	3	12	CA000519005      	2	20000515	G	7200	230371302	BEARING         	LYC         	ALF502R5    	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3	FAILED          	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA						LF05461A		LF05461A			(CAN) NR 3 ENGINE BEARING SEAL FAILED. 						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2000072600247	20000726	00247	EU  	2000	7	26	CA000519006      	1	20000502	G	7500	1462502034	LINE            			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BLEED AIR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			69280					841			(CAN) WHEN STARTING, PILOT NOTICED HE HAD TO MOVE POWER LEVER TO ALMOST HALF THROTTLE TO GET ENGINE STARTED.  IN-FLIGHT,	 LACK OF POWER WAS NOT EVIDENT.  UPON LANDING, IT WAS DISCOVERED THE BLEED AIR LINE HAD BROKEN COMPLETELY OFF NEAR THE 9	0 DEGREE FITTING WHERE THE LINE WENT INTO THE COMPRESSOR SECTION OF ENGINE.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001031200424	20010312	00424	EU  	2001	3	12	CA000519007      	1	20000404	G	5302		ATTACH FITTING  			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUSE TO TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9601 					303			(CAN) CRACK FOUND ON THE FUSELAGE TO TAILBOOM ATTACHMENT FLANGE.  CRACK LOCATED (LOOKING FORWARD) AT 2:30 POSITION ON RI	GHT SIDE.  CRACK LENGTH WAS APROXIMATELY 3.5 CM LONG AND ABOUT 2 MM FROM EDGE.  THE TORQUE ON FUS/TAILBOOM ATTACH BOLTS 	WERE UNKNOWN AT THE TIME OF TAILBOOM REMOVAL (RE: CF-93-12R1).				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000083000171	20000830	00171	CE  	2000	8	30	CA000519008      	1	20000515	G	2430	S159660	CIRCUIT BREAKER 	MECHPRODUCTS	MP1601      	CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					INTERNAL	BURNED          	W				D	 	 	 	RETURN TO BLOCK         				B	H	 	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		TX	TAXI/GRND HDL  	1			CA			10973					L4570027A			(CAN) VOLTAGE REGULATOR A WIRE SHORTED TO GROUND.  THE 60 AMP ALTERNATOR CIRCUIT BREAKER SMOKED BUT DID NOT TRIP.  THE M	ANUFACTURING DATE ON THE CIRCUIT BREAKER WAS FEB, 1972. THE CIRCUIT BREAKER WAS REPLACED WITH ONE SUPPLIED IN A CESSNA S	ERVICE KIT.  INTERNAL EXAMINATION SHOWED HEAVY CONTACT MELTING WHILE STILL EXHIBITING CONTINUITY.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2000083000172	20000830	00172	CE  	2000	8	30	CA000519009      	1	20000523	G	2821	07560052	STRINGER        	CESSNA      	07560051    	CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	TUBE AT FUEL INL	MISINSTALLED    	W				O	 	 	 	OTHER                   				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			37980					22292473R	737870		(CAN) AIRCRAFT FUEL STRAINER INSPECTED IAW AD 2000-06-01 EVEN THOUGH THE TECHNICAL RECORDS DID NOT INDICATE THE FUEL STR	AINER TOP ASSY HAD BEEN CHANGED DURING THE SPECIFIED TIME PERIOD.  THE FUEL STRAINER TUBE WAS FOUND TO BE LONGER THAN TH	E SPECIFIED LENGTH, AND WITH A LIGHT PULL THE INLET TUBE WAS PULLED FREE OF THE TOP ASSEMBLY.  THE SUBMITTER STATED THAT	 THE TUBE DID NOT LOOK LIKE AN ORIGINAL PART AND FEELS THAT IT HAD BEEN REPLACED PREVIOUSLY WITH AN UNAPPROVED OR HOME M	ADE PART. THE SUBMITTER ALSO CAUTIONS AGAINST REINSTALLING THE TUBE IN THE TOP ASSY BECAUSE INSERTING THE TUBE TOO FAR C	OULD RESTRICT OR BLOCK OFF THE FLOW OF FUEL INTO THE FUEL STRAINER.	1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2000081000026	20000810	00026	CE  	2000	8	10	CA000519010      	1	20000523	G	5553	2070702	HINGE           	PIPER       	20730       	PIPER 	PA24  	PA24180     	7102402	CE  	LYC   	O360  	O360A1D     	41514	EA  					UP HNG VERT FIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			31270			20730		L369136			(CAN) UPON STRIPING OF THE VERTICAL STABILIZER, A CRACK WAS NOTED IN THE UPPER HINGE. THIS AIRCRAFT HAS THE RUDDER BALAN	CE WEIGHT INSTALLATION.  PIPER KIT NR 760705 INSTALLED MARCH 15, 1973.  THIS AIRCRAFT WAS VANDALIZED BUT NO VISIBLE DAMA	GE TO CONTROL WAS NOTED.  THE CRACK MAY HAVE BEEN A RESULT OF PRE-RUDDER BALANCE FLUTTER OR AN ORIGINAL INSERTION OF THE	 BEARING, NO INDICATION OF OF NEW BEARING INSTALLED.  HINGE REPLACED.			1	L	7	1 	3O	3	O	NT	1A15    	E286				 
2000081000027	20000810	00027	SO  	2000	8	10	CA000519012      	1	20000429	G	5312	4475800	BULKHEAD        	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LWR ATTACH FLANG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			93640			318052048		L236368A			(CAN) THE LEFT AND RIGHT FUSELAGE MOUNTED FORWARD WING SUPPORT BULKHEADS WERE INSPECTED AND FOUND TO BE CRACKED ON THEIR	 LOWER MOUNTING FLANGES.  (P/NS 44758-00 AND 44758-01).					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000081000028	20000810	00028	SO  	2000	8	10	CA000519013      	1	20000429	G	5312	4475800	BULKHEAD        	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LWR ATTACH FLANG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			87070			317752096		L57468A			(CAN) THE LEFT AND RIGHT MOUNTED FWD WING SUPPORT BULKHEADS WERE INSPECTED AND FOUND TO BE CRACKED ON THEIR LOWER MOUNTI	NG FLANGES.  (P/NS 44758-00 L/H & 44758-01 R/H)                                                                         	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031200425	20010312	00425	EA  	2001	3	12	CA000519015      	2	20000510	G	7321	324475315	SHAFT           	PWA         	PT6A50      	DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	FUEL CONTROL	SHEARED         	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			CR	CRUISE         	1			CA				2505 		86194					(CAN) NG AND ITT CLIMED BEYOND MANUFACTURES LIMITS.  FCU FOUND TO HAVE SHEARED SHAFT. 						2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001031200426	20010312	00426	EA  	2001	3	12	CA000519016      	1	20000515	G	2742	6009230165	ACTUATOR        			CNDAIR	CL600 	CL6002A12   	1900304	EA  	GE    	CF34  	CF341A      	 	NE  					PITCH TRIM	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				11200				350146			(CAN) WHILE TAXING TO RAMP PILOT MOVED STAB TRIM TO NOSE DOWN POSITION. CHANNEL 1 NOSE DOWN FAIL LIGHT CAME ON AND ACT W	OULD NOT MOVE. MAINT CHANGED PITCH TRIM ACTUATOR AND RETURNED A/C TO SERVICE. 					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031200428	20010312	00428	NM  	2001	3	12	CA000519018      	1	20000503	G	2612	P34797	CONNECTOR       		GTCP85129   	BOEING	737   	7372E1      	138448F	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU FIRE LOOP	DAMAGED         	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA						P34797		674284			(CAN) AT CRUISE APU FIRE HANDLE  ILLUMINATED AND AUDIBLE FIRE WARNING BELL. FIRE WARNING DRILL AND FIRE WARNING HANDLE W	AS PULLED AND FIRE BOTTLE DISCHARGED.ATC ADVISED AND A/C LANDED SAFELY. APU AREA CLEANED AND INSPECTED. APU DMIDAND FLOW	N FOR REPAIRS. APU FIRE BOTLE AND SQUIB REPLACED. FIRE LOOP PLUG FOUND FAULTY. PLUG REPAIRED AND APU GROUND RUN SERVICEA	BLE. 			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031200429	20010312	00429	EA  	2001	3	12	CA000519019      	1	20000518	G	2710		BEARING         			CNDAIR	CL600 	CL6002B19   	       	EA  										AILERON	STUCK           	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			37990								(CAN) ON APPROACH, PILOT REPORTED THAT EXCESSIVE FORCE WAS REQUIRED TO MOVE AILERONS WITH AN INTERMITTENT LOSS OF ARTIFI	CIAL FEEL. INSPECTION REVEALED THE LEFT REAR QUADRANTS BEARING WAS STIFF.  BOTH QUADRANTS REPLACED.					2	L	7	2 	4F			RT	A21EA   					 
2001031200430	20010312	00430	EA  	2001	3	12	CA000519020      	1	20000518	G	2740	7060883963	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										E/E BAY	MALFUNCTIONED   	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) WHILE INTERCEPTING ILS, STAB TRIM FAIL CAUTION MESSAGE APPEARED. THE A/C WAS STABLIZED. A SYSTEM TEST WAS CARRIED 	OUT, TRIM DID NOT RE-ENGAGE. STAB TRIM WAS IN NOSE DOWN ATTITUDE. WHILE ON APPROACH, EXCESSIVE FORCE WAS REQUIRED TO MAI	NTAIN THE A/C FROM PITCHING DOWN. EMERG WAS DECLARED.  LANDING NORMAL AT FLAPS 20. HSTCU AND HSTA REPLACED. 				2	L	7	2 	4F			RT	A21EA   					 
2001031200431	20010312	00431	EA  	2001	3	12	CA000519021      	1	20000518	G	2420	M832481910	PACKING         			CNDAIR	CL600 	CL6002B19   	       	EA  										NR 2 IDG	CUT             	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKE OFF ROLL, IDG NR  2 CAUTION MESSAGE POSTED AND WENT AWAY, BUT SEVERAL OTHER CAUTIONS POSTED INCLUDING 	WINDSHIELD AND WINDOW HEAT. MAINT FOUND OIL LEAK FROM NR 2 IDG OUTPORT CAUSED BY A CUT O-RING.					2	L	7	2 	4F			RT	A21EA   					 
2001031200433	20010312	00433	NM  	2001	3	12	CA000530002      	1	20000517	G	3097	SFA13M1R0A	WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER HEAT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21790	7691 				120832	860404		(CAN) LT PHASE B PROP HEAT CB POPPING.  BLADE HEAT WIRING BURNED. BLADE REPLACED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000072700239	20000727	00239	SW  	2000	7	27	CA000530010      	1	20000116	G	2810	2120606003E	FUEL LINE       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL CELL	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						608		CPPS61552			(CAN) WHEN REPLACING FLEXIBLE LINES INSIDE THE FUEL CELL, IT WAS NOTED THAT THE BOTTOM OF THE FUEL CELL WAS SPONGY.  IT 	WAS THEN DESCOVERED THAT LAYERS OF RUBBER WERE BREAKING DOWN AND SEPARATING.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000072700240	20000727	00240	EU  	2000	7	27	CA000530011      	1	20000515	G	6720	704A33651003	BEARING         		350A332004  	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	ROUGH           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10040			M1652		382			(CAN)WHILE PERFORMING AN INSPECTION OF THE  TAIL ROTOR PITCH CHANGE SPIDER BEARINGS FOR ROUGHNESS,  DRAG AND TORQUE, (AW	D 1999-085-076(A)R2).  IT  WAS DISCOVERED THAT   BEARING WAS VERY ROUGH AND RATCHETY.  THE AWD IS A REPETITIVE AWD FOR E	VERY 50 HOURS.  MANUFACTURES P/N 60102RS1HT33CA.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2000083000173	20000830	00173	EA  	2000	8	30	CA000530012      	1	20000515	G	6120	KX5116	BETA SWITCH     	HARTZL      		DHAV  	DHC6  	DHC6200     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BETA SWITCH	FAILED          	W				K	 	 	 	NONE                    				N		 	FALSE WARNING             			IN	INSP/MAINT     	1			CA								PCE20768	BUA20758		(CAN) NR 2 ENGINE BETA BACK UNSERVICEABLE, PROPELLER REVERSES WITH NO BLUE LIGHT IN TEST MODE.						1	H	7	2 	3T	3	T	 	A9EA    	E4EA	6	C	P15EA	 
2000083000174	20000830	00174	EA  	2000	8	30	CA000530013      	1	20000602	G	2914	3115818	PUMP            			DHAV  	DHC6  	DHC6100     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  					HYD HAND PUMP	JAMMED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						2801		PCE22476			(CAN) HYDRAULIC HAND PUMP JAMMED.						1	H	7	2 	3T	3	T	 	A9EA    	E4EA				 
2000072800034	20000728	00034		2000	7	28	CA000530014      	4	20000530	G	3414		INDICATOR       			SKRSKY	S76   	S76         	8143010	NE  										AIRSPEED INDICAT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) S76 REQUIRES A NON-STANDARD PITOT PRESSURE TO ACHIEVE CALIBRATION OF THE AIRSPEED INDICATOR.  SUBJECT INDICATOR WA	S FOUND TO BE IN PERFECT CALIBRATION WITH STANDARD PRESSURE APPLIED.  WITH THE RECOMMENDED PRESSURE APPLIED, THE AIRSPEE	D ERRORS WERE WELL IN EXCESS OF THE ALLOWABLE TOLERANCE.				1	G	7	2 	3U			 	H1NE    					 
2000072800035	20000728	00035	NE  	2000	7	28	CA000530015      	2	20000521	G	7314	P94B12208	PUMP            	ZENITH      		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	READS LOW       	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				32000		23455		4510			(CAN) PRIOR TO STARTING AIRCRAFT ENGINE, THE FUEL PRESSURE GAUGE WAS OBSERVED TO BE INDICATING ZERO PRESSURE WITH PUMP S	WITCHED ON.  WHEN LISTENED TO, THE PUMP SEEMED TO BE WORKING, BUT OBVIOUSLY THE ELECTRIC MOTOR WAS NOT ROTATING THE IMPE	LLER, AS PROVEN BY DISCONNECTING AN INLINE FUEL LINE AND OBTAINING NO FUEL FLOW.  TSO ON THE PUMP HAS ONLY 32.1 HOURS, T	HUS EITHER A POOR OVERHAUL OR A FAULTY INTERNAL PART IS SUSPECT. THE PUMP WAS REPLACED WITH A NEWLY OVERHAULED UNIT AND 	THE AIRCRAFT WAS RETURNED TO SERVICE.		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2000072800036	20000728	00036	NE  	2000	7	28	CA000530016      	2	20000510	G	7314	O94B12209	PUMP            	ZENITH      		SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	READS LOW       	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA				89600		20617		4510			(CAN) DURING FLIGHT, THE PILOT NOTICED THE FUEL PRESSURE INDICATING ZERO.  BEING CLOSE TO THE DESTINATION, THE SHORT FLI	GHT WAS COMPLETED WITHOUT INCIDENT.  WITH THE ENGINE SHUT DOWN, NOTICED THE PUMP OPERATION SOUNDED CORRECT WITH THE POWE	R APPLIED, BUT WAS FOUND TO BE PRODUCING NO PRESSURE AND WAS REMOVED.  THE IMPELLER TO MOTOR DRIVE CONNECTION SEEMS TO H	AVE FAILED.  A REPLACEMENT PUMP WAS INSTALLED AND THE ROTORCRAFT RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2000080300043	20000803	00043	WP  	2000	8	3	CA000530017      	1	20000518	G	6310	269A59993	BOOT            			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FAN HOUSING	TORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						S0714		L2660251A			(CAN)WHILE PERFORMING A  POST-FLIGHT INSPECTION, THE PILOT NOTED GREASE ON THE FAN HOUSING (SCROLL ASSY). INSPECTION SHO	WED A TEAR ON BOOT 269A-5473 INSTALLED ON ADAPTER 269A5411.  DRIVESHAFT GREASE HAS LEAKED RADIALLY FROM BOOT.  BOOT STIL	L CONTAINED SUFFICIENT GREASE TO LUBRICATE DRIVESHAFT.				1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2000100300263	20001003	00263	NE  	2000	10	3	CA000530018      	2	20000522	G	7314	AN4100	PUMP            	PWA         		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					SPLINE DRIVESHAF	FAILED          	W				E	C	 	 	ENGINE SHUTDOWN         	ABORTED TAKEOFF         			J	R	 	WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA				77600				415530			(CAN) LOW FUEL FLOW PRESSURE WARNING LIGHT AND INDICATION.  FUEL PUMP REPLACED DUE TO DE-COUPLED SPLINE DRIVESHAFT.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001032900016	20010329	00016	GL  	2001	3	29	CA000530019      	2	20000510	G	7321	321881	ROD             	BENDIX      	NPNZ        	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FCU	STRIPPED        	W				O	 	 	 	OTHER                   				E	X	J	VIBRATION/BUFFET          	ENGINE FLAMEOUT           	WARNING INDICATION        	LD	LANDING        	1			CA				2284 		321881					(CAN) THE THREADS BENEATH THE INNER POSITIONING NUT ON THE INTERCONNECT ROD WHICH LINKS THE CUT OF LEVER (QUADRANT POINT	ER) TO THE MAIN CONTROL SHAFT HAD FAILED. THIS ALLOWED THE FCU CUTOFF LEVER TO MOVE INTO CUTOFF INITIATING AN UNCOMMANDE	D ENGINE SHUTDOWN.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000083000175	20000830	00175	CE  	2000	8	30	CA000530021      	1	20000503	G	2520	551900922	TUBE            	CESSNA      	551901516   	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SEAT BASE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			50790					PCE70400			(CAN) DURING DAILY INSPECTION, THE RIGHT AFT SEAT WAS FOUND IN THE RECLINED POSITION.   PUSHING THE RETRACT BUTTON DID N	OT CAUSE THE SEAT BACK TO RETURN TO THE UPRIGHT POSITION.  MAINTENANCE PERSONNEL FOUND THE UPPER SEAT BASE TUBE CRACKED 	ADJACENT TO THE SEAT BACK PICKUPS.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000081700032	20000817	00032	CE  	2000	8	17	CA000530022      	1	20000402	G	2121		BRUSH HOLDER    	ELECTROMECH 	903840311   	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					NOSE CASE	SHORTED         	W				D	 	 	 	RETURN TO BLOCK         				B	B	 	SMOKE/FUMES/ODORS/SPARKS  	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			38300			1544		PCE25323			(CAN) THE AIRCRAFT HAD BEEN RUNNING FOR 2-3 MINUTES WHEN THE CREW COULD SMELL AND SEE SMOKE.  MAINTENANCE FOUND THE SOUR	CE OF SMOKE CAME FROM THE VENT BLOWER.  FURTHER INVESTIGATION FOUND THE POSITIVE BRUSH HOLD DOWN SPRING TO SHORTING OUT 	TO THE CASE CAUSING THE SPRING TO WELD ONTO IT.  MAINTENANCE ALSO FOUND THE CLEARANCE BETWEEN THE NEGATIVE BRUSH HOLD DO	WN SPRING AND THE CASE TO BE MINIMAL.  THIS CONCERN WAS FORWARDED TO BEECHCRAFT AND THE MANUFACTURER OF THE VENT BLOWER 	(ELECTRO MECH).  A REPORT WAS ALSO SENT TO TRANSPORT SAFETY BOARD.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2000083100901	20000831	00901	EA  	2000	8	31	CA000530023      	1	20000414	G	2710	C6CW10191	ROD             			DHAV  	DHC6  	DHC6100     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  					FLT CNTRL ROD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28137					PCE21168			(CAN) FLIGHT CONTROL ROD FROM BELLCRANK TO AILERON FOUND CRACKED.  ROD REPLACED.						1	H	7	2 	3T	3	T	 	A9EA    	E4EA				 
2000083100902	20000831	00902	CE  	2000	8	31	CA000530024      	1	20000511	G	2120	551530824	DUCT            			CESSNA	500   	500CESSNA   	2076602	CE  										PRESS DUCT	DISCONNECTED    	W				B	 	 	 	EMER. DESCENT           				W	 	 	INADEQUATE Q C            			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT AT FL 280, THE CABIN PRESSURE STARTED TO DECREASE. SHORTLY THEREAFTER A LOUD BANG WAS HEARD	 AND THE CABIN PRESSURE BEGAN TO RAPIDLY DECREASE.  AN EMERGENCY DECENT WAS CARRIED OUT AND THE AIRCRAFT LANDED WITHOUT 	FURTHER INCIDENT.  INVESTIGATION REVEALED THAT THE PRESSURIZATION DUCT DOWNSTREAM OF THE WATER SEPARATOR HAD BECOME DISC	ONNECTED.			1	L	7	2 	4F			 	A22CE   					 
2000083100903	20000831	00903	CE  	2000	8	31	CA000530025      	1	20000530	G	3230	504501033	TORQUE TUBE     			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT LDG	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA								815023R	722156		(CAN) AFTER TAKEOFF, THE CREW NOTICED THAT THE LEFT MAIN GEAR HAD NOT RETRACTED AND THE CREW RETURNED FOR LANDING.  UPON	 INSPECTION, THE LEFT TORQUE TUBE ASSEMBLY WAS FOUND TO BE CRACKED ALONG ITS LENGTH LIKE AN UNWRAPPED PAPER TOWEL CARDBO	ARD TUBE.  THE CRACK APPEARED TO ORIGINATE FROM THE WELD AROUND THE HOLE FOR THE MAIN LANDING GEAR FORK BOLT.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000081700035	20000817	00035	SW  	2000	8	17	CA000530027      	1	20000411	G	3213	31600	AXLE            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320A2D     	41508	EA  					UPPER FWD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L4943227A			(CAN) CRACK FOUND IN BEND JUST BELOW FORWARD UPPER BOLT HOLE                                                            	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	H	7	1 	3O	3	O	NC	A759    	E274				 
2000083100904	20000831	00904	EA  	2000	8	31	CA000530028      	1	20000516	G	6123	7982132002	ECU             	HAMSTD      		DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					ELECT ENG CNTRL	DEFECTIVE       	W				C	 	 	 	ABORTED TAKEOFF         				J	R	 	WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA			15932			88121889		123010			(CAN) AUTO FEATHER ACTIVATED ON TAKEOFF.  FDR REMOVED AND ANALYZED POINTING TO DEFECTIVE  EEC .						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2000083100905	20000831	00905	CE  	2000	8	31	CA000530029      	1	20000516	G	2421	DOFF10300F	ALTERNATOR      			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					LOWER CASE HALF	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				32800				21411772A			(CAN) LOWER CASE HALF WEBS FOUND CRACKED.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001031500144	20010315	00144	NM  	2001	3	15	CA000530030      	1	20000418	G	3242	BACH30A50	LINE            			BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BRAKE ASSY	RUPTURED        	W				O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA								655816			(CAN) NR 2 MAIN WHEEL BRAKE FOUND ON FIRE FOLLOWING ENGINE SHUT DOWN.  HYD BRAKE LINE TO NR 1 BRAKE RUPTURED. LINE AND N	R 1 AND 2 BRAKE REPLACED.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000083100906	20000831	00906	SO  	2000	8	31	CA000530031      	1	20000501	G	3222	67054003	TRUNNION        			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360F    	17025	SO  					SHIMMY DAMPNER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			18500					232766R			(CAN) DURING A 50-HOUR INSPECTION OF THE LANDING GEAR, THE NOSE GEAR TRUNNION WAS FOUND CRACKED AT SHIMMY DAMPENER ATTAC	HMENT POINT.  POSSIBLE CAUSE - OVERSTEER.					1	L	7	1 	3O	3	O	 	2A13    	E9CE				 
2000082200021	20000822	00021	GL  	2000	8	22	CA000530032      	3	20000517	G	6140	503890571	TACH GENERATOR  	HARTZL      		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	DRIVESHAFT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA				14050				PCE50295	EAA1113		(CAN) WHILE IN CRUISE, THE RT PROPELLER INDICATION WENT TO ZERO.  NO ACTION WAS TAKEN, AIRCRAFT WAS RETURNING TO BASE.  	 MAINTENANCE REMOVED TACH GENERATOR AND FOUND DRIVESHAFT ROUNDED OFF.  NEW TACH GENERATOR INSTALLED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P40EA	 
2000083100907	20000831	00907	GL  	2000	8	31	CA000530033      	3	20000517	G	6111		PROPELLER       	MCAULY      	1C160CTM    	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	CAMBER FACE	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			60960			723879		L4121327A	723879		(CAN) CORROSION ON CAMBER AND FACE OF PROPELLER BLADE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000082200022	20000822	00022	SO  	2000	8	22	CA000530034      	1	20000504	G	3260	327	BULB            	GE          		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA								L185661			(CAN) PILOT VERIFIED BURNT RIGHT GEAR BULB USING PRESS-TO-TEST FEATURE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083100908	20000831	00908	NE  	2000	8	31	CA000530035      	2	20000523	G	7261	AS3209018	O-RING          	PWA         	310958701   	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					FILLER OIL STICK	FAILED          	W				A		 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CR	CRUISE         	1			CA			70700					PCEPR0130			(CAN) O-RING ON FILLER NECK STICK WAS DISPLACED AND CAUSED OIL EGRESS.  REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2000090600001	20000906	00001	CE  	2000	9	6	CA000530036      	1	20000530	G	2620	873364	CARTRIDGE       	KIDDE       	8980662     	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SQUIB	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						97688EK		71749			(CAN) AFTER THE FIRE BOTTLE WAS DISCHARGED, THE SQUIB (FIRE BOTTLE CARTRIDGE) WAS FOUND BLOWN APART.  THE SUMITTER SUGGE	STED THAT PERSONNEL OR ADJACENT EQUIPMENT WAS AT RISK OF DAMAGE OR INJURY DUE TO THE EXTERNAL EXPLOSION OF THE SQUIB.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000083100909	20000831	00909	CE  	2000	8	31	CA000530037      	1	20000506	G	3310	A343	CONNECTOR       	CESSNA      		CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	POST LIGHT	BURNED          	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								901223H	728088		(CAN) DURING CRUISE FLIGHT, ONE POST LIGHT CONNECTOR BURNT.   IT APPEARED THAT THE CONNECTOR SPRING BROKE AND CAUSED AN 	ARC, OVERHEATING THE CONNECTOR AND CAUSING SMOKE IN THE COCKPIT.  THE LIGHTING SYSTEM WAS DEACTIVATED AND THE AIRCRAFT R	ETURNED TO BASE.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000083100910	20000831	00910	CE  	2000	8	31	CA000530038      	1	20000504	G	2434	03601018	BEARING         	LUCAS       	2308023     	LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					FRONT BEARING	DISINTEGRATED   	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA			34900	15060		95121		P99334			(CAN) LEFT GENERATOR TRIPPED OFF IN-FLIGHT AND WOULD NOT RESET.  ON INSPECTION, FOUND GENERATOR FRONT BEARING UNSERVICEA	BLE.   REMOVED GENERATOR AND REPLACED WITH O/H UNIT.  VIBRATIONS FELT THROUGHOUT AIRCRAFT WHEN GEN TRIPPED OFF LINE.					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
2000082200023	20000822	00023	CE  	2000	8	22	CA000530039      	1	20000525	G	3246	21406300	BEARING         	CLEVELAND   	04028900    	BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  					CUP SURFACE	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						24772		PCE50392			(CAN) INBOARD BEARING CUPS HAVE BEEN PITTING AND SCRATCHING ON A CONSTANT BASIS.  THIS IS THE ONLY WHEEL TYPE THAT DOES 	THIS IN OUR OPERATION AND OCCURS ONLY ON THE INBOARD SIDE OF THE WHEEL ASSY.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000082200024	20000822	00024	CE  	2000	8	22	CA000530040      	1	20000525	G	3213	50810318605	BOSS            		115810000651	BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  					TORQ KNEE BOSS	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						AMA1135		PCE50392			(CAN) LEFT MAIN GEAR LOWER ASSEMBLY CRACKED AT THE TORQUE KNEE BOSS.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000082200025	20000822	00025	CE  	2000	8	22	CA000530041      	1	20000525	G	5510	1154400313U	BRACKET         	BEECH       	1154400313  	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					WEB HINGE POINT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE51808			(CAN) UPON INSPECTION OF THE HORIZONTAL STABILIZER ATTACH BRACKET, IT WAS DISCOVERED THAT THE CASTING WAS CRACKED IN THE	 WEB BY THE ATTACH HOLES.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000082200030	20000822	00030	CE  	2000	8	22	CA000530043      	1	20000517	G	3297	V3100	WIRE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					WIRE CONNECTION	LOOSE           	W				A				UNSCHED LANDING         				J	S		WARNING INDICATION        	AFFECT SYSTEMS            		IN	INSP/MAINT     	1			CA								PCE40975			(CAN) GEAR WAS SELECTED UP AND THE GEAR WOULD NOT RETRACT. THE SELECTION WAS TRIED SEVERAL TIMES AND FINALLY RETRACTED.A	 LOOSE WIRE WAS FOUND ON THE EMERGENCY EXTENSION MICROSWITCH LOCATED BY THE GEAR TRANSMISSION. THE CONNECTION WAS RESECU	RED.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001031500145	20010315	00145	WP  	2001	3	15	CA000530044      	2	20000525	G	7200		ENGINE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NACELLE	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P44121C	881807		(CAN) CHIP DETECTOR WARNING -  SMALL SLIVER WAS FOUND. A RECENT ENGINE CHANGE HAD TAKEN PLACE. 						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2001031500146	20010315	00146	WP  	2001	3	15	CA000530045      	2	20000502	G	7260		GEARBOX         			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENG ACCESSORY	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			CA								P44727C	881807		(CAN) AIRCRAFT WAS ON TRAINING FLIGHT WHEN THE CAPTAIN NOTICED NO POWER CHANGE WITH LEVER INPUT CHANGE.  ALL PARAMETERS 	WERE NORMAL EXCEPT FOR POWER OUTPUT. ENGINE WAS SHUT DOWN AND RETURNED TO BASE. UPON INVESTIGATION METAL WAS FOUND IN OI	L.THE EXACT CAUSE IS STILL NOT FINALIZED. TWO LOCATING PINS AT THE CENTER BORE OF THE AGB HOUSING WERE WORN. THE PIN BOR	ES WERE ALSO WORN OBLONG AND THE LOCATING PINS COULD EASILY BE REMOVED BY HAND WITH LITTLE RESISTANCE. IT IS POSSIBLE TH	AT THE CONDITION OF THE PINS CAUSED MOVEMENT BETWEEN THE BEARING SUPPORT, BEARING, AGB CASE AND THE IDLER ARM. SUBMITTER	 SPECIFIED A SUPPLEMENTAL SDR WILL BE FILED ALONG WITH THE TEAR DOWN REPORT.	2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2001032900017	20010329	00017		2001	3	29	CA000530047      	4	20000519	G	3421	RCA227	GYRO            			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					COCKPIT	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) SUSPECTED UNAPPROVED PART DETECTED DURING IMPORTATION INSPECTION. UNIT INSTALLED: SEPT 10 1999 INVESTIGATION IN PR	OGRESS BY NEW OWNER. INVESTIGATION INTO DISCREPANCIES BETWEEN THE INSTALL AND PURCHASE DATES. FOLLOW UP BY PAH-HAM IN PR	OGRESS				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001031500147	20010315	00147	CE  	2001	3	15	CA000530048      	1	20000502	G	3246	13600LA902A1	BEARING         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					MAIN WHEEL	FAILED          	W				L	D			ABORTED APPROACH        	RETURN TO BLOCK         			D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA								PCE32130			(CAN) NR 4 MAIN WHEEL DISLODGED FROM ITS AXLE IN FLIGHT.  NO OTHER APPARENT DAMAGE TO GEAR OR AIRFRAME.THE BRAKES AND TI	RES ON THIS AXLE WERE REMOVED AND REPLACED JANUARY 06, 2000.  NR 4 MAIN WHEEL HAS NOT BEEN LOCATED. SUPPLEMENTAL: RECORD	S INDICATE NEW BEARING INSTALLED ONTO NR 4 WHEEL ASSY.  TOTAL TIME ON BEARING, 367 CYCLES. FURTHER FOLLOW UP INDICATES T	HE FORMER HAVING THE SAME PART NUMBERS INSTALLED ONTO NR 4 WHEEL ASSY. TOTAL TIME ON THIS BEARING WAS 2036 CYCLES FROM F	EB 28/97 TO MAY 20/00.  ALTHOUGH BOTH BEARINGS ARE THE SAME PART NUMBER, THERE IS NO INDICATION AS TO WHAT POSITION THEY	 ARE INSTALLED INTO DURING WHEEL ASSY. BUILD UP.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2000101000336	20001010	00336	EU  	2000	10	10	CA000530049      	1	20000512	G	3250	5322012276	STOP            			PILATS	PC12  	PC1245      	       	EU  										LEFT SUPPORT ARM	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			79300								(CAN) NOSE GEAR TURN LIMIT STOP INDICATOR FOUND CRACKED ON THE LEFT SUPPORT ARM.						1	L	7	1 	3T			RT	A78EU   					 
2001011104661	20010111	04661	EU  	2001	1	11	CA000530050      	1	20000512	G	2510	5251512026	COVER           			PILATS	PC12  	PC1245      	       	EU  										SEAT BASE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			79300								(CAN) AFT COVER PLATE ON SEAT BASE WAS FOUND CRACKED AT THE MOUNTING HOLES. 						1	L	7	1 	3T			RT	A78EU   					 
2001031500148	20010315	00148	NM  	2001	3	15	CA000530051      	1	20000517	G	2150	6806404	ACM             			BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					LEFT	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								30863			(CAN) CREW UNABLE TO CONTROL FLIGHT DECK, LT AIR CYCLE MACHINE SEIZED, SENT TO SHOP FOR REPAIR AND REPORT.						2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001031500149	20010315	00149	WP  	2001	3	15	CA000530053      	1	20000521	G	2120	958132	CHECK VALVE     			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					AIR DUCTING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								10217			(CAN) NO FLOW WAS COMING OUT OF  NR 3 PACK. WHEN REMOVING NR 3 PACK CONTROL VALVE, FOUND PART OF A CHECK VALVE STUCKED I	NSIDE THE PACK VALVE. AFTER INVESTIGATION, FOUND 2 PIE SHAPE SEGMENTS MISSING OF THE APU DISCHARGED CHECK VALVE. PNEUMAT	IC SYSTEM DUCTS INSPECTED AT MOST PROBABLE AREAS AND NO PART FOUND. ALL PACK CONTROL VALVES, AIR CLEANERS. APU DISCHARGE	 VALVE REPLACED AND PNEUMATIC SYSTEM CHECK SERVICEABLE. DUE TO THE FACT THAT ALL SYSTEM OPERATE NORMALLY AND THE MISSING	 PART WAS UNFINDABLE, SUSPECT THAT THE PART WAS PREVIOUSLY REMOVED FROM THE SYSTEM DURING PREVIOUS MAINTENANCE, AIRCRAFT	 RETURNED TO SERVICE.	2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001031500150	20010315	00150	EA  	2001	3	15	CA000530055      	1	20000524	G	7931	601509197	TRANSDUCER      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					OIL PRESSURE	INOPERATIVE     	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) OIL PRESSURE TRANSDUCER WAS INOPERATIVE, GIVING FALSE LOW  PSI READING.  NO EICAS SYSTEM WARNING PRESENT. 						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031500151	20010315	00151	EA  	2001	3	15	CA000530056      	1	20000530	G	2612	356024310	FIRE LOOP       			CNDAIR	CL600 	CL6002B19   	       	EA  										LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER T.O. EICAS WARNING 14TH STAGE DUCT APPEARED. LT ENGINE WAS SHUT DOWN IN FLIGHT. A/C RETURNED TO LAND	. LT ENG 14TH STAGE HEAT SENSING ELEMENT REPLACED. 					2	L	7	2 	4F			RT	A21EA   					 
2001031500152	20010315	00152	EA  	2001	3	15	CA000530057      	1	20000530	G	2916		RESERVOIR       			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	FAILED          	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) ON RETURN FROM FLIGHT, NR 2 HYD RES SYSTEM WAS OBSERVED AT 20 PERCENT QUANTITY CONTINUED TO DECREASE UNTIL LOW PRE	SSURE MESSAGE WAS DISPLAYED. 					2	L	7	2 	4F			RT	A21EA   					 
2001031500156	20010315	00156	NM  	2001	3	15	CA000530062      	1	20000507	G	2910	41010029	POWER UNIT      			AIRBUS	A319  	A319114     	       	NM  										HYD SYSTEM	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) LOSS OF YELLOW SYSTEM HYD. SYS FLUID. POWER TRANSFER UNIT DEACTIVATED. INVESTIGATION REVEALED PTU LEAKING AT QUICK	 DISCONNECT. SEALS REPLACED. 					2	L	7	2 	4F			RT	A28NM   					 
2001031500157	20010315	00157	NE  	2001	3	15	CA000530063      	2	20000501	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								807154			(CAN) NOT ABLE TO DUPLICATE SNAG, NO FAULT FOUND. 						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031500163	20010315	00163	NM  	2001	3	15	CA000530070      	1	20000427	G	5610	141T48011	WINDOW          			BOEING	767   	767209      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA								P709688			(CAN) DURING CRUISE AT FL 360 FIRST OFFICER WINDOW OUTER PANE FAILED. CREW COMMENTED ARCING ON WINDSCREEN. WINDOW AND CO	NTROLLER REPLACED. 					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001031500164	20010315	00164	NM  	2001	3	15	CA000530071      	1	20000518	G	2572	732591A	FAN             			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					E/E BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA								P707531			(CAN)  ELECTRICAL BURNING SMELL IN COCKPIT DURING APPROACH, ELECTRICAL COOLING SWITCH SELECTED TO OVERIDE SMELL DISSIPAT	ED. NR 1 EQUIPMENT COOLING VAN SOURCE OF SMELL AND GRINDING DURING ROTATION. CHANGED. 					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001031500165	20010315	00165	NM  	2001	3	15	CA000530072      	1	20000427	G	2933	851307683020	SWITCH          			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					INDICATOR	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								P724359			(CAN) CENTER HYD PUMP FAILED IN CRUISE ELECTRICAL BURN SMELL IN COCKPIT, SMOKE EVIDENT, PUMP SHUT OFF, SMOKE DISSIPATED.	 SWAPPED C1 AND C2 DELAY MODULE AND CHANGED C1 LIGHT SWITCH. ON CLIMB THERE WAS A BURNING SMELL, C1 HYD SYSTEM SHUT DOWN	 A/C DIVERTED. FOUND C1 SWITCH LIGHT AND C2 DELAY MODULES BURNT. NEW TIME DELAY INSTALLED AND C2 POSITION SWAPPED FOR RE	CIRC FAN SWITCH. 			2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001031500166	20010315	00166	NM  	2001	3	15	CA000530073      	1	20000517	G	2910		LINE            			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					HYDRAULIC SYS	RUPTURED        	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA								P716610			(CAN) ON LANDING CENTER HYD SYSTEM FLUID DROPPED TO ZERO. PRESSURE LINE FROM CENTER HYD SYS PUMP RUPTURED. LINE REPLACED	, SYS SERVICED AND LEAK CHECK OK. 					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2000073100044	20000731	00044	CE  	2000	7	31	CA000530074      	1	20000518	G	2750		WIRE            			CESSNA	500   	S550        	2076607	CE  										CENTER CNTR	CHAFED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			47260								(CAN) DURING CLIMB, THE FLAP CONTROL CIRCUIT BREAKER TRIPPED AS THE FLAPS WERE BEING RETRACTED.  THE BREAKER WAS RESET A	ND IT TRIPPED AGAIN. THE FLIGHT WAS CONTINUED WITH THE FLAPS PARTIALLY EXTENDED.  MAINTENANCE PERSONNEL FOUND THE FLAP C	ONTROL CIRCUIT WIRING WAS CHAFED AND SHORTING WHERE THE WIRES ARE ROUTED THROUGH THE RIGHT HAND WING FAIRING (APPROX WS 	100.00, ZONE 612 AND 622).			1	L	7	2 	4F			RT	A22CE   					 
2001031500167	20010315	00167	EA  	2001	3	15	CA000530075      	1	20000511	G	3246	C3US1563	BOLT            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					AT SHEAR POINT	BROKEN          	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA			158  								(CAN) DURING TAKEOFF RUN, A SOUND WAS HEARD OUTSIDE THE AIRCRAFT.  THE PASSENGER IN RIGHT SEAT NOTED RIGHT SKI WAS TIPPE	D FORWARD AMD HANGING BY CHECK CABLE.  LANDING WAS CARRIED OUT AND RESULTED IN SKI DIGGING IN FRONT AND CUTTING THE REAR	 GEAR ATTACHMENT STRUT. 				1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000082800016	20000828	00016	CE  	2000	8	28	CA000606003      	1	20000601	G	2824	13341511	VALVE           			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					OPERATOR MOTOR	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				A	 	 	FLAME/FIRE                			CR	CRUISE         	1			CA			18651					P27223C			(CAN) DURING CRUISE, THE CREW STARTED TO TRANSFER TIP FUEL WITH NO PROBLEM.  WHEN THE CREW SELECTED TIP TRANSFER OFF, TH	E RT TIP TANK CONTINUED TO FLOW UNTIL TIP TANK PRESSURE WAS EXHAUSTED.  THIS CAUSED ABOUT A 15 GALLON FUEL IMBALANCE BET	WEEN THE TIP TANKS (RT LIGHTER).  DURING LANDING AND TAXI WITH A FULL MAIN TANK AND THE LEFT WING LOW DUE TO THE FUEL IM	BALANCE, A SMALL AMOUNT OF FUEL PASSED BY THE SNORKLE CHECK VALVE AND ACCUMULATED IN THE VENT SYSTEM, WHICH DRAINED ONTO	 THE GROUND SLOWLY AFTER THE AIRCRAFT WAS PARKED.  THE VALVE WAS REPLACED WITH A SERVICEABLE VALVE AND THE AIRCRAFT RETU	RNED TO SERVICE.	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
2000073100045	20000731	00045	CE  	2000	7	31	CA000606006      	1	20000527	G	2730	115610010325	TORQUE TUBE     			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					TAPER PIN HOLES	WORN            	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			57800					PCE50050			(CAN) AUDITOR INSPECTION OF AIRCRAFT NOTICED LOOSE ELEVATOR TORQUE TUBES.  FOUND LEFT ELEVATOR TORQUE TUBE HOLES WORN BE	YOND LIMITS.  EXAM OF HOLES NOTED HOLES NOT ROUND, APPEARED THAT FACTORY REAMER CHATTERED MAKING LEDGES IN HOLE.  ALSO N	OTED FACTORY INSTALLED TAPER PINS ALREADY BEYOND LIMITS OF PROTRUSION.  RAYTHEON CONTACTED.  TORQUE TUBE ASSEMBLY REPLAC	ED.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000101000337	20001010	00337	CE  	2000	10	10	CA000606007      	1	20000520	G	5753	052390113	SUPPORT BRACKET 	CESSNA      	052390138   	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	BEHIND BRG ROLLE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			26650					355524	771797		(CAN) WEAR WAS FOUND WHERE ROLLER IS ATTACHED TO THE FLAP SUPPORT RIB.  BEARING MUST BE REMOVED TO INSPECT.  FOUND WORN 	OVER 1/3 THROUGH FLAP SUPPORT RIB, IN NICE CIRCLES CAUSED BY BEARING/ROLLER ITSELF. THIS THE 2ND CASE SUBMITTER HAS SEEN	.				1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
2000071800200	20000718	00200	GL  	2000	7	18	CA000606009      	2	20000521	G	7260	6890914	BEARING         	ALLSN       	6894171     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SUPP ADAPTR GEAR	WORN            	W				A	 	 	 	UNSCHED LANDING         				D	P	 	INFLIGHT SEPARATION       	NO WARNING INDICATION     		CR	CRUISE         	1			CA			49420			CAG34043		CAE801640BA			(CAN) WHILE IN-FLIGHT, THE PILOT COULD HEAR A LOUD METALLIC SCREAMING GRINDING NOISE FROM THE ENGINE.  HE LANDED AT A CL	EARING AND SHUT DOWN ENGINE.  THE ENGINE GEARBOX HAD QUICK DISCONNECT CHIP PLUGS, PULLED THE CHIP DETECTORS AND FOUND FE	RROUS METAL ON THE OUTER PERIMETER, BUT NO CHIPS CROSSING ONTO THE CENTER PROBE TO GIVE THE PILOT A CHIP LIGHT ON THE IN	STRUMENT PANEL.  THE SYSTEM WAS INSPECTED FOR LIGHT INDICATION AND FOUND SERVICEABLE. GEARBOX TSN 11,413.5 HOURS. TIME S	INCE LAST MAJOR INSPECTION 4941.9 HOURS.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001031500170	20010315	00170	EU  	2001	3	15	CA000606010      	1	20000602	G	2742	1TW18	SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  										STAB ACTUATOR	OUT OF RIG      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) PILOTS NOTICED OUTBOUND OF YXE. THAT THE HORIZONTAL STAB TRIM WHEEL WAS UNABLE TO BE ADJUSTED. THE CREW DECIDED TO	 RETURN  AND AT THAT TIME THEY REALIZED THAT THE UTILITY AND FLIGHT CONTROL SYSTEM STAB CAUTION LIGHTS WERE ON - INDICAT	ING NO HYDRAULIC POWER TO THE STAB. AS PER THE PILOTS CHECKLIST, THE CREW MANUALLY SELECTED THE STAB SWITCHES OFF AND TH	EN PROCEEDED TO USE THE STAB VIA THE ALTERNATE STAB ELECTRIC SWITCH. THE AIRCRAFT RETURNED& LANDED WITHOUT INCIDENT. MAI	NTENANCE INSPECTION FOUND THE HORIZONTAL STAB STICKING SWITCH OUT OF RIG. MAINTENANCE RE-RIGGED THE SWITCH & CHECKED IT 	AS SERVICEABLE. TEST FLIGHT WAS COMPLETED & CHECKED OK.	2	L	7	2 	4F			RT	A20EU   					 
2001031500171	20010315	00171	EU  	2001	3	15	CA000606011      	1	20000604	G	2612	30262A18A19	SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FIRE DETECTION	INTERMITTENT    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								9077			(CAN) PILOTS REPORTED THAT ON HEAD START DEPARTURE OUT OF YVR, THE NR 1 ENGINE FIRE DETECT SYSTEM WOULD NOT TEST. MAINTE	NANCE WAS CALLED OUT TO THE AIRCRAFT AND FOUND THAT THE PROBLEM TO BE THE TEST SWITCH. THEY SPRAY CLEANED THE SWITCH & I	T TESTED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE HOWEVER ON THE OUTBOARD LEG THE FIRE DETECT SYSTEM WOULD NOT TEST ONC	E AIRBORNE. CREW ELECTED TO RETURN TO YVR & LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE NR 1 FIRE WARNING TEST SWI	TCH, P/N 3026218A9, & TESTED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.		2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2000080800016	20000808	00016	GL  	2000	8	8	CA000606012      	1	20000526	G	7900		ENGINE          	ROTAX       		DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			13380					4412605			(CAN) ENGINE OIL PRESSURE WENT FROM 60 PSI TO 32 PSI AFTER TAKEOFF WHEN THE AIRCRAFT WAS LEVELED OFF FOR CRUISE.  PILOT 	RETURNED AND LANDED SAFELY.  ENGINE HAS BEEN GROUND RUN TWICE AND CHECKED.  COULD NOT DUPLICATE ON GROUND.  AIRCRAFT RET	URNED TO SERVICE.  NO FURTHER REPORTS.				1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2000073100046	20000731	00046	CE  	2000	7	31	CA000606013      	1	20000531	G	3230		LANDING GEAR    			BEECH 	100   	B100        	1152919	CE  										GEAR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	O	 	WARNING INDICATION        	OTHER                     		TO	TAKEOFF        	1			CA											(CAN) PILOT SELECTED GEAR UP AFTER TAKEOFF WITH NO GEAR RESPONSE.  PILOT CHECKED CONTROL AND POWER CIRCUIT BREAKER AND R	ECYCLED GEAR, NO RESPONSE.  EMERGENCY GEAR EXTENSION AND LANDING C/O-NORMAL.  AIRCRAFT PLACED ON JACKS, NO POWER TO GEAR	 MOTOR.  AFTER APPROX. 20 MINUTES, GEAR POWER C/B (60 AMP) RESET AND HEARD TO CLICK GEAR FUNCTION NORMAL.  NO FAULT FOUN	D - NOTE - PILOT HANDBOOK ELECTRIC LOAD LIMITS LIST GEAR MOTOR AT 140 AMPS.  AMP TEST OF AIRCRAFT WHEN GEAR CYCLING.  75	 AMPS NOMINAL TO 120 AMPS PEAK.		1	L	7	2 	4T			 	A14CE   					 
2000080900004	20000809	00004	EA  	2000	8	9	CA000606014      	2	20000228	G	8530		CYLINDER        	LYC         		CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LT FWD NR 2 CYL	FAILED          	W				A	B	 	 	UNSCHED LANDING         	EMER. DESCENT           			R	K	 	PARTIAL RPM/PWR LOSS      	FLUID LOSS                		CL	CLIMB          	1			CA				16000				L909339A	83414		(CAN) AIRCRAFT IN-FLIGHT, OVER LETHBRIDGE CLIMB-OUT.  BIG BANG, NR 2 CYLINDER EXITED LEFT COWL, OIL ALL OVER.  PILOT LAN	DED AIRCRAFT AT LETHBRIDGE.  ENGINE MADE ENOUGH POWER TO GET AIRCRAFT TO AIRPORT.  CYLINDER NOT FOUND.  SMALL PART OF PI	STON, RINGS, HYDRAULIC LIFTER, FOUND IN COWL,  NO PISTON PIN FOUND.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001011104700	20010111	04700	EU  	2001	1	11	CA000606017      	1	20000531	G	7921	5791012038	STRUT           	PWA         		PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					CLEVIS END	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			25950					PCEPR0090			(CAN) THE HOLES IN THE FLAP STRUT ON THE CLEVIS END ARE ELONGATED.  THIS STRUT OPENS THE OIL COOLER DOOR WHEN THE GEAR I	S EXTENDED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2000080900005	20000809	00005	CE  	2000	8	9	CA000606018      	1	20000531	G	3246	16218000	WHEEL           	CLEVELAND   	40289       	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					BEAD AREA	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			24900			14532		PCE40209			(CAN) WHEEL FOUND CRACKED IN THE BEAD AREA ON THE 3RD TIRE CHANGE CYCLE.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000080900006	20000809	00006	CE  	2000	8	9	CA000606019      	1	20000601	G	3246	04028900A	WHEEL           	CLEVELAND   	16118000    	BEECH 	100   	A100C       	1152917	CE  	PWA   	PT6   	PT6A28      	 	EA  					BEAD AREA	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						15142		PCE40919			(CAN) WHEEL HALF FOUND CRACKED IN BEAD AREA DURING LPI.  THIS RIM ASSEMBLY WAS ON ITS 23RD TIRE CHANGE.						1	L	7	2 	4T	4	T	 	A14CE   	E4EA				 
2000080900007	20000809	00007	CE  	2000	8	9	CA000606020      	1	20000601	G	3260	V31001	SWITCH          	BEECH       	115810052   	BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  					TERMINAL	LOOSE           	W				O	 	 	 	OTHER                   				J	S	 	WARNING INDICATION        	AFFECT SYSTEMS            		CL	CLIMB          	1			CA								PCE41919			(CAN) LANDING GEAR WOULD NOT RETRACT.  THERE WAS NO IN TRANSIT LIGHT ON AND THE THREE GREEN DOWN AND LOCKED POSITION LIG	HTS REMAINED ON.  A LOOSE WIRE WAS FOUND ON THE EMERGENCY EXTENSION SAFETY SWITCH PREVENTING THE GEAR FROM RETRACTING BY	 REMOVING ALL POWER TO THE MOTOR.  WIRE SECURED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000101000338	20001010	00338	EA  	2000	10	10	CA000606021      	1	20000514	G	2711	C6CW108727	CONTROL ROD     	DHAV        		DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FROM RIVET HOLE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						382		PCE40329			(CAN) DURING INSPECTION THE SERVO TAB LINK FOR THE AILERON WAS FOUND CRACKED AT THE UPPER END. THE CRACK EXTENDED FROM T	HE ROD END BEARING RETENTION RIVET HOLE TO THE END OF THE ROD.  FOR REFERENCE SEE DEHAVILLAND IPC 27-10-00, FIG. 5 (SHEE	T 1 OF 1), ITEM 90.  THE ROD WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2000101000339	20001010	00339	EA  	2000	10	10	CA000606023      	1	20000605	G	3246	AN4424	BOLT            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					EYE PORTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE40906			(CAN) INSPECTION OF CANOE RACK FOR LOOSENESS FOUND EYE BOLT HEAD SLIGHTLY BENT WITH CRACK ON FORWARD FACE.  EYE BOLT REP	LACED.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001011104701	20010111	04701	EU  	2001	1	11	CA000606024      	1	20000525	G	7712	5771112105B	LINE            			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					TRANSDUCER	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			57400					PCEPR0141			(CAN) TORQUE TRANSDUCER AND OIL SUPPLY LINES MEET.  DETERMINED THAT LINE 577.11.12.105B AT TQ LIMITER CONNECTION WAS LOO	SE.  IT SURMISED THAT BY MULTIPLE CONNECT/RE-CONNECT AT 'T', BENDING AND POTENTIAL FOR MOVEMENT OF ENTIRE PLUMBING BUNDL	E, LACK OF TORQUE APPLIED AT TQ LIMITER NUT CONNECTION, CAUSED BREACH AND RESULTED IN LEAK. TIGHTENING OF NUT AND SUBSEQ	UENT GROUND RUNS AND TEST FLIGHT SHOWED NO FURTHER SIGNS OF OIL LEAKAGE.  MORE THOROUGH POST INSP ENGINE GROUND RUN WILL	 BE INCORPORATED.  SUGGESTION :  BENDING POTENTIAL IS GREAT, CONSIDERING LINES ARE OF COMBINED RIGID AND FLEXIBLE DESIGN	.  IT WOULD BE ADVANTAGEOUS TO INCORPORATE TEE FIT ING AND SAFTIED CAP FOR PURPOSE OF ATTACHMENT.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2001032900018	20010329	00018	GL  	2001	3	29	CA000606026      	3	20000425	G	6112	9598901035	BOOT            			PILATS	PC12  	PC1245      	       	EU  						HARTZL	HCE4A	HCE4A3D     	GL  	LT STAB	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON PRE-FLIGHT THE PILOT NOTICED THE BOOT HAD BECOME UNGLUED ON THE TOP FOR ABOUT TWO FEET. HE ADVISED THE ENGINEER	 & BOOT WAS REGLUED UNTIL A NEW BOOT COULD BE ORDERED. WHEN NEW BOOT ARRIVED THE OLD BOOT WAS PEELED OFF AND NEW ONE INS	TALLED. THE OLD BOOT WAS NOT STUCK DOWN VERY WELL AND WAS EASY TO PEEL OFF.				1	L	7	1 	3T			RT	A78EU   		5	C	P210NE	 
2001032900019	20010329	00019	EU  	2001	3	29	CA000606027      	1	20000606	G	2752	951D10011	ACTUATOR        			PILATS	PC12  	PC1245      	       	EU  										TE FLAPS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			17800								(CAN) ON INSPECTION OF BACKLASH CHECK UNITS WORN BEYOND LIMITS ON THREE OUT OF FOUR ACTUATORS. THEY ALL HAVE THE SAME CY	CLES AND HOURS ON THE UNITS.					1	L	7	1 	3T			RT	A78EU   					 
2001032900020	20010329	00020	EU  	2001	3	29	CA000606028      	1	20000414	G	5753	951D10011	ACTUATOR        			PILATS	PC12  	PC1245      	       	EU  										TE FLAPS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			26000								(CAN) ON INSPECTION THE BACKLASH WAS BEYOND LIMITS.						1	L	7	1 	3T			RT	A78EU   					 
2001031500175	20010315	00175	GL  	2001	3	15	CA000606030      	3	20000526	G	6114	A2043	NUT             													HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									CH20345		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. REPLACED 10 OUT OF 10 NUTS. 																5	C	P920	 
2000072800037	20000728	00037	EU  	2000	7	28	CA000606031      	1	20000526	G	2612	B232M	FIRE DETECTOR   			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LOOSE           	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA								CAE835650			(CAN) #1 FIRE WARNING LIGHT CAME ON IN CRUISE FLIGHT. PILOT RETARDED THROTTLE TO IDLE & RETURNED TO BASE. AIRCRAFT INSPE	CTED LOOSE WIRE ON DETECTOR FOUND, WIRE (MEET) TORQUED SYSTEM CHECKED & FOUND SERVICEABLE, AIRCRAFT RETURNED TO SERVICE.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2000080900008	20000809	00008	SO  	2000	8	9	CA000606032      	1	20000525	G	3213	4028800	TRUNNION        			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					REINFORCEMNT RIB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			79530					PCE92353			(CAN) DURING INSPECTION, A CRACK WAS FOUND ON THE AFT RIGHT MAIN LANDING GEAR TRUNNION ASSEMBLY.  THE CRACK WAS FOUND TO	 BE ON THE UPPER REINFORCEMENT RIB.  THE PART WAS REPLACED WITH NEW.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2000080900009	20000809	00009	GL  	2000	8	9	CA000606033      	3	20000531	G	6111	900CB8	BLADE           	MCAULY      	C2A34C204   	CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	L/E & FACE	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				87400		831059		470465	831059		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  BLADES TRIMMED, ALODINED, PAINTED.						1	L	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2000080900010	20000809	00010	GL  	2000	8	9	CA000606034      	3	20000606	G	6111		PROPELLER       	MCAULY      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	LEADING EDGE	ERODED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			11790					L4029827A	724384		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000080900011	20000809	00011	EA  	2000	8	9	CA000606035      	2	20000515	G	7310	3026779	TUBE            	PWA         		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					AFT B NUT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA				26060				PCE80073			(CAN) AFTER TAKEOFF, FUEL VAPOR SMELL IN CABIN, SHUT OFF BLEED AIR, SMELL WENT DOWN.  AIRCRAFT RETURNED TO YQB.  FOUND F	UEL PRESSURE TUBE ASSY CRACKED JUST AFT OF B-NUT.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000100300072	20001003	00072	SO  	2000	10	3	CA000606036      	2	20000526	G	8520	5A10204	EXHAUST VALVE   	CONT        		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					STEM	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				R	E	 	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			CA			13640					621372AR			(CAN) IN-FLIGHT, THE ENGINE WAS RUNNING ROUGH.  NR 3 CYLINDER SPARK PLUGS FOUND BROKEN.  NR 3 CYLINDER MOVED AND REPLACE	D BY OVERHAULED ONE (EXHAUST VALVE FOUND BROKEN).					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001011104721	20010111	04721	EA  	2001	1	11	CA000606037      	1	20000530	G	5610	C2F249	STRUCTURE       	DHAV        		DHAV  	DHC3  	DHC3        	2800202	EA  										WINDSCREEN SEAT	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			18798			135					(CAN) WINDSCREEN SEAT CLEANED AT REPLACEMENT.  INSPECTED PER SB 3/29.CORROSION FOUND AS INDICATED IN SB. 0.250 INCH HOLE	S FOUND AT LOWER AREA OF DOOR POST.  NEW REPLACEMENTS WILL BE INSTALLED.					1	H	7	1 	3R			 	A815    					 
2001031500176	20010315	00176	WP  	2001	3	15	CA000614001      	1	20000525	G	2434	G3004BM1	GENERATOR       			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	LT ENGINE	DESTROYED       	W				H				DEACTIVATE SYST/CIRCUITS				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA				14   				PC10164C	196156		(CAN) LT ENGINE GEN FAILURE LIGHT CAME ON & GEN SELECTED OFF. WHEN A/C SLOWED FOR LDG SMOKE OBSERVED IN COCKPIT. ELECT. 	SYS WERE SHUT OFF & SMOKE DISSIPATED. UPON INVESTIGATION FOUND THAT GENERATOR HAD SHEARED OFF ALL OF MOUNTING STUDS WITH	 GEN LYING IN BOTTOM OF ENGINE COWLS. GEN REMOVED & RETURNED TO CONAIR, ABBOTSFORD FOR FURTHER INVESTIGATION. GEN SHAFT 	SHEARED & END-BEARING P/B JH 203-10 FOUND DESTROYED . GEN ELECTRICAL WIRING SECURED & ENGINE GROUND RUN COMPLETED.ENGINE	 FUNCTION TESTED SATISFACTORILY. ENGINE FILTER CHECKED FOR CONTAMINANTS - NONE FOUND. ELECT. WIRING CHECKED FOR DAMAGE -	 WIRING REPD/REPL, AS NECESSARY.	2	H	7	2 	4R	4	R	 	A25WE   	E259	6	C	P8879	 
2001031500177	20010315	00177		2001	3	15	CA000614002      	4	20000517	G	2565	D31022102	SLIDE           			AIRBUS	310   	A310304     	       	EU  										OVERWING	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			30037	2722 							(CAN) AIRCRAFT 204, MAY 17/2000, TRENTON, LOG SEQUENCE 0511852. DURING SCHEDULED TEST DEPLOYMENT OF RT OVERWING SLIDE, I	T FAILED TO DEPLOY. SLIDE WAS DEPLOYED BY FURTHER ACTUATION OF AUTOMATIC CABLE. SLIDE DID NOT FULLY INFLATE.  					2	L	7	2 	4F			RT	A35EU   					 
2001031500178	20010315	00178	NM  	2001	3	15	CA000614003      	1	20000602	G	3244	26010452	TIRE            			BOEING	737   	7372T2      	1384491	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					MLG	SEPARATED       	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			9162 	324  				709382			(CAN) ON ROTATION, STRONG VIBRATION FELT FROM NOSE GEAR. TOWER ADVISED, PIECES OF RUBBER AND METAL FOUND ON RUNWAY AFTER	 TAKEOFF. RETURNED TO RAMP. REPLACED BOTH NOSE WHEEL ASSEMBLIES DUE LT NOSE WHEEL TIRE TREAD HAD SEPARATED. LT NOSE SKI 	TO WHEEL SEAL RETAINER MISSING. OFF CANADIAN PART NUMBERS, LT WHEEL & TIRE 7-3241-9-0022 S/N 0315, ON S/N 2169. RT WHEEL	 & TIRE 7-3241-9-0022 S/N 3687, ON S/N 0203. WHEELS & TIRES REPLACED AS PER WORK CARD 4147. TRIMMED SEAL AND REMAINING S	EAL RETAINER. OVERWEIGHT LANDING INSPECTION COMPLETED AS PER WORK CARD 4041. AIRCRAFT OK FOR SERVICE.		2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001031500179	20010315	00179	NM  	2001	3	15	CA000614004      	1	20000608	G	3230	106122615	SENSOR          			BOEING	737   	737275C     	       	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	OUT OF TOLERANCE	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								687895			(CAN) ON TAKEOFF, LANDING  GEARS WOULD NOT RETRACT WITHOUT USING GEAR OVERRIDE. AIRCRAFT RETURNED. LANDING GEAR ACCESSOR	Y MODULE REPLACED AS PER WORK CARD 4281. OFF CANADIAN PART 7-326-9-0010 SERIAL 0054, ON SERIAL #0438. FURTHER TROUBLESHO	OTING FOUND AIR SENSOR OUT OF TOLERANCE. SENSOR ADJUSTED AS PER MM 32-09-200, PAGES 501. GEAR SWING ACCOMPLISHED AND CHE	CKED OK. 			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000080900003	20000809	00003	CE  	2000	8	9	CA000614005      	1	20000607	G	7603	016A43298	NUT             			MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316252M 	01514	NE  					POWER LEVER	LOOSE           	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			11099					P33087C			(CAN) INVESTIGATION REVEALED THE P/N 016A-43298 LT-RT THREADED ADJUSTMENT ROD ON THE POWER  LEVER ATTACHMENT TO THE ENGI	NE, HAD COME LOOSE AND HAD MOVED, CAUSING A POWER LEVER MISMATCH.  IT IS ASSUMED THAT THE LOCKNUTS WERE NOT SUFFICIENTLY	 TORQUED FOLLOWING ADJUSTMENT.  NO FURTHER PROBLEM WAS FOUND. THE POWER LEVER WAS RE-RIGGED AND LOCKNUTS TORQUED, ENGINE	 GROUND RUN OK AND RETURNED TO SERVICE.			1	H	7	2 	3T			RT	A10SW   	E2WE				 
2001031500180	20010315	00180	EU  	2001	3	15	CA000614007      	2	20000515	G	7200		ENGINE          			FOKKER	F27   	F27MK400    	4990626	EU  	RROYCE	DART  	DART5327    	54509	EU  					NACELLE	FAILED          	W				C	E			ABORTED TAKEOFF         	ENGINE SHUTDOWN         			M	R		OVER TEMP                 	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA			19130	2218 				13185			(CAN) AS PILOT APPLIED TAKEOFF POWER THERE WAS A CHANGE IN NOISE PITCH & THEN A DROP IN POWER WAS NOTICED. AFTER POWER R	EDUCED & TAKEOFF ABORTED E.G.T. WAS PEGGED. ENGINE SHUTDOWN & E.G.T. STARTED DROPPING. ENGINE HAD JUST BEEN INSTALLED & 	GROUND TESTED OK. CAUSE OF FAILURE UKN. TC: FOLLOW-UP / TEARDOWN REPORT EXPECTED FROM OPERATOR. 				2	H	7	2 	4T	4	T	 	A817    	E297				 
2000072800038	20000728	00038	SW  	2000	7	28	CA000614008      	1	20000520	G	6420	206016201131	BEARING         	BELL        	206011810125	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					TAIL ROTOR	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			58600			A805		CAE895116			(CAN) AIRCRAFT WAS GROUND RUN TO GROUND IDLE.  TAIL ROTOR PEDDLES STARTED TO STIFFEN UP.   AS THE AIRCRAFT RPM WAS INCRE	ASED TO 100 PERCENT NR, TAIL ROTOR PEDDLES STIFFENED TO BEYOND LIMITS APPROXIMATELY 35 POUNDS.  FORCE REQUIRED TO MOVE T	HE PEDDLES.  AT THIS RPM, THE TAIL ROTOR SYSTEM WAS THOROUGHLY INSPECTED AND NO PROBLEMS FOUND. THE TAIL ROTOR BLADES WE	RE REMOVED AND THE AIRCRAFT RUN UP TO 100 PERCENT WITH ONLY THE T/R HUB INSTALLED.  THE PEDDLES MOVED FREELY WITH NO STI	FFNESS.  SPHERICAL BEARINGS REPLACED ON BOTH BLADES.  AIRCRAFT RUN UP AND PEDDLES MOVED FREELY WITH NO STIFFNESS.  BEARI	NGS ARE AVAILABLE FOR INSPECTION.	1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2000072800039	20000728	00039	EU  	2000	7	28	CA000614009      	1	20000522	G	2932	NE15BAT11TFGNOIR	SWITCH          		350A27055300	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COLLECTIVE	CRACKED         	W				O	 	 	 	OTHER                   				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			21150					341			(CAN) PILOT REPORTED THAT THE SWITCH WAS INTERMITTENT (HYDRAULIC CUT-OFF SWITCH ON COLLECTIVE STICK).						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000080900012	20000809	00012	CE  	2000	8	9	CA000614010      	1	20000530	G	7603	S122225A	THROTTLE CONTROL	CESSNA      	STC207      	CESSNA	207   	207         	2073602	CE  	CONT  	O550  	IO550F      	17042	SO  					THROTTLE CONTROL	DEFECTIVE       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			24600			20700228		284748R			(CAN) AT SCHEDULED MAINTENANCE FUNCTION, THE THROTTLE CONTROL WAS FOUND TO BE DEFECTIVE. THE OUTER CASING (SHROUD) HAD S	EPARATED AT A SWAGED FITTING NEAR THE ENGINE END.					1	H	7	1 	3O	3	O	 	A16CE   	E3SO				 
2000072800040	20000728	00040	SW  	2000	7	28	CA000614011      	1	20000427	G	6720	206001020045	PITCH LINK      		206B        	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	UNSAFETIED      	W				O	 	 	 	OTHER                   				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			11200			3055		CAE270029			(CAN) DURING MAINTENANCE, PERFORMED BELOW THE ENGINE PAN, A TAIL ROTOR FLIGHT CONTROL BOLT WAS FOUND UNFASTENED.  T/R AN	TI-TORQUE CONTROL TUBE (ITEM NR 21, 206 IPC FIG.67-2) REAR ATTACHMENT BOLT FOUND WITH NUT BACKED OFF, NO COTTER PIN INST	ALLED.  AIRCRAFT GROUNDED AND ALL FLIGHT CONTROLS WERE INSPECTED FOR SAFETY.  ONE MORE BOLT THAT ATTACHES THE T/R PITCH 	CONTROL ROD TO THE PITCH CONTROL LEVER  WAS ALSO FOUND UN-SAFETIED WITHOUT A COTTER PIN SAFETING THE NUT/BOLT.  A QUALIT	Y CONTROL PROBLEM DURING RECENT A/C REBUILD IS SUSPECTED TO BE A FACTOR IN THE FINDINGS. THE OVERHAUL SHOP HAS BEEN MADE	 AWARE OF THE FINDINGS.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000080200001	20000802	00001	SW  	2000	8	2	CA000614012      	1	20000529	G	5320	206001734001101	BOLT            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					UPPER FUS AREA	LOOSE           	W				O	 	 	 	OTHER                   				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			18200					CAE270029			(CAN) DURING A ROUTINE CLEANING BEHIND HAT RACK AREA, 2 BOLTS ATTACHING A SUPPORT ASSY (ITEM 34, 206 IPC FIG.67-2) WERE 	FOUND SIGNIFICANTLY LOOSE.  AREA WAS INSPECTED FOR FURTHER DEFECTS, NONE FOUND.  BOLTS WERE TIGHTENED PER BELL 206 MAINT	ENANCE MANUAL.  A QUALITY CONTROL PROBLEM DURING A/C REASSEMBLY FOLLOWING AN A/C ACCIDENT IS SUSPECTED TO BE THE CAUSE. 	THE OVERHAUL SHOP HAS BEEN MADE AWARE OF THE FINDINGS.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001031500181	20010315	00181	EU  	2001	3	15	CA000614014      	1	20000602	G	2742	1110043A3	ACTUATOR        			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					STABILIZER	CONTAMINATED    	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			23959								(CAN) ON JUN 6/2000 MASTER FLT CAUTION LIGHT ILLUMINATED ALONG WITH BOTH UTILITY & FLT CNTL CHANNEL LIGHTS ON FLT CNTL P	ANEL AS REORTED BY CREW INBOUND ALT ELECTRIC SYS POPPED CCT BREAKER TWICE UPON ACTIVATION. CREW  THEN PROCEEDED AS PER C	HECK LIST WITH JAMMED HORIZ STAB & A/C LANDED W/O INCID.. ENGINEERS  INSPECT & PREP A/C FOR FERRY FLT TO YVR. MAINT INSP	 FOUND WATER CONTAMINATION IN STAB GEARBOX CLUTCHES. FLUID FLUSHED IN ACCORD WITH CRA TECHNICAL INFO BULLETIN F28-27-03R	2, SYS TESTED SEVERAL TIMES WITH HYDRAULIC POWER & STANDBY ELECT. POWER, NO FAULT FOUND. A/C INSP & FOUND SAFE FOR FERRY	 FLT TO YVR. YVR MAINTENACE REPLACING STAB ACTUATOR.	2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001032900021	20010329	00021	NE  	2001	3	29	CA000614015      	2	20000531	G	7532	118010502	HOUSING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ACTUATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PART WAS SUSPECTED TO BE CRACKED DURING A DAILY INSPECTION OF THE AIRCRAFT. THE PART WAS MOVED FOR INVESTIGATION A	ND THE CRACK FAILED. IF THE PART HAD FAILED IN FLIGHT IT WOULD HAVE CAUSED SEVERE COMPRESSOR STALLING OF THE ENGINE.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2000080900019	20000809	00019	CE  	2000	8	9	CA000614016      	1	20000601	G	2510	04142221	FRAME           	CESSNA      	040011887   	CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  					AFT O/B LUG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			63250					619465A			(CAN) DURING 100 HOUR INSPECTION, IT WAS DISCOVERED THAT THERE WERE 2 SMALL CRACKS ON THE FRAME REAR LUG THAT HOUSES THE	 ADJUSTING CAM FOR THE SEAT BACK. ONE CRACK WAS FOUND ATTHE LUG WELD WHILE THE OTHER WAS FROM THE HOLE FOR THE SHAFT ASS	Y (0411105-1).IT WAS ALSO DISCOVERED THAT THE SHAFT ASSY ITSELF WAS CRACKED/SPLIT AT THE ENDS INCLUDING UNDER THE CAM. S	EAT FRAME IS TO BE REPAIRED AND THE SHAFT ASSY REPLACED.                                                                	                                                                                                                        	                                                                                                                       	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2000080900020	20000809	00020	GL  	2000	8	9	CA000614017      	3	20000602	G	6114	57B32518R	HUB             	HARTZL      		CESSNA	206   	U206G       	2073356	CE  						HARTZL	HCC3Y	PHCC3YF1    	GL  		CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			17230						EE2171A		(CAN) FIELD MAINTENANCE FOUND SUSPECTED CRACK,  N.D.T. CONFIRMED CRACK.  HUB REPLACED,  PROPELLER RETURNED TO SERVICE.						1	H	7	1 	3O			 	A4CE    		5	C	P25EA	 
2000071800240	20000718	00240		2000	7	18	CA000614018      	4	20000605	G	2562	4000	ELT             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ELT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						406329		CAE834205			(CAN) DURING ANNUAL RECERTIFICATION, THE ELT WAS FOUND TO HAVE NO TRANSMIT POWER OUTPUT.  THE UNIT WAS SENT BACK TO  FOR	 REPAIR STATION.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011105145	20010111	05145	EA  	2001	1	11	CA000614019      	1	20000606	G	5741	C2FS209	STRUT           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					MLG	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								JP211236			(CAN) DURING INSPECTION AS DIRECTED BY CF-98-37R1, THE STRUTS WERE FOUND BEYOND THE LIMIT SET BY THE AD.  BOTH LEFT AND 	RIGHT STRUTS ARE BEING REPLACED.  					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000080900021	20000809	00021	CE  	2000	8	9	CA000614022      	1	20000523	G	7120	265102215	RING ASSEMBLY   	CESSNA      	265102319   	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					RT LWR CORNER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			20800			1032		PCE19415			(CAN) DURING HOT SETION INSP PROCEDURES OF A/C ENGINE. ROUTINE INSP OF ENG MOUNT REVEALED A ONE INCH LONG CRACK IN ENG M	OUNT RING LOWER (AFT) CORNER, RT SIDE. CRACKING OF RING SUBJECT OF AWD 90-05-04 AND CESSNA S/B CAB 88-14 INVOLVING A/C S	/NS 208B0001 THRU S/N 208B0086, AND IS NOT APPLICABLE TO THIS A/C S/N - HOWEVER, SINCE WE ARE CONSTANTLY FLYING INTO OIL	/MINING COMPANY UNIMPROVED STRIPS, COMPANY INTERNAL INSP PROCEDURES INCLUDE REPETITIVE, DETAILED INSPS OF ENGINE MOUNT A	ND ACCELERATED OVERHAUL PERIODS FOR NOSE LDG GEAR SHIMMY DAMPER.  ENGINE MOUNT RING REMOVED FOR REPAIR AND OVERHAUL.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000082200033	20000822	00033	SO  	2000	8	22	CA000614023      	1	20000602	G	5311	1220502	CHANNEL         	PIPER       		PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  					CHANNEL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			35810			187290		L597427A			(CAN) DURING INSPECTION, CRACK WAS FOUND ON ONE VERTICAL MEMBER FROM CHANNEL.  WHEN THE RIGHT HAND WING WAS REMOVED TO C	ARRY OUT REPAIR, THE WELDS ON THE ADJACENT VERTICAL MEMBER WAS FOUND TO BE CRACKED. ALSO THE WELD AT THE FRONT OF THE UP	PER DOOR CHANNEL WAS FOUND CRACKED.  CRACKS WERE REPAIRED BY WELDING AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	 	1A2     	E274				 
2000080900022	20000809	00022	CE  	2000	8	9	CA000614024      	1	20000505	G	5210	12170534	HANDLE          			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					SPLINE OF DOOR	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				D	 	 	INFLIGHT SEPARATION       			CL	CLIMB          	1			CA							U20602938	286376R			(CAN) PILOT CLOSED DOOR WITH HANDLE SELECTED TO THE CLOSED POSITION,  HOWEVER, HANDLE WAS PARTIAL STRIP ON INSIDE GEARIN	G, AND DOOR WAS NOT FULLY LOCKED.  MAINTENANCE REPLACED DOOR HANDLE WITH SERVICEABLE HANDLE AND RETURNED THE AIRCRAFT TO	 SERVICE.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000080900023	20000809	00023	SO  	2000	8	9	CA000614025      	2	20000526	G	8530	TM639272	CYLINDER        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	CYLINDER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								221410	781584		(CAN) CRACK BETWEEN SPARK PLUG AND EXHAUST PORT.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2000080900024	20000809	00024	EA  	2000	8	9	CA000614026      	2	20000601	G	7532	310082903	BLEED VALVE     	PWA         		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					BLEED VALVE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				R	 	 	PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			CA				41900				PCE50216			(CAN) DURING FINAL POWER REDUCTION ON LANDING IN YYC, THE RIGHT ENGINE DEVELOPED SYMPTOMS OF COMPRESSOR STALL . ENGINE W	AS SHUTDOWN AND SECURED.  AIRCRAFT LANDING UNEVENTFUL.  MAINTENANCE DISCOVERED ENGINE  VALVE REPLACED WITH SERVICEABLE U	NIT.  ENGINE GROUND RUN C/O PERFORMANCE SATISFACTORY.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000081000001	20000810	00001	SO  	2000	8	10	CA000614027      	1	20000602	G	2120	4998903	CLAMP           			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					TUBE CLAMP STRAP	IMPROPER PART   	W				B	 	 	 	EMER. DESCENT           				W	 	 	INADEQUATE Q C            			CR	CRUISE         	1			CA								P50694			(CAN) AIRCRAFT LOST CABIN PRESSURE WHILE IN CRUISE AT FL 210.  PILOT DESCENDED AND RETURNED TO BASE.  MAINTENANCE DISCOV	ERED AIR DISTRIBUTION TUBE (P/N 46504-00) AND HOSE (P/N 49990-06) CONNECTION HAD COME APART. FURTHER INVESTIGATION DETER	MINED THE WRONG SIZE STRAP HAD BEEN INSTALLED UNDER THE CLAMP THAT SECURES THE HOSE/TUBE CONNECTION. THE SUSPECT STRAP I	S USED ON THE PARALLEL TUBE ADJACENT TO THE FAILED CONNECTION. THIS PARALLEL TUBE HAD ONE INCORRECT STRAP INSTALLED AS W	ELL.  STRAPS SWITCHED TO PROPER TUBE/HOSE ASSEMBLIES AND TIGHTENED.  NOTE: CAUTION WHEN REMOVING BOTH TUBES AT SAME TIME	 TO PREVENT INCORRECT STRAP INSTALLATION.	1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000081700011	20000817	00011	EU  	2000	8	17	CA000614030      	1	20000604	G	2910	9738114306	PRESSURE SWITCH 		5291312004  	PILATS	PC12  	PC1245      	       	EU  										PRESSURE SWITCH	FAILED          	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN  THE HIGH PRESSURE CONDITION COULD NOT BE DUPLICATED IN THE HANGAR. THE PREVIOUS DAYS  FLYING WAS A TRIP FROM ST. J	OHNS TO GOOSE BAY, 2 HRS AT FL 280 AND -45 DEGREES.   SUSPECT THE HYD SYSTEM, UPON BEING SUPER CHILLED AT ALTITUDE, IS C	AUSING THE OVER PRESSURE CONDITION.  SYSTEM PRESSURE SWITCH AND POWER PAC IS LOCATED IN LEFT WING ROOT.  SYSTEM RECHARGE	S IN FLIGHT WHEN COMMANDED BY THE SYSTEM PRESSURE SWITCH.  WHEN RECHARGING AT THESE TEMPS IT IS SUSPECTED THAT THE PRESS	URE SWITCH BECOMES LAZY DUE TO THE TEMPERATURE AND VISCOSITY OF THE HYDRAULIC SYSTEM.  THERE IS NO OVER PRESSURE INDICAT	ION ON THE FLIGHT DECK. WILL MONITOR THE SYSTEM IN FUTURE TO SEE IF THE OVER PRESSURE CONDITION CAN BE DUPLICATED.	1	L	7	1 	3T			RT	A78EU   					 
2001031500183	20010315	00183	SO  	2001	3	15	CA000614031      	1	20000602	G	7931		ENGINE          			LKHEED	382   	382G        	526414U	SO  	ALLSN 	501D  	501D22A     	03006	GL  	HAMSTD	54H	54H60117    	NE  	NR 3	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA								550859	2303445		(CAN) ENROUTE LOUISVILLE KY FROM YGQ DURING MODERATE TURBULENCE THE NR 3 ENGINE HAD LOW ENGINE OIL PRESSURE INDICATION. 	THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT CONTINUED TO DESTINATION. INVESTIGATION FOUND NO FAULT & GROUND RUN RESULTS WE	RE NORMAL. THE AIRCRAFT RETURNED TO YGQ WITH NO FURTHER DIFFICULTY. NO SOURCE FOR THIS ANNOMOLY HAS BEEN DETERMINED.				2	H	7	4 	4T	4	T	 	A1SO    	E282	6	C	P906	 
2001011105147	20010111	05147	EA  	2001	1	11	CA000614033      	1	20000610	G	2720	C3CF1314	PEDAL           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					RUDDER CONTROL	BROKEN          	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA								PCE40906			(CAN) WHILE TAXIING ON THE WATER IN STRONG WIND CONDITIONS, PILOT LOST RIGHT RUDDER CONTROL.  PART WAS REPLACED.   AIRCR	AFT WAS RETURNED TO SERVICE.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001011105148	20010111	05148	EA  	2001	1	11	CA000614034      	1	20000611	G	5753	C3WF46	RIB             	DHAV        	C3WF527     	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT WING	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE40691			(CAN) WHILE THE AME WAS CARRYING OUT A 100 HOUR INSPECTON OF THE LT WING FLIGHT CONTROLS, NOTICED THERE WAS A SMALL CRAC	K ON THE TOP SKIN AND SEVERAL SHEARED RIVETS. THE FLAP WAS REMOVED, DISASSEMBLED AND INSPECTED.   IT WAS FOUND THAT THE 	INTERNAL RIB P/N C3WF46 WAS SHATTERED.  THE RIB WAS REPLACED, THE FLAP REASSEMBLED, REPAIRED AND RETURNED TO SERVICE. CO	ULD FIND NO APPARENT REASON FOR THE CAUSE OF THIS FAILURE.			1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000081700012	20000817	00012	CE  	2000	8	17	CA000614036      	1	20000614	G	2740	505244953	WIRE            		995240554   	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					THROUGH DASH	BROKEN          	W				A	D			UNSCHED LANDING         	RETURN TO BLOCK         			F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA								PCE41799			(CAN) AIRCRAFT DEPARTED AND SHORTLY AFTER TAKEOFF, THE MAIN STABILIZER TRIM FAILED. AIRCRAFT RETURNED TO BASE.  A WIRE W	AS FOUND BROKEN ON THE COPILOT''''S SIDE WHERE THE WIRE GOES THROUGH THE DASH.  WIRE REPAIRED AND AIRCRAFT RELEASED TO S	ERVICE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001011105021	20010111	05021	NM  	2001	1	11	CA000614038      	1	20000427	G	5210	85210195001	HANDLE          	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PAX DOOR	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA						052					(CAN) DURING DESCENT AT FLIGHT IDLE THE CABIN DOOR HANDLE MOVED TO THE MID POSITION WHICH IN TURN COLLAPSED THE DOOR SEA	L FOLLOWED BY A WHISTLING NOISE AND CABIN DEPRESSURIZATION. WITHOUT CONSULTING WITH THE FLIGHT CREW THE CABIN ATTENDANT 	PUSHED THE HANDLE TO THE CLOSED POSITION SEAL INFLATED AND CABIN PRESSURE RETURNED TO NORMAL. AIRCRAFT LANDED WITHOUT IN	CIDENT. DOOR MECHANISM RIGGING WAS CARRIED OUT AS PER THE AMM. FUNCTIONAL CHECKS DONE. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000081700013	20000817	00013	CE  	2000	8	17	CA000614039      	1	20000511	G	2612	99120363	SENSOR          	MACCHI      	99120363    	CESSNA	500   	500CESSNA   	2076602	CE  										LT ENGINE	CHAFED          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA			23350								(CAN) AIRCRAFT WAS RUNNING ON GROUND FOR APPROX 30-40 MINUTES PRIOR TO DEPARTURE. UPON CLIMB OUT,  LT ENGINE FIRE LIGHT 	FLICKERED AND STAYED EXTINGUISHED.  AIRCRAFT CONTINUED FLIGHT WITH NO FURTHER OCCURRENCE.  ENGINE WAS GROUND RUN TO CHEC	K FOR BLEED AIR LEAKS AND NONE WERE FOUND.  FIRE WIRE INSPECTED AND FOUND CHAFED NEARLY IN HALF,  BEHIND INBOARD BLEED A	IR COUPLER.  SYSTEM STILL WAS ABLE TO SELF-TEST OK.  SUSPECT THE LACK OF MATERIAL ON THE FIRE WIRE CAUSED LIGHT TO ILLUM	INATE EARLIER THAT NORMAL.  ULTIMATELY THE ENTIRE FIRE WIRE WAS REPLACED.		1	L	7	2 	4F			 	A22CE   					 
2000082200034	20000822	00034	EU  	2000	8	22	CA000614040      	2	20000607	G	7414	996538	STATOR          	ROTAX       		DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					PICK UP COIL	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			48400					4380628			(CAN) DURING MAINTENANCE GROUND RUN, TROUBLESHOOTING COULD NOT CORRECT ROUGH RUNNING ENGINE BY MANUAL (TECH) PROCEDURES.	  FURTHER INSPECTION SHOWED DETERIORATING STATOR PICKUP COIL AND SHROUD PER PREVIOUS SDR 2000505014 RE:SB 98-9R-026R3.  	FAILURE OF CONPONENT IN-FLIGHT WILL PREVENT ENGINE RE-STARTING DURING EMERGENCY PROCEDURES.  AD 98-912-026R3 REFERS				1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2000081700014	20000817	00014	EA  	2000	8	17	CA000614041      	3	20000602	G	6111		BLADE           			BEECH 	23    	C23         	1151242	CE  						SNSNCH	76E	76EM8       	EA  	AT 34.20 STA	INACCURATE      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				10600					7625K		(CAN) DIMENSIONAL CHECK, FOUND PROPELLER TO BE JUST UNDER MINIMUM ALLOWABLE THICKNESS AT THE 34.20 INCH STATION.  PROPEL	LER RETIRED FROM SERVICE.					1	L	7	1 	3O			 	A1CE    		5	N	P4EA	 
2000081700017	20000817	00017	CE  	2000	8	17	CA000614045      	1	20000526	G	2720	NAS697A3	NUT             			CESSNA	150   	150A        	2071804	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	RUD STOP BOLT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			22460					25741A	F4459		(CAN) AIRCRAFT WAS INSPECTED AS A RESULT OF SDR AL-2000-04.   ANCHOR NUT FOR RUDDER STOP BOLT FOUND CRACKED.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000081700018	20000817	00018	EU  	2000	8	17	CA000614046      	1	20000526	G	2810	PC642031L	FUEL TANK       			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  					RT SIDE WELD	CRACKED         	W				K	 	 	 	NONE                    				B	K	 	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		IN	INSP/MAINT     	1			CA			78400					L2594848A			(CAN) FUEL TANK CRACKED ALONG SIDE WHERE WELDED.  AUTOMATIC FUEL CATCH SHIELD DID NOT WORK AND GAS DRIPPED INTO CABIN NO	T OVERBOARD AS SUPPOSED TO.					1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
2000081700019	20000817	00019	EA  	2000	8	17	CA000614047      	3	20000608	G	6111		PROPELLER       			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	L/E & FACE	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				66530				L2240115	K2857		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.                                                                      	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                        	                                                                                                                       	1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045	 
2000083100911	20000831	00911		2000	8	31	CA000614057      	4	20000602	G	3422	1426200113	GYRO            	EDOAIREXXXXX	H000B12     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					INSTRUMENT PANEL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				33200		65247		L159368A			(CAN) WHEN RE-SETTING COURSE,  PILOT HAD LET-GO SETTING KNOB WHICH SNAPPED BACK IN PLACE.  LATER DIRECTIONAL GYRO WOULD 	NOT FOLLOW COURSE CHANGE UNLESS PILOT HELD KNOB PULLED OUT.   EVIDENTLY, KNOB SPRING BROKE INSIDE.  INSTRUMENT TECHNICIA	N STATED KNOB SHOULD NOT BE LET GO TO SNAP IN BUT BE FOLLOWED IN.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083100912	20000831	00912	SO  	2000	8	31	CA000614058      	1	20000606	G	2823	400440	BOLT            	DUKES       	3487001     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT WING ROOT	JAMMED          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			12455					L159368A			(CAN) PILOT REPORTED LT FUEL SELECTOR STIFF AND JAMMING ON INBD TANK AT PRE-TAKEOFF CHECK.  WITH ENOUGH PRESSURE, SELECT	OR COMPLETED TRAVEL, PILOT CHECKED OPER OF ENGINE, INBD, OTBD, POSITIONS AND IN OFF, SEVERAL TIMES PRIOR TO ELECT TO TAK	EOFF AND REPORTED SNAG IN LOG AND VERBAL DEBRIEFING AT ARRIVAL.  CORRECTIVE ACTIONS TAKEN IMMEDIATELY.  ACCESS PANEL OFF	, OPER OF SELECTOR SHOWED STIFF AT SOME TRAVEL POINT 2 TIMES OUT OF 3.  POSSIBLE JAMMING.  FOUND BOLT NR 400-440 (AN3-6A	), AT TIMES, CHAFING ON SELECTOR CASING ASSY SCREW HEAD.  FOUND WASHER BETWEEN CABLE TERMINAL NR 44668-000 (MS20668-4) A	ND SELECTOR ARM, WORN RENDERING BOLT TOO LONG ON NUT SIDE.  ALSO, OTHER 2 WASHERS IN WRONG SEQUENCE. RE-INST NEW HDWE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031900067	20010319	00067	CE  	2001	3	19	CA000614059      	1	20000614	G	3020	1299700321	TUBE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					DE-ICE SYSTEM	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			9037 								(CAN) RT BLEED AIR FAIL WARNING LIGHT COME ON DURING FLIGHT. AFTER INVESTIGATION WE FOUND THAT LINE P/N 129-970032-1 WAS	 CRACKED AT WELDING JOINT OF THREADED FITTING. 					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001031900068	20010319	00068	EA  	2001	3	19	CA000614060      	1	20000530	G	2612	356024310	FIRE LOOP       			CNDAIR	CL600 	CL6002B19   	       	EA  										LT ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKE-OFF EICAS WARNING  14TH STAGE DUCT APPEARED.LT ENGINE WAS SHUTDOWN IN FLIGHT.AIRCRAFT RETURN TO	 LAND.LT ENGINE 14TH STAGE HEAT SENSING ELEMENT REPLACED.NOTE: LT ENGINE WAS NOT SHUTDOWN IN FLIGHT AS REPORTED. DATE 17	 JUNE 2000. 				2	L	7	2 	4F			RT	A21EA   					 
2001031900075	20010319	00075	EA  	2001	3	19	CA000614061      	1	20000611	G	2612	35602310	FIRE LOOP       			CNDAIR	CL600 	CL6002B19   	       	EA  										LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, PILOT REPORTED L 14TH DUCT MESSAGE. EMERGENCY PROCEDURES CARRIED OUT AS PER AFM, WARNING PERSISTED. 	PILOT SHUT DOWN THE ENGINE AS PER AFM & PERFORMED AN UNEVENTFUL SINGLE ENGINE LANDING IN VIE, SINGLE ENGINE FLIGHT LASTE	D 15 MINUTES. MECHANICS FOUND A FAILED LOOP WHICH WAS REPLACED. 				2	L	7	2 	4F			RT	A21EA   					 
2001031900076	20010319	00076	EA  	2001	3	19	CA000614062      	1	20000611	G	7900	6018T30P06	CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					TURBINE DISK	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			10423								(CAN) DURING A FLIGHT, THE CREW NOTICED A FUEL/OIL ODOR IN THE COCKPIT. IT WAS ALSO NOTICED IN THE CABIN WHILE ON THE GR	OUND. THE NR 1 CARBON SEAL WAS REPLACED. THE FAN DISK ASSEMBLY P/N 6078T57G04, S/N GEE0893 WAS REPLACED (TSN: 10423.9, C	NS: 9754). 				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000092100001	20000921	00001	SO  	2000	9	21	CA000614063      	1	20000607	G	3230	41789000	BOLT            			PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6A11      	52043	NE  					UPPR DNLK HK ROD	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE10037			(CAN) UPON MAKING A QUICK/INSPECTION OF THE MAIN GEAR DRAG BRACES AND RODS, FOUND EXCESSIVE PLAY IN THE DOWNLOCK ROD AT 	THE CLEVIS BOLT.  THE RT CLEVIS BOLT P/N 41789-000 WAS FOUND SHEARED; AND THE LT CLEVIS WORN ON ITS WAY TO SHEARING.					1	L	7	2 	3T	3	T	 	A8EA    	E4EA				 
2000072000235	20000720	00235	NE  	2000	7	20	CA000614064      	2	20000614	G	7250	M031070	TURBINE         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL INJECT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TO	TAKEOFF        	1			CA			59300			7984810		786			(CAN) DURING START PROCEDURE STARTER WAS UNABLE TO MOTOR ENGINE.  AFTER INSPECTING ENGINE FOR F.O.D. AND REMOVING COMPON	ENTS ON THE ACCESSORY GEARBOX,, ENGINE WAS DISMANTLED TO ISOLATE THE LOCK UP.   LOCK UP WAS FOUND TO BE IN THE GAS PRODU	CER ASSEMBLY (M024M03).  ASSEMBLY WAS SENT TO REPAIR CENTER WHERE IT WAS FOUND TO BE FUEL COKING ON THE LABYRINTH SEALS 	OF THE CENTRIFUGAL INJECTION WHEEL.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001031900079	20010319	00079	NM  	2001	3	19	CA000621004      	1	20000615	G	7830		SWITCH          			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					THRUST REVERSER	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) ON TAKE, THRUST REVERSER ISOLATION VALVE WARNING LIGHT ILLUMINATED. RETURNED TO YYZ. THRUST REVERSERS OPERATED AS 	PER WORK CARD 1187, COULD NOT DUPLICATE DISCREPANCY. REPLACED NR 1 AND 2 THRUST REVERSER PRESSURE SWITCHES PER MM 78-31-	16. OVERWEIGHT LANDING CHECK COMPLETED AS PER FLYAWAY MANUAL PAGE 02.01.01, NO FAULTS NOTED. 				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001032900023	20010329	00023	NM  	2001	3	29	CA000621005      	1	20000617	G	2420		OIL COOLER      			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 CSD	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			40768	37820							(CAN) A/C 759, , FLT 195,  NR 2 CSD DISCONNECTED DUE LOW OIL PRESSURE LIGHT CAME ON. REPLACED NR 2 CSD OIL COOLER DUE CO	OLER BLOCKED BY PIECES OF FAN DIFUSER DUCT LINING, THAT HAD BROKEN UP. REPLACED NR 2 ENGINE AS PER WORK CARD 1125-2,					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001032900025	20010329	00025	NE  	2001	3	29	CA000621008      	2	20000607	G	7321	324476810	BEARING         	BENDIX      	324476810   	BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUEL CONTROL	SEIZED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				2624 		A69446					(CAN) DURING CRUISE RT ENGINE FLUXUATES ALL PARAMETERS THAN DROPS TO GROUND IDLE. UNEVENTFUL LANDING. T/S P3,PY ALL SYST	EM FOR LEAKS AND OR BLOCKAGE - NONE FOUND. PULLED FCU AND FOUND DRIVE BEARING SEIZED AND DRIVE COUPLER BROKEN.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000092100002	20000921	00002	EA  	2000	9	21	CA000621009      	1	20000610	G	5740	C6TFM1022	ATTACH FITTING  	DHAV        		DHAV  	DHC6  	DHC6200     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  					BOTTOM PLATE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						176		PCE20768			(CAN) LEVEL 3 CORROSION FOUND ON PLATE BETWEEN ATTACH POINTS.						1	H	7	2 	3T	3	T	 	A9EA    	E4EA				 
2001032900026	20010329	00026	EU  	2001	3	29	CA000621010      	2	20000601	G	8520		BEARING         	ROTAX       	912F3       	DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE MAIN	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1790 			4380740					(CAN) UPON REGULAR 200 HR ON CONDITION INSP, STEEL & ALUMINUM, BABBITT PARTICLES FOUND IN OIL & FILTER. PISTONS & CYLIND	ERS PULLED & INSP. NO EVIDENCE OF PART FAILURE: GEARBOX REMOVED, SLIGHT FRETTING OF VALLEYS ON DOGS - ADJUSTED FRICTION.	 ENGINE RE-ASSEMBLED & FLOWN DUAL LCL ONLY FOR 5 HRS ON ADVICE OF DIRECTOR OF MAINT OF ROTAX CANADA.  AFTER 5 HRS FLT A/	C ENGINE INSP METAL.  MOSTLY BABBITT & ALUMINUM FOUND IN OIL & OIL FILTER. ENGINE REMVD & SENT TO ROTAX IN VERNON.  UPON	 THEIR INSP CRANKSHAFT MAIN CTR BEARING & CRANKSHAFT MAIN CTR SURFACE WHERE WEARING, EXCEPT FOR METAL.  FOUND DURING INS	P, ENGINE RAN & TESTED WITHIN ALL SPECIFIED PARAMETERS.  OVERHAULED ENGINE WILL BE INSTALLED.	1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2001031900080	20010319	00080	EU  	2001	3	19	CA000621011      	1	20000616	G	3244	5504632	TIRE            			FOKKER	F28   	F28MK1000   	4990808	EU  										MLG	FAILED          	W				A				UNSCHED LANDING         				D	N		INFLIGHT SEPARATION       	FALSE WARNING             		CL	CLIMB          	1			CA											(CAN) THE PILOT OF CRA A/CRPTED LT INBOARD MAIN WHEEL TIRE ASSY BLEW ON ROTATION OUT OF QUE CITY, QUE &GEAR SAFE IND. LI	GHT WENT OUT. MAINT CNTL TROUBLESHOT PROBLEM WITH FLT CREW BUT WERE UNABLE TO GET LEFT MAIN GEA R TO INDICATE DOWN & LOC	KED.THE DECISION MADE TO DIVERT A/C TO MONTREAL (YUL) WHERE EMERG LDG CARRIED OUT - AFTER BURNING OFF EXCESS FUEL. A/C L	ANDED W/O INCIDENT, PASSENGERS WERE DEPLAINED & TRANSPORTED TO TERMINAL BY BUS. INIT MAINT INSP REVEALED RETREAD ON NR 2	 TIRE HAD LET GO, TIRE ASSY STILL AT 100 PSI. MAINT INST THEG EAR PINS, CHANGED NR 1 & 2 TIRES (P/N 9550463-2) & FERRIED	 A/C TO TORONTO (YYZ). FURTHER INSPECTION IN YYZ REVEALED DAMAGE TO LT SIDE.	2	L	7	2 	4F			RT	A20EU   					 
2001031900081	20010319	00081	SO  	2001	3	19	CA000621012      	1	20000607	G	2721	63457003	ARM             			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					RUDDER CONTROL	FAILED          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			LD	LANDING        	1			CA			2256 					L1253048			(CAN) - PILOT REPORTED POOR LT AUTHORITY ONLANDING, UNABLE TO TRIM. - INSPECTION FOUND THE TAB THAT RUDDER TRIM CONTROL 	ATTACHES TO AN ARM ASSEMBLY P/N 63457-003, WAS TORN OUT OF THE TUBE.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001031900082	20010319	00082	SO  	2001	3	19	CA000621013      	1	20000612	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCC4Y	HCC4YR2     	GL  	HYD SYSTEM	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			193  						FH271		(CAN) LANDING GEAR SELECTOR HANDLE WOULD NOT RETURN TO NEUTRAL DURING ENGINE SHUTDOWN CHECK. NEW HYDRULIC PUMP INSTALLED	 AND LANDING GEAR SELECTOR CHECK FUNCTIONED NORMALLY. SUSPECT LOW VOLUME AND/OR PRESSURE OUTPUT FROM REMOVED PUMP. DEFEC	TIVE PART RETURNED TO MFR. FOR WARRANTY CONSIDERATION. HYDRAULIC PUMP DISCHARGE FILTER DID NOT SHOW ANY SIGN OF METAL CO	NTAMINATION.			1	L	7	2 	3O			 	A20SO   		5	C	P52GL	 
2001032900027	20010329	00027	CE  	2001	3	29	CA000621014      	1	20000407	G	7120	05510171	MOUNT           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ENGINE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON ROUTINE 100 HOUR INSPECTION LT VERTICAL TUBE ON ENGINE MOUNT WAS FOUND BROKEN.FURTHER INVESTIGATION FOUND THAT 	THIS AIRCRAFT HAD HAD A LONG HISTORY OF NOSE WHEEL SHIMMY. OVERHAULED ENGINE MOUNT AND SERVICING OF SHIMMY DAMPER, FIXED	 THE PROBLEMS.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001031900087	20010319	00087	CE  	2001	3	19	CA000621015      	1	20000324	G	3411		STATIC LINE     			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	PITOT/STATIC SYS	KINKED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								L3063527A	710364		(CAN) THE AIRSPEED INDICATOR HAD BEEN REMOVED FOR MAINTENACE, AND RE-INSTALLED. SUPPOSEDLY A PITOT/STATIC TEST WAS CARRI	ED OUT, AND SIGNED FOR. AIRCRAFT WHEN ON INITIAL FLIGHT AND AIRSPEED & ALTIMETER DID NOT FUNCTION.THE CAUSE OF THE PROBL	EM WAS THAT, THE STATIC LINE TO AIRSPEED WAS TOTALLY KINKED OFF. THE LINE WAS REPAIRED WITH A SATISFACTORY PITOT/STATIC 	TEST BEING CARRIED OUT.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001031900088	20010319	00088	CE  	2001	3	19	CA000621016      	1	20000531	G	7810	991029910	ELBOW           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1371 					521338			(CAN) MINOR HEAT STRESS CRACK ADJACENT TO EXISTING SEAM WELD.						1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2001031900092	20010319	00092	SO  	2001	3	19	CA000621020      	1	20000612	G	2620	7395603	SWITCH          			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					EXTINGUISHER	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			CR	CRUISE         	1			CA			5222 					PCE99130			(CAN) PILOT EXPERIENCED RIGHT ENGINE FIRE WARNING AND MASTER CAUTION ANNUCIATORS. ENGINE WAS SHUTDOWN BY CHECKLIST AND R	E FIRE BOTTLE DISCHARGE SWITCH ACTIVATED. LANDING C/O UNEVENTFUL. MAINTENANCE DETERMINED ENGINE FIRE WARNING WAS FALSE A	ND THAT THE FIRE BOTTLE DID NOT DISCHARGE. INSPECTION REVEALED THE CONNECTOR HAD SEPARATED ON THE BACK OF THE FIRE EXTIN	GUISHER SWITCH ASSEMBLY. NO CAUSE OF THE FALSE FIRE WARNING COULD BE DETERMINED AS ALL PROBES TESTED IN SPEC. WIRING HAR	NESS INSPECTED SERVICEABLE AND GROUND RUNS SATISFACTORY. FIRE EXTINGUISHER SWITCH CONNECTOR ATTACHED AND SECURED. TEST F	LIGHT C/O SATISFACTORY, AIRCRAFT RELEASED.	1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2000092100003	20000921	00003	CE  	2000	9	21	CA000621021      	1	20000610	G	3240	1280506130	LINE            			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520A      	17032	SO  					R/H BRAKE LINE	CHAFED          	W				D	 	 	 	RETURN TO BLOCK         				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA								112560R			(CAN) DURING TAXI, THE PILOT NOTICED THE RT BRAKE HAD LESS PRESSURE THAN THE LT.  AIRCRAFT RETURNED TO BLOCKS,. INVESTIG	ATION REVEALED THAT THE RT BRAKE LINE HAD BEEN CHAFED BY A FAIRING SCREW AND WAS LEAKING.  BRAKE LINE REPLACED, SHORTER 	SCREWS INSTALLED IN  FAIRING.				1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2000092100004	20000921	00004	SO  	2000	9	21	CA000621022      	1	20000609	G	3250	1505800002	GEAR            		1521500001  	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					SECTOR GEAR	FAILED          	W				O		 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA								PCE56711			(CAN) PILOT REPORTED A WOBBLY NOSE GEAR SHIMMY ON LANDING ROLL-OUT WITH LIMITED RT TURNING CAPACITY.  MAINTENANCE FOUND 	TEETH MISSING OFF THE SECTOR GEAR JAMMING ON THE RACK FOR LIMITED TRAVEL WITH A GAP IN THE CENTER CAUSING THE SEVERE SHI	MMY.   THE GEAR WAS DISMANTLED, CLEANED WITH A SERVICEABLE SECTOR GEAR INSTALLED.  REGREASED ASSEMBLED AIRCRAFT TO BE FE	RRY FLOWN TO YTH FOR PERMANENT REPAIRS.  POSSIBLE CAUSE, TAXIING ONE ENGINE OR TOWING CONNECTED, HOWEVER, NOTHING REPORT	ED.		1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2001032900029	20010329	00029	EA  	2001	3	29	CA000621024      	1	20000621	G	2720	C3CF1314	LEVER           			DHAV  	DHC3  	DHC3        	2800202	EA  										RUDDER PEDAL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION ON THE RUDDER PEDALS THE ENGINEER FOUND A CRACK AT THE TOP OF THE RUDDER 	PEDAL LEVER. THE LEVER WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3R			 	A815    					 
2001032900030	20010329	00030	GL  	2001	3	29	CA000621025      	3	20000613	G	6111	S82NB2	BLADE           			BEECH 	33    	3533        	1151402	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	PROPELLER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				51   							(CAN) FOUND CORROSION ON THE BLADE THREADS DURING THE CORROSIION INSPECTION. BLADES REPLACED WITH USED SERVICEABLE. IN A	CCORDANCE WITH MCCAULEY MANUAL 720415.					1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2001032900031	20010329	00031	GL  	2001	3	29	CA000621026      	3	20000621	G	6114		FLANGE          													MCAULY	1A200	1A200DFA    	GL  	PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			281  								(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.																5	N	P874	 
2000092100005	20000921	00005		2000	9	21	CA000621027      	4	20000612	G	6122	B4183	FLYWEIGHT       	HARTZL      	F624        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	CUP	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			CA						C549T		L199468N	DJDJ10707A		(CAN) FLYWEIGHT CUP IS SPOT WELDED TO FLYWEIGHT HEAD.  SPOT WELD BROKE, HEAD SPUN WITHOUT CUP AND CUT CUP CAUSING FAILUR	E.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001032900032	20010329	00032	NM  	2001	3	29	CA000621028      	1	20000612	G	2120	65405521	MUFFLER         			BOEING	727   	72725       	1384006	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					AIR DISTRIBUTION	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING OF AIRCRAFT FOR A PRESSURIZATION DEFECT, IT WAS NOTICED THAT THE RT ACCOUSTIC MUFFLER INTER	IOR LINING HAD BECOME DETACHED. THE PIECES WERE FOUND BLOCKING THE PRIMARY HEAT EXCHANGER. THIS WAS DETERMINED TO BE THE	 CAUSE OF THE PRESSURIZATION DIFFICULTY. THE MUFFLER WAS REPLACED. PARTS WERE REMOVED AND AREA CLEANED. AIRCRAFT RETURNE	D TO SERVICE.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000092100006	20000921	00006	SO  	2000	9	21	CA000621029      	1	20000615	G	2701	6855811	WHEEL           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					L/H O/B TOP	BROKEN          	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA			10677					RL4406027A			(CAN) PILOT SIDE OF CONTROL WHEEL BROKE IN-FLIGHT.  LEFT SIDE OF WHEEL TOP PORTION AT CENTER OF WHEEL WHERE A HOLE HAD B	EEN DRILLED TO ACCEPT WIRE FROM CONTROL SHAFT TO MIKE SWITCH MOUNTED ON TOP LEFT SIDE.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001032900033	20010329	00033	NM  	2001	3	29	CA000621030      	1	20000608	G	3246	4312176	BOLT            			BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					WHEEL	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE MECHANIC WAS CARRYING OUT HIS INSPECTION HE OBSERVED THAT NR 7 MAIN WHEEL ASSEMBLY TIE BOLTS WERE SHEARED OF	F (X3). MAIN WHEEL ASSEMBLY WAS REMOVED & SERVICEABLE ASSEMBLY WAS INSTALLEDI.A.W. M.M. 32-45-01. NO FUTHER PROBLEMS ON 	SUBSEQUENT FLIGHTS.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001032900035	20010329	00035	WP  	2001	3	29	CA000621032      	1	20000519	G	3260		BULB            			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					LIGHT	BURNED OUT      	W				L	 	 	 	ABORTED APPROACH        				N	 	 	FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) DURING APPROACH , NO INDICATION DOWN AND LOCK FOR NOSE LANDING GEAR. AIRCRAFT MADE GO AROUND TO VISUALLY VERIFY GE	AR DOWN AND LOCK AND FINALLY LAND WITH NO PROBLEM. THE PROBLEM RESULT AT 2 LIGHT BULB BURNT OUT. BULB REPLACED AND AIRCR	AFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001032900039	20010329	00039	NM  	2001	3	29	CA000621037      	1	20000603	G	3251	3790037107	VALVE           			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					NLG STEERING	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING TAXI, AIRCRAFT STOPPED RESPONDING TO RIGHT STEERING TILLER OR RIGHT RUDDER PEDAL INPUTS. STEERING WOULD ONL	Y RESPOND TO CENTRE TO LEFT POSITIONS. AIRCRAFT RETURNED TO GATE. NOSE WHEEL STEERING METERING VALVE MODULE REPLACED AND	 SYSTEM CHECKED SERVICEABLE AS PER MAINTENANCE MANUAL				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001032900041	20010329	00041	WP  	2001	3	29	CA000621039      	1	20000508	G	2131	20219741	CONTROLLER      			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					CABIN PRESSURE	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) TRANSFER LOCKOUT/STANDBY ON LIGHT ON, QUICK REFERENCE HANDBOOK PROCEDURE CARRIED OUT AND SYSTEM CAUSED SURGE AND L	ARGE CABIN RATE CHANGE, USING STANDBY LEVER HUNGTING +/- 2 INCHES. CHANGED NR 2 CABIN PRESSURE CONTROLLER AND OUTFLOW VA	LVE ACTUATOR.				2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001032900044	20010329	00044	NM  	2001	3	29	CA000621042      	1	20000621	G	5280	NAS6706D26B	BOLT            			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					MLG	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A/C ARRIVED AT GATE (YUL) MAINT FOUND ON WALK AROUND CHECK DAMAGE TO RT LOWER WING PANEL , RT LDG GEAR DRAG 	STRUT, & RIGHT LDG GEAR STRUT DOOR. HEAD OF BOLT ATTACHING RIGHT STRUT DOOR TO LANDING GEAR STRUT FOUND SHEARED OFF. STR	UT DOOR THEN ALLOWED TO MOVE AFT&HANG DOWN INTO AIRSTREAM RESULTING IN DAMAGE TO BOTH DOORS & WING PANEL.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001032900047	20010329	00047	NE  	2001	3	29	CA000621045      	2	20000311	G	7260	312137201	SPUR GEAR       	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ACCESSORY DRIVE	WORN            	W				E	 	 	 	ENGINE SHUTDOWN         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			15076			PCE120369					(CAN) EXAMINATION OF AGB BREATHER GEAR SHOWED THAT ALL OF DRIVE TEETH FOR FUEL PUMP GEAR HAD FRACTURED FROM ROOT WITH EX	CEPTION OF 5 TEETH. THESE 5 TEETH DISPLAYED SEVERE WEAR PATTERN ON TOOTH FLANK, MAINLY BELOW PITCH LINE. IN-FLT SHUT DOW	N CAUSED BY LOSS OF FUEL PUMP DRIVE DUE TO AGB BREATHER & FUEL PUMP GEARS TEETH FRACTURE: THE TEETH FRACTURE OF ACCESSOR	Y DRIVE BREATHER GEAR OCCURED FROM FATIGUE, WHICH ORIGINATED AT TEETH ROOT RADIUS BELOW TEETH WEAR. HIGH STRESS CONTACT 	FATIGUE COMBINED WITH HIGH HRS OF OP ON GEARS PROBABLY CAUSED TEETH WEAR AT PITCH LINE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001031900084	20010319	00084	NM  	2001	3	19	CA000706001      	1	20000620	G	2420	915F2125	GCU             			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			46203								(CAN) NR 2 ENGINE GENERATOR SYSTEM FAILED, UNABLE TO ESTABLISH APU ON AIRCRAFT BUSS. AIRCRAFT DIVERTED TO YHZ. NR 2 GENE	RATOR CONTROL PANEL REPLACED AS PER WORK CARD, SYSTEM CHECKED SERVICEABLE. APU GENERATOR OPERATIONS CHECKED NORMAL WHEN 	FUNCTIONED GROUND AND FLIGHT MODE.  				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031900085	20010319	00085	NM  	2001	3	19	CA000706002      	1	20000617	G	7120		CSD             			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			40768	37820				707408			(CAN) A/C 759, JUNE 17/2000, FLT 195, LOG SEQUENCE 0300876. NR 2 CSD DISCONNECTED DUE LOW OIL PRESSURE LIGHT CAME ON. RE	PLACED NR 2 CSD OIL COOLER DUE COOLER BLOCKED BY PIECES OF FAN DIFFUSER DUCT LINING, THAT HAD BROKEN UP. REPLACED NR 2 E	NGINE AS PER WORK CARD 1125-2, OFF CANADIAN PART NUMBER 7-7200-9-0001, ON SERIAL NUMBER 4240. 				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031900109	20010319	00109	NM  	2001	3	19	CA000706003      	1	20000623	G	2910		O-RING          			BOEING	767   	767375      	       	NM  										HYD SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CREW REPORTED CENTER SYSTEM HYDRAULIC LOW QUANTITY LIGHT ON. TURNED OFF ALL CENTER HYDRAULIC PUMPS. FLIGHT DIVERTE	D, DECLARED AN EMERGENCY, LANDED WITHOUT INCIDENT. ON INSPECTION FOUND LEAK AT DELTA P FITTING ON CENTER SYSTEM CASE DRA	IN FILTER MODULE. O-RING REPLACED LEAK CHECKED OK. 				2	L	7	2 	4F			RT	A1NM    					 
2001031900128	20010319	00128	NM  	2001	3	19	CA000706004      	1	20000625	G	3244	H40X14519	TIRE            	BENDIX      	26066712    	BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					LT MLG	MISSING         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			42747	21210		5095					(CAN) AIRCRAFT ON TAKEOFF, REPORTED TIRE DEBRIS ON RUNWAY. MAINTENANCE ADVISED, UNABLE TO DETERMINE  FLT, LANDING, CREW 	REQUESTED CFR, DUE POTENTIAL TIRE PROBLEMS. FLIGHT LANDED WITHOUT INCIDENT. INSPECTION FOUND TIRE CAP MISSING FROM LEFT 	INBOARD WHEEL. DAMAGE NOTED ON LT INBOARD AFT FLAP AND TRAILING EDGE PANEL. WHEEL AND TIRE REPLACED, FLAP AND PANEL POST	ED FOR REPAIR. 			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031900158	20010319	00158	NM  	2001	3	19	CA000706006      	1	20000629	G	7312	320115	VALVE           			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUEL HEAT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			39104	9633 							(CAN) ON CLIMBOUT FROM MCO, NR 1 FUEL  HEAT VALVE FAILED IN OPEN POSITION, CAUSING NR 1 ENGINE HIGH OIL TEMP. RETURNED T	O MCO. REPLACED NR 1 ENGINE FUEL HEAT VALVE AS PER MM 73-14-11 PAGE 401, TESTED AS PER MM 73-14-11 PAGE 501. CHECKED OK.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031200437	20010312	00437	EA  	2001	3	12	CA000706014      	1	20000705	G	2430	31890	TERMINAL        			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					NR 1 DC GEN	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED THAT NR 1 D.C. GENERATOR LOAD METER WAS INDICATING A LOAD OF 1.26 CONTINUOUSLY. MAINTENAN	CE INVESTIGATION REVEALED A BAD (HIGH RESISTANCE) ON THE R1 TERMINAL CONNECTION OF THE GENERATOR SHUNT LOCATED BEHIND TH	E LT LANDING LIGHT. THE TERMINAL LUGS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031200438	20010312	00438	NE  	2001	3	12	CA000706015      	2	20000705	G	7532		WIRE            			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					BLEED VALVE	CHAFED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED THAT THE NR 1 BLEED SYSTEM CONTROL CIRCUIT BREAKER POPPED. MAINTENANCE INVESTIGATION REVA	LED A CHAFED WIRE AT THE NR 1 HGIH PRESSUE BLEED VALVE CONNECTOR PLUG 2121-P9. THE WIRE WAS REPAIRED AND THE AIRCRAFT WA	S RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600221	20010326	00221	EA  	2001	3	26	CA000706021      	2	20000626	G	7261	LW13904	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					OIL FILTER	LEAKING         	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			149  								(CAN) PILOT REPORTED OBSRVING WHITE FUMES COMING OUT OF LT ENGINE DURING CRUISE. EMERGENCY  FIRE DRILL CARRRIED OUT & FI	RE OUT. INVESTESTIGATION ON GROUND CONDUCTED, FOUND FIRE DAMAGE TO HIGH TENSION MAGNETO LEADS, OIL HOSES, HYDRAULIC & FU	EL HOSES & ELECTRIC WIRINGS. MAGNETO , FUEL PUMP, HYD PUMP, VACUUM PUMP WIRE AFFECTED. OIL STAINS REMAINING WITHIN AREA 	BETWEEN FIREWALL & AFT OF CRANKCASE ACCESSORY HOUSING & FIRE CONTAINED WITHIN AREA ONLY ATTEMPTED TO FIND CAUSE OF FIRE,	 FUEL PUMP TURNED ON, & NO FUEL LEAKAGE EVIDENT FROM PUMP & HOSES, DRY MOTOR RUN ALSO CARRIED OUT, & DISCOVERED FRESH OI	L DRIPPING THROUGH PRESSURE FILTER OIL SEAL AS REFERRED ABOVE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031200443	20010312	00443	CE  	2001	3	12	CA000706023      	1	20000613	G	3260	327	BULB            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					NLG INDICATOR	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA			5560 								(CAN) ON APPROACH TO PENTICTION NOSE GEAR LIGHTS DID NOT ILLUMINATE. INTRANSIT LIGHT WAS EXTINGUISHED & NOSE LIGHTS DID 	NOT ILLUMINATE DURING PRESS TO TEST. PILOT DID FLYBY OF TOWER & ALL LOOKED GOOD. HE THEN ELECTED NOT TO LAND BUT RETURN 	TOCALGARY WHERE HE DID ANOTHER PASS BY THE TOWER & AS A PRECAUTION. ALSO HAD EMERGENCY SERVICES CALLED OUT. AN UNEVENTFU	L LANDING WAS DONE & THE AIRCRAFT BROUGHT TO THE HANGAR WHERE THIS BULBS IN THE ANNUNICATOR WERE REPLACED P/N 327 AND GE	AR SWINGS COMPLETED WITH ALL SYSTEMS OPERATING NORMALLY. 		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2000092100009	20000921	00009	CE  	2000	9	21	CA000706025      	1	20000617	G	5751	991300003	AILERON         	RAYTHN      	STC100BEECH 	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					UPR/LWR JOINTS	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						B40		PCE50050			(CAN) DURING REPETITIVE AILERON STRUCTURE INSPECTION, FOUND SKIN CRACKS ALONG FORWARD/AFT UPPER AND LOWER SKIN LAP JOINT	S.  CRACKS (2 FOUND INITIALLY) RUN LATERALLY ALONG LAP JOINT.  ON SKIN REMOVAL, FOUND CORROSION UNDER SKIN AND 5 CRACKS 	VERYING FROM LESS THAN 1 INCH TO 3 INCHES LONG.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032600223	20010326	00223	EU  	2001	3	26	CA000706026      	1	20000618	G	6420	350A33211905	HOUSING         			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					T/R DRIVE SHAFT	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			898  								(CAN) DURING HUB REMOVAL TO C/W SB 65.00.38 (T/R SPYDER BEARING KIT INSTALLATION) THE KEY THAT ALIGNS HUB TO T/R SHAFT W	AS FOUND SHEARED & THE HUB HAD SPUN APPROX. 110 DEGREES. THE T/R LONG DRIVE SHAFT P/N 350A34-0110-07 WAS FOUND TO HAVE A	N APPROX 60 DEGREES TWIST IN IT.  FOLLOWING PARTS WERE REPLACED DUE TO SUSPECT T/R STRIKE. LONG DRIVE SHAFT, T/R HUB, T/	R GEAR BOX, T/R HUB BOLT,  T/R BLADES,  T/R COUPLE MGBOLTS, EXPANDABLE PIN, SPLIT BUSHINGS,  T/R PITCH LINKS.			1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001032600226	20010326	00226	SW  	2001	3	26	CA000706033      	1	20000201	G	2820		LINE            			MOONEY	M20   	M20D        	5870210	SW  	LYC   	O360  	O360A1D     	41514	EA  					FUEL SYSTEM	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				N	B	 	FALSE WARNING             	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA			6082 								(CAN) ON 1 FEB 2000 PILOT REPORTED FLUCTUATING FUEL PRESSURE GAUGE. ALSO IN THE PAST PILOTS FELT IT READ LOW AND SOMETIM	ES NOTICED A FUEL SMELL. FOUND: THE SHORT CURVED FUEL LINE (NOT SHOWN IN MANUAL)  THAT PASSES THROUGH THE CABIN BETWEEN 	THE FUEL SELECTOR & THE FUEL STRAINER HAD BEEN RUBBING WHERE IT PASSES THROUGH BULKHEAD. THE HOLE WAS AT THE TOP OF THE 	BEND AT THE HIGHEST POINT OFTHE FUEL SYSTEM. THEREFORE IT DID NOT LEAK BUT SENT OUT AN ODOR. WHEN RUNNING, AIR WOULD BE 	INJECTED THROUGH THIS HOLE  CAUSING LOW FUEL PRESSURE AND FLUCTUATIONS. A NEW LINE WAS MADE AND FUEL PRESSURE IS NOW NOR	MAL.	1	L	7	1 	3O	3	O	 	2A3     	E286				 
2000092100011	20000921	00011	CE  	2000	9	21	CA000706034      	1	20000327	G	7430	C2925010105	IGNITION SWITCH 			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					INTERNAL	DIRTY           	W				O	 	 	 	OTHER                   				Y	 	 	ENGINE STOPPAGE           			CL	CLIMB          	1			CA			24300			20593970A		20593970A			(CAN) ON MARCH 27, 2000, PILOT REPORTED ON CLIMB-OUT, ENGINE SUDDENLY RAN ROUGH AND COMPLETE ELECTRICAL FAILURE FOR 5 SE	CONDS.  CHECKED ALL WIRING AND ENGINE FOR ANY ABNORMAL SIGNS.  NONE FOUND.  RAN FINE ON GROUND, ETC.  OPENED IGNITION SW	ITCH AND FOUND A LITTLE DIRTY (BUT DRY).  CLEANED CONTACT PLATES AND LUBRICATED WITH ELECTRICAL LUBE AND RE-ASSEMBLED.  	PERFORMED TEST FLIGHT AND FOUND NOT EVEN A STUTTER.  AIRCRAFT WAS FLOWN 150 HRS SINCE THEN WITH NO DIFFICULTY.   NOTE:  	SUBMITTER NOT POSITIVE THAT THE IGNITION SWITCH CAUSED THIS.  COULD BE SOMETHING ELSE AND DID NOT THINK THE SWITCH WAS T	HAT BAD BUT COULD NOT FIND ANYTHING ELSE.	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001032600229	20010326	00229	SW  	2001	3	26	CA000706035      	1	20000504	G	6520	206031446001	CASTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R GEARBOX	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9069 								(CAN) CRACK FOUND AT AFT CASTING WHERE TAIL ROTOR GEARBOX MOUNTS IN TAILBOOM ON R/H HOLE. CASTING REMOVED BY OVERHAUL SH	OP FOR REPLACEMENT AND CRACK ALSO LOCATED IN LT MOUNTING AREA. CRACK WAS FOUND ON SCHEDULED 100 HOUR INSPECTION OF AIRCR	AFT.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000080300219	20000803	00219	SW  	2000	8	3	CA000706036      	1	20000607	G	6230	206010154003	WASHER          	BELL        	206011100021	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					LWR BLADE BOLT	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				71200		AAB54008		CAE832459			(CAN) DEFECT WAS FOUND DURING PREFLIGHT.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001031500099	20010315	00099	EU  	2001	3	15	CA000712002      	2	20000621	G	7313	VC070	INJECTOR        			MORAVN	Z142  	Z142        	       	EU  	AVIA  	M337  	M337AK      	 	EU  					FUEL SYSTEM	MISSING         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA			1124 					9241143			(CAN) DURING A CLIMB, THE ENGINE STARTED VIBRATING, AND RUNNING ROUGH. THE FLIGHT WAS CANCELLED AND THE AIRPLANE RETURNE	D SAFELY TO THE AIRPORT.  TROUBLESHOOTING FOUND THE PROBLEM TO BE A FUEL INJECTOR IN THE NR 1 CYLINDER. THE NOZZLE OF TH	E INJECTOR WAS MISSING.   A VISUAL INSPECTION OF THE INTAKE VALVE AND CYLINDER FOUND NO DAMAGE.  A COMPRESSION TEST WAS 	PERFORMED AND WAS NORMAL.  THE INJECTOR WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 			1	L	7	1 	3O	3	I	NT	A76EU   	EXPE3I				 
2001032600232	20010326	00232	SO  	2001	3	26	CA000712009      	1	20000611	G	3230	4032700	TRUNNION        		4550726     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT MLG	CRACKED         	W				O	 	 	 	OTHER                   				K		 	FLUID LOSS                			LD	LANDING        	1			CA			5638 								(CAN) - PIPER AIRCRAFT SETTLED LOWER TO LEFT SIDE ON LANDING.  INITIAL INSPECTION REVEALED FLAT LEFT MAIN OLEO & EVIDENC	E OF HYDRAULIC FLUID  LEAK ON LEFT GEAR AND UNDER LEFT WING.  FURTHER INSPECTION REVEALED AN APPROX 6 INCH CRACK ON AFT/	BOTTOM SIDE OFUPPER GEAR TRUNNION. ADDITIONAL INFO: PART AFFECTED HAS 5638 HRS PREVIOUS TAKEOFF.  LANDINGS OF THE DAY WE	RE REPORTED NORMAL.  AIRCRAFT OPERATES WITH INCREASED TAKEOFF  WEIGHT OF 7368 LBS IN ACCORDANCE WITH BOUNDARY LAYER RESE	ARCH VORTEX  GENERATOR KIT STC # SA00192SE, INSTALLED APRIL 1995.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031200445	20010312	00445	NM  	2001	3	12	CA000712011      	1	20000619	G	3230	69546002	CYLINDER        			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								688675			(CAN) DURING WALK AROUND,  AIRCRAFT HYDRAULIC FLUID WAS NOTICED COMING FROM THE LEFT HAND WHEEL WELL. FURTHER INVESTIGAT	ION FOUND THE FLUID WAS LEAKING FROM A CRACK IN THE MAIN LANDING GEAR TRANSFER CYLINDER. THE TRANSFER CYLINDER ASSY WAS 	REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001032600236	20010326	00236	SO  	2001	3	26	CA000712012      	1	20000606	G	2730	71056003	SPRING          	PIPER       	41963       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ELEVATOR BUNGEE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			774  								(CAN) DURING A ROUTINE INSPECTION, MAINTENANCE CREW WERE COMPLYING TO PIPER SB 626C AND FOUND THE ELEVATOR BUNGEE SPRING	 BROKE AT THE HOOK END. NO COMPLAINTS OR SNAGS WERE REPORTED OR DETECTED BY THE PILOT. IT WAS THEREFORE ASSUMED TO HAVE 	BROKEN AFTER THE AIRCRAFT LANDED.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032600237	20010326	00237	SO  	2001	3	26	CA000712013      	1	20000621	G	2810	531035	RETAINER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					FUEL CAP	SEPARATED       	W				A	 	 	 	UNSCHED LANDING         				D	K	 	INFLIGHT SEPARATION       	FLUID LOSS                		TO	TAKEOFF        	1			CA											(CAN)  WHEN THE AIRCRAFT WAS BEING REFUELED, THE GAS ATTENDANT HAD ROTATED THE GAS CAP TO REMOVE THE CAP. THIS ACTION IN	 TURN ROTATED THE RETAINER (P/N 531-035), CAUSING IT TO BECOME UNLOCKED FROM THE FILLER NECK. THE CAP WAS THEN PUT BACK 	ON AND LOCKED DOWN GIVING THE APPEARANCE OF BEING LOCKED. WHEN THE AIRCRAFT ROTATED ON TAKEOFF THE GAS CAP CAME OFF. THE	 RETAINER IS WHAT THE FUEL CAP LOCKS ONTO AND BECAUSE IT WAS NO LONGER LOCKED ONTO THE FILLER NECK THE CAP JUST FELL OFF	. IT WAS LATER FOUND THAT THE LOCKS ON THE RETAINER HAD TO BE BENT DOWN MORE TO PROVIDE A MORE SUITABLE LOCK FOR THE RET	AINER. THREE OF THE FUEL CAPS ON THE AIRCRAFT HAD THE SAME PROBLEM.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000100300239	20001003	00239	EA  	2000	10	3	CA000712014      	1	20000712	G	2750		ROD END         	DHAV        	C3CF1057    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					RIVIT	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE40906			(CAN) WHILST CARRYING OUT A 100 HOUR INSPECTION OF THE CONTROL SYSTEM, THE ENGINEER NOTICED THAT THE RT FLAP PUSH/PULL R	OD END FITTING APPEARED TO BE LOOSE.  THE ROD WAS REMOVED FROM THE AIRCRAFT FOR FURTHER INVESTIGATION.  IT WAS FOUND THA	T THE RIVETS WHICH SECURE THE END FITTING TO THE FLAP PUSH/PULL ROD WERE LOOSE. THE RIVETS WERE REMOVED, THE END FITTING	 REMOVED AND A DETAILED INSPECTION CARRIED OUT - NO DAMAGE WAS FOUND TO THE FITTING OR THE ROD.   IT WAS RE-ASSEMBLED AN	D RE-RIVETED.   IT SHOULD BE NOTED THAT FAILURE OF THESE RIVETS WOULD HAVE CAUSED AN ASYMMETRIC FLAP CONDITION.		1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100300109	20001003	00109	EA  	2000	10	3	CA000712015      	1	20000621	G	5230	C3FS23843	LOCK            	DHAV        	C3FS21925   	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					LOCK	MALFUNCTIONED   	W				B	 	 	 	EMER. DESCENT           				O	 	 	OTHER                     			CR	CRUISE         	1			CA								PCE92418			(CAN) DURING FLIGHT IN ROUGH TURBULENCE, THE REAR CARGO DOOR CAME OPEN.  THE FLIGHT CREW ADVISED THAT THE LOCKS HAD BEEN	 SECURED AND LOCKED.  THE AIRCRAFT IS HERE UNDERGOING REPAIR.  INSPECTED THE LOCKS AND CAN FIND NO PROBLEM WITH THEM AS 	OF YET.				1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001040200267	20010402	00267	NE  	2001	4	2	CA000712016      	2	20000621	G	7261	3020290	BREATHER TUBE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	LEAKING         	W				B	 	 	 	EMER. DESCENT           				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE AIRPLANE CONSUMED APPROXIMATELY 5 LITERS OF OIL IN 1 HOUR OF FLIGHT. THE CENTRIFUGAL BREATHER WAS REMOVED FOR 	INSPECTION AND DEEMED UNSERVICEABLE BY THE PRATT & WHITNEY FIELD REP ON HAND. A REPLACEMENT PART WAS INSTALLED.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100300110	20001003	00110	CE  	2000	10	3	CA000712017      	1	20000703	G	3246	10320400	BOLT            	PARKERHANFIN	40179       	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					BOLT	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						02		PCE19192			(CAN) WHILE CARRYING REGULAR MAINT ON A/C, NOTICED ONE NUT WAS MISSING FROM WHEEL HUB BOLTS.  UPON FURTHER INVESTIGATION	, FOUND THAT BOLT HAD SHEARED AND NUT HAD FALLEN OFF, AT WHICH POINT, BOLT BACKED OUT OF HUB AND HIT BRAKE TORQUE PLATE,	 BENDING BOLT AND SCORING TORQUE PLATE.  WHEEL AND TORQUE PLATE WERE REPLACED.  BOLT HAD 173.7 HRS SINCE NEW.  IT WAS RE	PLACED AT LAST TIRE CHANGE.  STANDARD PROCEDURE IS ALL WHEEL HUB BOLTS ARE REPLACED AT TIRE CHANGE AND TORQUED IAW MFGS 	SPECS.  THIS IS SECOND OCCURENCE OF THIS BOLT FALLING IN LAST 2 YRS.  BOLT PART NUMBER IS 103-20400, BUT MAY ALSO BE REC	OGNIZED UNDER AN5-40A.  (X)	1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000100300111	20001003	00111	EA  	2000	10	3	CA000712018      	1	20000703	G	2731	C3TE1312	TAB             			DHAV  	DHC3  	DHC3        	2800202	EA  										SERVO TAB	TWISTED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE 100 HOUR INSPECTION OF THE TAIL OF THE TURBO OTTER, THE ENGINEER FOUND THE ELEVATOR SERVO TAB WAS	 BENT AND TWISTED.  FURTHER EXAMINATION FOUND THAT THE SERVO TAB WAS BENT AND TWISTED.  SUBMITTER STATED THERE HAVE BEEN	 NUMEROUS SDRS FILLED OUT ON THE SERVO TAB OF THE TURBO OTTER.				1	H	7	1 	3R			 	A815    					 
2000100300112	20001003	00112	EA  	2000	10	3	CA000712019      	1	20000703	G	2730	C6CF113711	BELLCRANK       	DHAV        	C6CF11371   	DHAV  	DHC6  	DHC6200     	       	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABLE QUADRANT	TWISTED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCEPG0034	BU8721		(CAN) WHILE CARRYING OUT AD CF-72-06R4 PART III, THE ELEVATOR QUADRANT WAS FOUND TO BE RUBBING AGAINST THE SIDE OF THE C	ABLE GUARD AS DESCRIBED IN THE AD.  THE QUADRANT ASSEMBLY INCLUDING SUPPORT BRACKET WAS REPLACED PRIOR TO FLIGHT.  (X)					1	H	7	2 	3T	4	T	 	A9EA    	E4EA	6	C	P15EA	 
2001032600471	20010326	00471	CE  	2001	3	26	CA000712021      	1	20000704	G	5741	9041101S	FITTING         			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  					LT WING ROOT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DISCOVERED DURING LPI OF FITTINGS CALLED UP BY AD. CRACK WAS FOUND AT RADIUS OF WING ROOT ATTACH FLANGE ON F	ORWARD SIDE OF FITTING. BY THE SLOT ON THE SIDE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032600472	20010326	00472	CE  	2001	3	26	CA000712022      	1	20000704	G	5741	9041102S	FITTING         			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  					RT WING ROOT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED AT RADIUS OF WING ROOT ATTACH FLANGE ON FORWARD SIDE OF FITTING.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032600473	20010326	00473	CE  	2001	3	26	CA000712023      	1	20000704	G	5741	9041102S	FITTING         			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					RT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WING FITTING CRACKED AT RADIUS PORTION OF UPPER SURFACE OF WING FITTING. SLOT AREA.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032600474	20010326	00474	CE  	2001	3	26	CA000712024      	1	20000704	G	5741	9041063S	FITTING         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					LT WING ROOT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED AT RADIUS OF WING ROOT ATTACH FLANGE ON FORWARD SIDE OF FITTING. SLOT AREA.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001031200446	20010312	00446	WP  	2001	3	12	CA000712026      	2	20000612	G	7321		GEAR            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	FUEL CONTROL	FAILED          	W				E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		LD	LANDING        	1			CA								P44717C	911170		(CAN) UPON SHORT FINAL ENGINE FLAMED OUT DUE TO THE DRIVE THAT TURNS THE FUEL PUMP AND FCU STOPPED. CAUSE UNKNOWN AT THI	S TIME. AIRCRAFT LANDED WITHOUT INCIDENT AND THE ENGINE WAS REPLACED. AIRCRAFT RETURNED TO SERVICE. TEARDOWN TO BE ACCOM	PLISHED THIS WEEK. 				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2001032600480	20010326	00480	CE  	2001	3	26	CA000712028      	1	20000623	G	6123	A15941	SPRING          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC3Y	HCC3YF2     	GL  	PROP FEATHER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1342 							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. FEATHER SPRING FOUND CRACKED.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P25EA	 
2001032600081	20010326	00081	CE  	2001	3	26	CA000712029      	1	20000623	G	6123	B15941	SPRING          	HARTZL      	PHCC3YF2FU  	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC3Y	HCC3YF2     	GL  	PROP FEATHER	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1342 		EB1378					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTON.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P25EA	 
2000100300113	20001003	00113	GL  	2000	10	3	CA000712030      	3	20000622	G	6111		PROPELLER       	MCAULY      	1C160DTM    	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	LE & FACE	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				21770		723286		L3643127A	723286		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000100300114	20001003	00114	CE  	2000	10	3	CA000712031      	1	20000623	G	6121	D22011	HUB             	HARTZL      		CESSNA	172   	172D        	2072410	CE  	FRNKLN	6AV350	6A350C2     	27043	EA  	HARTZL	HCC2Y	HCC2YF1     	GL  	C/S SEAL AREA	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			14200					610653	AM2505		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E9EA	5	C	P920	 
2001032600082	20010326	00082	SW  	2001	3	26	CA000713002      	1	20000120	G	2720	45300655	BRACKET         			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					RUDDER PULLEY	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10569								(CAN) ON INSPECTION BOTH LT AND RT RUDDER PULLEY BRACKETS WERE FOUND CRACKED AT THE TOP PORTION. PULLEY BRACKETS WERE PA	TCHED USING THICKER ALUMINUM. FURTHER INSPECTIONS FOUND TWO OTHER  PULLEY BRACKETS CRACKED IN THE SAME LOCATION.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001032600083	20010326	00083	CE  	2001	3	26	CA000713003      	1	20000303	G	3230	MS203921C21	CLEVIS PIN      	CESSNA      	12805043    	CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360GB     	17025	SO  					DOWNLOCK ACTUATO	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10038								(CAN) ON INSPECTION OF LANDING GEAR DOWNLOCK ACTUATOR THE RT CLEVIS PIN HALF WAS MISSING. THE CLEVIS PIN WAS REMOVED AND	 FOUND TO BE SHEARED. A NEW PIN WAS INSTALLED.ON FURTHER INSPECTIONS TWO OTHERS WERE FOUND SHEARED AND MANY OTHER BENT O	N DIFERENT AIRCRAFT.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2000080200210	20000802	00210	SW  	2000	8	2	CA000713004      	1	20000509	G	6230	206010152101	NUT             	BELL        	206011100021	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					OTBD SHANK RADIU	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			69950								(CAN) DURING A SCHEDULED OVERHAUL OF THE ABOVE DESCRIBED MAIN ROTOR HUB ASSEMBLY, A COMPONENT WITHIN THIS ASSEMBLY KNOWN	 AS THE MAST NUT WAS FOUND TO HAVE A CRACK INDICATION. THIS WAS DETECTED DURING THE MAGNETIC PARTICLE INSPECTION. THIS N	UT HAS SINCE BEEN SENT TO BELLL HELICOPTER FOR FURTHER INSPECTION AND TESTING.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001031200447	20010312	00447	NM  	2001	3	12	CA000713005      	1	20000602	G	3246	31414	WHEEL           			BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN WHEEL ASSEMBLY FOUND DAMAGED FROM A BRAKE DRIVE KEY COMING LOOSE.BRAKE ASSEMBLY DAMAGED BY WHEEL DRIVE KEY CO	MING LOOSE. MAIN WHEELAND  BRAKE ASSEMBLY REPLACED AND CHECKS SERVICEABLE. 					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000091900001	20000919	00001	EA  	2000	9	19	CA000713006      	1	20000608	G	2710	C2CF1125A	CONTROL CABLE   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					RT LWR DOOR BKHD	FRAYED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA								JP206759			(CAN) DURING DISMANTLING REQUIRED BY AD CF-98-37, ALL CABLES WERE CHANGED AS PRECAUTIONARY MEASURE.  HOWEVER, UPON REMOV	AL, CABLE WAS FOUND WORN AND FRAYED AT LOWER RT DOOR BULKHEAD PULLEY.  AREA IS DIFFICULT TO INSPECT AT ROUTINE INSPECTIO	N.  (X)				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001021400002	20010214	00002	NE  	2001	2	14	CA000713008      	2	20000613	G	7420	37C311098P101	IGNITION LEAD   	GE          	CF7002D2    	AMD   	FALCON	FALCON20    	2730103	EU  	GE    	CF700 	CF7002D2    	30010	NE  					ENGINE	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						245VO95		245VO95			(CAN) DURING ROUTINE MAINTENANCE, THE IGNITION LEAD WAS REMOVED FROM THE IGNITOR PLUG TO FACILITATE REPLACEMENT OF THE P	LUG. IT WAS NOTED THAT THE LEAD WAS STUCK IN THE PLUG. REMOVAL OF THE LEAD CAUSED THE PIN TO BECOME DETECHED FROM THE AS	SEMBLY. THE LEAD WAS REPLACED WITH A NEW SERVICEABLE UNIT, NO FURTHER ACTION TAKEN.				2	L	7	2 	4F	4	F	RT	A7EU    	E7EA				 
2000091900002	20000919	00002	EU  	2000	9	19	CA000713009      	1	20000615	G	2400	AZS5	CIRCUIT BREAKER 			ZLIN  	242   	Z242L       	9970204	EU  										C/B PANEL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			35440								(CAN) AS PART OF AN INSPECTION OF THE AIRCRAFT WIRING AND PROTECTON DEVICES, IT WAS FOUND THAT (2) CIRCUIT BRAKER SWITCH	ES FAILED TO PERFORM THEIR INTENDED FUNCTION. THE BREAKER SWITCHES WERE TESTED AT TWICE THEIR RATED CURRENT FOR A PERIOD	 OF 3 MINUTES AND THEY WOULD NOT OPEN.  THE SWITCHES APPEAR TO BE NON MIL SPEC.  THE REMAINING CIRCUIT BREAKERS WORKED A	S INTENDED.  ALL BREAKER SWITCHES ARE TO BE REPLACED WITH MS 24508-B-X MIL SPEC CIRCUIT BREAKER SWITCHES.   NOTE:  NORMA	LLY CIRCUIT BREAKERS AND SWITCHES ARE ON CONDITION AND ARE NOT TESTED UNDER THESE CIRCUMSTANCES AS PART OF NORMAL MAINTE	NANCE PRACTICES.	1	L	7	1 	3O			0	A76EU   					 
2001031200449	20010312	00449	EA  	2001	3	12	CA000713010      	1	20000614	G	5314		SKIN            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	FUSELAGE	BULGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			31460					PCE86483	237795		(CAN) DURING ROUTINE INSPECTION THE AIRCRAFT SKIN WAS FOUND BULGING OUTWARDS & 3 RIVETS WERE PULLED THROUGH THE SKIN.  						2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2000100200065	20001002	00065	EU  	2000	10	2	CA000713011      	1	20000617	G	5521	9408308602	BEARING         		5552012194  	PILATS	PC12  	PC1245      	       	EU  										ON CNTRL LEVER	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			24260								(CAN) - ON INSPECTION, FOUND BEARING TO BE LOOSE IN ITS BORE.  BEARING IS AT ATTACH POINT FOR CONTROL INPUT LEVER/ROD.  	BEARING RE-BONDED IN BORE PER PILATUS TECH MEMO EF-12-TM-778.					1	L	7	1 	3T			RT	A78EU   					 
2000091900003	20000919	00003	EA  	2000	9	19	CA000713012      	2	20000619	G	8530	73806	PUSHROD         	LYC         		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	INTAKE	BENT            	W				A	 	 	 	UNSCHED LANDING         				R	E	 	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA			29640					L2330615	R770128		(CAN) - BENT PUSHROD CAUSING POWER LOSS AND ROUGH RUNNING ENGINE. - REASON FOR BENDING UNKNOWN.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2000091900004	20000919	00004	CE  	2000	9	19	CA000713013      	1	20000619	G	2740		BRACKET         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LEFT STABILIZER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			69000					9011950H	760187		(CAN) THE ANGLE TAIL CONE REINFORCEMENT WAS CHANGED AS IT WAS CRACKED.  P/N 0712048-7 WAS REPLACED WITH NEW PART USING E	XISTING RIVET SIZE AND PATTERN.  THE BRACKET ON THE LEFT STABILIZER WAS CHANGED AS IT WAS FOUND TO BE CRACKED.  P/N 0712	3021 WAS REPLACED WITH NEW PART USING EXISTING RIVET SIZE AND PATTERN. THE REINFORCEMENT STABILIZER HINGE (BOX) ON THE H	ORIZONTAL STABILIZER WAS CHANGED.  P/N 0732101-4 WAS REPLACED WITH NEW PART USING EXISTING RIVET SIZE AND PATTERN.			1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2000091900005	20000919	00005	CE  	2000	9	19	CA000713014      	1	20000626	G	2110	1H953	CHECK VALVE     			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT PNEU TAILCON	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA			38960					71752			(CAN) DURING THE PHASE 1,2,3 & 4 INSPECTION, AN OPERATIONAL CHECK OF THE INFLATABLE DOOR SEAL WAS CARRIED OUT. THE RESUL	TING TEST FOUND THAT PRESSURE WAS ZERO DOWNSTREAM FROM THE REGULATOR MEASURED AT MAIN DOOR SEAL INFLATING FITTING.  ALSO	 NOTICED THE DE-ICING BOOTS WERE NOT INFLATING TO THEIR FULL FIRMNESS.  THE AIRCRAFT WAS TAKEN OUT FOR A GROUND RUN WITH	 RT ENGINE ONLY OPERATING TO SEE IF THE SAME RESULTS WOULD APPEAR.  ALL SYSTEMS WERE OPERATING NORMALLY.  TROUBLESHOOTIN	G THE PNEUMATIC SYSTEM REVEALED THE BLEED AIR CHECK VALVE P/N 1H95-3 FOR THE LEFT HAND ENGINE HAD THE FLAPPER VALVE BROK	EN FROM ITS HINGE ASSEMBLY.  AIR WAS ESCAPING VIA THE BLEED AIR LINE TO LT ENGINE.	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000091900006	20000919	00006	CE  	2000	9	19	CA000713015      	1	20000703	G	3110	MS24693BB30	SCREW           	CESSNA      	551818694   	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					SCREW	INADEQUATE      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								71749			(CAN) DUE TO PREVIOUS SDR (APR/MAR 99), INSPECTION OF GLARESHIELD ATTACHING SCREWS RESULTED IN FINDING SLIGHT CHAFING (D	ISCOLORATION) OF WIRE BUNDLE (3 PLACES) THAT RUNS THROUGH INSTRUMENT PANEL SUPPORT ASSEMBLY, INSULATION NOT BROKEN.  WIR	E BUNDLE SPY WRAPPED, SCREWS SHORTENED TO ONE FULL THREAD PROTRUDING PAST NUTPLATE LOCKING AS PER CAMPAIGN NOTICE 851-01	0 MAR 3/99.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001031200450	20010312	00450	EA  	2001	3	12	CA000713016      	2	20000624	G	7321	324475316	FUEL CONTROL    			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				6952 							(CAN) FUEL CONTROL UNIT WAS REPLACED. ENGINE RUN CARRIED OUT, TEST OKAY.AIRCRAFT RELEASED TO SERVICE. 						2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001031200451	20010312	00451	GL  	2001	3	12	CA000713017      	1	20000713	G	2710	2057500000	HINGE           			DIAMON	DA20  	DA20A1      	       	GL  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - CRACKS FOUND ON SEVERAL CONTROL SURFACE HINGE ON AIRCRAFT OPERATED IN THE  U.K. -  CRACKS VISABLE AS BUBBLED PAI	NT EXPOSED ON LOWER SURFACE.- ON REMOVAL OF PAINT, CRACK WAS FOUND RUNNING FROM HINGE PIN HOLE TO  SURFACE. -  PRESSED H	INGE BUSHING WAS REMOVED FROM HINGE AND MINIMAL CORROSION WAS  FOUND. - HINGE, REMOVED AND REPLACED WITH NEW.				1	L	7	1 	3O			NT	TA4CH   					 
2001011105115	20010111	05115	EA  	2001	1	11	CA000714002      	1	20000624	G	3411		INDICATOR       			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKE OFF CO-PILOT NOTICED NO AIRSPEED ON PFD2, TAKE OFF WAS ABORTED AND AIRCRAFT RETURNED TO GATE.THEY FOUND TH	E CO-PILOT COVER THAT WAS NOT REMOVED PRIOR TO DISPATCHING THE AIRCRAFT.					2	L	7	2 	4F			RT	A21EA   					 
2001031200452	20010312	00452	NE  	2001	3	12	CA000714003      	2	20000624	G	7230		BLADE           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COMPRESSOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								807040			(CAN) DURING SCHEDULE BORESCOPE INSPECTION SEVERAL STAGE ON COMPRESSOR BLADES ON NR 1 ENGINE, FOUND NICKS. 						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031200453	20010312	00453	EA  	2001	3	12	CA000714004      	1	20000624	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ON DESCENT THE CAPTAIN FRONT WINDSHIELD CENTRE PLY SHATTERED. 						2	L	7	2 	4F			RT	A21EA   					 
2001031200454	20010312	00454	EA  	2001	3	12	CA000714005      	1	20000628	G	5210		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  										PAX DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FROM CVG TO MKE, THE FLIGHT CREW REPORTED DURING CLIMB OUT THE PAX DR OUT HNDL CAUTION MESSAGE APPEARED ON ED1. TH	E FLIGHT CREW INITIATED EMERGENCY DESCENT, FOLLOWING THE QRH PROCEDURE. MAINTENANCE ACTION: COMPLIED WITH OPERAITONAL CH	ECK REQUIREMENTS AS PER AMM, FOUND SERVICEABLE. 				2	L	7	2 	4F			RT	A21EA   					 
2001011105098	20010111	05098	EA  	2001	1	11	CA000714006      	1	20000628	G	5240		PANEL           			CNDAIR	CL600 	CL6002B19   	       	EA  										O2 SERVICE	OPEN            	W				D	 	 	 	RETURN TO BLOCK         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN)  ON CLIMB OUT OF MEMPHIS, THE CREW REPORTED A LOUD NOISE COMING FROM THE R/H FORWARD SECTION ASSOCIATED WITH A STA	LL FAIL MESSAGE.MAINTENANCE FOUND THE O2 SERVICING PANEL OPEN. THE PANEL WAS CLOSE AND THE AIRCRAFT RETURNED TO SERVICE.	 				2	L	7	2 	4F			RT	A21EA   					 
2001031200455	20010312	00455	EA  	2001	3	12	CA000714007      	1	20000702	G	3251		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG STEERING	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								807042			(CAN) AFTER TAKE OFF, NOSE GEAR WOULD NOT RETRACT, WITH ASSOCIATED MSG, WOW INPUT, STEERING FAIL ETC. CREW DECLARED AN E	MERGENCY AND COMPLETED AN UNEVENTFUL LANDING, RETURNING TO THEIR ORIGINATING BASE. MAINTENANCE REPLACED STEERING HARNESS	 P/N: DOWTY 17300-233 AND NOSE GEAR RETRACT ACTUATOR P/N: DOWTY 16520-101. 				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031200456	20010312	00456	EA  	2001	3	12	CA000714008      	1	20000702	G	2613		WARNING SYSTEM  			CNDAIR	CL600 	CL6002B19   	       	EA  										EICAS	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED DURING CRUISE L 14TH DUCT WARNING MESSAGE APPEARED ON EICAS WITH AURAL BLEED AIR DUCT MES	SAGE. THE FLIGHT CREW INITIATED LT ENGINE SHUT-DOWN AND LANDED AT THE NEAREST AVAILABLE AIRPORT.  TROUBLESHOOTING CARRIE	D OUT AND NOT ABLE TO DUPLICATE DEFECT AT THIS TIME.				2	L	7	2 	4F			RT	A21EA   					 
2001031200457	20010312	00457	NM  	2001	3	12	CA000714009      	1	20000620	G	2120	214N211512	DUCT            			BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					PAX AIR	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA						A8310					(CAN) IN FLIGHT, LOUD WISHING NOISE FROM CEILING AT ROW 12 AND PASSENGER WERE COMPLAINING ABOUT VERY COLD TEMPERATURE. A	FTER INVESTIGATION, MAINTENANCE FOUND A LEAK AT AIR PLENUM AROUND R2/L2 DOOR AREA. LEAK WAS COMING FROM A PREVIOUS REPAI	R. PLENUM REPAIRED AND CHECKED SERVICEABLE. 				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001031200459	20010312	00459	NE  	2001	3	12	CA000714011      	2	20000622	G	7200		ENGINE          	RROYCE      	RB21122B02  	LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					NR 1	OVERHEATED      	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		TO	TAKEOFF        	1			CA						10164		10164			(CAN) DURING TAKE OFF OUT OF LAS VEGAS, TGT ON NR 1 ENGINE WENT UP TO 740 DEG FOR 2 SEC. E.P.R. BROUGHT BACK IMMEDIATELY	 TO MAINTAIN 728 DEG. WHEN SAFELY AIRBORNE, E.P.R. REDUCED TO .462 MAINTAIN 725 DEG. BECAUSE OF PREVIOUS PROBLEM WITH TH	IS  ENGINE, YYZ MAINTENANCE REDUCE N2 BY 5 CLICKS AND AIRPLANE FLEW BACK TO YMX WITH NO PAX FOR ENGINE CHANGE. WAITING F	OR SHOP REPORT. 			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001031200461	20010312	00461		2001	3	12	CA000714013      	4	20000630	G	2565	416N21133	RETAINER        			BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					GIRT BAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								30732			(CAN) DURING SLIDE/RAFT REPLACEMENT, THE GIRT BAR RETAINER PLATE FOUND SPLIT IN HALF DUE TO EXCESSIVE CORROSION. PLATE R	EPLACED AND FLEET CAMPAIGN WILL BE DONE TO VERIFIED THE CONDITION OF THE PLATE AS PER SPECIAL INSPECTION 3-25-30 REV-0. 					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001031200465	20010312	00465	WP  	2001	3	12	CA000714017      	1	20000606	G	7830		CABLE           			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					THRUST REVERSER	OUT OF RIG      	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								P657715D			(CAN) REJECTED TAKEOFF DUE LEFT HAND ENGINE REVERSER UNLOCK AMBER LIGHT ON. QUICK REFERENCE HANDBOOK PROCEDURE CARRIED O	UT. REDUCING POWER RESULTED IN LIGHT GOING OUT. REVERSER RETRACTED. RE-RIGGED UNLOCK LATCH CABLE. OPERATION CHECKED NORM	AL. 				2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001031200469	20010312	00469	EA  	2001	3	12	CA000714021      	1	20000610	G	3260		UPLOCK TARGET   			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA								807264			(CAN) EICAS (ENGINE INDICATION AND CREW ALERT SYSTEM) MESSAGE FOR DISAGREEMENT FOR LANDING GEAR RETRACTION, (FOR UP LOCK	) AIRCRAFT RETURNED TO LAND IN PHILADELPHIA AFTER QRH PROCEDURE APPLIED.AFTER INSPECTION, FOUND THE UP LOCK TARGET TO BE	 LOOSE. RE-TIGHTENED THE TARGET, GEAR SWING COMPLETED, LANDING GEAR CHECKED SERVICEABLE. 				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031200470	20010312	00470	WP  	2001	3	12	CA000714022      	1	20000613	G	2720	5616068501	BRACKET         			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					RT ATTACH  LUG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P657537D			(CAN) FIRST OFFICER RUDDER PEDAL ATTACH BRACKET CRACKED AT FORWARD RT ATTACH LUG RADIUS. AD 89-14-02. REPLACED BRACKET. 						2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2000091900007	20000919	00007	GL  	2000	9	19	CA000714024      	3	20000302	G	6114		HUB             	MCAULY      												MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER HUB	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				38800							(CAN) HUB MOUNTING DOWEL STUD WAS STRIPPED DUE TO AN EXCESSIVE TORQUE AT INSTALLATION.  HUB S/N 733929 REMOVED FROM SERV	ICE AND REPLACED BY S/N 775546.  (X)															5	C	P22EA	 
2000091900008	20000919	00008	NE  	2000	9	19	CA000714025      	3	20000412	G	6114	51430	BRACKET         	HAMSTD      		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	BRACKET	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			43630					JP211684	T34151		(CAN) BARREL P/N S8462, S/N T34151 FOUND CORRODED BEYOND REPAIRABLE LIMIT IAW BARREL BLADE BORE INSIDE DIAMETER SPECIFIC	ATIONS.  REPLACED BY BARREL S/N: NO-65520.  ONE BRACKET P/N 51430 FOUND CRACKED IN RETENTION TEETH AND WAS REPLACED BY N	EW PARTS.				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2000091900009	20000919	00009	NE  	2000	9	19	CA000714029      	2	20000616	G	8500		GASKET          	ORENDA      		DHAV  	DHC3  	DHC3        	2800202	EA  	ORENDA	OE600A	OE600A      	 	NE  					GASKETS	BLOWN           	W				A	 	 	 	UNSCHED LANDING         				Y	 	 	ENGINE STOPPAGE           			CL	CLIMB          	1			CA								OE600A0016			(CAN) AIRCRAFT CENTER FUEL TANK INADVERTENTLY FUELED WITH JET B IN KANGIRSUK, QUE ALTHOUGH SEALED DRUM CLEARLY MARKED JE	T B IT ALSO LABELLED GASOLINE 100 LL NR 19 OF 30 ON M.   AIRCRAFT THEN FLEW FROM YAS TO MNR CAMP AT KANGISAVIP LAKE USIN	G ONLY FIRST TANK, UNLOADED AND RETURNING TO YAS.  JUST PRIOR TO TAKEOFF, PILOT SELECTED CENTER TANK FOR RETURN TRIP.  J	UST AFTER LIFT OFF, ENGINE BEGAN RUNNING ROUGH AND SUFFERED REDUCTION IN POWER OUTPUT, AN INCREASE IN  COOLANT TEMP AND 	PRESSURE ALSO NOTED.  SUCCESSFUL FORCED LANDING CARRIED OUT.  AN INTERNAL INSP CARRIED OUT REF. C AR625 APP.G . INSP REV	EALED BLOWN HEADGASKET.	1	H	7	1 	3R	3	V	 	A815    	E0006A				 
2001031200475	20010312	00475	EA  	2001	3	12	CA000714030      	2	20000616	G	7322	MA3PA	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA				2183 				L1972515	KC015		(CAN)  CARBURETOR REPLACED - MALADJUSTED.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001032600241	20010326	00241	CE  	2001	3	26	CA000714031      	1	20000621	G	7810	12502632	EXHAUST PIPE    			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					ENGINE	BURNED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) EXHAUST COLLECTOR FOUND BURNED AND CRACKED.						1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2001031200476	20010312	00476	CE  	2001	3	12	CA000714032      	1	20000622	G	5751	991300009	SKIN            		B100        	BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BE39					(CAN) CRACK DISCOVERED ON THE TOP OF THE AILERON SKIN.SKIN REPLACED.AILERON REINSTALLED.						1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2000091900010	20000919	00010	GL  	2000	9	19	CA000714033      	3	20000624	G	6111	FC8475B14	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	LT HUB PROP	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			69800	37420				L286061A	CJ283		(CAN)  BLADES REPLACED NEW:  21 OCT 83 - PAGE 2 OF LOG.  TSN:  3742.3.  LAST COMPLETE OVERHAUL:  15 MAR 99 - PAGE 16 OF 	LOG. TSO: 6947.93.  PROPELLER TIME SINCE NEW - EXCEPT FOR BLADES:  5459.4.  GREASE SPLASH DETECTED ON A/C SIDE OF FUSELA	GE AND ICE SHIELD.   GREASE LEAK FURTHER DETECTED AT ROOT OF NR 1 BLADE.  SOME PLAY IN PITCH OF BLADE.  PREVIOUS OVERHAU	LER INFORMED.  PROPELLER RECALLED TO OVERHAUL SHOP.  REMOVED AND SHIPPED FOR REPAIRS.  A/C AFTT: 8637.2 HRS.  ENG TSO: 1	104.6 HRS.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2000080200211	20000802	00211	EU  	2000	8	2	CA000714034      	1	20000503	G	5310	145201	CARGO HOOK      	BREEZE      	A25LT       	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					CABLE END	TWISTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			HO	HOVERING       	1			CA			54560			3186		CAE835697			(CAN) THE PILOT CAME BACK FROM WORK AND REPORTED HE COULD NOT LATCH LOAD ON  CARGO HOOK.  A VISUAL INSP ON CARGO HOOK EM	ERG RELEASE CABLE SHOWED THERE WAS TOO MUCH STRAIN ON CABLE THAT CAUSED MECHANICAL RELEASE TO MOVE THE INTERNAL HOOK MEC	HANISM FROM LATCHED TO UNLATCHED MODE.  SHOCK LOAD COULD THEN RELEASE LOAD FROM HOOK.  TENSION ON CABLE CAME FROM POOR R	OUTING UNDER FUSELAGE COCKPIT T HANDLE.  MIN BEND RADIUS NOT DONE WHEN INSTALLING THE CABLE WHICH GAVE TOO MUCH STRAIN T	O WHOLE ASSY.  PILOT TWISTED SWAGED END OF CABLE BY TRYING TO PUSH T HANDLE ON FLOOR ON FEW OCCASIONS.  NEW UPPER RELEAS	E CABLE INSTALLED, RE-ROUTED, AND ASSY IS NOW WORKING  PROPERLY.	1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2000091900011	20000919	00011	SO  	2000	9	19	CA000714036      	1	20000604	G	2421	902241	FAN BLADE       	FORD        	ALY6421     	PIPER 	PA44  	PA44180     	7104402	SO  										LT ALTERNATOR	DISINTEGRATED   	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13680			6L000102					(CAN) DURING RUN-UP, LEFT ALTERNATOR WAS REPORTED NOT CHARGING, FLIGHT CANCELLED.  AME WALKING UP TO LEFT ENGINE, FOUND 	TWO METAL SHARDS STICKING OUT OF NOSE BOWL COWLING.  INSPECTION REVEALED THAT THE ALTERNATOR COOLING FAN DISINTEGRATED (	ALL BLADES WERE GONE FROM BEHING THE PLATE) AND THE TWO PIECES STUCK IN THE COWLING WERE BLADES.  FIELD WIRE FOUND CUT. 	  NO EVIDENCE OF JAMMING (NO DAMAGE TO ALT BODY) OR BELT SLIPPAGE.  NEW ALTERNATOR INSTALLED AND FIELD WIRE REPAIRED.			1	L	7	2 	3O			 	A19S0   					 
2000100200097	20001002	00097	SO  	2000	10	2	CA000714037      	1	20000614	G	7160	6367400	SCREW           	PIPER       	6577800     	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	THUMB SCREW	WORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA								L4002627A	A56007		(CAN) THE RETAINING BOLT FOR THE AIR FILTER HOUSING BACKED OFF FROM THE TORQUED POSITION AND ALLOWED THE HOUSING TO MOVE	 FORWARD AND STRIKE THE PROPELLER DURING FLIGHT.  A VIBRATION WAS FELT BY THE PILOT AND HE RETURNED THE AIRCRAFT TO BASE	 AND LANDED SAFELY.  MAINTENANCE INSPECTION REVEALED THAT THE FIBER LOCK ANCHOR NUT IN THE AIR FILTER HOUSING WAS IN WOR	N CONDITION WITH LITTLE OR NO LOCK FEATURE REMAINING.  A FLEET CAMPAIGN TO CHECK ALL SIMILAR INSTALLATION IS IN PROGRESS	.  (ENGINE/PROP REMOVED FOR REPAIR.)		1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000100200098	20001002	00098	EA  	2000	10	2	CA000714038      	2	20000525	G	8530		PUSHROD         	LYC         		PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  					PUSHROD	BENT            	W				A	E	 	 	UNSCHED LANDING         	ENGINE SHUTDOWN         			E	 	 	VIBRATION/BUFFET          			AP	APPROACH       	1			CA			40000					L32867A			(CAN) CREW EXPERIENCED ROUGH RUNNING ENGINE (RT) WHILE ON APPROACH.  CREW POWERED BACK, LANDING WITHOUT FURTHER INCIDENT	.  UPON INVESTIGATION BY MAINTENANCE, IT WAS DISCOVERED THAT 2 NUTS HAD BACKED OFF ON THE COVER PLATE FOR THE ROCKER PIN	 CAUSING THE PLATE TO FALL OFF.  THIS CAUSED THE PIN TO MOVE ITS WAY OUT OF THE CYLINDER CAUSING THE PUSHROD TO BEND AND	 SUBSEQUENT OIL LEAKAGE.  CYLINDER ASSEMBLY WAS REPLACED.  AIRCRAFT RELEASED TO SERVICE WITHOUT FURTHER INCIDENT.			1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2000100200099	20001002	00099	EA  	2000	10	2	CA000714039      	1	20000614	G	2435	30F1611C	GENERATOR       	BENDIX      		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					GENERATOR	FAILED          	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			CA				27700		R1081M					(CAN) GENERATOR NOT SUPPLYING POWER.						1	H	7	1 	3R	3	R	 	A815    	5E2				 
2000100200100	20001002	00100	NE  	2000	10	2	CA000714040      	2	20000618	G	8530		CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					CYLINDER ASSY	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				28600							(CAN) NR 1 CYLINDER HEAD CRACKED.						1	H	7	1 	3R	3	R	 	A815    	5E2				 
2000100200242	20001002	00242	EA  	2000	10	2	CA000718017      	2	20000626	G	8550	LW13904	ADAPTER         	CONT        		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					CONVERTER PLATE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			14900					L224168A			(CAN) PILOT REPORTED OBSERVING WHITE FUMES COMING OUT OF LEFT ENGINE DURING CRUISE.  EMERG FIRE DRILL CARRIED OUT, AND F	IRE OUT.  JOURNEY LOG NR 653 REFERS.  INVEST ON GROUND CONDUCTED, FOUND FIRE DAMAGE TO HIGH TENSION MAGNETO LEADS, OIL H	OSES, HYDRAULIC  AND FUEL HOSES, ELECTRIC WIRINGS.  MAGNETO, FUEL PUMP, HYDRAULIC PUMP, VACUUM PUMP WERE AFFECTED.  OIL 	STAINS REMAINING WITHIN AREA BETWEEN FIREWALL AND AFT OF CRANKCASE ACCESSORY HOUSING, AND FIRE CONTAINED WITHIN THIS ARE	A ONLY.  ATTEMPTED TO FIND CAUSE OF FIRE:  FUEL PUMP TURNED ON, NIL FUEL LEAKAGE EVIDENT FROM PUMP AND HOSES.  DRY MOTOR	 RUN ALSO CARRIED OUT, DISCOVERED FRESH OIL DRIPPING THROUGH PRESSURE OIL FILTER SEAL.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031300009	20010313	00009	EA  	2001	3	13	CA000718018      	2	20000705	G	8500		ENGINE          			GRUMAN	TS2   	TS2ACALFORST	3951102	WP  	WRIGHT	R1820 	982C9HE2    	67020	EA  	HAMSTD	43D	43D51       	NE  	ENGINE BAY	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA				719  				524181	229707		(CAN) DURING FIREFIGHTING OPERATIONS THE PILOT NOTICED AN INCREASE IN OIL TEMPERATURE AND A DECREASE IN OIL PRESSURE. PO	WER WAS REDUCED AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED TO YKA. THE MAIN OIL SCREEN AND THE HIGH CAPACITY	 OIL SCREENS WERE REMOVED FOR INSPECTION. BOTH FILTERS HAD STEEL AND ALUMINUM CONTAMINATION. THE ENGINE WAS REMOVED AND 	A SERVICEABLE ENGINE QCU WAS INSTALLED. THE AIRCRAFT WAS TEST FLOWN AND RETURNED TO SERVICE.			2	H	7	2 	4R	4	R	 	A25WE   	E259	6	C	P8879	 
2000080200212	20000802	00212	SW  	2000	8	2	CA000718019      	1	20000626	G	6410	212010750105	TAIL ROTOR      	BELL        	212010701029	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					OUTBOARD TIP	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			26790			A2901262		LEO7669C			(CAN) WHILE IN FLIGHT,TAIL ROTOR TIP CLOSURE FROM BLADE S/N A-9612 DEPARTED BLADE. ENSUING, EXTREME VIBRATION, CAUSED PI	LOT TO LAND IMMEDIATELY, WITHOUT FURTHER DAMAGE TO A/C.  INSPECTION OF T/R SHOWED TIP CLOSURE OF BLADE S/N A-9612 TO BE 	GONE IN ITS ENTIRETY, LEAVING HONEYCOMB INNER STRUCTURE TOTALLY EXPOSED.  BOTH BLADES WERE REMOVED FROM ASSY AND WERE FO	RWARDED TO TSB (PICKWICK). T/R HUB ASSY IS BEING HELD IN QUARANTINE AT CONAIR HELICOPTERS TILL FURTHER NOTICE. AS AN ADD	ITIONAL PRECAUTION 90 DEGREES T/R GEARBOX HAS BEEN REMOVED FOR OVERHAUL.  A/C INSP FOR FURTHER DAMAGE - NONE FOUND.  REP	LACED 90 DEGREES TAIL ROTOR GEARBOX,  TAIL ROTOR ASSY AND PITCH CHANGE ASSY INSTA	1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2000080200213	20000802	00213	SW  	2000	8	2	CA000719003      	1	20000406	G	5330	2050310778	FASTENER        	BELL        	STC212      	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					LT DOOR POST	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			88740			30877		CPPS61425			(CAN) EXCESSIVE DISSIMILAR METAL CORROSION CAUSED BY SHEET METAL CLECOS BEING LEFT IN SINCE MANUFACTURE. THEY WERE LOCAT	ED IN THE LEFT-HAND DOOR POST ON BULKHEAD STATION 63.27.   NOTE: THIS AREA IS NOT ACCESSIBLE UNLESS THE SKIN IS REMOVED.	  IT WAS FOUND DURING A 300.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000080200214	20000802	00214	EU  	2000	8	2	CA000719004      	1	20000502	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			32770	5700 		4432		4432			(CAN) STARTER/GENERATOR FOUND TO BE CAUSING EXCESSIVE ENGINE VIBRATION.  UNIT REPLACED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032600377	20010326	00377	EU  	2001	3	26	CA000719007      	1	20000628	G	2810	1608550	VALVE           			FOKKER	F28   	F28MK1000   	4990808	EU  										FUSELAGE	STUCK           	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF OUT OF WINNIPEG, CREW NOTED THAT FUEL WAS VENTING OUT OF LT WING. CREW ELECTED TO RETURN YWG, & LANDED 	WITH NO FURTHER EVENTS. MAINT INVEST. REVEALED NR 1 TANK OVERFLO W VALVE WAS STUCK IN OPEN POS, CONFIRMED BY GREN IND ON	 A/C REFUELING PANEL. VALVE WAS CLOSED MANU, & PRESSURE REFUELING SYS WAS ACTIVATED A NO OF TIMES TO C HECK VALVE OPERAI	TON, NO FURTHER DISCREPANCIES. A/C WAS RT-SRV. NOTE: OVERFLOW VALVES  INDICATE OPEN ON REFUELING PANEL DURING REFUELING.	  IT IS STANDARD PROC FOR REFUEL ERS TO ADVISE FLT CREW WHEN GREEN LIGHT(S) REMAIN ON ON COMPLETION OF REFUELINGTHIS WAS	 MISSED ON THIS OCCASION.	2	L	7	2 	4F			RT	A20EU   					 
2000100200254	20001002	00254	CE  	2000	10	2	CA000719009      	1	20000623	G	2800	120040696	LINE            			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					FUEL LINE ASSY	ERODED          	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA								572188			(CAN) FUEL WAS LEAKING FROM BELLY OF AIRCRAFT WHILE PARKED.  FLOOR WAS OPENED AND FUEL LINE BETWEEN FUEL PUMP AND F/W WA	S ERODED (PITTED) AND LEAKING FUEL INTO BELLY.  LINE WAS REMOVED AND REPLACEMENT LINE INSTALLED.					1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001032600385	20010326	00385	CE  	2001	3	26	CA000719010      	1	20000628	G	5311		FRAME           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 0.75 INCH CRACK AT TOP OF SIDE FRAME INSIDE BEND RADIUS.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001032600386	20010326	00386	CE  	2001	3	26	CA000719011      	1	20000629	G	2500	551900921	SEAT            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5137 								(CAN) THE LEFT AFT SEAT WAS REMOVED AND INSPECTED FOR CRACKING OF THE SEATBACK MOUNT TUBE. THE TUBE WAS FOUND CRACKED OU	TBOARD OF THE OUTBOARD SEAT BACK PICKUP AND A CRACK JUST STARTING OUTBOARD OF THE INBOARD SEATBACK PICKUP. SEAT REPAIRED	 AND REINSTALLED.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000100200257	20001002	00257	WP  	2000	10	2	CA000719012      	1	20000708	G	7721	84085A1	CYLINDER        	PWA         		CVAC  	PBY5  	PBY5A       	2421208	WP  	PWA   	R1830 	R183092     	52020	NE  					CYLINDER	CRACKED         	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				66800		CP316780		CP316780			(CAN) DURING CLIMB OUT , THE RIGHT ENGINE STARTED TO RUN ROUGH. THE PILOT FEATHERED THE ENGINE AND RETURNED TO YELLOWKNI	FE  .MAINTENANCE FOUND 2 CRACKS AT THE EXHAUST PORT OF NR 7 CYLINDER OF THE RT ENGINE. THESE HAD STARTED TO SPREAD AND L	IKELY CAUSED THE EXHAUST VALVE TO MALFUNCTION.   MAIN OIL SCREEN CHECKED AND SUMP DRAINED,  NO CONTAMINATION FOUND. THE 	CYLINDER WAS REPLACED,  ENGINE GROUND RUN AND RETURNED TO SERVICE.  (X)			2	H	7	2 	4R	4	R	 	2548    	5E4				 
2000080300220	20000803	00220	SW  	2000	8	3	CA000719013      	1	20000630	G	6320	206040151015	CASE            	BELL        	206040002013	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	CRACKED         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				51500		B1285		CAE820706			(CAN) OIL WAS NOTED LEAKING FROM TRANSMISSION DURING GROUND RUN.  REMOVAL OF THE PAINT REVEALED A CRACK ON THE UPPER CAS	E STARTING FROM THE SPLIT LINE BETWEEN TWO MOUNTING STUDS AT THE 4:30 POSITION, VIEWED FROM THE TOP.  AIRCRAFT WAS GROUN	DED, TRANSMISSION  REMOVED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000100200258	20001002	00258	SO  	2000	10	2	CA000719014      	1	20000620	G	5310	46624	DOUBLER         	PIPER       		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					BEND RADIUS	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						31T7620019		PCE42096			(CAN) DOUBLER CRACKED IN RADIUS.  DOUBLER IS A COMPONENT IN STRUCTURE SEWING AIR STAIR DOOR HINGE TO DOOR AND SUBSEQUENT	LY THE DOOR TO THE AIRFRAME.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000100200066	20001002	00066	EU  	2000	10	2	CA000719016      	1	20000707	G	5520		ELEVATOR        	PILATS      		PILATS	PC12  	PC1245      	       	EU  										RT ELEVATOR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			CA						193					(CAN) AIRCRAFT WAS STRUCK BY LIGHTNING DURING DESCENT.  LIGHTNING STRUCK RT ELEVATOR OUTBOARD TIP.  EXIT THROUGH PROPELL	ER.  SLIGHT BURN/ARC DAMAGE TO ELEVATOR.  BURN/ARC DAMAGE ON PROPELLER 5 INCHES FROM TIP ON ONE BLADE.  UNKNOWN DAMAGE T	O POWER SECTION OF ENGINE DUE TO ARC DAMAGE TO BEARINGS.  AIRCRAFT WAS FERRIED TO V. KELNER - THUNDER BAY, ONTARIO FOR P	ROP AND ENGINE CHANGE AND REPAIRS TO RT ELEVATOR.			1	L	7	1 	3T			RT	A78EU   					 
2000100200259	20001002	00259	SO  	2000	10	2	CA000719017      	1	20000702	G	3213	40327000	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	T53   	T5313B      	41549	NE  	HARTZL	HCE3Y	HCE3YR2     	GL  	FORGING SEAMLINE	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								LEO7592			(CAN) DURING OVERHAUL AND LPI NDT, NOTED CRACK ON FORGING SEAM LINE.  ATTEMPTS TO DRESS OUT SEAM LINE AND CRACK WERE UNS	UCCESSFUL AS CRACK WAS TOO DEEP.  THIS PROBLEM WAS NOT VISIBLE TO THE NAKED EYE.					1	L	7	2 	3O	4	U	 	A20SO   	E17EA	5	C	P33EA	 
2000100200260	20001002	00260	EU  	2000	10	2	CA000719018      	1	20000525	G	5541	NB4513544	BEAM            	BNORM       		BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  					RUDDER BEAM	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						2017		RL1609440A			(CAN) FLUORESCENT LP EXAMINATION WAS CONDUCTED ON THE AIRCRAFT PILOT, COPILOT LT, RT RUDDER PEDAL TORQUE ARM RADIUS.  RE	SULTS:  COPILOT RUDDER SET REVEALED REJECTABLE CRACK INDICATIONS AS MARKED.  IN SERVICE BULLETIN (PRECAUTIONARY EXAMINAT	ION) THERE WERE NO REJECTABLE INDICATION IN ACCORDANCE WITH CODE ON THE PILOT SET.				1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2000100200262	20001002	00262	CE  	2000	10	2	CA000719019      	1	20000717	G	7603	5038901215	CABLE           	CONT        		BEECH 	100   	100BEECH    	1152916	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	THROTTLE CABLE	SEPARATED       	W				E	 	 	 	ENGINE SHUTDOWN         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			28850			468033		468033	711344		(CAN) DURING CRUISE FLIGHT, THE RIGHT THROTTLE CABLE FAILED RESULTING IN A FULL THROTTLE CONDITION.  THE ENGINE WAS SHUT	 DOWN AND SECURED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  THE THROTTLE CABLE WAS REPLACED AND THE AIRCRAFT RE	TURNED TO SERVICE.				1	L	7	2 	3T	3	O	 	A14CE   	3E1	5	C	P5EA	 
2000100200263	20001002	00263	SO  	2000	10	2	CA000719020      	1	20000621	G	5312	416580	BULKHEAD        	PIPER       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					FLANGE RADIUS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			12596			31743		L198561			(CAN) WHILE PERFORMING UNSCHEDULED MAINTENANCE, A BULGE WAS OBSERVED ON FUSELAGE SKIN AROUND THE FORWARD WING SPAR PICKU	P FITTING.  FURTHER INSPECTION REVEALED BOTH LT AND RT FROST SPAR ATTACHMENT BULKHEADS P/NS 41658-0 AND -1 WERE CRACKED 	AND ALSO LT AND LT FRONT SPAR ATTACHMENT CHANNEL P/N''S 40603-0 AND -1 WERE CRACKED.  ATTACHMENT BULKHEADS WERE REPLACED	 WITH NEW PIPER P/N''S 52694-0 AND 52694-01.  FRONT SPAR ATTACHMENT CHANNELS WERE REPLACED.  WITH NEW PIPER P/N''S 40603	-02 AND 40603-03.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000080300221	20000803	00221	SW  	2000	8	3	CA000719021      	1	20000630	G	6410	206310105101	BEARING         	BELL        	206016201127	BELL  	206   	206L        	1181522	SW  										TAIL ROTOR BLACE	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			63700			CS5021					(CAN) EXCESS BEARING PLAY.  BEARING WAS LOOSE IN THE SLEEVE.  REPLACED BEARINGS IN ACCORDANCE WITH BHT 206L M&O.						1	G	7	1 	3U			 	H2SW    					 
2001031300011	20010313	00011	EA  	2001	3	13	CA000719022      	1	20000626	G	2612	28506038	DETECTOR        			CNDAIR	CL215 	CL2151A10   	       	EA  						HAMSTD	43E	43E60       	NE  	RT NACELLE	FALSE INDICATION	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			NR	NOT REPORTED   	1			CA			3274 								(CAN) WHILE PICKING UP A WATER LOAD THE GROUND POWER UNIT - 2 FIRE WARNING LIGHT STARTED TO FLICKER AND THEN STAYED ON S	TEADY WITH THE WARNING BELL. FOLLOWING PROCEDURES THE CREW SHUT DOWN THE RT ENGINE AND DISCHARGED FIRE BOTTLE INTO THE N	ACELLE PROTECTED AREA. AIRCRAFT LANDED WITHOUT INCIDENT. NO SIGN OF FIRE IN GPU-2 AREA. APPEARS TO HAVE BEEN A FALSE IND	ICATION. SYSTEM WIRING CHECKED BY MAINTENANCE - UNABLE TO DUPLICATE FIRE WARNING.			2	H	7	2 	4R			 	A14EA   		6	C	P871	 
2000100200264	20001002	00264	EU  	2000	10	2	CA000719023      	1	20000705	G	5510	NS03089301	BRACKET         	TRNSQP      		TRNSQP	KR03A 	KR03A       	1130847	EU  										HORIZ  STAB	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			70000			0402					(CAN) WHILE INSPECTING VERTICAL STABILIZER LEADING EDGE IMPACT ON SKIN, A CRACK WAS IDENTIFIED ON THE LEFT HAND HORIZONT	AL STABILIZER  ATTACH BRACKET.  NDT BY EDDY CURRENT METHOD CONFIRMED A .0625 INCH CRACK EMANATING FROM A WELD TERMINATIO	N OF A DOUBLER ON BRACKET.  NEW BRACKETS INSTALLED ON BOTH LEFT AND RIGHT SIDES AS NEW BRACKETS MADE FROM THICKER, NON-W	ELDED MATERIAL.			1	K	0	0 	  			RC	G56EU   					 
2000100200147	20001002	00147	CE  	2000	10	2	CA000719024      	1	20000625	G	2820	50921592	RESTRICTOR VALVE			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					DEBONDED	BACKED OUT      	W				A		 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			42580					PCE25678			(CAN) PILOTS REPORTED A PROBLEM OF SLOW TO NO FUEL TRANSFER ON PORT SIDE OF FUEL SYSTEM.  UPON TROUBLESHOOTING THE SYSTE	M, FOUND THE RESTRICTOR FROM THE TEE RESTRICTOR P/N 50-921592 HAD BECOME DEBONDED AND TRAVELLED DOWN STREAM TO THE NEXT 	TEE FITTING AND BECAME LODGED.  THIS RESTRICTED THE LINE AND LIMITED THE FLOW OF FUEL FROM THE TEE FITTING TO THE NACELL	E TANK CAUSING THE SLOW FUEL TRANSFER PROBLEM.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2001032600019	20010326	00019	CE  	2001	3	26	CA000719025      	1	20000710	G	2752	505212234	ACTUATOR        			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A27      	52043	EA  					TE FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PART NUMBER FOR TIME X CONDITION. CENTRE SHAFT LONGITUDINAL CRACKED. CRACK DISCOVERED AFTER REMOVAL.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032600020	20010326	00020	CE  	2001	3	26	CA000719026      	1	20000709	G	2750	101380001	SHAFT           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT WING TE FLAPS	TWISTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) FLAP JUMPED FLAP LIMIT & SWITCH, WHILE GOING IN TO THE UP POSITION AND CAUSING A FAILURE OF THE FLAP SHAFT LT OUTB	OARD TELEFLEX  ASSY. RECTIFICATION: REPLACED THE FLAP MOTOR. INSPECTED THE 90 DEGREES DRIVE. INSPECTED THE FLAP TRANSMIS	SION AND REPLACED THE FLAP FLEXIBLE DRIVE (SHAFT ASSY). FLAP SYSTEM RIGGED, TESTED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001031300012	20010313	00012	EA  	2001	3	13	CA000719027      	1	20000606	G	2913		SCREW           			CNDAIR	CL215 	CL2151A10   	       	EA  						HAMSTD	43E	43E60       	NE  	LT HYD PUMP	BROKEN          	W				K				NONE                    				J	K		WARNING INDICATION        	FLUID LOSS                		IN	INSP/MAINT     	1			CA				570  					N184505		(CAN) HYDRAULIC PUMP CAP SCREWS BROKEN ALLOWING HEAD TO SEPARATE FROM BODY. HYDAULIC FLUID DISCHARGED THROUGH SEPARATION	 IN PUMP. CREW LANDED AIRCRAFT USING EMERGENCY HYDRAULICS.  					2	H	7	2 	4R			 	A14EA   		6	C	P871	 
2001032600025	20010326	00025	GL  	2001	3	26	CA000719028      	2	20000607	G	7250	23053299	BLADE           								ALLSN 	250C  	250C30P     	03013	GL  					1ST TURB WHEEL	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1136 								(CAN)  DURING DISMANTLING OF THE TURBINE, THE 1ST STAGE WHEEL HAD SUFFERED A SINGLE BLADE FAILURE. AFTER THE FAILURE, TH	E BLADE DAMAGED THE REMAINING COMPONENTS DOWNSTREAM CRACK ORIGINATION SITE APPEARS TO BE ON LOWER LEADING EDGE OF BLADE.	 2ND STAGE EXTEX NOZZLE INSTALLED IN THE TURBINE.									3	U			E1GL				 
2001032600026	20010326	00026	SO  	2001	3	26	CA000719029      	1	20000621	G	3230	14469	BOLT            		14480       	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					TORQUE LINK ASSY	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA											(CAN) A/C ON LANDING ROLLOUT PULLED TO R/H WHEN STOPPED. RT GEAR 90 DEGS TO DIRECTION OF FLT. MAINT HALF OF P/N 16469 CE	NTRE TORQUE LINK BOLT STILL IN PLACE. REPLACED BOLT FERRIED A/C TO MAINBASE. INSP CARRIED OUT USING MAINTENANCE MANUAL &	 625 APPENDIX G. ABNORMAL OCCURRENCES FOR REFERENCE & INSPECTING AXLES & DRAG BRACES FOR AREAS THAT WOULD BE AFFECTED BY	 HIGH DRAG LOAD. VISUAL INSP CARRIED OUT ON P/N 14469 ON REMAINING EMBS WITH FLEET WIDE REPLACEMENT TO FOLLOW. TOOLING M	ARKS ARE FROM REMOVAL.		1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2000100200148	20001002	00148	CE  	2000	10	2	CA000719030      	1	20000607	G	2120	131823E4	CLAMP           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					EVA TUBING CLAMP	FAILED          	W				A	E	 	 	UNSCHED LANDING         	ENGINE SHUTDOWN         			I	 	 	FLT. ATTITUDE INST.       			CR	CRUISE         	1			CA								PCE50661			(CAN) DURING A COMPANY TRAINING FLIGHT, THE LT BLEED AIR FAIL ANNUNCIATOR LIGHT (RED) ILLUMINATED. A S PER PROCEDURES, T	HE LT BLEED AIR SWITCH WAS SELECTED TO THE OFF POSITION.  A VISUAL MEANS TO ASCERTAIN THE VALVE IS WORKING IS WHEN SELEC	TED TO OFF, A SLIGHT RISE IN TQ OCCURS. THE CREW WAS UNCERTAIN THAT THE VALVE WAS OPERATIONAL AND THUS THEY COMPLETED A 	PRECAUTIONARY ENGINE SHUTDOWN.  UPON INSPECTION IN THE HANGAR, NOTED THE EVA TUBING HAD SOMEHOW BECOME DISCONNECTED FROM	 THE EVA TUBING SUPPLY MANIFOLD, REDUCING PRESS TO ZERO AND ACTIVATING THE ANNUNCIATOR LAMP.  THE LINE WAS RE-SECURED.  	THE BLEED AIR SHUT-OFF VALVE (LT) WAS ALSO TESTED AND FOUND TO BE FUNCTIONING PROPERLY.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000100200149	20001002	00149	EA  	2000	10	2	CA000720002      	1	20000106	G	5712	C6WF110067768	RIB             	DHAV        	C6WF10023   	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FLAP CNTRE HINGE	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			23987			317		PCE40361			(CAN) EXCESSIVE LOOSENESS BETWEEN THE TWO HALVES OF THE FLAP AT THE CENTER HINGE ARM POSITION. THE RIBS ON EITHER SIDE O	F THE HINGE ARM ARE ASSEMBLED TO THE ARM BY THE USE OF LONG MS20470AD5 SOLID RIVETS.  IT WOULD APPEAR THAT THERE HAS BEE	N SOME WORKING BETWEEN THE RIVET HEADS (MANUFACTURES) AND THE OUTBOARD RIB WHICH HAS CAUSED WEARING OF THE RIB AROUND TH	E RIVET HOLES.  (X)			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2000100200150	20001002	00150	EA  	2000	10	2	CA000720003      	1	20000709	G	8012	3020958	VALVE SEAT      	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					VALVE SEAT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA								41697			(CAN) THE PILOT FLYING ALONG.  WHEN REDUCED POWER FOR DESCENT, OIL PRESSURE DROPPED FROM 90 PSI TO 50 PSI.  PILOT LANDED	 IMMEDIATELY AND SHUT DOWN ENGINE.  ENGINE INSP, FOUND NON-MAGNETIC PARTICLES IN OIL FILTER.  THE CHIP DETECTOR AND REDU	CTION GEARBOX AREA WERE CHECKED.   NO PARTICLES FOUND.  OIL TANK DRAINED AND CHECKED.  NO PARTICLES FOUND.  REAR ACCESSO	RY GEARBOX DRAINED AND CHECKED.  FEW SMALL PARTICLES FOUND.  PRESSURE RELIEF VALVE REMOVED, DISASSEMBLED.  FOUND SMALL P	ARTICLE OF NON-MAGNETIC MATERIAL ON VALVE SEAT.  PRESSURE RELIEF VALVE RE-ASSEMBLED AND INST OIL SYS FLUSHED, REPLENISHE	D.  GROUND RUNS AND INSPS WERE CARRIED OUT IAW WITH P&W MM.  NO FURTHER METAL GENERATED.	1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100200219	20001002	00219	EA  	2000	10	2	CA000720004      	1	20000714	G	2710	C3CF2015	CONTROL CABLE   	DHAV        		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A27      	52043	EA  					AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE40691			(CAN) WHILE CARRYING  OUT AN 800 HOUR INSPECTION, THE RT AILERON CABLE WAS FOUND TO BE FRAYED.  THE DAMAGE TO THE CABLE 	WAS LOCATED AT THE PULLEY WHERE THE CABLE GOES THROUGH THE COCKPIT FLOOR BY THE COPILOT SEAT.  THE 800 HOUR INSPECTION R	EQUIRES THAT YOU INSPECT THE CABLE THROUGHOUT ITS ENTIRE LENGTH.  IT SHOULD BE NOTED THAT THIS DAMAGE WOULD NOT HAVE BEE	N FOUND WITHOUT THE REMOVAL OF THE CABLE WHICH IS STANDARD COMPANY POLICY ON AN 800 HOUR INSPECTION.			1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100200220	20001002	00220	EA  	2000	10	2	CA000720005      	1	20000714	G	5523	C3TE1312	TAB             	DHAV        	C3TE1111    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					LEVER	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								PCE92418			(CAN) WHILE CARRYING OUT THE 100 HOUR INSPECTION OF THE SERVO TAB, THE ENGINEER NOTICED THAT THERE WAS EXCESSIVE PLAY IN	 THE ELEVATOR SERVO TAB OPERATING LEVER.  UPON FURTHER INVESTIGATION, FOUND THE SERVO TAB HAD TO BE REPLACED DUE TO WEAR	 ON THE OPERATING LEVER BOLT HOLE.  SUBMITTER STATED IT SHOULD BE NOTED THAT NUMEROUS PROBLEMS HAVE BEEN FOUND IN THIS A	REA. WOULD IT NOT BE WISE TO MANDATE A 50 HOUR INSPECTION OF THE SERVO TABS?			1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100200221	20001002	00221	EA  	2000	10	2	CA000720006      	1	20000714	G	2720	VALC3UF619	CONTROL CABLE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					WATER RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE92418			(CAN) WHILE CARRYING OUT AN INSPECTION OF THE WATER RUDDER CABLES, THE ENGINEER FOUND THE WATER RUDDER STEERING CABLE TH	AT ATTACHES TO THE RUDDER BELLCRANK BELOW THE PILOTS FLOOR WAS SEVERELY FRAYED WHERE IT CONTACTS THE FORWARD PULLEY ON T	HE BACKSIDE OF THE FIREWALL. THE CABLE WAS REPLACED.				1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100200067	20001002	00067	EU  	2000	10	2	CA000720007      	1	20000706	G	2434	HED60CR132903	BRUSH BLOCK     		5243212158  	PILATS	PC12  	PC1245      	       	EU  										BRUSH BLCOK ASSY	WORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			68600			100092					(CAN) UPON LANDING NR 2 GENERATOR WENT OFF LINE RED ANNUNCIATOR GEN 2 OFF ILLUMINATED.  PILOT WAS UNABLE TO RESET GENERA	TOR.  INVESTIGATION OF GENERATOR SYSTEM FOUND NR 2 GENERATOR BRUSHES WERE WORN TO THE EXTENT THE BRUSHES NO LONGER CONTA	CTED THE SLIP RINGS.  A NEW GENERATOR WAS INSTALLED.  GROUND RUN CARRIED OUT AND ALL WAS SATISFACTORY.  SUBMITTER STATED	 THERE IS NO CALL OUT IN THE PILATUS MAINTENANCE MANUALS TO INSPECT CONDITION OF NR 2 GENERATOR BRUSHES FOR CONDITION OR	 LENGTH.		1	L	7	1 	3T			RT	A78EU   					 
2000072700171	20000727	00171	CE  	2000	7	27	CA000720008      	1	20000720	G	7100	105217	CARBURETOR      	LYC         	O320H2AD    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MIXTURE CNTRL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				85000		L81876T		L81876T	79744		(CAN) THE RECENTLY OVERHAULED ENGINE WOULD START (ON PRIMING FUEL) AND THEN QUIT (AS IF THE MIXTURE CONTROL WAS IN IDLE 	CUTOFF),  CARBURETOR REMOVED AND ANOTHER CARB PUT ON ENGINE - RAN NORMAL CARB MIXTURE, CONTROL SEEMS TO BE STUCK ON IDLE	 CUT-OFF INTERNALLY, ALTHOUGH EXTERNAL CONTROL ARM MOVES FROM LEAN TO RICH - SENT TO OVERHAUL FACILITY FOR REPAIR.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000072700172	20000727	00172	CE  	2000	7	27	CA000720009      	1	20000620	G	7100		O-RING          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CASE/STUD	WRONG PART      	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				77500				L623815			(CAN) DURING TROUBLESHOOTING FOR AN ENGINE OIL LEAK, IT WAS DETERMINED THAT OIL WAS SEEPING OUT THE CENTER THROUGH-BOLT 	STUDS; ENGINE AND CRANKCASE WAS DISASSEMBLED FOR ACCESS TO THE THROUGH-STUD O-RINGS.  IT WAS THEN DISCOVERED THAT THE WR	ONG O-RINGS WERE INSTALLED ON THE 6 THROUGH-STUDS.  THE O-RINGS WERE THICKER THAN THE RECESS WAS GROOVED OUT FOR AND AS 	A RESULT THE 6 O-RINGS WERE SQUASHED AND STUCK IN THE MATING SURFACES OF THE CRANKCASE HALVES, WHICH RESULTED IN A LOSS 	OF TORQUE AND FRETTING OF THE CRANKCASE MATING SURFACES.  THE CRANKCASE HALVES NEEDED TO BE MILLED AND LINE BORED.		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2000072700173	20000727	00173	SO  	2000	7	27	CA000720010      	1	20000628	G	3260	487862	SWITCH          			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					NLG	OUT OF ADJ      	W				L	 	 	 	ABORTED APPROACH        				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA								PCE92653			(CAN) -  PILOT DID NOT RECEIVE NOSE GEAR DOWN LIGHT INDICATION AFTER CYCLING GEAR DOWN FOR LANDING.   MAINTENANCE ADVISE	D PILOT TO USE RUDDER PEDALS TO ACTIVATE NOSE GEAR DOWN MICROSWITCH.  THIS ACTION GAVE NOSE GEAR DOWN INDICATION TO PILO	T.   THE AIRCRAFT WAS LANDED WITHOUT ANY INCIDENT.  MAINTENANCE JACKED THE AIRCRAFT, CYCLED GEARS AND ADJUSTED THE NOSE 	GEAR  DOWN MICROSWITCH.			1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2000080300222	20000803	00222	GL  	2000	8	3	CA000720012      	2	20000705	G	7240	23031260	COMBUSTION CHAMB	ALLSN       	6898734     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					PATCH AREA	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13900			CAT31672		CAE820619			(CAN) A HIGHER THAN NORMAL T.O.T. WAS EXPERIENCED UNDER NORMAL OPERATING TO-QUE SETTINGS.  AIRCRAFT ENGINE WAS INSPECTED	 UPON LANDING TO DETECT A POSSIBLE MALFUNCTION.  A CRACK WAS DISCOVERED IN THE COMBUSTION CASE ASSEMBLY IN THE REINFORCE	D PATCH AREA OF THE LEFT TUBE INSIDE CURVE AREA.  A PREVIOUS AND RECURRING PROBLEM; HENCE, THE REINFORCING PATCH.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032600034	20010326	00034		2001	3	26	CA000720014      	4	20000620	G	2562	BP1020	BATTERY         	DORNEMARGLN 	DMELT1411   	CNDAIR	CL600 	CL6002A12   	1900304	EA  	GE    	CF34  	CF343A1     	30015	NE  					ELT	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						2062A					(CAN) UPON ELT RECERTIFICATION, A NON TC APPROVED BATTERY WAS FOUND IN THE UNIT.ONLY THE DM U158-1 IS APPROVED BY TC (RE	F AWN BO14, EDITION 4) FOR USE IN THIS ELT. CORRECT BATTERY WAS INSTALLED AND ELT RECERTIFIED.SUP					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000073100208	20000731	00208	SO  	2000	7	31	CA000720015      	1	20000628	G	3250	AN3H7A	BOLT            		4531400     	PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					TOP OF CYL	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			11272					PCE92427			(CAN) UPON LANDING THE AIRCRAFT, THE PILOTS NOTICED A PULLING TO THE LEFT.   AFTER A BRIEF INSPECTION, THE THREE UPPER A	N3 BOLTS, WHICH HOLD THE STEERING ARM AND BRACKET TO THE NOSE GEAR CYLINDER, WERE FOUND TO BE SHEARED.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2000073100209	20000731	00209	SO  	2000	7	31	CA000720017      	2	20000707	G	8530	646657A2	CYLINDER        			CESSNA	207   	T207A       	2073614	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	D3A34	D3A34C401   	GL  	EX. VALVE NR 5	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								291516R			(CAN) WHEN PERFORMING A CYLINDER DIFFERENTIAL COMPRESSION CHECK, FOUND CYLINDER NR 5 HAD A 60/80 COMPRESSION, AND AIR WA	S LEAKING OUTSIDE CYLINDER.  AFTER FURTHER INSPECTION, FOUND CRACK COULD BE SEEN JUST INBOARD OF THE EXHAUST PIPE FLANGE	. CYLINDER WAS REMOVED FROM SERVICE. NEW OVERHAULED CYLINDER WAS INSTALLED.				1	H	7	1 	3O	3	O	 	A16CE   	E8CE	5	C	P47GL	 
2001031300019	20010313	00019	EU  	2001	3	13	CA000721009      	1	20000627	G	2120		AIR FILTER      			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					AIR DISTRIBUTION	CONTAMINATED    	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA								731248			(CAN) ON GROUND AFTER ENGINE START, SMELL OF EXHAUST (POSSIBLE FUEL VAPORS) IN REAR CABIN, DISSIPATED BEFORE DEPARTURE. 	ON FINAL APPROACH A STRONG KEROSENE SMELL EMANATED THROUGHOUT FORWARD GALLEY AND J CLASS CABIN AND SMELL DIDNT DISSPATE 	UNTIL AFTER ENGINES SHUT DOWN.ENGINE GROUND RUN CARRIED OUT WITH INDIVIDUAL ENGINE AND APU BLEEDS ISOLATED. NO FAULT FOU	ND. ENGINE FUEL NOZZLES INSPECTED AS PER JOB CARD, NO FAULT FOUND.BOTH CABIN AIR RECALCULATION FILTER REPLACED AND SYSTE	M CHECKED SERVICEABLE.		2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001031300021	20010313	00021	EA  	2001	3	13	CA000724002      	1	20000716	G	2910		LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  										HYDRAULIC SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) LOST OF HYDRAULIC PRESSURE SYSTEM NR 1 AND QUANTITY IN CRUISE AT FLIGHT LEVEL 310. NO QUANTITY OR PRESSURE FOR 36 	MINUTES BEFORE ENGINE SHUTDOWN AFTER LANDING. THE EDP AND THE LEAKING HYDRAULIC PRESSURE LINE REPLACED.					2	L	7	2 	4F			RT	A21EA   					 
2001031300022	20010313	00022	EA  	2001	3	13	CA000724003      	1	20000714	G	7540		FIRE LOOP       			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE ON FLIGHT 5367 FROM CINCINNATI TO MINNEAPOLIS / ST PAUL LT 14TH STAGE DUCT WARN ILLUMINATED. CREW FOLLOW	ED THEIR QRH AND SHUT DOWN THE ENGINE. AFTER DECLARING AN EMERGENCY AND DIVERTING TO MADISON THEY COMPLETED AN UNEVENTFU	L LANDING.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300023	20010313	00023	EA  	2001	3	13	CA000724004      	1	20000711	G	2910		HYDRAULIC LINE  			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF341A      	 	NE  					HYDRAULIC SYS	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								807038			(CAN) ON FLIGHT 5692 FROM CINCINNATI (CVG) TO MYRTLE BEACH SC (MYR), HYDRAULIC NR 2 PRESSURE CAUTION MESSAGE IN FLIGHT. 	CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LANDING BACK AT CINCINNATI. MAINTENANCE ACTION: MAINTENANCE FOUND AN H	YDRAULIC LEAK IN THE AFT FUSE, FOUND TO BE NR 2 ENGINE CASE DRAIN LINE LEAKING, MAINTENANCE REPLACED HYDRAULIC LINE, AIR	CRAFT WAS BACK TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300024	20010313	00024	EA  	2001	3	13	CA000724005      	1	20000713	G	2916		RESERVOIR       			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF341A      	 	NE  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA								807038			(CAN) ON A FLIGHT FROM CVG TO MYR, THE HYDRAULIC NR 2 LOW PRESSURE CAUTION MESSAGE OCCURRED IN FLIGHT. SYSTEM PRESSURE W	AS LESS THAN 15 PERCENT. CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LANDING BACK AT CINCINNATI. THE NR 2 RESERVOI	R WAS IDENTIFIED AS BEING THE CAUSE OF THE PROBLEM.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300025	20010313	00025	EA  	2001	3	13	CA000724006      	1	20000707	G	5330		SKIN            			CNDAIR	CL600 	CL6002B19   	       	EA  										FUSELAGE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C CHECK MAINTENANCE,  MAINTENANCE REQUIRED ACCESS TO RIVETS FOUND UNDER THE TRAILING EDGE PYLON ASSEMBLY. A	FTER REMOVAL OF THE PYLON TRAILING EDGE ASSEMBLY, LT AND RT,  MAINTENANCE NOTED ABRASION DAMAGE TO THE FUSELAGE (CHAFING	). THE DAMAGE WAS LOCATED IN AN UNPRESSURIZED AREA AND IN SOME LOCATION WAS AS MUCH AS .050 DEEP. MAINTENANCE ACTION: RE	PAIR ENGINEERING ORDER PROVIDED TO CUSTOMER.			2	L	7	2 	4F			RT	A21EA   					 
2001031300026	20010313	00026	EA  	2001	3	13	CA000724007      	1	20000709	G	2750		BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										RIGHT	FAILED          	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) FLAP FAIL CAUTION MESSAGE ILLUMINATED IN CRUISE AT 25,000 FEET (FLAPS STAYED AT 0 DEGREE). CREW DECLARED AN EMERGE	NCY AND MADE AN UNEVENTFUL LANDING. MAINTENANCE REPLACED THE RIGHT BPSU.					2	L	7	2 	4F			RT	A21EA   					 
2001031300027	20010313	00027	NE  	2001	3	13	CA000724008      	2	20000711	G	7250		TURBINE         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 2 ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	T	J	ENGINE FLAMEOUT           	ENGINE CASE PENETRATION   	WARNING INDICATION        	CL	CLIMB          	1			CA								807084			(CAN) ON CLIMB OUT NR 2 ENGINE N2 EXCEEDED LIMITS, THEN SHUT DOWN. CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LAN	DING. AFTER INVESTIGATION MAINTENANCE REPORT LPT (LOW PRESSURE TURBINE SECTION) CASE PENETRATION (PRIMARILY AT THE 7-8 O	CLOCK POSITION). THE ENGINE HAS BEEN CHANGE OUT AND THE AIRCRAFT IS BACK IN SERVICE.ENGINE HISTORY: APPROXIMATELY 14,300	 CYCLES ON IT - AND HAD PREVIOUSLY BEEN OFF AT 6000 CYCLES FOR AN HSI.FSR QUERIED ON FOREIGN SDR NO DETAILS AVAILABLE. 2	000,08,09		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000081700089	20000817	00089	CE  	2000	8	17	CA000724010      	1	20000628	G	3297		WIRE            	CESSNA      	664164068R  	CESSNA	560   	560XL       	2076702	CE  										LUG END	BROKEN          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			103  			040					(CAN) ON JUNE 28, 2000, THE AIRCRAFT WAS ON TRAINING PURPOSE WHEN DURING NORMAL PROCEDURE OF DESCENT AND AFTER THE GEAR 	DOWN WAS SELECTED, THE CREW NOTICE THAT NO INDICATION FOR THE RIGHT GEAR DOWN AND LOCKED BUT LIGHT TESTED OK. THE CREW D	ECLARED AN EMERGENCY LANDING AT ST-HUBERT AIRPORT.  THE AIRCRAFT MADE AN UNEVENTFUL LANDING.AFTER INSPECTION OF THE LAND	ING GEAR SYSTEM, TECHNICIANS FOUND A GROUND WIRE (GR008) BROKEN AT LUG. THE LUG WAS REPLACED, THE SYSTEM CHECKED SERVICE	ABLE AND THE AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F			RT	A22CE   					 
2000081700090	20000817	00090	EA  	2000	8	17	CA000724011      	1	20000707	G	2701	215T9027622	TORQUE TUBE     	CNDAIR      		CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  					OTBD SHAFT	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			588  			2023					(CAN) WHEN OPPOSING FORCE BETWEEN LT AND RT ELEVATOR CONTROL COLUMN, MINOR LOOSENESS CAN BE FELT ON LT COLUMN PRODUCED B	Y OUTBOARD FASTENERS LOOSENESS ON OUTBOARD LAYSHAFT. S EE K/M/ PSP492,27-31-00,  P602 FIG CC OUTBOARD SIDE.  NOTE: (ACTI	ON) REPAIRED C/O I.A.W. BOMBARDIER R.E.O. 215-27-30-03.				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE				 
2001031300029	20010313	00029	NE  	2001	3	13	CA000724012      	2	20000705	G	7200		ENGINE          			CNDAIR	CL600 	CL6001A11   	1900302	EA  	LYC   	ALF502	ALF502L2    	41580	NE  					RIGHT	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT 41,000 FT THE FLIGHT CREW NOTICED A SMALL SURGE IN POWER ON THE RT ENGINE FOLLOWED ABOUT 10 SECON	DS LATER BY A DECREASE IN RPM AND INCREASE IN ITT. THE ENGINE AND AIRCRAFT IMMEDIATELY BEGAN VIBRATING, WITH THE RT ENGI	NE VIBE METER INDICATING MAXIMUM. THE CREW SHUTDOWN THE ENGINE BUT A HIGH LEVEL OF VIBRATION CONTINUED AS THE ENGINE WIN	DMILLED. THE AIRCRAFT DIVERTED AND HAD AN UNEVENTFUL LANDING APPROXIMATELY ONE HOUR 30 MIN LATER. THE ENGINE WAS REPLACE	D, THE ENGINE MOUNTS INSPECTED AND THE AIRCRAFT RETURNED TO SERVICE.DETAILS REGARDNG THE TEARDOWN AND FAILURE INVESTIGAT	ION OF THE ENGINE WILL FOLLOW.2000-11-08TC: NO INFORMATION RECEIVED.	2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2001031300030	20010313	00030	EA  	2001	3	13	CA000724013      	2	20000708	G	7250		TURBINE         			CNDAIR	CL600 	CL6001A11   	1900302	EA  	LYC   	ALF502	ALF502*     	41580	EA  					RT ENGINE	SEIZED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			LD	LANDING        	1			CA								3066S			(CAN) AFTER LANDING, DURING ROLLOUT, THE CREW DEPLOYED THE THRUST REVERSER AND THE RT ENGINE SHUTDOWN. THE AIRCRAFT CONT	INUED TO THE HANGAR AND AN INITIAL EVALUATION OF THE ENGINE REVEALED THAT THE TURBINE WHEEL HAD SEIZED.FURTHER DETAILS O	F THE ENGINE INSPECTION AND REPAIR WILL FOLLOW.2000,10,04, - THE NUMBER 2 ENGINE GAS PRODUCER AND COMBUSTOR TURBINE MODU	LE (S/N 81H005) WAS REMOVED AND REPLACED ON WING.SUBSEQUENT OVERHAUL REVEALED PLASMA COATING MISSING FROM THE COMPRESSOR	, EVIDENCE OF AN IMPELLER RUB AND GROUND UP METAL ON THE DIFFUSER VANES.  BLADE MATERIAL TRANSFER RESULTED IN DAMAGE AND	 SEIZURE OF THE TURBINE ASSEMBLY	2	L	7	2 	4F	4	F	RT	A21EA   	E6NE				 
2001031300031	20010313	00031	CE  	2001	3	13	CA000724014      	1	20000702	G	3234	MS24171D1	RELAY           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  						FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								GGMPS0027			(CAN) AFTER TAKEOFF THE PILOT SELECTED THE GEAR UP BUT THEY DIDN'T MOVE. THEY DIVERTED THE FLIGHT TO YQB. AFTER INVESTIG	ATION WE FOUND RELAY LANDING GEAR MOTOR P/N MS24171D1 IN LT NACELLE COMPLETELY BURNED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001031300032	20010313	00032	EA  	2001	3	13	CA000724015      	1	20000706	G	2730	215T9027622	SHAFT           			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	PW120 	PW123       	 	NE  					TORQUE TUBE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5731 								(CAN) WHEN OPPOSING FORCE ON LT AND RT CONTROL COLUMN. MINOR LOOSENESS CAN BE FEEL ON LT CONTROL COLUMN PRODUCE BY OUTBO	ARD FASTENERS LOOSENESS ON OUTBOARD LAYSHAFT. SEE M.M.492, 27-31-00 P602 FIG. CC OUTBOARD SIDE.NOTE: (ACTION) REPAIRS/OU	T I.A.W. BOMBARDIER REO 215-27-30-03.				2	H	7	2 	4R	4	T	 	A14EA   	E20NE				 
2001031300033	20010313	00033	NE  	2001	3	13	CA000724016      	2	20000709	G	8550	AN929A4	OIL CAP         			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	CA3         	52026	NE  					PRE OILING SYS	LOOSE           	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA								32875			(CAN)  ENGINE HAD TO BE FEATHERED IN FLIGHT DUE TO LOW OIL PRESSURE AND OIL QUANTITY DRIPPING. AFTER LANDING, A TECHNICI	AN FOUND THAT THE PRE-OILING PLUG LOOSEN.HE REINSTALLED THE PLUG, FILL THE OIL TANK, PERFORMED AN ENGINE RUN AND RETURN 	THE AIRCRAFT TO SERVICE.				2	H	7	2 	4R	4	R	 	A14EA   	E231				 
2000081700091	20000817	00091	SO  	2000	8	17	CA000724018      	1	20000706	G	3710	441CC7	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT ENGINE	JAMMED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				362  		85687		L586361A			(CAN) PUMP S/N 856871.  DETECTED SQUEAKING WHEN TURNING PROPELLER DURING TEARDOWN FOR ENGINE CHANGE.  PUMP REMOVED.   HA	RDLY ABLE TO TURN IT BY HAND.  INSTALLED 14 FEB. 2000 AT 12269.2 = 6 MS AND 361.6 HRS.  REMOVED  06 JUL.2000 AT 12630 = 	6 MS & 361.6 HRS.  WHEN INSTALLED, MAN. INSTRUCTIONS FOLLOWED METICULOUSLY CLEAN HOSES, COOLING HOSE AND BAFFLE, R.V. FI	LTERS.  133-5-1 FILTERS REPLACED EVERY 100 HOURS.  NOTE:  POOR DESIGN:  PUMP BREATHERS FROM AIR INTAKE UNDER NACELLE NEA	R COWL FLAPS AND EXHAUSTS.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000081700092	20000817	00092	SO  	2000	8	17	CA000724019      	1	20000706	G	3242	07900300	SCREW           	CLEVELAND   	309C        	PIPER 	PA18  	PA18150     	7101828	SO  										BLEEED VLV/RT BK	MISSING         	W				E	O	 	 	ENGINE SHUTDOWN         	OTHER                   			K	R	 	FLUID LOSS                	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			CA			5738 								(CAN)  THIS REPORT FOLLOWS LANDING INCIDENT.   NO RIGHT BRAKE.   AIRCRAFT LANDED AND PILOT CNTLLED A/C ONTO ECHO TAXIWAY	.  SHUT DOWN AND PUSHED A/C OFF TAXIWAY BY HAND.  ON SITE, PRELIMINARY INSP AND TOWED A/C CLEAR OF ALL TRAFFIC AREAS - U	NDER AIRPORT MGRS ESCORT.  BRAKE BLEEDER ASSY (SEAT PN 08100100, SCREW PN 07900300, CAP PN 18300100) MISSING FROM CYLIND	ER P/N 061-03901.  IT APPEARED THAT IT ORIGINALLY NOT SCREWED IN  VERY DEEP, 2 OR 3  THREADS. 1ST THREADS BURNED FIELD R	EPLACED, BLED AND SERVICED.  ENTRY IN LOG TO BE REVIEWED AT HOME BASE (REMOVED AND RE-INSP).  PILOT AND AMO ADVISED.  TA	XI-TESTED AND LEAK CHECKED.  NOTE:  A/C AMPHIBIOUS - FLOATS - LAST TAKEOFF FROM GRAVEL.	1	H	7	1 	3O			 	1A2     					 
2000081700093	20000817	00093	SO  	2000	8	17	CA000724020      	1	20000627	G	2710	677550100	BELLCRANK       			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					RIGHT WING	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3023 					L772851A			(CAN) THE RIGHT AILERON CONTROL BELLCRANK LOWER ANGLE WAS FOUND CRACKED DURING INSPECTION.						1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2000081700094	20000817	00094	SO  	2000	8	17	CA000724021      	1	20000704	G	3244	50644	TIRE            	CLEVELAND   	4040        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NLG	BLOWN           	W				O		 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA			622  			182		L159368A			(CAN) THIS REPORT FOLLOWS LANDING INCIDENT,  TOWED OFF RUNWAY.  RUNWAY INSP, NO DEBRIS.  TEAR DOWN OF WHEEL ASSY SHOWED 	TIRE TREAD OBLIQUE - SKID - FLAT SPOT.  POSSIBLY DUE T O CRAB LDG OR TO SKIDDING AFTER BLOWING AT TOUCH DOWN.  BALANCE P	ATCH 1 OZ INSIDE TIRE FOUND DISINTEGRATED.  INSIDE CORD BROKEN, POSSIBLY DUE TO TOWING ACFT OFF RUNWAY.  TUBE FOUND PUNC	TURED AND CHAFED, BURNED, DISCARDED.   BEARINGS AND CUP BURNERS SHOWING LIGHT SIGNS OF HEATING.  NO SIGNS OF POSSIBLE FO	REIGN OBJECT IN TIRE, NAIL, PIN, STONE ETC.  WHEEL AND LANDING GEAR INSP PER ASM.  NO DEFECT.  REPAIRED WHEEL WITH NEW B	EARING RUNNERS, WITH NEW TUBE AND NEW MICHELLIN-AVIATOR TIRE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000081700095	20000817	00095	CE  	2000	8	17	CA000724022      	1	20000621	G	3297		WIRE            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  						BROKEN          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA								275423R			(CAN) UPON ACTIVATION OF THE LANDING GEAR, THE LEFT GREEN DOWN AND LOCKED LIGHT DID NOT ILLUMINATE.   AFTER VISUAL CONFI	RMATION, THE AIRCRAFT LANDED SAFELY.  BROKEN WIRE CAUSED THE PROBLEM.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2000081700096	20000817	00096	GL  	2000	8	17	CA000724023      	3	20000704	G	6114		HUB             			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	HUB SHELF	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1166 				L17755	4246		(CAN)  DAMAGE BEYOND LIMIT TO HUB SHELF DUE TO A PREVIOUS PROPELLER STRIKE.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2000081700097	20000817	00097	SO  	2000	8	17	CA000724024      	1	20000709	G	3243	16748000	MASTER CYLINDER 			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					RT RUD PEDAL	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				1046 				L585248			(CAN)  WHILE WORKING ON ANOTHER NEARBY AIRCRAFT IN HANGAR, MECHANIC NOTICED PUDDLE OF HYDRAULIC FLUID UNDER THE AZTEC.  	MONITORED FOR ONE HOUR, INCREASED IN SIZE OF PUDDLE COMFIRMED LEAK TO BE MAJOR.  OIL RAN FROM NOSE NACELLE AREA TO MID-C	ENTER SECTION BEFORE DRIPPING DOWN.  CHECKED HYDRAULIC SYSTEM.  BRAKE RESERVOIR FOUND EMPTY.   RIGHT BRAKE MASTER CYLIND	ER LEAKING. TOP SEALS.  TSO: 1045.7 HR.  INSTALLED 17 OCT 91. REPLACED UNIT - BLED AND SERVICED.			1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2000081700098	20000817	00098	EA  	2000	8	17	CA000724025      	2	20000628	G	7322	25245009	SERVO           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENGINE	FAILED          	W				O	 	 	 	OTHER                   				Y	Z	 	ENGINE STOPPAGE           	SIGNIFICANT FAILURE REPORT		IN	INSP/MAINT     	1			CA				379  		70698		L159368A			(CAN)  INSTALLED 20 JAN 2000 BY OVERHAULED ON O/H ENGINE.   AT TSO:  119.7 HRS.  IDLE MIXTURE RICHENED 3 NOTCHES.   AT T	SO:  153.3 HRS.  IDLE MIXTURE RICHENED 1 NOTCH  FROM ONE FLIGHT TO ANOTHER, PILOT REPORTED DIFFICULTIES IN SETTING MIXTU	RE, FUEL FLOW AND EGT.  SEVERAL VERIFICATIONS OF SYSTEM CARRIED OUT DURING THAT PERIOD, TIMING, INTAKE LEAKS, INJECTOR N	OZZLE, SPARK PLUGS ALWAYS TO SHOW NORMAL OPERATION AFTERWARDS.  ALTHOUGH INDICATING PARAMETERS GOOD, SOME GAUGES REPLACE	D,  EXHAUST STACKS INDICATING LEAN EXHAUST.  THIS TIME, PILOT ENCOUNTERED HARD TO START AND NO CUTTING OUT WHEN MIXTURE 	PULLED BACK.  UNSTABLE UNIT - REPLACED.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000081700099	20000817	00099	SO  	2000	8	17	CA000726002      	1	20000623	G	2730	4030700	ELEVATOR        	PIPER       		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					LOWER BEARING	WORN            	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA						31T7920008		PCE51839			(CAN) DURING INSPECTION BELLCRANK FOUND TO BE WORN IN BEARING LOCATION WHERE ELEVATOR PUSH-PULL ROD ATTACHES, TO THE POI	NT WHERE THE BEARING WAS LOOSE IN BELLCRANK.  PROBLEM SEEMED TO BE CAUSED BY BEARING BECOMING SEIZED.					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000080800171	20000808	00171	NE  	2000	8	8	CA000726003      	2	20000628	G	7200		WHEEL           	TMECA       	70BM035240  	SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					GAS GENERATOR	COKED           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			2999 	175  		5258		7139			(CAN) THIRD OCCASION THAT THE COMPRESSOR SECTION HAD BECOME DIFFICULT TO TURN DUE TO COKING AROUND LABYRINTH SEAL AT INJ	ECTION WHEEL.  ONLY SOLUTION IS TO REMOVE ENGINE M.O.2 SECTION SENT TO OVERHAUL FACILITY FOR REPAIR. TURBOMECA IS NOW LO	OKING INTO THIS PROBLEM DUE TO OTHER OCCURRENCES OF THIS PROBLEM.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001031300035	20010313	00035	CE  	2001	3	13	CA000726004      	1	20000619	G	2752	503801537	DRIVE SHAFT     	BEECH       	1295210501  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					FLAP ACTUATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6669 			796B96		PCEPS0104			(CAN) INITY MAINT NOTIFIED THAT  WHEN SELECTING FLAPS TO UP POS (ON GROUND) THAT FLAP IND. SHOWING 20 DEGS&THAT FLAPS WE	RE NOT ABLE TO RETRACT ANY FURTHER. MAINT FOUND L/H INBOARD FLAP IN APPROX. 25DEGS DOWN POS,&THAT FLAP SPLIT SYS PREVENT	ING FURTHER FLAP-MOTOR OP. ALL FLAPS WERE MANU RETRACTED&CONFIRMED LOCKED IN UP POS. A/C DISPATCHED AS PER MEL PROCEDURE	 FOR FLAP-UP OPS.DURING T TROUBLE-SHOOTING IT FOUND THAT L/H INBOARD FLAP ACTUATOR ASSY FAILING, INTERNALLY. GEAR INTERN	ALLY OF DRIVE ASSY, WHICH IS PART OF FLAP ACTUATOR ASSY FOUND WORN WITH SECTION OF GEAR BROKEN OFF.L/H INBOARD FLAP ACTU	ATOR REPLACED BEFORE FURTHER FLT.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001011105199	20010111	05199	NM  	2001	1	11	CA000731008      	1	20000722	G	5753		CONTROL UNIT    			BOEING	767   	767375      	       	NM  										TE FLAPS	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) A/C 640, JULY 22/2000, FLT 51, YYZ, LOG SEQUENCE 0272985, ON LANDING YYZ, CAPTAIN DECLARED AN EMERGENCY, DUE TRAIL	ING EDGE FLAP ASYMMETRY OCCURRED WITH FLAPS BEYOND 20 DEGREES. LANDED WITHOUT INCIDENT. SYSTEM RESET AS PER  FAULT ISOLA	TION MANUAL 27-51-00 FIG.114C, FOR TRAILING EDGE FLAP SHUTDOWN, NO FAULTS INDICATED. AFTER RESET FLAPS CYCLED SEVERAL TI	MES WITH HYDRAULICS AND IN ALTERNATE MODE, UNABLE TO DUPLICATE SNAG.			2	L	7	2 	4F			RT	A1NM    					 
2000081700100	20000817	00100	NM  	2000	8	17	CA000731015      	1	20000717	G	5530	220015001	FITTING         	PIPER       	220000999   	PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					FITTING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3981 			14071		L1600248A			(CAN) AN A INSPECTION WAS BEING ACCOMPLISHED ON THE AIRCRAFT.  DURING THIS INSPECTION, A CRACK WAS FOUND ON THE AFT VERT	ICAL STABILIZER ATTACH FITTING.  THE CRACK WAS CONFIRMED USING EDDY CURRENT INSPECTION METHOD.  AFTER THE FITTING WAS RE	MOVED FROM THE STABILIZER A FURTHER EDDY CURRENT INSPECTION INDICATED A TOTAL OF 5 DIFFERENT CRACKS IN THE FITTING. T HE	 CRACKS ALL EXTEND GRAIN-WISE BETWEEN FASTENER HOLES ON BOTH FLANGES OF THE FITTING.  THE FITTING WAS REPLACED WITH A NE	W FITTING.  CONAIR WILL BE CONDUCTING A FLEET CAMPAIGN TO INSPECT THE AFT VERTICAL STABILIZER ATTACH FITTING TO DETERMIN	E THE EXTENT OF THE PROBLEM AND RECTIFY (I.E. REPLACE) DEFECTIVE FITTINGS.	1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2001031400115	20010314	00115	EU  	2001	3	14	CA000731016      	1	20000719	G	3233	AIR111506	ACTUATOR        			BRAERO	DH125 	HS125700B   	1500205	EU  										MLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			5059 								(CAN) DURING A ROUTINE MAINTENANCE GEAR SWING, A VISUAL CHECK INDICATED FLUID LEAKAGE FROM THE ACTUATOR HEAD. INVESTIGAT	ION SHOWED A 2.0 INCH LONG LONGITUDINAL CRACK RUNNING FROM THE BASE THROUGH A SET SCREW HOLE TOWARDS MAIN BUSHING PIVOT 	BORE IN THE 3.0 INCH LONG JACK CYLINDER HEAD. ASSEMBLY REPLACED WITH OVERHAULED PART. SUGGEST OPERATORS OF ALL A/C SERIE	S DETAIL INSPECT ACTUATORS FOR LEAKAGE OR HIDDEN CRACKING UNDER LOOSE PAINT.			2	L	7	2 	4F			 	A3EU    					 
2000081400173	20000814	00173	SW  	2000	8	14	CA000731018      	1	20000627	G	2912	206076022005	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HYD PUMP & RESRV	CONTAMINATED    	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			12147	4995 		CC211858		CAE820296			(CAN) AFTER A DAYS FLYING, IT WAS DISCOVERED THAT THE HYDRAULIC FILTER BYPASS BUTTON HAD POPPED.  THE BUTTON WAS DEPRESS	ED, AIRCRAFT RUN UP, BUTTON POPPED AGAIN. CONTAMINATES WERE FOUND IN THE FILTER.  ALL HYDRAULIC LINES, SERVOS WERE FLUSH	ED, A NEW FILTER INSTALLED. THE AIRCRAFT WAS RUN AGAIN FOR 10 MINUTES, FEEDBACK WAS DISCOVERED IN THE CONTROLS. THE FILT	ER HAD MORE CONTAMINATES, CONTAMINATES WERE ALSO FOUND IN THE RESERVOIR. THE PUMP AND RESERVOIR ASSEMBLY WERE REPLACED, 	AS WELL AS A SERVO.  CONTAMINATES AND FEEDBACK NO LONGER EXIST.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000101300001	20001013	00001		2000	10	13	CA000731020      	4	20000512	G	8300	BP252	GEARBOX         	KLIMOV      	TB3117BMA   	KAMOV 	KA32  	KA32A1      	       	SW  										ASSY G/B	CONTAMINATED    	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			971  			708789210008		708789210008			(CAN) GEARBOX CHIP LIGHT, METAL CHIPS ON DETECTOR.  (X)						1	G	7	2 	4U			NC	        					 
2001032700127	20010327	00127	SW  	2001	3	27	CA000731021      	1	20000512	G	6220	D26212090	BEARING         		D262000DB   	KAMOV 	KA32  	KA32A1      	       	SW  										MAIN ROTOR HUB	FLAKING         	W				A	 	 	 	UNSCHED LANDING         				E		 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA			887  			920018					(CAN) VIRBATION, METAL FLAKES IN OIL. REDESIGN OF FLAPPING BEARING HUB IN PROGRESS.						1	G	7	2 	4U			NC	        					 
2001031400116	20010314	00116	CE  	2001	3	14	CA000731022      	1	20000630	G	3610	1143800025	COOLER          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					RT ENG NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6199 					PCE0S0115			(CAN) AIRCRAFT ARRIVED WITH SMALL OIL LEAK ON RT LOWER ENGINE NACELLE. PRECOOLER HAD CRACKED ALLOWING HOT P3 AIR TO BLOW	 ONTO OIL COOLER. OIL COOLER FINS MELTED ALLOWING OIL LEAK. OIL COOLER P/N 114-389000-5.THIS IS SECOND INSTANCE FOR THIS	 DEFECT FOR OUR FLEET IN LAST MONTH.NONE PREVIOUSLY NOTED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001031400117	20010314	00117	CE  	2001	3	14	CA000731023      	1	20000616	G	3610	1143800025	COOLER          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					RT ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5841 					PCEPSO141			(CAN) PILOTS REPORT RT ENGINE RUNNING HOTTER THAN LT. RT PRECOOLER HAD CRACK IN IT, P3 AIR STRIKING OIL COOLER CAUSED LE	AK. SMALL AMOUNT OF OIL COMING FROM OIL COOLER, P/N 114-3890005. THIS IS ONE OF TWO INSTANCES OF PRECOOLER BURNING INTO 	OIL COOLER THIS MONTH. NO PREVIOUS INSTANCES NOTED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE				 
2001032700128	20010327	00128	SW  	2001	3	27	CA000731025      	1	20000721	G	3320	4501221	PIVOT           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					CABIN LIGHTS	WRONG PART      	W				K	 	 	 	NONE                    				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PARTS NOT TO MANUFACTURERS SPECIFICATIONS I.E. BOGUS.ADDITION TO MULTIPLE REPORT PREVIOUSLY RE THE SAME PROBLEM. M	ELT DOWN.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000081700101	20000817	00101	CE  	2000	8	17	CA000801003      	1	20000717	G	5711	5147L	SPAR            	ARONCA      	11AC        	BBAVIA	11    	11AC        	0191102	CE  	CONT  	A65   	A658        	17003	SO  					REAR/OTBD END	CRACKED         	W				O	 	 	 	OTHER                   				O	P	 	OTHER                     	NO WARNING INDICATION     		IN	INSP/MAINT     	1			CA			1558 			11AC257		4699168			(CAN) DURING INSPECTION OF WING FOLLOWING WIND DAMAGE, CRACK FOUND IN UPPER EDGE OF LEFT REAR SPAR, OUTBOARD OF STRUT AT	TACH PLY PLATES.  SPAR REPLACED.					1	H	7	1 	3O	3	O	 	A761    	E205				 
2000080800173	20000808	00173	GL  	2000	8	8	CA000801006      	2	20000718	G	7240	68709926	CASE            	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMBUSTION CASE	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								CAE822700			(CAN) DURING A 100 HOUR INSPECTION AND TURBINE CHANGE THE AME NOTICED A CRACK IN THE ARMPIT AREA OF THE OUTER COMBUSTION	 CASE. INSPECTION C/W PER ALLISON 250-C20 SERIES O&M 10W2, 72-40-00 PARA 2B.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700132	20010327	00132	SW  	2001	3	27	CA000801009      	1	20000719	G	6420	212010782101	BEARING         		212010701055	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					T/R HUB	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			294  			AFS1486					(CAN) T/R BECAME UNBALANCED. INSPECTED HUB AND FOUND BEARING TEFLON LINER CAME OFF FROM OUTER RACE.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2000080800174	20000808	00174	WP  	2000	8	8	CA000801012      	1	20000722	G	6200	252466715H	GOVERNOR        	BENDIX      	252466715   	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			HO	HOVERING       	1			CA				567  		31160		CAE822593			(CAN) WHILE MAKING POWER CHANGES IN HOVER, THE ROTOR RPM DROPS AND OVERSPEEDS. 152.0 HOURS SINCE REPAIR.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001032700134	20010327	00134	EU  	2001	3	27	CA000801013      	1	20000719	G	2422	PC250	INVERTER        			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ELECTRICAL SYS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER CUSTOMER COMPLAINED OF OSCILLATION IN COMPASS CARD OF EHSI,  DETERMINED THAT PROBLEM CAUSED BY VOLTAGE FLUX 	OF NR 1 AC BUS. TROUBLESHOOTING REVEALED THAT VOLTAGE FLUX ONLY PRESENT WHEN INVERTER OPERATED AT APPROXIMATELY 12 TO 20	 PERCENT OF FULL LOAD. IT ALSO FOUND THAT BOTH INVERTERS ON A/C PRESENTED SAME PROBLEM. INVERTERS ARE MARATHON POWER TEC	HNOLOGIES MODEL PC-250, SER-NO 4343&4346. BOTH INVERTS ARE AT MOD LEVEL C. WHEN INVERTS W/O MOD C WERE INST IN A/C PROBL	EM NO LONGER PRESENT.		1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2000081700102	20000817	00102	CE  	2000	8	17	CA000801014      	1	20000619	G	5510	07123021	BRACKET         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	LT STABILIZER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6900 					9011950H	760187		(CAN) THE BRACKET ON THE LEFT STABILIZER WAS CHANGED AS IT WAS FOUND TO BE CRACKED.  P/N 0712302-1 WAS REPLACED WITH NEW	 PART USING EXISTING RIVET SIZE AND PATTERN.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2000081700103	20000817	00103	CE  	2000	8	17	CA000801015      	1	20000619	G	2740	07321014	HINGE BRACKET   			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	HORIZONTAL STAB	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6900 					9011950H	760187		(CAN) THE REINFORCEMENT STABILIZER HINGE (BOX) ON THE HORIZONTAL STABILIZER WAS CHANGED.  P/N 0732101-4 WAS REPLACED WIT	H NEW PART USING EXISTING RIVET SIZE AND PATTERN.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2000112800123	20001128	00123	SW  	2000	11	28	CA000801016      	1	20000801	G	2910	MS287786	O-RING          		PU304426    	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					O-RING	PINCHED         	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CR	CRUISE         	1			CA						R512341		P52065C			(CAN) DURING CRUISE FLIGHT, A TOTAL HYDRAULIC FAILURE WAS ENCOUNTERED, AN EMERGENCY GEAR EXTENSION WAS PERFORMED AND THE	 AIRCRAFT LANDED WITHOUT INCIDENT.  A SUBSEQUENT INSPECTION REVEALED THAT THE HYDRAULIC SYSTEM FLUID LEVEL WAS AT ZERO, 	CAUSED BY A LEAK AT THE OUTPUT FITTING PIN AN815-65 OF THE LT HYDRAULIC PUMP, FURTHER INSPECTION REVEALED THAT THE O-RIN	G FOR THIS FITTING HAD BEEN PINCHED ON INSTALLATION OF THE HYDRAULIC PUMP THE PREVIOUS DAY. THE O-RING WAS REPLACED, THE	 HYDRAULIC SYSTEM SERVICED AND THE AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2000112800125	20001128	00125	EU  	2000	11	28	CA000801021      	3	20000405	G	6111		BLADE           	MUHBR       		RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  	MUHBR	MTV	MTV3BC      	EU  	PROPELLER BLADES	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			744  					L2594848A	97059		(CAN) LOOSE PROPELLER BLADES.						1	M	7	1 	3O	3	O	NC	EA67U   	1E4	5	C	USSR	 
2000112800126	20001128	00126	EU  	2000	11	28	CA000801022      	1	20000531	G	5412		FIREWALL        			RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  					FIREWALL	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA			740  			043		L2594848A			(CAN) FIRE WALL NEEDS TO BE STIFFENED.						1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
2000112800127	20001128	00127	EU  	2000	11	28	CA000801023      	1	20000531	G	7110		COWLING         	LYC         		RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  					HOLE	ELONGATED       	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			743  			L2592348A		L2592348A			(CAN) SAME PROBLEM AS WITH C-GAKN.  COWLING IS FALLING OFF DUE TO STRUCTURALLY INADEQUATE FIREWALL.						1	M	7	1 	3O	3	O	NC	EA67U   	1E4				 
2000083101005	20000831	01005	SO  	2000	8	31	CA000801027      	2	20000720	G	7314	476411	PUMP            	CONT        		CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	WIRE ENTER.PUMP	SHORTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			56   					276649R	7911065		(CAN) THE ELECTRICAL WIRE WHERE IT ENTERS THE PUMP HAS SHORTED.  THIS WIRE IS COVERED BY A BRAIDED WIRE.  NO DISASSEMBLY	 HAS BEEN CARRIED OUT, HOWEVER, 24V WAS APPLIED TO PUMP TO CONFIRM SHORT.  SUBMITTER STATED THIS IS THE SECOND PUMP REPL	ACEMENT ON THIS AIRCRAFT IN THREE MONTHS.				1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2000083101006	20000831	01006	SO  	2000	8	31	CA000801028      	2	20000704	G	7314	476411	PUMP            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FUEL PUMP	INOPERATIVE     	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			19   					815004R	767565		(CAN) BURNING ODOR WAS NOTICED FROM LT WING TIP AND LT LANDING LIGHT.  CIRCUIT BREAKER TRIPPED.  (TIP TRANSFER PUMP RECE	IVES POWER FROM THIS BREAKER AND PUMP IS RUNNING WHENEVER MASTER SWITCH IS ON).  PUMP WAS REMOVED AND APPROXIMATELY 1/2 	OF THE PUMP BODY WAS FOUND DISCOLORED BY HEAT.  (PROBLEM NOTICED ON WALKAROUND).  SUBMITTER STATED THESE PUMPS FAIL ON A	 REGULAR BASIS (LT PUMP RECENTLY CHANGED WITH 90 HOURS SINCE NEW),  HOWEVER, THIS IS THE FIRST ONE FOUND HEAT DISCOLORED	.  NORMAL FAILURE MODE IS FOR THE PUMP TO SLOWLY STOP RUNNING.  NOTE:  IN THIS INSTALLATION THE PUMP IS USED TO PUMP FUE	L INTERNALLY IN THE TANK TO THE AREA OF THE FUEL OUTLET.	1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000083101007	20000831	01007	EA  	2000	8	31	CA000801029      	2	20000721	G	7322	105062N	CARBURETOR      			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	CARBURETOR	FAILED          	W				O	 	 	 	OTHER                   				R		 	PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA						BC01025					(CAN) DURING ENGINE START, ENGINE BACKFIRED.AFTER ENGINE START, ENGINE WOULD IDLE, BUT NOT DEVELOP POWER.  ENGINE RUNS S	MOOTH UNDER 1,000 RPM,  OVER 1,000 RPM ENGINE RUNS ROUGH.  WILL NOT EXCEED 1200 RPM.  REMOVED CARBURETOR AND INSTALLED O	VERHAULED UNIT.  ENGINE RUNS PERFORMED.  ALL PARAMETERS NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000083101008	20000831	01008	CE  	2000	8	31	CA000801030      	1	20000721	G	7920	AE3663162E0210	HOSE            	PWA         		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					HOSE ASSY	LOOSE           	W				E	 	 	 	ENGINE SHUTDOWN         				J	K	 	WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA								PCE70491			(CAN)  IN CRUISE AT APPROXIMATELY 31,000 FEET, PILOT NOTICED RT ENGINE OIL PRESSURE SLOWLY DROPPING, PER THE FLIGHT MANU	AL, THEN REDUCED POWER AND AS THE PRESSURE APPROACHED 36 PSI THEY PERFORMED A PRECAUTIONARY SHUTDOWN AND LANDED IN CINCI	NNATI, OHIO.  MAINTENANCE FLEW DOWN AND PERFORMED AN INSPECTION, FOUND OIL PRESSURE LINE TO OIL PRESSURE TRANSDUCER LOOS	E, APPROXIMATELY  2 TURNS TO TIGHTEN, LINE TIGHTENED ADDED 5 QUARTS OF AEROSHELL 500 AND PERFORMED FULL POWER RUNS.  NO 	LEAKS OBSERVED.  PRESSURE AND TEMPERATURES  NORMAL.  AIRCRAFT RETURNED TO SERVICE.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2000083101009	20000831	01009	CE  	2000	8	31	CA000801031      	1	20000717	G	7120	05510171	MOUNT           	CONT        		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					LOWER INNER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1900 				L2800027A			(CAN) CRACK DISCOVERED.  SCHEDULED MAINTENANCE, MOUNT REMOVED - SENT FOR NDT - REPAIR - NDT - PAINT RE-INSTALLED.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001032700135	20010327	00135	CE  	2001	3	27	CA000801033      	1	20000717	G	2134		PRESSURE SWITCH 			LEAR  	25    	25B         	5170511	CE  										CABIN PRESSURE	FAILED          	W				B	 	 	 	EMER. DESCENT           				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) A/C EXCEDED MAX ALT DUE TO UPDRAFT, A/C PRESSURIZATION SYSTEM ANORIDE SWITCH OPERATED TO SPEC UPON DESCNET SYSTEM 	OPERATED NORMALLY. I.A.W. L25 MM 21-30-07.					2	L	7	2 	4J			 	A10CE   					 
2001031400127	20010314	00127	EA  	2001	3	14	CA000802007      	1	20000720	G	2742		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										STABILIZER	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN)  DEPARTING MONTEREY, CA. CLIMBING OUT THRU FL200. EICAS ALERTED US OF AP PITCH TRIM MASTER CAUTION FOLLOWED BY AP 	PITCH TRIM NOSE DOWN MASTER CAUTION ANNUNCIATOR. WE FOLLOWED CFM PROCS&UPON DISCONNECTING AUTOPILOT HAD TO MAINTAIN ABOU	T 2 IN OF NOSE DOWN PRESSURE ON YOKE TO MAINTAIN LEVEL FLT. WOULD NOT TRIM DOWN IT STUCK AT 4 UNITS. IT WOULD TRI M UP B	UT NOT DOWN . WE CALLED MIX ON SELCAL THEN TALKED TO DISPATCH & DECIDED  TO DIVERT TO FRESNO, CALF. APPROXIMATELY 20 MIN	 AWAY. WE DECLARED EMERGENCY & LANDED UNEVENTFULLY ON 29 RT, IN FRESNO .		2	L	7	2 	4F			RT	A21EA   					 
2001031400128	20010314	00128		2001	3	14	CA000802008      	4	20000709	G	2397	31116062	WIRE            			LKHEED	1011  	1011385115  	5265015	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					TRANSCEIVER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE TROUBLE SHOOTING HF PROBLEM, FOUND COAX CABLE BEHIND TRANSCEIVER DAMAGE AT CONNECTOR (SHIELD BROKEN). CABLE 	REPLACED AND AIRCRAFT RETURNED TO SERVICE. SPECIAL INSPECTION WILL BE IN PLACE SHORTLY TO INSPECT THESE CABLE ON ALL L-1	011.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001031400130	20010314	00130	NM  	2001	3	14	CA000802010      	1	20000713	G	2820		COUPLING        			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					FUEL LINE	CONTAMINATED    	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								30739			(CAN) UNABLE TO ACHIEVE TAKEOFF POWER, WITHOUT RETURNING AT THE DATE, CREW DID A SUCCESSFUL POWER RUN AND A/C DEPARTED. 	SAME THING HAPPENED ON THE NEXT LEG. AFTER INVESTIGATION, MAINTENANCE FOUND COUPLING BETWEEN ENGINE AND FRAME FFG CABLE 	CONNECTOR CONTAMINATED WITH CARBON AND DIRT. CLAMP CLEANED AND RETORQUED. A/C RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001031400131	20010314	00131	NE  	2001	3	14	CA000802011      	2	20000722	G	7260		CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	LEAKING         	W				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  PILOT REPORTED LT ENGINE OIL PRESSURE WARNING AND OIL PRESSURE FLUCTUATING BETWEEN 24 & 45 PSI. PILOT SHUT DOWN T	HE ENGINE. MAINTENANCE FOUND THAT THE ENGINE REQUIRED 5 LITERS OF OIL. NO EXTERNAL LEAK FOUND. ENGINE RUN CARRIED OUT AN	D LEAKAGE FOUND FROM IDG DRIVE PAD CARBON SEAL.CARBON SEAL REPLACED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400132	20010314	00132	EA  	2001	3	14	CA000802012      	1	20000722	G	2612	47259701	FIRE DETECTOR   			CNDAIR	CL600 	CL6002B19   	       	EA  										APU	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, FLT APU FIRE WARNING MESSAGE APPEARED ON ED NR 1. QRH FOLLOWED, MESSAGE REMAINED FOLLOWED BY A RT E	XAUST PIPE OVERHEATED WARNING MESSAGE. THEN LT ENGINE FIRE WARNING MESSAGE APPEARED ON EDI. QRH FOLLOWED, LEFT ENGINE SH	UTDOWN AND AIRCRAFT DIVERTED TO TYS AND A SINGLE ENGINE LANDING. AIRCRAFT WAS EVACUATED.THE FIRE DETECTOR P/N 472597-01 	WAS REPLACED.			2	L	7	2 	4F			RT	A21EA   					 
2001031400133	20010314	00133	EA  	2001	3	14	CA000802013      	1	20000722	G	3222		STRUT           			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, WHEN GEAR HANDLE SELECTED UP, GEAR DISAGREE WARNING MESSAGE, WOW INPUT CAUTION MESSAGE, NOSE DOOR O	PEN, STEERING INOP MESSAGE. CREW DECLARED AN EMERGENCY AND RETURNED TO CVG, COMPLETING AN UNEVENTFUL LANDING. THE NOSE S	TRUT WAS SERVICED AND A/C RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001032700136	20010327	00136	EA  	2001	3	27	CA000802014      	1	20000722	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				B	 	 	 	EMER. DESCENT           				F		 	FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) REMOVED AND REPLACED THE BPSU. INSTALLED  BUT IT FAILED DURING THE TEST AND FIRED THE FBCU (CRITICAL FAILURE).						2	L	7	2 	4F			RT	A21EA   					 
2001032700137	20010327	00137		2001	3	27	CA000802015      	4	20000715	G	2562	762357	STRAP           	NARCO       	5480054     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ELT SUPPORT	WORN            	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			12649								(CAN)   AT ANNUAL INSPECTION REMOVAL OF ELT FOR CERTIFICATION.  REMOVED DORSAL FIN ACCESS TO ELT PANEL & FOUND ELT NOT S	ECURED PROPERLY IN ITS MANUFACTURERS SUPPORT BASE LATCH ON STRAP  HAD COME UNDONE, WHAT APPEARS FROM VIBRATION. IT IS PL	AUSIBLE TO THINK THAT IF THE AIRCRAFT IMPACTED FWD & WITH NAGATIVE UPWARDS FORCES, ELT MIGHT NOT COME ON. A PORTION OF T	HE SPRING IN THE LATCH WAS WORN, THUS RELEASING WHEN TAPPED OR SLIGHTLY SHAKEN.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083101010	20000831	01010	SO  	2000	8	31	CA000802016      	1	20000715	G	3050	597257	ANTENNA         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT TOP FUSELAGE	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			12649					L159368A			(CAN) 1) COMING UP THE STEP LADDER TO REPLACE ELT FOR ANNUAL CERTIFICATION AND BATTERY DUE CAR 625 APP. C PARA 11A).  ME	CHANIC/AME NOTICED ELT ANTENNA MISSING.  BROKEN FLUSH AT BASE NUT TO FUSELAGE SKIN AND DOUBLER.  REPLACED WITH NEW KIT N	R 455-9000 REV D. - 110-324 REV A ANTENNA WHIP W/INDUCTOR - 611-6013-10 REV A COAX CABLE NARCO.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000080700176	20000807	00176	WP  	2000	8	7	CA000802017      	1	20000718	G	5510	369D2363312	TIP CAP         		369D23601   	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					RIGHT STABILIZER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			2695 			1571		CAE830428			(CAN) DURING  FLIGHT A VIBRATION WAS FELT IN THE FLOOR AND WENT AWAY AS THE AIRCRAFT WAS RETURNING TO THE LANDING SITE. 	THE ENGINEER INSPECTED THE AIRCRAFT AND FOUND THE TIP PLATE OF THE R/H SIDE OF THE HORIZONTAL STABILIZER WAS MISSING.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000083101011	20000831	01011	NE  	2000	8	31	CA000802018      	2	20000710	G	8530		CYLINDER        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					AROUND HEAD	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				12   		41557		41557			(CAN) THE CYLINDER HEAD SEPARATED FROM CYLINDER BARREL.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001032700138	20010327	00138	CE  	2001	3	27	CA000802019      	1	20000713	G	2121	50041	MOTOR           		1013841001  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					BLOWER	FAILED          	W				I	G	 	 	CABIN DEPRESSURIZATION  	O2 MASK DEPLOYED        			B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				400  		1709					(CAN) - AIRPLANE HAD SMOKE IN COCKPIT / CABIN.  AFTER TROUBLESHOOTING FOUND THAT FORWARD BLOWER MOTOR MAKING GRINDING  N	OISE AND SMOKE.  REPLACED FORWARD BLOWER ASSEMBLY GROUND CHECK SERVICE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000083101012	20000831	01012	EA  	2000	8	31	CA000802020      	2	20000714	G	7414	ES10382681	CAPACITOR       	BENDIX      	1068291618  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LT MAG-DUAL	BURNED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TO	TAKEOFF        	1			CA				418  		8010918		L159368A			(CAN)  PRE-TAKEOFF RUN, PILOT CHECKED RT MAG OFF.  ENGINE QUIT.   PILOT TOLD FUEL NATURE OF DEFECT TO FSS MONT-JOLI WHEN	 ADVISING THEM WERE RETURNING TO BLOCK.  LEFT MAGNETA (DUAL TYPE) CAPACITOR CHECKED.  NO CONTINUITY.  SIGNS OF BURNS WHE	RE WIRE IS SEALED-PITTED INTO CAPACITOR.  REPLACED, RUN-UP, LOG ENTRY.  NOTE:   FAILED CAPACITOR WAS CHECKED ON 18 MARCH	 2000 AS N/A BY DATE AND NAME OF  MANUFACTURER.  AEF:  LYC SB 541 (TCM CSB NR 662A AND S.1.2  NR 642).			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000083101013	20000831	01013	CE  	2000	8	31	CA000802023      	1	20000714	G	3230	51577A1	SOLENOID        			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	SOLENOID	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			5024 					19879072H	19879072H		(CAN) AFTER TAKEOFF AND LANDING SELECTED UP AND LOCKED.  LANDING GEAR CIRCUIT BREAKER TRIPPED.  (PROBLEM RETURNED INTERM	ITTENTLY.)  PROBLEM TRACED TO DEFECTIVE LANDING GEAR SOLENOID.  SOLENOID REPLACED, PROBLEM SOLVED.					1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P21EA	 
2000101000349	20001010	00349	CE  	2000	10	10	CA000802024      	1	20000714	G	2730	12326241	BRACKET         			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	LT INBD	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4955 					19879072H	19879072H		(CAN) DURING THE INSPECTION OF THE STABILIZER, A CRACK WAS FOUND ON THE INBOARD LT STABILIZER BRACKET TO ELEVATOR P/N 12	32624-1 ATTACHED TO THE SPAR.  PROBLEM WAS REPAIRED.					1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P21EA	 
2000101000350	20001010	00350	SO  	2000	10	10	CA000803002      	2	20000717	G	8530	635448	CYLINDER        	CONT        		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	CYLINDER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				580  				566472	777484		(CAN) HEAD CRACKED TWO/THIRDS AROUND AT 3RD FIN FROM BOTTOM OF HEAD.  HEARD BY MAINTENANCE WHEN AIRCRAFT WAS TAXIING TO 	DOCK, PILOT REPORTED NO INDICATION OF PROBLEM.  NO CAUSE FOUND.  CYLINDER REPLACED.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2000101000351	20001010	00351	NM  	2000	10	10	CA000803003      	1	20000712	G	3242	214664	HOUSING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					PISTON BORE	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10198	1275 		1168					(CAN) BRAKE REMOVED FROM AIRCRAFT BECAUSE OF BRAKE BEING WORN TO LIMITS. INSPECTION AT SHOP REVEALED A CRACK IN ONE PIST	ON BORE .700 INCH.  BRAKE HOUSING SCRAPPED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2000101000352	20001010	00352	SO  	2000	10	10	CA000803004      	1	20000718	G	7797		WIRE            	PIPER       	86749002    	PIPER 	PA44  	PA44180     	7104402	SO  										8 IN FROM SENDER	CHAFED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING TRAINING, FLT INSTRUCTOR NOTICED LEFT ENGINE TEMP GAUGE PEGGED AT HIGH RED LINE.  PREVIOUS SCANS OF INSTRUM	ENTS, BY BOTH STUDENT AND INSTRUCTOR HAD NOT INDICATED ANY PROBLEM.  LOWER POWER SETTING TRIED BUT DID NOT DECREASE THE 	TEMP: PILOT MADE DECISION TO SHUT DOWN ENGINE TO AVOID DAMAGE AND HEADED INBOUND TO FIELD (YQM). A/C LANDED WITHOUT FURT	HER INCIDENT.  ENGINE GROUND RUN SERVICEABLE, BUT DECISION MADE TO INSPECT FURTHER.  WIRE FROM INBOARD OF NACELLE, TO TE	MP SENDER REMOVED FOR INSP.  WIRE FOUND CHAFED 8 INCHES FROM SENDER.  IT RUBBING ON ENGINE MOUNT OBSTRUCTED BY TY-RAPS A	TTACHING IT.  WIRE REPLACED, ISOLATED AND ACFT RETURNED TO SERVICE	1	L	7	2 	3O			 	A19S0   					 
2000101000353	20001010	00353	EU  	2000	10	10	CA000803005      	1	20000707	G	2434	ALK8421	ALTERNATOR      			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					RT ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				283  		A121326		L2371751A			(CAN)ALTERNATOR  NOT CHARGING, POSSIBLY DUE TO INTERNAL PROBLEMS.						1	H	7	2 	3O	3	O	 	A31EU   	1E10				 
2000081600336	20000816	00336	SW  	2000	8	16	CA000803006      	1	20000719	G	7930	B3225C	CHIP DETECTOR   	BELL        	2060402703  	BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FREEWHEEL ASSY	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						BLA05631		CAE295348			(CAN) DURING DAILY INSPECTION, IT WAS NOTICED THAT A PIN WAS NOT IN THE CHIP DETECTOR HOUSING ASSEMBLY.  UPON REMOVAL IT	 WAS FOUND THAT 2 OF THE 3 PINS WHICH HOLD THE CHIP DETECTOR IN PLACE WERE MISSING.  PINS COULD NOT BE FOUND.  CHIP DETE	CTOR ASSEMBLY WAS REPLACED.  (X)				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001031500106	20010315	00106	NM  	2001	3	15	CA000804007      	1	20000803	G	2700	841005	PSEU            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILERS	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA			27962			009		120833	860404		(CAN) ROLL SPOILER INBOARD / OUTBOARD GROUND CAUTION LIGHTS ILLUMINATED WHEN POWER LEVERS ADVANCE. DURING GROUND RUNS. F	AULT PERSISTED WITH AUTO-FEATHER ON OR OFF. DRIVER FAULT ON PSEU. PSEU REPLACED, MICRO SWITCHES CLEANED AND AIRCRAFT RET	URNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2000100200012	20001002	00012	CE  	2000	10	2	CA000804011      	1	20000723	G	2434	ES4147	STATOR          	FORD        	10300J      	BEECH 	P35   	P35         	1151530	CE  	CONT  	O470  	IO470N      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	DIODE PLATE	BROKEN          	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			20   					CS961508NR	705112		(CAN) TWO LEGS OF STATOR WINDING BROKE AT DIODE PLATE.  RESULTS NO ALTERNATOR OUTPUT.  (X)						1	L	7	1 	3O	3	O	RT	3A15    	3E1	5	C	P880	 
2000100200027	20001002	00027		2000	10	2	CA000804014      	4	20000711	G	3452	414201128	TRANSPONDER     	CESSNA      		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	INTRNL CIR BOARD	MELTED          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						16577		467467	7710865		(CAN) AIRCRAFT HAD BEEN AT CRUISE ALTITUDE FOR ABOUT TWO HOURS WHEN A STRONG BURNING SMELL WAS NOTICED BY ALL ABOARD.  A	N IMMEDIATE DESCENT WAS INITIATED AND CALGARY ATC DID AN EXCELLENT JOB OF DIVERTING TRAFFIC TO ALLOW A STRAIGHT IN APPRO	ACH.  PILOT ATTEMPTED TO SHED ALL UNNECESSARY ELECTRICAL LOADS AND AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  (X)				1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001031500110	20010315	00110	NM  	2001	3	15	CA000804015      	1	20000722	G	3244	0396772	TIRE            			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA								674569			(CAN) CREW REPORTED LOUD BANG FROM NOSE WHEEL AREA ON TAKEOFF ROLL AND JUST BEFORE ROTATION. THEY ALSO NOTICED SOMEHTING	 GO PAST THE WINDSCREEN. A FLY PAST THE CONTROL TOWER AND DEBRIS FOUND ON THE RUNWAY CONFIRMED TREAD SEPARATION FROM ONE	 OF THE NOSE WHEEL TIRES. THE AIRCRAFT FLEW AROUND TO BURN OFF SUFFICIENT FUEL AND LANDED WITHOUT INCIDENT.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031500111	20010315	00111	NM  	2001	3	15	CA000804016      	1	20000722	G	2121	215201	MOTOR           			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					GASPER FAN	SEIZED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			6915 	776  				P685509B			(CAN) DURING THE CLIMB FROM 4XS (SASKATOON) THE CREW BECAME AWARE OF A STRANGE ODOR / SMELL IN THE CABIN. THERE WAS NO S	MOKE OBSERVED BUT THE CREW ELECTED TO RETURN TO THE STATION AS A PRECAUTION. ON THE GROUND THE CREW CHECKED AND FOUND TH	E GASPER FAN C/B POPPED. WHEN THEY ATTEMPTED TO RESET IT THE ODOR RETURNED TO THE CABIN. THE C/B WAS PULLED AND MEL 21-2	4 WAS APPLIED. THE GASPER FAN WAS REPLACED AT THE NEXT MAINTENANCE OPPORTUNITY.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031500112	20010315	00112	NM  	2001	3	15	CA000804017      	1	20000712	G	5754	65555261	TRACK           			BOEING	737   	737297      	1384480	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					SLATS	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P665885			(CAN) DURING THE WALK AROUND AND INSPECTION FOR AN A CHECK THE MECHANIC NOTICED EXCESSIVE MOVEMENT IN THE NR 6 SLAT. FUR	THER INVESTIGATION REVEALED THAT THE CENTER AUX RACK HAD BROKEN AT THE ATTACH POINT TO THE SLAT. THE SLAT ASSEMBLE WAS R	EPLACED WITH A SERVICEABLE UNIT. REFERENCE ATTACHED PHOTOGRAPHS.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000100200029	20001002	00029	SO  	2000	10	2	CA000804019      	1	20000725	G	7714	574AW	TACHOMETER      	CONSOLCNTRLS		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					TACHOMETER	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA				187  		7124		L91668A			(CAN) PILOT REPORTED RIGHT TACHOMETER NEEDLE ERRATIC.  TACHOMETER REPLACED WITH SERVICEABLE UNIT.  GROUND RUN CARRIED OU	T SATISFACTORILY.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031500114	20010315	00114	GL  	2001	3	15	CA000808002      	1	20000719	G	2730	SOGC4193000	CONTROL UNIT    			BOMBDR	BD700 	BD7001A10   	1390006	GL  										ELEVATORS	FAILED          	W				A				UNSCHED LANDING         				L	F		NO TEST                   	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) DURING PRODUCTION TEST FLIGHT STALL RECOVERY TEST 30 DEG FLAP, GEARDOWN, THE AIRCRAFT EXPERIENCED ABNORMALLY HEAVY	 PITCH CONTROL FORCES. THE ABNORMALITY WAS CLEARED BY HIGH PILOT EFFORT AT THE CONTROL COLUMN. ALL PRODUCTION FLIGHT TES	TING WAS STOPPED AT THAT POINT AND THE AIRCRAFT RTURNED SAFELY TO BASE WITHOUT FURTHER INCIDENT.				2	L	7	2 	4F			RT	T00003NY					 
2000100200033	20001002	00033	EA  	2000	10	2	CA000808004      	3	20000707	G	6111		PROPELLER       	SNSNCH      		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	L/E & FACE	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				115  				L2254827A	A56025		(CAN)  PROPELLER RECEIVED FOR CORROSION INSPECTION; TRIMMED, ANODIZED, PAINTED.  (X)						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000100200034	20001002	00034	EA  	2000	10	2	CA000808005      	3	20000711	G	6111		BLADE           	SNSNCH      		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	CAMBER SIDE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA								L3331127A	K35171		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000100200035	20001002	00035	EA  	2000	10	2	CA000808006      	3	20000710	G	6111		PROPELLER       	SNSNCH      		PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	FACE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				903  				L1737427A	A52179		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  REQUIRED OVERHAUL DUE TO CORROSION.  (X)						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2000100200036	20001002	00036	NE  	2000	10	2	CA000808008      	3	20000726	G	6110		PROPELLER       	HAMSTD      		NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	PROPELLER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1134 		8872CPL		404173	8872CPL		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CWT BRACKET WEB WORN BEYOND REPAIR.  BLADE MERROR FINISHED WITH DEEP	 CORROSION.  NOTE:  MERROR FINISH IS NOT A GOOD THING FOR PROPELLER BLADES, IT DOES NOT OFFER ANY CORROSION PROTECTION. 	 BLADE BEARINGS DRY.   (X)				1	L	7	1 	3R	3	R	 	EXPA1L71	5E2	5	C	P257	 
2000100200037	20001002	00037	CE  	2000	10	2	CA000808009      	1	20000801	G	3411	201314217	SELECTOR VALVE  			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  						LEAKING         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA								PCE19192			(CAN) IN FLIGHT PILOT NOTICED A DISCREPANCY BETWEEN COPILOT AND PILOT AIR SPEED AND ALTIMETER. PILOT RETURNED TO MAINTEN	ANCE BASE AND FOUND BODY OF SELECTOR VALVE SPARATED FROM DASH MOUNT PLATE CAUSING LARGE STATIC LEAK. VALVE WAS REMOVED, 	REASSEMBLED USING ORIGINAL PARTS AND REINSTALLED IN AIRCRAFT. LEAK CHECKED OK AND RETURNED TO SERVICE.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000100200038	20001002	00038		2000	10	2	CA000808010      	4	20000720	G	6122		RELIEF VALVE    	HAMSTD      		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	RELIEF VALVE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			167  			T16413		JP207431	T16413		(CAN) LOW PITCH STOP NUTS BROKEN, CWT SHAFTS BENT.  THIS PROPELLER  USES GOVERNOR OIL PRESSURE TO MOVE PROP TO LOW PITCH	 WITH RELIEF VALVE SET AT 200 PSI WHICH WILL NOT DAMAGE LOW STOPS.  RELIEF VALVE HAD TO BE NON-OPERATIONAL DUE TO CONTAM	INATION, CORROSION OR TAMPERING TO CAUSE THIS DAMAGE.  (X)				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2001031500116	20010315	00116	WP  	2001	3	15	CA000808012      	1	20000728	G	7920	95551655	LINE            			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  					LT ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								461615			(CAN) HOSE REMOVED DUE ON CONDITION STATUS WHICH IS UNKNOWN. OUTER RUBBER FALLING OFF AND BRAIDING EXPOSED AND RUST CORR	OSION ON BRAIDING FULL LENGTH OF HOSE, FROM OIL COOLER TO OIL TANK.					2	L	7	2 	4R	4	R	 	A669    	5E4				 
2001031500117	20010315	00117	EA  	2001	3	15	CA000808013      	1	20000726	G	4950		FILTER          			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					BLEED AIR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			270  					350132			(CAN) ON JULY 25, 2000 CREW REPORTED UPON SELECTION OF APU BLEED AIR ASSOCIATED INDICATOR. OF LOAD CONTROL VALVE OPENING	 HAD FAILED.  A/C MAINT ENGINEER OPENED EXTERNAL AIR SOURCE PANEL  ONLY TO FIND APU FAULT INDICATOR PANEL HAD MELTED. FU	RTHER INVEST. FOUND THAT APUS LOAD CONTROL VALVE FILTER HAD DEPARTED FROM VALVE ASSY & TRAVELLED THROUGH PNEUMATIC PLUMB	ING EVENTUALLY JAMMING CHECK VALVE LOCATED AT EXTERNAL AIR SOURCE COUPLING. RESULTANT 10TH STAGE AIR LEAKED INTO ACCESS 	PANEL AREA & HEATED APU FAULT PANEL TO POINT OF MELTING IT. THE FAULT PANEL WAS ISOLATED, PNEUMATIC SYS INSP & A NEW LOA	D CONTROL VALVE INSTALLED, DISCREPANCY RECTIFIED.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2001032700139	20010327	00139	EA  	2001	3	27	CA000808022      	1	20000730	G	2730	276003	PCU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT & RT ELEVATOR	LEAKING         	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING FIRST FLIGHT OF THE DAY ELEVATOR SYSTEM CHECK USING NR 2 HYDRAULIC SYSTEM ONLY, ELEVATOR POSITION	 EICAS READINGS SHOWING SPLIT AS MUCH AS 15-24 DEGREES. LT ELEVATOR PCU NR 2 AND RT ELEVATOR PCU NR 3  REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031500124	20010315	00124	NE  	2001	3	15	CA000808023      	2	20000730	G	7321		FUEL CONTROL    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CAPTAIN BROUGHT THROTTLES BACK TO FLIGHT IDLE AND THE NR 1 ENGINE STAYED AT A CRUISE POWER SETTING. IN FLIGHT SHUT	DOWN PERFORMED ON THE LT ENGINE. DECLARED EMERGENCY. MAINTENANCE REPLACED THE LT ENGINE FUEL CONTROL UNIT. ENGINE CHECKE	D SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031500125	20010315	00125	NE  	2001	3	15	CA000808024      	2	20000731	G	7261		O-RING          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	K		WARNING INDICATION        	FLUID LOSS                		CL	CLIMB          	1			CA											(CAN) DURING A FERRY FLIGHT FROM MORLAIX TO CAEN, PILOTS REPORTED A LT ENGINE N2 FLUCTUATION FOLLOWED BY A LOW OIL PRESS	URE WARNING MESSAGE. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT COMPLETED AN UNEVENTFUL  LANDING IN MORLAIX. FINDINGS:   	OIL LEAK WAS FOUND AROUND THE AXIS . A O-RING RETAINER, 5 LITRES OF OIL ADDED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000100200234	20001002	00234	NE  	2000	10	2	CA000808025      	2	20000808	G	8530	399356	CYLINDER        	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					CYLINDER HEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				286  		13569		13569			(CAN) NR 4 CYLINDER HEAD FOUND CRACKED WHILE DOING AN UNSCHEDULED VISUAL INSPECTION OF THE ENGINE FORWARD FACE.  CRACK W	AS NOT DETECTED AT THE LAST INSPECTION 60.3 HOURS BEFORE THIS EVENT.  CRACK LOCATED AT EXHAUST PUSH ROD/ROCKER  HORN.  S	ERVICEABLE UNIT INSTALLED AND RETURNED TO SERVICE.  (X)				1	H	7	1 	3R	3	R	 	A815    	5E2				 
2001032700142	20010327	00142		2001	3	27	CA000809006      	4	20000724	G	2312	064105430	TRANSCEIVER     			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					VHF SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				B		 	SMOKE/FUMES/ODORS/SPARKS  			FF	FIRE FIGHTING  	1			CA											(CAN) DURING FIRE FIGHTING OPERATIONS THE NUMBER 2 POSITION VHF TRANSCEIVER HAD FAILED. THE PILOT SMELLED SMOKE IN THE C	OCKPIT AND TURNED OFF THE RADIO. THE AIRCRAFT RETURNED TO YKA. THE SOURCE OF THE SMOKE WAS INVESTIGATED AND FOUND TO BE 	FROM THE NUMBER 2 VHF RADIO. THE RADIO WAS REPLACED WITH A SERVICEABLE UNIT.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000100200049	20001002	00049	WP  	2000	10	2	CA000809007      	2	20000730	G	7250	31015701	SEAL            	ALIDSG      	310210610   						GARRTT	TPE331	TPE331*     	01514	WP  					LABYRINTH SEAL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2680 			5013455176					(CAN) DURING PRE-INSTALLATION INSPECTION, IT WAS NOTICED THAT THERE WAS EXCESSIVE GAP BETWEEN THE SEAL AND THE ROTOR.  G	AP WAS MEASURED AT 0.022 INCHES.  IRM 72-IR-15 R9 STATES THAT THE GAP SHOULD BE NO LARGER THAN 0.010 INCHES.										3	T			E2WE				 
2001032700144	20010327	00144	CE  	2001	3	27	CA000809011      	1	20000713	G	3213	998100289	BRACE           			BEECH 	99    	99          	1154002	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4060 								(CAN) FATIGUE CRACKS LOCATED AT BASE OF TQ KNEE LUG ON UPPER BRACE. CRACKS RANGE IN SIZE FROM 1/4 TO 3/8 INCH LONG AND R	UN PARALLEL TO THE TQ KNEE LUG RADIUS. UPPER BRACE REMOVED FROM SERVICE.					1	L	7	2 	3T			 	A14CE   					 
2001032700145	20010327	00145	CE  	2001	3	27	CA000809012      	1	20000724	G	2134	44EVAB4	TUBE            			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					BLEED AIR	SPLIT           	W				B		 	 	EMER. DESCENT           				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB CREW OBSERVED A RT BLEED AIR LIGHT. WHEN RT BLEED AIR SWITCHED OFF, LT BLEED WOULD NOT HOLD CABIN PRE	SSURE. AN EMERGENCY DESCENT WAS CARRIED OUT. AT 7,000 THE AIRCRAFT LEVELED OFF AND RETURNED TO BASE. THE DAMAGED PIECE O	F TUBING WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THIS TUBING IS PRESSURIZED BY THE BLEED AIR SYSTEM. IF IT LE	AKS. AS IS THE CASE WITH THIS AIRCRAFT IT WILL GIVE A BLEED AIR INDICATION, AND A FALSE WARNING TO THE FLIGHT CREW.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001032700146	20010327	00146		2001	3	27	CA000809013      	4	20000728	G	3418		CONTROL UNIT    			DHAV  	DHC7  	DHC7*       	       	EA  										STALL WARNING	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			24220								(CAN) ARKIA AIRLINES FLIGHT CREW REPORT RECEIVING A STALL WARN/STICK SHAKER DURING INITIAL CLIMB, APPROXIMATELY 500 FT. 	IAS 100 KTS/120 KTS AT THE TIME THE INCIDENT OCCURRED. CREW REACTED BY ADVANCING PLA ON ALL ENGINES & REPORT ALL THE ALL	 STALL WARNINGS LASTED APPROX. 30 SECS. CREW THEN CARRIED OUT AN IMMEDIATE AIR RETURN TO DOV AIRPORT. NO EMERGENCY WAS D	ECLARED & AIRCRAFT LANDING WAS UNEVENTFUL DFDR & CVR REMOVED FOR ANALYSIS.			2	H	7	4 	4T			RT	A20EA   					 
2001032700147	20010327	00147	NE  	2001	3	27	CA000809014      	2	20000728	G	7261	310573507	REGULATOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					OIL PRESSURE	LEAKING         	W				E	 	 	 	ENGINE SHUTDOWN         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  NR 2 ENGINE OIL PRESSURE WARNING LIGHT ILLUMINATED DURING THE CRUISE PHASE OF FLIGHT. NR 2 OIL PRESSURE DROPPED T	O BELOW 40 PSI.  ENGINE SHUT DOWN. OIL LEAK FOUND ON NR 2 ENGINE OIL PRESSURE REGULATOR VALVE, HOUSING ASSEMBLY. AT THE 	TEST POINT, PRESSURE REGULATOR ASSEMBLY REPLACED, GROUND RUNS COMPLETED SATISFACTORY.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700148	20010327	00148	EA  	2001	3	27	CA000810002      	1	20000807	G	3230	601R7520615	PRIORITY VALVE  			CNDAIR	CL600 	CL6002B19   	       	EA  										MLG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED DURING CRUISE: WHEN FOLLOWING THE QRH PROCEDURES FOR A MLG OVERHEAT FAIL MESSAGE . THE GE	AR DISAGREE WARNING MESSAGE ILLUMINATED. THE A/C COULD NOT CONTINUE THE FLIGHT WITH GEAR SELECTED DOWN DUE TO THE MLG OV	ERHEAT FAIL MESSAGE & THE ADDITIONAL FUEL REQUIREMENT. AIRCRAFT RETURNED TO THE DEPARTING AIRPORT & DECLARED EMERGENCY. 	MAINTENANCE REPLACED THE NOSE & MAIN LANDING GEAR PRIORITY VALVE. AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F			RT	A21EA   					 
2001032700149	20010327	00149	EA  	2001	3	27	CA000810003      	1	20000807	G	3260		PROXIMITY SWITCH			CNDAIR	CL600 	CL6002B19   	       	EA  										RT MLG	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE FLIGHT CREW REPORTED: ON DEPARTUE, THE GEAR DISAGREE WARNING MESSAGE IN ASSOCIATION WITH THE RIGHT GEAR SHOWIN	G RED. QRH PROCEDURE FOLLOWED AND AIRCRAFT RETURNED TO THE DEPARTING AIRPORT, EMERGENCY DECLARED, THE LANDING WAS UNEVEN	TFUL. MAINTENANCE FOUND LOOSE PROX TARGETON THE RIGHT MLG. TARGET RE-SECURED AND AIRCRAFT RETURNED TO SERVICE AFTER A GE	AR SWING.			2	L	7	2 	4F			RT	A21EA   					 
2001032700150	20010327	00150	EA  	2001	3	27	CA000810004      	1	20000807	G	3220		STRUT           			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) THE FLIGHT CREW REPORTED: GEAR UP DISAGREEMENT (NOSE) ON TAKEOFF. QRH PROCEDURE WERE COMPLIED WITH (PRECAUTIONARY 	LANDING). AIRCRAFT RETURNED TO DEPARTING AIRPORT. MAINTENANCE FOUND NOSE STRUT IMPROPERLY SERVICED (RE-SERVICED NOSE GEA	R STRUT ASSEMBLY) AND GEAR RETRACTION CARRIED OUT.				2	L	7	2 	4F			RT	A21EA   					 
2001032700151	20010327	00151	EA  	2001	3	27	CA000810005      	1	20000807	G	3320	BR95005	BALLAST         			CNDAIR	CL600 	CL6002B19   	       	EA  										CABIN	SHORTED         	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED: NOTICED BURNING SMELLL IN DURING FLIGHT. AIRCRAFT RETURNED TO DEPARTING AIRPORT.MAINTENA	NCE REPLACED BALLAST  AT CABIN SEAT LOCATION 3BC.					2	L	7	2 	4F			RT	A21EA   					 
2001032700152	20010327	00152	EA  	2001	3	27	CA000810006      	1	20000807	G	2910	AE2460210E0164	LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON INITIAL CLIMB, AFTER SELECTING THE LANDING GEAR UP, THE GEAR DISAGREE WARNING MESSAGE WAS POSTED ON EICAS. SHOR	TLY AFTER, HYD 3 LO PRESS CAUTION MESSAGE WAS POSTED. AIRCRAFT RETURNED TO DEPARTING AIRPORT. MAINTENANCE DISCOVERED THA	T THE HYDRAULIC HOSE ASSEMBLY CONNECTING TO THE NOSE GEAR SELECTOR VALVE WAS DAMAGE WHICH CAUSED THE FLUID LOSS. HOSE RE	PLACED AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F			RT	A21EA   					 
2001032700153	20010327	00153	EA  	2001	3	27	CA000810007      	1	20000807	G	3310	BC10059001	SOCKET          			CNDAIR	CL600 	CL6002B19   	       	EA  										GALLEY	SHORTED         	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) FLIGHT CREW REPORTED, NOTICED ELECTRIC SMOKE DURING FLIGHT. AIRCRAFT RETURNED TO DEPARTURE AIRPORT, NO EMERGENCY D	ECLARED. MAINTENANCE FOUND GALLEY LIGHT SOCKET SHORTED. SOCKET REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032700154	20010327	00154	EA  	2001	3	27	CA000810008      	1	20000806	G	3310	BR95005	BALLAST         			CNDAIR	CL600 	CL6002B19   	       	EA  										ROW 3BC	SHORTED         	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN)  THE FLIGHT CREW REPORTED: NOTICED BURNING SMELL IN AIRCRAFT DURING FLIGHT. AIRCRAFT RETURNED TO DEPARTURE AIRPORT	, NO EMERGENCY DECLARED. THE MAINTENANCE REPLACED THE BALLAST AT THE CABIN SEAT LOCATION 3BC.					2	L	7	2 	4F			RT	A21EA   					 
2001032700155	20010327	00155	EA  	2001	3	27	CA000810009      	1	20000806	G	7500	7062814460101	DUCT            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					14TH STAGE	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING A PERIOD OF 4 DAYS, THE CREW REPORTED NUMEROUS INDICATION OF RT JET OVHT FAIL, CAUTION MESSAGE AND RT JET P	IPE OVHT WARNING MESAGE. WHEN RETARDING THE THRUST AS PER QRH, THE MESSAGES WENT AWAY. THE PROBLEM WAS IDENTIFIED AS A 1	4TH STAGE DUCT LEAK IN THE PYLON. THE DUCT WAS CONFIRMED TO BE CRACKED (APPROX 2 INCHES LONG) ON THE CIRCUMFERENCE AT TH	E FLANGE OF ITS JOINT IN THE PYLON. THE DUCT  WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700156	20010327	00156	EA  	2001	3	27	CA000810010      	1	20000806	G	2742	70623	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										STABILIZER	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) BRIT AIR HAVE REPORTED A STABILIZER PIVOT BUSHING SEIZED AND BOTH STAB TRIM CHANNELS INOPERATIVE. THE MAINTENANCE 	REPLACED THE MCU  AND THE HSTA. ALSO ONE BUSHING, TWO BUSHINGS  AND ONE FITTING WERE REPLACED.AIRCRAFT RETURNED TO SERVI	CE.				2	L	7	2 	4F			RT	A21EA   					 
2001032700157	20010327	00157		2001	3	27	CA000810011      	4	20000808	G	3414		LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  										P3	LEAKING         	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) ABORTED TAKEOFF, NO AIRSPEED ON STANDBY AIRSPEED INDICATOR. MAINTENANCE PURGE P3 LINE AND PERFORMED LEAK TEST IAW 	AMM TASK 34-11-00-790-803.					2	L	7	2 	4F			RT	A21EA   					 
2001032700159	20010327	00159	SO  	2001	3	27	CA000810014      	2	20000725	G	8530	SA530830	PISTON PIN      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	ENGINE	CHIPPED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1659 	1659 							(CAN) ALUMINIUM CHIPS FOUND IN OIL FILTER.ALL CYLINDER REMOVED AND PISTON PIN NR 1, 2 AND 3 REPLACED (NR 4 WAS REPLACED 	AT 1171.4).					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000081600337	20000816	00337	EU  	2000	8	16	CA000810015      	1	20000720	G	6220	350A31190703	STARFLEX        		360A31000008	SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					M/R HEAD	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1407 			M447		LE43520E			(CAN) STAR FOUND CRACK IN YELLOW. P STAR FLEX REPLACED.						1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2000090800090	20000908	00090	SO  	2000	9	8	CA000810016      	1	20000727	G	8120	4066109020	TURBOCHARGER    	LYC         		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					RT ENGINE	SLUGGISH        	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				543  		L524661A					(CAN) TAKEOFF AT 43 HG - ON LEG RETURN TO HOME BASE.   FIRST POWER SETTING TO 40 HG - THROTTLE BACK - DID NOT RESPOND.  	SECOND POWER SETTING TO 35 HG - PILOT HAD TO PULL THROTTLE QUITE  FAR BACK AND THEN FORWARD TO SET POWER.  WASTEGATE, TH	ROTTLE LINKAGE CHECKED.  INSPECTION OF TURBO SHOW HEAVY RESIDUES OF GRAY SUIT ON COMPRESSOR HOUSING AND SOME ON EXHAUST 	IMPELLER.  REPLACED TURBOCHARGER.  EVIDENCE OF IMPROPER COOLING AFTER FLIGHT OR RUN-UP  .LATELY: DAMP, HEAVY HOT CLIMATE	.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000090800096	20000908	00096	EA  	2000	9	8	CA000810017      	1	20000810	G	2910		LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					HYD LINE	BURST           	W				A	 	 	 	UNSCHED LANDING         				J	S	K	WARNING INDICATION        	AFFECT SYSTEMS            	FLUID LOSS                	TO	TAKEOFF        	1			CA											(CAN) DESCRIPTION OF DEFECTS:  AIRCRAFT AFTER TAKEOFF AND ON CLAIM RECEIVED HYD 3 PRESS EICAS WARNING MESSAGE.  SYSTEM N	R 3 HAD NO PRESSURE.  AIRCRAFT DECLARED EMERGENCY LANDING AND EMERGENCY GEAR EXTENSION AND RETURN TO FIELD.  MAINTENANCE	 ACTIONS:  MAINTENANCE HAS FOUND A HYDRAULIC LINE BURST.  LINE WILL BE REPLACED WHEN PART IS GOING TO BE AVAILABLE AND A	IRCRAFT WILL BE SENT BACK TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000092800086	20000928	00086	EU  	2000	9	28	CA000811003      	1	20000714	G	6230	4619305032M	MAST            		3638001009  	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA			6061 	671  		1024					(CAN) EVENT:  DURING PILOT TRAINING OFF-LEVEL LANDING BEING CONDUCTED;  A/C LANDED ON SLOPE WITH RT SKID LOW.  PILOTS WE	RE CHECKING THEIR RESPECTIVE SIDES OF A/C AND A/C MOVED ON SLOPE.  PILOT APPLIED CYCLIC INPUT WHEN THE A/C SLIPPED.  WHE	N A/C LIFTED INTO HOVER,TRAINING PILOT NOTICED MAST MOMENT IND. LIGHT ON STEADY, AND A/C RETURNED TO BASE.  MAINT ACTION	:  MAINT MANUAL CHECKED FOR PROCEDURES WHEN MAST MOMENT LIMITS EXCEEDED.  MAIN ROTOR STUDS WERE CHECKED FOR LOSS OF TORQ	UE.  RESULTS OF TORQUE INSP REVEALED THAT ALL 12 NUTS HAD LESS THAN MIN 140 NEWTON METERS OF TORQUE 4 OF 12 NUTS MOVED A	PPROXIMATELY 1/4 OF FLAT TO BRING THEM UP TO TORQUE.	1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2000090800097	20000908	00097	SO  	2000	9	8	CA000811004      	2	20000720	G	8520	649133	CRANKSHAFT      	CONT        		CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	IO470D      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	FWD - NR 1 ROW	SEPARATED       	W				B	A	 	 	EMER. DESCENT           	UNSCHED LANDING         			E	T	Y	VIBRATION/BUFFET          	ENGINE CASE PENETRATION   	ENGINE STOPPAGE           	CR	CRUISE         	1			CA			3746 	82   		791680D					(CAN) AIRCRAFT WAS IN A  CRUISE ATTITUDE, IN PREPARATION TO DISEMBARK SKYDIVERS, WHEN PILOT NOTICED AN ENGINE VIBRATION 	FOLLOWED BY A BANG, ENGINE CAME TO A SUDDEN STOP.   AIRCRAFT LANDED AT AIRPORT OF DEPARTURE WITHOUT FURTHER INCIDENT.  U	PON INSPECTION, FOUND CRANKSHAFT HAD FAILED AND PUNCTURED THROUGH THE TOP OF THE CRANKCASE.  THIS AIRCRAFT ENGINE HAS BE	EN MODIFIED PER STA NR SA95-55 AND SE95-9.			1	H	7	1 	3O	3	O	NT	3A13    	3E1	5	C	P3EA	 
2000090800098	20000908	00098	NM  	2000	9	8	CA000824002      	1	20000818	G	2910	82970410119	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT NACELLE	FAILED          	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC PRESSURE LINE NR 1 SYSTEM WORN THROUGH 1/2 WALL THICK AT LOCATION  X124 LT NACELLE ABOVE EXHAUST.  LINE 	WORN BECAUSE ADEL CLAMPS BROKE ALONG SIDE MLG RETRACTION  ACTUATOR FITTER LOCATION AND RUBBED AGAINST LINE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001032700163	20010327	00163	EA  	2001	3	27	CA000824006      	2	20000815	G	8550	7581378	SEAL            		LW13904     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	RUPTURED        	W				E	C	 	 	ENGINE SHUTDOWN         	ABORTED TAKEOFF         			K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA			586  								(CAN) RT ENGINE OIL FILTER CONVERTER PLATE SEAL RUPTURED DURING TAKEOFF, CAUSING OIL LOSS ONTO HOT TUBOCHARGER AND EXHAU	ST COMPONENTS. THE FLIGHT CREW NOTED DECAYING OIL PRESSURE AND LOSS OF PROPELLER RPM CONTROL, AND INITIATED ENGINE IN-FL	IGHT SHUTDOWN. INVESTIGATION REVEALED AN APPARENT BREAK-DOWN OF THE BONDED RUBBER SEAL MATERIAL BETWEEN THE OIL FILTER C	ONVERTER-PLATE AND THE ENGINE CASE. THE SWELLED RUBBER INDICATED AN INCOMPATIBILITY WITH THE ENGINE OIL.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000090800099	20000908	00099	CE  	2000	9	8	CA000824010      	1	20000730	G	7820	04504003	MUFFLER         	CESSNA      	045040021   	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					BACK END	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				Y	 	 	ENGINE STOPPAGE           			CL	CLIMB          	1			CA			4623 								(CAN) AFTER TAKEOFF AND IN CLIMB-OUT, PILOT EXPERIENCED POWER LOSS (90 PERCENT).  PILOT RETURNED TO THE AIRPORT AND LAND	ED SAFELY.  ON ROLL OUT, ENGINE STOPPED COMPLETELY AND COULD NOT BE RESTARTED. INVESTIGATION FOUND THE REAR SECTION OF T	HE LEFT HAND EXHAUST MUFF WAS CRACKED LEAVING A HOLE ALLOWING HOT EXHAUST GASES TO ESCAPE INTO THE ENGINE COMPARTMENT.  	THE HOT GASES MELTED THE MAGNETO P-LEAD WIRES RUNNING ALONG THE FIREWALL.  BECAUSE THE P-LEADS WERE SHIELDED, THE OUTER 	GROUND SHIELDING MELTED AND CONTACTED THE INNER P-LEAD WIRE. THUS GROUNDING OUT THE MAGNETOS CAUSING THE ENGINE TO QUIT.	 THE MUFFLER WAS INSPECTED PER CF-90-13R2.	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001031500128	20010315	00128	EU  	2001	3	15	CA000824011      	1	20000728	G	3230		GEAR            			HWKSLY	DH1254	HS125400F   	230145 	EU  										LEVER	UNSECURE        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER MAINTENANCE, AIRCRAFT WAS DELIVERED TO CUSTOMER. ON DEPARTURE DURING INITIAL CLIMB, GEAR WAS SELECTED UP. CR	EW STATED GEAR APPEARED TO RETRACT (GREEN LIGHT OUT) BUT A WARNING LIGHT REMAINED ON RT GEAR. ATC REPORTED GEAR WAS NOT 	FULLY RETRACTED SO THE AIRCRAFT CANCELLED AND RETURNED. SEVERAL GEAR SWINGS WERE PERFORMED AND NOTHING FOUND. PRIOR TO F	LIGHT EMERGENCY HYDRAULIC LEVER HAD BEEN LIFTED TO DROP GEAR DOORS FOR WHEEL WELL INSPECTION BY CREW PRIOR TO FLIGHT. WE	 SUSPECT LEVER WAS NOT FULLY STOWED ALLOWING BYPASS OF HYDRAULIC PRESSURE AND PREVENTING THE FULL RETRACTION OF GEAR. AI	RCRAFT DEPARTED AGAIN AND GEAR FUNCTIONED NORMAL.	2	L	7	2 	3F			RT	A3EU    					 
2000100200137	20001002	00137		2000	10	2	CA000824013      	4	20000731	G	3460	TH2502FF	CONTROL BOX     			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					FM CNTRL HEAD	BURNED          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						2011					(CAN) PILOT REPORTED SMOKE IN THE COCKPIT AND LANDED.  INSPECTION FOUND THAT FM CONTROL HEAD WAS UNSERVICEABLE AND SMELL	ED BURNT.  SERVICEABLE FM CONTROL HEAD WAS INSTALLED AND TESTED WITHOUT RECURRENCE.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2000100200209	20001002	00209	CE  	2000	10	2	CA000824021      	1	20000604	G	5710	8178512	BOLT            	BEECH       		BEECH 	100   	B100        	1152919	CE  										UPPER FWD WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						BE131	BE131				(CAN) UPPER FORWARD WING - BOLT FOUND CRACKED DURING ROUTINE INSPECTION.						1	L	7	2 	4T			 	A14CE   					 
2000100200210	20001002	00210	NE  	2000	10	2	CA000824022      	2	20000618	G	8530	366249	CYLINDER        	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					ROCKER EAR	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				712  		4215119					(CAN) ROCKER EAR SEPARATION AT ROCKER PIN.						1	H	7	1 	3R	3	R	 	A815    	5E2				 
2000100200211	20001002	00211	CE  	2000	10	2	CA000824023      	1	20000623	G	2410	DOFF10300B	ALTERNATOR      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ALTERNATOR	FAILED          	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			CA											(CAN) UPON DESCENT, PILOT NOTICED AMP METER IN DISCHARGE POSITION. AFTER CHECKING BREAKERS, HE SWITCHED OFF MOST ELECTRI	CAL SWITCHES TO CONSERVE BATTERY POWER THROUGH LANDING.  INVESTIGATION REVEALED ALTERNATOR AND CONTROLLER NOT FUNCTIONIN	G.  BOTH PARTS REPLACED AND AIRCRAFT RETURNED TO SERVICE BY AME.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000100200212	20001002	00212	SO  	2000	10	2	CA000824024      	2	20000629	G	7414	X13964	MAGNETO         	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					RT MAGNETO	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA						1686209F					(CAN) WHILE TAXIING AFTER LANDING, PILOT TESTED MAG SWITCH TO DISCOVER DEAD RT MAGNETO.  INVESTIGATION BY AME DISCOVERED	 RT MAGNETO NOT WORKING.  PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000100200213	20001002	00213	CE  	2000	10	2	CA000824025      	1	20000725	G	8100	12502557	MOUNT BRACKET   	CESSNA      	12502557    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					RT LWR FIREWALL	BROKEN          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA											(CAN) PILOT NOTED SLIGHT ENGINE VIBRATION, ENGINE PARAMETERS NORMAL  .INVESTIGATION REVEALED EXHAUST SUPPORT MOUNT P/N 1	250255-7 BROKEN, ALSO DISCOVERED MUFFLER (P/N 1250251-13) HEAT SHIELD MOUNT CRACKED AT WELD.  EXHAUST SUPPORT MOUNT AND 	MUFFLER REPLACED, VIBRATION PROBLEM SOLVED.   AIRCRAFT OPERATES ON FLOATS, SUSPECT THAT MOUNT FAILED AND ALLOWING MUFFLE	R, TAILPIPE TO RESONATE, CAUSING MUFFLER TO CRACK.			1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001032700170	20010327	00170	CE  	2001	3	27	CA000824026      	1	20000705	G	7603	S110113	ROD END         			CESSNA	210   	210         	2073402	CE  	CONT  	O470  	IO470E      	17026	SO  	MCAULY	2A34C	D2A34C58    	GL  	THROTTLE	SEPARATED       	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LACK OF THROTTLE RESPONSE. THE AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND THROTTLE ROD END SEPARATED	 FROM BALL AT THROTTLE ARM ON THE FUEL CONTROL. A NEW ROD END					1	H	7	1 	3O	3	O	RT	3A21    	3E1	5	C	P3EA	 
2001032700171	20010327	00171	CE  	2001	3	27	CA000824027      	1	20000713	G	2921	MS287001	ACCUMULATOR     			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					HYD SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) 1 HOUR INTO RETURN LEG, MOTOR LIGHT STARTED TO ILLUMINATE MORE OFTEN, FINALLY RUNNING CONTINUOUSLY BEFORE 60 AMP B	REAKER IN FLOOR OPENED. PILOT PERFORMED NORMAL GEAR BLOW DOWN AND LANDED. - MAINTENANCE FOUND GEAR SYSTEM ACCUMULATION P	RESSURE LOW.- SYSTEM SERVICED AND RUN, RELEASED FOR FLIGHT. AGAIN FOUND SYSTEM LOW AFTER RETURN TO BASE. SYSTEM SERVICED	, AGAIN SAME PROBLEM. SWAPPED ACCUMULATOR WITH ANOTHER AIRCRAFT. BOTH ARE RUNNING FINE. HOLDING PRESSURE.			1	L	7	2 	4T	4	T	 	A14CE   	E2WE				 
2001032700173	20010327	00173	CE  	2001	3	27	CA000824029      	1	20000720	G	2510	56140593	SEAT            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7058 								(CAN) PILOTS SEAT SUPPORT LEFT/RIGHT CHANNELS CRACKED / BROKEN / MISSING PIECES. NEW LEFT / RIGHT SUPPORT CHANNELS FABRI	CATED  AND INSTALLED. FOUND DURING ROUTINE SCHEDULED INSPECTION.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000100200032	20001002	00032	SO  	2000	10	2	CA000824030      	1	20000728	G	3233		GROUND WIRE     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	TERMINAL END	BROKEN          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA			866  								(CAN) THIS AIRCRAFT SUFFERED A PARTIAL GEAR UP LANDING ON JUNE 19, 2000. TEMPORARY REPAIRS WERE MADE AND THE AIRCRAFT WA	S FERRIED TO CYEG FOR FURTHER INSPECTION AND REPAIR.  NECESSARY REPAIRS WERE MADE.  INSPECTION BEFORE FURTHER FLIGHT REV	EALED THAT THE STAKON TERMINAL END ON THE HYDRAULIC PUMP ELECTRIC MOTOR GROUND WIRE WAS CRIMPED OVER THE INSULATION WITH	 ONLY ONE OR TWO STRANDS OF WIRE MAKING CONTACT.  GROUND CONTACT COULD BE MADE OR BROKEN SIMPLY BY FLEXING THE WIRE AT T	HE STAKON TERMINAL END.  HIS COULD HAVE BEEN THE CAUSE OF THE UNDERCARRIAGE MALFUNCTION.  IT APPEARS TO BE ORIGINAL FACT	ORY INSTALLATION.	1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2001032700174	20010327	00174	EA  	2001	3	27	CA000824031      	1	20000728	G	2400		HOSE            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					HEATER	BURNED          	W				C		 	 	ABORTED TAKEOFF         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF RUN SMOKE STARTED COMING FROM UNDER INSTRUMENT PANEL. THE TAKEOFF WAS ABORTED PRIOR TO LIFT-OFF THE WAT	ER. MAINTENANCE FOUND THAT A SCAT HOSE IN THE HEATER SYSTEM FWD OF THE RT INSTRUMENT PANEL HAD MOVED REARWARD AND CONTAC	TED THE HOT BUS SIDE OF THE C/BS. CURRENT FOUND A GROUND THROUGH THE WIRE IN THE SCAT HOSE AND CAUSED ARICH SECTION OF T	HE SCAT HOSE TO BURN.THE EFFECT HOSE WAS REMOVED AND C/BS WITH PITTING ON THE HOT TERMINALS WERE REPLACED. ELECTRICAL SY	STEM WILL BE PROTECTED FROM ANY POSSIBLE REARWARD MOVEMENT OF SCAT HOSE WHEN HOSE IS REINSTALLED.		1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2000100200215	20001002	00215	NE  	2000	10	2	CA000828004      	2	20000714	G	8530	366249	VALVE           	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					EXHAUST VALVE	FRACTURED       	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA				1115 		P326010					(CAN) UPON REACHING DESTINATION, THE PILOT REDUCED POWER TO LAND.  UPON DOING SO, THE ENGINE STARTED TO BACKFIRE AND RUN	 ROUGH.  NORMAL LANDING PROCEDURES WERE CARRIED OUT FOR REDUCED POWER AND AIRCRAFT LANDED WITHOUT INCIDENT.  PRIOR TO TH	IS, THE ENGINE HAD NOT GIVEN ANY INDICATION OF ANY PROBLEMS.  UPON INVESTIGATION OF THE ENGINE, IT WAS NOTED THE EXHAUST	 VALVE IN THE NR 1 CYLINDER HAD BROKEN OFF AND HAD DAMAGED THE PISTON AND CYLINDER HEAD.  PARTS OF THE VALVE WERE ALSO F	OUND AT THE NR 5 AND NR 6 CYLINDERS INTAKE TUBES.  INTAKES NRS 4, 5, 6, AND 7 WERE CLEANED, ENGINE WAS INSPECTED FOR OTH	ER DAMAGE AND NR 1 CYLINDER CHANGED AND AIRCRAFT WAS RETURNED TO SERVICE.	1	H	7	1 	3R	3	R	 	A815    	E142				 
2000100200216	20001002	00216	NE  	2000	10	2	CA000828005      	2	20000727	G	8530	366249	CYLINDER        	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					BROKEN RINGS	WORN            	W				A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			CR	CRUISE         	1			CA				1138 		P326010					(CAN) AIRCRAFT DEPARTED, JUST AFTER TAKEOFF, THE PILOT NOTICED OIL ON THE WINDSHIELD.  AFTER CHECKING ENGINE INSTRUMENTS	, OIL TEMP NORMAL, OIL PRESSURE NORMAL.  CYLINDER HEAD TEMP 240 (OAT FOR THE DAY WAS ABOUT 30 DEGREES CELSIUS).  PILOT D	ECIDED TO CONTINUE THE FLIGHT TO MAIN BASE ABOUT 16 MILES AWAY.  ABOUT 8 MILES FROM BASE, THE OIL LEAK STARTED TO WORSEN	 AND ENGINE STARTED RUNNING ROUGH.  PILOT DECIDED TO LAND.  THE PLANE LANDED WITHOUT INCIDENT.  ON INVESTIGATION OF THE 	ENGINE, NR 9 PISTON DISCOVERED BROKEN AND MISSING 2 TOP RINGS WHICH CAUSED THE CASE TO PRESSURIZE AND BLOW OIL OUT THE N	OSE CASE.  NR 9  CYLINDER WAS CHANGED AND ENGINE INSPECTED FOR ANY OTHER DAMAGE.  AIRCRAFT WAS RETURNED TO SERVICE.	1	H	7	1 	3R	3	R	 	A815    	E142				 
2000100200217	20001002	00217	CE  	2000	10	2	CA000828006      	1	20000815	G	5300		SKIN            	BEECH       		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LEFT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13697			BB14					(CAN) FUSELAGE SKIN CRACK IN PRESSURE VESSEL LOCATED AT WING TO FUSELAGE FILLET MOUNTING SCREW HOLE (ANCHOR NUT) AT LEFT	 HAND WING LEADING EDGE (APPROX 1.25 INCHES LONG).					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001032700176	20010327	00176	CE  	2001	3	27	CA000828007      	1	20000804	G	7810		GASKET          			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	EXHAUST STACK	LEAKING         	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) CARBON MONOXIDE IN CABIN DUE TO LEAKING EXHAUST GASKETS						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2000100200218	20001002	00218	SO  	2000	10	2	CA000828008      	1	20000802	G	3230	452383	ROD END BEARING 	PIPER       	4194902     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					BEARING	SEIZED          	W				O	 	 	 	OTHER                   				J	R	 	WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CA											(CAN) PILOT REPORTED LEFTMAIN GEAR UNSAFE LIGHT WHEN GEAR WAS SELECTED DOWN.  GEAR HANDLE WAS PUT IN THE DOWN POSITION A	ND MASTER SWITCH SELECTED OFF TO MAINTAIN HYDRAULIC PRESSURE TO THE ACTUATOR, PREVENTING GEAR COLLAPSE.  MAINTENANCE FOU	ND THE DOWNLOCK LATCH NOT LOCKED.  THE ROD END BEARING ON THE DOWNLOCK ROD WAS SEIZED PREVENTING THE LATCH FROM ENGAGING	.  BEARING WAS REPLACED, SYSTEM CLEANED, GEAR SWING COMPLETED SUCCESSFULLY.  AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032700178	20010327	00178	NM  	2001	3	27	CA000829003      	1	20000731	G	2910		LINE            			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW120 	PW123       	 	NE  					HYD SYSTEM	FAILED          	W				D		 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AFTER PUSH BACK, AND AFTER START CHECKS COMPLETED (BOTH ENGINES IN FEATHER). WHEN PARK BRAKE RELEASED, AIRCRAFT MO	VED FORWARD DESPITE CAPTAINS & CO-PILOT FOOTBRAKES APPLIED, EMERGENCY/PARK BRAKE APPLIED GENTLY TO STOP AIRCRAFT. AIRCRA	FT THEN TOWED BACK TO STAND.ADDITIONAL INFO:ENGINEERS COMPLETED CHECKS & FOUND NO DEFECT WITH SYSTEM, ALL HYDRAULIC LEVE	LS CHECKED & FUNCTION OF SYSTEM PROVED SATISFACTORY.ONE WEEK PREVIOUS THE HYDRAULIC ISOLATION MOD WAS COMPLETED WITH VAR	IOUS HYDRAULIC PIPES REPLACED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700179	20010327	00179		2001	3	27	CA000829004      	4	20000731	G	2565		SLIDE           			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					LEFT	DEPLOYED        	W				O	 	 	 	OTHER                   				O		 	OTHER                     			CR	CRUISE         	1			CA											(CAN) CABIN CREW INFORMED. FLIGHT CREW F USUAL NOISE IN VICINITY OF ROW 11, SUSPECT, LEFT HAND DITCHING DAM DEPLYMENT, V	ISUALLY CONFIRMED BY THE CABIN CREW. FLIGHT CONTINUED TO DESTINATION AIRPORT AT REDUCED AIRSPEED 190 KTS. 26 MAY 2000 LE	FT HAND DITCHING DAM REPLOYED IN FLIGHT. AIRSPEED SLOWED TO 160 KTS & FLIGHT CONTINUED TO MANCHESTER.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700180	20010327	00180	NM  	2001	3	27	CA000829005      	1	20000802	G	3260		DOWNLOCK SENSOR 			DHAV  	DHC8  	DHC8*       	       	NM  										MLG	OUT OF RIG      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON FINAL APPROACH, FLT 650 AT APPROX 1830 HRS, FOLLOWING GEAR DOWN SELECTION, RT MLG UNSAFE INDICATION. GEAR CYCLE	D 2 TIMES, RT MLG STILL UNSAFE. ALTERNATE EXTENSION CARRIED OUT WITH SAME INDICATION. ALTERNATE DOWNLOCK INDICATION SHOW	ED THREE GREEN AFTER ALL GEAR DOWN SELECTIONS. AT APPOX. 17:15 HRS CET AN EMERGENCY LANDING WAS DECLARED AND THE AIRCRAF	T LANDED WITHOUT INCIDENT.NOTE: TROUBLESHOOTING BY TECHNICIANS FOUND PRIMARY DOWNLOCK SENSOR OUT OF RIG. TOO FAR INDICAT	ED ON PSEU. SENSOR RE-RIGGER AND PSEU CHECKED SERVICEABLE. CHECK / POSITIONING FLIGHT CARRIED OUT. NO FURTHER INCIDENTS.		2	H	7	2 	4T			RT	A13NM   					 
2001030600056	20010306	00056	NM  	2001	3	6	CA000829006      	1	20000802	G	2720	82710016003	SHAFT           			DHAV  	DHC8  	DHC8103     	1386005	NM  										RT RUDDER PEDAL	BROKEN          	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AFFECTED PART RUDDER PEDAL SHAFT ASSY (WELDED) P/N 8270016-003. DURING BRAKING FOR FULL STOP ON TARMAC, R/H RUDDER	 PEDAL ASSEMBLY P/N 82710016-003 FAILED ON CAPTAINS PEDALS. INSPECTION REVEALED A BROKEN ARM ON THE RUDDER PEDAL SHAFT A	SSY. DETAIL ISPECTION  SHOWED THAT A CRACK IN THE WELD HAD PROPAGATED UNTIL TOTAL SEPARATION OF THE ARM FROM THE SHAFT. 	A PART OF THE WELD INDICATED THAT THIS CRACK STARTED A LONG TIME AGO SINCE HALF OF THE CRACK SURFACE LENGTH HAD EVIDENCE	 OF RUST. WE HAVE INITIATED A ONE TIME BORESCOPE INSPECTION ON ALL OUR A/C, WHICH WE EXPECT TO COMPLETE WITHIN AUGUST 10	. THIS ALSO IS REPORTED TO THE NORWEGIAN CAA. KARE PEDERSON (DIRECTOR ENG. DEPT.)	2	H	7	2 	4T			RT	A13NM   					 
2001011105313	20010111	05313	NM  	2001	1	11	CA000829007      	1	20000802	G	2730	MS276434	BEARING         			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					RT ELEVATOR	WORN            	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH INTO BRISTOL PILOT REPORTED LOOSE & FLOPPY ELEVATOR CONTROL.NOTE: ELEVATOR TENSION CARRIED OUT AND RIG	 CHECK. INSPECTION OF ELEVATORS REVEALED INPUT LEVER BEARINGS WORN. BEARINGS REPLACED AND FUNCTIONS COMPLETED SATISFACTO	RY.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030600057	20010306	00057	NM  	2001	3	6	CA000829008      	1	20000802	G	5610	85C0043012	WINDSHIELD      			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					COCKPIT	FAILED          	W				B		 	 	EMER. DESCENT           				O			OTHER                     			CL	CLIMB          	1			CA						963439H4741					(CAN) BW1A AIRCRAFT MSN-489, LANDED WITH THE FIRST OFFICERS WINDSHIELD SHATTERED. INFORMATION FROM JOURNEY LOG: CLIMBING	 OUT OF 17,500 FT, RIGHT WINDSHIELD (OUTER GLASS) SHATTERED WITH LOUD BANG. AIRCRAFT WAS DESCENDED TO 10,000 PLUS PROCED	URES CARRIED OUT. AT TIME OF DAMAGE, WX WAS GOOD, CABIN DIFF.5.O, NO ABNORMAL INDICATIONS. MC VERBALLY REPORTED THAT CRE	W DECLARED AN EMERGENCY LANDING.FSR WAS CALLED TO ASSIST IN REPLACEMENT OF WINDSCREEN. THE FIRST OFFICERS WINDSHIELD SHO	WS FOD DAMAGE IN THE FORM OF A CHIP IN THE WINDSHIELD. SUSPECT PRESSURIZATION AND W/S CYCLING CAUSED W/S TO SHATTER.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030600058	20010306	00058	NE  	2001	3	6	CA000829009      	2	20000804	G	7310	3036484	FUEL LINE       	PWA         	PWC123      	DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					NR 2 ENGINE	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA						PCEAR0014					(CAN) FSR WAS CALLED INTO ASSIST. BW1A MAINTENANCE CONTROL ON AOG WITH AIRCRAFT 9Y-WIN, WITH A LEAKING FUEL LINE ON THE 	NR2 ENGINE. THE AIRCRAFT WAS IN BARBADOS WITH NO PARTS. PRELIMINARY REPORTS WAS THE LINE FROM THE FUEL COOLED OIL COOLER	 HAS PIN HOLE, LEAKING FUEL ON GROUND. (REFERENCE PWC IPC 72-01-40 FIG 3, PG2 ITEM 80.)REPLACEMENT. LINE WAS LOANED TO B	W1A FROM ALM, THE LINE INSTALED AND WIRE HARNESS CORRECTLY RE-INSTALLED, ADEL CLAMPS WERE ADJUSTED BY MAINTENANCE IN BGI	.INVESTIGATION BY FSR, SHOWS A PIN HOLE WHICH LOOKS LIKE IT WAS CAUSED BY ARCING OR THE WIRE HARNESS ON THE FUEL LINE EX	ITING THE FUEL COOLED OIL COVER TO THE FLOW DIVIDER. CAW:SB BEING DEVELOPED - CF AD PENDING SEPT 2000.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030600059	20010306	00059	NM  	2001	3	6	CA000829010      	1	20000803	G	5753	6521630188	SKIN            			BOEING	727   	72722C      	138400F	NM  	PWA   	JT8   	JT8D7B      	52053	NE  	ALLSN	A6441	A6441FN606  	GL  	RT FORE FLAP	SEPARATED       	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA						BN62					(CAN) CREW REPORTED ABNORMAL AILERON CORRECTION REQUIRED AT FLAPS 15 OR GREATER INBOUND TO YQM. ON INSPECTION IT WAS FOU	ND THAT THE RIGHT HAND FORWARD INBD FORE FLAP HAD SPLIT OPEN AT THE SPAR. THE FLAP WAS REPLACED AND AIRCRAFT RELEASED. U	PON INSPECTION OF FLAP IN SHOP, IT WOULD APPEAR THAT THE AFT HONEYCOMB SECTION HAS SEPARATED FROM THE SPAR DUE TO DISBON	DING OF THE JOINT. FURTHER INVESTIGATION REVEALS THAT THE SPAR WAS NOT PROTECTED BY PRIMER AND THE BONDING WAS SPORADIC 	PERHAPS ONLY 20-30% OF THE WHOLE LENGTH OF THE FLAP.		2	L	7	3 	4F	4	F	 	A3WE    	E2EA	6	C	P898	 
2001030600060	20010306	00060	CE  	2001	3	6	CA000829011      	1	20000810	G	3230	404188446	DRAG BRACE      			BEECH 	18    	E18S9700    	1151008	CE  	PWA   	R985  	R985AN14B   	52008	NE  					LT MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13781								(CAN) DURING ROUTINE 100 HOUR INSPECTION OF AIRCRAFT THE L/H MAIN GEAR DRAG BRACE WAS FOUND TO BE CRACKED PERPENDICULAR 	TO THE TUBE JUST ABOVE THE LOWER ATTACH POINT, ACROSS THE WELD. THE DRAG BRACE WAS REMOVED AND A SERVICEABLE UNIT WAS IN	STALLED WITH MULTIPLE GEAR SWINGS PERFORMED. SERVICEABLE.				1	L	7	2 	3R	3	R	 	A765    	5E1				 
2001030600061	20010306	00061	SW  	2001	3	6	CA000829012      	1	20000721	G	5753	21583	MOUNT           	BBAVIA      	8GCBC       	BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					LT FLAP	CRACKED         	W				K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			DE	DESCENT        	1			CA			2334 			27278					(CAN) PILOT REPORTED A TENDENCY FOR A/C TO ROLL TO RIGHT, ON FULL FLAP SELECTION. VISUAL INSPECTION INDICATED L/H INBOAR	D FLAP MOUNT HAD CONSIDERABLE VERTICAL MOVEMENT. FURTHER INSPECTION REVEALED THAT INBOARD FLAP MOUNT LOWER ATTACHMENT PO	INT HAD BROKEN FREE.				1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2001011105326	20010111	05326	EA  	2001	1	11	CA000829013      	1	20000817	G	3244	256K433	TIRE            		6008512315R 	CNDAIR	CL601 	CL6012A12   	1900303	EA  										MLG	BULGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AVG82470					(CAN) TIRE HAS BULGES ON RADIUS OF TIRE. THE TREAD IS DELAMINATING AND LETTING AIR COLLECT BETWEEN LAYERS CAUSING BULGES	 AND SOFT SPOTS.					2	L	7	2 	4F			RT	A21AE   					 
2001030100076	20010301	00076	CE  	2001	3	1	CA000829014      	1	20000808	G	5520	1156200219	HINGE           	BEECH       		BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19788			B8					(CAN) DURING PRE-FLIGHT INSPECTION GROUND CREW HEARD A NOISE WHEN ELEVATOR MOVED, INVESTIGATION REVEALED R/H OUTBOARD HI	NGE BROKEN AT INSIDE STABILIZER. AIRCRAFT GROUNDED. HINGE REPLACED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001030600062	20010306	00062	EA  	2001	3	6	CA000829015      	1	20000817	G	2700	7X19	CONTROL CABLE   		C3CF1975R   	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					FLIGHT CONTROLS	FRAYED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			302  								(CAN) WHILST CARRYING OUT AN 800 HOUR INSPECTION OF THE AIRCRAFT, SEVERAL CABLES WERE FOUND THAT HAD A QUANTITY OF BROKE	N STRANDS BEYOND THE ALLOWABLE LIMITS. THIS IS ONE OF TH CABLES THAT WAS FOUND. IT SHOULD BE NOTED THAT THE AIRCRAFT MAN	UAL STATES THAT THE CABLES MUST BE INSPECTED THROUGHOUT THEIR ENTIRE LENGTH. IN ORDER FOR THIS TO BE ACCOMPLISHED, THE C	ABLES MUST BE REMOVED FROM THE AIRCRAFT. IT SHOULD BE NOTED THAT THESE DEFECTIVE CABLES WOULD NOT HAVE BEEN FOUND BY INS	PECTING THE CABLES WHILE STILL INSTALLED ON THE AIRCRAFT.		1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001030600063	20010306	00063	EA  	2001	3	6	CA000829016      	1	20000817	G	2700	7X19	CONTROL CABLE   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					FLIGHT CONTROLS	FRAYED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILST P/N C3CF195-7 AND P/N C3CF199-5. WHILST CARRYING OUT AN 800 HOUR INSPECTION OF THE AIRCRAFT, SEVERAL CABLES	 WERE FOUND THAT HAD A QUANTITY OF BROKEN STRANDS BEYOND THE ALLOWABLE LIMITS. THESE ARE TWO OF THE CABLES. IT SHOULD BE	 NOTED THAT THE AIRCRAFT MANUAL STATES THAT THE CABLES MUST BE INSPECTD THROUGHOUT THEIR ENTIRE LENGTH. IN ORDER FOR THI	S TO BE ACCOMPLISHED, THE CABLES MUST BE REMOVED FROM THE AIRCRAFT. IT SHOULD BE NOTED THAT THESE DEFECTIVE CABLES WOULD	 NOT HAVE BEEN FOUND BY INSPECTING THE CABLES WHILE STILL INSTALLED ON THE AIRCRAFT.		1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001030600064	20010306	00064	EA  	2001	3	6	CA000829017      	1	20000817	G	2700	7X19	CONTROL CABLE   		C3CF1935    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					FLIGHT CONTROLS	FRAYED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILST CARRYING OUT AN 800 HOUR INSPECTION OF THE AIRCRAFT, SEVERAL CABLES WERE FOUND WHICH HAD A QUANTITY OF BROK	EN STRANDS BEYOND THE ALLOWABLE LIMITS. THIS IS ONE OF THE CABLES THAT WAS FOUND. IT SHOULD BE NOTED THAT THE AIRCRAFT M	ANUAL STATES THAT THE CABLES MUST BE INSPECTED THROUGHOUT THEIR ENTIRE LENGTH. IN ORDER FOR THIS TO BE ACCOMPLISHED, THE	 CABLES MUST BE REMOVED FROM THE AIRCRAFT. IT SHOULD BE NOTED THAT THESE DEFECTIVE CABLES WOULD NOT HAVE BEEN FOUND BY I	NSPECTING THE CABLES WHILE STILL INSTALLED ON THE AIRCRAFT.		1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001030600065	20010306	00065	EA  	2001	3	6	CA000829018      	1	20000820	G	2700		SCREW           		C3TE1213    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					SERVO TAB	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOT AN SDR - WHILST CARRYING OUT A 100 HOUR INSPECTION, THE ENGINEER NOTICED THAT THE SCREWS ATTACHING THE COUNTER	WEIGHT ARM TO THE SERVO TAB WERE LOOSE. THE TRIM TAB WAS OPENED UP, THE SCREWS WERE TIGHTENED, THE TAB WAS CLOSED UP AND	 THE AIRCRAFT WAS RETURNED TO SERVICE.				1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001030600066	20010306	00066	EA  	2001	3	6	CA000829019      	1	20000820	G	2731		ROD END         	DHAV        	C3CF4195    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					ELEVATOR TAB	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN CARRYING OUT A 100 HOUR INSPECTION, THE ENGINEER NOTICED THAT THE ROD END BEARING ON THE ELEVATOR TRIM TAB RO	D LOOKED UNUSUAL. UPON FURTHER INVETIGATION, THE ENGINEER NOTED THAT IT WAS UNLIKE ANY OTHER HE HAD EVER SEEN!THE PART O	F UNKNOWN ORIGIN WAS REPLACED WITH THE PROPER ROD END - P/N M34-14.				1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001030200062	20010302	00062	WP  	2001	3	2	CA000830010      	1	20000731	G	3244	32700821	TIRE            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					LT MLG	BLOWN           	W				C				ABORTED TAKEOFF         				C	Y		F.O.D.                    	ENGINE STOPPAGE           		TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT REJECTED TAKEOFF DUE TO LT ENGINE POWER LOSS (125-130 KNOTS). NR 2 MAIN TIRE BLOWN, TIRE SEPARATION, DEBR	IS OF TIRE FLEW INTO LT ENGINE CAUSING DAMAGE, THE DEBRIS ALSO DAMAGED THE LT INBOARD FLAP. REPLACED ALL FOUR MAIN TIRE 	AND FOUR MAIN BRAKES. REPAIR FLAP AS PER ENGINEERING PRODUCTION PERMIT 7-57-50/351-57-854.REPLACED LT FAN BLADES AND HUB	, LEAK AND OPERATIONAL CHECK CARRIED OUT (VIB CHECK, CONDITIONAL CHECKS) ALL CHECKS FOUND SATISFACTORY.NOTE: GOODYEAR WA	S ADVISE.		2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001030700657	20010307	00657	NM  	2001	3	7	CA000830011      	1	20000716	G	2121	732591A	FAN             			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					E&E BAY	FAILED          	W				K	 	 	 	NONE                    				B	J	 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) SMOKE IN COCKPIT IN FLIGHT WHILE EXITING AN INBOUND HOLD. AFTER INVESTIGATION, AN AFTER SMOKE DISSIPATED AN EICAS 	(ENGINE INDICATION AND CREW ALERT SYSTEM) MESSAGE APPEARED FOR A TRIPPED OFF LINEOF THE FORWARD ELECTRICAL SUPPLY FAN. R	EPLACED AIR COOLING FAN AND REPLACED ELECTRICAL/ELECTRONICS EQUIPMENT COOLING SYSTEM 9 INCH DIAMETER AIR CHECK VALVE THA	T WAS FOUND BROKEN. FAN SYSTEM OPERATIONAL AND MESSAGE CLEARED.			2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030700658	20010307	00658	NM  	2001	3	7	CA000830012      	1	20000727	G	2920	729550014	CAP             			BOEING	767   	767275      	1385155	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					RAM AIR TURBINE	SHEARED         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) CENTRE HYDRAULIC QUANTITY WENT TO 0 AFTER FLAP SELECTION 1, ON FINAL APPROACH. QRH APPLIED, AIRCRAFT LANDED SAFELY	. AFTER INVESTIGATION, FOUND TH RAT CHECK OUT MODULE (RAM AIR TURBINE) CHECK VALVE CAP SHEARED (CAP COMPLETELY SEPARATED	 FROM THE REST OF THE HOUSING).REPLACED RAT UNIT CHECK OUT MODULE, AS PER BOEING TASK 29-21-11-004-042 OPERATIONAL CHECK	 CARRIED OUT, FOUND SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030700659	20010307	00659	CE  	2001	3	7	CA000830015      	1	20000804	G	5730		RIVET           	BEECH       	96110005703 	BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520CB     	17032	SO  					WING	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8386 			TE1197					(CAN) DURING SCHEDULED MAINTENANCE ON THE AIRCRAFT WE HAVE FOUND LOOSE RIVETS ON THE WING SKIN LOWER MAIN PANEL AFT OF T	HE SPAR AT WING STA 70-00 TO STA 76-00. AFTER A CONTACT WITH A TECH REP AT BEECH AIRCRAFT, WE HAVE REPLACED THE LOOSE RI	VETS WITH STANDARD MS20470AD-5 SOLID RIVETS DIPPED IN WET ZINCHROMATE PRIMER AS REQUIRED IN BEECH REPAIRS MANUAL AND REC	OMMENDED BY BEECH TECH REP.			1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001030700660	20010307	00660	NM  	2001	3	7	CA000830016      	1	20000807	G	5230		DOOR SEAL       			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					CARGO DOOR	OBSTRUCTED      	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) AIRCRAFT RETURNED TO BASE AFTER NOT BEING ABLE TO MAINTAIN CABIN PRESSURIZATION ABOVE 23,000 FEET,. DURING GRD PRE	SSURIZATION CHECK FOUND HEAVY AIR LEAK FROM L/H PRSOV AND C1 CARGO. C1 CARGO FOUND NET OVER CARGO DOOR SEAL, NET REPOSIT	IONED. PRSOV LOCKED IN THE CLOSED POSITION PER MEL 21-31-00. GROUND PRESSURIZATION TEST ACCOMPLISHED IN ACCORDANCE WITH 	AMM 21-31-00, AIRCRAFT RELEASED.			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001030700661	20010307	00661	NM  	2001	3	7	CA000830017      	1	20000805	G	7830	52754031	CABLE           	RROYCE      	RB211535E4  	BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					THRUST REVERSER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			CA						30739					(CAN) LOG BOOK DEFECT REPORTED BY FLIGHT CREW ON ARRIVAL . NR2 ENGINE THROTTLE BINDING. FOUND THRUST REVERSER FEEDBACK P	USH PULL CABLE DAMAGED CAUSING THE T/R FEEDBACK CAM TO BEND. FORWARD THRUST FEED AND SENSE C/O, NO FAULT FOUND, T/R LOCK	ED OUT AS PER MEL.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001030200065	20010302	00065	EA  	2001	3	2	CA000830018      	1	20000801	G	2913	NAS1611008	PACKING         	VICKERS     	PV304448    	CNDAIR	CL600 	CL6002B19   	       	EA  										HYDRAULIC PUMP	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA						MX590791A					(CAN) CREW REPORTED HYDRAULIC LEVEL SYSTEM NR1 AT 30% AT TOP OF CLIMB. DROPPED TO 25% 3 MINUTES LATER. MAINTENANCE FOUND	 LEAK FROM HYDRAULIC PUMP. THEY REPLACED THE PACKING.					2	L	7	2 	4F			RT	A21EA   					 
2001030200066	20010302	00066	NE  	2001	3	2	CA000830019      	2	20000815	G	7200		ENGINE          	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, WITH TAKEOFF POWER APPLIED, THE CREW HEARD A LOUD BANG. AFTER THE NOISE, THE LT ENGINE ITT & N2 WEN	T INTO THE RED. PILOT SET ENGINE TO IDLE AND OPERATION WAS NORMAL AT IDLE. PILOTS WERE THEN UNABLE TO INCREASE THRUST, E	NGINE WOULD NOT RESPOND TO THROTTLE SETTING. THE MDC REVEALED AN ITT OF 1147 DEGREES C FOR 7.4 SECONDS AND N2 OF 102.5% 	FOR 2.3 SECONDS.  THE LT ENGINE HAS BEEN REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030700664	20010307	00664	EA  	2001	3	7	CA000830020      	1	20000815	G	2760		PCU             			CNDAIR	CL600 	CL6002B19   	       	EA  										SPOILER SYSTEM	OUT OF RIG      	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ABORTED TAKEOFF AT ABOUT 135 KTS DUE TO A CONFIG SPOILER WARNING MESSAGE. ON ALL FOUR BRAKES, NOT MORE THAN 5 UNIT	S INDICATED.THE SECU #1 WAS REPLACED AND THE NEXT DAY AFTER THE REOCCURRENCE OF THE SAME PROBLEM, THE R/H INBOARD SPOILE	RON PCU WAS RERIGGED.				2	L	7	2 	4F			RT	A21EA   					 
2001030700665	20010307	00665	EA  	2001	3	7	CA000830021      	1	20000815	G	3234	750006000	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			652  								(CAN) AFTER TAKEOFF, THE GEAR DID NOT COME UP AFTER SELECTION.NOSE LANDING GEAR SELECTOR VALVE REPLACED DUE OF EVIDENCE 	OF A LEAK.					2	L	7	2 	4F			RT	A21EA   					 
2001030200067	20010302	00067	EA  	2001	3	2	CA000830022      	1	20000801	G	4900		APU             			CNDAIR	CL600 	CL6002B19   	       	EA  										APU	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE SMOKE TOILET CAUTION MESSAGE DISPLAYED DURING FLIGHT, ACCOMPANIED WITH SMOKE ODOR AND HAZE IN THE CABIN.INITIA	L REPORT FOUND NO DISCREPANCY, SECOND REPORT RESULTED INTO AN APU REPLACEMENT.					2	L	7	2 	4F			RT	A21EA   					 
2001030200068	20010302	00068	EA  	2001	3	2	CA000830023      	1	20000815	G	4900	38004883	APU             			CNDAIR	CL600 	CL6002B19   	       	EA  										APU BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA						P177					(CAN) THE FLIGHT CREW REPORTED THE SMOKE JUST PRIOR TO LANDING, SMOKE ODOR DETECTED, WHEN THE AIR CONDITIONING PACKS WER	E TRANSFERRED FROM THE ENGINE TO THE APU PROCEEDED TO DESTINATION AIRPORT (CVG) DECLARED EMERGENCY. THE APU WAS REPLACED	.				2	L	7	2 	4F			RT	A21EA   					 
2001030700666	20010307	00666		2001	3	7	CA000830024      	4	20000801	G	3418	45150340	VANE            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT AOA	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE FLIGHT CREW ABORTED THE TAKEOFF WHEN THE STALL FAIL CAUTION MESSAGE APPEARED AT 70 TO 80 KNOTS. (ABORTED T/O).	THE LEFT AOA VANE WAS REPLACED AND THE AIRCRAFT RETURNED IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030700667	20010307	00667	EA  	2001	3	7	CA000830025      	1	20000823	G	5210		HANDLE          	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	OUT OF RIG      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						7127					(CAN) MAIN PAX DOOR HANDLE WAS STUCK. DOOR WILL NOT OPEN FROM INSIDE OR OUTSIDE.PAX DOOR RIGGED AS PER AMM 52-11-02-820-	801 AND SL 52-010.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030200069	20010302	00069	NE  	2001	3	2	CA000830026      	2	20000821	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	MALFUNCTIONED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE RIGHT ENGINE OIL PRESSURE WAS FLUCTUATING RAPIDLY 55-42 PSI. THE PILOT DECLARED EMERGENCY, THE 	LANDING WAS UNEVENTFUL. MAINTENANCE CONTROL REPLACED THE RT ENGINE (THE EXACT CAUSE IS NOT KNOWN) (S/N OFF: 807100/S/N O	N: 807432).				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030700668	20010307	00668	EA  	2001	3	7	CA000830027      	1	20000821	G	3231	555405	SELECTOR VALVE  			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG DOOR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, WHEN SELECTING THE LANDING GEAR UP, THE NOSE DOOR OPEN WARNING APPEARED. MAINTENANCE REPLACED THE N	OSE GEAR DOOR SELECTOR VALVE (P/N:55540-5, S/N OFF: 1131/S/N ON: 1197) AND THE PROX. SENSOR P/N: 8-648-07 & P/N: 8-648-0	8.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030200070	20010302	00070	EA  	2001	3	2	CA000830028      	1	20000820	G	5610	1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA						00036H9096					(CAN) DURING FLIGHT THE RT WINDSHIELD MIDDLE PLY CRACKS. THE AIRCRAFT LANDED WITHOUT ANY FURTHER COMPLICATION.						2	L	7	2 	4F			RT	A21EA   					 
2001030200071	20010302	00071	EA  	2001	3	2	CA000830029      	1	20000820	G	2710	6224404101	AILERON         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	JAMMED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA						459					(CAN) THE FLIGHT CREW REPORTED AFTER TAKEOFF THE RIGHT AILERON APPEARS TO BE JAMMED. ON DESCENT, THE AILERON CAME UN-JAM	MED AND APPEARED TO BE NORMAL.AILERON SERVO REPLACED AS PRE-CAUTIONARY MEASURE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030700669	20010307	00669	EA  	2001	3	7	CA000830030      	1	20000811	G	3234	601R509677	CONTROL HANDLE  			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA			652  			0018A					(CAN) AFTER TAKEOFF, UPON A GEAR RETRACTION, THE LANDING GEAR HANDLES SHAFT BROKE. AIRCRAFT RETURNED TO BASE AND LANDED 	SUCCESSFULLY.					2	L	7	2 	4F			RT	A21EA   					 
2000101200172	20001012	00172	SO  	2000	10	12	CA000830032      	2	20000805	G	8530	TCK654970K	CYLINDER        			CESSNA	172   	172         	2072402	CE  	CONT  	O360  	IO360K      	17025	SO  					FRT RT NR 5 POS	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				1030 		355597					(CAN) AMERICAN PRIVATE OWNED AIRCRAFT TOURING GASPE REGN.  TAKEOFF FROM STE .ANNE DES MONTS.  20 MILES OUT-WEST, ENGINE 	WENT ROUGH AND RISE IN CHT.  DATE:  25 JUL 2000.  TIME:  02 HR.25.  PILOT PURCHED GPS INDICATING STE.ANNE AS NEAREST AIR	PORT AND ADVISED FSSYZV (SERT-ILES) OF PROBLEM.  NR 5 CYLINDER HEAD BROKEN OFF AT BOTH ROCKER HOUSING.  NOTE: PILOT HAD 	STOPPED ON WAY IN, AT GRANDFALLS, NB WITH OIL LEAK, ASSUMED TO BE FROM ROCKER COVER.  RESEALED.  BROKEN PORTION OF CYLIN	DER INDICATE PREVIOUS CRACKS.  NOTE:  A/C HAD LAST MONTH FLOWN WITH COWL PLUGS ON FOR 50 MILES. (X)		1	H	7	1 	3O	3	O	NT	3A12    	E1CE				 
2001030700671	20010307	00671	SO  	2001	3	7	CA000830034      	2	20000801	G	8530	633106	LIFTER          	CONT        	TSIO360GB   	MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					NR 6 CYLINDER	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			1752 			309457					(CAN) ENGINE KNOCKING IN FLIGHT. AIRCRAFT LANDED. VALVE ROCKER SHAFT STUDS FOUND BROKEN NR6 EXHAUST. PUSH ROD FOUND DAMA	GED ON EXHAUST SIDE. INTAKE PUSH ROD ALSO FOUND DAMAGED. CYLINDER REMOVED FOR INSPECTION & REPAIR. INTAKE LIFTER FOUND D	AMAGED BUT COMPLETE. EXHAUST LIFTER FOUND DAMAGED AND MISSING SPRING.CYLINDER REPAIRED BY ENGINE SHOP., PUSH ROD REPLACE	D, LIFTERS REPLACED AND RUN-UP CARRIED OUT.CYLINDER NR6 TTSN: 80:55 HOURS; CYLINDER NR6 WAS INSTALLED NEW AT AFTT:1671 H	OURS.		1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2001030700672	20010307	00672		2001	3	7	CA000830035      	4	20000608	G	3416	GH3000	ALTIMETER       			CNDAIR	CL601 	CL6013A     	8070802	EA  										INSTRUMENT PNL	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS UNIT WAS INSTALLED AS PART OF LSTC Q-LSA-5020. ITEM REPORTED BY OPERATOR, RDAF (DANISH AIRFORCE). NO FURTHER 	DETAILS SUPPLIED. INFORMATION ON THIS UNSERVICEABILITY WAS RECEIVED ON 8 JUNE 2000 FROM OUR PROGRAMS DIVISION AS A RESUL	T OF A WARRANTY CLAIM BY RDAF WITH EQUIPMENT VENDOR. SINCE THE A/C IS REGISTERED AND OPERATED BY A NON-CIVIL OPERATOR (R	DAF), WE BELIEVED IT DID NOT REQUIRE AN SDR TO TC UNTIL WE QUESTIONED TC AND WERE ADVISED 4 AUG 2000 THAT IT SHOULD BE R	EPORTED.THE EQUIPMENT VENDOR (GOODRICH) ADVISED THEY COULD NOT REPRODUCE FAULT AND THEY BELIEVED A SOFTWARE UPGRADE MAY 	SOLVE PROBLEM. WE ARE UNAWARE WHAT HAS HAPPENED SINCE.	2	L	7	2 	4F			RT	A21EA   					 
2001030700673	20010307	00673	NM  	2001	3	7	CA000830036      	1	20000727	G	2910	65468581103	HYDRAULIC LINE  			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT ENGINE	RUPTURED        	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) LOSS OF HYDRAULIC FLUID DURING DESCENT AND LANDING.  NR2 ENGINE THRUST REVERSER PRESSURE LINE WAS FOUND RUPTURED I	N PYLON UNDER A SUPPORT CLAMP.HYDRAULIC PUMP AND FILTER WERE CHECKED FOR CONTAMINATION AND FOUND SERVICEABLE. HYDRAULIC 	LINE REPLACED AS PER M.M. CAMPAIGN ON FLEET CARRIED OUT AND AN REPETITIVE INSPECTION AT 2B CHECK IS  ESTABLISHED.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030700676	20010307	00676	NM  	2001	3	7	CA000830040      	1	20000809	G	2410		CONNECTOR       			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CSD	CONTAMINATED    	W				D	 	 	 	RETURN TO BLOCK         				N	 	 	FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) NR1 CSD IN TEMP ROSE TOWARDS 160 DEGREES WITH POWERED UP TO 80% TAKEOFF.  FOUND MAIN CONNECTOR AT RIGHT SIDE OF CS	D CONTAMINATED WITH OIL. THE CONNECTOR WAS CLEANED AND ENGINE GROUND RUN CARRIED OUT. SYSTEM CHECK SERVICEABLE. NO FUTHE	R ABNORMALITIES REPORTED.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030200072	20010302	00072	GL  	2001	3	2	CA000830042      	3	20000724	G	6114		HUB             	MCAULY      	D2A34C58    	CESSNA	206   	U206D       	2073342	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1269 	533  		797406					(CAN) CRACK IN RETENTION THREAD. SEE MCCAULEY SB # 205B						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2001030200074	20010302	00074	SW  	2001	3	2	CA000830044      	1	20000808	G	2911	EA1563	ACCUMULATOR     	OZONE       		GULSTM	690TP 	695A        	7630519	SW  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R306	R306382F7   	GL  	HYDRAULIC SYSTEM	FAILED          	W				A	D			UNSCHED LANDING         	RETURN TO BLOCK         			O			OTHER                     			DE	DESCENT        	1			CA				3    		041200X					(CAN) 1.A/C JUST COMPLETED ROUTINE 100 HR PERIODIC INSP. 2. HYDRAULIC ACCUMULATOR REGULATOR ASSY REPL, DUE TO LEAKING AC	CUMULATOR (INTERNAL). IT WOULD NOT STORE FLUID PRESSURE: O HR T.S.O. PART INST FUNCTION TESTS & P OST INSP CHECK FLT CAR	RIED OUT NO FAULT FOUND. 3. ON ROUTINE FLT TO BANGOR CREW SELECTED GEAR DOWN, HYDRAULIC SYS PRESSUE DROPPED TO ZERO. GEA	R EMERG EXTENSION PROCS WERE APPLIED, GEAR LOCKED DOWN&A/C RETURNED TO BASE (SAINT JOHN).  A/CLANDED & TAXIED TO HANGAR.	 ELECTRO-PUMP - BACKUP WORKED NORMAL FOR BRAKES &  STEERING. NO HYD FLOW LIGHTS WERE ON. HYD PUMPS WORKINGOK. NO FLUID L	OSS OR EXTERNAL LEAKAGE EVIDENT.4. GROUND TESTS INDICATE FLUID BYPASSING WITHIN ACCUM	1	H	7	2 	4T	4	T	 	2A4     	E4WE	6	C	P8EU	 
2001030200077	20010302	00077	NM  	2001	3	2	CA000901003      	1	20000822	G	6120	3612001	ACTUATOR        			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	RT PROPELLER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			8501 			960518					(CAN)  TIME SINCE REPAIR 4379. RIGHT PROP LEAKING OIL. RT PROP ACTUATOR REPLACED AND AIRCRAFT RETURNED TO SERVICE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001030200081	20010302	00081		2001	3	2	CA000901007      	4	20000815	G	3425	5222782004	INDICATOR       			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			36822	7730 							(CAN) IN CRUISE CAPTAINS HORIZONTAL SITUATION INDICATOR STOPPED TURNING WHEN AIRCRAFT WAS IN A TURN. COMPARATOR LIGHT CA	ME ON. RETURNED. CAPTAINS HSI REPLACED.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030200082	20010302	00082	CE  	2001	3	2	CA000901008      	1	20000825	G	2820	050011874	FUEL LINE       			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5564 								(CAN) FUEL LINE LOCATED BETWEEN THE FUEL SELECTOR VALVE AND FUEL STRAINER & PASSES UNDER THE CO-PILOTS RUDDER PEDALS. TH	E RUDDER PEDALS MOVE THE STEERING ROD RUBBED AGAINST THE FUEL LINE. THE FUEL LINE WAS RUBBED MORE THAN HALF THROUGH.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000092100508	20000921	00508	SO  	2000	9	21	CA000901012      	1	20000802	G	8120	4066109020	TURBOCHARGER    	HONEYWELL   		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					EXH BLDE LET GO	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				O	 	 	OTHER                     			CR	CRUISE         	1			CA						2B005672					(CAN) CLIMBING THROUGH 16,000 FEET, RIGHT ENGINE SHUTDOWN.  GOING THROUGH 10,000 FEET, ENGINE RESTARTED AND PARTIAL POWE	R WAS AVAILABLE.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000092100509	20000921	00509	EA  	2000	9	21	CA000901013      	2	20000714	G	8530	AEL19001	VALVE           		AEL651024   	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					VALVE TIP	FAILED          	W				K		 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			102  			7558303H					(CAN) ENGINE WAS SHOWING SIGNS OF METAL IN OIL FILTER.  ENGINE DISMANTLED TO FIND CAUSE OF METAL.  ONE EXHAUST VALVE FOU	ND TO BE PROTRUDING FROM CYLINDER FARTHER THAN USUAL.  EXHAUST VALVE REMOVED AND FOUND TO BE MISSING APPROXIMATELY .1250	 INCH MATERIAL WHERE RETANING KEYS HOLD VALVE.  (X)				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000092800113	20000928	00113	NE  	2000	9	28	CA000901015      	2	20000824	G	7200		ENGINE          	TMECA       	ARRIEL1B    	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	POWER LOSS      	W				A	 	 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			CA						4124					(CAN) HELICOPTER WAS IN A HOVER WHEN A POWER LOSS OCCURRED.  UNKNOWN AT THIS TIME WHAT THE CAUSE WAS.  TC AWAITING FOLLO	W-UP REPORT.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000092800114	20000928	00114	EU  	2000	9	28	CA000901016      	1	20000829	G	2913	S40	COUPLING        	AEROSP      	350A35013004	SNIAS 	350   	AS350B2     	8680813	EU  										SPLINES	WORN            	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE PILOT WAS IN CRUISE WHEN HE LOST HYDRAULIC BOOST. THE PILOT INITIATED A HYDRAULIC FAILURE PROCEDURE AND LANDED	 THE HELICOPTER WITHOUT AN ACCIDENT.  AN ENGINEER FOUND WORN OUT SPLINES ON THE COUPLING SLEEVE OF THE HYDRAULIC PUMP PU	LLEY ASSEMBLY.  AS A PRECAUTION, REPLACED THE HYDRAULIC PUMP.  THE INSPECTION PERIOD AND REGREASE BY EUROCOPTER IS EVERY	 500 HOURS.  OUR MAINTENANCE SCHEDULE IS EVERY 100 HOURS.  THE RECOMMENDED GREASE BY EUROCOPTER IS G355 (ROYCO 49B) GREA	SE.  (X)		1	G	7	1 	3U			 	H9EU    					 
2000092800115	20000928	00115	SW  	2000	9	28	CA000901017      	1	20000804	G	6320	BP252	GEARBOX         		TB3117BMA   	KAMOV 	KA32  	KA32A1      	       	SW  										M/R GEARBOX	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			HO	HOVERING       	1			CA			649  	364  		708789210008					(CAN) DURING LOGGING OPERATION, PILOT REPORTED GEARBOX CHIP WARNING INDICATION AND LANDED IN SERVICE  LANDING. INSPECTIO	N OF CHIP DEECTORS REVEALED METALLIC FUZZ.  DETECTORS CLEANED, AIRCRAFT GROUND RUN AND TEST FLOWN IN ACCORDANCE WITH BP2	52 MAINTENANCE MANUAL 84.10.00 P.103, RETURNED TO SERVICE. PROBLEM RECURRED, METAL DETECTED ON CHIP DETECTORS.  GEARBOX 	REMOVED FROM SERVICE.  (X)			1	G	7	2 	4U			NC	        					 
2000092100511	20000921	00511	WP  	2000	9	21	CA000905002      	2	20000822	G	7261	31012801	TUBE            	GARRTT      		MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					GEARBOX END	CRACKED         	W				E	 	 	 	ENGINE SHUTDOWN         				J	K	 	WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA				2000 		P20148C					(CAN) THE ENGINE WAS SHUTDOWN IN FLIGHT AS A PRECAUTION DUE TO AN OIL LEAK AND LOW OIL PRESSURE. ONCE ON THE GROUND, THE	 SOURCE OF THE OIL LEAK COULD NOT POSITIVELY BE LOCATED.THE ENGINE WAS MOUNTED IN THE TEST CELL AND THE OIL LEAK WAS FIN	ALLY TRACED TO A CRACKED FLARE ON THE OIL SUPPLY TUBE P/N 3101280-1 UNDER THE FLARE NUT AT THE GEARBOX END. THIS NUT IS 	LOCATED UNDER THE PROP PITCH CONTROL, AND BEHIND THE PROPELLER GOVERNOR, WHICH COMPLICATED LOCATING THE SOUCE OF THE LEA	K IN THE FIELD. THE TUBE WAS REPLACED WITH A SERVICEABLE TUBE, ENGINE RE-ASSEMBLED, AND TESTED IN THE TEST CELL OK. THE 	ENGINE HAS BEEN FOUND ACCEPTABLE FOR RETURN TO SERVICE.	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
2001011105375	20010111	05375	EU  	2001	1	11	CA000905004      	1	20000616	G	3244	5504632	TIRE            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) THE PILOT RPTED LT INBOARD MAIN WHEEL TIRE ASSY BLEW ON ROTATION & GEAR SAFE IND. LIGHT WENT OUT. MAINT CNTL TROUB	LESHOT PROBLEM WITH FLT CREW BUT WERE UNABLE TO GET LEFT MAIN GEAR TO INDICATE DOWN AND  LOCKED. DECISION MADE TO DIVERT	 WHERE EMERG LDG CARRIED OUT - AFTER BURNING OFF EXCESS FUEL. A/C LANDED W/O INCID., PASSENGERS WERE DEPLANED & TRANSPOR	TED TO TERMINAL BY BUS. INIT MAINT INSP REVEALED RETREAD ON NR 2 TIRE HAD LET GO - TIRE ASSY STILL AT 100 PSI. MAINT INS	T GEAR PINS, CHANGED #1 & #2 TIRES (P/N 9550462-2)&FERRIED FURTHER INSP REVEALED DAMAGE TO L/H SIDE STAY ASSY (P/N 20049	00 1), LOWER TOGGLE STRIKER SUB-ASSY (P/N 200	2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001011105376	20010111	05376	EU  	2001	1	11	CA000905005      	1	20000720	G	5280	200642005	STOP            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG DOOR	LOOSE           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF AIRCRAFT REPORTED THE LEFT MAIN GEAR DOOR WOULD NOT CLOSE AFTER GEAR RETRACTION. THE GEAR WA	S CYCLED SEVERAL TIMES WITH THE SAME RESULT. THE CREW ELECTED TO RETURN TO WITH THE GEAR DOWN SELECTION NORMAL - 5 GREEN	 LIGHTS AND BOTH MAIN GEAR DOORS CLOSED. AIRCRAFT LANDED WITHOUT INCIDENT - CFR WAS CALLED OUT ON STANDBY AS A PRECAUTIO	N. AIRCRAFT INSPECTED AND FOUND SAFE FOR FERRY FLIGHT WITH GEAR DOWN AND PINS INSTALLED. MAINTENANCE INSPECTION FOUND TH	E LEFT HAND MAIN LANDING GEAR DOOR WOULD NOT LOCK BECAUSE THE DOOR STOP WAS LOOSE. STOP WAS ADJUSTED AND LOCK WIRED - GE	AR SWINGS CARRIED OUT AND CHECKED SERVICEABLE.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.	2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001030700651	20010307	00651	EU  	2001	3	7	CA000905006      	1	20000725	G	5210	A26084005	SEAL            	FOKKER      	A26050801   	FOKKER	F28   	F28MK1000   	4990808	EU  										PAX DOOR	LOOSE           	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						048					(CAN) SHORTLY AFTER TAKEOFF THE CREW REPORTED THE AIRCRAFT WOULD NOT PRESSURIZE BECAUSE THE MAIN CABIN DOOR WAS NOT SEAL	ING PROPERLY. AICRAFT RETURNEDAND LANDED WITHOUT INCIDENT. PASSENGERS DEPLANED AND TRANSFERED TO A WAITING AIRCRAFT. MAI	NTENANCE TAXIED AIRCRAFT BACK TO THE HANGAR AND INSPECTED THE DOOR AREA. MAINTENANCE FOUND THE MAIN CABIN WOULD NOT SEAT	 PROPERLY WHEN AIRCRAFT WAS PRESSURIZED TO MAX DIFFERENTIAL.DOOR SEAL WAS RE-ADJUSTED AND AIRCRAFT GROUND PRESSURIZED SE	RVICEABLE.AIRCRAFT RETURNED TO SERVICE WITH NO FUTHER INCIDENTS TO REPORT.		2	L	7	2 	4F			RT	A20EU   					 
2001030700652	20010307	00652	EU  	2001	3	7	CA000905007      	1	20000723	G	2910		LINE            			FOKKER	F28   	F28MK1000   	4990808	EU  										HYD SYSTEM	RUPTURED        	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) AIRCRAFT RETURNED TO BLOCKS BECAUSE THE CREW REPORTED THE NR 2 SYSTEM HYDRAULIC PUMP LIGHTS ILLUMINATED AND THEN T	HE NR 2 SYSTEM QUANTITY AND PRESSURE DROPPED QUICKLY. AIRCRAFT RETURNED TO YVR AND LANDED WITHOUT INCIDENT. MAINTENANCE 	INSPECTION REVEALED A RUPTURED LINE FOUND IN THE STUB WING AFT OF THE NR 2 SHUT OFF VALVE. LINE REPLACED, AREA INSPECTED	 AND GROUND CHECKED SERVICEABLE - AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.			2	L	7	2 	4F			RT	A20EU   					 
2001030700653	20010307	00653		2001	3	7	CA000905008      	4	20000722	G	3442	20671570153	RADAR           			FOKKER	F28   	F28MK1000   	4990808	EU  										WEATHER	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			9583 								(CAN) AIRCRAFT REPORTED THE WEATHER RADAR WAS U/S ON CLIMB OUT. THE CREW DECIDED TO RETURN DUE TO UNFAVORABLE WEATHER CO	NDITIONS - AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE SENT AND TESTED THE SYSTEM - TECHNICIAN REPORTED SYSTEM CHECKED	 SERVICEABLE. DECISION MADE TO REPLACE WEATHER RADAR FOR TROUBLESHOOTING REASONS. R/T REPLACED, S/NON1523, S/N OFF 4972,	 SYSTEM GROUND CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT.			2	L	7	2 	4F			RT	A20EU   					 
2001010200013	20010102	00013	WP  	2001	1	2	CA000905010      	2	20000529	G	7320		DIAPHRAGM       	WOODWARD    	89356110    	BEECH 	100   	100BEECH    	1152916	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					SIDEWALL OF ROLL	PIN HOLE        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA						1705317					(CAN) TORQUE ON LEFT ENGINE WOULD NOT GO BELOW 900 POUND/FEET OF TORQUE AT FLIGHT IDLE, ENGINE SHUT DOWN ON LANDING.  FC	U DIAPHRAGM FAILED LEAK TEST.  FOUND BELLOW/DIAPHRAGM ASSY WITH PIN HOLES.  NOTE:  FCU HAS 5709 ON, AND TSO DIAPHRAGM IS	 A 300 HR REPLACEMENT ITEM.  SHOULD HAVE BEEN REPLACED AT 3000 HOURS WHEN AIRCRAFT WAS U.S. REGISTERED - TECHNICAL HISTO	RY ON ENGINE DOES NOT REFLECT FCU MAINTENANCE.			1	L	7	2 	3T	4	T	 	A14CE   	E2WE				 
2000092800116	20000928	00116	SW  	2000	9	28	CA000905011      	1	20000822	G	6510	205040176101	BOOT            	BELL        	205040004101	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN DRIVE SHAFT	TORN            	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			CA				2064 		A2011823					(CAN) - LEAKAGE OF GREASE  WAS DISCOVERED COMING FROM THE MAIN DRIVE SHAFT AFTER  AIRCRAFT WAS SHUT DOWN .  FURTHER INVE	STIGATION REVEALED THAT THE BOOT WAS TORN THUS ALLOWING  LEAKAGE OF  GREASE FROM THE DRIVE SHAFT COUPLING.- NO INDICATIO	N OF OVERHEATING.				1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001030700684	20010307	00684	SO  	2001	3	7	CA000905012      	2	20000823	G	7414	M3050	IMPULSE COUPLING	SLICK       	6310        	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					MAGNETO	FAILED          	W				K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA				1446 		96111161					(CAN) MAGNETO HAD 125 HOURS  SINCE LAST 500 HOUR INSPECTION, AT WHICH TIME IMPULSE COUPLING WS WITHIN SPECS AS CALLED OU	T IN SLICK MAINTENANCE AND OVERHAUL MANUAL. DURING END RUN FOR 50 HOUR A/C INSPECTION, R/H MAG FOUND DEAD. DURING INSPEC	TION, FOUND MAG LYING ON TOP OF ENGINE WITH BUSTED MOUNTING FLANGE. INSPECTION FOUND THAT IMPULSE COUPLING HAD COME APAR	T DURING END RUN - SEIZED MAG THUS BUSTING FLANGE.			1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2000092800117	20000928	00117	GL  	2000	9	28	CA000905014      	2	20000811	G	7314	6899253	PUMP            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROLL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			HO	HOVERING       	1			CA				3650 		T1271					(CAN) WHILE IN 4 FT HOVER, AN ENGINE FLAMEOUT OCCURRED. UPON INVESTIGATION  IT WAS DISCOVER THE THE ENGINE DRIVEN FUEL P	UMP TO BE IN BY PASS. FUEL CONTROL AND FUEL PUMP REPLACED.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001030700686	20010307	00686	GL  	2001	3	7	CA000905015      	2	20000816	G	7323	23065121	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				R	 	 	PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				203  		14151					(CAN) WHILE RUNNING ON THE GROUND AT 100% N2 THE PILOT PULLED COLLECTIVE. AS HE PULLED IN POWER THE ROTOR RPM DROPPED TO	 80%, ALL AIR LINES WERE LEAK CHECKED, GOVERNOR REPLACED & THE PROBLEM WENT AWAY.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001030700654	20010307	00654	NM  	2001	3	7	CA000905016      	1	20000818	G	4990	GTCP85129CKA	BLEED VALVE     			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					APU	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			O			OTHER                     			CR	CRUISE         	1			CA			31440	1440 		P35248C					(CAN) ON TWO OCCASIONS, THE CREW EXPERIENCED A FIRE INDICATION ON THE APU WHILE THE AIRCRAFT WAS AT CRUISING ALTITUDE. O	N BOTH OCCASIONS, THE APU SHUT DOWN AND THROUGH CREW PROCEDURES, THE APU FIRE BOTTLE WAS DISCHARGED. IN BOTH OCCURRENCES	, MAINTENANCE INSPECTED THE APU COMPARTMENT AND FOUND NO SIGNS THAT A FIRE HAD OCCURRED AND THE AIRCRAFT CONTINUED IN SE	RVICE WITH THE APU ON MEL FOR THE DISCHARGED BOTTLE. FOUND PINS ON BLEED VALVE CORRODED, LOAD CONTROL VALVE AND REGULATO	R REPLACED.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000092100512	20000921	00512	SO  	2000	9	21	CA000906002      	1	20000807	G	3231	1776604	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ADJ TO FITTING	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				K		 	FLUID LOSS                			TO	TAKEOFF        	1			CA											(CAN) WHEN DEPARTING YTH, ON 4 AUG 2000, WITH GEAR SELECTED UP, U/C FAILED TO RETRACT.  PILOT LOCKED U/C DOWN BY HAND PU	MP AND RETURNED TO YTH.  FLY PAST CARRIED TO CONFIRM U/C POS AND UNEVENTFUL LDG MADE  .INSP REVEALED THAT HYDRAULIC HOSE	 TO PORT U/C DOOR ACTUATOR LEAKING AND CAUSED HYDRAULIC SYS FLUID LOSS.  NEW HOSE INST AND HYDRAULIC SYS PRIMED, BLED. U	/C CYCLED THROUGH SEVERAL RETRACTIONS WITH NO FAULTS.  AIRCRA FT RETURNED TO SERVICE.  HOSE LEAKING FROM STEEL BRAIDS AT	 END ADJACENT TO END FITTING CONNECTED TO DOOR ACTUATOR.  EXAMINATION OF HOSE SHOWED 2 BROKEN STRANDS IN STEEL OUTER BRA	IDING,&VERY SLIGHT DISTORTION OF HOSE IN AREA OF END FITTING.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000092800128	20000928	00128	SW  	2000	9	28	CA000906003      	1	20000816	G	6730	204076052009	SERVO           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					ACTUATOR	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA				612  		62656					(CAN) THE PILOT FELT A FEEDBACK IN THE CYCLIC STICK IN THE FORWARD RIGHT HAND QUADRANT.  THIS FEEDBACK WAS NOT SATISFACT	ORY TO THE AIRCRAFT TYPE.  THE RIGHT HAND SERVO WAS REMOVED AND EXCHANGED WITH THE LEFT HAND CYCLIC SERVO.  THE SUSPECT 	SERVO NOW IN THE LEFT HAND POSITIION CAUSED AN EXCESSIVE FEEDBACK IN THE FORWARD LEFT HAND QUANDRANT. THE SUSPECT SERVO 	WAS REMOVED AND REPLACED WITH A SERVO (TSO 0:0 HOURS) WHICH ELIMINATED THE CYCLIC STICK FEEDBACK.  THE AIRCRAFT WAS FOUN	D SATISFACTORY TO TYPE AND SUBSEQUENTLY RELEASED TO SERVICE.  (X)		1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2000092100513	20000921	00513	SO  	2000	9	21	CA000906005      	1	20000821	G	7930	3030359	CHIP DETECTOR   	PWA         		PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					BSE-THRDED AREA	BROKEN          	W				E	F	A	 	ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	UNSCHED LANDING         		B	K	 	SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		CL	CLIMB          	1			CA						PCE99130					(CAN) DURING CLIMB, PILOT NOTICED SMOKE FROM LEFT ENGINE.  SUSPECTING FIRE, ENGINE WAS SHUTDOWN AND SECURED AND FIRE BOT	TTLE ACTIVATED.  UNEVENTFUL LANDING C/O SASKATOON.  MAINTENANCE DISCOVERED BROKEN CHIP DETECTOR ALLOWING ENGINE OIL TO L	EAK ONTO ENGINE CASE, RESULTING IN SMOKE. OIL REPLENISHED, DETECTOR REPLACED NEW.  FIRE BOTTLE REMOVED FOR RECHARGE.  CR	ACK FOUND AT THE CHIP DETECTORS BASE TO THREADED AREA.  (X)			1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2000092100514	20000921	00514	CE  	2000	9	21	CA000906006      	1	20000817	G	5610	10138402518	WINDSHIELD      			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RT WINDSHIELD	FAILED          	W				I	A	 	 	CABIN DEPRESSURIZATION  	UNSCHED LANDING         			S	 	 	AFFECT SYSTEMS            			CR	CRUISE         	1			CA			1374 			97058H9808					(CAN) WHILE IN CRUISE AT 28,000 FEET, THE R/H WINDSHIELD FAILED. THE INNER LAMINATION SUSTAINED A FAILURE RESULTING IN A	 LATTICE LIKE SERIES OF CRACKS. (INSTALLED MAY 1997.)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000092100515	20000921	00515	SO  	2000	9	21	CA000906008      	2	20000816	G	8520		ENGINE          			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED DURING CRUISE HE HAD BRIEF VIBRATION FOLLOWED BY A LOSS OF OIL PRESSURE AND IMMEDIATE ENGINE FAILUR	E.  AN UNEVENTFUL FORCED LANDING WAS CONDUCTED ON A LAKE 40 NAUTICAL MILES NORTHWEST OF RANKIN INLET, NUNAVUT.  MAINTENA	NCE FOUND THE FRONT HALF OF THE ENGINE FREE AND WOULD TURN OVER, HOWEVER, AN ACCESSORY CASE AND REAR OF ENGINE APPEARS S	EIZED INDICATING A POSSIBLE CRANK FAILURE. THIS DATE THE A/C IS IN THE PROCESS OF RECEIVING A ZERO TIME ENGINE.  THE FAI	LED ENGINE IS TO BE RETURNED TO PROGRESSIVE AIR IN KAMLOOPS FOR ANALYSIS. HAVE REQUESTED A FURTHER SDR AND STRIP REPORT 	.  (X)	1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000092100516	20000921	00516	SO  	2000	9	21	CA000906009      	1	20000817	G	3246	16107200	WHEEL           	CLEVELAND   	40106       	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					BEAD FLANGE RADI	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RECENT LPI NDT TESTS REVEALED WHEEL HALF CRACKING IN THE BEAD FLANGE AREA.  CLEVELAND WHEELS ARE DATE MARKED AND N	DT SERIALIZED.  AFFECTED WHEELS WERE DATED JUNE 1994 AND JUNE 1991.  WHEELS REMOVED FROM SERVICE.  (X)					1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000092100517	20000921	00517	EA  	2000	9	21	CA000906010      	2	20000723	G	7421	RHB32E	SPARK PLUG      	CHAMPION    		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					SPARK PLUG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			CA						L78161					(CAN) SPARK PLUG MISFIRING THROUGH ALTITUDE.  TESTED WITH PLUG MACHINE AND FOUND ERRATIC AND YELLOW COLOR SPARK.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000092800103	20000928	00103	SW  	2000	9	28	CA000907002      	1	20000821	G	6220	206011125001	PIN             	BELL        		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					CENTER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			582  			A1417					(CAN) DURING MAINTENANCE TEARDOWN, PINS FOUND TO HAVE MECHANICAL WEAR AND REPLACED.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001030700655	20010307	00655	NM  	2001	3	7	CA000907003      	1	20000823	G	2782	269002910	ACTUATOR        			BOEING	727   	727217      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SLATS	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA				10522							(CAN) LOST " A" SYSTEM HYDRAULICS, PRESSUE AND QUANTITY READ ZERO. TROUBLESHOOTING CARRIED OUT FOUND NR 3 LEADING EDGE S	LAT ACTUATOR HOUSING CRACKED. LEADING EDGE SLAT ACTUATOR REPLACED PER MM 27-81-22.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2000091800022	20000918	00022	SO  	2000	9	18	CA000907004      	2	20000823	G	7414	M3081	POINTS          	SLICK       	4371        	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					CONTACT POINT	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			651  			99020938					(CAN) THE MAGNETO WAS REMOVED FROM SERVICE DUE TO INTERMITTENT FIRING.  ON INSPECTION, THE STATIONARY POINT WAS FOUND LO	OSE. THE POINT, IS MANUFACTURED WITH A STEM TO BE RIVETED TO THE STEEL FRAME. TOTAL TIME ON NEW POINT SET INSTALLED AT T	HE 500 HOUR MAINTENANCE CHECK IS 151.2 HOURS.  (X)				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001030800001	20010308	00001	GL  	2001	3	8	CA000907005      	3	20000826	G	6111	PFA12D19B	BLADE           	HAMSTD      	24PF305     	DHAV  	DHC7  	DHC71       	2802702	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	PROPELLER	MISREPAIRED     	W				K	 	 	 	NONE                    				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			9257 	2860 		238306					(CAN) . BLADE SER #841280. BLADE RECD FROM OPERATOR WITH FIBREGLASS DAMAGE BEYONG MANUAL LIMITSL. BLADE RETURNED TO MFG 	FOR REPAIR. BLADE RETURNED FROM MFG AFTER REPAIR ANDFOUND NOT TO COMPLY WITH COMPONENT MAINT MANUAL IN 2 AREAS. CMM61-13	-01.1ST: ALUMINUM PORTION OF BLADE SHANK PAINTED WITH REQD BLACK EROSIION COATING THAT IS  CONDUCTIVE. BUT BLADE NOT COA	TED WITH REQD CLEAR POLYURATHANE COATING ON TOP OF BLACK EROSION COATING. IS NEW REQMT WHEN MANUAL REVISED TO REVISION 1	0 IN JUN 1999.2ND: BLADE FOUND WITH CORK INST IN TAPER BORE: CORK MUST BE REMVD FROM BLADE AS PART OF DISASSY PROC& T		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001011105149	20010111	05149	NM  	2001	1	11	CA000907006      	1	20000825	G	3260	1010153	POSITION SWITCH 			BOEING	727   	727233      	138408A	NM  	PWA   	JT8   	JT8D15      	52051	NE  					SPRING ANCHOR	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) FAILED NLG POS IND. SWITCH YIELDED FOLLOWING RESULTS. CURSORY INSP DETECTED INTERNAL RATTLE. WHEN CASE OPENED LOOS	E DRIVE SCREW & SLEEVE (THIMBLE) WHICH COMPRISE SWITCH ARM SPRING ANCHOR ASSY WERE FOUND. THE CONTACTOR ASSY APPEARED TO	 BE IN AS NEW CONDITION. CLOSER EXAMINATION REVEALED DRIVE SCREW WHICH RETAINS SWITCH ARM SPRING ANCHOR THIMBLE APPEARED	 TO BE INADEQUATE.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2000091800023	20000918	00023	EU  	2000	9	18	CA000907008      	1	20000828	G	6120	9717517102	WIRE            		975290201   	PILATS	PC12  	PC1245      	7090551	EU  						HARTZL	HCE4A	HCE4A3D     	GL  	PIN	BROKEN          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA						081					(CAN) CAREW REPORTED APPROXIMATELY 200 RPM PROP INDICATION FLUCTUATION IN-FLIGHT.  ALL OTHER ENGINE PARAMETERS WERE OK. 	 SYSTEM INSPECTED AND A PIN IN THE PROP MAGNETIC PICK UP CANNON PLUG WAS FOUND WITH A BROKEN WIRE.  WIRE/PIN CONNECTION 	REPAIRED AND RUN-UP CARRIED OUT SERVICEABLE.  (X)				1	L	7	1 	3T			RT	A78EU   		5	C	P210NE	 
2000091800024	20000918	00024	EU  	2000	9	18	CA000907009      	1	20000828	G	7331	9753512602	TRANSMITTER     	PWA         		PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					INTERNAL	INACCURATE      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA			3121 			PCEPR0090					(CAN) PILOT REPORTED THAT THE EIS PANEL WAS ONLY READING 50 POUNDS PER HOUR FUEL FLOW.  REPLACED FUEL FLOW TRANSMITTER A	ND FUEL FLOW CHECKED SERVICEABLE.  (X)					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2000091800025	20000918	00025	CE  	2000	9	18	CA000907014      	1	20000816	G	6100		PROPELLER       	MCAULY      		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	L/E & FACE	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1498 		K18663					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2000091800026	20000918	00026	SO  	2000	9	18	CA000907015      	1	20000819	G	5311	4521504	BULKHEAD        	PIPER       		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					SNUBR UPR BOLT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			14755			31T7920045					(CAN) DOOR FRAME (BULKHEAD) CRACKED AT SNUBBER UPPER ATTACHMENT POINT.  (X)						1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2000091800027	20000918	00027	CE  	2000	9	18	CA000907016      	1	20000824	G	7400	103572001	IGNITION SWITCH 	CONT        		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					LT MAG CONTACTS	SHORTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6711 			L2620227A					(CAN) FLIGHT SCHOOL INSTRUCTOR AND STUDENT PERFORMED POST FLIGHT MAG CHECK BEFORE SHUTDOWN.  WHEN SELECTING LT MAG, AIRC	RAFT STARTED TO FILL WITH SMOKE FOLLOWED BY THE INSTRUMENT BREAKER TRIPPING.  AMES FOUND THE PROBLEM TO ORIGINATE AT THE	 IGNITION SWITCH GROUNDING OUT.  SWITCH WAS REPLACED AND FUNCTION TESTED.  SYSTEM FOUND TO BE SERVICEABLE.  (X)				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001011105150	20010111	05150	NM  	2001	1	11	CA000907018      	1	20000801	G	2435	230880026	STARTER GEN     			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					NR 1 ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1859 								(CAN) AIRCRAFT ARRIVED IN GEORGETOWN (GGO) WITH THE " NR 1 DC GEN HOT" CAUTION LIGHT & HEATER CAUTION LIGHT. THE STARTER	 GENERATOR AND AREA AROUND IT INSPECTED AS PER MEL 24-1, STARTER GENERATOR FUNCTIONED CHECKED. OK.AIRCRAFT ARRIVED LATER	 AT PORT OF SPAIN (POS), WHEN THE CREW WAS READY TO DEPART AND COMMENCE STARTING OF THE NR 1 ENGINE, IT WOULD NOT START.	STARTER GENERATOR REPLACED, SYSTEM OPERATES CORRECTLY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030800005	20010308	00005	NM  	2001	3	8	CA000907019      	1	20000815	G	3260	DSC201	HARNESS         	ELDEC       	858601      	DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  					MLG	DEFECTIVE       	W				C	D	 	 	ABORTED TAKEOFF         	RETURN TO BLOCK         			N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF ROLL AT APPROX. 50 KTS LEFT MAIN GEAR DOOR ADVISORY LIGHT ILLUMINATED ONLY, PILOT ABORTED TAKEOFF AND R	ETURNED TO STAND. ON CHECKING PSEU FAULT CODES 06 AND 53 WITH EXPANDED TEST 72 APPARENT LEFT MAIN GEAR DOOR WIL NOT CLOS	E. TECHNICIANS - TROUBLESHOOTING REVEALED, CORRECT OPERATION NOTE GEAR & R/H MAIN GEAR (UP & DOWN), LEFT GEAR SEQUENCE V	ALVE - NO POWER. FURTHER INVESTIGATION REVEALED A DEFECT WITH THE WOW NR2 WIRING HARNESS, NR2 WOW HARNESS (MLG) ORDERLY 	AOG - REPLACED HARNESS & CHAFED RELAY WIRE.PSEU REPLACED - AIRCRAFT SERVICEABLE AT 1900 HOURS17 AUGUST 2000.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030800006	20010308	00006	NM  	2001	3	8	CA000907020      	1	20000821	G	2913	570347	PUMP            			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					NR 1 ENGINE	MALFUNCTIONED   	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) AT 4 MILES FINAL FLAPS SELECTED TO 15 DEGREES NR1 ENGINE HYDRAULIC CAUTION LIGHT ILLUMINATED TOGETHER WITH ROD PRE	SSURE NR1 AND ROD HYDRAULIC NR1 AND MASTER CAUTION.STANDBY AND MAIN PRESSURES OBSERVED TO BE 1500 PSI FLAPS CONTINUED TO	 TRAVEL TO 15 DEGREES. STANDBY AND MAIN PRESSURES 3000 PSI. STANDBY AND MAIN PRESSURES OBSERVED NORMAL, HYDRAULIC QUANTI	TIES NORMAL. FLAPS OBSERVED AT 15 DEGREES. NR1 ENGINE HYDRAULIC PUMP CAUTION LIGHT REMAINED ILLUMINATED. UNEVENTFUL LAND	ING MADE. NR1 ENGINE DRIVEN PUMP REPLACED. FUNCTIONED SATISFACTORY.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001011105151	20010111	05151	NM  	2001	1	11	CA000907021      	1	20000720	G	3040	8SC0043011	WINDSHIELD      			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			4803 			97326H1600					(CAN) DURING A FLIGHT THE CAPTAIN NOTICED A SMELL & SOME SMOKE COMING FROM THE TOP OF HIS WINDSHIELD. WINDSHIELD DE-ICIN	G WAS TURNED OFF AND THE SMELL WENT AWAY. AIRCRAFT CONTINUED WITH DE-ICE OFF. MAINTENANCE NOTICED THAT THE STUD FOR THE 	GROUND AT THE WINDOW WAS VERY DARK AND BURNT. THE STUD WAS REPLACED AND WINDOW HEAT WAS FUNCTIONED. AS SOON AS THE HEAT 	WAS SELECTED TO NORM THE WINDOW SHATTERED. WINDSHIELD WAS REPLACED. SECOND WINDOW TO SHATTER IN A YEAR. BOTH CASES FINE 	GLASS SPRAYED IN THE FLIGHT COMPARTMENT. FIRST WINDOW 12,000 HOURS, SECOND WINDOW 4,803HOURS.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030800007	20010308	00007	NM  	2001	3	8	CA000907022      	1	20000811	G	5270	864202	PROXIMITY SWITCH		85220284003 	DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					FWD EMERG EXIT	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING THE CRUISE THE FORWARD EMERGENCY EXIT ILLUMINATED EMERGENCY CHECK LIST ENTERED AND AIRCRAFT DIVERTED TO MAN	CHESTER, UNEVENTFUL LANDING MADE AT MANCHESTER AIRPORT. ENGINEERS FOUND THAT THE PROXIMITY SENSOR WAS NOT WIRE LOCKED LA	RGER THAN NORMAL OPERATING GAP. SWITCH ADJUSTED AS PER MAINTENANCE MANUAL, CHECKED FOUND SATISFACTORY. SWITCH NOW WIRELO	CKED. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2000091800028	20000918	00028	SO  	2000	9	18	CA000907024      	1	20000806	G	3260	451823	ACTUATOR        	PIPER       	6741108     	PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					LT MAIN GEAR	BROKEN          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			2720 								(CAN) GEAR WOULD NOT RETRACT AFTER TAKEOFF.  AT RETURN TO BASE, SQUAT SWITCH ACTUATOR ARM WAS FOUND TO BE BROKEN.  NEW A	CTUATOR INSTALLED, NORMAL FUNCTION RETURNED.  (X)					1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2000091800029	20000918	00029	CE  	2000	9	18	CA000907025      	1	20000808	G	3233	99124852	ACTUATOR        			CESSNA	500   	550         	2076604	CE  										NOSE GEAR ACT	FAILED          	W				O	 	 	 	OTHER                   				R	D	 	PARTIAL RPM/PWR LOSS      	INFLIGHT SEPARATION       		LD	LANDING        	1			CA			1519 			015					(CAN) NOSE GEAR COLLAPSED UPON LANDING, WITH 3 GREEN INDICATIONS.  PILOT APPLIED UP ELEVATOR EASING THE WEIGHT ON THE NO	SE AND THE NOSE GEAR CAME BACK DOWN AND LOCKED.  TAXIED TO FBO OK.  MAINTENANCE AND CESSNA REP REMOVED GEAR DOORS AND CO	NFIRMED DOWN AND LOCKED.   AIRCRAFT FERRIED TO YYZ FROM YHM.  NOSE GEAR ACTUATOR REMOVED.  SENT TO FAA ACO WICHITA KS FO	R TESTING.  REPLACED  ACTUATOR.  GEAR SWINGS CARRIED OUT.  CHECKED OK.  (X)			1	L	7	2 	4F			 	A22CE   					 
2001011105159	20010111	05159	NM  	2001	1	11	CA000907027      	1	20000822	G	6310		ENGINE          			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) PRIOR TO DESCENT INTO YYC LOW OIL PRESSURE LIGHT ON FOR NR  2 ENGINE OIL PRESSURE DECREASING AND OIL QUANTITY DECR	EASING.ENGINE FAILURE AND SHUTDOWN FOLLOWED BY ONE ENGINE INOPERATIVE CHECKLIST CARRIED OUT. DECLARED EMERGENCY LANDING.	 TROUBLESHOOTING CARRIED OUT, FOUND REQUIRES ENGINE CHANGE. PRESENTLY IN PROCESS OF MAKING ARRANGEMENT TO REPLACE ENGINE	 IN YYC.			2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2001030700662	20010307	00662	WP  	2001	3	7	CA000918003      	1	20000808	G	2121	5007025211	FAN             			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					E/E BAY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BURNING SMELL ON PRE-DEPARTURE COMING FROM THE ELECTRICAL EQUIPMENT COMPARTMENT. FOUND THE A/C BUS CONTROL PANEL C	IRCUIT BREAKER POPPED,  UNABLE TO RESET. REPLACED THE RADIO RACK COOLING FAN AND ALSO THE A/C BUS CONTROL PANEL.					2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001030800010	20010308	00010	WP  	2001	3	8	CA000918006      	1	20000817	G	2420		WIRE            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					LT GENERATOR	DAMAGED         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) STALL INDICATION FAILURE LIGHT ON TRAINING FLIGHT, AIRCRAFT RETURNED TO BASE. FOUND LT GENERATOR TRIPPED, ATTEMPTE	D RESET, NIL FIX, FOUND DAMAGED WIRING.REPLACED WIRE X4A2N, SYSTEM CHECK SERVICEABLE.					2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001011105184	20010111	05184	NM  	2001	1	11	CA000918010      	1	20000807	G	2613	285N002821	CIRCUIT BOARD   			BOEING	767   	767209      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LOGIC TEST CARD	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) REJECTED TAKEOFF AT 80 KNOTS FOR A FIRE/OVERHEAT SYSTEM FAULT. DISPLAYED ON THE (EICAS) ENGINE INDICATION AND CREW	 ALERT SYSTEM. (CARGO INDICATION) THE A FAULT CARDS WERE SWAPPED, NIL FIX PROBLEM REPEATED. SUSPECT TO BE THE AFT LOGIC 	TEST CARD. REPLACED THE AFT LOGIC TEST CARD, TEST PERFORMED AND CHECK SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030800013	20010308	00013	NM  	2001	3	8	CA000918011      	1	20000810	G	7700	834802	PROXIMITY SWITCH	PWA         	JT9D7R4D    	BOEING	767   	767209      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LEFT	FAULTY          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA						P709699					(CAN) AIRCRAFT REJECTED TAKEOFF AT 76 KNOTS FOR AN (EICAS) ENGINE INDICATION AND CREW ALERT SYSTEM MESSAGE INDICATION. F	OUND LT SLEEVE UNLOCK PROXIMITY SWITCH AT FAULT. REPLACED LT PROXIMITY SWITCH.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030800014	20010308	00014		2001	3	8	CA000919002      	4	20000831	G	3418		SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) FLIGHT NR 5805 FROM CVG TO ISP, THE FLIGHT CREW REPORTED. STALL FAIL MSG AT 80 KTS, ON TAKEOFF ROLL. (ABORTED TAKE	OFF BELOW 80 KTS). AIRCRAFT RETURNED TO THE GATE FOR INVESTIGATION. MAINTENANCE CREW REPLACED THE AOA SENSOR AND THE AIR	CRAFT RETURNED IN SERVICE 28 AUGUST 2000.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030800015	20010308	00015	EA  	2001	3	8	CA000919003      	1	20000831	G	7603		GEARBOX         			CNDAIR	CL600 	CL6002B19   	       	EA  										ATR	FAILED          	W				B				EMER. DESCENT           				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) FLIGHT NR 5743 FROM CVG TO CLT, THE FLIGHT CREW REPORTED: IN FLIGHT (DESCENT), NR 2 ENGINE, THE N2 SET AT 82%, DID	 NOT RESPOND THE THRUST LEVER MOVEMENT. SHUT ENGINE DOWN IN FLIGHT, ECLRED EMERGENCY LANDING WITH NR 1 ENGINE ONLY, LAND	ING WAS UNEVENTFUL. T/S IN PROGRESS, APPEARS TO BE ATR GEARBOX.				2	L	7	2 	4F			RT	A21EA   					 
2001030800016	20010308	00016	EA  	2001	3	8	CA000919004      	1	20000831	G	3250		TORQUE LINK     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG STEERING	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) FLIGHT NR 5122 FROM MSY TO MCO, THE FLIGHT CREW REPORTED: THE NOSE GEAR STEERING DISCONNECTED ON TAXI OUT (SCISSOR	S).  MAINTENANCE RECONNECTED THE NOSE GEAR STEERING TORQUE LINK (SCISSORS).					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001011105177	20010111	05177	EA  	2001	1	11	CA000919005      	1	20000831	G	5270		HANDLE          	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						7067					(CAN) CREW REPORTED PAX DOOR OUTER HANDLE MSG POSTED AFTER TAKEOFF. A/C RETURNED TO FRESNO, CA. MAINTENANCE CONFIRMED GR	OUND CHECKS NORMAL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000113000001	20001130	00001	NE  	2000	11	30	CA000919006      	2	20000818	G	8530	71167	EXHAUST VALVE   	PWA         		DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					STEM MEET HEAD	BROKEN          	W				A		 	 	UNSCHED LANDING         				E	B	 	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			769  			22910					(CAN) THE AIRCRAFT WAS CRUISING AT 4500 ASL WHEN THE ENGINE BEGAN RUNNING ROUGH,  SOME SMOKE WAS SEEN, THE ENGINE WAS SH	UT DOWN AND A SUCCESSFUL FORCED LANDING WAS CARRIED OUT ON A LAKE 26.5 NM SOUTH OF PUVIRNITUQ, QUEBEC.  INVESTIGATION IN	TO THE CAUSE FOUND THAT THE VALVE HEAD OF NR 2 CYLINDER EXHAUST HAD SEPARATED AND BEAT ABOUT THE PISTON AND CYLINDER HEA	D UNTIL THE CYLINDER HEAD FINALLY CRACKED OPEN.  NR 2 CYLINDER AND PISTON ASSEMBLY WERE REPLACED.  ENGINE WAS GROUND RUN	 AND FOUND SERVICEABLE.  (X)		1	H	7	1 	3R	3	R	 	A815    	E142				 
2001030800017	20010308	00017	EA  	2001	3	8	CA000919007      	1	20000831	G	2760	4916405	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										SPOILER	FAILED          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) THE CREW CARRIE OUT AN AIR TURNBACK AND RETURNED TO MADRID. THE CREW REPORTED: SPOILERONS, FLIGHT SPOILERS AND GRO	UND SPOILERS FAULTS ON THE EICAS.MAINTENANCE RPLACED THE SECU NR 2.					2	L	7	2 	4F			RT	A21EA   					 
2001030800018	20010308	00018	EA  	2001	3	8	CA000919008      	1	20000826	G	2742	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	FAILED          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) PRIOR TO DEPARTURE, HORIZONTAL STABILIZER CHANNEL NR 2 WOULD NOT ENGAGE. FOUND MOTOR NR 2 FAULT. SENT A/C TO HANGA	R, REPLACE HSTA AND MCU. DURING REPLACEMENT, FOUND RESTRICTED MOVEMENT OF STAB SURFACE. PIVOT PIN WAS BINDING. SENT AIRC	RAFT TO MAINTENANCE FACILITY TO PERFORM STRUCTURAL REPAIRS.				2	L	7	2 	4F			RT	A21EA   					 
2001030800019	20010308	00019	EA  	2001	3	8	CA000919009      	1	20000827	G	5270	840534	PROXIMITY SWITCH			CNDAIR	CL600 	CL6002B19   	       	EA  										PAX DOOR	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) FLIGHT CREW REPORTED A PAX DOOR MESSAGE APPEARED IN ASSOCIATION WITH THE STOW HANDLE CAUTION, INTERMITTENTLY. REPL	ACED PROXIMITY SENSOR DI-16.					2	L	7	2 	4F			RT	A21EA   					 
2001030800020	20010308	00020	EA  	2001	3	8	CA000919010      	1	20000827	G	3234	601R509677	HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			657  								(CAN) UPON GEAR DOWN SELECTION ON APPROACH, THE LANDING GEAR HANDLE BROKE OFF. AN EMERGENCY WAS DECLARED, MANUAL RELEASE	 OF THE LANDING GEAR WAS PERFORMED AND LANDING WITH NO FURTHER EVENTS.THE HANDLE ASSEMBLY WAS REPLACED, A/C BACK IN SERV	ICE.AN AD IS BEING ISSUED TO ADDRESS THIS PROBLEM.				2	L	7	2 	4F			RT	A21EA   					 
2001030800021	20010308	00021	NE  	2001	3	8	CA000919011      	2	20000831	G	7261		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) FLIGHT NR 5737 FROM CVG TO MSN, THE FLIGHT CREW RPORTED: THE RIGHT ENGINE OIL PRESSURE WARNING ILLUMINTED IN FLIGH	T. ENGINE WAS SHUT DOWN AS PER QRH PROCEDURE: DECLARED EMERGENCY LANDING AND RETURNED TO THE DEPARTURE AIRPORT. THE LAND	ING WAS UNEVENTFUL. MAINTENANCE REPLENISHED THE OIL SYSTEM. T/S ONGOING.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030800022	20010308	00022	NE  	2001	3	8	CA000919012      	2	20000824	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA											(CAN) FLIGHT NR 6047 FROM (LGA) TO (BUF) CLIMBING THROUGH 17,000 FT LEFT ENGINE FAILED. MADE A SINGLE ENGINE LANDING WIT	HOUT INCIDENT. CREW DECLARED AN EMERGENCY AND MADE AN UNSCHEDULED LANDING INTO (AVP).SENT MECHANICS, FOUND BLADES MISSIN	G ON LPT. STILL INVESTIGATING.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030800023	20010308	00023		2001	3	8	CA000919013      	4	20000824	G	3418	601R550221	SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT/RT AOA	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) FLIGHT NR 5979 FROM (CVG) TO (GRR), THE FLIGHT CREW REPORTED: DURING TAKEOFF ROLL AT APPROXIMATELY 80 KTS, THE STA	LL FAIL MSG ILLUMINATED (TAKEOFF ABORTED)(SECOND ATTEMPT).MAINTENANCE REPLACED LT AND RT AOA SENSORS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030800024	20010308	00024	EA  	2001	3	8	CA000919014      	1	20000824	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING DELIVERY FLIGHT OF AIRCRAFT 7419, CIMBER UPON FIRST LANDING IN KEFLAVIK, ICELAND CAPT FWD WINDSHIELD MIDDLE	 PLY CRAACKED FROM THE USUAL AREA. CIMBER OBTAINED CONCESSION LETTER CO95-1652 TO BRING THE AIRCRAFT TO A REPAIR FACILIT	Y.MAINTENANCE REPLACED THE WINDSHIELD.				2	L	7	2 	4F			RT	A21EA   					 
2001030800025	20010308	00025	NE  	2001	3	8	CA000919015      	2	20000824	G	7261		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT & LT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)  IN FLIGHT. ENCOUNTERED EXTREME TURBULENCE, BOTH L/R ENGINE OIL PRESS WARNING MESSAGES APPEAED. IT WAS NEAR IMPOSS	IBLE TO CONTROL THE AIRCRAFT. THE LANDING WAS UNEVENTFUL. SEVERE TURBULENCE INSPECTION CARRIED OUT, NO DAMAGE RPORTED (F	DR WAS REMOVED FOR READOUT).				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000113000002	20001130	00002	GL  	2000	11	30	CA000920002      	3	20000825	G	6114		HUB             	MCAULY      												MCAULY	2A34C	D2A34C58    	GL  	RETENTION THREAD	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1314 	1116 		763862					(CAN) CRACK FOUND IN RETENTION THREAD AREA DURING EDDY CURRENT INSPECTION AS SPECIFIED IN MCAULEY SB NR 205B INSTRUCTION	S.  (X)															5	C	P3EA	 
2000101300109	20001013	00109	GL  	2000	10	13	CA000920005      	2	20000811	G	7261	23053298	TURBINE         	ALLSN       		HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					OIL STRUT	CARBONED        	W				B	 	 	 	EMER. DESCENT           				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			8778 	2302 				CAE295439			(CAN) DURING  FLIGHT,  A LOSS OF OIL PRESSURE AND TORQUE INDICATION WAS NOTED.  AN IMMEDIATE LANDING WAS PERFORMED AND  	THE ENGINE WAS SECURED.  THE ENGINE OIL  LEVEL WAS CHECKED AND IT WAS  THEN DISCOVERED THAT THE ENGINE OIL TANK WAS ENPT	Y.  THE PILOT STATED THAT HEAVY SMOKE WAS SEEN   COMING FROM THE EXHAUST ON SHUT DOWN. THERE WAS NO DAMAGE TO THE AIRCRA	FT.  PILOT  LANDED WITH POWER ON.  (X)			1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2000113000003	20001130	00003	CE  	2000	11	30	CA000920006      	1	20000822	G	3710		PUMP            			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ENG REAR ACCY	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			1356 								(CAN)   PUMP  FAILED ABOUT HALF WAY DURING 1.7 HOURS FLIGHT TG3 TO CYXK.  ALTERNATOR FAILURE FOLLOWED.  ALTHOUGH PUMP TU	RNED FREE BY HAND, BROKEN NYLON DRIVE SHOWED SIGNS OF  PRE-FAILURE DETERIORATION.  PUMP HAD 1356.1 HOURS, WAS INSTALLED 	NEW 7 APRIL 1977, CHECKED OK AT TSN: 1046.9 HOURS AT ENGINE OVERHAUL ON 21 MAR. 1996.  AIRCRAFT FLOWN 309.2 HOURS IN LAS	T 4 YEARS AND 5 MONTHS.  AVERAGE OF 70.11 HOURS A YEAR.   HANGARED 95 PERCENT OF TIME ON GROUND.  PRIVATE OWNED. .REPLAC	ED PUMP - NEW. REPLACED B3-5-1FILTER - AIR INLET.  (X)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000113000004	20001130	00004	CE  	2000	11	30	CA000920007      	1	20000822	G	2497	DOFF103001	WIRE            			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ALT TERMINAL	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			2980 			111					(CAN)  ALTERNATOR NO CHARGE LIGHT CAME ON ABOUT HALF WAY DURING 1.7 HOUR FLIGHT FROM TG3 TO CYXK, JUST AFTER VACUUM PUMP	 FAILURE.  PILOT SHUT DOWN ELECTRICAL SYSTEMS TO SAVE BATTERY POWER AND WAS ABLE TO PERFORM NECESSARY COMMUNICATIONS WIT	H FSS ,AND TERMINATED FLIGHT AS INTENDED.   PRELIMINARY INSPECTION DID NOT SHOW TROUBLE AS WIRES TIED IN BUNDLE AT VICIN	ITY OF ALTERNATOR.  BEGAN TO REMOVE ALTERNATOR.  MAIN CABLE TERMINAL LUG FELL OFF THE END OF CABLE.  REPLACED LUG.  GROU	ND RUN OK.  (X)		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000113000005	20001130	00005	EA  	2000	11	30	CA000920008      	2	20000821	G	7414	ES10382681	CAPACITOR       	BENDIX      	1068218     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENGINE	SHORTED         	W				A		 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA						8010918					(CAN)  AIRCRAFT DEPARTED RIMOUSKI AT 9 + 10, TO MADELEINA ISLANDS (FLIGHT DURATION ESTIMITATED 1.5 HRS), FLYING OFF SHOR	E AT CHARLD N.B., RT ENGINE STARTED TO CUT-OUT MOMENTARILY.  PILOT ELECTED TO TURN BACK, ENGINE CONTINUED COUGHING EVERY	 5 MINUTES AND INDICATED HIGH OIL TEMP.  LANDED AT 9 + 50. TOTAL AIR TIME 0176 A/C LOADED - CARGO).  FOUND CAPACITOR IN 	RT MAG HAVING LOOSE SPRING AND WORN P-LEAD TIP.  REPAIRED TIP AND REPLACED CAPACITOR RT.  NOTE DATE ON CAPACITOR 93-07, 	HOWEVER, INSTALLED AT OVERHAUL ON 99/12/20.  LT CAPACITOR DATED 92-35 WAS PREVIOUSLY REPLACED ON JULY 14, 2000.  SUBMITT	ER RECOMMENDED:  TO MAKE MANDATORY REPLACEMENT OF CAPACITORS AT ENGINE T.B.O. AND O/H.  (X)	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001011105183	20010111	05183	SO  	2001	1	11	CA000920009      	1	20000817	G	8120	MS20500624	NUT             	LYC         	TIO540A2B   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					TURBO CHARGER	WRONG PART      	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA						L286061A					(CAN) NOT AN SDR - SEE PMI1. OVERHAULED TURBO CHARGER WAS INSTALLED AS SUPPLIED BY OVER HAULER, PREVIOUS REPORT, FOR TRO	UBLE SHOOTING. 2. NEW MS20500-624 NUTS WERE ORDERED WITH ACCESSORY.3. SHOP SHIPPED MS21045-6 NUTS - HEAT RESISTING.4. WE	 CALLED OVER HAULER AS TO SIGNAL THAT HE SENT WRONG PARTS. HE APPEARED NOT AWARE OF DIFFERENCE BETWEEN THE TWO TYPES. 5.	 LYCOMING.P.C. SPECIFIES #MS20500-624.NOTE:  MS 20500-624  =HART RESIST 1200 DEGREE F.MS 21045-6 = HEAT RESIST250 DEGREE	 F. IF WRONG TYPE UTILIZED, DAMAGE CAN BE INDUCED TO STUDS AT REMOVAL, UNSEEN & WHEN REINSTALLED, TURBO COULD EVENTUALLY	 COME LOOSE ON BASE.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000113000006	20001130	00006	SO  	2000	11	30	CA000920010      	1	20000811	G	8120	12A19770	BRACKET         	LYC         		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2A   	41532	EA  					LT LWR INBD	BROKEN          	W				O	 	 	 	OTHER                   				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				551  		L564261A					(CAN)  AT 246.2 HOURS TSO BOLT LW31S4.10 HAD BEEN FOUND SHEARED AND WAS REPLACED.   AT 543.6 HOURS TSO, BOLT FOUND LOOSE	.  REMOVED. FOUND THAT BUSHING INSTALLED BY OVERHAULER IN THE DYNAFOCAL MOUNT BRACKET HAD PIECE OF FLANGE BROKEN.  TEMPO	RARY SHIMMED AND NEW BOLT INSTALLED.  NEW BRACKET ORDERED.  AT 550.6 HOURS:  THIS TIME (U.0 HRS FLOWN WITH INSPECTION OF	 SHIMMED REPAIRED AT EVERY LANDING) (A/C FLOWN TO AVIOINICS SHOP FOR MAINTENANCE).  NEW BOLT LW31S4.10, NEW NUT STD1420,	 AND NEW WASHERS STD 2197) INSTALLED, TORQUED, AND SAFETIED PER LYC S.I. NR 1384 AND A CERTIFIED BRACKET SUPPLIED BY OVE	RHAULER INSTALLED.  NOTE: SEE SDR - 14-08-00 FOR C-GPXW SIMILAR PROBLEM - SAME OVERHAULER.  (X)	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000113000007	20001130	00007	SO  	2000	11	30	CA000920011      	1	20000814	G	8120	LW31S444	BOLT            	LYC         	LW18302     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					LWR OTBD	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				481  							(CAN)  OUTBOARD TURBO MOUNT LOWER BOLT TO ENGINE DYNAFOCAL MOUNT BRACKET WAS FOUND LOOSE (HAND LOOSE) WITH PLAY IN MOUNT	.  HOWEVER, CUTTER PIN WAS INSTALLED. NO WASHER P/N STD 2197 BETWEEN NUT P/N STD 1420 AND FACE OF BOSS ON MOUNT P/N LW-1	8302 (SUPPORT ASSY) ON BOLT P/N LW-31S4.44.  NO TORQUE ON NUT AND BOLT ASSY.  CAUGHT IN TIME, NO SIGNIFICANT FRETTTING O	N SUPPORT BOSS OR ON  DYNAFOCAL MOUNT BRACKET.  (X)			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000113000008	20001130	00008	EA  	2000	11	30	CA000920012      	2	20000811	G	7313	25245008R	INJECTOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENGINE	DIRTY           	W				C	D	 	 	ABORTED TAKEOFF         	RETURN TO BLOCK         			R	 	 	PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				481  		65298					(CAN) 1. RIGHT ENGINE DEVELOPED ONLY 2300 RPM AT MAX  M.P. ON TAKEOFF.  COULD NOT DUPLICATE ON GROUND RUN.  INVESTIGATED	 ENGINE AND PROP SYSTEMS.  FUEL SERVO FUEL INLET SCREEN SHOWED SMALL PARTICLES.  CLEANED.  FUEL SYSTEM - AIRCRAFT - MAIN	 BOWL SCREEN SHOWED SMALL PIN HEAD PARTICLES - NO IMPORTANT QUANTITY.  RT FUEL TANKS DRAINED - CLEAR.  GROUND RUN AND RE	TURNED TO SERVICE.  REF:  SEE ALSO SDR CA00920014.  (X)			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000113000009	20001130	00009	EA  	2000	11	30	CA000920013      	2	20000811	G	7322		SERVO           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					FUEL TANK CAP	INTERFERENCE    	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA											(CAN)  RECENTLY REMOVED AS UNSCHEDULED, A FUEL SERVO FROM THE A/C ENGINE FUEL INJECTION SYSTEM, AS MIXTURE WOULD NOT CLO	SE PROPERLY.  TEAR DOWN INSPECTION:  OVERHAULER INFORMED US HE HAD FOUND SMALL PARTICLES OF BLUE THIN PLASTIC-PAPER IN S	CREEN AND UNDER MIXTURE INTERNALMACHANISM.  IDENTIFIED TO OCTANE RATING DECAL OF PLACARDS, SOLD AT LARGE ON THE AVIATION	 MARKET.  REFUELERS DRAG THE REFUELING NOZZLE OR/AND FUEL CAPS ON DECAL AND TEAR SMALL PIECES THAT GOES INTO THE TANKS; 	HENCE, INJECTOR PROBLEMS AND FUEL DRAIN COCKS PROBLEMS.  REMOVED AND INSTALLED PROPER RECTANGULAR PLACARDS - ABOVE FUEL 	FILLERS.  (X)	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000113000010	20001130	00010	EA  	2000	11	30	CA000920014      	2	20000816	G	7414	1068291018	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RT ENGINE	MISINSTALLED    	W				A	 	 	 	UNSCHED LANDING         				W	R	 	INADEQUATE Q C            	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA				484  		8010918					(CAN)  FUEL SYSTEM CONTAMINATION.  LEAVING GROUND ON TAKEOFF, RT ENGINE AGAIN SURGED, COMMITTED TO CONTINUE TAKEOFF - PI	LOT COMPLETED CIIRCUIT BACK TO BASE.  NOTE:  SINCE LAST REPAIR; CLEANING FUEL, A/C HAD FLOWN TWICE FOR 3-4 HOURS , NO IN	CIDENT.  AGAIN, FOUND SOME LEFT OVER PARTICLES IN FUEL.  AFTER REPAIRS:   RUN-UP OK, BUT AMES EXPERIENCED EARS DETECTED 	SOME PUFFING UNEVEN.  MAGNETO TIMING CHECKED:  SHOWED (DUAL MAG) 17 - 15 DEGREE BTDC.  RETIMER:  LT AT 20 DEGREES  PER M	AN. GIVING RT 18 DEGREES IN LIMITS OF 3 DEGREES.  REPLACED LOWER PLUGS.  GROUND RUN OK.  AIRCRAFT IN-FLIGHT  AT THIS TIM	E.  (X)	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000113000011	20001130	00011	EA  	2000	11	30	CA000920015      	2	20000815	G	8520	75060	BOLT            	LYC         	LW10646     	BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					SHANK	SHEARED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			T	E	E	ENGINE CASE PENETRATION   	VIBRATION/BUFFET          	VIBRATION/BUFFET          	CR	CRUISE         	1			CA			1993 								(CAN) THE NR 3 CYLINDER CONNECTING ROD BOLT FAILED DUE TO FATIGUE, OR DEFECTIVE MATERIAL.						1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2000113000012	20001130	00012	EA  	2000	11	30	CA000921002      	1	20000625	G	2700	C3CF2179	CABLE           			DHAV  	DHC3  	DHC3        	2800202	EA  										FLAP CNTRLS	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT SUNK IN SALT WATER ON A MOORING IN NAIN LABRADOR.  AIRCRAFT SALVAGED AND FLOATED.  AIRCRAFT FLUSHED WITH 	FRESH WATER, INSTRUMENTS CHANGED,  ENGINE COMPONENTS CHANGED, AIRCRAFT READIED FOR FERRY FLIGHT USING PROCEDURES IN ACCO	RDANCE WITH CARS 625 APP. G.  CORROSION FOUND (SEVERE) IN FOLLOWING BELLCRANKS - FLAP CONTROLS, AILERON AND RUDDER CONTR	OLS.  P/N''''S AFFECTED AND REPLACED BEFORE FLIGHT:  (1).  C3CF217-9.  (2).  C3CF217-10.  (3).  C3CF218-9. (4). C3CF218-	10.   (5).  C3CF40-116.  C3CF77-5 7.  C3CF37-5.  (X)		1	H	7	1 	3R			 	A815    					 
2001030900001	20010309	00001	SO  	2001	3	9	CA000921003      	1	20000808	G	3246	16200600	WHEEL           			PIPER 	PA22  	PA22135     	7102206	SO  	LYC   	O320  	O320B2A     	41508	EA  					MLG	CRACKED         	W				K				NONE                    				D			INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			2556 								(CAN) WHEEL HALF DISCOVERED WITH A PIECE MISSING AND THE WITH TIRE & TUBE BULGING OUT IN THAT AREA.						1	H	7	1 	3O	3	O	 	1A6     	E274				 
2001030800027	20010308	00027	EA  	2001	3	8	CA000921004      	2	20000808	G	7300	3032125	LINE            	PWA         	PT6A65B     	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					P3	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				5600 		PCE32182					(CAN) ENGINE WENT TO FLIGHT IDEL JUST AFTER TAKE OFF ALONG WITH RESULTANT AUTOFEATHER AFTER TORQUE DROPPED BELOW 250 LBS	. P3 LINE CRACKED AT FLARE.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001030800028	20010308	00028	SW  	2001	3	8	CA000921005      	1	20000814	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS ON FORE AND AFT OUTER DISC SEGMENTS.   INSTALLED AT 1202.8 HOURS, DECEMBER 12, 1999.  NR 7 BEARING  INSTALL	ED AT 1060.2 HOURS, SEPTEMBER 17, 1999.  NR 3 BEARING (UNDER OIL COOLER).					1	G	7	1 	3U			O	H2SW    					 
2001030800029	20010308	00029	SW  	2001	3	8	CA000925002      	1	20000605	G	2810	50061530000001	FUEL TANK       			KAMOV 	KA32  	KA32A1      	       	SW  										FUSELAGE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			5311 								(CAN) FUEL LEAK.NOTE: TANK P/N 500.6154.000.001 S/N 9106808 WAS REPLACED (CHAFED),  ALSO BECAUSE IT IS INTER-CONNECTED T	O TANK P/N 500.6153.0000.001.					1	G	7	2 	4U			NC	        					 
2000101600355	20001016	00355	SW  	2000	10	16	CA000925003      	1	20000512	G	6220	D2B211002	BEARING         		D2B200000B  	KAMOV 	KA32  	KA32A1      	       	SW  										FLAP HINGE BRG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			887  			920018					(CAN) ROTOR SYSTEM VIBRATION, METAL NOTICED IN OIL AT OIL CHANGE MAINTENANCE.						1	G	7	2 	4U			NC	        					 
2000101600356	20001016	00356	SW  	2000	10	16	CA000925004      	1	20000512	G	6320	BP252	GEARBOX         			KAMOV 	KA32  	KA32A1      	       	SW  										MAIN GEARBOX	CONTAMINATED    	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			CA			971  			0703003					(CAN) METAL CONTAMINATION:  THREE CONSECUTIVE CHIP LIGHTS,  GEARBOX REMOVED.  (X)						1	G	7	2 	4U			NC	        					 
2000113000013	20001130	00013	CE  	2000	11	30	CA000925005      	1	20000731	G	3230	MC815AS1	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MOTOR CONTROLLER	STUCK           	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) LANDING GEAR WOULD NOT RETRACT WHEN SELECTED.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000101600357	20001016	00357	NE  	2000	10	16	CA000925006      	2	20000809	G	7321	216062022	FUEL CONTROL    	LYC         		BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					N2 GOVERNOR	WORN            	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			5283 	1801 							(CAN) PERIODIC ENGINE N2 DROOP WITH POWER APPLICATION WITH SLOW RECOVERY WAS REPORTED.  DURING SUBSEQUENT TROUBLESHOOTIN	G, N2 DROOPED WITH NO NR RECOVERY UNTIL COLLECTIVE WAS CYCLED SEVERAL TIMES.  N2 LEVER ON FUEL CONTROL UNIT APPEARS TO B	E ROUGH WHEN CYCLED BY HAND. THE NOTED FCU WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT.  (X)				2	G	7	1 	4U	4	U	 	H6SW    	E4NE				 
2001030800030	20010308	00030	NE  	2001	3	8	CA000925007      	2	20000815	G	8520		BEARING         	PWA         	WASPCB3     	DOUG  	DC6   	DC6A        	3021706	WP  	PWA   	R2800 	CB3         	52026	NE  	HAMSTD	43E	43E60       	NE  	MASTER ROD	FAILED          	W				D		 	 	RETURN TO BLOCK         				Y	 	 	ENGINE STOPPAGE           			TO	TAKEOFF        	1			CA				1038 		55249					(CAN) ON TAKEOFF ENGINE AUTO-FEATHERED, AND LOAD OF RETARDANT WAS JETTISONED. AIRCRAFT RETURNEDTO  AIRPORT WITH THREE EN	GINES OPERATIVE. INSPECTIONS COMPLETED - I.E. NOSE CASE REMOVED AND CHIPPED TEETH FOUND ON COUNTER BALANCE DRIVE GEARS A	ND THE SUPPORT BEARING WAS FOUND CRACKED. ENGINE WAS RE-ASSEMBLED FOR THREE ENGINE FERRY. NOSE CASE WAS AGAIN REMOVED TO	 DETERMINE EXTENT OF DAMAGE. DAMAGE FOUND INDICATED A MASTER ROD BEARING FAILURE WHICH RESULTED IN THE MASTER ROD COMING	 LOOSE AND DAMAGING THE REAR CYLINDERS. SERVICEABLE ENGINE INSTALLED AND AIRCRAFT DISPATCHED FOR FIRE FIGHTING.		2	L	7	4 	4R	4	R	 	6A3     	E264	6	C	P871	 
2001030800031	20010308	00031	WP  	2001	3	8	CA000925008      	1	20000826	G	2752	5363998403	BRACKET         			DOUG  	DC6   	DC6A        	3021706	WP  						HAMSTD	43E	43E60       	NE  	ACTUATOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING THE ROUTNE A INSPECTION THE OUTBOARD FLAP ACTUATOR ATTACHMENT ARMS WERE FOUND BROKEN. THE AIRCRAF	T WAS GROUNDED UNTIL THE FLAP WAS REPLACED. PARTS ARE BEING SHIPPED BACK TO CONAIR FOR INSPECTION.ALL ACTIVE AIRCRAFT IN	SPECTED AND FOUND SERVICEABLE.				2	L	7	4 	4R			 	6A3     		6	C	P871	 
2001030800032	20010308	00032		2001	3	8	CA000925009      	4	20000901	G	3414	4039891903	INDICATOR       	HONEYWELL   		BOEING	767   	7673S1      	1385211	NM  										COCKPIT	FAILED          	W				C		 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA			32336	897  		89031649					(CAN) FIRST OFFICERS AIRSPEED FAILED AT 60 KNOTS ON TAKEOFF ROLL. REJECTED TAKEOFF AT 100 KNOTS. FIRST OFFICERS AIRSPEED	 INDICATOR REPLACED . WHEELS AND TIRES INSPECTED AS PER FLYAWAY MANUAL 2.02-05.02, DUE RTO, NO DAMAGE FOUND, BRAKE TEMP 	INDICATIONS NORMAL.				2	L	7	2 	4F			RT	A1NM    					 
2001030800033	20010308	00033	NM  	2001	3	8	CA000925010      	1	20000901	G	5280		DOOR            	BOEING      	767375      	BOEING	767   	767375      	       	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					RT MLG DOOR	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA						24083					(CAN) AIRCRAFT DEPARTED, CDL32-12A APPLIED PIOR TO DEPARTURE DUE R/H GEAR TRUNNION DOOR DAMAGE. CDL INDICATED A MINOR AI	RCRAFT WEIGHT PENALTY. VMO/MMO SWITCH PLACED IN ALTERNATE POSITION DUE CDL. ON AKEOFF, (APPROX 250 KTS) OVERSPEED AURAL 	WARNING AND BARBER POLE WARNINGS INDICATED. FLIGHT CREW CONTACTED DISPATCH AND MOC, IT WAS NOTED THAT WITH VMO/MMO SWITC	H IN ALTERNATE POSITION SPEED IS LIMITED TO 260 KTS. DECISION WAS MADE TO RETURN, DUE SPEED RESTRICTIONS ON AIRSPEED IN 	CRUISE. AIRCRAFT LANDED YVR NORMALLY. DOOR REPAIRS COMPLETED AS PER LOG SEQUENCE 0304937. OVERWEIGHT LANDING CHECK COMPL	ETED AS PER FLYAWAY MANUAL..	2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000101600358	20001016	00358	NE  	2000	10	16	CA000925011      	1	20000816	G	6410	S611730101045	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					TAIL ROTOR BLADE	CRACKED         	W				K	 	 	 	NONE                    				P	 	 	NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA			18854			61VR18181785					(CAN) THE T/R SPINDLE INSPECTION WAS BEING C/O AT WHICH TIME A CRACK IN THE SKIN OF THE TAIL ROTOR BLADE WAS DISCOVERED.	  THE BLADE WAS REMOVED FROM SERVICE AND  IMMEDIATELY  SENT BACK TO THE MANUFACTURER FOR REPAIR EVALUATION.  (X)					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2000101800126	20001018	00126	NE  	2000	10	18	CA000925012      	1	20000818	G	6320	S613520670	GEARBOX         	SKRSKY      	S61352060004	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					M/R TRANS	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			NR	NOT REPORTED   	1			CA				97   		A14D2667789					(CAN) OIL LEAK WAS DETECTED ON RIGHT HAND FORWARD SIDE OF MAIN GEARBOX.  AFTER FURTHER INVESTIGATION, FOUND THERE WAS A 	CRACK IN THE LOWER HOUSING ASSY.  THE CRACK WAS 2.75 INCHES LONG AND LOCATED APPROXIMATELY 4 INCHES ABOVE AND FORWARD OF	 THE FORE AND AFT SERVO BRACKET.  THE AIRCRAFT WAS THEN GROUNDED AND THE GEARBOX ASSY WAS REMOVED AND SENT FOR REPAIR.  	(X)			2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2000101900278	20001019	00278	NE  	2000	10	19	CA000925024      	1	20000905	G	2910	7665104001051	HYDRAULIC LINE  			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					MAIN HYD SYS	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) PRIOR TO TAKEOFF,  NR 1 SERVO JAM LIGHT CAME ON.  NR 1 HYDRAULIC SYSTEM LEVEL HAD DROPPED TO THE REFILL LINE AND A	CTIVATED THE LOW LEVEL SWITCH. AFTER REMOVAL OF T/R COWLS, HYD FLUID WAS WIPED UP BUT NO CRACK COULD BE SEEN - FLUID LEV	EL WAS TOPPED UP AND A/C WAS GROUND RUN AT 3000 PSI.  FLUID WAS LEAKING FROM HYD LINE AT 6 INCHES FROM T/R SERVO.  LINE 	WAS CHANGED AND GROUND RUN CHECKED SERVICEABLE.  (PORUS SECTION WHERE LEAK IS, IS NOT VISIBLE TO NAKED EYE).  (X)			1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001011105596	20010111	05596	NM  	2001	1	11	CA000925025      	1	20000820	G	2750		CONTROL UNIT    	BOEING      	767375      	BOEING	767   	767375      	       	NM  										TE FLAPS	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA						25120					(CAN) A/C 641, AUG 20/2000, FLT 30, LOG SEQUENCE 0225444. AT APPROXIMATELY 14,000 FEET, LEADING EDGE SLAT ASYMMETRY WARN	ING ILLUMINATED ON EICAS, FLAP POSITION NEEDLE INDICATED BETWEEN 1 UNIT AND UP. RETURNED TO PEK. BITE CHECK COMPLETED ON	 PSEU, NIL FAULTS INDICATED. SLATS AND FLAPS EXTENSION CHECKED SEVERAL TIMES NO FAULTS FOUND. COCKPIT INDICATION CHECKED	 OK.			2	L	7	2 	4F			RT	A1NM    					 
2000101900279	20001019	00279	SW  	2000	10	19	CA000925028      	1	20000818	G	6310	206040106003	SPRING          	BELL        	206040015103	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R DRIVE SHAFT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10443			AMN52117					(CAN) 600/YEARLY INSPECTION BEING CARRIED OUT ON MAIN DRIVESHAFT.  UPON REMOVAL OF COUPLING CAP, FOUND SPRING BROKEN IN 	A DOZEN PIECES.  THE PIECES DAMAGED THE INNER COUPLING RENDERING IT UNSERVICEABLE. THE CAP, SPRING AND INNER COUPLING WE	RE SCRAPED.  (X)				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000102000042	20001020	00042	SW  	2000	10	20	CA000925029      	1	20000830	G	6330	212040106103	MOUNT           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					M/R TRANSMISSION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IN THE PROCESS OF CHANGING WEAK TRANSMISSION LORD MOUNTS, FOUND A CRACKED LIFT LINK (FITTING) MOUNT.  THE RIGHT FO	RWARD EAR WAS CRACKED. THE FITTING IS ON THE TRANSMISSION. THE DAMPERS WERE WEAK ALSO.   (X)					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000102700108	20001027	00108	SW  	2000	10	27	CA000925030      	1	20000911	G	6720	206010793101	PITCH LINK      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ROD END BRG WALL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DISCOVERED DURING DAILY INSPECTION.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000113000014	20001130	00014	CE  	2000	11	30	CA000925032      	1	20000911	G	2750	0512128	PULLEY BRACKET  			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  					UNDER FLOOR	BROKEN          	W				O		 	 	OTHER                   				F	I	 	FLT CONT AFFECTED         	FLT. ATTITUDE INST.       		AP	APPROACH       	1			CA			5742 								(CAN) A BROKEN FLAP CONTROL CABLE  PULLEY BRACKET CAUSED THE RIGHT FLAP EXTEND CABLE TO GO SLACK, RESULTING IN THE RIGHT	 FLAP PANEL PARTIALLY RETRACTING.  THE AIRCRAFT EXPERIENCED AN UNCOMMANDED ROLL TO THE RIGHT AND THE PILOT HAD TO RETRAC	T THE FLAPS TO RECOVER A LEVEL FLIGHT ATTITUDE. THE PILOT THEN CARRIED OUT AN UNEVENTFUL FLAPLESS LANDING.  (X)				1	H	7	1 	3O	3	O	 	5A6     	E273				 
2000113000015	20001130	00015	SO  	2000	11	30	CA000925033      	2	20000823	G	8530	642167A1	CRANKCASE       	CONT        	IO470S      	CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	D2A34C49    	GL  	LTCRANKCASE	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				1202 		CSIO23832S					(CAN) OIL LEAK TRACED TO CYLINDER HOLD DOWN AREA OF NR 2 CYLINDER.  LARGE CRACK FROM 3 O''CLOCK POSITION.  NR 2 CYLINDER	 UP TO 11 O''CLOCK.  (X)					1	H	7	1 	3O	3	O	 	3A21    	3E1	5	C	P3EA	 
2000113000016	20001130	00016	NE  	2000	11	30	CA000925034      	2	20000826	G	7322	P19248	HOUSING         		A302503     	GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985AN14B   	52008	NE  					BLW THRTLE SHAFT	CRACKED         	W				K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA				705  		5715901					(CAN) CRACK LINE DEVELOPED AT MIXTURE ADJUSTING LEVER ONE INCH BELOW THE THROTTLE SHAFT AND PROPAGATED IN A HORIZONTAL D	IRECTION AROUND THE CIRCUMFERENCE OF THE THROTTLE BODY UNIT.  ENGINE DEVELOPED AN IDLING PROBLEM AND ON INSPECTION, CRAC	K FAULT WAS DETECTED.  SUBMITTER SUSPECTED THE FAULT CAUSE TO BE CASTING FLAW OR MECHANICAL DAMAGE.  CARBURETOR RETURNED	 TO OVERHAUL FACILITY FOR REPAIR AND DAMAGE INVESTIGATION.  (X)			1	H	7	2 	3R	3	R	 	TC654   	5E1				 
2001030800050	20010308	00050	EU  	2001	3	8	CA000926005      	1	20000906	G	5270	4HS26	SWITCH          	FOKKER      	A33200401   	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					AFT CARGO DOOR	MALFUNCTIONED   	W				K	 	 	 	NONE                    				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) PILOTS RPTED OUTBOUND THAT CARGO DOOR WARNING LIGHT CAME ON AT 4.4 PSI DIFFERENTIAL. A/C RETURNED & LANDED W/O INC	ID..MAINT INSP FOUND WIRING ON REAR CARGO DOOR HANDLE SWITCH CHAFED & GROUNDING OUT ON WARNING CCT. WIRING REPD IN ACCOR	D WITH APPLICABLE STANDARDS OF A/W & A/C DEEMED SERVICEABLE FOR TEST FLT. CARGO DOOR LIGHT CONTINUED TO ILLUMINATE ON TE	ST FLT - A/C RETURNED TO BASE & LANDED W/O INCID..MAINT REPLD REAR CARGO DOOR HANDLE SWITCH & GROUND PRESSURIZED A/C TO 	6.6 PSI DIFFERENTIALWITH NO FAULTS TO RPT. TEST FLT SUCCESSFULLY COMPLETED. A/C RT-SRV WITH NO FURTHER INCID. TO RPT.		2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2000113000017	20001130	00017	EU  	2000	11	30	CA000926006      	1	20000910	G	2752	951D10011	ACTUATOR        			PILATS	PC12  	PC1245      	       	EU  										FLAP ACTUATOR	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			302  			0186AB					(CAN) ON INSPECTION, THE BACKLASH WAS FOUND EXCESSIVE.  (X)						1	L	7	1 	3T			RT	A78EU   					 
2001030800051	20010308	00051	EU  	2001	3	8	CA000926007      	1	20000801	G	3246	AH52689	WHEEL           			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEEL DISASSEMBLED FOR TIRE REPLACEMENT NOTED TO HAVE IMPACT DAMAGE 70.032 IN AND GAUGE AROUND WHEEL BEARING BOSS.	 IMPACT DAMAGE BEYOND LIMITS. WHEEL SCRAPPED. APPEARS TO HAVE BEEN CAUSED BY BRAKE ASSY - NO OBVIOUS DEFECTS.					2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
2000113000018	20001130	00018	EA  	2000	11	30	CA000926008      	1	20000820	G	2711	C6CW10861	SLEEVE          			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3T*      	GL  	SWAGED AREA	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOMBARDIER NOT IN COMPLIANCE WITH AIRWORTHINESS DIRECTIVE CF-80-03R.  SLEEVE MISSING FROM SWAGED AREA OF ROD ENDS.	  ROD PURCHASED NEW AS A SPARE PART.  (X)					1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2000112100001	20001121	00001	NE  	2000	11	21	CA000926011      	2	20000509	G	7320	117024093	REGULATOR       			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					FUEL REGULATOR	FAILED          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			HO	HOVERING       	1			CA						702AS9102					(CAN) - BLEED BAND OPENED WITH COLLECTIVE PITCH UP AND TORQUE INDICATOR SPIKED AND N1  SPOOL UP.  BLEED BAND WOULD NOT C	LOSE.  N1 TOPPED UP AND TORQUE STAYS LOW.  REPLACED BLEED BAND ACTUATOR WOULD NOT SOLVE PROBLEM.  PROBLEM WAS FIXED WITH	 REPLACEMENT OF  FUEL REGULATOR .  (X)				1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2000112200001	20001122	00001	SW  	2000	11	22	CA000926012      	1	20000511	G	7332	8G506	SWITCH          			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					FUEL PRESS SW	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			IN	INSP/MAINT     	1			CA						6044					(CAN)  FUEL PUMP CAUTION LIGHT ILLUMINATED AFTER REPLACING FUEL REGULATOR.  REPLACED PRESS SWITCH.  CHECKED THIS SWITCH.	  CIRCUIT WAS CLOSED WITH PRESSURE.  (X)					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001030800053	20010308	00053	SO  	2001	3	8	CA000926013      	2	20000626	G	8530	GO300D	ENGINE          			CESSNA	172   	P172D       	2072202	CE  	CONT  	O300  	GO300E      	17022	SO  	MCAULY	1B175	1B175*      	GL  	ENGINE BAY	FAILED          	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA			2055 	3    							(CAN) - ENGINE INSTALLED AFTER OVERHAUL  GROUND RUNS COMPLETED, STATIC R.P.M., 0.1 PRESSURE AND OIL TEMPERATURE NORMAL, 	 ENGINE CONTROLS FUNCTIONING NORMAL.- FIRST FLIGHT WAS APPROXIMATELY 12 MINUTES AIR TIME AND SEEMED TO RUNSMOOTHLY. - SE	COND FLIGHT WAS CONDUCTED AND AIRCRAFT STARTED TO MAKE NOISES AND  VIBRATE DURING THE LEFT TURN OUT FROM THE CIRCUIT. SH	OT DOWN WAS  COMPLETED AND PILOT WAS ABLE TO LAND AT AIRPORT. -  ENGINE INSPECTION FOUND CENTRE CYLINDER ON PASSENGER SI	DE, PISTON NOT MOVING. ENGINE REMOVED.		1	H	7	1 	3O	3	O	 	3A17    	E298	5	N	P857	 
2000113000019	20001130	00019	CE  	2000	11	30	CA000926014      	1	20000824	G	2434	991059111	ALTERNATOR      			CESSNA	172   	172R        	2072401	CE  										ALTERNATOR	SEIZED          	W				K	 	 	 	NONE                    				B	H	 	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA			1249 			A129346					(CAN) ALTERNATOR SEIZED.  BELT PULLEY SHEARED FROM MAIN DRIVESHAFT.  (X)						1	H	7	1 	3O			NT	3A12    					 
2000113000020	20001130	00020	CE  	2000	11	30	CA000926015      	1	20000906	G	2750	65651203CR	CONTROL CABLE   			CESSNA	500   	560CESSNA   	2076750	CE  										TE FLAP	BROKEN          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			CA			5936 								(CAN) ON SELECTING FULL FLAPS, PILOT NOTED THAT HYDRAULIC PRESSURE LIGHT DID NOT EXTINGUISH AFTER FLAPS REACHED FULL POS	ITION.  DURING TAXI FOLLOWING LANDING, WHEN PILOT SELECTED TAKEOFF AND APPROACH POSITION, FLAP INDICATOR WOULD NOT RESPO	ND.  AFT FLAP PRE-SELECT CABLE FOUND BROKEN AT ZONE 272.  (X)				2	L	7	2 	4F			RT	A22CE   					 
2000113000021	20001130	00021	SO  	2000	11	30	CA000926016      	1	20000710	G	5313	9947008	SKIN            	PIPER       		PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360KB  	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	INTEGRAL STRINGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9264 			348233048					(CAN) WHILE CARRYING OUT SB 856 (STABILATOR ATTACH FITTING CORROSION INSPECTION), NOTED THAT THE LOWER RIGHT INTEGRAL ST	RINGER ON SKIN P/N 99470-08 WAS CRACKED COMPLETELY THROUGH.  WHEN THE STABILATOR WAS MOVED FORE AND AFT, THERE WAS CONSI	DERABLE MOVEMENT IN THE AREA THAT WAS CRACKED.  POSSIBLE CAUSE FOR CRACK - DUE TO THE  STEEL BRACKET AND EXTRUDED ANGLE 	NOT BEING TIED TOGETHER MAKING THE AREA IN BETWEEN WEAK.  THIS AREA WAS REPAIRED BY INSTALLING AN .063 INCH ALUMINUM ANG	LE TO TIE THE ATTACH FITTING AND THE EXTRUDED ANGLE TOGETHER PER APPROVED ENGINEERING DRAWINGS.   NOTE:  LT SKIN WAS NOT	 CRACKED, BUT WAS REPAIRED THE SAME TO PREVENT FURTHER CRACKS.  (X)	1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2000112200002	20001122	00002	SW  	2000	11	22	CA000926017      	1	20000914	G	6510	327211	DISC PACK       	BELL        	327211      	BELL  	206   	206BELL     	1181502	SW  	ALLSN 	250C  	250C20      	03013	GL  	MCAULY	D3A34	D3A34C402   	GL  	T/R DRIVE	MISINSTALLED    	W				O	 	 	 	OTHER                   				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSPECTING A NEW PART PRIOR TO INSTALLATION, IT WAS NOTED THAT INDIVIDUAL DISCS WERE NOT CORRECTLY STACKED P	ER BELL 206 MAINTENANCE MANUAL (FIGURE 65-6, PARAGRAPH 65-19 CAUTION COPY ATTACHED.) THE NOTE ATTACHED TO THE DISC SET S	TATES THAT THEY MUST BE INSTALLED AS ONE UNIT EXACTLY AS PACKED.  THREE DISC PACKS WERE FOUND MIS-STACKED.  (X)				1	G	7	1 	3U	3	U	 	H2SW    	E4CE	5	C	P47GL	 
2000113000023	20001130	00023	CE  	2000	11	30	CA000927003      	1	20000831	G	3231	08411065	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ACTUATING ARM	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER LANDING, PILOT NOTICED THAT THE GEAR DOOR ON THE LEFT MAIN WAS HANGING DOWN.  AIRCRAFT WAS PLACED ON JACKS A	ND GEAR DOOR BELLCRANK WAS FOUND TO BE BROKEN.  PART WAS REMOVED AND NEW PART INSTALLED.  GEAR SWING WAS COMPLETED 5 TIM	ES AND GEAR DOOR WORKED CORRECTLY.  COULD NOT DETERMINE WHY THE PART HAD BROKEN.  THERE WAS NO EVIDENCE OF DAMAGE TO THE	 ASSEMBLY.  (X)			1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2000113000024	20001130	00024	NE  	2000	11	30	CA000927004      	2	20000828	G	7321	324476812	FUEL CONTROL    	PWA         		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FUEL CNTRL UNIT	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				E	 	 	VIBRATION/BUFFET          			AP	APPROACH       	1			CA			2275 			PCE94483					(CAN) UPON APPROACH TO YRT, PILOTS DISCOVERED NR 1 ENGINE WOULD NOT RESPOND TO POWER LEVER COMMANDS.  AS A RESULT, THE P	ILOTS HAD TO SHUT DOWN NR 1 ENGINE TO LAND.  FCU WAS REPLACED.  ENGINE GROUND TESTED SERVICEABLE.  (X)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2000120600029	20001206	00029	CE  	2000	12	6	CA000927006      	1	20000827	G	2750	51152531	SHAFT           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	SIDE OF ACTUATOR	LOOSE           	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) THE FLAPS WOULD NOT MOVE DURING TAXI.  PILOTS WERE ADVISED TO ENSURE THE FLAPS WERE RETRACTED, PULL AND SECURE THE	 FLAP CIRCUIT BREAKER, AND RETURN TO MAINTENANCE FLAPLESS FOR REPAIRS. MAINTENANCE FOUND THE INPUT ROD OR SHAFT THAT MOV	ES THE CAM TO THE UP OR DOWN LIMIT SWITCH WAS LOOSE AND SLIPPING. THIS CAUSED THE FLAPS TO OVER RETRACT, CAUSING PULLEY 	PIN FAILURE ON THE ACTUATOR CHAIN GEAR, AND A PULLEY BRACKET TO BE  DAMAGED.  THE NECESSARY REPAIRS WERE MADE TO THE BRA	CKET BY REPLACING THE BRACKET.  INSPECTION OF FLAP ACTUATOR, FLAP CABLES, AND FLAP LINKS WAS CARRIED OUT.  THE FLAPS WER	E RERIGGED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (X)	1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001032900049	20010329	00049	CE  	2001	3	29	CA000927008      	1	20000829	G	5753		FLAP TRACK      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	RT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5667 								(CAN) THE ATTACHING PART BETWEEN THE FLAP TRACK AND LOWER WING SKIN WAS FOUND CRACKED DURING A ROUTINE INSPECTION. UPON 	INSPECTION OF ANOTHER AIRCRAFT OF THE SAME MODEL IT WAS FOUND THAT REINFORCING PART  WERE NOT INSTALLED AT THE FACTORY O	N SUBJECT AIRCRAFT.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001031900163	20010319	00163	SO  	2001	3	19	CA000927009      	2	20000831	G	7310		LINE            			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					FUEL SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING GROUND HANDLING FUEL LEAK ON LT ENGINE WAS OBSERVED. FURTHER INVESTIGATION REVEALED THAT FUEL LINE BETWEEN 	FCU AND FUEL LIMITER WAS CHAFED THROUGH. TEMPORARY REPAIR TO FLY AIRCRAFT BACK TO HOME BASE. AT HOME BASE FUEL LINE REPL	ACED BY NEW AND AIRCRAFT RETURNED TO SERVICE.ASSUMED REASON FOR DAMAGE: DISLOCATION DUE TO BROKEN BRACKET ON FUEL LIMITE	R (REPLACED AS WELL), RESULTING IN CHAFING CONTACT WITH AIR BOX.			1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2000120600030	20001206	00030	SO  	2000	12	6	CA000927011      	1	20000902	G	7603	S18193	ROD END         	PWA         		CURTIS	C46   	C46AAIRLIFT 	       	SO  	PWA   	R2800 	R280051     	52026	NE  					THROTTLE LINKAGE	WORN            	W				C	E	 	 	ABORTED TAKEOFF         	ENGINE SHUTDOWN         			O	 	 	OTHER                     			TO	TAKEOFF        	1			CA						FPO65143					(CAN) DURING TAKEOFF OUT OF SANDY LAKE, THE PILOT NOTICED NR 1 THROTTLE SETTING LOOSE.   HE ABORTED THE TAKEOFF AND SHUT	 DOWN THE ENGINE.  UPON INSPECTION, IT WAS FOUND THAT THE JAM NUT CAME LOOSE, AND WORE THE THREADS OUT OF THE ROD END.  	(X)				2	L	7	2 	4R	4	R	 	3A2     	5E8				 
2000120600031	20001206	00031	CE  	2000	12	6	CA000927012      	1	20000903	G	5740	6147514435	WASHER          	BEECH       		BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					PRELD INDIC RING	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						B149					(CAN) WHILE REASSEMBLING THE WING FOLLOWING INSPECTION IN ACCORDANCE WITH CF-81-25R5, A NEW PRELOAD INDICATING WASHER AS	SY INSTALLED ON THE LT LOWER FORWARD WING BOLT INDICATED THE BOLT WAS TORQUED AT AN ABNORMALLY LOW TORQUE. THE BOLT WAS 	UNDONE AND THE WASHER KIT FURTHER EXAMINED.  THE INNER RING WAS FOUND TO BE THINNER THAN THE INDICATOR RING CAUSING THE 	INDICATOR RING TO INDICATE THE BOLT WAS TORQUED AS SOON AS THE NUT CONTACTED THE WASHER ASSY, BEFORE ANY TORQUE WAS APPL	IED.  PART WAS RECEIVED WITH P/N 8130 FORM FROM RAYTHEON AIRCRAFT.  (X)		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000120600032	20001206	00032	CE  	2000	12	6	CA000928002      	1	20000901	G	6100		PROPELLER       	MCAULY      		CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101HCM    	GL  	L. EDGE & FACE	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				5227 		G11772					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001032900050	20010329	00050	SW  	2001	3	29	CA000928004      	1	20000901	G	6320	206075660001	LINE            			BELL  	206   	206L        	1181522	SW  										M/R GEARBOX	CHAFED          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) PILOT LANDED & SHUT DOWN NORMALLY. HE THEN NOTICED FLUID RUNNING DOWN SIDE OF FUSELAGE. INVESTIGATION REVEALED THA	T LEAKING OIL WAS COMING FROM THE MGB OIL PRESSURE INDICATING LINE, LOCATED UNDER THE TRANSMISSION RESTRAINT. THE CHAFIN	G OF THE FOIL FLEX LINE GOING TO THE FREEWHEELING UNIT LIKELY CAUSED THE OIL PRESSURE INDICATING LINE TO FAIL AND LEAK O	IL. THE LINE WAS REPLACED. THE DG CLAMPS ATTACHING THE OIL FLEX LINE TO THE TRANSMISSION RESTRAINT WERE RE-ARRANGED TO G	IVE MORE CLEARANCE BETWEEN THE TWO LINES. THE OIL LEVEL WAS ADJUSTED, THE HELICOPTER WASHED, GROUND RUN AND RETURNED TO 	SERVICE.	1	G	7	1 	3U			 	H2SW    					 
2001040300037	20010403	00037		2001	4	3	CA000928005      	4	20000906	G	3418	C6SC106027	STALL BAR       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RIGHT	DEBONDED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED MAINTENANCE CHECK,, THE RT STALL BAR WAS FOUND TO BE PARTIALLY UNGLUED. THE STALL BAR WAS REMOV	ED, CLEANED AND REBONDED AS PER DHC MAINTENANCE INSTRUCTIONS.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2001031900165	20010319	00165	NM  	2001	3	19	CA000928008      	1	20000911	G	2722	591005013	PCU             			BOEING	727   	727217      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					RUDDER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA						572					(CAN) ON SERVICE CHECK FOUND LOWER RUDDER DEFLECTED TO THE LEFT WITH ZERO INPUT, A SYSTEM PRESSURIZED. FURTHER TROUBLE S	HOOTING REVEALED LOWER RUDDER PCU BYPASSING. LOWER RUDDER PCU REPLACED AND INSTALLATION LEAK, FUNCTION INSPECTED SERVICE	ABLE IN ACCORDANCE WITH MM 27-20-141.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2001032900053	20010329	00053	NM  	2001	3	29	CA000928009      	1	20000920	G	2133	7110033	OUTFLOW VALVE   			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					CABIN PRESSURE	INTERMITTENT    	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA						168503					(CAN)   AIRCRAFT WOULD NOT PRESSURIZE AFTER TAKEOFF. OUTFLOW VALVE STUCK OPEN. ATTEMPTED STANDBY, ALSO STUCK OPEN. AC MO	DE CLOSED OUTFLOW VALVE ONLY AFTER MOVING SWITCH TO OPEN, THEN CLOSE. AUTO APPEARS TO NOT WORK. FOOUND OUTFLOW VALVE INT	ERMITTENT IN MANUAL AC/DC. OUTFLOW VALVE REPLACED PER MM 21-31-11.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000120600033	20001206	00033	CE  	2000	12	6	CA000928011      	1	20000911	G	2913	1240084CR0190	LINE            	BEECH       	9938800213  	BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  					1/2 FROM FITTIN	LEAKING         	W				A	D	 	 	UNSCHED LANDING         	RETURN TO BLOCK         			J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA						37					(CAN) HYDRAULIC POWER PACK STARTED TO CYCLE FREQUENTLY AND THE HYDRAULIC LOW LIGHT CAME ON AND STAYED ON.  HYDRAULIC CON	TROL CIRCUIT BREAKER TRIPPED.  PILOT RETURNED TO BASE AND DID A MANUAL EXTENSION AND LANDED AIRCRAFT WITH 3 GREEN.  MAIN	TENANCE FOUND LINE GOING FROM MAINTENANCE VALVE TO POWER PACK GEAR UP SIDE TO BE LEAKING.  LINE REPLACED AND CHECKED SER	VICEABLE.  (X)			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000120600034	20001206	00034	EA  	2000	12	6	CA000928012      	1	20000910	G	2730	MS206674	FITTING         		C3CF1935    	DHAV  	DHC3  	DHC3        	2800202	EA  										HOLE	INACCURATE      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE ATTEMPTING TO FIT THE ELEVATOR CONTROL CABLE TO A DHC-3T DURING A 400 HOUR INSPECTION, IT WAS FOUND THAT THE	 END FITTING ON THE NEW CABLE HAD AN INCORRECTLY SIZED HOLE. THE END FITTING HOLE IN THE ORIGINAL PART WAS 14 INCHES IN 	DIAMETER, AND THAT IN THE NEW PART SUPPLIED WAS .1875 INCH IN DIAMETER.  A NEW CABLE ASSEMBLY WAS REQUESTED.  (X)				1	H	7	1 	3R			 	A815    					 
2001032900054	20010329	00054	EA  	2001	3	29	CA000928013      	1	20000911	G	2730	C3TE134	LEVER           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					ELEVATOR	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			100  								(CAN) DURING A ROUTINE 400 HOUR INSPECTION OF THE ELEVATOR SERVO TAB, THE ENGINEER FOUND THAT THE RIVETS SECURING THE LE	VER TO THE SERVO TABLWERE LOOSE. THE ENGINEER REMOVED THE TAB, AND REPLACED THE LOOSE RIVET WITH NEW RIVETS. THE SERVO T	AB WAS REINSTALLED.				1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001032900055	20010329	00055	EA  	2001	3	29	CA000928014      	1	20000911	G	2730	AGS6052	CLAMP           			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A27      	52043	EA  					ELEVATOR	JAMMED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT THE END OF THE DAY WHEN THE PILOT WAS SECURING THE FLIGHT CONTROLS HE FOUND THAT WHEN HE PULLED THE ELEVATORS T	O THE FULL BACK POSITION, THEY WOULD STICK IN THAT POSITION. IT WAS FOUND THAT THE CLAMP THAT SECURES THE COVER TO THE E	LEVATOR TRIM JACK WAS GETTING CAUGHT ON THE ELEVATOR CONTROL LEVER. INSPECTION FOUND THAT THE IMPROPER CLAMP WAS INSTALL	ED. THE CLAMP WAS REMOVED AND REPLACED WITH THE PROPER PART. THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3T	4	T	 	A806    	E4EA				 
2000120600035	20001206	00035	SO  	2000	12	6	CA000928017      	2	20000604	G	8530	654651A8	CYLINDER        	CONT        		BEECH 	45    	A45         	1152006	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	CYLINDER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA				363  		562878					(CAN) AFTER TAKEOFF, PILOT HAD VIBRATION IN ENGINE.  RETURNED TO AIRPORT, MAINTENANCE FOUND NR 2 CYLINDER CRACKED AT SPA	RK PLUG HOLE TO EXHAUST VALVE.  CRACK APPROXIMATELY 5 INCHES LONG.  CYLINDER REPLACED WITH NEW CONTINENTAL CYCLES AND RE	TURN TO SERVICE.  (X)				1	L	7	1 	3O	3	O	 	5A3     	E5CE	5	C	P21EA	 
2000120600036	20001206	00036	CE  	2000	12	6	CA000928019      	1	20000830	G	3110		RACK            	CESSNA      	08134551    	CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470V      	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	TOP SUPRT BRCKET	CHAFED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			6471 								(CAN) UPON PERFORMING FLAIR DURING LANDING, THE PILOTS NOTICED THE ELEVATOR CONTROLS WERE FEELING A LITTLE STIFF.  UPON 	MAINTENANCE INVESTIGATION, FOUND THE RADIO IN THE CENTER INSTRUMENT PANEL (RADIO RACK) WERE SETTING DOWN AND MAKING CONT	ACT WITH THE CONTROL YOKE.  FORWARD RADIO RACK SUPPORT WAS REPAIRED, RADIO RACK WAS ADJUSTED TO PROVIDE ADEQUATE CLEARAN	CE.  CONTROLS MOVED TO EXTREMES, NO CONTACT NOTICED.  (X)			1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P22EA	 
2000120700086	20001207	00086	CE  	2000	12	7	CA000928020      	1	20000711	G	2844		FUEL LINE       	AEROQUIP    	AE7013127022	CESSNA	310   	310D        	2074212	CE  	CONT  	O470  	IO470D      	17026	SO  					AT THE FLARE	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			108  								(CAN) BOTH LT AND RT FUEL PRESSURE LINES WERE MADE LOCALLY BY OTHERS OUT OF -2 SOFT COPPER. COPPER MOST LIKELY  WORK HAR	DENED AND CRACKED.  CORRECT P/N HOSES AS ABOVE WILL NOT FIT IN AIRCRAFT AS AIRCRAFT USES -2 FITTING ON BACK OF PUMP AND 	FIREWALL.  ACCORDING TO MIL AERO, THESE HOSE ASSEMBLIES ARE -4 HOSE WITH SPECIAL -3 ENDS.  TWO HOSES WERE MADE OF AEROQU	IP 306 -2 RUBBER HOSE AND INSTALLED.  (X)			1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2001032900058	20010329	00058	CE  	2001	3	29	CA000928021      	1	20000826	G	2742	NAS56138	ROLL PIN        	CESSNA      	07125002    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					TRIM ACTUATOR	DISPLACED       	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ROLL PIN ON LEFT STABILIZER ACTUATOR SLID OUT AND GOT CAUGHT ON THE ACTUATOR HINGE ASSEMBLY. THIS PREVENTED THE ST	ABILIZER TRIM FROM MOVING. THE TRIM ACTUATORS WERE REMOVED, THE PIN RE-INSTALLED, AND LOCKWIRED. SUGGEST LOCKWIRING PINS	 IN ALL ACTUATORS.				1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2000120700087	20001207	00087		2000	12	7	CA000928022      	4	20000816	G	2562	BS2173	BATTERY         	DORNEMARGLN 	DMELT6C     	UNIVAR	415   	A2ALON      	0540102	NM  	CONT  	C90   	C9016F      	17009	SO  					BATTERY	WRONG PART      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						0006					(CAN) ELT WAS EQUIPPED WITH NON-APPROVED BATTERY MADE BY AVIAL PER B014 AIRWORTHINESS NOTICE.  AVIALL BATTERY PACK IS ON	LY APPROVED FOR DMELT 6 OR 8.  (X)					1	L	7	1 	3O	3	O	 	A787    	E252				 
2001032900059	20010329	00059	CE  	2001	3	29	CA000928024      	1	20000823	G	5347	051100014	SEAT TRACK      			CESSNA	170   	170         	2072302	CE  	CONT  	C145  	C1452       	17012	SO  	MCAULY	1A170	1A170DM     	GL  	COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2067 			18527					(CAN) DURING THE ANNUAL INSPECTION IT WAS DISCOVERED THAT THE RIGHT SIDE INBOARD SEAT RAIL HAD NUMEROUS CRACKS. SEAT RAI	L DID NOT MEET AIRWORTHINESS DIRECTIVE CF 87-15 R2CRITERIA. SEAT RAIL REPLACED WITH NEW CESSNA SEAT RAIL. RAIL SECURED U	SING INSTRUCTIONS DETAILED IN CESSNA SERVICE MANUALS AND THE AC 43-13-1B, CHAPTER 2, PARA 99, RIVETING STANDARDS.				1	H	7	1 	3O	3	O	NT	A799    	E253	5	N	P857	 
2000120700088	20001207	00088	CE  	2000	12	7	CA000928026      	1	20000626	G	3600	14953	CHECK VALVE     			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT PRESS T/CONE	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			91   								(CAN) DURING TROUBLESHOOTING EXERCISE, OPAL CHECK OF INFLATABLE DOOR SEAL CARRIED OUT.  RESULTING TEST FOUND THAT PRESSU	RE ZERO DOWNSTREAM FROM REGULATOR MEASURED AT MAIN DOOR SEAL INFLATION FITTING.  IT ALSO NOTICED THAT THE DE-ICE BOOTS W	ERE NOT INFLATING WHEN SELECTED.  WITH PRESSURE STILL APPLIED AT TEST PORT IN TAILCONE, AIR NOISE HEARD FROM LT ENGINE E	XHAUST DUCT.  DUE TO PREVIOUS SIMILAR PROBLEM (REPORTED ON SDR NR 20000713014) LT PNEUMATIC CHECK VALVE REMOVED FROM A/C	 AND FLAP PER VALVE HINGE ASSY FOUND BROKEN INSIDE VALVE BODY.  ONLY TIME THAT WOULD CAUSE SERIOUS PROBLEM IS WHEN ENGIN	E FAILURE WOULD OCCUR AND ALL OR MOST OF BLEED AIR WOULD ESCAPE TO THE FAILED ENGINE AND CHECK VALVE.  (X)	1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001032900062	20010329	00062	NM  	2001	3	29	CA000928029      	1	20000907	G	2433	10333671	BUSS TIE        		1152230     	DHAV  	DHC8  	DHC8*       	       	NM  										DC CONTACTOR BOX	OVERHEATED      	W				D	 	 	 	RETURN TO BLOCK         				H	 	 	ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA			314  			10333					(CAN) IT WAS REPORTED FROM OPERATOR AIRCRAFT RETURNED TO GATE WITH LOSS NR 1 TRU, & ANTI-ICE CAUTION LIGHTS ON. MAINTENA	NCE REPORTS, DISCOVERING SOME OVERHEATING OF BUS BAR T4 & K6, THESE PARTS & ASSOCIATED HARDWARE WERE REPLACED & AIRCRAFT	 RETURNED TO SERVICE.				2	H	7	2 	4T			RT	A13NM   					 
2000120700089	20001207	00089	CE  	2000	12	7	CA000928031      	1	20000910	G	5240	6610169311	DOOR            			CESSNA	560   	560XL       	       	CE  										BATTERY DOOR	DEPARTED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			130  								(CAN) AFTER 45 MINUTES AT CRUISE ALTITUDE 31,000 FEET, CREW HEARD LOUD BANG.  UPON LANDING,  NOTICED THAT BATTERY DOOR O	N LEFT SIDE OF A/C HAD DEPARTED.  BATTERY FLOOR LOWER OUTSIDE SKIN CREASED.  FWD HYDRAULIC BELLY PANEL HAD MINOR DING, U	NILINK COM ANTENNA CUT IN HALF, AND AFT BELLY HYDRAULIC PANEL SCRATCHED.  BOTH CREW MEMBERS HAD VISUALLY INSP BATTERY DO	OR PRIOR TO DEPARTUE AND VERIFIED THAT ALL 4 LATCHED WERE SECURED AND DOOR LOCKED IN LINE WITH BLACK LOCKED MARK.  (X)			2	L	7	2 	4F			RT	A22CE   					 
2001032900063	20010329	00063	NE  	2001	3	29	CA000928032      	2	20000908	G	7397	302114F202	WIRE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					OIL COOLER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4245 								(CAN) DURING A SCHEDULED ENGINE CHANGE, DURING CHANGE  REMOVED & PARTS/WIRING WERE TRANSFERRED TO NEW ENGINE. DURING ECU	 CHANGE THE WIRING TO FUEL OIL COOLER UNIT WAS DISCOVERED CHAGED. WIRE WAS EPAIRED IAW AMM CH20 .					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2000101800016	20001018	00016	SO  	2000	10	18	CA000928036      	2	20000814	G	8520		LIFTER          	CONT        		CESSNA	206   	U206D       	2073342	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FOLLOWING FACE	CHIPPED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						552992					(CAN) A LARGE AMOUNT OF ALUMINUM WAS FOUND IN THE OIL SCREEN.  A CYLINDER DIFFERENTIAL COMPRESSION CHECK WAS PERFORMED A	ND FOUND TO BE ALL ABOVE 70/80.  STARTER DRIVE WAS REMOVED AND INSPECTED, NO DAMAGE FOUND AT THIS TIME (SUSPECTED USING 	ONLY A BORESCOPE).  CYLINDERS 3 AND 1 WERE REMOVED FOR INTERNAL ENGINE INSPECTION.  NR 1 CYLINDER INTAKE HYDRAULIC LIFTE	R WAS FOUND TO HAVE A .25 INCH BY .25 INCH BY .0625 INCH (APPROX) CHIP OUT OF THE FOLLOWING FACE.  AT THIS POINT THE ENG	INE WAS REMOVED FOR REPAIR AT AIRCRAFT TECHNICAL CONSULTANTS. 7 A,, B AND C FOUND DURING A 50 HR OIL CHANGE.  (X)		1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2000101800022	20001018	00022	SO  	2000	10	18	CA000928037      	2	20000828	G	8520	654149	CRANKCASE       	CONT        		CESSNA	206   	U206D       	2073342	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	CRANKCASE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				720  		552992					(CAN) NR 2 MAIN BEARING HAD STARTED TO SPIN IN CRANKCASE CAUSING ALUMINUM IN FILTER.  CRANKCASE SENT OUT FOR REPAIR.  EN	GINE ASSEMBLED WITH NEW CRANKCASE.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2000101800023	20001018	00023	CE  	2000	10	18	CA000928044      	1	20000928	G	3211	998100287	BRACE           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					BRACE	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED WAS FOUND THROUGH EDDY CURRENT TESTING.  (X)						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032900065	20010329	00065	EA  	2001	3	29	CA001002002      	1	20000904	G	2740	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										STABILIZER	FAILED          	W				A		 	 	UNSCHED LANDING         				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) BOTH STABILIZER TRIM CHANNEL NR 1 AND 2 AND MACH TRIM DISENGAGED UPON LANDING.EVENT: WOULD NOT REST (LANDING WAS U	NEVENTFUL, NO EMERGENCY DECLARATION).  ON CLIMB OUT THROUGH 2000 FEET, THE STAB / MACH TRIM CAUTION MESSAGE APPEARED. RE	SET SYSTEM TWICE. RETURNED TO DEPARTURE AIRPORT, LANDING WAS UNEVENTFUL.  REPLACED THE MACH TRIM / STAB CONTROL PANEL, R	EPLACED THE STABILIZER ACTUATOR AND MCU, A/C RETURNED TO SERVICE			2	L	7	2 	4F			RT	A21EA   					 
2001032900066	20010329	00066	EA  	2001	3	29	CA001002003      	1	20000904	G	5210		SPRING          	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR ROD	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA						7145					(CAN) FLIGHT CREW REPORTED THE PRESSURIZATION VALVE ON THE MAIN CABIN DOOR WILL NOT CLOSED. MAINTENANCE FOUND THE ROD SP	RING WEAK, THEY REPLACED THE ROD ASSY.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032900067	20010329	00067	EA  	2001	3	29	CA001002004      	1	20000904	G	2910		LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) HIGH TEMP CAUTION MSG APPEARED IN FLIGHT FOLLOWED BY AN INTERMITTENT HYDRAULIC NR 2 LOW PRESSURE. MAINTENANCE REPL	ACED THE HYDRAULIC LINE TO THE EDP NR 2.					2	L	7	2 	4F			RT	A21EA   					 
2001032900068	20010329	00068	EA  	2001	3	29	CA001002005      	1	20000904	G	2740		BUSHING         			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AP PITCH TRIM MESSAGE ON EICAS, ELECTRICAL STAB TRIM OPERATED APPROX. 10 PERCENT OF THE TIME AND SOME OF THE TIME 	IN ONE DIRECTION. HORIZONTAL STAB BUSHING FOUND STIFF.					2	L	7	2 	4F			RT	A21EA   					 
2001032900069	20010329	00069		2001	3	29	CA001002006      	4	20000904	G	3418		VANE            			CNDAIR	CL600 	CL6002B19   	       	EA  										AOA	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) FLIGHT CREW REPORTED ATERNATE TAKEOFF STALL FAIL ON EICAS ALONG WITH THE SHAKER.MAINTENANCE FOUND NR 2 AOA VANE DA	MAGE. THEY REPLACED THE 2 AOA VANES AND THE STALL COMPUTER.					2	L	7	2 	4F			RT	A21EA   					 
2001031900170	20010319	00170	EA  	2001	3	19	CA001002007      	1	20000904	G	2710		PCU             			CNDAIR	CL600 	CL6002B19   	       	EA  										RT AILERON	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED THE A/C WANT TO ROLL TO THE RIGHT, REQUIRED EXCESSIVE TRIM LWD TO MAINTAIN FLIGHT LEVEL. MAIN	TENANCE REPLACED THE R/H AILERON PCU CONNECTING HARDWARE.					2	L	7	2 	4F			RT	A21EA   					 
2001032900070	20010329	00070		2001	3	29	CA001002008      	4	20000907	G	3418		TRANSDUCER      			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL SYSTEM	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF THE STALL FAIL CAUTION MESSAGE APPEARED, FOLLOWED BY THE CONFIG SPOILERS AURAL. THEY DID A REJECTED	 TAKEOFF. MAINTENANCE REPLACED THE MACH TRANSDUCER.					2	L	7	2 	4F			RT	A21EA   					 
2001031900171	20010319	00171	EA  	2001	3	19	CA001002010      	1	20000908	G	7932		PROBE           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE OIL	FAILED          	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT, ENG OIL WENT RED ON LEFT ENGINE (>165 DEG C). QRH UTILIZED AND TEMP BROUGHT BACK INTO GREEN AT A VERY	 REDUCED POWER SETTING. ITT NORMAL THROUGHOUT EVOLUTION. PRESSURE WAS LOW BUT IN NORMAL RANGE. MAINTENANCE FOUND OIL REP	LENISHMENT SYSTEM CONTINUOUSLY RUNNING OIL INTO LEFT ENGINE. DESERVICED GEARBOX & ENGINE. FOUND 8 QTS IN GEARBOX. REPLAC	ED OIL LEVEL PROBE IN OIL REPLENISHMENT SYSTEM AND A/C RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032900071	20010329	00071		2001	3	29	CA001002011      	4	20000908	G	8300	M832481910	PACKING         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 IDG	CUT             	W				C	 	 	 	ABORTED TAKEOFF         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) ABORTED TAKEOFF DUE TO THE IDG 2 CAUTION MESSAGE. MAINTENANCE FOUND AN OIL LEAK FROM THE IDG NR 2 OUT PORT CAUSED 	BY A CUT O-RING . O-RING REPLACED AND A/C RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031900172	20010319	00172		2001	3	19	CA001002012      	4	20000909	G	3418		WARNING SYSTEM  			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ACCELERATION, EICAS MESSAGE STALL FAIL APPEARED. CREW ABORTED TAKEOFF AND RETURN TO GATE FOR MAINTE	NANCE ACTION. MDC REVEALED NO ANOMALIES. STALL PROTECTION COMPUTER WAS RESET AND THE AIRCRAFT WAS RETURNED TO SERVICE WI	TH NO FURTHER ANOMALIES.				2	L	7	2 	4F			RT	A21EA   					 
2001031900173	20010319	00173	EA  	2001	3	19	CA001002013      	1	20000912	G	2910	AE7120311	LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  										HYDRAULIC SYS	CUT             	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CREW REPORTED HYDRAULIC LOW PRESSURE WARNING AND THE ZERO QUANTITY INDICATION ON THE EICAS. MAINTENANCE REPLACED H	YDRAULIC ON THE NR 2 ENGINE THAT WAS FOUND CUT.					2	L	7	2 	4F			RT	A21EA   					 
2001031900174	20010319	00174		2001	3	19	CA001002014      	4	20000912	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE POSTED ON EICAS UPON TAKEOFF. ABORTED TAKEOFF AND RETURNED TO BLOCKS. RESET STALL COMPU	TER. A/C RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032900072	20010329	00072	EA  	2001	3	29	CA001002015      	1	20000901	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT & RIGHT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS FAIL EICAS MESSAGE AFTER SWITCHING NR 2 GENERATOR ON LINE AFTER ENGINE START. FERRIED A/C TO MAIN BASE. REPL	ACED LT & RT BRAKE POSITION SENSOR UNIT (BPSU). A/C RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032900073	20010329	00073	EA  	2001	3	29	CA001003002      	1	20000915	G	2740		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AT APPROXIMATELY 100 KTS, THE STAB TRIM & MACH TRIM FAILED. THEY ABORTED THE TAKEOFF AND RETURNED TO GATE.THEY REP	LACED THE HSTCU AND CARRIED OUT AN ABORTED TAKEOFF INSPECTION.					2	L	7	2 	4F			RT	A21EA   					 
2001032900074	20010329	00074		2001	3	29	CA001003003      	4	20000915	G	3418		SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  										LT AOA	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AT APPROXIMATELY 90 KTS, THEY HAD A STALL FAIL, FOLLOWED BY A CONFIG SPOILERS MESSAGE. THEY ABORTED THE TAKEOFF AN	D RETURNED TO THE GATE. THE MAINTENANCE REPLACED THE LEFT AOA SENSOR AND CARRIED OUT AN ABORTED TAKEOFF INSPECTION.					2	L	7	2 	4F			RT	A21EA   					 
2001032900075	20010329	00075	EA  	2001	3	29	CA001003004      	1	20000916	G	3244		TIRE            			CNDAIR	CL600 	CL6002B19   	       	EA  										LT NR 1 & 2	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			CA											(CAN) DURING THE TAKEOFF, WHILE THE AIRCRAFT WAS ACCELERATING, AN IMORTANT VIBRATION WAS FELT IN THE COCKPIT. THRUST RET	ARDED TO IDLE AN AIRCRAFT RETURNED TO THE GATE AFTER THE ABORTED TAKEOFF. MAINTENANCE FOUND BOTH LT MLG TIRES DAMAGED . 	ALSO DAMAGE WAS FOUND TO THE LEFT INBOARD FLAP (INBOARD SIDE OF TRAILING EDGE), THE WING TRAILING EDGE AROUND WWS 56.177	 AND THE LEFT GEAR DOOR. DEEP INSPECTION OF THE AIRCRAFT SYSTEM CARRIED OUT BEFORE RELEASING THE WE ARE WAITING FOR A MO	RE COMPLETE REPORT.		2	L	7	2 	4F			RT	A21EA   					 
2001031900177	20010319	00177		2001	3	19	CA001003005      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF. A/C MADE AN AIR RETURN TO THE BASE. STALL COMPUTER RE-RACKED, O	PERATIONAL TEST CARRIED OUT, A/C RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031900178	20010319	00178		2001	3	19	CA001003006      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER. A/C BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001031900179	20010319	00179		2001	3	19	CA001003007      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER, A/C BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001031900180	20010319	00180		2001	3	19	CA001003008      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER, A/C BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001032000053	20010320	00053		2001	3	20	CA001003009      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.RESET STALL COMPUTER, A/C BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001032000054	20010320	00054		2001	3	20	CA001003010      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS AFTER TAKEOFF. A/C MADE AN AIR RETURN TO THE BASE. AOA CHECKED, NO CODES FO	R SPC IN MDC, PUSHER CHECKED GOOD. STALL COMPUTER RESET. A/C RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032000055	20010320	00055		2001	3	20	CA001003011      	4	20000919	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS AFTER TAKEOFF. A/C MADE AN AIR RETURN TO THE BASE. REPLACED STALL COMPUTER 	AND TESTED PER AMM. A/C BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032900076	20010329	00076	EA  	2001	3	29	CA001003012      	1	20000920	G	2750		BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS FAIL MESSAGE APPEARED IN FLIGHT AT 45 DEGREES.MAINTENANCE ACTION : REPLACED THE RIGHT BPSU. A/C RETURNED TO 	SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032000056	20010320	00056	EA  	2001	3	20	CA001003013      	1	20000920	G	2740		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STAB TRIM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STAB TRIM CHANNEL NR 2 MESSAGE ON EICAS POSTED PRIOR TO DEPARTURE.MAINTENANCE REPLACED THE MCU (MOTOR CONTROL UNIT	). A/C RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032000057	20010320	00057		2001	3	20	CA001003014      	4	20000920	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON EICAS DURING FLIGHT. MAINTENANCE REPLACED THE STALL COMPUTER.A/C BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001032000058	20010320	00058	EA  	2001	3	20	CA001003015      	1	20000920	G	2450		CIRCUIT BREAKER 			CNDAIR	CL600 	CL6002B19   	       	EA  										STAB TRIM	TRIPPED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) DURING DESCENT, STAB TRIM CHANNEL NR 1 CAUTION MESSAGE APPEARED ALONG WITH MACH TRIM MESSAGE. MAINTENANCE FOUND CI	RCUIT BREAKER TRIPPED.CIRCUIT BREAKER RESET, A/C BACK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032000059	20010320	00059	NE  	2001	3	20	CA001003016      	2	20000920	G	7220		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					RIGHT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING MORNING CREW PRE-FLIGHT WALK AROUND, RT ENGINE INTAKE, FAN & GUIDE VANES FOUND DAMAGED.ENGINE CHANGED, A/C	 BACK IN SERVICE.TC:  SUSPECT FOD NO -  FURTHER ACTION					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032000060	20010320	00060		2001	3	20	CA001003017      	4	20000920	G	3418		TRANSDUCER      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE ON EICAS FOLLOWED BY INBD SPOILERS MESSAGE ON TAKE OFF ROLL. REPLACED AOA NR 1 TRANSDUC	ER AND AOA NR 2 TRANSDUCER (STIFF WHEN ROTATING). A/C BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032000061	20010320	00061		2001	3	20	CA001003018      	4	20000922	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF. RESET STALL COMPUTER, A/C BACK IN SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032000062	20010320	00062		2001	3	20	CA001003019      	4	20000922	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF, ASSOCIATED WITH CONFIGURATION SPOILERS AND PAX DOOR OUTER HANDLE. 	RESET STALL COMPUTER. A/C BACK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032000063	20010320	00063		2001	3	20	CA001003020      	4	20000922	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS ON TAKEOFF.A/C  RETURNED TO THE BASE.STALL COMPUTER RESET, OPERATIONAL TEST	 CARRIED OUT. A/C RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032000064	20010320	00064	EA  	2001	3	20	CA001003021      	1	20000922	G	3230	601R510087	CONTROL PANEL   			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AFTER TAKEOFF, THE LANDING GEAR WOULD NOT RETRACT. REPLACED LANDING GEAR CONTROL PANEL, GEAR SWING CARRIED OUT. A/	C BACK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032900077	20010329	00077	EA  	2001	3	29	CA001003022      	1	20000922	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										LT TE FLAPS	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FLAPS FAIL CAUTION MESSAGE POSTED ON EICAS. REPLACED LEFT BPSU AND ALLL 8 FLAP ACTUATORS. A/C BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001032900078	20010329	00078	EA  	2001	3	29	CA001003023      	1	20000922	G	2740	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					HORIZONTAL STAB	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) STAB TRIM CHANNEL NR 2 WILL NOT ENGAGE & MACH TRIM CATUION MESSAGE AT THE GATE. REPLACED THE HSTA AND THE MCU ON S	PEC.NOTE: DURING REPLACEMENT, FOUND THE STABILIZER SURFACE TO BE EXCESSIVELY STIFF TO MOVE. STABILIZER PIVOT LUBRICATED.	 A/C BACK IN SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032900079	20010329	00079	EA  	2001	3	29	CA001004004      	2	20000911	G	8540	13519648	GEAR            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					CRANKSHAFT	DESTROYED       	W				O	 	 	 	OTHER                   				Y	J	 	ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA				1108 							(CAN) CRANKSHAFT GEAR FAIL CAUSING DAMAGE TO OTHER ACCESSORY GEARS AND RESULTING IN ENGINE STOPPAGE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032900080	20010329	00080	NE  	2001	3	29	CA001004006      	2	20000814	G	8530	331107	VALVE           			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	CA3         	52026	NE  					NR 3 CYLINDER	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				R	Y	 	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CR	CRUISE         	1			CA			680  	680  							(CAN) DURING SCOOP OPERATION, RT ENGINE BEGIN BACKFIRING. THE PILOT IN COMMAND DECIDED TO ABORT THE OPERATION AND TOOK O	FF. ONCE THE AIRCRAFT WAS IN CRUISE, THEY PERFORMED A PERFORMANCE TEST ON THE RT ENGINE AND AS THOSE TESTS SHOWED THAT E	NGINE COULD NOT MEET ITS SPECIFICATIONS AND PERFORMANCE, HE SHUT DOWN IT AND LAND AT THE CLOSEST AIRPORT.  BOTH INTAKE A	ND EXHAUST VALVES OF REAR NR 3 CYLINDER  WERE DAMAGED. EXHAUST VALVE WAS LOST WHILE THE INTAKE VALVE WAS BENT. HE ALSO F	OUND THE UPPER BEARING OF THE MAGNETO ALMOST DESTROYED.		2	H	7	2 	4R	4	R	 	A14EA   	E231				 
2001032000066	20010320	00066	EA  	2001	3	20	CA001004007      	1	20000824	G	5244		DOOR            			CNDAIR	CL215 	CL2151A10   	       	EA  										ACCESSORY BAY	SEPARATED       	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) THE PILOT COMMAND (PIC) A REPORTED THAT DURING A SCOOPING OPERATION, HE FELT SOMETHING DRAGGING THE AIRCRAFT. THE 	PIC NOTICED THE WATER SYSTEM INDICATION PANEL ON THE GLARE SHIELD INDICATED THAT THE RT WATER DOOR WAS OPENED. THEN THE 	PIC PULLED BACK THE THROTTLE AND STOPPED ENGINES. HE LOOKED AT THE WATER DOOR MECHANISM AND SAW BOTH WATER DOOR ACTUATOR	S PROTRUDING THROUGH THE WOODEN FLOOR. THE ACA INITIALLY REPORTED THAT BOTH THE WATER DOOR SPIGOTS WERE TORN FROM THE BU	LKHEAD AT FS 371.5 AND THE RT WATER DOOR WAS OPENED AND COULD NOT MECHANICALLY BE CLOSED. THE RT WATER DOOR WAS MANUALLY	 CLOSED AND STRAPED TO PERMIT A TAKE OFF FROM THE SEA AND RETURN TO THE MAINTENANCE BASE.	2	H	7	2 	4R			 	A14EA   					 
2001032900082	20010329	00082	NM  	2001	3	29	CA001004009      	1	20000830	G	2121	731376	FAN             			BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					EQUIPMENT BAY	SEIZED          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) AIRCRAFT WAS DIVERTED DUE TO BURNING ODOR IN COCKPIT AND FWD CABIN, CREW STATED THAT ODOR STOPPED AS SOON AS ALTER	NATE FAN SELECTION WAS CARRIED OUT. UPON ARRIVALMAINTENANCE FOUND NR 1 EQUIPMENT COOLING FAN BREAKER POPPED, FAN FOUND S	EIZED. AIRCRAFT WAS RELEASED UNDER MEL 21-58-3.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001032000067	20010320	00067	SO  	2001	3	20	CA001004010      	1	20000911	G	3233	2060500005	ROD END         			EMB   	120   	EMB120ER    	3260203	SO  	PWA   	118   	PW118       	 	NE  	HAMSTD	14RF	14RF9       	NE  	ACTUATOR	BROKEN          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) WHEN SELECTION GEAR UP, RED LIGHT STAY ON AT THE NOSE SYSTEM INDICATION. INVESTIGATION CUT OUT, A/C ON JACKS, GEAR	 SELECTED AT UP POSITION, FOUND NLG NOT LOCKED PROPERLY BY THE UPLOCK HOOK. RETRACTION ACTUATOR ADJUSTMENT WAS USSPECTED	 (P/N 20605-000-05) DECISION WAS MADE TO READJUST THE ROD END OF THE RETRACTION ACTUATOR BEOFORE ANY ADJUSTMENT WAS MADE	, FOUND BROKEN LOCK WASHER (P/N 19803). INSIDE TANG WAS MISSING AND ROD END ADJUSTMENT HAD CHANGE (MOVED IN), THE LENGTH	 OF THE ACTUATOR WAS SHORTER. NEW LOCK WASHER INSTALLED AND ACTUATOR ADJUSTED AS PER M/M 32-32-11 AND SYSTEM CHECKED OK.		2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001032000070	20010320	00070	WP  	2001	3	20	CA001004015      	1	20000825	G	2710	2587788902	SERVO           			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					AILERONS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AILERON SERVO WILL NOT DISENGAGE WITH SERVO SWITCHED OFF. UNABLE TO DISENGAGE AUTO PILOT. AILERON SERVO AND NR 1 D	IRECTIONAL GYRO CHANGED.					2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001032900083	20010329	00083	NM  	2001	3	29	CA001004016      	1	20000815	G	5414	313T3200238	PANEL           		767233      	BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					NACELLE	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON WALKAROUND FOUND PANEL MISSING ON INBOARD SIDE OF RIGHT HAND ENGINE STRUT. NIL PART AVAILABLE, PLACED ON MEL 54	-51-0100. NEW PANEL INSTALLED.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001032900084	20010329	00084	WP  	2001	3	29	CA001004017      	1	20000824	G	2740	95901	MOTOR           			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					STAB TRIM	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PRIMARY LONGITUDINAL TRIM DID NOT WORK SHORTLY AFTER TAKEOFF. NEITHER SUITCASE HANDLES OR THUMB SWITCHES WORKED. A	LTERNATE TRIM WORKED AND SHORTLY THEREAFTER THE PRIMARY TRIM BEGAN TO WORK. PRIMARY STABILIZER TRIM MOTOR REPLACED AS PE	R MAINTENANCE MANUAL REF 27-40-01 AND OPERATION CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001032000071	20010320	00071	NE  	2001	3	20	CA001004018      	2	20000824	G	7200		ENGINE          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					NR 1	FIRE            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HELICOPTER PILOT REPORTING SEEING FIRE IN BACK OF ONE ENGINE AFTER LANDING. A VISUAL INSPECTION OF BOTH ENGINES WA	S COMPLETED WITH NO UNUSUAL FINDINGS. ALSO PILOTS DID NOT SEE ANY ABNORMAL INDICATION IN THE COCKPIT. AIRCRAFT CONSIDERE	D SERVICEABLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001032900085	20010329	00085	NM  	2001	3	29	CA001004021      	1	20000819	G	2750		CONTROL UNIT    			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					TE FLAPS	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) UPON SELECTION OF FLAPS (25 FLAP) ICAS MESSAGE TE FLAP DISAGREE AND STATUS MESSAGE TE FLAP SHUTDOWN ILUMINATED. FL	AP INDICATION SHOWED SLIGHTLY ASYMMETRY AT 23 DEGREES. CHENAGED FLAP SLAT ELECTRICAL UNIT (F.S.E.U.) AND TEST CARRIED OU	T AS PER FAUALT ISOLATION MANUAL (F.I.M.) 27-50-00 PAGE 160, FIGURE 114C. NR 4 FLAP POSITION TRANSMITTER (M476) ADJUSTED	. OPERATIONAL CHECK CARRIED OUT, CHECKED SERVICEABLE, BITE CHECKED FSEU NO FAULTS FOUND.			2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001032900086	20010329	00086	NE  	2001	3	29	CA001005003      	2	20000811	G	8530	33645	PUSHROD TUBE    			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	CA3         	52026	NE  					NR 7 CYLINDER	CRACKED         	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			K	B	 	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			CA			1145 								(CAN) SHORTLY AFTER TAKEOFF, DURING INITIAL CLIMB, TOWER REPORTED SMOKE FROM RT ENGINE.PILOT IN COMMAND ACKNOWLEDGED SIT	UATION AND SHUT DOWN THE RT ENGINE AND RETURNED FOR LANDING.SIGNIFICANT OIL QUANTITY WAS LOST AS INDICATED ON OIL QUANTI	TY INDICATOR. APPROXIMATELY 7 GALS LOST.UPON INVESTIGATOIN, IT WAS FOUND EXHAUST PUSH ROD HOUSING OF CYLINDER NR 7 CRACK	ED. THEN, DURING THE REPLACEMENT, IT WAS FOUND THAT THE PUSH ROD ITSELF WAS SEPARATED AND CRACKED.PUSH ROD AND PUSH ROD 	HOUSING WERE REPLACED IAW PRATT & WHITNEY AND THE AIRCRAFT WAS RELEASED TO RETURN TO SERVICE.		2	H	7	2 	4R	4	R	 	A14EA   	E231				 
2001032900087	20010329	00087	EU  	2001	3	29	CA001005004      	2	20000628	G	7250	AS20625	NUT             								RROYCE	SPEY  	SPEY5118    	54523	EU  					GUIDE VANE RING	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6194 	608  							(CAN) THE NUT AS20625 HOLDING THE OUTLET GUIDE VANE RING BETWEEN THE LOW PRESSURE COMPRESSOR ROTOR AND THE HIGH PRESSURE	 COMPRESSOR ROTOR WAS UNTORQUE AND ENTERED INTO THE HIGH PRESSURE COMPRESSOR ROTOR DAMAGING THE HP COMPRESSOR BLADES. TH	E BOLT K1861114 ATTACHED BY THE NUT AS20625 HAS DAMAGED THE LP COMPRESSOR ROTOR BLADE STAGE 5 AND ALSO THE LP COMPRESSOR	 ROTOR DRUM. ENGINE REMOVED AFTER A POST FLIGHT INSPECTION BY THE CUSTOMER. ROLLS ROYCE MOD 5270 WHICH CORRECT THIS PROB	LEM, WILL BE RE-EMBODY ON ENGINE, AND TORQUE RE-APPLY AS PER SERVICE BULLETIN. SERVICE BULLETIN SB 72-5270 IS THE STANDA	RD RE-BUILD FOR SPEY 511-8 AT RRC.						4	F			E2EU				 
2000101800061	20001018	00061	SO  	2000	10	18	CA001005005      	1	20000906	G	2720	7C1015015	CONTROL CABLE   			GULSTM	GA7   	GA7         	3960401	SO  	LYC   	O320  	O320D1D     	41508	EA  					RUDDER CABLES	LOOSE           	W				O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) RUDDER CABLE TENSION NOT WITHIN SPECS - TOO LOOSE - SUSPECT REVERSAL OF RUDDER PEDAL BELLCRANK (7C10302-2) IF CABL	E TENSION IS NOT WITHIN SPECS THIS BELLCRANK CAN BE REVERSED AND ARM CAN TRAVEL UNDER SHAFT.  SPRING 7C10415-5 KEEPS THI	S ARM IN POSITION.  (FOUND ONE OF THESE SPRINGS PREVIOUSLY BROKEN CAUSING A SIMILAR OCCURRENCE - GROUND ONLY) RUDDER SYS	TEM RIGGED PER S.M.  (X)			1	L	7	2 	3O	3	O	 	A17SO   	E274				 
2000101800062	20001018	00062		2000	10	18	CA001005006      	4	20000829	G	2562	0507002	BATTERY         	LEIGH       	SHARC7K191  	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					INTEGRATED - ELT	UNSERVICEABLE   	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						225049					(CAN)   AIRCRAFT FLEW FROM 16 APR 1999 TO 16 JUL 1999 (11.7 HRS) TRAINING WITH PILOT-OWNER UNAWARE THAT ELT BATTERY EXPI	RED ON APR 1999 DECAL BY R.S.  A/C RADIO LTD. ON UNIT SHOWS BATTERY EXPIRED APR 1999, LAST TEST:  OCT 5, 1998, NEXT TEST	:  OCT 5 1999.  NO ENTRY OR NOTE, ETC., IN JOURNAL LOG NR 2, P. 1 TO 3 INCLUSIVE.  IN AF TECH LOG SECTION 1, LAST REF. T	O ELT IS DATED MAY 16/96.  IN AF TACH LOG SECT 2, LAST REF TO ELT  IS DATED JUN 1986.  A/C SOLD TO ACTUAL OWNER AND DELI	VERED AT CYXK ON 28 MAR 1999 FEW DAYS PRIOR TO BATTERY DUE.   (X)		1	L	7	1 	3O	3	O	 	2A13    	E274				 
2000112200008	20001122	00008	GL  	2000	11	22	CA001005009      	1	20000808	G	7333	CASC211	REGULATOR       	RROYCE      		ENSTRM	F28   	F28ENSTRM   	3300404	GL  	RROYCE	SPEY  	SPEY55515P  	54521	EU  					FUEL FLOW REG	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA				2562 		9786					(CAN) AFTER TAKEOFF, THE FLIGHT CREW WAS UNABLE TO THROTTLE BACK THE ENGINE. THEY SUBSEQUENTLY SHUT THE ENGINE DOWN AND 	RETURNED TO FIELD.  REPLACEMENT OF FUEL FLOW REGULATOR CORRECTED THE PROBLEM.  DEFECTIVE FFR UNDER INVESTIGATION AT RRC.	  (X)				1	G	7	1 	3O	4	F	 	H1CE    	E2EU				 
2000101800063	20001018	00063	CE  	2000	10	18	CA001005010      	1	20000409	G	3230	084122510	DOWNLOCK        			CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	IO470U      	17026	SO  					DOWNLOCK ASSY	MISALIGNED      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			5429 								(CAN) - RIGHT GEAR COLLAPSED AFTER LANDING.   DOWNLOCK FOUND MISADJUSTED (TOO SHORT).   DOWNLOCK BELLCRANK, SIDE BRACE L	INK REPLACED.  DOWNLOCK READJUSTED.  (X)					1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2000101800064	20001018	00064	CE  	2000	10	18	CA001005012      	1	20000907	G	7920		ENGINE          			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) ENGINE WAS SENT OUT FOR A PROP STRIKE INSPECTION TO AN APPROVED ENGINE OVERHAUL SHOP.  AFTER REINSTALLATION PROBLE	MS OF FLUCTUATING INTERMITTENT OIL PRESSURE OCCURRED, TROUBLESHOOTING AND INVESTIGATION OF OIL PRESSURE SYSTEM LED TO TH	E FINDING OF A PIECE OF MASKING TAPE 23 INCHES LONG IN THE OIL PAN WHICH OBSTRUCTED INTERMITTENTLY THE OIL PRESSURE SCRE	EN AND LED TO THE RELATED PROBLEM.  AIRCRAFT FLIGHT TESTED SATISFACTORY AND RETURNED TO SERVICE.  (X)			1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001032900089	20010329	00089	SO  	2001	3	29	CA001005015      	1	20000911	G	7713	17766100	HOSE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MANIFOLD	DETERIORATED    	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA			1207 								(CAN) LOW TAKEOFF MANIFOLD PRESSURE. RAPID DIMINUTION OF MANIFOLD PRESSURE DURING CLIMB.ON INSPECTION, HOSE APPEARED BRO	WNISH & DRY. DURING MANIPULATION TO CHECK NUMBERS ON/DENT BAND, HOSE BROKE IN TWO PIECES AT 4.5 INCHES FROM DIFF. CONTRO	LLER IN VICINITY OF EXHAUST PIPE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032900090	20010329	00090	NM  	2001	3	29	CA001005017      	1	20000907	G	2751	2061141	INDICATOR       			BOEING	737   	7372E1      	138448F	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH FLAPS 1 SELECTED & T/E ASYMMETRY OCCURRED. FLAP INDICATING GAUGE FAULTY. GAUGE REPLACED I.A.W. M.M. 27	-58-41 & CHECK  SERVICEABLE. NO PROBLEMS FOUND DURING SUBSEQUENT FLIGHT.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000112800081	20001128	00081	SW  	2000	11	28	CA001005019      	1	20000825	G	5302	206031418007	SUPPORT BRACKET 	BELL        	206033004NA 	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					VERTICAL FIN	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9918 			AOKP02014					(CAN) DURING A DAILY INSPECTION CHECK, TWO BREAKS WERE FOUND IN TH E  UPPER MAIN ATTACHMENT POINT FOR THE VERTICAL FIN R	EAR SUPPORT.  THE BROKEN PIECE IS APPROXIMATELY 1 INCH BY 1 INCH IN SIZE.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000101800066	20001018	00066	EA  	2000	10	18	CA001006005      	2	20000907	G	7414	4372	MAGNETO         			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					LEFT MAGNETO	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				485  		98060355					(CAN) ENGINE SHUT DOWN NORMAL WENT TO RESTART, NO SPARK LEFT MAGNETO PROBLEM INTERNAL GROUNDING.  (X)						1	H	7	2 	3O	3	O	 	A31EU   	1E10				 
2000110300059	20001103	00059	CE  	2000	11	3	CA001012002      	1	20000914	G	5510	04320049	BRACKET         	CESSNA      		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					TOP LT FWD CORNR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			16000			15283403					(CAN) BRACKET CRACKED ALONG WELDED SEAM ALONG LT FRONT TOP OF BRACKET.  CRACK RUNS AROUND THE BOLT HOLE OF VERTICAL FIN 	LT OUTBOARD ATTACH BOLT.  (X)					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001032900092	20010329	00092	NE  	2001	3	29	CA001012003      	1	20000918	G	6320		GEARBOX         			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					NR 2 ENGINE	FAILED          	W				C		 	 	ABORTED TAKEOFF         				Y	J	 	ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) TAKEOFF WAS ABORTED WHEN A LOUD BANG WAS HEARD BY FLIGHT CREW. NR 2 ENGINE SHUT DOWN & A/C LANDED BACK ON THE HELI	 PAD. ON TOUCH DOWN THE TAIL WHEEL MISSED THE PAD & THE AIRCRAFT CAME TO REST ON THE KEEL JUST FORWARD OF THE TAIL WHEEL	. ALL PAX WERE UNLOADED & MOVED AWAY FROM THE AIRCRAFT. THE FLIGHT CREW THEN TAXIED THE AIRCRAFT (SINGLE ENGINE) TO THE 	FAR CORNER OF THE HELIPAD & SHUTDOWN - TSB HAS ALL COMPONENT RECORDS AT THIS TIME.			2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2000110300011	20001103	00011	SO  	2000	11	3	CA001012004      	1	20000922	G	3230	755956	ROD END         	PIPER       	4204200     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FROM ARM	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			13223								(CAN) LOG PAGE 665 REFERS.  PILOT REPORTED GEAR NOT LOCKED, LIGHT ILLUMINATE AFTER TAKEOFF - RECYCLED 3 TIMES FOR 3 GREE	N LIGHT FOR LANDING. MAINTENANCE FOUND LEFT MAIN GEAR RETRACTION ARM BROKEN OFF FROM ROD END.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032000081	20010320	00081	NM  	2001	3	20	CA001012007      	1	20000919	G	2782	252T13013	ACTUATOR        			BOEING	767   	767375      	       	NM  	GE    	CF6   	CF680C2B6   	30025	NE  					NR 5 SPOILER	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA			54992								(CAN) DURING APPROACH , GEAR DOWN, FLAPS 20, AUTOPILOT ON. VIBRATION, FELT LIKE SPOILERS UP. CONTROL WHEEL SHOWED 1/2 TO	 3/4 (TOTAL) WHEEL MOVEMENT ROLL TO RIGHT. DISCONNECTED AUTOPILOT & AUTO THROTTLE, A AIRCRAFT, THEN ROLLED HARD TO LEFT,	  REQUIRED LARGE AMOUNT OF RIGHT WING DOWN TO KEEP A/C LEVEL. LANDED WITH FLAPS AT 25 UNITS, SAME AILERON INPUT REQUIRED	 TO KEEP WINGS LEVEL, VIBRATIONS DOWN TO &  INCLUDING LDG. AILERON & AILERON TRIM CHECKED AS PER MM 27-11-00 P. 501, NO 	FAULT FOUND. AILERON DROOP CHECK COMPLETED AS PER MM 27-11-00 P. 513, CHECKED OK. FOUND #5 SPOILER VIBRATING HEAVILY WIT	H AILERON INPUT. SPOILER ACTUATOR REPLACED AS PER MM 27-61-01 P. 401. TEST FLT COMPLETED, OPERATIONS NORMAL.	2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2000110900265	20001109	00265	NE  	2000	11	9	CA001012009      	1	20000921	G	1230	1368DP	CHECK VALVE     		HP6101002C10	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					CHECK VALVE	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) DURING REFUELING OF HELICOPTER, A HYDRAULIC LEAK WAS DETECTED.  THE FAULT WAS FOUND TO BE A CHECK VALVE/FITTING FO	R THE PRIMARY HYDRAULIC MANIFOLD.  FITTING WAS REPLACED WITH A LATER P/N STEEL PART.  (X)					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2000112200009	20001122	00009	NE  	2000	11	22	CA001012010      	1	20000927	G	1230		HOSE            			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					HYDRAULIC HOSE	LEAKING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) WHILE IN-FLIGHT, PRIMARY HYDRAULIC PRESSURE DROPPED.  AFTER LANDING, FOUND A HYDRAULIC PRESSURE HOSE FROM THE PUMP	 TO THE MANIFOLD HAD STARTED TO LEAK.  HOSE WAS REPLACED AND LEAK CHECKED.  AIRCRAFT RETURNED TO SERVICE.  (X)					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2000110300035	20001103	00035	CE  	2000	11	3	CA001012011      	1	20000929	G	2720	S16751	BEARING SUPPORT 			CESSNA	172   	172R        	2072401	CE  										CENTER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1077 								(CAN) DURING ROUTINE INSPECTION, RUDDER PEDAL TORQUE TUBE SUPPORT BEARING FOUND CRACKED IN HALF AT APPROXIMATELY THE CEN	TER OF THE UPPER BEARING HALF.  BEARING HALVES WERE BOTH REPLACED.  BEARING FAILURE APPEARS TO HAVE OCCURED DUE TO MANUF	ACTURING DEFECT.  (X)				1	H	7	1 	3O			NT	3A12    					 
2001033000002	20010330	00002	NE  	2001	3	30	CA001012012      	1	20000921	G	6310		O-RING          			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					INPUT COUPLING	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) WE HAVE HAD 5 CASES OF UNACCEPTABLE GREASE LEAKAGE RATES FROM THE INPUT COUPLINGS.WHEN THE COUPLINGS WERE DISASSEM	BLED THE O-RING P/N M83248-1-132 WAS FOUND TO BE EITHER FLAT OR DETERIORATED. ACRO (LANGLEY) TOLD ME THAT THEY DID A HAR	DNESS TEST ON THEIR BATCH OF O-RINGS AND FOUND THAT THEY FAILED. ATTACHED TO THIS REPORT YOU WIL FIND A COPY OF THE LOT 	NUMBER OF THE O-RINGS IN QUESTION.			2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001032900094	20010329	00094	NE  	2001	3	29	CA001012013      	1	20000918	G	6320	7620903001054	FITTING         			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					TRANSMISSION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10194								(CAN) UPON PURCHASE OF THIS AIRCRAFT AND DISASSEMBLED FOR REFURBISHING. THE RT MAIN TRANSMISSION SUPPORT FITTING WAS FOU	ND TO BE CRACKED. DURING INSPECTION.					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001032900095	20010329	00095	NE  	2001	3	29	CA001012014      	1	20000922	G	6710	NAS464P842	BOLT            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					M/R PITCH ROD	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON PURCHASE OF THIS AIRCRAFT AND DISASSEMBLED FOR INSPECTION AND RE-FURBISHING. THE YELLOW & BLACK M/R PITCH ROD	, LOWER ATTACH BOLTS WERE FOUND TO BE EXTREMELY WORN.					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001032900096	20010329	00096	EU  	2001	3	29	CA001013002      	1	20000203	G	6730	AC67246	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ROTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			20   	20   		EDK277					(CAN) FORE AND AFT SERVO WORKED WELL ON THE INSTALLATION, HOWEVER AFTER 19.7 HOURS IT WAS MOTORING AND CAUSING FEED BACK	. UNIT REPLACED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032900097	20010329	00097		2001	3	29	CA001013003      	4	20000304	G	2562	C4000	ELT             			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CABIN	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						403899					(CAN) ELT WAS TESTED AS PER THE 100 HOUR INSPECTION SCHEDULED AND UNIT WOULD NOT ACTIVATE AFTER BEING SHAKEN OR WHEN THE	 MASTER SWITCH WAS TURNED TO THE ON POSITION. UNIT REPLACED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001032900098	20010329	00098	EU  	2001	3	29	CA001013004      	1	20000403	G	2810		SUPPORT BRACKET 			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL CELL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6563 								(CAN) AFTER THE FUEL CELL WAS REMOVED FOR INSPECTION,  CRACKS WERE DETECTED IN THE AREA OF THE UPPER TWO BOLT HOLES  FOR	 THE FUEL CELL SUPPORT SADDLES. CRACKED WERE REPAIRED AS PER MRR 53-10-21-777.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032900099	20010329	00099	EU  	2001	3	29	CA001013005      	1	20000403	G	6220		SHIM            			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FREQ ADAPTOR	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE MAIN ROTOR BLADE REMOVAL,  NOTICED THAT THE BLADE PINS WERE HARD TO REMOVE. AFTER INSPECTION, FOUND THA	T THE SHIMS WERE MISSING FROM THE FREQUENCY ADAPTERS. ONCE THE SHIMS WERE INSTALLED THE BLADE PIN INSTALL WAS NORMAL.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032900100	20010329	00100	NE  	2001	3	29	CA001013006      	2	20000405	G	7532	9550158260	BLEED VALVE     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COMPRESSOR	FAILED          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			CA				1005 							(CAN) INTERMITTENT FAILURE TO CLOSE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032900102	20010329	00102	EU  	2001	3	29	CA001013008      	1	20000414	G	6210	350A11001007	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3398 								(CAN) CRACKED AT STATION 570, ALSO LEADING EDGE EROSION. BLADE REPLACED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000112700052	20001127	00052	NE  	2000	11	27	CA001013009      	2	20000415	G	7321	0164448380	FUEL CONTROL    			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			1758 								(CAN)  THE ROTOR RPM WAS ADJUSTED SEVERAL TIMES OVER THE COURSE OF A MONTH, AT WHICH TIME THE UNIT FAILED THE CHARACTERI	STICS CHECK.  UNIT REPLACED.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032900103	20010329	00103	SW  	2001	3	29	CA001013010      	1	20000421	G	6220	206031509005	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R HEAD	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				127  							(CAN) BEARING FOUND LOOSE IN THE DRAG PIN, POOR STAKING SEEMS TO BE THE CAUSE.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032900104	20010329	00104	SW  	2001	3	29	CA001013011      	1	20000425	G	2820		CHECK VALVE     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL SYSTEM	FAILED          	W				K	 	 	 	NONE                    				X	J	 	ENGINE FLAMEOUT           	WARNING INDICATION        		IN	INSP/MAINT     	1			CA											(CAN) C-GLMV UNDERGOING AFTER FUEL SYS MAINT CHECK, (2 MIN AT 100 PERCENT NR WITH BOOST PUMPS OFF) WHEN IT FLAMED OUT. A	/C  HAD BEEN RUNNING FOR APPROX. 10 MIN W/O INCID. PRIOR TO PULLING PUMPS. A/C THEN BLED & RESTARTED & RUN AT 100% FOR 2	0 MIN. BOOST PUMPS WERE TURNED OFF & ENG FLAMED OUT AGAIN. FUEL SYS INVESTIGATED & IT FOUND THAT BOTH OF INLINE CHECK VA	LVES WERE STUCK IN OPEN POSITION. ALLOWED ENG DRIVEN PUMP TO DRAW AIR INTO SYS ONCE BOOST PUMPS WERE PULLED OFF LINE. A/	C ONLY HAD 125 LBS OF FUEL ON BOARD SO FWDTANKS WOULD HAVE BEEN EMPTY DURING TEST.AFTER INSP OF CHECK VALVES THEY WERE F	OUND TO HAVE SAND IN THEM. INLINE FILTERS WERE ALSO DIRTY	1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001032900105	20010329	00105	EU  	2001	3	29	CA001013012      	1	20000427	G	6210	350A11001001	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7207 								(CAN) MAIN ROTOR BLADE  AFTER BALANCING SEVERAL TIMES WINDS UP FLYING OUT OF TRACK, CAUSING A CYCLIC STICK FEEDBACK WHEN	 THE HYDRAULICS ARE OFF.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032900107	20010329	00107	EU  	2001	3	29	CA001013014      	1	20000519	G	6420	350A33200405	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R SPIDER	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				304  		ACRO03					(CAN) DURING A 50 HR INSPECTION ON THIS SPIDER, THE BEARING WAS FOUND TO BE ROUGH. NOTE THE BEARING ONLY REACHED 10 PERC	ENT OF ITS SERVICE LIFE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001032900110	20010329	00110	EU  	2001	3	29	CA001013018      	1	20000529	G	6420	350A33200406	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R SPIDER	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			678  	9    							(CAN) EXCESSIVE PLAY FOUND BETWEEN THE BEARING AND SPIDER HOUSING. ALSO FOUND SIGNS OF OVERHEATING WITH LOSS OF GREASE A	ND PAINT MELTING.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2000122900006	20001229	00006	GL  	2000	12	29	CA001013019      	2	20000531	G	7250	6898734	TURBINE         	ALLSN       		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6893 	1248 		CAT31125P					(CAN) DURING A COMPRESSOR WASH, BRULIN AND WATER MIX WAS COMING OUT OF THE NR 6 AND NR 7 AIR DELIVERY TUBE.  UPON FURTHE	R INVESTIGATON IT WAS DISCOVERED THAT THE TUBE WAS NOT WELDED TO THE ASSY.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032900111	20010329	00111	SW  	2001	3	29	CA001013020      	1	20000613	G	7712	206075185103	GAUGE           			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TORQUE	FAILED          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			NR	NOT REPORTED   	1			CA				10   							(CAN) THIS GAUGE DID NOT INDICATE PROPERLY FROM THE INITIAL INSTALLATION AND DURING THE REPLACEMENT THE NEEDLE CAME OFF.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001032900112	20010329	00112	GL  	2001	3	29	CA001013021      	2	20000621	G	7323	23006259	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN CHECKING THE GOVERNOR ON RECEIPT, IT WAS NOTED THAT THE T FITTING WAS INSTALLED IN THE WRONG PORT. FITTING WA	S REMOVED AND INSTALLED IN THE CORRECT PORT.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032900113	20010329	00113	SW  	2001	3	29	CA001013022      	1	20000628	G	6710	2060627211	ACTUATOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE LINEAR ACTUATOR IS SEIZED IN THE MOST FORWARD POSITION. WHEN THE UNIT IS ACTUATED THE MOTOR RUNS AND THEN STOP	S RIGHT AWAY.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032900114	20010329	00114	SW  	2001	3	29	CA001013023      	1	20000821	G	6230	206010450113	SEAL            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					SWASHPLATE	SPINNING        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			14328	212  							(CAN) THE UPPER SEAL FOUND SPINNING IN THE CAP.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032900115	20010329	00115	EU  	2001	3	29	CA001013024      	1	20000920	G	6210	350A11001007	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3398 			7252					(CAN) BLADE CRACKED AT STATION 570, ALSO LEADING EDGE EROSION.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000112000026	20001120	00026	CE  	2000	11	20	CA001013025      	1	20000831	G	2824	AHE05D92	PUMP            			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	POWER LEAD	SHORTED         	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			109  								(CAN) THIS PUMP IS LOCATED ON AFT SIDE OF BACK WALL OF TIP TANK.  ITS PURPOSE IS TO CIRCULATE FUEL FROM FRONT OF TANK TO	 CENTER SECTION OF TANK WHERE FUEL PICKUP IS.  IT IS CONNECTED TO TEN AMP CCTT BREAKER, SHARED BY THE LDG LIGHT ON THAT 	SIDE.  BREAKER HAD TRIPPED IN-FLIGHT AND PILOT WROTE SNAG UP AS LDG LIGHT PROBLEM.  WHEN TROUBLESHOOTING SYS, BREAKER RE	SET AND POWER APPLIED TO SYS.  ARCING HEARD AND POWER LEAD BEGAN TO SMOKE.  BREAKER TRIPPED IMMEDIATELY.   IS PMA UNIT A	ND HAD BEEN INST IN ACFT ONLY 109.2 HRS BEFORE IT FAILED.  WERE NO EXTERNAL SIGNS THAT POWER LEAD CHAFED OR WORN.  SHORT	 APPEARS TO HAVE OCCURRED INSID E CONNECTOR TO FUEL PUMP.  (X)	1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000112000027	20001120	00027	CE  	2000	11	20	CA001013026      	1	20000909	G	3231	08411066	BELLCRANK       			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520EB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ACTUATING LINK	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			6814 								(CAN) AFTER LANDING, PILOT NOTICED THE RT MAIN GEAR DOOR WAS NOT CLOSED.  MAINTENANCE DISCOVERED THE DOOR ACTUATING BELL	CRANK HAD BROKEN HALF WAY BETWEEN THE PIVOT AND THE ACTUATING LINKAGE. HAVE SEEN THIS SAME PART BREAK IN THE SAME PLACE 	ON AN AIRCRAFT THAT HAD OPERATED IN THE PAST.  FROM THE COLOR OF THE METAL AT THE FAILURE, IT APPEARS THAT THE FAILURE D	ID NOT OCCUR ALL AT ONCE.  ABOUT 70 PERCENT OF THE CROSS SECTION APPEARED TO BE OXIDIZED.  BOTH TIMES  HAVING SEEN THIS 	FAILURE, NO OTHER PROBLEMS HAVE RESULTED FROM THE DOOR HANGING OPEN, BUT THERE IS THE POTENTIAL FOR THE GEAR DOOR TO JAM	 OR OTHERWISE CAUSE PROBLEMS.  (X)	1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001033000003	20010330	00003	NM  	2001	3	30	CA001013027      	1	20001007	G	5302	500N34223	FITTING         		500N34215   	DOUG  	600N  	600N        	3027377	NM  										TAIL BOOM	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1496 								(CAN) DURING REMOVAL OF TAILBOOM ASSY TO FACILITATE MAINTENANCE A CRACK WAS DISCOVERED AT THE UPPER RT TAILBOOM ATTACH F	ITTING. FURTHER INVESTIGATION IN THE FUSELAGE STRUCTURE REVEALED MORE CRACKING IN THE FUSELAGE TAILBOOM SUPPORT STRUCTUR	E.				1	G	7	1 	3U			NC	H3WE    					 
2001032900116	20010329	00116	NM  	2001	3	29	CA001013028      	1	20001007	G	6210	369D21102523	BLADE           			DOUG  	600N  	600N        	3027377	NM  										MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1233 			099992836					(CAN) CRACK DETECTED IN M/R BLADE ASSY LOWER SKIN APPROX 16 INCHES FROM ROOT FITTING. CRACK APPEARS TO HAVE STARTED IN T	HE CENTRE OF THE BLADE SKIN AND PROGRESSED IN A CHORDWISE MANNER TOWARD THE TRAILING EDGE AND THE BLADE SPAR. CRACK WAS 	DISCOVERED DURING A 100 HOUR INSP OF THE M/R BLADES, AS A PRECAUTION ALL M/R BLADES (6) WERE REPLACED. M/R BLADES REMOVE	D HAVE BEEN RETURNED TO THE MANUFACTURER FOR FURTHER EVALUATION AT THEIR REQUEST.			1	G	7	1 	3U			NC	H3WE    					 
2001032900117	20010329	00117	NM  	2001	3	29	CA001013029      	1	20001007	G	2840	60N810713	INDICATOR       			DOUG  	600N  	600N        	3027377	NM  										FUEL QUANTITY	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ERRATIC FUEL QUANTITY INDICATION DISCOVERED DURING REFUELING. FUEL QUANTITY INDICATOR WAS FOUND TO BE INDICATING M	ORE FUEL ON BOARD THAN THE AIRCRAFT COULD BE SERVICED WITH. AIRCRAFT WAS DEFUELED AND FUEL SYSTEM WAS RECALIBRATED AND T	HE DEFECT APPEARED TO RECTIFIED. PROBLEM OCCURRED AGAIN AND FUEL INDICATOR WAS REPLACED AT AFT 1402.3 HOURS. REPORT IS B	EING SUBMITTED BECAUSE THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM. FUEL INDICATOR WAS PREVIOUSLY REPLACED AT AFT 990.	4 HOURS.		1	G	7	1 	3U			NC	H3WE    					 
2000112000028	20001120	00028	SO  	2000	11	20	CA001013030      	1	20000929	G	2731	41734078	CONTROL CABLE   			PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCC4Y	HCC4YR2     	GL  	ELEVATOR TRIM	FRAYED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) UPON ROUTINE INSPECTION OF ELEVATOR TRIM SYSTEM, AFT TRIM CABLE FOUND FRAYED AND WITH  BROKEN STRANDS.  DAMAGE TO 	CABLE BELIEVED TO BE CAUSED BY SHARP BENDS AND HIGH FREQUENCY OF MOVEMENT USING ELECTRIC TRIM SERVO.  (X)					1	L	7	2 	3O			 	A20SO   		5	C	P52GL	 
2001032900118	20010329	00118	SW  	2001	3	29	CA001013032      	1	20000913	G	6710	212010403005	LEVER           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					COLLECTIVE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PIN PRESSED INTO ASSEMBLY CAME LOOSE. FOUND WHEN SWASHPLATE ASSY CHANGE.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001032900119	20010329	00119	SW  	2001	3	29	CA001013033      	1	20000929	G	2910	212076372001	LINE            			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					HYD SYSTEM	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			293  								(CAN) NR 1 HYDRAULIC SYSTEM RETURN LINE WAS CHAFED WITH NR 2 PUMP PRESSURE LINE,  REPLACED. THIS TUBE ASSEMBLY WAS INSTA	LLED 293.1 HOURS BEFORE.FOUND PRESSURE LINE WAS ROUTED OTHER SIDE OF NR 2 PUMP.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001032900120	20010329	00120	WP  	2001	3	29	CA001013034      	1	20000928	G	2435	150SG1052B	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER GEN	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			433  								(CAN) STARTER-GENERATOR WAS REMOVED TO INVESTIGATE AN ENGINE VIBRATION. AME FOUND THE DRIVE END BEARING WAS VERY LOOSE, 	WITH RADIAL PLAY. SENT UNIT TO AMO. AMO DISASSEMBLED & FOUND D.E. BALL BEARING HAD CONSIDERABLE PLAY IN BOTH RADIAL (.01	0) X AXIAL (.025) DIRECTIONS. NO OTHER FAULTS FOUND.NEW BEARING INSTALLED & UNIT TESTED AND RETURNED RO SERVICE.U/S BEAR	ING SENT TO OEM FOR WARRANTY ASSESSMENT.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000112700053	20001127	00053	WP  	2000	11	27	CA001016002      	1	20000920	G	2435	6054424	STARTER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER SEAL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			22   								(CAN) PILOT NOTICED SPRAY OUT OF ENGINE BAY AREA AND WHEN HE CHECKED INSTRUMENT PANEL, TORQUE GAUGE WAS FLUCTUATING AND 	OIL PRESSURE WAS DROPPING BELOW 30 PSI.  AIRCRAFT WAS LANDED AND LARGE AMOUNT OF OIL NOTICED COMING OUT OF STARTER AREA.	  STARTER WAS REMOVED AND SEAL WAS FOUND TO HAVE COME OUT OF HOLE.  DUE TO POSSIBLE ENGINE DAMAGE AND METAL ON CHIP PLUG	, AIRCRAFT WAS TRUCKED BACK TO BASE.  (X)			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000112000029	20001120	00029	SO  	2000	11	20	CA001016003      	1	20000914	G	2912	460635	HOUSING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					THREADED AREA	CRACKED         	W				O	 	 	 	OTHER                   				K		 	FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) UPON CLIMB OUT, PILOT SELECTED GEAR UP AT WHICH POINT THE GEAR WOULD NOT LOCK IN THE UP POSITION.  PILOT THEN TRIE	D TO CYCLE THE GEAR DOWN, BUT THE GEAR WOULD NOT RESPOND.  THE PILOT MADE AN EMERGENCY LANDING GEAR EXTENSION SUCCESSFUL	LY ACHIEVING THREE GREEN.  A LANDING WAS MADE WITHOUT INCIDENT.  UPON INSPECTION, MAINTENANCE FOUND A LARGE HYDRAULIC LE	AK FROM THE RT ENGINE COWL CAUSED BY A CRACKED HYDRAULIC FILTER HOUSING LOCATED ON THE ENGINE FIREWALL.  A NEW HOUSING W	AS INSTALLED WITH NO FURTHER PROBLEMS.  IT IS FELT THE HOUSING FAILED DUE TO OVERTORQUEING.  (X)		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032000083	20010320	00083	NM  	2001	3	20	CA001016005      	1	20000915	G	2421		SHAFT           		976J1198    	BOEING	727   	727171C     	1384057	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					GENERATOR	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				1509 		YL4921					(CAN) DURING CRUISE FLIGHT NR 3 ENGINE GENERATOR INDICATED UNDER EXCITATION FOLLOWED BY UNDER VOLTAGE THEN A FIELD TRIP.	 THE RESIDUAL VOLTAGE WAS BELOW MINIMUM AS SUCH THE CSD WAS DISCONNECTED AND THE ELECTRICAL BUSS LOADS WERE REDUCED. THE	 GENERATOR WAS FOUND TO HAVE A FAILED INPUT SHAFT. THE GENERATOR WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000112000030	20001120	00030	CE  	2000	11	20	CA001016006      	1	20000902	G	5540	05310081	HORN            	CESSNA      	053100681   	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					STOP BOLT CONTAC	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10560								(CAN) RUDDER WAS ALLOWED TO MOVE BEYOND TRAVEL LIMITS DUE TO WORN HORN P/N 0531008-1.  HORN WAS REPLACED WITH NEW FACTOR	Y PART AND NEW RUDDER STOP NUT P/N MS21042L5 AND BOLT AN5-5A.  RUDDER CHECKED FOR TRAVEL AND SAFETY.  (X)					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001032000084	20010320	00084	NM  	2001	3	20	CA001016007      	1	20000921	G	2751	106079113	INDICATOR       			BOEING	737   	737284      	138448R	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAPS	SPLIT           	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			4490 	156  							(CAN) ON APPROACH FLIGHT CREW WERE UNABLE TO EXTEND THE FLAPS PAST 5 UNITS DUE TO AN ASYMMETRY INDICATION. AN UNEVENTFUL	 FLAPS 5 LANDING WAS CARRIED OUT. MAINTENANCE INSPECTED THE TRAILING EDGE FLAPS WITH NO FAULTS FOUND. THE PROBLEM WAS TR	ACED TO THE INDICATOR, WHICH WAS REPLACED. THE SYSTEM THEN CHECKED SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000112700054	20001127	00054	EU  	2000	11	27	CA001016010      	1	20000920	G	2435	29282PML	BRUSHES         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			22000	458  		114					(CAN) PREMATURE WEAR OF STARTER BRUSHES AND ARMATURE. THERE APPEARS TO BE NO EXCESS CURRENT DRAW ON GENERATOR. NO OTHER 	ELECTRICAL ABNORMALITIES ON THIS AIRCRAFT. BRUSH WEAR WAS DETECTED ON 100 HOUR INSPECTION. STARTER GENERATOR WAS SENT TO	 CANADIAN AERO ACCESSORIES WITH A COPY OF THIS SDR. PLEASE FIND ATTACHED A COPY OF THE COMPONENT CARD.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032000085	20010320	00085	NM  	2001	3	20	CA001016011      	1	20001001	G	5320	6937241	BOLT            			BOEING	737   	7372M8      	1384483	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ELEVATOR PCU	MISSING         	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) CREW REPORTED ON TAXI OUT WHEN THEY CHECKED THE FLIGHT CONTROLS THE ELEVATOR FELT VERY RESTRICTED IN DOWN TRAVEL M	OTION. OPERATION FELT NORMAL WITH A SYSTEM HYDRAULIC DEPRESSURIZED. UPON INVESTIGATION FOUND A SYSTEM ELEVATOR PCU INPUT	 ROD TO ELEVATOR INPUT TORQUE TUBE ATTACH BOLT NOT INSTALLED. BOLT WAS REINSTALLED WITH NEW WASHER AND LOCKNUT. ELEVATOR	 SYSTEM FUNCTION CHECKED I.A.W. MAINTENANCE MANUAL 27-31-101. NOTE: BOLT WAS FOUND AT BOTTOM OF TAIL CONE. NO NUT OR WAS	HER WAS PRESENT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000112700055	20001127	00055	GL  	2000	11	27	CA001017007      	2	20000915	G	7530	6890550	COMPRESSOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					AFT DIFFUSER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4517 	460  		CAC2458					(CAN) DURING 100-HOUR INSPECTION OF THE HELICOPTER, A BLACK LINE WAS OBSERVED ON ONE OF THE COMPRESSOR ASSEMBLY MOUNTING	 PAD ARMS WHICH FORMS THE REAR DIFFUSER OF THE COMPRESSOR.  CLOSER VISUAL INSPECTION WITH MAGNIFYING GLASS CONFIRMED CRA	CK.  THE CRACKED MOUNTING ARM IS AT THE 4:00 POSITION WHEN LOOKING AT THE AFT SIDE OF THE COMPRESSOR. COMPRESSOR ASSEMBL	Y FOR REPAIR.  (X)			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001033000005	20010330	00005	CE  	2001	3	30	CA001017008      	1	20000923	G	3246	16218000	WHEEL           	CLEVELAND   	40289       	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE INSPECTION MAINTENANCE NOTICED A CRACK IN THE PAINT IN THE BEAD AREA. AREA WAS CLEANED  WITH A LI	QUID DYE PEN INSPECTION FOUND A 2.5 INCH CRACK FOLLOWING THE CIRCUMFERENCE. WHEEL ASSEMBLY WAS REPLACED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2000112000032	20001120	00032	SO  	2000	11	20	CA001017009      	2	20000927	G	7414	BL5005561R	MAGNETO         	CONT        		CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					LT MAGNETO	FAILED          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				35   		810084R					(CAN) MAGNETO FAILED REPEATEDLY ON THAT AIRCRAFT AND ENGINE. THIS ONE LASTED 35.4 HOURS.  UNIT REPLACED BY OVERHAULED ON	E.  (X)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001033000006	20010330	00006	CE  	2001	3	30	CA001017010      	1	20001004	G	5521	5061000090	BRACKET         			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4478 								(CAN) DURING A ROUTINE MAINTENANCE, IT WAS OBSERVED THAT THERE WAS A CRACK ON THE ELEVATOR INBOARD RIB BRACKET,  UPON DI	SASSEMBLY OF THE PART FOR REPLACEMENT, IT WAS NOTICED THAT THE INBOARD RIB WAS ALSO CRACKED IN THE SAME AREA. THE CRACK 	ON THE RIB WAS FROM A RIVET HOLE. THIS PROBLEM HAS BEEN REPORTED BY US INITIALLY ON AIRCRAFT.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2000112000033	20001120	00033	WP  	2000	11	20	CA001017011      	2	20000724	G	7250	31081821	TURBINE WHEEL   	GARRTT      	310355011   						GARRTT	TPE331	TPE33110U   	01514	WP  					T/E OF BLADE	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3796 								(CAN) ENGINE REMOVED FOR HIGH TAXI AND GROUND IDLE SNAG.  DISASSEMBLY REVEALED NR 1 COMPRESSOR IMPELLER HAD A PIECE BROK	EN OUT OF THE TRAILING EDGE OF 1 BLADE .085 INCH UP FROM THE PLATE .480 INCH FROM THE OUTER RIM OF THE PLATE. THE RESULT	ING DAMAGE DOWN STREAM FROM THE NR 1 IMPELLER IS EXTENSIVE.  IT CONSISTS OF 3101829 SHROUD, 3103496 DIFFUSER, 893482, NR	 2 IMPELLER, 893384 DIFFUSER, 3102022 HOUSING, 3108164-2 NR 1 ROTOR, 3102106-10 NR 2 ROTOR, 3102655-2 NR 3 ROTOR, 310151	3-17 STATOR, 3101515-6 STATOR, 5 OF 3101846 NOZZLE SEGMENTS, 12 OF 3103128 SHROUD SEGMENTS.  (X)							4	T			E4WE				 
2000112000034	20001120	00034	CE  	2000	11	20	CA001018003      	1	20000915	G	5540	995241791	SPRING          	BEECH       	100600012   	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					END OF SPRING	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2469 								(CAN) DURING UNSCHEDULED MAINTENANCE, BOTH LT AND RT RUDDER RETURN SPRINGS WERE FOUND BROKEN.  NO FLIGHT CONTROL PROBLEM	S WERE REPORTED FROM THE FLIGHT CREW.  THE SPRINGS WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THESE RETURN SPRI	NGS ARE AN IMPROVED VERSION CHANGED AS A RESULT OF AN OPTIONAL SERVICE BULLETIN. THE IMPROVEMENT WAS A LONGER SERVICE LI	FE.  (X)			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001033000008	20010330	00008	SW  	2001	3	30	CA001018004      	1	20000926	G	5551	22123	BRACKET         			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					STABILIZER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7826 								(CAN) ON 100 HOUR INSPECTION, LOWER STABILIZER ATTACHMENT BRACKET, WHICH SPANS BETWEEN TAIL POST AND STAB AFT SPAR FITTI	NG, WAS FOUND CRACKED APPROXIMATELY 1 INCH UP FROM LOWER WELD AREA. CRACKS FOUND ON BOTH SIDE ANGLES.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2000112000035	20001120	00035		2000	11	20	CA001018005      	4	20000928	G	2562	BS2166	BATTERY         	NARCO       	ELT10C      	CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					BATTERY	WRONG PART      	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						81688					(CAN) ELT WAS EQUIPPED WITH A NON-APPROVED BATTERY FOR THE ELT TYPE.  REF:  ANO B014 EDITION 4, NOVEMBER 20, 1998.  (X)						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001033000009	20010330	00009	EA  	2001	3	30	CA001018006      	2	20000921	G	8550	LW13388	GASKET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H1AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	OIL SYSTEM	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			240  								(CAN) OIL FILTER ADAPTER REMOVED FOR INSPECTION OF GASKET IN RESPONSE TO EMERGENCY AD 2000-18-53 AND FOUND GASKET TO BE 	IN A MUSHY, SOFT, DETERIORATING CONDITION, RATHER THAN THE FIRM RUBBER IT IS SUPPOSED TO BE LIKE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001033000010	20010330	00010	EA  	2001	3	30	CA001018007      	2	20000921	G	8550	LW13388	GASKET          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					OIL SYSTEM	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			200  								(CAN) OIL FILTER ADAPTER REMOVED FOR INSPECTION OF GASKET IN RESPONSE TO EMERGENCY AD 2000-18-53 AND FOUND GASKET TO BE 	IN A MUSHY, SOFT DETERIORATING CONDITION, RATHER THAN THE FIRM RUBBER IT IS SUPPOSED TO BE LIKE.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2001011105393	20010111	05393	CE  	2001	1	11	CA001018011      	1	20000926	G	6100		BEARING         	MCAULY      	C2A34C204   	CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1694 	317  		765389					(CAN) PROPELLER PARTS CORRODED BEYOND REPAIR.  BLADE BEARING RACES AND BALLS.  BLADE SPLIT RETAINING RINGS.  PISTON AND 	PISTON PINS.  CYLINDER ACTUATING PINS.  NOTE: THESE PARTS CORRODED AFTER 6 YEARS, NOW REGULATION IS 10 YEARS.  (X)					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2001033000016	20010330	00016		2001	3	30	CA001018016      	4	20001003	G	3418	727422	CIRCUIT BREAKER 			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      	 	EA  					STALL WARNING	TRIPPED         	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) PILOT DEPARTED AIRPORT, A GEAR UP SELECTION WAS MADE AND THE GEAR DID NOT RETRACT. THE CONTROL CB WAS POPPED. PILO	T ELECTED TO RETURN TO BASE TO HAVE IT CHECKED OUT. AIRCRAFT WAS PUT ON JACKS AND GEAR SWINGS WERE CARRIED OUT AND NOTHI	NGWAS FOUND. FURTHER INVESTIGATION SHOWED THE CONTROL CB WAS PULLED THE NIGHT BEFORE FOR MAINTENANCE REASONS. THE CB WAS	 NOT RESET AND NO ONE NOTICED UNTIL THE ARICRAFT WAS IN THE AIR AND THE GEAR WOULD NOT RETRACT.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001033000017	20010330	00017	EA  	2001	3	30	CA001018017      	1	20000928	G	3230	6A05533001	SPRING          	WIPLINEINC  	8000        	DHAV  	DHC3  	DHC3        	2800202	EA  										MLG	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			AP	APPROACH       	1			CA											(CAN) PILOT COMPLAINED OF NO GEAR DOWN AND LOCK INDICATION - RT MAIN GEAR. UPON INSPECTION FOUND LOCK SPRING BROKEN AND 	HALF MISSING, PLUS COVER TORN AWAY. LOCKING MECHANISM FOUND NON FUNCTIONAL DUE TO STRAIN OF BOLT BECOMING BENT WHEN FORW	ARD LOCK CONTACTED GEAR TUNNEL TOP. SPRING AND BOLT WERE REPLACED. FUNCTION TESTED - OK. AIRCRAFT WAS RETURNED TO SERVIC	E. IT SHOULD BE FURTHER NOTED THAT THE OTHER MAIN GEAR LOCK SPRING WAS FOUND CRACKED AND REPLACED AT THE SAME TIME.			1	H	7	1 	3R			 	A815    					 
2000112000036	20001120	00036	SO  	2000	11	20	CA001019003      	2	20000920	G	8530	ST68ER	CYLINDER        	CONT        		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	INTKE & EXH VALV	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1702 			286771R					(CAN) DURING ROUTINE MAINTENANCE, A LOW DIFFERENTIAL COMPRESSION READING WAS NOTED ON THREE OF THE SIX CYLINDERS.  IT WA	S ALSO NOTED THE LEAKAGE WAS APPARENTLY COMING FROM THE EXHAUST VALVES ON TWO CYLINDERS AND FROM THE INTAKE VALVE ON ANO	THER. THE REMAINING THREE CYLINDERS ALSO SHOWED A DECREASED READING COMPARED TO PREVIOUS CHECKS ON RECORD.  ALL SIX CYLI	NDERS WERE REMOVED AND FORWARDED TO AN ENGINE REPAIR FACILITY FOR EVALUATION.  THE CYLINDERS WERE REPAIRED WITH NEW PART	S AS NECESSARY.  FIVE OF THE INTAKE VALVES ARE SHOWING THE FACE OF THE VALVE WORN BYEOND GRINDING LIMITS.  ALL OF THE GU	IDE AND STEM WEAR WAS DEEMED NORMAL CONSIDERING THE AMOUNT OF TIME ON THESE CYLINDERS.  (X)	1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2000112000037	20001120	00037	EU  	2000	11	20	CA001019005      	1	20001002	G	3233	9603001111	ACTUATOR        	PILATS      	5322012039  	PILATS	PC12  	PC1245      	       	EU  										NOSE SHAFT SEAL	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA			1423 								(CAN) DURING AN ANNUAL INSPECTION, A LEAK WAS NOTED ON THE NOSE GEAR ACTUATOR.  THE ACTUATOR WAS NOTED LEAKING IN THE SH	AFT SEAL. THE ACTUATOR WAS REPLACED WITH A SERVICEABLE SPARE AND WILL BE MONITORED ON A REGULAR BASIS TO DETERMINE INTEG	RITY.  (X)				1	L	7	1 	3T			RT	A78EU   					 
2000112000038	20001120	00038	CE  	2000	11	20	CA001019008      	1	20000913	G	2730	05341221	ELEVATOR        			CESSNA	172   	172S        	2072439	CE  										BELLCRNK BRG HOL	WORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			154  								(CAN) ELEVATOR WORN.						1	H	7	1 	3O			NT	3A12    					 
2001033000023	20010330	00023	EA  	2001	3	30	CA001019009      	2	20000911	G	8520		STUD            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ROCKR CAM	BROKEN          	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THIS INCIDENT OCCURRED 30 MI EAST OF ATIKOKAN. CREW CONTINUED FLIGHT UNITL REACHING THE ATIKOKAN AIRPORT. FAILURE 	OF NR 2 CYLINDER EXHAUST ROCKER CAM STUD. THE CONDITION OF THE BROKEN STUD AND NUT WOULD INDICATE THAT THE NUT WAS INSTA	LLED IN A CROSS THREADED POSITION; THEREFORE IF A TORQUE WAS USED, THERE WAS NOT SUFFICIENT TORQUE ON THE ROCKER CAM TO 	HOLD IT TIGHT. COMPLETE CYLINDER ASSEMBLY CHANGED WITH SERVICEABLE UNIT. ENGINE GROUND RUN WAS NORMAL. AIRCRAFT RETURNED	 TO SERVICE.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001032000087	20010320	00087	NM  	2001	3	20	CA001019010      	1	20000921	G	5754	65173531	RIB             			BOEING	727   	72725       	1384006	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					NR 8 SLAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE A CHECK IT WAS NOTICED THAT THE NR 8 SLAT ACTUATOR MOUNT WAS CRACKED AT THE ROD END ATTACH POINT.	 SLAT WAS REMOVED AND MOUNT BRACKETS AND RIB FOUND TO BE BROKEN. SLAT WAS REPLACED AND AIRCRAFT RELEASED. REPLACEMENT PE	R BOEING M.M. 27-81-11.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001033000024	20010330	00024	WP  	2001	3	30	CA001019011      	2	20000922	G	7200	NAS1303	BOLT            	GARRTT      	TFE7312     	AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					ENGINE	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						P73211					(CAN) ENGINE AFTERBODY LT FOUND SEVERAL FASTENERS WERE NOT NAS 1303 PER FALCON 10 I.P.C. 54-22-05 PAGE 1-1 - INCORRECT H	ARDWARE, REPLACED BY CORRECT HARDWARE PER FALCON 10 IPC 54-22-05 PAGE 1-1.					2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2000103100107	20001031	00107	EA  	2000	10	31	CA001019012      	2	20000925	G	7414	M3100	IMPULSE COUPLING	SLICK       	4372        	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					LATCHING PAWL	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2135 			96100405					(CAN) A STUDENT PILOT REPORTED ENGINE WOULD NOT START.  MAINT NOTICED IMPULSE COUPLING WAS NOT SNAPPING (THE LT MAGNETO 	HAS IMPULSE COUPLING ONLY).  LT MAGNETO WAS REMOVED, FOUND ONE OF IMPULSE COUPLING PAWL RIVETS HAD SHEARED CAUSING PAWL 	TO FALL DOWN BEHIND REMAINING PAWL NOT ALLOWING IT TO ENGAGE ON MAGNETO STOP PIN.  MAGNETO ROTOR SHAFT WAS ALSO DAMAGED 	BEYOND REPAIR BY UNATTACHED PAWL.  SLICK  500 HR INSP REQUIRES AN INSP BE CARRIED OUT ON IMPULSE HUB ASSY PAWL AND THEIR	 RETAINING RIVETS - A MEASUREMENT IS GIVEN IN SLICK MAINT MANUAL FOR CLEARANCE BETWEEN PAWL BOSS  AND PAWL PLATE.  (X)		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2001032000088	20010320	00088	NM  	2001	3	20	CA001019013      	1	20000926	G	2710	82700566S001	CONTROL CABLE   			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					LT AILERON	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA				6500 							(CAN) PILOT REPORTED ON WALKAROUND, ITEM STICKING OUT OF FLAP WELL, MAINTENANCE CALLED IN, DISCOVERED BROKEN CABLE STRAN	DS AT STATION YW 174 AT THE FAIR LEAD. ITEM WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001033000025	20010330	00025	NE  	2001	3	30	CA001019014      	2	20000926	G	7532	310533701	GASKET          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					PORT ENGINE	BLOWN           	W				A		 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			8927 								(CAN) LIAT, OPERATOR MAINTENANCE CONTROL REPORT:AFTER TAKEOFF, PORT ENGINE TORQUE, STARTED TO FLUCTUATE UNCONTROLLABLY. 	POWER LEVER WAS RETARDED TO AVOID OVER-TORQUE CONDITION, FLUCTUATIONS CONTINUED, AND PORT CONDITION LEVER WAS MOVED TO S	TART/FEATHER. AIRCRAFT RETURNED TO LAND UNEVENTFULLY. ENGINE REPORT:ON EXAMINATION HBOV GASKET WAS BLOWN, GASKET WAS REP	LACED AND EGR CARRIED OUT SATISFACTORY. AIRCRAFT RETURN TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001033000027	20010330	00027	CE  	2001	3	30	CA001019017      	1	20000814	G	3397	99131	WIRE            	AVTECH      		CESSNA	560   	560XL       	2076702	CE  										LT CONSOLE	BURNED OUT      	W				B	H			EMER. DESCENT           	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA			96   			600					(CAN) UPON DESCENT INTO MUSKOKA CAPTAIN NOTICED SMOKE BY HIS L/H KNEE, AT FIRST MINOR, THEN INTENSIFIED. CAPTAIN DECLARE	D AN EMERGENCY AND INITIATED AN EMERGENCY DESCENT AND LANDING AT MUSKOKA. PASSENGERS AND CREW DEPARTED THE AIRCRAFT WITH	 NO INJURIES. MAINTENANCE PERSONEL DISASSEMBLED COCKPIT PILOTS SIDE FOR INVESTIGATION OF SMOKE IN THE COCKPIT. MAINTENAN	CE PERSONEL FOUND SOME OVERHEATED/ BURNED WIRING AT THE PC038 CONNECTOR TO THE EMERGENCY LIGHTING BATTERY. THE BATTERY W	AS SENT TO CESSNA FOR EVALUATION AND THEY REPORTED THAT ALTHOUGH THERE WERE SOME CHAFED WIRES INSIDE THE BATTERY PACK, T	HEY WERE NOT THE SOURCE OF ANY SMOKE.	2	L	7	2 	4F			RT	A22CE   					 
2001032000095	20010320	00095	NM  	2001	3	20	CA001019025      	1	20000912	G	4920	49600011	APU             			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					APU BAY	FAILED          	W				D				RETURN TO BLOCK         				T	J		ENGINE CASE PENETRATION   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PUSH BACK AND ENGINE START OF RIGHT HAND ENGINE, AUXILIARY POWER UNIT FAULT LIGHT AND SHUTDOWN. AUXILIARY P	OWER UNIT HAD INTERNAL SEIZURE, CAUSING TURBINE TO BE DISCHARGED. METAL PIECE WAS EJECTED OUT OF EXHAUST PORT. AUXILIARY	 POWER UNIT CHANGED AND OPERATION CHECK CARRIED OUT. FURTHER INFORMATION WILL FOLLOW AFTER INVESTIGATION.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001032000096	20010320	00096	NM  	2001	3	20	CA001019026      	1	20000917	G	2520	86526002	SEAT BACK       			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					ROW 22	COLLAPSED       	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, PASSENGER SEATS 22H & 22K BACKREST METAL FRAME COLLAPSED. BACKREST FELL ON THE PASSENGERS SEATED IN	 23 H/K. NO REPORTED INJURY. SEAT ASSEMBLY REPLACED.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001011105419	20010111	05419	WP  	2001	1	11	CA001019027      	1	20000826	G	5610	9615059002	CONTROLLER      	DOUG        	DC932       	DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					APU	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						47198					(CAN) THE CAPTAIN RECEIVED A SUBSTANTIAL ELECTRICAL SHOCK WHILE AIRCRAFT WAS PARKED, FROM AROUND THE EDGE OF THE SLIDING	 WINDOW.WITH THE AIRCRAFT ON EXTERNAL POWER. THE CAPTAIN WAS SEATING IN THE FLIGHT DECK, IS HAND TOUCHED THE EXTERIOR SK	IN OF THE AIRCRAFT THROUGH THE OPEN WINDOW. THE WINDOW WAS REPLACED. SECOND OCCURRENCE.  WITH AIRCRAFT ON AUXILIARY POWE	R UNIT, AND GROUND POWER DISCONNECTED NO SHOCK FELT.CLEANED EXTERNAL POWER RECEPTACLE, CHECKED FOR GROUND BETWEEN PIN "N	" TO GROUND, CHECKED FOR GROUND BETWEEN SLIDING WINDOW FRAME TO GROUND. "0" VOLT. AIRCRAFT CONSIDERED SERVICEABLE.		2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001032000097	20010320	00097	WP  	2001	3	20	CA001019029      	1	20000903	G	3246	MS2000634	BOLT            			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					LT NLG WHEEL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING WALK AROUND INSPECTION OF AIRCRAFT, LEFT HAND NOSE LANDING GEAR WHEEL ASSEMBLY, FOUND WITH ONE TIE BOLT MIS	SING. (TIE BOLT ATTACHES HUB HALVES TOGETHER) SUSPECT TIE BOLT CRACKED AND SEPARATED FROM WHEEL HUB. TIRE ASSEMBLY REPLA	CED AS PER MAINTENANCE MANUAL REF. 32-40-02.				2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001033000029	20010330	00029	SW  	2001	3	30	CA001020004      	1	20000928	G	2910	222040125001	SUPPORT BRACKET 			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101650C3 	41560	NE  					HYD ACTUATOR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3541 								(CAN) FOUND UNSATISFACTORY HYDRAULIC ACTUATOR SUPPORT REMOVED FOR DIMENSIONAL VERIFICATION, RESULTS SATISFACTORY;   TRAN	SMISSION UPPER & LOWER CASE ASSY INSP  RESULTS SATISFACTORY;   HYDRAULIC ACTUATOR SUPPORT REINST ON A/C WITH NEW HARDWAR	E.				1	G	7	2 	3U	3	U	 	H9SW    	E5NE				 
2001033000030	20010330	00030		2001	3	30	CA001020005      	4	20000817	G	3100	B19030FA	MODULE          			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					VEMD TOP SCREEN	FAILED          	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				H	 	 	ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA			165  								(CAN) VEMD. MODULE 1 WAS DISAPPEARING MOMENTARILY.						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2001033000031	20010330	00031	NE  	2001	3	30	CA001020008      	2	20000907	G	7250	UL20025	SHAFT           			BOEING	757   	757*        	       	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					HP TURBINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			41808								(CAN) DURING A SCHEDULED ENGINE VISIT AT RRC, THE HP TURBINE STUB SHAFT WAS FOUND TO BE EXCESSIVELY CORRODED AROUND BOLT	 HOLES. RRC LAB REPORT CONFIRMED CORROSION AND THE STUB SHAFT WAS SCAPPED AND A NEW REPLACEMENT FITTED.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001033000032	20010330	00032	NE  	2001	3	30	CA001020009      	2	20000914	G	7230	UL16758	DRUM            								RROYCE	RB211 	RB211535E4  	54555	NE  					COMPRESSOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			38465	7458 		DN36651					(CAN) INTERMEDIATE PRESSURE COMPRESSOR ROTOR DRUM P/N UL16758 S/N 36651 EX ESN 30534 & MODULE 02 DM3560 WAS SNAGGED AT I	NIT INSP DURING OVERHAUL OF THIS MODULE AT RRC DUE TO CRACKING FOUND IN D OVE TAIL OF BLADE SLOTS OF STAGE 6 & STAGE 3. 	CRACKS CAN BE DETECTED BY VISUAL INSP ALONE. STAGE 6 DOVE TAIL SLOTS FEATURE CRACKS IN PRESSURE FACE TO RUNOUT RADIUS OF	 DOVE TAIL SLOTS. WORST AFFECTED DOVE TAIL AT NR 7 POS WHICH FEATURES AN OPEN CRACK APROX 0.410 LONG & EXTENDS ONTO FWD 	FACE. ROTOR WILL BE SENT BACK TO ROLLS ROYCE, DERBY, UK FOR INVESTIGATIO N. NO RPTS FROM OPERATOR OF ANY ABNORMAL MODE O	F OP.2000-11-06TC:  FOLOW-UP DETAILS REQD						4	F			E12EU				 
2001033000033	20010330	00033	CE  	2001	3	30	CA001020010      	1	20000906	G	3246	C1630030201	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FISSURE SUR LE REBOURD DE JANTE A PROXIMITE DES LEVRE POUR TENIR LES ENJOLIEURS DE ROUE. (WHEEL CRACKED)						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001032000101	20010320	00101	NE  	2001	3	20	CA001020011      	2	20000809	G	7260	AS20625	NUT             								RROYCE	RB211 	RB211535E4  	54555	NE  					FUEL PUMP GEAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS ENGINE BELONGING TO CANADA 3000 WAS ROUTINELY INSPECTED AT TSN 34,557.3 & TSR 10.164.5 HOURS. FOUND 1 OFF NUT	 (AS20625) IN THE MCD CAVITY. THE ENGINE WAS REMOVED AND SENT TO RRC. UPON INVESTIGATION AT RRC IT WAS FOUND THAT THE NU	T HAVE COME LOOSE FROM ONE OF THE STUDS ATTACHING THE HP FUEL PUMP IDLER GEAR OUTER RACE TO THE FRONT HOUSING OF THE GEA	R. NO DAMAGE WAS FOUND ON THE GEARBOX. THE MODULE WAS OVERHAULED TO A LEVEL 4 WORK SCOPE AND RETURNED TO SERVICE.								4	F			E12EU				 
2000103100108	20001031	00108	EA  	2000	10	31	CA001020012      	2	20000830	G	7414		SWITCH          	SLICK       	6250        	PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  					RT MAGNETO	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3801 			90120008					(CAN) PILOT PHONE A.M.E., SAYS HE HAS NO MAG DROP ON ONE MAG.  ASKED IF HE DID A LIVE/DEAD MAGS CHECK AT LAST SHUTDOWN, 	HE SAID HE FORGOT EVEN AFTER HE WAS REMINDED TO DO SO ON PREVIOUS OCCASION.  BROKEN WIRE AT TERMINAL ON MAGNETO RIGHT.  	REPLACED TERMINAL.  (X)				1	L	7	1 	3O	3	O	 	1A15    	E295				 
2000103100109	20001031	00109	EA  	2000	10	31	CA001020014      	2	20000914	G	7300	LW10682	CONTROLLER      	LYC         	TIO540A2B   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					LEFT	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				1215 		L161761					(CAN) OIL LEAK DETACHED DURING HOSE REPLACEMENT.  UNSCHEDULED REMOVAL.   INSTALLED OVERHAULED UNIT.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000103100110	20001031	00110	SO  	2000	10	31	CA001020015      	1	20000921	G	3244	0613160	TIRE            	PARKERHANFIN	401402800   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					TIRE	CUT             	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			1059 								(CAN)  DETECTED FIRST CUT AT REMOVAL OF TOW-BAR.  DETECTED TWO MORE CUTS .50 INCH SPACED APPROX 10 INCHES FROM EACH OTHE	R, WHEN INSPECTING TIRE AFTER REMOVAL.  IT WAS REPORTED THAT AIRCRAFT WAS LANDED ONCE WITH PILOT APPLYING BRAKES BEFORE 	NOSE GEAR TOUCHED GROUND.  INSPECTED, NO SIGNS OF HARD LANDING.  HOWEVER, DAMAGE MAY HAVE BEEN DONE WHEN APPROACHING AIR	CRAFT WITH TOW-BAR OR AT HANGAR ENTRANCE,  DOOR SILL HAVING HUMPER-GUIDES.  NOTE:  HANGAR DOORS BEING MODIFIED AND TRAIN	ING GIVEN TO PERSONNEL ON HOOKING TOW BAR.  (X)		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000103100111	20001031	00111	SO  	2000	10	31	CA001020016      	1	20000927	G	2822	481802	PUMP            	PIPER       	DWG54300    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT WING ROOT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			3332 			317405479					(CAN)  THIS PUMP TURNS ON FROM ENGINE START UNTIL SHUT DOWN.  AT THE END OF GING TO LEG, PILOT NOTICED FUEL PRESSURE HIT	TING VARY  MIN (25 PSI)A T IDLE 750 RPM, UNBURN RUNNING OK AT 1000 RPM.  (CARGO FLIGHT ON RETURN LAG, TAKEOFF AND CLIMB 	OK.  DURING CRUISE, RIGHT FUEL BOOST PUMP INOP  LIGHT CAME ON FOR THE REST OF THE FLIGHT.  PILOT PULLED CIRCUIT BREAKER 	OFF.  AFTER LANDING, PUMP CHECKED AS DEAD, INOP, WITH EFFORT TO START WHEN TAPPED ON.  REPLACED PUMP.  NOTE:  CHECKED AL	L AIRCRAFT ASM, SBS, SLS/INSP PROG, NO TBO PRESCRIBED.  (X)		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000103100112	20001031	00112	EA  	2000	10	31	CA001020017      	2	20000928	G	7314	RG9080J4A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				565  		C9728					(CAN) RECURRING PROBLEM.  AIRCRAFT HAS FLOWN 48.7 HOURS SINCE LAST OCCURRENCE AND REPAIRS.  THIS TIME FOLLOWS REPLACEMEN	T OF IN-LINE ELECTRIC FUEL BOOST PUMP 481-802, AFTER FAILURE.  FUEL SERVO SCREEN CHECKED, NOZZLES REMOVED, FLUSHED LINES	 SERVO TO NOZZLES.  INSTALLED NEW NOZZLE BODIES 2541946.  REPLACED FUEL PUMP TOO. TEST FLIGHT.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032000102	20010320	00102	EU  	2001	3	20	CA001020019      	1	20000913	G	3411		PITOT TUBE      			BRAERO	DH125 	BAE125800A  	1500285	EU  										PITOT/STATIC SYS	CLOGGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) PILOTS REPORTED LOSS OF ALL PITOT-STATIC INSTRUMENTATION ON TAKEOFF - ALL ADC SUPPLIED INSTRUMENTATION FLAGGED & N	O INFO FROM STANDBY EQUIP. A/C RETURNED TO AIRPORT. IDENT INHIBIT LIGHT  WAS ON - UPON LDG.  ALL INSTRUMENTATION RETURNE	D TO NORMAL. - SUSPECT NR 2 PITOT WAS PLUGGED, WEATHER WAS CLEAR, UFR - BASED ON FAILURE NR 2 PITOT SYS DISASSEMBLED AND	 BLOWN CLEAR - REASSEMBLED & TESTED PE R ST0571 APPENDIX B STALL 3 SYS RESET & BOTH ADC TESTED, SWITCHING FROM 1-2 TESTE	D SERVICEABLE, BOTH BACKUP BATTERY PACKS SERVICED & REINSTALLED - UNABLE TO DUPLICATE SNAG. A/C RELEASED ON CONDITION OF	 SATISFACTORY TEST FLT.- TEST FLT PERFORMED SERVICEABLE ALL EQUIP OP NORMALLY. A/C RT-SRV.	2	L	7	2 	4F			RT	A3EU    					 
2001032600417	20010326	00417	SO  	2001	3	26	CA001020020      	2	20000929	G	7414	36066	DRIVE GEAR      			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					MAGNETO	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			855  								(CAN) L/H MAGNETO (SLICK 4310 S/N 99042051) HAS BEEN REMOVED FOR 500 HR INSPECTION. FOUND ONE (1) TOOTH ON THE DRIVE GEA	R WAS MISSING. REPLACED DRIVE GEAR (P/N 36066). REMOVED ENGINE OIL SUMP AND FOUND THE MISSING GEAR TOOTH.					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2001031300040	20010313	00040	WP  	2001	3	13	CA001020021      	1	20000920	G	7810	90632323	TAILPIPE        			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					RT ENGINE	BROKEN          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW OBSERVED A RT ENGINE ZONE 1 FIRE WARNING, THE ENGINE WAS SHUTDOWN AND THE FIRE WARNING WENT OUT PR	IOR TO FIRING THE FIRE EXTINGUISHER. RECTIFICATION: THE RT ENGINE TAIL PIPE, UNIVERSAL JOINT P/N 906323-23 REPLACED, SYS	TEM TESTED ON GROUND AIRCRAFT RELEASED FOR FLIGHT.				2	L	7	2 	4R	4	T	 	6A6     	E282				 
2001031300041	20010313	00041	EA  	2001	3	13	CA001020022      	1	20000923	G	3250		CONTROL UNIT    			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					NLG STEERING	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PIC REPORTED TO YVP FSS (22:40 H LCL) THAT THE NOSE WHEEL STEERING TILLER WAS STUCK IN RT POSITION. THE AIRCRAFT L	ANDED WITHOUT INCIDENT.NOSE WHEEL STEERING SYSTEM INSPECTED WITH AIRCRAFT ON JACKS; CABLE TENSION VERIFIED, HYDRAULIC SY	STEM CHECKED, ACTUATOR TORQUE LINKS ETAL - TAXI CHECKED 90 - NO FAULT FOUND. LACK OF HYDRAULIC PRESSURE DUE TO CB NOT CL	OSED CONSIDERED PROBABLE.NO SUBSEQUENT PROBLEM REPORTED BY FLIGHT CREWS.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2001031300042	20010313	00042	NE  	2001	3	13	CA001024002      	2	20000822	G	7200		ENGINE          			CNDAIR	CL601 	CL6013A     	8070802	EA  	GE    	CF34  	CF343A      	30015	NE  					RIGHT	NOISY           	W				E				ENGINE SHUTDOWN         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		DE	DESCENT        	1			CA			4650 	4650 							(CAN) CREW REPORTED ZERO OIL PRESSURE ON RT ENGINE DURING FLIGHT FROM ARAPAHO, COLORADO TO WASHINGTON, DC, AS THEY PASSE	D OVER ST. LOUIS AT FL370 WITH ALL OTHER PARAMETERS NORMAL (INCLUDING OIL TEMP). CORP WINGS MAINTENANCE CONTACTED VIA FL	IGHT PHONE AND PILOTS DIRECTED TO DROP TO FL330 AND SEE IF ANY CHANGE. NONE REPORTED, SO PILOT CONTINUED FLIGHT. ON DESC	ENT IN PREPARATION FOR APPROACH TO FL250, CREW HEARD 2 DISTINCT POPPING SOUNDS FROM THE RT ENGINE AND ELECTED TO SHUT TH	E ENGINE DOWN WHILE OVER VIRGINIA. AIRCRAFT DIVERTED TO DULLAS IN THE NORMAL LANDING PATTERN, PERFORMED UNEVENTFUL SINGL	E ENGINE LANDING AND TAXIED TO THEIR FBO. 2000-10-31TC: FOLLOW-UP REPORT EXPECTED FROM ORIGINATOR.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300043	20010313	00043	EA  	2001	3	13	CA001024003      	1	20001012	G	2434	2CM70D6A	GENERATOR       			CNDAIR	CL215 	CL2151A10   	       	EA  										GEN BAY	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1770 	109  							(CAN) NORMAL TIME BETWEEN OVERHAULS FOR THIS UNIT IS 1300 HOURS; THIS GEN ONLY HAD 109 TSO. THE FOLLOWING PROBLEMS WERE 	FOUND:  BRUSHES WERE WORN, FOUR SCREWS WHICH RETAIN A PLATE ON THE GEN WERE COMPLETELY WORN OUT EVEN IF THEY HAD ALWAYS 	BEEN HELD TOGETHER WITH LOCK WIRE. GEN CHANGED AND DEFECTIVE PIECE SENT FOR OVERHAUL.				2	H	7	2 	4R			 	A14EA   					 
2001031300044	20010313	00044		2001	3	13	CA001024004      	4	20000923	G	3418		WARNING SYSTEM  			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	ACTIVATED       	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE CREW ABORTED TAKEOFF DUE TO A STALL FAIL CAUTION MESSAGE. AFTER REDUCING THE SPEED WHEN ABORTING THE TAKEOFF, 	THE STALL FAIL MESSAGE CLEARED ITSELF. BREAKERS RESETTED AND AIRCRAFT RETURNED TO SERVICE (EICAS 2000 INCORPORATED ON TH	IS A/C).				2	L	7	2 	4F			RT	A21EA   					 
2001031300045	20010313	00045		2001	3	13	CA001024005      	4	20000923	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) A STALL FAIL CAUTION MESSAGE APPEARED ON TAKEOFF ROLL AT 70 KTS, FOLLOWED BY A CONFIG SPLRS WARNING MESSAGE (THE T	AKEOFF WAS NOT ABORTED).THE STALL COMPUTER WAS RESET (EICAS 2000 INCORPORATED ON THIS A/C).					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300046	20010313	00046		2001	3	13	CA001024006      	4	20000923	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE STALL FAIL CAUTION MESSAGE APPEARED ON TAKEOFF ROLL AT 70 KTS.THE STALL COMPUTER WAS RESET (EICAS 2000 INCORPO	RATED ON THIS A/C).					2	L	7	2 	4F			RT	A21EA   					 
2001031300047	20010313	00047		2001	3	13	CA001024007      	4	20000923	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA											(CAN) THE FLIGHT CREW REPORTED A STALL FAIL CAUTION MESSAGE BEFORE TAXI OUT.THE STALL COMPUTER WAS RESET (EICAS 2000 INC	ORPORATED ON THIS A/C).					2	L	7	2 	4F			RT	A21EA   					 
2001031300048	20010313	00048	EA  	2001	3	13	CA001024008      	1	20000923	G	2761	4916405	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										SPOILERS	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						1032					(CAN) AFTER TAKEOFF A FLIGHT SPOILERS FAULT STATUS MESSAGE APPEARED ON ED2. THE MAINTENANCE REPLACED THE SECU NR 2 AND T	HE LEFT FLIGHT SPOILER OUTBOARD PCU (P/N: 27000-3, S/N: MAL.3438).					2	L	7	2 	4F			RT	A21EA   					 
2001031300049	20010313	00049	EA  	2001	3	13	CA001024009      	1	20000923	G	2752	853D10018	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) CREW REPORTED FLAP FAIL MESSAGE AND FLAPS MOVEMENT STOPPED AFTER SELECTION FROM 0 TO 8 DEGREES DURING APPROACH. (N	OTE: SB 601R-27-111 WAS CARRIED OUT 3 WEEKS AGO.) THE MAINTENANCE FOUND THE FLEXSHAFT BETWEEN NR 3 & NR 4 ACTUATORS TWIS	TED/KINKED. CABLES REPLACED AND AIRCRAFT FERRIED TO SLC TO REPLACE THE ACTUATOR AS PER FAA AD 98-20-01.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300050	20010313	00050		2001	3	13	CA001024010      	4	20000927	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) STALL FAIL MESSAGE POSTED ON THE EICAS IN FLIGHT AT 250 KTS.STALL COMPUTER RESET. AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300051	20010313	00051		2001	3	13	CA001024011      	4	20000927	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF, ASSOCIATED WITH CONFIG SPOILERS WARNING.ABORTED TAKEOFF AT 80 KTS.	RESET STALL COMPUTER. SYSTEM OPS CHECKED GOOD.AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300052	20010313	00052		2001	3	13	CA001024012      	4	20000927	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE POSTED UPON TAKEOFF, ASSOCIATED WITH CONFIG SPOILERS WARNING.ABORTED TAKEOFF AT 80 KTS.	RESET STALL COMPUTER. AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032600418	20010326	00418	NE  	2001	3	26	CA001024013      	2	20000929	G	7200		CARBON SEAL     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT ENGINE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB FLIGHT CREW NOTICED LEFT ENGINE OIL PRESSURE FLUCTUATION. AIRCRAFT RETURNED TO DEPARTING AIRPORT. LT 	ENGINE CARBON SEAL REPLACED. AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300053	20010313	00053	EA  	2001	3	13	CA001024014      	1	20000929	G	3260		VALVE           			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED A GEAR DISAGREE WARNING MESSAGE UPON SELECTION, AND THE NOSE LANDING GEAR DID NOT EXTEND.MAINTENANC	E REPLACED THE MAIN AND NOSE LANDING GEAR PRIORITY VALVES.					2	L	7	2 	4F			RT	A21EA   					 
2001031300054	20010313	00054	EA  	2001	3	13	CA001024015      	1	20000930	G	5210		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  										PAX DOOR	LACK OF LUBE    	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, PAX DOOR OUTER HANDLE MESSAGE POSTED ON EICAS, FOLLOWED QRH - RESTOWED SUCCESSFULLY. OUTER HANDLE C	ONFIRMED STIFF DURING STOWING AND EJECTION. ADJUSTED OUTER HANDLE SUPPORT BOX, AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300055	20010313	00055	EA  	2001	3	13	CA001024016      	1	20000930	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										RT WING TE FLAPS	DEFECTIVE       	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA			916  								(CAN) UPON FLAP SELECTION FROM 20 TO 0 DEGREES, FLAP FAIL MESSAGE ON EICAS. RT BPSU REPLACED, AIRCRAFT BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001031300056	20010313	00056	EA  	2001	3	13	CA001024017      	1	20000930	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				F				ACTIVATE FIRE EXT.      				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FLAP FAIL MESSAGE APPEARED ON FLIGHT (CRUISE) WHEN FLAPS AT 0 DEGREES.RESET THE FLAP SYSTEM, AIRCRAFT BACK IN SERV	ICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300057	20010313	00057	EA  	2001	3	13	CA001024018      	1	20000930	G	2742		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					HORIZONTAL STAB	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) WHEN OPERATING THE PILOT/CO-PILOT STAB TRIM SWITCHES, THE STAB TRIM CHANNEL NR 1 INOP MESSAGE APPEARS.REPLACED THE	 HSTA AND MCU. SERIAL NUMBERS NOT AVAILABLE AT THIS TIME. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300058	20010313	00058	EA  	2001	3	13	CA001024019      	1	20001001	G	3242		BRAKE ASSY      			CNDAIR	CL600 	CL6002B19   	       	EA  										RT MLG	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT WAS TAXIING TO POSITION WITH 34 PEOPLE ON BOARD, CREW REPORTED THAT THEY FELT THE RIGHT SIDE BRAKES DRAGG	ING AND THEY ALSO REPORTED THAT ANOTHER AIRCRAFT HAD SEEN SMOKE COMING FROM RIGHT WHEELS. AIRCRAFT WAS STRANDED ON ACTIV	E TAXI WAY. RIGHT HAND INBOARD TIRE HAD BLOWN AND THE RIGHT HAND INBOARD BRAKE HAD LOCKED UP. THE BRAKE AND WHEEL ASSEMB	LY WERE REPLACED OPS CHECKED GOOD.			2	L	7	2 	4F			RT	A21EA   					 
2001031300059	20010313	00059	EA  	2001	3	13	CA001024020      	1	20001001	G	3230	4622	PRIORITY VALVE  			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) NOSE GEAR INDICATOR SLOW TO SEQUENCE WHEN GEAR PLACED TO DOWN POSITION. GEAR DISAGREE & NOSE DOOR OPEN WARNING MES	SAGES.MAINTENANCE REPLACED THE NOSE LANDING GEAR PRIORITY VALVE (P/N: 4622) AND ELECTICAL HYDRAULIC PUMP REPLACED (P/N: 	848847).				2	L	7	2 	4F			RT	A21EA   					 
2001031300060	20010313	00060		2001	3	13	CA001024021      	4	20001003	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE FLIGHT CREW REPORTED THE STALL FAIL CAUTION MESSAGE AT THE BEGINNING OF THE TAKEOFF AT 80 KTS, TAKEOFF WAS ABO	RTED. THIS IS AN AIRCRAFT WITH EICAS 2000 INCORPORATED. MAINTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVI	CE.				2	L	7	2 	4F			RT	A21EA   					 
2001031300061	20010313	00061		2001	3	13	CA001024022      	4	20001003	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE CREW REPORTED THE STALL FAIL CAUTION MESSAGE AT THE BEGINNING OF THE TAKEOFF AT 95 KTS, TAKEOFF WAS ABORTED.TH	IS IS AN AIRCRAFT WITH EICAS 2000 INCORPORATED. MAINTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300062	20010313	00062		2001	3	13	CA001024023      	4	20001003	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE CREW REPORTED THE STALL FAIL CAUTION MESSAGE ON CLIMB OUT.THE EICAS 2000 STATUS ON THIS AIRCRAFT IS UNKNOWN.MA	INTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300063	20010313	00063		2001	3	13	CA001024024      	4	20001003	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE CREW REPORTED THE STALL FAIL CAUTION MESSAGE AT THE BEGINNING OF THE TAKEOFF, TAKEOFF WAS ABORTED.THE EICAS 20	00 STATUS ON THIS AIRCRAFT IS UNKNOWN. MAINTENANCE RESET THE STALL COMPUTER, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300064	20010313	00064	EA  	2001	3	13	CA001024025      	1	20001007	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING LANDING, PILOTS WINDSHIELD CRACKED. LANDING UNEVENTFUL.AWAITING FOR PARTS TO REPLACE.						2	L	7	2 	4F			RT	A21EA   					 
2001031300065	20010313	00065	NE  	2001	3	13	CA001024026      	2	20001006	G	7250		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1	FAILED          	W				E	B	A		ENGINE SHUTDOWN         	EMER. DESCENT           	UNSCHED LANDING         		B	Y		SMOKE/FUMES/ODORS/SPARKS  	ENGINE STOPPAGE           		CL	CLIMB          	1			CA											(CAN) DURING CLIMB, NR 1 ENGINE EXPERIENCED AN UN-COMMANDED SHUT DOWN. FLIGHT CREW DECLARED AN EMERGENCY LANDING (UNEVEN	TFUL). THE AIRPORT FIRE DEPARTMENT FOAMED THE ENGINE AFTER LANDING BECAUSE OF VISIBLE SMOKE COMING OUT OF THE JET PIPE. 	THE ENGINE LPT HAD DAMAGE VISIBLE FROM THE EXHAUST. THE ENGINE WAS REPLACED.AIRCRAFT BACK IN SERVICE. 2000-10-31TC: FOLL	OW-UP REPORT EXPECTED FROM ORIGINATOR.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300066	20010313	00066	NE  	2001	3	13	CA001024027      	2	20001006	G	7532	32895902	BLEED VALVE     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF341A      	 	NE  					LT ENGINE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CREW REPORTED A WING ANTI-ICE DUCT WARNING MESSAGE IN CRUISE. UNABLE TO DUPLICATE THE PROBLEM ON GROUND, HOWEVER, 	UPON CHECKING THE SYSTEM, MAINTENANCE NOTICED THE 14TH STAGE SOV LT WOULD ALWAYS REMAIN OPEN, REGARDLESS OF THE SELECTIO	N IN THE COCKPIT. REPLACED THE LT 14TH STAGE SOV.AIRCRAFT BACK IN SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300067	20010313	00067	EA  	2001	3	13	CA001024028      	1	20001006	G	2740	70608	CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					HORIZONTAL STAB	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) CREW REPORTED SEVERAL STAB AND MACH TRIM CAUTION MESSAGES INTERMITTENT IN CLIMB AND CRUISE. REPLACED THE HSTCU, AI	RCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032600489	20010326	00489	EA  	2001	3	26	CA001024029      	1	20001006	G	7830		TORQUE BOX      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					THRUST REVERSER	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, AN UNUSUAL RUMBLING NOISE AND SOME VIBRATION WAS OBSERVED. ALL ENGINE PARAMETERS WERE NORMAL. CREW 	ELECTED TO DECLARE AN EMERGENCY LANDING AS A PRECAUTIONARY MEASURE. FOUND THE LT THRUST REVERSERS TORQUE BOX DAMAGED, AL	ONG WITH THE UPPER STANG FAIRING.DAMAGED PARTS REPLACED, AIRCRAFT BACK IN SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300068	20010313	00068	EA  	2001	3	13	CA001024030      	1	20001006	G	2740		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					HORIZONTAL STAB	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) CREW REPORTED A CONFIG STAB WARNING MESSAGE DURING TAKEOFF ROLL AND STAB NOSE UP BY ITSELF. ABORTED TAKEOFF AT 97 	KNOTS.NO FAULTS ON HSTCU NOR ON THE MDC. PERFORMED FULL OPERATIONAL CHECK OF STAB. NO FAULTS FOUND. AIRCRAFT RETURNED TO	 SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300069	20010313	00069	NE  	2001	3	13	CA001024031      	2	20001006	G	7314	99D671	FILTER          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					FUEL PUMP	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) CREW REPORTED A RT FUEL TO PRESSURE CAUTION MESSAGE IN DESCENT. MESSAGE WENT AWAY WHEN THE THRUST LEVERS WERE PUSH	ED FORWARD.MAINTENANCE REPLACEDTHE RT ENGINE FUEL FILTER ELEMENT AND RT ENGINE FUEL LO PRESS SWITCH. AIRCRAFT BACK IN SE	RVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300070	20010313	00070	EA  	2001	3	13	CA001024032      	1	20001006	G	2750	860D10018	FCU             			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, ON A FERRY FLIGHT, PILOT REPORTED A FLAPS HALFSPEED MESSAGE, QUICKLY FOLLOWED BY A FLAPS FAIL. A 0 	DEGREES FLAP LANDING WAS PERFORMED. REPLACED THE FECU.					2	L	7	2 	4F			RT	A21EA   					 
2001031300071	20010313	00071	EA  	2001	3	13	CA001024033      	1	20001006	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										RIGHT	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) FLAPS FAIL UPON SELECTION, CREW REPORTED THAT THE FLAPS DID NOT MOVE. RT BPSU REPLACED, AIRCRAFT BACK IN SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001031300072	20010313	00072	EA  	2001	3	13	CA001024034      	1	20001006	G	2421		IDG             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	LACK OF LUBE    	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) UPON TAKEOFF, NR 1 IDG DROPPED OFFLINE, ABORTED TAKEOFF. FOUND LEFT IDG OIL LEVEL LOW. SERVICED IDG PER AMM. AIRCR	AFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300073	20010313	00073	EA  	2001	3	13	CA001024035      	1	20001006	G	2740		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING 2 STAB TRIM TESTS, CHANNEL 2 FAILED INDICATED ON HSTCU FROM PANEL. REPLACED HSTCU, SYSTEM OPS CHECKED GOOD 	ON GROUND.AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300074	20010313	00074	EA  	2001	3	13	CA001024036      	1	20001006	G	5230		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					CARGO DOOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) CREW REPORTED A CARGO DOOR CAUTION MESSAGE DURING CLIMB. CREW RETURNED TO FIELD.LUBED CARGO DOOR HANDLE AND OPS CH	ECK PER AMM.AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300075	20010313	00075	EA  	2001	3	13	CA001024037      	1	20001006	G	5270		WARNING SYSTEM  	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					CARGO DOOR	ACTIVATED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						7028					(CAN) CREW REPORTED A CARGO DOOR CAUTION MESSAGE AFTER TAKEOFF. CREW RETURNED TO FIELD. OPS CHECKED PER AMM.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300076	20010313	00076		2001	3	13	CA001024038      	4	20001006	G	3417	607300001	TRANSDUCER      			CNDAIR	CL600 	CL6002B19   	       	EA  										ADC	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) CREW REPORTED A STALL FAIL CAUTION MESSAGE POSTED AFTER TAKEOFF. RETURNED TO BASE. (AIRCRAFT POST EICAS 2000).REMO	VED AND REPLACED NR 1 MACH TRANSDUCER. SYSTEM CHECK GOOD.					2	L	7	2 	4F			RT	A21EA   					 
2001031300077	20010313	00077		2001	3	13	CA001024039      	4	20001006	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE POSTED FOLLOWED BY CONFIG SPOILERS MESSAGE AT APPROX. 80 KTS.ABORTED TAKEOFF, AND RETUR	NED TO BLOCKS.SPC MEMORY RESET PER AMM. AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300078	20010313	00078	EA  	2001	3	13	CA001024040      	1	20001017	G	2752		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS FAILED AT 38 DEGREES. PERFORMED ACTUATOR TORQUE CHECKS PER AMM, FOOUND NR 1 ACTUATOR RT WITH SLIGHTLY HIGHER	 TORQUE THAN THE OTHER ONES. REPLACED NR1 ACTUATOR RT.					2	L	7	2 	4F			RT	A21EA   					 
2001031300079	20010313	00079		2001	3	13	CA001024041      	4	20001007	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) STALL FAIL CAUTION MESSAGE FOLLOWED BY CONFIG SPOILERS AT APPROX 80 KTS.ABORTED TAKEOFF.SPC RESET PER AMM, AIRCRAF	T BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300080	20010313	00080	NE  	2001	3	13	CA001024042      	2	20001007	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1	OVERHEATED      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	M	J	FLUID LOSS                	OVER TEMP                 	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, NR 1 ENGINE OIL TEMPERATURE PARAMETER WENT INTO RED FOLLOWED BY A LOW OIL PRESSURE WARNING.	 ENGINE SHUT DOWN, EMERGENCY DECLARED AND UNEVENTFULY LANDING. NR 1 ENGINE REPLACED AND AIRCRAFT RETURNED TO SERVICE. 20	00-10-31TC:  FOLLOW-UP REPORT EXPECTED FROM ORIGINATOR				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300081	20010313	00081	EA  	2001	3	13	CA001024043      	1	20001007	G	2742		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					HORIZONTAL STAB	FAILED          	W				C				ABORTED TAKEOFF         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, STAB TRIM CAUTION MESSAGE ILLUMINATED. TAKEOFF ABORTED AT 100 KNOTS.RTO INSPECTION, HSTA AND MCU R	EPLACEMENT CARRIED OUT ON AIRCRAFT BEFORE RETURNING INTO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300082	20010313	00082		2001	3	13	CA001024044      	4	20001007	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) STALL FAIL CAUTION MESSAGE ILLUMINATED ON CLIMB JUST AFTER TAKEOFF. NO EMERGENCY DECLARED.SPC RESET AS PER AMM, AI	RCRAFT BACK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300083	20010313	00083		2001	3	13	CA001024045      	4	20001007	G	3444		ANTENNA         			CNDAIR	CL600 	CL6002B19   	       	EA  										GROUND PROXIMITY	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) IN CLIMB AT ABOUT 4500 FEET; FLIGHT CREW RECEIVED AURAL WARNING TERRAIN, TERRAIN, PULL UP, PULL UP & GPWS WARNING 	LIGHT.RADAR ALTIMETER ANTENNA AND COAX CABLES REPLACED, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300084	20010313	00084		2001	3	13	CA001024046      	4	20001007	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF STALL FAIL CAUTION MESSAGE ILLUMINATED. TAKEOFF ABORTED.STALL PROTECTION COMPUTER RESET AS PER AMM,	 AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300085	20010313	00085		2001	3	13	CA001024047      	4	20001007	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, AT 80 KNOTS, STALL FAIL CAUTION MESSAGE ILLUMINATED.TAKEOFF ABORTED.STALL PROTECTION COMPUTER RESE	T AS PER AMM, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001031300086	20010313	00086		2001	3	13	CA001024048      	4	20001007	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					STALL WARNING	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, AT 160 KNOTS AND 1500 FEET, STALL FAIL CAUTION MESSAGE ILLUMINATED. STALL PROTECTION COMPUTER RE	SET AS PER AMM, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300087	20010313	00087	EA  	2001	3	13	CA001024049      	1	20001007	G	3230	75000600	VALVE           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NLG	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH UNABLE TO EXTEND NOSE LANDING GEAR. MANUAL EXTENSION USED. NOSE WHEEL STEERING FAILED ON LANDING. NLG 	EXTEND AND STEERING VALVE REPLACED AS PER AMM. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032600253	20010326	00253	EA  	2001	3	26	CA001026012      	1	20001004	G	3320	KCD4N	RELAY           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					CABIN LIGHTS	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENANCE IT WAS DISCOVERED THAT THE LT SIDEWALL LIGHTING WOULD NOT SHUT OFF WHEN SELECTED. THE LIGHTING 	RELAY 3325-K2 WAS REPLACED AND THE LIGHTING FUNCTION CHECKED SERVICEABLE. THE RELAY IS SUSPECTED TO BE ORIGINAL EQUIPMEN	T. TTAF 22,015 HRS, 32,623 CYCLES.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2000112100213	20001121	00213	CE  	2000	11	21	CA001026014      	1	20000930	G	2913	10138800519	MOTOR           			BEECH 	300   	300BEECH    	1152930	CE  										ELECTRIC MOTOR	SHORTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			1957 			221					(CAN) MOTOR WOULD RUN AS DESIGNED BUT BECAUSE OF ONE BAD COMUTATOR SEGMENT WOULD NOT TURN WHEN SELECTED IF BRUSH WAS ON 	BAD SEGMENT.  DURING FLT AS HYD PRESS IS LOWERED (DUE TO TEMP) PUMP WILL COME ON FOR 1-2 SECONDS TO BUILD UP FROM 2,750 	PSI TO 3,000 AND SHUT OFF.  A SAFETY MACHINE IS BUILT IN IF AFTER POWER IS SELECTED TO 15 SECONDS - 02 AMP BREAKER WILL 	POP AND SHUT OFF SYS - NORMAL GEAR EXT OR RETRACTION IS 8 SECONDS.  1ST TIME AFTER ONE ONE- HALF HRS OF FLT - C/B TRIPPE	D AND GEAR PUMPED DOWN BY HAND.  ACFT PLACED ON JACK, NORMAL,  PRESSURE SWITCH CHANGED AS IT WAS FELT TO BE INTERMITENT 	2ND TIME IT HAPPENED - GEAR PUMPED DOWN AGAIN AND REMAINED FAILED.  POWER PAK  REPLACED.  (X)	2	L	7	2 	4T			 	A24CE   					 
2001032600254	20010326	00254	EA  	2001	3	26	CA001026015      	1	20001012	G	5755		FITTING         			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	SPOILER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE LEFT HAND OUTBOARD GROUND SPOILER INBOARD FITTING WAS FOUND CRACKED. SPOILER REMOVED FROM AI	RCRAFT AND WILL BE REPLACED. THE CRACK LENGTH IS 0.75. NOTE: THE P/N  WAS TAKEN FROM THE DATA PLATE ON THE SPOILER.					2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001032600255	20010326	00255	EA  	2001	3	26	CA001026016      	1	20001012	G	5755		FITTING         			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	SPOILER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, THE LEFT HAND INBOARD GROUND SPOILER FITTING WAS FOUND TO BE CRACKED BETWEEN FASTENERS. (NOTE: 	P/N WAS TAKEN FROM DATA PLATE ON THE SPOILER. SPOILER WILL BE REPLACED PRIOR TO AIRCRAFT RETURNING TO SERVICE. THE CRACK	ED FITTING IS LOCATED AT THE OUTBOARD POSITION. THE LENGTH OF THE CRACK IS APPROXIMATELY 1/2 INCH.				2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2000112800299	20001128	00299	NE  	2000	11	28	CA001026019      	1	20001002	G	6220	SB7003102	BEARING         	SKRSKY      	761030801004	SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					AFT BASE END	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						B02700478					(CAN) UPON PURCHASE OF THIS HELICOPTER AND DISASSEMBLY FOR INSPECTION AND RE-FURBISHING, THE BLUE POSITION M/R SPINDLE, 	RETENTION BEARING AND THRUST BEARING WERE REMOVED AS A COMPLETE UNIT.  THE AFT BASE END OF THE THRUST BEARING, APPROX .7	5 INCH, WAS FOUND SEPARATED FROM THE MAIN BODY OF THE BEARING.  (X)				1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2000112800237	20001128	00237	NE  	2000	11	28	CA001026020      	1	20001002	G	6220	7610308010049	HUB             	SKRSKY      	763510950004	SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					SPINDLE MOUNT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10194			A08100110					(CAN) UPON PURCHASE OF THIS AIRCRAFT AND DISASSEMBLED FOR INSPECTION AND RE-FURBISHING, THE MAIN ROTOR HEAD ASSEMBLY WAS	 FOUND CRACKED AT THE FOLLOWING LOCATION   THE LOWER ATTACHMENT EAR FOR THE MAIN ROTOR DAMPER (RED POSITION).  (X)					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001031300095	20010313	00095	NM  	2001	3	13	CA001027004      	1	20001011	G	2497	BMS1331	WIRE            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 3 WIRES P/N BMS13-31 TYPE 1 CLASS 1 AWG4 AT CONNECTOR P/N FRF0E28-22S LOCATED FROM APU SHROUD THEN 3 FEET FORWARD 	TO SPLICES. FOUND TO HAVE MULTIPLE LONGITUDINAL SPLITS IN INSULATOR COATINGS. SPLITS FOUND TO BE 6 INCHES TO 12 INCHES I	N LENGTH WITH BARE WIRE EXPOSURE UP TO 0.100 IN WIDTH.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031300096	20010313	00096	NM  	2001	3	13	CA001027005      	1	20001018	G	5551	69702513	BOLT            			BOEING	737   	737200      	1384453	NM  										HORIZONTAL STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ACCOMPLISHING D CHECK ON US REGISTERED B737 IT WAS NOTED THAT LEFT HAND AND RIGHT HAND AFT HORIZ STAB ATTACH POINT	 BOLTS FOUND ONLY HAND TIGHT. UPON FURTHER INVESTIGATION ALL THREE BOLTS AFT ON R/H HORIZ STAB AND ALL THREE BOLTS AFT L	T HORIZ STAB HAVE WEAR/FRETTING, PITTING AND LIGHT CORROSION ON THE SHAFTS INDICATING IMPROPER TORQUE VALUE.				2	L	7	2 	4F			 	A16WE   					 
2001032600258	20010326	00258	EU  	2001	3	26	CA001027006      	1	20000920	G	5753	137205B68	BRACKET         			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	SLAT/FLAPS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28332			SDJ4904					(CAN) DURING UNSCHEDULED RAMP INSPECTION, AIRWORTHINESS INSPECTOR NOTED 1 BRACKET TO BE CRACKED. BRACKET ATTACHES SLAT T	O FLAP AND CLASSIFIED AS PRIMARY CLASS 2 STRUCTURE. AIRCRAFT FERRIED TO MAINTENANCE BASE,  WHERE 1 ADDITIONAL BRACKET WA	S FOUND TO BE CRACKED. 2 BRACKETS FABRICATED AND  INSTALLED, BRACKET(S) APPEAR TO HAVE BEEN CRACKED FOR QUITE SOME TIME.	 IN ADDITION TO AGE AND CYCLES ON AIRCRAFT POSSIBLE CONTRIBUTING FACTOR COULD BE COMPONENT LOCATION IN PROXIMITY OF ENGI	NE EXHAUST CAUSING CORROSION.		2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
2000112100214	20001121	00214	CE  	2000	11	21	CA001027012      	1	20000929	G	3246	C1660610301	WHEEL           			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  					INNER WHEEL HALF	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) FLANGE ON INNER WHEEL HALF CRACKED CAUSING BRAKE TO JAM.  AIRCRAFT HAD DIFFICULTY TAXIING.  (X)						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000112800238	20001128	00238	WP  	2000	11	28	CA001027014      	1	20001004	G	6210	369D21100517	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			HO	HOVERING       	1			CA			2634 			009999JI48					(CAN) PILOT REPORTED A STRANGE VIBRATION IN THE HELICOPTER. UPON INVESTIGATION ENGINEERING FOUND THE UPPER LEADING EDGE 	LUG OF THE BLADE CRACKED AND BROKE LOOSE FROM THE BLADE AND ONE BLADE RETENTION PIN BENT. MAIN ROTOR BLADE AND BLADE RET	ENTION PINS WERE REPLACED.  AS A PRECAUTIONARY MEASURE MAIN ROTOR HUB LEAD LAG LINKS WERE REPLACED.  REMAINING BLADES, L	INKS AND PINS WERE CHECKED AND FOUND SERVICEABLE.  (X)			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000112100215	20001121	00215	CE  	2000	11	21	CA001027016      	1	20001019	G	8011	PM2401	STARTER         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	STARTER	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			897  			80078307					(CAN) MULTIPLE PIECES OF A BURNED AND BROKEN BOLT FOUND IN ENGINE COWLS.  BOLT DETERMINED TO BE FROM REAR OF STARTER HOU	SING.  UPON FURTHER INSPECTION, TWO OF THE REMAINING THREE CASE THROUGH-BOLTS WERE FOUND LOOSE.  MISSING BOLT SHOWED SIG	NS OF ELECTRICAL ARCING LEADING TO EVENTUAL CUTTING OF THE BOLT.  (X)				1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001032600466	20010326	00466	EA  	2001	3	26	CA001027017      	1	20001007	G	2730	C6TEM104229	ARM             			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A20      	52043	EA  					LT ELEVATOR	FAILED          	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE SIX ATTACH HOLES ARE COUNTERSUNK TOO DEEP FOR THE INTENDED FASTENERS (PLT110-6) IF INSTALLED THIS ITEM COULD C	OME LOOSE RESULTING IN LOSS OF LT ELEVATOR CONTROL. CONCERNED ABOUT MOR IN SAME BATCH IN SERVICE. PLEASE SEE ATTACHED PH	OTO COPY.				1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2000112100216	20001121	00216	CE  	2000	11	21	CA001027018      	1	20001027	G	3240		LINE            			CESSNA	206   	U206A       	2073316	CE  	CONT  	O520  	IO520F      	17032	SO  					LT/RT	BROKEN          	W				D	 	 	 	RETURN TO BLOCK         				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LOADING PASSENGERS, AIRCRAFT STARTED TO TAXI.  WHILE ON RUNWAY, PILOT HAD A FAILED BRAKE ON RT SIDE FOLLOWED	 BY A FAILURE ON THE LT SIDE.  AIRCRAFT WAS PUSHED TO TAXIWAY.  PASSENGERS HAD STEPPED ON BRAKELINES DURING BOARDING AND	 BROKEN THEM OFF.  BRAKE LINES RE-FLARED AND AIRCRAFT RETURNED TO SERVICE.  (X)				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000112100217	20001121	00217	NE  	2000	11	21	CA001030002      	2	20000919	G	7230		COMPRESSOR      	PWA         		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COMPR SHROUD	FAILED          	W				B	 	 	 	EMER. DESCENT           				B		 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA			3953 	681  		PCE94208					(CAN) SHORTLY AFTER TAKEOFF, THE CABIN FILLED WITH FUMES AND LIGHT SMOKE. THE AIRCRAFT RETURNED TO THE POINT OF DEPARTUR	E.  ENGINE WAS SPLIT AT THE C-FLANGE.  NO OBVIOUS DAMAGE OR ABNORMALITIES  WERE FOUND.   A NEW NR 2 BEARING COVER AND GA	SKET WERE INSTALLED.  ENGINE TEST RUN AND PROBLEM FOUND TO PERSIST.  ENGINE REMOVED AND COMPRESSOR SECTION TORN DOWN AT 	STANDARD AERO.  FOUND THE CENTRIFUGAL COMPRESSOR RUBBING ON THE COMPRESSOR SHROUD HOUSING.  CLEARANCES RESTORED, ENGINE 	RE-ASSEMBLED, INSTALLED, TEST RUN AND AIRCRAFT TEST FLOWN.  FUMES AND SMOKE NO LONGER PRESENT.  (X)		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001032600467	20010326	00467	EA  	2001	3	26	CA001030003      	1	20001004	G	5230	21526063960	SHAFT           			CNDAIR	CL215 	CL2151A10   	       	EA  										CARGO DOOR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3390 								(CAN) TOTAL SURFACE CORROSION ON INSIDE DIAMETER OF TORQUE SHAFTS AFFECTING 50 - 65 PERCENT OF TOTAL DIAMETER THE FULL L	ENGTH OF ONE SHAFT AND APPROX. 60 PERCENT OF LENGTH OF THE OTHER SHAFT. BOTH SHAFTS HAVE SCATTERED PIN HEAD TO 0.250 DIA	METER PITTS THROUGH OUT REMAINING AREA.-  SHAFT NR 1 HAS MIN. WALL THICKNESS .240 TO AV. THICKNESS .260-  SHAFT NR 2 HAS	 MIN. WALL THICKNESS .245 TO AV. THICKNESS ..255 THERE IS NO SURFACE CORROSION PROTECTION ON THE INSIDE DIAMETER OF THE 	SHAFTS.SPLINED ENDS OF SHAFTS (MACHINED AND WELDED SEPARATELY) ARE FREE OF ALL DEFECTS AS PER NDT.		2	H	7	2 	4R			 	A14EA   					 
2001032600468	20010326	00468	CE  	2001	3	26	CA001030004      	1	20001004	G	5330	58130412	SKIN            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10534								(CAN) SKIN CRACKED BY LEFT NOSE GEAR DRAG BRACE ATTACH POINT. SKIN REPLACED. TEE GUSSETT, DOUBLER AND BRACKET WERE ALSO 	REPLACED. RETRACTION TEST COMPLETED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2000112800239	20001128	00239	SW  	2000	11	28	CA001030005      	1	20001017	G	2910	70061H00A180A	LINE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					UPPER DECK	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) OIL LINE FAILED AT AREA WHERE IT IS CLAMPED TO THE UPPER DECK.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011105863	20010111	05863	EU  	2001	1	11	CA001030008      	1	20001019	G	7722	9717382108	PIN             	PILATS      	975290201   	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  					CONNECTOR	LOOSE           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA						170					(CAN) AIRCRAFT DEPARTED AND SHORTLY AFTER, THE ITT INDICATION STARTED FLUCTUATING BETWEEN 700 AND 300.  ALL OTHER ENGINE	 PARAMETERS WERE WITHIN MANUFACTURER'S SPECIFICATIONS.  AIRCRAFT RETURNED TO BASE FOR INSPECTION.  PROBLEM WAS FOUND TO 	BE A LOOSE PIN CONNECTION AT THE BACK OF THE EIS PANEL.  PIN WAS SECURED AND AIRCRAFT RETURNED TO SERVICE.  (X)				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2001032600475	20010326	00475	EU  	2001	3	26	CA001031003      	1	20001016	G	7920	13X395MOM18182	LINE            			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE OIL	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING SCHEDULED MAINTENANCE (HOSES REPLACEMENT 5 YEAR) ENGINE OIL HOSES (FROM ENGINE TO OIL COOLER) P/N 13X395 M	OM 1818.2 WAS FOUND: RADIUS ON THE HOSE WAS BELOW MINIMUM RECOMMANDED RADIUS (10 X DIAMETER OF THE HOSE). MEASURED RADIU	S WAS 5 INCH, NEW HOSE SAME P/N INSTALLED. RECOMMENDED ACTION TO THE OWNER IN CLOSED 100 HR INSPECTION PROVIDE NEW ENGIN	E OIL HOSE (LONGER) AND RE-ROUTING ENGINE HOSE.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2001032600476	20010326	00476	EU  	2001	3	26	CA001031004      	1	20001017	G	7110	71100071	COWLING         			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8070 								(CAN) UPON INSPECTION FOUND AN BOLTS IN AFT ENG COWLINGS FLANGE. REPLACED WITH NAS I.A.W. HAWKER RAYTHEON I.P.C.						2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2001032600477	20010326	00477	NM  	2001	3	26	CA001031005      	1	20000218	G	2497	22AWG	WIRE            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	PW120 	PW123       	 	NE  					COCKPIT	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				H	N		ELECT. POWER LOSS-50 PC   	FALSE WARNING             		CR	CRUISE         	1			CA											(CAN) THE FOLLOWING WAS REPORTED TO US. NR 1AC GENERATOR  FAILED IN FLIGHT, MTW ACTIONS REPLACED AC GENERATOR, CHECKED, 	FAULT REMAINED, TROUBLESHOT GCU REPLACED, CHECKED, FAULT REMAINED, ON INSPECTION FOUND CHAFED WIRES BEHIND CB PANEL - CB	2421-3, -5, -7 & -9. WIRES REPLACED. A/C CHECKED CARRIED OUT SATISFACTORY, A/C RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600478	20010326	00478	NM  	2001	3	26	CA001031008      	1	20000229	G	2731	82700562059	CONTROL CABLE   			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					ELEVATOR	LOOSE           	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) FLIGHT CREW REPORTED RECEIVING A MIS-TRIM MESSAGE ON THE ID-802. THE AUTO-PILOT WAS THEN DISENGAGED & FLT CREW ATT	EMPTED TO MOVE TRIM MANUALLY TO A NOSE DOWN ATTITUDE. A RESTRICTION TO THIS MOVEMENT WAS FELT IN THE TRIM CONTROL. AN EX	TENDED ROUTE WAS REQUESTED FROM ATC & THE AIRCRAFT LANDED WITHOUT INCIDENT. IT WAS NOTED THAT THE ELEVATOR MANUAL TRIM A	PPEARED TO OPERATE NORMALLY AFT OF THE RESTRICTION. (DETAIL: INCIDENT OCCURRED DESCENDING THROUGH 150, VMC, +5C REF: ASR	44R/00/DH8ENGINEERS: COULD NOT REPRODUCE FAULT, BUT ON FURTHER INVESTIGATION TRIM CABLE TENSION DISCOVERED TO BE 0 LBS O	NLY, CABLES THOROUGHLY INSPECTED, RE-TENSIONED.  FUNCTIONALLY CHECKED & A/C RETURNED TO SERVICE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031500100	20010315	00100	EA  	2001	3	15	CA001031010      	2	20001007	G	7261	305306301	SLEEVE          			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					OIL VALVE	LEAKING         	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) THE FOLLOWING REPORT TO US: FOLLOWING FLT OCCURRENCE REPORT FROM PILOT IN COMMAND OF FLT SK0765 (SAS COMMUTER): DU	RING TAXI, 5 MIN AFTER ENGINE START, A/C HELD DUE TO GROUND WORKS, JUST AFTER A/C COME TO COMPETE STOP, SMOKE WARNING FR	OM LAVATORY ACTIVATED. ??? AT CAI STATION OPENED COCKPIT DOOR&INFORMED ABOUT WARNING AS WELL. AT TIME SMELL OF SMOKE REC	OGNIZED BY CABIN CREW. VISIBLE SMOKE OBSERVED WHEN THEY OPENED LAVATORY DOOR,A GROUND EMERG EVACUATION PERFORMED ACCORDI	NG TO PROCS & FIRE BRIGADE ASSISTANCE REQUIRED VIA ATC. MAINT:ENGINE GROUND RUNS HAVE SINCE BEEN CARRIED OUT & IT HAS BE	EN DETERMINED THAT LAVATORY SMOKE DETECTOR SET OFF BY OIL FUMES FROM RT ENGINE.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2001032600481	20010326	00481	NM  	2001	3	26	CA001031011      	1	20001009	G	2611	473082	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8*       	       	NM  										CARGO BAY	FAILED          	W				F	A	 	 	ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) THE FOLLOWING FLT OCCURRENCE RPT MADE BY PILOT IN COMMAND OF FLT SK0764 (SAS COMMUTER):  JUST AFTER TAKEOFF DURING	 INIT CLIMB AT APPROX. 3,000 FT, CREW RECEIVED SMOKE FWD CARGO WARNING INTERMITTENTLY FOR APPROX. 3 SEC OR SO. AFTER ONL	Y 10 SEC, IT CAME ON AGAIN, AT 1ST IT FLICKERED, THEN CAME ON PERSISTENTLY.I THEN DID MEMORY ITEM & DISCHARGED FWD-CARGO	 BAY FIRE BOTTLE, CALLED ITC, INFORMED CAI & HAD RADAR VECTOR TO RWY 24 ILS.A NORMAL LDG MAD E&AFTER LDG, TURNED TO LEFT	 ON TAXI-WAY B. AFTER APPROX. 50 METERS, PASSENGERS WERE EVACUATED THROUGH FWD LT EXIT. SMOKE IND. DISAPPEARED JUST AFTE	R BOTTLE EXTINGUISHED. THE FIRE BRIGADE ON TAXI-WAY ON STANDBY, READY TO TAKE ACTION  IF NECESSARY.	2	H	7	2 	4T			RT	A13NM   					 
2001032600482	20010326	00482	NM  	2001	3	26	CA001031012      	1	20001011	G	3411		PITOT TUBE      			DHAV  	DHC8  	DHC8*       	       	NM  										PITOT STATIC SYS	CONTAMINATED    	W				A	 	 	 	UNSCHED LANDING         				G	J		MULTIPLE FAILURE          	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) : (FLT NOSK1868 - DEPARTING STAVANGER AT 1225 TO COPENHAGEN). PILOTS RPT IN A/C TECH LOG (L528) STATES:AT FL160 IA	S MISMATCH APPEARED. DISAGREEMENT BETWEEN ALL INSTRUMENTS & STANDBY INSTRUMENTS. LOT OF LIGHTS CAME ON CAUTION WARN PANE	L. SOME OF THESE WERE PITCH TRIM, ELEV FEEL, SOME SPOILER LIGHTS, NR1 STALL SYS FAIL, & PUSHER SYS FAIL. AFTER APPROX. 8	 MINS, MOST FAILURES CANCELED THEMSELVES EXCEPT FOR NR 1 STALL SYS FAIL & PUSHER SYS FAIL.  DURING FAIL PERIOD, LT AIRSP	EED & ALTIMETER FAILED COMPLETELY FOR APPROX 3-4 MINS. RUDDER CONTROL CAUTION LIGHT ALSO CAME ON DURING FAILURE PERIOD. 	LT AIRSPEED WENT TO 30, RT AIRSPEED 230 IAS, STANDBY160 IAS.MAINT: TROUBLESHOOTING FOUND WATER CONTA	2	H	7	2 	4T			RT	A13NM   					 
2001032600483	20010326	00483	NM  	2001	3	26	CA001031014      	1	20000921	G	3231	83232017103	LINK            	DHAV        	83232017003 	DHAV  	DHC8  	DHC8*       	       	NM  										SEQUENCE VALVE	BROKEN          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA			838  								(CAN)  CREW SELECTED GEAR DOWN DURING DESCENT INTO AMAKUSA. LT MLG WOULD NOT EXTEND (DOORS FAILED TO OPEN). CREW PERFORM	ED ALT EXT PER QRH & GEAR CAME DOWN & LOCKED INTO POS. A/C MADE UNEVENTFUL LDG AT AMAKUSA AIRPORT. CHIEF PILOT FLYING&NO	TED  LT MLG SLOW TO DISPLAY UP&LOCKED AFTER TAKEOFF&POPPING SOUND HEARD DURING RETRACTION. ELECTED TO EXTEND GEAR EARLIE	R THAN NORMAL DURING DESCENT AND SUBSEQUENTLY DISCOVERED PROBLEM AND ACTED ACCORDINGLY. FSR WASNT NOTIFIED UNTIL NEXT MO	RNING. AMX MAINT INVEST. FOUND LT MLG DOOR SEQUENCE LINK TO BE BROKEN IN 2 PIECES (HENCE MLG DOORS WOULD NOT OPEN HYDRAU	LICALLY).	2	H	7	2 	4T			RT	A13NM   					 
2001031300098	20010313	00098	NM  	2001	3	13	CA001031015      	1	20000924	G	2720	7G772	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8301     	       	NM  										RUDDER DAMPER	FAILED          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			2161 								(CAN) FROM BWIA MAINTENANCE REPORT: NR 2 RUDDER HYDRAULIC CAUTION LIGHT ILLUMINATED, SWITCHES SWAPPED FOR TROUBLESHOOTIN	G. PROBLEM TRANSFEREE TO NR 1 SIDE. NR 1 PRESSURE SWITCH ON RUDDER DAMPER REPLACED (SWITCH WAS SWAPPED).AIRCRAFT FUNCTIO	NALLY TESTED SATISFACTORY, RETURNED TO SERVICE.				2	H	7	2 	4T			RT	A13NM   					 
2001031300099	20010313	00099	NM  	2001	3	13	CA001031016      	1	20000926	G	2720	7G772	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8301     	       	NM  										RUDDER DAMPER	FAILED          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			12   								(CAN) BWIA MCC REPORT FROM GEORGETOWN, BARBADOS: NR 2 RUDDER HYDRAULIC CAUTION LIGHT ILLUMINATED (SWITCHES SWAPPED FOR T	ROUBLESHOOTING), PROBLEM TRANSFERRED TO NR 1 SIDE. NR 1 PRESSURE SWITCH ON RUDDER DAMPER REPLACED (SWITCH WAS SWAPPED).A	IRCRAFT FUNCTIONALLY TESTED SATISFACTORY, RETURN TO SERVICE.				2	H	7	2 	4T			RT	A13NM   					 
2001031300100	20010313	00100	NM  	2001	3	13	CA001031017      	1	20000804	G	2910	NAS16124	O-RING          			DHAV  	DHC8  	DHC8301     	       	NM  										PRESS MANIFOLD	DETERIORATED    	W				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA											(CAN) THE FOLLOWING REPORTED TO US (BRYMON MAINT CTL): DURING CRUISE AT 16,000 FT ON ROUTE TO GLASGOW SPARE CAUTION LIGH	T ILLUMINATED (LIGHT ABOVE FUEL TANK LOW LEVEL) THEN EXTINGUISHED FOLLOWED BY HYDRAULIC CAUTION LIGHTS. HYDRAULIC CONTEN	TS I INDICATED NR 2 SYS DEPLETED. EMERGENCY CHECKLIST CONSULTED & PAN DECLARED.GEAR EXTENDED ON FINAL AT GLASGOW TO PERM	IT EMERGENCY CHECK LIST ACTION BEFORE UNEVENTFUL APPROACH & LDG. A/C CLEARED RWY&SHUTDOWN. LDG GEAR PINS INSERTED INTO G	EAR & A/C TOWED TO STAND, PASSENGERS DISEMBARKED. MAINT: FOUND NR 2 HYDRAULIC PRESSURE MANIFOLD LEAKING AT BLANK (AN814-	4D).SEAL FOUND DETERIORATED. NEW SEAL FITTED & BLANK REPLACED. FOLLOWING ITEMS ALSO REPLACED, AS SYS RAN DRY. 1) ENGINE	2	H	7	2 	4T			RT	A13NM   					 
2001032600484	20010326	00484	NM  	2001	3	26	CA001031018      	1	20000813	G	2910	NAS16121	O-RING          		8291000255  	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					SEQUENCE VALVE	DEFORMED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING A DAILY INSPECTION WHILE ON A MAINTENANCE INPUT; CREW FIXED OXYGEN BOTTLE & ASSOCIATED HOSES FOUND COVERED	 IN HYDRAULIC FLUID. ACTION: OXYGEN BOTTLE & HOSES REMOVED. HYDRAULIC POWER APPLIED TO THE NR 2 SYSTEM HYDRAULIC LEAK FO	UND AT NOSE GEAR SOLENOID SELECTOR VALVE RESTRICTOR UNION O-RING. O-RING REPLACED AND CHECKED SATISFACTORY. AREA THOROUG	HLY CLEANED AND OXYGEN EQUIPMENT REFITTED WITH NEW HOSES.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600485	20010326	00485	NM  	2001	3	26	CA001031019      	1	20001011	G	2910	AN81510D	O-RING          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					HYD SYSTEM	CRACKED         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			4723 								(CAN)  ON APPROACH TO POS, WITH GEAR UP, GOT HIS NR 2 EDP HYDRAULIC CAUTION LIGHT AND NOTICED HIS NR 2 HYDRAULIC QUANTIT	Y DROPPED TO ZERO. FOLLOWED PROCEDURES PER QRH. AIRCRAFT LANDED IN PORT OF SPAIN & TOWED TO GATE. MAINTENANCE: NR 2 EDP 	SUPPLY LINE TO THE PRESSURE MANIFOLD, UNION FOUND SHEARED OFF AT PRESSURE MANIFOLD SIDE. UNION STILL ATTACHED TO LINE. T	HIS IS EXACT DEFECT REPORTED.MANIFOLD REPLACED & AIRCRAFT FUNCTION TESTED, LEAK CHECKED AND RETURNEED  TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600486	20010326	00486	NM  	2001	3	26	CA001031021      	1	20000828	G	2810	82820045104	TUBE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					FUEL SYSTEM	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			14059								(CAN)  DURING SCHEDULED INSPECTION OF RT FUEL TANK, SERIOUS WEAR ON THE AFFECTED FUEL TUBE WAS DETECTED. THE INTERFERENC	E WITH THE BONDING STRAP CREATED HEAVY WEAR & PENETRATION OF THE TUBE WALL. THE STRAP INSTALLATION MUST BE CORRECTED AND	 FORWARD INSTALLATION OF THE FUEL TUBE. ACTION: WORN TUBE REPLACED AND BONDING STRAP ROUTED CORRECTLY.QIR INVESTIGATION 	REPORT - DMAR-NDAR-00-00003 FILED BY BOMBARDIER, DEHAVILLAND.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031300101	20010313	00101	NM  	2001	3	13	CA001031022      	1	20001009	G	5270	8520200015	WARNING SYSTEM  	DHAV        	DHC8300     	DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					SERVICE DOOR	ACTIVATED       	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA						422					(CAN) THE FOLLOWING WAS REPORTED TO US (FROM BRYMON SAFETY REPORT 213R/00/DH8): TAKEOFF ABORTED SHORTLY AFTER POWER APPL	ICATION, DUE TO INTERMITTENT SERVICE DOOR WARNING LIGHT ILLUMINATION. PILOT LIAISON WITH CABIN ATTENDANT WHO ADVISED SER	VICE DOOR HANDLE NOT ACCURATELY STOWED. RESET HANDLE,  WARNING LIGHT CLEARED (EXTINGUISHED), AIRCRAFT RETURNED TO TAKEOF	F, SATISFACTORY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700004	20010327	00004	NM  	2001	3	27	CA001031023      	1	20000905	G	2910	DSC1896	CHECK VALVE     			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					RT WING	FRACTURED       	W				D	 	 	 	RETURN TO BLOCK         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN)  DURING TAXI, DECREASE IN HYDRAULIC FLUID QUANTITY OBSERVED. AIRCRAFT RETURNED TO RAMP. HYDRAULIC FLUID NOTICED TO	 BE COMING FROM RIGHT WING/ARMPIT AREA. INSPECTION  REVEALED A BROKEN AND SEVERED BODY OF THE PTU CHECK VALVE AND A DIST	ORTED HYDRAULIC LINE (P.N. 82940010-159). BOTH ITEMS REPLACED. GROUND RUN CARRIED OUT, SYSTEMS FUNCTION CHECK AND LEAK C	HECK CARRIED OUT S ATISFACTORY. AIRCRAFT RETURNED TO SERVICE.NOTE: OPERATOR FLEETWIDE CAMPAIGN IN EFFECT TO CHECK FOR DE	FECTS IN ASSOCIATED PARTS. DEFECTIVE PART TO BE SENT TO MANUFACTURER FOR ANALYSIS.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600487	20010326	00487	NM  	2001	3	26	CA001031025      	1	20001009	G	3411	PH1001DH	PITOT HEAD      			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					PITOT STATIC SYS	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN)  NR 1 ASI FAILED TO REGISTER UP TO 70 KTS, REJECTED TAKEOFF COMPLETED. AFTER REJECTED TAKEOFF, AIRCRAFT RETURNED T	O STAND FOR INVESTIGATION. ENGINEER CLEARED PITOT HEAD AND REPORTED, EXCESSIVE WATER APPARENT IN TUBE. AIRCRAFT WAS PARK	ED OVERNIGHT IN HEAVY RAIN AND THIS WAS THE FIRST FLIGHT OF THE DAY.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031300102	20010313	00102	EA  	2001	3	13	CA001031026      	1	20001009	G	2910	AN81510D	CONNECTOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					PRESS MANIFOLD	SHEARED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			11837								(CAN) THE FOLLOWING WAS REPORTED TO US: INFO GATHERED FROM RETURNING ENGINEER (TODAY 10TH OCT) STATES THAT CAPTAIN REPOR	TED ON APPROACH HE NOTICED THAT NR  2 ENGINE HYDRAULIC PUMP CAUTION LIGHT ILLUMINATED AND WITHIN 3 SECONDS OBSERVED TOTA	L LOSS OF NR 2 HYDRAULIC FLUID IN THE SYSTEM.PER QRH, ALT EXT WAS CARRIED OUT AND AIRCRAFT LANDED UNEVENTFULLY. AIRCRAFT	 WAS REPORTED TO HAVE STOPPED AT 7,500 FEET FROM POINT  OF TOUCH DOWN. CAPTAIN REQUESTED AIRCRAFT BE TOWED TO GATE.MAINT	ENANCE:REPLACED MANIFOLD ASSEMBLY AND UNION, NR 2 HYDRAULIC SYSTEM FLUID REPLENISHED, SYSTEM BLED AND AIRCRAFT RELEASED 	AS SERVICEABLE.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032600488	20010326	00488	NM  	2001	3	26	CA001031027      	1	20000306	G	2913	82970007001	PUMP            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					HYD SYSTEM	FAILED          	W				A		 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			688  								(CAN) AFTER TAKEOFF ON GEAR RETRACTION, NR 2 EDP CAUTION LIGHT ILLUMINATED, LEFT DOOR, AND NOSE DOOR ADVISORY LIGHT ILLU	MINATED ON AND NR 2 MAIN AND STANDBY HYDRAULIC PRESSURE FELL TO BELOW 1000 PSI. LANDING GEAR LOWERED USING PTU. AIRCRAFT	 LANDED NORMALLY. NR 2 EDP REPLACED, RETRACTION CHECK CARRIED OUT ON TEST FLIGHT, CHECKED OK. S/N ON: MX500840CD S/N OFF	: MX614976D			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031300103	20010313	00103	EA  	2001	3	13	CA001031028      	1	20001020	G	6120	57B1901	LINK            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			17196	3566 							(CAN) CRACK INDICATION ON THE LINK ARM FOUND DURING OVERHAUL INSPECTION.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2001031300104	20010313	00104	EA  	2001	3	13	CA001101003      	1	20001010	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE LT WINDSHIELD SHATTERED. MAINTENANCE REPLACED THE WINDSHIELD P/N NP139321-5 (S/N ON:00119H6340).						2	L	7	2 	4F			RT	A21EA   					 
2001011106126	20010111	06126	EA  	2001	1	11	CA001101006      	1	20001010	G	5610		WINDOW          	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			2839 			7343					(CAN) DURING CRUISE, A LOUD BANG WAS HEARD AND THE RT SIDE WINDOW WAS OBSERVED TO BE SHATTERED. AN EVENTFUL LANDING FOLL	OWED.BOTH CORE AND OUTER LAYERS FOUND TO BE DAMAGED. WINDOW REPLACED AND A/C RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032600116	20010326	00116	EA  	2001	3	26	CA001101007      	1	20001014	G	2612	47259701	CONTROL PANEL   			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, APU FIRE WARNING BELLS SOUNDED. CREW DISCHARGED FIRE EXTINGUISHER AND APU FIRE WARNING STOPPED. MU	LTIPLE FIRE FAIL MESSAGES WEREALSO POSTED.MAINTENANCE CREW OBSERVED SPILLED BEVERAGE CONTAINER ON L/H SIDE CONSOLE AND F	LUID EVIDENT IN FIRE AND OVERHEAT CONTROL UNIT. REPLACED FIRE AND OVERHEAT CONTROL UNIT.AIRCRAFTRETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300105	20010313	00105	EA  	2001	3	13	CA001101008      	1	20001014	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) DURING DESCENT, FLAPS FAIL AMBER MESSAGE ON EICAS, AS CREW SELECTED FLAPS TO 8 DEGREES. 0 DEGREES FLAPS LANDING PE	RFORMED WITH NO FURTHER EVENTS. FURTHER DETAILS TO FOLLOW.					2	L	7	2 	4F			RT	A21EA   					 
2001032600127	20010326	00127	EA  	2001	3	26	CA001101010      	1	20001015	G	3260	864806	PSEU            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF341A      	 	NE  					MLG	FAILED          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) GEAR DISAGREE WARNING MESSAGE POSTED DURING APPROACH. NOSE GEAR SHOWED DOWN AND LOCKED WHILE MAIN GEAR SHOWED UP &	 LOCKED.ABORTED APPRAOCH, PERFORMED MANUAL GEAR EXTENSION AND PERFORMED UNEVENTFUL EMERGENCY LANDING. PSEU REPLACED, AIR	CRAFT BACK IN SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300106	20010313	00106	SO  	2001	3	13	CA001101016      	1	20001003	G	3244	613160	TIRE            	CLEVELAND   	40140       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					NOSE WHEEL	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			29   								(CAN) 1)  AT REPLACEMENT: NEW BEARINGS & CUPS & AXLE CHECKED.2) NEXT FLIGHTS PILOT REPORTED SHIMMING.3) SHIMMY DAMPENER 	LOW IN FLUID, RESERVICED.4) FURTHER ON PILOT PRECISED - NOT SHIMMING BUT SAID THE NOSE WHEEL SKIPPING ON TAKEOFF AS SPEE	D INCREASED. 5) AIRCRAFT ON JACKS: CALIPERED TIRE TO LD GEAR FORK, NOT ROUND.6) INSTALLED NEW TIRE. PILOT REPORTS NOW OK	.7) RETURNED FAULTY TIRE TO API LTD ON WARRANTY. NOTE: NO FLAT SPOTS, NO BULGES ON DEFECTIVE TIRE.  TIRE, MICHELIN-AVIAT	OR 6.00X6PR TT		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001031300107	20010313	00107	EA  	2001	3	13	CA001101020      	1	20001015	G	4990		APU             			CNDAIR	CL600 	CL6002B19   	       	EA  										APU BAY	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) APU OIL TEMP CAUTION MESSAGE POSTED ON EICAS IN FLIGHT, WITH APU OPERATING BECAUSE IDG NR 1 WAS DEFERRED. CREW DEC	LARED AN EMERGENCY LANDING AND MADE AN UNSCHEDULED LANDING.INSPECTED APU AND FOUND IT LOW ON OIL. SERVICED WITH ON QUART	 OF OIL. AIRCRAFT BACK IN SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001031300108	20010313	00108	EA  	2001	3	13	CA001101021      	1	20001020	G	2710		AILERON         			CNDAIR	CL600 	CL6002B19   	       	EA  										WING	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) AP RWD MESSAGE. TRANSFERED TO MANUAL FLIGHT. ON FLIGHT CONTROL SYNOPTIC PAGE, ONLY THE LEFT AILERON WAS DEFLECTING	. THERE WAS THE FEELING OF A BLOCKAGE. AFTER PILOT TOOK OVER, HEAVY JERK DURING A LEFT TURN AND NORMAL FLIGHT AFTER. AIL	ERON MOVES AGAIN.				2	L	7	2 	4F			RT	A21EA   					 
2001031300109	20010313	00109	EA  	2001	3	13	CA001101023      	1	20001020	G	2710		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										AILERON	FAULTY          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AT 80 KTS DURING TAKEOFF ROLL, THE AILERON WARNING MSG APPEARED.THE FLIGHT CREW ABORTED TAKEOFF AT 85  TO 90 KTS. 	(UNEVENTFUL). AIRCRAFT WAS ROUTED TO THE HANGAR FACILITY FOR HIGH SPEED TAKEOFF INSPECTION AND AILERON INVESTIGATION. NO	 DEFECT NOTED, AIRCRAFT RELEASED FOR SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001031300110	20010313	00110	EA  	2001	3	13	CA001101024      	1	20001020	G	2750		FCU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A      	30015	NE  					TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) THE FLAPS FAIL CAUTION MSG APPEARED UPON FLAP SELECTION AFTER TAKEOFF. FLAPS INDICATED 8 DEGREES  WITH FLAPS SELEC	TED TO 0 DEGREE (APPROXIMATELY.). THE FLIGHT CREW RETURNED TO THE DEPARTING AIRPORT (ALLENTOWN --PA (ABE) & DECLARED AN 	EMERGENCY LANDING.MAINTENANCE ACTION: INSPECTED FLAP FOR CONDITION AND SECURITY (OK) (FIRST EVENT) RESET THE FLAP SYSTEM	, OPERATION CHECK, SERVICEABLE (72 HOURS).			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031300111	20010313	00111	EA  	2001	3	13	CA001101025      	1	20001020	G	5610		WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) CREW ADVISED THAT AFTER TAKEOFF CAPTAINS SIDE WINDOW OUTER PANE SHATTERED. AIRCRAFT RETURNED TO NASHVILLE. MAINTEN	ANCE DISPATCHED FROM ATLANTA TO REPLACE WINDOW.					2	L	7	2 	4F			RT	A21EA   					 
2001011106135	20010111	06135	WP  	2001	1	11	CA001102002      	1	20001008	G	2460		CIRCUIT BREAKER 			LKHEED	1011  	10113851    	5265010	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					GALLEY	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) SPARKS WHERE SEEN COMING FROM LT MID GALLEY SERVICE OUTLET DURING TAKEOFF, CIRCUIT BREAKERS J19 & C13 PULLED AND C	OLLARED. SYSTEM DE-ACTIVATED AND AIRCRAFT RELEASED UNDER MEL.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001031300112	20010313	00112	WP  	2001	3	13	CA001102003      	1	20001013	G	2720		CONNECTOR       	WHITTAKER   	1496452     	LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					SHUTOFF VALVE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						67M					(CAN) DURING DEFECT TROUBLE SHOOTING OF THE YAW SAS 2 FAIL & RUDDER HYDRAULIC LIMITER FOUND WRONG PART INSTALLED, (UNION	 WITH OUT A RESTRICTOR), INSTALLED ON THE HYDRAULIC SHUTOFF VALVE REPLACED AIRCRAFT DISPATCHED.PART WAS FOUND NOT TO HAV	E BEEN INSTALLED BY AIR TRANSIT (PART WAS NOT IN THE AIR TRANSIT SYSTEM), THE AIRCRAFT COULD HAVE BEEN IMPORTED IN THIS 	MANNER.WITHOUT DISASSEMBLY COULD NOT VISUALLY CONFIRM THAT THE PROPER UNION IS INSTALLED.			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001031400001	20010314	00001	NE  	2001	3	14	CA001102006      	3	20001012	G	6111	6903A10S	BLADE           	HAMSTD      	43E60581    	CNDAIR	CL215 	CL2151A10   	       	EA  						HAMSTD	43E	43E60       	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3737 	2329 		206025					(CAN) CRACK FOUND ON LEADING EDGE IN SHOT PEENED AREA, LOCATED IN A OLD LOCAL REPAIR AT STATION 46 INCH.						2	H	7	2 	4R			 	A14EA   		6	C	P871	 
2001032600146	20010326	00146	CE  	2001	3	26	CA001102007      	1	20001002	G	3222	0542106	SPRING          			CESSNA	170   	170B        	2072306	CE  	LYC   	O360  	O360A1A     	41514	EA  					TAIL WHEEL	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			4012 								(CAN)  DURING LANDING ON A GRAVEL STRIP THE TAIL WHEEL SPRING BROKE. PILOT KEPT CONTROL OF THE PLANE AND HAD NO OTHER DA	MAGE. THE LOWER SPRING LEAF (P.N. O542106) HAS BEEN FOUND BROKEN AT TWO PLACES. ALL (4) SPRING LEAVES HAVE BEEN REPLACED	 WITH NEW UNITS.				1	H	7	1 	3O	3	O	 	A799    	E286				 
2001032600147	20010326	00147	EA  	2001	3	26	CA001102009      	1	20000919	G	3242	2158750224	BRAKE ASSY      			CNDAIR	CL215 	CL2156B11415	       	EA  										LT BRAKE	OVERHEATED      	W				O	 	 	 	OTHER                   				M	B	 	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			15   	15   							(CAN) WHEN THE AIRCRAFT STOPPED, THE GROUND CREW NOTICED SMOKE COMING FROM THE LEFT WHEEL. FANS WERE USED TO COOL OFF TH	E BRAKES. THE FUSE PLUGS HAVE MELTED. AIRCRAFT BRAKE SYSTEM WAS INSPECTED AND FOUND TO BE IAW THE MAINTENANCE MANUAL. TH	E LEFT BRAKE AND WHEEL ASSEMBLY WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE BRAKE HAS BEEN SENT FOR EXPERTIS	E DUE TO DISKS JAMMING.			2	H	7	2 	4T			RT	A14EA   					 
2001031400002	20010314	00002	EA  	2001	3	14	CA001102010      	1	20000829	G	5311	21531036252	FRAME           			CNDAIR	CL215 	CL2151A10   	       	EA  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2184 								(CAN) DURING 50 HRS INSPAT 2184 HRS TAT, 1579 LAND LDGS & 9512 WATER DROPS, CRACK RPTED AT UPPER FASTENER OF LT REAR SPA	R OUTBOARD WING TO FUSELAGE FRAME ANGLE LOCATED AT FS 434.5 & LBL 51. IN ORDER TO KEEP A/C IN SE RVICE, AMOC FOR AD CF-9	7-07R2 GRANTED BY TCA - ALLEVIATION NOAARDG 2000/A116. ALLEVIATION REQ VISUAL INSP OF CRACK PROPAGATION AT INTERVALS NOT	 TO EXCEED 10 HRS. DURING VISUAL INSP AT 2224 HRS TAT, 1596 LAND LA NDINGS & 9621 WATER DROPS, ANOTHER CRACK RPTED IN SA	ME AREA ON ANGLE P/N 215-31036-68. ANGLE IS FASTENED ON FRAME ANGLE P/N 215-31036-252 AT WL218. ONCE THAT ANGLE -68 REMV	D TO BE REPL, THEN 2ND CRACK FOUND ON  FRAME ANGLE 215-31036-252.	2	H	7	2 	4R			 	A14EA   					 
2001031400003	20010314	00003	NE  	2001	3	14	CA001102011      	2	20000922	G	8550		LINE            			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	R2800CA3    	52026	NE  					OIL PRESSURE	SHEARED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA				1354 							(CAN)  A MISSION HAS BEEN ABORTED DUE TO IMPORTANT OIL LEAK FROM THE ENGINE FRONT CASE ASSEMBLY. AFTER AN INVESTIGATION,	 IT WAS FOUND THAT THE UPPER OIL TRANSFER TUBE PORT THREADS ON THE FRONT CASE DAMAGED AND HAD ITS PLUG LOOSENED THAT CAU	SED AN EXCESSIVE OIL LEAK. NOTE: SERVICE BULLETIN NO.1755, FRONT CASE OIL TRANSFER TUBE PORT THREAD REPAIR WAS NOT INCOR	PORATED.			2	H	7	2 	4R	4	R	 	A14EA   	5E8				 
2001031400004	20010314	00004	NM  	2001	3	14	CA001102014      	1	20000925	G	2782	6544851	ACTUATOR        			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					GROUND SPOILER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON LANDING DURING GROUND SPOILER DEPLOYMENT HYDRAULIC FLUID WAS OBSERVED LEAKING FROM THE NR 5 GROUND SPOILER NR 5	 ACTUATOR. OBSERVATION REVEALED THAT UNDER PRESSURE A CRACK WOULD OPEN UP IN THE CASE. SPOILER ACTUATOR WAS REPLACED. CH	ECKED SERVICEABLE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400005	20010314	00005	NM  	2001	3	14	CA001102015      	1	20000929	G	3222	L507945	BEARING         	BENDIX      	26010452    	BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				137  		B5472					(CAN) ABNORMAL NOSE WHEEL VIBRATION OBSERVED DURING TAXI. MAINT JACKED A/C NOSE GEAR ASSY. REMOVED NR 1 & NR 2 NOSE WHEE	L ASSY, OBSERVED NR 1 NOSE WHEEL ASSY OUTER BEARING HAD FAILED CAUSING DAMAGE TO AXLE ASSY (P/N 65-46215-2). A/C  REMOVE	D FROM SERVICE.AXLE / INNER CYLINDER ASSY REPLACED (P/N 65-46315-12). INVEST.  IS ONGOING BY QA AS TO WHY BEARING FAILED	.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400008	20010314	00008		2001	3	14	CA001103007      	4	20001020	G	2310	5985999522043	ANTENNA         			BOEING	737   	737230      	       	NM  										TENSIONER	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) DURING TEST FLIGHT, THE NR 1 HF ANTENNA SEPARATED AT THE CABLE TENSIONER AFTER TENSIONER FAILURE. THE FREED CABLE 	WHIPPED AGAINST THE FUSELAGE, DAMAGING 4 CABIN WINDOWS AND DENTING THE FUSELAGE AT 2 PLACES (STA 685 AND 688). THE TURN 	BARREN SECTION OF THE TENSIONER FLAPPED AGAINST THE NR 4 SPOILER CAUSING DAMAGE TO THE SPOILER.				2	L	7	2 	4F			RT	A16WE   					 
2001032600242	20010326	00242	CE  	2001	3	26	CA001103009      	1	20001020	G	2434	1101912	GENERATOR       			CESSNA	182   	182G        	2072716	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	ELECTRICAL	FAILED          	W				K	 	 	 	NONE                    				H	L	 	ELECT. POWER LOSS-50 PC   	NO TEST                   		IN	INSP/MAINT     	1			CA											(CAN) 4 GENERATORS WERE TRIED ON THIS AIRCRAFT OVER A PERIOD OF 15 - 18 MONTHS, THE END RESULT WAS INSTALLING AN ALTERNA	TOR KIT, AS THE COMPANY OVERHAULED THE GENERATOR WAS DOING SUBSTANDARD WORK.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001031400010	20010314	00010	NM  	2001	3	14	CA001103010      	1	20000919	G	5410	654685015	FITTING         			BOEING	737   	737230C     	1384472	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 1 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DETECTED VISUALLY IN WEB OF RIGHT ARM OF THE NR 1 ENGINE FORWARD MOUNT FITTING. THE ENGINE WAS REMOVED TO FA	CILITATE LAP JOINT MODIFICATION AND REMOVAL TASK CARD CALLS FOR INSPECTION OF ALL ENGINE MOUNTS.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400011	20010314	00011	EA  	2001	3	14	CA001103011      	2	20001025	G	7310	LW120980170	LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL MANIFOLD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L640661A			(CAN) AD 93-02-05 AND LYC SB 342C ADDR BENDING LIMITS FOR FUEL LINE ALONG WITH MEANS OF MINIMIZING HAZARDS OF FUEL LINE 	DAMAGE.  2 LIMITS LISTED ARE NO BENDS WITHIN 0.69 INCH FROM END AND MIN RADIUS OF 0.62 INCH  (.6250 INCH) TO CENTER OF F	UEL LINE.  WHEN LINE IS BENT TO THESE LIMITS AND INST ON NR 2 CYL, IT COMES WITHIN 0.20 INCH OF COWL, OVERLAPS COWL HALF	 JOIN BY 0.40 INCH IN VERTICAL PLANE.  WITH OVERLAP, TORQUE DEFLECTION OF ENG COULD ALLOW CONTACT OF FUEL LINE TO INNER 	COWL FLANGE.  MINOR DEVIATION FROM SB INSTRUCTIONS WILL ELIMINATE HAZARD.  IF BEND STARTS AT 0.69 INCH FROM END AND MIN 	RADIUS IS REDUCED TO 0.30 INCH, DISTANCE TO INNER COWL IS ACCEPTABLE AND NO DANGER OF CONTACT WITH COWL EXISTS.  (X)	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000112800151	20001128	00151	NE  	2000	11	28	CA001103013      	2	20001005	G	7321	430128307	FUEL CONTROL    	LYC         		BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE	INOPERATIVE     	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				2364 		LE45704EFA					(CAN) DURING TEST FLIGHT FOR NR 1 ENGINE AIRFLOW MODULATOR REPLACEMENT, IT WAS DISCOVERED THAT THE  NR 2 ENGINE WAS N1 L	IMITED CAUSING LOW POWER.  (X)					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001031400013	20010314	00013	NM  	2001	3	14	CA001103017      	1	20001018	G	2751	2061141	INDICATOR       			BOEING	737   	7372A3      	138448A	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA				482  							(CAN) ON APPROACH THE FLAPS FAILED TO EXTEND BEYOND 5 UNITS AND INDICATED AN ASYMMETRICAL CONDITION. THE AIRCRAFT LANDED	 WITHOUT INCIDENT. FLAP POSITION INDICATOR WAS REPLACED AND THE SYSTEM CHECK WITH NO FURTHER FAULT FOUND. THE AIRCRAFT W	AS RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000112800154	20001128	00154		2000	11	28	CA001103018      	4	20001026	G	2562	4000	TRANSPONDER     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CABIN	FAILED          	W				K	O	 	 	NONE                    	OTHER                   			O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA						406184					(CAN) DURING ANNUAL INSPECTION, THE ELT FAILED BECAUSE OF NO OUTPUT POWER.  THE ELT WAS RETURNED TO THE MANUFACTURER FOR	 REPAIR. THIS IS THE SECOND TIME THAT THIS ELT HAS FAILED ITS ANNUAL INSPECTION DUE TO LACK OF OUTPUT POWER.  IT PREVIOU	SLY FAILED JUNE 2, 1999.  (X)				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001031400014	20010314	00014	NM  	2001	3	14	CA001103019      	1	20001015	G	3242		STATOR          	BENDIX      	26010425    	BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BRAKE ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B4429					(CAN) NR 2 BRAKE FOUND DAMAGED DURING MAIN WHEEL ASSEMBLY (WORN TO LIMITS) REPLACEMENT. BROKEN PIECE FELL OUT ONTO GROUN	D. REF. ATTACHED PICTURE. NR 2 BRAKE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000122900116	20001229	00116	EU  	2000	12	29	CA001103020      	1	20000517	G	2435		BRUSHES         		150SG122Q   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER GEN	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5674 	393  		6451					(CAN) ON A ROUTINE START-UP BRUSH INSPECTION, IT WAS NOTED THAT THE BRUSHES WERE WORN.  STARTER/GENERATION WAS REPLACED.	  THE SUBJECT STARTER WAS FOR REPAIR.  INSPECTION REPORT:  PREVIOUS CONDITION (06/14/99) BRUSHES WERE RUN DOWN TO RIVETS	 CAUSING SEVERE COMMUTATOR WEAR.  DUE TO THE COMMUTATOR WEAR, THE ARMATURE WAS ON THE LAST RUN.  (X)				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000112900325	20001129	00325	SW  	2000	11	29	CA001103021      	1	20000909	G	2821	A2802	SOLENOID VALVE  			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL SUMP	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE THE FUEL SUMPS WERE BEING DRAINED IN PREPARATION FOR FLIGHT, IT WAS NOTED THAT THE LEFT FUEL SUMP WAS LEAKIN	G.  THE SUMP SOLENOID WAS RECYCLED AND FUEL LEAK STOPPED.  WITH SIMPLEX SPRAY SYS INST FUEL DRAIN SOLENOID IS INACCESSIB	LE. TH E SOLENOID DRAIN VALVE P/N A280-2 REPL. DRAIN VALVE DISASSEMBLED TO TRY AND LOCATE CAUSE FOR FUEL LEAK.  UPON EXA	MINING DISASSEMBLED VALVE, IT FOUND TO CONTAIN 3 PIECES OF SAND IN VALVE.  SUBMITTER SUSPECTED THAT PIECE OF SAND OR OTH	ER FOREIGN MATTER PREVENTED SEALING SURFACES ON VALVE FROM SEALING PROPERLY.  SHOULD BE ISOLATED INCID. AT THIS PARTICUL	AR OPERATION.  IF, UPON CONDUCTING SUMP DRAIN, FUEL CONTINUES TO LEAK, RECYCLE DRAIN SOLENOID.  (X)	1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2000120700197	20001207	00197	SW  	2000	12	7	CA001106002      	1	20001012	G	2420	LW13039	BRACKET         			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					MIDDLE	FAILED          	W				K	 	 	 	NONE                    				B	H	 	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		LD	LANDING        	1			CA			2431 								(CAN) IN-FLIGHT FAILURE OF REAR HALF OF BRACKET CAUSING ALTERNATOR FORWARD MOUNT TO BREAK.  PILOT NOTICED BURNING SMELL 	IN COCKPIT FROM ALTERNATOR BELT AND UPON LANDING, INVESTIGATED AND FOUND ALTERNATOR HANGING ONLY BY THE WIRES AND SUPPOR	T OF 1 SCAT HOSE.  (X)				1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2001032600243	20010326	00243	CE  	2001	3	26	CA001106003      	1	20001023	G	5553	04310093	FITTING         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	VERTICAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			21318								(CAN) CRACK FOUND IN BRACKET THAT ATTACHES VERTICAL FIN TO FUSELAGE, AT THE REAR ATTACH POINT.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2000120700198	20001207	00198	GL  	2000	12	7	CA001106006      	2	20001020	G	7250	6898782	BLADE           								ALLSN 	250C  	250C20B     	03013	GL  					2ND ST BLADE RT	MISSING         	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			1644 			HX119758					(CAN) N1 AND N2 SYSTEMS ABLE TO ROTATE PRIOR TO DISMANTLING, TURBINE FULLY DISMANTLED.  NO EVIDENCE OF FOD UPSTREAM OF 2	ND STAGE TURBINE WHEEL.  HEAVY D.O.D. DOWNSTREAM OF 2ND WHEEL.  2ND TURBINE WHEEL MISSING ONE TURBINE BLADE.  QTY SIX BL	ADES APPROX. 180 INCHES AWAY EXHIBIT DAMAGE ON THE TRAILING EDGES.  THE NR 8 STATIONARY LAB SEAL IS BROKEN IN TWO PIECES	, HOWEVER, BEARING LOCATION IS ONLY MINIMALLY EFFECTED.  GP FORWARD ROTATING LAB SEAL BROKEN, PART OF SEAL HAS NOT BEEN 	LOCATED.  1ST AND 2ND BLADE PATHS EXHIBIT SUBSTANTIAL TIP RUB INDICATIONS.  ALL OIL NOZZLES, SHAFTS, SUPPORTS AND BEARIN	GS ARE IN NORMAL CONDITION.  (X)						3	U			E4CE				 
2000112900326	20001129	00326	SW  	2000	11	29	CA001106007      	1	20001020	G	6520	206030446001F	MOUNT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX	FAILED          	W				K	 	 	 	NONE                    				P	 	 	NO WARNING INDICATION     			NR	NOT REPORTED   	1			CA											(CAN) CRACK RADIATING ACROSS REAR PORT SIDE ATTACHMENT HOLE FOR THE TAIL ROTOR GEARBOX STUDS.  (X)						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032600245	20010326	00245	NM  	2001	3	26	CA001106009      	1	20000303	G	2910	82920010363	LINE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					HYD PUMP	FRACTURED       	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			4532 								(CAN)   CLIMBING THOUGH FL80 FROM COPENHAGEN, 1ST OFFICER REPORTED LOSS OF NR 2 HYDRAULIC SYSTEM CONTENTS. AIRCRAFT RETU	RNED TO COPENHAGEN, CARRYING OUT ACTION IAW EMERGENCY CHECKLIST NR 2 HYDRAULIC SYSTEM FLUID LOSS. AIRCRAFT STATICS: TOTA	L HOURS 4532.10  TOTAL CYCLES 4601REF/ASR050/00/DH8 ENGINE INSPECTION FOUND HYDRAULIC PRESSURE LINE FRACTURED, PIPE ASSE	MBLY REPLACED AND LEAK CHECK CARRIED OUT SATISFACTORY. DURING ENGINE RUN, HYDRAULIC NR 2 SYSTEM DEPLETED AND ILLUMINATIO	N OF CAUTION LIGHTS & NR  2 SPU CCT BKR POPPED, MAINTENANCE FOUND LEAK FROM NR 2 SPU CASE DRAINCASE, SPU REPLACED & NR 2	 CASE DRAIN FILTER REPLACED & NR 2 ENGINE DRIVEN PUMP REPLACED IAW DHC-8  AMM 5-50-33 DUE	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400015	20010314	00015	NM  	2001	3	14	CA001106010      	1	20000312	G	5260	85210276101	BOLT            	DHAV        	85210001001 	DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					AIRSTAIRS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19202								(CAN) THE FOLLOWING WAS REPORTED TO US (FROM BRYMON MAINTENANCE CONTROL):  AFTER LANDING IN ABERDEEN THE NR 1 CABIN ATTE	NDANT WAS UNABLE TO OPEN PASSENGER AIRSTAIR DOOR. ENGINEERS WERE CALLED TO ASSIST WITH OPENING THE DOOR USING THE EXTERN	AL MECHANISM.AIRCRAFT STATISTICS: TOTAL HOURS: 19202.35 TOTAL CYCLES:  20379 REF ASR - 057/00/DH8. UPON INSPECTION:  BRY	MON ENGINEERS FOUND A THREADED INSERT HAD WORKED LOOSE FROM THE BOLT AND INTERFERED WITH THE DOOR LINKAGE. THE BOLT AND 	THREADED INSERT WERE REPLACED WITH NEW ITEMS AND AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400017	20010314	00017	NM  	2001	3	14	CA001106013      	1	20001018	G	5610	8SC0043005	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			4120 								(CAN) WHILE IN CRUISE AT 18,000 FT PILOTS FORWARD WINDSHIELD SHATTERED. NO BIRD OR F.O.D. REPORTED. ABNORMAL PROCEDURES 	CARRIED OUT. AIRCRAFT DESCENT TO STAY CLEAR OF ICING. CABIN PRESSURIZATION 3.0 LBS MAX & 150 IAS AS PER CHECKLIST. NORMA	L LANDING C/O NO FURTHER COMPLICATIONS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001030600003	20010306	00003	EA  	2001	3	6	CA001106015      	1	20001025	G	2711	C2CF451ND	ROD             			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT AILERON	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION, THE LT AILERON PUSH ROD WAS FOUND TO BE NOTICEABLY HEAVIER THAN THE OTHER. THE TUBE WAS CHECKED W	ITH A MAGNET AND FOUND TO BE STEEL. NO RECORD CAN BE FOUND OF STEEL PUSH RODS BEING APPROVED FOR DHC-2 BEAVER AIRCRAFT -	 SUSPECT BOGUS PART. THE TUBE SECTION WAS REPLACED WITH AN APPROVED COMPONENT.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001032600004	20010326	00004	EA  	2001	3	26	CA001106016      	1	20001031	G	5341	C3FS145	BUSHING         	DHAV        	DHC3        	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					TIE BAR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						172					(CAN) DURING AD CF-82-26R1,  FOUND THAT TIE BAR BUSHINGS WERE NOT OF NORMAL TYPE PER PARTS MANUAL. TIE BAR BUSHINGS WERE	 REMVD&VISUAL&DYE CHECK INSP CARRIED OUT ON END FITTING. DURING NDT INSPE CTION, IND.S WERE THAT CRACK RADIATING FROM BU	SHING HOLE ON TOP INBOARD EDGE. FOR PURPOSES, OF FURTHER INSP, SURFACE MATERIAL REMVD TO MIN THICKNESS OF TIE BAR LUG. F	LUORESCENT PENETRANT INSPECTION CARRIED OUT AGAIN, & CRACK IND.			1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001031400019	20010314	00019	EU  	2001	3	14	CA001106018      	1	20001027	G	3297	9717510230	WIRE            		9603001102  	PILATS	PC12  	PC1245      	7090551	EU  										MLG ACTUATOR	CORRODED        	W				A				UNSCHED LANDING         				N			FALSE WARNING             			LD	LANDING        	1			CA			2792 			0163					(CAN) UPON LOWRING OF LANDING GEAR FLT CREW RPTED THEY HAD NO R/H GREEN DOWN &LOCKED GEAR IND.. FLT CREW NOTIFIED ATC&UN	EVENTFUL PRECAUTIONARY LDG CARRIED OUT. A/C TOWED OFF RWY & MAINT CREWS INVESTIGATED THE  FALSE IND.. PLUG PG 057 REMVD 	FROM RT MLG ACTUATOR DOWN IND. SWITCH, (SW IS INTERNAL IN ACTUATOR)&JUMPER PLACED TO SIMULATE SW OPEARTION. PROVIDED GRE	EN IND. TO COCKPIT SO ACTUATOR (MISTA KENLY) CONSIDERED AS HAVING FAULTY IND. MICRO SWITCH,&REPL. SEVERAL GEAR SWINGS WE	RE CARRIED OUT WITH NORMAL IND.S&A/C RT-SRV. A/C DEPARTED TO ITS NEXT DESTINATION&AGAIN FAILED TO HAVE R/HGEAR DOWN&LOCK	ED INDICTION UPON LOWERING OF	1	L	7	1 	3T			RT	A78EU   					 
2001032600011	20010326	00011	CE  	2001	3	26	CA001106020      	1	20001024	G	2820	AN9176D	FITTING         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUEL LINE	CRACKED         	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA			1600 								(CAN) THERE WAS A STRONG SMELL OF FUEL WHEN THE AIRCRAFT WAS PARKED AND DOOR OPENED.A CHECK OF THE COMPLETE FUEL SYSTEM,	 FOUND UNDER CABIN FLOOR. LEFT SIDE WHERE FRONT AND REARFUEL TANK LINES ARE CONNECTED, TEE FITTING WAS LEAKING. UPON REM	OVAL ATHE TEE FITTING P/N AN917-6D IT WAS FOUND TO BE CRACKED.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2001031400024	20010314	00024	NM  	2001	3	14	CA001107005      	1	20001031	G	2620	453N260220	TUBE            			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					EXTINGUISHER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK INSPECTION, FOUND CARGO FIRE EXTINGUISHING TUBE RUBBED THROUGH BY CONTACTING APU BLEED AIR DUCT. CA	USE OF PROBLEM IS THE APU DUCT VIBRATION WITH CLOSE TOLERANCE. FIX IS INCORPORATION OF SB 57-26A0040.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001031400025	20010314	00025	EA  	2001	3	14	CA001107006      	1	20001013	G	7830	22850741115	SWITCH          	GE          	CF343A1     	CNDAIR	CL600 	CL600*      	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					THRUST REVERSER	INTERMITTENT    	W				E				ENGINE SHUTDOWN         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						4066					(CAN) AIRCRAFT DEPARTED FARNBOROUGH  EN ROUTE TO BEIRUT. CLIMBING THROUGH 45,000 FEET AT 220 KNOTS, THE RT AMBER REVERSE	R UNLOCK CAPTION ILLUMINATED. CHECK LISTS FOLLOWED, EMERGENCY STOW WAS SELECTED. ENGINE WAS SHUT DOWN AND AIRCRAFT DIVER	TED TO STANSTED AIRPORT. FURTHER TROUBLESHOOTING REVEALED THAT THE STOW SWITCH FROM THE RT THRUST REVERSER WAS FOUND INT	ERMITTENT.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400026	20010314	00026	NE  	2001	3	14	CA001107008      	2	20001029	G	7321	6078T55P20	FUEL CONTROL    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			M			OVER TEMP                 			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, NR 2 ENGINE N2 NOTED DROPPING TOWARDS ZERO AND ITT RAPIDLY INCREASING INTO THE RED.FAULTY MFC CONFI	RMED DURING GROUND RUN. MFC REPLACED AND A SUCCESSFUL GROUND RUN FOLLOWED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400027	20010314	00027	NE  	2001	3	14	CA001107009      	2	20001029	G	7230		COMPRESSOR      	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	DAMAGED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA						807499					(CAN) CREW REPORTED NR 1 ENGINE VIBRATION AFTER TAKEOFF FOLLOWED BY UNCOMMANDED ENGINE STOPPAGE.BOROSCOPE INSPECTION REV	EALED EXTENSIVE COMPRESSOR DAMAGE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2000112900327	20001129	00327	EU  	2000	11	29	CA001107011      	1	20001026	G	6220	704A3363320851	MAIN ROTOR      		350A31000001	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARFLEX END	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			718  			M375					(CAN) DELAMINATION DETECTED WITH REFERENCE TO EUROCOPTER AS350 MAINTENANCE WORK CARD 62.20.00.601 PARAGRAPH 4.3 (ILLUSTR	ATION FIGURE 5, DETAIL A,  LOCATION ON PART AT DETAIL N).  PENETRATION WITH A 010 INCH FEELER GAUGE TO A DEPTH OF APPROX	IMATELY .75 INCH DETECTED BETWEEN ATTACHMENT BLOCK TO STARFLEX AND LAMINATED COMPONENT.  TOLERANCE EXCEED PRESCRIBED LIM	ITS.  (P=.45 INCH APPROXIMATELY, L=1.0 INCH APPROXIMATELY).  PART HAS A 6,400 HOUR SERVICE LIFE LIMIT.  DEFECT OCCURRED 	AT 718 HOURS IN SERVICE.  (X)		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001031400028	20010314	00028	NE  	2001	3	14	CA001107012      	2	20001107	G	8530	404473	ROCKER          			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	CA3         	52026	NE  					CAP	BROKEN          	W				O				OTHER                   				K	E		FLUID LOSS                	VIBRATION/BUFFET          		CR	CRUISE         	1			CA				951  							(CAN) AIRCREW REPORTED LT ENGINE ROUGH RUNNING AND OIL LEAK UPON INVESTIGATION EXHAUST ROCKER CAP FOUND BROKEN. BOTH ROC	KER ARM ADJUSTERS INTAKE AND EXHAUST WERE BACKED ALL WAY OUT. AT NUMBER 8 CYLINDER.					2	H	7	2 	4R	4	R	 	A14EA   	E231				 
2001031400029	20010314	00029	NM  	2001	3	14	CA001107015      	1	20001007	G	3411		PITOT LINE      			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					AIRSPEED IND	LOOSE           	W				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) LOSS OF CAPTAINS AIRSPEED INDICATOR DURING TAKEOFF. FOUND PITOT LINE LOOSE. PITOT LINE TIGHTENED. SYSTEM LEAK CHEC	KED AND TESTED AS PER M.M. 34-11-0.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000120400200	20001204	00200	SO  	2000	12	4	CA001107016      	1	20001024	G	3250	AN3H10A	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					BOOT	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING ON THE GROUND, THE PILOT NOTICED THERE WAS NO CONTROL OF THE NOSE WHEEL.  AFTER CHECKING THE 3 BOLTS	, AN3H-10A WERE FOUND SHEARED OFF. THE BOLTS WERE REPLACED AND PROPERLY TORQUED AND LOCKED PER MAINTENANCE MANUAL.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032600014	20010326	00014	GL  	2001	3	26	CA001107017      	1	20001016	G	2701	83450712	SWITCH          		GC41511003  	BOMBDR	BD700 	BD7001A10   	1390006	GL  										CONTROL YOKE	SHORTED         	W				K	 	 	 	NONE                    				N		 	FALSE WARNING             			IN	INSP/MAINT     	1			CA						0047					(CAN) INTERMITTENT TCS ADVISORY (AMBER) POSTED ON PILOTS FLIGHT DIRECTOR DURING PREFLIGHT INSPECTION. FOUND BOLT (P/N NA	S6203-40, ATA 27-11-01) HAD PENETRATED WIRING HARNESS TO THE PILOTS BUTTON AND SWITCH CONTROLS IN THE STEERING YOKE. SPE	CIFICALLY THE TCS BUTTON (TOUCH CONTROL STEEING, ATA 22-11-05). ON REMOVAL OF THE HARNESS FROM THE COLUMN, IT WAS FOUND 	THAT ONE ADDITIONAL WIRE HAD BEEN DAMAGED. IN BOTH CASES THE INSULATION HAD BEEN STRIPPED OFF ABOUT 1/4.			2	L	7	2 	4F			RT	T00003NY					 
2000120400201	20001204	00201	SO  	2000	12	4	CA001107018      	2	20001019	G	7414		ROTOR SHAFT     	SLICK       	4309        	DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  					MAGNET & SEAL	SHEARED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			400  			99040600					(CAN) PLANE HAD BEEN SNAGGED FOR A 200 RPM DROP ON RT MAGNETO.  MAGNETO WAS PULLED FOR INSPECTION, FOUND THE ROTOR SHAFT	 TO BE SHEARED.  A NEW MAGNETO HAS BEEN RE-INSTALLED.  (X)					1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO				 
2000120400202	20001204	00202	SO  	2000	12	4	CA001107019      	1	20001018	G	3710	441CC7	COUPLING        	AIRBORNE    	RAPCD441CC7 	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					RT ENGINE	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				678  		81089					(CAN) AIRCRAFT ON FLIGHT FROM RIMOUSKI TO HALIFAX.  AT ARRIVAL, PILOT ADVISED HIS AMO THAT RT VACUUM PUMP INDICATED 0 AT	 SHUT DOWN PROCEDURE.  AMO ARRANGED FOR PUMP REPLACEMENT AT HALIFAX.   NOTE:  USUAL FAILURE:  SHEARED DRIVE.  (X)					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000112900330	20001129	00330	EU  	2000	11	29	CA001107020      	1	20001020	G	5532		STABILIZER      	VECTOR      	350A14002008	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					L/E LWR SECTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			3633 			TB2968					(CAN) CRACK FOUND ON UPPER VERTICAL FIN LOWER SECTION OF LEADING EDGE BETWEEN TWO RIVETS, 2.6250 INCHES ABOVE STAMPED FI	TTING, 2.50 INCHES, LENGTH OF CRACK.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001031400030	20010314	00030	NM  	2001	3	14	CA001107021      	1	20001017	G	5610	65528038	CONTROLLER      			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9       	52048	NE  					WINDOW HEAT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA				17525							(CAN) CAPTAINS NR 2 SLIDING WINDOW - EXTERIOR PANE SHATTERED ON CLIMB OUT. WINDOW HEAT SHORTED RESULTING IN SPARKS AND S	MOKE FROM ARCING.WINDOW AND CONTROLLER REPLACED. TEARDOWN REPORT CONFIRMED  THE WINDOW HEAT CONTROL FAILED.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2000120400203	20001204	00203	EA  	2000	12	4	CA001108002      	2	20001024	G	7414	1068255514	MAGNETO         	LYC         		CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	POINTS	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				185  		L75776					(CAN) ENGINE STARTED TO RUN ROUGH IN FLIGHT AND THEN QUIT.  AIRCRAFT FORCED TO DO EMERG LANDING. PRIOR TO INCIDENT, 4.1 	HRS EARLIER, RIGHT MAG ROUGH AND DROPPING BELOW LIMITS ON STATIC RUN.  MAG REMOVED INTERNAL TIMING SET, REINSTALLED.  PO	INT GAP PRIOR TO RE-TIMING FOUND CLOSER THAN NORMAL. JUST ATTRIBUTED TO POINTS WEARING IN.  AFTER FORCED LANDING, MAG RE	MOVED, POINTS CHECKED,  NO POINT GAP NOTED.  POINTS WERE TIGHT, WERE NOT MOVABLE, HAD NOT MOVED SINCE INTERNAL TIMING HA	D BEEN CARRIED OUT.  POINTS REMOVED, APPEARED PLASTIC CAM FOLLOWER MELTED, CAM FOLLOWER WORN DOWN TO APPROX. 1/2 OF NEW 	SET.  CAM FOLLOWER APPEARED TO HAVE GOTTEN HOT.  CONDENSORS, MAG HAVE BEEN SENT FOR FURTHER INVESTIGATION.  (X)	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2000120400204	20001204	00204	SO  	2000	12	4	CA001108003      	1	20001030	G	2730	40060	CHANNEL         	PIPER       	5423224     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					BETWEEN RIBS	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			12856			31176					(CAN)  CRACKS FOUND WHEN TEARING DOWN ELEVATOR TO PERFORM INSTALLATION OF KIT 766-642 PER SB 1008 - BUTT RIB REPLACEMENT	.   SB 998A RELACEMENT OF SPAR ALSO CARRIED OUT TO COMPLY WITH AD 99-12-05.  NOTE:  NEW CHANNEL COMES IN KIT 766-642.  T	HESE CRACKS COULD NOT HAVE BEEN DETECTED IN SB 998A AND SB 1008 INSPECTION PROCEDURE AS CHANNEL IS CLOSED IN.  SUBMITTER	 STATED TO SEE THAT AREA, AN INSPECTION HOLE AND BLANKING PLUG WOULD BE REQUIRED SUCH AS IN SB 998A, BUT LOCATED SOMEWHE	RE  BETWEEN THE RIBS AS ABOVE AND REAR OF THE CHANNEL.  (X)		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000112900331	20001129	00331	NE  	2000	11	29	CA001108008      	1	20001022	G	6310	7636109103104	SHAFT           	SKRSKY      		SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					OUTPUT SHAFT	SHEARED         	W				K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		NR	NOT REPORTED   	1			CA						A06700640					(CAN) POWER OUTPUT SHAFT FOUND SHEARED AT THE THREADED END WHEN ENGINE WAS REMOVED FOR SCHEDULED MAINTENANCE.  POSSIBLE 	CAUSE IS ENGINE DRIVESHAFT MISALIGNMENT - NEW SHAFT WAS INSTALLED ON ENGINE AND SHAFT ALIGNMENT CARRIED OUT ON REINSTALL	ATION OF ENGINE.  (X)				1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2000112900332	20001129	00332	GL  	2000	11	29	CA001108009      	2	20001025	G	7314	6896810	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FUEL PUMP	WORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				2549 				CAE890189S			(CAN) NR 2 ENGINE DECELLED IN-FLIGHT.  INLET FUEL LINE TO FUEL PUMP (P/N 76307-02003-083) HAD WORN A GROOVE ON FUEL PUMP	 UNION (P/N AN919-19D). THIS  ALLOWED AIR INTO THE FUEL SUPPLY SYSTEM.  FUEL PUMP P/N 6896810 REPLACED.  AN919-10D UNION	 REPLACED.  ENGINE GROUND RUN AND FLIGHT TESTED,  SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.  (X)				1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2000112900333	20001129	00333	NE  	2000	11	29	CA001108010      	1	20001026	G	5320	7620202003126	POST            	SKRSKY      		SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					STA 215	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10194			760015					(CAN) CHANNEL (POST) CRACKED AT BAGGAGE FLOOR LEVEL.  STATION 215 AND BL ZERO REPAIR CENTERLINE POST IAW SRM 53-10-03 PA	GE 219, 30 NOV. 1998 AVAILABLE FOR REPAIR.  (X)					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2000112900334	20001129	00334	NE  	2000	11	29	CA001108011      	1	20001026	G	6230	7610408500041	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					SWASHPLATE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						A2300027					(CAN) UPON PURCHASE AND DISASSEMBLY OF THIS HELICOPTER, THE SWASHPLATE BEARING SHOWED SIGNS OF CORROSION AND LACK OF GRE	ASE. THE SWASHPLATE DRIVE LINK LUG ALSO SHOWED SIGNS OF CORROSION.  (X)					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001010900001	20010109	00001	EA  	2001	1	9	CA001109004      	1	20001026	G	2910		FITTING         			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	HYD LINE	BROKEN          	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			31593								(CAN) DURING CLIMB NR 2 HYDRAULIC PUMP CAUTION LIGHT ILLUMINTED, SYSTEM PRESSURE AND QUANTITY DROPPED TO ZERO. NR 1 HYDR	AULIC PUMP THEN FAILED SHORTLY AFTER.  MAINTENANCE DISCOVERED AN ALUMINUM HYDRAULIC LINE BROKEN AT THE FLARED FITTING. T	HIS LINE IS LOCATED AFT OF THE ENGINE FIRE WALL IN THE NR 2 NACELLE. NR 1 & NR 2 HYDRAULIC PUMP & FILTERS REPLACED. THE 	SYSTEM BLED AND LEAK CHECKED AND THE AIRCRAFT RETURNED TO SERVICE.			2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001031400032	20010314	00032	NM  	2001	3	14	CA001109008      	1	20001101	G	3211	69186803	BOLT            			BOEING	727   	727217      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG FITTING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1393 							(CAN) DURING DISASSEMBLY OF RT MAIN LANDING GEAR OLEO TO CARRY OUT OLEO SEAL REPLACEMENT DUE STRUT LEAKING, IT WAS FOUND	 THAT THE RT MAIN LANDING GEAR UPPER SIDE STRUT UNIVERSAL FITTING ATTACH BOLT HEAD WAS CRACKED. RT UPPER SIDE STRUT UNIV	ERSAL FITTING ATTACH BOLT REPLACED WITH NEW BOLT, GEAR SWING CARRIED OUT CHECKS SERVICEABLE PER M/M 32-11-41. NOTE AFTER	 REVIEW OF THE BOLT IT WAS OBSERVED THAT THE BOLT IS CORRODED UNDER THE HEAD AS THE HEAD CAME OFF WHILE BEING REMOVED. U	NSERVICEABLE BOLT IS NOW IN OUR QUARANTINE AWAITING DISPOSITION.		2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2001032700009	20010327	00009	SO  	2001	3	27	CA001110002      	1	20001023	G	3710	442CW	SPLINE ADAPTER  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	SHEARED         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA				808  							(CAN)  PNEUMATIC PUMP WARNING CAME ON IN CRUISE ON RETURN FLIGHT TO BASE (CARGO  FLIGHT).  REPLACED PUMP, USUAL DRY AIR 	PUMP FAILURE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000120400205	20001204	00205	EA  	2000	12	4	CA001110003      	2	20001018	G	7314	02480010402	PUMP            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					FUEL PUMP	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3617 			1689					(CAN) FUEL PUMP FAILED.  (X)						1	L	7	2 	3T	3	T	 	3A20    	E4EA				 
2001032700010	20010327	00010	EA  	2001	3	27	CA001110004      	2	20001101	G	7414	1068291018	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				R	Y	 	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA				119  							(CAN)   PILOT REPORTED HE HAD MAG DROP AT END OF LEG. OK AT RESTART AND AGAIN BAD AT ARRIVAL. RETURN LEG SHOWED HI-EGT A	ND HI-CHT. CHECKED MAGNETO TIMING FIRING AT TDC INSTEAD OF  20 DEGREES BDC. ATTEMPTED RE TIMING TO 20 DEGREES IN VAIN.  	CONCLUSION: INTERNAL  WEAR AND SLIPPAGE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032700011	20010327	00011	NM  	2001	3	27	CA001110007      	1	20001023	G	5730	149T17500159	PANEL           			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					FUSELAGE	MISSING         	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) ON AIRCRAFT ARRIVAL FOUND PANEL MISSING ON LEFT HAND WING ROOT TO FUSELAGE. PANEL 195CL INSTALLED NEW ANCHOR NUTS 	AND PANEL.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001032700013	20010327	00013	NM  	2001	3	27	CA001110009      	1	20001023	G	2913	MPN6294502	MOTOR           			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					HYD PUMP	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH TO TORONTO, CENTRE HYDRAULIC LOSS. EXTENDED THE GEARS MANUALLY, AIRCRAFT LANDED WITHOUT FURTHER INCIDE	NT. HYDRAULIC FILTERS, AC MOTOR HYDRAULIC PUMP DRIVE, AND AIR DRIVEN PUMP UNIT WERE CHANGED. OPERATION CHECK CARRIED OUT	, NORMAL.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001032700014	20010327	00014	NM  	2001	3	27	CA001110013      	1	20001014	G	7722	285N002821	CARD            			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					RT ENGINE	FAULTY          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			N	 	 	FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) RIGHT HAND ENGINE OVERHEAT ON ENGINE CREW ALERT SYSTEM, AND MASTER CAUTION CAME ON ON CLIMB OUT. ENGINE SHUT DOWN 	AND DIVERTED INTO WINNIPEG. FOUND RIGHT HAND ENGINE LOGIC CARD M10274 AT FAULT. REPLACED M10274 CARD.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001032700017	20010327	00017	WP  	2001	3	27	CA001110016      	1	20001009	G	5610	5613217519	WINDOW          			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  					COCKPIT	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CREW REPORTED SMALL HOLE 1/4 - 1/2 INCH IN COCKPIT LEFT HAND SLIDING WINDOW.CHANGED LEFT HAND COCKPIT WINDOW.						2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001032700018	20010327	00018	NM  	2001	3	27	CA001110018      	1	20001010	G	3350		LIGHT           			BOEING	747   	747433      	       	NM  	PWA   	4056  	PW4056      	 	NE  					CABIN	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) NUMEROUS EMERGENCY LIGHTS OUT ON AIRCRAFT FLOOR PATH LIGHTING. LIGHTS REPAIRED AT R1 DOOR, ISLES R3 AND UPPER DECK	 LIGHT SYSTEM CHECKED SERVICEABLE.					2	L	7	4 	4F	4	F	RT	A20WE   	E24NE				 
2001031400041	20010314	00041	EA  	2001	3	14	CA001110026      	1	20001101	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			420  								(CAN) CREW REPORTED THAT AFTER LANDING THE PILOTS WINDSHIELD SHATTERED, AIRCRAFT TAXIED TO THE GATE. ASA DISPATCHED MAIN	TENANCE PERSONNEL FROM ATL ALONG WITH A WINDSHIELD TO CARRY OUT REPAIRS.THE WINDSHIELD WAS REPLACED AND THE AIRCRAFT RET	URNED INTO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001031400042	20010314	00042	EA  	2001	3	14	CA001110028      	1	20001101	G	2611	473052	SMOKE DETECTOR  			CNDAIR	CL600 	CL6002B19   	       	EA  										CARGO BAY	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) CARGO SMOKE WARNING CAME ON DURING CRUISE FLIGHT. CREW FOLLOWED QRH. BOTH EXTINGUISHER BOTTLES BLOWN. MESSAGE REMA	INED. DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT, RETURNING TO CVG. R&R THE CARGO SMOKE DETECTOR BOXES.					2	L	7	2 	4F			RT	A21EA   					 
2001031400043	20010314	00043	EA  	2001	3	14	CA001110029      	1	20001101	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			1220 								(CAN) AFTER TAKEOFF FROM DES MOINES, IOWA CREW REPORTED THAT THE PILOTS SIDE WINDOW SHATTERED, NO LOSS OF PRESSURIZATION	. AIRCRAFT RETURNED TO DES MOINES, AND COMPLETED AN UNEVENTFUL LANDING. ASA DISPATCHED MAINTENANCE PERSONNEL TO REPLACE 	THE WINDOW.				2	L	7	2 	4F			RT	A21EA   					 
2001032700020	20010327	00020	EA  	2001	3	27	CA001110031      	1	20001102	G	7600	5071T98P03	AMPLIFIER       			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 ENGINE	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLT 4627,  AFTER SETTING CLIMB THRUST THE LT ENGINE ACCELERATED TO OVER 101 PERCENT. THE POWER LEVER WAS RETARDED 	AND THE ENGINE (N1) THEN LATER DROPPED BY 6 PERCENT UNCOMMANDED. REMOVE AND REPLACE NR 1 ENGINE N1 CONTROL AMPLIFIER. PE	RFORMED FUNCTIONAL CHECK IAW CRJ POWER PLANT GROUND RUN MANUAL 77-00-00. OPS CHECK GOOD.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700021	20010327	00021	EA  	2001	3	27	CA001110032      	1	20001102	G	2400		RELAY           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					WARNING SYSTEM	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) APR INOP CAUTION MESSAGE ON TAKEOFF ROLL, ABORTED TAKEOFF. REMOVED AND REPLACED APR ARM RELAY (K1KL) IN JB-5. OPS 	CHECKED, SYSTEM NORMAL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400044	20010314	00044	EA  	2001	3	14	CA001110033      	1	20001102	G	3234	601R510087	HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  										MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) CREW REPORTED THAT DURING SELECTION OF THE LANDING GEAR TO THE DOWN POSITION, THE LANDING GEAR SELECTOR HANDLE BRO	KE. THE LANDING GEAR DID EXTEND TO A DOWN AND LOCKED POSITION AND THE AIRCRAFT LANDED WITHOUT INCIDENT. REMOVED, REPLACE	D AND TESTED THE LANDING GEAR HANDLE PANEL ASSY IAW AMM. AIRCRAFT BACK IN SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001031400045	20010314	00045	NE  	2001	3	14	CA001110034      	2	20001102	G	7230	6078T27G01	COMPRESSOR      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1 ENGINE	DAMAGED         	W				A				UNSCHED LANDING         				E	X	J	VIBRATION/BUFFET          	ENGINE FLAMEOUT           	WARNING INDICATION        	CL	CLIMB          	1			CA			7243 	7243 							(CAN) CREW REPORTED NR 1 ENGINE VIBRATION AFTER TAKEOFF FOLLOWED BY AN UNCOMMANDED ENGINE STOPPAGE. MAINTENANCE REPORTED	 THAT A BORESCOPE INSPECTION REVEALED EXTENSIVE COMPRESSOR DAMAGE. 2000-11-14TC:					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400046	20010314	00046	EA  	2001	3	14	CA001110035      	1	20001102	G	2130	21197646	CONTROL PANEL   			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	DEFECTIVE       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT OF MEMPHIS THE CREW WERE UNABLE TO PRESSURIZE THE AIRCRAFT USING EITHER AUTO OR MANUAL MODES. MAINTEN	ANCE FOUND THE OVERHEAD PRESSURIZATION CONTROL PANEL TO BE DEFECTIVE. A NEW PRESSURIZATION CONTROL PANEL WAS INSTALLED A	ND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001031400047	20010314	00047	EA  	2001	3	14	CA001110036      	1	20001102	G	2910	601R7528637	LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	CHAFED          	W				A				UNSCHED LANDING         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA											(CAN) FIGHT CREW RECEIVED NR 1 HYDRAULIC LOW PRESSURE CAUTION MESSAGE, FOLLOWED QRH, DIVERTED TO BNA FOR REPAIR. MAINTEN	ANCE FOUND 3/4 INCH HYDRAULIC PRESSURE LINE CHAFED, REPAIRED LINE WITH PERMASWAGE FITTINGS IAW AMM. REMOVED AND REPLACED	 NR 1 HYD EDP, AND FLEXIBLE LINE P/N 601R75147-19 DUE TO APPARENT FLUID SEEPAGE, OPS AND LEAK CHECKED GOOD.				2	L	7	2 	4F			RT	A21EA   					 
2001032700022	20010327	00022	EA  	2001	3	27	CA001110038      	1	20001104	G	2120	14243101	DUCT            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					AIR DISTRIBUTION	CRACKED         	W				O	 	 	 	OTHER                   				B		 	SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER FLIGHT 5401 FROM CVG TO TOL, WHILE PARKED AT THE GATE WITH APU RUNNING GOT A SMOKE TOILET WARNING MSG & LAV 	SMOKE DETECTOR WAS BEEPING. ALSO SMOKE IN THE CABIN. PERFORMED QRH, SMOKE DETECTOR STOPPED BEEPING & WARNING MSG CLEARED	, AND CALLED FOR FIRE TRUCK. NO PAX WERE ON BOARD.FOUND DUCT P/N 14243-101 FROM RT PRSOV TO RT PACK HEAT EXCHANGER CRACK	ED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400048	20010314	00048	NE  	2001	3	14	CA001110039      	2	20001107	G	7230		BLADE           	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COMPRESSOR FAN	DAMAGED         	W				A				UNSCHED LANDING         				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		TO	TAKEOFF        	1			CA						807402					(CAN) AFTER TAKEOFF OUT OF MANCHESTER NH (MHT) GOT N1 VIB ICON. FOLLOWED BY SMOKE IN CABIN. CREW SHUT DOWN THE ENGINE AN	D RETURNED TO BLOCKS. PRELIMINARY REPORT OF EXTENSIVE FAN BLADE DAMAGE. ROAD CREW BEING ARRANGED TO GO TO MHT FOR POSSIB	LE ENGINE CHANGE. AVIONICS TECH DISPATCHED TO DO AN FDR DOWN LOAD. 2000-11-14TC:  EXPECT FOLLOW-UP SDR FROM ORIGINATOR A	S TO CAUSE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400049	20010314	00049	NE  	2001	3	14	CA001110040      	2	20001107	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NACELLE	FAILED          	W				A				UNSCHED LANDING         				E	X	J	VIBRATION/BUFFET          	ENGINE FLAMEOUT           	WARNING INDICATION        	AP	APPROACH       	1			CA				9000 							(CAN) INBOUND FLIGHT FROM RALIEGH / DURHAM, NC (RDC). PILOT FELT SLIGHT VIBRATION IN SEAT. OIL PRESSURE WENT TO ZERO. EN	GINE AUTO-SHUTDOWN. AIRCRAFT MADE AN UNEVENTFUL LANDING. CHIP DETECTOR HAS LARGE AMOUNT OF DEBRIS ON IT.ENGINE HAS APPRO	XIMATELY 9000 HOURS ON IT AND WAS INSTALLED ON OCT 10/2000. PREVIOUS SHOP VISIT WAS FOR COMPRESSOR DAMAGE. AIRCRAFT CURR	ENTLY IN HANGAR AT CINCINNATI. COWLINGS HAVE BEEN OPENED. NO OBVIOUS SIGN OF DAMAGE - NO OIL IN TAILPIPE.FDR READOUT BEI	NG MADE. 2000-11-14TC:  EXPECT FOLLOW-UP SDR FROM ORIGINATOR AS TO CAUSE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700023	20010327	00023	EA  	2001	3	27	CA001110041      	1	20001109	G	5510		BUSHING         			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				J	F	 	WARNING INDICATION        	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) SHORTLY AFTER TAKEOFF, THREE MINUTES AFTER AUTOPILOT WAS ENGAGED PILOT RECEIVED AP PITCH TRIM MESSAGE. SECOND FAIL	URE OF AUOPILOT OCCURRED 1 MINUTE AFTER RE-ENGAGEMENT MESSAGES POSTED ON EICAS DURING EVENT WERE AP TRIM IS ND AND NU. E	LECTRIC STAB TRIM OPERATED APPROX 10 PERCENT OF THE TIME IN ONE DIRECTION. PILOT ADVISED ATC OF THE PORBLEM, CONTACTED F	LIGHT CONTROL, HEADED BACK TO DFW, DECLARED AND EMERGENCY AND MADE AN UNEVENTFUL APPROACH AND LANDING. TROUBLESHOOTING W	AS CARRIED OUT. HORIZONTAL STAB BUSHINGS FOUND STIFF. EXCESSIVE FORCE USED TO MOVE STAB UP OR DOWN MANUALLY WITH HSTA DI	SCONNECTED. RJ SL-55-001 WILL BE APPLIED TO AIRCRAFT.	2	L	7	2 	4F			RT	A21EA   					 
2001032700024	20010327	00024	EA  	2001	3	27	CA001110042      	1	20001109	G	2740		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	FAILED          	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF CREW REPORTED THAT BOTH CHANNELS OF THE STAB TRIM DISCONNECTED. CREW REPORTED THAT THEY WERE UNABLE 	TO RESET EITHER CHANNEL. AFTER LANDING CREW REPORTED THAT THEY COULD RESET BOTH CHANNELS, OUTSTATION MAINTENANCE PERFORM	ED A DOWN LOAD OF THE MDC. INDICATIONS SHOWED POSSIBLY POBLEM WITH PILOTS DISCONNECT SWITCH,  MAINTENANCE WAS UNABLE TO 	DUPLICATE PROBLEM. MAINTENANCE DID A SYSTEM RESET AND FULL BITE TEST OF THE STAB HSTCU, NO FAULTS NOTED. MAINTENANCE PER	FORMED FULL SYSTEM CHECK OF STAB NO DEFECTS NOTED, AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F			RT	A21EA   					 
2000112900335	20001129	00335	GL  	2000	11	29	CA001110045      	2	20001017	G	7323	LN93556X32	BOLT            			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COLLECTIVE	FAILED          	W				K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA								CAE834907			(CAN) DURING CRUISE FLIGHT, PILOT WAS ONLY ABLE TO ACHIEVE 98 PERCENT N2 ON NR 1 ENGINE.  UPON LANDING AT THE MAINTENANC	E FACILITY, AN INSPECTION  FOUND THE NR 1 ENGINE GOVERNOR CABLE WHERE IT ATTACHES TO THE COLLECTIVE FORK HAD BECOME DISE	NGAGED.  REF:  MBB PARTS BOOK FIG 621 ITEM NR 40 CONNECTION FIGURE 438 ITEMS, NR 440 BOLT, NR 60 FORK LEVER, AND NR 110 	ANCHOR NUT.  BOLT NR 440 HAD BACKED OUT OF THE ANCHOR NUT NR 110 AND ALLOWED THE CABLE TO COME FREE OF THE COLLECTIVE FO	RK  NR 60. THE BOLT AND N2 CABLE WERE RE-ASSEMBLED AND FUNCTIONAL CHECK COMPLETED ON THE GOVERNOR/RIGGING ALL SYSTEMS FO	UND SERVICEABLE.  THE AIRCRAFT WAS THEN RETURNED TO SERVICE.  (X)	1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001032700025	20010327	00025	NE  	2001	3	27	CA001122002      	2	20001108	G	7510	69701561	CLAMP           			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 1 ENGINE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) NR 1 ENGINE SHUT DOWN, APPROXIMATELY 12 MINUTES INTO FLT.  DUE TO ENGINE OVERHEAT AND START VALVE OPEN LIGHT ON. F	OUND THERMAL ANTI-ICE DUCT CLAMP FAILED. REPLACED CLAMP, RT 8TH STAGE BLEED DUCT, AND 13TH STAGE BLEED DUCT TO EXPANSION	 BELLOWS. ENGINE RUN CARRIED OUT ALL SYSTEMS CHECK NORMAL AND NO LEAKS FOUND. A/C RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400051	20010314	00051	NM  	2001	3	14	CA001122003      	1	20000920	G	2710		CONTROL UNIT    			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					AILERONS	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) EN ROUTE CREW REPORTED AILERONS WERE STIFF, BEYOND 5 DEGREES INPUT WITH AUTOPILOT SELECTED OFF. AUTOPILOT ON AILER	ONS WERE BETTER. AIRCRAFT TAKEN OUT OF SERVICE FOR TOURBLESHOOTING. AILERON POWER CONTROL UNIT RIGGING CARRIED OUT AS PE	R WORK CARD 51143, ITEM 7. AILERON CABLES CHECKED LT AND RT SIDE AND LT AILERON LUBED. NO FAULTS FOUND.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001032700026	20010327	00026	EA  	2001	3	27	CA001122006      	1	20001101	G	5720	C2W1071	BUSHING         	DHAV        	C2W1104A    	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN1     	52008	NE  					LIFT STRUT	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9010 			A0026					(CAN) DURING ROUTINE INSPECTION THE RT TOP LIFT STRUT BUSHING WAS FOUND TO BE WORN. THIS CONDITION APPEARS TO BE A WEAK 	PART IN DESIGN AS WE ARE CONSTANTLY REPAIRING THE TOP END OF THE LIFT STRUTS. : THE ALUMINIUM LIFT STRUT ENDS ARE FIELD 	REPAIRABLE.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2000112800042	20001128	00042	EA  	2000	11	28	CA001122007      	1	20001101	G	5522	S6129661170	FITTING         		S6109210101 	CARSON	S61   	S61LSKRSKY  	       	EA  	GE    	CT58  	CT581401    	30011	NE  					ATTACH LUG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1491 							(CAN) ON POST-FLIGHT INSPECTION, UPPER LEFT HAND LUG OF TAIL PYLON HINGE FITTING WAS FOUND CRACKED.  HINGE REPLACED WITH	 STEEL PART NR S6120-66117-041 IN ACCORDANCE WITH S61320-23.  (X)					2	G	7	2 	4U	4	U	 	H8EA    	1E3				 
2001031400053	20010314	00053	EU  	2001	3	14	CA001122008      	1	20001103	G	5210	350902001	WINDOW          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COPILOTS DOOR	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) COPILOTS  WINDOW DEPARTED IN-FLIGHT.  SUBMITTER SUSPECTED THAT THE WINDOW HAD A NICK IN IT CAUSING IT TO CRACK AND	 DEPART OUT OF AIRCRAFT.  WINDOW IS INSTALLED ON A RUBBER SEAL THAT ATTACHES TO THE DOOR WINDOW FRAME. THE WINDOW IS A L	ITTLE LARGER THAN THE DOOR WINDOW OPENING. TWO WEEK PRIOR TO THIS INCIDENT THE WINDOW WAS REMOVED AND RE-INSTALLED.  (X)				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001032700027	20010327	00027	NE  	2001	3	27	CA001122010      	2	20001109	G	7261	D9798	RESTRICTOR VALVE			BOEING	727   	72725       	1384006	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					OIL PRESSURE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) ON DESCENT INTO YEG THE NR 1 ENGINE OIL PRESSURE BEGAN FLUCTUATING BETWEEN 0-35 PSI. IMMEDIATELY FOLLOWING THIS IN	DICATION THE LOW OIL PRESSURE BYPASS LIGHT ILLUMINATED. ENGINE WAS SHUT DOWN. TROUBLE SHOOTING REVEALED RESTRICTOR GOING	 TO OIL PRESSURE INDICATION SYSTEM FAILED. ALSO REPLACE OIL PRESSURE RELIEF VALVE. THE ENGINE WAS GROUND RUN AT HIGH POW	ER SETTING FOR 45 MINUTES WITH NO FURTHER INDICATIONS PROBLEMS. THE AIRCRAFT HAS OPERATED FROM YEG TO YWG TO YHM TO YWG 	WITHOUT ANY FUTHER PROBLEMS. THE COMPANY HAS CONSIDERED IT A DEFINITE FIX..		2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2000113000154	20001130	00154	GL  	2000	11	30	CA001122011      	2	20000601	G	7321	78315	SCREW           	BENDIX      	252464429   	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL CONTROL	SHEARED         	W				O	 	 	 	OTHER                   				D	X	J	INFLIGHT SEPARATION       	ENGINE FLAMEOUT           	WARNING INDICATION        	NR	NOT REPORTED   	1			CA						334377					(CAN) THE SCREW HEAD RETAINING THE FUEL CONTROL UNIT RATIO LEVER COVER (FUEL SIDE) SEPARATED IN-FLIGHT ALLOWING FUEL TO 	LEAK INTO THE ENGINE COMPARTMENT UNDER HIGH PRESSURE AND REDUCE THE FUEL FLOW TO THE ENGINE TO THE POINT WHERE CONTINUED	 FLIGHT WAS NOT POSSIBLE. THE HELICOPTER CRASHED AND BURNED WHILE ATTEMPTING AN AUTORATIONAL LANDING (TSB REPORT A00W010	5) RESULTING IN THE DEATH OF THE PILOT.  EXAMINATION OF THE FRACTURED SCREW HEAD AT THE TSB LAB (PROJECT LP 72/00) DETER	MINED THE FRACTURE WAS THE RESULT OF THE HEC.  IT WAS ALSO DETERMINED THE SCREW MATERIAL AND MARKINGS DID NOT MEET THE M	ANUFACTURER''S SPECIFICATIONS PLACING THE SCREW IN THE CATEGORY OF A SUSPECTED UNAPPROVED PART.  (X)	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000112800155	20001128	00155	SO  	2000	11	28	CA001122012      	2	20001108	G	8530	652956	EXHAUST VALVE   	CONT        	654653A4    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  	MCAULY	D3A34	D3A34C401   	GL  	SEAL SURFACE	BURNED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			518  								(CAN) AFTER COMPLETING THE ENGINE CYLINDER DIFFERENTIAL COMPRESSION TEST ON A ROUTINE INSPECTION, DETERMINED NR 3 AND NR	 4 CYLINDERS HAD EXCESSIVE LEAKAGE THROUGH THE EXHAUST VALVES.  THE BAFFLES AT EACH END OF THE EXHAUST MUFFLER WERE FOUN	D BROKEN AWAY FROM THE ORIGINAL LOCATION AND JAMMED NEAR THE OUTLET PORT.  EXCESSIVE EXHAUST BACK PRESSURE COULD HAVE CA	USED THE EXHAUST VALVES TO DETERIORATE PREMATURELY.  (X)			1	H	7	1 	3O	3	O	 	3A24    	E3SO	5	C	P47GL	 
2000112800156	20001128	00156	EU  	2000	11	28	CA001122013      	1	20001112	G	3242	9595601511	BRAKE           			PILATS	PC12  	PC1245      	       	EU  										RT GEAR	FROZEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA				1110 							(CAN) RIGHT BRAKE FROZEN, ON LANDING, RIGHT TIRE DID NOT ROTATE; THUS, TIRE WORE THROUGH AND WENT FLAT.  AIRCRAFT WAS ST	OPPED ON RUNWAY.  MAINTENANCE CALLED. TIRE REMOVED,  GEAR INSPECTED AND NEW WHEEL AND TIRE INSTALLED.  (X)					1	L	7	1 	3T			RT	A78EU   					 
2001031400055	20010314	00055	NE  	2001	3	14	CA001122016      	2	20001108	G	7200		ENGINE          			BOEING	737   	7372M8      	1384483	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB FROM VANCOUVER THE CREW NOTICED NR 2 ENGINE OIL QUANTITY DROP TO ZERO. THEY INITIATED A PRECAUTIONARY	 SHUT DOWN OF THE ENGINE AND RETURNED TO VANCOUVER. MAINTENANCE PERSONNEL IN VANCOUVER FOUND NORMAL OIL QUANTITY IN THE 	ENGINE. THEY CARRIED OUT AN ENGINE RUN TO CHECK OTHER PARAMETERS AND FOUND THEM TO BE NORMAL. NR 2 ENGINE OIL QUANTITY W	AS DEFERRED ON MEL79-1 AND THE AIRCRAFT RELEASED TO SERVICE.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400056	20010314	00056	NM  	2001	3	14	CA001122017      	1	20000925	G	3244	0397692	TIRE            			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				773  							(CAN) DURING THE TAKEOFF ROLL NR 4 MAIN WHEEL TIRE TREAD SEPARATED. THERE WAS NOTHING UNUSUAL NOTED BY THE FLIGHT CREW A	ND THE AIRCRAFT PROCEEDED TO SASKATOON. THE SEPARATED TIRE TREAD WAS DISCOVERED ON THE RUNWAY BY AIRPORT MAINTENANCE CRE	WS AND REPORTED TO CALGARY MAINTENANCE. THE AIRCRAFT LANDED AT SASKATOON WITHOUT INCIDENT AND AN INSPECTION OF THE AIRCR	AFT WAS ACCOMPLISHED AND TIRE CONDITION WAS CONFIRMED. A MAINTENANCE CREW WAS DISPATCHED FROM CALGARY AND ASSESSED THE D	AMAGE AND REPLACED THE MAIN WHEEL ASSY. THE AIRCRAFT WAS FERRIED BACK TO CALGARY FOR REPAIR.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400057	20010314	00057	NM  	2001	3	14	CA001122018      	1	20001107	G	3242		STATOR          	BENDIX      	26010425    	BOEING	737   	737284      	138448R	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					BRAKE ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			405  			B3962					(CAN) DURING THE SERVICE CHECK NR 3 BRAKE TENSION ADJUSTMENT PINS WERE FOUND LOOSE. WHEN CHECKED FURTHER ONE OF THE BRAK	E STATORS HAD BROKEN AND THERE WERE MULTIPLE PIECES FOUND CONTAINED INSIDE THE WHEEL. NR 3 BRAKE WAS REPLACED AND NR 3 M	AIN WHEEL ASSEMBLY DUE TO DAMAGE. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400058	20010314	00058	NM  	2001	3	14	CA001122019      	1	20001103	G	3242	6544566	O-RING          	BENDIX      	26010425    	BOEING	737   	7372A3      	138448A	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					VALVE	DAMAGED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			2274 	4    		BC0650					(CAN) CREW REPORTED A LOSS OF B SYSTEM HYDRAULIC FLUID EN ROUTE FROM ABBOTTSFORD TO CALGARY. UPON ARRIVAL IN CALGARY THE	 NR 1 BRAKE WAS FOUND TO BE LEAKING AT QUICK DISCONNECT FITTING AT THE BRAKE ASSY. WHEN THE FITTING WAS REMOVED THE BACK	 UP O-RING WAS FOUND DAMAGED. A BRAKE O-RING KIT WAS INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001032700029	20010327	00029	CE  	2001	3	27	CA001122020      	1	20000707	G	7603	C2995050101	THROTTLE CABLE  			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	SEIZED          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A NEW THROTTLE CABLE RECEIVED FROM CESSNA WAS INSTALLED ON THE AIRCRAFT BUT SEIZED UP WHEN THE CABLE WAS FLEXED TO	 ALLOW HOOKUP TO THE THROTTLE CABLE. ANOTHER NEW CABLE FROM CESSNA WAS TRIED WITH THE SAME RESULT.A THROTTLE CABLE MADE 	BY MCFARLANE MCC299505-0101 WAS INSTALLED AND RIGGED PROPERLY WITHOUT FAULT.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2000112800160	20001128	00160	CE  	2000	11	28	CA001122022      	1	20001002	G	8011	PS1432	CASTING         	PRESTOLITE  	MZ4222      	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NEAR FRONT BRG	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				356  		A143350					(CAN) CASTING SUPPORTING THE DRIVE GEAR CRACKED. THE DRIVE GEAR STAYED ENGAGED AFTER ENGINE WAS STARTED.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001032700030	20010327	00030	EA  	2001	3	27	CA001122023      	2	20001027	G	7322		SCREW           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					FLOAT BOWL	LOOSE           	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			2185 	31   							(CAN) ENGINE WAS RUNNING ROUGH, OVER TORQUING AND MIXTURE CONTROL WOULD NOT SHUT DOWN ENGINE. THE FLOAT BOWL SCREWS WERE	 FOUND LOOSE AND THE TWO HALVES OF THE CABLES WERE SEPARATED BY ABOUT .040 INCH. THE LOWER FLOAT BOWL NEEDED HELICOILS  	BECAUSE THE THREADS WERE DAMAGED / MISSING AND THEN THE SCREWS HEADS WERE LOCKWIRED TO EACH OTHER UPON REASSEMBLY. SEVER	AL OTHER 172S HAVE HAD THE SAME PROBLEM WITH DIFERENT TSN ON THE CARBS.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001011106119	20010111	06119	CE  	2001	1	11	CA001122024      	1	20001102	G	5510	07326015	FITTING         	CESSNA      	123260026   	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					HORIZONTAL STAB	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7436 								(CAN) ON INSPECTION, NOTICED THAT THE HORIZONTAL STABILIZER WOULD MAKE A NOISE WHEN THE TIP WAS MOVED UP AND DOWN. THE T	AIL WAS TAKEN APART AND THE 10 RIVETS HOLDING THE FRONT FITTING. THE TOP 3 RIVETS ON EACH FITTING WAS SHEARED. THE RIVET	S WERE ALL REPLACED.  (X)				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001032700031	20010327	00031	CE  	2001	3	27	CA001122025      	1	20001107	G	3250	071230916	BELLCRANK       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	TAILWHEEL STEER	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8910 								(CAN) DURING INSPECTION OF TAIL WHEEL STEERING CABLES, WORN BELLCRANKS WERE DISCOVERED AT SPRING ATTACH POINT.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2001032700033	20010327	00033	CE  	2001	3	27	CA001122027      	1	20001102	G	2720	07135295	LINK            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	RUDDER TRIM	STRIPPED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED RUDDER TRIM HARD TO ADJUST. PARTS REMOVED AND FOUND THREADS ON WHEEL SCREW AND LINK ROD STRIPPED. A	 PORTION OF SCREW FOUND BROKEN INSIDE LINK ROD.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2001011106120	20010111	06120	EU  	2001	1	11	CA001122028      	1	20001102	G	5510	350A23002029	PLATE           	SNIAS       		SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8725 			1232					(CAN) AT 8,724.9 AIRFRAME HOURS, WHILE CONDUCTING A 100-HOUR INSPECTION, A CRACK WAS DETECTED ON THE LT UPPER HORIZONTAL	 STABILIZER ATTACHMENT DOUBLER. THIS IS A KNOWN STRESS AREA AND REPLACEMENT PARTS ARE NOW UPGRADED.  EUROCOPTER SERVICE 	LETTER 400-53-82 SHOWS THE UPGRADED PARTS.  UPGRADED PARTS HAVE BEEN INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE.  (X	)			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001032700034	20010327	00034	NM  	2001	3	27	CA001122029      	1	20001114	G	2612	896767	FIRE LOOP       			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					APU	CHAFED          	W				F	 	 	 	ACTIVATE FIRE EXT.      				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) APU FIRE WARNING IN CRUISE, APU FIRE HANDLED & WARNING CEASED, BOTTLE DISCHARGED.  AIRCRAFT CARRIED OUT A NORMAL L	ANDING. MAINTENANCE INSPECTED APU & AREA AND FOUND NO INDICATIONS OF FIRE OR OVERHEAT. THE AIRCRAFT WAS RELEASED UNDER T	HE PROVISIONS OF THE MEL.  NEXT OVERNIGHT MAINTENANCE DISCOVERED DAMAGED WIRING AT THE TAIL PIPE FIRE LOOP. WIRING & LOO	P WERE REPLACED ALONG WITH THE FIRE BOTTLE. THE SYSTEM TESTED SERVICEABLE AND THE AIRCRAFT RELEASED.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001040200118	20010402	00118	EU  	2001	4	2	CA001122030      	1	20000923	G	5753	137202B61	BRACKET         			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LT & RT FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			27932								(CAN) LT FLAP BRACKET FOR FLAP TO SLAT ATTACHMENT 4TH FROM INBOARD END FOUND CRACKED. BRACKET REPLACED WITH MADE REPAIR 	PART. RT FLAP BRACKET FOR FLAP TO SLAT ATTACHMENT 7TH FROM INBOARD END FOUND CRACKED. BRACKET REPLACED WITH MADE REPAIR 	PART.				2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
2001040200119	20010402	00119	EU  	2001	4	2	CA001122031      	1	20000930	G	5753	137202B61	BRACKET         			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LT FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28385								(CAN) DURING SCHEDULED MAINTENANCE INSPECTION ATTACHMENT BRACKET FOR FLAP TO SLAT FOUND BROKEN. BRACKET POSITION LT OUTB	OARD FLAP, SECOND INBOARD FROM OUTBOARD END. BRACKET REPLACED WITH MADE REPAIR PART.					2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
2001040200120	20010402	00120	EU  	2001	4	2	CA001122032      	1	20001003	G	5753	137202B61	BRACKET         			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LT FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			27976								(CAN) LT OUTBOARD FLAP TO SLAT ATTACHMENT BRACKET FOUND CRACKED. BRACKET REPLACED WITH MADE REPAIR PART.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL	 
2001031400059	20010314	00059	SW  	2001	3	14	CA001122033      	1	20000913	G	2913	66948	CLIP            	BELL        	212076011001	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					HYD PUMP	MISSING         	W				O				OTHER                   				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			CA						AV3001058E					(CAN) CIRCLIP AT END OF PUMP, (SOME PARTS FOUND IN PUMP P/S CAVITY) WAS FOUND MISSING, AND ALLOWED THE DRIVE SHAFT TO DI	SENGAGE FROM PUMP AND MOVE INTO THE TRANSMISSION DRIVE QUILL. THE PUMP WAS REMOVED AND SENT FOR TEST AND INSPECTION WHIC	H CONFIRMED SUSPICION.REPORT OF PUMP TEST AND PILOTS INCIDENT REPORT ATTACHED. CIRCLIP AND EXTERNAL P/S REPLACED AS PER 	BHT TB-205-86-70.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001032700035	20010327	00035	SO  	2001	3	27	CA001123002      	1	20001026	G	2730	71056003	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ELEVATOR BUNGEE	BROKEN          	W				O	 	 	 	OTHER                   				O	G		OTHER                     	MULTIPLE FAILURE          		TO	TAKEOFF        	1			CA			648  								(CAN) ON TAKEOFF, PILOT FELT A SNAP ON THE CONTROL WHEEL, THINKING THAT THE TRIM HAD STUCK MOMENTARILY HE FLEW THE AIRCR	AFT TO ITS NEXT DESTINATION WITHOUT ANY PROBLEMS BUT NOTICED NO DOWN PRESSURE ON THE CONTROLS ONCE HE LANDED. ON INVESTI	GATION WE FOUND THE ELEVATOR DOWN SPRING HAD BROKEN AT THE REAR PORTION OF THE SPRING, ABOUT AN INCH FROM THE HOOK END.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001011106123	20010111	06123	CE  	2001	1	11	CA001123003      	1	20001108	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PRE-FLIGHT INSPECTION, THE FLIGHT CREW NOTICED A CRACK IN THE LT WINDSHIELD.  MAINTENANCE ADVISED.  AIRCRAF	T REMOVED FROM SERVICE WINDSHIELD REPLACED.  (X)					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001032700038	20010327	00038	SO  	2001	3	27	CA001123007      	1	20001030	G	5320	4810100	SILL            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					CABIN DOOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAINTENANCE INSPECTION REVEALED DOOR SILL AREA CRACKING UNDER THE FLOOR AND ADJACENT TO THE CABIN DOOR HINGE AREA.	 PARTS AFFECTED OR REPLACED INCLUDE P/N 48101-00 RIB (BULKHEAD) (CRACKING), 45648-00 DOOR SILL (CRACKING). AIRSTAIR HING	E(S) 46396-00/46395-00 AND PIN 81761-70 REPLACED NEW AT THIS TIME. STRUCTURAL REPAIRS C/O AS REQUIRED. AIRCRAFT RETURNED	 TO SERVICE.A/C TTSN 17769.7			1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2001032700039	20010327	00039	SO  	2001	3	27	CA001123008      	1	20001031	G	3230	4204202	ARM             			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) CREW REPORTED DIFFICULT EXTENDING AND RETRACTING LANDING GEAR. GEAR EXTENDED AND LOCKED ON 2ND ATTEMPT AND UNEVENT	FUL LANDING C/O.MAINTENANCE DISCOVERED BROKEN MAIN LANDING GEAR RETRACTION ARM P/N 42042-02. LT PART REPLACED NEW. GEAR 	SWING C/O A/C RELEASED.				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2001032700040	20010327	00040	NM  	2001	3	27	CA001123009      	1	20001116	G	2130	1305026	SELECTOR KNOB   			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					CABIN PRESSURE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THRU 10,000 FEET CABIN ALTITUDE EICAS WARNING. QRH ACTIONED. AIRCRAFT RETURNED TO YYZ WITHOUT INCIDENT. CABIN PRES	SURE SELECTOR REPLACED.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001032700041	20010327	00041	SO  	2001	3	27	CA001123010      	1	20001120	G	5610	7955300	FITTING         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	WINDSCREEN	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2611 								(CAN) WHEN ENDEAVOURING TO REPLACED THE WINDSCREENS, THESE BRACKETS WERE FOUND HEAVILY CORRODED AND HAD TO BE REPLACED.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P9EA	 
2001032700042	20010327	00042		2001	3	27	CA001123011      	4	20001120	G	6113	05503214	BULKHEAD        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8616 								(CAN) DURING ENGINE AND PROP REMOVAL, THE SPINNER BULKHEAD WAS FOUND CRACKED AROUND THE BOLT HOLES.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001040300035	20010403	00035	SW  	2001	4	3	CA001123016      	1	20001110	G	6420	206011724003	VENT            			BELL  	206   	206L        	1181522	SW  										T/R PITCH CHANGE	CLOGGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1031 							(CAN) DURING REPLACEMENT OF BOOT ON TAIL ROTOR PITCH CHANGE MECHANISM, THE VENT HOLE IN TUBE ASSY P/N 206-011-724-003 WA	S FOUND OBSTRUCTED. FUTHER INVESTIGATION REVEALED THAT DRIED GREASE WAS PLUGGING THE HOLE. THE VENT HOLE WAS CLEANED, AN	D THE TUBE RE-ASSEMBLED. THE GREASE USED FOR LUBRICATION OF THE TRUNNION AND HOUSING BEARINGS IS AEROSHELL 22. AFTER LUB	RICATION OF THOSE BEARINGS, THE MANUFACTURER RECOMMENDS WIPING THE AREA WITH A CLEAN CLOTH. THIS OPERATION VERY LIKELY P	ACKED THE GREASE IN THE HOLE, ALLOWING IT TO DRY AND PREVENTING THE NECESSARY VENTING OF THE BOOT AREA. MAINTENANCE PERS	ONNEL HAS BEEN ADVISE TO MAKE SURE  THE VENT HOLE IS CLEARED AFTER EACH LUBRICATION.	1	G	7	1 	3U			 	H2SW    					 
2001032700048	20010327	00048	NM  	2001	3	27	CA001123018      	1	20001017	G	2934	AERO983614	CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					RESERVOIR	CORRODED        	W				O	 	 	 	OTHER                   				J		 	WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) ON LANDING ROLL SPOILER INBOARD HYDRAULIC AND NR 1 ISO VALVE CAUTION LIGHTS ILLUMINATED -- INSPECTED AND FOUND SEV	ERE CORROSION ON ISO VALVE SWITCH CANNON PLUG AND SOCKET. R&R SWITCH AND CANNON PLUG, OPS CHECK GOOD AT THIS TIME. DEFER	RAL INSPECTED AIRCRAFT AND NR 1 RUDDER ISOLATION VALVE. FOUND EVIDENCE OF ARCING AT NR 1 ISOLATION VALVE CONNECTOR AT RE	SERVOIR.RESERVOIR LEVEL SWITCH & CANNON PLUG REPLACED, OPS CHECK CARRIED OUT, AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700049	20010327	00049		2001	3	27	CA001123019      	4	20001024	G	2565	82560034021	COVER           			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					DITCHING DAM	MISSING         	W				O	 	 	 	OTHER                   				D		 	INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) DITCHING DAM COVER DETACHED, DAM SEPARATED INFLT. A/C JUST LEVELLED IN CRUISE, CABIN CREW RPTED LOAD BANGING NOISE	, SPEED REDUCED, 1ST OFFICER INSP&CONFIRMED DAM COVER DETACHED, BUT DAM STILL ATTACHED. PAN DECLARED, INITY ELECTED TO D	IVERT OT NEWQUAY TO AVOID DAMAGE TO PERSON/PROPERTY ON GROUND. HOWEVER DAM DETACHED INFLT SO DECISION MADE TO CONTINUE T	O PLYMOUTH AS PER FLT SCHEDULE. BRYMON ENGINEERS CONFIRMED A/C PRE-MOD 8/1690 FITMENT OF NEOPRENE DIAPHRAGM REQD TO HELP	 PREVENT INADVERTANT DAM DEPLOYMENT BY CABIN PRESSURE: INSP DIAPHRAGM P/N 83510007-101 INST CABIN PRESSURE AIR INFLATED 	BAG SUFFICIENTLY TO DEPLOY DITCHING DAM.N2 BOTTLE HAS BEEN PREV REPL. NEW PARTS FITTED&A/C RETURN TO SERVICE.  CARRY OU	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700050	20010327	00050	NM  	2001	3	27	CA001123020      	1	20001025	G	5270	82420109033	PROXIMITY SWITCH			DHAV  	DHC8  	DHC8*       	       	NM  										EMERGENCY EXIT	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN)   DURING CLIMB OUT FROM ARLANDA, AT APP FL150 WE GOT A FUSELAGE DOOR WARNING. MFD SHOWED THE FWD EMERGENCY EXIT. I	 INFORMED THE PURSER ABOUT THE PROBLEM AND WE HAD 72 PAX ONBOARD SO NO RESEATING WAS POSSIBLE.DURING DESCENT THE WARNING	 DISAPPEARED. NORMAL UNEVENTFUL LANDING CARRIED OUT .  TECHNICIANS LUBRICATED AND ADJUSTED THE PROXIMITY SWITCH TARGET M	ECHANISM AND TESTED IT WITHOUT ANY REMARKS. A/C RETURNED TO SERVICE.			2	H	7	2 	4T			RT	A13NM   					 
2001032700051	20010327	00051	EA  	2001	3	27	CA001123021      	2	20001024	G	7261	305306301	REGULATOR VALVE 			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				B	J	 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN)   DEPARTED COPENHAGEN ON  ATTEMPT TO CARRY OUT A POSITIONING FLIGHT (SK9100), COPY FROM PILOTS (FOR):- SHORTLY AFT	ER TAKEOFF WE HEARD SMOKE WARNING FROM LAVATORY. INSPECTION REVEALED NO SMOKE OR FIRE.AND FLIGHT RETURNED TO COPENHAGEN 	FOR TECHNICAL INVESTIGATION.THE LAVATORY SMOKE DETECTOR IS SENSITIVE TO ENGINE FUMES AND BOTH ENGINES PRIOR TO THIS FLIG	HT WERE PRE-MOD (S/B 35038).			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2001032700052	20010327	00052	NM  	2001	3	27	CA001123023      	1	20001012	G	2611	473082	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8*       	       	NM  										CARGO BAY	FAILED          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) FLT 210 FLYING AT 240 KTS IAS, VMC APPROXIMATELY 10 MINS AFTER TAKEOFF. WE GOT A SMOKE WARNING, ON CAUTION / WARNI	NG PANEL, MASTER WARNING FLASHING, TRIPLE CHIME & FWD FIRE BOTTLE ARM  ;T ON, FWD BAGGAGE EXT SWITCH LT/PUSH BUTTON ON. 	ALL INTERMITENTLY ON SEVERAL TIMES FOR 4/5 MINS PERIOD. REQUESTED RETURN - STARTED DESCENT INFORMED CA, INFORMED PAX, OR	H - CHECKLIST FOLLOWED, DUE TO INTERMITENT WARNING - NOT ABLE TO BOTTLE, SEVERAL MORE WARNINGS DURING APPROACH SVG. NORM	AL LANDING, PASSENGERS DISEMBARKED AT STAND 40, THROUGH L1-PAX DOOR. NEVER ANY SMELL OF SMOKE OR VISUAL SIGN OF SMOKE/FI	RE.	2	H	7	2 	4T			RT	A13NM   					 
2001032700053	20010327	00053	NM  	2001	3	27	CA001123024      	1	20001105	G	3320	BR9120WW	LAMP            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					ROW 5	SHORTED         	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) MAINTENANCE NOTIFIED OF ELECTRICAL SMOKE FROM CABIN OVERHEAD LIGHT AT ROW 5 D/F, BULB WAS REMOVED, AND MEL ISSUED 	FOR OVERHEAD LIGHTING SYSTEM, A/C RETURN TO SERVICE. LAMP WAS REPLACED ON 7 NOV 2000, OPERATIONAL CHECK GOOD, MEL REMOVE	D.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700054	20010327	00054	NM  	2001	3	27	CA001123025      	1	20001026	G	2611	473054	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					CARGO BAY	MALFUNCTIONED   	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			DE	DESCENT        	1			CA			15347	4277 							(CAN) DURING DESCENT INTO PHL, BAGGAGE COMPARTMENT SMOKE DETECTOR LIGHT ILLUMINATED. EMERGENCY DECLARED, FLIGHT LANDED W	ITHOUT INCIDENT. NR 2 SMOKE DETECTOR REPLACED, NR 1 SMOKE DISCONNECTED IN ACCORDANCE WITH MEL 26-08, AIRCRAFT WAS RETURN	ED TO SERVICE. NR 1 SMOKE DETECTOR REPLACED ON 27TH OCTOBER 2000.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400060	20010314	00060	NM  	2001	3	14	CA001123027      	1	20001025	G	3240		BRAKE ASSY      			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	RT NACELLE	OVERSERVICED    	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE FOLLOWING WAS REPORTED TO US FROM ALLEGANY AIRLINES:  FLIGHT 3968 UPON LANDING IN MHT, NEW HAMPSHIRE, NORMAL B	RAKES LOST, FLUID LEAK OUT OF RIGHT NACELLE, CONTENTS LOW ON NR 1 SYSTEM (APPROXIMATELY 0.7 QTS). FOUND OVERSPILL CAN RI	GHT WHEEL WELL FULL. ENGINEERS EMPTIED AND SERVICED NR 1 & 2 SYSTEMS, CLEANED WHEEL WELL, RAN AND TAXIED AIRCRAFT, NO LE	AKS NOTED, BRAKES STOPPED NORMALLY. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001031400061	20010314	00061	NM  	2001	3	14	CA001123028      	1	20001109	G	5270		WARNING SYSTEM  	DHAV        	DHC8402     	DHAV  	DHC8  	DHC8*       	       	NM  										SERVICE DOOR	FALSE INDICATION	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA						4025					(CAN) PILOTS REPORT:  SERVICE DOOR WARNING CAME ON WHEN REACHING FL230 INTERMITTENT BETWEEN FL180-060,  STEADY ON BELOW 	FL060.MAINTENANCE ACTION: DOOR INSPECTION CARRIED OUT AND FOUND PULL FORCE LESS THAN 10 KG,  ACTION TAKEN. PULL TEST CAR	RIED OUT AGAIN,  POST DOOR RE-RIGGED IAW AMM 52-22-00 AND PULL TEST PASSED,  AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T			RT	A13NM   					 
2001031400062	20010314	00062	NM  	2001	3	14	CA001123029      	1	20001103	G	6100		PROPELLER       			DHAV  	DHC8  	DHC8*       	       	NM  										LT AND RT	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) PILOTS FLIGHT OCCURRENCE REPORT: DURING TAKEOFF ROLL, WE DIDN'T GET A/F ARMED, ABORTED TAKEOFF AND RETURNED TO THE	 GATE. MAINTENANCE REPORT: MAINTENANCE LOG ENTRY FOR RECTIFICATION OF DEFECT AS FOLLOWS: REF LOG SEQUENCE NO L072 PROPEL	LERS; A/F NOT ARMED UPON DEPARTURE<<CDS CHECKED, FAULT CODE 64 LT AND RT FOUND, FAULT CLEARED AND A/F TEST PERFORMED WIT	HOUT ANY FAULTS. A/C RETURNED TO SERVICE. NO FURTHER PROBLEMS.			2	H	7	2 	4T			RT	A13NM   					 
2001031400063	20010314	00063	NM  	2001	3	14	CA001123031      	1	20001030	G	2730		CONTROL UNIT    			DHAV  	DHC8  	DHC8*       	       	NM  										ELEVATOR	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) (COPY OF PILOT IN COMMAND FLIGHT OCCURRENCE REPORT:  JUST AFTER DEPARTURE, DURING CLIMB WE HAD A ELEVATOR ASYMMETR	Y FAULT AND WERE ADVISED TO RETURN. A/C RETURNED TO SERVICE. SUPPLEMENTARY CLOSING REPORT: MAINTENANCE REPORT: ON GROUND	 ELEVATOR SPLIT (1 DEGREE) READING, FAULT WAS RESET ON COMPUTER AND ENGINEERS CARRIED OUT A FULL ELEVATOR RIGGING CHECK,	 INCLUDING ELEVATOR CABLE TENSION CHECKS AND ASYMMETRY CHECK OF SYSTEM IAW AMM TABLE CARD 27-31-750-801 - NO FURTHER FAU	LTS REPORTS. A/C RETURNED TO SERVICE.		2	H	7	2 	4T			RT	A13NM   					 
2001011105924	20010111	05924	NM  	2001	1	11	CA001123032      	1	20001030	G	5610	83040010006	WINDSHIELD WIPER	DHAV        	DHC8402     	DHAV  	DHC8  	DHC8*       	       	NM  										WINDSCREEN	STUCK           	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						4021					(CAN) (COPY OF PILOT IN COMMAND FLIGHT OCCURRENCE REPORT: JUST AFTER DEPARTURE, DURING CLIMB THE RT WINDSHIELD WIPER MOV	ED AWAY FROM THE PARK POSITION AND WAS STUCK AT APPROXIMATELY 30CM ABOVE THE GLASS. TECH DEPARTMENT TOLD THEM TO RETURN 	TO CPH. WHERE THE PROBLEM WAS SOLVED AND AFTERWARDS AIRCRAFT RETURNED TO SERVICE, NO FURTHER PROBLEMS, A/C RETURNED TO S	ERVICE.			2	H	7	2 	4T			RT	A13NM   					 
2001031400064	20010314	00064	NM  	2001	3	14	CA001123033      	1	20001027	G	3260	464503	SENSOR          			DHAV  	DHC8  	DHC8*       	       	NM  										RT MLG DOOR	OUT OF ADJ      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) (COPY OF PILOT IN COMMAND FLIGHT OCCURRENCE REPORT: JUST AFTER DEPARTURE,  WHEN GEAR WAS SELECTED UP,  RT GEAR DOO	R UNSAFE LIGHT (YELLOW) FLICKERED ON SEVERAL TIMES. THE GEAR WAS RE CYCLED WITHOUT SUCCESS. THE FLIGHT RETURNED FOR LAND	ING AT CPH. AFTER GEAR DOWN SELECTED BEFORE LANDING, THE GEAR DOOR UNSAFE LIGHT REMAINED ON RT REAR DOOR SENSOR GAP WAS 	MEASURED AT 0.047.MAINTENANCE RE-RIGGED GAP TO 0.037  IAW INSTRUCTION LETTER RIL-84-32-001 ISSUED BY DEHAVILLAND ISE AND	 NO FURTHER PROBLEMS. GEAR OPERATIONAL CHECKS CARRIED OUT AND INDICATIONS ARE NORMAL, A/C RETURNED TO SERVICE.		2	H	7	2 	4T			RT	A13NM   					 
2001031400065	20010314	00065	NM  	2001	3	14	CA001123034      	1	20001026	G	3260	464503	SENSOR          			DHAV  	DHC8  	DHC8*       	       	NM  										RT MLG DOOR	OUT OF ADJ      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) (COPY OF PILOT IN COMMAND FLIGHT OCCURRENCE REPORT: JUST AFTER DEPARTURE,   WHEN GEAR WAS SELECTED UP,   RT GEAR  	DOOR UNSAFE LIGHT (YELLOW) FLICKERED ON SEVERAL TIMES. THE GEAR WAS RECYCLED WITHOUT SUCCESS. THE FLIGHT RETURNED FOR LA	NDING AT CPH. AFTER GEAR  DOWN SELECTED BEFORE LANDING, THE GEAR DOOR UNSAFE LIGHT REMAINED ON. RT REAR DOOR SENSOR GAP 	WAS MEASURED AS OUT OF TOLERANCE. MAINTENANCE RE-RIGGED GAP AND NO FURTHER PROBLEMS. GEAR OPERATIONAL CHECKS CARRIED OUT	 AND INDICATIONS ARE NORMAL, A/CA RETURNED TO SERVICE.		2	H	7	2 	4T			RT	A13NM   					 
2001031400066	20010314	00066	NM  	2001	3	14	CA001123035      	1	20001023	G	2730	35993001010	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  										ELEVATOR CONTROL	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE AT FL120, A/C IN CLEAN CONFIGURATION. MASTER CAUTION LIGHT FOR ELEVATOR FEEL CAME ON- ILLUMINATED. A	BNORMAL  CHECKLIST QRH PERFORMED, MAINTENANCE REMOVED ELEVATOR FEEL ACTUATOR IAW AMM AND REPLACED IT WITH NEW ITEM, OPER	ATIONAL CHECKS CARRIED OUT AND A/C RETURNED TO SERVICE.				2	H	7	2 	4T			RT	A13NM   					 
2001031400067	20010314	00067	NM  	2001	3	14	CA001128002      	1	20001014	G	2760	DH10201153CSI	WARNING LIGHT   			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					COCKPIT	ILLUMINATED     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) NR 2 SPU AUXILIARY POWER CAUTION LIGHT ILLUMINATED. PILOT REPORTED CAUTION LIGHT CYCLED ON & OFF FOR 3 MINS. PILOT	 REPORTED THERE WAS NO DRILL IN THE EMERGENCY CHECK LIST (DEHAVILLAND QRH PSM 1-83-1B ITEM 12.8 IDENTIFIES PROCEDURE FOR	 THIS EVENT). LT REMAINED ON FOR REMAINDER OF FLIGHT. LT. EXTINGUISHED ON LANDING. AIRCRAFT DEPARTED GLASGOW FOR BRISTOL	, IN THE CRUISE LT. ILLUMINATED AGAIN. NR 2 AUXILIARY POWER CONTROLLER REPLACED. NOW SATISFACTORY, AIRCRAFT RETURNED TO 	SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700055	20010327	00055	NM  	2001	3	27	CA001128003      	1	20001014	G	7997		WIRE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120       	 	NE  					OIL PRESSURE SYS	CHAFED          	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN)    THE CREW NOTICED THE NR 2 ENGINE OIL PRESSURE ''LOW'' - (NO SPECIFIC VALVE IS KNOWN OR WHETHER IT WAS FLUCTUATI	NG OR STEADY). THE CREW THEN SHUT DOWN FOR THIS PROBLEM WITHOUT THE PRESENCE OF A WARNING LIGHT. THE DEFECT WAS TRACED T	O CHAFED WIRING IN THE LOOM BETWEEN THE ENGINE OIL PRESSURE TRANSMITTER  AND THE NR 2 ENGINE DISCONNECT . 4 WIRES WERE R	EPLACED. THERE WAS NO PROBLEM WITH THE ENGINE OIL PRESSURE SYSTEM. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400068	20010314	00068	NM  	2001	3	14	CA001128004      	1	20001019	G	5220	CMQ1546	VALVE           			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					EXIT SEAL	SEIZED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FORWARD EMERGENCY EXIT SEAL FAILED TO DEFLATE, EXIT UNABLE TO OPEN. LOTS OF WATER FOUND IN EXIT DOOR SHELL, SEAL I	NFLATION VALVE REPLACED AND LUBRICATED. OLD VALVE SHOWED NO SIGNS OF LUBRICATION. OPERATOR INFORMED OF LUBRICATION TASKS	 AT PER ISAR 97-09 (DEHAVILLAND).				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700056	20010327	00056	NE  	2001	3	27	CA001128005      	3	20001022	G	6114	7826691	BOLT            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14RF	14RF9       	NE  	PROPELLER	SHEARED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7030 	7030 							(CAN)   WHILE APPLYING TORQUE TO THE PROP MTG BOLT NUTS, AFTER REPLACEMENT OF THIS PROPELLER ASSEMBLY, ONE OF THE BOLTS 	SHEARED OFF.NORMAL TORQUE WAS BEING APPLIED AS PER THE AMM. THE TORQUE WRENCH WAS SENT OUT FOR CALIBRATION TEST, NO PROB	LEMS WERE FOUND. PROP HUB & ALL MTG BOLTS REPLACED, RETURNED TO HAMILTON STANDARD. NEW PROP & MTG BOLTS FITTED. A/C RETU	RNED TO SERVICE, POST GROUND RUNS AND ALL CHECKS CARRIED OUT SATISFACTORY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P11NE	 
2001031400069	20010314	00069	WP  	2001	3	14	CA001128009      	2	20001101	G	7321	30768008	FUEL CONTROL    			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					LT ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			8700 								(CAN) RT ENGINE UNCONTROLLED ACCELERATION AFTER 10 MINS AT CRUISE ALT 39,000 DESCENDED DOWN TO 21,000 ENGINE OK HAD CONT	ROL.CHANGED (1) FCU, P/N 3076800-8 S/N ON A3538PT/OFF A 4778T(2) PT2 SENSOR P/N 3070816-4 (3) ENGINE COMPUTER P/N 949572	-8 S/N  ON 94-576/OFF 15-415 (4) NZ SENSOR P/N 307022-3. LT ENGINE GROUND CHECKED OK TEST FLIGHT CARRIED OUT TO 395 NO P	ROBLEMS. ENGINE PERFORMED OK NOTE: ENGINES ARE LOANERS FROM BIZJET (918-832-7733).			2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2001031400072	20010314	00072	EU  	2001	3	14	CA001128021      	1	20001002	G	2900	11745406	STRUCTURE       		11745020V002	BOLKMS	117   	BK117A1     	5626010	EU  										HYD BAY	CORRODED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			6375 			050245					(CAN) DISASSEMBLED FOR REPAIR OF HYDRAULIC LEAKAGE. CORROSION FOUND BEYOND ALLOWABLE LIMITS.  THIS HYDRAULIC UNIT IS ON 	CONDITION NO OVERHAUL LIFE.  THIS UNIT RECEIVED FROM THE USA.  (X)					1	G	7	2 	3U			 	H13EU   					 
2001031400073	20010314	00073	EA  	2001	3	14	CA001129002      	2	20001108	G	7322	1060301	CARBURETOR      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			90   								(CAN) ENGINE MISSED WITH THROTTLE ROLLED ON.  REMOVED SENT FOR REPAIR AT PRECISION.  (X)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2001031400074	20010314	00074	SW  	2001	3	14	CA001129003      	1	20001108	G	7930	306000018	TRANSMITTER     			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					PRESS INDICTOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) HIGH PRESSURE READING/INDICATION. REPLACED PART.  (X)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2001031400075	20010314	00075	CE  	2001	3	14	CA001129004      	1	20001101	G	7721	LW12427	CYLINDER        			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1871 								(CAN) THE CYLINDER ASSEMBLY CRACKED AT THE CYLINDER HEAD FLANGE.  THE CRACK EXTENDED HALF WAY THROUGH THE CIRCUMFERENCE 	OF THE CYLINDER.  (X)					1	L	7	1 	3O	3	O	 	A1CE    	E286				 
2001032700064	20010327	00064	GL  	2001	3	27	CA001129008      	1	20001101	G	3340	GE5300031	LENS            		GE53600031  	BOMBDR	BD700 	BD7001A10   	1390006	GL  										LT WING	MISSING         	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			TX	TAXI/GRND HDL  	1			CA			116  	116  		1057					(CAN) ON RETURN FROM FLIGHT NR 1 AFTER COMPLETION LT LANDING TAXI LIGHT LENS WAS MISSING. CREW HAD ENTER LOG SNAG. PUT L	T LANDING LIGHT ON AT 8000 C/B TRIPPED COULD NOT RESET ( TAXI LT. ON EMS CDU)					2	L	7	2 	4F			RT	T00003NY					 
2001032700065	20010327	00065	NE  	2001	3	27	CA001129009      	2	20001009	G	7250		BLADE           			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					STAGE 1	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				D	E	 	INFLIGHT SEPARATION       	VIBRATION/BUFFET          		DE	DESCENT        	1			CA			22   								(CAN) DURING A FLIGHT TEST OF THIS AIRCRAFT AND DURING DESCENT THE ENGINE VIBRTION (NH) HAS GONE ABOVE LIMIT. ENGINE HAS	 BEEN REMOVED SENT TO RRC FOR BORESCOPIC INSPECTION. BORESCOPE INSPECTION REVEALED ONE OFF STAGE 1 BLADE BROKEN OFF AT A	PPROXIMATELY MID SPAN. RRC REPORTED FINDINGS TO THE OEM WHO THEN REQUESTED THE ENGINE TO BE SENT BACK TO GERMANY FOR INV	ESTIGATION.			2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2001031400076	20010314	00076	CE  	2001	3	14	CA001129010      	1	20001101	G	7721	LW12427	CYLINDER        			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1871 	425  							(CAN) THE CYLINDER ASSEMBLY CRACKED AT THE CYLINDER HEAD FLANGE.  THE CRACK EXTENDED HALF WAY THROUGH THE CIRCUMFERENCE 	OF THE CYLINDER.  (X)					1	L	7	1 	3O	3	O	 	A1CE    	E286				 
2001032700067	20010327	00067	EA  	2001	3	27	CA001129012      	1	20001110	G	2612	24410457	FIRE DETECTOR   			CNDAIR	CL600 	CL6002B19   	       	EA  										RT ENGINE	CHAFED          	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, THE RIGHT ENGINE FIRE WARNING LIGHT ILLUMINATED. THE THROTTLE WAS RETARDED AND THE LIGHT WENT OU	T.THE AIRCRAFT RETURNED TO HOME BASE, WITHOUT INCIDENT. FOUND A FIRE LOOP CHAFED THROUGH THE OUTER SHEATH.					2	L	7	2 	4F			RT	A21EA   					 
2001032700068	20010327	00068	EA  	2001	3	27	CA001129013      	1	20001110	G	2612		EXTINGUISHER    			CNDAIR	CL600 	CL6002B19   	       	EA  										CARGO BAY	FAILED          	W				F	B	A	 	ACTIVATE FIRE EXT.      	EMER. DESCENT           	UNSCHED LANDING         		N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) CARGO SMOKE WARNING DURING CRUISE. QRH ACTIONED, FIRE EXTINGUISHER SYSTEM ACTIONED AND AIRCRFT DIVERTED.MAINTENANC	E ACTION: NO EVIDENCE FOUND OF SMOKE OR FIRE, FIRE BOTTLES WERE REPLACED.					2	L	7	2 	4F			RT	A21EA   					 
2001032700069	20010327	00069	EA  	2001	3	27	CA001129014      	1	20001110	G	2613		ELEMENT         			CNDAIR	CL600 	CL6002B19   	       	EA  										14 STAGE DUCT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB AT FL160 RT 14 STAGE DUCT MESSAGE WITH AURAL WARNING WITH ANTI ICE ON. CREW CARRIED OUT QRH PROCEDURE	 AND TRIED UNSUCCESSFULLY TO RESET THE SYSTEM, MESSAGE CLEARED WHEN RT THRUST LEVER RETARDED. MAINTENANCE ACTION: FOUND 	14 STAGE DUCT ELEMENT TOUCHING THE DUCTING. MOVEMENT OF THE ELEMENT AND TEST OF THE SYSTEM CONCLUDED THIS PROBLEM.				2	L	7	2 	4F			RT	A21EA   					 
2001032700070	20010327	00070	EA  	2001	3	27	CA001129015      	1	20001112	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										RIGHT	FAILED          	W				O	 	 	 	OTHER                   				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA						1004A					(CAN) ON APPROACH, CREW SELECTED FLAP 8 DEGREES AND FLAP FAIL. CAUTION MESSAGE SHOWN ON EICAS.A/C DIVERTED DUE TO WEATHE	R AND 0 FLAP LANDING PERFORMED UNEVENTFUL.MAINTENANCE REPLACED RT BPSU AS PER AMM AND A/C RETURNED INTO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032700071	20010327	00071	EA  	2001	3	27	CA001129016      	1	20001116	G	2612	365000183	FIRE DETECTOR   			CNDAIR	CL600 	CL6002B19   	       	EA  										CARGO BAY	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) CREW GOT INTERMITTENT CARGO SMOKE INDICATIONS. DECISION WAS MADE TO DISCHARGE FIRE EXTINGUISHERS. UPON ARRIVAL, IT	 WAS DISCOVERED THERE HAD BEEN NO FIRE. AIRCRAFT OPERATED ON MEL, UNTIL FIRE EXTINGUISHERS COULD BE REPLACED. NO OTHER M	AINTENANCE PERFORMED PRIOR TO RETURN TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001032700072	20010327	00072	EA  	2001	3	27	CA001129017      	1	20001116	G	2910	601R7528661	TUBE            			CNDAIR	CL600 	CL6002B19   	       	EA  										HYD SYSTEM	CHAFED          	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) CREW RECEIVED HYD 1 LOW PRESSURE INDICATION, CHECKED QUANTITY AND FOUND IT TO BE ZERO. CREW FOLLOWED QRH PROCEDURE	S AND DIVERTED. ON SITE MECHANIC VERIFIED FLUID COVERING AFT EQUIPMENT BAY. CHAFE FOUND TO BE IN TUBE ASSY 601R7528661. 	REPAIR SECTION PERMASWAGED IN PLACE AND TUBE FAIR LEAD REPLACED. EDP NR 1 REPLACED.				2	L	7	2 	4F			RT	A21EA   					 
2001032700073	20010327	00073	EA  	2001	3	27	CA001129018      	1	20001118	G	2613	356024310	ELEMENT         			CNDAIR	CL600 	CL6002B19   	       	EA  										14TH STAG DUCT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) A LEFT 14TH DUCT WARNING INDICATION WITH THE BLEED AIR DUCT AURAL WARNING WAS OBSERVED TRANSIENTLY AT FL210, THIS 	THEN CLEARED AND REAPPEARED AT FL290 AND STAYED ON. LEFT HAND ENGINE WAS SHUTDOWN AND AIRCRAFT LANDED UNEVENTFULLY. THE 	LEFT 14TH STAGE HEAT SENSING ELEMENT REPLACED.				2	L	7	2 	4F			RT	A21EA   					 
2001032700074	20010327	00074		2001	3	27	CA001129019      	4	20001118	G	3418	45150340	SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE CREW REPORTED A STALL FAIL CAUTION MESSAGE TWICE DURING CRUISE. THE RIGHT ANGLE OF ATTACK WAS REPLACED BY THE 	MAINTENANCE.					2	L	7	2 	4F			RT	A21EA   					 
2001032700075	20010327	00075	EA  	2001	3	27	CA001129020      	1	20001118	G	3260	864202	SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, THE AIRCRAFT HAD A GEAR DISAGREE. NO EMERGENCY DECLARED.MAINTENANCE ADJUSTED THE NOSE GEAR CENTERI	NG PROXIMITY SENSOR.					2	L	7	2 	4F			RT	A21EA   					 
2001032700076	20010327	00076	EA  	2001	3	27	CA001129021      	1	20001115	G	3260	864202	SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  										NLG	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DIROMG TAKEOFF, THE AIRCRAFT HAD A GAR DISAGREE. NO EMERGENCY DECLARED. MAINTENANCE ADJUSTED THE NOSE GEAR CENTERI	NG PROXIMITY SENSOR.					2	L	7	2 	4F			RT	A21EA   					 
2001031400077	20010314	00077		2001	3	14	CA001129022      	4	20001119	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										STALL WARNING	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE STALL FAIL MESSAGE APPEARED IN CRUISE.THE MAINTENANCE DID A RESET OF THE STALL COMPUTER.						2	L	7	2 	4F			RT	A21EA   					 
2001031400078	20010314	00078	EA  	2001	3	14	CA001129023      	1	20001119	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) THE FLAP FAIL MESSAGE APPEARED AFTER LANDING (FLAP INOP AT 27 DEGREE).THE FECU WAS RESETTED AND THE AIRCRAFT WAS R	ETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032700077	20010327	00077	EA  	2001	3	27	CA001129024      	1	20001119	G	7830		FLEX COUPLING   			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					THRUST REVERSER	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) AT CRUISE ALTITUDE OF 23,000, THE LT REV UNLOCKED CAUTION MESSAGE APPEARED WITH THE REV ICON ON THE N1 GAUGE AND T	HE T/R REV EMERGENCY STOW LIGHT ILLUMINATED. EMERGENCY DECLARED. THE MAINTENANCE REPLACED THE THRUST REVERSER / PDU FLEX	SHAFT LOCK OUT UNIT. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400079	20010314	00079	EA  	2001	3	14	CA001129026      	1	20001113	G	5753		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAPS FAIL ON APPROACH TO OTTAWA. INTERROGATED FECU, FOUND FLAPS JAM MESSAGE. NR 5 CABLE LEFT AND RIGHT BENT. CHAN	GED NR 5 CABLE, CHECKED FLAP TORQUE, NO FAULT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400081	20010314	00081	EA  	2001	3	14	CA001129032      	1	20001110	G	2750		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON APPROACH TO OTTAWA, FLAP FAIL MESSAGE ON ENGINE INDICATING AND CREW ALERT SYSTEM, WHEN FLAPS SELECTED TO 8 DEGR	EES. FLAPS INSPECTED, SYSTEM RESET AND OPERATION CHECKED NORMAL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400082	20010314	00082	NM  	2001	3	14	CA001129033      	1	20001102	G	2422	MPN7077604	INVERTER        			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					AC SYSTEM	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) CREW REPORT OF BURNING SMELL/SMOKE IN COCKPIT, STANDBY POWER INVERTER MESSAGE CAME ON ENGINE INDICATING AND CREW A	LERT SYSTEM.CIRCUIT BREAKER PULLED FOR STANDBY INVERTER AND BEGAN SMOKE EVACUATION PROCEDURE. WHEN SWITCHES TO NORMAL, S	MELL RETURNED. AIRCRAFT DIVERTED, STATIC INVERTER CHANGED AND SYSTEM CHECKED.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001032700082	20010327	00082	EA  	2001	3	27	CA001129036      	1	20001102	G	7603	160	PIN             			CNDAIR	CL604 	CL604       	       	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2093 								(CAN) DURING DISASSEMBLY OF THROTTLE QUADRANT TO COMPLY WITH BOMBARDIER SB 604-76-001/RATHER FIGEAL SB FE210-76-01 IT WA	S FOUND THAT PIN 160 HAD MIGRATED OUT OF LATCH ASSEMBLY. THIS PIN IS A PRESS FIT AND WE FOUND IT COULD BE REMOVED BY HAN	D. IF THIS PIN IS REMOVED OR FALLS OUT OF THE LATCH ASSEMBLY THE THROTTLE LEVER CAN JAM COMING OUT OF REVERSE THRUST.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001031400084	20010314	00084	SW  	2001	3	14	CA001130002      	1	20001102	G	6310		ENGINE          			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	NACELLE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2269 							(CAN) DURING RUNUP AND POWER CHECK,  ENGINE TORQUE NOTED TO BE 4 PERCENT LOWER THAN REQUIRED BY POWER CHART. ENGINE FUEL	 SYSTEM, BLEED AIR, AND RIGGING INSPECTED. COMPRESSOR DISCHARGE PRESSURE MEASURED TO BE 120 PSI. NORMAL PRESSURE IS 130 	- 135 PSI. ENGINE REMOVED AND SENT TO OVERHAUL/REPAIR FACILITY  HONEYWELL ALLIED SIGNAL (OEM).				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001031400085	20010314	00085	SW  	2001	3	14	CA001130003      	1	20001103	G	6320	212040001127	TRANSMISSION    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			8491 	70   							(CAN) APPROXIMATELY 1.3 HR INTO FLT MAIN TRANSMISSION WARNING LIGHT ILLUMINATED. A/C WAS APPROXIMATELY. 3 MINS AWAY FROM	 AN ON ROUTE AIRPORT; THE PILOT ELECTED TO LAND AT AIRPORT & HAVE MAINTENANCE ENGINEER INVESTIGATE PROBLEM. AME PULLED M	AGNETIC CHIP DETECTOR, TRANSMISSION INTERNAL & EXTERNAL OIL FILTERS. THERE WAS A HEAVY ACCUMULATION OF METAL PARTICLES O	N CHIP DETECTOR AS WELL AS PRESENCE OF METAL ACCUMULATION IN BOTH OF FILTERS. THIS METAL APPEARS TO BE THAT OF A BEARING	. A/C HAS BEEN REMOVED FROM SERVICE &  REPLACED TRANSMISSION WILL BE INSTALLED D. MAIN ROTOR MAST WILL BE INSP & REPLACE	D OR REPLACED AS DEEMED NECESSARY BY OUR OVERHAUL FACILITIES.	1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001032700083	20010327	00083		2001	3	27	CA001201002      	4	20001029	G	2210		SWITCH          			AIRBUS	310   	A310304     	       	EU  										AUTOPILOT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AIRCRAFT HAD 2 AIR TURNBACKS DUE TO NR 2 PITCH TRIM LEVER DISENGAGING DURING CLIMB. THE NR 1 PITCH TRIM SYSTEM WAS	 ON MEL, AT THIS TIME. AFTER THE FIRST TURNBACK, THE NR 2 FLIGHT AUGMENTATION COMPUTER WAS REPLACED.  THE NR 2 FAC TESTE	D SERVICEABLE. NR 1 SYSTEM REMAINED ON MEL. AIRCRAFT DEPARTED, DURING CLIMB NR 2 PITCH TRIM DISCONNECTED WITH ANOTHER NR	 2 FAC FAULT. AIRCRAFT RETURNED TO BASE. THE TORQUE LIMIT SWITCH WAS REPLACED AS PER AMM 22-13-24 PAGE 401, FOR THE NR 1	 SYSTEM. THE NR 2 FAC REPLACED AS PER AMM 22-26-34. OFF PART NUMBERS 2-2221-9-0001.		2	L	7	2 	4F			RT	A35EU   					 
2001032700084	20010327	00084	EU  	2001	3	27	CA001201003      	1	20001031	G	2780		CONTROL UNIT    			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					SLATS	FAILED          	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH, FLAPS 1 SELECTED AT 215 KNOTS, ECAM INDICATED SLAT LOCK. DECLARED AN EMERGENCY, LANDED WITH SLATS RET	RACTED. MAINTENANCE TESTED BOTH SFCC,S NR 1 AND NR 2, TESTED OK. RESET WING TIP BRAKES, SYSTEM FUNCTION CHECKED SERVICEA	BLE.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001031400087	20010314	00087	NM  	2001	3	14	CA001201005      	1	20001112	G	2841	39302601837	INDICATOR       			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUEL QTY	INACCURATE      	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA			68854	10150							(CAN) LOG SEQUENCE 0154872. APPROXIMATELY 20 MINUTES FROM LANDING  FUEL QUANTITY INDICATORS SHOWED 3000 POUND IMBALANCE.	 SUSPECTED A FUEL LEAK AND DECLARED AN EMERGENCY TO LAND. STOPPED ON RUNWAY AND CONFIRMED NO LEAK. MAINTENANCE FOUND NR 	1 COCKPIT INDICATOR READING 7500 LBS AND NR 2 READING 4000 LBS, WING INDICATOR READINGS NR 1 4200 LBS. ENGINES INSPECTED	 FOR FUEL LEAKS, CHECKED OK. REFUELED USING DRIP STICKS. NR 1 FUEL QUANTITY INDICATOR REPLACED.			2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001031400088	20010314	00088	NE  	2001	3	14	CA001201006      	2	20001113	G	7200		ENGINE          			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 1	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			CA			45647								(CAN) A/C 723, NOV 13/2000, FLT 7012, YFC, LOG SEQUENCE 0298768. ON LANDING YFC, WITH REVERSE THRUST SELECTED,  A BANG W	AS FELT.  FLIGHT CREW THOUGHT IT WAS A TIRE. NOTICED NR 1 ENGINE EPR AND OTHER PARAMETERS DECREASING, SHUTDOWN NR 1 ENGI	NE. INSPECTION OF ENGINE FOUND TURBINE DAMAGE. REPLACED NR 1 ENGINE AS PER WORK CARD 1125-1.REPLACED NR 1 THRUST REVERSE	R AS PER WORK CARD 1192-1. OFF CANADIAN ENGINE PART NUMBER, 7-7200-9-0007, SERIAL 9396, ON SERIAL 9399. OFF CANADIAN REV	ERSER PART NUMBER 7-7831-9-0037, SERIAL 1041, ON SERIAL  1034.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400089	20010314	00089	NM  	2001	3	14	CA001201007      	1	20001116	G	3260	8344	SENSOR          			BOEING	767   	767375      	       	NM  										MLG	DIRTY           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FLIGHT RETURNED TO FCO, DUE LANDING GEAR DOOR CAUTION LIGHT AND STATUS MESSAGE LG MONITOR. GEAR CYCLED IN FLIGHT, 	BUT SNAG STILL REMAINED. LANDING WEIGHT WAS 380,000 LBS. BITE FUNCTION OF PSEU INDICATED TARGETS S234, S235 AND S257, WE	RE THE PROBLEM. SENSORS CLEANED, BITE FUNCTION COMPLETED ON PSEU OK, NOSE GEAR DOORS CYCLED, LIGHTS FUNCTIONED SERVICEAB	LE. OVERWEIGHT LANDING INSPECTION COMPLETED AS PER FLYAWAY MANUAL SECTION 02-01.01. NO FAULTS INDICATED.			2	L	7	2 	4F			RT	A1NM    					 
2001031400090	20010314	00090	NM  	2001	3	14	CA001201009      	1	20001123	G	2701		BEARING         			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					CONTROL COLUMN	BINDING         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED THAT THE AILERON SYSTEM HAD BECOME PROGRESSIVELY STIFFER DURING THEIR FLIGHT.  MAINTENANCE IN	SPECTED THE AIRCRAFT, CLEANED AND LUBRICATED PULLEYS AND BEARINGS IAW THE MM THE AIRCRAFT WAS RELEASE FOR A FERRY FLT.  	MAINTENANCE FOUND BEARING BINDING IN THE CAPTAINS CONTROL COLUMN. COLUMN REMOVED AND DISASSEMBLED, REMOVED AND REPLACED 	BEARINGS, SYSTEM REINSTALLED AND CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001031400091	20010314	00091	NM  	2001	3	14	CA001201010      	1	20001109	G	2910	BACV10BU1	CHECK VALVE     			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17      	52049	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN)   NR 2 ''A'' SYSTEM HYDRAULIC LOW PRESSURE LIGHT ILLUMINATED WHEN FLAPS SELECTED. DECLARED AN EMERGENCY, LANDED WI	THOUT FURTHER INCIDENT. AIRCRAFT TOWED FROM RUNWAY.  FOUND ''A'' SYSTEM HYDRAULIC TANK PRESSURE LEAKING FROM SERVICING P	ORT.  CHECK VALVE CLEANED AND SERVICING CAP SECURED. TANK TOPPED UP 5 LITRES AND PRESSURIZED. AIRCRAFT CHECKED SERVICEAB	LE.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001031400092	20010314	00092	NM  	2001	3	14	CA001201013      	1	20001025	G	2424	915F2124	GCU             			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 2 GENERATOR	FAILED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			29984	28993							(CAN) DEPARTED WITH MEL ON NR 2 GENERATOR, GENERATOR HAD BEEN DISCONNECTED. 50 MILES SOUTH WEST OF YQB, THE APU GENERATO	R FAILED. NR 1 BUS TRANSFER DID NOT TAKE PLACE, FIRST OFFICER WAS WITHOUT INSTRUMENTS. REQUESTED LANDING TO YQB, LANDED 	WITHOUT INCIDENT. APU GENERATOR CONTROL UNIT CIRCUIT BREAKER HAD TRIPPED. REPLACED GCU AS PER WORK CARD 2271-2. OFF CANA	DIAN PART 7-2450-9-0001, SERIAL 0758, ON SERIAL 2847. OFF CANADIAN PART #7-2450-9-0002 SERIAL 0776, ON S/N 1112.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2000121200340	20001212	00340	EA  	2000	12	12	CA001201015      	2	20001109	G	7414	ES10382585	CONTACTOR       	BENDIX      	D4RN3000    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUB BLOCK	WORN            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			100  			E219103G					(CAN) FAILURE OF THIS MAG WAS CAUSED BY EXCESSIVE WEAR OF THE NYLON RUB BLOCKS ON THE POINTS.  TEAR DOWN INSPECTION OF T	HE MAG REVEALED WORN BLOCKS AND THE WICKS WERE DRYER THAN NORMAL. THERE IS NO EVIDENCE OF THE TYPE OF OVERHEATING THAT I	S CAUSED BY A FAILED CAPACITOR. THIS LEAVES THREE POSSIBILITIES:  1. DEFECTIVE MATERIAL IN RUB BLOCKS.  2.  INADEQUATE L	UBRICATION IN WICKS. 3.  CONTAMINATION OF THE SINTERED IRON CAM.  LUBRICATION OF THE WICKS WAS DONE IN ACCORDANCE WITH T	HE OVERHAUL MANUAL AT THE TIME OF OVERHAUL. THE FACT THAT THE WICKS WERE DRY AFTER ONLY 100 HOURS IN SERVICE WARRANTS FU	RTHER INVESTIGATION.  CONTAMINATION OF THE CAM ALSO IS POSSIBLE AND WILL REQUIRE FURTHER INVESTIGATION.  (X)	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001032700086	20010327	00086	GL  	2001	3	27	CA001201018      	2	20001116	G	7310	6870035	LINE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FCU	LOOSE           	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ENGINE DECELERATED ON TAKEOFF FOR TEST FLIGHT AFTER ENGINE CHANGE. CAUSE WAS DETERMINED TO BE LOOSE B-NUT ON GOVER	NOR TO FUEL CONTROL UNIT AIR LINE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700088	20010327	00088	WP  	2001	3	27	CA001201020      	1	20001125	G	6210	369A10045	PIN             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	BROKEN          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			CA			5011 			D098840810					(CAN) DURING AN APPROACH FOR LANDING TO REFUEL, THE PILOT AND ENGINEER ON BOARD  EXPERIENCED A NOTICEABLE VIBRATION. UPO	N LANDING THE ENGINEER FOUND THAT A M/R BLADE PIN WAS SITTING A BIT HIGHER THAN THE OTHERS. WHEN HE UNLATCHED TO PIN, TH	E THREADED PORTION OF THE PIN  DROPPED OUT, INDICATING THAT IT HAD BROKEN NEAR THE SHANK AND TOP OF THE  THREADED REGION	. THE AIRCRAFT WAS GROUNDED, NEW PIN ORDERED, AND ALL OF THE REMAINING M/RBLADES PINS WERE INSPECTED..			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2000121200341	20001212	00341	SW  	2000	12	12	CA001201021      	1	20001124	G	2700	708101	CONTROL CABLE   			AIRTRC	AT802 	AT802       	0390305	SW  										ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			593  								(CAN) WHILE REMOVING PANELS FOR ANNUAL INSP, CABLE FOR ELEV - FLAP INTERCONNECT HAD POPPED OFF FWD LOWER PULLEY ASSY AND	 WAS TRAPPED BETWEEN PULLEY AND PULLEY GUARD.  CABLE P/N 70810-1 HAD BEEN BENT SHARPLY AND WAS SPIKED.  INTERCONNECT PUS	H ROD WAS BENT AT BOTH ROD END LOCATIONS (ROD P/N 70696-1).   ACTUATING LEVER ON FLAP TORQUE TUBE WAS BENT VERY SLIGHTLY	.  IT APPEARS SYS WAS OUT OF RIG.  MFG WAS CONTACTED FOR MORE RIGGING INFO.  DAMAGED CABLE AND INTERCONNECT TUBE WERE RE	PLACED, ACTUATING LEVER WAS INSP AND REPAIRED.  SYS RE-RIGGED AND FUNCTIONS CORRECTLY.  OTHER AT-802''S IN FLEET WILL BE	 INSP FOR CORRECT RIGGING.  (X)	1	L	7	1 	3T			NC	A19SW   					 
2000121200342	20001212	00342	EA  	2000	12	12	CA001201022      	1	20001120	G	7721	12973	ROCKER          	PWA         	AE92181ER   	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					EXH VAL ROCKER	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			593  								(CAN) TIP OF ROCKER ARM THAT PUSH ROD PUSHES ON ARM TO DEPRESS EXHAUST VALVE BROKE OFF. THIS TYPE OF BREAK IS THE FIRST 	ONE I HAVE SEEN IN THE 31 YEARS THAT I HAVE WORKED WITH TYPE OF ENGINE. THE CYLINDER WAS NEW WITH ONLY A TOTAL OF 593 HO	URS ON UNIT.  REMOVED PART FROM CYLINDER FOR EVALUATION IF REQUESTED.  AIRCRAFT WAS FORCED TO MAKE AN EMERGENCY LANDING 	ON WATER.  AIRCRAFT IS FLOAT EQUIPPED.  (X)			1	H	7	1 	3R	3	R	 	A815    	E142				 
2001040200146	20010402	00146	EU  	2001	4	2	CA001205002      	1	20000825	G	8110	Z4377200000	ROD             	MORAVN      	Z14277000000	MORAVN	Z142  	Z142        	       	EU  	AVIA  	M337  	M337AK      	 	EU  					SUPERCHARGER	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1014 								(CAN) PILOT REPORTED UNABLE TO DISENGAGE SUPERCHARGER (COMPRESSOR). INSPECTION FOUND THE PUSH-PULL CONTROL ROD HOUSING W	ORN THROUGH TO THE INNER ROD WHERE IT PASSED A FLANGE IN THE INSTRUMENT PANEL. A NEW PART WAS INSTALLED. EXTRA ABRASION 	PROTECTION WAS INSTALLED TO PROTECT FROM RE-OCCURRENCE, DUE TO LOCATION, AND SITUATION IN INSTRUMENT PANEL, FURTHER CLAM	PING IS NOT POSSIBLEA SECOND AIRPLANE IN THE FLEET WAS INSPECTED AND SLIGHT WEAR WAS FOUND ON THE HOUSING. NEW ABRASION 	PROTECTION WAS INSTALLED, NO FURTHER DEFECTS NOTED. AN OWNER IN THE U.S. HAS ALSO REPORTED THE SAME PROBLEM.2000-12-07TC	: FEEDBACKISSUE.	1	L	7	1 	3O	3	I	NT	A76EU   	EXPE3I				 
2001032700091	20010327	00091	SW  	2001	3	27	CA001205004      	1	20000705	G	6410	212010750105	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3493 	158  							(CAN) TAIL ROTOR BLADE DELAMINATION FOUND BETWEEN THE SKIN AND THE TIP BLOCK THAT WAS BEYOND LIMITS. TAILROTOR ASSEMBLY 	REPLACED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001032700092	20010327	00092	SW  	2001	3	27	CA001205005      	1	20000712	G	6720	B0500025	WASHER          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R PEDAL	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN INVESTIGATING EXCESSIVE PLAY OF THE PILOTS PEDAL ADJUSTMENT,  IT WAS NOTED THAT MISSING AND INCORRECT PARTS E	XISTED. B0500-26 WASHERS WERE MISSING FROM THE ASSEMBLY AND THE TIE BOLT HAD ALMOST 1/4 OF END PLAY. (NOTE: PARTS ON ORD	ER.)				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700093	20010327	00093	SW  	2001	3	27	CA001205006      	1	20000729	G	7722	206075790001	INDICATOR       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COCKPIT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						1927					(CAN) THIS INDICATOR WAS ERRATIC EVER SINCE IT WAS INSTALLED. IT BOUNCES, GIVING BOUNCY READINGS OF 100 DEGREES C.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011106088	20010111	06088	GL  	2001	1	11	CA001205007      	2	20000625	G	7210		NOZZLE          	ALLSN       	6898734     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					1ST STAGE	FAILED          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			15634	1751 		CAT31609P					(CAN) DURING A SCHEDULED REMOVAL OF THE COMPRESSOR ASSEMBLY, THE FIRST STAGE NOZZLE WAS VISUALLY INSPECTED AND OBSERVED 	THAT 4 VANES WERE CRACKED BEYOND MANUFACTURER'S LIMITS.  UNIT REPLACED.  (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700094	20010327	00094	GL  	2001	3	27	CA001205008      	2	20000729	G	7323	23065123	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				949  		17939					(CAN) SPIKES ON OR ABOVE 103 PERCENT N2 WHEN THE TORQUE IS ABOUT 73 PERCENT. QUADRANT READS 93 ON POINTER TO ATTAIN 103 	PERCENT. SO ENGINE DOES NOT GENERAGE ENOUGH POWER AT THE STANDARD RIGGING LOCATION OF 81. UNIT REPLACED.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001032700095	20010327	00095	SW  	2001	3	27	CA001205009      	1	20000602	G	6710	206010355007	PITCH LINK      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			1089 								(CAN) INCORRECT P/N FORK INSTALLED ON THE UPPER END OF THE ASSEMBLY. THIS FORK HAS THE SAME DIMENSION AS THE BOTTOM FORK	 (.8621). WHEN INSTALLED OVER THE TRUNNION THERE IS A SPREAD STRESS OF .013 INCHES.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700096	20010327	00096	SW  	2001	3	27	CA001205010      	1	20000816	G	6320	206040002025	TRANSMISSION    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	FAILED          	W				K		 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7922 	2555 							(CAN) DURING THE SERVICEABILITY CHECK (AFTER THE METAL WAS FOUND ON THE CHIP PLUG) MORE METAL WAS FOUND ON THE CHIP PLUG	S AND THE OIL MONITOR. MAST AND THE TRANSMISSION WERE REPLACED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001011106089	20010111	06089	SW  	2001	1	11	CA001205011      	1	20001123	G	6230	206040002007	MAST            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11307	1396 							(CAN) DURING THE SERVICEABILITY CHECK (AFTER THE METAL WAS FOUND ON THE CHIP PLUG) MORE METAL WAS FOUND ON THE CHIP PLUG	S AND THE OIL MONITOR.  MAST AND THE TRANSMISSION WERE REPLACED.   (X)					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700097	20010327	00097	SW  	2001	3	27	CA001205012      	1	20000915	G	6310	206040270003	STUD            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FREEWHEEL HOUSIN	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			11719								(CAN) DURING INSTALLATION THERE WAS NO TORQUE OF THE FORWARD HOUSING NUTS, IT WAS NOTED THAT THE STUD WAS PULLING FROM T	HE HOUSING. THE UNIT WAS REMOVED AND SENT BACK TO ACRO FOR REPAIR.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032700098	20010327	00098	NE  	2001	3	27	CA001205013      	2	20000904	G	7532	9580115620	BLEED VALVE     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) BLEED VALVE WONT CLOSE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001032700099	20010327	00099	GL  	2001	3	27	CA001205014      	2	20000923	G	7323	23065123	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1188 							(CAN) GOVERNOR ARM ALMOST SEIZED (SHAFT TO BODY). UNIT REQUIRED EXTREME FORCE TO MOVE, WAS ALSO CAUSING HEAVY COLLECTIVE	.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001032700100	20010327	00100	EU  	2001	3	27	CA001205015      	1	20000928	G	2841	647510032	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL QUANTITY	FAILED          	W				K		 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						807					(CAN) UNIT STICKING AT 70 PERCENT AND WHEN DRAINING TANK FOUND FUEL TANK EMPTY AND GAUGE READS 15 PERCENT AND THE FUEL L	OW LIGHT WAS NOT ON.					1	G	7	1 	3U			 	H9EU    					 
2001032700101	20010327	00101	CE  	2001	3	27	CA001205016      	1	20001028	G	2742	6627401000001	ACTUATOR        			LEAR  	45    	45LEAR      	5170805	CE  										HORIZ STAB TRIM	FAILED          	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				J		 	WARNING INDICATION        			DE	DESCENT        	1			CA			420  								(CAN) PRIMARY HORIZONTAL STABILIZER TRIM FAILED CREW ADVISORY SYSTEM WARNING. SECONDARY TRIM SERVICEABLE. REPLACED HORIZ	ONTAL TRIM ACTUATOR.					2	L	7	2 	4F			RT	T00008WI					 
2000121500187	20001215	00187	EU  	2000	12	15	CA001205018      	1	20001114	G	2435	230851382	STATOR          	LUCAS       	23085014    	PILATS	PC12  	PC1245      	       	EU  										WINDINGS	SHORTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				977  		98177					(CAN) STARTER/GENERATOR WAS REMOVED SERVICEABLE, FOR OVERHAUL. DURING OVERHAUL, THE STATOR FAILED HI-POT INSULATION BREA	KDOWN INSPECTION, EVEN AFTER EXTENSIVE REPEATED CLEANING.  VARNISH ON WINDOW WAS DARKER THAN NORMAL. THIS UNIT RAN WITH 	LONG-LIFE BRUSHES P/N 23088-1321.  LUCAS HAD PROBLEMS WITH EXCESSIVE HEAT BUILDING ON THE PILATUS INSTALLATION AND SUBSE	QUENTLY ISSUED SERVICE BULLETIN NR  23085-014-24-01 IN JULY 1999 TO REMOVE THIS BRUSH AND INSTALL P/N 30300-1413. THE ST	ATOR HAS NOW BEEN REWOUND,THE SB HAS BEEN ACCOMPLISHED, AND THE STARTER/GENERATOR IS BEING PREPARED FOR RETURN TO SERVIC	E AS OVERHAULED.  (X)	1	L	7	1 	3T			RT	A78EU   					 
2000121500188	20001215	00188	SO  	2000	12	15	CA001205019      	1	20001116	G	3230		UPLOCK          	PIPER       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					UPLOCK ASSY	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA			8998 			UP					(CAN) ON APPROACH GEAR WAS SELECTED DOWN, NOSE AND RT MAIN INDICATED DOWN AND LOCKED.  GEAR WAS CYCLED 3 TIMES, ON FOURT	H TRY ALL GEAR EXTENDED AND LOCKED DOWN, AIRCRAFT LANDED NO PROBLEM.  AIRCRAFT FLOWN TO MAINTENANCE BASE, PLACED ON JACK	S, GEAR SYSTEM TESTED SERVICEABLE.  POSSIBLE CAUSE:   AIRCRAFT WAS CLEANED BY FLIGHT CREW AND UPLOCK WAS NOT LUBED.  ALL	 AIR AND GROUND CREWS HAVE BEEN ADVISED OF SITUATION.  (X)			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000121500189	20001215	00189	CE  	2000	12	15	CA001205020      	1	20001116	G	3244	083316	TIRE            			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	TREAD FACE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						2028N00593					(CAN) SMALL HUMP IN TREAD AT ONE SPOT IN CIRCUMFERENCE OF TIRE. DEFECT WAS NOTED WHEN MOVING AIRCRAFT BY HAND AND TREAD 	GROOVES APPEARED TO SPREAD APART AT THIS SPOT.  SUSPECT PARTIAL FAILURE OF REINFORCING PLIES BENEATH THE SURFACE.  THERE	 IS NO VISIBLE TRAUMA ANYWHERE ON THE TIRE, AND NO VISIBLE DEFECT WHEN VIEWED FROM INSIDE.  TIRE DID NOT APPEAR TO BE AB	OUT TO FAIL COMPLETELY. TIRE WAS REMOVED AND REPLACED WITH A NEW TIRE.  (X)			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001032700102	20010327	00102	CE  	2001	3	27	CA001205021      	1	20001116	G	2750	51152373	GEAR            			CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					TE FLAP GEARBOX	CRACKED         	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			AP	APPROACH       	1			CA			6163 								(CAN) - IN FLIGHT, FLAPS SELECTED,  FLAPS DID NOT RESPOND. ON GROUND CHECKED ELECTRICAL CONNECTIONS & TESTED. FOUND THAT	 THE FLAPS EXTENDED, BUT WOULD NOT RETRACT FULLY.  ISOLATED PROBLEM TO STRIPPED REDUCTION GEAR BOX AS FLAPS COULD BE HEL	D IN POSITION BY HAND AND MOTOR WOULD RUN MOVING CAM TO LIMIT SWITCHES AND FLAPS WOULD NOT MOVE UNLESS LET GO (FREE RUN)	  WITH TENSION ON FLAPS AS IN FLIGHT, INPUTED SELECTION WOULD ONLY ROTATE CAM UNTIL CONTACT WITH WITH MICRO / UNIT SWITC	HES MADE.  REMOVED GEAR BOX  OPENED UP AND FOUND CRACKED GEAR.		1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2000121500190	20001215	00190	CE  	2000	12	15	CA001205022      	1	20001117	G	5520	1156100181	FITTING         	BEECH       	115610010325	BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3315     	01514	WP  					TAPER PIN HOLE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE CRACKS WERE DISCOVERED EMANATING FROM THE TAPER PIN HOLES ON THE ELEVATOR TORQUE TUBE	 MIDDLE FITTINGS (BOTH SIDES). (ONE CRACK PER FITTING - TWO FITTING TOTAL).  TAPER PINS WERE ALSO FOUND TO BEYOND THE .0	60 INCH MAX PROTRUSION.  PINS MUST HAVE BEEN HAMMERED ON IN THE PAST TO TIGHTEN THEM UP IN THE FITTING/TORQUE TUBE CAUSI	NG HIGHER THAN NORMAL STRESS IN FITTING HOLE.  MAINTENANCE MANUAL STATED NOT TO HAMMER BUT TO TORQUE NUT ONLY.  (X)			1	L	7	2 	4T	4	T	 	A14CE   	E4WE				 
2001010200132	20010102	00132	CE  	2001	1	2	CA001205023      	1	20001120	G	5753	55165051114	SKIN            	BEECH       		BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					L/E MID SPAN 6	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED SPAR PART NR 35-165050-229.  (X)						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001011106096	20010111	06096	SW  	2001	1	11	CA001205024      	1	20001123	G	2550		BEARING         	BELL        	204072915011	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CARGO HOOK	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				15053		CAL875					(CAN) TOP BEARING SEIZED ON CARGO HOOK CAUSING SUPPORT TO CRACK AT BOLT HOLES, SEVERE STRESS ON MOUNTING BOLTS AND BUSHI	NG CAUSING ABNORMAL WEAR OF MOUNTING BUSHING.  (X)					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001031400094	20010314	00094	SW  	2001	3	14	CA001206002      	1	20000605	G	6410	212010750009	BLADE           	BELL        	21201070135 	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313A      	41549	NE  					TAIL ROTOR	DAMAGED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA			4518 			AHN56522					(CAN) BOTTOM 1 INCH OF TAIL ROTOR SKIN PEELED OFF AND DEPARTED IN-FLIGHT.  (X)						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001010200133	20010102	00133	SO  	2001	1	2	CA001206003      	1	20001109	G	3246	16207500	WHEEL           	CLEVELAND   	40166       	PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					WHEL HLF SIDEWAL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						0697					(CAN) SCHEDULED MAINTENANCE INSPECTION DISCOVERED CRACKED WHEEL HALF DURING TIRE REPLACEMENT.  CRACK IS IN OUTER WHEEL H	ALF AND ORIGINATES FROM A LARGE LIGHTENING HOLE.  CRACK APPROXIMATELY .250 INCH  IN LENGTH.  WHEEL HALF SCRAPPED.  (X)					1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2001010200134	20010102	00134	CE  	2001	1	2	CA001206005      	1	20001121	G	3230	16001260	CIRCUIT BREAKER 	BEECH       	1153800025  	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					UNDER THE FLOOR	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA			4637 								(CAN) REFERENCE: TRANSPORT CANADA REQUEST THROUGH FEEDBACK 2/2000.  ON 18 AUGUST 2000 PILOT REPORTED UNSAFE NOSE GEAR IN	DICATION,  ON DESCENT, THE GEAR WAS EXTENDED MANUALLY (EMERGENCY).   AIRCRAFT LANDED SAFELY.  DURING INVESTIGATION, IT W	AS OBSERVED THAT THE HYDRAULIC POWER PAC MOTOR 60 AMP CIRCUIT BREAKER WAS TRIPPED.  THE CIRCUIT BREAKER WAS RESET AND GE	AR RETRACTIONS WERE CARRIED OUT.  MAINTENANCE COULD NOT DUPLICATE THE PROBLEM ON THEGROUND.  AFTER NUMBER OF EXTENSIONS 	AND RETRACTIONS, AIRCRAFT WAS RELEASED TO SERVICE.  (X)		1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2001031400095	20010314	00095	CE  	2001	3	14	CA001206006      	1	20001117	G	5620	660011510	WINDOW          			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					CABIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10715								(CAN)  DURING AN INSPECTION THE RT FORWARD CABIN WINDOW WAS FOUND CRACKED. THE CRACKS WERE FROM ONE FASTENER HOLE TO THE	 NEXT. THE WINDOW WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2001032700103	20010327	00103	CE  	2001	3	27	CA001206007      	1	20001117	G	5620	660011510	WINDOW          			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					EMERGENCY EXIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10715								(CAN)  DURING AN INSPECTION THE EMERGENCY EXIT WINDOW WAS FOUND CRACKED. THE CRACKS WERE FROM ONE FASTENER HOLE TO THE N	EXT. THE WINDOW WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2001031400096	20010314	00096	CE  	2001	3	14	CA001206008      	1	20001117	G	5541	263300352553	RIB             	LEAR        	249300015   	LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10764								(CAN)  DURING AN INSPECTION THE TOP RIB OF THE RUDDER WAS FOUND CRACKED.  THE CRACKS WERE LOCATED AROUND THE FORWARD ANC	HOR NUT PLATES. THE RIB WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2001032700104	20010327	00104	NM  	2001	3	27	CA001207002      	1	20000623	G	3240	83200502001	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					RT BRAKE	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			24045								(CAN) ON LANDING A LOUD BANG WAS HEARD, AND THE RT BRAKE PEDAL WENT FLUSH AGAINST THE FLOOR, ON THE CAPTS AND FOS SIDE. 	INSPECTION ACCOMPLISHED AND FOUND THE RIGHT PEDAL CABLE BROKEN IN AREA UNDER THE COCKPIT FLOOR. BROKEN CABLE REPLACED AN	D CHECKED SATISFACTORY.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700105	20010327	00105	NM  	2001	3	27	CA001207003      	1	20000624	G	2720	82710038100	FITTING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					RUDDER PEDAL	BROKEN          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			22743								(CAN)  ON PRE-FLIGHT CREW NOTICED BINDING AND AUDIBLE RUBBING WHEN MOVING RUDDER PEDALS. MAINTENANCE FOUND TOP PLATE ON 	PILOTS RUDDER PEDAL ASSEMBLY BROKEN. PLATE AND BEARING REPLACED, CHECKED SATISFACTORY AND AIRCRAFT RETURN TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700106	20010327	00106	NM  	2001	3	27	CA001207004      	1	20000722	G	3230	85310055	ATTACH ANGLE    			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					UPLOCK ACTUATOR	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			AP	APPROACH       	1			CA			24260								(CAN) ON APPROACH A LOUD THUMP NOISE WAS HEARD AFTER THE LANDING GEAR WAS SELECTED DOWN. INSPECTION FOUND NOSE LANDING G	EAR UPLOCK ACTUATOR ATTACHES CRACKED. AIRCRAFT REPAIRED AND RETURNED TO SERVICE.REPAIRED IN ACCORDANCE WITH THE RD8-53-5	82. WEB 8510056 PIVOT FLOOR ALSO CRACKED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700107	20010327	00107	NM  	2001	3	27	CA001207005      	1	20001009	G	2731	MS210424	NUT             		85520003009 	DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					ELEVATOR	LOOSE           	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL AT APPROXIMATELY 60 KNOTS THE PILOT IN CONTROL WAS ALERTED TO A CONTROL PROBLEM. APPROXIMATELY	 90 KG BACK PRESSURE WAS REQUIRED TO MOVE THE CONTROLS. TAKEOFF WAS ABORTED. INSPECTION FOUND RT ELEVATOR SPRING TAB WAS	 IN A FULL UP POSITION. FURTHER INVESTIGATION REVEALED THE COUNTER BALANCE RETAINING BOLT HAD DISPLACED DUE TO NUT COMIN	G LOOSE AND HAD JAMMED TAB. BOLT AND NUT INSTALLED AND RETORQUED IN COUNTER BALANCE, TAB INSPECTED, SATISFACTORY, OPERAT	IONS CHECKED SATISFACTORY. AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400100	20010314	00100	NM  	2001	3	14	CA001207007      	1	20001115	G	5542	85540001003	SKIN            	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24928			289					(CAN) DURING ROUTINE MAINTENANCE INSPECTION, STARBOARD SIDE OF FORE RUDDER FOUND TO HAVE A 10 INCH C SHAPE CRACK. FORE R	UDDER ASSEMBLY REPLACED IN ACCORDANCE WITH DEHAVILLAND DASH 8 MM CHP 27-20-00.AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700108	20010327	00108		2001	3	27	CA001207008      	4	20001117	G	2565	82560038021	SLIDE           			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					CABIN	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA											(CAN) ON DESCENT DITCHING DAM DEPLOYED. RATE OF DESCENT WAS APPROXIMATELY 600 TPM. AIRCRAFT SPEED APPROXIMATELY 210 KNOT	S WHEN RUMBLING NOISE NOTICED. TURBULENCE WAS SLIGHT, NO LARGE CONTROL INPUTS. MAINTENANCE FOUND DITCHING DAM FAIRING OP	EN. A LEAK CHECK WAS ACCOMPLISHED ON SYSTEM TO DETERMINE CAUSE NO LEAKS FOUND. DAMAGE WAS BEYOND REPAIR CAUSED BY SLIP S	TREAM. FUSELAGE WAS DENTED BY METAL BRAIDED INFLATION HOSE ASSY ORDERED AOG.RUBBER DAM WAS STILL ATTACHED TO AIRCRAFT AF	TER LANDING. AIRCRAFT DEPARTED STATION AFTER LOANER UNIT FITTED. MINOR DENTS IN FUSELAGE CAUSED BY BRAIDED HOSE ARE COVE	RED IN THE SRM,	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400101	20010314	00101	NM  	2001	3	14	CA001207009      	1	20001117	G	5522	85520056012	SKIN            		85520001002 	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120       	 	NE  					ELEVATOR	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			27001			CAP0056					(CAN) RT ELEVATOR UPPER AND LOWER SKINS PT 85520056-012 AND PT 85520055-010 FOUND DISBONDED DURING TASK CARD INSPECTION.	 THE AIRCRAFT IS GROUNDED AWAITING SKINS FOR REPLACEMENT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700109	20010327	00109	NM  	2001	3	27	CA001207010      	1	20001117	G	5260	85210109009	STRUCTURE       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					AIRSTAIR RAIL	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CREW DISCOVERED AIRSTAIR DOOR JAMS AND WILL NOT FULLY OPEN. MAINTENANCE MADE AN INTERIM REPAIR TO DOOR STRUT SUPPO	RT HARDWARE. DOOR FORWARD STRUT HANDRAIL HARDWARE WAS LATER REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400102	20010314	00102	NM  	2001	3	14	CA001207012      	1	20001120	G	5610	17180003	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14451								(CAN) CAPTAINS SIDE WINDOW FOUND CRACKED ENTIRE LENGTH. WINDOW REPLACED IN ACCORDANCE WITH MM 56-10-16. OPS CHECKED SATI	SFACTORY ON GROUND RUNUP. AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400103	20010314	00103	NM  	2001	3	14	CA001207013      	1	20001120	G	5610	17180003	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			7089 								(CAN) CAPTAINS SIDE WINDOW FOUND CRACKED.  WINDOW REMOVED AND REPLACED IN ACCORDANCE WITH MM GROUND RUN ACCOMPLISHED,  O	PERATIONS SATISFACTORY.  AIRCRAFT RETURNED TO SERVICE.NOTE: FAA SDR RAISED. REF  PCAA0011076.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001032700110	20010327	00110	NM  	2001	3	27	CA001207014      	1	20001122	G	3233	8400105	ACTUATOR        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					NLG	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA			22765								(CAN) NOSE GROUND FAILED TO EXTEND WHEN GROUND SELECTED DOWN. RED NOSE GEAR LIGHT REMAINED ON. ALTERNATE EXTENSION COMPL	ETED. NOSE DRAG STRUT ACTUATOR REPLACED IN ACCORDANCE WITH MM 32-30-36. OPERATIONS CHECKED SATISFACTORY, AIRCRAFT RETURN	ED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001031400104	20010314	00104	NM  	2001	3	14	CA001207015      	1	20001123	G	5610	17180003	WINDOW          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13462								(CAN) CAPTAINS SIDE WINDOW FOUND CRACKED. WINDOW REPLACED IN ACCORDANCE WITH MM 56-10-16. AIRCRAFT RETURNED TO SERVICE. 	NOTE: FAA PCAA0011078.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001010200136	20010102	00136	CE  	2001	1	2	CA001207017      	1	20001124	G	7603	975240151	CONTROL ARM     	BEECH       	999400011   	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					AT DETENT	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE LEVER BROKE AT THE DETENT PLATE IN THE COCKPIT PEDESTAL AREA WHEN THE CONDITION LEVER WAS OPERATED AT START-UP	 OF THE ENGINE.  (X)					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001032700112	20010327	00112	CE  	2001	3	27	CA001207020      	1	20001123	G	3230	08421201	TUBE            			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470VO     	17026	SO  	MCAULY	3AF32C	D3AF32C80   	GL  	NLG	CRACKED         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA			6677 								(CAN) WHILE PERFORMING FLT TEST, GEAR SELECTED DOWN AND OVERSHOOT PERFORMED. GEAR SELECTED UP SUCCESSFULLY. A/C RE-JOINE	D CCT & ON APPROACH GEAR SELECTED DOWN WITH GREEN LIGHTS INDICATING GOOD MAINS BUT NOTHING ON NOSE. UPON LDG THROTTLES W	ERE PULLED BACK & IDLE MIXTURE CUT-OFF PERFORMED. NOSE OF A/C HELD UP AS LONG AS POSSIBLE, AS NOSE OF A/C SETTLED,  NOSE	GEAR COLLAPSED. 3 BLADES OF EACH PROP STRUCK GROUND AS PROPS WERE WINDMILLING, & A/C SKIDDED ON ITS NOSE FOR ABOUT 50 FE	ET. ONCE A/C REMOVED FROM RWY & PLACED IN HANGAR. IT WAS EVIDENT THAT NOSE GEAR DRIVE TUBE THAT IS NORMALLY 22.5 INCHES 	IN LENGTH AND DIRECTLY ATTACHED TO LDG GEAR ACTUATOR WAS BENT AND CRACKED.	1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P22EA	 
2001032700113	20010327	00113	EU  	2001	3	27	CA001207022      	1	20001117	G	2121	F34PB6224A	FAN             			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					AIR DISTRIBUTION	INOPERATIVE     	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA											(CAN) DUE TO COOLING DIFFICULTIES A TEMPORARY LOSS OF COMMUNICATION ON COMM NR 1 AND COMM NR 2 WAS EXPERIENCED ON APPROA	CH INTO YVR FOR APPROXIMATELY 15 MINUTES.					2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2001031400105	20010314	00105	NM  	2001	3	14	CA001207023      	1	20001118	G	3213	651952022	STRUT           			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED WEIGHT UPGRADE MODIFICATIONS, THE RT LOWER SIDE STRUT WAS FOUND TO CONTAIN MULTIPLE CRACKED WITH 	IN THE THREADED END PORTION OF THE STRUT. A 1 1/2 X 1/2 INCH PIECE OF THE THREADED WAS MISSING. THE LT LOWER STRUT WAS A	LSO FOUND TO BE CORRODED,  BUT NOT DAMAGED. BOTH STRUTS WERE REPLACED.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001031400106	20010314	00106		2001	3	14	CA001207025      	4	20001121	G	3418		WARNING SYSTEM  			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					STALL WARNING	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN)  IMMEDIATELY FOLLOWING MAIN WHEELS LEAVING THE GROUND STICK SHAKERS AND STALL WARNING ACTIVATED.  CREW CONTINUED W	ITH TAKEOFF,  THE AIRCRAFT RETURNED TO AIRPORT. CREW REPORTED THAT DURING SLAT RETRACTION THAT THEY COULD NOT FULLY RETR	ACT THE SLATS (DUE TO STALL WARNING). STALL WARNING CONTINUED THROUGH OUT FLIGHT & DID NOT STOP UNTIL AIRCRAFT TOUCHED D	OWN ON THE RUNWAY. MAINTENANCE FOUND THAT THE STALL WARNING SYSTEM #2 WAS ACTIVATING PREMATURELY, SYSTEM #2 STALL WARNIN	G WAS DEACTIVATED AND THE AIRCRAFT DISPATCHED AS PER MEL WITH NO FURTHER FAULTS.		2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2001032700115	20010327	00115	SW  	2001	3	27	CA001207026      	1	20000803	G	5753	21583	MOUNT           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2000 								(CAN) ON PER FLIGHT PILOT NOTICED LT FLAP WAS NOT FAIRED WITH UPPER WING GAP COVER.FURTHER INSPECTION FOUND L/H INBOARD 	FLAP MOUNT LOWER BOLT HOLE CRACKED OUT.DUE TO PREVIOUS FAILURES, A FLEET VIAUAL SPECIAL INSPECTION WAS CARRIED OUT, ON I	NBOARD FLAP MOUNTS, AND REVEALED TWO ADDITIONAL A/C WITH CRACKED MOUNTS. ADDITIONAL NDT INSPECTION WILL BE CARRIED OUT A	T OUR 500 HOUR CHECKS. APPROXIMATELY TIME OF UNITS IN SERVICE 2000 HRS. PROBABLE CAUSE A GREATER SPRING (TENSION) LOAD I	S USED TO COMPENSATE FOR THE LARGER FLAPS EMPLOYED ON THE METAL SPARED WINGS, AND A HIGHER NUMBER OF FLAP CYCLES PER HOU	R USED IN TOWING OPERATION.	1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2001010200137	20010102	00137	SW  	2001	1	2	CA001207027      	1	20001017	G	7120	41663	MOUNT           	LYC         	O360C2E     	BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RT UPPER WELD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				2000 		L1937436A					(CAN) ENGINE MOUNT WAS REMOVED FOR NDT INSPECTION DURING ENGINE CHANGE DUE TBO.  (X)						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2001010200138	20010102	00138	CE  	2001	1	2	CA001207029      	1	20001117	G	3230	52725	BALL            		55275042    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BALL	MISSING         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						CE349					(CAN) DURING A ROUTINE MAINTENANCE CHECK THE LEAKING LEFT UPLOCK ACTUATOR WAS REPLACED WITH AN OVERHAULED UNIT. ON GEAR 	RETRACTION TEST, THE LEFT GEAR WOULD NOT EXTEND FULLY.  THE GEAR WOULD UNLOCK AND FALL, BUT NOT EXTEND TO THE LOCKED POS	ITION.  DUE TO THE NATURE OF OPERATION, THE BALL P/N 5272-5 WAS SUSPECTED TO BE MISSING.  THIS WAS CONFIRMED AFTER A PAR	TIAL DISASSEMBLY OF THE ACTUATOR.  (X)			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001010200139	20010102	00139	CE  	2001	1	2	CA001207030      	1	20001103	G	2720	04310071	HORN            	CESSNA      	04310043    	CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					RT HORN	BENT            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2941 								(CAN) DURING ANNUAL INSP AND PER AD CF-2000-20, RUDDER CNTL SYS CLOSELY INSP. RT SIDE OF RUDDER HORN HAD NICKS ON LOWER 	OTBD EDGE AND CANTED UP SEVERAL DEGS.  AT ROOT OF RT HORN WERE TEETH  MARKS INDICATING PLIERS HAD BEEN USED TO ATTEMPT T	O STRAIGHTEN HORN.   ACFT HAD BEEN PAINTED 18 MONTHS PRIOR.  PAINT IN TEETH MARKS INDICATING IT HAD BEEN BENT PRIOR TO P	AINT.   AS WELL, DEPRESSION FROM STOP BOLT HITTING STOP FLANGE IN 2 DIFFERENT SPOTS, ORIG SPOT COVERED BY PAINT.  REPL H	ORN WITH NEW CESSNA P/N 0431007-4.   FOUND THAT REQD NEW BUSHINGS (P/N NAS 74A3-004) AND NEW CLEVIS FORK END (P/N AN486-	3) TO MATCH NEW P/N HORN.  (X)	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001010200140	20010102	00140	EA  	2001	1	2	CA001211002      	1	20001109	G	7810	C2EE253	COLLECTOR RING  	PWA         	R985AN14B   	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					EXHAUST SEGMENT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						200406					(CAN) NR 7 EXHAUST SEGMENT BLEW APART ON THE INNER SIDE AT A PREVIOUSLY REPAIRED AREA.  (X)						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001010200141	20010102	00141	CE  	2001	1	2	CA001211004      	1	20001020	G	3251	15420015	CAM             			CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C307  	GL  	SHIMMY DAMPER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2851 								(CAN) DISCOVERED DURING A 100-HOUR INSPECTION. THE SHIMMY DAMPER ATTACH BRACKET WAS FOUND CRACKED. DUE TO THIS, THE LAND	ING GEAR (NOSE) WAS REMOVED AND THE STEERING CAM WAS SENT OUT FOR NDT.  THE CAM WAS FOUND CRACKED AT THE LOWER FORWARD S	HIMMY DAMPER ATTACH POINT.  THE CRACK WAS .1250 INCH AND RAN AT THE EDGE OF THE ATTACH POINT.  (X)				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2001010200142	20010102	00142	SO  	2001	1	2	CA001211006      	1	20001122	G	7900		LUBRICATION     	LYC         	O360E1A6    	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE OIL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				816  		L35872T					(CAN) 28 AUG 2000 AIRCRAFT LANDED GEAR UP, PROPELLER DAMAGED BEYOND REPAIR.  ENGINE SENT OUT TO OVERHAUL SHOP FOR PROP S	TRIKE INSPECTION.  NO DAMAGE FROM PROP STRIKE, HOWEVER, CAMSHAFT, TAPPETS AND MANY BUSHINGS HAD TO BE REPLACED BECAUSE O	F WEAR. THIS ENGINE HAS 715.5 HOURS ON IT.  USE AEROSHELL 15W50 OIL WHICH ELIMINATES THE USE OF LYCOMING LW-16702 OIL AD	DITIVE.  (X)			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2001010200143	20010102	00143	SO  	2001	1	2	CA001211007      	1	20001122	G	7900		LUBRICATION     	LYC         	O360E1A6D   	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE OIL	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				816  		RL35077T					(CAN) 28 AUG 2000, AIRCRAFT LANDED GEAR UP, PROPELLER DAMAGE BEYOND REPAIR. ENGINE SENT OUT TO OVERHAUL SHOP FOR PROP ST	RIKE INSPECTION.  NO DAMAGE FROM PROP STRIKE. HOWEVER, CAMSHAFT, TAPPETS AND MANY BUSHINGS HAD TO BE REPLACED BECAUSE OF	 WEAR. THIS ENGINE HAS 815.5 HOURS ON IT.  AEROSHELL15W50 OIL WHICH ELIMINATES THE USE OF LYCOMING LW-16702 OIL ADDITIVE	.  (X)			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2001031400107	20010314	00107	NE  	2001	3	14	CA001211008      	2	20001019	G	7321		METERING VALVE  	LUCAS       	189111      	LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					HMU	STUCK           	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			123  			1891555					(CAN) AFTER FLIGHT, BOTH ENGINES WILL NOT START. NO FUEL WAS COMING OUT OF THE HMU. BOTH HUMS R REPLACED. BOTH ENGINE ST	ARTED. THE NEXT DAY, THE RT  ENGINE DIDN'T START. THE RT HMU WAS REPLACED. FUEL WAS DRAINED, EVEN IF NO CONTAMINATION WA	S FOUND AND NO FILTERS WERE CLOGGED. PWC IS STILL INVESTIGATING.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2001032700118	20010327	00118	EU  	2001	3	27	CA001211009      	1	20001104	G	5230	811BR	PANEL           			AIRBUS	310   	A310304     	       	EU  										CARGO DOOR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING WALK-AROUND OF AIRCRAFT, FORWARD CARGO DOOR AFT ACCESS PANEL FOUND BUCKLED AND PEELED BACK,  PANEL REPLACE	D, NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHTS.					2	L	7	2 	4F			RT	A35EU   					 
2001032700119	20010327	00119	GL  	2001	3	27	CA001211010      	1	20001029	G	2751	GT41557023	DETECTOR        			BOMBDR	BD700 	BD7001A10   	1390006	GL  										TE FLAP	SEIZED          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			AP	APPROACH       	1			CA			326  			1163					(CAN) DURING APPROACH THE FLAPS WERE SELECTED AND FAILED IMMEDIATELY WITH A FLAP FAIL MESSAGE ON THE EICAS. THE AIRCRAFT	 LANDED SAFELY WITH FLAPS AT 1 DEGREES. THE OPERATOR ATTEMPTED TO CLEAR THE LATCHED FAULT ON THE GROUND THROUGH CAIMS BU	T THE FAULT WOULD NOT CLEAR. THE ACTIVE FAULT REPORTED BY CAIMS WAS LEFT ACTUATOR 3 & 4 INCHE. DURING INSPECTION OF THE 	FLAP DRIVELINE THE OPERATOR FOUND THE FORWARD ATTACHMENT BRACKET OF THE LT NR 3 SKEW DETECTOR SHEARED OFF FROM THE HI-LO	KS AND CAME TO REST ON THE BOTTOM OF THE FLAP FAIRING. NO FUEL LEAKED AS A REULT OF THE SHEARED BRACKET. THE BRACKET AND	 SKEW DETECTOR WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. CONDITION UNDER INVESTIGATION.	2	L	7	2 	4F			RT	T00003NY					 
2001032700120	20010327	00120	EA  	2001	3	27	CA001211013      	1	20001124	G	2731	3094334	TRIM SWITCH     			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	INOPERATIVE     	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			6778 								(CAN) FIRST OFFICER TRIM SWITCH WORKS OK IN TRIM DOWN BUT INTERMITTENT IN TRIM UP. WILL WORK WITH EXTREME FORCE APPLIED.	 MAINTENANCE DISPATCHED FROM ATL. FOUND BROKEN WIRE ON BACK OF TRIM SWITCH. WIRE REPAIRED, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032700121	20010327	00121	EA  	2001	3	27	CA001211014      	1	20001122	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										RIGHT	BROKEN          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			2778 	2313 							(CAN) AT THE GATE THE CREW REPORTED THE LT FLAP READING 2 DEGREES AND THE RT FLAP READING 0 DEGREE WITH THE FLAP FAIL CA	UTION MESSAGE.THE MAINTENANCE CREW REPLACED THE RIGHT BPSU, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001032700122	20010327	00122	EA  	2001	3	27	CA001211016      	1	20001122	G	2752	853D10018	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	INOPERATIVE     	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED A FLAP FAIL CAUTION MESSAGE AT 14 DEGREES DURING APPROACH.THE MAINTENANCE CREW REPLACED THE RT N	R 3 ACTUATOR.					2	L	7	2 	4F			RT	A21EA   					 
2001032700123	20010327	00123	EA  	2001	3	27	CA001211017      	1	20001122	G	2761	270007	PCU             			CNDAIR	CL600 	CL6002B19   	       	EA  										SPOILERS	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORT THAT WHILE DEPLOYING THE FLIGHT SPOILERS AT FL90, THE LT FLIGHT SPOILER DEPLOYED, THE RT FL	IGHT SPOILER DID NOT DEPLOY. THE RT FLIGHT SPOILER CAUTION MESSAGE APPEARED. THE CREW THEN RETRACTED THE FLIGHT SPOILER.	 THE MAINTENANCE CREW REPLACED THE R/H INBOARD FLIGHT SPOILER PCU AND THE SECU NR 2.				2	L	7	2 	4F			RT	A21EA   					 
2001032700124	20010327	00124	EA  	2001	3	27	CA001211019      	1	20001124	G	2740		CONTROL CABLE   			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT FLEXDRIVE	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) AFTER SELECTING THE FLAPS TO 8 DEGREE, THE FLAP FAIL CAUTION MSG APPEARED. FLAPS REMAINED AT 0 DEGREE.REPLACED THE	 LEFT EPSU REPLACED THE RIGHT BPSU FOUND RIGHT FLEXDRIVE SEVERAL STRANDS WERE BROKEN & TWISTED AROUND THE FLEX DRIVE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700125	20010327	00125	EA  	2001	3	27	CA001211021      	1	20001128	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING COCKPIT CHECK, THE CREW DISCOVERED A FLAP FAIL MESSAGE WITH FLAPS AT 0 DEGREE. THE MAINTENANCE REPLACED THE	 LEFT BPSU AND DID THE RIGGING OF THE SYSTEM.					2	L	7	2 	4F			RT	A21EA   					 
2001032700126	20010327	00126	EA  	2001	3	27	CA001211022      	1	20001128	G	3234	7179015	HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  										MLG	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, DURING THE RETRACTION OF THE GEARS, THE KNOB BROKE OFF ON THE LANDING GEAR CONTROL LEVER.THE MAINTE	NANCE REMOVED AND REPLACED THE LG CONTROL HANDLE.					2	L	7	2 	4F			RT	A21EA   					 
2001022200149	20010222	00149	EA  	2001	2	22	CA001211023      	1	20001128	G	5610	601R330332	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING THE GROUND HANDLING, THE FO WINDSHIELD HAS SEVERAL LARGE CRACKS. THE MAINTENANCE FOUND SEVERAL SCREWS IN TH	E WINDSHIELD OVERTORQUED. SOME SCREWS HAD TO BE DRILLED OUT. THE FO WINDSHIELD WAS PREVIOUSLY REMOVED DURING THE PRODUCT	ION PROCESS. THEY REPLACED THE WINDSHIELD AND RETURNED THE AIRCRAFT TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001022200152	20010222	00152	NM  	2001	2	22	CA001212007      	1	20001119	G	5754	114N300252	STRUCTURE       			BOEING	757   	75728A      	1384976	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					NR 6 SLAT	MISSING         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) AIRCRAFT IN CLIMB PHASE OF TAKEOFF. CREW REPORTED THAT WHEN THEY MOVED THE FLAP/SLAT HANDLE FROM POSITION 1 TO FUL	LY RETRACTED THAT A NOISE WAS HEARD. UPON CARRYING OUT A VISUAL INSPECTION,  IT WAS OBSERVED THAT A PORTION APPROXIMATEL	Y 800 SQUARE INCHES OF THE TRAILING UPPER EDGE OF #6 SLAT WAS MISSING. THE CAUSE IS NOT YET DETERMINED.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001030500033	20010305	00033	EA  	2001	3	5	CA001212009      	1	20001119	G	2750	865D1007	POWER UNIT      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					FLAPS	FAILED          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) FLAP FAIL FROM ZERO DEGREE FLAP POSITION 10,000 FEET ALTITUDE LEVEL. SPEED 210 KNOTS. REPLACED FLAP POWER DRIVE UN	IT AND BRAKE POSITION SENSING UNIT (BPSU) P/N 865D100-9.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001022200153	20010222	00153	EA  	2001	2	22	CA001212011      	1	20001120	G	2750		CONTROLLER      	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA						7065					(CAN) FLAPS FAILED AT 20 DEGREE'S ON APPROACH TO TORONTO. FLAPS RETRACTED TO 8 DEGREES ON GROUND, AND FAIL MESSAGE CLEAR	ED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001022200154	20010222	00154	NM  	2001	2	22	CA001212013      	1	20001114	G	2780	285T004953	FCU             			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					LE FLAPS	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH AT SPEED 170K, SELECTED FLAPS FROM 20 TO 25, FLAPS STOPPED AT 23 DEGREES, CAUTION LIGHT TRAILING EDGE 	FLAP DISAGREE. GO AROUND CARRIED OUT. CHANGED FLAP SLAT ELECTRONIC CONTROL UNIT (FSCU). OPERATION CHECK NORMAL.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001030500035	20010305	00035	EU  	2001	3	5	CA001212014      	1	20001115	G	5270		SENSOR          	AIRBUS      	A320211     	AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					AFT CARGO DOOR	OUT OF ADJ      	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CR	CRUISE         	1			CA						350					(CAN) IN CRUISE AFT CARGO DOOR INDICATED OPEN ON ELECTRONIC CENTRALIZED AIRCRAFT MONITORING.NORMAL PRESSURIZATION AND NO	 VIBRATION.  ADJUSTED DOOR PROXIMITY SENSOR 34WV, SYSTEM CHECKED NORMAL.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001022200155	20010222	00155	EA  	2001	2	22	CA001212016      	1	20001122	G	2701	21590500883	CONTROL COLUMN  			CNDAIR	CL215 	CL2151A10   	       	EA  										COCKPIT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2328 	2328 							(CAN) CHERRY RIVETS HOLDING PROTECTIVE TUBE AND LOWER MEMBER OF CONTROL COLUMN HAVE BEEN FOUND LOOSE. REF. PSP 298 CHAP.	 27-10-0 FIG 1A.					2	H	7	2 	4R			 	A14EA   					 
2001011106072	20010111	06072	EA  	2001	1	11	CA001212017      	1	20001110	G	2824	60062633689	LINE            			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					FUEL TRANSFER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN INTERNAL FUEL LEAK NOTED DURING FINAL STAGES OF 600 HR INSP ON A/C. AS WINGS WHERE FILLED WITH FUEL TO CHECK FO	R LEAKS FOR SB- THAT HAD BEEN INCORP, RT AUXILIARY TANK FOUND TO BE FILLING WITH FUEL. LATER INVEST., IT DISCOVERED THAT	 FLEXIBLE STEEL BRADED FUEL LINE CONNECTED TO R/H BOOST PUMP ACCESS PANEL HAD BEEN CHAFED AGAINST RIGID ALUMINUM LINE PR	ODUCING SMALL HOLE CAUSING LEAK.AS BOOST PUMP ACCESS  PANEL IS PLACED IN POS DURING CLOSEOUT, POS OF FLEXIBLE LINE CANNO	T BE CHECKED FOR CLEARANCE WITH RIGID LINE.A NEW RIGID LINE INST&FLEXIBLE LINE REPOSED (BY RE-TIGHTENING NUT) ON ACCESS 	PANEL IN ORDER TO PROVIDE ADEQUATE CLEARANCE.	2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2001030500039	20010305	00039	SO  	2001	3	5	CA001212021      	1	20001114	G	2913		POWERPACK       	PRESTOLITE  	ERH406151   	PIPER 	PA44  	PA44180     	7104402	SO  										HYDRAULIC SYSTEM	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			AP	APPROACH       	1			CA						AAM1472					(CAN) FLIGHT CREW REPORTED LANDING GEAR SELECTOR HAD TO BE ACTIVATED SEVERAL TIMES BEFORE GEAR LOWERED AND THREE GEARLIG	HTS ILLUMINATED. SUBSEQUENT GEAR SWINGS RESULTED IN POWER PAC REPLACEMENT.					1	L	7	2 	3O			 	A19S0   					 
2001010200144	20010102	00144	EA  	2001	1	2	CA001212022      	2	20001114	G	7414		MAGNETO         	LYC         	O360A4M     	CESSNA	172   	172M        	2072418	CE  	LYC   	O360  	O360A4M     	41514	EA  					LT MAGNETO	FAILED          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA						L2102036A					(CAN) LT MAGNETO SHOWED EXCESSIVE RPM DROP DURING GROUND RUN.  (X)						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001010200145	20010102	00145	CE  	2001	1	2	CA001212023      	1	20001121	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW HEARD A NOISE IN THE FRONT OF THE AIRCRAFT AND UPON INVESTIGATION, DETERMINED THAT THE CAPTAINS WI	NDSCREEN HAD CRACKED IN THE OUTER PANE OF GLASS.  THE AIRCRAFT RETURNED TO BASE AND LANDED UNEVENTFULLY.  MAINTENANCE RE	PLACED THE WINDSHIELD AND THE AIRCRAFT WAS RELEASED.  NO SPECIFIC CAUSE WAS DETERMINED FOR THE FAILURE.  (X)				1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001022200156	20010222	00156	NM  	2001	2	22	CA001214002      	1	20001129	G	2780	654465112	SWITCH          			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 3 SLAT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) TOP OF CLIMB, NR 3 SLAT INTRANSIT LIGHT ON OVERHEAD PANEL AND LEADING EDGE FLAP INTRANSIT LIGHT ON, FORWARD PANEL,	 INTERMITTENTLY, WITH ASSOCIATED MINOR AIRFRAME VIBRATION. FLIGHT RETURNED. REPLACED NR 3 SLAT ACTUATOR RODEND SWITCH AS	SEMBLY, SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001022200157	20010222	00157	NM  	2001	2	22	CA001214004      	1	20001201	G	2612		FIRE DETECTOR   			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 ENGINE	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT FROM YVR, CREW SAW A MOMENTARY FLASH OF NR 1 ENGINE FIRE HANDLE LIGHT. IT BECAME INTERMITTENT AS CLIMB	 CONTINUED. CREW ELECTED TO RETURN, REQUESTED CFR ON ARRIVAL. AFTER CLEARANCE TO RETURN RECEIVED AND DESCENT STARTED, FI	RE HANDLE WARNING LIGHT ILLUMINATED STEADY AS DID MASTER CAUTION LIGHTS. PRIMARY FIRE CHECKLIST COMPLETED, NR 1 ENGINE W	AS SHUTDOWN. FIRE BOTTLES WERE DISCHARGED. ON LANDING, CAME TO FULL STOP ON RUNWAY, ONCE THE FIRE CREWS CLEARED AIRCRAFT	 PROCEEDED TO BRIDGE. REPLACED ELECTRICAL CONNECTORS D980 AND D978 ON M332, UPPER FIREWALL FIRE/OVERHEAT DETECTOR. M332 	DETECTOR REPLACED AS PER WORK CARD 1203, NR 1 ENGINE FIRE AND OVERHEAT TESTED SERVICEABLE. FIRE BOTTLES REPLACED.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001022200158	20010222	00158	NM  	2001	2	22	CA001214005      	1	20001211	G	2133	20473124	SHAFT           		22048013    	BOEING	767   	76735H      	1385208	NM  										OUTFLOW VALVE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36011			24348					(CAN) REMOVED ACTUATOR FROM A/C DUE REPEAT PREP. SHOP INSPECTION  FOUND SPUR GEAR SPLINE HAD A SEGMENT MISSING. THIS MIS	SING SEGMENT HAD BEEN REPLACED BY A ROLL PIN LAID IN THE OPEN AREA F THE SPLINE. NO APPROVED REPAIR ALLOWS THE USE OF RO	LL PINS IN REPAIRS TO THE SPUR GEAR. REPAIR WAS DETERMINED TO BE ILLEGAL.				2	L	7	2 	4F			RT	A1NM    					 
2001030500048	20010305	00048	EU  	2001	3	5	CA001214013      	1	20001117	G	5350	SL4758	SEAL            	BRAERO      	BAE146200   	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING ROOT PNL	DETERIORATED    	W				K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			CA			29370			E2106					(CAN) THE FLIGHT CREW REPORTED AN AIRFRAME VIBRATION BETWEEN 235 - 250 KNOTS IN CLIMB. INVESTIGATION REVEALED THAT THE A	ERODYNAMIC SEALS ON WING ROOT PANELS 285/286 CT WERE BADLY DETERIORATED. THE SEALS WERE REPLACED AND A SATISFACTORY TEST	 FLIGHT PERFORMED.				2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001022300060	20010223	00060	EU  	2001	2	23	CA001214015      	1	20001112	G	2913	716988	PUMP            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						MX634989					(CAN) INVESTIGATION OF A HYDRAULIC FLUID LEAK FROM THE NR 2 ENGINE RESULTED IN REPLACEMENT OF THE ENGINE DRIVEN HYDRAULI	C PUMP,  WHICH WAS FOUND TO BE LEAKING FROM THE SHAFT SEAL. THIS UNIT HAD ONLY ACCUMULATED 272 HOURS AND 172 CYCLES SINC	E REPAIR FOR A SIMILAR PROBLEM.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001022200159	20010222	00159	SO  	2001	2	22	CA001214016      	1	20001204	G	5510		BRACKET         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE HORIZONTAL STABILIZER UPPER AND LOWER SKIN AT THE RIGHT HAND ELEVATOR ATTACH BRACKET WERE FOUND DENTED AND CRA	CKED. THE DAMAGED AREA WAS OUT AWAY AND REPAIRED BY INSTALLING AN INNER SPLICE PLATE AND AN EXTERNAL DOUBLERS PLATE PATC	H OF 2024T3 ALUMINUM IN ACCORDANCE WITH THE EMB-110P1 STRUCTURAL REPAIR MANUAL T.O.1C95A-3 FIGURE 3-14 AND 3-15. THE ADJ	ACENT STRUCTURE WAS INSPECTED PRIOR TO INSTALLATION OF THE PLATES AND FOUND TO BE SERVICEABLE.			1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2001011105925	20010111	05925	EU  	2001	1	11	CA001218002      	1	20001127	G	3200	200736001	LANDING GEAR    			FOKKER	F28   	F28MK1000   	4990808	EU  										NOSE	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA						DRG178870					(CAN) OVERSHOT RWY BY SOME 140 METERS. PASSENGERS & CREW MEMBERS WERE DEPLANED W/O REQUIREMENT OF EMERGENCY EVACUATION &	 WERE TRANSPORTED TO YFC AIRPORT TERMINAL - WERE NO INJURIES TO REPORT. A/C CAME TO REST IN MUD PAST END OF RWY WITH NOS	E GEAR BURIED UP TO NOSE GAR DOORS - NO REPORTED DAMAGE TO DOORS OR GEAR. SEVERAL MAINT PERSONNEL. A/C REMOVED FROM END 	OF RWY BY 1500 LOCAL TIME AFTER MUCH DILIGENCE FROM THESE PERSONNEL. INIT INSP REVEALED VISIBLE DAMAGE TO BE MINIMAL BUT	 FURTHER DETAILED INSP WILL FOLLOW. A/C INSP  & DEEMED SAFE FOR FERRY FLT. THOROUGH SPCL INSP AFTER ABNORMAL GROUND LOAD	S OF A/C COMPLETED, NOSE LDG GEAR DOORS REPLACED & NOSE LDG GEAR	2	L	7	2 	4F			RT	A20EU   					 
2001011105950	20010111	05950		2001	1	11	CA001218005      	4	20001210	G	2311	40001278500	TRANSCEIVER     			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					UHF	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1621					(CAN) TRANSCEIVER STICKS IN RX MODE MAKING COMMUNICATION IMPOSSIBLE ON THE FM UHF BAND. UNIT WAS REPLACED.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001011105951	20010111	05951	EU  	2001	1	11	CA001218006      	1	20001210	G	3211	40001278500	TRANSCEIVER     			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					UHF SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1659					(CAN) INSTALLED TRANSCEIVER IN HELICOPTER AND DISCOVERED DURING RADIO TESTS THAT THE UNIT HAD VERY POOR TRANSMIT AND REC	EIVE FUNCTIONING. NOTE THAT THIS UNIT WAS BRAND NEW.UNIT REMOVED AND SERVICEABLE RT WAS INSTALLED.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001011105952	20010111	05952	EU  	2001	1	11	CA001218007      	1	20001211	G	2824	1178978301	DETECTOR        			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					FUEL PUMP	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA						169					(CAN) UPON APPROACH BOTH FUEL TRANSFER PUMP WARNING LIGHTS ILLUMINATED. HELICOPTER LANDED WITHOUT INCIDENT AND IT WAS DI	SCOVERED THAT BOTH PUMPS WERE OPERATING NORMALLY. THE FALSE INDICATION OF FUEL PUMP FAILURE WAS TRACED TO THE DETECTOR. 	THE UNIT WAS REPLACED WITH A SERVICEABLE UNIT AND THE SYSTEM TESTED SERVICEABLE.				1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001022300063	20010223	00063	NM  	2001	2	23	CA001218008      	1	20001118	G	2612	1061096115	FIRE LOOP       			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 1 ENGINE	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) NR 1 ENGINE FIRE WARNING LIGHT INDICATION ILLUMINATED, TOP OF DESCENT INTO YYC. CREW SHUT DOWN NR 1 ENGINE, DISCHA	RGED FIRE BOTTLE AND CARRIED OUT A SINGLE ENGINE LANDING. FIRE WARNING SYSTEM INSPECTED, NR 1 ENGINE LOWER FIRE DETECTIO	N LOOP, 4 CONNECTORS AND FIRE BOTTLE REPLACED.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001011105953	20010111	05953	EU  	2001	1	11	CA001218011      	1	20001127	G	2840		CONNECTOR       			BAG   	JETSTM	JETSTM3212  	1500217	EU  						ROTOL	R333	R333482F12  	GL  	FUEL TANK	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28574								(CAN) FUEL INDICATION SYSTEM WAS ERRATIC, IT WAS DETERMINED THAT THE PROBE WIRES WERE LOSING THE SHIELDING CIRCUIT. IT W	AS FURTHER DETERMINED THAT THE INTER PROBE WIRES HAD SILVER PLATED BNC CONNECTIONS TO EACH PROBE, THE SILVER WAS SO TARN	ISHED THAT THE CONTINUITY WAS LOST. IT WAS ALSO DETERMINED THAT THE BNC  SHELLS WERE NO LONGER TIGHT ENOUGH WHEN LOOKED 	UP TO PREVENT AN ERRATIC READING WHEN FUEL WAS SLOSHING IN THE TANK AND TUGGING ON THE WIRING. CLEANING THE SILVER BNC C	ONNECTORS AND SLIGHTLY CRIMPING THE BNC SHELL PROVIDED A TIGHT CONNECTION AND ELIMINATED THE ERRATIC READINGS.		2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL	 
2001022300066	20010223	00066	SW  	2001	2	23	CA001218013      	1	20001128	G	5510	206020123008	FITTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HORIZONTAL STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7254 								(CAN) UPON SCHEDULED INSPECTION THE RT HORIZONTAL STABILIZER WAS FOUND TO HAVE SOME PLAY. FURTHER INVESTIGATION REVEALED	 THE FITTING WHICH ATTACHES THE STABILIZER TO THE TAIL BOOM WAS CRACKED. WHEN THE STAB WAS REMOVED, THE FITTING CAME OFF	 IN 2 PIECES. IT WAS BROKEN ACROSS THE CENTER.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001022300067	20010223	00067	EU  	2001	2	23	CA001218015      	1	20001108	G	6210	23340AK30130LE	PIN             			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					MAIN ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BROKEN PIN WAS DISCOVERED STILL SITTING IN PLACE INSIDE THE TWO BLADE PINS. THE PILOT CLAIMS TO HAVE DONE AN A	PPROPRIATE PRE-FLIGHT CHECK THAT MORNING. IT IS UNKNOWN HOW MANY HOURS THE AIRCRAFT FLEW IN THIS CONDITION.					1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2001022300068	20010223	00068	EU  	2001	2	23	CA001218017      	1	20001205	G	6410		BLADE           	EVEREADY    	355A12004008	SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						5230					(CAN) - UNABLE TO BALANCE TAIL ROTOR ASSEMBLY.  REMOVED TAIL ROTOR ASSEMBLY FOR INVESTIGATION.  REMOVED HUB ASSEMBLY & B	EARING FROM TAIL ROTOR ASSEMBLY, TO MOVE TAIL ROTOR TIP UP & DOWN & HEAR ABNORMAL NOISE.  CLICKING NOISE WAS HEARD. RE: 	DGAC AD 84-064-037(B)R3  APPLIES.				1	G	7	1 	3U			 	H9EU    					 
2001022300069	20010223	00069	NM  	2001	2	23	CA001218019      	1	20001205	G	5540	654516317	ANGLE           			BOEING	737   	737204      	1384458	NM  	PWA   	JT8   	JT8D15      	52051	NE  					RUDDER	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			90521								(CAN) FLIGHT CREW REPORTED AN IN-FLIGHT VIBRATION. WHILE INVESTIGATING, MAINTENANCE DISCOVERED THE RUDDER PCU FORWARD AT	TACH BEAM LOOSE. INSPECTION REVEALED THE HI-LOKS AT THE TWO LOWER ANGLES LOOSE AND WORKING, AS WELL AS THE LOWER LT CLIP	 ASSY CRACKED. THE DISCREPANT STRUCTURE IS TO BE REPLACED, THE AIRCRAFT WILL TEHN BE RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001011105992	20010111	05992	EA  	2001	1	11	CA001219002      	1	20001204	G	2731		TUBE            	DHAV        	C3CF4195    	DHAV  	DHC3  	DHC3        	2800202	EA  										ROD END	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION NOTICED CORROSION AT END OF LEFT HAND ELEVATOR TRIM TAB PUSH ROD. CLEANED AREA AND FOUND TUBE TO	 BE CORRODED THROUGH AT RIVETED ROD END. REPLACED PUSH ROD TUBE.					1	H	7	1 	3R			 	A815    					 
2001011105993	20010111	05993	EA  	2001	1	11	CA001219003      	1	20001206	G	5330		SKIN            	DHAV        	DHC3        	DHAV  	DHC3  	DHC3        	2800202	EA  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						77					(CAN) ON INSPECTION FOUND CRACKS AT RIVET JUST BELOW STATION 398 VERTICAL FIN JOINT IN SKIN. THIS IS THE FIFTH SUBSEQUEN	T CRACK FOUND ON FIVE DIFFERENT TURBINE OTTER AIRCRAFT. CRACK PATCHED AS PER SRM.					1	H	7	1 	3R			 	A815    					 
2001011105997	20010111	05997		2001	1	11	CA001219009      	4	20001121	G	2565	30656126	TUBE            			BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					ESCAPE SLIDE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						0480					(CAN) THIS UNIT WAS SENT FOR OVERHAUL AND FAILED HYDROSTATIC TEST, AND THE INFLATABLE FAILED THE PROOF TEST, ALSO NOTICE	 THAT THE LOWER TUBE FAILED THE TEST AT 4 PSI AND SEPARATED ALONG THE MAIN SEAM ADJACENT TO THE PRESSURE RELEASE VALVE.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001022300072	20010223	00072		2001	2	23	CA001221002      	4	20000805	G	3400	83423051009	CONTROLLER      			DHAV  	DHC8  	DHC8102     	2809003	NM  										COCKPIT	SMOKE           	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			14835			ES0013					(CAN) SAHS CONTROL PANEL STARTED TO SMOKE IN FLIGHT. EMERGENCY DECLARED & A/C LANDED WITHOUT FURTHER INCIDENT. PROBLEM C	ONFIRMED TO BE SAHS STANDBY CONTROL. ASSEMBLY REMOVED AND REPLACED, OPS CHECKED SATISFACTORY, A/C RETURNED TO SERVICE.					2	H	7	2 	4T			RT	A13NM   					 
2001011106215	20010111	06215	NM  	2001	1	11	CA001221004      	1	20001206	G	2460	MS35061	RECEPTACLE      			DHAV  	DHC8  	DHC8*       	       	NM  										NR 1 ENGINE	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) ON DEC 6/2000 AFTER ENGINE START ENG NR 1 SMOKE REPORTED COMING FROM DC EXT POWER RECEPTACLE, ENG SHUT DOWN AND PO	WER RECEPTACLE INSPECTED. FOUND SIGNS OF OVERHEAT WITH MELTED PLASTIC AROUND RECEPTACLE AND SMELL OF BURNED PLASTIC/RUBB	ER IN NOSE COMPARTMENT. A/C GROUNDED FOR FURTHER INSPECTION. A/C THEN FERRIED TO MAIN BASE FOR FURTHER INSPECTION. FOUND	 POSITIVE PIN ON RECEPTACLE, BURNT NUT SECURING WIRING LUG TO THE POSITIVE TERMINAL WAS ONLY FINGER TIGHT, PLUS HARDWARE	 WAS PLAIN NUT AND PLAIN WASHER. RECEPTACLE WAS REPLACED UTILIZING LOCK NUTS. A/C RETURNED TO SERVICE.		2	H	7	2 	4T			RT	A13NM   					 
2001022300073	20010223	00073	NE  	2001	2	23	CA001221005      	2	20001108	G	7200		ENGINE          	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					NR 2	MAKING METAL    	W				B				EMER. DESCENT           				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		DE	DESCENT        	1			CA			25473			120051					(CAN) ON DECEMBER 8/2000. DURING DESCENT SMOKE REPORTED IN CABIN. CREW NOTICED NR 2 ENGINE I.T.T. SPIKING ALSO NOTED VIB	RATION & SPUTTERING NOISE. ENGINE SHUT DOWN, EMERGENCY DECLARED. A/C LANDED WITHOUT INCIDENT. INSPECTION FOUND METAL IN 	JET PIPE AND METAL PARTICLES ON CHIP DETECTOR ENGINE NR 2 REPLACED, GROUND RUN AND LEAK CHECK SATISFACTORY, A/C RETURNED	 TO SERVICE, 2001-01-03TC:  EXPECT FOLLOW-UP REPORT FROM ORIGINATOR.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300074	20010223	00074	NM  	2001	2	23	CA001221006      	1	20001211	G	3260	83231044005	GUARD           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	CRUSHED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			26043								(CAN) AFTER TAKEOFF ON GEAR RETRACTION THREE CAUTION LIGHTS AND ARIGHT MAIN GROUND WARNING LIGHT ON. MOTORING SOUND HEAR	D AND GEAR WOULD NOT RETRACT. IN TRANSIT LIGHT ON IN GEAR RETRACT LEVER, MAINTENANCE INSPECTION FOUND RIGHT HAND NACELLE	 AFT ACCESS PANEL CRUSHED BETWEEN GEAR & WHEEL PIN CUTOUT. PREVENTING RT GEAR FROM FULLY GOING INTO UPLOCK POSITION . PA	NEL REPLACED, GEAR RETRACTION TEST SATISFACTORY. A/C RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001022300075	20010223	00075	NM  	2001	2	23	CA001221007      	1	20001009	G	5260	85210263101	STRUT           	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FWD AIRSTAIR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23257			292					(CAN) CREW FOUND FORWARD AIRSTAIR DOOR SUPPORT STRUT ATTACH POINT BROKEN. STRUT REPLACED AND AIRCRAFT RETURNED TO SERVIC	E.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300076	20010223	00076	NM  	2001	2	23	CA001228002      	1	20001201	G	2730	82760174006	JACKSCREW       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					ELEVATOR	FROZEN          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			21342								(CAN) DURING CRUISE ATTEMPTED TO DESCENT USING THE AUTOPILOT. CREW RECEIVED A MIS-TRIM LIGHT AND TURNED OFF THE AUTOPILO	T. EXPERIENCED AN OUT OF TRIM CONDITION. THE ELEVATOR TRIM WOULD NOT ADJUST MANUALLY, TEMPERATURE -19 DEGREES C. MAINTEN	ANCE INSPECTED AND FOUND THE ELEVATOR TRIM TO OPERATE NORMALLY, FREEZING SUSPECTED. THE TABS AND ELEVATORS WERE SUSPECTE	D AND LUBRICATED IN ACCORDANCE WITH DHC PROCEDURES. OPERATIONAL CHECK PROVED SATISFACTORY. AIRCRAFT WAS RETURNED TO SERV	ICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300077	20010223	00077	NM  	2001	2	23	CA001228003      	1	20000830	G	3234	574205	SELECTOR VALVE  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					MLG	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			3049 			276					(CAN) WHEN GEAR WAS SELECTED DOWN, THE CAREW RECEIVED YELLOW CAUTION LIGHTS FOR HANDLE AND GEAR DOORS. LANDING GEAR REMO	VED IN THE UP POSITION - CREW PERFORMED ALTERNATE GEAR EXTENSION AND THE AIRCRAFT LANDED UNEVENTFULLY. MAINTENANCE TROUB	LESHOT SYSTEM, FOUND THE LANDING GEAR SELECTOR VALVE LEAKING - REMOVED/REPLACED CARRIED OUT, OPERATION CHECKS, GOOD. AIR	CRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300078	20010223	00078	NM  	2001	2	23	CA001228004      	1	20000730	G	5311	8551084	DOUBLER         	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18888			335					(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4, PORT SIDE/AFT FUSE, CRACK	 WAS REPAIRED USING DEHAVILLAND REPAIR DWG  (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300079	20010223	00079	NM  	2001	2	23	CA001228005      	1	20000806	G	5330	8551084	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23069								(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURES WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE/AFT F	USE, CRACK WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300080	20010223	00080	NM  	2001	2	23	CA001228006      	1	20000804	G	5311	8551084	DOUBLER         	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14945			392					(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURES WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4, PORT SIDE/AFT 	FUSE, CRACK WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300081	20010223	00081	NM  	2001	2	23	CA001228007      	1	20000804	G	5311	8551084	DOUBLER         	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14945			392					(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURES WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4, PORT SIDE/AFT 	FUSE, CRACK WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300082	20010223	00082	NM  	2001	2	23	CA001228008      	1	20000804	G	5330	8551084	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22562								(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE/AFT FU	SE, CRACK WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300083	20010223	00083	NM  	2001	2	23	CA001228009      	1	20000805	G	5330	8551084	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21648								(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME #4, STRINGER #4 PORT SIDE/AFT FUSE, 	CRACK WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300084	20010223	00084	NM  	2001	2	23	CA001228010      	1	20000809	G	5330	8551084	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			23366								(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME  NR 4, STRINGER NR 4 PORT SIDE, CRAC	K WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022300085	20010223	00085	NM  	2001	2	23	CA001228011      	1	20000809	G	5330	8551084	DOUBLER         	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15454			389					(CAN) DURING A FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE, CRACK	 WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001011106255	20010111	06255	NM  	2001	1	11	CA001228012      	1	20000813	G	5320	8551084	DOUBLER         	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22347			308					(CAN) DURING FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE, CRACK W	AS REPAIRED USING DEHAVILLAND  REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600083	20010226	00083	NM  	2001	2	26	CA001228013      	1	20000827	G	5330	8551084	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24727								(CAN) DURING FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE, CRACK W	AS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600084	20010226	00084	NE  	2001	2	26	CA001228014      	2	20000921	G	7261		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					NR 2	LACK OF LUBE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA			22801								(CAN) DURING FLIGHT NR 2 ENGINE OIL PRESSURE FLUCTUATED BETWEEN 48-65 PSI, ENGINE SHUTDOWN AS PRECAUTION. ABNORMAL CHECK	 LIST COMPLIED WITH, AIRCRAFT DIVERTED TO NEAREST AIRPORT, AFTER LANDING ENGINE OIL SERVICED WITH 4 QUARTS OF OIL, AIRCR	AFT RAN, OPERATIONAL CHECKS GOOD, AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600085	20010226	00085	NM  	2001	2	26	CA001228015      	1	20000901	G	5330	85530184	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22410								(CAN) DURING FLEET INSPECTION REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4, PORT SIDE, CRACK W	AS REPAIRED USING DEHAVILLAND REPAIR DWG  (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600086	20010226	00086	NM  	2001	2	26	CA001228016      	1	20000904	G	5313	85530184	DOUBLER         			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22214								(CAN) DURING FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE, CRACK W	AS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600087	20010226	00087	NM  	2001	2	26	CA001228017      	1	20000907	G	5330	85530184	DOUBLER         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19349								(CAN) DURING FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4 PORT SIDE, CRACK W	AS REPAIRED USING DEHAVILLAND REPAIR DWG  (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600088	20010226	00088	NM  	2001	2	26	CA001228018      	1	20000914	G	2611	473054	SMOKE DETECTOR  			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					CABIN	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB SMOKE DETECTOR LIGHT ILLUMINATED IN FLIGHT FOR 5 SECONDS, AIRCRAFT RETURNED TO THE FIELD. MAINTENANCE	 SECURED A LOOSE CONNECTOR PLUG ON THE BULKHEAD, SMOKE DETECTOR OPERATIONAL CHECK WAS GOOD. AIRCRAFT RETURNED TO SERVICE	..				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001022600089	20010226	00089	NE  	2001	2	26	CA001228019      	2	20000922	G	7261		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					NR 2	LACK OF LUBE    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA			29207								(CAN) DURING TAKEOFF NR 2 ENGINE OIL PRESSURE LT ILLUMINATED WITH, OIL PRESSURE FLUCTUATING BETWEEN  35-60 PSI. ENGINE W	AS SHUTDOWN & AIRCRAFT RETURNED TO FIELD. NO EMERGENCY WAS DECLARED, PAX DEPLANED, NR 2 ENGINE OIL WAS SERVICED, 4 QUART	S OF OIL. ENGINE RUN AND ALL INDICATIONS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001011106312	20010111	06312	NM  	2001	1	11	CA001228020      	1	20001008	G	5313	85530184	DOUBLER         	DHAV        	DHC8100     	DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	PW121 	PW121       	52124	NE  					DOUBLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21903			329					(CAN) DURING FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR 4, STRINGER NR 4, PORT SIDE, CRACK 	WAS REPAIRED USING DEHAVILLAND REPAIR DWG (RD8-55-199).					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030500050	20010305	00050	NM  	2001	3	5	CA001228022      	1	20001108	G	5330	85530184	DOUBLER         	DHAV        	DHC8102     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	PW121 	PW121       	52124	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			19793			327					(CAN) DURING FLEET INSPECTION, REAR FUSELAGE STRUCTURE WAS FOUND CRACKED AT FRAME NR4, STRINGER NR4, PORT SIDE, CRACK WA	S REPAIRED USING DEHAVILLAND REPAIR DWG RD8-55-199. AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030500051	20010305	00051	NM  	2001	3	5	CA001228023      	1	20001106	G	2750	734386B	DRIVE SHAFT     			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					LT FLAP	MISINSTALLED    	W				K	 	 	 	NONE                    				J	W		WARNING INDICATION        	INADEQUATE Q C            		LD	LANDING        	1			CA			3924 								(CAN) MAINTENANCE REPORT: AFTER LANDING, FLAP DRIVE CAUTION LIGHT ILLUMINATED DURING FLAP RETRACTION. FLIGHT CREW COULD 	SEE THE PRIMARY DRIVE SHAFT WAS DISCONNECTED AT L/H NR2 BALL SCREW ACTUATOR OUTBOARD SPUNE CONNECTION. (MECHANICS WERE D	ISPATCHED TO MINAMI TO INSPECT/RE-CONNECT AND RIG FLAP SYSTEM - NO DAMAGE FOUND AND AIRCRAFT RETURNED TO SERVICE). CAUSE	: ON OCTOBER 23-27 THE A/C UNDERWENT 3RD PARTY SERVICING - TASK 2750/02 - LUBRICATION OF FLAP PRIMARY TO SHAFT SPUNES - 	MAINTENANCE DID NOT INSTALL THE THROUGH BOLT AT L/H NR2 BALL SCREW ACTUATOR OUTBOARD SPLINE CONNECTION CORRECTLY.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030500052	20010305	00052	NM  	2001	3	5	CA001228024      	1	20001108	G	2721	682015	TRIM SWITCH     			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  					COCKPIT	FAULTY          	W				O	 	 	 	OTHER                   				F		 	FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) PILOT REPORT): OPERATION OF RUDDER TRIM CAUSED TRIM MOTOR FULL DEFLECTION RIGHT. YAW CORRECTED WITH RUDDER INPUT -	 ABLE TO RE-CENTRE TRIM, BUT SUBSEQUENT OPERATION OF TRIM CAUSED FAULT TO RETURN. (INITIAL IDENTIFICATION OF FAULT HINDE	RED BY DEFECTIVE RUDDER TRIM INDICATOR) (ADD - UNDER MEL).EMERGENCY RUDDER TRIM SWITCH.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001011106334	20010111	06334	EA  	2001	1	11	CA001228025      	1	20001114	G	6100	88062323	BLADE           	HAMSTD      	8067001     	DHAV  	DHC8  	DHC8311     	1386006	EA  						HAMSTD	14SF	14SF*       	NE  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12752								(CAN) DURING PREFLIGHT INSPECTION #2 HEATER ELEMENT FOUND BURNED. BLADE REPLACED IAW AMM, A/C RETURNED TO SERVICE.						2	H	7	2 	4T			RT	A13NM   		6	C	P7NE	 
2001030500053	20010305	00053	EA  	2001	3	5	CA001228029      	1	20001201	G	3010	2488294	FILTER          	DHAV        	44E061A     	DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	DEICE SYSTEM	PLUGGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA				1190 							(CAN) PENUMATIC DE-ICE SYSTEM FAILED IN FLIGHT. DE-ICE PRESSURE WAS DOWN TO 12-15 PSI INFLIGHT AND 8-10 PSI ON GROUND. M	ANUAL PRESSURE 1518 +/-1 PSI. MAINTENANCE FOUND THE SYSTEM FROZEN, AND ALL THE WATER SEPARATOR FILTERS PLUGGED WITH SOOT	. THE FILTERS WERE ALSO BRITTLE FROM TIME. THE INSPECTION/REPLACEMENT TIME ON THESE FILTERS IS 1800 HOURS. THE DE-ICE SY	STEM WAS REPAIRED AND NEW FILTERS INSTALLED. BASED ON THE FINDINGS ON THIS A/C, ANOTHER DHC-7 WAS INSPECTED AND THE FILT	ERS APPEARED THE SAME. WE ARE LOOKING AT CHANGING THE FILTER INTERVAL.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001030500002	20010305	00002	SO  	2001	3	5	CA001228035      	1	20001130	G	2510	564877	HARNESS         			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					PILOT	FRAYED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			320  								(CAN) PILOTS SHOULDER HARNESS FRAYED.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001030500056	20010305	00056	NE  	2001	3	5	CA001229004      	2	20001004	G	8520		BEARING         	PWA         	R985AN14B   	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1161 		200097					(CAN) DURING 100 HOUR INSPECTION, 2 LARGE (1/4 X 3/18) PIECES WERE FOUND IN THE ENGINE SUMP. ONE CYLINDER WAS REMOVED AN	D A PIECE OF THE CONNECTING ROD BEARING WAS FOUND MISSING. THE ENGINE WAS REPLACED.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001022600096	20010226	00096		2001	2	26	CA001229006      	4	20001129	G	2562		CONTACTOR       	AMERIKING   	AK450       	PIPER 	J3    	J3C65       	7100510	SO  	CONT  	A65   	A658        	17003	SO  					ELT BATTERY	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						455056					(CAN) SOLDER CONNECTIONS ON SPRING STEEL BATTERY TERMINAL BREAK OFF.IT IS NOT POSSIBLE TO GET A GOOD SOLDER JOINT, TRYIN	G TO SOLDER TO STEEL. CONTACTED MANUFACTURER WHO HAS NO ANSWER EXCEPT TO RETURN TO FACTORY.					1	H	7	1 	3O	3	O	 	A691    	E205				 
2001022600097	20010226	00097	CE  	2001	2	26	CA001229011      	1	20001130	G	7120	05510171	MOUNT           	CONT        	O320E2D     	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5193 			L4361827A					(CAN) CRACK DEVELOPED IN CORNER WELD OF CROSS TUBE MEMBER.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001030500061	20010305	00061	CE  	2001	3	5	CA001229012      	1	20001204	G	2810	121640748	RESERVOIR       			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	FUEL SYSTEM	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) FOUND FUEL STAINING AROUND THE AFT FUEL INLET ON BOTH FUEL RESERVOIRS (FUEL ODOUR NOTICEABLE). REMOVED TANKS AND I	NSPECTED, FOUND VERY SMALL HAIRLINE CRACKS ON THE OUTER EDGE OF THE WELD. 16X MAGNIFYING GLASS HELPED TO IDENTIFY CRACK.					1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2001030100057	20010301	00057	EA  	2001	3	1	CA001229013      	2	20001205	G	8520	LW19173	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LOBE	WORN            	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA				1365 							(CAN) PILOTS REPORTED LOW FUEL FLOW ON RIGHT ENGINE.THE RIGHT ENGINE WAS INSPECTED AND ONE CAMSHAFT LOBE WAS FOUND DEFEC	TIVE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030100058	20010301	00058	NE  	2001	3	1	CA001229014      	2	20001207	G	7321	6078T55P13	O-RING          			CNDAIR	CL604 	CL604       	       	EA  	GE    	CF34  	CF343B1     	 	NE  					FUEL CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						WYG98157					(CAN) FUEL WAS FOUND POOLED IN LEFT HAND ENGINE COWLING DURING POST FLIGHT INSPECTION. ENGINE RUN CARRIED OUT FOR LEAK C	HECK PURPOSES AND FOUND FUEL STREAMING FROM MFC. MFC REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2001-01-03TC:  MANUFACTU	RE OF AIRCRAFT AND ENGINE HAS DISCUSSED SDR WITH TC.FAA AD PENDING, AND AIRWORTHINESS LIMITATION SECTION BEING REVISED I	N TYPE CERTIFICATE.  THIS OCCURRENCE IS ASSOCIATED WITH SDR 20010102009 AND 20010102010.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030500062	20010305	00062	EA  	2001	3	5	CA001229015      	1	20001202	G	2611	473052	SMOKE DETECTOR  			CNDAIR	CL600 	CL6002B19   	       	EA  										CARGO BAY	MALFUNCTIONED   	W				F	A	 	 	ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE CARGO SMOKE DETECTION CAME ON. EMERGENCY WAS DECLARED. EMERGENCY DESCENT WAS TAKEN AND BOTH FIR	E BOTTLES WERE DISCHARGED. LANDED WITHOUT FURTHER INCIDENT. REMOVED AND REPLACED BOTH FIRE BOTTLES AND SQUIBS PLUS REPLA	CED BOTH SMOKE DETECTORS. OPERATIONAL CHECKED GOOD, THE AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A21EA   					 
2001030500063	20010305	00063	EA  	2001	3	5	CA001229016      	1	20001202	G	2760		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  										SPOILER SYSTEM	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) ON TAKE OFF ROLL RECEIVED STALL FAIL CAUTION MESSAGE FOLLOWED BY CONFIG SPLRS WARNING MESSAGE AND CONFIG SPOILERS 	AURAL WARNING. ABORTED TAKEOFF AND MADE SECOND TAKEOFF ATTEMPT. SAME INDICATIONS. ABORTED SECOND TAKEOFF ATTEMPT. RESET 	SECU AND SPC MEMORY. CARRIED OUT TWO HIGH SPEED TAXIS AND A TEST FLIGHT WITH NO DISCREPANCIES.				2	L	7	2 	4F			RT	A21EA   					 
2001030500064	20010305	00064	EA  	2001	3	5	CA001229017      	1	20001202	G	2820	7366439	COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  										FUEL SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CENTRE TO MAIN FUEL TANK TRANSFER, R/H VALVE CLOSED AT 4450+/- 100 LBS, LEFT TANK FUELED TO 4900 LBS. COULD	 NOT BALANCE FUEL WEIGHT. RETURNED TO SLC.REPLACED FUEL SYSTEM COMPUTER IAW MM 28-41-26. OPS CHECK GOOD.					2	L	7	2 	4F			RT	A21EA   					 
2001030500065	20010305	00065	EA  	2001	3	5	CA001229018      	1	20001211	G	2742	83963	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										HORIZONTAL STAB	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	F	 	WARNING INDICATION        	FLT CONT AFFECTED         		TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF, THE STAB TRIM CHANNEL 1 DISCONNECTED IN FLIGHT. AIRCRAFT RETURNED NORMALLY TO THE AIRPORT.MAINTENA	NCE REMOVED AND REPLACED THE HORIZONTAL STAB TRIM ACTUATOR.					2	L	7	2 	4F			RT	A21EA   					 
2001030500066	20010305	00066	EA  	2001	3	5	CA001229019      	1	20001211	G	2752	853D10012	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										RT FLAP	EXCESS PLAY     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			AP	APPROACH       	1			CA						0818					(CAN) UNUSUAL NOISE (THUMPING SOUND) BETWEEN FLAPS 30 AND 40 DEGREES DURING FINAL APPROACH. MAINTENANCE REPLACED THE R/H	 NR3 FLAP ACTUATOR, DUE TO EXCESSIVE PLAY.					2	L	7	2 	4F			RT	A21EA   					 
2001030500067	20010305	00067	EA  	2001	3	5	CA001229020      	1	20001211	G	2750	855D1009	BPSU            			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAP	FAILED          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						1367B					(CAN) AFTER THE LANDING, THE CREW SELECTED THE FLAPS AT 20 DEGREES, THE FLAP FAIL CAUTION MESSAGE WAS DISPLAYED AND THE 	FLAPS STOPPED AT 24 DEGREES.THE MAINTENANCE INTERROGATED THE FECU WHICH WS POINTING TO THE L/H BPSU WHICH WAS REPLACED (	P/N 844D100-9, S/N:1367B). DURING THE RIGGING THEY FOUND THE FLEXSHAFT BETWEEN THE NR3 & NR4 ACTUATORS SHEARED AT THE NR	4 ACTUATOR LOCATION, IT WAS THEN REPLACED (P/N 1104SD100-40, S/N:3513). AFTER THE REPLACEMENT OF THE FLEXSHAFT, A GRIND 	NOISE WAS HEARD COMING FROM THE NR4 R/H ACTUATOR WHICH WAS THEN REPLACED (P/N 854D100-12, S/N:1170AB).		2	L	7	2 	4F			RT	A21EA   					 
2001030500068	20010305	00068		2001	3	5	CA001229021      	4	20001211	G	3417	8220372140	ADC             			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE NR1 ADC FAILED IN FLIGHT.NR1 ADC REPLACED, AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F			RT	A21EA   					 
2001030100059	20010301	00059	EA  	2001	3	1	CA001229022      	1	20001211	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			2468 								(CAN) COPILOT WINDSHIELD SHATTERED IN FLIGHT AT 15500 FEET AND 290 KTS. MAINTENANCE REPLACED THE WINDSHIELD, AIRCRAFT RE	TURNED TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001030100060	20010301	00060	EA  	2001	3	1	CA001229023      	1	20001211	G	2410		STATOR          	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ALTERNATOR	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAIN REPORTED A LEFT ENGINE N2 FLUCTUATION AT CRUISE BETWEEN 88.2 AND 97.6.FOLLOWING SEVERAL PROCEDURES AND PAR	T CHANGES (ADJUSTMENT OF IDLE SPEED, VG FEEDBACK, REPLACEMENT OF FCU & OF T2C SENSOR), THE AIRCRAFT WAS FERRY TO THE MAI	N BASE. THE MAINTENANCE THEN REPLACED THE ALTERNATOR STATOR AND ROTOR (STATOR S/N GJAHJ368 AND ROTOR S/N GJAK1576). AIRC	RAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030500069	20010305	00069	EA  	2001	3	5	CA001229024      	1	20001211	G	7830		ACTUATOR        	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LT&RT T/R	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) THE L REV UNLOCKED MESSAGE POSTED AFTER TAKEOFF. NO OTHER INDICATION OF T/R DEPLOYMENT. THE MAINTENANCE REPLACE TH	E LEFT T/R POWER DRIVE UNIT, AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030500070	20010305	00070	EA  	2001	3	5	CA010102002      	1	20001206	G	2611		SMOKE DETECTOR  			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LAVATORY	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) THE CREW REPORTED A SMOKE TOILET CAUTION MESSAGE DURING CRUISE. THE MAINTENANCE DID AN INSPECTION AND FOUND NO EVI	DENCE OF BURNING SMELL. THEY REPLACE THE SMOKE DETECTOR AFTER THEY FERRIED THE A/C TO THE MAIN BASE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030500071	20010305	00071	EA  	2001	3	5	CA010102003      	1	20001207	G	3080		DETECTOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										ICE DETECTION	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) THE CREW REPORTED A ICE CAUTION MESSAGE ON TAKEOFF ROLL AT OVER 100 KTS. THEY ABORTED THE TAKEOFF AND RETURNED TO 	BLOCKS. THE MAINTENANCE CREW CLEANED THE ICE DETECTION PROBES AND CARRIED OUT A TEST OF THE SYSTEM, NO FAULTS FOUND. A/C	 WAS FERRIED TO THE MAIN BASE AND RETURNED TO SERVICE WITH NFF.				2	L	7	2 	4F			RT	A21EA   					 
2001030500072	20010305	00072	EA  	2001	3	5	CA010102004      	1	20001206	G	3234	7455021	CONTROL HANDLE  			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) THE CREW REPORTED THAT DURING CLIMB, THE GEAR HANDLE WAS SELECTED TO THE UP POSITION, THE GEAR REMAINED DOWN AND A	 EICAS ANTI-SKID MESSAGE CAME ON. THE MAINTENANCE REPLACE THE L/G HANDLE, A/C WAS RETURNED TO SERVICE AFTER THE TEST.					2	L	7	2 	4F			RT	A21EA   					 
2001030500073	20010305	00073	EA  	2001	3	5	CA010102005      	1	20001206	G	5270		SENSOR          	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					DOOR WARNING	DIRTY           	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA						7107					(CAN) THE CREW REPORTED THAT DURING CLIMB, AT 7000 FT, A PASSENGER DOOR CAUTION MESSAGE (NOT SPECIFIED) CAME ON. AT 1100	0 FT, THE PASSENGER DOOR WARNING MESSAGE CAME ON. THE MAINTENANCE INTERROGATED THE PSEU, FOUND S76 AND S27 AT FAULTY. TH	E SENSORS WERE CLEANED AND THEY PRESSURIZED THE A/C TO 2.5 PSI, AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030500074	20010305	00074	EA  	2001	3	5	CA010102006      	1	20001204	G	5751		AILERON         	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  										RT WING	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						7335					(CAN) ON THE RAMP IN ATL, NOTICED THAT THE RIGHT AILERON LOWER SURFACE LEADING EDGE HAD CONTACTED THE WING LOWER SKIN TR	AILING EDGE, CAUSING DAMAGE TO THE AILERON LOWER ACCESS PANELS AND WING TRAILING EDGE SKIN REMOVABLE PANEL. IT SHOULD BE	 NOTED HERE THAT NO REPORT WAS MADE OF OPERATIONAL PROBLEMS WITH THE RIGHT AILERON. MAINTENANCE PERSONNEL REPORTED AILER	ON OPERATED PROPERLY. THE FOLLOWING PARTS WERE DAMAGED ON THE RIGHT AILERON:601R13031-156 LOWER ACCESS PANEL (INBD) 601R	13031-154 LOWER ACCESS PANEL (CTR)LOWER SKIN INBD  SRM 57-60-00 FIG 1, ITEM 48RIBS SRM 57-50-00 FIG 1, ITEMS 54, 57 PLAT	ESSRM 57-60-00 FIG 1, ITEMS 53, 55THE FOLLOWING PART DAMAGED ON WING TRAILING EDGE: 601R102	2	L	7	2 	4F			RT	A21EA   					 
2001030100061	20010301	00061	NE  	2001	3	1	CA010102007      	2	20001206	G	7210		GEARBOX         	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA						872311					(CAN) THE CREW REPORTED THAT DURING CLIMB, THE RT ENGINE WAS LOST. THE CREW DECLARED EMERGENCY PROCEDURES, THEY LANDED W	ITHOUT FURTHER INCIDENT. THE MAINTENANCE REPORTED GEARBOX FAILURE. RT ENGINE WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030100062	20010301	00062	NE  	2001	3	1	CA010102009      	2	20001207	G	7321	6078T55P13	O-RING          	WOODWARD    	6078T55P13  	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					THROTTLE BODY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3265 	2541 		WYG98661					(CAN) THE MAINTENANCE WAS DOING AN ENGINE RUN WHEN THEY NOTICED A FUEL LEAK THROUGH THE LT CORE COWL DRAIN.THE MAINTENAN	CE OPENED THE LOWER CORE COWL AND THEY FOUND THAT THE FUEL WAS LEAKING THROUGH THE LT MFC THROTTLE SHAFT BODY WITH THE S	TANDBY FUEL PUMPS ON. THE MFC WAS REPLACED. 2001-01-03TC:  MANUFACTURE OF AIRCRAFT AND ENGINE HAS DISCUSSED SDR WITH TC.	FAA ASB PENDING, AND AIRWORTHINESS LIMITATION SECTION BEING REVISED IN TYPE CERTIFICATE.THIS OCCURRENCE IS ASSOCIATED WI	TH SDR 20010102009		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030100063	20010301	00063	NE  	2001	3	1	CA010102010      	2	20001204	G	7420		HARNESS         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	ARCED           	W				A				UNSCHED LANDING         				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE CREW REPORTED HIGH RT N1 VIBRATION, THE FLIGHT CREW DECIDED TO RETURN TO THE BASE.THE MAINTENAN	CE FOUND THE RED ENGINE HARNESS, THE IDG CABLES, THE THERMOCOUPLE HARNESS AND THE RT LOWER CORE COWL WITH BURNT MARKS. T	HEY FOUND THE IDG CABLE SHROUD SOAKED WITH FUEL. THE FUEL LEAK PASSING BY THE  RT MFC THROTTLE SHAFT BODY. THEY REPLACED	 THE RT ENGINE. 2001-01-03TC:  MANUFACTURE OF AIRCRAFT AND ENGINE HAS DISCUSSED SDR WITH TC.FAA ASB PENDING, AND AIRWORT	HINESS LIMITATION SECTION BEING REVISED IN TYPE CERTIFICATE.THIS OCCURRENCE IS ASSOCIATED WITH SDR 20010102009		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030100064	20010301	00064	WP  	2001	3	1	CA010103002      	1	20001204	G	6220	C1541	HUB             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	WORN            	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			1062 								(CAN) AFTER NOTICING A RAPID INCREASE IN VIBRATION WE TRIED TO DYNAMICALLY BALANCE THE MAIN ROTOR. SINCE WE WERE UNABLE 	TO BE WITHIN RECEPTACLE LIMITS, WE REMOVED THE MAIN ROTOR HEAD AND ROTOR BLADES FOR FURTHER INSPECTION. WE FOUND THE HUB	 HOLE ENLARGED, THE JOURNAL BUSHINGS C-106 WERE WORN BEYOND LIMITS, AND THE BEARING C648-1 WAS OVAL IN SHAPE AND COMPLET	ELY WORN ON ONE SIDE BY APPROXIMATELY 0.200.THE ROTOR HEAD HAS BEEN REMOVED AND SHIPPED TO ROBINSON HELICOPTER CO. FOR O	VERHAUL OR PROBABLE REPLACEMENT.THE PROBABLE CAUSE APPEARS TO BE A PREMATURE WEAR WHICH WAS AGGRAVATED WITH SUBSEQUENT F	LIGHTS.	1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001030100066	20010301	00066	SO  	2001	3	1	CA010103005      	1	20001202	G	5347	1023173	BRACKET         	GRUMAV      	16102304503 	AMRGEN	AA1   	AA1B        	0631206	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	PILOT SEAT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1480 								(CAN)  PILOT SEAT TILLED TO LEFT. FOUND FORWARD OUTBOARD ATTACH FLANGE BROKE AWAY FROM THE BRACKET.NEW BRACKET INSTALLED	.					1	L	7	1 	3O	3	O	 	A11EA   	E274	5	N	P88614	 
2001030500078	20010305	00078	NE  	2001	3	5	CA010103009      	2	20001124	G	7250	EU18671	TURBINE         	RROYCE      	TAY65015    						RROYCE	TAY   	TAY65015    	54557	NE  					ENGINE	DAMAGED         	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA			21214	10355		17339					(CAN) U.S. AIRWAYS ESN 17339 WAS REMOVED FOR HIGH VIBRATION UPON STRIP. THE FOLLOWING WAS NOTED.1. HP TURBINE MIGRATED A	XIALLY REARWARDS TO THE EXTENT THE HP1 TURBINE BLADE INNER PLATFORM REAR FACES CONTACTED THE HP2 NGV INNER PLATFORM FRON	T FACES.2. THE ASSOCAITED LOCKING COUPLING SPLINES SHOW EVIDENCE OF WEAR TO A DEPTH OF 0.004.3. THE HPC SHAFT SPHERICAL 	COUPLING LOCKING TANGS ARE HEAVILY WORN SUCH THAT THE CIRCUMFERENTIAL WIDTH OF THE TANGS HAS BEEN REDUCED TO 0.110 WIDE 	AGAINST A WIDTH OF 0.165 IN THE UNWORN AREARS. 4. THERE HAVE BEEN NO OTHER FINDINGS MADE SO FAR THAT WOULD EXPLAIN THE  	REARWARD AXIAL MOVEMENT.						4	F			E25NE				 
2001011106357	20010111	06357	GL  	2001	1	11	CA010103010      	2	20001127	G	7323	6870035	B-NUT           	BENDIX      	23057869    	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					LINE	LOOSE           	W				E				ENGINE SHUTDOWN         				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TX	TAXI/GRND HDL  	1			CA			4642 			84250036					(CAN) ENGINE HUNG START AT 38 PERCENT N1 GOVERNOR PC AIR TUBE FITTING "B" NUT FOUND LOOSE.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001030500079	20010305	00079		2001	3	5	CA010103011      	4	20001121	G	2312	JJ034	RECEPTACLE      			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					COCKPIT	SHORTED         	W				A		 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) FOLLOWING TAKEOFF NR1 AND NR2 V.H.F. UNABLE TO TRANSMIT OR RECEIVE. AIRCRAFT LANDED AT AIRPORT. CAPTAINS MICROPHON	E JACK REPLACED. SYSTEMS TESTED SERVICEABLE. AIRCRAFT RELEASED FOR FLIGHT WITH NO FURTHER REPORT.					2	L	7	2 	4R	4	T	 	6A6     	E282				 
2001030500081	20010305	00081	GL  	2001	3	5	CA010103014      	3	20001207	G	6114	C7036	NUT             													MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	DAMAGED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			446  	446  							(CAN) CRACK FOUND ON TREADS AREA. 2001-01-09TC: REFERENCE AD 95-24-05 R1 MCCAULEY ACCESSORY DIVISION,																5	C	P22EA	 
2001030500082	20010305	00082	NE  	2001	3	5	CA010103015      	3	20001207	G	6114	97722	SUPPORT BRACKET 	HAMSTD      	43E60581    											HAMSTD	43E	43E60       	NE  	PROPELLER	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			2689 	1130 		206010					(CAN) BARREL SUPPORT WAS FOUND CRACKED, SEPARATED IN TWO PIECES.																6	C	P871	 
2001030500083	20010305	00083	NE  	2001	3	5	CA010103016      	3	20001018	G	6114	97722	SUPPORT BRACKET 	HAMSTD      	43E60581    											HAMSTD	43E	43E60       	NE  	PROPELLER	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			3737 	2329 		206025					(CAN) BARREL SUPPORT FOUND COMPLETELY CRACKED (IN TWO PIECES).																6	C	P871	 
2001030500084	20010305	00084	NM  	2001	3	5	CA010103018      	1	20001125	G	7600	40025001	CONTROL VALVE   			BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					NR 1 ENGINE	STUCK           	W				D	 	 	 	RETURN TO BLOCK         				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			1146 								(CAN) AFTER LANDING, PILOT REPORTED THAT NR 1 ENGINE THROTTLE WAS JAMMED AT IDLE. FOUND NR 1 DCV (DIRECTIONAL CONTROL VA	LVE) STUCKED IN EXTEND POSITION. DCV WAS REPLACED AND THROTTLE WAS SERVICE.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001030500086	20010305	00086	WP  	2001	3	5	CA010103020      	1	20001127	G	5754	1615157103	PANEL           			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					LT LE SLAT	MISSING         	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) ACFT ARRIVED TO WITH L/H LE SLAT ACCESS PANEL MISSING. AREA INSPECTED, NEW PANEL INSTALLED.FEW SCREWS FOUND LOOSE 	ON THIS PANEL, WHICH MADE THE PANEL TO DROP ENOUGH FOR THE PIN TO COME OUT. DUE TO VIBRATION THE LE PANEL CAME LOOSE DUR	ING FLIGHT AND DETACHED.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001030500087	20010305	00087	NM  	2001	3	5	CA010103021      	1	20001129	G	2120	LJ76554	EXPANSION RING  			BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					AIR DISTRIBUTION	LEAKING         	W				O	 	 	 	OTHER                   				M	J	 	OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) HP 6 EXPANSION DUCT LEAK CAUSING BURNS TO DIFFERENT COMPONENTS IN THE AREA (NR 1 PYLON). THE MAJOR COMPONENT THAT 	WAS AFFECED IS THE C DUCT RT SIDE THE FWD UPPER CORNER IS DELAMINATED AND REQUIRED REPAIR MANY OTHER PARTS HAD DAMAGES A	ND NEEDED REPLACEMENT AND A LIST IS ATTACHED. WE ALSO HAD TO REPAIR A WIRE HARNESS THAT RUN IN THIS AREA.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001030500089	20010305	00089	CE  	2001	3	5	CA010104006      	1	20001127	G	5347	05112405	SEAT TRACK      			CESSNA	172   	172L        	2072432	CE  										FUSELAGE	MISMANUFACTURED 	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) NEW CESSNA SEAT RAIL, HOLE DOUBLE DRILLED MAKING SEAT RAIL GARBAGE. EXAMPLE OF VERY POOR QA ON PART OF MANUFACTURE	.					1	H	7	1 	3O			NT	3A12    					 
2001030500090	20010305	00090	NM  	2001	3	5	CA010105002      	1	20001211	G	2133	20473124	SPUR GEAR       	ALIDSG      	22048013    	BOEING	767   	76735H      	1385208	NM  										ACTUATOR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			36011			24348					(CAN) REMOVED ACTUATOR FROM A/C DUE REPEAT PIREP. SHOP INSPECTION FOUND SPUR GEAR SPLINE HAD A SEGMENT MISSING. THIS MIS	SING SEGMENT HAD BEEN REPLACED BY A ROLL PIN LAID IN THE OPEN AREA OF THE SPLINE. NO APPROVED REPAIR ALLOWS THE USE OF R	OLL PINS IN REPAIRS TO THE SPUR GEAR. REPAIR WAS DETERMINED TO BE ILLEGAL.				2	L	7	2 	4F			RT	A1NM    					 
2001030500091	20010305	00091	NM  	2001	3	5	CA010105003      	1	20001227	G	7711	LG80A6	TRANSMITTER     			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					EPR	FAILED          	W				A		 	 	UNSCHED LANDING         				L	 	 	NO TEST                   			CL	CLIMB          	1			CA			41564	41560							(CAN) EPR INDICATION UNSERVICEABLE. REPLACED INDICATOR AND TRANSMITTER. A/C RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030100071	20010301	00071	NM  	2001	3	1	CA010105004      	1	20001222	G	2730	2827001009	CONTROL UNIT    			BOEING	767   	7673Y0      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					ELEVATOR	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE, FL350, CENTER HYDRAULIC QUANTITY EICAS WARNING ILLUMINATED. HYDRAULIC QUANTITY ON STATUS PAGE INDIC	ATED IT WAS 0.40. CENTER HYDRAULIC PUMPS WERE SHUTDOWN FOR REMAINDER OF FLIGHT. YVR ATC ADVISED AND AN EMERGENCY WAS DEC	LARED. LANDED AT YVR WITHOUT INCIDENT. HYDRAULIC LEAK DETECTED AT LT CENTER ELEVATOR PCA. REPLACED LT CENTER PCA, SYSTEM	 CHECKED SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001011100073	20010111	00073	EU  	2001	1	11	CA010105008      	1	20001214	G	4900		APU             			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					APU BAY	FAULTY          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) A/C 415, DEC 14/2000, FLT 3598, YEG, LOG SEQUENCE 0291486. ON TAKEOFF FROM YEG, AFT CARGO SMOKE ECAM MESSAGE APPEA	RED & A BURNING SMELL NOTICED IN CABIN & COCKPIT. EMERGENCY DECLARED & A/C RETURNED TO YEG. CFR DID A VISUAL INSP AFTER 	LDG, NO EVIDENCE OF SMOKE OR FLAMES., AT GATE CARGO HOLD WAS CHECKED, NO PROBLEMS FOUND. OVERWEIGHT LDG CHECK COMPLETED 	AS PER FLYAWAY MANUAL 02-02-06 P.S 1 THROUGH 38. INSP APU FOR OIL LEAKS & CONTAMINATION AS PER TSM 40-00-00-810-846. CLE	ANED INLET SCREEN OVER IGV. NO LEAKS OR CONTAMINATION FOUND. REPLACED CARGO BAY FIRE BOTTLES AS PER WORK CARD 26904. CAR	GO BAY SMOKE DETECTION OP CHECK COMPLETED AS PER WORK CARD 26100.	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001030500006	20010305	00006	NE  	2001	3	5	CA010108019      	1	20001206	G	6220	S611520502042	HUB             	SKRSKY      	S61152050104	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					BLADE POCKET	TORN            	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			8401 			61M68106529					(CAN) DURING SHUTDOWN PILOTS NOTICED A WHISTLING SOUND COMING FROM MAIN ROTOR BLADES. DURING A VISUAL INSPECTION AFTER R	OTORS HAD STOPPED A POCKET LOWER SKIN WAS SEEN TO BE MISSING. ROTOR BLADE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERV	ICE.				2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001030500007	20010305	00007	WP  	2001	3	5	CA010108021      	1	20001108	G	6210	500P2100101	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1984 								(CAN) M/R BLADE P/N 500P2100-101 S/N A204 WS INSPECTED I.A.W. THE MANUFACTURERS RECOMMENDATIONS AND HELICOPTER TECHNOLOG	Y CORP SB 2100-2 INSPECTION OF M/R BLADE FOR DEBONDING. THE M/R BLADE WAS INSTALLED ON THE A/C AND A SERIES OF FLIGHTS W	ERE CONDUCTED FOR TRACK AND BALANCE. UPON COMPLETION AND DURING FINAL SAFETY OF THE M/R PITCH CONTROL LINKS AND DAMPERS 	AFFECTED, IT WAS NOTED THE TRAILING EDGE OF THE BLADE CLOSEST TO THE ROOT VISUALLY APPEARED TO BE OPEN. FURTHER INSPECTI	ON BY PRYING OR PROBING WITH FINGERS REVEALED THE BONDING OF THE TRAILING EDGE WAS NOT HOLDING AND WAS EASILY SEPARATED 	BY LIGHTLY PRYING.	1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001030500008	20010305	00008	SO  	2001	3	5	CA010108022      	1	20001207	G	2410	37A19773382	BELT            	PRESTOLITE  	RLU8421R    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ALTERNATOR	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			811  			N000002					(CAN) ON DAY OF INCID. A/C SAT ON GROUND, PILOTS RPORT APPROX. 10 MIN WAITING FOR TAKEOFF CLEARANCE, ENGINE AT 1000-1200	 RPM, RADIOS ON, ALL LIGHTS ON TAKEOFF, EVERYTHING NORMAL, VOLTAGE REGULATOR INDICATING IN GREEN ARC 24-28 VO LTS TEN MI	NS OUT PILOTS EXPERIENCED RADIO COMMUNICATION PROBLEMS&FAILURE OF AUTO PILOT WHILE TRYING TO ISOLATE PROBLEM, VOLTAGE GA	GE ANNUNCIATOR PANEL THAT ONE OF ALTNR INOPERATIVE. THEY CONTACTED CNTL TOWER BYCELL PHONE&RETURNED TO AIRPORT. COCKPIT 	LIGHTS WERE DIM. UPON INSP L/H ENGINE ALTNR BELT FOUND BROKEN OFF&R/H BELT SHOWED SIGNS OF SLIPPING. L/H BELT&ALTNR REPL	. R/H BELT TIGHTENED. A/C GROUN D RUN, ALL SYSS CHECKED OUT OK, NO PROBLEM WAS	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030500106	20010305	00106	CE  	2001	3	5	CA010108024      	1	20001219	G	5230	12116895	ROD             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	CARGO DOOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT CARGO DOOR RIGGING ROD LOWER FOUND BROKEN IN THREADED PORTION OF ROD. FURTHER INVESTIGATION ALSO FOUND THE LOW	ER DOOR LATCH HOOK CLEVIS PIN, WORN EXCESSIVELY.I WOULD RECOMMEND THAT THE DOOR OPERATING MECHANISM BE INSPECTED ANNUALL	Y.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2001030500108	20010305	00108	WP  	2001	3	5	CA010110006      	1	20001213	G	6510	NAS62045	BOLT            		369D255013  	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING COUPLING REPLACEMENT (BENDIX TO KAMATIC), IT WAS NOTED THAT THE TAIL ROTOR DRIVESHAFT TO COUPLING BOLTS WER	E TOO LONG AND IF ALLOWED TO REMAIN IN SERVICE WOULD CONTACT THE COUPLING WEB AND SET UP STRESS RISES.THE BOLTS CALLED O	UT IN THE IPC ARE THE SAME FOR EITHER COUPLING. THE INSTALLATION INSTRUCTIONS DO NOT MENTION CHANGING THE BOLTS TO PREVE	NT THIS FROM HAPPENING.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001030500011	20010305	00011	WP  	2001	3	5	CA010110007      	1	20001213	G	6510	369A5516	SHIM            		369D255013  	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TAIL ROTOR GEARBOX REPLACEMENT, IT WAS NOTED THAT THE TORQUE WAS LOST ON THE KAMATIC COUPLING BOLT. FURTHER	 INVESTIGATION REVEALED THE SHIMS BETWEEN COUPLING AND TAIL ROTOR GEARBOX WERE FOUND SPLIT DUE TO COUPLING BOLT TORQUE. 	MAINTENANCE MANUAL INSTRUCTIONS FOR INSTALLATION OF KAMATIC COUPLINGS CALL FOR ALL SHIMMING TO BE DONE AT THE MAIN ROTOR	 TRANSMISSION. HOWEVER FIGURES IN THE MAINTENANCE MANUAL SHOW SHIMS UNDER TAIL ROTOR GEARBOX COUPLING.OPERATOR HAS CHECK	ED ALL 8 LIKE AIRCRAFT AND REMOVED ANY SHIMS FROM AFT COUPLING AND INSTALLED ON FORWARD COUPLINGS.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001030500109	20010305	00109	WP  	2001	3	5	CA010110008      	2	20001211	G	7260	M274263116A	RETAINER        	GARRETTLTD  	30700934    	BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HORIZ DRV SHAFT	BROKEN          	W				O	 	 	 	OTHER                   				Y	 	 	ENGINE STOPPAGE           			IN	INSP/MAINT     	1			CA						P7387					(CAN) RIGHT HAND ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN AFTER START. HORIZONTAL DRIVESHAFT FOUND UNCOUPLED FROM TRAN	SFER GEARBOX DUE TO BROKEN RETAINING RING P/N M27426-3116A.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001030500012	20010305	00012	EA  	2001	3	5	CA010110009      	2	20001215	G	8550		ENGINE          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					RIGHT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) ON CLIMB OUT FROM YXD, THE PILOTS NOTICED FLAMES FROM INSIDE THE ENGINE COWL ACCESS DOOR ON RT ENGINE. FOLLOWING F	LIGHT MANUAL PROCEDURES, THEY THEN SHUT DOWN THE ENGINE AND FEATHERED THE PROPELLER. THEY THEN MADE AN UNSCHEDULED LANDI	NG  IN YEG WHERE MAINTENANCE HAD A LOOK AT THE ENGINE. THE BURNT REMAINS OF, WHAT IS THOUGHT TO BE, A SHOP RAG WAS FOUND	 IN THE AFT OF THE ENGINE COWL. THE REMAINS WERE REMOVED, THE ENGINE INSPECTED FOR FIRE DAMAGE, AND THE AIRCRAFT RETURNE	D TO SERVICE.THERE WAS NO FIRE DAMAGE NOTED AT TIME OF INSPECTION.		1	L	7	2 	3O	3	O		A20SO   	E14EA				 
2001030500013	20010305	00013	CE  	2001	3	5	CA010110012      	1	20001204	G	5520	11561001422	STRUCTURE       			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13041								(CAN) ON INSPECTION A SMALL CRACKED WAS NOTICED STARTING FROM THE ONE OF THREE BOLT HOLES ON THE HORN ASSEMBLY. A NEW R/	H HORN ASSEMBLY WAS INSTALLED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001030500111	20010305	00111	SW  	2001	3	5	CA010110014      	1	20001212	G	6210	AN412A	BOLT            	BELL        	206010200133	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						A5007					(CAN) INBOARD LATERAL BALANCE WEIGHTS LOOSE. INBOARD BOLT P/N AN4-12A WAS TOO LONG FOR THE AMOUNT BALANCE WEIGHTS INSTAL	LED. WE CONTACTED PRODUCT SUPPORT AND THEY SAID TO INSTALL A SHORTER AN4 BOLT. WE INSTALLED AN AN4-11A BOLT.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001030500015	20010305	00015	EA  	2001	3	5	CA010110017      	2	20001201	G	8520		BEARING         	LYC         	TIO540AE2A  	PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			176  			L1012561A					(CAN) DURING A SCHEDULED OIL/FILTER CHANGE, METAL PARTICLES WERE FOUND IN THE ENGINE OIL SCREEN. IN REFERENCE TO PIPER V	SP-127 AND TEXTRON LYCOMINGS SPECIAL ADVISORY 59-800, SAMPLE WAS SENT TO TEXTRON FOR ANALYSIS. AS PER THE SERVICE ADVISO	RY THE AIRCRAFT WAS GROUNDED. TEXTRON REPORTED THEIR FINDINGS TO BE THAT THE CONTAMINATION WAS ALUMINUM WITH 5% IN CONTE	NT FROM THE BEARING INSERTS. ENGINE WAS REMOVED AT THEIR INSTRUCTION AND SENT TO THE FACTORY FOR WARRANTY REPAIR.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001030500017	20010305	00017	CE  	2001	3	5	CA010110021      	1	20001220	G	2822	503801775	PUMP            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUEL BOOST	FAILED          	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			CR	CRUISE         	1			CA				91   							(CAN) LEVEL AT FL220. FUEL BOOST PUMP LITEON AIRCRAFT RETURNED WINNIPEG. PUMP REPLACED.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2001030500018	20010305	00018	CE  	2001	3	5	CA010110022      	1	20001218	G	7721		CYLINDER        			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				2413 							(CAN) ON INSPECTION FOUND 3 SHEARED STUDS ON TOP 4 SHEARED STUDS ON THE BOTTOM OF NR 1 CYLINDER/CYLINDER WAS COCKED TO T	HE REAR AT A SLANT AT 10 DEGREES.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001030500019	20010305	00019	SW  	2001	3	5	CA010110023      	1	20001222	G	2913		GEAR            	PARKERHANFIN	206076022101	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					HYD PUMP	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA						BD1070					(CAN) BURR ON GEAR FACE CAUSED DAMAGE TO THE BEARING.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001030500022	20010305	00022	EU  	2001	3	5	CA010111004      	1	20001211	G	3340	9728787321R	LIGHT           			PILATS	PC12  	PC1245      	       	EU  										WING TIP STROBE	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA			835  								(CAN) RT WING TIP STROBE LIGHT FOUND INOP DURING DAILY INSPECTOIN. REPLACED WITH NEW, TESTED.						1	L	7	1 	3T			RT	A78EU   					 
2001030600029	20010306	00029	EA  	2001	3	6	CA010111021      	1	20000812	G	7921	10528A	OIL COOLER      			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT ENGINE	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				5394 		79K62					(CAN) IT WAS OBSERVED BY THE ENGINEER THAT THE LEFT ENGINE COWLING AFT OF THE OIL COOLER AIR EXHAUST WAS COVER WITH OIL.	 THE OIL COOLER WAS PRESSURE TESTED, HOWEVER, A VISUAL LEAK WAS NOT DETECTABLE. THE OIL COOLER WAS REPLACED AND THE OIL 	ON THE COWLING HAS NOT APPEARED SINCE.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2001030600025	20010306	00025	NE  	2001	3	6	CA010111025      	2	20001208	G	7200		ENGINE          	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				E	 	 	 	ENGINE SHUTDOWN         				B	E	 	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		DE	DESCENT        	1			CA			25473			120051					(CAN) DURING DESCENT SMOKE REPORTED IN CABIN. CREW NOTICED NR2 ENGINE ITT SPIKING ALSO NOTED VIBRATION AND SPUTTERING NO	ISE. ENGINE SHUT DOWN, EMERGENCY DECLARED. A/C LANDED WITHOUT INCIDENT. INSPECTION FOUND METAL IN JET PIPE AND METAL PAR	TICLES ON CHIP DETECTOR. ENGINE NR2 REPLACED, GROUND RUN AND LEAK CHECK SATISFACTORY, A/C RETURNED TO SERVICE.FURTHER TO	 INITIAL REPORT: FURTHER INVESTIGATION ON TEAR DOWN REPORT SHOWED THAT NR5 BEARING WAS DESTROYED DUE TO OIL NOZZLE LAST 	CHANGE SCREEN COMING ADRIFT AND DESTROYING THE BEARINGS. THE SCREEN WAS CONTAMINATED WITH DEBRIS LEFT OVER FROM A RECENT	 REFURBISHMENT.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001030600035	20010306	00035	CE  	2001	3	6	CA010112007      	1	20001221	G	7810	32023	EXHAUST PIPE    			CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470J       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						83772					(CAN) ON INSPECTION FOUND PART TO BE CRACKED AT CENTRE OF LOWER SEAM APPROXIMATELY TWO INCHES. PART SENT FOR REPAIR.						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P3EA	 
2001030600037	20010306	00037	WP  	2001	3	6	CA010112013      	1	20001205	G	5552	240201090014	HINGE FITTING   	CVAC        	STC340CVAC  	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13      	03004	GL  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						154					(CAN) DURING INSPECTION MAINTENANCE FOUND R/H MID ELEVATOR HINGE FITTING CRACKED. FITTING REPLACED.						2	L	7	2 	4R	4	T	 	6A6     	E282				 
2001030600038	20010306	00038	SO  	2001	3	6	CA010112015      	1	20001229	G	5520	4007600	STRUCTURE       	PIPER       	5423235     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7011 			311049					(CAN) UNDER EACH HINGE BRACKET P/N 40042-09 (CENTRE) AND P/N 40042-08 (INBOARD) APPROXIMATELY 1 INCH CRACKS REINFORCING 	PLATE INSTALLED AFTER STOP DRILLING RE AC43 13-1B, FIGURE 4-21, PAGE 4-42.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030600039	20010306	00039	NM  	2001	3	6	CA010112016      	1	20001027	G	2761	A44700007	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	SPOILER	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA			22017			0951					(CAN) A REPORTED HYDRAULIC LEAK WAS FOUND TO BE CAUSED BY A CRACKED ROLL SPOILER BODY. UNIT REPLACED WITH NEW ACTUATOR A	ND AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001030600040	20010306	00040	EU  	2001	3	6	CA010112017      	1	20001208	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										T/R HUB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1863 			6910					(CAN) 40 MM CRACK ON TRAILING EDGE TOP AND BOTTOM SURFACE ORIGINATING UNDER TRIM TAB. SEE ATTACHED PHOTO WITH TRIM TAB R	EMOVED. TC COMMENTS: THIS PARTICULAR BLADE HAS A 4000 HOUR LIFE AND WAS FOUND WITH CRACK AT 1862.8 HOURS TSN. ORIGINATOR	 REPORTS THAT THIS IS FIRST TIME FOR CRACKS FOUND IN THIS AREA UNDER TE TRIM TAB.				1	G	7	1 	3U			 	H9EU    					 
2001030600041	20010306	00041	EU  	2001	3	6	CA010112018      	1	20001208	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R HUB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2756 			6815					(CAN) 15 MM CRACK ON TRAILING EDGE ON UPPER AND LOWER SURFACE ORIGINATING UNDER TRIM TAB. SEE ATTACHED PHOTO WITH TRIM T	AB REMOVED. NOT DETECTED UNTIL TRIM TAB REMOVED FOR ANOTHER REASON. TC COMMENTS: THIS PARTICULAR BLADE HAS A LIFE OF 400	0 HOURS BUT WAS FOUND CRACKED AT 2756.3 HOURS. THIS IS SECOND TIME ORIGINATOR HAS FOUND A CRACK  IN THIS AREA AT TE TRIM	 TAB (SEE SDR 20010112017).			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001030600042	20010306	00042	CE  	2001	3	6	CA010115003      	1	20001209	G	5270		WARNING SYSTEM  			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					INSTRUMENT PANEL	ACTIVATED       	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) PASSENGER DOOR OUTER HANDLE CAUTION AT 8000 FEET, QUICK REFERENCE HANDBOOK PROCEDURE CARRIED OUT, UNSUCCESSFULLY, 	THEN RED WARNING DOOR MESSAGE CAME ON.PASSENGER DOOR RIGGING CARRIED OUT.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001030600043	20010306	00043	NM  	2001	3	6	CA010115004      	1	20001208	G	2710	550030019	ACTUATOR        			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					RT AILERON	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON LOCKOUT IN CRUISE/LANDING/GATE.FOUND CIRCUIT BREAKER POPPED, RIGHT AND LEFT AILERON RESET, CARRIED OUT TES	T. SPOILER AILERON MODULE FAULTED RIGHT HAND AILERON LOCKOUT. CIRCUIT BREAKER POPPED AGAIN. CHANGED RIGHT HAND AILERON L	OCKOUT ACTUATOR.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030600044	20010306	00044	EU  	2001	3	6	CA010115007      	1	20001123	G	2750		WARNING SYSTEM  	AIRBUS      	A340313     	AIRBUS	A340  	A340313     	       	EU  										COCKPIT	ACTIVATED       	W				O	 	 	 	OTHER                   				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			CA						216					(CAN) ELECTRONIC CENTRALIZED AIRCRAFT MONITORING MESSAGE FLIGHT CONTROL FLAP FAULT DURING LANDING.FLAPLESS LANDING. SYST	EM RESET, FLAPS NR1 & NR2 RESET AND OPERATION CHECKED CARRIED OUT, SERVICEABLE.					2	L	7	4 	4F			RT	A197    					 
2001030600045	20010306	00045	NM  	2001	3	6	CA010115008      	1	20001118	G	5754	114T0202102	ACCESS DOOR     	BOEING      	767209      	BOEING	767   	767209      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					LT NR1 SLAT	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						22681					(CAN) ON WALK AROUND LEFT HAND WING NR1 SLAT ACTUATING ROD FAIRING PEELED BACK.NEW BRACKET AND DOOR INSTALLED.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001030600048	20010306	00048	EA  	2001	3	6	CA010116029      	1	20001228	G	5610	NP193219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A      	30015	NE  					COCKPIT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA						94055H2887					(CAN) IN CRUISE, THE CAPTAINS WINDSHIELD SHATTERED. THE CREW DECLARED EMERGENCY ADN THE AIRCRAFT LANDED UNEVENTFUL. THE 	MAINTENANCE REPLACED THE WINDSHIELD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030600049	20010306	00049	EA  	2001	3	6	CA010116030      	1	20001226	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA						99018H12134					(CAN) THE CAPTAINS WINDSHIELD SHATTERED AT FLIGHT LEVEL 10,000 FEET, THE AIRCRAFT RETURNED TO THE AIRPORT (UNEVENTFUL LA	NDING). THE MAINTENANCE REPLACED THE WINDSHIELD.					2	L	7	2 	4F			RT	A21EA   					 
2001030600050	20010306	00050	EA  	2001	3	6	CA010116031      	1	20001218	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA						96171H1046					(CAN) THE CAPTAINS WINDSHIELD CRACKED ON TAXI OUT.THE MAINTENANCE REPLACED THE WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030600051	20010306	00051	NE  	2001	3	6	CA010116033      	2	20001220	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF34*       	 	NE  					LT ENGINE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN FLIGHT, THE CREW REPORTED THE L ENG OIL PRESS WARNING MESSAGE ACCOMPANIED WITH LOSS OF OIL PRESSURE ON THE LEFT	 ENGINE (SHOWING 8 PSI). THEY DECLARED EMERGENCY, THE LANDING WAS UNEVENTFUL. THE MAINTENANCE REPLACED THE LEFT ENGINE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030600052	20010306	00052	GL  	2001	3	6	CA010117006      	2	20001128	G	7250	23058145	MOUNT           	ALLSN       	23063354    	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					NR 1 NOZZLE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3    			CAT44719					(CAN) ENGINE CAME IN FOR REPAIR FOR SMOKING ON SHUTDOWN. AFTER TESTING THE ENGINE, IT WAS NOTICED THAT THERE WAS OIL PRE	SENT IN THE NR1 NOZZLE AREA. UPON DISSASSEMBLY, A SMALL CRACK WAS FOUND ON THE NR1 NOZZLE MOUNT FACE. AFTER CLEANING, IT	 WAS NOTED THAT THE CRACK WAS NOW A HOLE. FURTHER INSPECTION REVEALED THAT THE NR8 OIL PRESSURE BORE WAS DRILLED TO .700	 AND THE PRINT DIMENSION IS .595 TO .605. THE CUSTOMER AND THE MANUFACTURER WERE NOTIFIED OF THE DEFECT AND THE PART WAS	 RETURNED TO THE MANUFACTURER.		1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001030600053	20010306	00053	NM  	2001	3	6	CA010117007      	1	20001130	G	3260	6552811115	PIN             			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					UPLOCK SENSOR	BACKED OUT      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA						M00760					(CAN) LANDING GEAR WOULD NOT RETRACT & CONFIGURATION HORN SOUNDED AT TAKEOFF. A/C RETURNED AS PER QRH PROCEDURE. MAIN R/	H LANDING GEAR OLEO SERVICED. ON SUBSEQUENT FLIGHT, L/R GEAR SHOWED RED. GEAR SELECTED DOWN 3 GREEN. L/G ACCESSORY UNIT 	CHANGED. A/C TEST FLOWN WITH SAME PROBLEM. TROUBLESHOOTING CARRIED OUT. FOUND PIN FOR THE UPLOCK SENSOR PUSHED BACK AT J	UNCTION BOX. PIN REINSTALLED AND SYSTEM TESTED AS PER MM FOUND TO BE SERVICEABLE. NO FURTHER PROBLEM DURING SUBSEQUENT F	LIGHT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030600054	20010306	00054	NM  	2001	3	6	CA010117009      	1	20001206	G	5610		WINDSHIELD      	BOEING      	7372E1      	BOEING	737   	7372E1      	138448F	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	LEAKING         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA						20681					(CAN) DURING CLIMB AT 4,000 FEET, IT WAS OBSERVED THAT F/O WINDSHIELD R/H UPPER CORNER WAS LEAKING. A/C RETURNED TO STAT	ION. WINDSHIELD REMOVED AND AREA CLEANED AND RE-INSTALLED I.A.W. MM 56-11-11. LEAK CHECK CARRIED OUT SERVICEABLE. NO FUR	THER PROBLEMS DURING SUBSEQUENT FLIGHTS.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001030600055	20010306	00055	CE  	2001	3	6	CA010117015      	1	20001206	G	5312	071111222	BULKHEAD        	CESSNA      	A185F       	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						18503743					(CAN) ON FUSELAGE BULKHEAD P/N 0711112-22 WE HAVE FOUND CRACK ON L/H & R/H SIDE OF BULKHEAD JUST ABOVE THE FLOATS ATTACH	 FITTINGS ON THE FORWARD SIDE OF THE BULKHEAD. AN ANGLE DOUBLER HAS BEEN INSTALLED AS PER AC-43.13,1B.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P21EA	 
2001033000034	20010330	00034	WP  	2001	3	30	CA010118002      	2	20001219	G	7321	307080022	FUEL CONTROL    			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE7312     	01518	WP  					RT ENGINE	BYPASSING       	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			X	J	 	ENGINE FLAMEOUT           	WARNING INDICATION        		DE	DESCENT        	1			CA			530  								(CAN) DURING DESCENT, RIGHT ENGINE FLAME OUT, SINGLE ENGINE APPROACH AND LANDING IN CYQB, NO DAMAGE TO AIRCRAFT, PASSENG	ERS UNHURT(5).1. CREW NOTICED RT FUEL PRESSURE RED ANNUNCIATOR, SWITCH BOOST PUMP ON  LIGHT OUT BUT ENGINE BEGAN SPOOL D	OWN. 2. ENGINE FLAME OUT AT 10,000 FEET AGL. 3. UNEVENTFUL SINGLE ENGINE LANDING IN CYQB.INTERNAL BY-PASSINSIDE FCU CAUS	ED FUEL PRESURE DROP AT AROUND 50 PSI AT 18 PERCENT N2 (MIN. SHOULD BE 200 PSI). CAUSE UNKNOWN.			2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2001033000038	20010330	00038	EA  	2001	3	30	CA010118007      	1	20001223	G	2913	601R751133	PUMP            			CNDAIR	CL600 	CL6002B19   	       	EA  										LT ENGINE	OVERHEATED      	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J	 	OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA			7    								(CAN) FOLLOWING LT ENGINE RELIGHT HYDRAULIC HIGH TEMPERATURE CAUTION MESSAGE HYDTEMP 135 DEGREES C. AFTER FOUR MINUTES P	RESSURE +/- 3750 P.S.I., LEFT ENGINE SHUT DOWN. LANDING CARRIED OUT SINGLE ENGINE.					2	L	7	2 	4F			RT	A21EA   					 
2001033000039	20010330	00039	SO  	2001	3	30	CA010118008      	1	20001231	G	5720	1001	VORTEX GEN      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT WING TIP	MISSING         	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) - AIRCRAFT OVERNIGHTED AT ALTERNATE AIRPORT DUE TO SNOW & RAIN (ICE). - WAS DEICE NEXT DAY.  HOME BASE, AME NOTICE	D MISSING VORTEX GEN & NEXT INBOARD BENT.- THIS IS OUTBOARD VICINITY OF OUTBOARD FUEL CAP. - NOT ESTABLISHED IF DONE DUR	ING DE-ICING OR DURING REFUELING.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001033000040	20010330	00040	GL  	2001	3	30	CA010118010      	1	20001128	G	3240		BRACKET         		24200101    	BOMBDR	BD700 	BD7001A10   	1390006	GL  										SPRING	DAMAGED         	W				K		 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1033 								(CAN) DURING INSP OF BRAKE-PEDAL RETURN SPRINGS, WE NOTICED THAT SPRINGS ON RT SIDE WERE VERY LOSE, NO TENSION ON THEM. 	WE INVESTIGATED FURTHER TO FIND THAT DISTANCE BETWEEN SPRINGS HOLDING BRACKET & BRAKE-PEDAL POS TRANSDUCER SUPPORT WAS N	OT SAME ON RT & LT SIDE OF A/C. FIG.1 ATTACHED. DISTANCE BETWEEN SPRINGS HOLDING BRACKET & THE TRANSDUCER SUPPORT IS 5.2	50 INCH ON LEFT SIDE & 5.813 INCH ON RT SIDE. WE VERIFIED ON A 2ND A/C OF SAME TYPE TO FIND A DIMENSION OF 5.250 ON BOTH	 LT & RT SIDES.WE STRONGLY SUSPECT THAT RT SPRING HOLDING BRACKET WAS NOT POSED & INST PROPERLY AT MANUFACTURE:		2	L	7	2 	4F			RT	T00003NY					 
2001033000044	20010330	00044	NM  	2001	3	30	CA010119003      	1	20001217	G	5754	69378524	FITTING         			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					LT LE FLAP	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE LEFT OUTBOARD FORE FLAP ATTACHMENT BRACKET WAS FOUND CRACKED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001033000047	20010330	00047	CE  	2001	3	30	CA010119007      	1	20001218	G	2510	051422714	PAN             	CESSNA      		CESSNA	172   	172R        	2072401	CE  										SEAT ASSY	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION, IT WAS OBSERVED THAT THE SEAT PAN ASSEMBLY THAT SUPPORTS THE LOWER SET CUSHION ON BO	TH PILOT AND CO-PILOT SEAT HAD A CRACK APPROXIMATELY 2 1/2 INCH TO 3 INCH LONG, RADIATING FROM BOTH REAR CORNERS TO THE 	LIGHTENING HOLES JUST INBOARD AND FORWARD OF THE SAME LOCATION.A SHEET METAL PATCH WAS INSTALLED ON BOTH SIDES I.A.W. MA	NUFACTURERS RECOMMENDED REPAIR PROCEDURES TO REINFORCE THE PROBLEM AREAS.AS THIS CONDITION WAS OBSERVED ON BOTH OF THE F	RONT SEATS, AND OCCURRED IN EXACTLY THE SAME AREAS.		1	H	7	1 	3O			NT	3A12    					 
2001033000048	20010330	00048	NE  	2001	3	30	CA010125003      	2	20001217	G	7250		TURBINE         			DOUG  	DC9   	DC9         	3022002	WP  	PWA   	JT8   	JT8D7B      	52053	NE  					ENGINE	FAILED          	W				E	C	 	 	ENGINE SHUTDOWN         	ABORTED TAKEOFF         			R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) OPERATOR REPORTED: ENGINE EPR DROPPED FROM 2.1 DOWN TO ABOUT 1.6 ON TAKEOFF ROLL.- F/A REPORTED LOUD BANG. - OCCUR	ENCE DATE: DECEMBER 17, 2000.SHOP INDUCTION DATE: JANUARY 17, 2001-01-19.PROBABLE CAUSE: LOW PRESSURE TURBINE FAILURE. 2	001-01-29 TC: A USA ENGINE MANUFACTURES REPRESENTATIVE BASED IN BRAZIL HAS SUBMITTED THIS SDR TO TC SINCE THE AIRCRAFT O	PERATOR WAS DOMESTIC. HE HAS  SPECIFIED THAT A FOLLOW-UP SDR WILL FOLLOW AFTER TEAR DOWN.			2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001033000058	20010330	00058	EU  	2001	3	30	CA010126014      	1	20001220	G	2742	1110039AAA	CONTROL UNIT    			FOKKER	F28   	F28MK1000   	4990808	EU  										HORIZONTAL STAB	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			CA						MC188					(CAN) HORIZONTAL STAB LOCKED UP. PILOTS COULD MOVE NOSE DOWN BUT NOT BACK TO NOSE UP WITH TRIM WHEEL. HOWEVER, STAB WORK	ED NORMAL ELECT.LY. MAINT CNTL ADVISED CREW TO CYCLE STAB SWITCHES&RESET HYDRAULIC CNTL PANE L - UNSUCCESSFUL RESULTS. A	/C RETURNED&LANDED W/O INCID. - CFR WERE ON STANDBY. A/C LANDED WITH LDG WT AT 61,000 LBS - 5 PERCENT UNDER ALLOWED LDG 	WT BEFORE HEAVY LDG INSP IS REQD. MAINT INSPECTION OF HORIZ STAB CNTL UNIT REVEALED ACTUATOR LEAKING AROUND VENT CAPS AT	 CLUTCH PINS. MAINT REPL HORIZ STAB CNTL UNIT&LEAKED CHECKED A/C - GROUND CHECKED SERVICEABLE. A/C RETURNED TO SERVICE W	ITH NO FURTHER INCID. TO RPT.	2	L	7	2 	4F			RT	A20EU   					 
2001033000059	20010330	00059	EU  	2001	3	30	CA010129002      	1	20001220	G	4990	38075412	APU             			FOKKER	F28   	F28MK1000   	4990808	EU  										APU BAY	FAILED          	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA						P36229C					(CAN) ON DEPTR LAV SMOKE DETECTOR SOUNDED AROUND SAME TIME CREW STARTING FEELING NAUSEOUS. ALSO CREW RPTED PASSENGERS CO	MMENTING ON BURNING SMELL IN CABIN. A/C RETURNED TO YWG & LANDED W/O INCID.. MAINTENANCE INSP REVEALED APU OIL LEVEL DOW	N TO 1/2 TANK - SUSPECTED SOURCE OF CONTAMINATION. ENGINEERS CARRIED OUT ENGINE RUN TO 80 PERCENT THRUST & PURGED AIR-CO	ND DUCTS - SMELL DISSIPATED DURING RUNS. A/C CHECKED SERVICEABLE FOR POS ITION FLTPOSING FLT CREW RPTS SMOKE ODOR RETURN	ED, VERY EVIDENT IN COCKPIT ON DESCENT. A/C LANDED W/O INCID.. MAINT REPL APU, S/N: ON P37566, S/N: OFF P39229C - A/C GR	OUND CHECKED SERVICEABLE - NO FURTHER RPTS OF OIL SMELL IN CABIN OR COCKPIT.	2	L	7	2 	4F			RT	A20EU   					 
2001040300049	20010403	00049	WP  	2001	4	3	CA010129005      	2	20001227	G	7314		DRIVE SHAFT     	GARRTT      	TPE33110UGR 	BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	AT GEARBOX	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				X	 	 	ENGINE FLAMEOUT           			DE	DESCENT        	1			CA						P63016					(CAN) UPON DISASSEMBLY OF THE FCU AND FUEL PUMP, IT WAS FOUND THAT THE DRIVESHAFT FOR THESE UNITS ROTATED FREELY HAVING 	BECOME DISENGAGED IN THE GEARBOX. THE  ENGINE IS BEING SHIPPED TO NATIONAL FLIGHT FOR ASSESSMENT AND REPAIR. A REPORT ON	 FAILED PARTS WILL FOLLOW. TIME FROM GEARBOX INSPECTION WAS 1671.6 HOURS. 2001-01-30 TC: AWAIT TEARDOWN REPORT FROM ORIG	INATOR.			2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2001033000061	20010330	00061	EU  	2001	3	30	CA010129009      	1	20001229	G	6420	22129BE140182L	BOLT            	AEROSP      	355A31000106	SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR HEAD	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						M1077					(CAN) BOLT SHANKS CORRODED OVER APPROXIMATELY 50 PERCENT OF SURFACE AREA.DISCOVERED WHEN DISASSEMBLING MAIN ROTOR SLEEVE	 TO REPLACE WORN BEARINGS ON END OF SLEEVES.					1	G	7	1 	3U			 	H9EU    					 
2001033000062	20010330	00062	EU  	2001	3	30	CA010129010      	1	20001229	G	6420	117775P	STARFLEX        			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR HEAD	FLAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						M1077					(CAN) DISCOVERED TELFLON FLAKING OUT OF BEARING RACE BETWEEN INNER SELF ALIGNING BALL AND OUTER RACE. ALL THREE STAR ARM	 BEARINGS AREPLACED DUE TO WEAR. DISCOVERED WHEN DISASSEMBLING HEAD TO INSTALL LOW TEMPERATURE SPHERICAL THRUST BEARINGS	.				1	G	7	1 	3U			 	H9EU    					 
2001033000064	20010330	00064	NM  	2001	3	30	CA010129013      	1	20001217	G	7931	ST1042	TRANSMITTER     			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					OIL PRESSURE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA						B18					(CAN) ON CLIMB ENGINE OIL PRESSURE WAS NOTICED TO DROP TO 41 PSI AND DID NOT RESPOND TO THROTTLE MOVEMENT. THE FLIGHT CR	EW ELECTED TO RETURN WHERE MAINTENANCE REPLACED THE OIL PRESSURE TRANSMITTRER ON THE NR 2 ENGINE.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001033000076	20010330	00076	CE  	2001	3	30	CA010131019      	1	20001120	G	5312	58111491	BULKHEAD        			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			12758	12758							(CAN) DURING A ROUTINE INSP BULKHEAD REFD ABOVE FOUND CRACKED. BULKHEAD IS LOCATED AT STA 115 BENEATH FLOOR & ATTACHED T	O AFT SIDE IS A PULLEY FOR RUDDER PEDAL BALANCE CABLE. CRACK EXTENDED FROM A LARGE LIGHTENING HOLE TO A SMALLER HOLE USE	D FOR RUDDER PEDAL BALANCE CABLE. ADDITIONALLY, A 2ND CRACK WAS DISCOVERED EXTENDING FROM OTHER BALANCE CABLE HOLE TO A 	 HOLE PROVIDED FOR CNTL CABLE ROUTING. BULKHEAD HAD BEEN PREV REPD BY ANOTHER OPERATOR BUT FOUND TO BE INADEQUATE. A DAR	 WAS CONTACTED TO PROVIDE A REPAIR SCHEME WHICH WAS THEN IMPLEMEN TED.QUITE PROBABLY THIS CRACKING IS CAUSED BY FLEXING 	OF BULKHEAD WHEN BOTH PEDALS ARE DEPRESSED SIMULTANEOUSLY.	1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001033000079	20010330	00079	NE  	2001	3	30	CA010201006      	2	20000925	G	7530	77655557	SHAFT           			BOEING	767   	767275      	1385155	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					BLEED CONTROLLER	FAILED          	W				O	 	 	 	OTHER                   				Y	J	 	ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) STARTING DESCENT FROM 33,000 FEET, LEFT HAND ENGINE COMPRESSOR STALL, AS SOON AS ENGINE WENT TO IDLE EXHAUST GAS T	EMPERATURE WENT CLOSE TO MAXIMUM RED. ENGINE WAS SHUT DOWN. ON PRELIMINARY BORESCOPE INSPECTION FOUND 5TH STAGE BLADES B	ENT.AFTER INVESTIGATION, THE COMPRESSOR STALL WAS DUE TO THE FAILURE OF THE EVBC (ENGINE VANE-BLEED CONTROLLER)  WHICH H	AD A BROKEN SHAFT. THIS CAUSE THE VANES TO CLOSE AND THE NR 3 BLEED TO OPEN.THE DAMAGE WAS LIMIT TO SOME C5 BLADES BENT.	ENGINE CHANGED.		2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001033000080	20010330	00080	EA  	2001	3	30	CA010201007      	1	20001231	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CAPTAINS WINDSHIELD CRACKED ON DESCENT TO TORONTO AT 25,000 FEET. REPLACED CAPTAINS WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000081	20010330	00081	EA  	2001	3	30	CA010201010      	1	20001213	G	5210	601R3190139	HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					PAX DOOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER TAKEOFF, AN OPEN DOOR PASSENGER DOOR WARNING MESSAGE APPEARED. THE AIRCRAFT RETURNED TO OTTAWA. AFTER LANDIN	G, THEY FOUND THAT THE OUTER HANDLE WAS POPPED OUT. THE INNER HANDLE STOP WAS ADJUSTED. THE INNER DOOR RIGGING CHECK OK,	 PASSENGER DOOR SENSORS S26 AND S27 ADJUSTED AS PER MAINTENANCE MANUAL.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000086	20010330	00086	EA  	2001	3	30	CA010202006      	1	20001224	G	2150		A/C PACK        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ACM BAY	OVERHEATED      	W				A	 	 	 	UNSCHED LANDING         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE CREW REPORTED SMOKE IN THE COCKPIT AND DECLARED AN EMERGENCY. THE LANDING WAS UNEVENTFUL.THE MA	INTENANCE CREW REPORTED THAT ONE OR BOTH PACKS OVERHEATED AND CAUSED THE SMOKE. THE MAINTENANCE INSPECTED THE ECS SYSTEM	 AND NOTED NO DEFECT. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040300122	20010403	00122	NM  	2001	4	3	CA010205021      	1	20001215	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			51583								(CAN) AIRCRAFT WAS ON D CHECK AND ON IMPORTATION PROCESS. ON FUSELAGE AT FS 727 BETWEEN STRINGER 27 LT AND 27 RT AN EXTE	RNAL REPAIR WAS EVALUATED FOR COMPLIANCE WE FOUND BULGING AT RIVETS. THE REPAIR WAS REMOVED AND WE FOUND HEAVY CORROSION	 IN BETWEEN SKIN. BOEING WAS CONTACTED FOR A REPAIR. NO EFFECT ON SSID PROGRAM.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001040200250	20010402	00250	EA  	2001	4	2	CA010205028      	1	20001211	G	2822		PUMP            		6006255021  	CNDAIR	CL604 	CL604       	       	EA  	GE    	CF34  	CF343B1     	 	NE  					BOOST PUMP	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FUEL FOUND IN BOTH STANDBY AND APU FUEL BOOST PUMPS UNDER PLUG (REF CMM 28-20-78 PAGE 1010, ITEM 100).FUEL WAS FOU	ND ON BOTH SIDE OF PLUG AND ALSO FOUND IN CONDUIT WHERE WIRING FOR PUMP RUNS TO FRONT SPAR. LOCATION OF LEAK UNKNOWN AT 	THIS TIME.SEE ATTACHED IPC REFERENCES (AREAS OF LEAK HI-LIGHTED IN RED).				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700208	20010327	00208	EA  	2001	3	27	CA010213017      	1	20001204	G	7920	2810044101	CHECK VALVE     	GE          	CF343A      	CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					OIL REPLNH LINE	OPEN            	W				E	 	 	 	ENGINE SHUTDOWN         				J		 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) A LOP WARNING APPEARED IN FLIGHT DEC.4,2000 AT 14:45 Z. THE CREW SHUTDOWN THE AFFECTED ENGINE AND CARRIED OUT AN U	NEVENTFUL LANDING AT DESTINATION IN PORTUGAL. TROUBLESHOOTING REVEALED A REDUCED ENGINE OIL LEVEL DUE TO A FAILED OPEN C	HECK VALVE IN THE OIL REPLENISHMENT LINE OF THAT SYSTEM. VALVE REPLACED, OIL REPLENISHED AND AIRCRAFT RETURNED TO SERVIC	E. INVESTIGATION STILL IN PROGRESS.			2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2001040400011	20010404	00011	SW  	2001	4	4	CA010219002      	1	20001208	G	6320	076004001	BEVEL GEAR      		BP252       	KAMOV 	KA32  	KA32A1      	       	SW  										GEARBOX	BROKEN          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			129  			20006005K					(CAN) NOISE HEARD WHILE TURNING ROTOR BACKWARDS DURING MAINTENANCE.						1	G	7	2 	4U			NC	        					 
2001040400012	20010404	00012	EA  	2001	4	4	CA010219004      	2	20001222	G	7421	RHB37E	SPARK PLUG      			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					ENGINE	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS ENGINE HAD APPROXIMATELY 16 MINUTES AFTER ENGINE OVERHAUL. THIS WAS ON NR 2 ENGINE THAT THE SPARK PLUG SEPARA	TED. WE THEN REMOVED ALL SPARK PLUGS IN NR 2 & NR 1 ENGINES AND REPLACED WITH CHAMPION, AND WHEN REMOVING SPARK PLUGS ON	 NR 1 ENGINE ANOTHER SPARK PLUG CAME VERY CLOSE TO SEPARATE. THE NR 2 ENGINE SPARK PLUG WHEN IT SEPARATED IT DAMAGED THE	 PITCH CONTROL (MELTED THE OUTER CASING OF IT) AND ALSO BLACKENED 2 IGNITION LEADS AND BLOW A HOLE THRU THE BAFFLE SEAL.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2001040400013	20010404	00013	GL  	2001	4	4	CA010219007      	2	20000920	G	7530	369H8407	TUBE            		369H90020531	HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					BLEED AIR HEAT	LEAKING         	W				O	 	 	 	OTHER                   				M	J	 	OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			962  								(CAN) PILOT REPORTED INCREASED START TEMPERATURE. ON RUN-UP IT WAS DISCOVERED THAT THE LARGE AIR LINE BETWEEN THE ENGINE	 COMPRESSOR AND THE FIREWALL WAS LEAKING AIR FROM THE FLEXIBLE BRAID SECTION. ENGINE WAS SHUT DOWN AND THE LINE WAS REPL	ACED. THE LEAK IS NOT DETECTABLE BY VISUAL INSPECTION.				1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2001040400030	20010404	00030	SO  	2001	4	4	CA010223005      	1	20001123	G	3260	67411005	LIMIT SWITCH    			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					MLG	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) GEAR WOULD NOT RETRACT. AIRCRAFT LANDED NORMALLY. AIRCRAFT JACKED. NEW UPLIMIT SWITCHES INSTALLED IN MAIN GEAR, RI	GGED. SUBSEQUENT TEST FLIGHTS REVEALED OTHER PROBLEMS. BROKEN WIRES WITH WIRE BUNDLES POORLY REPAIRED. REPAIRS DONE TO W	IRES. AUTOMATIC GEAR DOWN VALVE FOUND TO BE LEAKING INTERNALLY. VALVE REPLACED WITH SERVICEABLE PART. REVIEW OF LOG SHOW	S MANY GEAR PROBLEMS/REPAIRS IN THE PAST. AGE AND CONDITION OF AIRCRAFT A FACTOR IN THIS.			1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001040400031	20010404	00031	EA  	2001	4	4	CA010223006      	2	20001123	G	7322	25244508RC	SERVO           			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					INJECTOR	MALFUNCTIONED   	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		AP	APPROACH       	1			CA				1084 							(CAN) ENGINE STUMBLES ON ADDING THROTTLE. ENGINE RUNS LEAN. UNABLE TO RICHEN MIXTURE. INJECTOR SERVO REMOVED. OVERHAUL U	NIT INSTALLED. IDLE MIXTURE AND SPEED SET. ENGINE RUN UP NORMAL.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001040400212	20010404	00212	EU  	2001	4	4	CA010302013      	1	20001123	G	7710	1179405303	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					TRIPLE TACH	INTERMITTENT    	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				21   		391					(CAN) UNIT WAS REPAIRED AND TESTED AT IFR PRECISION INSTRUMENTS (EDM.AB) AND RELEASED SERVICEABLE ON APRIL 3, 1997. UNIT	 IN STARS STORES IN THE MEANTIME. WHEN INSTALLED IT LASTED 21 HOURS BEFORE THE SAME FAULT OCCURRED: NR 1 ENGINE N2 INDIC	ATOR NEEDLE WOULD DROP OFF SUDDENLY AND TEMPORARY. THIS SAME INSTRUMENT WAS HAVING THE SAME PROBLEM IN C-FIOM BEFORE REP	AIR AND PILOTS RECOGNIZED THIS WAS AN INDICATION PROBLEM.			1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001040500228	20010405	00228	EA  	2001	4	5	CA010321007      	1	20001231	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA											(CAN) CAPTAINS WINDSHIELD CRACKED ON DESCENT TO TORONTO AT 25,000 FEET. REPLACED CAPTAINS WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500231	20010405	00231	NE  	2001	4	5	CA010321010      	2	20001218	G	7250		TURBINE BLADES  			DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7B      	52053	NE  					LT ENGINE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT REJECTED TAKEOFF ON ROLL DUE TO THE EPR INDICATION THAT WENT FROM 2.01 DOWN TO 1.6 (ENGINE PRESSURE RATIO	). FLIGHT ATTENDANT REPORTED HEARING A LOUD BANG. ENGINE CONTAINED. MECHANIC FOUND EVIDENCE OF DAMAGE TO THE TURBINE SEC	TION. REPLACED LT ENGINE. ENGINE UNDER INVESTIGATION FOR FINAL REPORT. SHOP INDUCTION DATE: JANUARY 17, 2001.THE ENGINE 	WAS DISASSEMBLED AT GE CELMA SHOP, THE SECOND STAGE BLADES FAILED CAUSING DAMAGE IN THE REST OF LPT BLADES AND VANES. A 	SAMPLE OF THESE FAILED BLADES WERE SENT TO THE MATERIALS LABORATORY AND OVERTEMPERATURE WAS DETECTED. THE OVERTEMPERATUR	E COULD BE CAUSED BY A HOT START OR BE A CONSEQUENCE OF THE FAILURE.	2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001051500366	20010515	00366	GL  	2001	5	15	CA010507002      	3	20000707	G	6114		HUB             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				669  							(CAN) A ROUTINE MAINTENANCE INSPECTION RED DYE LEAKAGE WAS OBSERVED ON PROP BLADES. PROP WAS REMOVED AND SHIPPED TO PROP	ELLER SHOP AND HUB WAS FOUND CRACKED. 2001-05-09 TC: FAA AD PERTAINS.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2001051500367	20010515	00367	SO  	2001	5	15	CA010507003      	1	20001116	G	3245		TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG TIRE	PIN HOLE        	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			194  								(CAN) NOSE TIRE DEFLATED. TUBE WAS FOUND DEFECTIVE WITH PIN HOLE IN SIDE WALL.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001051500368	20010515	00368	SO  	2001	5	15	CA010507004      	1	20001202	G	3245	600X6	TUBE            	MICHEL      	600X6       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG TIRE	PIN HOLE        	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			23   								(CAN) NOSE TIRE DEFLATED. TUBE WAS FOUND DEFECTIVE WITH PIN HOLE IN SIDE WALL.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001051500369	20010515	00369	SO  	2001	5	15	CA010507005      	1	20001209	G	3245	600X6	TUBE            	MCCREARY    	6006        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG TIRE	PIN HOLE        	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			14   								(CAN) NOSE TIRE DEFLATED. TUBE WAS FOUND DEFECTIVE WITH PIN HOLE IN SIDE WALL.MANUFACTURE NOTIFIED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001061400021	20010614	00021	EU  	2001	6	14	CA010518004      	1	20001129	G	6730		SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			3190 	807  		292M					(CAN) ROUTINE DAILY INSPECTION REVEALED EXCESSIVE LEAKAGE FROM MAIN ROTOR SERVO. SERVO REMOVED FOR REPAIR.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001061400022	20010614	00022	EU  	2001	6	14	CA010518005      	1	20001012	G	6730		SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			6285 	969  		103M					(CAN) SCHEDULED INSPECTION REVEALED EXCESSIVE LEAKAGE FROM MAIN ROTOR SERVO. SERVO REMOVED FOR REPAIR.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001061400023	20010614	00023	EU  	2001	6	14	CA010518006      	1	20001128	G	6730		SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			6656 	1854 		219M					(CAN) DURING ROUTINE DAILY INSPECTION, MAIN ROTOR SERVO WAS FOUND TO BE LEAKING EXCESSIVELY. SERVO WAS REMOVED FOR REPAI	R.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001061400024	20010614	00024	EU  	2001	6	14	CA010518007      	1	20001012	G	6730		SERVO           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1685 			87					(CAN) SCHEDULED INSPECTION REVEALED EXCESSIVE LEAKAGE FROM MAIN ROTOR SERVO. SERVO REMOVED FOR REPAIR.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001061400025	20010614	00025	EU  	2001	6	14	CA010518008      	1	20001111	G	6210		BLADE           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3209 								(CAN) MAIN ROTOR BLADE WAS REMOVED FROM AIRCRAFT AND SHIPPED TO REPAIR FACILITY FOR DEBONDING REPAIR REQUIRED TO STAINLE	SS STEEL LEADING EDGE. UPON FURTHER INSPECTION BY THE REPAIR FACILITY, THE BLADE WAS FOUND TO HAVE A SPAR BURNING CRACK 	LOCATED AT STN 1000, DETERMINED TO BE NOT REPAIRABLE.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001092400016	20010924	00016	EA  	2001	9	24	CA010912004      	1	20000905	G	5714		FRAME           			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	CA3         	52026	NE  	HAMSTD	43E	43E60       	NE  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3390 			1093					(CAN) WHILE HAVING NDT PERFORMED TO COMPLY WITH AD CF-97-07 REV.2, WING TO FUSELAGE FRAME ANGLE INSPECTION, THE LT FRONT	 OUT BOARD ANGLE WAS FOUND CRACKED. ANGLE WAS REPAIRED IN ACCORDANCE WITH DRAWING 215-53-10-54 PAGES 2,3 & 6. THE AIRCRA	FT HAD ACCUMULATED A TOTAL OF 217.2 HOURS SINCE AD WAS LAST DONE.				2	H	7	2 	4R	4	R	 	A14EA   	E231	6	C	P871	 
2001100200045	20011002	00045	EU  	2001	10	2	CA010921004      	1	20000726	G	6420	NAS620425	BOLT            			HUGHES	369   	369FF       	       	EU  	ALLSN 	250C  	250C30      	03013	GL  					T/R GEARBOX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1200 								(CAN) - TAILROTOR GEARBOX RETENTION HARDWARE, BOLT HEAD FOUND MISSING DURING SCHEDULED MAINTENANCE. - 3 REMAINING BOLTS 	WERE INSPECTED  WITH NO FAILURES FOUND.  ALL THE TAILROTOR GEARBOX RETENTION HARDWARE WAS REPLACED WITH NEW. A 300 HOUR 	RETIREMENT SCHEDULE HAS BEEN ESTABLISHED FOR THE PARTS IN QUESTION.				1	G	7	1 	3U	3	U	 	H3WE    	E1GL				 
2002011700114	20020117	00114	SW  	2002	1	17	CA011120006      	1	20001010	G	7603	50059300750012	THROTTLE CABLE  			KAMOV 	KA32  	KA32A1      	       	SW  										ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CABLE CHAFED THROUGH AT ENGINE DECK, OPENING IN ENGINE DECK PRESSURE SEAL INCREASED TO PREVENT RE-OCCURRENCE.						1	G	7	2 	4U			NC	        					 
2002021200181	20020212	00181	WP  	2002	2	12	CA011211006      	1	20000922	G	3320	5511261	TRANSFORMER     			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					LAV LIGHT	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED,  DURING FLIGHT,  EXCESSIVE HEAT GENERATED BY BOTH FWD LAVATORY CEILLING LIGHTS FLUORESCENT A	ND INCADESCENT BULB VERY HOT,  WHEN MASTER LAVATORY SWITCHON, BOTH LIGHTS ON FULL BRIGHT IN BOTH LAVATORIES,  SMELL OF B	URNED RUBBER VERY PRESENT.  FOUND BOTH LAVATORY CEILLING LIGHTS TRANSFORMERS BURNED. DEACTIVATED CONNECTOR PLUG OFF AND 	C/B FWD LAVATORY LIGHT PULLED ON CB 2. THE TRANSFORMERS WERE REPLACED.			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002021400037	20020214	00037	GL  	2002	2	14	CA020103016      	2	20000816	G	7230	23097911	COUPLING        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CIRCUMFERENCE CRACKS ON PILOT O.D AREA. DISCREPANCY FOUND DURING COMPRESSOR REPAIR. DUE TO CUSTOMER REPORT METAL C	ONTAMINATION.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300031	20020503	00031	SW  	2002	5	3	CA020405010      	1	20000908	G	6730		SEAL            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					HYD SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) EXCESSIVE FLUID LEAKAGE PAST SEAL.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002050300032	20020503	00032	SW  	2002	5	3	CA020405011      	1	20000908	G	6730		SEAL            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					HYD SERVO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) EXCESSIVE FLUID LEAKAGE PAST SEALS.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002051300014	20020513	00014	SW  	2002	5	13	CA020405012      	1	20000908	G	6730		SEAL            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					HYD SERVO	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  HYD SERVO HAS EXCESSIVE FLUID LEAKAGE PAST SEALS.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002091200019	20020912	00019	SW  	2002	9	12	CA020905003      	1	20000821	G	6510	206040106001	SPRING          	BELL        	206040015   	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					COUPLING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						AMN50548					(CAN) BROKEN SPRING INSIDE COUPLING. DAMAGE TO SPHERICAL COUPLING AND END CAP.  PROBLEM FOUND DURING 600 HR / 12 MTH LUB	RICATION.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003071800091	20030718	00091	SO  	2003	7	18	CA030709003      	2	20000720	G	8520		STUD            			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ENGINE REMOVED TO INSTALL NEW CAM.   WHEN THE ENGINE WAS REPAIRED, IT LEAKED OIL FROM THROUGH STUD. ENGINE WAS REM	OVED. NEW TYPE STUDS INSTALLED. IT SOLVED THE PROBLEM. TTAC 4603					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2003072100054	20030721	00054	CE  	2003	7	21	CA030709004      	1	20000810	G	7120		MOUNT           			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) CROSS TUBE ON ENGINE MOUNT BROKE ON TAKEOFF, DURING THE APPLICATION OFF POWER.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2003102000004	20031020	00004		2003	10	20	CA030731014      	4	20000727	G	2350		GROUND WIRE     			SNIAS 	350   	AS350B3     	8680954	EU  										AUDIO CONTROL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1001					(CAN) AUDIO NOISE PROBLEM HAS BEEN OBSERVED IN SERVICE, AMS43 TSO UNITS DURING ACTIVATION OF HIGH CURRENT DEVICES IN A/C	, NOISE OF BLOWER MOTORS, BOOST PUMPS AND ELECTRIC MOTORS HAVE BEEN COUPLED INTO AUDIO SYS.  AMS43 TSO UNIT WAS RE-TESTE	D AND WAS CONFIRMED THAT PWR SUPPLY FILTERING WAS INADEQUATE.   OUT OF SPECIFICATION CONDITION RESULTS IN INCREASED NOIS	E ON A/C AUDIO SYS DURING OPERATION OF HIGH CURRENT ELECTRICAL DEVICES. NAT HAS DETERMINED THAT MOVING GROUND RETURNS OF	 MICROPHONE BIAS CAPACITORS TO AN ELECTRICALLY CLEANER NODE WILL RESULT IN LESS RIPPLE CURRENT FLOWING THROUGH GROUND, L	ESS NOISE IS COUPLED INTO MICROPHONE BIAS CIRCUIT.  MODIFIED UNIT WAS SUBJECTED TO THE REQUIRED TESTS AND PASSED.	1	G	7	1 	3U			 	H9EU    					 
2003090900001	20030909	00001		2003	9	9	CA030811002      	4	20000727	G	2397		GROUND WIRE     			SNIAS 	350   	AS350B3     	8680954	EU  										AUDIO CONTROL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AN AUDIO NOISE PROBLEM HAS BEEN OBSERVED IN SERVICE WITH THE AMS43 TSO DURING ACTIVATION OF HIGH CURRENT DEVICES I	N THE A/C. NOISE OF ELECTRICAL MOTORS, & BOOST PUMPS HAS BEEN COUPLED INTO THE AUDIO SYS. AN AMS43 TSO WAS RETESTED TO R	TCA DO-160C, IT WAS CONFIRMED THAT THE POWER SUPPLY FILTERING WAS INADEQUATE TO FILTER OUT THE SPECIFIED VOLT RIPPLE FRO	M THE POWER LIGHT.			1	G	7	1 	3U			 	H9EU    					 
2001032000052	20010320	00052	CE  	2001	3	20	CE8S20010001     	1	20001227	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LT MLG	BROKEN          	C			CE8S	O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			SW	99	6344V					172RG0635	L2881936A	804954		LEFT GEAR DID NOT GO UP ALTHOUGH GEAR UP LIGHT WAS ON, GEAR WAS JUST DANGLING.  PUT GEAR HANDLE IN DOWN POSITION AND GOT	 A GREEN LIGHT AND LANDED SAFELY.  UPON INSPECTION OF GEAR ACTUATOR, FOUND FORWARD ATTACH BOLT HOLE WAS CRACKED COMPLETE	LY THROUGH ON BOTH SIDES OF THE CASTING.				1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2000040400642	20000404	00642		2000	4	4	CIHA200096001    	4	20000329	G	2565	6164789	BATTERY PACK    			BOEING	727   	7272J4      	1384006	NM  										ESCAPE SLIDE	DISCHARGED      	A			C1HA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	696CA					22574				L-1 DOOR AND R-1 DOOR EMERGENCY SLIDE LIGHTS ARE INOP.						2	L	7	3 	4F			RT	A3WE    					 
2000030400169	20000304	00169	SW  	2000	3	4	EATA066006       	1	20000218	G	3340	A7151	BRACKET         			BELL  	206   	206B3       	1181506	SW  										FLIR LAMP	CRACKED         	H			EATA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	581Z	538  				3462				LIGHT IS PART OF EAC HELICOPTERS, INC. STC NR SR00786CH FOR THE FLIR ULTRA MEDIA RS CAMERA SYSTEM.  LIGHTS MOUNTED ON FO	RWARD CROSSTUBE.  ATTACHMENT BRACKET THAT ATTACHES TO THE CROSSTUBE CLAMP FOUND CRACKED.  REPLACED LIGHT ASSEMBLY.					1	G	7	1 	3U				H2SW    					 
2000030400170	20000304	00170	SW  	2000	3	4	EATA066007       	1	20000218	G	3340	A7151	BRACKET         			BELL  	206   	206B3       	1181506	SW  										FLIR LAMP	CRACKED         	H			EATA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	581Z					3462				LIGHT IS PART OF EAC HELICOPTERS, INC. STC NR SR00786CH FOR THE FLIR ULTRA MEDIA RS CAMERA SYSTEM.  LIGHTS ARE MOUNTED O	N THE FORWARD CROSSTUBE.  THE BRACKET THAT ATTACHES THE LIGHT TO THE CROSSTUBE CLAMP FOUND CRACKED.   REPLACED LIGHT ASS	EMBLY.				1	G	7	1 	3U				H2SW    					 
2000030400171	20000304	00171	SW  	2000	3	4	EATA066008       	1	20000218	G	3340	A7151	BRACKET         			BELL  	206   	206B3       	1181506	SW  										FLIR LAMP	CRACKED         	H			EATA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	581Z	158  				3462				LIGHT IS PART OF EAC HELICOPTERS, INC. STC NR SH00786CH FOR THE FLIR ULTRA MEDIA RS CAMERA SYSTEM.  LIGHT IS MOUNTED ON 	THE FORWARD CROSSTUBE.  BRACKET THAT ATTACHES THE LIGHT TO THE CROSSTUBE CLAMP FOUND CRACKED.   REPLACED LIGHT ASSEMBLY.					1	G	7	1 	3U				H2SW    					 
2000012200460	20000122	00460	EU  	2000	1	22	ERAA065659       	1	20000105	G	3242	A23008020	TIE BOLT        			BOLKMS	105   	BO105S      	5626006	EU  										MLG	FLAKING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	131EH					S595				NEW TIE BOLTS  FROM STOCK THAT COULD NOT BE USED ON AIRCRAFT DUE TO PLATING FLAKING OFF ON MUTE.						1	G	7	2 	3U				H3EU    					 
2000012200461	20000122	00461	EU  	2000	1	22	ERAA065660       	1	20000105	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	292EH	33   				S843				SPECIAL COATING WORN OFF AND SHAFT ONLY HAS 32.6 HOURS TT.						1	G	7	2 	3U				H3EU    					 
2000012200462	20000122	00462	EU  	2000	1	22	ERAA065661       	1	20000106	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	128EH	28   				S572				NEW FREEWHEEL SHAFT WITH 27.9 HOURS THAT HAS SPECIAL COATING WORN.						1	G	7	2 	3U				H3EU    					 
2000012200463	20000122	00463	EU  	2000	1	22	ERAA065662       	1	20000106	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	128EH	477  				S572				SPECIAL COATING ON FREEWHEEL SHAFT HAS A GROOVE WHERE SEAL RIDES.						1	G	7	2 	3U				H3EU    					 
2000021900612	20000219	00612	NE  	2000	2	19	ERAA065944       	1	20000105	G	7714	54487129110	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										N1 TACH	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	576EH					760212				N1 TACH INDICATOR PURCHASED FROM TURBOMECA  9/13/99.  LED DIGITS WILL NOT ILLUMINATE.						1	G	7	2 	3U				H1NE    					 
2000021900613	20000219	00613	GL  	2000	2	19	ERAA065950       	2	20000110	G	7240	23031260	COMBUSTION CASE 			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MISOVERHAULED   	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	124EH					559				COMBUSTION CASE REPAIRED AND RETURNED WITH AIR TUBE BOSS RETAINING RING NOT BEING MACHINED.  COULD NOT BE INSTALLED ON A	IRCRAFT.					1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2000021900614	20000219	00614	NE  	2000	2	19	ERAA065951       	1	20000110	G	7714	0177555240	TACHOMETER      			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	INOPERATIVE     	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	577EH					760222				NEW TACH BOX  RECEIVED IN NON-SERVICEABLE CONDITION.  NO OVERSPEED LIGHT OR STARTER RELAY  ENGAGEMENT.  UNABLE TO RESTAR	T.					1	G	7	2 	3U				H1NE    					 
2000021900619	20000219	00619	EU  	2000	2	19	ERAA065952       	1	20000110	G	6230	4638205005	ROTOR MAST      		4638001007  	BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	294EH	5401 			1316	S846				MAIN ROTOR MAST CRACKED BETWEEN WEBS.  REMOVED PER AD-97-26-02 / ASB-BO-105-10-110.						1	G	7	2 	3U				H3EU    					 
2000021900615	20000219	00615	GL  	2000	2	19	ERAA065953       	2	20000113	G	7250	E23062750	HEAT SHIELD     			BOLKMS	105   	BO105A      		EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	290EH					S850				NEW HEAT SHIELD WITH OUTER BAND TOO THICK.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2000021900616	20000219	00616	SW  	2000	2	19	ERAA065954       	1	20000114	G	2435	230461030	ARMATURE        			BELL  	412   	412         	1182202	SW  										STARTER/GEN	MISREPAIRED     	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	164EH					33004				ARMATURE REPAIRED 11/5/99.  SHAFT IS OUT OF LIMITS.						1	G	7	2 	4U				H4SW    					 
2000021900617	20000219	00617	EU  	2000	2	19	ERAA065955       	1	20000114	G	6420	1053172901	HUB             			BOLKMS	105   	BO105A      		EU  										TAIL ROTOR	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	290EH					S850				BEARING JOURNALS MACHINED TOO THICK.  CAUSING RACE TO SPLIT AND SPIN.						1	G	7	2 	3U				H3EU    					 
2000021900620	20000219	00620	EU  	2000	2	19	ERAA065956       	1	20000131	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CHIPPING        	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	293EH	3719 				S844				TAILROTOR BLADES REPAIRED POG143564 4/99.  PAINT CRACKED BEYOND LIMITS AND PAINT CHIPPING OFF.						1	G	7	2 	3U				H3EU    					 
2000021900618	20000219	00618	EU  	2000	2	19	ERAA065957       	1	20000131	G	6420	10531729	HUB             			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	293EH	2406 				S844				BEARING JOURNALS SLIGHTLY OVERSIZED FROM LAST REPAIR.						1	G	7	2 	3U				H3EU    					 
2000082300001	20000823	00001	GL  	2000	8	23	EY2R48568        	3	20000613	G	6114	D6382C703	HUB             	MCAULY      		CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	MOUNTING SURFACE	CORRODED        	B			EY2R	O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03		4179 	1485 					900848		HUB CORRODED ON MOUNTING SURFACE BEYOND LIMITS.  HUB RETIRED FROM SERVICE.						1	H	7	1 	3T	3	T	NT	A37CE   	E2NE	5	C	P60GL	 
2000082300010	20000823	00010	GL  	2000	8	23	EY2R49550C       	3	20000626	G	6111	E106GA0	BLADE           	MCAULY      		CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	3AF34C	3GFR34C703  	GL  	LEADING EDGE	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4484 	998  					900933		BLADES HAVE EXFOLIATION, SENT TO MANUFACTURER FOR EVALUATION.  BLADE S/N''''S KF043, KF044, KF046 REMOVED FROM SERVICE.						1	H	7	1 	3T	3	T	NT	A37CE   	E2NE	5	C	P60GL	 
2000061600336	20000616	00336	GL  	2000	6	16	EY2R54036        	3	20000503	G	6111	57D04952	FORK            	HARTZL      		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FORWARDEARS	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					FY561			FY561		FORWARD EARS OF PITCH CHANGE FOR CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.   2 EACH CRACKS.						1	L	7	2 	4T	3	T	 	A24CE   	E2NE	5	C	STC	 
2001011104608	20010111	04608	GL  	2001	1	11	EY2R56151        	3	20000525	G	6111	C08382	CLAMP           			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  	HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CORRODED        	B			EY2R	O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03								H2485		CLAMP ASSY'S CORRODED ON BOTH INNER AND OUTER SURFACE.						1	L	7	1 	3O	3	O	 	1A15    	E295	5	C	P23EA	 
2001011103849	20010111	03849	GL  	2001	1	11	EY2R56151B       	3	20000525	G	6111	B08288	PISTON          	HARTZL      		PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540*       	41532	EA  	HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03					H2485			H2485		PISTON CORROSION ON OUTSIDE DIAMETER BEYOND LIMITS.						1	L	7	1 	3O	3	O	 	1A15    	E295	5	C	P23EA	 
2000061600414	20000616	00414	GL  	2000	6	16	EY2R56491        	3	20000605	G	6114	C4716C58	HUB             	MCAULY      	D2A34C58    	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	NR 2 BLADE SOCKE	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					788328			788328		CRACK FOUND IN NR 2 BLADE SOCKET BETWEEN 6-7 O''''CLOCK, ENGINE SIDE.  (X)						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2000061600415	20000616	00415	GL  	2000	6	16	EY2R56491A       	3	20000605	G	6111	S90AT4	BLADE           	MCAULY      	D2A34C58O   	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	THREAD AREA	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					788328			788328		TWO EACH BLADES CRACKED IN THREAD AREA.  (X)						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2000061600416	20000616	00416	GL  	2000	6	16	EY2R56491B       	3	20000605	G	6111	C4902	NUT             	MCAULY      	D2A34C58O   	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	THREAD AREA	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					788328			788328		BLADE NUT CRACKED IN THREAD AREA.  (X)						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2000061600417	20000616	00417	GL  	2000	6	16	EY2R56492        	3	20000605	G	6111	C4902	NUT             	MCAULY      	D2A34C58O   	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	THREAD AREA	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					7910189			7910189		BLADE NUT CRACKED IN THREAD AREA.  (X)						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2000061600418	20000616	00418	GL  	2000	6	16	EY2R56492A       	3	20000605	G	6114	C4716C58	HUB             	MCAULY      	D2A34C58O   	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	MOUNTING SURFACE	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					7910189			7910189		HUB CORRODED ON MOUNTING SURFACE BEYOND LIMITS.  (X)						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2000061600419	20000616	00419	CE  	2000	6	16	EY2R56492B       	1	20000605	G	6100	C3054	FERRULE         	MCAULY      	D2A34C58O   	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	THREADED AREA	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					7910189			7910189		FERRULE CORRODED IN THREADED AREA.						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2000061600442	20000616	00442	CE  	2000	6	16	EY2R56492C       	1	20000605	G	6100	C5262	CYLINDER        	MCAULY      	D2A34C58O   	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	INNER SURFACE	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					7910189			7910189		CYLINDER CORRODED ON INNER SURFACE BEYOND LIMITS.						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2001011103851	20010111	03851	GL  	2001	1	11	EY2R56606        	3	20000525	G	6110	D3252	FORK            	HARTZL      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					DJ9316A			DJ9316A		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  1 CRACK.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2000100300240	20001003	00240	CE  	2000	10	3	EY2R56607        	1	20000512	G	6100	C4503	FORK            	HARTZL      	HCC4YF2     	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCC4Y	HCC4YF2     	GL  	FORWARD EAR	CRACKED         	B			EY2R	O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03					GL60			GL60		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  8 EACH CRACKS.						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P52GL	 
2000062600051	20000626	00051	CE  	2000	6	26	EY2R56608        	1	20000512	G	6100	C4503	FORK            	HARTZL      	HCC4YF2     	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	HARTZL	HCC4Y	HCC4YF2     	GL  	FORWARD EAR	CRACKED         	B			EY2R	O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03					GL61			GL61		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.   1 EACH CRACK.						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P52GL	 
2001011103852	20010111	03852	GL  	2001	1	11	EY2R56619        	3	20000525	G	6114	D4326C211	HUB             	MCAULY      		CESSNA	177   	177         	2073704	CE  	CONT  	IO360 	IO360*      	17025	CE  	MCAULY	2D34C	B2D34C211   	GL  	PROPELLER	CORRODED        	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					762618			762618		EXTERIOR SURFACE OF HUB CORRODED BEYOND LIMITS.						1	H	7	1 	3O	3	O	NT	A13CE   	E1CE	5	C	P7EA	 
2000062600026	20000626	00026	GL  	2000	6	26	EY2R56628        	3	20000511	G	6114	57C4503	FORK            	HARTZL      		PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	FORWARD EAR	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					FH685			FH685		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS. 1 EACH CRACK.						1	L	7	1 	3O	3	O	RT	A20SO   	E14EA	5	C	P52GL	 
2000062100010	20000621	00010	GL  	2000	6	21	EY2R56679        	3	20000510	G	6111	82PA6	BLADE           	MCAULY      	B2D34C208   	CESSNA	172   	172         	2072402	CE  	LYC   	O360  	O360A1A     	41514	EA  	MCAULY	2D34C	B2D34C208   	GL  	TIP	BROKEN          	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			287  		745149			745149		TIP OF NR 2 BLADE SNAPPED OFF 3.50 INCHES. 						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P7EA	 
2000070300621	20000703	00621	GL  	2000	7	3	EY2R56802        	3	20000613	G	6111	A1851T	BEARING         	HARTZL      	HCB3TN3     						PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	SURFACE	CORRODED        	B			EY2R	O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03					BU11072			BU11072		BLADE BEARING SURFACE CORRODED.											3	T			E2NE	6	C	P15EA	 
2000091400005	20000914	00005	CE  	2000	9	14	EY2R5703         	1	20000719	G	6100	B0468	BUMPER BLOCK    	HARTZL      		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	THREADS	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4583 	1863 					FY271		FORK BUMPER CRACKED AT THE START OF THE THREADS.  REPLACED.						1	L	7	2 	4T	3	T	 	A24CE   	E2NE	5	C	STC	 
2000092100013	20000921	00013	GL  	2000	9	21	EY2R57048        	3	20000719	G	6114	B5299	STUD            	MCAULY      	DL104DSZO   	BEECH 	2000  	2000        	1152000	CE  	PWA   	PT6   	PT6*        	52043	EA  	MCAULY	5JFR36	5JFR36C1003 	GL  	OUTSIDE DIAMETER	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2112 	785  		890916					TWO STUDS CORRODED ON OUTSIDE DIAMETER.  (X)						1	L	7	2 	4T	3	T	RT	A38ACE  	E2NE	6	C	P15NE	 
2000091400012	20000914	00012	CE  	2000	9	14	EY2R57052        	1	20000720	G	6100	C7036	NUT             	MCAULY      		CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	THREADS	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			928  		724888			724888		CORROSION IN THREADS OF BLADE NUT.  REPLACED PART.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2000110100010	20001101	00010	CE  	2000	11	1	EY2R57052A       	1	20000720	G	6100	B4459	PIN             	MCAULY      		CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	SURFACE	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			928  		724888			74888		ACTUATING PIN CORRODED ON SURFACE.  (QTY. 2)  REPLACED.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA	 
2000073100221	20000731	00221	CE  	2000	7	31	EY2R57053        	1	20000727	G	6100	C3266	HUB             	HARTZL      		BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541*     	41536	EA  	HARTZL	HCF3Y	HCF3YR2     	GL  	INSIDE EXTENSION	CORRODED        	B			EY2R	O				OTHER                   				Z			SIGNIFICANT FAILURE REPORT			IN	INSP/MAINT     	1			GL	03								DA711		HUB CORRODED INSIDE EXTENSION AT THE PARTING SURFACE.						1	L	7	2 	3O	3	O	 	A12CE   	E10EA	5	C	P31EA	 
2000121800010	20001218	00010	CE  	2000	12	18	EY2R57093        	1	20000801	G	6100	A4460	PIN             	MCAULY      	3A32C88     	CESSNA	210   	210         	2073402	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	SURFACE	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					758019			758019		ACTUATING PIN CORRODED ON SURFACE OF PIN.  REPLACED.  (X)						1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P21EA	 
2000121800011	20001218	00011	GL  	2000	12	18	EY2R57093A       	3	20000801	G	6111	C4904	NUT             	MCAULY      	3A32C88     	CESSNA	210   	210         	2073402	CE  	CONT  	O520  	IO520*      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	THREAD AREA	CORRODED        	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					758019			758019		THREADS ON BLADE RETENTION NUT CORRODED.  REPLACED.  (X)						1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P21EA	 
2000110700011	20001107	00011		2000	11	7	EY2R57139        	4	20000802	G	6113	D54991	BULKHEAD        	MCAULY      		BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	MOUNTING HOLES	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03								861397		BULKHEAD CRACKED AROUND MOUNTING HOLES.  REPLACED.  (X)						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P22EA	 
2000110700024	20001107	00024	CE  	2000	11	7	EY2R57140        	1	20000802	G	3060	B5725	BRACKET         	MCAULY      	3AF32C512   	BEECH 	58    	58A         	       	CE  	CONT  	O550  	IO550*      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	RADIUS	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					861404			861404		DEICE BRACKET CRACKED IN RADIUS.  REPLACED.						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P22EA	 
2000061300291	20000613	00291	GL  	2000	6	13	EY2R811K         	3	20000428	G	6111	S78FBM15	BLADE           			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A2B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	THRD/SHNK AREA	CRACKED         	B			EY2R	O				OTHER                   				O			OTHER                     			UK	UNKNOWN        	1			GL	03								900526		BLADE CRACKED IN SHANK AND THREAD AREA.						1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P7EA	 
2000021900001	20000219	00001	SW  	2000	2	19	GJQA065663       	1	20000201	G	6320	406040021101	BEVEL GEAR      		206040004115	BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CRACKED         	H			GJQA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	01	404W	3185 			A199	52055				TRANSMISSION LOWER CHIP LIGHT ILLUMINATED IN-FLIGHT. AFTER LANDING, INSPECTION REVEALED FAIRLY LARGE FERROUS CHIP THAT A	PPEARED LIKE PIECE OF GEAR TOOTH.  TEAR DOWN INSPECTION REVEALED INPUT SPIRAL BEVEL GEAR CRACKED 360 DEGREES THROUGH THE	 RING. THE CRACK PATH EXTENDED THROUGH ONE BOLT HOLE.				1	G	7	1 	3U			NC	H2SW    					 
2000080700002	20000807	00002	SW  	2000	8	7	GJQR0000264      	1	20000209	G	6320	400040041103	SHAFT           			BELL  	206   	206L4       	1182110	SW  										M/R GEARBOX	FRETTED         	B			GJQR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	404W					52055				FRETTING FROM GEAR IN CRACK AREA.  (X)						1	G	7	1 	3U			NC	H2SW    					 
2000080700001	20000807	00001	SW  	2000	8	7	GJQR0000266      	1	20000209	G	6320	50501008380401	SEAL            			BELL  	206   	206L4       	1182110	SW  										OIL PUMP	WORN            	B			GJQR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	404W					52055				EXCESSIVE WEAR ON OIL PUMP DRIVE SHAFT.  (X)						1	G	7	1 	3U			NC	H2SW    					 
2000051600153	20000516	00153		2000	5	16	GJQR0000267      	4	20000215	G	3422	206075606107	GYRO            			BELL  	206   	206L4       	1182110	SW  										COCKPIT	DAMAGED         	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	GGWGP					52212				SETTING KNOB SLIPS WHEN TRYING TO RESET COMPASS CARD. (X)						1	G	7	1 	3U			NC	H2SW    					 
2000051600154	20000516	00154	SW  	2000	5	16	GJQR0000268      	1	20000322	G	6220	206011118001	BEARING         			BELL  	206   	206L4       	1182110	SW  										MAIN ROTOR HUB	CORRODED        	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	404W					52055				STAIN AND CORROSION PITS ON ROLLERS. (X)						1	G	7	1 	3U			NC	H2SW    					 
2000081400231	20000814	00231	SW  	2000	8	14	GJQR0000272      	1	20000419	G	7931	209062002001	INDICATOR       			BELL  	212   	212         	1181420	SW  										ENGINE	BROKEN          	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	98W	2    				35100				INDICATOR BUTTON WAS EXTREMELY DIFFICULT TO RESET AND WAS BROKE OFF WHEN ATTEMPTING TO PUSH IN.  (X)						1	G	7	1 	4U			 	H4SW    					 
2000071200003	20000712	00003	SW  	2000	7	12	GJQR0000276      	1	20000419	G	6330	206033509003	BEARING         			BELL  	206   	206L4       	1182110	SW  										XMSN RESTRAINT	WORN            	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGWGP	795  				52212				BEARINGS WORN OUT.  (X)						1	G	7	1 	3U			NC	H2SW    					 
2000071200006	20000712	00006	SW  	2000	7	12	GJQR0000277      	1	20000201	G	5210	206333001105	FRAME           			BELL  	206   	206L4       	1182110	SW  										PASSENGER DOOR	CRACKED         	B			GLQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGWGP	795  				52212				RECEIVED AND FOUND NUMEROUS DINGS THAT CAN BE FELT BY A .020 INCH PROBE, 6 DINGS MARKED.  PART CRACKED.  (X)						1	G	7	1 	3U			NC	H2SW    					 
2000051600155	20000516	00155	SW  	2000	5	16	GJQR0000278      	1	20000201	G	5320	206072406127	PANEL           			BELL  	206   	206L4       	1182110	SW  										COCKPIT	CRACKED         	B			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGWGP					552212				PLASTIC PANEL CRACKED.  NOTE:  THESE PLASTIC PANELS BECOME VERY BRITTLE IN CANADIAN WINTER WEATHER.  (X)						1	G	7	1 	3U			NC	H2SW    					 
2000080300001	20000803	00001	SW  	2000	8	3	GJQR0000280      	1	20000201	G	6420	206011819109	YOKE            			BELL  	206   	206L4       	1182110	SW  										T/R HUB	WORN            	B			GLBR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGWGP	627  				52212				YOKE WORN BEYOND ALLOWABLE LIMITS AT CONTACT AREA WITH STATIC STOP BUMPER. BUMPER MATERIAL IS VERY HARD.   (X)						1	G	7	1 	3U			NC	H2SW    					 
2000080300002	20000803	00002	SW  	2000	8	3	GJQR0000282      	1	20000419	G	6320	NAS6606D25	BOLT            			BELL  	206   	206L4       	1182110	SW  										MAIN TRANS	WORN            	B			GJQR	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGWGP	796  				52212				BOLTS WORN TRANSMISSION RESTRAINT.   (X)						1	G	7	1 	3U			NC	H2SW    					 
2000100200230	20001002	00230	SW  	2000	10	2	GJQR20000601     	1	20000619	G	6320	206040221003	SHAFT           	BELL        		BELL  	206   	206B3       	1181506	SW  										FREE WHEEL UNIT	WORN            	B			GJQR	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			NM	01	GPGH	2976 			B53497	4022				DURING OVERHAUL INSPECTION OF FREE WHEELING UNIT, IT WAS DISCOVERED THAT THE BEARING OUTER RACE HAD ROTATED IN THE HOUSI	NG. ALSO THERE WAS EXCESSIVE WEAR IN THE HOUSING INTERNAL DIMENSION.  WILL UPGRADE WITH BELL TECHNICAL BULLETIN 206-95-1	55 WITH SLOTTED OUTER SHAFT AND KEYED BEARING.  SUBMITTER STATED THIS SHOULD PREVENT THIS CONDITION IN FUTURE.				1	G	7	1 	3U			 	H2SW    					 
2001011105127	20010111	05127	CE  	2001	1	11	GLBA9190         	1	20001230	G	2810		FUEL CAP        			BEECH 	1900  	1900C       	1154161	CE  										MAIN FUEL CELL	LEAKING         	A			GLBA	A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CE	01	123UE					UC123				RETURN TO BLOCK - LEFT MAIN FUEL CAP LEAKING, REMOVED AND REINSTALLED FUEL CAP OPS CHECKED GOOD						2	L	7	2 	4T			RT	A24CE   					 
2000113000037	20001130	00037	WP  	2000	11	30	GW4R01100300     	2	20001003	G	7210	30719551	SHAFT           	GARRTT      							GARRTT	TFE731	TFE73122B   	01518	WP  					NOSE CONE	CRACKED         	B			GW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11		10786	1400 		3P5852		P74160			THIS FAN SHAFT WAS BEING INSPECTED IAW A ROUTINE HSI.  FOUND 2.5 INCH CRACK RADIATING FROM LOCK CUT-OUT.  THIS IS A PRE 	SB 72-3498 FAN SHAFT.  (X)										4	F			E6WE				 
2000062800191	20000628	00191	NM  	2000	6	28	GXPA00008        	1	20000505	G	5220	250003503	WINDOW          			PIPER 	PA60  	PA60601     	7106010	NM  										EMERGENCY WIND	BLEW OUT        	E			GXPA	O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			GL	25	160GA					61002150				AIRCRAFT EMERGENCY WINDOW BLEW OUT, WHILE IN CRUISE, AFTER TAKEOFF FROM TOLEDO.  AIRCRAFT LANDED BACK IN TOLEDO.  AIRCRA	FT GROUNDED DUE TO AWAITING REPLACEMENT WINDOW.  (X)					1	M	7	2 	3O			RT	A17WE   					 
2000082300004	20000823	00004	EA  	2000	8	23	GXPA00010        	2	20000523	G	7322		FUEL CONTROL    			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540*      	41532	EA  						MALFUNCTIONED   	E			GXPA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	25	158GA						19933			LEFT ENGINE WOULD NOT GET ABOVE 1,500 RPM BEFORE TAKEOFF.  TRIP CANCELLED.  PERFORMED GROUND RUN ON LEFT AND RIGHT ENGIN	ES.  BOTH ENGINES PERFORMED SATISFACTORILY.  FUEL MIXTURE SETTINGS MIGHT HAVE RICH CAUSING RPM LIMITATION.  AIRCRAFT S/N	, 6006087961195.  (X)				1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2000030400191	20000304	00191	EU  	2000	3	4	HCMA066409       	1	20000217	G	6520	350A33215300	HINGE           			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	422B	508  				2391				HINGE WORN BEYOND LIMITS AND CAUSES A T/R VIBRATION.						1	G	7	1 	3U			NC	H9EU    					 
2001091000254	20010910	00254	EU  	2001	9	10	HCMA075294       	1	20000629	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										TACHOMETER	DEFECTIVE       	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	A									PART IS 100 RPM LOW UPON RECEIPT FROM AEC. RMA# R026332						1	G	7	1 	3U			 	H9EU    					 
2001091000255	20010910	00255	EU  	2001	9	10	HCMA075297       	1	20000808	G	6420	350A33215300	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	862BH	737  				2713				BEARING IS WORN BEYOND LIMITS.						1	G	7	1 	3U			NC	H9EU    					 
2001091000256	20010910	00256	EU  	2001	9	10	HCMA075303       	1	20000809	G	6420	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DEFECTIVE       	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	997BH	861  				2666				PART IS DEFECTIVE. FAILED "J" GAP.						1	G	7	1 	3U			 	H9EU    					 
2001091000257	20010910	00257	EU  	2001	9	10	HCMA075308       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350BA     	8680817	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	532BH	1289 				2494				PART IS WORN BEYOND LIMITS. PLEASE OVERHAUL PC LINKS.						1	G	7	1 	3U			NC	H9EU    					 
2001091000258	20010910	00258	EU  	2001	9	10	HCMA075309       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350BA     	8680817	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	642BH					2495				PART IS WORN BEYOND LIMITS. PLEASE OVERHAUL PC LINKS. TOTAL TIME UNKNOWN.						1	G	7	1 	3U			NC	H9EU    					 
2001091000259	20010910	00259	EU  	2001	9	10	HCMA075310       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	972BH	594  				2804				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000260	20010910	00260	EU  	2001	9	10	HCMA075311       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	972BH	996  				2804				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000261	20010910	00261	EU  	2001	9	10	HCMA075312       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	982BH					2876				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS. TOTAL TIME UNKNOWN.						1	G	7	1 	3U			 	H9EU    					 
2001091000262	20010910	00262	EU  	2001	9	10	HCMA075313       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	923  				2889				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000263	20010910	00263	EU  	2001	9	10	HCMA075314       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH					2889				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS. TOTAL TIME UNKNOWN.						1	G	7	1 	3U			 	H9EU    					 
2001091000264	20010910	00264	EU  	2001	9	10	HCMA075315       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	194BH	1093 				2903				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS. TOTAL TIME UNKNOWN.						1	G	7	1 	3U			 	H9EU    					 
2001091000265	20010910	00265	EU  	2001	9	10	HCMA075316       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	194BH	588  				2903				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000266	20010910	00266	EU  	2001	9	10	HCMA075317       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	995BH					2987				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS. TOTAL TIME UNKNOWN.						1	G	7	1 	3U			 	H9EU    					 
2001091000267	20010910	00267	EU  	2001	9	10	HCMA075318       	1	20000920	G	6410	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	995BH	879  				2987				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000268	20010910	00268	EU  	2001	9	10	HCMA075319       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	196BH					3036				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS. TOTAL TIME UNKNOWN.						1	G	7	1 	3U			 	H9EU    					 
2001091000269	20010910	00269	EU  	2001	9	10	HCMA075320       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	196BH	205  				3036				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000270	20010910	00270	EU  	2001	9	10	HCMA075321       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	197BH	857  				2666				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000271	20010910	00271	EU  	2001	9	10	HCMA075322       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	197BH	430  				2666				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000272	20010910	00272	EU  	2001	9	10	HCMA075323       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	198BH	653  				3126				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000288	20010910	00288	EU  	2001	9	10	HCMA075324       	1	20000920	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	198BH	834  				3126				PART IS WORN BEYOND LIMITS.PLEASE REPLACE BEARINGS UNDER WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2000012200401	20000122	00401	SW  	2000	1	22	HEEA065587       	1	20000105	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				STARTER SPINS, BUT WILL NOT ENGAGE ENGINE.						2	G	7	2 	4U				H10SW   					 
2000012200402	20000122	00402	SW  	2000	1	22	HEEA065588       	1	20000105	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	437PH					53072				LINK WORN.  SERIAL NUMBERS REMOVED ARE NHFS-4444 AND NHFS-4552.  REPLACED WITH SERIAL NUMBERS NHFS-4333 AND NHFS-4373. D	MR NR  65595700 AND 65595701.					1	G	7	1 	3U			O	H2SW    					 
2000012200403	20000122	00403	SW  	2000	1	22	HEEA065589       	1	20000105	G	5210	407070620205	COVER           			BELL  	407   	407         		SW  										CREW DOOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	720PH					53277				COVER CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2000012200404	20000122	00404	SW  	2000	1	22	HEEA065590       	1	20000105	G	6720	406012129101	LINK ASSEMBLY   			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				LINK ASSY BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200405	20000122	00405	SW  	2000	1	22	HEEA065591       	1	20000105	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				GAUGE PRESSURE READS LOW.						1	G	7	1 	3U			O	H2SW    					 
2000012200406	20000122	00406	SW  	2000	1	22	HEEA065592       	1	20000105	G	3212	206050247137	COVER           			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200407	20000122	00407	SW  	2000	1	22	HEEA065593       	1	20000105	G	3212	206050247135	COVER           			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200408	20000122	00408	SW  	2000	1	22	HEEA065594       	1	20000105	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				LINK HAD WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000012200409	20000122	00409	SW  	2000	1	22	HEEA065595       	1	20000105	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				LINK HAD WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000012200410	20000122	00410	SW  	2000	1	22	HEEA065596       	1	20000105	G	2840	222366621103	FUEL FILTER     			BELL  	407   	407         		SW  										FUEL SYSTEM	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				FUEL FILTER LIGHT STAYS ON.						1	G	7	1 	3U			O	H2SW    					 
2000012200411	20000122	00411	SW  	2000	1	22	HEEA065597       	1	20000105	G	6220	407010150105A	FRAHM ASSY      			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				FRAM ASSY SPRING BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2000012200412	20000122	00412	SW  	2000	1	22	HEEA065599       	1	20000105	G	6420	407310203101	MOUNT           			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				MOUNT WORN AND SEPARATED.						1	G	7	1 	3U			O	H2SW    					 
2000012200413	20000122	00413	SW  	2000	1	22	HEEA065600       	1	20000105	G	3212	206050247138	COVER           			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200414	20000122	00414	SW  	2000	1	22	HEEA065601       	1	20000105	G	7120	407060111101	BIPOD MOUNT     			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BIPOD MOUNT HAD WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000012200415	20000122	00415	SW  	2000	1	22	HEEA065602       	1	20000105	G	6510	407340340101	DISC PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				DISC PACK CRACKED AND BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2000012200416	20000122	00416	SW  	2000	1	22	HEEA065603       	1	20000105	G	6710	407001523101	IDLER ASSY      			BELL  	407   	407         		SW  										M/R CONTROL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				BEARINGS ROUGH AND STAINLESS STEEL CHAFE PLATE MISSING ON IDLER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000012200453	20000122	00453	EU  	2000	1	22	HEEA065604       	1	20000106	G	6410	10531791	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J	791  				S826				PAINT ON TAIL ROTOR BLADE  FLAKING.						1	G	7	2 	3U				H3EU    					 
2000012200454	20000122	00454	EU  	2000	1	22	HEEA065605       	1	20000106	G	6410	10531791	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J	791  				S826				PAINT ON TAIL ROTOR BLADE FLAKING.						1	G	7	2 	3U				H3EU    					 
2000012200417	20000122	00417	SW  	2000	1	22	HEEA065606       	1	20000106	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				PRESSURE SWITCH INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2000012200418	20000122	00418	SW  	2000	1	22	HEEA065607       	1	20000106	G	6420	407312100101	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53003				ELASTOMERIC SEPARATION ON BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000012200419	20000122	00419	SW  	2000	1	22	HEEA065608       	1	20000106	G	6420	407012109101	CROSSHEAD       			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				T/R CROSS HEAD GROOVED WHERE P/C LINK ATTACHES.						1	G	7	1 	3U			O	H2SW    					 
2000012200420	20000122	00420	SW  	2000	1	22	HEEA065609       	1	20000106	G	2840	407362005103	SWITCH          			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LOW LEVEL LIGHT COMES ON WITH 400 POUNDS OF FUEL.						1	G	7	1 	3U			O	H2SW    					 
2000012200421	20000122	00421	SW  	2000	1	22	HEEA065610       	1	20000106	G	3212	407350301101	FLOAT           			BELL  	407   	407         		SW  										LT MLG	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	417PH					53038				LEFT FLOAT BAG LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2000012200422	20000122	00422	SW  	2000	1	22	HEEA065611       	1	20000106	G	6710	407001523101	IDLER ASSY      			BELL  	407   	407         		SW  										M/R CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				IDLER ASSY BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200423	20000122	00423	SW  	2000	1	22	HEEA065612       	1	20000106	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				GAUGE PRESSURE NEEDLE STICKS.						1	G	7	1 	3U			O	H2SW    					 
2000012200424	20000122	00424	SW  	2000	1	22	HEEA065613       	1	20000107	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				INDEX CARD LOOSE ON PRESSURE GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2000012200425	20000122	00425	SW  	2000	1	22	HEEA065614       	1	20000107	G	6710	406010421103	SPACER          			BELL  	407   	407         		SW  										CYCLIC	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				SPACER WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200426	20000122	00426	SW  	2000	1	22	HEEA065615       	1	20000107	G	6420	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH				53146	53147				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200427	20000122	00427	SW  	2000	1	22	HEEA065616       	1	20000107	G	6420	407312100101	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				ELASTOMER SEPARATION ON BEARING						1	G	7	1 	3U			O	H2SW    					 
2000012200428	20000122	00428	SW  	2000	1	22	HEEA065617       	1	20000107	G	2820	222366649101	VALVE           			BELL  	407   	407         		SW  										SUMP DRAIN	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				SUMP DRAIN LEAKING THROUGH VALVE.						1	G	7	1 	3U			O	H2SW    					 
2000012200429	20000122	00429	SW  	2000	1	22	HEEA065618       	1	20000107	G	6300	406010417101	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				BEARING WORN.  REPLACED WITH SERIAL NUMBERS A-2319 AND A-1979.						1	G	7	1 	3U			O	H2SW    					 
2000012200430	20000122	00430	SW  	2000	1	22	HEEA065619       	1	20000107	G	3310	A490A	POWER SUPPLY    			BELL  	407   	407         		SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407MM					53060				POWER SUPPLY WORKED INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2000012200431	20000122	00431	SW  	2000	1	22	HEEA065620       	1	20000107	G	6320	214040806003	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				PRESSURE SWITCH WORN.						1	G	7	1 	3U			O	H2SW    					 
2000012200432	20000122	00432	SW  	2000	1	22	HEEA065621       	1	20000107	G	5210	407070620205	COVER           			BELL  	407   	407         		SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				COVER WORN/CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2000012200433	20000122	00433	SW  	2000	1	22	HEEA065622       	1	20000107	G	6321	406010429101	PIN             			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				PIN WORN.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200434	20000122	00434	SW  	2000	1	22	HEEA065623       	1	20000107	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				NEEDLE STICKS ON PRESSURE GAUGE.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200435	20000122	00435	SW  	2000	1	22	HEEA065624       	1	20000107	G	6230	406310411101	BOOT            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				BOOT WORN.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200436	20000122	00436	SW  	2000	1	22	HEEA065625       	1	20000107	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				VELCRO DETACHING ON FLOAT COVER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000012200437	20000122	00437	SW  	2000	1	22	HEEA065626       	1	20000107	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				VELCRO RIPPING OFF OF FLOAT COVER ASSY.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200438	20000122	00438	SW  	2000	1	22	HEEA065627       	1	20000107	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										M/R DRIVE	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				MGT INDICATOR STUCK ON ZERO DURING START-UP FOR 10 TO 15 SECONDS.						1	G	7	1 	3U			O	H2SW    					 
2000012200439	20000122	00439	SW  	2000	1	22	HEEA065628       	1	20000107	G	6220	407012110101	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				ELASTOMER IN FLAPPING BEARING.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200440	20000122	00440	SW  	2000	1	22	HEEA065629       	1	20000107	G	5210	407070620137	PANEL           			BELL  	407   	407         		SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				CREW PANEL DOOR CRACKED AND WORN.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200441	20000122	00441	SW  	2000	1	22	HEEA065630       	1	20000107	G	5210	407070620125	PANEL           			BELL  	407   	407         		SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				COLLECTIVE PANEL CRACKED.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200442	20000122	00442	SW  	2000	1	22	HEEA065631       	1	20000107	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				LINK HAD WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS-3233 AND NHFS-3283.   REPLACED WITH SERIAL NUMBERS NHFS-4667.						1	G	7	1 	3U			O	H2SW    					 
2000012200443	20000122	00443	SW  	2000	1	22	HEEA065633       	1	20000107	G	6230	289053499	SEAL            			BELL  	407   	407         		SW  										M/R MAST	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				SEAL WORN.   SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2000012200444	20000122	00444	SW  	2000	1	22	HEEA065635       	1	20000107	G	6220	407001732101	BELLCRANK       			BELL  	407   	407         	1182206	SW  										T/R CONTROL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				TAIL ROTOR CONTROL BELLCRANK ASSY HAD GROOVE WORN INTO CLEVIS FROM ROD ENDS (2 PLACES).						1	G	7	1 	3U			O	H2SW    					 
2000012200445	20000122	00445	SW  	2000	1	22	HEEA065636       	1	20000107	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA				53006	53016				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000012200446	20000122	00446	SW  	2000	1	22	HEEA065638       	1	20000107	G	3260	8869K59	SWITCH          			BELL  	407   	407         		SW  										MLG	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				SWITCH INOPERATIVE.  SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2000012200447	20000122	00447	SW  	2000	1	22	HEEA065640       	1	20000107	G	2510	407370721105	RESTRAINT       			BELL  	407   	407         		SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				RESTRAINT ASSY FRAYED.  SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000012200448	20000122	00448	SW  	2000	1	22	HEEA065641       	1	20000107	G	6420	406312100101	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	825  				53003				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000012200449	20000122	00449	SW  	2000	1	22	HEEA065642       	1	20000107	G	6320	214040806003	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				PRESSURE SWITCH STICKS IN OPEN POSITION.						1	G	7	1 	3U			O	H2SW    					 
2000012200450	20000122	00450	SW  	2000	1	22	HEEA065643       	1	20000107	G	2910	206076035103	FILTER          			BELL  	407   	407         		SW  										HYD SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				BYPASS WILL NOT EXTEND ALL THE WAY ON FILTER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000012200451	20000122	00451	SW  	2000	1	22	HEEA065644       	1	20000107	G	2900	206076035103	FILTER ASSY     			BELL  	407   	407         		SW  										FUEL SYSTEM	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	510PH					53209				FILTER ASSY LEAKS FROM FILTER BOWL.						1	G	7	1 	3U			O	H2SW    					 
2000012200452	20000122	00452	SW  	2000	1	22	HEEA065645       	1	20000107	G	6420	406312100101	BEARING         			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000021900002	20000219	00002	GL  	2000	2	19	HEEA065850       	2	20000203	G	7260	230312681	BEARING         		23035178    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610C	6559 			CAG95682	51425	CAE895674			ENGINE REMOVED DUE TO TURBINE WHEEL RETIREMENT.   GEARBOX REPAIRED DUE TO CEBA72-3217R-2.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900003	20000219	00003	GL  	2000	2	19	HEEA065851       	2	20000203	G	7260	23031219	BEARING         		23035178    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610C	6559 			CAG95682	51425	CAE895674			ENGINE REMOVED DUE TO TURBINE WHEEL RETIREMENT.   GEARBOX REPAIRED DUE TO CEBA72-3217R-2.  SERIAL NUMBERS REMOVED ARE MP	04047 AND MP04048.  REPLACED WITH SERIAL NUMBERS JJ02742 AND JJ02782.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900004	20000219	00004	GL  	2000	2	19	HEEA065852       	2	20000203	G	7260	230312081	BEARING         		23035179    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G	6866 			CAG90831	760232	CAE890823S			ENGINE REMOVED DUE TO CYCLED OUT.  GEARBOX REPAIRED DUE TO CEBA72-3217R-2.						1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2000021900005	20000219	00005	GL  	2000	2	19	HEEA065853       	2	20000203	G	7260	23031458	BEARING         		23035179    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 3 PINION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G	6866 			CAG90831	760232	CAE890823S			ENGINE REMOVED DUE TO CYCLED OUT.  GEARBOX REPAIRED DUE TO CEBA72-3217R-2.  SERIAL NUMBERS REMOVED ARE CG0230 AND CG0222	.  REPLACED WITH SERIAL NUMBERS JJ02757 AND JJ02739.					1	G	7	2 	3U	3	U		H1NE    	E1GL				 
2000021900006	20000219	00006	GL  	2000	2	19	HEEA065854       	2	20000203	G	7260	230312681	BEARING         		23035178    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E	6286 			CAG95553	51498	CAE895547			ENGINE REMOVED DUE TO TURBINE WHEEL RETIREMENT.   GEARBOX REPAIRED DUE TO CEBA72-3217R-2.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900007	20000219	00007	GL  	2000	2	19	HEEA065855       	2	20000203	G	7260	23031219	BEARING         		23035178    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E	6286 			CAG95553	51498	CAE895547			ENGINE REMOVED DUE TO TURBINE WHEEL RETIREMENT.  GEARBOX REPAIRED DUE TO CEBA72-3217R-2.  SERIAL NUMBERS REMOVED ARE MP0	2952 AND MP02953.  REPLACED WITH SERIAL NUMBERS JJ02399 AND JJ03506.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900008	20000219	00008	GL  	2000	2	19	HEEA065856       	2	20000203	G	7260	23031219	BEARING         		23053349    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077	10236			CAG95111	51520	CAE895111			ENGINE REMOVED DUE TO TURBINE WHEEL RETIREMENT.   GEARBOX REPAIRED DUE TO CEBA72-3217R-2.  SERIAL NUMBERS REMOVED ARE MP	01281 AND MP01162.  REPLACED WITH SERIAL NUMBERS JJ02329 AND JJ02198.					1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900009	20000219	00009	GL  	2000	2	19	HEEA065857       	2	20000203	G	7260	230312681	BEARING         		23053349    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077	5292 			CAG95111	51520	CAE895111			ENGINE REMOVED DUE TO TURBINE WHEEL RETIREMENT.   GEARBOX REPAIRED DUE TO CEBA72-3217R-2.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900010	20000219	00010	GL  	2000	2	19	HEEA065858       	2	20000203	G	7260	23031219	BEARING         		23035178    	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127	6149 			CAG95720	52023	CAE895712			ENGINE REMOVED DUE TO CYCLED OUT.  GEARBOX REPAIRED DUE TO CEBA72-3217R-2.  SERIAL NUMBERS REMOVED ARE MP04281 AND MP043	70.  REPLACED WITH SERIAL NUMBERS JJ02784 AND JJ02743.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2000021900011	20000219	00011	GL  	2000	2	19	HEEA065859       	2	20000203	G	7260	230312681	BEARING         		23035178    	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 3 & 4	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127	6149 			CAG95720	52023	CAE895712			ENGINE REMOVED DUE TO CYCLED OUT.  GEARBOX REPAIRED DUE TO CEBA72-3217R-2.						1	G	7	1 	3U	3	U	NC	H2SW    	E1GL				 
2000021900012	20000219	00012	GL  	2000	2	19	HEEA065860       	2	20000203	G	7250	23032345	COUPLING        		23035128    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					N1	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4282Z				CAT97772	51499	CAE890024			RECEIVING INSPECTION REVEALED PART NOT PRESERVED AT MANUFACTURER CAUSING RUST.  CLEANED, INSPECTED AND PRESERVED PART.						1	G	7	1 	3U	3	U		H2SW    	E1GL				 
2000021900013	20000219	00013	GL  	2000	2	19	HEEA065861       	2	20000203	G	7320	23069551	HMU             			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	1217 				53207	CAE847080			HMU REMOVED DUE TO FADEC DEGRADE LIGHT AND FOUND ROLL PIN BROKEN UPON 300 HOUR BACKLASH INSPECTION.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2000021900014	20000219	00014	GL  	2000	2	19	HEEA065862       	2	20000203	G	7320	23069551	HMU             			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH	870  				53142	CAE847043			SHEARED DRIVE SHAFT PIN.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2000021900015	20000219	00015		2000	2	19	HEEA065863       	4	20000203	G	2210	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				ROLL CHANNEL WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW   					 
2000021900070	20000219	00070	EU  	2000	2	19	HEEA065864       	1	20000203	G	6310	350A35105901	COUPLING        			SNIAS 	350   	AS350B2     	8680813	EU  										ENG TO G/B	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	350BZ					2653				COUPLING-BUSHES CRACKED.						1	G	7	1 	3U				H9EU    					 
2000021900071	20000219	00071	EU  	2000	2	19	HEEA065867       	1	20000203	G	6520	350A33200406	SPIDER          			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	950AE	41   				3235				SPIDER ASSY CRACKED.						1	G	7	1 	3U				H9EU    					 
2000021900072	20000219	00072	EU  	2000	2	19	HEEA065869       	1	20000203	G	7921	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  										OIL COOLER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				BLOWER NOT WORKING.						1	G	7	1 	3U				H9EU    					 
2000021900073	20000219	00073	EU  	2000	2	19	HEEA065870       	1	20000203	G	6320	350A37000402	TRANSMISSION    			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L	3016 				2873				COATING ON MAST WORN.  P/N 704A33-651-158, S/N NR-1176; P/N 350A37-1290-03, S/N M4661 INCLUDED.  (BUILT-UP UPPER TRANS. 	S/PLATE).					1	G	7	1 	3U				H9EU    					 
2000021900016	20000219	00016	SW  	2000	2	19	HEEA065874       	1	20000204	G	6410		BEARING         		407012101111	BELL  	407   	407         		SW  										T/R BLADE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1152 			53327	53060				WORN FEATHERING BEARINGS.  SERIAL NUMBERS REMOVED ARE A-2248 AND A-2252.  REPLACED WITH SERIAL NUMBERS A-2099 (DMR NR 68	61800) AND A-2098 (DMR NR 6861801).					1	G	7	1 	3U			O	H2SW    					 
2000021900017	20000219	00017	SW  	2000	2	19	HEEA065876       	1	20000204	G	6220	407001524105	BEARING         			BELL  	407   	407         		SW  										M/R BELLCRANK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH	2149 				53188				BELLCRANK HAD WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000021900018	20000219	00018	SW  	2000	2	19	HEEA065877       	1	20000204	G	6300	407340339103	BEARING         		406040320101	BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH				AFS1174	53288				UNABLE TO BALANCE.  SERIAL NUMBERS REMOVED ARE H99-1801 AND H99-1785.						1	G	7	1 	3U			O	H2SW    					 
2000021900019	20000219	00019	SW  	2000	2	19	HEEA065878       	1	20000204	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				UNABLE TO BALANCE SHAFT ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900020	20000219	00020	SW  	2000	2	19	HEEA065879       	1	20000204	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				LCD DISPLAY WENT BLANK IN CRUISE FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2000021900021	20000219	00021	SW  	2000	2	19	HEEA065880       	1	20000204	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	ERRATIC         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				ERRATIC ON GROUND AND FAILS IN-FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2000021900022	20000219	00022	SW  	2000	2	19	HEEA065881       	1	20000204	G	6220	407010150105A	FRAHM ASSY      			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				SPRING BROKEN ON FRAM ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900023	20000219	00023	SW  	2000	2	19	HEEA065884       	1	20000204	G	6300	407340339103	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				UNABLE TO BALANCE DUE TO BEARING VIBRATION.  SERIAL NUMBERS REMOVED ARE J98-1872 AND J98-1857.						1	G	7	1 	3U			O	H2SW    					 
2000021900024	20000219	00024	SW  	2000	2	19	HEEA065885       	1	20000204	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				SHAFT ASSY HAD WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2000021900025	20000219	00025	SW  	2000	2	19	HEEA065886       	1	20000204	G	6300	407340339103	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				ROUGH BEARINGS.  SERIAL NUMBERS REMOVED ARE H98-2216 AND H98-2303.						1	G	7	1 	3U			O	H2SW    					 
2000021900026	20000219	00026	SW  	2000	2	19	HEEA065887       	1	20000204	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				SPLINES WORN ON SHAFT ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900027	20000219	00027	SW  	2000	2	19	HEEA065888       	1	20000204	G	6300	407340339103	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				ROUGH BEARINGS.  SERIAL NUMBERS REMOVED ARE H98-2245 AND H98-2324.						1	G	7	1 	3U			O	H2SW    					 
2000021900028	20000219	00028	SW  	2000	2	19	HEEA065889       	1	20000204	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				SPLINES WORN ON SHAFT ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900029	20000219	00029	SW  	2000	2	19	HEEA065890       	1	20000204	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				SPLINES WORN ON SHAFT ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900030	20000219	00030	SW  	2000	2	19	HEEA065891       	1	20000204	G	6300	407340339103	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				ROUGH BEARINGS.  SERIAL NUMBERS REMOVED ARE H98-2243 AND H98-2317.						1	G	7	1 	3U			O	H2SW    					 
2000021900031	20000219	00031	SW  	2000	2	19	HEEA065892       	1	20000204	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH				53170	53072				BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900032	20000219	00032		2000	2	19	HEEA065893       	4	20000204	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         		SW  										COCKPIT	SLOW            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				CLOCK LOSES 1 HOUR EVERY 12 HOURS.						1	G	7	1 	3U			O	H2SW    					 
2000021900033	20000219	00033	SW  	2000	2	19	HEEA065894       	1	20000204	G	6510	206061432116	HOUSING         			BELL  	407   	407         		SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2000021900034	20000219	00034	SW  	2000	2	19	HEEA065895       	1	20000204	G	2840	407362005103	SWITCH          			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				LOW LEVEL LIGHT CAME ON WITH 800 POUNDS FUEL.						1	G	7	1 	3U			O	H2SW    					 
2000021900035	20000219	00035	SW  	2000	2	19	HEEA065896       	1	20000204	G	7110	206061249001	FITTING         			BELL  	407   	407         		SW  										ENGINE COWL	GALLED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				FITTING HAD GALLED THREADS.						1	G	7	1 	3U			O	H2SW    					 
2000021900036	20000219	00036	SW  	2000	2	19	HEEA065897       	1	20000204	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900037	20000219	00037	SW  	2000	2	19	HEEA065898       	1	20000204	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1152 			53327	53060				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000021900038	20000219	00038	SW  	2000	2	19	HEEA065900       	1	20000204	G	6310	406340102101	CARBON SEAL     			BELL  	407   	407         		SW  										FREE WHEEL	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				CARBON SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2000021900039	20000219	00039	SW  	2000	2	19	HEEA065901       	1	20000204	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				LINK HAD WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS-3303 AND NHFS-3299.   REPLACED WITH SERIAL NUMBERS NHFS-4662 (D	MR NR 65600801) AND NHFS-4672 (DMR NR 65600900).					1	G	7	1 	3U			O	H2SW    					 
2000021900040	20000219	00040	SW  	2000	2	19	HEEA065902       	1	20000204	G	7700	407375016103	SIGNAL COND     			BELL  	407   	407         		SW  										ENGINE	ERRATIC         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				SIGNAL COND ERRATIC IN-FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2000021900041	20000219	00041	SW  	2000	2	19	HEEA065903       	1	20000204	G	6300	407010206103	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	1325 				53199				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000021900042	20000219	00042	SW  	2000	2	19	HEEA065904       	1	20000204	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2000021900043	20000219	00043	SW  	2000	2	19	HEEA065905       	1	20000204	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH					53114				FAILED TO START THREE TIMES WITH NO START OR IGNITION LIGHT.						1	G	7	1 	3U			O	H2SW    					 
2000021900044	20000219	00044	SW  	2000	2	19	HEEA065906       	1	20000204	G	5620	407030607101	WINDOW          			BELL  	407   	407         		SW  										CABIN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH	73   				53390				WINDOW CRACKED DUE TO SCREWS TIGHTENED TOO TIGHT.						1	G	7	1 	3U			O	H2SW    					 
2000021900045	20000219	00045	SW  	2000	2	19	HEEA065907       	1	20000204	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900046	20000219	00046	SW  	2000	2	19	HEEA065908       	1	20000204	G	3230	70079H100F210	HOSE            			BELL  	407   	407         		SW  										MLG	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				HOSE ASSY CHAFED AT END.						1	G	7	1 	3U			O	H2SW    					 
2000021900047	20000219	00047	SW  	2000	2	19	HEEA065909       	1	20000204	G	3230	70079H100F210	HOSE            			BELL  	407   	407         		SW  										MLG	TWISTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				HOSE ASSY TWISTED.						1	G	7	1 	3U			O	H2SW    					 
2000021900048	20000219	00048	SW  	2000	2	19	HEEA065910       	1	20000204	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900049	20000219	00049	SW  	2000	2	19	HEEA065911       	1	20000204	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900050	20000219	00050	SW  	2000	2	19	HEEA065912       	1	20000204	G	3230	70079H100F210	HOSE            			BELL  	407   	407         		SW  										MLG	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				NIPPLE BROKEN OFF IN B-NUT ON HOSE ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900051	20000219	00051	SW  	2000	2	19	HEEA065913       	1	20000204	G	7120	407060111101	BIPOD MOUNT     			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				BIPOD MOUNT HAD BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900052	20000219	00052	SW  	2000	2	19	HEEA065914       	1	20000204	G	6510	206061432121	HOUSING         			BELL  	407   	407         		SW  										BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				BLOWER HOUSING HAD WORKING AND MISSING RIVETS.						1	G	7	1 	3U			O	H2SW    					 
2000021900053	20000219	00053	SW  	2000	2	19	HEEA065915       	1	20000204	G	5210	20898422	LATCH           			BELL  	407   	407         		SW  										CREW DOOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				LATCH ASSY HAD SPRING BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2000021900054	20000219	00054	SW  	2000	2	19	HEEA065916       	1	20000204	G	6710	407001523101	IDLER ASSY      			BELL  	407   	407         		SW  										M/R CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				IDLER ASSY HAD BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900055	20000219	00055	SW  	2000	2	19	HEEA065917       	1	20000204	G	3230	70079H100F210	HOSE            			BELL  	407   	407         		SW  										MLG	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				HOSE ASSY BENT AND KINKED.						1	G	7	1 	3U			O	H2SW    					 
2000021900056	20000219	00056	SW  	2000	2	19	HEEA065918       	1	20000204	G	3246	206053184121	SKID TUBE       			BELL  	407   	407         		SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				SKID TUBE ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900057	20000219	00057	SW  	2000	2	19	HEEA065919       	1	20000204	G	3246	206053184122	SKID TUBE       			BELL  	407   	407         		SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				SKID TUBE ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900058	20000219	00058	SW  	2000	2	19	HEEA065920       	1	20000204	G	3230	70079F045Z083	HOSE            			BELL  	407   	407         		SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				HOSE ASSY LEAKS AT FITTING.						1	G	7	1 	3U			O	H2SW    					 
2000021900059	20000219	00059	SW  	2000	2	19	HEEA065921       	1	20000204	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				LINK HAD WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000021900060	20000219	00060	SW  	2000	2	19	HEEA065922       	1	20000204	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				LIGHT WILL NOT ILLUMINATE IN OFF POSITION.						1	G	7	1 	3U			O	H2SW    					 
2000021900061	20000219	00061	SW  	2000	2	19	HEEA065923       	1	20000204	G	6710	406010421103	SPACER          			BELL  	407   	407         		SW  										CYCLIC	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				SPACER HAD WORN BUSHING ON DRIVE LINK.						1	G	7	1 	3U			O	H2SW    					 
2000021900062	20000219	00062	SW  	2000	2	19	HEEA065924       	1	20000204	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				LINK HAD WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000021900063	20000219	00063	SW  	2000	2	19	HEEA065925       	1	20000204	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				LINK HAD WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000021900064	20000219	00064	SW  	2000	2	19	HEEA065926       	1	20000204	G	6220	407310101101	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				BEARING  WORN AND SHEARED RUBBER.  SERIAL NUMBERS REMOVED ARE LK5157 AND LK5154.  REPLACED WITH SERIAL NUMBERS LP7115 (D	MR NR 65607101) AND LP5718 (DMR NR 65607102).					1	G	7	1 	3U			O	H2SW    					 
2000021900065	20000219	00065	SW  	2000	2	19	HEEA065927       	1	20000204	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										MLG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				VELCRO TEARING ON FLOAT COVER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900066	20000219	00066	SW  	2000	2	19	HEEA065928       	1	20000204	G	3212	206050247132	COVER           			BELL  	407   	407         		SW  										MLG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				VELCRO TEARING ON FLOAT COVER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900067	20000219	00067	SW  	2000	2	19	HEEA065929       	1	20000204	G	3212	206050247135	COVER           			BELL  	407   	407         		SW  										MLG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				VELCRO TEARING ON FLOAT COVER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900068	20000219	00068	SW  	2000	2	19	HEEA065930       	1	20000204	G	3212	206050247138	COVER           			BELL  	407   	407         		SW  										MLG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				VELCRO TEARING ON FLOAT COVER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900069	20000219	00069	SW  	2000	2	19	HEEA065931       	1	20000204	G	3110	407375005101	INDICATOR       			BELL  	407   	407         		SW  										TRANS OIL TEMP	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	409PH					53059				PRESSURE SIDE GOES INTO TEST MODE INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2000021900630	20000219	00630	SW  	2000	2	19	HEEA065971       	1	20000110	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				LINK HAD WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS-2385 AND NHFS-2833.  REPLACED WITH SERIAL NUMBERS NHFSA-4778 AN	D NHFSA-4380.					1	G	7	1 	3U			O	H2SW    					 
2000021900631	20000219	00631	SW  	2000	2	19	HEEA065973       	1	20000110	G	5302	407030801101B	SKIN            			BELL  	407   	407         		SW  										TAIL BOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH	1574 				53147				SKIN CRACKED AT LT SIDE AT HORIZONTAL STABILIZER.						1	G	7	1 	3U			O	H2SW    					 
2000021900649	20000219	00649	EU  	2000	2	19	HEEA065974       	1	20000110	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL BOOST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				FUEL PUMP INOPERATIVE.						1	G	7	1 	3U				H9EU    					 
2000021900650	20000219	00650	EU  	2000	2	19	HEEA065975       	1	20000110	G	2510	504305401	INERTIA REEL    			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				INERTIA REEL STAYS STUCK.						1	G	7	1 	3U				H9EU    					 
2000021900651	20000219	00651	EU  	2000	2	19	HEEA065976       	1	20000110	G	6220	704A3363310951	STOP ASSY       			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	1609 				2653				BEARINGS CRACKED AND SEPARATED.  SERIAL NUMBERS REMOVED ARE 11534 AND 11705.  REPLACED WITH SERIAL NUMBERS 0931 AND 0906	.					1	G	7	1 	3U				H9EU    					 
2000021900652	20000219	00652	EU  	2000	2	19	HEEA065977       	1	20000110	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				ROD, PITCH CONTROL HAD WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE S3672 AND S3739.   REPLACED WITH SERIAL NUMBERS S3796 	AND S3811.					1	G	7	1 	3U				H9EU    					 
2000021900653	20000219	00653	EU  	2000	2	19	HEEA065978       	1	20000110	G	6230	350A37112702	LINK SCISSORS   			SNIAS 	350   	AS350B2     	8680813	EU  										M/R MAST	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				LINK SCISSORS HAD WORN BEARINGS.						1	G	7	1 	3U				H9EU    					 
2000021900654	20000219	00654	EU  	2000	2	19	HEEA065979       	1	20000110	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										HYD SYSTEM	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				HYDRAULIC PUMP HAD WORN SPLINES.						1	G	7	1 	3U				H9EU    					 
2000021900655	20000219	00655	EU  	2000	2	19	HEEA065980       	1	20000110	G	2913	350A35013004	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										HYD SYSTEM	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				HYDRAULIC PUMP HAD WORN SPLINES.						1	G	7	1 	3U				H9EU    					 
2000021900629	20000219	00629	GL  	2000	2	19	HEEA065981       	2	20000113	G	7250	23008020	TIE BOLT        		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE SECTION	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	81832				CAT33770	S828	CAE830763			RECEIVING INSPECTION REVEALED FREE LENGTH .0005 INCH OVER SERVICEABLE LIMITS.						1	G	7	2 	3U	3	U		H3EU    	E4CE				 
2000021900656	20000219	00656	EU  	2000	2	19	HEEA065982       	1	20000117	G	2435	150SG122Q	SHAFT           			SNIAS 	350   	AS350B2     	8680813	EU  										STARTER/GEN	SHEARED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4031L					2907				STARTER/GENERATOR SHAFT SHEARED.						1	G	7	1 	3U				H9EU    					 
2000021900657	20000219	00657	EU  	2000	2	19	HEEA065983       	1	20000117	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										OIL PRESSURE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				TRANSMITTER DID NOT REGISTER OIL PRESSURE ON INDICATOR.						1	G	7	1 	3U				H9EU    					 
2000021900658	20000219	00658	NE  	2000	2	19	HEEA065984       	2	20000117	G	7200		ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE BAY	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				ENGINE MAKING METAL.						1	G	7	1 	3U	3	U		H9EU    	E19EU				 
2000021900632	20000219	00632	SW  	2000	2	19	HEEA065985       	1	20000117	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										MGT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				MGT INDICATOR QUIT ON ENGINE WASH.						1	G	7	1 	3U			O	H2SW    					 
2000021900633	20000219	00633	SW  	2000	2	19	HEEA065986       	1	20000117	G	6510	206061432119	IMPELLER        			BELL  	407   	407         		SW  										BLOWER ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				IMPELLER WORN ON BLOWER ASSY.						1	G	7	1 	3U			O	H2SW    					 
2000021900634	20000219	00634	SW  	2000	2	19	HEEA065990       	1	20000117	G	6321	206340301103	BOLT            			BELL  	407   	407         		SW  										ROTOR BRAKE	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	3077 				53159				STRIPPED BOLTS WHEN SAFETY BRAKE.						1	G	7	1 	3U			O	H2SW    					 
2000021900635	20000219	00635	SW  	2000	2	19	HEEA065991       	1	20000117	G	6321	206340301103	BOLT            			BELL  	407   	407         		SW  										ROTOR BRAKE	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	3077 				53159				STRIPPED BOLTS WHEN SAFETY BRAKE.						1	G	7	1 	3U			O	H2SW    					 
2000021900636	20000219	00636	SW  	2000	2	19	HEEA065992       	1	20000117	G	6420	407310203101	MOUNT           			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				ELASTOMERIC WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900637	20000219	00637	SW  	2000	2	19	HEEA065993       	1	20000117	G	6420	407012109101	CROSSHEAD       			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				WORN SPOTS ON CROSSHEAD FROM P/C LINKS.						1	G	7	1 	3U			O	H2SW    					 
2000021900638	20000219	00638	SW  	2000	2	19	HEEA065994       	1	20000117	G	2840	407362005103	SWITCH          			BELL  	407   	407         		SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				LOW LEVEL LIFT WILL NOT GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2000021900639	20000219	00639	SW  	2000	2	19	HEEA065995       	1	20000117	G	6320	222060084101	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				PRESSURE SWITCH FAILED.						1	G	7	1 	3U			O	H2SW    					 
2000021900640	20000219	00640	SW  	2000	2	19	HEEA065996       	1	20000117	G	6510	206061432121	HOUSING         			BELL  	407   	407         		SW  										BLOWER ASSY	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				WORKING RIVETS AND ONE MISSING ON BLOWER HOUSING.						1	G	7	1 	3U			O	H2SW    					 
2000021900641	20000219	00641	SW  	2000	2	19	HEEA065997       	1	20000117	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				LINK HAD BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900642	20000219	00642	SW  	2000	2	19	HEEA065998       	1	20000117	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				LINK HAD BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900643	20000219	00643	SW  	2000	2	19	HEEA065999       	1	20000117	G	6510	407040316101	FLYWHEEL        			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				FLYWHEEL HAD WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2000021900644	20000219	00644	SW  	2000	2	19	HEEA066000       	1	20000117	G	3310	FCB205AT4	RELAY           			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				BAD CAUTION LIGHT AND HORN DID NOT WORK.						1	G	7	1 	3U			O	H2SW    					 
2000021900645	20000219	00645	SW  	2000	2	19	HEEA066001       	1	20000118	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	722PH					53288				UNIVERSAL LEAKING GREASE FITTING.						1	G	7	1 	3U			O	H2SW    					 
2000021900646	20000219	00646	SW  	2000	2	19	HEEA066002       	1	20000118	G	3212	407350302101	FLOAT BAG       			BELL  	407   	407         		SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	721PH					53278				FLOAT BAG LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2000021900647	20000219	00647	SW  	2000	2	19	HEEA066003       	1	20000118	G	6710	406312103101	LINK            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				LINK BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2000021900648	20000219	00648	SW  	2000	2	19	HEEA066004       	1	20000119	G	2450	M835362028M	RELAY           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				HORN WOULD NOT COME ON.  PART SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000032300589	20000323	00589	SW  	2000	3	23	HEEA066501       	1	20000215	G	6420	407012101111	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	2778 				53159				REMOVED TAIL ROTOR ASSEMBLY DUE TO TRUNNION ELASTOMERIC BEARING SEPARATION AND EXTRUDING.						1	G	7	1 	3U			O	H2SW    					 
2000032300590	20000323	00590	SW  	2000	3	23	HEEA066502       	1	20000215	G	6520	406040400117FM	GEARBOX         			BELL  	407   	407         		SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	723PH	1038 				53283				TAIL ROTOR GEARBOX LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2000032300591	20000323	00591	SW  	2000	3	23	HEEA066503       	1	20000215	G	6230	406010401115	SWASHPLATE      			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	1164 				53267				MECHANICAL DAMAGE ON HORNS OF STATIONARY RING.						1	G	7	1 	3U			O	H2SW    					 
2000032300592	20000323	00592	SW  	2000	3	23	HEEA066504       	1	20000215	G	6220	407010100111	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	1240 				53199				DUE GRIP RETIREMENT.  AT INSPECTION OF PARTS FOUND CORROSION IN DAMPER BEARING BORE AND CORROSION UNDER PADS OF PITCH HO	RNS.					1	G	7	1 	3U			O	H2SW    					 
2000032300593	20000323	00593	SW  	2000	3	23	HEEA066505       	1	20000215	G	2435	206062200113	DRIVESHAFT      			BELL  	407   	407         		SW  										STARTER/GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH	1378 				53147				STARTER/GENERATOR INOPERATIVE.  INSPECTED BY ACCESSORY SHOP AND FOUND FAN WAS LOOSE, DRIVESHAFT, FAN AND ARMATURE SPLINE	S WORN, BACKPLATE, DAMPENER PLATE, HUB AND FRICTION RING ALSO WORN.					1	G	7	1 	3U			O	H2SW    					 
2000032300594	20000323	00594	SW  	2000	3	23	HEEA066506       	1	20000215	G	6322	PHIPBH40701	BLOWER          			BELL  	407   	407         		SW  										OIL COOLER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				OIL COOLER BLOWER HAS ROUGH BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000032300595	20000323	00595	SW  	2000	3	23	HEEA066507       	1	20000215	G	6420	407012101111	HUB             			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH	933  				53283				FEATHERING BEARINGS WORN AND TEFLON COMING OUT FROM AROUND BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000032300596	20000323	00596	SW  	2000	3	23	HEEA066508       	1	20000215	G	6320	407040006107	TRANSMISSION    			BELL  	407   	407         		SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	416  				53207				TRANSMISSION MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2000032300597	20000323	00597	SW  	2000	3	23	HEEA066509       	1	20000215	G	6321	D01631	PAD ASSY        			BELL  	407   	407         		SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				PAD ASSEMBLY WORN.  SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000032300598	20000323	00598	SW  	2000	3	23	HEEA066510       	1	20000215	G	5320	206032305129	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				ANGLE CRACKED.  SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2000032300599	20000323	00599	SW  	2000	3	23	HEEA066512       	1	20000215	G	7920	407040623101	OIL TUBE        			BELL  	407   	407         		SW  										SLEEVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				OIL TUBE HAS CRACKED SLEEVE.						1	G	7	1 	3U			O	H2SW    					 
2000032300600	20000323	00600	SW  	2000	3	23	HEEA066513       	1	20000215	G	2432	28SP100	CELL            			BELL  	407   	407         		SW  										BATTERY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				BURNT CELL.						1	G	7	1 	3U			O	H2SW    					 
2000032300601	20000323	00601	SW  	2000	3	23	HEEA066514       	1	20000215	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				LINK HAS WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS-4335 AND NHFS-4384.  REPLACED WITH SERIAL NUMBERS NHFS-4806 (DM	R NR 65602300) AND NHFS-4763 (DMR NR 65602301).					1	G	7	1 	3U			O	H2SW    					 
2000032300602	20000323	00602	SW  	2000	3	23	HEEA066515       	1	20000215	G	6420	407310203101	MOUNT           			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				RUBBER ON MOUNT DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2000032300603	20000323	00603	SW  	2000	3	23	HEEA066516       	1	20000216	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER/GEN	WORN            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	57416	1170 				53070				FAILED 300 HOUR INSPECTION.  INSPECTED BY ACCESSORY SHOP AND FOUND BRUSHES EXCESSIVELY WORN. REPAIRED BY PHI.  PARTS AND	 LABOR TO BE BILLED...J0077086-CU  (DMR#686695)					1	G	7	1 	3U			O	H2SW    					 
2000032300604	20000323	00604	SW  	2000	3	23	HEEA066517       	1	20000216	G	7712	407375003107	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				WITH POWER ON, GAUGE INDICATES AN EXCESS OF 134.5.						1	G	7	1 	3U			O	H2SW    					 
2000032300605	20000323	00605	SW  	2000	3	23	HEEA066518       	1	20000216	G	6710	412074101101	TRANSDUCER      			BELL  	407   	407         		SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				FADEC DEGRADE MESSAGE CODE:  CPFIT.						1	G	7	1 	3U			O	H2SW    					 
2000032300606	20000323	00606	SW  	2000	3	23	HEEA066519       	1	20000216	G	6710	PM212302	SWITCH          			BELL  	407   	407         		SW  										CYCLIC STICK	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				SWITCH BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2000032300607	20000323	00607	SW  	2000	3	23	HEEA066520       	1	20000216	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										FUEL QTY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53323				AFTER 10 MINUTES OF USE, FUEL QUANTITY INDICATION FLASHES BETWEEN SCREEN AND ALL LEDS LIT.						1	G	7	1 	3U			O	H2SW    					 
2000032300608	20000323	00608	SW  	2000	3	23	HEEA066521       	1	20000216	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000032300609	20000323	00609	SW  	2000	3	23	HEEA066522       	1	20000216	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2000032300610	20000323	00610	SW  	2000	3	23	HEEA066523       	1	20000216	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000032300611	20000323	00611	SW  	2000	3	23	HEEA066524       	1	20000216	G	7120	407060111101	BIPOD MOUNT     			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				BEARINGS WORN ON BIPOD MOUNT BAD.						1	G	7	1 	3U			O	H2SW    					 
2000032300612	20000323	00612	SW  	2000	3	23	HEEA066525       	1	20000216	G	7120	407060111101	BIPOD MOUNT     			BELL  	407   	407         		SW  										ENGINE	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				BIPOD MOUNT HAS LOOSE BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000032300613	20000323	00613	SW  	2000	3	23	HEEA066526       	1	20000216	G	6710	214001423109	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	745H					28200				ACTUATOR MOTOR FROZEN.						2	G	7	2 	4U				H10SW   					 
2000032300614	20000323	00614	SW  	2000	3	23	HEEA066528       	1	20000218	G	6300	214031817102	CLEVIS ASSY     			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	MISREPAIRED     	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										CLEVIS IN-LINE REAM TO BUSHING NOT CORRECT.						2	G	7	2 	4U				H10SW   					 
2000032300615	20000323	00615	SW  	2000	3	23	HEEA066529       	1	20000218	G	5320	206032305129A	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				ANGLE CRACKED AT RIVET HOLE.						1	G	7	1 	3U			O	H2SW    					 
2000032300616	20000323	00616	SW  	2000	3	23	HEEA066530       	1	20000218	G	5320	206032305127	CHANNEL         			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				CHANNEL CRACKED IN RADIUS.						1	G	7	1 	3U			O	H2SW    					 
2000032300617	20000323	00617	SW  	2000	3	23	HEEA066533       	1	20000218	G	2821	206061634003	VALVE           			BELL  	407   	407         		SW  										FUEL FILTER	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	437PH					53072				VALVE LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2000032300618	20000323	00618	SW  	2000	3	23	HEEA066534       	1	20000218	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				INTERNAL FACE LOOSE ON PRESSURE GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2000032300631	20000323	00631	EU  	2000	3	23	HEEA066535       	1	20000218	G	6520	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				WORN BEARING ON PITCH CONTROL ROD.  SERIAL NUMBERS REMOVED ARE S3986 AND S2860.  REPLACED WITH SERIAL NUMBERS S1783 AND 	S1800.					1	G	7	1 	3U				H9EU    					 
2000032300632	20000323	00632	EU  	2000	3	23	HEEA066536       	1	20000218	G	2435	150SG122Q	STARTER         			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				STARTER WILL NOT TURN ENGINE.						1	G	7	1 	3U				H9EU    					 
2000032300633	20000323	00633	EU  	2000	3	23	HEEA066537       	1	20000223	G	6520	350A33200406	SPIDER          			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466	1219 				3004				AD 99-09-06 WAS COMPLIED WITH AT AIRCRAFT TOTAL TIME 1060:30 HOURS, PART WAS REMOVED FROM AIRCRAFT FOR BEARING PLAY AND 	SLING GREASE AT 1219:40 HOURS.  P/N 704A33-651-190, S/N 1448 BEARING HAS TOTAL TIME 159:10 HOURS.					1	G	7	1 	3U				H9EU    					 
2000032300634	20000323	00634		2000	3	23	HEEA066538       	4	20000228	G	3416	350A76103606	ALTIMETER       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				ALTIMETER READS 300 FEET LOW.						1	G	7	1 	3U				H9EU    					 
2000032300619	20000323	00619	SW  	2000	3	23	HEEA066539       	1	20000228	G	3212	206050247138	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW    					 
2000032300620	20000323	00620	SW  	2000	3	23	HEEA066541       	1	20000228	G	6720	406012129101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	OUT OF ADJ      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				BEARING BAD ADJUSTMENT END.						1	G	7	1 	3U			O	H2SW    					 
2000032300621	20000323	00621	SW  	2000	3	23	HEEA066542       	1	20000228	G	6720	406012129101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				LINK ASSEMBLY HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000032300622	20000323	00622	SW  	2000	3	23	HEEA066543       	1	20000228	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2000032300623	20000323	00623	SW  	2000	3	23	HEEA066544       	1	20000228	G	7120	206064103001	BEARING         			BELL  	407   	407         		SW  										LEG ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				EXCESSIVE WEAR ON BEARING.						1	G	7	1 	3U			O	H2SW    					 
2000032300624	20000323	00624	SW  	2000	3	23	HEEA066546       	1	20000228	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				PRESSURE SWITCH NOT WORKING PROPERLY.  LIGHT STAYS OFF.						1	G	7	1 	3U			O	H2SW    					 
2000032300625	20000323	00625	SW  	2000	3	23	HEEA066547       	1	20000228	G	6300	406010421101	SPACER          			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				TO INSTALL NEW LEVER. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#71	032001.					1	G	7	1 	3U			O	H2SW    					 
2000032300626	20000323	00626	SW  	2000	3	23	HEEA066548       	1	20000228	G	7921	407062021101	DUCT            			BELL  	407   	407         		SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				DUCT IS CRACKED IN CORNER AT BLOWER END.						1	G	7	1 	3U			O	H2SW    					 
2000032300627	20000323	00627	SW  	2000	3	23	HEEA066549       	1	20000228	G	6710	406010407101	IDLER           			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH	3163 				53072				TEFLON WORN ON COLLECTIVE IDLER.						1	G	7	1 	3U			O	H2SW    					 
2000032300628	20000323	00628	SW  	2000	3	23	HEEA066550       	1	20000228	G	6300	406010421101	SPACER          			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				TO INSTALL NEW LEVER. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#71	032000.					1	G	7	1 	3U			O	H2SW    					 
2000032300629	20000323	00629	SW  	2000	3	23	HEEA066551       	1	20000228	G	6710	406310407101	SEAL            			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	510PH					53209				SEAL LEAKS.						1	G	7	1 	3U			O	H2SW    					 
2000032300630	20000323	00630	SW  	2000	3	23	HEEA066552       	1	20000228	G	5510	407023801128S	SUPPORT         			BELL  	407   	407         		SW  										HORIZ STAB	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				SUPPORT CRACKED IN BEND RADIUS ON FORWARD.						1	G	7	1 	3U			O	H2SW    					 
2000021200650	20000212	00650	NE  	2000	2	12	HEED065830       	2	20000124	G	7250	2S1	TURBINE         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	RUBBING         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	478X	1020 				760493				TURBINE RUB.  REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2000021200651	20000212	00651	NE  	2000	2	12	HEED065831       	2	20000124	G	7261	0292105230	PUMP            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					NR 1 ENGINE	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X	269  				760436				PUMP WAS REMOVED FROM NR 1 ENGINE S/N 15529TEC DUE TO PRESSURE DROPPED BELOW 25 PSI (INTO THE YELLOW RANGE) WITH THE THR	OTTLE SET TO THE FLY POSITION. REPLACED UNIT.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2000021200652	20000212	00652		2000	2	12	HEED065832       	4	20000124	G	2300	A30161ACR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT RADIO	MALFUNCTIONED   	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	278X	3287 				760440				PILOT HEARS GENERATOR NOISE IN HIS HEAD SET. ONLY COPILOT SIDE. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2000021200653	20000212	00653		2000	2	12	HEED065833       	4	20000124	G	2312	064102300	TRANSCEIVER     			SKRSKY	S76   	S76C        	8143008	NE  										VHF COMM	MALFUNCTIONED   	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	278X	3287 				760440				AUTO SQUELCH COMES IN INTERMITTENTLY.  REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2000021200654	20000212	00654	NE  	2000	2	12	HEED065834       	2	20000124	G	7421	955016670	IGNITER         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	ERRODED         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	89H					760406				ERODED AND FIRES INTERMITTENTLY.  REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2000021200655	20000212	00655	NE  	2000	2	12	HEED065835       	1	20000124	G	2840	23356	PRESSURE SWITCH 			SKRSKY	S76   	S76C        	8143008	NE  										FUEL PRESSURE	BROKEN          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	89H	3546 				760406				ELECTRICAL CONNECTOR BROKEN.  REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2000021200656	20000212	00656	NE  	2000	2	12	HEED065836       	1	20000124	G	7714	7645001076101	TACHOMETER      			SKRSKY	S76   	S76C        	8143008	NE  										GAS GENERATOR	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	478X	1051 				760493				TURN ON ANALOG LIGHTS, DIGITAL GOES OFF.  REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2000021200657	20000212	00657	NE  	2000	2	12	HEED065837       	1	20000124	G	7714	7645001096101	TACHOMETER      			SKRSKY	S76   	S76C        	8143008	NE  										GAS GENERATOR	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	478X	103  				760493				N1 GAUGE DIGITAL LIGHTS CANNOT BE READ WHEN NON-   FLIGHT INST. LIGHT SWITCH IS ON.  REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2000021200709	20000212	00709	SW  	2000	2	12	HEED065838       	1	20000124	G	2910	230065546101	TUBE ASSY       			BELL  	230   	230         	1182149	SW  										HYD SYSTEM	DAMAGED         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	236X	4590 				23015				DAMAGED FLAIR. REPLACED UNIT.						1	G	7	2 	3U			NC	H9SW    					 
2000021200710	20000212	00710	SW  	2000	2	12	HEED065841       	1	20000124	G	3340	4596	LAMP            			BELL  	407   	407         		SW  										LANDING LIGHT	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	26   				53276				LAMP BURNT OUT.  REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2000021200711	20000212	00711	SW  	2000	2	12	HEED065842       	1	20000124	G	2841	407375016103	SIGNAL COND     			BELL  	407   	407         		SW  										FUEL QUANTITY	MALFUNCTIONED   	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	128  				53276				FUEL QUANTITY INDICATION IS INACCURATE.  REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2000021200712	20000212	00712	SW  	2000	2	12	HEED065843       	1	20000124	G	7120	407060111101	BEARING         			BELL  	407   	407         		SW  										BI POD ASSY	WORN            	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	3939 				53276				LEFT BEARING WORN. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2000021200713	20000212	00713	SW  	2000	2	12	HEED065844       	1	20000124	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										FUEL QUANITY	INTERMITTENT    	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	918  				53276				DROP TO ZERO INTERMITTENTLY. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2000021200658	20000212	00658	NE  	2000	2	12	HEED065846       	2	20000124	G	7261	0292105320	PUMP            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE OIL	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X	451  				760436	15035			OIL PRESSURE DROPPED TO YELLOW RANGE AT 100 PERCENT N2.  REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2000021200659	20000212	00659		2000	2	12	HEED065847       	4	20000124	G	3457	8144002241B	GPS             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					COCKPIT	MALFUNCTIONED   	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	89H	123  				760406	15035			GPS DIGITAL DISPLAY DOES NOT MATCH CDI INDICATIONS- GPS WILL NOT DRIVE HSI DURING SYNCRO TEST.  REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2000021200660	20000212	00660	NE  	2000	2	12	HEED065848       	2	20000124	G	7421	9550166670	H.E. IGNITER    			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					EINGINE	INOPERATIVE     	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	89H	128  				760406				BOTH PARTS WILL NOT DISCHARGE (INOPERATIVE).  REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2000021900077	20000219	00077	SW  	2000	2	19	LS1R065936       	1	20000211	G	2436	CSV115212A	VOLT REGULATOR  			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	SHORTED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				VOLTAGE REGULATOR  SHORTED OUT.						1	G	7	1 	4U				EXPA1G71					 
2000021900609	20000219	00609		2000	2	19	LS1R065941       	4	20000211	G	2340	C6533ARC	CONTROLLER      			BELL  	204   	UH1H        	1181407	SW  										INTERPHONE	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				INTERPHONE DOES NOT TRANSMIT.						1	G	7	1 	4U				EXPA1G71					 
2000021900611	20000219	00611	SW  	2000	2	19	LS1R065943       	1	20000211	G	2436	CSV115212A	VOLT REGULATOR  			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	SHORTED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				VOLTAGE REGULATOR SHORTED OUT.						1	G	7	1 	4U				EXPA1G71					 
2000021900621	20000219	00621	WP  	2000	2	19	LS1R065958       	1	20000211	G	3310	369H64255	DIMMER CONTROL  			HUGHES	369   	369D        	4470706	WP  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				DIMMER CONTROL  IS INOPERATIVE, PANEL LIGHTS INOPERATIVE.						1	G	7	1 	3U				H3WE    					 
2000021900622	20000219	00622	SW  	2000	2	19	LS1R065962       	1	20000215	G	7600	DYLM735011	LINEAR ACTUATOR 			BELL  	204   	UH1H        	1181407	SW  										ENGINE CONTROLS	INOP            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	52AG					7015746				LINEAR ACTUATOR  IS INOPERATIVE.						1	G	7	1 	4U				EXPA1G71					 
2000021900623	20000219	00623	SW  	2000	2	19	LS1R065963       	1	20000215	G	7714	206075681003	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										DUAL TACH	STICKING        	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				DUAL TACHOMETER INDICATOR HAD STICKING NEEDLES.						1	G	7	1 	3U				H2SW    					 
2000021900624	20000219	00624	WP  	2000	2	19	LS1R065964       	1	20000215	G	7810	369A8230503	EXHAUST PIPE    			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				EXHAUST PIPE CRACKED.						1	G	7	1 	3U				H3WE    					 
2000021900625	20000219	00625	WP  	2000	2	19	LS1R065965       	1	20000215	G	7810	369A8230503	EXHAUST PIPE    			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				EXHAUST PIPE CRACKED.						1	G	7	1 	3U				H3WE    					 
2000021900626	20000219	00626	SW  	2000	2	19	LS1R065966       	1	20000215	G	6230	206010455103	CAP             			BELL  	206   	OH58A       	1181579	SW  										SWASHPLATE	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	58AG					7221131				CAP IS WORN EXCESSIVELY.						1	G	7	1 	3U				H2SW    					 
2000021900627	20000219	00627	WP  	2000	2	19	LS1R065967       	1	20000215	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				RIGHT EXHAUST STACK  IS CRACKED.						1	G	7	1 	3U				H3WE    					 
2000021900628	20000219	00628	WP  	2000	2	19	LS1R065968       	1	20000215	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5070J					121096D				RIGHT EXHAUST STACK IIS CRACKED.						1	G	7	1 	3U				H3WE    					 
2000030400172	20000304	00172	SW  	2000	3	4	LS1R066009       	1	20000215	G	6420	2060104515	RING ASSY       			BELL  	206   	206B3       	1181506	SW  										TAIL ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				RING ASSY  WORN EXCESSIVELY BEYOND LIMITS.						1	G	7	1 	3U				H2SW    					 
2000030400173	20000304	00173		2000	3	4	LS1R066010       	4	20000217	G	2330	C6533	AUDIO PANEL     			BELL  	204   	UH1H        	1181407	SW  										COCKPIT	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				ICS BOX  DOES NOT TRANSMIT.						1	G	7	1 	4U				EXPA1G71					 
2000030400174	20000304	00174		2000	3	4	LS1R066011       	4	20000217	G	2330	C1611D	AUDIO PANEL     			BELL  	204   	UH1H        	1181407	SW  										COCKPIT	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	52AG					7015746				ICS BOX  DOES NOT TRANSMIT.						1	G	7	1 	4U				EXPA1G71					 
2000030400192	20000304	00192	WP  	2000	3	4	LS1R066418       	1	20000223	G	2432	G641	BATTERY         			HUGHES	369   	369D        	4470706	WP  										BATTERY BAY	DISCHARGED      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW	1490 				470117D				BATTERY IS NOT HOLDING VOLTAGE.						1	G	7	1 	3U				H3WE    					 
2000030400193	20000304	00193	SW  	2000	3	4	LS1R066419       	1	20000223	G	6520	204040623111	BEARING         			BELL  	204   	UH1H        	1181407	SW  										TAIL ROTOR	DAMAGED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	52AG	74   				7015746				BEARING SLINGING GREASE.						1	G	7	1 	4U				EXPA1G71					 
2000030400194	20000304	00194	SW  	2000	3	4	LS1R066420       	1	20000223	G	6520	204040633111	BEARING         			BELL  	204   	UH1H        	1181407	SW  										TAIL ROTOR	DAMAGED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	52AG	74   				7015746				BEARING SLINGING GREASE.						1	G	7	1 	4U				EXPA1G71					 
2000030400195	20000304	00195	SW  	2000	3	4	LS1R066421       	1	20000223	G	6520	204040623111	BEARING         			BELL  	204   	UH1H        	1181407	SW  										TAIL ROTOR	DAMAGED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	52AG	74   				7015746				BEARING SLINGING GREASE.						1	G	7	1 	4U				EXPA1G71					 
2000030400196	20000304	00196	SW  	2000	3	4	LS1R066431       	1	20000224	G	2560	0010009	BATTERY         			BELL  	206   	206B3       	1181506	SW  										ELT	EXPIRED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY					2871				BATTERY  IS EXPIRED.						1	G	7	1 	3U				H2SW    					 
2000030400197	20000304	00197	WP  	2000	3	4	LS1R066432       	1	20000224	G	6310	369A535041	CLUTCH          			HUGHES	369   	369D        	4470706	WP  										ENGINE	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5070J	1071 				121096D				CLUTCH IS WORN EXCESSIVELY.						1	G	7	1 	3U				H3WE    					 
2000030400198	20000304	00198	WP  	2000	3	4	LS1R066433       	1	20000224	G	7920	174083904	BOWL            			HUGHES	369   	369D        	4470706	WP  										OIL SYSTEM	INOPERATIVE     	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	5027P					611002D				PART IS INOPERATIVE, FAILED BYPASS INDICATOR TEST.						1	G	7	1 	3U				H3WE    					 
2000030400199	20000304	00199	SW  	2000	3	4	LS1R066434       	1	20000224	G	6510	204011166007	BOLT            			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BOLT  WORN EXCESSIVELY.						1	G	7	1 	4U				H4SW    					 
2000030400200	20000304	00200	SW  	2000	3	4	LS1R066435       	1	20000224	G	6510	204011166007	BOLT            			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BOLT WORN EXCESSIVELY.						1	G	7	1 	4U				H4SW    					 
2000030400201	20000304	00201		2000	3	4	LS1R066436       	4	20000224	G	3423	MS179832	COMPASS         			HUGHES	369   	369D        	4470706	WP  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				COMPASS INOPERATIVE,  WILL NOT HOLD HEADING SPINS.						1	G	7	1 	3U				H3WE    					 
2000030400202	20000304	00202		2000	3	4	LS1R066437       	4	20000224	G	2340	AA34300	INTERPHONE      			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				INTERPHONE  WILL NOT TRANSMIT.						1	G	7	1 	3U				H3WE    					 
2000030400203	20000304	00203	SW  	2000	3	4	LS1R066438       	1	20000224	G	6510	204011151601	PIN             			BELL  	212   	212         	1181420	SW  										M/R BLADE	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BLADE PIN  WORN EXCESSIVELY.						1	G	7	1 	4U				H4SW    					 
2000030400204	20000304	00204	SW  	2000	3	4	LS1R066439       	1	20000224	G	6510	204011151001	BOLT            			BELL  	212   	212         	1181420	SW  										TAIL ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BOLT ASSY  WORN EXCESSIVELY.						1	G	7	1 	4U				H4SW    					 
2000030400205	20000304	00205	WP  	2000	3	4	LS1R066440       	1	20000224	G	3110	369H45267	TORQUE GAUGE    			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FLUCTUATED      	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	500DC					290456D				GAUGE FLUCTUATING IN POWER.						1	G	7	1 	3U				H3WE    					 
2000030400206	20000304	00206	WP  	2000	3	4	LS1R066441       	1	20000224	G	7810	369A8230504	STACK           			HUGHES	369   	369D        	4470706	WP  										EXHAUST	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				RIGHT EXHAUST STACK IS CRACKED.						1	G	7	1 	3U				H3WE    					 
2000030400207	20000304	00207	WP  	2000	3	4	LS1R066442       	1	20000224	G	7810	369A8230503	PIPE            			HUGHES	369   	369D        	4470706	WP  										EXHAUST	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				EXHAUST PIPE CRACKED.						1	G	7	1 	3U				H3WE    					 
2000030400208	20000304	00208	WP  	2000	3	4	LS1R066443       	1	20000224	G	7810	369A8230504	STACK           			HUGHES	369   	369D        	4470706	WP  										EXHAUST	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5070J					121096D				RIGHT EXHAUST STACK IS CRACKED.						1	G	7	1 	3U				H3WE    					 
2000030400209	20000304	00209	WP  	2000	3	4	LS1R066444       	1	20000224	G	7810	369A8230503	PIPE            			HUGHES	369   	369D        	4470706	WP  										EXHAUST	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				EXHAUST PIPE IS CRACKED.						1	G	7	1 	3U				H3WE    					 
2000030400168	20000304	00168	SW  	2000	3	4	LS1R066445       	1	20000229	G	6540	204040623111	BEARING         			BELL  	204   	UH1H        	1181407	SW  										T/R INDICATOR	ROUGH           	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	51AG	4854 				7120178				BEARING EXTREMELY ROUGH, AND RATCHETY.						1	G	7	1 	4U				EXPA1G71					 
2000032300588	20000323	00588		2000	3	23	LS1R066498       	2	20000303	G	7323	252476911	PT GOVERNOR     			HUGHES	369   	369D        	4470706	WP  										ENGINE	INOPERATIVE     	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J	8372 				900801D				PT GOVERNOR INOPERABLE, UNABLE TO HOLD N2 RPM.						1	G	7	1 	3U				H3WE    					 
2000041300004	20000413	00004	WP  	2000	4	13	LS1R066557       	1	20000307	G	2510	369H6525503	SEAT            			HUGHES	369   	369D        	4470706	WP  										COCKPIT	BROKEN          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				BOTTOM OF SEAT IS BROKEN.						1	G	7	1 	3U			 	H3WE    					 
2000042800010	20000428	00010		2000	4	28	LS1R066558       	4	20000307	G	2300	AA85001	TRANSCEIVER     			HUGHES	369   	369D        	4470706	WP  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				PART IS INOPERATIVE.  WILL NOT ADJUST VOLUME.						1	G	7	1 	3U			 	H3WE    					 
2000041300005	20000413	00005	WP  	2000	4	13	LS1R066559       	1	20000307	G	7714	369D29630921	GAUGE           			HUGHES	369   	369D        	4470706	WP  										COCKPIT	INACCURATE      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				GAUGE IS INACCURATE.						1	G	7	1 	3U			 	H3WE    					 
2000041300006	20000413	00006	SW  	2000	4	13	LS1R066560       	1	20000307	G	7700	20907532545	ANNUNCIATOR     			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				ANNUNCIATOR IS INOPERATIVE.						1	G	7	1 	4U			 	H4SW    					 
2000042800011	20000428	00011	WP  	2000	4	28	LS1R066561       	1	20000307	G	7714	369A45165	GAUGE           			HUGHES	369   	369D        	4470706	WP  										COCKPIT	STUCK           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				GAUGE IS STICKING.						1	G	7	1 	3U			 	H3WE    					 
2000041300357	20000413	00357	SW  	2000	4	13	LS1R066563       	1	20000315	G	7930	1740996	FILTER          			BELL  	206   	206B3       	1181506	SW  										ENGINE OIL	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322					1736				FILTER IS INOPERATIVE.  WILL NOT EXCITE.						1	G	7	1 	3U			 	H2SW    					 
2000041300007	20000413	00007	SW  	2000	4	13	LS1R066564       	1	20000315	G	6510	206011139001	ARM             			BELL  	206   	206B3       	1181506	SW  										TAIL ROTOR	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				ARM ASSEMBLY IS INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2000041300008	20000413	00008	SW  	2000	4	13	LS1R066565       	1	20000315	G	6510	206011139001	ARM             			BELL  	206   	206B3       	1181506	SW  										TAIL ROTOR	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				ARM ASSEMBLY IS INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2000041300009	20000413	00009	WP  	2000	4	13	LS1R066566       	1	20000315	G	7712	369H45267	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				TORQUE GAUGE NEEDLE BOUNCES.						1	G	7	1 	3U			 	H3WE    					 
2000041300010	20000413	00010		2000	4	13	LS1R066567       	4	20000315	G	3423	C230014124B	COMPASS         			BELL  	206   	206B3       	1181506	SW  										COCKPIT	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				MAGNETIC COMPASS IS UNSERVICEABLE.						1	G	7	1 	3U			 	H2SW    					 
2000041300011	20000413	00011	SW  	2000	4	13	LS1R066568       	1	20000316	G	6330	204031920003	DAMPER          			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				DAMPER IS  WORN EXCESSIVELY.						1	G	7	1 	4U			 	H4SW    					 
2000041300012	20000413	00012	SW  	2000	4	13	LS1R066569       	1	20000316	G	6330	204031920003	DAMPER          			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				DAMPER IS WORN EXCESSIVELY.						1	G	7	1 	4U			 	H4SW    					 
2000041300013	20000413	00013	SW  	2000	4	13	LS1R066570       	1	20000316	G	3210	J154524V	STRAP           			BELL  	212   	212         	1181420	SW  										MLG	TORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				STRAP IS TORN.  (RUBBER COMING APART).						1	G	7	1 	4U			 	H4SW    					 
2000041300014	20000413	00014	SW  	2000	4	13	LS1R066571       	1	20000316	G	3210	J154523V	STRAP           			BELL  	212   	212         	1181420	SW  										MLG	TORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				STRAP  IS TORN.  (RUBBER COMING APART).						1	G	7	1 	4U			 	H4SW    					 
2000041300015	20000413	00015	GL  	2000	4	13	LS1R066572       	2	20000320	G	7322		FCU             			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				PART IS RUPTURED.   HOLE IN SKID.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2000042800012	20000428	00012	SW  	2000	4	28	LS1R066573       	1	20000320	G	2930	124043	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STUCK           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				GAUGE IS STICKING.						1	G	7	1 	4U			 	H4SW    					 
2000042800013	20000428	00013	WP  	2000	4	28	LS1R066574       	1	20000320	G	7714	369H4551	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				TACHOMETER/GENERATOR IS INOPERATIVE.  NO SIGNAL FROM LEA WINDING.						1	G	7	1 	3U			 	H3WE    					 
2003020500030	20030205	00030	CE  	2003	2	5	MEA200302        	1	20000202	G	5610	10138402517	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	FAILED          	C				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			GL	23	593MA	1481 				FL68				A/C WAS ENROUTE TO TEB AT FL290, WINDSHIELD ANTI-ICE WAS SELECTED FOR 1HOUR WHEN A LOUD CRACK WAS HEARD AND THE PILOTS W	INSHIELD SHATTERED THE INNER PANE INTO PEA SIZED PIECES. CREW FOLLOWED AIRCRAFT ABNORMAL PROCEDURES AND DESCENDED BELOW 	25,000 FEET AND KEEP CABIN PSI BETWEEN 2 AND 4 PSI. TEMP AT ALTITUDE WAS -39C. AIRCRAFT WAS FLOWN TO TEB AND REPAIRED				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2000062100005	20000621	00005	SO  	2000	6	21	PNSA000402       	1	20000420	G	3245	600X6	TIRE            			PIPER 	PA31  	PA31350     	7103110	SO  											FLAT            	E			PNSA	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AL	03	28KE		48   			318152049				DURING TAXI TO RUNWAY FOR TAKEOFF, NOSE WHEEL WENT FLAT.  REPLACED TIRE.  (X)						1	L	7	2 	3O			 	A20SO   					 
2000062100004	20000621	00004	SO  	2000	6	21	PNSA000403       	1	20000420	G	7330	565583	FUEL LINE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FUEL INDICATOR	LEAKING         	E			PNSA	A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			AL	03	15PR					318052011				DURING CRUISE, PILOT SMELLED FUEL.  AFTER LOOKING AROUND THE COCKPIT, PILOT NOTICED A SMALL FUEL STAIN IN THE COPILOT''S	 CARPET.  THE AIRCRAFT IMMEDIATELY RETURNED TO THE AIRPORT.  REPLACED FUEL  LINE TO FUEL FLOW INDICATOR. 					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000062100006	20000621	00006	SO  	2000	6	21	PNSA000405       	1	20000428	G	3244	600X66	TIRE            			PIPER 	PA32  	PA32301     	7103207	SO  											FLAT            	E			PNSA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AL	03	8402S		36   			328106075				NOSE TIRE WENT FLAT DURING ROLL-OUT AFTER LANDING.  REPLACED TIRE.  (X)						1	L	7	1 	3O			 	A3SO    					 
2000112900004	20001129	00004	SO  	2000	11	29	PNSA000702       	1	20000723	G	3244	600X66	TIRE            			PIPER 	PA32  	PA32301     	7103207	SO  											CUT             	E			PNSA	K				NONE                    				O			OTHER                     			LD	LANDING        	1			AL	03	4327P					328406002				LEFT MAIN TIRE WENT FLAT DURING ROLL-OUT.  REPLACED  CUT TIRE.  (X)						1	L	7	1 	3O			 	A3SO    					 
2000101200020	20001012	00020	SO  	2000	10	12	PNSA0801         	1	20000818	G	5210		DOOR LATCH      			PIPER 	PA32  	PA32301     	7103207	SO  										PASS	UNLOCKED        	E			PNSA	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AL	03	81052					328206023				EN ROUTE, PASSENGER DOOR TOP LATCH UNLATCHED.  CONTINUED TO NEXT AIRPORT.  RE-SECURED TRIM SCREW BLOCKING LATCH FROM PRO	PER OPERATION.  DOOR OPS CHECK OK.  (X)					1	L	7	1 	3O			 	A3SO    					 
2000112900053	20001129	00053	SO  	2000	11	29	PNSA0802         	1	20000812	G	7714		INDICATOR       			PIPER 	PA31  	PA31350     	7103110	SO  											MALFUNCTIONED   	E			PNSA	C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AL	03	28KE					318152049				PROPELLER RPM WAS LOW ON TAKEOFF.   TAKEOFF WAS ABORTED.  PROBLEM COULD NOT BE DUPLICATED.  (X)						1	L	7	2 	3O			 	A20SO   					 
2000101200005	20001012	00005	GL  	2000	10	12	PNSA0803         	3	20000813	G	6110		PROPELLER       			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR1     	GL  		BINDING         	E			PNSA	C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AL	03	28KE					318152049		DJ8178A		PROPELLER RPM WAS LOW ON TAKEOFF.  FOUND PROP WAS BINDING INTERNALLY.  REPLACED PROPELLER.  OPS CHECK OK.  (X)						1	L	7	2 	3O			 	A20SO   		5	C	P33EA	 
2000101200156	20001012	00156	NE  	2000	10	12	PNSA0804         	2	20000801	G	7320		FUEL CONTROL    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  						FAILED          	E			PNSA	A				UNSCHED LANDING         				Z	M		SIGNIFICANT FAILURE REPORT	OVER TEMP                 		CR	CRUISE         	1			AL	03	750PA					208B0628	PCO517			DURING CRUISE, ENGINE WENT TO MAX POWER AND WAS UNCONTROLLABLE.  ENGINE WOULD NOT RESPOND TO POWER LEVER OR EMERGENCY PO	WER LEVER.  ENGINE WAS CONTINUOUSLY OVER TORQUE AND OVER TEMP LIMITS FOR 7 MINUTES.  AIRCRAFT WAS FLOWN TO NEAREST AIRPO	RT BY CYCLING THE PROP IN AND OUT OF FEATHER.  ALL ENGINE RIGGING WAS FOUND TO BE INTACT.  SUBMITTER SUSPECTED FUEL CONT	ROL DRIVE SHAFT FAILURE. THIS EVENT IS STILL UNDER INVESTIGATION.  (X)			1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2000101200157	20001012	00157	SO  	2000	10	12	PNSA0805         	1	20000803	G	5210		DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  										CREW	UNLOCKED        	E			PNSA	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AL	03	3588Z					318052130				LOWER CREW DOOR LATCH OPENED IN-FLIGHT.  RETURNED TO AIRPORT, RESECURED DOOR.  NO OTHER PROBLEMS NOTED.  (X)						1	L	7	2 	3O			 	A20SO   					 
2000101800003	20001018	00003	CE  	2000	10	18	PNSA0901         	1	20000901	G	7712	99103311	TRANSDUCER      			CESSNA	441   	441         	2076020	CE  										INTERNAL	MALFUNCTIONED   	E			PNSA	K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AL	03	441LL					441139				TORQUE INDICATION WENT TO ZERO DURING DESCENT.  AFTER UNEVENTFUL LANDING, REPLACED TORQUE TRANSDUCER.  OPERATIONAL CHECK	 OK.  (X)					1	L	7	2 	3T			RT	A28CE   					 
2000101800041	20001018	00041	SO  	2000	10	18	PNSA0903         	1	20000926	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  						SEIZED          	E			PNSA	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AL	03	27663		1057 			317852094	L294161A			SHORTLY AFTER TAKEOFF, LEFT ENGINE LOST POWER.  RETURNED TO BASE.  REPLACED TURBOCHARGER.  OPS CHECKED OK.  (X)						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000111500020	20001115	00020	EA  	2000	11	15	QXEA0002163      	1	20000805	G	3350	6104781	BATTERY         			DHAV  	DHC2  	DHC2*       	2800108	EA  										CABIN	MALFUNCTIONED   	A			QXEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	09	375PH	*    	545  			529				SEA-RIGHT HAND AFT EMERGENCY EXIT LIGHT INOPERATIVE.  REPLACED BATTERY AT PS4. OPERATIONAL CHECKS GOOD.  AIRCRAFT RETURN	ED TO SERVICE.  (X)					1	H	7	1 	3R			 	A806    					 
2000082800186	20000828	00186	NE  	2000	8	28	R09R001          	2	20000704	G	7300	3024476B	FLOW DIVIDER    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 1 ENGINE	FAILED          	B			R09R	D				RETURN TO BLOCK         				X			ENGINE FLAMEOUT           			TO	TAKEOFF        	1			SO	19	37201	33   				5500655	PCE71677			ENGINE FLAMED OUT ON TAKEOFF.  (X)						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001011101458	20010111	01458	CE  	2001	1	11	R3R2001201       	1	20001201	G	5700	MC24694C48	SCREW           			CESSNA	500   	550         	2076604	CE  										LEADING EDGE	INCORRECT       	B			R3R2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	2663Y					5500602				THE OUTBOARD ATTACH SCREW IN THE HEATED LEADING EDGE IS TOO LONG AND CAN DAMAGE THE WING SKIN BELOW IT. THE IPC CALLS OU	T A MS24694-C48 SCREW IT IS TOO LONG.  (X)					1	L	7	2 	4F			 	A22CE   					 
2001011101459	20010111	01459	CE  	2001	1	11	R3R2001201B      	1	20001204	G	5710	MS24694C48	SCREW           			CESSNA	500   	550         	2076604	CE  										LEADING EDGE	INCORRECT       	B			R3R2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	586RE					5500222				THE OB ATTACH SCREW IN THE HEATED LEADING EDGE IS TOO LONG AND CAN DAMAGE THE WING SKIN BELOW IT. THE IPC CALLS OUT A MS	24693-C48 SCREW BUT IT IS TOO LONG.					1	L	7	2 	4F			 	A22CE   					 
2001011101460	20010111	01460	CE  	2001	1	11	R3R2001201C      	1	20001204	G	5710	MS24694C48	SCREW           			CESSNA	500   	550         	2076604	CE  										LEADING EDGE	INCORRECT       	B			R3R2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	43SA					5500096				THE OB ATTACH SCREW IN THE HEATED LEADING EDGE IS TOO LONG AND CAN DAMAGE THE WING SKINBELOW IT. THE IPC CALLS OUT A MS2	4693-C48 SCREW BUT IT IS TOO LONG.					1	L	7	2 	4F			 	A22CE   					 
2001030700637	20010307	00637	NM  	2001	3	7	R7MR32373        	1	20001121	G	7712	900A3720002111	DISPLAY         			DOUG  	MD900 	MD900       	3027375	NM  										COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	114  				90000012				DISPLAY OF RT TORQUE/BARS AND NUMBERS/ INTERMITTENLY GOES BLACK.  REPLACED WITH REPAIRED UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U			NC	H19NM   					 
2001030700624	20010307	00624	NE  	2001	3	7	R7MR32500        	2	20000910	G	7250	311586401	STRUCTURE       			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					TURBINE EXHAUST	CRACKED         	B			R7MA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	135SJ	1443 				EC1350054	PCEBB0049			CRACKED BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001030700607	20010307	00607	EU  	2001	3	7	R7MR32578        	1	20001210	G	2400	45033500	CONTROL UNIT    			UROCOP	EC135 	EC135P1     	8680990	EU  										START SWITCH	INOPERATIVE     	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	135SJ	1210 				EC1350054				UNIT INOPERATIVE.  ENGINE WILL NOT SPOOL UP WHEN START SWITCH IS ENGAGED.  SAME BEHAVIOR WHEN VENT SWITCH ACTIVATED.  PO	SSIBLE STARTER RELAY POWER IS COMMING TO PIN 22 OF PLUG 1.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.					1	G	7	2 	3U			O	H88EU   					 
2001040500121	20010405	00121	EU  	2001	4	5	R7MR32624        	1	20001117	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B3     	8680954	EU  										STROBE	INOPERATIVE     	B			R7MA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	104LN	11   				3134				UNIT INOPERATIVE.  REPLACED WITH NEW UNIT. CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040500120	20010405	00120	EU  	2001	4	5	R7MR32625        	1	20000820	G	3340	356H2802	POWER UNIT      			SNIAS 	350   	AS350B2     	8680813	EU  										STROBE	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	101LN	808  				3038				UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040500118	20010405	00118	NE  	2001	4	5	R7MR32626        	2	20001222	G	7321	45033501	ECU             			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206B      	0	NE  					E/E BAY	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135N	11   				EC1350086				UNIT INOPERATIVE. HAS ERRORS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040500119	20010405	00119	EU  	2001	4	5	R7MR32627        	1	20001118	G	7714	117902101	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	117SU	954  				7527				UNIT INOPERATIVE.  DIGITIAL TEST BUTTON INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM						1	G	7	2 	3U			NC	H13EU   					 
2001040500122	20010405	00122	EU  	2001	4	5	R7MR32628        	1	20001021	G	7931	1179586901	HARNESS         			BOLKMS	BK117 	BK117C1     	5626025	EU  										INDICATOR	SHORTED         	B			R7MR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	117SU	894  				7527				INTERNAL SHORT.  PEGS NEEDLE ON NUMBER 2 TRANSMISSION OIL PRESSURE INDICATOR.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM	.					1	G	7	2 	3U			NC	H13EU   					 
2001050300044	20010503	00044	EU  	2001	5	3	R7MR32655        	1	20001124	G	8010	845UN01Q4AA5F	SWITCH          			SNIAS 	350   	AS350B3     	8680954	EU  										STARTER	INOPERATIVE     	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52285	443  				3251				UNIT INOPERATIVE.  REMOVED AND REPLACED WITH NEW UNIT,  CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900030	20010409	00030	EU  	2001	4	9	R7MR32665        	1	20001201	G	6410	704A33633171	HINGE           			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5771C	454  				1369				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A332153-00, CORRECT	ED PROBLEM.  2 TEETERING BEARINGS EQUALS 1 KIT.					1	G	7	1 	3U			 	H9EU    					 
2001040900033	20010409	00033	EU  	2001	4	9	R7MR32672        	1	20001201	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5771C	454  				1369				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A09-1036-01 CORRECT	ED PROBLEM.  4 HALF SHELLS EQUALS 1 KIT.					1	G	7	1 	3U			 	H9EU    					 
2001040900034	20010409	00034	EU  	2001	4	9	R7MR32674        	1	20001121	G	7160	350A54108421	SEAL            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE INTAKE	TORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	774  				3128				ENGINE INTAKE SEAL TORN.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900047	20010409	00047	EU  	2001	4	9	R7MR32686        	1	20001118	G	7430	355A72302302	SENSOR          			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20      	03013	GL  					ENG IGNITION	INOPERATIVE     	B			R7MA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	07	30LG	222  				5065				UNIT INOPERATIVE.  NO PRESSURE DROOP INDICATION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001040900048	20010409	00048	EU  	2001	4	9	R7MR32689        	1	20001230	G	7931	1130021089	PRESSURE SWITCH 			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					GEARBOX OIL	INOPERATIVE     	C			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	911LR					2404				UNIT INOPERATIVE UPON INSTALLATION.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900232	20010409	00232		2001	4	9	R7MR32707        	4	20001007	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B3     	8680954	EU  										COCKPIT	INOPERATIVE     	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	104LN	1052 				3134				UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001011101461	20010111	01461	NE  	2001	1	11	R8RR010147       	2	20001016	G	7230	70BM035420	GAS GENERATOR   	TMECA       		SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	COKED           	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6095U	823  			9524	2699	9524			AFTER LANDING AND SHUT DOWN, THE MECHANIC CHECKED THE COMPRESSOR FOR FREEDOM OF ROTATION.  THE COMPRESSOR WAS SEIZED.  S	USPECT FUEL INJECTION WHEEL COKING.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000121500184	20001215	00184	NE  	2000	12	15	R8RR0102A2       	2	20001124	G	7240	70BM035420	GAS GENERATOR   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1A1   	60030	NE  					ENGINE	SEIZED          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6095U	1759 	53   			2699	9524			ENGINE COMPRESSOR SEIZED AFTER SHUT DOWN.  SUSPECT FUEL INJECTION WHEEL COKING.  THIS HAS BEEN A RECURRING PROBLEM IN TU	CSON.  THE CURRENT THEORY IS THE FUEL (JP8) SOURCE.  WE ARE NOW USING JET A TO SEE IF THE PROBLEM PERSISTS.  (X)					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2000121500183	20001215	00183	CE  	2000	12	15	R8RR010307002    	1	20001204	G	5730	MS24694C51	SCREW           			CESSNA	500   	550         	2076604	CE  										BOTH WINGS	OVERSIZED       	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6763L					5500673				LEFT WING AND RIGHT WING LEADING EDGE SKIN HAS BEEN CHAFED BY THE UPPER SCREW OF THE OUTBOARD ROW OF SCREWS ATTACHING TH	E HEATED LEADING EDGE TO THE WING.  THE SCREWS INSTALLED WERE TOO LONG, ALTHOUGH THEY WERE THE ONES CALLED FOR IN THE PA	RTS CATALOG.  THEY CHAFED INTO THE WING LEADING EDGE SKIN ABOUT 0.026 INCH DEEP INTO THE LEFT WING AND 0.024 INCH INTO T	HE RIGHT WING.  THE SKIN IS 0.040 INCH ALUMINUM.  CESSNA HAS APPROVED A SHORTER SCREW TO BE INSTALLED AND IS CURRENTLY W	ORKING ON A PERMANENT REPAIR.  (X)		1	L	7	2 	4F			 	A22CE   					 
2000121500185	20001215	00185	CE  	2000	12	15	R8RR010307004    	1	20001205	G	3242	1338932	STATOR          	BFGOODRICH  		CESSNA	500   	550         	2076604	CE  										BRAKE	BROKEN          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6763L		415  		00781877	5500673				DURING COMPLIANCE WITH CESSNA SB 550-32-41 BRAKE INSPECTION,  FOUND BOTH BRAKES HAD BROKEN STATORS.  BOTH BRAKES HAD 415	 LANDINGS SINCE OVERHAUL.  (X)					1	L	7	2 	4F			 	A22CE   					 
2000121500180	20001215	00180	CE  	2000	12	15	R8RR010310       	1	20001206	G	5730	MS24694C51	SCREW           			CESSNA	500   	550         	2076604	CE  										LT WING	OVERSERVICED    	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3262M					5500652				LEFT WING LEADING EDGE SKIN HAS BEEN CHAFED BY THE UPPER SCREW OF THE OUTBOARD ROW OF SCREWS ATTACHING THE HEATED LEADIN	G EDGE TO THE WING.  THE SCREW INSTALLED WAS TOO LONG, ALTHOUGH IT WAS THE ONE CALLED FOR IN THE PARTS CATALOG.  IT CHAF	ED INTO THE WING LEADING EDGE SKIN ABOUT 0.020 INCH DEEP.  THE SKIN IS 0.040 INCH ALUMINUM.  CESSNA HAS APPROVED A SHORT	ER SCREW TO BE INSTALLED AND IS CURRENTLY WORKING ON A PERMANENT REPAIR.  (X)			1	L	7	2 	4F			 	A22CE   					 
2001011102690	20010111	02690	WP  	2001	1	11	RX8R2000001      	1	20001227	G	6210	500P2100101	BLADE           			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	DELAMINATED     	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5247S	91   	18   			0119E	CAE835520			HELICOPTER TECHNOLOGY COMPANY MAIN ROTOR BLADES PN 500P2100-101 WERE INSTALLED NEW 8/14/00 TTAC 5096.0.  BLADES WERE INS	PECTED IAW A.D.2000-24-51 (MSB 2100-02) ON 11/11/00, TTAC 5149.7 AND NO DEFECTS WERE NOTED.  BLADES WERE INSPECTED IAW A	.D. 2000-25-52 (MSB 2100-02R2) ON 11/20/00, TTAC  5169.2 AND NO DEFECTD WERE NOTED.  AD IS NOT RECURRING, BUT INSPECTED 	BLADES WITH A 100 HR INSPECTION ON 12/27/00, TTAC 5187.3 AND FOUND 2 BLADES DELAMINATED.  RECOMMEND A. BE MADE RECURRING	.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001011100710	20010111	00710	EU  	2001	1	11	SIMA3236         	1	20001118	G	3350	3011210	LIGHT           			BRAERO	DH125 	BAE125800A  	1500285	EU  										EXTERIOR	INOPERATIVE     	A			SIMA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	21	494AT					NA0404				DFW - DURING PHASE 4 INSPECTION MAINTENANCE FOUND THE PASSENGER DOOR EXTERIOR EMERGENCY LIGHT TO BE INOPERATIVE.  MAINTE	NANCE FOUND LIGHT SOCKET LOOSE AND WRONG TYPE BULB INSTALLED.  LIGHT ASSEMBLY WAS REPLACED WITH CORRECT BULB.  OPERATION	AL CHECK WAS GOOD AND AIRCRAFT WAS RETURNED TO SERVICE.  (M)				2	L	7	2 	4F			RT	A3EU    					 
2001011900082	20010119	00082	EU  	2001	1	19	SIMA3331         	1	20001128	G	3350	AGS005424005	BULB            			BOLKMS	117   	BK117B1     	5626012	EU  										CABIN	INOPERATIVE     	A			SIMA	K				NONE                    				L			NO TEST                   			TX	TAXI/GRND HDL  	1			SW	21	214AE					7206				DFW - FLT 1925 - EMERGENCY FLOOR LIGHT AT ROW 8 IS INOPERATIVE.  REMOVED AND REPLACED LIGHT BULB.  OPS CHECK GOOD.  (M)						1	G	7	2 	3U			 	H13EU   					 
2000101800060	20001018	00060	GL  	2000	10	18	SJ3RR003186      	3	20001005	G	6110	LT10282NB53R	BLADE           	HARTZL      		MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	BLADE AIRFOIL	MISOVERHAULED   	B			SJ3R	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	469MA	971  				1543SA		CDA3361CDA3		CUSTOMER WORK ORDER WAS OPENED TO DYNAMIC BALANCE PROPELLERS.  UPON INSPECTION OF THE AIRCRAFT, THE BLADES WERE FOUND NO	T TO BE SHOT PEENED IN ACCORDANCE WITH AD 95-01-02.  THE PROPELLERS HAD BEEN PREVIOUSLY OVERHAULED BY YINGLING AIRCRAFT,	 INC., ON 7-31-2000.  BOTH PROPELLERS WERE REMOVED FOR OVERHAUL AND AD COMPLIANCE.  PROPELLER SERIAL NUMBERS:  CDA3361, 	CDA3363.  BLADE SERIAL NUMBERS: H57913, H57910, H57908, H57916, H57911, H57912, H57909, H57917.  (X)			1	H	7	2 	3T	4	T	RT	A10SW   	E4WE	6	C	P40EA	 
2001011100590	20010111	00590	GL  	2001	1	11	SJ3RR003569      	3	20001121	G	6111	M10877K	BLADE           	HARTZL      	HCB4MP3A    	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	MISOVERHAULED   	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05										THE OVERHAUL PERFORMED ON THIS BLADE WAS NOT TO HARTZEL SPECIFICATION, AND AS A RESULT, THE BLADE HAD SOME SIGNIFICANT P	ROBLEMS THAT COULD HAVE RESULTED IN SAFETY OF FLIGHT ISSUES.  UNABLE TO DETERMINE WHERE THE OVERHAUL WAS PERFORMED.  PLE	ASE REFERENCE HARTZEL ENGINEERING REPORT NR 1861 FOR DETAILS OR CONTACT TOMASO DIPAOLO AT THE CHICAGO AIRCRAFT CERTIFICA	TION OFFICE.  (X)			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2000041200100	20000412	00100	NM  	2000	4	12	SROM200000000    	1	20000313	G	3397	58782	WIRE            			BOEING	737   	737205      	1384456	NM  										CABIN	DAMAGED         	C			SROM	O				OTHER                   				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733A		98   			23466				SECTION OF TRACK LIGHTING JUST AFT OF OVERWING EMERGENCY EXITS INOP.  FOUND RIVET DEBRIS IN TRACK LIGHTING CHANNEL THAT 	DAMAGED THE TRACK LIGHTING ELECTRICAL CABLE TRACK ASSY.  REPLACED SAME AND ASSOCIATED PARTS AND OPERATION CHECKED NORMAL	.  SOURCE OR HOW LONG RIVET DEBRIS WAS PRESENT IS UNKNOWN.  IT WAS TRAPPED UNDER TRACK LIGHTING STRIP AND WAS NOT VISIBL	E UNTIL SAME REMOVED.			2	L	7	2 	4F			RT	A16WE   					 
2000060700076	20000607	00076	NM  	2000	6	7	SROM200000005    	1	20000418	G	2613		WIRE            			BOEING	737   	737205      	1384456	NM  										APU BAY	CHAFED          	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			AL	03	736BP		353  			23465				LEFT HAND WING/BODY OVERHEAT INDICATION.  FOUND CHAFED SHORTED WIRE AT D-866 IN APU COMPARTMENT.  REPLACED SAME AND OPS 	CHECKED PER MAINTENANCE MANUAL 26-18-0.					2	L	7	2 	4F			RT	A16WE   					 
2000060700060	20000607	00060	NM  	2000	6	7	SROM200000006    	1	20000425	G	3222	65737625	STRUT           			BOEING	737   	737205      	       	NM  										NLG	DISCHARGED      	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	736BP	26560	371  			23465				AFTER TAKEOFF AND GEAR RETRACTION, NOSE GEAR FAILED TO INDICATE UP AND LOCKED.  AIR NOISE CONFIRMED GEAR NOT UP AND LOCK	ED.  AIRCRAFT RETURNED TO DEPARTURE AIRPORT.  INSPECTION CONFIRMED NOSE GEAR WAS FLAT, WITH NO SIGNS OF FLUID LEAKAGE.  	NITROGEN SERVICING SCHRADER VALVE WITH ORING WAS REPLACED.  RESERVICED STRUT WITH FLUID AND NITROGEN.  NOSE GEAR WAS OPE	RATIONALLY RETRACTION TEST GOOD.  AIRCRAFT RELEASED FOR FLIGHT WITH NO REOCCURANCE OF PROBLEM.  NOTE:  THIS AIRCRAFT IS 	EQUIPPED WITH A NOSE GEAR GRAVEL DEFLECTION SKI.		2	L	7	2 	4F			 	A16WE   					 
2001011100562	20010111	00562	NM  	2001	1	11	SROM200000011    	1	20001129	G	3230	657376210	GEAR            			BOEING	737   	737205      	       	NM  										NLG	OBSTRUCTED      	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733AR		1160 			23466				AFTER TAKEOFF WITH GEAR HANDLE UP, NOSE GEAR GREEN LIGHT OUT AND RED GEAR LIGHT ILLUMINATED,  CYCLED GEAR SAME INDICATIO	N.   RETURNED TO AIRPORT, NORMAL INDICATIONS AND LANDING.  REMOVED ICE AND SNOW.  REMOVED AND REPLACED NOSE GEAR TRAN CY	LINDER, REF MM 32-33-41.  CHECKED NOSE STRUT SERVICE PER W/C 1832017.  CYCLED GEAR, INDICATION NORMAL.  NOTE:  THIS IS A	 GRAVEL EQUIPPED AIRCRAFT WITH A NOSE GEAR DEFLECTION SKI.  ICE AND SNOW ON UPPER SKI SURFACE THE APPARENT CAUSE.  REPLA	CEMENT OF TRANSFER CYCLINDER WAS FOR PRECAUTIONARY PURPOSES.  (X)		2	L	7	2 	4F			 	A16WE   					 
2001021400055	20010214	00055	CE  	2001	2	14	T58A20001127     	1	20001128	G	2612	473275	FIRE DETECTOR   			BEECH 	200   	B200        	1152922	CE  										RT ENGINE	MALFUNCTIONED   	E			T58A	E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			CL	CLIMB          	1			EA	05	1PD					BB908				RIGHT ENGINE FIRE LIGHT ILLUMINATED DURING INITIAL CLIMB-OUT.  RIGHT ENGINE WAS SECURED, AND THE FIRE LIGHT REMAINED ILL	UMINATED.  RIGHT ENGINE FIRE EXTINGUISHER WAS THEN DISCHARGED AND ABOUT 2 MINUTES LATER THE FIRE LIGHT EXTINGUISHED.  UP	ON LANDING, ENGINE WAS INSPECTED, AND IT WAS DETERMINED THERE WAS NO FIRE, IN ADDITION, THE FIRE DETECTION SYSTEM OPERAT	IONALLY CHECKED OK.  (X)			1	L	7	2 	4T			 	A24CE   					 
2001082000036	20010820	00036	EU  	2001	8	20	TI1R001370       	1	20001127	G	6330	L633M2010101	MOUNT           			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					TRANSMISSION	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV					0070				Z ARIS, FAILED, REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001082000038	20010820	00038		2001	8	20	TI1R001371       	4	20001114	G	3416	1042011968E	ALTIMETER       			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	INOPERATIVE     	B			TI1R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	05	117MK					7196				ENCO ALTIMETER, CODE OFF, FLAG WILL NOT PULL.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
2001082000039	20010820	00039	NE  	2001	8	20	TI1R001372       	2	20001115	G	7314	9A2045	PUMP            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					ENGINE	FAILED          	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV					0070				FUEL PUMP CARTRIDGE, MOTOR WINDINGS OPEN.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001082000040	20010820	00040	GL  	2001	8	20	TI1R001373       	2	20001106	G	7240	6899081	COMBUSTION LINER								ALLSN 	250C  	250C30      	03013	GL  					ENGINE	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										ALT NR 23051100 - CEB-A72-3229 NOT COMPLIED WITH AND BAD WELDS.  REMOVED AND REPLACED.											3	U			E1GL				 
2001082000042	20010820	00042	EU  	2001	8	20	TI1R001375       	1	20001115	G	7931	IPT20RT1100080G	TRANSDUCER      			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					OIL PRESSURE	FLUCTUATES      	B			TI1R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	05	911SV					0070				PRESSURE TRANSDUCER, OIL PRESSURE GAUGE NEEDLE OSCILLATES, RMA R028741, REMOVED AND REPLACE.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001092500108	20010925	00108	EU  	2001	9	25	TI1R001452       	1	20000319	G	6220	552200	BEARING         			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV					0070				BEARING, REMOVED FROM NR 1 POSITION, REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2000041100013	20000411	00013	NM  	2000	4	11	TWAA0003801      	1	20000308	G	3350		LIGHT           			BOEING	767   	7673Y0      	       	NM  										CABIN	INOPERATIVE     	A			TWAA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	05	632TW					24953				THE LEFT SIDE NUMBER 3 CABIN DOOR EXTERIOR EMERGENCY LIGHTS, AND THE EMERGENCY LIGHTS UNDER THE AFT GALLEY JUMP SEAT, WE	RE INOPERATIVE.  REPLACED THE LAMP, (P/N 767), FOR THE EXTERIOR LIGHT, AND TWO LIGHT MODULES, (P/N 02021775-003), FOR TH	E AFT GALLEY JUMP SEAT.  CHECK-C 11-23-99 MCI.  				2	L	7	2 	4F			RT	A1NM    					 
2000031700036	20000317	00036	EU  	2000	3	17	VJ1R2000001      	1	20000202	G	4900	3403009	DUCT            			AMD   	FALC50	FALCON50MYST	2730106	EU  										APU	FAILED          	B			VJ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	150TX	8430 				13				SUNDSTRAND AUXILIARY POWER UNIT, P/N 160371-100, MODEL T62-T40C-7D, S/N 807301.  HOBBS AT 3,384.  EVENTS AT 1,643.  EXPE	RIENCED EXHAUST DUCT FAILURE.  DUCT, P/N 340300-9, TSN:  8,429.7 HOURS.  AS1251ED.  SOLAR T62-T40C-7D 'ENGINE AND EQUIPM	ENT' DATED SEPT 1981 DWG NR 340050, SHTS 1 AND 2 DATED 8-27-81.  LAST INSPECTION PERFORMED AT AN ANNUAL PERIODIC INSPECT	ION REQUIREMENT DATED 10-8-99.  (X)			2	L	7	3 	4F				A46EU   					 
2000031700035	20000317	00035	EU  	2000	3	17	VJ1R2000002      	1	20000210	G	4920	M1672221	TURBINE WHEEL   		1675101200  	BRAERO	1000  	BAE1251000A 	1500104	EU  										APU	FAILED          	B			VJ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	119PW		662  		V16H329N	259007				TURBINE WHEEL FAILURE.  TURBINE WHEEL, P/N M167222-1, S/N V16-H329N.  TSN:  661.9 HOURS.  CSN:  2,311.  SUBMITTER STATED	 THIS TURBINE WHEEL INSTALLED IN THIS APU 5-9-97.  (X)					2	L	7	2 	4F			RT	A3EU    					 
2001011102498	20010111	02498		2001	1	11	VW3R200000001    	4	20001201	G	2562	P3030029010	ELT             	BFGOODRICH  																CABIN	INOPERATIVE     	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R434					ELT DOES NOT TRANSMIT AFTER 5 MONTHS IN SERVICE.  ELT HAS DAMAGED INFLATION CHAMBER OF RAFT.  (X)																			 
2001011102499	20010111	02499		2001	1	11	VW3R200000002    	4	20001201	G	2562	P3030029010	ELT             	BFGOODRICH  																CABIN	INOPERATIVE     	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09					10R316					ELT DOES NOT TRANSMIT.  ELT WAS PACKED IN 10-MAN LIFE RAFT THAT WAS MANUFACTURED IN 10/99.  (X)																			 
2001011102500	20010111	02500		2001	1	11	VW3R200000003    	4	20001120	G	2562	P3030029010	ELT             																	CABIN	MALFUNCTIONED   	B			VW3R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			WP	09										UNIT BEGINS TRANSMITTING INSTEAD OF GOING ON STANDBY WHEN ARMING PIN IS PULLED.  UNIT IS DESIGNED TO TRANSMIT AFTER WATE	R ACTIVATION SENSORS ARE MOISTENED.  UNIT MALFUNCTIONS BY TRANSMITTING FROM STANDBY WITHOUT MOISTURE BEING APPLIED.   TH	IS UNIT WAS RECEIVED NEW FROM THE DISTRIBUTOR.  (X)																	 
2001011102501	20010111	02501		2001	1	11	VW3R200000004    	4	20001120	G	2562	P3030029010	ELT             																	CABIN	MALFUNCTIONED   	B			VW3R	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			WP	09										UNIT BEGINS TRANSMITTING INSTEAD GOING ON STANDBY WHEN ARMING PIN IS PULLED.  UNIT IS DESIGNED TO TRANSMIT AFTER WATER A	CTIVATION SENSORS ARE MOISTENED.  UNIT MALFUNCTIONS BY TRANSMITTING FROM STANDBY WITHOUT MOISTURE BEING APPLIED.  THIS U	NIT WAS RECEIVED NEW FROM THE DISTRIBUTOR.  (X)																	 
2001011102502	20010111	02502		2001	1	11	VW3R200000005    	4	20001120	G	2562	P3030029010	ELT             																	CABIN	INOPERATIVE     	B			VW3R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	09										UNIT RECEIVED BACK AFTER OVERHAUL TO RESTORE SIGNAL TRANSMISSION.  UNIT STILL WILL NOT TRANSMIT ANY SIGNAL.  UNIT HAD BE	EN SENT IN FOR OVERHAUL AFTER ONE YEAR OF SERVICE.  (X)																		 
2000082100166	20000821	00166	GL  	2000	8	21	WBVA00600        	3	20000609	G	6110		PROPELLER       			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  		FAILED          	I			WVBA	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			AL	01	27755	3532 	1765 			317852148		DJ11552A		PILOT REPORTED PROPELLER RPM VARIES DURING CLIMB-OUT.  CONTROL CABLE, PROPELLER GOVERNOR AS WELL AS HUB AIR PRESSURE AND	 BLADE ANGLE WERE DETERMINED TO BE SERVICEABLE. SERVICEABLE PROPELLER WAS INSTALLED AND CHECK FLIGHT WAS OK.  AWAITING O	VERHAUL REPORT.  (X)				1	L	7	2 	3O			 	A20SO   		5	C	P33EA	 
2001050900289	20010509	00289	SO  	2001	5	9	WI1              	2	20000701	G	7260	632617	GEAR            			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  					ACCESSORY DRIVE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2364S	120  	120  			0664	060696R			ACCESSORY DRIVE GEAR TEETH WORN AWAY 120 HOURS SINCE FACTORY REBUILD.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001040900495	20010409	00495	NM  	2001	4	9	WP012000B1305    	1	20000526	G	2782	65447581	STUD            			BOEING	737   	737377      	       	NM  										LE STAT ACT STUD	CRACKED         	B			XQ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										FATIGUE CRACKS IN HOLE DETECTED DURING MAGNETIC INSPECTION.						2	L	7	2 	4F			RT	A16WE   					 
2000082100185	20000821	00185	EA  	2000	8	21	WVBA00500        	2	20000609	G	8520	LW19340	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR1,2 INTAKELOBE	DAMAGED         	I			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	59764		1417 			317652037	L741861A			DURING INSPECTION, BOTH CYLINDERS NR 1 AND NR 2 HAD LOW COMPRESSION.  UPON REMOVING CYLINDERS INTAKE LOBES OF CAMSHAFT H	AD EXTREME WEAR.  THE TAPPET FACES WERE ALSO SPALLED.  OVER PAST YEAR, THERE HAS BEEN FOUR SIMILAR PROBLEMS.  SUBMITTER 	SUSPECTED PROBLEM IN MANUFACTURING PROCESS.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000110600189	20001106	00189	GL  	2000	11	6	WVBA00800        	3	20000702	G	6114		PROPELLER       			CESSNA	207   	207A        	2073604	CE  						HARTZL	HCC3Y	HCC3YF1     	GL  	PROPELLER HUB	CRACKED         	I			WVBA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	7380U	4267 	1476 			20700428		EC1144A		DURING ANNUAL INSPECTION, OIL STREAK DISCOVERED ON AFT HALF OF PROPELLER HUB CASTING.  A DYE PENETRANT INSPECTION PERFOR	MED AND REVEALED HUB TO BE CRACKED.  CRACK WAS APPROXIMATELY 1.50 INCHES LONG HAIR LINE.  AWAITING TEAR-DOWN REPORT FROM	 OVERHAUL SHOP.  (X)				1	H	7	1 	3O			 	A16CE   		5	C	P25EA	 
2000110600093	20001106	00093	EA  	2000	11	6	WVBA01100        	2	20000724	G	8510	LW19340	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 4/NR 6 INTAKE	DAMAGED         	I			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	300ED		1454 			317852008	L983961A			DURING INSPECTION, METAL CONTAMINATION WAS DISCOVERED IN THE SPIN ON OIL FILTER.  FURTHER INVESTIGATION FOUND NR 4 AND N	R 6 CYLINDER INTAKE VALVE LIFT IN EXCESS.  NR 6 CYLINDER REMOVED AND THE INTAKE LOBE OF  NR 4/NR 6 CYLINDERS ON THE CAMS	HAFT TO HAVE SEVERE WEAR AS WELL AS FACES OF THE TAPPETS.  (X)				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2000110600100	20001106	00100	SO  	2000	11	6	WVBA01200        	1	20000724	G	7920	LW13388	GASKET          	LYC         		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					OIL FILTER CONV	DELAMINATED     	A			WVBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	42WP	114  				318252038	RL29368A			FOUND RT ENGINE OIL FILTER ADAPTER WITH SEAL OOZING OUT.  REMOVED PLATE AND FOUND GASKET MATERIAL AS THOUGH IT WAS BEING	 RESOLVED BY SOMETHING.  IT WAS SOFT, STICKY DELAMINATION AND SWOLLEN.  COMPARING IT TO A PLATE REMOVED FROM A TBO''D EN	GINE WEAR SUGGESTED THE NOTION THAT SOMETHING HAD DISSOLVED IT.  THE TBO''S PART SEAL IS FIRM, UNIFORM AND SHOWS NO SWEL	LING OR DELAMINATION.  (X)			1	L	7	2 	3O	3	O	 	A20SO   	E14EA